WorldWideScience

Sample records for atlas rockets

  1. Rocket

    Directory of Open Access Journals (Sweden)

    K. Karmarkar

    1952-09-01

    Full Text Available The rockets of World War II represented, not the invention of a new weapon, but the modernization of a very old one. As early as 1232 A.D, the Chinese launched rockets against the Mongols. About a hundred years later the knowledge of ledge of rockets was quite widespread and they were used to set fire to buildings and to terrorize the enemy. But as cannon developed, rockets declined in warfare. However rockets were used occasionally as weapons till about 1530 A.D. About this time improvements in artillery-rifled gun barrel and mechanism to absorb recoil-established a standard of efficiency with which rockets could not compare until World War II brought pew conditions

  2. ATLAS

    Data.gov (United States)

    Federal Laboratory Consortium — ATLAS is a particle physics experiment at the Large Hadron Collider at CERN, the European Organization for Nuclear Research. Scientists from Brookhaven have played...

  3. Rocket Flight.

    Science.gov (United States)

    Van Evera, Bill; Sterling, Donna R.

    2002-01-01

    Describes an activity for designing, building, and launching rockets that provides students with an intrinsically motivating and real-life application of what could have been classroom-only concepts. Includes rocket design guidelines and a sample grading rubric. (KHR)

  4. ATLAS

    CERN Multimedia

    2002-01-01

    Barrel and END-CAP Toroids In order to produce a powerful magnetic field to bend the paths of the muons, the ATLAS detector uses an exceptionally large system of air-core toroids arranged outside the calorimeter volumes. The large volume magnetic field has a wide angular coverage and strengths of up to 4.7tesla. The toroids system contains over 100km of superconducting wire and has a design current of 20 500 amperes. (ATLAS brochure: The Technical Challenges)

  5. ATLAS

    CERN Multimedia

    Akhnazarov, V; Canepa, A; Bremer, J; Burckhart, H; Cattai, A; Voss, R; Hervas, L; Kaplon, J; Nessi, M; Werner, P; Ten kate, H; Tyrvainen, H; Vandelli, W; Krasznahorkay, A; Gray, H; Alvarez gonzalez, B; Eifert, T F; Rolando, G; Oide, H; Barak, L; Glatzer, J; Backhaus, M; Schaefer, D M; Maciejewski, J P; Milic, A; Jin, S; Von torne, E; Limbach, C; Medinnis, M J; Gregor, I; Levonian, S; Schmitt, S; Waananen, A; Monnier, E; Muanza, S G; Pralavorio, P; Talby, M; Tiouchichine, E; Tocut, V M; Rybkin, G; Wang, S; Lacour, D; Laforge, B; Ocariz, J H; Bertoli, W; Malaescu, B; Sbarra, C; Yamamoto, A; Sasaki, O; Koriki, T; Hara, K; Da silva gomes, A; Carvalho maneira, J; Marcalo da palma, A; Chekulaev, S; Tikhomirov, V; Snesarev, A; Buzykaev, A; Maslennikov, A; Peleganchuk, S; Sukharev, A; Kaplan, B E; Swiatlowski, M J; Nef, P D; Schnoor, U; Oakham, G F; Ueno, R; Orr, R S; Abouzeid, O; Haug, S; Peng, H; Kus, V; Vitek, M; Temming, K K; Dang, N P; Meier, K; Schultz-coulon, H; Geisler, M P; Sander, H; Schaefer, U; Ellinghaus, F; Rieke, S; Nussbaumer, A; Liu, Y; Richter, R; Kortner, S; Fernandez-bosman, M; Ullan comes, M; Espinal curull, J; Chiriotti alvarez, S; Caubet serrabou, M; Valladolid gallego, E; Kaci, M; Carrasco vela, N; Lancon, E C; Besson, N E; Gautard, V; Bracinik, J; Bartsch, V C; Potter, C J; Lester, C G; Moeller, V A; Rosten, J; Crooks, D; Mathieson, K; Houston, S C; Wright, M; Jones, T W; Harris, O B; Byatt, T J; Dobson, E; Hodgson, P; Hodgkinson, M C; Dris, M; Karakostas, K; Ntekas, K; Oren, D; Duchovni, E; Etzion, E; Oren, Y; Ferrer, L M; Testa, M; Doria, A; Merola, L; Sekhniaidze, G; Giordano, R; Ricciardi, S; Milazzo, A; Falciano, S; De pedis, D; Dionisi, C; Veneziano, S; Cardarelli, R; Verzegnassi, C; Soualah, R; Ochi, A; Ohshima, T; Kishiki, S; Linde, F L; Vreeswijk, M; Werneke, P; Muijs, A; Vankov, P H; Jansweijer, P P M; Dale, O; Lund, E; Bruckman de renstrom, P; Dabrowski, W; Adamek, J D; Wolters, H; Micu, L; Pantea, D; Tudorache, V; Mjoernmark, J; Klimek, P J; Ferrari, A; Abdinov, O; Akhoundov, A; Hashimov, R; Shelkov, G; Khubua, J; Ladygin, E; Lazarev, A; Glagolev, V; Dedovich, D; Lykasov, G; Zhemchugov, A; Zolnikov, Y; Ryabenko, M; Sivoklokov, S; Vasilyev, I; Shalimov, A; Lobanov, M; Paramoshkina, E; Mosidze, M; Bingul, A; Nodulman, L J; Guarino, V J; Yoshida, R; Drake, G R; Calafiura, P; Haber, C; Quarrie, D R; Alonso, J R; Anderson, C; Evans, H; Lammers, S W; Baubock, M; Anderson, K; Petti, R; Suhr, C A; Linnemann, J T; Richards, R A; Tollefson, K A; Holzbauer, J L; Stoker, D P; Pier, S; Nelson, A J; Isakov, V; Martin, A J; Adelman, J A; Paganini, M; Gutierrez, P; Snow, J M; Pearson, B L; Cleland, W E; Savinov, V; Wong, W; Goodson, J J; Li, H; Lacey, R A; Gordeev, A; Gordon, H; Lanni, F; Nevski, P; Rescia, S; Kierstead, J A; Liu, Z; Yu, W W H; Bensinger, J; Hashemi, K S; Bogavac, D; Cindro, V; Hoeferkamp, M R; Coelli, S; Iodice, M; Piegaia, R N; Alonso, F; Wahlberg, H P; Barberio, E L; Limosani, A; Rodd, N L; Jennens, D T; Hill, E C; Pospisil, S; Smolek, K; Schaile, D A; Rauscher, F G; Adomeit, S; Mattig, P M; Wahlen, H; Volkmer, F; Calvente lopez, S; Sanchis peris, E J; Pallin, D; Podlyski, F; Says, L; Boumediene, D E; Scott, W; Phillips, P W; Greenall, A; Turner, P; Gwilliam, C B; Kluge, T; Wrona, B; Sellers, G J; Millward, G; Adragna, P; Hartin, A; Alpigiani, C; Piccaro, E; Bret cano, M; Hughes jones, R E; Mercer, D; Oh, A; Chavda, V S; Carminati, L; Cavasinni, V; Fedin, O; Patrichev, S; Ryabov, Y; Nesterov, S; Grebenyuk, O; Sasso, J; Mahmood, H; Polsdofer, E; Dai, T; Ferretti, C; Liu, H; Hegazy, K H; Benjamin, D P; Zobernig, G; Ban, J; Brooijmans, G H; Keener, P; Williams, H H; Le geyt, B C; Hines, E J; Fadeyev, V; Schumm, B A; Law, A T; Kuhl, A D; Neubauer, M S; Shang, R; Gagliardi, G; Calabro, D; Conta, C; Zinna, M; Jones, G; Li, J; Stradling, A R; Hadavand, H K; Mcguigan, P; Chiu, P; Baldelomar, E; Stroynowski, R A; Kehoe, R L; De groot, N; Timmermans, C; Lach-heb, F; Addy, T N; Nakano, I; Moreno lopez, D; Grosse-knetter, J; Tyson, B; Rude, G D; Tafirout, R; Benoit, P; Danielsson, H O; Elsing, M; Fassnacht, P; Froidevaux, D; Ganis, G; Gorini, B; Lasseur, C; Lehmann miotto, G; Kollar, D; Aleksa, M; Sfyrla, A; Duehrssen-debling, K; Fressard-batraneanu, S; Van der ster, D C; Bortolin, C; Schumacher, J; Mentink, M; Geich-gimbel, C; Yau wong, K H; Lafaye, R; Crepe-renaudin, S; Albrand, S; Hoffmann, D; Pangaud, P; Meessen, C; Hrivnac, J; Vernay, E; Perus, A; Henrot versille, S L; Le dortz, O; Derue, F; Piccinini, M; Polini, A; Terada, S; Arai, Y; Ikeno, M; Fujii, H; Nagano, K; Ukegawa, F; Aguilar saavedra, J A; Conde muino, P; Castro, N F; Eremin, V; Kopytine, M; Sulin, V; Tsukerman, I; Korol, A; Nemethy, P; Bartoldus, R; Glatte, A; Chelsky, S; Van nieuwkoop, J; Bellerive, A; Sinervo, J K; Battaglia, A; Barbier, G J; Pohl, M; Rosselet, L; Alexandre, G B; Prokoshin, F; Pezoa rivera, R A; Batkova, L; Kladiva, E; Stastny, J; Kubes, T; Vidlakova, Z; Esch, H; Homann, M; Herten, L G; Zimmermann, S U; Pfeifer, B; Stenzel, H; Andrei, G V; Wessels, M; Buescher, V; Kleinknecht, K; Fiedler, F M; Schroeder, C D; Fernandez, E; Mir martinez, L; Vorwerk, V; Bernabeu verdu, J; Salt, J; Civera navarrete, J V; Bernard, R; Berriaud, C P; Chevalier, L P; Hubbard, R; Schune, P; Nikolopoulos, K; Batley, J R; Brochu, F M; Phillips, A W; Teixeira-dias, P J; Rose, M B D; Buttar, C; Buckley, A G; Nurse, E L; Larner, A B; Boddy, C; Henderson, J; Costanzo, D; Tarem, S; Maccarrone, G; Laurelli, P F; Alviggi, M; Chiaramonte, R; Izzo, V; Palumbo, V; Fraternali, M; Crosetti, G; Marchese, F; Yamaguchi, Y; Hessey, N P; Mechnich, J M; Liebig, W; Kastanas, K A; Sjursen, T B; Zalieckas, J; Cameron, D G; Banka, P; Kowalewska, A B; Dwuznik, M; Mindur, B; Boldea, V; Hedberg, V; Smirnova, O; Sellden, B; Allahverdiyev, T; Gornushkin, Y; Koultchitski, I; Tokmenin, V; Chizhov, M; Gongadze, A; Khramov, E; Sadykov, R; Krasnoslobodtsev, I; Smirnova, L; Kramarenko, V; Minaenko, A; Zenin, O; Beddall, A J; Ozcan, E V; Hou, S; Wang, S; Moyse, E; Willocq, S; Chekanov, S; Le compte, T J; Love, J R; Ciocio, A; Hinchliffe, I; Tsulaia, V; Gomez, A; Luehring, F; Zieminska, D; Huth, J E; Gonski, J L; Oreglia, M; Tang, F; Shochet, M J; Costin, T; Mcleod, A; Uzunyan, S; Martin, S P; Pope, B G; Schwienhorst, R H; Brau, J E; Ptacek, E S; Milburn, R H; Sabancilar, E; Lauer, R; Saleem, M; Mohamed meera lebbai, M R; Lou, X; Reeves, K B; Rijssenbeek, M; Novakova, P N; Rahm, D; Steinberg, P A; Wenaus, T J; Paige, F; Ye, S; Kotcher, J R; Assamagan, K A; Oliveira damazio, D; Maeno, T; Henry, A; Dushkin, A; Costa, G; Meroni, C; Resconi, S; Lari, T; Biglietti, M; Lohse, T; Gonzalez silva, M L; Monticelli, F G; Saavedra, A F; Patel, N D; Ciodaro xavier, T; Asevedo nepomuceno, A; Lefebvre, M; Albert, J E; Kubik, P; Faltova, J; Turecek, D; Solc, J; Schaile, O; Ebke, J; Losel, P J; Zeitnitz, C; Sturm, P D; Barreiro alonso, F; Modesto alapont, P; Soret medel, J; Garzon alama, E J; Gee, C N; Mccubbin, N A; Sankey, D; Emeliyanov, D; Dewhurst, A L; Houlden, M A; Klein, M; Burdin, S; Lehan, A K; Eisenhandler, E; Lloyd, S; Traynor, D P; Ibbotson, M; Marshall, R; Pater, J; Freestone, J; Masik, J; Haughton, I; Manousakis katsikakis, A; Sampsonidis, D; Krepouri, A; Roda, C; Sarri, F; Fukunaga, C; Nadtochiy, A; Kara, S O; Timm, S; Alam, S M; Rashid, T; Goldfarb, S; Espahbodi, S; Marley, D E; Rau, A W; Dos anjos, A R; Haque, S; Grau, N C; Havener, L B; Thomson, E J; Newcomer, F M; Hansl-kozanecki, G; Deberg, H A; Takeshita, T; Goggi, V; Ennis, J S; Olness, F I; Kama, S; Ordonez sanz, G; Koetsveld, F; Elamri, M; Mansoor-ul-islam, S; Lemmer, B; Kawamura, G; Bindi, M; Schulte, S; Kugel, A; Kretz, M P; Kurchaninov, L; Blanchot, G; Chromek-burckhart, D; Di girolamo, B; Francis, D; Gianotti, F; Nordberg, M Y; Pernegger, H; Roe, S; Boyd, J; Wilkens, H G; Pauly, T; Fabre, C; Tricoli, A; Bertet, D; Ruiz martinez, M A; Arnaez, O L; Lenzi, B; Boveia, A J; Gillberg, D I; Davies, J M; Zimmermann, R; Uhlenbrock, M; Kraus, J K; Narayan, R T; John, A; Dam, M; Padilla aranda, C; Bellachia, F; Le flour chollet, F M; Jezequel, S; Dumont dayot, N; Fede, E; Mathieu, M; Gensolen, F D; Alio, L; Arnault, C; Bouchel, M; Ducorps, A; Kado, M M; Lounis, A; Zhang, Z P; De vivie de regie, J; Beau, T; Bruni, A; Bruni, G; Grafstrom, P; Romano, M; Lasagni manghi, F; Massa, L; Shaw, K; Ikegami, Y; Tsuno, S; Kawanishi, Y; Benincasa, G; Blagov, M; Fedorchuk, R; Shatalov, P; Romaniouk, A; Belotskiy, K; Timoshenko, S; Hooft van huysduynen, L; Lewis, G H; Wittgen, M M; Mader, W F; Rudolph, C J; Gumpert, C; Mamuzic, J; Rudolph, G; Schmid, P; Corriveau, F; Belanger-champagne, C; Yarkoni, S; Leroy, C; Koffas, T; Harack, B D; Weber, M S; Beck, H; Leger, A; Gonzalez sevilla, S; Zhu, Y; Gao, J; Zhang, X; Blazek, T; Rames, J; Sicho, P; Kouba, T; Sluka, T; Lysak, R; Ristic, B; Kompatscher, A E; Von radziewski, H; Groll, M; Meyer, C P; Oberlack, H; Stonjek, S M; Cortiana, G; Werthenbach, U; Ibragimov, I; Czirr, H S; Cavalli-sforza, M; Puigdengoles olive, C; Tallada crespi, P; Marti i garcia, S; Gonzalez de la hoz, S; Guyot, C; Meyer, J; Schoeffel, L O; Garvey, J; Hawkes, C; Hillier, S J; Staley, R J; Salvatore, P F; Santoyo castillo, I; Carter, J; Yusuff, I B; Barlow, N R; Berry, T S; Savage, G; Wraight, K G; Steele, G E; Hughes, G; Walder, J W; Love, P A; Crone, G J; Waugh, B M; Boeser, S; Sarkar, A M; Holmes, A; Massey, R; Pinder, A; Nicholson, R; Korolkova, E; Katsoufis, I; Maltezos, S; Tsipolitis, G; Leontsinis, S; Levinson, L J; Shoa, M; Abramowicz, H E; Bella, G; Gershon, A; Urkovsky, E; Taiblum, N; Gatti, C; Della pietra, M; Lanza, A; Negri, A; Flaminio, V; Lacava, F; Petrolo, E; Pontecorvo, L; Rosati, S; Zanello, L; Pasqualucci, E; Di ciaccio, A; Giordani, M; Yamazaki, Y; Jinno, T; Nomachi, M; De jong, P J; Ferrari, P; Homma, J; Van der graaf, H; Igonkina, O B; Stugu, B S; Buanes, T; Pedersen, M; Turala, M; Olszewski, A J; Koperny, S Z; Onofre, A; Castro nunes fiolhais, M; Alexa, C; Cuciuc, C M; Akesson, T P A; Hellman, S L; Milstead, D A; Bondyakov, A; Pushnova, V; Budagov, Y; Minashvili, I; Romanov, V; Sniatkov, V; Tskhadadze, E; Kalinovskaya, L; Shalyugin, A; Tavkhelidze, A; Rumyantsev, L; Karpov, S; Soloshenko, A; Vostrikov, A; Borissov, E; Solodkov, A; Vorob'ev, A; Sidorov, S; Malyaev, V; Lee, S; Grudzinski, J J; Virzi, J S; Vahsen, S E; Lys, J; Penwell, J W; Yan, Z; Bernard, C S; Barreiro guimaraes da costa, J P; Oliver, J N; Merritt, F S; Brubaker, E M; Kapliy, A; Kim, J; Zutshi, V V; Burghgrave, B O; Abolins, M A; Arabidze, G; Caughron, S A; Frey, R E; Radloff, P T; Schernau, M; Murillo garcia, R; Porter, R A; Mccormick, C A; Karn, P J; Sliwa, K J; Demers konezny, S M; Strauss, M G; Mueller, J A; Izen, J M; Klimentov, A; Lynn, D; Polychronakos, V; Radeka, V; Sondericker, J I I I; Bathe, S; Duffin, S; Chen, H; De castro faria salgado, P E; Kersevan, B P; Lacker, H M; Schulz, H; Kubota, T; Tan, K G; Yabsley, B D; Nunes de moura junior, N; Pinfold, J; Soluk, R A; Ouellette, E A; Leitner, R; Sykora, T; Solar, M; Sartisohn, G; Hirschbuehl, D; Huning, D; Fischer, J; Terron cuadrado, J; Glasman kuguel, C B; Lacasta llacer, C; Lopez-amengual, J; Calvet, D; Chevaleyre, J; Daudon, F; Montarou, G; Guicheney, C; Calvet, S P J; Tyndel, M; Dervan, P J; Maxfield, S J; Hayward, H S; Beck, G; Cox, B; Da via, C; Paschalias, P; Manolopoulou, M; Ragusa, F; Cimino, D; Ezzi, M; Fiuza de barros, N F; Yildiz, H; Ciftci, A K; Turkoz, S; Zain, S B; Tegenfeldt, F; Chapman, J W; Panikashvili, N; Bocci, A; Altheimer, A D; Martin, F F; Fratina, S; Jackson, B D; Grillo, A A; Seiden, A; Watts, G T; Mangiameli, S; Johns, K A; O'grady, F T; Errede, D R; Darbo, G; Ferretto parodi, A; Leahu, M C; Farbin, A; Ye, J; Liu, T; Wijnen, T A; Naito, D; Takashima, R; Sandoval usme, C E; Zinonos, Z; Moreno llacer, M; Agricola, J B; Mcgovern, S A; Sakurai, Y; Trigger, I M; Qing, D; De silva, A S; Butin, F; Dell'acqua, A; Hawkings, R J; Lamanna, M; Mapelli, L; Passardi, G; Rembser, C; Tremblet, L; Andreazza, W; Dobos, D A; Koblitz, B; Bianco, M; Dimitrov, G V; Schlenker, S; Armbruster, A J; Rammensee, M C; Romao rodrigues, L F; Peters, K; Pozo astigarraga, M E; Yi, Y; Desch, K K; Huegging, F G; Muller, K K; Stillings, J A; Schaetzel, S; Xella, S; Hansen, J D; Colas, J; Daguin, G; Wingerter, I; Ionescu, G D; Ledroit, F; Lucotte, A; Clement, B E; Stark, J; Clemens, J; Djama, F; Knoops, E; Coadou, Y; Vigeolas-choury, E; Feligioni, L; Iconomidou-fayard, L; Imbert, P; Schaffer, A C; Nikolic, I; Trincaz-duvoid, S; Warin, P; Camard, A F; Ridel, M; Pires, S; Giacobbe, B; Spighi, R; Villa, M; Negrini, M; Sato, K; Gavrilenko, I; Akimov, A; Khovanskiy, V; Talyshev, A; Voronkov, A; Hakobyan, H; Mallik, U; Shibata, A; Konoplich, R; Barklow, T L; Koi, T; Straessner, A; Stelzer, B; Robertson, S H; Vachon, B; Stoebe, M; Keyes, R A; Wang, K; Billoud, T R V; Strickland, V; Batygov, M; Krieger, P; Palacino caviedes, G D; Gay, C W; Jiang, Y; Han, L; Liu, M; Zenis, T; Lokajicek, M; Staroba, P; Tasevsky, M; Popule, J; Svatos, M; Seifert, F; Landgraf, U; Lai, S T; Schmitt, K H; Achenbach, R; Schuh, N; Kiesling, C; Macchiolo, A; Nisius, R; Schacht, P; Von der schmitt, J G; Kortner, O; Atlay, N B; Segura sole, E; Grinstein, S; Neissner, C; Bruckner, D M; Oliver garcia, E; Boonekamp, M; Perrin, P; Gaillot, F M; Wilson, J A; Thomas, J P; Thompson, P D; Palmer, J D; Falk, I E; Chavez barajas, C A; Sutton, M R; Robinson, D; Kaneti, S A; Wu, T; Robson, A; Shaw, C; Buzatu, A; Qin, G; Jones, R; Bouhova-thacker, E V; Viehhauser, G; Weidberg, A R; Gilbert, L; Johansson, P D C; Orphanides, M; Vlachos, S; Behar harpaz, S; Papish, O; Lellouch, D J H; Turgeman, D; Benary, O; La rotonda, L; Vena, R; Tarasio, A; Marzano, F; Gabrielli, A; Di stante, L; Liberti, B; Aielli, G; Oda, S; Nozaki, M; Takeda, H; Hayakawa, T; Miyazaki, K; Maeda, J; Sugimoto, T; Pettersson, N E; Bentvelsen, S; Groenstege, H L; Lipniacka, A; Vahabi, M; Ould-saada, F; Chwastowski, J J; Hajduk, Z; Kaczmarska, A; Olszowska, J B; Trzupek, A; Staszewski, R P; Palka, M; Constantinescu, S; Jarlskog, G; Lundberg, B L A; Pearce, M; Ellert, M F; Bannikov, A; Fechtchenko, A; Iambourenko, V; Kukhtin, V; Pozdniakov, V; Topilin, N; Vorozhtsov, S; Khassanov, A; Fliaguine, V; Kharchenko, D; Nikolaev, K; Kotenov, K; Kozhin, A; Zenin, A; Ivashin, A; Golubkov, D; Beddall, A; Su, D; Dallapiccola, C J; Cranshaw, J M; Price, L; Stanek, R W; Gieraltowski, G; Zhang, J; Gilchriese, M; Shapiro, M; Ahlen, S; Morii, M; Taylor, F E; Miller, R J; Phillips, F H; Torrence, E C; Wheeler, S J; Benedict, B H; Napier, A; Hamilton, S F; Petrescu, T A; Boyd, G R J; Jayasinghe, A L; Smith, J M; Mc carthy, R L; Adams, D L; Le vine, M J; Zhao, X; Patwa, A M; Baker, M; Kirsch, L; Krstic, J; Simic, L; Filipcic, A; Seidel, S C; Cantore-cavalli, D; Baroncelli, A; Kind, O M; Scarcella, M J; Maidantchik, C L L; Seixas, J; Balabram filho, L E; Vorobel, V; Spousta, M; Strachota, P; Vokac, P; Slavicek, T; Bergmann, B L; Biebel, O; Kersten, S; Srinivasan, M; Trefzger, T; Vazeille, F; Insa, C; Kirk, J; Middleton, R; Burke, S; Klein, U; Morris, J D; Ellis, K V; Millward, L R; Giokaris, N; Ioannou, P; Angelidakis, S; Bouzakis, K; Andreazza, A; Perini, L; Chtcheguelski, V; Spiridenkov, E; Yilmaz, M; Kaya, U; Ernst, J; Mahmood, A; Saland, J; Kutnink, T; Holler, J; Kagan, H P; Wang, C; Pan, Y; Xu, N; Ji, H; Willis, W J; Tuts, P M; Litke, A; Wilder, M; Rothberg, J; Twomey, M S; Rizatdinova, F; Loch, P; Rutherfoord, J P; Varnes, E W; Barberis, D; Osculati-becchi, B; Brandt, A G; Turvey, A J; Benchekroun, D; Nagasaka, Y; Thanakornworakij, T; Quadt, A; Nadal serrano, J; Magradze, E; Nackenhorst, O; Musheghyan, H; Kareem, M; Chytka, L; Perez codina, E; Stelzer-chilton, O; Brunel, B; Henriques correia, A M; Dittus, F; Hatch, M; Haug, F; Hauschild, M; Huhtinen, M; Lichard, P; Schuh-erhard, S; Spigo, G; Avolio, G; Tsarouchas, C; Ahmad, I; Backes, M P; Barisits, M; Gadatsch, S; Cerv, M; Sicoe, A D; Nattamai sekar, L P; Fazio, D; Shan, L; Sun, X; Gaycken, G F; Hemperek, T; Petersen, T C; Alonso diaz, A; Moynot, M; Werlen, M; Hryn'ova, T; Gallin-martel, M; Wu, M; Touchard, F; 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Shupe, M A; Wolin, S; Oshita, H; Gaudio, G; Das, R; Konig, A C; Croft, V A; Harvey, A; Maaroufi, F; Melo, I; Greenwood jr, Z D; Shabalina, E; Mchedlidze, G; Drechsler, E; Rieger, J K; Blackston, M; Colombo, T

    2002-01-01

    % ATLAS \\\\ \\\\ ATLAS is a general-purpose experiment for recording proton-proton collisions at LHC. The ATLAS collaboration consists of 144 participating institutions (June 1998) with more than 1750~physicists and engineers (700 from non-Member States). The detector design has been optimized to cover the largest possible range of LHC physics: searches for Higgs bosons and alternative schemes for the spontaneous symmetry-breaking mechanism; searches for supersymmetric particles, new gauge bosons, leptoquarks, and quark and lepton compositeness indicating extensions to the Standard Model and new physics beyond it; studies of the origin of CP violation via high-precision measurements of CP-violating B-decays; high-precision measurements of the third quark family such as the top-quark mass and decay properties, rare decays of B-hadrons, spectroscopy of rare B-hadrons, and $ B ^0 _{s} $-mixing. \\\\ \\\\The ATLAS dectector, shown in the Figure includes an inner tracking detector inside a 2~T~solenoid providing an axial...

  6. Rocket flames

    Directory of Open Access Journals (Sweden)

    W. M. Vaidya

    1952-09-01

    Full Text Available Among the important parameters which characterize the rocket flames are the (1 velocity, (2 pressure, (3 temperature of the exhaust gases and (4 the nature of chemical reactions in the flame of such gases. For the determination of these quantities ordinary methods fail because the flow of exhaust gases is supersonic in character. An introduction of a probe or any foreign body will create such strong disturbances in the supersonic flow that the readings of observing instruments will have no value. Spectroscopic methods are therefore eminently suitable because observations can be taken on the flame under running conditions.

  7. Hybrid Rocket Propulsion for Sounding Rocket Applications

    Science.gov (United States)

    1991-01-01

    A discussion of the H-225K hybrid rocket motor, produced by the American Rocket Company, is given. The H-225K motor is presented in terms of the following topics: (1) hybrid rocket fundamentals; (2) hybrid characteristics; and (3) hybrid advantages.

  8. Rocket propulsion elements

    CERN Document Server

    Sutton, George P

    2011-01-01

    The definitive text on rocket propulsion-now revised to reflect advancements in the field For sixty years, Sutton's Rocket Propulsion Elements has been regarded as the single most authoritative sourcebook on rocket propulsion technology. As with the previous edition, coauthored with Oscar Biblarz, the Eighth Edition of Rocket Propulsion Elements offers a thorough introduction to basic principles of rocket propulsion for guided missiles, space flight, or satellite flight. It describes the physical mechanisms and designs for various types of rockets' and provides an unders

  9. Castor Rocket Launch [video

    OpenAIRE

    Yakimenko, Oleg; Naval Postgraduate School (U.S.)

    2010-01-01

    The Naval Postgraduate School (NPS) and the AIAA Point Lobos section (PLS) entered three rockets into the 2010 AIAA Young Professionals Rocket Competition (YPRC). The event took place in the Mojave Desert on Koehn Dry lakebed July 17th 2010.

  10. Rockets two classic papers

    CERN Document Server

    Goddard, Robert

    2002-01-01

    Rockets, in the primitive form of fireworks, have existed since the Chinese invented them around the thirteenth century. But it was the work of American Robert Hutchings Goddard (1882-1945) and his development of liquid-fueled rockets that first produced a controlled rocket flight. Fascinated by rocketry since boyhood, Goddard designed, built, and launched the world's first liquid-fueled rocket in 1926. Ridiculed by the press for suggesting that rockets could be flown to the moon, he continued his experiments, supported partly by the Smithsonian Institution and defended by Charles Lindbergh. T

  11. Introduction to rocket science and engineering

    CERN Document Server

    Taylor, Travis S

    2009-01-01

    What Are Rockets? The History of RocketsRockets of the Modern EraRocket Anatomy and NomenclatureWhy Are Rockets Needed? Missions and PayloadsTrajectoriesOrbitsOrbit Changes and ManeuversBallistic Missile TrajectoriesHow Do Rockets Work? ThrustSpecific ImpulseWeight Flow RateTsiolkovsky's Rocket EquationStagingRocket Dynamics, Guidance, and ControlHow Do Rocket Engines Work? The Basic Rocket EngineThermodynamic Expansion and the Rocket NozzleExit VelocityRocket Engine Area Ratio and LengthsRocket Engine Design ExampleAre All Rockets the Same? Solid Rocket EnginesLiquid Propellant Rocket Engines

  12. Taming Liquid Hydrogen: The Centaur Upper Stage Rocket

    Science.gov (United States)

    2004-01-01

    The Centaur is one of the most powerful rockets in the world. As an upper-stage rocket for the Atlas and Titan boosters it has been a reliable workhorse for NASA for over forty years and has played an essential role in many of NASA's adventures into space. In this CD-ROM you will be able to explore the Centaur's history in various rooms to this virtual museum. Visit the "Movie Theater" to enjoy several video documentaries on the Centaur. Enter the "Interview Booth" to hear and read interviews with scientists and engineers closely responsible for building and operating the rocket. Go to the "Photo Gallery" to look at numerous photos of the rocket throughout its history. Wander into the "Centaur Library" to read various primary documents of the Centaur program. Finally, stop by the "Observation Deck" to watch a virtual Centaur in flight.

  13. The flight of uncontrolled rockets

    CERN Document Server

    Gantmakher, F R; Dryden, H L

    1964-01-01

    International Series of Monographs on Aeronautics and Astronautics, Division VII, Volume 5: The Flight of Uncontrolled Rockets focuses on external ballistics of uncontrolled rockets. The book first discusses the equations of motion of rockets. The rocket as a system of changing composition; application of solidification principle to rockets; rotational motion of rockets; and equations of motion of the center of mass of rockets are described. The text looks at the calculation of trajectory of rockets and the fundamentals of rocket dispersion. The selection further focuses on the dispersion of f

  14. Eddie Rocket's Franchise

    OpenAIRE

    Vahter, Jenni

    2008-01-01

    Eddie Rocket's Franchise - Setting up a franchise restaurant in Helsinki. TIIVISTELMÄ: Eddie Rocket's on menestynyt amerikkalaistyylinen 1950-luvun ”diner” franchiseravintolaketju Irlannista. Ravintoloita on perustettu viimeisen 18 vuoden aikana 28 kappaletta Irlantiin ja Isoon Britanniaan sekä yksi Espanjaan. Tämän tutkimuksen tarkoitus on tutkia onko Eddie Rocket'silla potentiaalia menestyä Helsingissä, Suomessa. Tutkimuskysymystä on lähestytty toimiala-analyysin, markkinatutkimuksen j...

  15. Model Rockets and Microchips.

    Science.gov (United States)

    Fitzsimmons, Charles P.

    1986-01-01

    Points out the instructional applications and program possibilities of a unit on model rocketry. Describes the ways that microcomputers can assist in model rocket design and in problem calculations. Provides a descriptive listing of model rocket software for the Apple II microcomputer. (ML)

  16. Indians Repulse British With Rocket

    Science.gov (United States)

    2004-01-01

    During the early introduction of rockets to Europe, they were used only as weapons. Enemy troops in India repulsed the British with rockets. Later, in Britain, Sir William Congreve developed a rocket that could fire to about 9,000 feet. The British fired Congreve rockets against the United States in the War of 1812.

  17. Another Look at Rocket Thrust

    Science.gov (United States)

    Hester, Brooke; Burris, Jennifer

    2012-01-01

    Rocket propulsion is often introduced as an example of Newton's third law. The rocket exerts a force on the exhaust gas being ejected; the gas exerts an equal and opposite force--the thrust--on the rocket. Equivalently, in the absence of a net external force, the total momentum of the system, rocket plus ejected gas, remains constant. The law of…

  18. Rocket University at KSC

    Science.gov (United States)

    Sullivan, Steven J.

    2014-01-01

    "Rocket University" is an exciting new initiative at Kennedy Space Center led by NASA's Engineering and Technology Directorate. This hands-on experience has been established to develop, refine & maintain targeted flight engineering skills to enable the Agency and KSC strategic goals. Through "RocketU", KSC is developing a nimble, rapid flight engineering life cycle systems knowledge base. Ongoing activities in RocketU develop and test new technologies and potential customer systems through small scale vehicles, build and maintain flight experience through balloon and small-scale rocket missions, and enable a revolving fresh perspective of engineers with hands on expertise back into the large scale NASA programs, providing a more experienced multi-disciplined set of systems engineers. This overview will define the Program, highlight aspects of the training curriculum, and identify recent accomplishments and activities.

  19. GPS Sounding Rocket Developments

    Science.gov (United States)

    Bull, Barton

    1999-01-01

    Sounding rockets are suborbital launch vehicles capable of carrying scientific payloads several hundred miles in altitude. These missions return a variety of scientific data including; chemical makeup and physical processes taking place In the atmosphere, natural radiation surrounding the Earth, data on the Sun, stars, galaxies and many other phenomena. In addition, sounding rockets provide a reasonably economical means of conducting engineering tests for instruments and devices used on satellites and other spacecraft prior to their use in more expensive activities. The NASA Sounding Rocket Program is managed by personnel from Goddard Space Flight Center Wallops Flight Facility (GSFC/WFF) in Virginia. Typically around thirty of these rockets are launched each year, either from established ranges at Wallops Island, Virginia, Poker Flat Research Range, Alaska; White Sands Missile Range, New Mexico or from Canada, Norway and Sweden. Many times launches are conducted from temporary launch ranges in remote parts of the world requi6ng considerable expense to transport and operate tracking radars. An inverse differential GPS system has been developed for Sounding Rocket. This paper addresses the NASA Wallops Island history of GPS Sounding Rocket experience since 1994 and the development of a high accurate and useful system.

  20. An Evaluation Of Rocket Parameters

    Directory of Open Access Journals (Sweden)

    J. N. Beri

    1959-07-01

    Full Text Available The dependence of conventional parameters of internal ballistics of Solid Propellant Rockets using external burning cruciform charge, on the geometry of charge aad rocket motor is discussed and results applied in a special case.

  1. Point Lobos Rocket Launch [video

    OpenAIRE

    Yakimenko, Oleg; Naval Postgraduate School (U.S.)

    2010-01-01

    The Naval Postgraduate School (NPS) and the AIAA Point Lobos section (PLS) entered three rockets into the 2010 AIAA Young Professionals Rocket Competition (YPRC). The event took place in the Mojave Desert on Koehn Dry lakebed July 17th 2010.

  2. Rocket Flight Path

    Directory of Open Access Journals (Sweden)

    Jamie Waters

    2014-09-01

    Full Text Available This project uses Newton’s Second Law of Motion, Euler’s method, basic physics, and basic calculus to model the flight path of a rocket. From this, one can find the height and velocity at any point from launch to the maximum altitude, or apogee. This can then be compared to the actual values to see if the method of estimation is a plausible. The rocket used for this project is modeled after Bullistic-1 which was launched by the Society of Aeronautics and Rocketry at the University of South Florida.

  3. Baking Soda and Vinegar Rockets

    Science.gov (United States)

    Claycomb, James R.; Zachary, Christopher; Tran, Quoc

    2009-01-01

    Rocket experiments demonstrating conservation of momentum will never fail to generate enthusiasm in undergraduate physics laboratories. In this paper, we describe tests on rockets from two vendors that combine baking soda and vinegar for propulsion. The experiment compared two analytical approximations for the maximum rocket height to the…

  4. Dr. Goddard Transports Rocket

    Science.gov (United States)

    1974-01-01

    Dr. Robert H. Goddard tows his rocket to the launching tower behind a Model A Ford truck, 15 miles northwest of Roswell, New Mexico. 1930- 1932. Dr. Goddard has been recognized as the 'Father of American Rocketry' and as one of three pioneers in the theoretical exploration of space. Robert Hutchings Goddard was born in Worcester, Massachusetts, on October 15, 1882. He was a theoretical scientist as well as a practical engineer. His dream was the conquest of the upper atmosphere and ultimately space through the use of rocket propulsion. Dr. Goddard, who died in 1945, was probably as responsible for the dawning of the Space Age as the Wright Brothers were for the begining of the Air Age. Yet his work attracted little serious attention during his lifetime. When the United States began to prepare for the conquest of space in the 1950's, American rocket scientists began to recognize the debt owed to the New England professor. They discovered that it was virtually impossible to construct a rocket or launch a satellite without acknowledging the work of Dr. Goddard. This great legacy was covered by more than 200 patents, many of which were issued after his death.

  5. This "Is" Rocket Science!

    Science.gov (United States)

    Keith, Wayne; Martin, Cynthia; Veltkamp, Pamela

    2013-01-01

    Using model rockets to teach physics can be an effective way to engage students in learning. In this paper, we present a curriculum developed in response to an expressed need for helping high school students review physics equations in preparation for a state-mandated exam. This required a mode of teaching that was more advanced and analytical…

  6. The Relativistic Rocket

    Science.gov (United States)

    Antippa, Adel F.

    2009-01-01

    We solve the problem of the relativistic rocket by making use of the relation between Lorentzian and Galilean velocities, as well as the laws of superposition of successive collinear Lorentz boosts in the limit of infinitesimal boosts. The solution is conceptually simple, and technically straightforward, and provides an example of a powerful…

  7. Rocketing to the Skies

    Institute of Scientific and Technical Information of China (English)

    1999-01-01

    ONE sunny morning,we startedfor Yanqi Lake,Huairou District,Beijing,to try“rocket bungy”,so farthe only facility for this sport inChina.On the way there,wequestioned our courage and heartendurance. Entering the gate we saw,towering over a banner saying,

  8. Low toxicity rocket propellants

    NARCIS (Netherlands)

    Wink, J.

    2014-01-01

    Hydrazine (N2H4) and its hypergolic mate nitrogen tetroxide (N2O4) are used on virtually all spacecraft and on a large number of launch vehicles. In recent years however, there has been an effort in identifying and developing alternatives to replace hydrazine as a rocket propellant.

  9. Hybrid Rocket Technology

    Directory of Open Access Journals (Sweden)

    Sankaran Venugopal

    2011-04-01

    Full Text Available With their unique operational characteristics, hybrid rockets can potentially provide safer, lower-cost avenues for spacecraft and missiles than the current solid propellant and liquid propellant systems. Classical hybrids can be throttled for thrust tailoring, perform in-flight motor shutdown and restart. In classical hybrids, the fuel is stored in the form of a solid grain, requiring only half the feed system hardware of liquid bipropellant engines. The commonly used fuels are benign, nontoxic, and not hazardous to store and transport. Solid fuel grains are not highly susceptible to cracks, imperfections, and environmental temperature and are therefore safer to manufacture, store, transport, and use for launch. The status of development based on the experience of the last few decades indicating the maturity of the hybrid rocket technology is given in brief.Defence Science Journal, 2011, 61(3, pp.193-200, DOI:http://dx.doi.org/10.14429/dsj.61.518

  10. Liquid rocket engine injectors

    Science.gov (United States)

    Gill, G. S.; Nurick, W. H.

    1976-01-01

    The injector in a liquid rocket engine atomizes and mixes the fuel with the oxidizer to produce efficient and stable combustion that will provide the required thrust without endangering hardware durability. Injectors usually take the form of a perforated disk at the head of the rocket engine combustion chamber, and have varied from a few inches to more than a yard in diameter. This monograph treats specifically bipropellant injectors, emphasis being placed on the liquid/liquid and liquid/gas injectors that have been developed for and used in flight-proven engines. The information provided has limited application to monopropellant injectors and gas/gas propellant systems. Critical problems that may arise during injector development and the approaches that lead to successful design are discussed.

  11. Sirius-5 experimental rocket

    Science.gov (United States)

    Kerstein, A.; Omersel, P.; Goljuf, L.; Zidaric, M.

    1981-09-01

    After giving a historical account of multistage rocket development in Yugoslavia, a status report is presented for the three-stage Sirius-5 program. The rocket is composed of: (1) a solid-propellant first stage, consisting of a cluster of eight standard motors yielding 220 kN thrust for 1.3 sec; (2) a mixed amines/inhibited red fuming nitric acid, bipropellant second stage generating 50 kN thrust; and (3) a third stage of the same design as the second but with only 62 kg of fuel, by contrast to 168 kg. Among the design principles adhered to are: minimization of the number of components, conservative design margins, and specifications for key subsystems based on demonstration programs. The primary use of this system is in amateur rocketry, being able to carry a 20 kg payload to 150 km.

  12. Hybrid Rocket Technology

    OpenAIRE

    Sankaran Venugopal; K.K. Rajesh; V. Ramanujachari

    2011-01-01

    With their unique operational characteristics, hybrid rockets can potentially provide safer, lower-cost avenues for spacecraft and missiles than the current solid propellant and liquid propellant systems. Classical hybrids can be throttled for thrust tailoring, perform in-flight motor shutdown and restart. In classical hybrids, the fuel is stored in the form of a solid grain, requiring only half the feed system hardware of liquid bipropellant engines. The commonly used fuels are benign, nonto...

  13. Microfabricated Liquid Rocket Motors

    Science.gov (United States)

    Epstein, Alan H.; Joppin, C.; Kerrebrock, J. L.; Schneider, Steven J. (Technical Monitor)

    2003-01-01

    Under NASA Glenn Research Center sponsorship, MIT has developed the concept of micromachined, bipropellant, liquid rocket engines. This is potentially a breakthrough technology changing the cost-performance tradeoffs for small propulsion systems, enabling new applications, and redefining the meaning of the term low-cost-access-to-space. With this NASA support, a liquid-cooled, gaseous propellant version of the thrust chamber and nozzle was designed, built, and tested as a first step. DARPA is currently funding MIT to demonstrate turbopumps and controls. The work performed herein was the second year of a proposed three-year effort to develop the technology and demonstrate very high power density, regeneratively cooled, liquid bipropellant rocket engine thrust chamber and nozzles. When combined with the DARPA turbopumps and controls, this work would enable the design and demonstration of a complete rocket propulsion system. The original MIT-NASA concept used liquid oxygen-ethanol propellants. The military applications important to DARPA imply that storable liquid propellants are needed. Thus, MIT examined various storable propellant combinations including N2O4 and hydrazine, and H2O2 and various hydrocarbons. The latter are preferred since they do not have the toxicity of N2O4 and hydrazine. In reflection of the newfound interest in H2O2, it is once again in production and available commercially. A critical issue for the microrocket engine concept is cooling of the walls in a regenerative design. This is even more important at microscale than for large engines due to cube-square scaling considerations. Furthermore, the coolant behavior of rocket propellants has not been characterized at microscale. Therefore, MIT designed and constructed an apparatus expressly for this purpose. The report details measurements of two candidate microrocket fuels, JP-7 and JP-10.

  14. Solid propellant rocket motor

    Science.gov (United States)

    Dowler, W. L.; Shafer, J. I.; Behm, J. W.; Strand, L. D. (Inventor)

    1973-01-01

    The characteristics of a solid propellant rocket engine with a controlled rate of thrust buildup to a desired thrust level are discussed. The engine uses a regressive burning controlled flow solid propellant igniter and a progressive burning main solid propellant charge. The igniter is capable of operating in a vacuum and sustains the burning of the propellant below its normal combustion limit until the burning propellant surface and combustion chamber pressure have increased sufficiently to provide a stable chamber pressure.

  15. Rocket Assembly and Checkout Facility

    Data.gov (United States)

    Federal Laboratory Consortium — FUNCTION: Integrates, tests, and calibrates scientific instruments flown on sounding rocket payloads. The scientific instruments are assembled on an optical bench;...

  16. Rocket + Science = Dialogue

    Science.gov (United States)

    Morris,Bruce; Sullivan, Greg; Burkey, Martin

    2010-01-01

    It's a cliche that rocket engineers and space scientists don t see eye-to-eye. That goes double for rocket engineers working on human spaceflight and scientists working on space telescopes and planetary probes. They work fundamentally different problems but often feel that they are competing for the same pot of money. Put the two groups together for a weekend, and the results could be unscientific or perhaps combustible. Fortunately, that wasn't the case when NASA put heavy lift launch vehicle designers together with astronomers and planetary scientists for two weekend workshops in 2008. The goal was to bring the top people from both groups together to see how the mass and volume capabilities of NASA's Ares V heavy lift launch vehicle could benefit the science community. Ares V is part of NASA's Constellation Program for resuming human exploration beyond low Earth orbit, starting with missions to the Moon. In the current mission scenario, Ares V launches a lunar lander into Earth orbit. A smaller Ares I rocket launches the Orion crew vehicle with up to four astronauts. Orion docks with the lander, attached to the Ares V Earth departure stage. The stage fires its engine to send the mated spacecraft to the Moon. Standing 360 feet high and weighing 7.4 million pounds, NASA's new heavy lifter will be bigger than the 1960s-era Saturn V. It can launch almost 60 percent more payload to translunar insertion together with the Ares I and 35 percent more mass to low Earth orbit than the Saturn V. This super-sized capability is, in short, designed to send more people to more places to do more things than the six Apollo missions.

  17. What fuel for a rocket?

    CERN Document Server

    Miranda, E N

    2012-01-01

    Elementary concepts from general physics and thermodynamics have been used to analyze rocket propulsion. Making some reasonable assumptions, an expression for the exit velocity of the gases is found. From that expression one can conclude what are the desired properties for a rocket fuel.

  18. Rhenium Rocket Manufacturing Technology

    Science.gov (United States)

    1997-01-01

    The NASA Lewis Research Center's On-Board Propulsion Branch has a research and technology program to develop high-temperature (2200 C), iridium-coated rhenium rocket chamber materials for radiation-cooled rockets in satellite propulsion systems. Although successful material demonstrations have gained much industry interest, acceptance of the technology has been hindered by a lack of demonstrated joining technologies and a sparse materials property data base. To alleviate these concerns, we fabricated rhenium to C-103 alloy joints by three methods: explosive bonding, diffusion bonding, and brazing. The joints were tested by simulating their incorporation into a structure by welding and by simulating high-temperature operation. Test results show that the shear strength of the joints degrades with welding and elevated temperature operation but that it is adequate for the application. Rhenium is known to form brittle intermetallics with a number of elements, and this phenomena is suspected to cause the strength degradation. Further bonding tests with a tantalum diffusion barrier between the rhenium and C-103 is planned to prevent the formation of brittle intermetallics.

  19. Mars Rocket Propulsion System

    Science.gov (United States)

    Zubrin, Robert; Harber, Dan; Nabors, Sammy

    2008-01-01

    A report discusses the methane and carbon monoxide/LOX (McLOx) rocket for ascent from Mars as well as other critical space propulsion tasks. The system offers a specific impulse over 370 s roughly 50 s higher than existing space-storable bio-propellants. Current Mars in-situ propellant production (ISPP) technologies produce impure methane and carbon monoxide in various combinations. While separation and purification of methane fuel is possible, it adds complexity to the propellant production process and discards an otherwise useful fuel product. The McLOx makes such complex and wasteful processes unnecessary by burning the methane/CO mixtures produced by the Mars ISPP systems without the need for further refinement. Despite the decrease in rocket-specific impulse caused by the CO admixture, the improvement offered by concomitant increased propellant density can provide a net improvement in stage performance. One advantage is the increase of the total amount of propellant produced, but with a decrease in mass and complexity of the required ISPP plant. Methane/CO fuel mixtures also may be produced by reprocessing the organic wastes of a Moon base or a space station, making McLOx engines key for a human Lunar initiative or the International Space Station (ISS) program. Because McLOx propellant components store at a common temperature, very lightweight and compact common bulkhead tanks can be employed, improving overall stage performance further.

  20. Nuclear Rocket Engine Reactor

    CERN Document Server

    Lanin, Anatoly

    2013-01-01

    The development of a nuclear rocket engine reactor (NRER ) is presented in this book. The working capacity of an active zone NRER under mechanical and thermal load, intensive neutron fluxes, high energy generation (up to 30 MBT/l) in a working medium (hydrogen) at temperatures up to 3100 K is displayed. Design principles and bearing capacity of reactors area discussed on the basis of simulation experiments and test data of a prototype reactor. Property data of dense constructional, porous thermal insulating and fuel materials like carbide and uranium carbide compounds in the temperatures interval 300 - 3000 K are presented. Technological aspects of strength and thermal strength resistance of materials are considered. The design procedure of possible emergency processes in the NRER is developed and risks for their origination are evaluated. Prospects of the NRER development for pilotless space devices and piloted interplanetary ships are viewed.

  1. Rockets Sulfur, Sputnik and scramjets

    CERN Document Server

    Macinnis, Peter

    2003-01-01

    Our story starts around 700 BC when the Chinese used a form of gunpowder to fumigate their houses. The first real rockets were gunpowder filled sections of bamboo thrown under horses to scare them; the next development was to tie these to arrows. The Mongols took rockets from China to Europe where only some, including Admiral Nelson and the Crown Prince of Sweden, were impressed. The Royal Navy used them in all sorts of odd actions against ""restless natives"" in Tierra Del Fuego, Australia and New Zealand and the Russian and Austrian empires adopted rockets as alternatives to artillery in b

  2. World Data Center A (rockets and satellites) catalogue of data. Volume 1, part A: Sounding rockets

    Science.gov (United States)

    1972-01-01

    A cumulative listing of all scientifically successful rockets that have been identified from various sources is presented. The listing starts with the V-2 rocket launched on 7 March 1947 and contains all rockets identified up to 31 December 1971.

  3. Alternate Propellant Thermal Rocket Project

    Data.gov (United States)

    National Aeronautics and Space Administration — The Alternate Propellant Thermal Rocket (APTR) is a novel concept for propulsion of space exploration or orbit transfer vehicles. APTR propulsion is provided by...

  4. Nuclear rocket engine reactor

    Energy Technology Data Exchange (ETDEWEB)

    Lanin, Anatoly

    2013-07-01

    Covers a new technology of nuclear reactors and the related materials aspects. Integrates physics, materials science and engineering Serves as a basic book for nuclear engineers and nuclear physicists. The development of a nuclear rocket engine reactor (NRER) is presented in this book. The working capacity of an active zone NRER under mechanical and thermal load, intensive neutron fluxes, high energy generation (up to 30 MBT/l) in a working medium (hydrogen) at temperatures up to 3100 K is displayed. Design principles and bearing capacity of reactors area discussed on the basis of simulation experiments and test data of a prototype reactor. Property data of dense constructional, porous thermal insulating and fuel materials like carbide and uranium carbide compounds in the temperatures interval 300 - 3000 K are presented. Technological aspects of strength and thermal strength resistance of materials are considered. The design procedure of possible emergency processes in the NRER is developed and risks for their origination are evaluated. Prospects of the NRER development for pilotless space devices and piloted interplanetary ships are viewed.

  5. Not just rocket science

    Energy Technology Data Exchange (ETDEWEB)

    MacAdam, S.; Anderson, R. [Celan Energy Systems, Rancho Cordova, CA (United States)

    2007-10-15

    The paper explains a different take on oxyfuel combustion. Clean Energy Systems (CES) has integrated aerospace technology into conventional power systems, creating a zero-emission power generation technology that has some advantages over other similar approaches. When using coal as a feedstock, the CES process burns syngas rather than raw coal. The process uses recycled water and steam to moderate the temperature, instead of recycled CO{sub 2}. With no air ingress, the CES process produces very pure CO{sub 2}. This makes it possible to capture over 99% of the CO{sub 2} resulting from combustion. CES uses the combustion products to drive the turbines, rather than indirectly raising steam for steam turbines, as in the oxyfuel process used by companies such as Vattenfall. The core of the process is a high-pressure oxy-combustor adapted from rocket engine technology. This combustor burns gaseous or liquid fuels with gaseous oxygen in the presence of water. Fuels include natural gas, coal or coke-derived synthesis gas, landfill and biodigester gases, glycerine solutions and oil/water emulsion. 2 figs.

  6. Supporting ATLAS

    CERN Multimedia

    maximilien brice

    2003-01-01

    Eighteen feet made of stainless steel will support the barrel ATLAS detector in the cavern at Point 1. In total, the ATLAS feet system will carry approximately 6000 tons, and will give the same inclination to the detector as the LHC accelerator.

  7. Rocket Science 101 Interactive Educational Program

    Science.gov (United States)

    Armstrong, Dennis; Funkhouse, Deborah; DiMarzio, Donald

    2007-01-01

    To better educate the public on the basic design of NASA s current mission rockets, Rocket Science 101 software has been developed as an interactive program designed to retain a user s attention and to teach about basic rocket parts. This program also has helped to expand NASA's presence on the Web regarding educating the public about the Agency s goals and accomplishments. The software was designed using Macromedia s Flash 8. It allows the user to select which type of rocket they want to learn about, interact with the basic parts, assemble the parts to create the whole rocket, and then review the basic flight profile of the rocket they have built.

  8. Supporting ATLAS

    CERN Multimedia

    2003-01-01

    Eighteen feet made of stainless steel will support the barrel ATLAS detector in the cavern at Point 1. In total, the ATLAS feet system will carry approximately 6000 tons, and will give the same inclination to the detector as the LHC accelerator. The installation of the feet is scheduled to finish during January 2004 with an installation precision at the 1 mm level despite their height of 5.3 metres. The manufacture was carried out in Russia (Company Izhorskiye Zavody in St. Petersburg), as part of a Russian and JINR Dubna in-kind contribution to ATLAS. Involved in the installation is a team from IHEP-Protvino (Russia), the ATLAS technical co-ordination team at CERN, and the CERN survey team. In all, about 15 people are involved. After the feet are in place, the barrel toroid magnet and the barrel calorimeters will be installed. This will keep the ATLAS team busy for the entire year 2004.

  9. Integrated Composite Rocket Nozzle Extension Project

    Data.gov (United States)

    National Aeronautics and Space Administration — ORBITEC proposes to develop and demonstrate an Integrated Composite Rocket Nozzle Extension (ICRNE) for use in rocket thrust chambers. The ICRNE will utilize an...

  10. Some typical solid propellant rocket motors

    NARCIS (Netherlands)

    Zandbergen, B.T.C.

    2013-01-01

    Typical Solid Propellant Rocket Motors (shortly referred to as Solid Rocket Motors; SRM's) are described with the purpose to form a database, which allows for comparative analysis and applications in practical SRM engineering.

  11. Rocket Science at the Nanoscale.

    Science.gov (United States)

    Li, Jinxing; Rozen, Isaac; Wang, Joseph

    2016-06-28

    Autonomous propulsion at the nanoscale represents one of the most challenging and demanding goals in nanotechnology. Over the past decade, numerous important advances in nanotechnology and material science have contributed to the creation of powerful self-propelled micro/nanomotors. In particular, micro- and nanoscale rockets (MNRs) offer impressive capabilities, including remarkable speeds, large cargo-towing forces, precise motion controls, and dynamic self-assembly, which have paved the way for designing multifunctional and intelligent nanoscale machines. These multipurpose nanoscale shuttles can propel and function in complex real-life media, actively transporting and releasing therapeutic payloads and remediation agents for diverse biomedical and environmental applications. This review discusses the challenges of designing efficient MNRs and presents an overview of their propulsion behavior, fabrication methods, potential rocket fuels, navigation strategies, practical applications, and the future prospects of rocket science and technology at the nanoscale. PMID:27219742

  12. Rocket Science at the Nanoscale.

    Science.gov (United States)

    Li, Jinxing; Rozen, Isaac; Wang, Joseph

    2016-06-28

    Autonomous propulsion at the nanoscale represents one of the most challenging and demanding goals in nanotechnology. Over the past decade, numerous important advances in nanotechnology and material science have contributed to the creation of powerful self-propelled micro/nanomotors. In particular, micro- and nanoscale rockets (MNRs) offer impressive capabilities, including remarkable speeds, large cargo-towing forces, precise motion controls, and dynamic self-assembly, which have paved the way for designing multifunctional and intelligent nanoscale machines. These multipurpose nanoscale shuttles can propel and function in complex real-life media, actively transporting and releasing therapeutic payloads and remediation agents for diverse biomedical and environmental applications. This review discusses the challenges of designing efficient MNRs and presents an overview of their propulsion behavior, fabrication methods, potential rocket fuels, navigation strategies, practical applications, and the future prospects of rocket science and technology at the nanoscale.

  13. Saving Lives With Rocket Power

    Science.gov (United States)

    2000-01-01

    Thiokol Propulsion uses NASA's surplus rocket fuel to produce a flare that can safely destroy land mines. Through a Memorandum of Agreement between Thiokol and Marshall Space Flight Center, Thiokol uses the scrap Reusable Solid Rocket Motor (RSRM) propellant. The resulting Demining Device was developed by Thiokol with the help of DE Technologies. The Demining Device neutralizes land mines in the field without setting them off. The Demining Device flare is placed next to an uncovered land mine. Using a battery-triggered electric match, the flare is then ignited. Using the excess and now solidified rocket fuel, the flare burns a hole in the mine's case and ignites the explosive contents. Once the explosive material is burned away, the mine is disarmed and no longer dangerous.

  14. Rocket Locations for Minimum Time Interception

    Directory of Open Access Journals (Sweden)

    T. N. Srivastava

    1971-07-01

    Full Text Available Interception of target rocket moving along a trajectory in a gravitational field by an interceptor rocket has been analysed to achieve interception in minimum time duration. Numerical values of the parameters of the intercepting trajectory and locations of the target rocket for launch and target orbits in Earth's gravitational field have been calculated for different impulsive velocity changes applied to the interceptor rocket.

  15. Small rocket research and technology

    Science.gov (United States)

    Schneider, Steven; Biaglow, James

    1993-01-01

    Small chemical rockets are used on nearly all space missions. The small rocket program provides propulsion technology for civil and government space systems. Small rocket concepts are developed for systems which encompass reaction control for launch and orbit transfer systems, as well as on-board propulsion for large space systems and earth orbit and planetary spacecraft. Major roles for on-board propulsion include apogee kick, delta-V, de-orbit, drag makeup, final insertions, north-south stationkeeping, orbit change/trim, perigee kick, and reboost. The program encompasses efforts on earth-storable, space storable, and cryogenic propellants. The earth-storable propellants include nitrogen tetroxide (NTO) as an oxidizer with monomethylhydrazine (MMH) or anhydrous hydrazine (AH) as fuels. The space storable propellants include liquid oxygen (LOX) as an oxidizer with hydrazine or hydrocarbons such as liquid methane, ethane, and ethanol as fuels. Cryogenic propellants are LOX or gaseous oxygen (GOX) as oxidizers and liquid or gaseous hydrogen as fuels. Improved performance and lifetime for small chemical rockets are sought through the development of new predictive tools to understand the combustion and flow physics, the introduction of high temperature materials to eliminate fuel film cooling and its associated combustion inefficiency, and improved component designs to optimize performance. Improved predictive technology is sought through the comparison of both local and global predictions with experimental data. Results indicate that modeling of the injector and combustion process in small rockets needs improvement. High temperature materials require the development of fabrication processes, a durability data base in both laboratory and rocket environments, and basic engineering property data such as strength, creep, fatigue, and work hardening properties at both room and elevated temperature. Promising materials under development include iridium-coated rhenium and a

  16. The Swedish Rocket Corps, 1833 - 1845

    Science.gov (United States)

    Skoog, A. I.

    1977-01-01

    Rockets for pyrotechnic displays used in Sweden in the 19th century are examined in terms of their use in war situations. Work done by the Swedish chemist J. J. Berzelius, who analyzed and improved the propellants of such rockets, and the German engineer, Martin Westermaijer, who researched manufacturing techniques of these rockets is also included.

  17. Measuring Model Rocket Engine Thrust Curves

    Science.gov (United States)

    Penn, Kim; Slaton, William V.

    2010-01-01

    This paper describes a method and setup to quickly and easily measure a model rocket engine's thrust curve using a computer data logger and force probe. Horst describes using Vernier's LabPro and force probe to measure the rocket engine's thrust curve; however, the method of attaching the rocket to the force probe is not discussed. We show how a…

  18. Summarization on variable liquid thrust rocket engines

    Institute of Scientific and Technical Information of China (English)

    2009-01-01

    The technology actuality and development trend of variable thrust rocket engines at home and abroad are summarized. Key technologies of developing variable thrust rocket engines are analyzed. Development advices on developing variable thrust rocket engines that are adapted to the situation of our country are brought forward.

  19. Mongolian Atlas

    Data.gov (United States)

    National Oceanic and Atmospheric Administration, Department of Commerce — Climatic atlas dated 1985, in Mongolian, with introductory material also in Russian and English. One hundred eight pages in single page PDFs.

  20. Rocket Ignition Demonstrations Using Silane

    Science.gov (United States)

    Pal, Sibtosh; Santoro, Robert; Watkins, William B.; Kincaid, Kevin

    1998-01-01

    Rocket ignition demonstration tests using silane were performed at the Penn State Combustion Research Laboratory. A heat sink combustor with one injection element was used with gaseous propellants. Mixtures of silane and hydrogen were used as fuel, and oxygen was used as oxidizer. Reliable ignition was demonstrated using fuel lead and and a swirl injection element.

  1. On pressure rise in rockets

    Directory of Open Access Journals (Sweden)

    S. K. Gupta

    1954-07-01

    Full Text Available The phenomenon of pressure rise in rockets has been discussed on the basis of r=CP/Sup/n as the law of burning. An explicit expression for the chamber pressure at any instant has been derived and illustrated by a table and a graph.

  2. Centrifugal pumps for rocket engines

    Science.gov (United States)

    Campbell, W. E.; Farquhar, J.

    1974-01-01

    The use of centrifugal pumps for rocket engines is described in terms of general requirements of operational and planned systems. Hydrodynamic and mechanical design considerations and techniques and test procedures are summarized. Some of the pump development experiences, in terms of both problems and solutions, are highlighted.

  3. Nanoparticles for solid rocket propulsion

    International Nuclear Information System (INIS)

    The characterization of several differently sized aluminium powders, by BET (specific surface), EM (electron microscopy), XRD (x-ray diffraction), and XPS (x-ray photoelectron spectroscopy), was performed in order to evaluate their application in solid rocket propellant compositions. These aluminium powders were used in manufacturing several laboratory composite solid rocket propellants, based on ammonium perchlorate (AP) as oxidizer and hydroxil-terminated polybutadiene (HTPB) as binder. The reference formulation was an AP/HTPB/Al composition with 68/17/15% mass fractions respectively. The ballistic characterization of the propellants, in terms of steady burning rates, shows better performance for propellant compositions employing nano-aluminium when compared to micro-aluminium. Results obtained in the pressure range 1-70 bar show that by increasing the nano-Al mass fraction or decreasing the nano-Al size, larger steady burning rates are measured with essentially the same pressure sensitivity

  4. Nanoparticles for solid rocket propulsion

    Science.gov (United States)

    Galfetti, L.; DeLuca, L. T.; Severini, F.; Meda, L.; Marra, G.; Marchetti, M.; Regi, M.; Bellucci, S.

    2006-08-01

    The characterization of several differently sized aluminium powders, by BET (specific surface), EM (electron microscopy), XRD (x-ray diffraction), and XPS (x-ray photoelectron spectroscopy), was performed in order to evaluate their application in solid rocket propellant compositions. These aluminium powders were used in manufacturing several laboratory composite solid rocket propellants, based on ammonium perchlorate (AP) as oxidizer and hydroxil-terminated polybutadiene (HTPB) as binder. The reference formulation was an AP/HTPB/Al composition with 68/17/15% mass fractions respectively. The ballistic characterization of the propellants, in terms of steady burning rates, shows better performance for propellant compositions employing nano-aluminium when compared to micro-aluminium. Results obtained in the pressure range 1-70 bar show that by increasing the nano-Al mass fraction or decreasing the nano-Al size, larger steady burning rates are measured with essentially the same pressure sensitivity.

  5. Emissivity of rocket plume particulates.

    OpenAIRE

    Whisman, Curtis D.

    1992-01-01

    The optical properties of motor aluminum oxide are required inputs to current plume signature prediction codes, such as SIRRM. Accurate predictions are possible only if variations in the particle emissivity due to changes in particle size, contamination, and changing temperature, etc. , are known . This investigation demonstrated a simplified method for determination of the emissivity of rocket motor generated alumina. Plume particulate material was collected on ...

  6. Extended temperature range rocket injector

    Science.gov (United States)

    Schneider, Steven J. (Inventor)

    1991-01-01

    A rocket injector is provided with multiple sets of manifolds for supplying propellants to injector elements. Sensors transmit the temperatures of the propellants to a suitable controller which is operably connnected to valves between these manifolds and propellant storage tanks. When cryogenic propellant temperatures are sensed, only a portion of the valves are opened to furnish propellants to some of the manifolds. When lower temperatures are sensed, additional valves are opened to furnish propellants to more of the manifolds.

  7. Rocket Engine Altitude Simulation Technologies

    Science.gov (United States)

    Woods, Jody L.; Lansaw, John

    2010-01-01

    John C. Stennis Space Center is embarking on a very ambitious era in its rocket engine propulsion test history. The first new large rocket engine test stand to be built at Stennis Space Center in over 40 years is under construction. The new A3 Test Stand is designed to test very large (294,000 Ibf thrust) cryogenic propellant rocket engines at a simulated altitude of 100,000 feet. A3 Test Stand will have an engine testing chamber where the engine will be fired after the air in the chamber has been evacuated to a pressure at the simulated altitude of less than 0.16 PSIA. This will result in a very unique environment with extremely low pressures inside a very large chamber and ambient pressures outside this chamber. The test chamber is evacuated of air using a 2-stage diffuser / ejector system powered by 5000 lb/sec of steam produced by 27 chemical steam generators. This large amount of power and flow during an engine test will result in a significant acoustic and vibrational environment in and around A3 Test Stand.

  8. Low thrust chemical rocket technology

    Science.gov (United States)

    Schneider, Steven J.

    1992-01-01

    An on-going technology program to improve the performance of low thrust chemical rockets for spacecraft on-board propulsion applications is reviewed. Improved performance and lifetime is sought by the development of new predictive tools to understand the combustion and flow physics, introduction of high temperature materials and improved component designs to optimize performance, and use of higher performance propellants. Improved predictive technology is sought through the comparison of both local and global predictions with experimental data. Predictions are based on both the RPLUS Navier-Stokes code with finite rate kinetics and the JANNAF methodology. Data were obtained with laser-based diagnostics along with global performance measurements. Results indicate that the modeling of the injector and the combustion process needs improvement in these codes and flow visualization with a technique such as 2-D laser induced fluorescence (LIF) would aid in resolving issues of flow symmetry and shear layer combustion processes. High temperature material fabrication processes are under development and small rockets are being designed, fabricated, and tested using these new materials. Rhenium coated with iridium for oxidation protection was produced by the Chemical Vapor Deposition (CVD) process and enabled an 800 K increase in rocket operating temperature. Performance gains with this material in rockets using Earth storable propellants (nitrogen tetroxide and monomethylhydrazine or hydrazine) were obtained through component redesign to eliminate fuel film cooling and its associated combustion inefficiency while managing head end thermal soakback. Material interdiffusion and oxidation characteristics indicated that the requisite lifetimes of tens of hours were available for thruster applications. Rockets were designed, fabricated, and tested with thrusts of 22, 62, 440 and 550 N. Performance improvements of 10 to 20 seconds specific impulse were demonstrated. Higher

  9. Miniature Autonomous Rocket Recovery System (MARRS)

    OpenAIRE

    Yakimenko, O.A.; Yingling, A.J.; Hewgley, C.W.; Seigenthaler, T.A.

    2011-01-01

    The article of record as published may be located at http://dx.doi.org/10.2514/6.2011-2597 Proceedings of the 21st AIAA Aerodynamic Decelerator Systems Technology Conference, Dublin, Ireland, May 23-26, 2011. This paper discusses the development and testing of the new-generation recovery system in highpowered rockets. It starts from the overall description of the rocket system, the requirements of the Miniature Autonomous Rocket Recovery System (MARRS) and is followed by a descrip...

  10. Rocket Engine Numerical Simulator (RENS)

    Science.gov (United States)

    Davidian, Kenneth O.

    1997-01-01

    Work is being done at three universities to help today's NASA engineers use the knowledge and experience of their Apolloera predecessors in designing liquid rocket engines. Ground-breaking work is being done in important subject areas to create a prototype of the most important functions for the Rocket Engine Numerical Simulator (RENS). The goal of RENS is to develop an interactive, realtime application that engineers can utilize for comprehensive preliminary propulsion system design functions. RENS will employ computer science and artificial intelligence research in knowledge acquisition, computer code parallelization and objectification, expert system architecture design, and object-oriented programming. In 1995, a 3year grant from the NASA Lewis Research Center was awarded to Dr. Douglas Moreman and Dr. John Dyer of Southern University at Baton Rouge, Louisiana, to begin acquiring knowledge in liquid rocket propulsion systems. Resources of the University of West Florida in Pensacola were enlisted to begin the process of enlisting knowledge from senior NASA engineers who are recognized experts in liquid rocket engine propulsion systems. Dr. John Coffey of the University of West Florida is utilizing his expertise in interviewing and concept mapping techniques to encode, classify, and integrate information obtained through personal interviews. The expertise extracted from the NASA engineers has been put into concept maps with supporting textual, audio, graphic, and video material. A fundamental concept map was delivered by the end of the first year of work and the development of maps containing increasing amounts of information is continuing. Find out more information about this work at the Southern University/University of West Florida. In 1996, the Southern University/University of West Florida team conducted a 4day group interview with a panel of five experts to discuss failures of the RL10 rocket engine in conjunction with the Centaur launch vehicle. The

  11. The four INTA-300 rocket prototypes

    Science.gov (United States)

    Calero, J. S.

    1985-03-01

    A development history and performance capability assessment is presented for the INTA-300 'Flamenco' sounding rocket prototype specimens. The Flamenco is a two-stage solid fuel rocket, based on British sounding rocket technology, that can lift 50 km payloads to altitudes of about 300 km. The flight of the first two prototypes, in 1974 and 1975, pointed to vibration problems which reduced the achievable apogee, and the third prototype's flight was marred by a premature detonation that destroyed the rocket. The fourth Flamenco flight, however, yielded much reliable data.

  12. ATLAS Outreach Highlights

    CERN Document Server

    Cheatham, Susan; The ATLAS collaboration

    2016-01-01

    The ATLAS outreach team is very active, promoting particle physics to a broad range of audiences including physicists, general public, policy makers, students and teachers, and media. A selection of current outreach activities and new projects will be presented. Recent highlights include the new ATLAS public website and ATLAS Open Data, the very recent public release of 1 fb-1 of ATLAS data.

  13. ATLAS Story

    CERN Multimedia

    Nordberg, Markus

    2012-01-01

    This film produced in July 2012 explains how fundamental research connects to Society and what benefits collaborative way of working can and may generate in the future, using ATLAS Collaboration as a case study. The film is intellectually inspired by the book "Collisions and Collaboration" (OUP) by Max Boisot (ed.), see: collisionsandcollaboration.com. The film is directed by Andrew Millington (OMNI Communications)

  14. The Advanced Solid Rocket Motor

    Science.gov (United States)

    Mitchell, Royce E.

    1992-08-01

    The Advanced Solid Rocket Motor will utilize improved design features and automated manufacturing methods to produce an inherently safer propulsive system for the Space Shuttle and future launch systems. This second-generation motor will also provide an additional 12,000 pounds of payload to orbit, enhancing the utility and efficiency of the Shuttle system. The new plant will feature strip-wound, asbestos-free insulation; propellant continuous mixing and casting; and extensive robotic systems. Following a series of static tests at the Stennis Space Center, MS flights are targeted to begin in early 1997.

  15. The Advanced Solid Rocket Motor

    Science.gov (United States)

    Mitchell, Royce E.

    1992-01-01

    The Advanced Solid Rocket Motor will utilize improved design features and automated manufacturing methods to produce an inherently safer propulsive system for the Space Shuttle and future launch systems. This second-generation motor will also provide an additional 12,000 pounds of payload to orbit, enhancing the utility and efficiency of the Shuttle system. The new plant will feature strip-wound, asbestos-free insulation; propellant continuous mixing and casting; and extensive robotic systems. Following a series of static tests at the Stennis Space Center, MS flights are targeted to begin in early 1997.

  16. Ionospheric shock waves triggered by rockets

    Science.gov (United States)

    Lin, C. H.; Lin, J. T.; Chen, C. H.; Liu, J. Y.; Sun, Y. Y.; Kakinami, Y.; Matsumura, M.; Chen, W. H.; Liu, H.; Rau, R. J.

    2014-09-01

    This paper presents a two-dimensional structure of the shock wave signatures in ionospheric electron density resulting from a rocket transit using the rate of change of the total electron content (TEC) derived from ground-based GPS receivers around Japan and Taiwan for the first time. From the TEC maps constructed for the 2009 North Korea (NK) Taepodong-2 and 2013 South Korea (SK) Korea Space Launch Vehicle-II (KSLV-II) rocket launches, features of the V-shaped shock wave fronts in TEC perturbations are prominently seen. These fronts, with periods of 100-600 s, produced by the propulsive blasts of the rockets appear immediately and then propagate perpendicularly outward from the rocket trajectory with supersonic velocities between 800-1200 m s-1 for both events. Additionally, clear rocket exhaust depletions of TECs are seen along the trajectory and are deflected by the background thermospheric neutral wind. Twenty minutes after the rocket transits, delayed electron density perturbation waves propagating along the bow wave direction appear with phase velocities of 800-1200 m s-1. According to their propagation character, these delayed waves may be generated by rocket exhaust plumes at earlier rocket locations at lower altitudes.

  17. A note on efficiency of rockets

    Directory of Open Access Journals (Sweden)

    S. K. Gupta

    1954-07-01

    Full Text Available The paper discusses the dependence of efficiency of a rocket on the expansion ratio and the ratio of the initial mass of the rocket and the mass of the propellant. The relation is illustrated by a table and two graphs.

  18. ATLAS Recordings

    CERN Multimedia

    Steven Goldfarb; Mitch McLachlan; Homer A. Neal

    Web Archives of ATLAS Plenary Sessions, Workshops, Meetings, and Tutorials from 2005 until this past month are available via the University of Michigan portal here. Most recent additions include the Trigger-Aware Analysis Tutorial by Monika Wielers on March 23 and the ROOT Workshop held at CERN on March 26-27.Viewing requires a standard web browser with RealPlayer plug-in (included in most browsers automatically) and works on any major platform. Lectures can be viewed directly over the web or downloaded locally.In addition, you will find access to a variety of general tutorials and events via the portal.Feedback WelcomeOur group is making arrangements now to record plenary sessions, tutorials, and other important ATLAS events for 2007. Your suggestions for potential recording, as well as your feedback on existing archives is always welcome. Please contact us at wlap@umich.edu. Thank you.Enjoy the Lectures!

  19. 21 CFR 866.4830 - Rocket immunoelectro-phoresis equipment.

    Science.gov (United States)

    2010-04-01

    ... 21 Food and Drugs 8 2010-04-01 2010-04-01 false Rocket immunoelectro-phoresis equipment. 866.4830... § 866.4830 Rocket immunoelectro-phoresis equipment. (a) Identification. Rocket immunoelectrophoresis... called rocket immunoelectrophoresis. In this procedure, an electric current causes the protein...

  20. Rocket Experiment For Neutral Upwelling

    Science.gov (United States)

    Kenward, D. R.; Lessard, M.

    2015-12-01

    Observations from the CHAMP satellite from 2004 show relatively small scale heating in the thermosphere. Several different mechanisms have been proposed to explain this phenomenon. The RENU 2 rocket mission includes a suite of 14 instruments which will acquire data to help understand processes involved in neutral upwelling in the cusp. Neutral, ion, and electron measurements will be made to provide an assessment of the upwelling process. SUPERDarn measurements of large- scale Joule heating in the cusp during overflight will also be acquired. Small-scale data which could possibly be associated with Alfvén waves, will be acquired using onboard electric field measurements. In-situ measurement of precipitating electrons and all other measurements will be used in thermodynamic and electrodynamic models for comparison to the observed upwelling.

  1. Centaur Rocket Installation in PSL #1

    Science.gov (United States)

    1962-01-01

    Centaur Rocket Installation in PSL - Propulsion Systems Laboratory #1. The RL-10 Rocket was developed by Pratt and Whitney in the late 1950's and tested at the Lewis Research Center (now known as the John H. Glenn Research Lewis Field). This power plant was the propulsion system for NASA's upper stage Centaur rocket and was significant for being the first to use liquid hydrogen and oxygen as fuel. The Centaur suffered a number of early failures, but later proved to be a very successful upper stage for numerous commercial, NASA and military payloads.

  2. Detection of Metallic Compounds in Rocket Plumes

    Science.gov (United States)

    Rogers, Chris; Dunn, Dr. Robert

    1998-04-01

    Recent experiments using metal mixed in hydroxyl-terminated polybutadiene (HTPB) fuel grains in small hybrid rocket indicates ion detectors may be effective in detection of metallic compounds in rocket plumes. We wanted to ascertain the extent to which the presence of metallic compounds in rocket plumes could be detected using ion probes and Gaussian rings. Charges that collide with or pass near the intruding probe are detected. Gaussian rings, short insulated cylindrical Gaussian surfaces, enclose the plume without intruding into the plume. Charges in the plume are detected by currents they induce in the cylinder.

  3. Early Spin-Stabilised Rockets - the Rockets of Bergrat Heinrich Gottlob Kuhn

    Science.gov (United States)

    Fricke, H.-D.

    19th century's war rockets were at first stabilised by sticks, but these sticks produced a very uncertain flight path and it often happened that rockets changed their direction and even flew back to their firing position. So very many early inventors in Europe, America, and British-India tried to stabilise the rocket's flight in a better way. They tried fins and even rotation but they did not succeed. It is said in history that William Hale was the first who succeeded in constructing a spin stabilised (i.e. rotating) rocket which worked. But before him, in the thirties of that century, a German amateur rocket inventor succeeded as well and secretly proved his stickless rotating rockets in trials for Prussian officers and some years later officially for Saxon artillery officers. His invention was then bought by the kingdom of Saxony, but these were never use in the field because of lack of money.

  4. Collaborative Sounding Rocket launch in Alaska and Development of Hybrid Rockets

    Science.gov (United States)

    Ono, Tomohisa; Tsutsumi, Akimasa; Ito, Toshiyuki; Kan, Yuji; Tohyama, Fumio; Nakashino, Kyouichi; Hawkins, Joseph

    Tokai University student rocket project (TSRP) was established in 1995 for a purpose of the space science and engineering hands-on education, consisting of two space programs; the one is sounding rocket experiment collaboration with University of Alaska Fairbanks and the other is development and launch of small hybrid rockets. In January of 2000 and March 2002, two collaborative sounding rockets were successfully launched at Poker Flat Research Range in Alaska. In 2001, the first Tokai hybrid rocket was successfully launched at Alaska. After that, 11 hybrid rockets were launched to the level of 180-1,000 m high at Hokkaido and Akita in Japan. Currently, Tokai students design and build all parts of the rockets. In addition, they are running the organization and development of the project under the tight budget control. This program has proven to be very effective in providing students with practical, real-engineering design experience and this program also allows students to participate in all phases of a sounding rocket mission. Also students learn scientific, engineering subjects, public affairs and system management through experiences of cooperative teamwork. In this report, we summarize the TSRP's hybrid rocket program and discuss the effectiveness of the program in terms of educational aspects.

  5. Estimation of Initial Disturbances for Rockets Based on Interactions of Rockets and Directional Tubes

    Institute of Scientific and Technical Information of China (English)

    2006-01-01

    In the range of the rockets/launcher system itself, the dynamic equations for rocket and directional tube during semi-constraint period have been constructed by using Newton-Euler method. Considering the interaction of rockets and directional tubes when clearances exist, the method of estimating initial disturbances for the rocket by using vibration data of the directional tube has been given. The estimated results have been compared with the simulation results computed by the dynamic simulating software ADAMS. Results computed by the two methods are basically consistent and the computing errors do not increase with the variation of the clearance. The validity of the proposed method has been proved.

  6. Electroweak Physics with ATLAS

    OpenAIRE

    Akhundov, Arif

    2008-01-01

    The precision measurements of electroweak parameters of the Standard Model with the ATLAS detector at LHC are reviewed. An emphasis is put on the bridge connecting the ATLAS measurements with the SM analysis at LEP/SLC and the Tevatron.

  7. Manufacturing Advanced Channel Wall Rocket Liners Project

    Data.gov (United States)

    National Aeronautics and Space Administration — This SBIR will adapt and demonstrate a low cost flexible method of manufacturing channel wall liquid rocket nozzles and combustors, while providing developers a...

  8. Hydroxyl Tagging Velocimetry for Rocket Plumes Project

    Data.gov (United States)

    National Aeronautics and Space Administration — To address the need for non-intrusive sensors for rocket plume properties, we propose a laser-based velocity diagnostic that does not require seeding, works in high...

  9. Advanced Vortex Hybrid Rocket Engine (AVHRE) Project

    Data.gov (United States)

    National Aeronautics and Space Administration — ORBITEC proposes to develop a unique Advanced Vortex Hybrid Rocket Engine (AVHRE) to achieve a safe, highly-reliable, low-cost and uniquely versatile propulsion...

  10. Advanced Vortex Hybrid Rocket Engine (AVHRE) Project

    Data.gov (United States)

    National Aeronautics and Space Administration — Orbital Technologies Corporation (ORBITEC) proposes to develop a unique Advanced Vortex Hybrid Rocket Engine (AVHRE) to achieve a highly-reliable, low-cost and...

  11. Fundamentals of aircraft and rocket propulsion

    CERN Document Server

    El-Sayed, Ahmed F

    2016-01-01

    This book provides a comprehensive basics-to-advanced course in an aero-thermal science vital to the design of engines for either type of craft. The text classifies engines powering aircraft and single/multi-stage rockets, and derives performance parameters for both from basic aerodynamics and thermodynamics laws. Each type of engine is analyzed for optimum performance goals, and mission-appropriate engines selection is explained. Fundamentals of Aircraft and Rocket Propulsion provides information about and analyses of: thermodynamic cycles of shaft engines (piston, turboprop, turboshaft and propfan); jet engines (pulsejet, pulse detonation engine, ramjet, scramjet, turbojet and turbofan); chemical and non-chemical rocket engines; conceptual design of modular rocket engines (combustor, nozzle and turbopumps); and conceptual design of different modules of aero-engines in their design and off-design state. Aimed at graduate and final-year undergraduate students, this textbook provides a thorough grounding in th...

  12. Magnesium Based Rockets for Martian Exploration Project

    Data.gov (United States)

    National Aeronautics and Space Administration — We propose to develop Mg rockets for Martian ascent vehicle applications. The propellant can be acquired in-situ from MgO in the Martian regolith (5.1% Mg by mass)...

  13. Hydroxyl Tagging Velocimetry for Rocket Plumes Project

    Data.gov (United States)

    National Aeronautics and Space Administration — A non-intrusive method for measuring velocities in a rocket exhaust is proposed in a joint effort by MetroLaser and Vanderbilt University. Hydroxyl Tagging...

  14. Infrared Imagery of Solid Rocket Exhaust Plumes

    Science.gov (United States)

    Moran, Robert P.; Houston, Janice D.

    2011-01-01

    The Ares I Scale Model Acoustic Test program consisted of a series of 18 solid rocket motor static firings, simulating the liftoff conditions of the Ares I five-segment Reusable Solid Rocket Motor Vehicle. Primary test objectives included acquiring acoustic and pressure data which will be used to validate analytical models for the prediction of Ares 1 liftoff acoustics and ignition overpressure environments. The test article consisted of a 5% scale Ares I vehicle and launch tower mounted on the Mobile Launch Pad. The testing also incorporated several Water Sound Suppression Systems. Infrared imagery was employed during the solid rocket testing to support the validation or improvement of analytical models, and identify corollaries between rocket plume size or shape and the accompanying measured level of noise suppression obtained by water sound suppression systems.

  15. Magnesium Based Rockets for Martian Exploration Project

    Data.gov (United States)

    National Aeronautics and Space Administration — In the proposed Phase II program, we will continue the development of Mg bipropellant rockets for Martian PAV applications. In Phase I, we proved the feasibility of...

  16. Stability of Rocket Flight during Burning

    Directory of Open Access Journals (Sweden)

    T. N. Srivastava

    1967-10-01

    Full Text Available Stability of the rocket motion during burning is discussed taking into consideration gravity, aerodynamic forces and torques. Conditions for stabilizing the rocket motion are investigated. Analysis for initial and final phases of burning is given separately. Stability regions of the projected motions on two dimensional co-ordinate planes are obtained and thereby stability region of the actual motion is derived. Stability diagrams illustrate statically and dynamically stable and unstable regions.

  17. Sensor Fusion Navigation for Sounding Rocket Applications

    OpenAIRE

    Nilsson, Mattias; Vinkvist, Rikard

    2008-01-01

    One of Saab Space’s products is the S19 guidance system for sounding rockets.Today this system is based on an inertial navigation system that blindly calculatesthe position of the rocket by integrating sensor readings with unknown bias. Thepurpose of this thesis is to integrate a Global Positioning System (GPS) receiverinto the guidance system to increase precision and robustness. There are mainlytwo problems involved in this integration. One is to integrate the GPS with sensorfusion into the...

  18. Rocket Rendezvous at Preassigned Destinations with Optimum

    Directory of Open Access Journals (Sweden)

    T. N. Srivastava

    1982-10-01

    Full Text Available The problem of rendezvous of an interceptor rocket vehicle through optimal exit path with a destination rocket vehicle at a preassigned location on the destination orbit has been investigated for non-coaxial coplanar elliptic launch and destination orbits in an inverse square gravitational field. The case, when launch and destination orbits are coplanar circular, is also discussed. In the end numerical results for rendezvous have been obtained taking Earth and Mars orbits as launch and destination orbits respectively.

  19. Recent ATLAS Articles on WLAP

    CERN Multimedia

    J. Herr

    As reported in the September 2004 ATLAS eNews, the Web Lecture Archive Project is a system for the archiving and publishing of multimedia presentations, using the Web as medium. We list here newly available WLAP items relating to ATLAS: Atlas Physics Workshop 6-11 June 2005 June 2005 ATLAS Week Plenary Session Click here to browse WLAP for all ATLAS lectures.

  20. Nitrous Oxide/Paraffin Hybrid Rocket Engines

    Science.gov (United States)

    Zubrin, Robert; Snyder, Gary

    2010-01-01

    Nitrous oxide/paraffin (N2OP) hybrid rocket engines have been invented as alternatives to other rocket engines especially those that burn granular, rubbery solid fuels consisting largely of hydroxyl- terminated polybutadiene (HTPB). Originally intended for use in launching spacecraft, these engines would also be suitable for terrestrial use in rocket-assisted takeoff of small airplanes. The main novel features of these engines are (1) the use of reinforced paraffin as the fuel and (2) the use of nitrous oxide as the oxidizer. Hybrid (solid-fuel/fluid-oxidizer) rocket engines offer advantages of safety and simplicity over fluid-bipropellant (fluid-fuel/fluid-oxidizer) rocket en - gines, but the thrusts of HTPB-based hybrid rocket engines are limited by the low regression rates of the fuel grains. Paraffin used as a solid fuel has a regression rate about 4 times that of HTPB, but pure paraffin fuel grains soften when heated; hence, paraffin fuel grains can, potentially, slump during firing. In a hybrid engine of the present type, the paraffin is molded into a 3-volume-percent graphite sponge or similar carbon matrix, which supports the paraffin against slumping during firing. In addition, because the carbon matrix material burns along with the paraffin, engine performance is not appreciably degraded by use of the matrix.

  1. Advanced Solid Rocket Launcher and Its Evolution

    Science.gov (United States)

    Morita, Yasuhiro; Imoto, Takayuki; Habu, Hiroto; Ohtsuka, Hirohito; Hori, Keiichi; Koreki, Takemasa; Fukuchi, Apollo; Uekusa, Yasuyuki; Akiba, Ryojiro

    The research on next generation solid propellant rockets is actively underway in various spectra. JAXA is developing the Advanced Solid Rocket (ASR) as a successor to the M-V launch vehicle, which was utilized over past ten years for space science programs including planetary missions. ASR is a result of the development of the next generation technology including a highly intelligent autonomous check-out system, which is connected to not only the solid rocket but also future transportation systems. It is expected to improve the efficiency of the launch system and double the cost performance. Far beyond this effort, the passion of the volunteers among the industry-government-academia cooperation has been united to establish the society of the freewheeling thinking “Next generation Solid Rocket Society (NSRS)”. It aims at a larger revolution than what the ASR provides so that the order of the cost performance is further improved. A study of the Low melting temperature Thermoplastic Propellant (LTP) is now at the experimental stage, which is expected to reform the manufacturing process of the solid rocket propellant and lead to a significant increase in cost performance. This paper indicates the direction of the big flow towards the next generation solid-propellant rockets: the concept of the intelligent ASR under development; and the innovation behind LTP.

  2. Hydrocarbon Rocket Technology Impact Forecasting

    Science.gov (United States)

    Stuber, Eric; Prasadh, Nishant; Edwards, Stephen; Mavris, Dimitri N.

    2012-01-01

    Forecasting method is a normative forecasting technique that allows the designer to quantify the effects of adding new technologies on a given design. This method can be used to assess and identify the necessary technological improvements needed to close the gap that exists between the current design and one that satisfies all constraints imposed on the design. The TIF methodology allows for more design knowledge to be brought to the earlier phases of the design process, making use of tools such as Quality Function Deployments, Morphological Matrices, Response Surface Methodology, and Monte Carlo Simulations.2 This increased knowledge allows for more informed decisions to be made earlier in the design process, resulting in shortened design cycle time. This paper will investigate applying the TIF method, which has been widely used in aircraft applications, to the conceptual design of a hydrocarbon rocket engine. In order to reinstate a manned presence in space, the U.S. must develop an affordable and sustainable launch capability. Hydrocarbon-fueled rockets have drawn interest from numerous major government and commercial entities because they offer a low-cost heavy-lift option that would allow for frequent launches1. However, the development of effective new hydrocarbon rockets would likely require new technologies in order to overcome certain design constraints. The use of advanced design methods, such as the TIF method, enables the designer to identify key areas in need of improvement, allowing one to dial in a proposed technology and assess its impact on the system. Through analyses such as this one, a conceptual design for a hydrocarbon-fueled vehicle that meets all imposed requirements can be achieved.

  3. EnviroAtlas - Portland, OR - Atlas Area Boundary

    Data.gov (United States)

    U.S. Environmental Protection Agency — This EnviroAtlas dataset shows the boundary of the Portland, OR Atlas Area. It represents the outside edge of all the block groups included in the EnviroAtlas Area....

  4. Atlas II and IIA analyses and environments validation

    Science.gov (United States)

    Martin, Richard E.

    1995-06-01

    General Dynamics has now flown all four versions of the Atlas commercial launch vehicle, which cover a payload weight capability to geosynchronous transfer orbit (GTO) in the range of 5000-8000 lb. The key analyses to set design and environmental test parameters for the vehicle modifications and the ground and flight test data that validated them were prepared in paper IAF-91-170 for the first version, Atlas I. This paper presents similar data for the next two versions, Atlas II and IIA. The Atlas II has propellant tanks lengthened by 12 ft and is boosted by MA-5A rocket engines uprated to 474,000 lb liftoff thrust. GTO payload capability is 6225 lb with the 11-ft fairing. The Atlas IIA is an Atlas II with uprated RL10A-4 engines on the lengthened Centaur II upper stage. The two 20,800 lb thrust, 449 s specific impulse engines with an optional extendible nozzle increase payload capability to GTO to 6635 lb. The paper describes design parameters and validated test results for many other improvements that have generally provided greater capability at less cost, weight and complexity and better reliability. Those described include: moving the MA-5A start system to the ground, replacing the vernier engines with a simple 50 lb thrust on-off hydrazine roll control system, addition of a POGO suppressor, replacement of Centaur jettisonable insulation panels with fixed foam, a new inertial navigation unit (INU) that combines in one package a ring-laser gyro based strapdown guidance system with two MIL-STD-1750A processors, redundant MIL-STD-1553 data bus interfaces, robust Ada-based software and a new Al-Li payload adapter. Payload environment is shown to be essentially unchanged from previous Atlas vehicles. Validation of load, stability, control and pressurization requirements for the larger vehicle is discussed. All flights to date (five Atlas II, one Atlas IIA) have been successful in launching satellites for EUTELSAT, the U.S. Air Force and INTELSAT. Significant design

  5. ATLAS Recordings

    CERN Multimedia

    Jeremy Herr; Homer A. Neal; Mitch McLachlan

    The University of Michigan Web Archives for the 2006 ATLAS Week Plenary Sessions, as well as the first of 2007, are now online. In addition, there are a wide variety of Software and Physics Tutorial sessions, recorded over the past couple years, to chose from. All ATLAS-specific archives are accessible here.Viewing requires a standard web browser with RealPlayer plug-in (included in most browsers automatically) and works on any major platform. Lectures can be viewed directly over the web or downloaded locally.In addition, you will find access to a variety of general tutorials and events via the portal. Shaping Collaboration 2006The Michigan group is happy to announce a complete set of recordings from the Shaping Collaboration conference held last December at the CICG in Geneva.The event hosted a mix of Collaborative Tool experts and LHC Users, and featured presentations by the CERN Deputy Director General, Prof. Jos Engelen, the President of Internet2, and chief developers from VRVS/EVO, WLAP, and other tools...

  6. NASA's Advanced solid rocket motor

    Science.gov (United States)

    Mitchell, Royce E.

    The Advanced Solid Rocket Motor (ASRM) will not only bring increased safety, reliability and performance for the Space Shuttle Booster, it will enhance overall Shuttle safety by effectively eliminating 174 failure points in the Space Shuttle Main Engine throttling system and by reducing the exposure time to aborts due to main engine loss or shutdown. In some missions, the vulnerability time to Return-to-Launch Site aborts is halved. The ASRM uses case joints which will close or remain static under the effects of motor ignition and pressurization. The case itself is constructed of the weldable steel alloy HP 9-4-0.30, having very high strength and with superior fracture toughness and stress corrosion resistance. The internal insulation is strip-wound and is free of asbestos. The nozzle employs light weight ablative parts and is some 5,000 pounds lighter than the Shuttle motor used to date. The payload performance of the ASRM-powered Shuttle is 12,000 pounds higher than that provided by the present motor. This is of particular benefit for payloads delivered to higher inclinations and/or altitudes. The ASRM facility uses state-of-the-art manufacturing techniques, including continuous propellant mixing and direct casting.

  7. NASA's Advanced solid rocket motor

    Science.gov (United States)

    Mitchell, Royce E.

    1993-01-01

    The Advanced Solid Rocket Motor (ASRM) will not only bring increased safety, reliability and performance for the Space Shuttle Booster, it will enhance overall Shuttle safety by effectively eliminating 174 failure points in the Space Shuttle Main Engine throttling system and by reducing the exposure time to aborts due to main engine loss or shutdown. In some missions, the vulnerability time to Return-to-Launch Site aborts is halved. The ASRM uses case joints which will close or remain static under the effects of motor ignition and pressurization. The case itself is constructed of the weldable steel alloy HP 9-4-0.30, having very high strength and with superior fracture toughness and stress corrosion resistance. The internal insulation is strip-wound and is free of asbestos. The nozzle employs light weight ablative parts and is some 5,000 pounds lighter than the Shuttle motor used to date. The payload performance of the ASRM-powered Shuttle is 12,000 pounds higher than that provided by the present motor. This is of particular benefit for payloads delivered to higher inclinations and/or altitudes. The ASRM facility uses state-of-the-art manufacturing techniques, including continuous propellant mixing and direct casting.

  8. Solid rocket motor cost model

    Science.gov (United States)

    Harney, A. G.; Raphael, L.; Warren, S.; Yakura, J. K.

    1972-01-01

    A systematic and standardized procedure for estimating life cycle costs of solid rocket motor booster configurations. The model consists of clearly defined cost categories and appropriate cost equations in which cost is related to program and hardware parameters. Cost estimating relationships are generally based on analogous experience. In this model the experience drawn on is from estimates prepared by the study contractors. Contractors' estimates are derived by means of engineering estimates for some predetermined level of detail of the SRM hardware and program functions of the system life cycle. This method is frequently referred to as bottom-up. A parametric cost analysis is a useful technique when rapid estimates are required. This is particularly true during the planning stages of a system when hardware designs and program definition are conceptual and constantly changing as the selection process, which includes cost comparisons or trade-offs, is performed. The use of cost estimating relationships also facilitates the performance of cost sensitivity studies in which relative and comparable cost comparisons are significant.

  9. NASA Space Rocket Logistics Challenges

    Science.gov (United States)

    Neeley, James R.; Jones, James V.; Watson, Michael D.; Bramon, Christopher J.; Inman, Sharon K.; Tuttle, Loraine

    2014-01-01

    The Space Launch System (SLS) is the new NASA heavy lift launch vehicle and is scheduled for its first mission in 2017. The goal of the first mission, which will be uncrewed, is to demonstrate the integrated system performance of the SLS rocket and spacecraft before a crewed flight in 2021. SLS has many of the same logistics challenges as any other large scale program. Common logistics concerns for SLS include integration of discreet programs geographically separated, multiple prime contractors with distinct and different goals, schedule pressures and funding constraints. However, SLS also faces unique challenges. The new program is a confluence of new hardware and heritage, with heritage hardware constituting seventy-five percent of the program. This unique approach to design makes logistics concerns such as commonality especially problematic. Additionally, a very low manifest rate of one flight every four years makes logistics comparatively expensive. That, along with the SLS architecture being developed using a block upgrade evolutionary approach, exacerbates long-range planning for supportability considerations. These common and unique logistics challenges must be clearly identified and tackled to allow SLS to have a successful program. This paper will address the common and unique challenges facing the SLS programs, along with the analysis and decisions the NASA Logistics engineers are making to mitigate the threats posed by each.

  10. ATLAS Distributed Computing Automation

    CERN Document Server

    Schovancova, J; The ATLAS collaboration; Borrego, C; Campana, S; Di Girolamo, A; Elmsheuser, J; Hejbal, J; Kouba, T; Legger, F; Magradze, E; Medrano Llamas, R; Negri, G; Rinaldi, L; Sciacca, G; Serfon, C; Van Der Ster, D C

    2012-01-01

    The ATLAS Experiment benefits from computing resources distributed worldwide at more than 100 WLCG sites. The ATLAS Grid sites provide over 100k CPU job slots, over 100 PB of storage space on disk or tape. Monitoring of status of such a complex infrastructure is essential. The ATLAS Grid infrastructure is monitored 24/7 by two teams of shifters distributed world-wide, by the ATLAS Distributed Computing experts, and by site administrators. In this paper we summarize automation efforts performed within the ATLAS Distributed Computing team in order to reduce manpower costs and improve the reliability of the system. Different aspects of the automation process are described: from the ATLAS Grid site topology provided by the ATLAS Grid Information System, via automatic site testing by the HammerCloud, to automatic exclusion from production or analysis activities.

  11. Cusp Alfven and Plasma Electrodynamics Rocket (CAPER) Project

    Data.gov (United States)

    National Aeronautics and Space Administration — Launch a single rocket from Andoya Rocket Range into an active cusp event. Observe electric and magnetic fields, HF waves, electron and ion distributions and...

  12. Hydrocarbon Rocket Engine Plume Imaging with Laser Induced Incandescence Project

    Data.gov (United States)

    National Aeronautics and Space Administration — NASA/ Marshall Space Flight Center (MSFC) needs sensors that can be operated on rocket engine plume environments to improve NASA/SSC rocket engine performance. In...

  13. Rocket studies of the lower ionosphere

    Science.gov (United States)

    Bowhill, Sidney A.

    1990-01-01

    The earth's ionosphere in the altitude range of 50 to 200 km was investigated by rocket-borne sensors, supplemented by ground-based measurement. The rocket payloads included mass spectrometers, energetic particle detectors, Langmuir probes and radio propagation experiments. Where possible, rocket flights were included in studies of specific phenomena, and the availability of data from other experiments greatly increased the significance of the results. The principal ionospheric phenomena studied were: winter anomaly in radiowave absorption, ozone and molecular oxygen densities, mid-latitude sporadic-E layers, energetic particle precipitation at middle and low latitudes, ionospheric instabilities and turbulence, and solar eclipse effects in the D and E regions. This document lists personnel who worked on the project, and provides a bibliography of resultant publications.

  14. Laser-fusion rocket for interplanetary propulsion

    International Nuclear Information System (INIS)

    A rocket powered by fusion microexplosions is well suited for quick interplanetary travel. Fusion pellets are sequentially injected into a magnetic thrust chamber. There, focused energy from a fusion Driver is used to implode and ignite them. Upon exploding, the plasma debris expands into the surrounding magnetic field and is redirected by it, producing thrust. This paper discusses the desired features and operation of the fusion pellet, its Driver, and magnetic thrust chamber. A rocket design is presented which uses slightly tritium-enriched deuterium as the fusion fuel, a high temperature KrF laser as the Driver, and a thrust chamber consisting of a single superconducting current loop protected from the pellet by a radiation shield. This rocket can be operated with a power-to-mass ratio of 110 W gm-1, which permits missions ranging from occasional 9 day VIP service to Mars, to routine 1 year, 1500 ton, Plutonian cargo runs

  15. Atmospheric scavenging of solid rocket exhaust effluents

    Science.gov (United States)

    Fenton, D. L.; Purcell, R. Y.

    1978-01-01

    Solid propellant rocket exhaust was directly utilized to ascertain raindrop scavenging rates for hydrogen chloride. Two chambers were used to conduct the experiments; a large, rigid walled, spherical chamber stored the exhaust constituents, while the smaller chamber housing all the experiments was charged as required with rocket exhaust HCl. Surface uptake experiments demonstrated an HCl concentration dependence for distilled water. Sea water and brackish water HCl uptake was below the detection limit of the chlorine-ion analysis technique used. Plant life HCl uptake experiments were limited to corn and soybeans. Plant age effectively correlated the HCl uptake data. Metallic corrosion was not significant for single 20 minute exposures to the exhaust HCl under varying relative humidity. Characterization of the aluminum oxide particles substantiated the similarity between the constituents of the small scale rocket and the full size vehicles.

  16. Laser-fusion rocket for interplanetary propulsion

    Energy Technology Data Exchange (ETDEWEB)

    Hyde, R.A.

    1983-09-27

    A rocket powered by fusion microexplosions is well suited for quick interplanetary travel. Fusion pellets are sequentially injected into a magnetic thrust chamber. There, focused energy from a fusion Driver is used to implode and ignite them. Upon exploding, the plasma debris expands into the surrounding magnetic field and is redirected by it, producing thrust. This paper discusses the desired features and operation of the fusion pellet, its Driver, and magnetic thrust chamber. A rocket design is presented which uses slightly tritium-enriched deuterium as the fusion fuel, a high temperature KrF laser as the Driver, and a thrust chamber consisting of a single superconducting current loop protected from the pellet by a radiation shield. This rocket can be operated with a power-to-mass ratio of 110 W gm/sup -1/, which permits missions ranging from occasional 9 day VIP service to Mars, to routine 1 year, 1500 ton, Plutonian cargo runs.

  17. The Norwegian Sounding Rocket and Balloon Program

    Science.gov (United States)

    Skatteboe, Rolf

    2001-08-01

    The status and recent developments of the Norwegian Sounding Rocket and Balloon Program are presented with focus on national activities and recent achievements. The main part of the Norwegian program is sounding rocket launches conducted by Andøya Rocket Range from the launch facilities on Andøya and at Svalbard. For the majority of the programs, the scientific goal is investigation of processes in the middle and upper atmosphere. The in situ measurements are supplemented by a large number of ground-based support instruments located at the ALOMAR Observatory. The ongoing and planned projects are described and the highlights of the latest completed projects are given. The scientific program for the period 2001-2003 will be reviewed. Several new programs have been started to improve the services available to the international science comunity. The Hotel Payload project and MiniDusty are important examples that will be introduced in the paper. Available space related infrastructure is summarized.

  18. Metallic Hydrogen: A Game Changing Rocket Propellant

    Science.gov (United States)

    Silvera, Isaac F.

    2016-01-01

    The objective of this research is to produce metallic hydrogen in the laboratory using an innovative approach, and to study its metastability properties. Current theoretical and experimental considerations expect that extremely high pressures of order 4-6 megabar are required to transform molecular hydrogen to the metallic phase. When metallic hydrogen is produced in the laboratory it will be extremely important to determine if it is metastable at modest temperatures, i.e. remains metallic when the pressure is released. Then it could be used as the most powerful chemical rocket fuel that exists and revolutionize rocketry, allowing single-stage rockets to enter orbit and chemically fueled rockets to explore our solar system.

  19. Regression Rate Study in HTPB/GOX Hybrid Rocket Motors.

    OpenAIRE

    Philmon George; Krishnan, S; Lalitha Ramachandran; P. M. Varkey; Raveendran, M

    1996-01-01

    The theoretical and experimenIal studies on hybrid rocket motor combustion research are briefly reviewed and the need for a clear understanding of hybrid rocket fuel regression rate mechanism is brought out. A test facility established at the Indian Institute of Technology, Madras, for hybrid rocket motor research study is described.The results of an experimental study on hydroxyl terminated polybutadiene and gaseous oxygen hybrid rocket motor are presented. Fuel grains with ammonium perchlor...

  20. Additive Manufacturing for Affordable Rocket Engines

    Science.gov (United States)

    West, Brian; Robertson, Elizabeth; Osborne, Robin; Calvert, Marty

    2016-01-01

    Additive manufacturing (also known as 3D printing) technology has the potential to drastically reduce costs and lead times associated with the development of complex liquid rocket engine systems. NASA is using 3D printing to manufacture rocket engine components including augmented spark igniters, injectors, turbopumps, and valves. NASA is advancing the process to certify these components for flight. Success Story: MSFC has been developing rocket 3D-printing technology using the Selective Laser Melting (SLM) process. Over the last several years, NASA has built and tested several injectors and combustion chambers. Recently, MSFC has 3D printed an augmented spark igniter for potential use the RS-25 engines that will be used on the Space Launch System. The new design is expected to reduce the cost of the igniter by a factor of four. MSFC has also 3D printed and tested a liquid hydrogen turbopump for potential use on an Upper Stage Engine. Additive manufacturing of the turbopump resulted in a 45% part count reduction. To understanding how the 3D printed parts perform and to certify them for flight, MSFC built a breadboard liquid rocket engine using additive manufactured components including injectors, turbomachinery, and valves. The liquid rocket engine was tested seven times in 2016 using liquid oxygen and liquid hydrogen. In addition to exposing the hardware to harsh environments, engineers learned to design for the new manufacturing technique, taking advantage of its capabilities and gaining awareness of its limitations. Benefit: The 3D-printing technology promises reduced cost and schedule for rocket engines. Cost is a function of complexity, and the most complicated features provide the largest opportunities for cost reductions. This is especially true where brazes or welds can be eliminated. The drastic reduction in part count achievable with 3D printing creates a waterfall effect that reduces the number of processes and drawings, decreases the amount of touch

  1. The XQC microcalorimeter sounding rocket: a stable LTD platform 30 seconds after rocket motor burnout

    Energy Technology Data Exchange (ETDEWEB)

    Porter, F.S. E-mail: frederick.s.porter@gsfc.nasa.gov; Almy, R.; Apodaca, E.; Figueroa-Feliciano, E.; Galeazzi, M.; Kelley, R.; McCammon, D.; Stahle, C.K.; Szymkowiak, A.E.; Sanders, W.T

    2000-04-07

    The XQC microcalorimeter sounding rocket experiment is designed to provide a stable thermal environment for an LTD detector system within 30 s of the burnout of its second stage rocket motor. The detector system used for this instrument is a 36-pixel microcalorimeter array operated at 60 mK with a single-stage adiabatic demagnetization refrigerator (ADR). The ADR is mounted on a space-pumped liquid helium tank with vapor cooled shields which is vibration isolated from the rocket structure. We present here some of the design and performance details of this mature LTD instrument, which has just completed its third suborbital flight.

  2. Rocket Propulsion Engineering Company Small Launch Vehicle

    OpenAIRE

    Grote, James; Pavia, Tom

    2000-01-01

    Rocket Propulsion Engineering (RPe) is developing the first in a family of two low-cost, two stage, small rocket vehicles suitable for target, suborbital, and small-sat orbital applications. The first of these two launch vehicles, the Prospect LV-1 will have an orbital payload of 300-400 lb. The larger vehicle, the Prospect LV-2, uses about 80% of the components and technology of the LV-1 and will orbit payloads of 1500-1700 lb. Two engines are being developed. A first stage 30,000 lbf class ...

  3. Device and process for attachment of parts to rocket motors

    Science.gov (United States)

    Yagla, Jon J.; Lowry, Robert W.; Mears, Otho L.

    1992-04-01

    An attachment platform positioned longitudinally on a rocket motor chamber and secured with laser welding techniques is described. Each attachment platform is continuously sealed longitudinally to the rocket motor chamber through the application of laser welding and optical seam tracking. Application of laser welding techniques allows for repair and installation of attachment platforms on rocket motors fully loaded with live propellant.

  4. Influence of Rocket Engine Characteristics on Shaft Sealing Technology Needs

    Science.gov (United States)

    Keba, John E.

    1999-01-01

    This paper presents viewgraphs of The Influence of Rocket Engine Characteristics on Shaft Sealing Technology Needs. The topics include: 1) Rocket Turbomachinery Shaft Seals (Inter-Propellant-Seal (IPS) Systems, Lift-off Seal Systems, and Technology Development Needs); 2) Rocket Engine Characteristics (Engine cycles, propellants, missions, etc., Influence on shaft sealing requirements); and 3) Conclusions.

  5. 14 CFR 437.67 - Tracking a reusable suborbital rocket.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Tracking a reusable suborbital rocket. 437... a reusable suborbital rocket. A permittee must— (a) During permitted flight, measure in real time the position and velocity of its reusable suborbital rocket; and (b) Provide position and...

  6. The ATLAS Analysis Model

    CERN Multimedia

    Amir Farbin

    The ATLAS Analysis Model is a continually developing vision of how to reconcile physics analysis requirements with the ATLAS offline software and computing model constraints. In the past year this vision has influenced the evolution of the ATLAS Event Data Model, the Athena software framework, and physics analysis tools. These developments, along with the October Analysis Model Workshop and the planning for CSC analyses have led to a rapid refinement of the ATLAS Analysis Model in the past few months. This article introduces some of the relevant issues and presents the current vision of the future ATLAS Analysis Model. Event Data Model The ATLAS Event Data Model (EDM) consists of several levels of details, each targeted for a specific set of tasks. For example the Event Summary Data (ESD) stores calorimeter cells and tracking system hits thereby permitting many calibration and alignment tasks, but will be only accessible at particular computing sites with potentially large latency. In contrast, the Analysis...

  7. The Irish Wind Atlas

    Energy Technology Data Exchange (ETDEWEB)

    Watson, R. [Univ. College Dublin, Dept. of Electronic and Electrical Engineering, Dublin (Ireland); Landberg, L. [Risoe National Lab., Meteorology and Wind Energy Dept., Roskilde (Denmark)

    1999-03-01

    The development work on the Irish Wind Atlas is nearing completion. The Irish Wind Atlas is an updated improved version of the Irish section of the European Wind Atlas. A map of the irish wind resource based on a WA{sup s}P analysis of the measured data and station description of 27 measuring stations is presented. The results of previously presented WA{sup s}P/KAMM runs show good agreement with these results. (au)

  8. Rocketing into the future the history and technology of rocket planes

    CERN Document Server

    van Pelt, Michel

    2012-01-01

    Rocketing into the Future journeys into the exciting world of rocket planes, examining the exotic concepts and actual flying vehicles that have been devised over the last one hundred years. Lavishly illustrated with over 150 photographs, it recounts the history of rocket planes from the early pioneers who attached simple rockets on to their wooden glider airplanes to the modern world of high-tech research vehicles. The book then looks at the possibilities for the future. The technological and economic challenges of the Space Shuttle proved insurmountable, and thus the program was unable to fulfill its promise of low-cost access to space. However, the burgeoning market of suborbital space tourism may yet give the necessary boost to the development of a truly reusable spaceplane.

  9. Internal ballistics of guns and rockets

    Directory of Open Access Journals (Sweden)

    Asim Ray

    1964-07-01

    Full Text Available An exact analytical solutions of the equations relating to the internals ballistics of guns and rockets in the non-isothermal model using tubular propellants which burns according to the pressure-index law has been obtained. An approximate solution to a pre-assigned level of accuracy has been presented.

  10. Straw Rockets Are out of This World

    Science.gov (United States)

    Gillman, Joan

    2013-01-01

    To capture students' excitement and engage their interest in rocketships and visiting planets in the solar system, the author designed lessons that give students the opportunity to experience the joys and challenges of developing straw rockets, and then observing which design can travel the longest distance. The lessons are appropriate for…

  11. Government Relations: It's Not Rocket Science

    Science.gov (United States)

    Radway, Mike

    2007-01-01

    Many people in the early childhood education field are afraid of government relations work, intimidated by politicians, and believe the whole process is unseemly. The author asserts that they should not be afraid nor be intimidated because government relations is not rocket science and fundamentally officeholders are no different from the rest of…

  12. Vibroacoustic studies on sounding rocket bulkheads

    Science.gov (United States)

    Comrie, Jeffrey L.; Korde, Umesh A.

    2012-04-01

    The natural frequency coupling of 2 components of a sounding rocket system is studied, the forward bulkhead (commonly referred to as the "bulkhead" or "BH") and the payload cavity within the fairing. The bulkhead was modeled as a thin, flat, circular plate with a clamped boundary condition. The payload cavity was modeled as a column of air with closed ends contained by the rocket fairing. Both components were studied individually, and added together to obtain a coupled effect. The components were studied in terms of theoretical calculations and understanding, while testing the theory against experiments conducted in the laboratory. When appreciable differences between theory and experimental results were within reason for the individual components, the coupled system was tested. This methodology enabled a "piecewise" approach to studying and acquiring natural frequency shifting of the sounding rocket model through coupling. Experimental work for frequency tuning of the bulkhead through internal pressure modulation is presented. Guidelines for improvement of the vibroacoustic response through structural redesign and frequency tuning of sounding rockets are detailed.

  13. Recent ATLAS Articles on WLAP

    CERN Multimedia

    Goldfarb, S

    2005-01-01

    As reported in the September 2004 ATLAS eNews, the Web Lecture Archive Project is a system for the archiving and publishing of multimedia presentations, using the Web as medium. We list here newly available WLAP items relating to ATLAS: Atlas Software Week Plenary 6-10 December 2004 North American ATLAS Physics Workshop (Tucson) 20-21 December 2004 (17 talks) Physics Analysis Tools Tutorial (Tucson) 19 December 2004 Full Chain Tutorial 21 September 2004 ATLAS Plenary Sessions, 17-18 February 2005 (17 talks) Coming soon: ATLAS Tutorial on Electroweak Physics, 14 Feb. 2005 Software Workshop, 21-22 February 2005 Click here to browse WLAP for all ATLAS lectures.

  14. Replacement of chemical rocket launchers by beamed energy propulsion.

    Science.gov (United States)

    Fukunari, Masafumi; Arnault, Anthony; Yamaguchi, Toshikazu; Komurasaki, Kimiya

    2014-11-01

    Microwave Rocket is a beamed energy propulsion system that is expected to reach space at drastically lower cost. This cost reduction is estimated by replacing the first-stage engine and solid rocket boosters of the Japanese H-IIB rocket with Microwave Rocket, using a recently developed thrust model in which thrust is generated through repetitively pulsed microwave detonation with a reed-valve air-breathing system. Results show that Microwave Rocket trajectory, in terms of velocity versus altitude, can be designed similarly to the current H-IIB first stage trajectory. Moreover, the payload ratio can be increased by 450%, resulting in launch-cost reduction of 74%. PMID:25402933

  15. Replacement of chemical rocket launchers by beamed energy propulsion.

    Science.gov (United States)

    Fukunari, Masafumi; Arnault, Anthony; Yamaguchi, Toshikazu; Komurasaki, Kimiya

    2014-11-01

    Microwave Rocket is a beamed energy propulsion system that is expected to reach space at drastically lower cost. This cost reduction is estimated by replacing the first-stage engine and solid rocket boosters of the Japanese H-IIB rocket with Microwave Rocket, using a recently developed thrust model in which thrust is generated through repetitively pulsed microwave detonation with a reed-valve air-breathing system. Results show that Microwave Rocket trajectory, in terms of velocity versus altitude, can be designed similarly to the current H-IIB first stage trajectory. Moreover, the payload ratio can be increased by 450%, resulting in launch-cost reduction of 74%.

  16. Measurements of temperature profiles at the exit of small rockets.

    Science.gov (United States)

    Griggs, M; Harshbarger, F C

    1966-02-01

    The sodium line reversal technique was used to determine the reversal temperature profile across the exit of small rockets. Measurements were made on one 73-kg thrust rocket, and two 23-kg thrust rockets with different injectors. The large rocket showed little variation of reversal temperature across the plume. However, the 23-kg rockets both showed a large decrease of reversal temperature from the axis to the edge of the plume. In addition, the sodium line reversal technique of temperature measurement was compared with an infrared technique developed in these laboratories.

  17. Development of Kabila rocket: A radioisotope heated thermionic plasma rocket engine

    Directory of Open Access Journals (Sweden)

    Kalomba Mboyi

    2015-04-01

    Full Text Available A new type of plasma rocket engine, the Kabila rocket, using a radioisotope heated thermionic heating chamber instead of a conventional combustion chamber or catalyst bed is introduced and it achieves specific impulses similar to the ones of conventional solid and bipropellant rockets. Curium-244 is chosen as a radioisotope heat source and a thermal reductive layer is also used to obtain precise thermionic emissions. The self-sufficiency principle is applied by simultaneously heating up the emitting material with the radioisotope decay heat and by powering the different valves of the plasma rocket engine with the same radioisotope decay heat using a radioisotope thermoelectric generator. This rocket engine is then benchmarked against a 1 N hydrazine thruster configuration operated on one of the Pleiades-HR-1 constellation spacecraft. A maximal specific impulse and power saving of respectively 529 s and 32% are achieved with helium as propellant. Its advantages are its power saving capability, high specific impulses and simultaneous ease of storage and restart. It can however be extremely voluminous and potentially hazardous. The Kabila rocket is found to bring great benefits to the existing spacecraft and further research should optimize its geometric characteristics and investigate the physical principals of its operation.

  18. US Rocket Propulsion Industrial Base Health Metrics

    Science.gov (United States)

    Doreswamy, Rajiv

    2013-01-01

    The number of active liquid rocket engine and solid rocket motor development programs has severely declined since the "space race" of the 1950s and 1960s center dot This downward trend has been exacerbated by the retirement of the Space Shuttle, transition from the Constellation Program to the Space launch System (SLS) and similar activity in DoD programs center dot In addition with consolidation in the industry, the rocket propulsion industrial base is under stress. To Improve the "health" of the RPIB, we need to understand - The current condition of the RPIB - How this compares to past history - The trend of RPIB health center dot This drives the need for a concise set of "metrics" - Analogous to the basic data a physician uses to determine the state of health of his patients - Easy to measure and collect - The trend is often more useful than the actual data point - Can be used to focus on problem areas and develop preventative measures The nation's capability to conceive, design, develop, manufacture, test, and support missions using liquid rocket engines and solid rocket motors that are critical to its national security, economic health and growth, and future scientific needs. center dot The RPIB encompasses US government, academic, and commercial (including industry primes and their supplier base) research, development, test, evaluation, and manufacturing capabilities and facilities. center dot The RPIB includes the skilled workforce, related intellectual property, engineering and support services, and supply chain operations and management. This definition touches the five main segments of the U.S. RPIB as categorized by the USG: defense, intelligence community, civil government, academia, and commercial sector. The nation's capability to conceive, design, develop, manufacture, test, and support missions using liquid rocket engines and solid rocket motors that are critical to its national security, economic health and growth, and future scientific needs

  19. Pressure-Equalizing Cradle for Booster Rocket Mounting

    Science.gov (United States)

    Rutan, Elbert L. (Inventor)

    2015-01-01

    A launch system and method improve the launch efficiency of a booster rocket and payload. A launch aircraft atop which the booster rocket is mounted in a cradle, is flown or towed to an elevation at which the booster rocket is released. The cradle provides for reduced structural requirements for the booster rocket by including a compressible layer, that may be provided by a plurality of gas or liquid-filled flexible chambers. The compressible layer contacts the booster rocket along most of the length of the booster rocket to distribute applied pressure, nearly eliminating bending loads. Distributing the pressure eliminates point loading conditions and bending moments that would otherwise be generated in the booster rocket structure during carrying. The chambers may be balloons distributed in rows and columns within the cradle or cylindrical chambers extending along a length of the cradle. The cradle may include a manifold communicating gas between chambers.

  20. Current status of rocket developments in universities -development of a small hybrid rocket with a swirling oxidizer flow type engine

    OpenAIRE

    Yuasa, Saburo; Kitagawa, Koki

    2005-01-01

    To develop an experimental small hybrid rocket with a swirling gaseous oxygen flow type engine, we made a flight model engine. Burning tests of the engine showed that a maximum thrust of 692 N and a specific impulse of 263 s (at sea level) were achieved. We designed a small hybrid rocket with this engine. The rocket measured 1.8 m in length and 15.4 kg in mass. To confirm the flight stability of the rocket, wind tunnel tests using a 112-scale model of the rocket and simulations of the flight ...

  1. Rocket center Peenemünde — Personal memories

    Science.gov (United States)

    Dannenberg, Konrad; Stuhlinger, Ernst

    Von Braun built his first rockets as a young teenager. At 14, he started making plans for rockets for human travel to the Moon and Mars. The German Army began a rocket program in 1929. Two years later, Colonel (later General) Becker contacted von Braun who experimented with rockets in Berlin, gave him a contract in 1932, and, jointly with the Air Force, in 1936 built the rocket center Peenemünde where von Braun and his team developed the A-4 (V-2) rocket under Army auspices, while the Air Force developed the V-1 (buzz bomb), wire-guided bombs, and rocket planes. Albert Speer, impressed by the work of the rocketeers, allowed a modest growth of the Peenemünde project; this brought Dannenberg to the von Braun team in 1940. Hitler did not believe in rockets; he ignored the A-4 project until 1942 when he began to support it, expecting that it could turn the fortunes of war for him. He drastically increased the Peenemünde work force and allowed the transfer of soldiers from the front to Peenemünde; that was when Stuhlinger, in 1943, came to Peenemünde as a Pfc.-Ph.D. Later that year, Himmler wrenched the authority over A-4 production out of the Army's hands, put it under his command, and forced production of the immature rocket at Mittelwerk, and its military deployment against targets in France, Belgium, and England. Throughout the development of the A-4 rocket, von Braun was the undisputed leader of the project. Although still immature by the end of the war, the A-4 had proceeded to a status which made it the first successful long-range precision rocket, the prototype for a large number of military rockets built by numerous nations after the war, and for space rockets that launched satellites and traveled to the Moon and the planets.

  2. ATLAS brochure (Norwegian version)

    CERN Multimedia

    Lefevre, C

    2009-01-01

    ATLAS is the largest detector at the LHC, the most powerful particle accelerator in the world. ATLAS is a multi-purpose detector, designed to throw light on fundamental questions such as the origin of mass and the nature of the Universe's dark matter. Français

  3. The ATLAS tile calorimeter

    CERN Multimedia

    Maximilien Brice

    2003-01-01

    Louis Rose-Dulcina, a technician from the ATLAS collaboration, works on the ATLAS tile calorimeter. Special manufacturing techniques were developed to mass produce the thousands of elements in this detector. Tile detectors are made in a sandwich-like structure where these scintillator tiles are placed between metal sheets.

  4. The ATLAS pixel detector

    OpenAIRE

    Cristinziani, M.

    2007-01-01

    After a ten years planning and construction phase, the ATLAS pixel detector is nearing its completion and is scheduled to be integrated into the ATLAS detector to take data with the first LHC collisions in 2007. An overview of the construction is presented with particular emphasis on some of the major and most recent problems encountered and solved.

  5. ATLAS TV PROJECT

    CERN Multimedia

    2005-01-01

    La Givrine near St Cergue Cross Country Skiing and Fondue at Basse Ruche with M Nordberg, P Jenni, M Nessi, F Gianotti and Co. ATLAS Management Fondu dinner, reviewing state of play of the experiment Many fun scenes from cross country skiing and after 41 minutes of the film starts the fondue dinner in a nice chalet with many persons working for ATLAS experiment

  6. ATLAS TV PROJECT

    CERN Multimedia

    2005-01-01

    Budker Nuclear Physics Institute, Novosibirsk Sequence 1 Shots of aircraft factory where machining for ATLAS is done Shots of aircraft Work on components for ATLAS big wheel Discussions between Tikhonov and Nordberg in workshop Sequence 2 Shots of downtown Novosibirsk, including little church which is mid-point of Russian Federation Sequence 3 Interview of Yuri Tikhonov by Andrew Millington

  7. ATLAS Colouring Book

    CERN Multimedia

    Anthony, Katarina

    2016-01-01

    The ATLAS Experiment Colouring Book is a free-to-download educational book, ideal for kids aged 5-9. It aims to introduce children to the field of High-Energy Physics, as well as the work being carried out by the ATLAS Collaboration.

  8. ATLAS people can run!

    CERN Multimedia

    Claudia Marcelloni de Oliveira; Pauline Gagnon

    It must be all the training we are getting every day, running around trying to get everything ready for the start of the LHC next year. This year, the ATLAS runners were in fine form and came in force. Nine ATLAS teams signed up for the 37th Annual CERN Relay Race with six runners per team. Under a blasting sun on Wednesday 23rd May 2007, each team covered the distances of 1000m, 800m, 800m, 500m, 500m and 300m taking the runners around the whole Meyrin site, hills included. A small reception took place in the ATLAS secretariat a week later to award the ATLAS Cup to the best ATLAS team. For the details on this complex calculation which takes into account the age of each runner, their gender and the color of their shoes, see the July 2006 issue of ATLAS e-news. The ATLAS Running Athena Team, the only all-women team enrolled this year, won the much coveted ATLAS Cup for the second year in a row. In fact, they are so good that Peter Schmid and Patrick Fassnacht are wondering about reducing the women's bonus in...

  9. ATLAS-Hadronic Calorimeter

    CERN Multimedia

    2003-01-01

    Hall 180 work on Hadronic Calorimeter The ATLAS hadronic tile calorimeter The Tile Calorimeter, which constitutes the central section of the ATLAS hadronic calorimeter, is a non-compensating sampling device made of iron and scintillating tiles. (IEEE Trans. Nucl. Sci. 53 (2006) 1275-81)

  10. A Slice of ATLAS

    CERN Multimedia

    2004-01-01

    An entire section of the ATLAS detector is being assembled at Prévessin. Since May the components have been tested using a beam from the SPS, giving the ATLAS team valuable experience of operating the detector as well as an opportunity to debug the system.

  11. ATLAS Brochure (english version)

    CERN Multimedia

    2004-01-01

    ATLAS is the largest detector at the LHC, the most powerful particle accelerator in the world, which will start up in 2008. ATLAS is a multi-purpose detector, designed to throw light on fundamental questions such as the origin of mass and the nature of the Universe's dark matter.

  12. ATLAS brochure (German version)

    CERN Multimedia

    Lefevre, C

    2012-01-01

    ATLAS is the largest detector at the LHC, the most powerful particle accelerator in the world. ATLAS is a multi-purpose detector, designed to throw light on fundamental questions such as the origin of mass and the nature of the Universe's dark matter.

  13. ATLAS Brochure (English version)

    CERN Multimedia

    Lefevre, Christiane

    2011-01-01

    ATLAS is the largest detector at the LHC, the most powerful particle accelerator in the world, which will start up in 2008. ATLAS is a multi-purpose detector, designed to throw light on fundamental questions such as the origin of mass and the nature of the Universe's dark matter.

  14. ATLAS brochure (Danish version)

    CERN Multimedia

    Lefevre, C

    2010-01-01

    ATLAS is the largest detector at the LHC, the most powerful particle accelerator in the world. ATLAS is a multi-purpose detector, designed to throw light on fundamental questions such as the origin of mass and the nature of the Universe's dark matter.

  15. ATLAS brochure (Italian version)

    CERN Multimedia

    Lefevre, C

    2010-01-01

    ATLAS is the largest detector at the LHC, the most powerful particle accelerator in the world. ATLAS is a multi-purpose detector, designed to throw light on fundamental questions such as the origin of mass and the nature of the Universe's dark matter.

  16. ATLAS brochure (French version)

    CERN Multimedia

    Lefevre, C

    2012-01-01

    ATLAS is the largest detector at the LHC, the most powerful particle accelerator in the world. ATLAS is a multi-purpose detector, designed to throw light on fundamental questions such as the origin of mass and the nature of the Universe's dark matter.

  17. ATLAS brochure (Catalan version)

    CERN Multimedia

    Lefevre, C

    2008-01-01

    ATLAS is the largest detector at the LHC, the most powerful particle accelerator in the world, which will start up in 2008. ATLAS is a multi-purpose detector, designed to throw light on fundamental questions such as the origin of mass and the nature of the Universe's dark matter.

  18. ATLAS Brochure (german version)

    CERN Multimedia

    Marcastel, F

    2007-01-01

    ATLAS is the largest detector at the LHC, the most powerful particle accelerator in the world, which will start up in 2008. ATLAS is a multi-purpose detector, designed to throw light on fundamental questions such as the origin of mass and the nature of the Universe's dark matter.

  19. ATLAS brochure (Polish version)

    CERN Multimedia

    Lefevre, C

    2007-01-01

    ATLAS is the largest detector at the LHC, the most powerful particle accelerator in the world, which will start up in 2008. ATLAS is a multi-purpose detector, designed to throw light on fundamental questions such as the origin of mass and the nature of the Universe's dark matter.

  20. ATLAS Brochure (english version)

    CERN Multimedia

    Marcastel, F

    2007-01-01

    ATLAS is the largest detector at the LHC, the most powerful particle accelerator in the world, which will start up in 2008. ATLAS is a multi-purpose detector, designed to throw light on fundamental questions such as the origin of mass and the nature of the Universe's dark matter.

  1. ATLAS Brochure (french version)

    CERN Multimedia

    Marcastel, F

    2007-01-01

    ATLAS is the largest detector at the LHC, the most powerful particle accelerator in the world, which will start up in 2008. ATLAS is a multi-purpose detector, designed to throw light on fundamental questions such as the origin of mass and the nature of the Universe's dark matter.

  2. ATLAS rewards industry

    CERN Multimedia

    Maximilien Brice

    2006-01-01

    For contributing vital pieces to the ATLAS puzzle, three industries were recognized on Friday 5 May during a supplier awards ceremony. After a welcome and overview of the ATLAS experiment by spokesperson Peter Jenni, CERN Secretary-General Maximilian Metzger stressed the importance of industry to CERN's scientific goals. Picture 30 : representatives of the three award-wining companies after the ceremony

  3. ATLAS Thesis Awards 2015

    CERN Multimedia

    Biondi, Silvia

    2016-01-01

    Winners of the ATLAS Thesis Award were presented with certificates and glass cubes during a ceremony on Thursday 25 February. The winners also presented their work in front of members of the ATLAS Collaboration. Winners: Javier Montejo Berlingen, Barcelona (Spain), Ruth Pöttgen, Mainz (Germany), Nils Ruthmann, Freiburg (Germany), and Steven Schramm, Toronto (Canada).

  4. ATLAS Visitors Centre

    CERN Multimedia

    claudia Marcelloni

    2009-01-01

    ATLAS Visitors Centre has opened its shiny new doors to the public. Officially launched on Monday February 23rd, 2009, the permanent exhibition at Point 1 was conceived as a tour resource for ATLAS guides, and as a way to preserve the public’s opportunity to get a close-up look at the experiment in action when the cavern is sealed.

  5. ATLAS brochure (Spanish version)

    CERN Multimedia

    Lefevre, C

    2008-01-01

    ATLAS is the largest detector at the LHC, the most powerful particle accelerator in the world, which will start up in 2008. ATLAS is a multi-purpose detector, designed to throw light on fundamental questions such as the origin of mass and the nature of the Universe's dark matter.

  6. Dear ATLAS colleagues,

    CERN Multimedia

    PH Department

    2008-01-01

    We are collecting old pairs of glasses to take out to Mali, where they can be re-used by people there. The price for a pair of glasses can often exceed 3 months salary, so they are prohibitively expensive for many people. If you have any old spectacles you can donate, please put them in the special box in the ATLAS secretariat, bldg.40-4-D01 before the Christmas closure on 19 December so we can take them with us when we leave for Africa at the end of the month. (more details in ATLAS e-news edition of 29 September 2008: http://atlas-service-enews.web.cern.ch/atlas-service-enews/news/news_mali.php) many thanks! Katharine Leney co-driver of the ATLAS car on the Charity Run to Mali

  7. ATLAS Virtual Visits

    CERN Document Server

    Goldfarb, Steven; The ATLAS collaboration

    2015-01-01

    ATLAS Virtual Visits is a project initiated in 2011 for the Education & Outreach program of the ATLAS Experiment at CERN. Its goal is to promote public appreciation of the LHC physics program and particle physics, in general, through direct dialogue between ATLAS physicists and remote audiences. A Virtual Visit is an IP-based videoconference, coupled with a public webcast and video recording, between ATLAS physicists and remote locations around the world, that typically include high school or university classrooms, Masterclasses, science fairs, or other special events, usually hosted by collaboration members. Over the past two years, more than 10,000 people, from all of the world’s continents, have actively participated in ATLAS Virtual Visits, with many more enjoying the experience from the publicly available webcasts and recordings. We present an overview of our experience and discuss potential development for the future.

  8. Wind Atlas for Egypt

    DEFF Research Database (Denmark)

    Mortensen, Niels Gylling; Said Said, Usama; Badger, Jake

    2006-01-01

    The results of a comprehensive, 8-year wind resource assessment programme in Egypt are presented. The objective has been to provide reliable and accurate wind atlas data sets for evaluating the potential wind power output from large electricityproducing wind turbine installations. The regional wind...... climates of Egypt have been determined by two independent methods: a traditional wind atlas based on observations from more than 30 stations all over Egypt, and a numerical wind atlas based on long-term reanalysis data and a mesoscale model (KAMM). The mean absolute error comparing the two methods is about...... 10% for two large-scale KAMM domains covering all of Egypt, and typically about 5% for several smaller-scale regional domains. The numerical wind atlas covers all of Egypt, whereas the meteorological stations are concentrated in six regions. The Wind Atlas for Egypt represents a significant step...

  9. Wind Atlas for Egypt

    DEFF Research Database (Denmark)

    The results of a comprehensive, 8-year wind resource assessment programme in Egypt are presented. The objective has been to provide reliable and accurate wind atlas data sets for evaluating the potential wind power output from large electricityproducing wind turbine installations. The regional wind...... climates of Egypt have been determined by two independent methods: a traditional wind atlas based on observations from more than 30 stations all over Egypt, and a numerical wind atlas based on long-term reanalysis data and a mesoscale model (KAMM). The mean absolute error comparing the two methods is about...... 10% for two large-scale KAMM domains covering all of Egypt, and typically about 5% for several smaller-scale regional domains. The numerical wind atlas covers all of Egypt, whereas the meteorological stations are concentrated in six regions. The Wind Atlas for Egypt represents a significant step...

  10. ATLAS' major cooling project

    CERN Multimedia

    2005-01-01

    In 2005, a considerable effort has been put into commissioning the various units of ATLAS' complex cryogenic system. This is in preparation for the imminent cooling of some of the largest components of the detector in their final underground configuration. The liquid helium and nitrogen ATLAS refrigerators in USA 15. Cryogenics plays a vital role in operating massive detectors such as ATLAS. In many ways the liquefied argon, nitrogen and helium are the life-blood of the detector. ATLAS could not function without cryogens that will be constantly pumped via proximity systems to the superconducting magnets and subdetectors. In recent weeks compressors at the surface and underground refrigerators, dewars, pumps, linkages and all manner of other components related to the cryogenic system have been tested and commissioned. Fifty metres underground The helium and nitrogen refrigerators, installed inside the service cavern, are an important part of the ATLAS cryogenic system. Two independent helium refrigerators ...

  11. Vega rocket series of multi-stage amateur's rocket program 1965-1968

    Science.gov (United States)

    Kerstein, Aleksander; Krmelj, Miloš

    2003-08-01

    The Astronautical and Rocket Society of Celje (ARSC — Astronavtično in raketno društvo Celje) Slovenia has been involved in experimental programs for students and adults since early in 1962 when the early maned space flight inspired many young people. In the history of ARSC (1962-1999) many project undergone the period 37 years, but one is significant; the PROJECT MULTISTAGE ROCKETS VEGA. The present paper contains chronological and systematical presentation of most rockets, launching and static tests undergone during the period of 1965-1968. VEGA - III - C launching was viewed by some of 500 participants of XVIII International Astronautic Federation Congress, which was held in Belgrade in the former Yugoslavia at that time. Project VEGA, whose main objecture was solid fuel ≫micrograne≪ motor of 100 mm to 160 mm diameter improvements and interconnecting motors in parallel spree and sequentially in stages has been completed with rocket VEGA - IV. This rocket has never been launched and it is still in storage.

  12. A Half Century of Sounding Rockets

    Science.gov (United States)

    Turner, J.

    2015-09-01

    One of the earliest and most successful sounding rocket activities in Europe, was the development of the Skylark system. The requirement for high altitude space research and the approaching International Geophysical Year in 1957-58, motivated the British to develop a sounding rocket system. After considerable investigation of the requirements for the propulsion system, the Raven motor and the necessary basic components and instrumentation of a payload system were developed. The first Skylark was launched on the 13th of February, 1957. This paper describes the development of the Skylark system, the advances in technology of its payload systems and their application in solar and stellar astronomy, upper atmosphere and microgravity research and technological proving of space systems.

  13. Solar Irradiance and Thermospheric Airglow Rocket Experiments

    Science.gov (United States)

    Solomon, Stanley C.

    1998-01-01

    This report describes work done in support of the Solar Irradiance and Thermospheric Air-glow Rocket Experiments at the University of Colorado for NASA grant NAG5-5021 under the direction of Dr. Stanley C. Solomon. (The overall rocket program is directed by Dr. Thomas N. Woods, formerly at the National Center for Atmospheric Research, and now also at the University of Colorado, for NASA grant NAG5-5141.) Grant NAG5-5021 provided assistance to the overall program through analysis of airglow and solar data, support of two graduate students, laboratory technical services, and field support. The general goals of the rocket program were to measure the solar extreme ultraviolet spectral irradiance, measure the terrestrial far-ultraviolet airglow, and analyze their relationship at various levels of solar activity, including near solar minimum. These have been met, as shown below. In addition, we have used the attenuation of solar radiation as the rocket descends through the thermosphere to measure density changes. This work demonstrates the maturity of the observational and modeling methods connecting energetic solar photon fluxes and airglow emissions through the processes of photoionization and photoelectron production and loss. Without a simultaneous photoelectron measurement, some aspects of this relationship remain obscure, and there are still questions pertaining to cascade contributions to molecular and atomic airglow emissions. However, by removing the solar irradiance as an "adjustable parameter" in the analysis, significant progress has been made toward understanding the relationship of far-ultraviolet airglow emissions to the solar and atmospheric conditions that control them.

  14. Rocket plume tomography of combustion species

    OpenAIRE

    Kutrieb, Joshua M.

    2001-01-01

    Interest in accurate detection and targeting of aggressor missiles has received considerable interest with the national priority of developing a missile defense system. Understanding the thermal signatures of the exhaust plumes of such missiles is key to accomplishing that mission. Before signature models can be precisely developed for specific rockets, the radiation of the molecular or combustion species within those plumes must be accurately predicted. A combination translation / rotation s...

  15. Design Study: Rocket Based MHD Generator

    Science.gov (United States)

    1997-01-01

    This report addresses the technical feasibility and design of a rocket based MHD generator using a sub-scale LOx/RP rocket motor. The design study was constrained by assuming the generator must function within the performance and structural limits of an existing magnet and by assuming realistic limits on (1) the axial electric field, (2) the Hall parameter, (3) current density, and (4) heat flux (given the criteria of heat sink operation). The major results of the work are summarized as follows: (1) A Faraday type of generator with rectangular cross section is designed to operate with a combustor pressure of 300 psi. Based on a magnetic field strength of 1.5 Tesla, the electrical power output from this generator is estimated to be 54.2 KW with potassium seed (weight fraction 3.74%) and 92 KW with cesium seed (weight fraction 9.66%). The former corresponds to a enthalpy extraction ratio of 2.36% while that for the latter is 4.16%; (2) A conceptual design of the Faraday MHD channel is proposed, based on a maximum operating time of 10 to 15 seconds. This concept utilizes a phenolic back wall for inserting the electrodes and inter-electrode insulators. Copper electrode and aluminum oxide insulator are suggested for this channel; and (3) A testing configuration for the sub-scale rocket based MHD system is proposed. An estimate of performance of an ideal rocket based MHD accelerator is performed. With a current density constraint of 5 Amps/cm(exp 2) and a conductivity of 30 Siemens/m, the push power density can be 250, 431, and 750 MW/m(sup 3) when the induced voltage uB have values of 5, 10, and 15 KV/m, respectively.

  16. Key technology for reusable rocket engine turbopump

    Science.gov (United States)

    Okayasu, A.; Ohta, T.; Kamijyo, A.; Yamada, H.

    2002-03-01

    Recently, there has been an increased need for evolved space transportation and the research of reusable rocket which enable low cost and high reliability and is generating a lot of interest all over the world. In the USA, the development of reusable launch vehicle "Venture Star" which will be used instead of space shuttle is planned and its half scale model "X-33" was developed for the first flight in 1999. In Japan, there has been agreement on the main points to develop the rocket type RLV based on the technology of H-IIA, HOPE-X before developing space plane type RLV. The planned reusable rocket engine was LOX/LH2 as propellant, has 100- 200 ton thrust and has a throttling capability. In addition, long life and high reliability are required for the engine system including LOX/LH2 turbopump. The paper introduces some key technologies for the reusable turbopump which IHI is promoting for research and development with NAL and Tohoku University.

  17. Radiation from advanced solid rocket motor plumes

    Science.gov (United States)

    Farmer, Richard C.; Smith, Sheldon D.; Myruski, Brian L.

    1994-01-01

    The overall objective of this study was to develop an understanding of solid rocket motor (SRM) plumes in sufficient detail to accurately explain the majority of plume radiation test data. Improved flowfield and radiation analysis codes were developed to accurately and efficiently account for all the factors which effect radiation heating from rocket plumes. These codes were verified by comparing predicted plume behavior with measured NASA/MSFC ASRM test data. Upon conducting a thorough review of the current state-of-the-art of SRM plume flowfield and radiation prediction methodology and the pertinent data base, the following analyses were developed for future design use. The NOZZRAD code was developed for preliminary base heating design and Al2O3 particle optical property data evaluation using a generalized two-flux solution to the radiative transfer equation. The IDARAD code was developed for rapid evaluation of plume radiation effects using the spherical harmonics method of differential approximation to the radiative transfer equation. The FDNS CFD code with fully coupled Euler-Lagrange particle tracking was validated by comparison to predictions made with the industry standard RAMP code for SRM nozzle flowfield analysis. The FDNS code provides the ability to analyze not only rocket nozzle flow, but also axisymmetric and three-dimensional plume flowfields with state-of-the-art CFD methodology. Procedures for conducting meaningful thermo-vision camera studies were developed.

  18. Computational simulation of liquid rocket injector anomalies

    Science.gov (United States)

    Przekwas, A. J.; Singhal, A. K.; Tam, L. T.; Davidian, K.

    1986-01-01

    A computer model has been developed to analyze the three-dimensional two-phase reactive flows in liquid fueled rocket combustors. The model is designed to study the influence of liquid propellant injection nonuniformities on the flow pattern, combustion and heat transfer within the combustor. The Eulerian-Lagrangian approach for simulating polidisperse spray flow, evaporation and combustion has been used. Full coupling between the phases is accounted for. A nonorthogonal, body fitted coordinate system along with a conservative control volume formulation is employed. The physical models built into the model include a kappa-epsilon turbulence model, a two-step chemical reaction, and the six-flux radiation model. Semiempirical models are used to describe all interphase coupling terms as well as chemical reaction rates. The purpose of this study was to demonstrate an analytical capability to predict the effects of reactant injection nonuniformities (injection anomalies) on combustion and heat transfer within the rocket combustion chamber. The results show promising application of the model to comprehensive modeling of liquid propellant rocket engines.

  19. Nuclear Thermal Rocket Element Environmental Simulator (NTREES)

    Science.gov (United States)

    Emrich, William J., Jr.

    2008-01-01

    To support the eventual development of a nuclear thermal rocket engine, a state-of-the-art experimental test setup has been constructed to evaluate the performance characteristics of candidate fuel element materials and geometries in representative environments. The test device simulates the environmental conditions (minus the radiation) to which nuclear rocket fuel components will be subjected during reactor operation. Test articles mounted in the simulator are inductively heated in such a manner as to accurately reproduce the temperatures and heat fluxes normally expected to occur as a result of nuclear fission while at the same time being exposed to flowing hydrogen. This project is referred to as the Nuclear Thermal Rocket Element Environment Simulator or NTREES. The NTREES device is located at the Marshall Space flight Center in a laboratory which has been modified to accommodate the high powers required to heat the test articles to the required temperatures and to handle the gaseous hydrogen flow required for the tests. Other modifications to the laboratory include the installation of a nitrogen gas supply system and a cooling water supply system. During the design and construction of the facility, every effort was made to comply with all pertinent regulations to provide assurance that the facility could be operated in a safe and efficient manner. The NTREES system can currently supply up to 50 kW of inductive heating to the fuel test articles, although the facility has been sized to eventually allow test article heating levels of up to several megawatts.

  20. ATLAS Forward Detectors and Physics

    CERN Document Server

    Soni, N

    2010-01-01

    In this communication I describe the ATLAS forward physics program and the detectors, LUCID, ZDC and ALFA that have been designed to meet this experimental challenge. In addition to their primary role in the determination of ATLAS luminosity these detectors - in conjunction with the main ATLAS detector - will be used to study soft QCD and diffractive physics in the initial low luminosity phase of ATLAS running. Finally, I will briefly describe the ATLAS Forward Proton (AFP) project that currently represents the future of the ATLAS forward physics program.

  1. The 2003 Goddard Rocket Replica Project: A Reconstruction of the World's First Functional Liquid Rocket System

    Science.gov (United States)

    Farr, R. A.; Elam, S. K.; Hicks, G. D.; Sanders, T. M.; London, J. R.; Mayne, A. W.; Christensen, D. L.

    2003-01-01

    As a part of NASA s 2003 Centennial of Flight celebration, engineers and technicians at Marshall Space Flight Center (MSFC), Huntsville, Alabama, in cooperation with the Alabama-Mississippi AIAA Section, have reconstructed historically accurate, functional replicas of Dr. Robert H. Goddard s 1926 first liquid- fuel rocket. The purposes of this project were to clearly understand, recreate, and document the mechanisms and workings of the 1926 rocket for exhibit and educational use, creating a vital resource for researchers studying the evolution of liquid rocketry for years to come. The MSFC team s reverse engineering activity has created detailed engineering-quality drawings and specifications describing the original rocket and how it was built, tested, and operated. Static hot-fire tests, as well as flight demonstrations, have further defined and quantified the actual performance and engineering actual performance and engineering challenges of this major segment in early aerospace history.

  2. Future Modeling Needs in Pulse Detonation Rocket Engine Design

    Science.gov (United States)

    Meade, Brian; Talley, Doug; Mueller, Donn; Tew, Dave; Guidos, Mike; Seymour, Dave

    2001-01-01

    This paper presents a performance model rocket engine design that takes advantage of pulse detonation to generate thrust. The contents include: 1) Introduction to the Pulse Detonation Rocket Engine (PDRE); 2) PDRE modeling issues and options; 3) Discussion of the PDRE Performance Workshop held at Marshall Space Flight Center; and 4) Identify needs involving an open performance model for Pulse Detonation Rocket Engines. This paper is in viewgraph form.

  3. Combustion and Magnetohydrodynamic Processes in Advanced Pulse Detonation Rocket Engines

    OpenAIRE

    Cole, Lord Kahil

    2012-01-01

    A number of promising alternative rocket propulsion concepts have been developed over the past two decades that take advantage of unsteady combustion waves in order to produce thrust. These concepts include the Pulse Detonation Rocket Engine (PDRE), in which repetitive ignition, propagation, and reflection of detonations and shocks can create a high pressure chamber from which gases may be exhausted in a controlled manner. The Pulse Detonation Rocket Induced Magnetohydrodynamic Ejector (PDRIM...

  4. Introduction to the Special Issue on Sounding Rockets and Instrumentation

    OpenAIRE

    Christe, Steven; Zeiger, Ben; Pfaff, Rob; Garcia, Michael

    2016-01-01

    Rocket technology, originally developed for military applications, has provided a low-cost observing platform to carry critical and rapid-response scientific investigations for over 70 years. Even with the development of launch vehicles that could put satellites into orbit, high altitude sounding rockets have remained relevant. In addition to science observations, sounding rockets provide a unique technology test platform and a valuable training ground for scientists and engineers. Most impor...

  5. Sounding Rocket Telemetry Emitter, MID Antenna and Ground Receiver Antennas

    OpenAIRE

    Marque, Alexandre; Ghiotto, Anthony

    2015-01-01

    IEEE MTT-S Undergraduate Scholarships Reports The goal of this research project is to design a complete 2.45 GHz data link for telemetry application between a sounding rocket and a ground station. The emission part is embedded in the rocket and has a lot of mechanical constraints. The design for the emitter, the rocket antenna and the ground station receiver are detailed.

  6. EnviroAtlas - Memphis, TN - EnviroAtlas Community Boundary

    Data.gov (United States)

    U.S. Environmental Protection Agency — This EnviroAtlas dataset shows the boundary of the Memphis, TN EnviroAtlas Community. It represents the outside edge of all the block groups included in the...

  7. Unsupervised Anomaly Detection for Liquid-Fueled Rocket Prop...

    Data.gov (United States)

    National Aeronautics and Space Administration — Title: Unsupervised Anomaly Detection for Liquid-Fueled Rocket Propulsion Health Monitoring. Abstract: This article describes the results of applying four...

  8. Regression Rate Study in HTPB/GOX Hybrid Rocket Motors.

    Directory of Open Access Journals (Sweden)

    Philmon George

    1996-12-01

    Full Text Available The theoretical and experimenIal studies on hybrid rocket motor combustion research are briefly reviewed and the need for a clear understanding of hybrid rocket fuel regression rate mechanism is brought out. A test facility established at the Indian Institute of Technology, Madras, for hybrid rocket motor research study is described.The results of an experimental study on hydroxyl terminated polybutadiene and gaseous oxygen hybrid rocket motor are presented. Fuel grains with ammonium perchlorate "additive" have shownenhanced oxidizermass flux dependence. Smallergrains have higher regression rates than those of the larger ones.

  9. Coning motion stability of wrap around fin rockets

    Institute of Scientific and Technical Information of China (English)

    MAO XueRui; YANG ShuXing; XU Yong

    2007-01-01

    Both the asymptotical stability criterion and the bounded stability criterion of the coning motion for wrap around fin (WAF) rockets are proposed through the analysis of coning motion equations, which can be easily used to determine the existence of the coning motion during the rocket design. The correctness of the criterions is verified by mathematical simulation examples of a WAF rocket with different setting angles. It is also found that the setting angle of WAF has great effects on the rolling moment and side moment of the rocket.

  10. Coning motion stability of wrap around fin rockets

    Institute of Scientific and Technical Information of China (English)

    2007-01-01

    Both the asymptotical stability criterion and the bounded stability criterion of the coning motion for wrap around fin(WAF) rockets are proposed through the analy-sis of coning motion equations,which can be easily used to determine the exis-tence of the coning motion during the rocket design. The correctness of the crite-rions is verified by mathematical simulation examples of a WAF rocket with differ-ent setting angles. It is also found that the setting angle of WAF has great effects on the rolling moment and side moment of the rocket.

  11. Numerical Simulation of Rocket Exhaust Interaction with Lunar Soil Project

    Data.gov (United States)

    National Aeronautics and Space Administration — Rocket plume impingement can cause significant damage and contaminate co-landing spacecraft and surrounding habitat structures during lunar landing operations....

  12. Numerical Simulation of Rocket Exhaust Interaction with Lunar Soil Project

    Data.gov (United States)

    National Aeronautics and Space Administration — Rocket plume impingement may cause significant damage and contaminate co-landed spacecraft and surrounding habitat structures during Lunar landing operations. Under...

  13. Ceremony for ATLAS cavern

    CERN Multimedia

    2003-01-01

    Wednesday 4 June will be a special day for CERN. The President of the Swiss Confederation, Pascal Couchepin, will officially inaugurate the huge ATLAS cavern now that the civil engineering works have ended. The inauguration ceremony will be held in the ATLAS surface building, with speeches by Pascal Couchepin and CERN, ATLAS and civil engineering personalities. This ceremony will be Webcast live. To access the Webcast on 4 June at 18h00 go to CERN Intranet home page or the following address : http://webcast.cern.ch/live.php

  14. ATLAS Inner Detector Alignment

    CERN Document Server

    Bocci, A

    2008-01-01

    The ATLAS experiment is a multi-purpose particle detector that will study high-energy particle collisions produced by the Large Hadron Collider at CERN. In order to achieve its physics goals, the ATLAS tracking requires that the positions of the silicon detector elements have to be known to a precision better than 10 μm. Several track-based alignment algorithms have been developed for the Inner Detector. An extensive validation has been performed with simulated events and real data coming from the ATLAS. Results from such validation are reported in this paper.

  15. ATLAS Event - First Splash of Particles in ATLAS

    CERN Multimedia

    ATLAS Outreach

    2008-01-01

    A simulated event. September 10, 2008 - The ATLAS detector lit up as a flood of particles traversed the detector when the beam was occasionally directed at a target near ATLAS. This allowed ATLAS physicists to study how well the various components of the detector were functioning in preparation for the forthcoming collisions. The first ATLAS data recorded on September 10, 2008 is seen here. Running time 24 seconds

  16. Recent ATLAS Articles on WLAP

    CERN Multimedia

    Goldfarb, S.

    As reported in the September 2004 ATLAS eNews, the Web Lecture Archive Project is a system for the archiving and publishing of multimedia presentations, using the Web as medium. We list here newly available WLAP items relating to ATLAS: June ATLAS Plenary Meeting Tutorial on Physics EDM and Tools (June) Freiburg Overview Week Ketevi Assamagan's Tutorial on Analysis Tools Click here to browse WLAP for all ATLAS lectures.

  17. Recent results from ATLAS experiment

    CERN Document Server

    Smirnov, Sergei; The ATLAS collaboration

    2016-01-01

    The 2nd LHC run has started in 2015 with a pp centre-of-mass collision energy of 13 TeV and ATLAS has taken more than 20 fb-1 of data at the new energy by 2016 summer. In this talk, an overview is given on the ATLAS data taking and the improvements made to the ATLAS experiment during the 2-year shutdown 2013/2014. Selected new results from the recent data analysis from ATLAS is also presented.

  18. ATLAS TV PROJECT

    CERN Multimedia

    OMNI communication

    2006-01-01

    CERN, Building 40 Interview with theorist Mr. Philip Hinchliffe (Berkeley) as well an interview with his wife Mrs. Hinchliffe who is also Physics Department head at Berkeley. They are both working in ATLAS Experiment.

  19. California Ocean Uses Atlas

    Data.gov (United States)

    National Oceanic and Atmospheric Administration, Department of Commerce — This dataset is a result of the California Ocean Uses Atlas Project: a collaboration between NOAA's National Marine Protected Areas Center and Marine Conservation...

  20. Lunar Sample Atlas

    Data.gov (United States)

    National Aeronautics and Space Administration — The Lunar Sample Atlas provides pictures of the Apollo samples taken in the Lunar Sample Laboratory, full-color views of the samples in microscopic thin-sections,...

  1. The Latest from ATLAS

    CERN Multimedia

    2009-01-01

    Since November 2008, ATLAS has undertaken detailed maintenance, consolidation and repair work on the detector (see Bulletin of 20 July 2009). Today, the fraction of the detector that is operational has increased compared to last year: less than 1% of dead channels for most of the sub-systems. "We are going to start taking data this year with a detector which is even more efficient than it was last year," agrees ATLAS Spokesperson, Fabiola Gianotti. By mid-September the detector was fully closed again, and the cavern sealed. The magnet system has been operated at nominal current for extensive periods over recent months. Once the cavern was sealed, ATLAS began two weeks of combined running. Right now, subsystems are joining the run incrementally until the point where the whole detector is integrated and running as one. In the words of ATLAS Technical Coordinator, Marzio Nessi: "Now we really start physics." In parallel, the analysis ...

  2. PeptideAtlas

    Data.gov (United States)

    U.S. Department of Health & Human Services — PeptideAtlas is a multi-organism, publicly accessible compendium of peptides identified in a large set of tandem mass spectrometry proteomics experiments. Mass...

  3. ATLAS Cavern baseplate

    CERN Multimedia

    It-UDS-Audiovisual Services

    2002-01-01

    This video shows the incredible amounth of iron used for ATLAS cavern. Please look at the related links and also videos that are concerning the civil engineering where you can see even more detailed cavern excavation work.

  4. Printed circuit for ATLAS

    CERN Multimedia

    Laurent Guiraud

    1999-01-01

    A printed circuit board made by scientists in the ATLAS collaboration for the transition radiaton tracker (TRT). This will read data produced when a high energy particle crosses the boundary between two materials with different electrical properties.

  5. ATLAS DAQ Configuration Databases

    Institute of Scientific and Technical Information of China (English)

    I.Alexandrov; A.Amorim; 等

    2001-01-01

    The configuration databases are an important part of the Trigger/DAQ system of the future ATLAS experiment .This paper describes their current status giving details of architecture,implementation,test results and plans for future work.

  6. ATLAS TV PROJECT

    CERN Multimedia

    2005-01-01

    ATLAS Physics Workshop at the University of Roma Tre held from Monday 06 June 2005 to Saturday 11 June 2005. Experts establishing workshop, poster, people milling Shots of Peter Jenni introduction Many audience shots Sequences from various talks

  7. General Dynamics Atlas family

    Science.gov (United States)

    Oates, James

    Developments concerning the Atlas family of launch vehicles over the last three or four years are summarized. Attention is given to the center of gravity, load factors, acoustics, pyroshock, low-frequency sinusoidal vibration, and high-frequency random vibration.

  8. Computational Analysis for Rocket-Based Combined-Cycle Systems During Rocket-Only Operation

    Science.gov (United States)

    Steffen, C. J., Jr.; Smith, T. D.; Yungster, S.; Keller, D. J.

    2000-01-01

    A series of Reynolds-averaged Navier-Stokes calculations were employed to study the performance of rocket-based combined-cycle systems operating in an all-rocket mode. This parametric series of calculations were executed within a statistical framework, commonly known as design of experiments. The parametric design space included four geometric and two flowfield variables set at three levels each, for a total of 729 possible combinations. A D-optimal design strategy was selected. It required that only 36 separate computational fluid dynamics (CFD) solutions be performed to develop a full response surface model, which quantified the linear, bilinear, and curvilinear effects of the six experimental variables. The axisymmetric, Reynolds-averaged Navier-Stokes simulations were executed with the NPARC v3.0 code. The response used in the statistical analysis was created from Isp efficiency data integrated from the 36 CFD simulations. The influence of turbulence modeling was analyzed by using both one- and two-equation models. Careful attention was also given to quantify the influence of mesh dependence, iterative convergence, and artificial viscosity upon the resulting statistical model. Thirteen statistically significant effects were observed to have an influence on rocket-based combined-cycle nozzle performance. It was apparent that the free-expansion process, directly downstream of the rocket nozzle, can influence the Isp efficiency. Numerical schlieren images and particle traces have been used to further understand the physical phenomena behind several of the statistically significant results.

  9. ATLAS Civil Engineering Point 1

    CERN Multimedia

    Jean-Claude Vialis

    1999-01-01

    Different phases of realisation to Point 1 : zone of the ATLAS experiment The ATLAS experimental area is located in Point 1, just across the main CERN entrance, in the commune of Meyrin. There people are ever so busy to finish the different infrastructures for ATLAS. Real underground video. The film has original working sound.

  10. Budker INP in ATLAS

    CERN Multimedia

    2001-01-01

    The Novosibirsk group has proposed a new design for the ATLAS liquid argon electromagnetic end-cap calorimeter with a constant thickness of absorber plates. This design has signifi- cant advantages compared to one in the Technical Proposal and it has been accepted by the ATLAS Collaboration. The Novosibirsk group is responsible for the fabrication of the precision aluminium structure for the e.m.end-cap calorimeter.

  11. ATLAS physics results

    CERN Document Server

    AUTHOR|(CDS)2074312

    2015-01-01

    The ATLAS experiment at the Large Hadron Collider at CERN has been successfully taking data since the end of 2009 in proton-proton collisions at centre-of-mass energies of 7 and 8 TeV, and in heavy ion collisions. In these lectures, some of the most recent ATLAS results will be given on Standard Model measurements, the discovery of the Higgs boson, searches for supersymmetry and exotics and on heavy-ion results.

  12. ATLAS Transitional Radiation Tracker

    CERN Multimedia

    ATLAS Outreach

    2006-01-01

    This colorful 3D animation is an excerpt from the film "ATLAS-Episode II, The Particles Strike Back." Shot with a bug's eye view of the inside of the detector. The viewer is taken on a tour of the inner workings of the transitional radiation tracker within the ATLAS detector. Subjects covered include what the tracker is used to measure, its structure, what happens when particles pass through the tracker, how it distinguishes between different types of particles within it.

  13. The ATLAS electromagnetic calorimeter

    CERN Document Server

    Maximilien Brice

    2003-01-01

    Michel Mathieu, a technician for the ATLAS collaboration, is cabling the ATLAS electromagnetic calorimeter's first end-cap, before insertion into its cryostat. Millions of wires are connected to the electromagnetic calorimeter on this end-cap that must be carefully fed out from the detector so that data can be read out. Every element on the detector will be attached to one of these wires so that a full digital map of the end-cap can be recreated.

  14. ATLAS Jet Energy Scale

    OpenAIRE

    D. Schouten; Tanasijczuk, A.; Vetterli, M.(Department of Physics, Simon Fraser University, Burnaby, BC, Canada); Collaboration, for the ATLAS

    2012-01-01

    Jets originating from the fragmentation of quarks and gluons are the most common, and complicated, final state objects produced at hadron colliders. A precise knowledge of their energy calibration is therefore of great importance at experiments at the Large Hadron Collider at CERN, while is very difficult to ascertain. We present in-situ techniques and results for the jet energy scale at ATLAS using recent collision data. ATLAS has demonstrated an understanding of the necessary jet energy cor...

  15. Ontogenic profiling of glucosinolates, flavonoids, and other secondary metabolites in Eruca sativa (salad rocket), Diplotaxis erucoides (wall rocket), Diplotaxis tenuifolia (wild rocket), and Bunias orientalis (Turkish rocket).

    Science.gov (United States)

    Bennett, Richard N; Rosa, Eduardo A S; Mellon, Fred A; Kroon, Paul A

    2006-05-31

    As an influence of the Mediterranean diet, rocket species such as Eruca sativa L., Diplotaxis species, and Bunias orientalis L. are eaten all over the world at different ontogenic stages in salads and soups. They are all species within the plant order Capparales (glucosinolate-containing species), and all are from the family Brassicaceae. Predominantly, the leaves of these species are eaten raw or cooked, although Eruca flowers are also consumed. There is considerable potential with raw plant material for a higher exposure to bioactive phytochemicals such as glucosinolates, their hydrolysis products, and also phenolics, flavonoids, and vitamins such as vitamin C. These compounds are susceptible to ontogenic variation, and the few published studies that have addressed this topic have been inconsistent. Thus, an ontogenic study was performed and all samples were analyzed using a previously developed robust liquid chromatography/mass spectrometry method for the identification and quantification of the major phytochemicals in all tissues of the rocket species. Seeds and roots of both Eruca and Diplotaxis contained predominantly 4-methylthiobutylglucosinolate. Leaves of Eruca and Diplotaxis contained high amounts of 4-mercaptobutylglucosinolate with lower levels of 4-methylthiobutlyglucosinolate and 4-methylsulfinylbutylglucosinolate. Flowers of Eruca and Diplotaxiscontained predominantly 4-methylsulfinylbutyl-glucosinolate. In addition, roots of both Diplotaxisspecies contained 4-hydroxybenzylglucosinolate but 4-hydroxybenzylglucosinolate was absent from roots of Eruca. Seeds and seedlings of all Eruca contained N-heterocyclic compounds but no sinapine, whereas Diplotaxis contained sinapine but not the N-heterocycles. In all tissues of B. orientalis, 4-hydroxybenzylglucosinolate and 4-methylsulfinyl-3-butenylglucosinolate were predominant. All rocket tissues, except roots, contained significant levels of polyglycosylated flavonoids, with/without hydroxycinnamoyl

  16. Rocket-Powered Parachutes Rescue Entire Planes

    Science.gov (United States)

    2010-01-01

    Small Business Innovation Research (SBIR) contracts with Langley Research Center helped BRS Aerospace, of Saint Paul, Minnesota, to develop technology that has saved 246 lives to date. The company s whole aircraft parachute systems deploy in less than 1 second thanks to solid rocket motors and are capable of arresting the descent of a small aircraft, lowering it safely to the ground. BRS has sold more than 30,000 systems worldwide, and the technology is now standard equipment on many of the world s top-selling aircraft. Parachutes for larger airplanes are in the works.

  17. Rocket engine diagnostics using qualitative modeling techniques

    Science.gov (United States)

    Binder, Michael; Maul, William; Meyer, Claudia; Sovie, Amy

    1992-01-01

    Researchers at NASA Lewis Research Center are presently developing qualitative modeling techniques for automated rocket engine diagnostics. A qualitative model of a turbopump interpropellant seal system has been created. The qualitative model describes the effects of seal failures on the system steady-state behavior. This model is able to diagnose the failure of particular seals in the system based on anomalous temperature and pressure values. The anomalous values input to the qualitative model are generated using numerical simulations. Diagnostic test cases include both single and multiple seal failures.

  18. ATLAS Facility Description Report

    International Nuclear Information System (INIS)

    A thermal-hydraulic integral effect test facility, ATLAS (Advanced Thermal-hydraulic Test Loop for Accident Simulation), has been constructed at KAERI (Korea Atomic Energy Research Institute). The ATLAS has the same two-loop features as the APR1400 and is designed according to the well-known scaling method suggested by Ishii and Kataoka to simulate the various test scenarios as realistically as possible. It is a half-height and 1/288-volume scaled test facility with respect to the APR1400. The fluid system of the ATLAS consists of a primary system, a secondary system, a safety injection system, a break simulating system, a containment simulating system, and auxiliary systems. The primary system includes a reactor vessel, two hot legs, four cold legs, a pressurizer, four reactor coolant pumps, and two steam generators. The secondary system of the ATLAS is simplified to be of a circulating loop-type. Most of the safety injection features of the APR1400 and the OPR1000 are incorporated into the safety injection system of the ATLAS. In the ATLAS test facility, about 1300 instrumentations are installed to precisely investigate the thermal-hydraulic behavior in simulation of the various test scenarios. This report describes the scaling methodology, the geometric data of the individual component, and the specification and the location of the instrumentations in detail

  19. Theoretical and Experimental Analysis of the Physics of Water Rockets

    Science.gov (United States)

    Barrio-Perotti, R.; Blanco-Marigorta, E.; Fernandez-Francos, J.; Galdo-Vega, M.

    2010-01-01

    A simple rocket can be made using a plastic bottle filled with a volume of water and pressurized air. When opened, the air pressure pushes the water out of the bottle. This causes an increase in the bottle momentum so that it can be propelled to fairly long distances or heights. Water rockets are widely used as an educational activity, and several…

  20. Sounding rocket experiment of bare electrodynamic tether system

    OpenAIRE

    Fujii, Hironori; Watanabe, Takeo; Kojima, Hirohisa; Kusagaya, Tairo; Oyama, Koh-ichiro; Yamagiwa, Yoshiki; Ohtsu, Hirotaka; Cho, Mengu; Sasaki, Susumu; Tanaka, Koji; Williams, John; Rubin, Binyamin; Les Jhonson, Charles; Khazanov, George; Sanmartín Losada, Juan Ramón

    2009-01-01

    An overview of asounding rocket S-520-25th, project on space tether technology experiment is presented.The project is prepared by an international research group consisting of Japanese,European,American,andAustralianresearchers.The sounding rocket will be assembled by the ISAS/JAXA and will be launched in the summer of 2009.

  1. The Effect of Atmospheric Pressure on Rocket Thrust -- Part I.

    Science.gov (United States)

    Leitner, Alfred

    1982-01-01

    The first of a two-part question asks: Does the total thrust of a rocket depend on the surrounding pressure? The answer to this question is provided, with accompanying diagrams of rockets. The second part of the question (and answer) are provided in v20 n7, p479, Oct 1982 of this journal. (Author/JN)

  2. Collaboration with and without Coauthorship: Rocket Science Versus Economic Science

    OpenAIRE

    Barnett, William

    2015-01-01

    This essay is about my prior experiences as a rocket scientist on Apollo rocket engines, with comparison to my subsequent experiences at the Federal Reserve, and in academia, with emphasis upon differences in collaboration and scientific methodology. A primary difference is in the emphasis on measurement.

  3. Project Stratos; reaching space with a student-built rocket

    NARCIS (Netherlands)

    Haneveer, M.

    2013-01-01

    In the spring of 2009 a team of 15 TU Delft students travelled to Kiruna, Sweden with only one goal: to launch the rocket Stratos I they had been working on for 2 years to an altitude of over 12km, thereby claiming the European Amateur Rocket Altitude record. These students were part of Delft Aerosp

  4. Some cases of vertical ascent of a rocket

    Directory of Open Access Journals (Sweden)

    M. Narsing Rao

    1960-07-01

    Full Text Available The differential equations of motion of vertically ascending rocket are integrated in closed form in terms of Bessel functions. During burning the drag co-efficient and acceleration due to gravity are assumed to be constant. Four different cases of motion are treated under different assumptions regarding the law of mass-variations of the rocket.

  5. Developments in REDES: The Rocket Engine Design Expert System

    Science.gov (United States)

    Davidian, Kenneth O.

    1990-01-01

    The Rocket Engine Design Expert System (REDES) was developed at NASA-Lewis to collect, automate, and perpetuate the existing expertise of performing a comprehensive rocket engine analysis and design. Currently, REDES uses the rigorous JANNAF methodology to analyze the performance of the thrust chamber and perform computational studies of liquid rocket engine problems. The following computer codes were included in REDES: a gas properties program named GASP; a nozzle design program named RAO; a regenerative cooling channel performance evaluation code named RTE; and the JANNAF standard liquid rocket engine performance prediction code TDK (including performance evaluation modules ODE, ODK, TDE, TDK, and BLM). Computational analyses are being conducted by REDES to provide solutions to liquid rocket engine thrust chamber problems. REDES was built in the Knowledge Engineering Environment (KEE) expert system shell and runs on a Sun 4/110 computer.

  6. Introduction to the Special Issue on Sounding Rockets and Instrumentation

    CERN Document Server

    Christe, Steven; Pfaff, Rob; Garcia, Michael

    2016-01-01

    Rocket technology, originally developed for military applications, has provided a low-cost observing platform to carry critical and rapid-response scientific investigations for over 70 years. Even with the development of launch vehicles that could put satellites into orbit, high altitude sounding rockets have remained relevant. In addition to science observations, sounding rockets provide a unique technology test platform and a valuable training ground for scientists and engineers. Most importantly, sounding rockets remain the only way to explore the tenuous regions of the Earth's atmosphere (the upper stratosphere, mesosphere, and lower ionosphere/thermosphere) above balloon altitudes ($\\sim$40 km) and below satellite orbits ($\\sim$160 km). They can lift remote sensing telescope payloads with masses up to 400 kg to altitudes of 350 km providing observing times of up to 6 minutes above the blocking influence of Earth's atmosphere. Though a number of sounding rocket research programs exist around the world, th...

  7. EnviroAtlas - Metrics for Austin, TX

    Data.gov (United States)

    U.S. Environmental Protection Agency — This EnviroAtlas web service supports research and online mapping activities related to EnviroAtlas (https://enviroatlas.epa.gov/EnviroAtlas). The layers in this...

  8. The Chameleon Solid Rocket Propulsion Model

    Science.gov (United States)

    Robertson, Glen A.

    2010-01-01

    The Khoury and Weltman (2004a and 2004b) Chameleon Model presents an addition to the gravitation force and was shown by the author (Robertson, 2009a and 2009b) to present a new means by which one can view other forces in the Universe. The Chameleon Model is basically a density-dependent model and while the idea is not new, this model is novel in that densities in the Universe to include the vacuum of space are viewed as scalar fields. Such an analogy gives the Chameleon scalar field, dark energy/dark matter like characteristics; fitting well within cosmological expansion theories. In respect to this forum, in this paper, it is shown how the Chameleon Model can be used to derive the thrust of a solid rocket motor. This presents a first step toward the development of new propulsion models using density variations verse mass ejection as the mechanism for thrust. Further, through the Chameleon Model connection, these new propulsion models can be tied to dark energy/dark matter toward new space propulsion systems utilizing the vacuum scalar field in a way understandable by engineers, the key toward the development of such systems. This paper provides corrections to the Chameleon rocket model in Robertson (2009b).

  9. Advanced materials for radiation-cooled rockets

    Science.gov (United States)

    Reed, Brian; Biaglow, James; Schneider, Steven

    1993-11-01

    The most common material system currently used for low thrust, radiation-cooled rockets is a niobium alloy (C-103) with a fused silica coating (R-512A or R-512E) for oxidation protection. However, significant amounts of fuel film cooling are usually required to keep the material below its maximum operating temperature of 1370 C, degrading engine performance. Also the R-512 coating is subject to cracking and eventual spalling after repeated thermal cycling. A new class of high-temperature, oxidation-resistant materials are being developed for radiation-cooled rockets, with the thermal margin to reduce or eliminate fuel film cooling, while still exceeding the life of silicide-coated niobium. Rhenium coated with iridium is the most developed of these high-temperature materials. Efforts are on-going to develop 22 N, 62 N, and 440 N engines composed of these materials for apogee insertion, attitude control, and other functions. There is also a complimentary NASA and industry effort to determine the life limiting mechanisms and characterize the thermomechanical properties of these materials. Other material systems are also being studied which may offer more thermal margin and/or oxidation resistance, such as hafnium carbide/tantalum carbide matrix composites and ceramic oxide-coated iridium/rhenium chambers.

  10. Physiological and phytosanitary potential of rocket seeds

    Directory of Open Access Journals (Sweden)

    Jucilayne Fernandes Vieira

    2015-02-01

    Full Text Available The objective of this study was to evaluate the physiological and sanitary quality of seeds of rocket; the research was done at the Laboratory of Seed Analysis and greenhouse of the Department of Plant Science, Federal University of Pelotas (UFPel. Four lots of the cultivar "Antonella'' were tested for following features: initial and final moisture content, germination rate, first count of germination, accelerated aging with saline solution, dry matter contents, seedling shoot and root length, emergence speed index, emergence of seedlings in substrate, electrical conductivity and sanitary condition. A completely randomized design with four replications was used for all tests done and means were compared by Tukey test (P≤0.05. For all tests performed it was concluded that despite changes in the ranking of the best lots, there was agreement regarding the indication of the inferiority of the lot 3 in all tests and it was also observed that the incidence of fungi associated with seeds of rocket interfere with the physiological quality of the lots.

  11. Characterization of nal powders for rocket propulsion

    Science.gov (United States)

    Merotto, L.; Galfetti, L.; Colombo, G.; DeLuca, L. T.

    2011-10-01

    Nanosized metal powders are known to significantly improve both solid and hybrid rocket performance, but have some drawbacks in terms of cost, safety, and possible influence on propellant mechanical properties. Performance enhancement through nanosized metal or metal hydride addition to solid fuels is currently under investigation also for hybrid propulsion. Therefore, a preburning characterization of the powders used in solid propellant or fuel manufacturing is useful to assess their effects on the ballistic properties and engine performance. An investigation concerning the comparative characterization of several aluminum powders having different particle size, age, and coating is presented. Surface area, morphology, chemical species concentration and characteristics, surface passivation layers, surface and subsurface chemical composition, ignition temperature and ignition delay are investigated. The aim of this characterization is to experimentally assess the effect of the nAl powder properties on ballistic characteristics of solid fuels and solidrocket composite-propellant performance, showing an increase in terms of Is caused by the decrease of two-phase losses in solid and a possible significant rf increase in hybrid rockets.

  12. Nuclear Thermal Rocket Simulation in NPSS

    Science.gov (United States)

    Belair, Michael L.; Sarmiento, Charles J.; Lavelle, Thomas M.

    2013-01-01

    Four nuclear thermal rocket (NTR) models have been created in the Numerical Propulsion System Simulation (NPSS) framework. The models are divided into two categories. One set is based upon the ZrC-graphite composite fuel element and tie tube-style reactor developed during the Nuclear Engine for Rocket Vehicle Application (NERVA) project in the late 1960s and early 1970s. The other reactor set is based upon a W-UO2 ceramic-metallic (CERMET) fuel element. Within each category, a small and a large thrust engine are modeled. The small engine models utilize RL-10 turbomachinery performance maps and have a thrust of approximately 33.4 kN (7,500 lbf ). The large engine models utilize scaled RL-60 turbomachinery performance maps and have a thrust of approximately 111.2 kN (25,000 lbf ). Power deposition profiles for each reactor were obtained from a detailed Monte Carlo N-Particle (MCNP5) model of the reactor cores. Performance factors such as thermodynamic state points, thrust, specific impulse, reactor power level, and maximum fuel temperature are analyzed for each engine design.

  13. Solid Rocket Launch Vehicle Explosion Environments

    Science.gov (United States)

    Richardson, E. H.; Blackwood, J. M.; Hays, M. J.; Skinner, T.

    2014-01-01

    Empirical explosion data from full scale solid rocket launch vehicle accidents and tests were collected from all available literature from the 1950s to the present. In general data included peak blast overpressure, blast impulse, fragment size, fragment speed, and fragment dispersion. Most propellants were 1.1 explosives but a few were 1.3. Oftentimes the data from a single accident was disjointed and/or missing key aspects. Despite this fact, once the data as a whole was digitized, categorized, and plotted clear trends appeared. Particular emphasis was placed on tests or accidents that would be applicable to scenarios from which a crew might need to escape. Therefore, such tests where a large quantity of high explosive was used to initiate the solid rocket explosion were differentiated. Also, high speed ground impacts or tests used to simulate such were also culled. It was found that the explosions from all accidents and applicable tests could be described using only the pressurized gas energy stored in the chamber at the time of failure. Additionally, fragmentation trends were produced. Only one accident mentioned the elusive "small" propellant fragments, but upon further analysis it was found that these were most likely produced as secondary fragments when larger primary fragments impacted the ground. Finally, a brief discussion of how this data is used in a new launch vehicle explosion model for improving crew/payload survival is presented.

  14. Computational simulation of liquid fuel rocket injectors

    Science.gov (United States)

    Landrum, D. Brian

    1994-01-01

    A major component of any liquid propellant rocket is the propellant injection system. Issues of interest include the degree of liquid vaporization and its impact on the combustion process, the pressure and temperature fields in the combustion chamber, and the cooling of the injector face and chamber walls. The Finite Difference Navier-Stokes (FDNS) code is a primary computational tool used in the MSFC Computational Fluid Dynamics Branch. The branch has dedicated a significant amount of resources to development of this code for prediction of both liquid and solid fuel rocket performance. The FDNS code is currently being upgraded to include the capability to model liquid/gas multi-phase flows for fuel injection simulation. An important aspect of this effort is benchmarking the code capabilities to predict existing experimental injection data. The objective of this MSFC/ASEE Summer Faculty Fellowship term was to evaluate the capabilities of the modified FDNS code to predict flow fields with liquid injection. Comparisons were made between code predictions and existing experimental data. A significant portion of the effort included a search for appropriate validation data. Also, code simulation deficiencies were identified.

  15. Advanced materials for radiation-cooled rockets

    Science.gov (United States)

    Reed, Brian; Biaglow, James; Schneider, Steven

    1993-01-01

    The most common material system currently used for low thrust, radiation-cooled rockets is a niobium alloy (C-103) with a fused silica coating (R-512A or R-512E) for oxidation protection. However, significant amounts of fuel film cooling are usually required to keep the material below its maximum operating temperature of 1370 C, degrading engine performance. Also the R-512 coating is subject to cracking and eventual spalling after repeated thermal cycling. A new class of high-temperature, oxidation-resistant materials are being developed for radiation-cooled rockets, with the thermal margin to reduce or eliminate fuel film cooling, while still exceeding the life of silicide-coated niobium. Rhenium coated with iridium is the most developed of these high-temperature materials. Efforts are on-going to develop 22 N, 62 N, and 440 N engines composed of these materials for apogee insertion, attitude control, and other functions. There is also a complimentary NASA and industry effort to determine the life limiting mechanisms and characterize the thermomechanical properties of these materials. Other material systems are also being studied which may offer more thermal margin and/or oxidation resistance, such as hafnium carbide/tantalum carbide matrix composites and ceramic oxide-coated iridium/rhenium chambers.

  16. Development of high performance hybrid rocket fuels

    Science.gov (United States)

    Zaseck, Christopher R.

    In this document I discuss paraffin fuel combustion and investigate the effects of additives on paraffin entrainment and regression. In general, hybrid rockets offer an economical and safe alternative to standard liquid and solid rockets. However, slow polymeric fuel regression and low combustion efficiency have limited the commercial use of hybrid rockets. Paraffin is a fast burning fuel that has received significant attention in the 2000's and 2010's as a replacement for standard fuels. Paraffin regresses three to four times faster than polymeric fuels due to the entrainment of a surface melt layer. However, further regression rate enhancement over the base paraffin fuel is necessary for widespread hybrid rocket adoption. I use a small scale opposed flow burner to investigate the effect of additives on the combustion of paraffin. Standard additives such as aluminum combust above the flame zone where sufficient oxidizer levels are present. As a result no heat is generated below the flame itself. In small scale opposed burner experiments the effect of limited heat feedback is apparent. Aluminum in particular does not improve the regression of paraffin in the opposed burner. The lack of heat feedback from additive combustion limits the applicability of the opposed burner. In turn, the results obtained in the opposed burner with metal additive loaded hybrid fuels do not match results from hybrid rocket experiments. In addition, nano-scale aluminum increases melt layer viscosity and greatly slows the regression of paraffin in the opposed flow burner. However, the reactive additives improve the regression rate of paraffin in the opposed burner where standard metals do not. At 5 wt.% mechanically activated titanium and carbon (Ti-C) improves the regression rate of paraffin by 47% in the opposed burner. The mechanically activated Ti C likely reacts in or near the melt layer and provides heat feedback below the flame region that results in faster opposed burner regression

  17. Multiple brain atlas database and atlas-based neuroimaging system.

    Science.gov (United States)

    Nowinski, W L; Fang, A; Nguyen, B T; Raphel, J K; Jagannathan, L; Raghavan, R; Bryan, R N; Miller, G A

    1997-01-01

    For the purpose of developing multiple, complementary, fully labeled electronic brain atlases and an atlas-based neuroimaging system for analysis, quantification, and real-time manipulation of cerebral structures in two and three dimensions, we have digitized, enhanced, segmented, and labeled the following print brain atlases: Co-Planar Stereotaxic Atlas of the Human Brain by Talairach and Tournoux, Atlas for Stereotaxy of the Human Brain by Schaltenbrand and Wahren, Referentially Oriented Cerebral MRI Anatomy by Talairach and Tournoux, and Atlas of the Cerebral Sulci by Ono, Kubik, and Abernathey. Three-dimensional extensions of these atlases have been developed as well. All two- and three-dimensional atlases are mutually preregistered and may be interactively registered with an actual patient's data. An atlas-based neuroimaging system has been developed that provides support for reformatting, registration, visualization, navigation, image processing, and quantification of clinical data. The anatomical index contains about 1,000 structures and over 400 sulcal patterns. Several new applications of the brain atlas database also have been developed, supported by various technologies such as virtual reality, the Internet, and electronic publishing. Fusion of information from multiple atlases assists the user in comprehensively understanding brain structures and identifying and quantifying anatomical regions in clinical data. The multiple brain atlas database and atlas-based neuroimaging system have substantial potential impact in stereotactic neurosurgery and radiotherapy by assisting in visualization and real-time manipulation in three dimensions of anatomical structures, in quantitative neuroradiology by allowing interactive analysis of clinical data, in three-dimensional neuroeducation, and in brain function studies. PMID:9148878

  18. Coordinated rocket and satellite measurements of an auroral event. II - The rocket observations and analysis

    Science.gov (United States)

    Sharp, W. E.; Rees, M. H.; Stewart, A. I.

    1979-01-01

    A rocket-borne payload launched into an aurora and a simultaneous overpass of the Atmosphere Explorer C satellite yielded measurements of auroral optical emission rates, thermal ion and electron densities, and low-energy electron fluxes. Model calculations of the thermospheric manifestation of the aurora were performed through use of rocket-determined auroral ionization rates and satellite-determined neutral gas densities. Measured oxygen densities provided a means of assessing the quenching rate of an excited state of N2. Energy transfer from this excited state appears to be the major source of 5577-A emission. Optical emission at 6300 A cannot be explained either by electron impact on atomic oxygen or by dissociative recombination of O2(+).

  19. Combustion Processes in Hybrid Rocket Engines

    Science.gov (United States)

    Venkateswaran,S.; Merkle, C. L.

    1996-01-01

    In recent years, there has been a resurgence of interest in the development of hybrid rocket engines for advanced launch vehicle applications. Hybrid propulsion systems use a solid fuel such as hydroxyl-terminated polybutadiene (HTPB) along with a gaseous/liquid oxidizer. The performance of hybrid combustors depends on the convective and radiative heat fluxes to the fuel surface, the rate of pyrolysis in the solid phase, and the turbulent combustion processes in the gaseous phases. These processes in combination specify the regression rates of the fuel surface and thereby the utilization efficiency of the fuel. In this paper, we employ computational fluid dynamics (CFD) techniques in order to gain a quantitative understanding of the physical trends in hybrid rocket combustors. The computational modeling is tailored to ongoing experiments at Penn State that employ a two dimensional slab burner configuration. The coordinated computational/experimental effort enables model validation while providing an understanding of the experimental observations. Computations to date have included the full length geometry with and with the aft nozzle section as well as shorter length domains for extensive parametric characterization. HTPB is sed as the fuel with 1,3 butadiene being taken as the gaseous product of the pyrolysis. Pure gaseous oxygen is taken as the oxidizer. The fuel regression rate is specified using an Arrhenius rate reaction, which the fuel surface temperature is given by an energy balance involving gas-phase convection and radiation as well as thermal conduction in the solid-phase. For the gas-phase combustion, a two step global reaction is used. The standard kappa - epsilon model is used for turbulence closure. Radiation is presently treated using a simple diffusion approximation which is valid for large optical path lengths, representative of radiation from soot particles. Computational results are obtained to determine the trends in the fuel burning or

  20. ATLAS: Exceeding all expectations

    CERN Multimedia

    CERN Bulletin

    2010-01-01

    “One year ago it would have been impossible for us to guess that the machine and the experiments could achieve so much so quickly”, says Fabiola Gianotti, ATLAS spokesperson. The whole chain – from collision to data analysis – has worked remarkably well in ATLAS.   The first LHC proton run undoubtedly exceeded expectations for the ATLAS experiment. “ATLAS has worked very well since the beginning. Its overall data-taking efficiency is greater than 90%”, says Fabiola Gianotti. “The quality and maturity of the reconstruction and simulation software turned out to be better than we expected for this initial stage of the experiment. The Grid is a great success, and right from the beginning it has allowed members of the collaboration all over the world to participate in the data analysis in an effective and timely manner, and to deliver physics results very quickly”. In just a few months of data taking, ATLAS has observed t...

  1. OCCIPITALIZATION OF ATLAS

    Directory of Open Access Journals (Sweden)

    Sween Walia

    2014-12-01

    Full Text Available Occipitalization of atlas is an osseous anomaly of the craniovertebral junction which occurs at the base of the skull in the region of the foramen magnum. The knowledge of such a fusion is important because skeletal abnormalities at the craniocervical junction may result in sudden death. During bone cleaning procedure and routine undergraduate osteology teaching, three skulls with Occipitalization of atlas were encountered in the department of Anatomy at MMIMSR, Mullana, India. In one skull, both anterior and posterior arch were completely fused with occipital bone while the transverse process on the right side was not fused whereas left transverse process was fused with occipital bone. Both anterior and posterior arch were completely fused whereas transverse process on both sides were not fused in other skull. In another skull, partial and asymmetrical Occipitalization of atlas vertebra with occipital bone was found with bifid posterior arch of atlas at the level of posterior tubercle. Anterior arch was completely fused with basilar part of occipital bone but both the transverse processes were not fused. Reduced diameter of foramen magnum due to the atlanto-occipital fusion might cause neurological complications due to compression of spinal cord or medulla oblongata, vertebral vessels, 1st cervical nerve, thus, knowledge of occipitalization of the atlas may be of substantial importance to orthopaedicians, neurosurgeons, physicians and radiologists dealing with abnormalities of the cervical spine.

  2. ATLAS Review Office

    CERN Multimedia

    Szeless, B

    The ATLAS internal reviews, be it the mandatory Production Readiness Reviews, the now newly installed Production Advancement Reviews, or the more and more requested different Design Reviews, have become a part of our ATLAS culture over the past years. The Activity Systems Status Overviews are, for the time being, a one in time event and should be held for each system as soon as possible to have some meaning. There seems to a consensus that the reviews have become a useful project tool for the ATLAS management but even more so for the sub-systems themselves making achievements as well as possible shortcomings visible. One other recognized byproduct is the increasing cross talk between the systems, a very important ingredient to make profit all the systems from the large collective knowledge we dispose of in ATLAS. In the last two months, the first two PARs were organized for the MDT End Caps and the TRT Barrel Modules, both part of the US contribution to the ATLAS Project. Furthermore several different design...

  3. Distributed analysis in ATLAS

    Science.gov (United States)

    Dewhurst, A.; Legger, F.

    2015-12-01

    The ATLAS experiment accumulated more than 140 PB of data during the first run of the Large Hadron Collider (LHC) at CERN. The analysis of such an amount of data is a challenging task for the distributed physics community. The Distributed Analysis (DA) system of the ATLAS experiment is an established and stable component of the ATLAS distributed computing operations. About half a million user jobs are running daily on DA resources, submitted by more than 1500 ATLAS physicists. The reliability of the DA system during the first run of the LHC and the following shutdown period has been high thanks to the continuous automatic validation of the distributed analysis sites and the user support provided by a dedicated team of expert shifters. During the LHC shutdown, the ATLAS computing model has undergone several changes to improve the analysis workflows, including the re-design of the production system, a new analysis data format and event model, and the development of common reduction and analysis frameworks. We report on the impact such changes have on the DA infrastructure, describe the new DA components, and include recent performance measurements.

  4. Distributed analysis in ATLAS

    CERN Document Server

    Legger, Federica; The ATLAS collaboration

    2015-01-01

    The ATLAS experiment accumulated more than 140 PB of data during the first run of the Large Hadron Collider (LHC) at CERN. The analysis of such an amount of data for the distributed physics community is a challenging task. The Distributed Analysis (DA) system of the ATLAS experiment is an established and stable component of the ATLAS distributed computing operations. About half a million user jobs are daily running on DA resources, submitted by more than 1500 ATLAS physicists. The reliability of the DA system during the first run of the LHC and the following shutdown period has been high thanks to the continuous automatic validation of the distributed analysis sites and the user support provided by a dedicated team of expert shifters. During the LHC shutdown, the ATLAS computing model has undergone several changes to improve the analysis workflows, including the re-design of the production system, a new analysis data format and event model, and the development of common reduction and analysis frameworks. We r...

  5. Beginnings of rocket development in the czech lands (Czechoslovakia)

    Science.gov (United States)

    Plavec, Michal

    2011-11-01

    Although the first references are from the 15th Century when both Hussites and crusaders are said to have used rockets during the Hussite Wars (also known as the Bohemian Wars) there is no strong evidence that rockets were actually used at that time. It is worth noting that Konrad Kyeser, who described several rockets in his Bellifortis manuscript written 1402-1405, served as advisor to Bohemian King Wenceslas IV. Rockets were in fact used as fireworks from the 16th century in noble circles. Some of these were built by Vavřinec Křička z Bitý\\vsky, who also published a book on fireworks, in which he described how to build rockets for firework displays. Czech soldiers were also involved in the creation of a rocket regiment in the Austrian (Austro-Hungarian) army in the first half of the 19th century. The pioneering era of modern rocket development began in the Czech lands during the 1920s. The first rockets were succesfully launched by Ludvík Očenášek in 1930 with one of them possibly reaching an altitude of 2000 metres. Vladimír Mandl, lawyer and author of the first book on the subject of space law, patented his project for a stage rocket (vysokostoupající raketa) in 1932, but this project never came to fruition. There were several factories during the so-called Protectorate of Bohemia and Moravia in 1939-1945, when the Czech lands were occupied by Nazi Germany, where parts for German Mark A-4/V-2 rockets were produced, but none of the Czech technicians or constructors were able to build an entire rocket. The main goal of the Czech aircraft industry after WW2 was to revive the stagnant aircraft industry. There was no place to create a rocket industry. Concerns about a rocket industry appeared at the end of the 1950s. The Political Board of the Central Committee of the Czechoslovak Communist Party started to study the possibilities of creating a rocket industry after the first flight into space and particularly after US nuclear weapons were based in Italy

  6. Rocket-Based Combined Cycle Engine Concept Development

    Science.gov (United States)

    Ratekin, G.; Goldman, Allen; Ortwerth, P.; Weisberg, S.; McArthur, J. Craig (Technical Monitor)

    2001-01-01

    The development of rocket-based combined cycle (RBCC) propulsion systems is part of a 12 year effort under both company funding and contract work. The concept is a fixed geometry integrated rocket, ramjet, scramjet, which is hydrogen fueled and uses hydrogen regenerative cooling. The baseline engine structural configuration uses an integral structure that eliminates panel seals, seal purge gas, and closeout side attachments. Engine A5 is the current configuration for NASA Marshall Space Flight Center (MSFC) for the ART program. Engine A5 models the complete flight engine flowpath of inlet, isolator, airbreathing combustor, and nozzle. High-performance rocket thrusters are integrated into the engine enabling both low speed air-augmented rocket (AAR) and high speed pure rocket operation. Engine A5 was tested in GASL's new Flight Acceleration Simulation Test (FAST) facility in all four operating modes, AAR, RAM, SCRAM, and Rocket. Additionally, transition from AAR to RAM and RAM to SCRAM was also demonstrated. Measured performance demonstrated vision vehicle performance levels for Mach 3 AAR operation and ramjet operation from Mach 3 to 4. SCRAM and rocket mode performance was above predictions. For the first time, testing also demonstrated transition between operating modes.

  7. Introduction to the Special Issue on Sounding Rockets and Instrumentation

    Science.gov (United States)

    Christe, Steven; Zeiger, Ben; Pfaff, Rob; Garcia, Michael

    2016-03-01

    Rocket technology, originally developed for military applications, has provided a low-cost observing platform to carry critical and rapid-response scientific investigations for over 70 years. Even with the development of launch vehicles that could put satellites into orbit, high altitude sounding rockets have remained relevant. In addition to science observations, sounding rockets provide a unique technology test platform and a valuable training ground for scientists and engineers. Most importantly, sounding rockets remain the only way to explore the tenuous regions of the Earth’s atmosphere (the upper stratosphere, mesosphere, and lower ionosphere/thermosphere) above balloon altitudes (˜40km) and below satellite orbits (˜160km). They can lift remote sensing telescope payloads with masses up to 400kg to altitudes of 350km providing observing times of up to 6min above the blocking influence of Earth’s atmosphere. Though a number of sounding rocket research programs exist around the world, this article focuses on the NASA Sounding Rocket Program, and particularly on the astrophysical and solar sounding rocket payloads.

  8. On the history of the development of solid-propellant rockets in the Soviet Union

    Science.gov (United States)

    Pobedonostsev, Y. A.

    1977-01-01

    Pre-World War II Soviet solid-propellant rocket technology is reviewed. Research and development regarding solid composite preparations of pyroxyline TNT powder is described, as well as early work on rocket loading calculations, problems of flight stability, and aircraft rocket launching and ground rocket launching capabilities.

  9. Sounding Rockets within Swedish National Balloon and Rocket Programme- Providing Access to Space from Esrange

    Science.gov (United States)

    Sjolander, K.; Karlsson, T.; Lockowandt, C.

    2015-09-01

    Initiated in 2012 by the Swedish National Space Board (SNSB), a new programme dedicated for Swedish scientists to gain access to space using balloons and sounding rockets was started. This programme promotes the possibility to ensure continuity in both the science and the technology used. The sounding rocket part of this national programme started with three possible missions. SPIDER (Small Payloads for Investigation of Disturbances in Electrojet by Rockets) from the Space and Plasma physics department of KTH, 0-STATES (Oxygen Species and Thermospheric Airglow in The Earth's Sky) from the Department of Meteorology Stockholm University (MISU) and LEEWAVES (Local Excitation and Effects of Waves on Atmospheric VErtical Structure) that is collaboration between KTH and MISU. These three missions were planned for launches in 2015 and 2016. SSc has been contracted on a launch ticket basis to provide the launch and service to the scientific instrumentation. This paper presents the SPIDER, 0-STATES and LEEWAVES missions focussing on a mission related technical solutions perspective.

  10. Rockets: Physical science teacher's guide with activities

    Science.gov (United States)

    Vogt, Gregory L.; Rosenberg, Carla R. (Editor)

    1993-01-01

    This guide begins with background information sections on the history of rocketry, scientific principles, and practical rocketry. The sections on scientific principles and practical rocketry are based on Isaac Newton's three laws of motion. These laws explain why rockets work and how to make them more efficient. The background sections are followed with a series of physical science activities that demonstrate the basic science of rocketry. Each activity is designed to be simple and take advantage of inexpensive materials. Construction diagrams, materials and tools lists, and instructions are included. A brief discussion elaborates on the concepts covered in the activities and is followed with teaching notes and discussion questions. The guide concludes with a glossary of terms, suggested reading list, NASA educational resources, and an evaluation questionnaire with a mailer.

  11. Characterization of rocket propellant combustion products

    Energy Technology Data Exchange (ETDEWEB)

    Jenkins, R.A.; Nestor, C.W.; Thompson, C.V.; Gayle, T.M.; Ma, C.Y.; Tomkins, B.A.; Moody, R.L.

    1991-12-09

    The overall objective of the work described in this report is four-fold: to (a) develop a standardized and experimentally validated approach to the sampling and chemical and physical characterization of the exhaust products of scaled-down rocket launch motors fired under experimentally controlled conditions at the Army's Signature Characterization Facility (ASCF) at Redstone Arsenal in Huntsville, Alabama; (b) determine the composition of the exhaust produces; (c) assess the accuracy of a selected existing computer model for predicting the composition of major and minor chemical species; (d) recommended alternations to both the sampling and analysis strategy and the computer model in order to achieve greater congruence between chemical measurements and computer prediction. 34 refs., 2 figs., 35 tabs.

  12. Additive Manufacturing a Liquid Hydrogen Rocket Engine

    Science.gov (United States)

    Jones, Carl P.; Robertson, Elizabeth H.; Koelbl, Mary Beth; Singer, Chris

    2016-01-01

    Space Propulsion is a 5 day event being held from 2nd May to the 6th May 2016 at the Rome Marriott Park Hotel in Rome, Italy. This event showcases products like Propulsion sub-systems and components, Production and manufacturing issues, Liquid, Solid, Hybrid and Air-breathing Propulsion Systems for Launcher and Upper Stages, Overview of current programmes, AIV issues and tools, Flight testing and experience, Technology building blocks for Future Space Transportation Propulsion Systems : Launchers, Exploration platforms & Space Tourism, Green Propulsion for Space Transportation, New propellants, Rocket propulsion & global environment, Cost related aspects of Space Transportation propulsion, Modelling, Pressure-Thrust oscillations issues, Impact of new requirements and regulations on design etc. in the Automotive, Manufacturing, Fabrication, Repair & Maintenance industries.

  13. Innovative Metallized Formulations for Solid Rocket Propulsion

    Institute of Scientific and Technical Information of China (English)

    Luigi T DeLUCA; Luciano GALFETTI; Filippo MAGGI; Giovanni COLOMBO; Alice REINA; Stefano DOSSI; Daniele CONSONNI; Melissa BRAMBILLA

    2012-01-01

    Several metallized solid rocket propellants,AP/Metal/HTPB in the ratio 68/18/1 4,were experimentally analyzed at the Space Propulsion Laboratory of Politecnico di Milano.Effects of the metals (micrometric and nanometric Al,B,Mg,and a variety of dual metals) on the performance of the propellant were studied and contrasted to a conventional micrometric aluminum (30 μm average grain size) taken as reference.It is shown that the propellant microstructure plays a fundamental role in controlling the critical aggregation/agglomeration phenomena occurring below and near the burning surface.Two specific effects of microstructure in terms of steady burning rate and average agglomerate size are illustrated.

  14. CFD Simulation of Liquid Rocket Engine Injectors

    Science.gov (United States)

    Farmer, Richard; Cheng, Gary; Chen, Yen-Sen; Garcia, Roberto (Technical Monitor)

    2001-01-01

    Detailed design issues associated with liquid rocket engine injectors and combustion chamber operation require CFD methodology which simulates highly three-dimensional, turbulent, vaporizing, and combusting flows. The primary utility of such simulations involves predicting multi-dimensional effects caused by specific injector configurations. SECA, Inc. and Engineering Sciences, Inc. have been developing appropriate computational methodology for NASA/MSFC for the past decade. CFD tools and computers have improved dramatically during this time period; however, the physical submodels used in these analyses must still remain relatively simple in order to produce useful results. Simulations of clustered coaxial and impinger injector elements for hydrogen and hydrocarbon fuels, which account for real fluid properties, is the immediate goal of this research. The spray combustion codes are based on the FDNS CFD code' and are structured to represent homogeneous and heterogeneous spray combustion. The homogeneous spray model treats the flow as a continuum of multi-phase, multicomponent fluids which move without thermal or velocity lags between the phases. Two heterogeneous models were developed: (1) a volume-of-fluid (VOF) model which represents the liquid core of coaxial or impinger jets and their atomization and vaporization, and (2) a Blob model which represents the injected streams as a cloud of droplets the size of the injector orifice which subsequently exhibit particle interaction, vaporization, and combustion. All of these spray models are computationally intensive, but this is unavoidable to accurately account for the complex physics and combustion which is to be predicted, Work is currently in progress to parallelize these codes to improve their computational efficiency. These spray combustion codes were used to simulate the three test cases which are the subject of the 2nd International Workshop on-Rocket Combustion Modeling. Such test cases are considered by

  15. Assumed PDF modeling in rocket combustor simulations

    Science.gov (United States)

    Lempke, M.; Gerlinger, P.; Aigner, M.

    2013-03-01

    In order to account for the interaction between turbulence and chemistry, a multivariate assumed PDF (Probability Density Function) approach is used to simulate a model rocket combustor with finite-rate chemistry. The reported test case is the PennState preburner combustor with a single shear coaxial injector. Experimental data for the wall heat flux is available for this configuration. Unsteady RANS (Reynolds-averaged Navier-Stokes) simulation results with and without the assumed PDF approach are analyzed and compared with the experimental data. Both calculations show a good agreement with the experimental wall heat flux data. Significant changes due to the utilization of the assumed PDF approach can be observed in the radicals, e. g., the OH mass fraction distribution, while the effect on the wall heat flux is insignificant.

  16. Liquid atomization by coaxial rocket injectors

    Science.gov (United States)

    Sankar, S. V.; Brena De La Rosa, A.; Isakovic, A.; Bachalo, W. D.

    1991-01-01

    The atomization characteristics of a scaled-down version of a coaxial rocket injector was investigated using a phase Doppler particle analyzer (PDPA). The injector was operated in the conventional mode with liquid being injected through its inner orifice and gas being injected through its outer annulus. The shearing action occurring at the liquid-gas interface causes the liquid jet to atomize. In this study, two different liquid-air systems, namely a water-air system and a liquid nitrogen-gaseous nitrogen system, were chosen for detailed investigation. This paper discusses the performance characteristics of the coaxial injector under different flow and geometric conditions. Specifically, the effects of injection gas pressure and the injector cavity size on variables such as the mean particle diameter, Sauter mean diameter, number density, volume flux, and velocity have been presented.

  17. Small centrifugal pumps for low thrust rockets

    Science.gov (United States)

    Gulbrandsen, N. C.; Furst, R. B.; Burgess, R. M.; Scheer, D. D.

    1985-01-01

    This paper presents the results of a combined analytical and experimental investigation of low specific speed pumps for potential use as components of propellant feed systems for low thrust rocket engines. Shrouded impellers and open face impellers were tested in volute type and vaned diffuser type pumps. Full- and partial-emission diffusers and full- and partial-admission impellers were tested. Axial and radial loads, head and efficiency versus flow, and cavitation tests were conducted. Predicted performance of two pumps are compared when pumping water and liquid hydrogen. Detailed pressure loss and parasitic power values are presented for two pump configurations. Partial-emission diffusers were found to permit use of larger impeller and diffuser passages with a minimal performance penalty. Normal manufacturing tolerances were found to result in substantial power requirement variation with only a small pressure rise change. Impeller wear ring leakage was found to reduce pump pressure rise to an increasing degree as the pump flowrate was decreased.

  18. Rocket Engine Innovations Advance Clean Energy

    Science.gov (United States)

    2012-01-01

    During launch countdown, at approximately T-7 seconds, the Space Shuttle Main Engines (SSMEs) roar to life. When the controllers indicate normal operation, the solid rocket boosters ignite and the shuttle blasts off. Initially, the SSMEs throttle down to reduce stress during the period of maximum dynamic pressure, but soon after, they throttle up to propel the orbiter to 17,500 miles per hour. In just under 9 minutes, the three SSMEs burn over 1.6 million pounds of propellant, and temperatures inside the main combustion chamber reach 6,000 F. To cool the engines, liquid hydrogen circulates through miles of tubing at -423 F. From 1981to 2011, the Space Shuttle fleet carried crew and cargo into orbit to perform a myriad of unprecedented tasks. After 30 years and 135 missions, the feat of engineering known as the SSME boasted a 100-percent flight success rate.

  19. Ocean recovery of Shuttle Solid Rocket Boosters.

    Science.gov (United States)

    Junker, L. J.

    1973-01-01

    Cost effective recovery of the expended Space-Shuttle Solid Rocket Boosters (SRB) from the ocean will result in significant overall cost savings to the Space Shuttle Program. The ocean recovery mission begins with the dispatching of the recovery team to the predicted splashdown area. The SRBs, drogue parachutes and main parachutes must be tracked, located, retrieved, and transported to land where they will be refurbished and recycled for reuse. Trade studies to be conducted will consider the recovery mission requirements and weigh the advantages, disadvantages and costs of various candidate recovery systems. Major parameters effecting the selection of the final system will ensure that the system will meet overall objectives. Large- and small-scale SRB model testing has been conducted to establish characteristics of SRBs during water entry, floating free and under tow.

  20. Improvement of Rocket Performance by Increasing the Thrust

    International Nuclear Information System (INIS)

    This paper describes one of the methods to increase the performance of the rocket. Based of the result of the static test, the measure of the combustion chamber pressure and the thrust of the rocket will increase, if the throat diameter was decreased. The result of the static test showed that the throat diameter of the nozzle was smaller, where as the combustion chamber pressure, the thrust and the specific Impulse were higher. Its mean that the performance of the rocket was increased. (author)

  1. ATLAS production system

    CERN Document Server

    Borodin, Mikhail; The ATLAS collaboration; De, Kaushik; Klimentov, Alexei; Golubkov, Dmitry; Maeno, Tadashi; Mashinistov, Ruslan; Wenaus, Torre; Padolski, Siarhei

    2016-01-01

    The second generation of the ATLAS production system called ProdSys2 is a distributed workload manager which used by thousands of physicists to analyze the data remotely, with the volume of processed data is beyond the exabyte scale, across a more than hundred heterogeneous sites. It achieves high utilization by combining dynamic job definition based on many criterias, such as input and output size, memory requirements and CPU consumption with manageable scheduling policies and by supporting different kind of computational resources, such as GRID, clouds, supercomputers and volunteering computers. Besides jobs definition Production System also includes flexible web user interface, which implements user-friendly environment for main ATLAS workflows, e.g. simple way of combining different data flows, and real-time monitoring, optimised for using with huge amount of information to present. We present an overview of the ATLAS Production System major components: job and task definition, workflow manager web user i...

  2. Two ATLAS suppliers honoured

    CERN Multimedia

    2007-01-01

    The ATLAS experiment has recognised the outstanding contribution of two firms to the pixel detector. Recipients of the supplier award with Peter Jenni, ATLAS spokesperson, and Maximilian Metzger, CERN Secretary-General.At a ceremony held at CERN on 28 November, the ATLAS collaboration presented awards to two of its suppliers that had produced sensor wafers for the pixel detector. The CiS Institut für Mikrosensorik of Erfurt in Germany has supplied 655 sensor wafers containing a total of 1652 sensor tiles and the firm ON Semiconductor has supplied 515 sensor wafers (1177 sensor tiles) from its foundry at Roznov in the Czech Republic. Both firms have successfully met the very demanding requirements. ATLAS’s huge pixel detector is very complicated, requiring expertise in highly specialised integrated microelectronics and precision mechanics. Pixel detector project leader Kevin Einsweiler admits that when the project was first propo...

  3. ATLAS rewards industry

    CERN Multimedia

    2006-01-01

    Showing excellence in mechanics, electronics and cryogenics, three industries are honoured for their contributions to the ATLAS experiment. Representatives of the three award-wining companies after the ceremony. For contributing vital pieces to the ATLAS puzzle, three industries were recognized on Friday 5 May during a supplier awards ceremony. After a welcome and overview of the ATLAS experiment by spokesperson Peter Jenni, CERN Secretary-General Maximilian Metzger stressed the importance of industry to CERN's scientific goals. Close interaction with CERN was a key factor in the selection of each rewarded company, in addition to the high-quality products they delivered to the experiment. Alu Menziken Industrie AG, of Switzerland, was honoured for the production of 380,000 aluminium tubes for the Monitored Drift Tube Chambers (MDT). As Giora Mikenberg, the Muon System Project Leader stressed, the aluminium tubes were delivered on time with an extraordinary quality and precision. Between October 2000 and Jan...

  4. ATLAS TDAQ System Administration:

    CERN Document Server

    Lee, Christopher Jon; The ATLAS collaboration; Bogdanchikov, Alexander; Ballestrero, Sergio; Contescu, Alexandru Cristian; Dubrov, Sergei; Fazio, Daniel; Korol, Aleksandr; Scannicchio, Diana; Twomey, Matthew Shaun; Voronkov, Artem

    2015-01-01

    The ATLAS Trigger and Data Acquisition (TDAQ) system is responsible for the online processing of live data, streaming from the ATLAS experiment at the Large Hadron Collider (LHC) at CERN. The online farm is composed of ̃3000 servers, processing the data readout from ̃100 million detector channels through multiple trigger levels. During the two years of the first Long Shutdown (LS1) there has been a tremendous amount of work done by the ATLAS TDAQ System Administrators, implementing numerous new software applications, upgrading the OS and the hardware, changing some design philosophies and exploiting the High Level Trigger farm with different purposes. During the data taking only critical security updates are applied and broken hardware is replaced to ensure a stable operational environment. The LS1 provided an excellent opportunity to look into new technologies and applications that would help to improve and streamline the daily tasks of not only the System Administrators, but also of the scientists who wil...

  5. Hypothetical Dark Matter/axion Rockets:. Dark Matter in Terms of Space Physics Propulsion

    Science.gov (United States)

    Beckwith, A.

    2010-12-01

    Current proposed photon rocket designs include the Nuclear Photonic Rocket and the Antimatter Photonic Rocket (proposed by Eugen Sanger in the 1950s, as reported by Ref. 1). This paper examines the feasibility of improving the thrust of photon-driven ramjet propulsion by using DM rocket propulsion. The open question is: would a heavy WIMP, if converted to photons, upgrade the power (thrust) of a photon rocket drive, to make interstellar travel a feasible proposition?

  6. ATLAS TV PROJECT

    CERN Multimedia

    2005-01-01

    CAMERA ON TOROID The ATLAS barrel toroid system consists of eight coils, each of axial length 25.3 m, assembled radially and symmetrically around the beam axis. The coils are of a flat racetrack type with two double-pancake windings made of 20.5 kA aluminium-stabilized niobium-titanium superconductor. The video is about the slow lowering of the toroid down to the cavern of ATLAS. It is very demanding task. The camera is placed on top of the toroid.

  7. ATLAS forward physics program

    CERN Document Server

    HELLER, M; The ATLAS collaboration

    2010-01-01

    The variety of forward detectors installed in the vicinity of the ATLAS experiment allows to look over a wide range of forward physics topics. They ensure a good information about rapidity gaps, and the installation of very forward detectors (ALFA and AFP) will allow to tag the leading proton(s) remaining from the different processes studied. Most of the studies have to be done at low luminosity to avoid pile-up, but the AFP project offers a really exiting future for the ATLAS forward physics program. We also present how these forward detectors can be used to measure the relative and absolute luminosity.

  8. ATLAS fast physics monitoring

    Indian Academy of Sciences (India)

    Karsten Köneke; on behalf of the ATLAS Collaboration

    2012-11-01

    The ATLAS experiment at the Large Hadron Collider is recording data from proton–proton collisions at a centre-of-mass energy of 7 TeV since the spring of 2010. The integrated luminosity has grown nearly exponentially since then and continues to rise fast. The ATLAS Collaboration has set up a framework to automatically process the rapidly growing dataset and produce performance and physics plots for the most interesting analyses. The system is designed to give fast feedback. The histograms are produced within hours of data reconstruction (2–3 days after data taking). Hints of potentially interesting physics signals obtained this way are followed up by physics groups.

  9. The Herschel ATLAS

    CERN Document Server

    Eales, S; Clements, D; Cooray, A R; De Zotti, G; Dye, S; Ivison, R; Jarvis, M; Lagache, G; Maddox, S; Negrello, M; Serjeant, S; Thompson, M A; Van Kampen, E; Amblard, A; Andreani, P; Baes, M; Beelen, A; Bendo, G J; Benford, D; Bertoldi, F; Bock, J; Bonfield, D; Boselli, A; Bridge, C; Buat, V; Burgarella, D; Carlberg, R; Cava, A; Chanial, P; Charlot, S; Christopher, N; Coles, P; Cortese, L; Dariush, A; Da Cunha, E; Dalton, G; Danese, L; Dannerbauer, H; Driver, S; Dunlop, J; Fan, L; Farrah, D; Frayer, D; Frenk, C; Geach, J; Gardner, J; Gomez, H; Gonzalez-Nuevo, J; Gonzalez-Solares, E; Griffin, M; Hardcastle, M; Hatziminaoglou, E; Herranz, D; Hughes, D; Ibar, E; Jeong, Woong-Seob; Lacey, C; Lapi, A; Lee, M; Leeuw, L; Liske, J; Lopez-Caniego, M; Müller, T; Nandra, K; Panuzzo, P; Papageorgiou, A; Patanchon, G; Peacock, J; Pearson, C; Phillipps, S; Pohlen, M; Popescu, C; Rawlings, S; Rigby, E; Rigopoulou, M; Rodighiero, G; Sansom, A; Schulz, B; Scott, D; Smith, D J B; Sibthorpe, B; Smail, I; Stevens, J; Sutherland, W; Takeuchi, T; Tedds, J; Temi, P; Tuffs, R; Trichas, M; Vaccari, M; Valtchanov, I; Van der Werf, P; Verma, A; Vieria, J; Vlahakis, C; White, Glenn J

    2009-01-01

    The Herschel ATLAS is the largest open-time key project that will be carried out on the Herschel Space Observatory. It will survey 510 square degrees of the extragalactic sky, four times larger than all the other Herschel surveys combined, in five far-infrared and submillimetre bands. We describe the survey, the complementary multi-wavelength datasets that will be combined with the Herschel data, and the six major science programmes we are undertaking. Using new models based on a previous submillimetre survey of galaxies, we present predictions of the properties of the ATLAS sources in other wavebands.

  10. The Herschel ATLAS

    Science.gov (United States)

    Eales, S.; Dunne, L.; Clements, D.; Cooray, A.; De Zotti, G.; Dye, S.; Ivison, R.; Jarvis, M.; Lagache, G.; Maddox, S.; Negrello, M.; Serjeant, S.; Thompson, M. A.; Van Kampen, E.; Amblard, A.; Andreani, P.; Baes, M.; Beelen, A.; Bendo, G. J.; Bertoldi, F.; Benford, D.; Bock, J.

    2010-01-01

    The Herschel ATLAS is the largest open-time key project that will be carried out on the Herschel Space Observatory. It will survey 570 sq deg of the extragalactic sky, 4 times larger than all the other Herschel extragalactic surveys combined, in five far-infrared and submillimeter bands. We describe the survey, the complementary multiwavelength data sets that will be combined with the Herschel data, and the six major science programs we are undertaking. Using new models based on a previous submillimeter survey of galaxies, we present predictions of the properties of the ATLAS sources in other wave bands.

  11. The ATLAS Simulation Infrastructure

    CERN Document Server

    Aad, Georges; Abdallah, Jalal; Abdelalim, Ahmed Ali; Abdesselam, Abdelouahab; Abdinov, Ovsat; Abi, Babak; Abolins, Maris; Abramowicz, Halina; Abreu, Henso; Acharya, Bobby Samir; Adams, David; Addy, Tetteh; Adelman, Jahred; Adorisio, Cristina; Adragna, Paolo; Adye, Tim; Aefsky, Scott; Aguilar-Saavedra, Juan Antonio; Aharrouche, Mohamed; Ahlen, Steven; Ahles, Florian; Ahmad, Ashfaq; Ahmed, Hossain; Ahsan, Mahsana; Aielli, Giulio; Akdogan, Taylan; Åkesson, Torsten Paul Ake; Akimoto, Ginga; Akimov , Andrei; Aktas, Adil; Alam, Mohammad; Alam, Muhammad Aftab; Albrand, Solveig; Aleksa, Martin; Aleksandrov, Igor; Alexa, Calin; Alexander, Gideon; Alexandre, Gauthier; Alexopoulos, Theodoros; Alhroob, Muhammad; Aliev, Malik; Alimonti, Gianluca; Alison, John; Aliyev, Magsud; Allport, Phillip; Allwood-Spiers, Sarah; Almond, John; Aloisio, Alberto; Alon, Raz; Alonso, Alejandro; Alviggi, Mariagrazia; Amako, Katsuya; Amelung, Christoph; Amorim, Antonio; Amorós, Gabriel; Amram, Nir; Anastopoulos, Christos; Andeen, Timothy; Anders, Christoph Falk; Anderson, Kelby; Andreazza, Attilio; Andrei, George Victor; Anduaga, Xabier; Angerami, Aaron; Anghinolfi, Francis; Anjos, Nuno; Annovi, Alberto; Antonaki, Ariadni; Antonelli, Mario; Antonelli, Stefano; Antos, Jaroslav; Antunovic, Bijana; Anulli, Fabio; Aoun, Sahar; Arabidze, Giorgi; Aracena, Ignacio; Arai, Yasuo; Arce, Ayana; Archambault, John-Paul; Arfaoui, Samir; Arguin, Jean-Francois; Argyropoulos, Theodoros; Arik, Metin; Armbruster, Aaron James; Arnaez, Olivier; Arnault, Christian; Artamonov, Andrei; Arutinov, David; Asai, Makoto; Asai, Shoji; Silva, José; Asfandiyarov, Ruslan; Ask, Stefan; Åsman, Barbro; Asner, David; Asquith, Lily; Assamagan, Ketevi; Astbury, Alan; Astvatsatourov, Anatoli; Atoian, Grigor; Auerbach, Benjamin; Augsten, Kamil; Aurousseau, Mathieu; Austin, Nicholas; Avolio, Giuseppe; Avramidou, Rachel Maria; Axen, David; Ay, Cano; Azuelos, Georges; Azuma, Yuya; Baak, Max; Bach, Andre; Bachacou, Henri; Bachas, Konstantinos; Backes, Moritz; Badescu, Elisabeta; Bagnaia, Paolo; Bai, Yu; Bain, Travis; Baines, John; Baker, Mark; Baker, Oliver Keith; Baker, Sarah; Baltasar Dos Santos Pedrosa, Fernando; Banas, Elzbieta; Banerjee, Piyali; Banerjee, Swagato; Banfi, Danilo; Bangert, Andrea Michelle; Bansal, Vikas; Baranov, Sergey; Baranov, Sergei; Barashkou, Andrei; Barber, Tom; Barberio, Elisabetta Luigia; Barberis, Dario; Barbero, Marlon; Bardin, Dmitri; Barillari, Teresa; Barisonzi, Marcello; Barklow, Timothy; Barlow, Nick; Barnett, Bruce; Barnett, Michael; Baroncelli, Antonio; Barr, Alan; Barreiro, Fernando; Barreiro Guimarães da Costa, João; Barrillon, Pierre; Bartoldus, Rainer; Bartsch, Detlef; Bates, Richard; Batkova, Lucia; Batley, Richard; Battaglia, Andreas; Battistin, Michele; Bauer, Florian; Bawa, Harinder Singh; Bazalova, Magdalena; Beare, Brian; Beau, Tristan; Beauchemin, Pierre-Hugues; Beccherle, Roberto; Becerici, Neslihan; Bechtle, Philip; Beck, Graham; Beck, Hans Peter; Beckingham, Matthew; Becks, Karl-Heinz; Beddall, Ayda; Beddall, Andrew; Bednyakov, Vadim; Bee, Christopher; Begel, Michael; Behar Harpaz, Silvia; Behera, Prafulla; Beimforde, Michael; Belanger-Champagne, Camille; Bell, Paul; Bell, William; Bella, Gideon; Bellagamba, Lorenzo; Bellina, Francesco; Bellomo, Massimiliano; Belloni, Alberto; Belotskiy, Konstantin; Beltramello, Olga; Ben Ami, Sagi; Benary, Odette; Benchekroun, Driss; Bendel, Markus; Benedict, Brian Hugues; Benekos, Nektarios; Benhammou, Yan; Benincasa, Gianpaolo; Benjamin, Douglas; Benoit, Mathieu; Bensinger, James; Benslama, Kamal; Bentvelsen, Stan; Beretta, Matteo; Berge, David; Bergeaas Kuutmann, Elin; Berger, Nicolas; Berghaus, Frank; Berglund, Elina; Beringer, Jürg; Bernat, Pauline; Bernhard, Ralf; Bernius, Catrin; Berry, Tracey; Bertin, Antonio; Besana, Maria Ilaria; Besson, Nathalie; Bethke, Siegfried; Bianchi, Riccardo-Maria; Bianco, Michele; Biebel, Otmar; Biesiada, Jed; Biglietti, Michela; Bilokon, Halina; Bindi, Marcello; Binet, Sebastien; Bingul, Ahmet; Bini, Cesare; Biscarat, Catherine; Bitenc, Urban; Black, Kevin; Blair, Robert; Blanchard, Jean-Baptiste; Blanchot, Georges; Blocker, Craig; Blondel, Alain; Blum, Walter; Blumenschein, Ulrike; Bobbink, Gerjan; Bocci, Andrea; Boehler, Michael; Boek, Jennifer; Boelaert, Nele; Böser, Sebastian; Bogaerts, Joannes Andreas; Bogouch, Andrei; Bohm, Christian; Bohm, Jan; Boisvert, Veronique; Bold, Tomasz; Boldea, Venera; Bondarenko, Valery; Bondioli, Mario; Boonekamp, Maarten; Bordoni, Stefania; Borer, Claudia; Borisov, Anatoly; Borissov, Guennadi; Borjanovic, Iris; Borroni, Sara; Bos, Kors; Boscherini, Davide; Bosman, Martine; Boterenbrood, Hendrik; Bouchami, Jihene; Boudreau, Joseph; Bouhova-Thacker, Evelina Vassileva; Boulahouache, Chaouki; Bourdarios, Claire; Boveia, Antonio; Boyd, James; Boyko, Igor; Bozovic-Jelisavcic, Ivanka; Bracinik, Juraj; Braem, André; Branchini, Paolo; Brandenburg, George; Brandt, Andrew; Brandt, Gerhard; Brandt, Oleg; Bratzler, Uwe; Brau, Benjamin; Brau, James; Braun, Helmut; Brelier, Bertrand; Bremer, Johan; Brenner, Richard; Bressler, Shikma; Britton, Dave; Brochu, Frederic; Brock, Ian; Brock, Raymond; Brodet, Eyal; Bromberg, Carl; Brooijmans, Gustaaf; Brooks, William; Brown, Gareth; Bruckman de Renstrom, Pawel; Bruncko, Dusan; Bruneliere, Renaud; Brunet, Sylvie; Bruni, Alessia; Bruni, Graziano; Bruschi, Marco; Bucci, Francesca; Buchanan, James; Buchholz, Peter; Buckley, Andrew; Budagov, Ioulian; Budick, Burton; Büscher, Volker; Bugge, Lars; Bulekov, Oleg; Bunse, Moritz; Buran, Torleiv; Burckhart, Helfried; Burdin, Sergey; Burgess, Thomas; Burke, Stephen; Busato, Emmanuel; Bussey, Peter; Buszello, Claus-Peter; Butin, Françcois; Butler, Bart; Butler, John; Buttar, Craig; Butterworth, Jonathan; Byatt, Tom; Caballero, Jose; Cabrera Urbán, Susana; Caforio, Davide; Cakir, Orhan; Calafiura, Paolo; Calderini, Giovanni; Calfayan, Philippe; Calkins, Robert; Caloba, Luiz; Calvet, David; Camarri, Paolo; Cameron, David; Campana, Simone; Campanelli, Mario; Canale, Vincenzo; Canelli, Florencia; Canepa, Anadi; Cantero, Josu; Capasso, Luciano; Capeans Garrido, Maria Del Mar; Caprini, Irinel; Caprini, Mihai; Capua, Marcella; Caputo, Regina; Caramarcu, Costin; Cardarelli, Roberto; Carli, Tancredi; Carlino, Gianpaolo; Carminati, Leonardo; Caron, Bryan; Caron, Sascha; Carrillo Montoya, German D.; Carron Montero, Sebastian; Carter, Antony; Carter, Janet; Carvalho, João; Casadei, Diego; Casado, Maria Pilar; Cascella, Michele; Castaneda Hernandez, Alfredo Martin; Castaneda-Miranda, Elizabeth; Castillo Gimenez, Victoria; Castro, Nuno Filipe; Cataldi, Gabriella; Catinaccio, Andrea; Catmore, James; Cattai, Ariella; Cattani, Giordano; Caughron, Seth; Cauz, Diego; Cavalleri, Pietro; Cavalli, Donatella; Cavalli-Sforza, Matteo; Cavasinni, Vincenzo; Ceradini, Filippo; Cerqueira, Augusto Santiago; Cerri, Alessandro; Cerrito, Lucio; Cerutti, Fabio; Cetin, Serkant Ali; Chafaq, Aziz; Chakraborty, Dhiman; Chan, Kevin; Chapman, John Derek; Chapman, John Wehrley; Chareyre, Eve; Charlton, Dave; Chavda, Vikash; Cheatham, Susan; Chekanov, Sergei; Chekulaev, Sergey; Chelkov, Gueorgui; Chen, Hucheng; Chen, Shenjian; Chen, Xin; Cheplakov, Alexander; Chepurnov, Vladimir; Cherkaoui El Moursli, Rajaa; Tcherniatine, Valeri; Chesneanu, Daniela; Cheu, Elliott; Cheung, Sing-Leung; Chevalier, Laurent; Chevallier, Florent; Chiarella, Vitaliano; Chiefari, Giovanni; Chikovani, Leila; Childers, John Taylor; Chilingarov, Alexandre; Chiodini, Gabriele; Chizhov, Mihail; Choudalakis, Georgios; Chouridou, Sofia; Christidi, Illectra-Athanasia; Christov, Asen; Chromek-Burckhart, Doris; Chu, Ming-Lee; Chudoba, Jiri; Ciapetti, Guido; Ciftci, Abbas Kenan; Ciftci, Rena; Cinca, Diane; Cindro, Vladimir; Ciobotaru, Matei Dan; Ciocca, Claudia; Ciocio, Alessandra; Cirilli, Manuela; Citterio, Mauro; Clark, Allan G.; Clark, Philip James; Cleland, Bill; Clemens, Jean-Claude; Clement, Benoit; Clement, Christophe; Coadou, Yann; Cobal, Marina; Coccaro, Andrea; Cochran, James H.; Coggeshall, James; Cogneras, Eric; Colijn, Auke-Pieter; Collard, Caroline; Collins, Neil; Collins-Tooth, Christopher; Collot, Johann; Colon, German; Conde Muiño, Patricia; Coniavitis, Elias; Consonni, Michele; Constantinescu, Serban; Conta, Claudio; Conventi, Francesco; Cooke, Mark; Cooper, Ben; Cooper-Sarkar, Amanda; Cooper-Smith, Neil; Copic, Katherine; Cornelissen, Thijs; Corradi, Massimo; Corriveau, Francois; Corso-Radu, Alina; Cortes-Gonzalez, Arely; Cortiana, Giorgio; Costa, Giuseppe; Costa, María José; Costanzo, Davide; Costin, Tudor; Côté, David; Coura Torres, Rodrigo; Courneyea, Lorraine; Cowan, Glen; Cowden, Christopher; Cox, Brian; Cranmer, Kyle; Cranshaw, Jack; Cristinziani, Markus; Crosetti, Giovanni; Crupi, Roberto; Crépé-Renaudin, Sabine; Cuenca Almenar, Cristóbal; Cuhadar Donszelmann, Tulay; Curatolo, Maria; Curtis, Chris; Cwetanski, Peter; Czyczula, Zofia; D'Auria, Saverio; D'Onofrio, Monica; D'Orazio, Alessia; Da Via, Cinzia; Dabrowski, Wladyslaw; Dai, Tiesheng; Dallapiccola, Carlo; Dallison, Steve; Daly, Colin; Dam, Mogens; Danielsson, Hans Olof; Dannheim, Dominik; Dao, Valerio; Darbo, Giovanni; Darlea, Georgiana Lavinia; Davey, Will; Davidek, Tomas; Davidson, Nadia; Davidson, Ruth; Davies, Merlin; Davison, Adam; Dawson, Ian; Daya, Rozmin; De, Kaushik; de Asmundis, Riccardo; De Castro, Stefano; De Castro Faria Salgado, Pedro; De Cecco, Sandro; de Graat, Julien; De Groot, Nicolo; de Jong, Paul; De Mora, Lee; De Oliveira Branco, Miguel; De Pedis, Daniele; De Salvo, Alessandro; De Sanctis, Umberto; De Santo, Antonella; De Vivie De Regie, Jean-Baptiste; De Zorzi, Guido; Dean, Simon; Dedovich, Dmitri; Degenhardt, James; Dehchar, Mohamed; Del Papa, Carlo; Del Peso, Jose; Del Prete, Tarcisio; Dell'Acqua, Andrea; Dell'Asta, Lidia; Della Pietra, Massimo; della Volpe, Domenico; Delmastro, Marco; Delsart, Pierre-Antoine; Deluca, Carolina; Demers, Sarah; Demichev, Mikhail; Demirkoz, Bilge; Deng, Jianrong; Deng, Wensheng; Denisov, Sergey; Derkaoui, Jamal Eddine; Derue, Frederic; Dervan, Paul; Desch, Klaus Kurt; Deviveiros, Pier-Olivier; Dewhurst, Alastair; DeWilde, Burton; Dhaliwal, Saminder; Dhullipudi, Ramasudhakar; Di Ciaccio, Anna; Di Ciaccio, Lucia; Di Domenico, Antonio; Di Girolamo, Alessandro; Di Girolamo, Beniamino; Di Luise, Silvestro; Di Mattia, Alessandro; Di Nardo, Roberto; Di Simone, Andrea; Di Sipio, Riccardo; Diaz, Marco Aurelio; Diblen, Faruk; Diehl, Edward; Dietrich, Janet; Dietzsch, Thorsten; Diglio, Sara; Dindar Yagci, Kamile; Dingfelder, Jochen; Dionisi, Carlo; Dita, Petre; Dita, Sanda; Dittus, Fridolin; Djama, Fares; Djilkibaev, Rashid; Djobava, Tamar; do Vale, Maria Aline Barros; Do Valle Wemans, André; Doan, Thi Kieu Oanh; Dobos, Daniel; Dobson, Ellie; Dobson, Marc; Doglioni, Caterina; Doherty, Tom; Dolejsi, Jiri; Dolenc, Irena; Dolezal, Zdenek; Dolgoshein, Boris; Dohmae, Takeshi; Donega, Mauro; Donini, Julien; Dopke, Jens; Doria, Alessandra; Dos Anjos, Andre; Dotti, Andrea; Dova, Maria-Teresa; Doxiadis, Alexander; Doyle, Tony; Drasal, Zbynek; Dris, Manolis; Dubbert, Jörg; Duchovni, Ehud; Duckeck, Guenter; Dudarev, Alexey; Dudziak, Fanny; Dührssen , Michael; Duflot, Laurent; Dufour, Marc-Andre; Dunford, Monica; Duran Yildiz, Hatice; Dushkin, Andrei; Duxfield, Robert; Dwuznik, Michal; Düren, Michael; Ebenstein, William; Ebke, Johannes; Eckweiler, Sebastian; Edmonds, Keith; Edwards, Clive; Egorov, Kirill; Ehrenfeld, Wolfgang; Ehrich, Thies; Eifert, Till; Eigen, Gerald; Einsweiler, Kevin; Eisenhandler, Eric; Ekelof, Tord; El Kacimi, Mohamed; Ellert, Mattias; Elles, Sabine; Ellinghaus, Frank; Ellis, Katherine; Ellis, Nicolas; Elmsheuser, Johannes; Elsing, Markus; Emeliyanov, Dmitry; Engelmann, Roderich; Engl, Albert; Epp, Brigitte; Eppig, Andrew; Erdmann, Johannes; Ereditato, Antonio; Eriksson, Daniel; Ermoline, Iouri; Ernst, Jesse; Ernst, Michael; Ernwein, Jean; Errede, Deborah; Errede, Steven; Ertel, Eugen; Escalier, Marc; Escobar, Carlos; Espinal Curull, Xavier; Esposito, Bellisario; Etienvre, Anne-Isabelle; Etzion, Erez; Evans, Hal; Fabbri, Laura; Fabre, Caroline; Facius, Katrine; Fakhrutdinov, Rinat; Falciano, Speranza; Fang, Yaquan; Fanti, Marcello; Farbin, Amir; Farilla, Addolorata; Farley, Jason; Farooque, Trisha; Farrington, Sinead; Farthouat, Philippe; Fassnacht, Patrick; Fassouliotis, Dimitrios; Fatholahzadeh, Baharak; Fayard, Louis; Fayette, Florent; Febbraro, Renato; Federic, Pavol; Fedin, Oleg; Fedorko, Woiciech; Feligioni, Lorenzo; Felzmann, Ulrich; Feng, Cunfeng; Feng, Eric; Fenyuk, Alexander; Ferencei, Jozef; Ferland, Jonathan; Fernandes, Bruno; Fernando, Waruna; Ferrag, Samir; Ferrando, James; Ferrara, Valentina; Ferrari, Arnaud; Ferrari, Pamela; Ferrari, Roberto; Ferrer, Antonio; Ferrer, Maria Lorenza; Ferrere, Didier; Ferretti, Claudio; Fiascaris, Maria; Fiedler, Frank; Filipčič, Andrej; Filippas, Anastasios; Filthaut, Frank; Fincke-Keeler, Margret; Fiolhais, Miguel; Fiorini, Luca; Firan, Ana; Fischer, Gordon; Fisher, Matthew; Flechl, Martin; Fleck, Ivor; Fleckner, Johanna; Fleischmann, Philipp; Fleischmann, Sebastian; Flick, Tobias; Flores Castillo, Luis; Flowerdew, Michael; Fonseca Martin, Teresa; Formica, Andrea; Forti, Alessandra; Fortin, Dominique; Fournier, Daniel; Fowler, Andrew; Fowler, Ken; Fox, Harald; Francavilla, Paolo; Franchino, Silvia; Francis, David; Franklin, Melissa; Franz, Sebastien; Fraternali, Marco; Fratina, Sasa; Freestone, Julian; French, Sky; Froeschl, Robert; Froidevaux, Daniel; Frost, James; Fukunaga, Chikara; Fullana Torregrosa, Esteban; Fuster, Juan; Gabaldon, Carolina; Gabizon, Ofir; Gadfort, Thomas; Gadomski, Szymon; Gagliardi, Guido; Gagnon, Pauline; Galea, Cristina; Gallas, Elizabeth; Gallas, Manuel; Gallo, Valentina Santina; Gallop, Bruce; Gallus, Petr; Galyaev, Eugene; Gan, K K; Gao, Yongsheng; Gaponenko, Andrei; Garcia-Sciveres, Maurice; García, Carmen; García Navarro, José Enrique; Gardner, Robert; Garelli, Nicoletta; Garitaonandia, Hegoi; Garonne, Vincent; Gatti, Claudio; Gaudio, Gabriella; Gautard, Valerie; Gauzzi, Paolo; Gavrilenko, Igor; Gay, Colin; Gaycken, Goetz; Gazis, Evangelos; Ge, Peng; Gee, Norman; Geich-Gimbel, Christoph; Gellerstedt, Karl; Gemme, Claudia; Genest, Marie-Hélène; Gentile, Simonetta; Georgatos, Fotios; George, Simon; Gershon, Avi; Ghazlane, Hamid; Ghodbane, Nabil; Giacobbe, Benedetto; Giagu, Stefano; Giakoumopoulou, Victoria; Giangiobbe, Vincent; Gianotti, Fabiola; Gibbard, Bruce; Gibson, Adam; Gibson, Stephen; Gilbert, Laura; Gilchriese, Murdock; Gilewsky, Valentin; Gingrich, Douglas; Ginzburg, Jonatan; Giokaris, Nikos; Giordani, MarioPaolo; Giordano, Raffaele; Giorgi, Francesco Michelangelo; Giovannini, Paola; Giraud, Pierre-Francois; Girtler, Peter; Giugni, Danilo; Giusti, Paolo; Gjelsten, Børge Kile; Gladilin, Leonid; Glasman, Claudia; Glazov, Alexandre; Glitza, Karl-Walter; Glonti, George; Godfrey, Jennifer; Godlewski, Jan; Goebel, Martin; Göpfert, Thomas; Goeringer, Christian; Gössling, Claus; Göttfert, Tobias; Goggi, Virginio; Goldfarb, Steven; Goldin, Daniel; Golling, Tobias; Gomes, Agostinho; Gomez Fajardo, Luz Stella; Gonçcalo, Ricardo; Gonella, Laura; Gong, Chenwei; González de la Hoz, Santiago; Gonzalez Silva, Laura; Gonzalez-Sevilla, Sergio; Goodson, Jeremiah Jet; Goossens, Luc; Gordon, Howard; Gorelov, Igor; Gorfine, Grant; Gorini, Benedetto; Gorini, Edoardo; Gorišek, Andrej; Gornicki, Edward; Gosdzik, Bjoern; Gosselink, Martijn; Gostkin, Mikhail Ivanovitch; Gough Eschrich, Ivo; Gouighri, Mohamed; Goujdami, Driss; Goulette, Marc Phillippe; Goussiou, Anna; Goy, Corinne; Grabowska-Bold, Iwona; Grafström, Per; Grahn, Karl-Johan; Grancagnolo, Sergio; Grassi, Valerio; Gratchev, Vadim; Grau, Nathan; Gray, Heather; Gray, Julia Ann; Graziani, Enrico; Green, Barry; Greenshaw, Timothy; Greenwood, Zeno Dixon; Gregor, Ingrid-Maria; Grenier, Philippe; Griesmayer, Erich; Griffiths, Justin; Grigalashvili, Nugzar; Grillo, Alexander; Grimm, Kathryn; Grinstein, Sebastian; Grishkevich, Yaroslav; Groh, Manfred; Groll, Marius; Gross, Eilam; Grosse-Knetter, Joern; Groth-Jensen, Jacob; Grybel, Kai; Guicheney, Christophe; Guida, Angelo; Guillemin, Thibault; Guler, Hulya; Gunther, Jaroslav; Guo, Bin; Gupta, Ambreesh; Gusakov, Yury; Gutierrez, Andrea; Gutierrez, Phillip; Guttman, Nir; Gutzwiller, Olivier; Guyot, Claude; Gwenlan, Claire; Gwilliam, Carl; Haas, Andy; Haas, Stefan; Haber, Carl; Hadavand, Haleh Khani; Hadley, David; Haefner, Petra; Härtel, Roland; Hajduk, Zbigniew; Hakobyan, Hrachya; Haller, Johannes; Hamacher, Klaus; Hamilton, Andrew; Hamilton, Samuel; Han, Liang; Hanagaki, Kazunori; Hance, Michael; Handel, Carsten; Hanke, Paul; Hansen, Jørgen Beck; Hansen, Jorn Dines; Hansen, John Renner; Hansen, Peter Henrik; Hansl-Kozanecka, Traudl; Hansson, Per; Hara, Kazuhiko; Hare, Gabriel; Harenberg, Torsten; Harrington, Robert; Harris, Orin; Harrison, Karl; Hartert, Jochen; Hartjes, Fred; Harvey, Alex; Hasegawa, Satoshi; Hasegawa, Yoji; Hashemi, Kevan; Hassani, Samira; Haug, Sigve; Hauschild, Michael; Hauser, Reiner; Havranek, Miroslav; Hawkes, Christopher; Hawkings, Richard John; Hayakawa, Takashi; Hayward, Helen; Haywood, Stephen; Head, Simon; Hedberg, Vincent; Heelan, Louise; Heim, Sarah; Heinemann, Beate; Heisterkamp, Simon; Helary, Louis; Heller, Mathieu; Hellman, Sten; Helsens, Clement; Hemperek, Tomasz; Henderson, Robert; Henke, Michael; Henrichs, Anna; Henriques Correia, Ana Maria; Henrot-Versille, Sophie; Hensel, Carsten; Henß, Tobias; Hernández Jiménez, Yesenia; Hershenhorn, Alon David; Herten, Gregor; Hertenberger, Ralf; Hervas, Luis; Hessey, Nigel; Higón-Rodriguez, Emilio; Hill, John; Hiller, Karl Heinz; Hillert, Sonja; Hillier, Stephen; Hinchliffe, Ian; Hines, Elizabeth; Hirose, Minoru; Hirsch, Florian; Hirschbuehl, Dominic; Hobbs, John; Hod, Noam; Hodgkinson, Mark; Hodgson, Paul; Hoecker, Andreas; Hoeferkamp, Martin; Hoffman, Julia; Hoffmann, Dirk; Hohlfeld, Marc; Holy, Tomas; Holzbauer, Jenny; Homma, Yasuhiro; Horazdovsky, Tomas; Hori, Takuya; Horn, Claus; Horner, Stephan; Hostachy, Jean-Yves; Hou, Suen; Hoummada, Abdeslam; Howe, Travis; Hrivnac, Julius; Hryn'ova, Tetiana; Hsu, Pai-hsien Jennifer; Hsu, Shih-Chieh; Huang, Guang Shun; Hubacek, Zdenek; Hubaut, Fabrice; Huegging, Fabian; Hughes, Emlyn; Hughes, Gareth; Hurwitz, Martina; Husemann, Ulrich; Huseynov, Nazim; Huston, Joey; Huth, John; Iacobucci, Giuseppe; Iakovidis, Georgios; Ibragimov, Iskander; Iconomidou-Fayard, Lydia; Idarraga, John; Iengo, Paolo; Igonkina, Olga; Ikegami, Yoichi; Ikeno, Masahiro; Ilchenko, Yuri; Iliadis, Dimitrios; Ince, Tayfun; Ioannou, Pavlos; Iodice, Mauro; Irles Quiles, Adrian; Ishikawa, Akimasa; Ishino, Masaya; Ishmukhametov, Renat; Isobe, Tadaaki; Issakov, Vladimir; Issever, Cigdem; Istin, Serhat; Itoh, Yuki; Ivashin, Anton; Iwanski, Wieslaw; Iwasaki, Hiroyuki; Izen, Joseph; Izzo, Vincenzo; Jackson, Brett; Jackson, John; Jackson, Paul; Jaekel, Martin; Jain, Vivek; Jakobs, Karl; Jakobsen, Sune; Jakubek, Jan; Jana, Dilip; Jansen, Eric; Jantsch, Andreas; Janus, Michel; Jared, Richard; Jarlskog, Göran; Jeanty, Laura; Jen-La Plante, Imai; Jenni, Peter; Jež, Pavel; Jézéquel, Stéphane; Ji, Weina; Jia, Jiangyong; Jiang, Yi; Jimenez Belenguer, Marcos; Jin, Shan; Jinnouchi, Osamu; Joffe, David; Johansen, Marianne; Johansson, Erik; Johansson, Per; Johnert, Sebastian; Johns, Kenneth; Jon-And, Kerstin; Jones, Graham; Jones, Roger; Jones, Tim; Jorge, Pedro; Joseph, John; Juranek, Vojtech; Jussel, Patrick; Kabachenko, Vasily; Kaci, Mohammed; Kaczmarska, Anna; Kado, Marumi; Kagan, Harris; Kagan, Michael; Kaiser, Steffen; Kajomovitz, Enrique; Kalinin, Sergey; Kalinovskaya, Lidia; Kalinowski, Artur; Kama, Sami; Kanaya, Naoko; Kaneda, Michiru; Kantserov, Vadim; Kanzaki, Junichi; Kaplan, Benjamin; Kapliy, Anton; Kaplon, Jan; Kar, Deepak; Karagounis, Michael; Karagoz, Muge; Kartvelishvili, Vakhtang; Karyukhin, Andrey; Kashif, Lashkar; Kasmi, Azzedine; Kass, Richard; Kastanas, Alex; Kastoryano, Michael; Kataoka, Mayuko; Kataoka, Yousuke; Katsoufis, Elias; Katzy, Judith; Kaushik, Venkatesh; Kawagoe, Kiyotomo; Kawamoto, Tatsuo; Kawamura, Gen; Kayl, Manuel; Kayumov, Fred; Kazanin, Vassili; Kazarinov, Makhail; Keates, James Robert; Keeler, Richard; Keener, Paul; Kehoe, Robert; Keil, Markus; Kekelidze, George; Kelly, Marc; Kenyon, Mike; Kepka, Oldrich; Kerschen, Nicolas; Kerševan, Borut Paul; Kersten, Susanne; Kessoku, Kohei; Khakzad, Mohsen; Khalil-zada, Farkhad; Khandanyan, Hovhannes; Khanov, Alexander; Kharchenko, Dmitri; Khodinov, Alexander; Khomich, Andrei; Khoriauli, Gia; Khovanskiy, Nikolai; Khovanskiy, Valery; Khramov, Evgeniy; Khubua, Jemal; Kim, Hyeon Jin; Kim, Min Suk; Kim, Peter; Kim, Shinhong; Kind, Oliver; Kind, Peter; King, Barry; Kirk, Julie; Kirsch, Guillaume; Kirsch, Lawrence; Kiryunin, Andrey; Kisielewska, Danuta; Kittelmann, Thomas; Kiyamura, Hironori; Kladiva, Eduard; Klein, Max; Klein, Uta; Kleinknecht, Konrad; Klemetti, Miika; Klier, Amit; Klimentov, Alexei; Klingenberg, Reiner; Klinkby, Esben; Klioutchnikova, Tatiana; Klok, Peter; Klous, Sander; Kluge, Eike-Erik; Kluge, Thomas; Kluit, Peter; Klute, Markus; Kluth, Stefan; Knecht, Neil; Kneringer, Emmerich; Ko, Byeong Rok; Kobayashi, Tomio; Kobel, Michael; Koblitz, Birger; Kocian, Martin; Kocnar, Antonin; Kodys, Peter; Köneke, Karsten; König, Adriaan; Koenig, Sebastian; Köpke, Lutz; Koetsveld, Folkert; Koevesarki, Peter; Koffas, Thomas; Koffeman, Els; Kohn, Fabian; Kohout, Zdenek; Kohriki, Takashi; Kolanoski, Hermann; Kolesnikov, Vladimir; Koletsou, Iro; Koll, James; Kollar, Daniel; Kolos, Serguei; Kolya, Scott; Komar, Aston; Komaragiri, Jyothsna Rani; Kondo, Takahiko; Kono, Takanori; Konoplich, Rostislav; Konovalov, Serguei; Konstantinidis, Nikolaos; Koperny, Stefan; Korcyl, Krzysztof; Kordas, Kostantinos; Korn, Andreas; Korolkov, Ilya; Korolkova, Elena; Korotkov, Vladislav; Kortner, Oliver; Kortner, Sandra; Kostka, Peter; Kostyukhin, Vadim; Kotov, Serguei; Kotov, Vladislav; Kotov, Konstantin; Kourkoumelis, Christine; Koutsman, Alex; Kowalewski, Robert Victor; Kowalski, Henri; Kowalski, Tadeusz; Kozanecki, Witold; Kozhin, Anatoly; Kral, Vlastimil; Kramarenko, Viktor; Kramberger, Gregor; Krasny, Mieczyslaw Witold; Krasznahorkay, Attila; Kreisel, Arik; Krejci, Frantisek; Kretzschmar, Jan; Krieger, Nina; Krieger, Peter; Kroeninger, Kevin; Kroha, Hubert; Kroll, Joe; Kroseberg, Juergen; Krstic, Jelena; Kruchonak, Uladzimir; Krüger, Hans; Krumshteyn, Zinovii; Kubota, Takashi; Kuehn, Susanne; Kugel, Andreas; Kuhl, Thorsten; Kuhn, Dietmar; Kukhtin, Victor; Kulchitsky, Yuri; Kuleshov, Sergey; Kummer, Christian; Kuna, Marine; Kunkle, Joshua; Kupco, Alexander; Kurashige, Hisaya; Kurata, Masakazu; Kurchaninov, Leonid; Kurochkin, Yurii; Kus, Vlastimil; Kwee, Regina; La Rotonda, Laura; Labbe, Julien; Lacasta, Carlos; Lacava, Francesco; Lacker, Heiko; Lacour, Didier; Lacuesta, Vicente Ramón; Ladygin, Evgueni; Lafaye, Rémi; Laforge, Bertrand; Lagouri, Theodota; Lai, Stanley; Lamanna, Massimo; Lampen, Caleb; Lampl, Walter; Lancon, Eric; Landgraf, Ulrich; Landon, Murrough; Lane, Jenna; Lankford, Andrew; Lanni, Francesco; Lantzsch, Kerstin; Lanza, Agostino; Laplace, Sandrine; Lapoire, Cecile; Laporte, Jean-Francois; Lari, Tommaso; Larner, Aimee; Lassnig, Mario; Laurelli, Paolo; Lavrijsen, Wim; Laycock, Paul; Lazarev, Alexandre; Lazzaro, Alfio; Le Dortz, Olivier; Le Guirriec, Emmanuel; Le Menedeu, Eve; Le Vine, Micheal; Lebedev, Alexander; Lebel, Céline; LeCompte, Thomas; Ledroit-Guillon, Fabienne Agnes Marie; Lee, Hurng-Chun; Lee, Jason; Lee, Shih-Chang; Lefebvre, Michel; Legendre, Marie; LeGeyt, Benjamin; Legger, Federica; Leggett, Charles; Lehmacher, Marc; Lehmann Miotto, Giovanna; Lei, Xiaowen; Leitner, Rupert; Lellouch, Daniel; Lellouch, Jeremie; Lendermann, Victor; Leney, Katharine; Lenz, Tatiana; Lenzen, Georg; Lenzi, Bruno; Leonhardt, Kathrin; Leroy, Claude; Lessard, Jean-Raphael; Lester, Christopher; Leung Fook Cheong, Annabelle; Levêque, Jessica; Levin, Daniel; Levinson, Lorne; Leyton, Michael; Li, Haifeng; Li, Shumin; Li, Xuefei; Liang, Zhihua; Liang, Zhijun; Liberti, Barbara; Lichard, Peter; Lichtnecker, Markus; Lie, Ki; Liebig, Wolfgang; Lilley, Joseph; Lim, Heuijin; Limosani, Antonio; Limper, Maaike; Lin, Simon; Linnemann, James; Lipeles, Elliot; Lipinsky, Lukas; Lipniacka, Anna; Liss, Tony; Lissauer, David; Lister, Alison; Litke, Alan; Liu, Chuanlei; Liu, Dong; Liu, Hao; Liu, Jianbei; Liu, Minghui; Liu, Tiankuan; Liu, Yanwen; Livan, Michele; Lleres, Annick; Lloyd, Stephen; Lobodzinska, Ewelina; Loch, Peter; Lockman, William; Lockwitz, Sarah; Loddenkoetter, Thomas; Loebinger, Fred; Loginov, Andrey; Loh, Chang Wei; Lohse, Thomas; Lohwasser, Kristin; Lokajicek, Milos; Long, Robin Eamonn; Lopes, Lourenco; Lopez Mateos, David; Losada, Marta; Loscutoff, Peter; Lou, Xinchou; Lounis, Abdenour; Loureiro, Karina; Lovas, Lubomir; Love, Jeremy; Love, Peter; Lowe, Andrew; Lu, Feng; Lubatti, Henry; Luci, Claudio; Lucotte, Arnaud; Ludwig, Andreas; Ludwig, Dörthe; Ludwig, Inga; Luehring, Frederick; Luisa, Luca; Lumb, Debra; Luminari, Lamberto; Lund, Esben; Lund-Jensen, Bengt; Lundberg, Björn; Lundberg, Johan; Lundquist, Johan; Lynn, David; Lys, Jeremy; Lytken, Else; Ma, Hong; Ma, Lian Liang; Macana Goia, Jorge Andres; Maccarrone, Giovanni; Macchiolo, Anna; Maček, Boštjan; Machado Miguens, Joana; Mackeprang, Rasmus; Madaras, Ronald; Mader, Wolfgang; Maenner, Reinhard; Maeno, Tadashi; Mättig, Peter; Mättig, Stefan; Magalhaes Martins, Paulo Jorge; Magradze, Erekle; Mahalalel, Yair; Mahboubi, Kambiz; Mahmood, A.; Maiani, Camilla; Maidantchik, Carmen; Maio, Amélia; Majewski, Stephanie; Makida, Yasuhiro; Makouski, Mikhail; Makovec, Nikola; Malecki, Piotr; Malecki, Pawel; Maleev, Victor; Malek, Fairouz; Mallik, Usha; Malon, David; Maltezos, Stavros; Malyshev, Vladimir; Malyukov, Sergei; Mambelli, Marco; Mameghani, Raphael; Mamuzic, Judita; Mandelli, Luciano; Mandić, Igor; Mandrysch, Rocco; Maneira, José; Mangeard, Pierre-Simon; Manjavidze, Ioseb; Manning, Peter; Manousakis-Katsikakis, Arkadios; Mansoulie, Bruno; Mapelli, Alessandro; Mapelli, Livio; March , Luis; Marchand, Jean-Francois; Marchese, Fabrizio; Marchiori, Giovanni; Marcisovsky, Michal; Marino, Christopher; Marroquim, Fernando; Marshall, Zach; Marti-Garcia, Salvador; Martin, Alex; Martin, Andrew; Martin, Brian; Martin, Brian; Martin, Franck Francois; Martin, Jean-Pierre; Martin, Tim; Martin dit Latour, Bertrand; Martinez, Mario; Martinez Outschoorn, Verena; Martini, Agnese; Martyniuk, Alex; Marzano, Francesco; Marzin, Antoine; Masetti, Lucia; Mashimo, Tetsuro; Mashinistov, Ruslan; Masik, Jiri; Maslennikov, Alexey; Massa, Ignazio; Massol, Nicolas; Mastroberardino, Anna; Masubuchi, Tatsuya; Matricon, Pierre; Matsunaga, Hiroyuki; Matsushita, Takashi; Mattravers, Carly; Maxfield, Stephen; Mayne, Anna; Mazini, Rachid; Mazur, Michael; Mazzanti, Marcello; Mc Donald, Jeffrey; Mc Kee, Shawn Patrick; McCarn, Allison; McCarthy, Robert; McCubbin, Norman; McFarlane, Kenneth; McGlone, Helen; Mchedlidze, Gvantsa; McMahon, Steve; McPherson, Robert; Meade, Andrew; Mechnich, Joerg; Mechtel, Markus; Medinnis, Mike; Meera-Lebbai, Razzak; Meguro, Tatsuma; Mehlhase, Sascha; Mehta, Andrew; Meier, Karlheinz; Meirose, Bernhard; Melachrinos, Constantinos; Mellado Garcia, Bruce Rafael; Mendoza Navas, Luis; Meng, Zhaoxia; Menke, Sven; Meoni, Evelin; Mermod, Philippe; Merola, Leonardo; Meroni, Chiara; Merritt, Frank; Messina, Andrea; Metcalfe, Jessica; Mete, Alaettin Serhan; Meyer, Jean-Pierre; Meyer, Jochen; Meyer, Joerg; Meyer, Thomas Christian; Meyer, W. Thomas; Miao, Jiayuan; Michal, Sebastien; Micu, Liliana; Middleton, Robin; Migas, Sylwia; Mijović, Liza; Mikenberg, Giora; Mikestikova, Marcela; Mikuž, Marko; Miller, David; Mills, Corrinne; Mills, Bill; Milov, Alexander; Milstead, David; Milstein, Dmitry; Minaenko, Andrey; Miñano, Mercedes; Minashvili, Irakli; Mincer, Allen; Mindur, Bartosz; Mineev, Mikhail; Ming, Yao; Mir, Lluisa-Maria; Mirabelli, Giovanni; Misawa, Shigeki; Miscetti, Stefano; Misiejuk, Andrzej; Mitrevski, Jovan; Mitsou, Vasiliki A.; Miyagawa, Paul; Mjörnmark, Jan-Ulf; Mladenov, Dimitar; Moa, Torbjoern; Moed, Shulamit; Moeller, Victoria; Mönig, Klaus; Möser, Nicolas; Mohr, Wolfgang; Mohrdieck-Möck, Susanne; Moles-Valls, Regina; Molina-Perez, Jorge; Monk, James; Monnier, Emmanuel; Montesano, Simone; Monticelli, Fernando; Moore, Roger; Mora Herrera, Clemencia; Moraes, Arthur; Morais, Antonio; Morel, Julien; Morello, Gianfranco; Moreno, Deywis; Moreno Llácer, María; Morettini, Paolo; Morii, Masahiro; Morley, Anthony Keith; Mornacchi, Giuseppe; Morozov, Sergey; Morris, John; Moser, Hans-Guenther; Mosidze, Maia; Moss, Josh; Mount, Richard; Mountricha, Eleni; Mouraviev, Sergei; Moyse, Edward; Mudrinic, Mihajlo; Mueller, Felix; Mueller, James; Mueller, Klemens; Müller, Thomas; Muenstermann, Daniel; Muir, Alex; Munwes, Yonathan; Murillo Garcia, Raul; Murray, Bill; Mussche, Ido; Musto, Elisa; Myagkov, Alexey; Myska, Miroslav; Nadal, Jordi; Nagai, Koichi; Nagano, Kunihiro; Nagasaka, Yasushi; Nairz, Armin Michael; Nakamura, Koji; Nakano, Itsuo; Nakatsuka, Hiroki; Nanava, Gizo; Napier, Austin; Nash, Michael; Nation, Nigel; Nattermann, Till; Naumann, Thomas; Navarro, Gabriela; Nderitu, Simon Kirichu; Neal, Homer; Nebot, Eduardo; Nechaeva, Polina; Negri, Andrea; Negri, Guido; Nelson, Andrew; Nelson, Timothy Knight; Nemecek, Stanislav; Nemethy, Peter; Nepomuceno, Andre Asevedo; Nessi, Marzio; Neubauer, Mark; Neusiedl, Andrea; Neves, Ricardo; Nevski, Pavel; Newcomer, Mitchel; Nickerson, Richard; Nicolaidou, Rosy; Nicolas, Ludovic; Nicoletti, Giovanni; Nicquevert, Bertrand; Niedercorn, Francois; Nielsen, Jason; Nikiforov, Andriy; Nikolaev, Kirill; Nikolic-Audit, Irena; Nikolopoulos, Konstantinos; Nilsen, Henrik; Nilsson, Paul; Nisati, Aleandro; Nishiyama, Tomonori; Nisius, Richard; Nodulman, Lawrence; Nomachi, Masaharu; Nomidis, Ioannis; Nordberg, Markus; Nordkvist, Bjoern; Notz, Dieter; Novakova, Jana; Nozaki, Mitsuaki; Nožička, Miroslav; Nugent, Ian Michael; Nuncio-Quiroz, Adriana-Elizabeth; Nunes Hanninger, Guilherme; Nunnemann, Thomas; Nurse, Emily; O'Neil, Dugan; O'Shea, Val; Oakham, Gerald; Oberlack, Horst; Ochi, Atsuhiko; Oda, Susumu; Odaka, Shigeru; Odier, Jerome; Ogren, Harold; Oh, Alexander; Oh, Seog; Ohm, Christian; Ohshima, Takayoshi; Ohshita, Hidetoshi; Ohsugi, Takashi; Okada, Shogo; Okawa, Hideki; Okumura, Yasuyuki; Okuyama, Toyonobu; Olchevski, Alexander; Oliveira, Miguel Alfonso; Oliveira Damazio, Denis; Oliver, John; Oliver Garcia, Elena; Olivito, Dominick; Olszewski, Andrzej; Olszowska, Jolanta; Omachi, Chihiro; Onofre, António; Onyisi, Peter; Oram, Christopher; Oreglia, Mark; Oren, Yona; Orestano, Domizia; Orlov, Iliya; Oropeza Barrera, Cristina; Orr, Robert; Ortega, Eduardo; Osculati, Bianca; Ospanov, Rustem; Osuna, Carlos; Ottersbach, John; Ould-Saada, Farid; Ouraou, Ahmimed; Ouyang, Qun; Owen, Mark; Owen, Simon; Oyarzun, Alejandro; Ozcan, Veysi Erkcan; Ozone, Kenji; Ozturk, Nurcan; Pacheco Pages, Andres; Padilla Aranda, Cristobal; Paganis, Efstathios; Pahl, Christoph; Paige, Frank; Pajchel, Katarina; Palestini, Sandro; Pallin, Dominique; Palma, Alberto; Palmer, Jody; Pan, Yibin; Panagiotopoulou, Evgenia; Panes, Boris; Panikashvili, Natalia; Panitkin, Sergey; Pantea, Dan; Panuskova, Monika; Paolone, Vittorio; Papadopoulou, Theodora; Park, Su-Jung; Park, Woochun; Parker, Andy; Parker, Sherwood; Parodi, Fabrizio; Parsons, John; Parzefall, Ulrich; Pasqualucci, Enrico; Passeri, Antonio; Pastore, Fernanda; Pastore, Francesca; Pásztor , Gabriella; Pataraia, Sophio; Pater, Joleen; Patricelli, Sergio; Patwa, Abid; Pauly, Thilo; Peak, Lawrence; Pecsy, Martin; Pedraza Morales, Maria Isabel; Peleganchuk, Sergey; Peng, Haiping; Penson, Alexander; Penwell, John; Perantoni, Marcelo; Perez, Kerstin; Perez Codina, Estel; Pérez García-Estañ, María Teresa; Perez Reale, Valeria; Perini, Laura; Pernegger, Heinz; Perrino, Roberto; Persembe, Seda; Perus, Antoine; Peshekhonov, Vladimir; Petersen, Brian; Petersen, Troels; Petit, Elisabeth; Petridou, Chariclia; Petrolo, Emilio; Petrucci, Fabrizio; Petschull, Dennis; Petteni, Michele; Pezoa, Raquel; Phan, Anna; Phillips, Alan; Piacquadio, Giacinto; Piccinini, Maurizio; Piegaia, Ricardo; Pilcher, James; Pilkington, Andrew; Pina, João Antonio; Pinamonti, Michele; Pinfold, James; Pinto, Belmiro; Pizio, Caterina; Placakyte, Ringaile; Plamondon, Mathieu; Pleier, Marc-Andre; Poblaguev, Andrei; Poddar, Sahill; Podlyski, Fabrice; Poffenberger, Paul; Poggioli, Luc; Pohl, Martin; Polci, Francesco; Polesello, Giacomo; Policicchio, Antonio; Polini, Alessandro; Poll, James; Polychronakos, Venetios; Pomeroy, Daniel; Pommès, Kathy; Ponsot, Patrick; Pontecorvo, Ludovico; Pope, Bernard; Popeneciu, Gabriel Alexandru; Popovic, Dragan; Poppleton, Alan; Popule, Jiri; Portell Bueso, Xavier; Porter, Robert; Pospelov, Guennady; Pospisil, Stanislav; Potekhin, Maxim; Potrap, Igor; Potter, Christina; Potter, Christopher; Potter, Keith; Poulard, Gilbert; Poveda, Joaquin; Prabhu, Robindra; Pralavorio, Pascal; Prasad, Srivas; Pravahan, Rishiraj; Pribyl, Lukas; Price, Darren; Price, Lawrence; Prichard, Paul; Prieur, Damien; Primavera, Margherita; Prokofiev, Kirill; Prokoshin, Fedor; Protopopescu, Serban; Proudfoot, James; Prudent, Xavier; Przysiezniak, Helenka; Psoroulas, Serena; Ptacek, Elizabeth; Puigdengoles, Carles; Purdham, John; Purohit, Milind; Puzo, Patrick; Pylypchenko, Yuriy; Qi, Ming; Qian, Jianming; Qian, Weiming; Qin, Zhonghua; Quadt, Arnulf; Quarrie, David; Quayle, William; Quinonez, Fernando; Raas, Marcel; Radeka, Veljko; Radescu, Voica; Radics, Balint; Rador, Tonguc; Ragusa, Francesco; Rahal, Ghita; Rahimi, Amir; Rajagopalan, Srinivasan; Rammensee, Michael; Rammes, Marcus; Rauscher, Felix; Rauter, Emanuel; Raymond, Michel; Read, Alexander Lincoln; Rebuzzi, Daniela; Redelbach, Andreas; Redlinger, George; Reece, Ryan; Reeves, Kendall; Reinherz-Aronis, Erez; Reinsch, Andreas; Reisinger, Ingo; Reljic, Dusan; Rembser, Christoph; Ren, Zhongliang; Renkel, Peter; Rescia, Sergio; Rescigno, Marco; Resconi, Silvia; Resende, Bernardo; Reznicek, Pavel; Rezvani, Reyhaneh; Richards, Alexander; Richards, Ronald; Richter, Robert; Richter-Was, Elzbieta; Ridel, Melissa; Rijpstra, Manouk; Rijssenbeek, Michael; Rimoldi, Adele; Rinaldi, Lorenzo; Rios, Ryan Randy; Riu, Imma; Rizatdinova, Flera; Rizvi, Eram; Roa Romero, Diego Alejandro; Robertson, Steven; Robichaud-Veronneau, Andree; Robinson, Dave; Robinson, James; Robinson, Mary; Robson, Aidan; Rocha de Lima, Jose Guilherme; Roda, Chiara; Roda Dos Santos, Denis; Rodriguez, Diego; Rodriguez Garcia, Yohany; Roe, Shaun; Røhne, Ole; Rojo, Victoria; Rolli, Simona; Romaniouk, Anatoli; Romanov, Victor; Romeo, Gaston; Romero Maltrana, Diego; Roos, Lydia; Ros, Eduardo; Rosati, Stefano; Rosenbaum, Gabriel; Rosselet, Laurent; Rossetti, Valerio; Rossi, Leonardo Paolo; Rotaru, Marina; Rothberg, Joseph; Rousseau, David; Royon, Christophe; Rozanov, Alexander; Rozen, Yoram; Ruan, Xifeng; Ruckert, Benjamin; Ruckstuhl, Nicole; Rud, Viacheslav; Rudolph, Gerald; Rühr, Frederik; Ruggieri, Federico; Ruiz-Martinez, Aranzazu; Rumyantsev, Leonid; Rurikova, Zuzana; Rusakovich, Nikolai; Rutherfoord, John; Ruwiedel, Christoph; Ruzicka, Pavel; Ryabov, Yury; Ryan, Patrick; Rybkin, Grigori; Rzaeva, Sevda; Saavedra, Aldo; Sadrozinski, Hartmut; Sadykov, Renat; Sakamoto, Hiroshi; Salamanna, Giuseppe; Salamon, Andrea; Saleem, Muhammad; Salihagic, Denis; Salnikov, Andrei; Salt, José; Salvachua Ferrando, Belén; Salvatore, Daniela; Salvatore, Pasquale Fabrizio; Salvucci, Antonio; Salzburger, Andreas; Sampsonidis, Dimitrios; Samset, Björn Hallvard; Sandaker, Heidi; Sander, Heinz Georg; Sanders, Michiel; Sandhoff, Marisa; Sandhu, Pawan; Sandstroem, Rikard; Sandvoss, Stephan; Sankey, Dave; Sanny, Bernd; Sansoni, Andrea; Santamarina Rios, Cibran; Santoni, Claudio; Santonico, Rinaldo; Saraiva, João; Sarangi, Tapas; Sarkisyan-Grinbaum, Edward; Sarri, Francesca; Sasaki, Osamu; Sasao, Noboru; Satsounkevitch, Igor; Sauvage, Gilles; Savard, Pierre; Savine, Alexandre; Savinov, Vladimir; Sawyer, Lee; Saxon, David; Says, Louis-Pierre; Sbarra, Carla; Sbrizzi, Antonio; Scannicchio, Diana; Schaarschmidt, Jana; Schacht, Peter; Schäfer, Uli; Schaetzel, Sebastian; Schaffer, Arthur; Schaile, Dorothee; Schamberger, R.~Dean; Schamov, Andrey; Schegelsky, Valery; Scheirich, Daniel; Schernau, Michael; Scherzer, Max; Schiavi, Carlo; Schieck, Jochen; Schioppa, Marco; Schlenker, Stefan; Schmidt, Evelyn; Schmieden, Kristof; Schmitt, Christian; Schmitz, Martin; Schott, Matthias; Schouten, Doug; Schovancova, Jaroslava; Schram, Malachi; Schreiner, Alexander; Schroeder, Christian; Schroer, Nicolai; Schroers, Marcel; Schultes, Joachim; Schultz-Coulon, Hans-Christian; Schumacher, Jan; Schumacher, Markus; Schumm, Bruce; Schune, Philippe; Schwanenberger, Christian; Schwartzman, Ariel; Schwemling, Philippe; Schwienhorst, Reinhard; Schwierz, Rainer; Schwindling, Jerome; Scott, Bill; Searcy, Jacob; Sedykh, Evgeny; Segura, Ester; Seidel, Sally; Seiden, Abraham; Seifert, Frank; Seixas, José; Sekhniaidze, Givi; Seliverstov, Dmitry; Sellden, Bjoern; Semprini-Cesari, Nicola; Serfon, Cedric; Serin, Laurent; Seuster, Rolf; Severini, Horst; Sevior, Martin; Sfyrla, Anna; Shabalina, Elizaveta; Shamim, Mansoora; Shan, Lianyou; Shank, James; Shao, Qi Tao; Shapiro, Marjorie; Shatalov, Pavel; Shaw, Kate; Sherman, Daniel; Sherwood, Peter; Shibata, Akira; Shimojima, Makoto; Shin, Taeksu; Shmeleva, Alevtina; Shochet, Mel; Shupe, Michael; Sicho, Petr; Sidoti, Antonio; Siegert, Frank; Siegrist, James; Sijacki, Djordje; Silbert, Ohad; Silver, Yiftah; Silverstein, Daniel; Silverstein, Samuel; Simak, Vladislav; Simic, Ljiljana; Simion, Stefan; Simmons, Brinick; Simonyan, Margar; Sinervo, Pekka; Sinev, Nikolai; Sipica, Valentin; Siragusa, Giovanni; Sisakyan, Alexei; Sivoklokov, Serguei; Sjölin, Jörgen; Sjursen, Therese; Skovpen, Kirill; Skubic, Patrick; Slater, Mark; Slavicek, Tomas; Sliwa, Krzysztof; Sloper, John erik; Sluka, Tomas; Smakhtin, Vladimir; Smirnov, Sergei; Smirnov, Yuri; Smirnova, Lidia; Smirnova, Oxana; Smith, Ben Campbell; Smith, Douglas; Smith, Kenway; Smizanska, Maria; Smolek, Karel; Snesarev, Andrei; Snow, Steve; Snow, Joel; Snuverink, Jochem; Snyder, Scott; Soares, Mara; Sobie, Randall; Sodomka, Jaromir; Soffer, Abner; Solans, Carlos; Solar, Michael; Solc, Jaroslav; Solfaroli Camillocci, Elena; Solodkov, Alexander; Solovyanov, Oleg; Soluk, Richard; Sondericker, John; Sopko, Vit; Sopko, Bruno; Sosebee, Mark; Soukharev, Andrey; Spagnolo, Stefania; Spanò, Francesco; Spencer, Edwin; Spighi, Roberto; Spigo, Giancarlo; Spila, Federico; Spiwoks, Ralf; Spousta, Martin; Spreitzer, Teresa; Spurlock, Barry; St. Denis, Richard Dante; Stahl, Thorsten; Stahlman, Jonathan; Stamen, Rainer; Stancu, Stefan Nicolae; Stanecka, Ewa; Stanek, Robert; Stanescu, Cristian; Stapnes, Steinar; Starchenko, Evgeny; Stark, Jan; Staroba, Pavel; Starovoitov, Pavel; Stastny, Jan; Stavina, Pavel; Stavropoulos, Georgios; Steele, Genevieve; Steinbach, Peter; Steinberg, Peter; Stekl, Ivan; Stelzer, Bernd; Stelzer, Harald Joerg; Stelzer-Chilton, Oliver; Stenzel, Hasko; Stevenson, Kyle; Stewart, Graeme; Stockton, Mark; Stoerig, Kathrin; Stoicea, Gabriel; Stonjek, Stefan; Strachota, Pavel; Stradling, Alden; Straessner, Arno; Strandberg, Jonas; Strandberg, Sara; Strandlie, Are; Strauss, Michael; Strizenec, Pavol; Ströhmer, Raimund; Strom, David; Stroynowski, Ryszard; Strube, Jan; Stugu, Bjarne; Su, Dong; Soh, Dart-yin; Sugaya, Yorihito; Sugimoto, Takuya; Suhr, Chad; Suk, Michal; Sulin, Vladimir; Sultansoy, Saleh; Sumida, Toshi; Sun, Xiaohu; Sundermann, Jan Erik; Suruliz, Kerim; Sushkov, Serge; Susinno, Giancarlo; Sutton, Mark; Suzuki, Takuya; Suzuki, Yu; Sykora, Ivan; Sykora, Tomas; Szymocha, Tadeusz; Sánchez, Javier; Ta, Duc; Tackmann, Kerstin; Taffard, Anyes; Tafirout, Reda; Taga, Adrian; Takahashi, Yuta; Takai, Helio; Takashima, Ryuichi; Takeda, Hiroshi; Takeshita, Tohru; Talby, Mossadek; Talyshev, Alexey; Tamsett, Matthew; Tanaka, Junichi; Tanaka, Reisaburo; Tanaka, Satoshi; Tanaka, Shuji; Tapprogge, Stefan; Tardif, Dominique; Tarem, Shlomit; Tarrade, Fabien; Tartarelli, Giuseppe Francesco; Tas, Petr; Tasevsky, Marek; Tassi, Enrico; Tatarkhanov, Mous; Taylor, Christopher; Taylor, Frank; Taylor, Geoffrey; Taylor, Ryan P.; Taylor, Wendy; Teixeira-Dias, Pedro; Ten Kate, Herman; Teng, Ping-Kun; Tennenbaum-Katan, Yaniv-David; Terada, Susumu; Terashi, Koji; Terron, Juan; Terwort, Mark; Testa, Marianna; Teuscher, Richard; Thioye, Moustapha; Thoma, Sascha; Thomas, Juergen; Thompson, Stan; Thompson, Emily; Thompson, Peter; Thompson, Paul; Thompson, Ray; Thomson, Evelyn; Thun, Rudolf; Tic, Tomas; Tikhomirov, Vladimir; Tikhonov, Yury; Tipton, Paul; Tique Aires Viegas, Florbela De Jes; Tisserant, Sylvain; Toczek, Barbara; Todorov, Theodore; Todorova-Nova, Sharka; Toggerson, Brokk; Tojo, Junji; Tokár, Stanislav; Tokushuku, Katsuo; Tollefson, Kirsten; Tomasek, Lukas; Tomasek, Michal; Tomoto, Makoto; Tompkins, Lauren; Toms, Konstantin; Tonoyan, Arshak; Topfel, Cyril; Topilin, Nikolai; Torrence, Eric; Torró Pastor, Emma; Toth, Jozsef; Touchard, Francois; Tovey, Daniel; Trefzger, Thomas; Tremblet, Louis; Tricoli, Alesandro; Trigger, Isabel Marian; Trincaz-Duvoid, Sophie; Trinh, Thi Nguyet; Tripiana, Martin; Triplett, Nathan; Trischuk, William; Trivedi, Arjun; Trocmé, Benjamin; Troncon, Clara; Trzupek, Adam; Tsarouchas, Charilaos; Tseng, Jeffrey; Tsiakiris, Menelaos; Tsiareshka, Pavel; Tsionou, Dimitra; Tsipolitis, Georgios; Tsiskaridze, Vakhtang; Tskhadadze, Edisher; Tsukerman, Ilya; Tsulaia, Vakhtang; Tsung, Jieh-Wen; Tsuno, Soshi; Tsybychev, Dmitri; Tuggle, Joseph; Turecek, Daniel; Turk Cakir, Ilkay; Turlay, Emmanuel; Tuts, Michael; Twomey, Matthew Shaun; Tylmad, Maja; Tyndel, Mike; Uchida, Kirika; Ueda, Ikuo; Ugland, Maren; Uhlenbrock, Mathias; Uhrmacher, Michael; Ukegawa, Fumihiko; Unal, Guillaume; Undrus, Alexander; Unel, Gokhan; Unno, Yoshinobu; Urbaniec, Dustin; Urkovsky, Evgeny; Urquijo, Phillip; Urrejola, Pedro; Usai, Giulio; Uslenghi, Massimiliano; Vacavant, Laurent; Vacek, Vaclav; Vachon, Brigitte; Vahsen, Sven; Valente, Paolo; Valentinetti, Sara; Valkar, Stefan; Valladolid Gallego, Eva; Vallecorsa, Sofia; Valls Ferrer, Juan Antonio; Van Berg, Richard; van der Graaf, Harry; van der Kraaij, Erik; van der Poel, Egge; van der Ster, Daniel; van Eldik, Niels; van Gemmeren, Peter; van Kesteren, Zdenko; van Vulpen, Ivo; Vandelli, Wainer; Vaniachine, Alexandre; Vankov, Peter; Vannucci, Francois; Vari, Riccardo; Varnes, Erich; Varouchas, Dimitris; Vartapetian, Armen; Varvell, Kevin; Vasilyeva, Lidia; Vassilakopoulos, Vassilios; Vazeille, Francois; Vellidis, Constantine; Veloso, Filipe; Veneziano, Stefano; Ventura, Andrea; Ventura, Daniel; Venturi, Manuela; Venturi, Nicola; Vercesi, Valerio; Verducci, Monica; Verkerke, Wouter; Vermeulen, Jos; Vetterli, Michel; Vichou, Irene; Vickey, Trevor; Viehhauser, Georg; Villa, Mauro; Villani, Giulio; Villaplana Perez, Miguel; Vilucchi, Elisabetta; Vincter, Manuella; Vinek, Elisabeth; Vinogradov, Vladimir; Viret, Sébastien; Virzi, Joseph; Vitale , Antonio; Vitells, Ofer; Vivarelli, Iacopo; Vives Vaque, Francesc; Vlachos, Sotirios; Vlasak, Michal; Vlasov, Nikolai; Vogel, Adrian; Vokac, Petr; Volpi, Matteo; von der Schmitt, Hans; von Loeben, Joerg; von Radziewski, Holger; von Toerne, Eckhard; Vorobel, Vit; Vorwerk, Volker; Vos, Marcel; Voss, Rudiger; Voss, Thorsten Tobias; Vossebeld, Joost; Vranjes, Nenad; Vranjes Milosavljevic, Marija; Vrba, Vaclav; Vreeswijk, Marcel; Vu Anh, Tuan; Vudragovic, Dusan; Vuillermet, Raphael; Vukotic, Ilija; Wagner, Peter; Walbersloh, Jorg; Walder, James; Walker, Rodney; Walkowiak, Wolfgang; Wall, Richard; Wang, Chiho; Wang, Haichen; Wang, Jin; Wang, Song-Ming; Warburton, Andreas; Ward, Patricia; Warsinsky, Markus; Wastie, Roy; Watkins, Peter; Watson, Alan; Watson, Miriam; Watts, Gordon; Watts, Stephen; Waugh, Anthony; Waugh, Ben; Weber, Marc; Weber, Manuel; Weber, Michele; Weber, Pavel; Weidberg, Anthony; Weingarten, Jens; Weiser, Christian; Wellenstein, Hermann; Wells, Phillippa; Wen, Mei; Wenaus, Torre; Wendler, Shanti; Wengler, Thorsten; Wenig, Siegfried; Wermes, Norbert; Werner, Matthias; Werner, Per; Werth, Michael; Werthenbach, Ulrich; Wessels, Martin; Whalen, Kathleen; White, Andrew; White, Martin; White, Sebastian; Whitehead, Samuel Robert; Whiteson, Daniel; Whittington, Denver; Wicek, Francois; Wicke, Daniel; Wickens, Fred; Wiedenmann, Werner; Wielers, Monika; Wienemann, Peter; Wiglesworth, Craig; Wiik, Liv Antje Mari; Wildauer, Andreas; Wildt, Martin Andre; Wilkens, Henric George; Williams, Eric; Williams, Hugh; Willocq, Stephane; Wilson, John; Wilson, Michael Galante; Wilson, Alan; Wingerter-Seez, Isabelle; Winklmeier, Frank; Wittgen, Matthias; Wolter, Marcin Wladyslaw; Wolters, Helmut; Wosiek, Barbara; Wotschack, Jorg; Woudstra, Martin; Wraight, Kenneth; Wright, Catherine; Wright, Dennis; Wrona, Bozydar; Wu, Sau Lan; Wu, Xin; Wulf, Evan; Wynne, Benjamin; Xaplanteris, Leonidas; Xella, Stefania; Xie, Song; Xu, Da; Xu, Neng; Yamada, Miho; Yamamoto, Akira; Yamamoto, Kyoko; Yamamoto, Shimpei; Yamamura, Taiki; Yamaoka, Jared; Yamazaki, Takayuki; Yamazaki, Yuji; Yan, Zhen; Yang, Haijun; Yang, Un-Ki; Yang, Zhaoyu; Yao, Weiming; Yao, Yushu; Yasu, Yoshiji; Ye, Jingbo; Ye, Shuwei; Yilmaz, Metin; Yoosoofmiya, Reza; Yorita, Kohei; Yoshida, Riktura; Young, Charles; Youssef, Saul; Yu, Dantong; Yu, Jaehoon; Yuan, Li; Yurkewicz, Adam; Zaidan, Remi; Zaitsev, Alexander; Zajacova, Zuzana; Zambrano, Valentina; Zanello, Lucia; Zaytsev, Alexander; Zeitnitz, Christian; Zeller, Michael; Zemla, Andrzej; Zendler, Carolin; Zenin, Oleg; Ženiš, Tibor; Zenonos, Zenonas; Zenz, Seth; Zerwas, Dirk; Zevi della Porta, Giovanni; Zhan, Zhichao; Zhang, Huaqiao; Zhang, Jinlong; Zhang, Qizhi; Zhang, Xueyao; Zhao, Long; Zhao, Tianchi; Zhao, Zhengguo; Zhemchugov, Alexey; Zhong, Jiahang; Zhou, Bing; Zhou, Ning; Zhou, Yue; Zhu, Cheng Guang; Zhu, Hongbo; Zhu, Yingchun; Zhuang, Xuai; Zhuravlov, Vadym; Zimmermann, Robert; Zimmermann, Simone; Zimmermann, Stephanie; Ziolkowski, Michael; Živković, Lidija; Zobernig, Georg; Zoccoli, Antonio; zur Nedden, Martin; Zutshi, Vishnu

    2010-01-01

    The simulation software for the ATLAS Experiment at the Large Hadron Collider is being used for large-scale production of events on the LHC Computing Grid. This simulation requires many components, from the generators that simulate particle collisions, through packages simulating the response of the various detectors and triggers. All of these components come together under the ATLAS simulation infrastructure. In this paper, that infrastructure is discussed, including that supporting the detector description, interfacing the event generation, and combining the GEANT4 simulation of the response of the individual detectors. Also described are the tools allowing the software validation, performance testing, and the validation of the simulated output against known physics processes.

  12. ATLAS Jet Energy Scale

    CERN Document Server

    Schouten, D; Vetterli, M

    2012-01-01

    Jets originating from the fragmentation of quarks and gluons are the most common, and complicated, final state objects produced at hadron colliders. A precise knowledge of their energy calibration is therefore of great importance at experiments at the Large Hadron Collider at CERN, while is very difficult to ascertain. We present in-situ techniques and results for the jet energy scale at ATLAS using recent collision data. ATLAS has demonstrated an understanding of the necessary jet energy corrections to within \\approx 4% in the central region of the calorimeter.

  13. ATLAS/CMS Upgrades

    CERN Document Server

    AUTHOR|(INSPIRE)INSPIRE-00370685; The ATLAS collaboration

    2016-01-01

    Precision studies of the Standard Model (SM) and the searches of the physics beyond the SM are ongoing at the ATLAS and CMS experiments at the Large Hadron Collider (LHC). A luminosity upgrade of LHC is planned, which provides a significant challenge for the experiments. In this report, the plans of the ATLAS and CMS upgrades are introduced. Physics prospects for selected topics, including Higgs coupling measurements, Bs,d -> mumu decays, and top quark decays through flavor changing neutral current, are also shown.

  14. Tactical Grade MEMS IMUs for Spin-Stabilized Rockets Project

    Data.gov (United States)

    National Aeronautics and Space Administration — We propose a tactical grade MEMS IMU for spin-stabilized rockets for metric tracking and autonomous systems. The enabling instrument is a gyroscope designed for...

  15. Gaseous Helium Reclamation at Rocket Test Systems Project

    Data.gov (United States)

    National Aeronautics and Space Administration — The ability to restore large amounts of vented gaseous helium (GHe) at rocket test sites preserves the GHe and reduces operating cost. The used GHe is vented into...

  16. Distributed Rocket Engine Testing Health Monitoring System Project

    Data.gov (United States)

    National Aeronautics and Space Administration — The on-ground and Distributed Rocket Engine Testing Health Monitoring System (DiRETHMS) provides a system architecture and software tools for performing diagnostics...

  17. Distributed Rocket Engine Testing Health Monitoring System Project

    Data.gov (United States)

    National Aeronautics and Space Administration — Leveraging the Phase I achievements of the Distributed Rocket Engine Testing Health Monitoring System (DiRETHMS) including its software toolsets and system building...

  18. Energy-Based Acoustic Measurement System for Rocket Noise Project

    Data.gov (United States)

    National Aeronautics and Space Administration — Accurate estimates of the vibroacoustic loading placed on space vehicles and payloads during launch require knowledge of the rocket noise source properties. Given...

  19. Dynamical Model of Rocket Propellant Loading with Liquid Hydrogen

    Data.gov (United States)

    National Aeronautics and Space Administration — A dynamical model describing the multi-stage process of rocket propellant loading has been developed. It accounts for both the nominal and faulty regimes of...

  20. Rocket Fuel Synthesis by Fisher-Tropsch Process Project

    Data.gov (United States)

    National Aeronautics and Space Administration — While In-Situ Resource Utilization (ISRU) studies for Mars return have emphasized methane fuel, only modest work has been done to develop the methane-powered rocket...

  1. Mars McLOX Rocket Propulsion System Project

    Data.gov (United States)

    National Aeronautics and Space Administration — The Methane and Carbon Monoxide/LOX rocket (MCLOX) is a technology for accomplishing ascent from Mars. Current Mars in-situ propellant production (ISPP)...

  2. The development of space solid rocket motors in China

    Science.gov (United States)

    Jianding, Huang; Dingyou, Ye

    1997-01-01

    China has undertaken to research and develop composite solid propellant rocket motors since 1958. At the request of the development of space technology, composite solid propellant rocket motor has developed from small to large, step by step. For the past thirty eight years, much progress has made, many technical obstacles, such as motor design, case materials and their processing technology, propellant formulations and manufacture, nozzles and thrust vector control, safe ignition, environment tests, nondestructive inspection and quality assurance, static firing test and measurement etc. have been solved. A serial of solid rocket motors have been offered for China's satellites launch. The systems of research, design, test and manufacture of solid rocket motors have been formed.

  3. Gaseous Helium Reclamation at Rocket Test Systems Project

    Data.gov (United States)

    National Aeronautics and Space Administration — GHe reclamation is critical in reducing operating costs at rocket engine test facilities. Increases in cost and shortages of helium will dramatically impact testing...

  4. Safety Analysis of Liquid Rocket Engine Using Bayesian Networks

    Institute of Scientific and Technical Information of China (English)

    WANG Hua-wei; YAN Zhi-qiang

    2007-01-01

    Safety analysis for liquid rocket engine has a great meaning for shortening development cycle, saving development expenditure and reducing development risk. The relationship between the structure and component of liquid rocket engine is much more complex, furthermore test data are absent in development phase. Thereby, the uncertainties exist in safety analysis for liquid rocket engine. A safety analysis model integrated with FMEA(failure mode and effect analysis)based on Bayesian networks (BN) is brought forward for liquid rocket engine, which can combine qualitative analysis with quantitative decision. The method has the advantages of fusing multi-information, saving sample amount and having high veracity. An example shows that the method is efficient.

  5. Simulation and experimental research on line throwing rocket with flight

    Directory of Open Access Journals (Sweden)

    Wen-bin Gu

    2014-06-01

    Full Text Available The finite segment method is used to model the line throwing rocket system. A dynamic model of line throwing rocket with flight motion based on Kane's method is presented by the kinematics description of the system and the consideration of the forces acting on the system. The experiment designed according to the parameters of the dynamic model is made. The simulation and experiment results, such as range, velocity and flight time, are compared and analyzed. The simulation results are basically agreed with the test data, which shows that the flight motion of the line throwing rocket can be predicted by the dynamic model. A theoretical model and guide for the further research on the disturbance of rope and the guidance, flight control of line throwing rocket are provided by the dynamic modeling.

  6. Propellant Flow Actuated Piezoelectric Rocket Engine Igniter Project

    Data.gov (United States)

    National Aeronautics and Space Administration — Spark ignition of a bi-propellant rocket engine is a classic, proven, and generally reliable process. However, timing can be critical, and the control logic,...

  7. 17 April 2008 - Head of Internal Audit Network meeting visiting the ATLAS experimental area with CERN ATLAS Team Leader P. Fassnacht, ATLAS Technical Coordinator M. Nessi and ATLAS Resources Manager M. Nordberg.

    CERN Multimedia

    Mona Schweizer

    2008-01-01

    17 April 2008 - Head of Internal Audit Network meeting visiting the ATLAS experimental area with CERN ATLAS Team Leader P. Fassnacht, ATLAS Technical Coordinator M. Nessi and ATLAS Resources Manager M. Nordberg.

  8. ATLAS Civil Engineering Point 1

    CERN Multimedia

    Jean-Claude Vialis

    2000-01-01

    Different phases of realisation to Point 1 : zone of the ATLAS experiment The ATLAS experimental area is located in Point 1, just across the main CERN entrance, in the commune of Meyrin. There people are ever so busy to finish the different infrastructures for ATLAS. Real underground video. When passing throw the walls the succeeding can be heard and seen. The film has original working sound.

  9. Numerical Modeling of a Ducted Rocket Combustor With Experimental Validation

    OpenAIRE

    Hewitt, Patrick

    2008-01-01

    The present work was conducted with the intent of developing a high-fidelity numerical model of a unique combustion flow problem combining multi-phase fuel injection with substantial momentum and temperature into a highly complex turbulent flow. This important problem is very different from typical and more widely known liquid fuel combustion problems and is found in practice in pulverized coal combustors and ducted rocket ramjets. As the ducted rocket engine cycle is only now finding wides...

  10. Blood Pump Development Using Rocket Engine Flow Simulation Technology

    Science.gov (United States)

    Kiris, Cetin C.; Kwak, Dochan

    2002-01-01

    This viewgraph presentation provides information on the transfer of rocket engine flow simulation technology to work involving the development of blood pumps. Details are offered regarding the design and requirements of mechanical heart assist devices, or VADs (ventricular assist device). There are various computational fluid dynamics issues involved in the visualization of flow in such devices, and these are highlighted and compared to those of rocket turbopumps.

  11. Investigation on Heat Transfer in Small Hydrocarbon Rocket Combustion Chambers

    OpenAIRE

    Kirchberger, Christoph Ulrich

    2015-01-01

    Low costs and nonhazardous properties draw interest in application of hydrocarbon fuels in liquid rocket engines. Within this work, results of experiments on heat transfer, film cooling, transpiration cooled and convectively cooled fiber-reinforced ceramics conducted at a kerosene/oxygen rocket combustion chamber test facility are presented. The experimental data serves as the base for design and validation of simple-to-use models and correlations, which allow estimates of heat flux and cooli...

  12. Technical Overview of Plume Radiation from a Solid Rocket Motor

    OpenAIRE

    SAKURAI, Yasushi; Kimura, Hiroshi

    1986-01-01

    Current technology for calculation of plume radiation from a solid rocket motor is overviewed and a useful engineering model is reviewed and recommended for design purpose. A solid rocket motor plume is a conical cloud which contains cold scattering particles and hot emitting-absorbing particles. Radiation to aft-end equipment of spacecraft is a major concern of thermal design engineers. Radiative properties of the plume totally depends on the particle behaviors in the flow field and the anal...

  13. Pulse Detonation Rocket Engine Research at NASA Marshall

    Science.gov (United States)

    Morris, Christopher I.

    2003-01-01

    Pulse detonation rocket engines (PDREs) offer potential performance improvements over conventional designs, but represent a challenging modeling task. A quasi 1-D, finite-rate chemistry CFD model for a PDRE is described and implemented. A parametric study of the effect of blowdown pressure ratio on the performance of an optimized, fixed PDRE nozzle configuration is reported. The results are compared to a steady-state rocket system using similar modeling assumptions.

  14. An apparatus for sizing particulate matter in solid rocket motors.

    OpenAIRE

    Harris, Robert Kelly

    1984-01-01

    Approved for public release; distribution is unlimited A light scattering apparatus to measure particle size (D₃₂) in a solid rocket motor was improved. Multiple consecutive scans of two photodiode arrays were accomplished with a pacing circuit and added memory. The device was calibrated using various suspended particle samples and found to make accurate measurements. Air Force Rocket Propulsion Laboratory F04611-84-X-0009 http://archive.org/details/apparatusforsizi00h...

  15. Taking ATLAS to new heights

    CERN Multimedia

    Abha Eli Phoboo, ATLAS experiment

    2013-01-01

    Earlier this month, 51 members of the ATLAS collaboration trekked up to the highest peak in the Atlas Mountains, Mt. Toubkal (4,167m), in North Africa.    The physicists were in Marrakech, Morocco, attending the ATLAS Overview Week (7 - 11 October), which was held for the first time on the African continent. Around 300 members of the collaboration met to discuss the status of the LS1 upgrades and plans for the next run of the LHC. Besides the trek, 42 ATLAS members explored the Saharan sand dunes of Morocco on camels.  Photos courtesy of Patrick Jussel.

  16. The Alfred Nobel rocket camera. An early aerial photography attempt

    Science.gov (United States)

    Ingemar Skoog, A.

    2010-02-01

    Alfred Nobel (1833-1896), mainly known for his invention of dynamite and the creation of the Nobel Prices, was an engineer and inventor active in many fields of science and engineering, e.g. chemistry, medicine, mechanics, metallurgy, optics, armoury and rocketry. Amongst his inventions in rocketry was the smokeless solid propellant ballistite (i.e. cordite) patented for the first time in 1887. As a very wealthy person he actively supported many Swedish inventors in their work. One of them was W.T. Unge, who was devoted to the development of rockets and their applications. Nobel and Unge had several rocket patents together and also jointly worked on various rocket applications. In mid-1896 Nobel applied for patents in England and France for "An Improved Mode of Obtaining Photographic Maps and Earth or Ground Measurements" using a photographic camera carried by a "…balloon, rocket or missile…". During the remaining of 1896 the mechanical design of the camera mechanism was pursued and cameras manufactured. In April 1897 (after the death of Alfred Nobel) the first aerial photos were taken by these cameras. These photos might be the first documented aerial photos taken by a rocket borne camera. Cameras and photos from 1897 have been preserved. Nobel did not only develop the rocket borne camera but also proposed methods on how to use the photographs taken for ground measurements and preparing maps.

  17. Atlas of NATO.

    Science.gov (United States)

    Young, Harry F.

    This atlas provides basic information about the North Atlantic Treaty Organization (NATO). Formed in response to growing concern for the security of Western Europe after World War II, NATO is a vehicle for Western efforts to reduce East-West tensions and the level of armaments. NATO promotes political and economic collaboration as well as military…

  18. Higgs searches with ATLAS

    CERN Document Server

    Price, J D; The ATLAS collaboration

    2013-01-01

    Summary of the ATLAS analyses for the rarer SM Higgs decay channels, and the limits of the SM Higgs invisible decay width. Analyses included are the VH->Vbb, H->tautau, VH->VWW, H->Zy, H->mumu, ttH->ttyy and ZH->ll+inv.

  19. HWW in ATLAS

    CERN Document Server

    Rados, Pere; The ATLAS collaboration

    2016-01-01

    The H-->WW channel plays an important role in Higgs boson property measurements, searches for rare decay modes, and searches for possible extended Higgs sectors. In this talk the latest H-->WW results from ATLAS will be briefly summarised.

  20. ATLAS Experiment Brochure

    CERN Multimedia

    Goldfarb, Steven

    2016-01-01

    ATLAS is one of the four major experiments at the Large Hadron Collider at CERN. It is a general-purpose particle physics experiment run by an international collaboration, and is designed to exploit the full discovery potential and the huge range of physics opportunities that the LHC provides.

  1. Exotic searches at ATLAS

    CERN Document Server

    Turra, Ruggero; The ATLAS collaboration

    2016-01-01

    The ATLAS detector has collected 3.2 fb^-1 of proton-proton collisions at 13 TeV centre of mass energy during the 2015 LHC run. A selected review of the recent result are presented in the context of the direct search for BSM, not SUSY, not BSM Higgs.

  2. ATLAS starts moving in

    CERN Multimedia

    2004-01-01

    The first large active detector component was lowered into the ATLAS cavern on 1 March. It consisted of the 8 modules forming the lower part of the central barrel of the tile hadronic calorimeter. The work of assembling the barrel, which comprises 64 modules, started the following day.

  3. A thermosiphon for ATLAS

    CERN Multimedia

    Rosaria Marraffino

    2013-01-01

    A new thermosiphon cooling system, designed for the ATLAS silicon detectors by CERN’s EN-CV team in collaboration with the experiment, will replace the current system in the next LHC run in 2015. Using the basic properties of density difference and making gravity do the hard work, the thermosiphon promises to be a very reliable solution that will ensure the long-term stability of the whole system.   Former compressor-based cooling system of the ATLAS inner detectors. The system is currently being replaced by the innovative thermosiphon. (Photo courtesy of Olivier Crespo-Lopez). Reliability is the major issue for the present cooling system of the ATLAS silicon detectors. The system was designed 13 years ago using a compressor-based cooling cycle. “The current cooling system uses oil-free compressors to avoid fluid pollution in the delicate parts of the silicon detectors,” says Michele Battistin, EN-CV-PJ section leader and project leader of the ATLAS thermosiphon....

  4. ATLAS solenoid operates underground

    CERN Multimedia

    2006-01-01

    A new phase for the ATLAS collaboration started with the first operation of a completed sub-system: the Central Solenoid. Teams monitoring the cooling and powering of the ATLAS solenoid in the control room. The solenoid was cooled down to 4.5 K from 17 to 23 May. The first current was established the same evening that the solenoid became cold and superconductive. 'This makes the ATLAS Central Solenoid the very first cold and superconducting magnet to be operated in the LHC underground areas!', said Takahiko Kondo, professor at KEK. Though the current was limited to 1 kA, the cool-down and powering of the solenoid was a major milestone for all of the control, cryogenic, power and vacuum systems-a milestone reached by the hard work and many long evenings invested by various teams from ATLAS, all of CERN's departments and several large and small companies. Since the Central Solenoid and the barrel liquid argon (LAr) calorimeter share the same cryostat vacuum vessel, this achievement was only possible in perfe...

  5. Prototype ATLAS straw tracker

    CERN Multimedia

    Laurent Guiraud

    1998-01-01

    This is an early prototype of the straw tracking device for the ATLAS detector at CERN. This detector will be part of the LHC project, scheduled to start operation in 2008. The straw tracker will consist of thousands of gas-filled straws, each containing a wire, allowing the tracks of particles to be followed.

  6. ATLAS "Splash event" 2008

    CERN Multimedia

    ATLAS, Experiment

    2014-01-01

    "Splash events": As the LHC was being tuned up on 10 September 2008, beam was initially directed at beam collimators just outside the detector, so that a splash of particles would fill much of the detector allowing ATLAS experimenters to prepare the detector for actual running.

  7. Prime wires for ATLAS

    CERN Multimedia

    2003-01-01

    In an award ceremony on 3 September, ATLAS honoured the French company Axon Cable for its special coaxial cables, which were purpose-built for the Liquid Argon calorimeter modules. Working for CERN since the 1970s, Axon' Cable received the ATLAS supplier award last week for its contribution to the liquid argon calorimeter cables of ATLAS (LAL/Orsay, France and University of Victoria, Canada), started in 1996. Its two sets of minicoaxial cables, called harnesses "A" and "B", are designed to function in the harsh conditions in the liquid argon (at 90 Kelvin or -183°C) and under extreme radiation (up to several Mrads). The cables are mainly used for the readout of the calorimeters, and are connected to the outside world by 114 signal feedthroughs with 1920 channels each. The signal from the detectors is transmitted directly without any amplification, which imposes tight restrictions on the impedance and on the signal propagation time of the cables. Peter Jenni, ATLAS spokesperson, gives the award for best s...

  8. Orbital transfer rocket engine technology 7.5K-LB thrust rocket engine preliminary design

    Science.gov (United States)

    Harmon, T. J.; Roschak, E.

    1993-01-01

    A preliminary design of an advanced LOX/LH2 expander cycle rocket engine producing 7,500 lbf thrust for Orbital Transfer vehicle missions was completed. Engine system, component and turbomachinery analysis at both on design and off design conditions were completed. The preliminary design analysis results showed engine requirements and performance goals were met. Computer models are described and model outputs are presented. Engine system assembly layouts, component layouts and valve and control system analysis are presented. Major design technologies were identified and remaining issues and concerns were listed.

  9. Russian Meteorological and Geophysical Rockets of New Generation

    Science.gov (United States)

    Yushkov, V.; Gvozdev, Yu.; Lykov, A.; Shershakov, V.; Ivanov, V.; Pozin, A.; Afanasenkov, A.; Savenkov, Yu.; Kuznetsov, V.

    2015-09-01

    To study the process in the middle and upper atmosphere, ionosphere and near-Earth space, as well as to monitor the geophysical environment in Russian Federal Service for Hydrology and Environmental Monitoring (ROSHYDROMET) the development of new generation of meteorological and geophysical rockets has been completed. The modern geophysical research rocket system MR-30 was created in Research and Production Association RPA "Typhoon". The basis of the complex MR-30 is a new geophysical sounding rocket MN-300 with solid propellant, Rocket launch takes place at an angle of 70º to 90º from the launcher, which is a farm with a guide rail type required for imparting initial rotation rocket. The Rocket is spin stabilized with a spin rate between 5 and 7 Hz. Launch weight is 1564 kg, and the mass of the payload of 50 to 150 kg. MR-300 is capable of lifting up to 300 km, while the area of dispersion points for booster falling is an ellipse with parameters 37x 60 km. The payload of the rocket MN-300 consists of two sections: a sealed, located below the instrument compartment, and not sealed, under the fairing. Block of scientific equipment is formed on the platform in a modular layout. This makes it possible to solve a wide range of tasks and conduct research and testing technologies using a unique environment of space, as well as to conduct technological experiments testing and research systems and spacecraft equipment. New Russian rocket system MERA (MEteorological Rocket for Atmospheric Research) belongs to so called "dart" technique that provide lifting of small scientific payload up to altitude 100 km and descending with parachute. It was developed at Central Aerological Observatory jointly with State Unitary Enterprise Instrument Design Bureau. The booster provides a very rapid acceleration to about Mach 5. After the burning phase of the buster the dart is separated and continues ballistic flight for about 2 minutes. The dart carries the instrument payload+ parachute

  10. Thrust Vector Control for Nuclear Thermal Rockets

    Science.gov (United States)

    Ensworth, Clinton B. F.

    2013-01-01

    Future space missions may use Nuclear Thermal Rocket (NTR) stages for human and cargo missions to Mars and other destinations. The vehicles are likely to require engine thrust vector control (TVC) to maintain desired flight trajectories. This paper explores requirements and concepts for TVC systems for representative NTR missions. Requirements for TVC systems were derived using 6 degree-of-freedom models of NTR vehicles. Various flight scenarios were evaluated to determine vehicle attitude control needs and to determine the applicability of TVC. Outputs from the models yielded key characteristics including engine gimbal angles, gimbal rates and gimbal actuator power. Additional factors such as engine thrust variability and engine thrust alignment errors were examined for impacts to gimbal requirements. Various technologies are surveyed for TVC systems for the NTR applications. A key factor in technology selection is the unique radiation environment present in NTR stages. Other considerations including mission duration and thermal environments influence the selection of optimal TVC technologies. Candidate technologies are compared to see which technologies, or combinations of technologies best fit the requirements for selected NTR missions. Representative TVC systems are proposed and key properties such as mass and power requirements are defined. The outputs from this effort can be used to refine NTR system sizing models, providing higher fidelity definition for TVC systems for future studies.

  11. Space Storable Rocket Technology (SSRT) basic program

    Science.gov (United States)

    Chazen, M. L.; Mueller, T.; Casillas, A. R.; Huang, D.

    1992-01-01

    The Space Storable Rocket Technology Program (SSRT) was conducted to establish a technology for a new class of high performance and long life bipropellant engines using space storable propellants. The results are described. Task 1 evaluated several characteristics for a number of fuels to determine the best space storable fuel for use with LO2. The results indicated that LO2-N2H4 is the best propellant combination and provides the maximum mission/system capability maximum payload into GEO of satellites. Task 2 developed two models, performance and thermal. The performance model indicated the performance goal of specific impulse greater than or = 340 seconds (sigma = 204) could be achieved. The thermal model was developed and anchored to hot fire test data. Task 3 consisted of design, fabrication, and testing of a 200 lbf thrust test engine operating at a chamber pressure of 200 psia using LO2-N2H4. A total of 76 hot fire tests were conducted demonstrating performance greater than 340 (sigma = 204) which is a 25 second specific impulse improvement over the existing highest performance flight apogee type engines.

  12. Solid Rocket Motor Design Using Hybrid Optimization

    Directory of Open Access Journals (Sweden)

    Kevin Albarado

    2012-01-01

    Full Text Available A particle swarm/pattern search hybrid optimizer was used to drive a solid rocket motor modeling code to an optimal solution. The solid motor code models tapered motor geometries using analytical burn back methods by slicing the grain into thin sections along the axial direction. Grains with circular perforated stars, wagon wheels, and dog bones can be considered and multiple tapered sections can be constructed. The hybrid approach to optimization is capable of exploring large areas of the solution space through particle swarming, but is also able to climb “hills” of optimality through gradient based pattern searching. A preliminary method for designing tapered internal geometry as well as tapered outer mold-line geometry is presented. A total of four optimization cases were performed. The first two case studies examines designing motors to match a given regressive-progressive-regressive burn profile. The third case study studies designing a neutrally burning right circular perforated grain (utilizing inner and external geometry tapering. The final case study studies designing a linearly regressive burning profile for right circular perforated (tapered grains.

  13. Rotational flow in tapered slab rocket motors

    Science.gov (United States)

    Saad, Tony; Sams, Oliver C.; Majdalani, Joseph

    2006-10-01

    Internal flow modeling is a requisite for obtaining critical parameters in the design and fabrication of modern solid rocket motors. In this work, the analytical formulation of internal flows particular to motors with tapered sidewalls is pursued. The analysis employs the vorticity-streamfunction approach to treat this problem assuming steady, incompressible, inviscid, and nonreactive flow conditions. The resulting solution is rotational following the analyses presented by Culick for a cylindrical motor. In an extension to Culick's work, Clayton has recently managed to incorporate the effect of tapered walls. Here, an approach similar to that of Clayton is applied to a slab motor in which the chamber is modeled as a rectangular channel with tapered sidewalls. The solutions are shown to be reducible, at leading order, to Taylor's inviscid profile in a porous channel. The analysis also captures the generation of vorticity at the surface of the propellant and its transport along the streamlines. It is from the axial pressure gradient that the proper form of the vorticity is ascertained. Regular perturbations are then used to solve the vorticity equation that prescribes the mean flow motion. Subsequently, numerical simulations via a finite volume solver are carried out to gain further confidence in the analytical approximations. In illustrating the effects of the taper on flow conditions, comparisons of total pressure and velocity profiles in tapered and nontapered chambers are entertained. Finally, a comparison with the axisymmetric flow analog is presented.

  14. Ammonium nitrate: a promising rocket propellant oxidizer

    Science.gov (United States)

    Oommen; Jain

    1999-06-30

    Ammonium nitrate (AN) is extensively used in the area of fertilizers and explosives. It is present as the major component in most industrial explosives. Its use as an oxidizer in the area of propellants, however, is not as extensive as in explosive compositions or gas generators. With the growing demand for environmental friendly chlorine free propellants, many attempts have been made of late to investigate oxidizers producing innocuous combustion products. AN, unlike the widely used ammonium perchlorate, produces completely ecofriendly smokeless products. Besides, it is one of the cheapest and easily available compounds. However, its use in large rocket motors is restricted due to some of its adverse characteristics like hygroscopicity, near room temperature phase transformation involving a volume change, and low burning rate (BR) and energetics. The review is an attempt to consolidate the information available on the various issues pertaining to its use as a solid propellant oxidizer. Detailed discussions on the aspects relating to phase modifications, decomposition chemistry, and BR and energetics of AN-based propellants, are presented. To make the review more comprehensive brief descriptions of the history, manufacture, safety, physical and chemical properties and various other applications of the salt are also included. Copyright 1999 Elsevier Science B.V.

  15. Measurements of reactive gaseous rocket injector admittances

    Science.gov (United States)

    Janardan, B. A.; Daniel, B. R.; Bell, W. A.; Zinn, B. T.

    1979-01-01

    The paper describes the results of an experimental study of the quantitative determination of the capabilities of the combustion processes associated with coaxial gaseous propellant rocket injectors to drive combustor pressure oscillations. The data, obtained by employing the modified impedance tube technique with compressed air as the oxidizer and acetylene gas as the fuel, describe the frequency dependence of the admittance of the combined injector-combustion process. The measured data are compared with the predictions of the Feiler and Heidmann analytical model utilizing different values for the characteristic combustion time tau sub b. The values of tau sub b which result in a best fit between the measured and predicted data are indicated for different equivalence ratios. It is shown that for the coaxial injector investigated in this study the tau sub b varies between 0.7 and 1.2 msec for equivalence ratios in the range of 0.57 to 1.31. In addition, the experimental data indicate that the tested injector system could drive combustion instabilities over a frequency range that is in qualitative agreement with the predictions of the Feiler and Heidmann model.

  16. Injector for liquid fueled rocket engine

    Science.gov (United States)

    Cornelius, Charles S. (Inventor); Myers, W. Neill (Inventor); Shadoan, Michael David (Inventor); Sparks, David L. (Inventor)

    2000-01-01

    An injector for liquid fueled rocket engines wherein a generally flat core having a frustoconical dome attached to one side of the core to serve as a manifold for a first liquid, with the core having a generally circular configuration having an axis. The other side of the core has a plurality of concentric annular first slots and a plurality of annular concentric second slots alternating with the first slots, the second slots having a greater depth than said first slots. A bore extends through the core for inletting a second liquid into said core, the bore intersecting the second slots to feed the second liquid into the second slots. The core also has a plurality of first passageways leading from the manifold to the first annular slots for feeding the first liquid into said first slots. A faceplate brazed to said other side of the core is provided with apertures extending from the first and second slots through said face plate, these apertures being positioned to direct fuel and liquid oxygen into contact with each other in the combustion chamber. The first liquid may be liquid oxygen and the second liquid may be kerosene or liquid hydrogen.

  17. Improving atlas methodology

    Science.gov (United States)

    Robbins, C.S.; Dowell, B.A.; O'Brien, J.

    1987-01-01

    We are studying a sample of Maryland (2 %) and New Hampshire (4 %) Atlas blocks and a small sample in Maine. These three States used different sampling methods and block sizes. We compare sampling techniques, roadside with off-road coverage, our coverage with that of the volunteers, and different methods of quantifying Atlas results. The 7 1/2' (12-km) blocks used in the Maine Atlas are satisfactory for coarse mapping, but are too large to enable changes to be detected in the future. Most states are subdividing the standard 7 1/2' maps into six 5-km blocks. The random 1/6 sample of 5-km blocks used in New Hampshire, Vermont (published 1985), and many other states has the advantage of permitting detection of some changes in the future, but the disadvantage of leaving important habitats unsampled. The Maryland system of atlasing all 1,200 5-km blocks and covering one out of each six by quarterblocks (2 1/2-km) is far superior if enough observers can be found. A good compromise, not yet attempted, would be to Atlas a 1/6 random sample of 5-km blocks and also one other carefully selected (non-random) block on the same 7 1/2' map--the block that would include the best sample of habitats or elevations not in the random block. In our sample the second block raised the percentage of birds found from 86% of the birds recorded in the 7 1/2' quadrangle to 93%. It was helpful to list the expected species in each block and to revise this list annually. We estimate that 90-100 species could be found with intensive effort in most Maryland blocks; perhaps 95-105 in New Hampshire. It was also helpful to know which species were under-sampled so we could make a special effort to search for these. A total of 75 species per block (or 75% of the expected species in blocks with very restricted habitat diversity) is considered a practical and adequate goal in these States. When fewer than 60 species are found per block, a high proportion of the rarer species are missed, as well as some of

  18. Rocket plume temperature measurement by wire welded thermocouples

    Science.gov (United States)

    Xu, Qiang

    2006-05-01

    The plume of solid rocket motor is a high velocity flow with high temperature. Temperature distribution in the plume is of great interest for analyzing the compatibility of rocket weapon system. The high temperature exhausted flow field would cause damage on certain equipment and loading vehicles. An instantaneous temperature field with sharp step is established by the exhausted flow field of rocket motor. The increasing rate of the step depends on the flow velocity at cross section of nozzle exit. To perform an accurate measurement of temperature inside the flow field, a thermocouple must be sturdy enough to endure the flow impingement. In the meantime, the thermocouple must have a short time constant to trace the temperature fluctuation in flow field and a small size to avoid disturbing the flow field severely. The dynamic performance of the thermocouples used in exhausted flow temperature measurement must be evaluated before the experiment. The thermocouple which can be used in measuring the temperature distribution in rocket plume was presented in this paper. A NAMNAC (R) self-renew-erode thermocouples with a nominal time constant of 10 microseconds was used as a reference in a dynamic calibration test for this kind of thermocouple. The thermocouple could trace the temperature increase in the exhausted flow perfectly. This kind of thermocouples was used in several real tests of rocket motors, such as the temperature in free exhausted flow field of a stationary rocket motor test, the stagnate temperature in a shock flow field during the launching of a rocket, and the temperature in a launch tube.

  19. Solid rocket combustion simulator technology using the hybrid rocket for simulation

    Science.gov (United States)

    Ramohalli, Kumar

    1994-01-01

    The hybrid rocket is reexamined in light of several important unanswered questions regarding its performance. The well-known heat transfer limited burning rate equation is quoted, and its limitations are pointed out. Several inconsistencies in the burning rate determination through fuel depolymerization are explicitly discussed. The resolution appears to be through the postulate of (surface) oxidative degradation of the fuel. Experiments are initiated to study the fuel degradation in mixtures of nitrogen/oxygen in the 99.9 percent/0.1 percent to 98 percent/2 percent range. The overall hybrid combustion behavior is studied in a 2 in-diameter rocket motor, where a PMMA tube is used as the fuel. The results include detailed, real-time infrared video images of the combustion zone. Space- and time-averaged images give a broad indication of the temperature reached in the gases. A brief outline is shown of future work, which will specifically concentrate on the exploration of the role of the oxidizer transport to the fuel surface, and the role of the unburned fuel that is reported to escape below the classical time-averaged boundary layer flame.

  20. ATLAS: civil engineering Point 1

    CERN Multimedia

    2000-01-01

    The ATLAS experimental area is located in Point 1, just across the main CERN entrance, in the commune of Meyrin. There people are busy to finish the different infrastructures for ATLAS. Real underground video. Nice view from the surface to the cavern from the pit side - all the big machines looked very small. The film has original working sound.

  1. The ATLAS Forward Physics Program

    OpenAIRE

    Royon, Christophe

    2010-01-01

    We describe the ATLAS Forward Physics Program at low luminosity using the rapidity gap method and a dedicated detector called ALFA to tag the protons. We also describe the physics topics of the ATLAS Forward Physics Project at high instantaneous luminosity.

  2. ATLAS recognises its best suppliers

    CERN Multimedia

    2002-01-01

    The ATLAS Collaboration has recently rewarded two of its suppliers in the construction of very major detector components, fabricated in Japan. The ATLAS Supplier Award in recognition of excellent supplier performance has just been attributed to Kawasaki Heavy Industries, while Toshiba Corporation received the award two months ago at their headquarters in Japan.

  3. Lowering the first ATLAS toroid

    CERN Multimedia

    Maximilien Brice

    2004-01-01

    The ATLAS detector on the LHC at CERN will consist of eight toroid magnets, the first of which was lowered into the cavern in these images on 26 October 2004. The coils are supported on platforms where they will be attached to form a giant torus. The platforms will hold about 300 tonnes of ATLAS' muon chambers and will envelop the inner detectors.

  4. ATLAS end-cap detector

    CERN Multimedia

    Maximilien Brice

    2003-01-01

    Three scientists from the Institute of Nuclear Phyiscs at Novossibirsk with one of the end-caps of the ATLAS detector. The end-caps will be used to detect particles produced in the proton-proton collisions at the heart of the ATLAS experiment that are travelling close to the axis of the two beams.

  5. Brain templates and atlases.

    Science.gov (United States)

    Evans, Alan C; Janke, Andrew L; Collins, D Louis; Baillet, Sylvain

    2012-08-15

    The core concept within the field of brain mapping is the use of a standardized, or "stereotaxic", 3D coordinate frame for data analysis and reporting of findings from neuroimaging experiments. This simple construct allows brain researchers to combine data from many subjects such that group-averaged signals, be they structural or functional, can be detected above the background noise that would swamp subtle signals from any single subject. Where the signal is robust enough to be detected in individuals, it allows for the exploration of inter-individual variance in the location of that signal. From a larger perspective, it provides a powerful medium for comparison and/or combination of brain mapping findings from different imaging modalities and laboratories around the world. Finally, it provides a framework for the creation of large-scale neuroimaging databases or "atlases" that capture the population mean and variance in anatomical or physiological metrics as a function of age or disease. However, while the above benefits are not in question at first order, there are a number of conceptual and practical challenges that introduce second-order incompatibilities among experimental data. Stereotaxic mapping requires two basic components: (i) the specification of the 3D stereotaxic coordinate space, and (ii) a mapping function that transforms a 3D brain image from "native" space, i.e. the coordinate frame of the scanner at data acquisition, to that stereotaxic space. The first component is usually expressed by the choice of a representative 3D MR image that serves as target "template" or atlas. The native image is re-sampled from native to stereotaxic space under the mapping function that may have few or many degrees of freedom, depending upon the experimental design. The optimal choice of atlas template and mapping function depend upon considerations of age, gender, hemispheric asymmetry, anatomical correspondence, spatial normalization methodology and disease

  6. ATLAS DQ2 DELETION SERVICE

    CERN Document Server

    Oleynik, D; The ATLAS collaboration; Garonne, V; Campana, S

    2012-01-01

    ATLAS DQ2 Deletion service is a sub system of the ATLAS Distributed Data Management (DDM) project DQ2. DDM DQ2 responsible for the replication, access and bookkeeping of ATLAS data across more than 130 distributed grid sites. It also enforces data management policies decided on by the collaboration and defined in the ATLAS computing model. Responsibility of ATLAS DQ2 Deletion service is serving deletion requests on the grid by interacting with grid middleware and the DQ2 catalogues. Furthermore, it also takes care of retry strategies, check-pointing transactions, load management and fault tolerance. In this talk special attention is paid to the technical details, which are used to achieve the high performance of service, accomplished without overloading either site storage, catalogues or other DQ2 components. Also specialty of database backend implementation will be described. Special section will be devote to the deletion monitoring service that allows operators a detailed view of the working system.

  7. ATLAS Award for Difficult Task

    CERN Multimedia

    2004-01-01

    Two Russian companies were honoured with an ATLAS Award, for supply of the ATLAS Inner Detector barrel support structure elements, last week. On 23 March the Russian company ORPE Technologiya and its subcontractor, RSP Khrunitchev, were jointly presented with an ATLAS Supplier Award. Since 1998, ORPE Technologiya has been actively involved in the development of the carbon-fibre reinforced plastic elements of the ATLAS Inner Detector barrel support structure. After three years of joint research and development, CERN and ORPE Technologiya launched the manufacturing contract. It had a tight delivery schedule and very demanding specifications in terms of mechanical tolerance and stability. The contract was successfully completed with the arrival of the last element of the structure at CERN on 8 January 2004. The delivery of this key component of the Inner Detector deserves an ATLAS Award given the difficulty of manufacturing the end-frames, which very few companies in the world would have been able to do at an ...

  8. Upper Atmosphere Sounding Rocket Projects at Esrange Space Center

    Science.gov (United States)

    Lockowandt, Christian; Kemi, Stig; Sjolander, Krister; Abrahamsson, Mattias

    Swedish Space Corporation, SSC has a long tradition of developing and launching scientific sounding rockets from Esrange Space Center with the aim to study the different layers of the atmosphere and near space. Now a new era has started with an initiative from the Swedish National Space Board, SNSB. The sounding rocket and atmospheric balloon activities will be vitalised with a national program offering the scientific community yearly rocket launches and balloon flights. The three upcoming sounding rocket missions that have recently started are: O-STATES O STATES (Oxygen transformation in the thermosphere) is a research project at the Meteorological Institute of Stockholm University with Prof. Jörg Gumbel, as responsible researcher. The payload comprises two instrument modules with totally 7 instruments for studying oxygen in its various forms. The payload will be launched twice on two sounding rockets at the same launch campaign, in different atmospheric conditions. This provides a cost-effective mission with a large research exchange. The launches from Esrange Space Center are preliminary scheduled to take place in August 2014 with an apogee of approximately 250 km. SPIDER SPIDER (Small Payloads for Investigation of Disturbances in Electrojet by Rockets) is a research project at Space and Plasma Physics, Royal Institute of Technology, Stockholm with Nicholay Ivchenko as responsible researcher. The mission includes up to 10 subsidiary payloads ejected from the main payload to measure the structure of the electrostatic turbulence in the ionosphere. The measurements take place entirely in the subsidiary payloads, which are completely autonomous and recovered individually after the flight. The launch from Esrange Space Center is preliminary scheduled to take place in March 2015 with a desired apogee of approximately 140 km. LEEWAVES LEEWAVES (Local Excitation and Effects of Waves on Atmospheric Vertical Structure) is a research project at the Meteorological

  9. Telemetry Boards Interpret Rocket, Airplane Engine Data

    Science.gov (United States)

    2009-01-01

    For all the data gathered by the space shuttle while in orbit, NASA engineers are just as concerned about the information it generates on the ground. From the moment the shuttle s wheels touch the runway to the break of its electrical umbilical cord at 0.4 seconds before its next launch, sensors feed streams of data about the status of the vehicle and its various systems to Kennedy Space Center s shuttle crews. Even while the shuttle orbiter is refitted in Kennedy s orbiter processing facility, engineers constantly monitor everything from power levels to the testing of the mechanical arm in the orbiter s payload bay. On the launch pad and up until liftoff, the Launch Control Center, attached to the large Vehicle Assembly Building, screens all of the shuttle s vital data. (Once the shuttle clears its launch tower, this responsibility shifts to Mission Control at Johnson Space Center, with Kennedy in a backup role.) Ground systems for satellite launches also generate significant amounts of data. At Cape Canaveral Air Force Station, across the Banana River from Kennedy s location on Merritt Island, Florida, NASA rockets carrying precious satellite payloads into space flood the Launch Vehicle Data Center with sensor information on temperature, speed, trajectory, and vibration. The remote measurement and transmission of systems data called telemetry is essential to ensuring the safe and successful launch of the Agency s space missions. When a launch is unsuccessful, as it was for this year s Orbiting Carbon Observatory satellite, telemetry data also provides valuable clues as to what went wrong and how to remedy any problems for future attempts. All of this information is streamed from sensors in the form of binary code: strings of ones and zeros. One small company has partnered with NASA to provide technology that renders raw telemetry data intelligible not only for Agency engineers, but also for those in the private sector.

  10. Liquid rocket combustion chamber acoustic characterization

    Directory of Open Access Journals (Sweden)

    Cândido Magno de Souza

    2010-09-01

    Full Text Available Over the last 40 years, many solid and liquid rocket motors have experienced combustion instabilities. Among other causes, there is the interaction of acoustic modes with the combustion and/or fluid dynamic processes inside the combustion chamber. Studies have been showing that, even if less than 1% of the available energy is diverted to an acoustic mode, combustion instability can be generated. On one hand, this instability can lead to ballistic pressure changes, couple with other propulsion systems such as guidance or thrust vector control, and in the worst case, cause motor structural failure. In this case, measures, applying acoustic techniques, must be taken to correct/minimize these influences on the combustion. The combustion chamber acoustic behavior in operating conditions can be estimated by considering its behavior in room conditions. In this way, acoustic tests can be easily performed, thus identifying the cavity modes. This paper describes the procedures to characterize the acoustic behavior in the inner cavity of four different configurations of a combustion chamber. Simple analytical models are used to calculate the acoustic resonance frequencies and these results are compared with acoustic natural frequencies measured at room conditions. Some comments about the measurement procedures are done, as well as the next steps for the continuity of this research. The analytical and experimental procedures results showed good agreement. However, limitations on high frequency band as well as in the identification of specific kinds of modes indicate that numerical methods able to model the real cavity geometry and an acoustic experimental modal analysis may be necessary for a more complete analysis. Future works shall also consider the presence of passive acoustic devices such as baffles and resonators capable of introducing damping and avoiding or limiting acoustic instabilities.

  11. Orbit transfer rocket engine technology program

    Science.gov (United States)

    Gustafson, N. B.; Harmon, T. J.

    1993-01-01

    An advanced near term (1990's) space-based Orbit Transfer Vehicle Engine (OTVE) system was designed, and the technologies applicable to its construction, maintenance, and operations were developed under Tasks A through F of the Orbit Transfer Rocket Engine Technology Program. Task A was a reporting task. In Task B, promising OTV turbomachinery technologies were explored: two stage partial admission turbines, high velocity ratio diffusing crossovers, soft wear ring seals, advanced bearing concepts, and a rotordynamic analysis. In Task C, a ribbed combustor design was developed. Possible rib and channel geometries were chosen analytically. Rib candidates were hot air tested and laser velocimeter boundary layer analyses were conducted. A channel geometry was also chosen on the basis of laser velocimeter data. To verify the predicted heat enhancement effects, a ribbed calorimeter spool was hot fire tested. Under Task D, the optimum expander cycle engine thrust, performance and envelope were established for a set of OTV missions. Optimal nozzle contours and quick disconnects for modularity were developed. Failure Modes and Effects Analyses, maintenance and reliability studies and component study results were incorporated into the engine system. Parametric trades on engine thrust, mixture ratio, and area ratio were also generated. A control system and the health monitoring and maintenance operations necessary for a space-based engine were outlined in Task E. In addition, combustor wall thickness measuring devices and a fiberoptic shaft monitor were developed. These monitoring devices were incorporated into preflight engine readiness checkout procedures. In Task F, the Integrated Component Evaluator (I.C.E.) was used to demonstrate performance and operational characteristics of an advanced expander cycle engine system and its component technologies. Sub-system checkouts and a system blowdown were performed. Short transitions were then made into main combustor ignition and

  12. The ATLAS Forward Calorimeter

    Science.gov (United States)

    Artamonov, A.; Bailey, D.; Belanger, G.; Cadabeschi, M.; Chen, T.-Y.; Epshteyn, V.; Gorbounov, P.; Joo, K. K.; Khakzad, M.; Khovanskiy, V.; Krieger, P.; Loch, P.; Mayer, J.; Neuheimer, E.; Oakham, F. G.; O'Neill, M.; Orr, R. S.; Qi, M.; Rutherfoord, J.; Savine, A.; Schram, M.; Shatalov, P.; Shaver, L.; Shupe, M.; Stairs, G.; Strickland, V.; Tompkins, D.; Tsukerman, I.; Vincent, K.

    2008-02-01

    Forward calorimeters, located near the incident beams, complete the nearly 4π coverage for high pT particles resulting from proton-proton collisions in the ATLAS detector at the Large Hadron Collider at CERN. Both the technology and the deployment of the forward calorimeters in ATLAS are novel. The liquid argon rod/tube electrode structure for the forward calorimeters was invented specifically for applications in high rate environments. The placement of the forward calorimeters adjacent to the other calorimeters relatively close to the interaction point provides several advantages including nearly seamless calorimetry and natural shielding for the muon system. The forward calorimeter performance requirements are driven by events with missing ET and tagging jets.

  13. The ATLAS ROBIN

    Energy Technology Data Exchange (ETDEWEB)

    Cranfield, R; Crone, G [University College London, London (United Kingdom); Francis, D; Gorini, B; Joos, M; Petersen, J; Tremblet, L; Unel, G [CERN, Geneva (Switzerland); Green, B; Misiejuk, A; Strong, J; Teixeira-Dias, P [Royal Holloway University of London, London (United Kingdom); Kieft, G; Vermeulen, J [FOM - Institute SAF and University of Amsterdam/Nikhef, Amsterdam (Netherlands); Kugel, A; Mueller, M; Yu, M [University of Mannheim, Mannheim (Germany); Perera, V; Wickens, F [Rutherford Appleton Laboratory, Didcot (United Kingdom)], E-mail: kugel@ti.uni-mannheim.de

    2008-01-15

    The ATLAS readout subsystem is the main interface between {approx} 1600 detector front-end readout links and the higher-level trigger farms. To handle the high event rate (up to 100 kHz) and bandwidth (up to 160 MB/s per link) the readout PCs are equipped with four ROBIN (readout buffer input) cards. Each ROBIN attaches to three optical links, provides local event buffering for approximately 300 ms and communicates with the higher-level trigger system for data and delete requests. According to the ATLAS baseline architecture this communication runs via the PCI bus of the host PC. In addition, each ROBIN provides a private Gigabit Ethernet port which can be used for the same purpose. Operational monitoring is performed via PCI. This paper presents a summary of the ROBIN hardware and software together with measurements results obtained from various test setups.

  14. Electroweak Physics at ATLAS

    CERN Document Server

    Conti, G; The ATLAS collaboration

    2013-01-01

    Various electroweak measurements have already been performed at the ATLAS experiment since the start of the Large Hadron Collider at CERN. A review of the latest results in $W/Z$ and diboson physics will be given here. The $W/Z$ physics results include the measurement of the high-mass Drell-Yan di-lepton production cross section, the $Wb(b)$ production cross section and the study of the transverse momentum of $Z/\\gamma^*$. The latest $WW$, $WZ$, $ZZ$, $W\\gamma$ and $Z\\gamma$ production cross sections will be summarized, including updated $WW$ and $ZZ$ results. In particular, the $ZZ^*$ channel has been added. The ATLAS diboson results are also used to set limits on charged triple gauge couplings ($WWZ$, $WW\\gamma$) and on neutral triple gauge couplings ($Z\\gamma\\gamma$, $ZZ\\gamma$, $ZZZ$).

  15. ATLAS software packaging

    CERN Document Server

    Rybkin, G

    2012-01-01

    Software packaging is indispensable part of build and prerequisite for deployment processes. Full ATLAS software stack consists of TDAQ, HLT, and Offline software. These software groups depend on some 80 external software packages. We present tools, package PackDist, developed and used to package all this software except for TDAQ project. PackDist is based on and driven by CMT, ATLAS software configuration and build tool, and consists of shell and Python scripts. The packaging unit used is CMT project. Each CMT project is packaged as several packages - platform dependent (one per platform available), source code excluding header files, other platform independent files, documentation, and debug information packages (the last two being built optionally). Packaging can be done recursively to package all the dependencies. The whole set of packages for one software release, distribution kit, also includes configuration packages and contains some 120 packages for one platform. Also packaged are physics analysis pro...

  16. Networks in ATLAS

    CERN Document Server

    Mc Kee, Shawn Patrick; The ATLAS collaboration

    2016-01-01

    Networks have played a critical role in high-energy physics (HEP), enabling us to access and effectively utilize globally distributed resources to meet the needs of our physicists. Because of their importance in enabling our grid computing infrastructure many physicists have taken leading roles in research and education (R&E) networking, participating in, and even convening, network related meetings and research programs with the broader networking community worldwide. This has led to HEP benefiting from excellent global networking capabilities for little to no direct cost. However, as other science domains ramp-up their need for similar networking it becomes less clear that this situation will continue unchanged. What this means for ATLAS in particular needs to be understood. ATLAS has evolved its computing model since the LHC started based upon its experience with using globally distributed resources. The most significant theme of those changes has been increased reliance upon, and use of, its networks....

  17. Electron isolation at ATLAS

    International Nuclear Information System (INIS)

    The ATLAS experiment at the Large Hadron Collider (LHC) will face the challenge of efficiently selecting interesting candidate events in pp collisions at 14 TeV centre-of-mass energy, whilst rejecting the enormous number of background events. Many of these interesting candidate events have isolated leptons in the final state, like for example events with a gauge boson or SUSY. On top of the standard ATLAS electron identification an isolation criterion has been developed using a likelihood as multivariate approach with several discriminating variables. The likelihood is constructed by selecting electrons from Z decays for the signal and for the background electrons from b quark jets. Results for the example of the associated Higgs boson production with top quarks and subsequent decay into a pair of W bosons are presented. In addition first results of a likelihood to discriminate against jets are given and a possible extension for muons is discussed

  18. Jet substructure in ATLAS

    CERN Document Server

    Miller, David W

    2011-01-01

    Measurements are presented of the jet invariant mass and substructure in proton-proton collisions at $\\sqrt{s} = 7$ TeV with the ATLAS detector using an integrated luminosity of 37 pb$^{-1}$. These results exercise the tools for distinguishing the signatures of new boosted massive particles in the hadronic final state. Two "fat" jet algorithms are used, along with the filtering jet grooming technique that was pioneered in ATLAS. New jet substructure observables are compared for the first time to data at the LHC. Finally, a sample of candidate boosted top quark events collected in the 2010 data is analyzed in detail for the jet substructure properties of hadronic "top-jets" in the final state. These measurements demonstrate not only our excellent understanding of QCD in a new energy regime but open the path to using complex jet substructure observables in the search for new physics.

  19. SUSY Searches in ATLAS

    CERN Document Server

    Zhuang, Xuai; The ATLAS collaboration

    2016-01-01

    Despite the absence of experimental evidence, weak scale supersymmetry remains one of the best motivated and studied Standard Model extensions. This talk summarises recent ATLAS results for searches for supersymmetric (SUSY) particles, with focus on those obtained using proton-proton collisions at a centre of mass energy of 13 TeV using 2015+2016 data. The searches with final states including jets, missing transverse momentum, light leptons will be presented.

  20. ATLAS support rails

    CERN Multimedia

    Maximilien Brice

    2003-01-01

    These supports will hold the 7000 tonne ATLAS detector in its cavern at the LHC. The huge toroid will be assembled from eight coils that will house some of the muon chambers. Supported within the toroid will be the inner detector, containing tracking devices, as well as devices to measure the energies of the particles produced in the 14 TeV proton-proton collisions at the LHC.

  1. Topographical atlas sheets

    Science.gov (United States)

    Wheeler, George Montague

    1876-01-01

    The following topographical atlas sheets, accompanying Appendix J.J. of the Annual Report of the Chief of Engineers, U.S. Army-being Annual Report upon U. S. Geographical Surveys-have been published during the fiscal year ending June 30, 1876, and are a portion of the series projected to embrace the territory of the United States lying west of the 100th meridian.

  2. Overview of ATLAS results

    CERN Document Server

    Grabowska-Bold, Iwona; The ATLAS collaboration

    2016-01-01

    The ATLAS experiment at the Large Hadron Collider has undertaken a broad physics program to probe and characterize the hot nuclear matter created in relativistic lead-lead collisions. This talk presents recent results based on Run 2 data on production of jet, electroweak bosons and quarkonium, electromagnetic processes in ultra-peripheral collisions, and bulk particle collectivity from PbPb, pPb and pp collisions.

  3. ATLAS/CMS Upgrades

    CERN Document Server

    Horii, Yasuyuki; The ATLAS collaboration

    2016-01-01

    Precise Higgs measurements and new physics searches are planned at LHC (HL-LHC) with integrated luminosity of 300 fb^{-1} (3000 fb^{-1}). An increased peak luminosity provides a significant challenge for the experiments. In this presentation, the plans for the ATLAS and CMS upgrades are introduced. Physics prospects for some topics related with ‘flavour’, e.g Higgs couplings, B_{s, d}->mumu, and FCNC top decays, are also shown.

  4. Hybrid Atlas Models

    CERN Document Server

    Ichiba, Tomoyuki; Banner, Adrian; Karatzas, Ioannis; Fernholz, Robert

    2009-01-01

    We study Atlas-type models of equity markets with local characteristics that depend on both name and rank, and in ways that induce a stability of the capital distribution. Ergodic properties and rankings of processes are examined with reference to the theory of reflected Brownian motions in polyhedral domains. In the context of such models, we discuss properties of various investment strategies, including the so-called growth-optimal and universal portfolios.

  5. L'esperimento ATLAS

    CERN Multimedia

    ATLAS Outreach Committee

    2000-01-01

    This award winning film gives a glimpse behind the scenes of building the ATLAS detector. This film asks: Why are so many physicists anxious to build this apparatus? Will they be able to answer fundamental questions such as: Where does mass come from? Why does the Universe have so little antimatter? Are there extra dimensions of space that are hidden from our view? Is there an underlying theory to find? Major surprises are likely in this unknown part of physics.

  6. El experimento ATLAS

    CERN Multimedia

    ATLAS Outreach Committee

    2000-01-01

    This award winning film gives a glimpse behind the scenes of building the ATLAS detector. This film asks: Why are so many physicists anxious to build this apparatus? Will they be able to answer fundamental questions such as: Where does mass come from? Why does the Universe have so little antimatter? Are there extra dimensions of space that are hidden from our view? Is there an underlying theory to find? Major surprises are likely in this unknown part of physics.

  7. The ATLAS Experiment Movie

    CERN Multimedia

    ATLAS Outreach Committee

    2000-01-01

    This award winning film gives a glimpse behind the scenes of building the ATLAS detector. This film asks: Why are so many physicists anxious to build this apparatus? Will they be able to answer fundamental questions such as: Where does mass come from? Why does the Universe have so little antimatter? Are there extra dimensions of space that are hidden from our view? Is there an underlying theory to find? Major surprises are likely in this unknown part of physics.

  8. The Genome Atlas Resource

    OpenAIRE

    Azam Qureshi, Matloob; Rotenberg, Eva; Stærfeldt, Hans Henrik; Hansson, Lena; Ussery, David

    2010-01-01

    Abstract. The Genome Atlas is a resource for addressing the challenges of synchronising prokaryotic genomic sequence data from multiple public repositories. This resource can integrate bioinformatic analyses in various data format and quality. Existing open source tools have been used together with scripts and algorithms developed in a variety of programming languages at the Centre for Biological Sequence Analysis in order to create a three-tier software application for genome analysis. The r...

  9. ATLAS Job Transforms

    CERN Document Server

    Stewart, G A; The ATLAS collaboration; Maddocks, H J; Harenberg, T; Sandhoff, M; Sarrazin, B

    2013-01-01

    The need to run complex workflows for a high energy physics experiment such as ATLAS has always been present. However, as computing resources have become even more constrained, compared to the wealth of data generated by the LHC, the need to use resources efficiently and manage complex workflows within a single grid job have increased. In ATLAS, a new Job Transform framework has been developed that we describe in this paper. This framework manages the multiple execution steps needed to `transform' one data type into another (e.g., RAW data to ESD to AOD to final ntuple) and also provides a consistent interface for the ATLAS production system. The new framework uses a data driven workflow definition which is both easy to manage and powerful. After a transform is defined, jobs are expressed simply by specifying the input data and the desired output data. The transform infrastructure then executes only the necessary substeps to produce the final data products. The global execution cost of running the job is mini...

  10. ATLAS Job Transforms

    CERN Document Server

    Stewart, G A; The ATLAS collaboration; Maddocks, H J; Harenberg, T; Sandhoff, M; Sarrazin, B

    2013-01-01

    The need to run complex workflows for a high energy physics experiment such as ATLAS has always been present. However, as computing resources have become even more constrained, compared to the wealth of data generated by the LHC, the need to use resources efficiently and manage complex workflows within a single grid job have increased. In ATLAS, a new Job Transform framework has been developed that we describe in this paper. This framework manages the multiple execution steps needed to 'transform' one data type into another (e.g., RAW data to ESD to AOD to final ntuple) and also provides a consistent interface for the ATLAS production system. The new framework uses a data driven workflow definition which is both easy to manage and powerful. After a transform is defined, jobs are expressed simply by specifying the input data and the desired output data. The transform infrastructure then executes only the necessary substeps to produce the final data products. The global execution cost of running the job is mini...

  11. ATLAS overview week highlights

    CERN Multimedia

    D. Froidevaux

    2005-01-01

    A warm and early October afternoon saw the beginning of the 2005 ATLAS overview week, which took place Rue de La Montagne Sainte-Geneviève in the heart of the Quartier Latin in Paris. All visitors had been warned many times by the ATLAS management and the organisers that the premises would be the subject of strict security clearance because of the "plan Vigipirate", which remains at some level of alert in all public buildings across France. The public building in question is now part of the Ministère de La Recherche, but used to host one of the so-called French "Grandes Ecoles", called l'Ecole Polytechnique (in France there is only one Ecole Polytechnique, whereas there are two in Switzerland) until the end of the seventies, a little while after it opened its doors also to women. In fact, the setting chosen for this ATLAS overview week by our hosts from LPNHE Paris has turned out to be ideal and the security was never an ordeal. For those seeing Paris for the first time, there we...

  12. ATLAS Detector Upgrade Prospects

    CERN Document Server

    Dobre, Monica; The ATLAS collaboration

    2016-01-01

    After the successful operation at the center-of-mass energies of 7 and 8 TeV in 2010 - 2012, the LHC is ramped up and successfully took data at the center-of-mass energies of 13 TeV in 2015. Meanwhile, plans are actively advancing for a series of upgrades of the accelerator, culminating roughly ten years from now in the high-luminosity LHC (HL-LHC) project, delivering of the order of five times the LHC nominal instantaneous luminosity along with luminosity leveling. The ultimate goal is to extend the dataset from about few hundred fb−1 expected for LHC running to 3000 fb−1 by around 2035 for ATLAS and CMS. The challenge of coping with the HL-LHC instantaneous and integrated luminosity, along with the associated radiation levels, requires further major changes to the ATLAS detector. The designs are developing rapidly for a new all-silicon tracker, significant upgrades of the calorimeter and muon systems, as well as improved triggers and data acquisition. ATLAS is also examining potential benefits of extens...

  13. Clean tracks for ATLAS

    CERN Multimedia

    2006-01-01

    First cosmic ray tracks in the integrated ATLAS barrel SCT and TRT tracking detectors. A snap-shot of a cosmic ray event seen in the different layers of both the SCT and TRT detectors. The ATLAS Inner Detector Integration Team celebrated a major success recently, when clean tracks of cosmic rays were detected in the completed semiconductor tracker (SCT) and transition radiation tracker (TRT) barrels. These tracking tests come just months after the successful insertion of the SCT into the TRT (See Bulletin 09/2006). The cosmic ray test is important for the experiment because, after 15 years of hard work, it is the last test performed on the fully assembled barrel before lowering it into the ATLAS cavern. The two trackers work together to provide millions of channels so that particles' tracks can be identified and measured with great accuracy. According to the team, the preliminary results were very encouraging. After first checks of noise levels in the final detectors, a critical goal was to study their re...

  14. History of the development of rocket technology and astronautics in Poland

    Science.gov (United States)

    Geisler, W.

    1977-01-01

    The development of rocket technology in Poland is outlined. The history cites 13th century use of war rockets in combating Tartars as well as 20th century studies of the future and reality of space flights.

  15. Implementing planetary protection on the Atlas V fairing and ground systems used to launch the Mars Science Laboratory.

    Science.gov (United States)

    Benardini, James N; La Duc, Myron T; Ballou, David; Koukol, Robert

    2014-01-01

    On November 26, 2011, the Mars Science Laboratory (MSL) launched from Florida's Cape Canaveral Air Force Station aboard an Atlas V 541 rocket, taking its first step toward exploring the past habitability of Mars' Gale Crater. Because microbial contamination could profoundly impact the integrity of the mission, and compliance with international treaty was a necessity, planetary protection measures were implemented on all MSL hardware to verify that bioburden levels complied with NASA regulations. The cleanliness of the Atlas V payload fairing (PLF) and associated ground support systems used to launch MSL were also evaluated. By applying proper recontamination countermeasures early and often in the encapsulation process, the PLF was kept extremely clean and was shown to pose little threat of recontaminating the enclosed MSL flight system upon launch. Contrary to prelaunch estimates that assumed that the interior PLF spore burden ranged from 500 to 1000 spores/m², the interior surfaces of the Atlas V PLF were extremely clean, housing a mere 4.65 spores/m². Reported here are the practices and results of the campaign to implement and verify planetary protection measures on the Atlas V launch vehicle and associated ground support systems used to launch MSL. All these facilities and systems were very well kept and exceeded the levels of cleanliness and rigor required in launching the MSL payload.

  16. Calibration of the Berkeley EUV Airglow Rocket Spectrometer

    Science.gov (United States)

    Cotton, Daniel M.; Chakrabarti, Supriya; Siegmund, Oswald

    1989-01-01

    The Berkeley Extreme-ultraviolet Airglow Rocket Spectrometer (BEARS), a multiinstrument sounding rocket payload, made comprehensive measurements of the earth's dayglow. The primary instruments consisted of two near-normal Rowland mount spectrometers: one channel to measure several atomic oxygen features at high spectral resolution (about 1.5 A) in the band passes 980-1040 and 1300-1360 A, and the other to measure EUV dayglow and the solar EUV simultaneously in a much broader bandpass (250-1150 A) at moderate resolution (about 10 A). The payload also included a hydrogen Lyman-alpha photometer to monitor the solar irradiance and goecoronal emissions. The instrument was calibrated at the EUV calibration facility at the University of California at Berkeley, and was subsequently launched successfully on September 30, 1988 aboard a four-stage experimental sounding rocket, Black Brant XII flight 12.041 WT. The calibration procedure and resulting data are presented.

  17. Vibration Isolation Design for the Micro-X Rocket Payload

    Science.gov (United States)

    Danowski, M. E.; Heine, S. N. T.; Figueroa-Feliciano, E.; Goldfinger, D.; Wikus, P.; McCammon, D.; Oakley, P.

    2016-08-01

    Micro-X is a NASA-funded sounding rocket-borne X-ray imaging spectrometer designed to enable high precision measurements of extended astrophysical systems. To perform high energy resolution measurements and capture unprecedented spectra of supernova remnants and galaxy clusters, Micro-X must maintain tight temperature control. One of the biggest challenges in payload design is to prevent heating of the detectors due to the vibrational loads on the rocket skin during launch. Several stages of vibration damping systems are implemented to prevent energy transmission from the rocket skin to the detector stage, each stage more rigid than the last. We describe recent redesign efforts to improve this vibration isolation by tuning the resonant frequencies of the various stages to minimize heating prior to the projected launch in 2016.

  18. Rocket experiment on microwave power transmission with Furoshiki deployment

    Science.gov (United States)

    Kaya, Nobuyuki; Iwashita, Masashi; Tanaka, Kohei; Nakasuka, Shinichi; Summerer, Leopold

    2009-07-01

    Huge antennas has many useful applications in space as well as on the ground, for example, Solar Power Satellite to provide electricity to the ground, telecommunication for cellular phones, radars for remote sensing, navigation and observation, and so on. The S-310-36 sounding rocket was successfully launched on 22 January 2006 to verify our newly proposed scheme to construct huge antennas under microgravity condition in space. The rocket experiment has three main objectives, the first objective of which is to verify the Furoshiki deployment system [S. Nakasuka, R. Funase, K. Nakada, N. Kaya, J. Mankins, Large membrane "FUROSHIKI Satellite" applied to phased array antenna and its sounding rocket experiment, in: Proceedings of the 54th International Astronautical Congress, 2003. [1

  19. Rocket effluent - Its ice nucleation activity and related properties

    Science.gov (United States)

    Parungo, F. P.; Allee, P. A.

    1978-01-01

    To investigate the possibility of inadvertent weather modification from rocket effluent, aerosol samples were collected from an instrumented aircraft subsequent to the Voyager I and II launches. The aerosol's morphology, concentration and size distribution were examined with an electron microscope. The elemental compositions of individual particles were analyzed with an X-ray energy spectrometer. Ice nucleus concentration was measured with a subfreezing thermal diffusion chamber. The particles' physical and chemical properties were related to their ice nucleation activity. A laboratory experiment on rocket propellant exhaust was conducted under controlled conditions. Both laboratory and field experimental results indicated that rocket propellant exhaust can produce active ice nuclei. Their consequences for potential inadvertant weather modification demand additional study.

  20. Rocket effluent: Its ice nucleation activity and related properties

    Science.gov (United States)

    Parungo, F. P.; Allee, P. A.

    1978-01-01

    To investigate the possibility of inadvertent weather modification from rocket effluent, aerosol samples were collected from an instrumented aircraft subsequent to the Voyager 1 and 2 launches. The aerosol's morphology, concentration, and size distribution were examined with an electron microscope. The elemental compositions of individual particles were analyzed with an X-ray energy spectrometer. Ice nucleus concentration was measured with a thermal diffusion chamber. The particles' physical and chemical properties were related to their ice nucleation activity. A laboratory experiment on rocket propellant exhaust was conducted under controlled conditions. Both laboratory and field experimental results indicated that rocket propellant exhaust can produce active ice nuclei and modify local weather in suitable meteorological conditions.

  1. Impact of rocket exhaust plumes on atmospheric composition and climate – an overview

    OpenAIRE

    Voigt, Christiane; Schumann, Ulrich; Graf, Kaspar; Gottschaldt, Klaus-Dirk

    2013-01-01

    Rockets are the only direct anthropogenic emission sources into the upper atmosphere. Gaseous rocket emissions include CO, N2, H2, H2O, and CO2, while solid rocket motors (SRM) additionally inject significant amounts of aluminum oxide (Al2O3) particles and gaseous chlorine species into the atmosphere. These emissions strongly perturb local at- mospheric trace gas and aerosol distributions. Here, the previous aircraft measurements in various rocket exhaust plumes including several large spa...

  2. Hydrodynamic Stability Analysis of Particle-Laden Solid Rocket Motors

    International Nuclear Information System (INIS)

    Fluid-wall interactions within solid rocket motors can result in parietal vortex shedding giving rise to hydrodynamic instabilities, or unsteady waves, that translate into pressure oscillations. The oscillations can result in vibrations observed by the rocket, rocket subsystems, or payload, which can lead to changes in flight characteristics, design failure, or other undesirable effects. For many years particles have been embedded in solid rocket propellants with the understanding that their presence increases specific impulse and suppresses fluctuations in the flowfield. This study utilizes a two dimensional framework to understand and quantify the aforementioned two-phase flowfield inside a motor case with a cylindrical grain perforation. This is accomplished through the use of linearized Navier-Stokes equations with the Stokes drag equation and application of the biglobal ansatz. Obtaining the biglobal equations for analysis requires quantification of the mean flowfield within the solid rocket motor. To that end, the extended Taylor-Culick form will be utilized to represent the gaseous phase of the mean flowfield while the self-similar form will be employed for the particle phase. Advancing the mean flowfield by quantifying the particle mass concentration with a semi-analytical solution the finalized mean flowfield is combined with the biglobal equations resulting in a system of eight partial differential equations. This system is solved using an eigensolver within the framework yielding the entire spectrum of eigenvalues, frequency and growth rate components, at once. This work will detail the parametric analysis performed to demonstrate the stabilizing and destabilizing effects of particles within solid rocket combustion

  3. ATLAS: Forecasting Falling Rocks

    Science.gov (United States)

    Heinze, Aren; Tonry, John L.; Denneau, Larry; Stalder, Brian; Sherstyuk, Andrei

    2016-10-01

    The Asteroid Terrestrial-impact Last Alert System (ATLAS) is a new asteroid survey aimed at detecting small (10-100 meter) asteroids inbound for impact with Earth. Relative to the larger objects targeted by most surveys, these small asteroids pose very different threats to our planet. Large asteroids can be seen at great distances and measured over many years, resulting in precise orbits that enable long-term impact predictions. If an impact were predicted, a costly deflection mission would be warranted to avert global catastrophe -- but a large asteroid impact is very unlikely in the next century. By contrast, impacts from small asteroids are inevitable. Such objects can be detected only during close encounters with Earth -- encounters too brief to yield long-term predictions. Only a few days' warning could be expected for an impactor in the 10-100 meter range, but fortunately the impact of such an asteroid would cause only regional damage. As in the case of a hurricane, a quixotic attempt to deflect or destroy it would be more expensive than the damage from its impact. A better response is to save human lives by evacuating the impact zone, and then rebuild. Only a few days warning are needed for this purpose, and ATLAS is unique among asteroid surveys in being optimized to provide it. While the optimization has many facets, the most important is rapidly surveying the entire accessible sky. A small asteroid could come from any direction and go from invisibility to impact in less than a week: ATLAS must look everywhere, all the time. Sky coverage is more important than exquisite sensitivity to faint objects, because asteroids inbound for impact will eventually become quite bright. This makes ATLAS complementary to other surveys, which scan the sky at a more leisurely pace but are able to detect asteroids at greater distances. We report on ATLAS' first year of survey operations, including the maturing of robotic observation and detection strategies, and asteroid and

  4. A proposed bare tether experiment on board a sounding rocket

    OpenAIRE

    Fujii, Hironori; OYAMA, Kohichiro; Sasaki, Susumu; Yamagiwa, Yoshiki; Cho, Mengu; Sanmartín Losada, Juan Ramón; Charro, Mario; Heide, Erik J. van der; Kruijff, Michiel; Lebreton, Jean-Pierre; Hilgers, Alain

    2005-01-01

    A sounding rocket experiment is proposed to carry out two experiments by the conductive bare-tether; 1) the test of the OML (Orbital-Motion-Limited) theory to collect electron, and II) the test of techniques to determine (neutral) density profile in critical E-layer. The main driver of the mission is provide a space tether technology experiment in low-Earth-Orbit (LEO) deploying a long tape tether in space and verify the performance of the bare electrodynamic tape tether. The sounding rocket ...

  5. Yuzhnoye's new liquid rocket engines as enablers for space exploration

    Science.gov (United States)

    Degtyarev, Alexander; Kushnaryov, Alexander; Shulga, Vladimir; Ventskovsky, Oleg

    2016-10-01

    Advanced liquid rocket engines (LREs) are being created by Yuzhnoye Design Office of Ukraine based on the fifty-year experience of rocket engines' and propulsion systems' development. These LREs use both hypergolic (NTO+UDMH) and cryogenic (liquid oxygen+kerosene) propellants. First stage engines have a range of thrust from 40 to 250 t, while the upper stage (used in space) engines - from several kilograms to 50 t and a re-ignition feature. The engines are intended for both Ukraine"s independent access to space and international market.

  6. Grooved Fuel Rings for Nuclear Thermal Rocket Engines

    Science.gov (United States)

    Emrich, William

    2009-01-01

    An alternative design concept for nuclear thermal rocket engines for interplanetary spacecraft calls for the use of grooved-ring fuel elements. Beyond spacecraft rocket engines, this concept also has potential for the design of terrestrial and spacecraft nuclear electric-power plants. The grooved ring fuel design attempts to retain the best features of the particle bed fuel element while eliminating most of its design deficiencies. In the grooved ring design, the hydrogen propellant enters the fuel element in a manner similar to that of the Particle Bed Reactor (PBR) fuel element.

  7. Flip-Flop Recovery System for sounding rocket payloads

    Science.gov (United States)

    Flores, A., Jr.

    1986-01-01

    The design, development, and testing of the Flip-Flop Recovery System, which protects sensitive forward-mounted instruments from ground impact during sounding rocket payload recovery operations, are discussed. The system was originally developed to reduce the impact damage to the expensive gold-plated forward-mounted spectrometers in two existing Taurus-Orion rocket payloads. The concept of the recovery system is simple: the payload is flipped over end-for-end at a predetermined time just after parachute deployment, thus minimizing the risk of damage to the sensitive forward portion of the payload from ground impact.

  8. The Application of Counter-Rotating Turbine in Rocket Turbopump

    Directory of Open Access Journals (Sweden)

    Tang Fei

    2008-01-01

    Full Text Available Counter rotating turbine offers advantages on weight, volume, efficiency, and maneuverability relative to the conventional turbine because of its special architecture. Nowadays, it has been a worldwide research emphasis and has been used widely in the aeronautic field, while its application in the astronautic field is seldom investigated. Researches of counter rotating turbine for rocket turbopump are reviewed in this paper. A primary analysis of a vaneless counter rotating-turbine configuration with rotors of different diameters and rotational speeds is presented. This unconventional configuration meets the requirements of turbopump and may benefit the performance and reliability of rocket engines.

  9. ROCKET-hanke väliraportti 2

    OpenAIRE

    Tenhunen, Lauri; Niittymäki, Seppo

    2012-01-01

    ROCKET – hanketta toteutettavat HAMK, KyAMK, Laurea, LUT Lahti, Metropolia, Saimaan AMK ja TuAMK. Toteutuksen kansainvälisenä yhteistyöverkostona on METNET -verkosto ja eräät kiinalaiset ja venäläiset korkeakoulut. Hankkeen päärahoittaja on Päijät-Hämeen liitto EAKR-rahoituksella. Rocket – hankkeen tavoitteena on kehittää suomalaisiin korkeakouluihin sellaisia verkottuneita rakenteita, jotka pysyvästi tukevat suomalaisten metalli- ja koneteknologia-alan yritysten innovaatiotoimintaa ja ...

  10. How High? How Fast? How Long? Modeling Water Rocket Flight with Calculus

    Science.gov (United States)

    Ashline, George; Ellis-Monaghan, Joanna

    2006-01-01

    We describe an easy and fun project using water rockets to demonstrate applications of single variable calculus concepts. We provide procedures and a supplies list for launching and videotaping a water rocket flight to provide the experimental data. Because of factors such as fuel expulsion and wind effects, the water rocket does not follow the…

  11. Propellant-Flow-Actuated Rocket Engine Igniter

    Science.gov (United States)

    Wollen, Mark

    2013-01-01

    A rocket engine igniter has been created that uses a pneumatically driven hammer that, by specialized geometry, is induced into an oscillatory state that can be used to either repeatedly impact a piezoelectric crystal with sufficient force to generate a spark capable of initiating combustion, or can be used with any other system capable of generating a spark from direct oscillatory motion. This innovation uses the energy of flowing gaseous propellant, which by means of pressure differentials and kinetic motion, causes a hammer object to oscillate. The concept works by mass flows being induced through orifices on both sides of a cylindrical tube with one or more vent paths. As the mass flow enters the chamber, the pressure differential is caused because the hammer object is supplied with flow on one side and the other side is opened with access to the vent path. The object then crosses the vent opening and begins to slow because the pressure differential across the ball reverses due to the geometry in the tube. Eventually, the object stops because of the increasing pressure differential on the object until all of the kinetic energy has been transferred to the gas via compression. This is the point where the object reverses direction because of the pressure differential. This behavior excites a piezoelectric crystal via direct impact from the hammer object. The hammer strikes a piezoelectric crystal, then reverses direction, and the resultant high voltage created from the crystal is transferred via an electrode to a spark gap in the ignition zone, thereby providing a spark to ignite the engine. Magnets, or other retention methods, might be employed to favorably position the hammer object prior to start, but are not necessary to maintain the oscillatory behavior. Various manifestations of the igniter have been developed and tested to improve device efficiency, and some improved designs are capable of operation at gas flow rates of a fraction of a gram per second (0

  12. ATLAS status and physics program

    International Nuclear Information System (INIS)

    Full text: The ATLAS detector will observe proton collisions in the Large Hadron Collider (LHC) at CERN, which is scheduled for commissioning in 2007. When operational the LHC will collide protons at a centre-of-mass energy of 14 TeV with nominally 2 X 108 collisions per second at each of four beam-crossing points. ATLAS has been optimised for the detection of the hypothesised Higgs Boson, the only missing component of the otherwise experimentally well-verified electro-weak theory. In addition ATLAS is also sensitive to many other physics processes including QCD, b-physics, heavy ion interactions and those that could provide first evidence for super-symmetry. The current status of the LHC and the various aspects of the ATLAS detector will be discussed as well as the ability of ATLAS to observe new physics. The Australian contributions to the ATLAS project will also be described. These include: 1. Development and implementation of components of the Semi-Conductor Tracker (SCT), which provides spatial information for charged particles traversing the ATLAS inner detector. 2. Fast algorithms for simulating electromagnetic events in the calorimeter. 3. Development and application of fast reconstruction algorithms within the ATLAS software framework. 4. Analysis of Monte-Carlo data produced using simulated models of the ATLAS detector. The information provided will determine the most efficient strategies in searching for new physics once collisions at the LHC commence. 5. Advances in grid computing to handle the storage, transfer and offline processing of data amassed by LHC experiments, which totals over 2.4 P-bytes per annum. Copyright (2005) Australian Institute of Physics

  13. Automated Loads Analysis System (ATLAS)

    Science.gov (United States)

    Gardner, Stephen; Frere, Scot; O’Reilly, Patrick

    2013-01-01

    ATLAS is a generalized solution that can be used for launch vehicles. ATLAS is used to produce modal transient analysis and quasi-static analysis results (i.e., accelerations, displacements, and forces) for the payload math models on a specific Shuttle Transport System (STS) flight using the shuttle math model and associated forcing functions. This innovation solves the problem of coupling of payload math models into a shuttle math model. It performs a transient loads analysis simulating liftoff, landing, and all flight events between liftoff and landing. ATLAS utilizes efficient and numerically stable algorithms available in MSC/NASTRAN.

  14. Electrons and Photons at ATLAS

    CERN Document Server

    Heim, Sarah; The ATLAS collaboration

    2016-01-01

    The performance of the reconstruction, calibration and identification of electrons and photons with the ATLAS detector at the LHC is a key component to realize the ATLAS full physics potential, both in the searches for new physics and in precision measurements. The algorithms used for the reconstruction and identification of electrons and photons with the ATLAS detector during LHC run 2 are presented. Measurements of the identification efficiencies are derived from data. The results from the 2015 pp collision data set at sqrt(s)=13 TeV are reported. The electron and photon energy calibration procedure and its performance are also discussed.

  15. The ATLAS Trigger Muon "Vertical Slice"

    CERN Document Server

    Sidoti, A; Biglietti, M; Carlino, G; Cataldi, G; Conventi, F; Del Prete, T; Di Mattia, A; Falciano, S; Gorini, S; Kanaya, N; Kohno, T; Krasznahorkay, A; Lagouri, T; Luci, C; Luminari, L; Marzano, F; Nagano, K; Nisati, A; Panikashvili, N; Pasqualucci, E; Primavera, M; Scannicchio, D A; Spagnolo, S; Tarem, S; Tarem, Z; Tokushuku, K; Usai, G; Ventura, A; Vercesi, V; Yamazaki, Y; 10th Pisa Meeting on Advanced Detectors : Frontier Detectors For Frontier Physics

    2007-01-01

    The muon trigger system is a fundamental component of the ATLAS detector at the LHC collider. In this paper we describe the ATLAS multi-level trigger selecting events with muons: the Muon Trigger Slice.

  16. EnviroAtlas - Metrics for Memphis, TN

    Data.gov (United States)

    U.S. Environmental Protection Agency — This EnviroAtlas web service supports research and online mapping activities related to EnviroAtlas (https://www.epa.gov/enviroatlas). The layers in this web...

  17. EnviroAtlas - Metrics for Portland, ME

    Data.gov (United States)

    U.S. Environmental Protection Agency — This EnviroAtlas web service supports research and online mapping activities related to EnviroAtlas (https://www.epa.gov/enviroatlas). The layers in this web...

  18. ATLAS Calorimeter Part 2/2

    CERN Multimedia

    2004-01-01

    There are two videos about lowering and this one is the second part that shows the final positioning of the object. The first part shows how the ATLAS calorimeter with solenoid is lowered down in the ATLAS cavern.

  19. Forward Physics at the ATLAS experiment

    CERN Document Server

    The ATLAS collaboration

    2009-01-01

    Poster summarize forward physics at the ATLAS experiment. It aims to AFP project which is the project to install forward detectors at 220m (AFP220) and 420m (AFP420) around ATLAS for measurements at high luminosity.

  20. EnviroAtlas - Metrics for Paterson, NJ

    Data.gov (United States)

    U.S. Environmental Protection Agency — These EnviroAtlas web services support research and online mapping activities related to EnviroAtlas (https://www.epa.gov/enviroatlas). The layers in these web...

  1. EnviroAtlas - Metrics for Tampa, FL

    Data.gov (United States)

    U.S. Environmental Protection Agency — This EnviroAtlas web service supports research and online mapping activities related to EnviroAtlas (https://www.epa.gov/enviroatlas). The layers in this web...

  2. EnviroAtlas - Metrics for Portland, OR

    Data.gov (United States)

    U.S. Environmental Protection Agency — These EnviroAtlas web services support research and online mapping activities related to EnviroAtlas (http:/www.epa.gov/enviroatlas). The layers in these web...

  3. EnviroAtlas - Metrics for Milwaukee, WI

    Data.gov (United States)

    U.S. Environmental Protection Agency — These EnviroAtlas web services support research and online mapping activities related to EnviroAtlas (http://www.epa.gov/enviroatlas). The layers in these web...

  4. EnviroAtlas - Durham, NC - Demo (Parent)

    Data.gov (United States)

    U.S. Environmental Protection Agency — This EnviroAtlas dataset is the base layer for the Durham, NC EnviroAtlas Area. The block groups are from the US Census Bureau and are included/excluded based on...

  5. EnviroAtlas - Memphis, TN - Block Groups

    Data.gov (United States)

    U.S. Environmental Protection Agency — This EnviroAtlas dataset is the base layer for the Memphis, TN EnviroAtlas community. The block groups are from the US Census Bureau and are included/excluded based...

  6. ATLAS : civil engineering at Point 1

    CERN Multimedia

    CERN Audiovisual Unit

    2002-01-01

    The ATLAS experimental area is located in Point 1, just across the main CERN entrance, in the commune of Meyrin. There people are ever so busy to finish the different infrastructures for ATLAS. Real underground video.

  7. EnviroAtlas - Metrics for Woodbine, IA

    Data.gov (United States)

    U.S. Environmental Protection Agency — This EnviroAtlas web service supports research and online mapping activities related to EnviroAtlas (https://www.epa.gov/enviroatlas). The layers in this web...

  8. EnviroAtlas - Metrics for Phoenix, AZ

    Data.gov (United States)

    U.S. Environmental Protection Agency — These EnviroAtlas web services support research and online mapping activities related to EnviroAtlas (https://www.epa.gov/enviroatlas). The layers in these web...

  9. EnviroAtlas - Metrics for Durham, NC

    Data.gov (United States)

    U.S. Environmental Protection Agency — These EnviroAtlas web services support research and online mapping activities related to EnviroAtlas (https://www.epa.gov/enviroatlas ). The layers in these web...

  10. EnviroAtlas - Metrics for Pittsburgh, PA

    Data.gov (United States)

    U.S. Environmental Protection Agency — These EnviroAtlas web services support research and online mapping activities related to EnviroAtlas (https://www.epa.gov/enviroatlas). The layers in these web...

  11. EnviroAtlas - Austin, TX - Block Groups

    Data.gov (United States)

    U.S. Environmental Protection Agency — This EnviroAtlas dataset is the base layer for the Austin, TX EnviroAtlas area. The block groups are from the US Census Bureau and are included/excluded based on...

  12. Women of ATLAS - International Women's Day 2016

    CERN Multimedia

    Biondi, Silvia

    2016-01-01

    Women play key roles in the ATLAS Experiment: from young physicists at the start of their careers to analysis group leaders and spokespersons of the collaboration. Celebrate International Women's Day by meeting a few of these inspiring ATLAS researchers.

  13. EnviroAtlas - Metrics for Fresno, CA

    Data.gov (United States)

    U.S. Environmental Protection Agency — This EnviroAtlas web service supports research and online mapping activities related to EnviroAtlas (https://www.epa.gov/enviroatlas). The layers in this web...

  14. CERN Open Days 2013, Point 1 - ATLAS: ATLAS Experiment

    CERN Multimedia

    CERN Photolab

    2013-01-01

    Stand description: The ATLAS Experiment at CERN is one of the largest and most complex scientific endeavours ever assembled. The detector, located at collision point 1 of the LHC, is designed to explore the fundamental components of nature and to study the forces that shape our universe. The past year’s discovery of a Higgs boson is one of the most important scientific achievements of our time, yet this is only one of many key goals of ATLAS. During a brief break in their journey, some of the 3000-member ATLAS collaboration will be taking time to share the excitement of this exploration with you. On surface no restricted access  The exhibit at Point 1 will give visitors a chance to meet these modern-day explorers and to learn from them how answers to the most fundamental questions of mankind are being sought. Activities will include a visit to the ATLAS detector, located 80m below ground; watching the prize-winning ATLAS movie in the ATLAS cinema; seeing real particle tracks in a cloud chamber and discussi...

  15. Residual velocities in combustion experiments on board of sounding rockets

    Science.gov (United States)

    Juste, G. L.

    1996-12-01

    Most combustion experiments on microgravity conditions require extensive testing time, thus making necessary the use of sounding rockets, satellites and spatial laboratories. Sounding rockets and satellites offer some advantages over spatial laboratories, i.e. less strict safety requirements than those in manned flights, the cost of the experiment is also lower. In combustion experiments, the gas velocities inside test modules must be smaller than the characteristic velocity of the process. The initial spin stabilization of sounding rockets has been identified as a possible origin of residual velocities inside the aforementioned modules. The object of the present work is to study the gas residual velocity in the module designed by SENER for carrying out of combustion experiments in microgravity conditions in sounding rockets. Particle image velocimetry was used to measure these velocities. The study shows that, after the spin stabilization, a rapid slowing down of such velocities is produced, decreasing by 5 mm/s after 10 s and down to 0.1 mm/s after 40 s.

  16. Implementation of microwave transmissions for rocket exhaust plume diagnostics

    Science.gov (United States)

    Coutu, Nicholas George

    Rocket-launched vehicles produce a trail of exhaust that contains ions, free electrons, and soot. The exhaust plume increases the effective conductor length of the rocket. A conductor in the presence of an electric field (e.g. near the electric charge stored within a cloud) can channel an electric discharge. The electrical conductivity of the exhaust plume is related to its concentration of free electrons. The risk of a lightning strike in-flight is a function of both the conductivity of the body and its effective length. This paper presents an approach that relates the electron number density of the exhaust plume to its propagation constant. Estimated values of the collision frequency and electron number density generated from a numerical simulation of a rocket plume are used to guide the design of the experimental apparatus. Test par meters are identified for the apparatus designed to transmit a signal sweep form 4 GHz to 7 GHz through the exhaust plume of a J-class solid rocket motor. Measurements of the scattering parameters imply that the transmission does not penetrate the plume, but instead diffracts around it. The electron density 20 cm downstream from the nozzle exit is estimated to be between 2.7x1014 m--3 and 5.6x10 15 m--3.

  17. Nuclear rocket propulsion technology - A joint NASA/DOE project

    Science.gov (United States)

    Clark, John S.

    1991-01-01

    NASA and the DOE have initiated critical technology development for nuclear rocket propulsion systems for SEI human and robotic missions to the moon and to Mars. The activities and project plan of the interagency project planning team in FY 1990 and 1991 are summarized. The project plan includes evolutionary technology development for both nuclear thermal and nuclear electric propulsion systems.

  18. Rocket Scientist for a Day: Investigating Alternatives for Chemical Propulsion

    Science.gov (United States)

    Angelin, Marcus; Rahm, Martin; Gabrielsson, Erik; Gumaelius, Lena

    2012-01-01

    This laboratory experiment introduces rocket science from a chemistry perspective. The focus is set on chemical propulsion, including its environmental impact and future development. By combining lecture-based teaching with practical, theoretical, and computational exercises, the students get to evaluate different propellant alternatives. To…

  19. In-flight calibration of mesospheric rocket plasma probes.

    Science.gov (United States)

    Havnes, Ove; Hartquist, Thomas W; Kassa, Meseret; Morfill, Gregor E

    2011-07-01

    Many effects and factors can influence the efficiency of a rocket plasma probe. These include payload charging, solar illumination, rocket payload orientation and rotation, and dust impact induced secondary charge production. As a consequence, considerable uncertainties can arise in the determination of the effective cross sections of plasma probes and measured electron and ion densities. We present a new method for calibrating mesospheric rocket plasma probes and obtaining reliable measurements of plasma densities. This method can be used if a payload also carries a probe for measuring the dust charge density. It is based on that a dust probe's effective cross section for measuring the charged component of dust normally is nearly equal to its geometric cross section, and it involves the comparison of variations in the dust charge density measured with the dust detector to the corresponding current variations measured with the electron and/or ion probes. In cases in which the dust charge density is significantly smaller than the electron density, the relation between plasma and dust charge density variations can be simplified and used to infer the effective cross sections of the plasma probes. We illustrate the utility of the method by analysing the data from a specific rocket flight of a payload containing both dust and electron probes.

  20. Adventures in Rocket Science. EG-2007-12-179-MSFC

    Science.gov (United States)

    Huegele, Vince; Hill, Kristy; Terry, Brenda

    2008-01-01

    This guide was prepared as a tool useful for informal education venues (4-H, Boys and Girls Clubs, Boy Scouts, Girl Scouts, etc.), science clubs and related programs, and can be adopted for formal education settings. An exciting and productive study in rocket science can be implemented using the selected activities for the above-mentioned…

  1. STS-27 Atlantis, OV-104, solid rocket booster (SRB) inspection

    Science.gov (United States)

    1988-01-01

    Engineers, kneeling inside a hollow solid rocket booster (SRB), closely inspect the SRB segments and seams in the Kennedy Space Center (KSC) rotation and processing facility. The SRB will be used on STS-27 Atlantis, Orbiter Vehicle (OV) 104. The booster segments were transported via rail car from Morton Thiokol's Utah manufacturing plant. View provided by KSC with alternate number KSC-88PC-492.

  2. Comet mission is blown off course by faulty rocket

    CERN Multimedia

    Henderson, M

    2003-01-01

    ESA has announced that the launch of the Rosetta probe, has been delayed indefinitely because of problems with the unreliable Ariane-5 rocket on which it was to fly. The project will now have to be redesigned completely to target a different comet at a later date (1/2 page).

  3. Structural Dynamics of Filament-Wound Booster Rockets

    Science.gov (United States)

    Bugg, F. M.

    1987-01-01

    Report summarizes program of measurements and calculations of vibrations in filament-wound composite models of Space Shuttle solid-rocket boosters. Vibrational behavior predicted by finite-element computer model of structural dynamics correlates well with data from tests on full- and quarter-scale models. Computer model developed with NASTRAN general-purpose structural-analysis computer code.

  4. Burn Rate Modelling of Solid Rocket Propellants (Short Communication

    Directory of Open Access Journals (Sweden)

    A.R. Kulkarni

    1998-01-01

    Full Text Available A generalised model of burning of a solid rocket propellant based on kinetics of propellant hasbeen developed. A complete set of variables has been formed after examining the existing models.Buckingham theorem provides the functional form of the model, such that the existing models are thesubcases of this generalised model. This proposed model has been validated by an experimental data.

  5. Radiation/convection coupling in rocket motors and plumes

    Science.gov (United States)

    Farmer, R. C.; Saladino, A. J.

    1993-01-01

    The three commonly used propellant systems - H2/O2, RP-1/O2, and solid propellants - primarily radiate as molecular emitters, non-scattering small particles, and scattering larger particles, respectively. Present technology has accepted the uncoupling of the radiation analysis from that of the flowfield. This approximation becomes increasingly inaccurate as one considers plumes, interior rocket chambers, and nuclear rocket propulsion devices. This study will develop a hierarchy of methods which will address radiation/convection coupling in all of the aforementioned propulsion systems. The nature of the radiation/convection coupled problem is that the divergence of the radiative heat flux must be included in the energy equation and that the local, volume-averaged intensity of the radiation must be determined by a solution of the radiative transfer equation (RTE). The intensity is approximated by solving the RTE along several lines of sight (LOS) for each point in the flowfield. Such a procedure is extremely costly; therefore, further approximations are needed. Modified differential approximations are being developed for this purpose. It is not obvious which order of approximations are required for a given rocket motor analysis. Therefore, LOS calculations have been made for typical rocket motor operating conditions in order to select the type approximations required. The results of these radiation calculations, and the interpretation of these intensity predictions are presented herein.

  6. Machine learning of fault characteristics from rocket engine simulation data

    Science.gov (United States)

    Ke, Min; Ali, Moonis

    1990-01-01

    Transformation of data into knowledge through conceptual induction has been the focus of our research described in this paper. We have developed a Machine Learning System (MLS) to analyze the rocket engine simulation data. MLS can provide to its users fault analysis, characteristics, and conceptual descriptions of faults, and the relationships of attributes and sensors. All the results are critically important in identifying faults.

  7. The Effect of Resistance on Rocket Injector Acoustics

    Science.gov (United States)

    Morgan, C. J.

    2015-01-01

    Combustion instability, where unsteady heat release couples with acoustic modes, has long been an area of concern in liquid rocket engines. Accurate modeling of the acoustic normal modes of the combustion chamber is important to understanding and preventing combustion instability. The injector resistance can have a significant influence on the chamber normal mode shape, and hence on the system stability.

  8. First results of the Auroral Turbulance II rocket experiment

    DEFF Research Database (Denmark)

    Danielides, M.A.; Ranta, A.; Ivchenco, N.;

    1999-01-01

    The Auroral Turbulance II sounding rocket was launched on February 11, 1997 into moderately active nightside aurora from the Poker Flat Research Range, Alaska, US. The experiment consisted of three independent, completely instrumented payloads launched by a single vehicle. The aim of the experiment...

  9. Selecting and using materials for a nuclear rocket engine reactor

    Energy Technology Data Exchange (ETDEWEB)

    Lanin, Anatolii G; Fedik, Ivan I [' Luch' Research and Production Association, Podol' sk, Moscow region (Russian Federation)

    2011-03-31

    This paper provides a historical account of how the nuclear rocket engine reactor was created and discusses the problem of selecting materials for a gas environment at a temperature of up to 3100 K and energy release of 30 MW per liter. (from the history of physics)

  10. Multivariable optimization of liquid rocket engines using particle swarm algorithms

    Science.gov (United States)

    Jones, Daniel Ray

    Liquid rocket engines are highly reliable, controllable, and efficient compared to other conventional forms of rocket propulsion. As such, they have seen wide use in the space industry and have become the standard propulsion system for launch vehicles, orbit insertion, and orbital maneuvering. Though these systems are well understood, historical optimization techniques are often inadequate due to the highly non-linear nature of the engine performance problem. In this thesis, a Particle Swarm Optimization (PSO) variant was applied to maximize the specific impulse of a finite-area combustion chamber (FAC) equilibrium flow rocket performance model by controlling the engine's oxidizer-to-fuel ratio and de Laval nozzle expansion and contraction ratios. In addition to the PSO-controlled parameters, engine performance was calculated based on propellant chemistry, combustion chamber pressure, and ambient pressure, which are provided as inputs to the program. The performance code was validated by comparison with NASA's Chemical Equilibrium with Applications (CEA) and the commercially available Rocket Propulsion Analysis (RPA) tool. Similarly, the PSO algorithm was validated by comparison with brute-force optimization, which calculates all possible solutions and subsequently determines which is the optimum. Particle Swarm Optimization was shown to be an effective optimizer capable of quick and reliable convergence for complex functions of multiple non-linear variables.

  11. U.S./CIS eye joint nuclear rocket venture

    Science.gov (United States)

    Clark, John S.; Mcilwain, Melvin C.; Smetanikov, Vladimir; D'Yakov, Evgenij K.; Pavshuk, Vladimir A.

    1993-01-01

    An account is given of the significance for U.S. spacecraft development of a nuclear thermal rocket (NTR) reactor concept that has been developed in the (formerly Soviet) Commonwealth of Independent States (CIS). The CIS NTR reactor employs a hydrogen-cooled zirconium hydride moderator and ternary carbide fuels; the comparatively cool operating temperatures associated with this design promise overall robustness.

  12. Polar 5, a Norwegian US electron accelerator sounding rocket

    International Nuclear Information System (INIS)

    A technical description of a mother daughter experiment including an electron gun is given. The payload was launched by a Nike/Tomahawk rocket from Andenes, North-Norway near 2030 local time on February 1, 1976. A few preliminary observations obtained by the HF-wave propagation experiment, the retarding potential analyzer and the energetic electron counters are be presented

  13. ATLAS experiment : mapping the secrets of the universe

    CERN Multimedia

    ATLAS Outreach

    2010-01-01

    This 4 page color brochure describes ATLAS and the LHC, the ATLAS inner detector, calorimeters, muon spectrometer, magnet system, a short definition of the terms "particles," "dark matter," "mass," "antimatter." It also explains the ATLAS collaboration and provides the ATLAS website address with some images of the detector and the ATLAS collaboration at work.

  14. World Ocean Atlas 2005, Temperature

    Data.gov (United States)

    National Oceanic and Atmospheric Administration, Department of Commerce — World Ocean Atlas 2005 (WOA05) is a set of objectively analyzed (1° grid) climatological fields of in situ temperature, salinity, dissolved oxygen, Apparent Oxygen...

  15. ATLAS online data quality monitoring

    CERN Document Server

    Cuenca Almenar, C; The ATLAS collaboration; Hadavand, H; Ilchenko, Y; Kolos, S; Slagle, K; Taffard, A

    2010-01-01

    Every minute the ATLAS detector is taking data, the monitoring framework serves several thousands physics events to monitoring data analysis applications, handles millions of histogram updates coming from thousands applications, executes over forty thousand advanced data quality checks for a subset of those histograms, displays histograms and results of these checks on several dozens of monitors installed in main and satellite ATLAS control rooms. The online data quality monitoring system has been of great help in providing quick feedback to the subsystems about the functioning and performance of the different parts of ATLAS by providing a configurable easy and fast visualization of all this information. The Data Quality Monitoring Display (DQMD) is a visualization tool for the automatic data quality assessment of the ATLAS experiment. It is the interface through which the shift crew and experts can validate the quality of the data being recorded or processed, be warned of problems related to data quality, an...

  16. Wheels lining up for ATLAS

    CERN Multimedia

    2003-01-01

    On 30 October, the mechanics test assembly of the central barrel of the ATLAS tile hadronic calorimeter was completed in building 185. It is the second wheel for the Tilecal completely assembled this year.

  17. Dartmouth Atlas of Health Care

    Data.gov (United States)

    U.S. Department of Health & Human Services — For more than 20 years, the Dartmouth Atlas Project has documented glaring variations in how medical resources are distributed and used in the United States. The...

  18. Nuclear Receptor Signaling Atlas (NURSA)

    Data.gov (United States)

    U.S. Department of Health & Human Services — The Nuclear Receptor Signaling Atlas (NURSA) is designed to foster the development of a comprehensive understanding of the structure, function, and role in disease...

  19. World Ocean Atlas 2005, Salinity

    Data.gov (United States)

    National Oceanic and Atmospheric Administration, Department of Commerce — World Ocean Atlas 2005 (WOA05) is a set of objectively analyzed (1° grid) climatological fields of in situ temperature, salinity, dissolved oxygen, Apparent Oxygen...

  20. World Ocean Atlas 2005, Temperature

    Data.gov (United States)

    National Oceanic and Atmospheric Administration, Department of Commerce — World Ocean Atlas 2005 (WOA05) is a set of objectively analyzed (1° grid) climatological fields of in situ temperature, salinity, dissolved oxygen, Apparent Oxygen...

  1. Two new wheels for ATLAS

    CERN Multimedia

    2002-01-01

    Juergen Zimmer (Max Planck Institute), Roy Langstaff (TRIUMF/Victoria) and Sergej Kakurin (JINR), in front of one of the completed wheels of the ATLAS Hadronic End Cap Calorimeter. A decade of careful preparation and construction by groups in three continents is nearing completion with the assembly of two of the four 4 m diameter wheels required for the ATLAS Hadronic End Cap Calorimeter. The first two wheels have successfully passed all their mechanical and electrical tests, and have been rotated on schedule into the vertical position required in the experiment. 'This is an important milestone in the completion of the ATLAS End Cap Calorimetry' explains Chris Oram, who heads the Hadronic End Cap Calorimeter group. Like most experiments at particle colliders, ATLAS consists of several layers of detectors in the form of a 'barrel' and two 'end caps'. The Hadronic Calorimeter layer, which measures the energies of particles such as protons and pions, uses two techniques. The barrel part (Tile Calorimeter) cons...

  2. ATLAS recognises its best suppliers

    CERN Multimedia

    Jenni, P

    The ATLAS Collaboration has recently rewarded two of its suppliers in the construction of very major detector components, fabricated in Japan. The ATLAS Supplier Award in recognition of excellent supplier performance was attributed on 2nd September 2002 during a ceremony in Hall 180 to Kawasaki Heavy Industries, while Toshiba Corporation received the award two months before at their headquarters in Japan. The ATLAS experiment will become a reality thanks to a large international collaboration partnership. The industrial suppliers for the components all over the world play a major role in the construction of this gigantic jigsaw for the LHC. And sometimes they perform so well, that their work deserves specially to be recognised. This is the case for Kawasaki Heavy Industries and Toshiba Corporation, producers of the Liquid Argon Barrel Cryostat and of the Superconducting Central Solenoid, respectively. With these awards, the ATLAS Collaboration wants to congratulate Kawasaki and Toshiba for fulfilling the hi...

  3. ATLAS Civil Engineering Point 1

    CERN Multimedia

    2001-01-01

    Different phases of realisation to Point 1: zone of the ATLAS experiment 14-02-2001Realising anchorage, isolations and scaffoldings at UX 15 18-04-2001Concreting the arch and posing the metal reinforcements at UX 15

  4. BioFuels Atlas (Presentation)

    Energy Technology Data Exchange (ETDEWEB)

    Moriarty, K.

    2011-02-01

    Presentation for biennial merit review of Biofuels Atlas, a first-pass visualization tool that allows users to explore the potential of biomass-to-biofuels conversions at various locations and scales.

  5. ATLAS software packaging

    Science.gov (United States)

    Rybkin, Grigory

    2012-12-01

    Software packaging is indispensable part of build and prerequisite for deployment processes. Full ATLAS software stack consists of TDAQ, HLT, and Offline software. These software groups depend on some 80 external software packages. We present tools, package PackDist, developed and used to package all this software except for TDAQ project. PackDist is based on and driven by CMT, ATLAS software configuration and build tool, and consists of shell and Python scripts. The packaging unit used is CMT project. Each CMT project is packaged as several packages—platform dependent (one per platform available), source code excluding header files, other platform independent files, documentation, and debug information packages (the last two being built optionally). Packaging can be done recursively to package all the dependencies. The whole set of packages for one software release, distribution kit, also includes configuration packages and contains some 120 packages for one platform. Also packaged are physics analysis projects (currently 6) used by particular physics groups on top of the full release. The tools provide an installation test for the full distribution kit. Packaging is done in two formats for use with the Pacman and RPM package managers. The tools are functional on the platforms supported by ATLAS—GNU/Linux and Mac OS X. The packaged software is used for software deployment on all ATLAS computing resources from the detector and trigger computing farms, collaboration laboratories computing centres, grid sites, to physicist laptops, and CERN VMFS and covers the use cases of running all applications as well as of software development.

  6. Parallelization of Rocket Engine Simulator Software (PRESS)

    Science.gov (United States)

    Cezzar, Ruknet

    1998-01-01

    /18/99). At the least, the research would need to be done on Windows 95/Windows NT based platforms. Moreover, with the acquisition of Lahey Fortran package for PC platform, and the existing Borland C + + 5. 0, we can do work on C + + wrapper issues. We have carefully studied the blueprint for Space Transportation Propulsion Integrated Design Environment for the next 25 years [13] and found the inclusion of HBCUs in that effort encouraging. Especially in the long period for which a map is provided, there is no doubt that HBCUs will grow and become better equipped to do meaningful research. In the shorter period, as was suggested in our presentation at the HBCU conference, some key decisions regarding the aging Fortran based software for rocket propellants will need to be made. One important issue is whether or not object oriented languages such as C + + or Java should be used for distributed computing. Whether or not "distributed computing" is necessary for the existing software is yet another, larger, question to be tackled with.

  7. Pulse Detonation Rocket MHD Power Experiment

    Science.gov (United States)

    Litchford, Ron J.; Cook, Stephen (Technical Monitor)

    2002-01-01

    A pulse detonation research engine (MSFC (Marshall Space Flight Center) Model PDRE (Pulse Detonation Rocket Engine) G-2) has been developed for the purpose of examining integrated propulsion and magnetohydrodynamic power generation applications. The engine is based on a rectangular cross-section tube coupled to a converging-diverging nozzle, which is in turn attached to a segmented Faraday channel. As part of the shakedown testing activity, the pressure wave was interrogated along the length of the engine while running on hydrogen/oxygen propellants. Rapid transition to detonation wave propagation was insured through the use of a short Schelkin spiral near the head of the engine. The measured detonation wave velocities were in excess of 2500 m/s in agreement with the theoretical C-J velocity. The engine was first tested in a straight tube configuration without a nozzle, and the time resolved thrust was measured simultaneously with the head-end pressure. Similar measurements were made with the converging-diverging nozzle attached. The time correlation of the thrust and head-end pressure data was found to be excellent. The major purpose of the converging-diverging nozzle was to configure the engine for driving an MHD generator for the direct production of electrical power. Additional tests were therefore necessary in which seed (cesium-hydroxide dissolved in methanol) was directly injected into the engine as a spray. The exhaust plume was then interrogated with a microwave interferometer in an attempt to characterize the plasma conditions, and emission spectroscopy measurements were also acquired. Data reduction efforts indicate that the plasma exhaust is very highly ionized, although there is some uncertainty at this time as to the relative abundance of negative OH ions. The emission spectroscopy data provided some indication of the species in the exhaust as well as a measurement of temperature. A 24-electrode-pair segmented Faraday channel and 0.6 Tesla permanent

  8. Nuclear Thermal Rocket (NTR) Development Risk Communication

    Science.gov (United States)

    Kim, Tony

    2014-01-01

    There are clear advantages of development of a Nuclear Thermal Rocket (NTR) for a crewed mission to Mars. NTR for in-space propulsion enables more ambitious space missions by providing high thrust at high specific impulse (approximately 900 sec) that is 2 times the best theoretical performance possible for chemical rockets. Missions can be optimized for maximum payload capability to take more payload with reduced total mass to orbit; saving cost on reduction of the number of launch vehicles needed. Or missions can be optimized to minimize trip time significantly to reduce the deep space radiation exposure to the crew. NTR propulsion technology is a game changer for space exploration. However, "NUCLEAR" is a word that is feared and vilified by some groups and the hostility towards development of any nuclear systems can meet great opposition by the public as well as from national leaders and people in authority. Communication of nuclear safety will be critical to the success of the development of the NTR. Why is there a fear of nuclear? A bomb that can level a city is a scary weapon. The first and only times the Nuclear Bomb was used in a war was on Hiroshima and Nagasaki during World War 2. The "Little Boy" atomic bomb was dropped on Hiroshima on August 6, 1945 and the "Fat Man" on Nagasaki 3 days later on August 9th. Within the first 4 months of bombings, 90- 166 thousand people died in Hiroshima and 60-80 thousand died in Nagasaki. It is important to note for comparison that over 500 thousand people died and 5 million made homeless due to strategic bombing (approximately 150 thousand tons) of Japanese cities and war assets with conventional non-nuclear weapons between 1942- 1945. A major bombing campaign of "firebombing" of Tokyo called "Operation Meetinghouse" on March 9 and 10 consisting of 334 B-29's dropped approximately1,700 tons of bombs around 16 square mile area and over 100 thousand people have been estimated to have died. The declaration of death is very

  9. The ATLAS Simulation Software

    CERN Document Server

    Marshall, Z

    2008-01-01

    We present the status of the ATLAS Simulation Pro ject. Recent detector description improvements have focussed on commissioning layouts, implementation of inert material, and comparisons to the as-built detector. Core Simulation is reviewed with a focus on parameter optimizations, physics list choices, visualization, large-scale production, and validation. A fast simulation is also briefly described, and its performance is evaluated with respect to the full Simulation. Digitization, the last step of the Monte Carlo chain, is described, including developments in pile up and data overlay.

  10. VH WW in ATLAS

    CERN Document Server

    Kinghorn-taenzer, Joseph Peter; The ATLAS collaboration

    2015-01-01

    A search for Higgs boson production in association with a W or Z boson, in the H -> WW decay channel, is performed with a data sample collected with the ATLAS detector at the LHC in proton– proton collisions at centre-of-mass energies sqrt(s) = 7 TeV and 8 TeV, corresponding to integrated luminosities of 4.5 fb-1 and 20.3 fb-1, respectively. The WH production mode is studied in two-lepton and three-lepton final states, while two-lepton and four-lepton final states are used to search for the ZH production mode.

  11. Atlas of liver imaging

    International Nuclear Information System (INIS)

    This atlas is an outcome of an IAEA co-ordinated research programme. In addition to Japan, nine other Asian countries participated in the project and 293 liver scintigrams (116 from Japanese institutions and 177 from seven Asian countries) were evaluated by physicians from the participating Asian countries. The computer analysis of the scan findings of the individual physicians was carried out and individual scores have been separately tabulated for: (a) scan abnormality; (b) space occupying lesions; (c) cirrhosis and (d) diffuse liver diseases like hepatitis. Refs, figs and tabs

  12. ATLAS TV PROJECT

    CERN Multimedia

    2005-01-01

    CPPM Laboratory Marseille Starting with the Workshop- adding modules to the strip 00:09:19 Exterior-entering the lab site by car, Sascha Rosanov and a PR lady walking, Lab sign on building -Physique des Particules de Marseille 00:20:00 Interviews of the ATLAS pixel work for bio-mediacal research 00:34:00 Interview of Roy Aleksov, Head of CPPM Laboratory, Working in international team, working with CERN and GRID The rest of the film inclusdes lab testingand some exterior shots.

  13. Dark Matter in ATLAS

    CERN Document Server

    Resconi, Silvia; The ATLAS collaboration

    2016-01-01

    An overview of Dark Matter searches with the ATLAS experiment at the Large Hadron Collider (LHC) is shown. Results of Mono-X analyses requiring large missing transverse momentum and a recoiling detectable physics object (X) are reported. The data were collected in proton-proton collisions at a centre-of-mass energy of 13 TeV. The observed data are in agreement with the expected Standard Model backgrounds for all analyses described. Exclusion limits are presented for Dark Matter models including pair production of Dark Matter candidates.

  14. Supersymmetry searches in ATLAS

    CERN Document Server

    Meloni, Federico; The ATLAS collaboration

    2015-01-01

    This document summarises recent ATLAS results for searches for supersymmetric particles using LHC proton-proton collision data. Despite the absence of experimental evidence, weak scale supersymmetry remains one of the best motivated and studied Standard Model extensions. We consider both R-Parity conserving and R-Parity violating SUSY scenarios. The searches involve final states including jets, missing transverse momentum, light leptons, taus or photons, as well as long-lived particle signatures. Sensitivity projections for the data that will be collected in 2015 are also presented.

  15. Supersymmetry searches in ATLAS

    CERN Document Server

    Meloni, Federico; The ATLAS collaboration

    2015-01-01

    Despite the absence of experimental evidence, weak scale supersymmetry remains one of the best motivated and studied Standard Model extensions. This talk summarises recent ATLAS results for searches for supersymmetric (SUSY) particles. Weak and strong production in both R-Parity conserving and R-Parity violating SUSY scenarios are considered. The searches involved final states including jets, missing transverse momentum, light leptons, taus or photons, as well as long-lived particle signatures. Sensitivity projections for the data that will be collected in 2015 are also presented.

  16. QCD Measurements at ATLAS

    CERN Document Server

    Hubacek, Zdenek; The ATLAS collaboration

    2016-01-01

    This paper presents recent QCD related measurements from the ATLAS Experiment at the LHC at CERN. The results on the total inelastic cross- section, charged particle production, jet production, photon production, and W-, Z-bosons productions are briefly summarized. The measurments are performed at different center-of-mass energies sqrt(s) = 7, 8, and 13 TeV. The measured cross-sections are generally found to be in agreement with the expectations from the Standard Model within the estimated uncertainties.

  17. Dark Matter in ATLAS

    CERN Document Server

    Resconi, Silvia; The ATLAS collaboration

    2016-01-01

    Results of Dark Matter searches in mono-X analysis with the ATLAS experiment at the Large Hadron Collider are reported. The data were collected in proton–proton collisions at a centre-of-mass energy of 13 TeV and correspond to an integrated luminosity of 3.2 fb-1. A description of the main characteristics of each analysis and how the main backgrounds are estimated is shown. The observed data are in agreement with the expected Standard Model backgrounds for all analysis described. Exclusion limits are presented for Dark Matter models including pair production of dark matter candidates.

  18. Surveying the ATLAS cavern

    CERN Multimedia

    Laurent Guiraud

    2000-01-01

    The cathedral-like cavern into which the ATLAS experiment will be lowered and installed forms a vital part of the engineering work at CERN in preparation for the new LHC accelerator. This cavern, being measured by surveyors in these images, will have one of the largest spans of any man-made underground structure. The massive 46X25X25 cubic metre detector will be the largest of its type in the world when it is completed for the LHC start-up in 2008.

  19. ATLAS TV PROJECT

    CERN Multimedia

    2005-01-01

    Budker Nuclear Physics Institute, Novosibirsk Sequence 1 Reception for Markus Nordberg and Andrew Millington by about 20 physicists from the Budker Nuclear Physics Institute Host: Yuri Tikhonov Various short talks and exchanges, with coffee Sequence 2 Visit to BINP Facilities Tikhonov and Nordberg walking and talking Visit to electron accelerator, old solar detector Sequence 3 Visit to BNIP workshops Work on big wheel segments shots over-exposed Work on Atlas coils LHC Magnets Men playing chess, exterior shots of Tikhonov, Nordberg arriving Sequence 4 Shots from car of journey from workshop to main BNIP building.

  20. Exotics searches in ATLAS

    CERN Document Server

    Vranjes, N; The ATLAS collaboration

    2016-01-01

    We report on the latest searches for (non-SUSY) Beyond Standard Model phenomena performed with the ATLAS detector. The searches have been performed with the data from proton-proton collisions at a centre-of-mass energy of 7 TeV collected in 2010 and 2011. Various experimental signatures have been studied involving reconstruction and measurement of leptons, photons, jets, missing transverse energy, as well as reconstruction of top quarks. For most of the signatures, the experimental reach is significantly increased with respect to previous results.

  1. Top Physics at ATLAS

    OpenAIRE

    Barisonzi, Marcello

    2005-01-01

    The Large Hadron Collider LHC is a top quark factory: due to its high design luminosity, LHC will produce about 200 millions of top quarks per year of operation. The large amount of data will allow to study with great precision the properties of the top quark, most notably cross-section, mass and spin. The Top Physics Working Group has been set up at the ATLAS experiment, to evaluate the precision reach of physics measurements in the top sector, and to study the systematic effects of the ATLA...

  2. The Genome Atlas Resource

    DEFF Research Database (Denmark)

    Azam Qureshi, Matloob; Rotenberg, Eva; Stærfeldt, Hans Henrik;

    2010-01-01

    Abstract. The Genome Atlas is a resource for addressing the challenges of synchronising prokaryotic genomic sequence data from multiple public repositories. This resource can integrate bioinformatic analyses in various data format and quality. Existing open source tools have been used together...... with scripts and algorithms developed in a variety of programming languages at the Centre for Biological Sequence Analysis in order to create a three-tier software application for genome analysis. The results are made available via a web interface developed in Java, PHP and Perl CGI. User...

  3. 27 CFR 9.140 - Atlas Peak.

    Science.gov (United States)

    2010-04-01

    ... 27 Alcohol, Tobacco Products and Firearms 1 2010-04-01 2010-04-01 false Atlas Peak. 9.140 Section... THE TREASURY LIQUORS AMERICAN VITICULTURAL AREAS Approved American Viticultural Areas § 9.140 Atlas Peak. (a) Name. The name of the viticultural area described in this section is “Atlas Peak.”...

  4. The PeptideAtlas Project

    OpenAIRE

    Deutsch, Eric W.

    2010-01-01

    PeptideAtlas is a multi-species compendium of peptides observed with tandem mass spectrometry methods. Raw mass spectrometer output files are collected from the community and reprocessed through a uniform analysis and validation pipeline that continues to advance. The results are loaded into a database and the information derived from the raw data is returned to the community via several web-based data exploration tools. The PeptideAtlas resource is useful for experiment planning, improving g...

  5. ATLAS Overview Week 2009 Barcelona

    CERN Multimedia

    Claudia Marcelloni

    2009-01-01

    From October 5th to October 9th about 400 physicists from the ATLAS Collaboration met in Barcelona (Catalonia) to discuss the status of the experiment. The event was organized by the Institut de Física d'Altes Energies (IFAE), a member of the ATLAS Collaboration. Besides the Scientific program, few social events were organized, such as Reception at the Palau de Pedralbes, a visit to the Fundacio Joan Miro and a social dinner at Maremagnunm hall.

  6. ATLAS discoveries of optical transients

    Science.gov (United States)

    Tonry, J.; Denneau, L.; Stalder, B.; Heinze, A.; Sherstyuk, A.; Rest, A.; Smith, K. W.; Smartt, S. J.

    2016-09-01

    We report the following transients found by the ATLAS survey (see Tonry et al. ATel #8680). ATLAS is a twin 0.5m telescope system on Haleakala and Mauna Loa. The first unit is operational on Haleakala is robotically surveying the sky. Two filters are used, cyan and orange (denoted c and o, all mags in AB system), more information is on http://www.fallingstar.com.

  7. Equity valuation : Atlas Copco AB

    OpenAIRE

    Santos, Ricardo Manuel Castro Lopes Alba

    2016-01-01

    This Dissertation presents a literature review of some of the most appraised theories on equity valuation models. A thoughtful analysis is made, presenting the main advantages and restrictions of each model and setting the path for a discussion about improvements to be made on this field of study. A practical implementation follows, proposing a fair value estimation of Atlas Copco AB shares. Atlas Copco is a Swedish-based capital goods company, operating across four differen...

  8. ATLAS discoveries of optical transients

    Science.gov (United States)

    Tonry, J.; Denneau, L.; Stalder, B.; Heinze, A.; Sherstyuk, A.; Rest, A.; Smith, K. W.; Smartt, S. J.

    2016-06-01

    We report the following transients found by the ATLAS survey (see Tonry et al. ATel #8680). ATLAS is a twin 0.5m telescope system on Haleakala and Mauna Loa. The first unit is operational on Haleakala is robotically surveying the sky. Two filters are used, cyan and orange (denoted c and o, all mags in AB system), more information is on http://www.fallingstar.com.

  9. Transporting the first ATLAS toroid

    CERN Multimedia

    Maximilien Brice

    2004-01-01

    The first coil for the ATLAS toroid magnet is transported from its assembly hall at the CERN Meyrin site to the storage hall above the ATLAS cavern. This involves driving the massive transportation vehicle first through the Meyrin site and then across a main road only metres from the France-Swiss border. Eight magnets in total will be transported in this way before being lowered into the experimental cavern where they will be mounted in a huge ring surrounding the detector.

  10. SLHC and ATLAS, Initial Plans

    CERN Document Server

    Nessi, M

    2008-01-01

    The recent developments in the plans and scenarios proposed by the LHC machine experts towards the SLHC, have triggered various concerns and reserves in the ATLAS community. In particular the eventual need to insert dipoles, quadrupoles and protection elements inside the detector creates major concerns, because of its complex logistics and the risk of reducing the effectiveness of the ATLAS internal radiation shielding. Justifications and constraints on how to best use this space are given.

  11. ATLAS discoveries of optical transients

    Science.gov (United States)

    Tonry, J.; Denneau, L.; Stalder, B.; Heinze, A.; Sherstyuk, A.; Rest, A.; Smith, K. W.; Smartt, S. J.

    2016-08-01

    We report the following transients found by the ATLAS survey (see Tonry et al. ATel #8680). ATLAS is a twin 0.5m telescope system on Haleakala and Mauna Loa. The first unit is operational on Haleakala is robotically surveying the sky. Two filters are used, cyan and orange (denoted c and o, all mags in AB system), more information is on http://www.fallingstar.com.

  12. ATLAS discoveries of optical transients

    Science.gov (United States)

    Tonry, J.; Denneau, L.; Stalder, B.; Heinze, A.; Sherstyuk, A.; Rest, A.; Smith, K. W.; Smartt, S. J.

    2016-10-01

    We report the following transients found by the ATLAS survey (see Tonry et al. ATel #8680). ATLAS is a twin 0.5m telescope system on Haleakala and Mauna Loa. The first unit is operational on Haleakala is robotically surveying the sky. Two filters are used, cyan and orange (denoted c and o, all mags in AB system), more information is on http://www.fallingstar.com.

  13. ATLAS Civil Engineering Point 1

    CERN Multimedia

    Jean-Claude Vialis

    2000-01-01

    Different phases of realisation to Point 1 : zone of the ATLAS experiment The film is about the excavation work in the cavern and tunnels of ATLAS experiment in the point 1. You can see people working for iron mounting at the side of the pit where the parts of the detector will be lowered in the future. Partly the film concentrates the USA 15 and the work done there.

  14. Characterization of abandoned rocket body families for active removal

    Science.gov (United States)

    Pardini, Carmen; Anselmo, Luciano

    2016-09-01

    A new ranking index was developed and applied to a wide set of rocket body families, characterized by stage dry masses greater than 500 kg and by the presence of at least 5 stages abandoned in LEO. The upper stages selected accounted for more than 80% of the unclassified rocket bodies in LEO and nearly 95% of the associated dry mass. The detailed results obtained for 657 objects clearly identified the most critical altitude-inclination bands and stage models, to be targeted first if and when a debris remediation strategy including the active removal of intact abandoned objects were deemed necessary. Apart from the evaluation of the criticality regarding the long-term evolution of the debris environment, resulting in a priority listing for optimal active removal, the application of the new ranking index is not limited to debris remediation. In fact, if applied before launch to spacecraft and rocket bodies to be disposed in orbit, at the end of mission, it would provide an additional debris mitigation analysis tool for evaluating competing disposal options. Concerning the rocket bodies abandoned in LEO, 274 resulted to have a criticality equal or larger than the average intact object abandoned in an 800 km sun-synchronous orbit. Among them, 243 belonged to the Russian Federation and Ukraine, 25 to China, 5 to Europe and 1 to Japan. In addition to being concentrated in relatively few and narrow altitude-inclinations bands, the most numerous rocket body families often present a quite uniform distribution in right ascension of the ascending node, which is especially convenient for multiple target removal missions.

  15. Development of miniaturised low cost attitude determination system for sounding rockets

    Science.gov (United States)

    Bekkeng, Jan Kenneth; Booij, Wilfred; Moen, J.

    2005-08-01

    Spacecraft attitude (orientation) information is needed in order to transform scientific vector measurements in the reference frame of the rocket into a more meaningful Earth-fixed reference frame. By fusing data from a 3-axial magnetometer, a sun sensor and three rate gyros the rockets attitude can be determined (reconstructed). Since the system does not need to determine the attitude in real time (the attitude data is not used to control the rocket orientation), all data from the attitude sensors can be transmitted back to ground, where they are fused to estimate an absolute orientation of the rocket. A prototype inertial measurement unit and a miniature high accuracy lens-less sun sensor for spinning rocket is under development. A test version of both instruments will be launched on a single stage Hotel Payload sounding rocket from Andøya Rocket Range in July 2005.

  16. High Energy Density Additives for Hybrid Fuel Rockets to Improve Performance and Enhance Safety

    Science.gov (United States)

    Jaffe, Richard L.

    2014-01-01

    We propose a conceptual study of prototype strained hydrocarbon molecules as high energy density additives for hybrid rocket fuels to boost the performance of these rockets without compromising safety and reliability. Use of these additives could extend the range of applications for which hybrid rockets become an attractive alternative to conventional solid or liquid fuel rockets. The objectives of the study were to confirm and quantify the high enthalpy of these strained molecules and to assess improvement in rocket performance that would be expected if these additives were blended with conventional fuels. We confirmed the chemical properties (including enthalpy) of these additives. However, the predicted improvement in rocket performance was too small to make this a useful strategy for boosting hybrid rocket performance.

  17. Advanced small rocket chambers. Option 3: 110 1bf Ir-Re rocket, volume 1

    Science.gov (United States)

    Jassowski, Donald M.; Schoenman, Leonard

    1995-02-01

    This report describes the AJ10-221, a high performance Iridium-coated Rhenium (Ir-Re) 110 lbf (490N) welded rocket chamber with 286:1 area ratio nozzle. This engine was designed, built, and hot fired for over 6 hours on this program. It demonstrated an I(s) of 321.8 sec, which is 10 sec higher than conventional 110 lbf silicide coated Cb chambers now in use. The approach used in this portion of the program was to demonstrate the performance improvement that can be made by the elimination of fuel film cooling and the use of a high temperature (4000F) (2200C) iridium-coated rhenium (Ir-Re) rocket chamber. Detailed thermal, performance, mechanical, and dynamic design analyses of the full engine were conducted by Aerojet. Two Ir-Re chambers were built to the Aerojet design by Ultramet, using the chemical vapor deposition (CVD) process. Incorporation of a secondary mixing device or Boundary Layer Trip (BLT) within the combustion chamber (Aerojet Patents 4882904 and 4936091) results in improvement in flow uniformity, and a significant life and performance increase. The 110 lbf engine design was verified in bolt-up hardware tests at sea level and altitude. The effects of injector design on performance were studied. Two duplicate injectors were fabricated matching the preferred design and were demonstrated to be interchangeable in operation. One of these units was fabricated matching the preferred design and was demonstrated to be interchangeable in operation. One of these units was welded into a flight type thruster which was tested for an accumulated duration of 22,590 sec in 93 firings, one of which was a continuous burn of two hours. A design deficiency in the C-103 nozzle near the Re-Cb transition joint was discovered, studied and corrected design has been prepared. Workhardening studies have been conducted to investigate methods for increasing the low yield strength of the Re in the annealed conditions. An advanced 490N high performance engine has been demonstrated

  18. Advanced small rocket chambers. Option 3: 110 1bf Ir-Re rocket, volume 2

    Science.gov (United States)

    Jassowski, Donald M.; Schoenman, Leonard

    1995-02-01

    This is the second part of a two-part report that describes the AJ10-221, a high performance iridium-coated rhenium (Ir-Re) 110 lbf (490N) welded rocket chamber with 286:1 area ratio nozzle. This engine was designed, built, and hot fired for over 6 hours on this program. It demonstrated an I(s) of 321.8 sec, which is 10 sec higher than conventional 110 lbf silicide coated Cb chambers now in use. The approach used in this portion of the program was to demonstrate the performance improvement that can be made by the elimination of fuel film cooling and the use of a high temperature (4000 F) (2200 C) iridium-coated rhenium (Ir-Re) rocket chamber. Detailed thermal, performance, mechanical, and dynamic design analyses of the full engine were conducted by Aerojet. Two Ir-Re chambers were built to the Aerojet design by Ultramet, using the chemical vapor deposition (CVD) process. Incorporation of a secondary mixing device or Boundary Layer Trip (BLT) within the combustion chamber (Aerojet Patents 4882904 and 4936091) results in improvement in flow uniformity, and a significant life and performance increase. The 110 lbf engine design was verified in bolt-up hardware tests at sea level and altitude. The effects of injector design on performance were studied. Two duplicate injectors were fabricated matching the preferred design and were demonstrated to be interchangeable in operation. One of these units were welded into a flight type thruster which was tested for an accumulated duration of 22,590 sec in 93 firings, one of which was a continuous burn of two hours. A design deficiency in the C-103 nozzle near the Re-Cb transition joint was discovered, studied and corrected design has been prepared. Workhardening studies have been conducted to investigate methods for increasing the low yield strength of the Re in the annealed conditions. An advanced 490N high performance engine has been demonstrated which, when proven to be capable of withstanding launch vibration, is ready for

  19. ATLAS cloud R and D

    International Nuclear Information System (INIS)

    The computing model of the ATLAS experiment was designed around the concept of grid computing and, since the start of data taking, this model has proven very successful. However, new cloud computing technologies bring attractive features to improve the operations and elasticity of scientific distributed computing. ATLAS sees grid and cloud computing as complementary technologies that will coexist at different levels of resource abstraction, and two years ago created an R and D working group to investigate the different integration scenarios. The ATLAS Cloud Computing R and D has been able to demonstrate the feasibility of offloading work from grid to cloud sites and, as of today, is able to integrate transparently various cloud resources into the PanDA workload management system. The ATLAS Cloud Computing R and D is operating various PanDA queues on private and public resources and has provided several hundred thousand CPU days to the experiment. As a result, the ATLAS Cloud Computing R and D group has gained a significant insight into the cloud computing landscape and has identified points that still need to be addressed in order to fully utilize this technology. This contribution will explain the cloud integration models that are being evaluated and will discuss ATLAS' learning during the collaboration with leading commercial and academic cloud providers.

  20. ATLAS Award for Shield Supplier

    CERN Multimedia

    2004-01-01

    ATLAS technical coordinator Dr. Marzio Nessi presents the ATLAS supplier award to Vojtech Novotny, Director General of Skoda Hute.On 3 November, the ATLAS experiment honoured one of its suppliers, Skoda Hute s.r.o., of Plzen, Czech Republic, for their work on the detector's forward shielding elements. These huge and very massive cylinders surround the beampipe at either end of the detector to block stray particles from interfering with the ATLAS's muon chambers. For the shields, Skoda Hute produced 10 cast iron pieces with a total weight of 780 tonnes at a cost of 1.4 million CHF. Although there are many iron foundries in the CERN member states, there are only a limited number that can produce castings of the necessary size: the large pieces range in weight from 59 to 89 tonnes and are up to 1.5 metres thick.The forward shielding was designed by the ATLAS Technical Coordination in close collaboration with the ATLAS groups from the Czech Technical University and Charles University in Prague. The Czech groups a...

  1. ATLAS Cloud R&D

    Science.gov (United States)

    Panitkin, Sergey; Barreiro Megino, Fernando; Caballero Bejar, Jose; Benjamin, Doug; Di Girolamo, Alessandro; Gable, Ian; Hendrix, Val; Hover, John; Kucharczyk, Katarzyna; Medrano Llamas, Ramon; Love, Peter; Ohman, Henrik; Paterson, Michael; Sobie, Randall; Taylor, Ryan; Walker, Rodney; Zaytsev, Alexander; Atlas Collaboration

    2014-06-01

    The computing model of the ATLAS experiment was designed around the concept of grid computing and, since the start of data taking, this model has proven very successful. However, new cloud computing technologies bring attractive features to improve the operations and elasticity of scientific distributed computing. ATLAS sees grid and cloud computing as complementary technologies that will coexist at different levels of resource abstraction, and two years ago created an R&D working group to investigate the different integration scenarios. The ATLAS Cloud Computing R&D has been able to demonstrate the feasibility of offloading work from grid to cloud sites and, as of today, is able to integrate transparently various cloud resources into the PanDA workload management system. The ATLAS Cloud Computing R&D is operating various PanDA queues on private and public resources and has provided several hundred thousand CPU days to the experiment. As a result, the ATLAS Cloud Computing R&D group has gained a significant insight into the cloud computing landscape and has identified points that still need to be addressed in order to fully utilize this technology. This contribution will explain the cloud integration models that are being evaluated and will discuss ATLAS' learning during the collaboration with leading commercial and academic cloud providers.

  2. A computerized adjustable brain atlas

    International Nuclear Information System (INIS)

    A computerized brain atlas, adjustable to the patients anatomy, has been developed. It is primarily intended for use in positron emission tomography, but may also be employed in other fields utilizing neuro imaging, such as sterotactic surgery, transmission computerized tomography (CT) and magnetic resonance imaging (MRI). The atlas is based on anatomical information obtained from digitized cryosectioned brains. It can be adjusted to fit a wide range of images from individual brains with normal anatomy. The corresponding transformation is chosen so that the modified atlas agrees with a set of CT or NMR images of the patient. The computerized atlas can be used to improve the quantification and evaluation of PET data by: Aiding and improving the selection of regions of interests. Facilitating comparisons of functional image data from different individuals or groups of individuals. Facilitating the comparison of different examinations of the same patient, thus reducing the need of reproducible fixation systems. Providing external a priori anatomical information to be used in the image reconstruction. Improving the attenuation and scatter corrections. Aiding in selecting a suitable patient orientation during the PET study. By applying the inverse atlas transformation to PET data set it is possible to relate the PET information to the anatomy of the reference atlas. Reformatted PET data from different patients can thus be averaged, and averages from different categories of patients can be compared. The method will facilitate the identification of statistically significant differences in the PET information from different groups of patients. (orig.)

  3. Electrets used in measuring rocket exhaust effluents from the space shuttle's solid rocket booster during static test firing, DM-3

    Science.gov (United States)

    Susko, M.

    1979-01-01

    The purpose of this experimental research was to compare Marshall Space Flight Center's electrets with Thiokol's fixed flow air samplers during the Space Shuttle Solid Rocket Booster Demonstration Model-3 static test firing on October 19, 1978. The measurement of rocket exhaust effluents by Thiokol's samplers and MSFC's electrets indicated that the firing of the Solid Rocket Booster had no significant effect on the quality of the air sampled. The highest measurement by Thiokol's samplers was obtained at Plant 3 (site 11) approximately 8 km at a 113 degree heading from the static test stand. At sites 11, 12, and 5, Thiokol's fixed flow air samplers measured 0.0048, 0.00016, and 0.00012 mg/m3 of CI. Alongside the fixed flow measurements, the electret counts from X-ray spectroscopy were 685, 894, and 719 counts. After background corrections, the counts were 334, 543, and 368, or an average of 415 counts. An additional electred, E20, which was the only measurement device at a site approximately 20 km northeast from the test site where no power was available, obtained 901 counts. After background correction, the count was 550. Again this data indicate there was no measurement of significant rocket exhaust effluents at the test site.

  4. The ATLAS Event Builder

    CERN Document Server

    Vandelli, W; Battaglia, A; Beck, H P; Blair, R; Bogaerts, A; Bosman, M; Ciobotaru, M; Cranfield, R; Crone, G; Dawson, J; Dobinson, Robert W; Dobson, M; Dos Anjos, A; Drake, G; Ermoline, Y; Ferrari, R; Ferrer, M L; Francis, D; Gadomski, S; Gameiro, S; Gorini, B; Green, B; Haberichter, W; Haberli, C; Hauser, R; Hinkelbein, C; Hughes-Jones, R; Joos, M; Kieft, G; Klous, S; Korcyl, K; Kordas, K; Kugel, A; Leahu, L; Lehmann, G; Martin, B; Mapelli, L; Meessen, C; Meirosu, C; Misiejuk, A; Mornacchi, G; Müller, M; Nagasaka, Y; Negri, A; Pasqualucci, E; Pauly, T; Petersen, J; Pope, B; Schlereth, J L; Spiwoks, R; Stancu, S; Strong, J; Sushkov, S; Szymocha, T; Tremblet, L; Ünel, G; Vermeulen, J; Werner, P; Wheeler-Ellis, S; Wickens, F; Wiedenmann, W; Yu, M; Yasu, Y; Zhang, J; Zobernig, H; 2007 IEEE Nuclear Science Symposium and Medical Imaging Conference

    2008-01-01

    Event data from proton-proton collisions at the LHC will be selected by the ATLAS experiment in a three-level trigger system, which, at its first two trigger levels (LVL1+LVL2), reduces the initial bunch crossing rate of 40~MHz to $sim$3~kHz. At this rate, the Event Builder collects the data from the readout system PCs (ROSs) and provides fully assembled events to the Event Filter (EF). The EF is the third trigger level and its aim is to achieve a further rate reduction to $sim$200~Hz on the permanent storage. The Event Builder is based on a farm of O(100) PCs, interconnected via a Gigabit Ethernet to O(150) ROSs. These PCs run Linux and multi-threaded software applications implemented in C++. All the ROSs, and substantial fractions of the Event Builder and Event Filter PCs have been installed and commissioned. We report on performance tests on this initial system, which is capable of going beyond the required data rates and bandwidths for Event Building for the ATLAS experiment.

  5. ATLAS Future Upgrade

    CERN Document Server

    Vankov, Peter; The ATLAS collaboration

    2016-01-01

    After the successful operation at the center-of-mass energies of 7 and 8 TeV in 2010 - 2012, the LHC is ramped up and successfully took data at the center-of-mass energies of 13 TeV in 2015. Meanwhile, plans are actively advancing for a series of upgrades of the accelerator, culminating roughly ten years from now in the high-luminosity LHC (HL-LHC) project, delivering of the order of five times the LHC nominal instantaneous luminosity along with luminosity leveling. The ultimate goal is to extend the dataset from about few hundred fb−1 expected for LHC running to 3000 fb−1 by around 2035 for ATLAS and CMS. In parallel, the experiments need to be keep lockstep with the accelerator to accommodate running beyond the nominal luminosity this decade. Along with maintenance and consolidation of the detector in the past few years, ATLAS has added inner b-layer to its tracking system. The challenge of coping with the HL-LHC instantaneous and integrated luminosity, along with the associated radiation levels, requir...

  6. ATLAS Physicist in Space

    CERN Multimedia

    Bengt Lund-Jensen

    2007-01-01

    On December 9, the former ATLAS physicist Christer Fuglesang was launched into space onboard the STS-116 Space Shuttle flight from Kennedy Space Center in Florida. Christer worked on the development of the accordion-type liquid argon calorimeter and SUSY simulations in what eventually became ATLAS until summer 1992 when he became one out of six astronaut trainees with the European Space Agency (ESA). His selection out of a very large number of applicants from all over the ESA member states involved a number of tests in order to choose the most suitable candidates. As ESA astronaut Christer trained with the Russian Soyuz programme in Star City outside of Moscow from 1993 until 1996, when he moved to Houston to train for space shuttle missions with NASA. Christer belonged to the backup crew for the Euromir95 mission. After additional training in Russia, Christer qualified as ‘Soyuz return commander’ in 1998. Christer rerouting cables during his second space walk. (Photo: courtesy NASA) During...

  7. Spring comes for ATLAS

    CERN Multimedia

    Butin, F.

    2004-01-01

    (First published in the CERN weekly bulletin 24/2004, 7 June 2004.) A short while ago the ATLAS cavern underwent a spring clean, marking the end of the installation of the detector's support structures and the cavern's general infrastructure. The list of infrastructure to be installed in the ATLAS cavern from September 2003 was long: a thousand tonnes of mechanical structures spread over 13 storeys, two lifts, two 65-tonne overhead travelling cranes 25 metres above cavern floor, with a telescopic boom and cradle to access the remaining 10 metres of the cavern, a ventilation system for the 55 000 cubic metre cavern, a drainage system, a standard sprinkler system and an innovative foam fire-extinguishing system, as well as the external cryogenic system for the superconducting magnets and the liquid argon calorimeters (comprising, amongst other things, two helium refrigeration units, a nitrogen refrigeration unit and 5 km of piping for gaseous or liquid helium and nitrogen), not to mention the handling eq...

  8. ATLAS construction schedule

    CERN Multimedia

    Kotamaki, M

    The goal during the last few months has been to freeze and baseline as much as possible the schedules of various ATLAS systems and activities. The main motivations for the re-baselining of the schedules have been the new LHC schedule aiming at first collisions in early 2006 and the encountered delays in civil engineering as well as in the production of some of the detectors. The process was started by first preparing a new installation schedule that takes into account all the new external constraints and the new ATLAS staging scenario. The installation schedule version 3 was approved in the March EB and it provides the Ready For Installation (RFI) milestones for each system, i.e. the date when the system should be available for the start of the installation. TCn is now interacting with the systems aiming at a more realistic and resource loaded version 4 before the end of the year. Using the new RFI milestones as driving dates a new summary schedule has been prepared, or is under preparation, for each system....

  9. ATLAS DBM Module Qualification

    Energy Technology Data Exchange (ETDEWEB)

    Soha, Aria [Fermi National Accelerator Lab. (FNAL), Batavia, IL (United States); Gorisek, Andrej [J. Stefan Inst., Ljubljana (Slovenia); Zavrtanik, Marko [J. Stefan Inst., Ljubljana (Slovenia); Sokhranyi, Grygorii [J. Stefan Inst., Ljubljana (Slovenia); McGoldrick, Garrin [Univ. of Toronto, ON (Canada); Cerv, Matevz [European Organization for Nuclear Research (CERN), Geneva (Switzerland)

    2014-06-18

    This is a technical scope of work (TSW) between the Fermi National Accelerator Laboratory (Fermilab) and the experimenters of Jozef Stefan Institute, CERN, and University of Toronto who have committed to participate in beam tests to be carried out during the 2014 Fermilab Test Beam Facility program. Chemical Vapour Deposition (CVD) diamond has a number of properties that make it attractive for high energy physics detector applications. Its large band-gap (5.5 eV) and large displacement energy (42 eV/atom) make it a material that is inherently radiation tolerant with very low leakage currents and high thermal conductivity. CVD diamond is being investigated by the RD42 Collaboration for use very close to LHC interaction regions, where the most extreme radiation conditions are found. This document builds on that work and proposes a highly spatially segmented diamond based luminosity monitor to complement the time segmented ATLAS Beam Conditions Monitor (BCM) so that when Minimum Bias Trigger Scintillators (MTBS) and LUCID (LUminosity measurement using a Cherenkov Integrating Detector) have difficulty functioning the ATLAS luminosity measurement is not compromised.

  10. ATLAS Christmas lunch

    CERN Document Server

    Francois Butin; Markus Nordberg

    The end of the year ATLAS pit lunch is now a well established tradition: the 4th edition took place in the most prestigious place at CERN; the "Globe de l'innovation", or simply "the Globe". This end-of-year event is the opportunity to thank all those working so hard at Point 1. The first event took place in December 2003. At that time, there was no Globe yet, and the party took place in SX1 building, at the top of the shafts leading to the ATLAS cavern, with some 100 guests. In December 2004, we had the privilege to be the first to organize a lunch in the Globe with some 200 guests. Since then, many have followed our example! Well, almost: we were requested to refrain from serving "Tartiflette" again in there (a Savoyard specialty, using vast amounts of Reblochon, a smelly cheese...). It was said to have left a poignant odour for following events throughout 2004... Long queues formed for this special event. In December 2005, we were authorized to party in the Globe again (once we promised we would b...

  11. ATLAS Solenoid Integration

    CERN Document Server

    Ruber, R

    Last month the central solenoid was installed in the barrel cryostat, which it shares with the liquid argon calorimeter. Figure 1: Some members of the solenoid and liquid argon teams proudly pose in front of the barrel cryosat, complete with detector and magnet. Some two years ago the central solenoid arrived at CERN after being manufactured and tested in Japan. It was kept in storage until last October when it was finally moved to the barrel cryostat integration area. Here a position survey of the solenoid (with respect to the cryostat's inner warm vessel) was performed. Figure 2: The alignment survey by Dirk Mergelkuhl and Aude Wiart. (EST-SU) At the start of the New Year the solenoid was moved to the cryostat insertion stand. Figure 3: The solenoid on the insertion stand, with Akira Yamamoto the solenoid designer and project leader. Figure 4: Taka Kondo, ATLAS Japan spokesperson, and Shoichi Mizumaki, Toshiba project engineer for the ATLAS solenoid, celebrate the insertion. Aft...

  12. The ATLAS Fast Tracker

    CERN Document Server

    Volpi, Guido; The ATLAS collaboration

    2015-01-01

    The use of tracking information at the trigger level in the LHC Run II period is crucial for the trigger an data acquisition (TDAQ) system. The tracking precision is in fact important to identify specific decay products of the Higgs boson or new phenomena, a well as to distinguish the contributions coming from many contemporary collisions that occur at every bunch crossing. However, the track reconstruction is among the most demanding tasks performed by the TDAQ computing farm; in fact, full reconstruction at full Level-1 trigger accept rate (100 KHz) is not possible. In order to overcome this limitation, the ATLAS experiment is planning the installation of a specific processor: the Fast Tracker (FTK), which is aimed at achieving this goal. The FTK is a pipeline of high performance electronic, based on custom and commercial devices, which is expected to reconstruct, with high resolution, the trajectories of charged tracks with a transverse momentum above 1 GeV, using the ATLAS inner tracker information. Patte...

  13. ATLAS starts moving in

    CERN Multimedia

    Della Mussia, S

    2004-01-01

    The first large active detector component was lowered into the ATLAS cavern on 1st March. It consisted of the 8 modules forming the lower part of the central barrel of the tile hadronic calorimeter. The work of assembling the barrel, which comprises 64 modules, started the following day. Two road trailers each with 64 wheels, positioned side by side. This was the solution chosen to transport the lower part of the central barrel of ATLAS' tile hadronic calorimeter from Building 185 to the PX16 shaft at Point 1 (see Figure 1). The transportation, and then the installation of the component in the experimental cavern, which took place over three days were, to say the least, rather spectacular. On 25 February, the component, consisting of eight 6-metre modules, was loaded on to the trailers. The segment of the barrel was transported on a steel support so that it wouldn't move an inch during the journey. On 26 February, once all the necessary safety checks had been carried out, the convoy was able to leave Buildi...

  14. ATLAS Maintenance and Operation management system

    CERN Multimedia

    Copy, B

    2007-01-01

    The maintenance and operation of the ATLAS detector will involve thousands of contributors from 170 physics institutes. Planning and coordinating the action of ATLAS members, ensuring their expertise is properly leveraged and that no parts of the detector are understaffed or overstaffed will be a challenging task. The ATLAS Maintenance and Operation application (referred to as Operation Task Planner inside the ATLAS experiment) offers a fluent web based interface that combines the flexibility and comfort of a desktop application, intuitive data visualization and navigation techniques, with a lightweight service oriented architecture. We will review the application, its usage within the ATLAS experiment, its underlying design and implementation.

  15. Last piece of the puzzle for ATLAS

    CERN Multimedia

    Clare Ryan

    At around 15.40 on Friday 29th February the ATLAS collaboration cracked open the champagne as the second of the small wheels was lowered into the cavern. Each of ATLAS' small wheels are 9.3 metres in diameter and weigh 100 tonnes including the massive shielding elements. They are the final parts of ATLAS' muon spectrometer. The first piece of ATLAS was installed in 2003 and since then many detector elements have journeyed down the 100 metre shaft into the ATLAS underground cavern. This last piece completes this gigantic puzzle.

  16. The Origin of the Term 'Atlas'

    Directory of Open Access Journals (Sweden)

    Miljenko Lapaine

    2008-05-01

    Full Text Available In this paper the origin of the term 'atlas', as a bound collection of maps, is considered. It is usually thought to derive from the name of the Titan, Atlas, who was punished by being forced to bear the entire celestial sphere or universe on his shoulders. However, on the basis of research into and translation of the original Preface of Mercator's Atlas sive cosmographicae meditationes de fabrica mvndi et fabricati figvra, it has been determined that Mercator did not refer to this legend, but named his atlas for the completely different characteristics, such as wisdom, erudition and humanity, of another Atlas.

  17. EnviroAtlas - Metrics for Des Moines, IA

    Data.gov (United States)

    U.S. Environmental Protection Agency — This EnviroAtlas web service supports research and online mapping activities related to EnviroAtlas (https://enviroatlas.epa.gov/EnviroAtlas). The layers in this...

  18. High Latitude Scintillations during the ICI-4 Rocket Campaign.

    Science.gov (United States)

    Patra, S.; Moen, J.

    2015-12-01

    We present the first results from the Norwegian ICI-4 sounding rocket campaign in February 2015. The ICI-4 was launched into F-region auroral blobs from the Andøya Space Center. The multi needle langmuir probe (m-NLP) on board the rocket sampled the ionospheric density structures at a sub-meter spatial resolution. A multi-phase screen model has been developed to estimate the scintillations from the density measurements acquired on-board spacecrafts. The phase screen model is validated and the comparison of the estimated values with scintillations measured by ground receivers during the campaign will be presented. A combination of scintillation receivers in Svalbard and surrounding areas as well as all sky imagers at Ny Ålesund, Longyerbyen, and Skibotn are used to improve the performance of the model.

  19. Solid rocket technology advancements for space tug and IUS applications

    Science.gov (United States)

    Ascher, W.; Bailey, R. L.; Behm, J. W.; Gin, W.

    1975-01-01

    In order for the shuttle tug or interim upper stage (IUS) to capture all the missions in the current mission model for the tug and the IUS, an auxiliary or kick stage, using a solid propellant rocket motor, is required. Two solid propellant rocket motor technology concepts are described. One concept, called the 'advanced propulsion module' motor, is an 1800-kg, high-mass-fraction motor, which is single-burn and contains Class 2 propellent. The other concept, called the high energy upper stage restartable solid, is a two-burn (stop-restartable on command) motor which at present contains 1400 kg of Class 7 propellant. The details and status of the motor design and component and motor test results to date are presented, along with the schedule for future work.

  20. A reanalysis of rocket measurements of the ultraviolet dayglow

    Science.gov (United States)

    Link, R.; Gladstone, G. R.; Chakrabarti, S.; Mcconnell, J. C.

    1988-01-01

    Rocket measurements of O I 989, 1304, 1356 A and N2 Lyman-Birge-Hopfield band emission in the midlatitude dayglow reported by Gentieu et al. (1979) and Eastes et al. (1985) are reexamined. MSIS-83 atomic oxygen densities, the 1304 and 1356 A excitation cross sections of Zipf and Erdman (1985), and SMM solar 1304 A irradiance measurements are consistent with the observed O I and N2 emission intensities. Atmosphere Explorer E (AE-E) measurements of the solar EUV irradiance near solar maximum are consistent with the 1980 rocket airglow data, but the solar EUV irradiance required to explain the 1978 airglow data is a factor of 1.5 larger than indicated by AE-E. Enhancement of the 1304 A excitation cross section due to radiative entrapment of cascade-feeding photons is much less than the factor of two predicted by the cascade model of Julienne and Davis (1976).

  1. Scanning Rocket Impact Area with an UAV: First Results

    Science.gov (United States)

    Santos, C. C. C.; Costa, D. A. L. M.; Junior, V. L. S.; Silva, B. R. F.; Leite, D. L.; Junor, C. E. B. S.; Liberator, B. A.; Nogueira, M. B.; Senna, M. D.; Santiago, G. S.; Dantas, J. B. D.; Alsina, P. J.; Albuquerque, G. L. A.

    2015-09-01

    This paper presents the first subsystems developed for an UAV used in safety procedures of sounding rockets campaigns. The aim of this UAV is to scan the rocket impact area in order to search for unexpected boats. To achieve this mission, designers developed an image recognition algorithm, two human-machine interfaces and two communication links, one to control the drone and the other for receiving telemetry data. In this paper, developers take all major engineering decisions in order to overcome the project constraints. A secondary goal of the project is to encourage young people to take part in Brazilian space program. For this reason, most of designers are undergraduate students under supervision of experts.

  2. Study on risk measurement about ammunition-rocket system

    Institute of Scientific and Technical Information of China (English)

    Gu Xiaohui; Zhao Youshou

    2005-01-01

    Modern ammunition-rocket system is a complicated multidisciplinary system. During its development,undetermined factors will bring many risks. This paper elaborates the importance of risk analysis approach to ammunition-rocket system development and analyses various methods of risk analysis and estimation. Combined with practical situation of weapon system development, the risk measurement function with characteristics of risk preference is given provided that the risk preference characteristic of behavior maker is risk neutral of fixed constant. The development risk analysis based on risk measurement function enables effective risk decision to be made on the basis of quantified risk.Taking anti-helicopter intelligent mine warhead as an example, the paper verifies the efficiency of the method and shows that it has a scientific and practical value.

  3. Feasibility and Performance of the Microwave Thermal Rocket Launcher

    Science.gov (United States)

    Parkin, Kevin L. G.; Culick, Fred E. C.

    2004-03-01

    Beamed-energy launch concepts employing a microwave thermal thruster are feasible in principle, and microwave sources of sufficient power to launch tons into LEO already exist. Microwave thermal thrusters operate on an analogous principle to nuclear thermal thrusters, which have experimentally demonstrated specific impulses exceeding 850 seconds. Assuming such performance, simple application of the rocket equation suggests that payload fractions of 10% are possible for a single stage to orbit (SSTO) microwave thermal rocket. We present an SSTO concept employing a scaled X-33 aeroshell. The flat aeroshell underside is covered by a thin-layer microwave absorbent heat-exchanger that forms part of the thruster. During ascent, the heat-exchanger faces the microwave beam. A simple ascent trajectory analysis incorporating X-33 aerodynamic data predicts a 10% payload fraction for a 1 ton craft of this type. In contrast, the Saturn V had 3 non-reusable stages and achieved a payload fraction of 4%.

  4. Magnetic bearings: A key technology for advanced rocket engines?

    Science.gov (United States)

    Girault, J. PH.

    1992-01-01

    For several years, active magnetic bearings (AMB) have demonstrated their capabilities in many fields, from industrial compressors to control wheel suspension for spacecraft. Despite this broad area, no significant advance has been observed in rocket propulsion turbomachinery, where size, efficiency, and cost are crucial design criteria. To this respect, Societe Europeenne de Propulsion (SEP) had funded for several years significant efforts to delineate the advantages and drawbacks of AMB applied to rocket propulsion systems. Objectives of this work, relative technological basis, and improvements are described and illustrated by advanced turbopump layouts. Profiting from the advantages of compact design in cryogenic environments, the designs show considerable improvements in engine life, performances, and reliability. However, these conclusions should still be tempered by high recurrent costs, mainly due to the space-rated electronics. Development work focused on this point and evolution of electronics show the possibility to decrease production costs by an order of magnitude.

  5. Star 48 solid rocket motor nozzle analyses and instrumented firings

    Science.gov (United States)

    Porter, R. L.

    1986-01-01

    The analyses and testing performed by NASA in support of an expanded and improved nozzle design data base for use by the U.S. solid rocket motor industry is presented. A production nozzle with a history of one ground failure and two flight failures was selected for analyses and testing. The stress analysis was performed with the Champion computer code developed by the U.S. Navy. Several improvements were made to the code. Strain predictions were made and compared to test data. Two short duration motor firings were conducted with highly instrumented nozzles. The first nozzle had 58 thermocouples, 66 strain gages, and 8 bondline pressure measurements. The second nozzle had 59 thermocouples, 68 strain measurements, and 8 bondline pressure measurements. Most of this instrumentation was on the nonmetallic parts, and provided significantly more thermal and strain data on the nonmetallic components of a nozzle than has been accumulated in a solid rocket motor test to date.

  6. Computational investigation on combustion instabilities in a rocket combustor

    Science.gov (United States)

    Yuan, Lei; Shen, Chibing

    2016-10-01

    High frequency combustion instability is viewed as the most challenging task in the development of Liquid Rocket Engines. In this article, results of attempts to capture the self-excited high frequency combustion instability in a rocket combustor are shown. The presence of combustion instability was demonstrated using point measurements, along with Fast Fourier Transform analysis and instantaneous flowfield contours. A baseline case demonstrates a similar wall heat flux profile as the associated experimental case. The acoustic oscillation modes and corresponding frequencies predicted by current simulations are almost the same as the results obtained from classic acoustic analysis. Pressure wave moving back and forth across the combustor was also observed. Then this baseline case was compared against different fuel-oxidizer velocity ratios. It predicts a general trend: the smaller velocity ratio produces larger oscillation amplitudes than the larger one. A possible explanation for the trend was given using the computational results.

  7. Standard Molded Composite Rocket Pyrogen Igniter - A progress report

    Science.gov (United States)

    Lucy, M. H.

    1978-01-01

    The pyrogen igniter has the function to furnish a controlled, high temperature, high pressure gas to ignite solid propellant surfaces in a rocket motor. Present pyrogens consist of numerous inert components. The Standard Molded Pyrogen Igniter (SMPI) consists of three basic parts, a cap with several integrally molded features, an ignition pellet retainer plate, and a tube with additional integrally molded features. A description is presented of an investigation which indicates that the SMPI concept is a viable approach to the design and manufacture of pyrogen igniters for solid propellant rocket motors. For some applications, combining the structural and thermal properties of molded composites can result in the manufacture of lighter assemblies at considerable cost reduction. It is demonstrated that high strength, thin walled tubes with high length to diameter ratios can be fabricated from reinforced plastic molding compound using the displacement compression process.

  8. Rocket injector anomalies study. Volume 2: Results of parametric studies

    Science.gov (United States)

    Przekwas, A. J.; Singhal, A. K.; Tam, L. T.

    1984-01-01

    The employment of a existing computer program to simulate three dimensional two phase gas spray flows in liquid propellant rocket engines. This was accomplished by modification of an existing three dimensional computer program (REFLAN3D) with Euler/Lagrange approach for simulating two phase spray flow, evaporation and combustion. The modified code is referred to as REFLAN3D-SPRAY. Computational studies of the model rocket engine combustion chamber are presented. The parametric studies of the two phase flow and combustion shows qualitatively correct response for variations in geometrical and physical parameters. The injection nonuniformity test with blocked central fuel injector holes shows significant changes in the central flame core and minor influence on the wall heat transfer fluxes.

  9. Characteristics of response factors of coaxial gaseous rocket injectors

    Science.gov (United States)

    Janardan, B. A.; Daniel, B. R.; Zinn, B. T.

    1975-01-01

    The results of an experimental investigation undertaken to determine the frequency dependence of the response factors of various gaseous propellant rocket injectors subject to axial instabilities are presented. The injector response factors were determined, using the modified impedance-tube technique, under cold-flow conditions simulating those observed in unstable rocket motors. The tested injectors included a gaseous-fuel injector element, a gaseous-oxidizer injector element and a coaxial injector with both fuel and oxidizer elements. Emphasis was given to the determination of the dependence of the injector response factor upon the open-area ratio of the injector, the length of the injector orifice, and the pressure drop across the injector orifices. The measured data are shown to be in reasonable agreement with the corresponding injector response factor data predicted by the Feiler and Heidmann model.

  10. The opportunity for hybrid rocket motors in commercial space

    Science.gov (United States)

    Estey, Paul N.; Hughes, Brian G. R.

    1992-07-01

    Hybrid rocket motors which utilize a liquid oxidizer and a solid fuel offer the potential of significantly reducing the cost of propulsion systems for space launch vehicles. Hybrid propulsion systems have a high energy efficiency, a robust combustion process and because of the separation of the propellants both physically and by phase, hybrids cannot explode. This fundamental safety feature enables the hybrid system to be fabricated and operated at costs below those of competitive solid and liquid systems. Due to the safety and low-cost nature of hybrids, they are very attractive to commercial operators. The basics of the hybrid propulsion system and its operation are discussed along with a brief history and status of hybrid motor development. Potential applications of the hybrid rocket motor for commercial space launch vehicles are presented.

  11. Design of a hybrid rocket / inflatable wing UAV

    Science.gov (United States)

    Sudduth, Cory

    This paper discusses the design challenges and development of a UAV that transitions from a rocket, which allows the aircraft to reach a target altitude rapidly, and then deploys an inflatable wing from an enclosed shell in midflight to allow for loitering and surveillance. The wing deployment and transition is tested in static and dynamic environments, while the performance and stability of both the aircraft mode and rocket mode are examined analytically. An in-depth discussion of key components, including the design, analysis and testing, is also included. Designing an UAV that transitions from a high velocity rocket, to a slow velocity UAV provides many difficult and unique design challenges. For example, the incorporation of deployable wing technology into a full UAV system results in many design constraints. In this particular design inflatable wings are used to generate lift during aircraft mode, and the stabilizing fins for the main wing also acted as the fins for the vehicle during its rocket phase. This required the balancing of the two different vehicle configurations to ensure that the aircraft would be able to fly stably in both modes, and transition between them without catastrophic failure. Significant research, and testing went into the finding the best method of storing the inflatable wing, as well as finding the required inflation rate to minimize unsteady aerodynamic affects. Design work was also invested in the development of an inflation system, as it had to be highly reliable, and yet very light weight for use in this small UAV. This paper discusses how these design challenges were overcome, the development and testing of individual sub-components and how they are incorporated into the overall vehicle. The analysis that went into this UAV, as well as methods used to optimize the design in order to minimize weight and maximize the aircraft performance and loitering time is also discussed.

  12. Comparison of HRDI wind measurements with radar and rocket observations

    Energy Technology Data Exchange (ETDEWEB)

    Burrage, M.D.; Skinner, W.R.; Marshall, A.R.; Hays, P.B.; Lieberman, R.S.; Gell, D.A.; Ortland, D.A.; Morton, Y.T.; Wu, D.L.; Franke, S.J.; Schmidlin, F.J.; Vincent, R.A.

    1993-06-18

    This paper reports wind measurements in the mesosphere and lower thermosphere made by the high resolution doppler imager (HRDI) on board the upper atmosphere research satellite (UARS). These measurements are correlated with ground based radar and rocket measurements. The HRDI makes measurements by observing doppler shifts in molecular oxygen lines. The intercomparison helps to validate the remote sensing results, helps to verify the on board calibration system, and also gives a common measurement which other measurements systems can be compared against.

  13. Effect of Thermodynamic Parameter on Cavitation in Rocket Inducer

    OpenAIRE

    吉田, 義樹; 菊田, 研吾; 新井山, 一樹; 渡邉, 聡; Yoshida, Yoshiki; Kikuta, Kengo; Niiyama, Kazuki; Watanabe, Satoshi

    2013-01-01

    Cavitation is physically "a vaporization of liquid" which needs latent heat for phase change. A cavity grows in the liquid, so the latent heat of vaporization can only be supplied by the liquid surrounding the cavity. Thus, the liquid close to the interface region of the cavity is cooled down. || In general, cryogenic liquids are very thermosensitive. For liquid hydrogen and oxygen used in rocket propulsion, the temperature in the cavity, i.e., the vapor pressure in the cavity, is lower tha...

  14. STERN – A Rocket programme for German Students

    OpenAIRE

    Stamminger, Andreas; Ciezki, Helmut; Kitsche, Wolfgang; Kobald, M.; Lappöhn, Karsten; Schmidt, Alexander

    2013-01-01

    In April 2012 the German Aerospace Center DLR, launched a support programme for students to develop, build and launch their own rockets. The programme goes by the acronym STERN (STudentische Experimental-RaketeN) which is also the German word for star. Supported by funds from the Federal Ministry of Economics and Technology (BMWi) and conducted by the DLR Space Administration of the German Aerospace Center DLR, the STERN programme provides aerospace engineering faculties at universities with ...

  15. Small Rocket Measurements / Validation in Support of SABER

    OpenAIRE

    Jensen, Anthony J.; Baker, Doran

    2003-01-01

    Small rocket measurements in the Mesosphere and lower Thermosphere / Ionosphere will serve to validate and improve measurements being made by the TIMED satellite's SABER instrument. This validation can be made more cost effective and versatile by developing a smaller, lighter, and less expensive radiometer module. Recent developments in technology have allowed us to proceed in developing this smaller, more lightweight radiometric instrument We are currently working on a miniature 2-channel ra...

  16. JANNAF Rocket Nozzle Technology Subcommittee Executive Committee Report

    Science.gov (United States)

    Lawrence, Timothy W.; Munafo, Paul M. (Technical Monitor)

    2002-01-01

    This viewgraph presentation provides information on the structure and activities of the panels of the Joint Army Navy NASA Air Force (JANNAF) Rocket Nozzle Technology Subcommittee. The panels profiled are the Processing Science and Materials Panel, the Nozzle Design, Test, and Evaluation Panel, the Nozzle Analysis and Modeling Panel, and the Nozzle Control Systems Panel. The presentation also lists meetings, workshops, and publications in which the subcommittee participated during the reporting period.

  17. Research Technology (ASTP) Rocket Based Combined Cycle (RBCC) Engine

    Science.gov (United States)

    2004-01-01

    Pictured is an artist's concept of the Rocket Based Combined Cycle (RBCC) launch. The RBCC's overall objective is to provide a technology test bed to investigate critical technologies associated with opperational usage of these engines. The program will focus on near term technologies that can be leveraged to ultimately serve as the near term basis for Two Stage to Orbit (TSTO) air breathing propulsions systems and ultimately a Single Stage To Orbit (SSTO) air breathing propulsion system.

  18. Integrated High Payoff Rocket Propulsion Technologies Program Material Development Plan

    Science.gov (United States)

    Clinton, R. G., Jr.; Stropki, M.; Cleyrat, D.; Stucke, B.; Phillips, S.; Reed, B.

    2001-01-01

    In this viewgraph presentation, IMWG (IHPRPT Materials Working Group) government and industry members, together with the IHPRPT (Integrated High Payoff Rocket Propulsion Technologies Program Material Development Plan) National Component Leads, have developed a materials plan to address the critical needs of the IHPRPT community: (1) liquids boost and orbit transfer; (2) solids boost and orbit transfer; (3) tactical propulsion; and (4) spacecraft propulsion. Criticality of materials' role in achieving IHPRPT goals is evidenced by the significant investment over the next five years.

  19. Deployment and Characterisation of a Telescopic Boom for Sounding Rockets

    OpenAIRE

    Wylie, Mark; Keegan, John; Curran, Stephen; Vather, Dinesh; Duffy, Paul

    2011-01-01

    In any sounding rocket, volume and mass are at a premium. Payload designers strive towards smaller, lighter and cheaper mechanisms which can achieve the same goals. This project aims to reduce the mass and volume for probe deployment booms and their deployment mechanisms. An experiment (Telescobe) to test a low cost novel method of boom deployment using telescopic carbon fibre poles was developed. A custom camera measurement system was also developed to measure boom length and harmonic deflec...

  20. Rf control system for a rocket-borne accelerator

    International Nuclear Information System (INIS)

    The Beam Experiments Aboard Rockets (BEAR) accelerator experiment imposes several nonstandard requirements on the rf control system. The experiment is entirely hands-off and must operate under local computer control. The rf control system must be extremely reliable, which implies excellence in design and fabrication as well as redundancy whenever possible. This paper describes the design of the frequency-source, frequency-control, and amplitude-control systems for the BEAR experiment