WorldWideScience

Sample records for renegade missile transfixed

  1. Retrieval of a broken guide wire transfixing the hip through the proximal femoral nail hole

    Institute of Scientific and Technical Information of China (English)

    Saurabh Jain; Abhishek Pathak; Rajeev Kant Pandey

    2014-01-01

    Retrieval of a broken guide wire transfixing the acetabulum or with intrapelvic migration is challenging and frustrating for surgeons.We here present a case report on a method to remove a broken guide wire transfixing the acetabulum through the proximal hole of recon nail using a grasping forceps.This method is little invasive,easy,time-saving and without need for changing the inital fixation.

  2. Retrieval of a broken guide wire transfixing the hip through the proximal femoral nail hole

    Directory of Open Access Journals (Sweden)

    Jain Saurabh

    2014-02-01

    Full Text Available 【Abstract】Retrieval of a broken guide wire transfixing the acetabulum or with intrapelvic migration is challenging and frustrating for surgeons. We here present a case report on a method to remove a broken guide wire transfixing the acetabulum through the proximal hole of recon nail using a grasping forceps. This method is little invasive, easy, time-saving and without need for changing the inital fixation.

  3. Transfixation cast technique for arthrodesis of the distal interphalangeal joint of horses.

    Science.gov (United States)

    Easter, J L; Schumacher, J; Watkins, J P

    2011-01-01

    Surgical arthrodesis of the distal interphalangeal (DIP) joint by transfixation casting was used to salvage a three-year-old filly and a yearling filly that were chronically lame because of infection of the DIP joint for breeding. Unlike previously described techniques for arthrodesis of the DIP joint, the technique used did not require insertion of implants across the joint, which may have contributed to the successful outcome.

  4. Surgical treatment of fresh complete acromioclavicular dislocation by coracoid process transfer and k-wire transfixation.

    Science.gov (United States)

    Wang, Yeming; Zhang, Jianguo

    2013-12-01

    Acromioclavicular dislocations are very common shoulder injuries. The optimal treatment for acute high-grade acromioclavicular joint injury remains a matter of debate. The purpose of this study was to evaluate the results of surgical treatment of complete acromioclavicular dislocation using coracoid process transfer and temporary K-wire transfixation. Twenty-one patients with complete acromioclavicular dislocation underwent coracoid process transfer and temporary K-wire transfixation. Patients were assessed at the follow-up based on visual analog scores (VAS), the Constant-Murley scoring system and the UCLA shoulder rating system. Radiographs were taken to check up vertical instability. The mean follow-up was 32.1 months (25-47 months). The mean Constant and Murley score and UCLA shoulder rating score was 89.9 ± 8.4 and 30.1 ± 4.4. There were fourteen excellent functional results and six results and one poor result. The overall rate of satisfaction, which means an excellent or good result, was 95.2 %. Nineteen patients (90.4 %) maintained their previous jobs or resume their daily activities. The mean final pain score, as measured from 1 to 10 on the visual analog scale, was 1.91 ± 1.09. The radiographic analysis revealed twenty patients had maintained reduction at the final follow-up. The coracoid process transfer and temporary K-wire transfixation is a reliable treatment for a complete acromioclavicular dislocation.

  5. [External femorotibial transfixation in femoral fracture with joint involvement in a child].

    Science.gov (United States)

    Nounla, J; Bennek, J; Bühligen, U; Rolle, U

    2001-07-01

    Long bone fractures combined with joint injuries run a high risk of destabilising the articulations. Remaining joints incongruence can lead to early arthosis especially in cases of severe injuries or not achieved anatomical reduction. A number of osteosynthesis methods are available for anatomical repair of the articular facet. This report presents a seven years old boy with an open comminuted fracture of the distal femur and consecutive joint instability, treated with a Transfixation (Orthofix) of the knee joint. The functional results suggest this method as an alternative treatment.

  6. Missile Aerodynamics (Aerodynamique des Missiles)

    Science.gov (United States)

    1998-11-01

    guerre froide la production des missiles a baisse’, avec pour consequence une diminution des budgets de d6veloppement. Les nouveaux types de conflits ...Roma) Directeur - Gestion de l’information LUXEMBOURG (Recherche et developpement) - DRDGI 3 Voir Belgique Ministbre de la Difense nationale NORVEGE

  7. MANAGEMENT OF WRIST GANGLIA BY TRANSFIXATION TECHNIQUE: OUR EXPERIENCE IN A RURAL TEACHING INSTITUTION

    Directory of Open Access Journals (Sweden)

    Sharma Man

    2014-06-01

    Full Text Available BACKGROUND: Ganglion is one of the commonly seen lesions in minor surgical practice. Treatment of wrist ganglia includes simple reassurance, watchful waiting, non-operative aspiration, injection, surgical excision and even sometimes advanced endoscopic excision. Although treatment is not often necessary, many patients seeking consultation ask for some form of definitive treatment. High incidence of recurrence is seen with cyst aspiration/injection or after surgical excision. Recurrence is the common problem, irrespective of the treatment modality. MATERIALS AND METHODS: This study evaluates results of a modified minimally invasive surgical technique used for the management of ganglia of the wrist. Thirty six wrist ganglia have been treated by using the transfixation technique. RESULTS: The successful results for the procedure were seen in 94.44% patients. Consequent to the procedure, an average of 2days off work were lost. Recurrence in the 2 year follow-up was seen in two patients. DISCUSSION: On comparing with other modalities this method is minimally invasive, cost-effective, less time consuming, low rate of recurrence and at the same time can be carried out under local anesthesia as a day case procedure and even not requiring any specific instrument and further this technique can be easily learned.

  8. Advanced Missile Signature Center

    Data.gov (United States)

    Federal Laboratory Consortium — The Advanced Missile Signature Center (AMSC) is a national facility supporting the Missile Defense Agency (MDA) and other DoD programs and customers with analysis,...

  9. Letters: Subs, Not Missiles

    National Research Council Canada - National Science Library

    Tsipis, Kosta

    1989-01-01

      In a letter, MIT physicist Kosta Tsipis responds to a column in the August 1988 "Bulletin of the Atomic Scientists" and clarifies his position in regard to the MX and Trident II missile programs...

  10. [Scapular/parascapular double skin-paddle free flap for transfixing blast injuries of the hand. A case report].

    Science.gov (United States)

    Colson, T; Pozetto, M; Gibert, N; Dautel, G

    2014-06-01

    Balistic transfixing hand traumas require a complex reconstruction management. Stabilization and reconstruction of the injuried tissues need a double skin-paddle coverage. We present an original case report of a double skin-paddle scapular/parascapular free flap used to cover a through and through gunshot injury of the right hand. A 14-years-old patient presents a severe and extensive wound with full-thickness palmar and dorsal skin defects, dislocation of the carpal bones, median nerve and flexor tendons losses. Distal vascularization is maintained by the deep palmar arch system supplied by the ulnar artery. The radial artery is severed at the level of the first dorsal interosseous space. The measured defect of the dorsal skin was 12×7cm and the palmar one was 6×3cm. After skeletal stabilization, tendinous and nerve preparation, the hand coverage was performed using a double skin-paddle scapular/parascapular free flap. The vascular anastomoses include an end-to-side arterial suture between the circumflex scapular and the radial arteries, and an end-to-end venous suture between the circumflex scapular and the dorsal radial veins. The scapular/parascapular double skin-paddle free flap is a safe and reliable technique to achieve a dorsal and palmar hand coverage in lack of local flaps alternatives. It can be used as a good option prior to bone graft, tendinous and nervous reconstruction. Copyright © 2013. Published by Elsevier Masson SAS.

  11. The Effectiveness of the U.S. Missile Defense Capabilities as a Deterrent to the North Korean Missile Threat

    Science.gov (United States)

    2007-12-01

    THE U.S. MISSILE DEFENSE CAPABILITIES AS A DETERRENT TO THE NORTH KOREAN MISSILE THREAT by Issac G. Gipson December 2007 Thesis Advisor...SUBJECT TERMS Missile Deterrence, Missile Defense , North Korean Missile Threat, North Korean Missile Systems, U.S. Missile Defense Capabilities, 16...19 III. CURRENT MISSILE DEFENSE ANALYSIS AGAINST NORTH KOREAN MISSILE THREAT

  12. Modeling Of Ballistic Missile Dynamics

    Directory of Open Access Journals (Sweden)

    Salih Mahmoud Attiya

    2013-05-01

    Full Text Available Aerodynamic modeling of ballistic missile in pitch plane is performed and the open-loop transfer function related to the jet deflector angle as input and pitch rate, normal acceleration as output has been derived with certain acceptable assumptions. For typical values of ballistic missile parameters such as mass, velocity, altitude, moment of inertia, thrust, moment and lift coefficient show that, the step time response and frequency response of the missile is unstable. The steady state gain, damping ratio and undraped natural frequency depend on the missile parameters. To stabilize the missile a lead compensator must be added to the forward loop.

  13. The North Korean Missile Program

    Science.gov (United States)

    Wright, David

    2001-04-01

    In recent years, the development of ballistic missiles by North Korea has been a key motivation for US efforts to stem missile proliferation and to develop defenses against intermediate and long-range missiles. In the 1980s, North Korea reverse-engineered short-range Soviet Scud missiles and began to produce and sell them. In 1993, it flight-tested a missile reported to have a range of up to 1,300 kilometers, which would allow it to target most of Japan. In 1998, it launched a multi-stage missile over Japan; it later announced that the launch had been an attempt to place a satellite in orbit. An important question is what these tests imply for its current capability and its possible future missile development. Since North Korea has sold missiles to countries in the Middle East and South Asia and is reported to be assisting Iran's missile development program, understanding its capabilities is relevant to security concerns in several parts of the world. In this talk I will discuss my analysis of the publicly available information about North Korea's missile tests, and my conclusions about possible future developments. This includes estimates of ranges and payloads of its next potential generation of missiles, and comments about their potential military utility.

  14. Missile defence : An overview

    NARCIS (Netherlands)

    Weimar, P.W.L.

    2012-01-01

    At the present day, an unparalleled number of international actors, be it national governments or non-state groups, have acquired or are seeking to acquire both weapons of mass destruction and the means to deliver them. Those means of delivery can be Ballistic Missiles that can bridge vast – even

  15. Missile defence : An overview

    NARCIS (Netherlands)

    Weimar, P.W.L.

    2012-01-01

    At the present day, an unparalleled number of international actors, be it national governments or non-state groups, have acquired or are seeking to acquire both weapons of mass destruction and the means to deliver them. Those means of delivery can be Ballistic Missiles that can bridge vast – even in

  16. Attacking the Cruise Missile Threat

    Science.gov (United States)

    2010-07-26

    little warning before a strike. Cruise missiles such as Silkworm and Exocet are designed to fly at “sea-skimming” levels only a few feet above the surface...the SS-N-2 Styx missile, a surface-to-surface antiship cruise missile. Most variants of modern cruise missiles are conversions of the Styx—the Silkworm ...number of Soviet built SS-N-2 Styxes that had been dismounted from boats.23 The Silkworm , the predominant of these variants, is the “Scud” of cruise

  17. European Missile Defense and Russia

    Science.gov (United States)

    2014-07-01

    most senior level—the only one that matters in Russian decisionmaking cul - ture—is also of significance today and will also be re- ferred to later in... org /missile-defense/us-ballistic-missile-defense/p30607. 9. Email exchange with author, July 2013. 10. “Safeguard,” Washington, DC: Federation of Ameri

  18. Adaptive Missile Guidance Using GPS

    Directory of Open Access Journals (Sweden)

    Pallavi Sharad Rupnar

    2013-05-01

    Full Text Available The name adaptive means we can guide any missile using GPS in any critical conditions. GPS guided missiles, using the exceptional navigational and surveying abilities of GPS, after being launched, could deliver a warhead to any part of the globe via the interface of the onboard computer in the missile with the GPS satellite system.GPS allows accurate targeting of various military weapons including ICBMs, cruise missiles and precision-guided munitions. Artillery projectiles with embedded GPS receivers able to withstand accelerations of 12,000 G have been developed for use in 155mm.GPS guided weapons, with their technological advances over previous, are the superior weapon of choice in modern days

  19. Ballistic Missile Defense System (BMDS)

    Science.gov (United States)

    2015-12-01

    Estimate RDT&E - Research , Development, Test, and Evaluation SAR - Selected Acquisition Report SCP - Service Cost Position TBD - To Be Determined TY - Then...all ranges and in all phases of flight. Following guidance from the President, the Secretary of Defense approved the Ballistic Missile Defense (BMD...based Midcourse Defense (GMD) system to enhance our capability against Intercontinental Ballistic Missiles. We are currently sustaining 30

  20. Hyper Velocity Missiles For Defence

    Directory of Open Access Journals (Sweden)

    Faqir Minhas

    2005-10-01

    Full Text Available The paper reviews the history of technical development in the field of hypervelocity missiles. It highlights the fact that the development of anti-ballistic systems in USA, Russia, France, UK, Sweden, and Israel is moving toward the final deployment stage; that USA and Israel are trying to sell PAC 2 and Arrow 2 to India; and that India’s Agni and Prithvi missiles have improved their accuracy, with assistance from Russia. Consequently, the paper proposes enhanced effort for development in Pakistan of a basic hypersonic tactical missile, with 300 KM range, 500 KG payload, and multi-rolecapability. The author argues that a system, developed within the country, at the existing or upgraded facilities, will not violate MTCR restrictions, and would greatly enhance the country’s defense capability. Furthermore, it would provide high technology jobs toPakistani citizens. The paper reinforces the idea by suggesting that evolution in the field of aviation and electronics favors the development of ballistic, cruise and guided missile technologies; and that flight time of short and intermediate range missiles is so short that its interception is virtually impossible.

  1. Joint Air-to-Ground Missile (JAGM)

    Science.gov (United States)

    2015-12-01

    Navy. The JAGM mission is to develop the next generation of aviation launched fire and forget missiles to replace the HELLFIRE laser and Longbow...EMD contract to develop the next generation of aviation launched missiles to replace the HELLFIRE laser and Longbow radar missiles . JAGM December 2015...Selected Acquisition Report (SAR) RCS: DD-A&T(Q&A)823-355 Joint Air-to-Ground Missile (JAGM) As of FY 2017 President’s Budget Defense Acquisition

  2. Bayesian Missile System Reliability from Point Estimates

    Science.gov (United States)

    2014-10-28

    OCT 2014 2. REPORT TYPE N/A 3. DATES COVERED - 4. TITLE AND SUBTITLE Bayesian Missile System Reliability from Point Estimates 5a. CONTRACT...Principle (MEP) to convert point estimates to probability distributions to be used as priors for Bayesian reliability analysis of missile data, and...illustrate this approach by applying the priors to a Bayesian reliability model of a missile system. 15. SUBJECT TERMS priors, Bayesian , missile

  3. 15 CFR 742.5 - Missile technology.

    Science.gov (United States)

    2010-01-01

    ... to the design, development, production, or use of missiles. These items are identified in ECCNs on... air vehicle systems (including cruise missile systems, target drones, and reconnaissance drones... the design, development, production, or use of missiles; (iii) The capabilities and objectives of...

  4. Tamponamento das lesões renais transfixantes com colágeno tipo I Type I collagen used to tamponade transfixing lesion of the kidney

    Directory of Open Access Journals (Sweden)

    Mario Mantovani

    1999-10-01

    Full Text Available Nos últimos anos temos atendido vítimas de trauma com ferimento transfixante dos rins direito e esquerdo. Em trabalho anterior utilizamos colágeno tipo I em ferimentos transfixantes do fígado, com bons resultados. Assim, extendemos a utilização do método para o rim aplicando o colágeno tipo I produzido na UNICAMP, o qual pode ser injetado e moldado ocupando toda a área lesada e o trajeto anfractuoso ou irregular. Desta forma pode-se conseguir um tamponamento completo, coibindo a hemorragia e sustando a perda de urina. O colágeno será posteriormente reabsorvido não funcionando como corpo estranho. Trinta e seis cães foram submetidos a lesão transfixante na região inferior do rim esquerdo, procurando simular uma lesão produzida por um projétil de arma de fogo. Seis destes animais não receberam tratamento e foram a óbito por choque hemorrágico. Em todos os outros 30 animais, aplicou-se o colágeno tipo I em toda a extensão do túnel formado pela lesão, através da injeção do material. Foram realizadas avaliações clínicas no pós-operatório, sendo os cães sacrificados, em grupos de seis, aos 4, 7,15, 30 e 60 dias de pós-operatório O estudo macroscópico e microscópico, revelou uma formação cicatricial homogênea, com regeneração renal intensa, precoce e organizada, a partir do 7º dia de pós-operatório. Conclui-se que a aplicação do colágeno tipo I, nestes tipos de ferimentos são de aplicação simples e segura.Over the past years we have used of the type I collagen to tamponade transfixing hepatic lesions in dogs, manufactured at University of Campinas. We have considered the use of this collagen to tamponed transfixing renal lesions, wich can be molded to the entire wounded area thus tamponading all surface irregularities. In this way, a complete tamponade way be achieved, and urinary loss is prevented. Thirty six mongrel dogs received a perforating transfixing lesion in the distal region of the kidney

  5. Impulsive control for hypervelocity missiles

    Science.gov (United States)

    Magness, R. W.

    1981-05-01

    A hypervelocity agile interceptor/quickshot is being developed for defense of ballistic missile launch sites. A guidance and control system is required to achieve the missile guidance accuracy necessary for direct target impact. Attitude control systems evaluated for the agile interceptor included aerodynamic controls, thrust vector controls and impulsive motor controls. The solid squib impulsive control motion was selected because of high response rate, low weight and low volume. A baseline motor configuration was designed and a solid propellant squib was developed for use in the control system. Ballistic pendulum and bench tests were conducted with a test impulsive control motor to measure nominal performance, establish the standard deviation of performance, and define requirements to prevent sympathetic ignition. A dynamic control wind tunnel test was also conducted to determine the impulse augmentation due to the impulsive motor jet interaction with the missile boundary layer. The degree and direction of augmentation was measured for variations in Mach number and angle of attack.

  6. Remote control missile model test

    Science.gov (United States)

    Allen, Jerry M.; Shaw, David S.; Sawyer, Wallace C.

    1989-01-01

    An extremely large, systematic, axisymmetric body/tail fin data base was gathered through tests of an innovative missile model design which is described herein. These data were originally obtained for incorporation into a missile aerodynamics code based on engineering methods (Program MISSILE3), but can also be used as diagnostic test cases for developing computational methods because of the individual-fin data included in the data base. Detailed analysis of four sample cases from these data are presented to illustrate interesting individual-fin force and moment trends. These samples quantitatively show how bow shock, fin orientation, fin deflection, and body vortices can produce strong, unusual, and computationally challenging effects on individual fin loads. Comparisons between these data and calculations from the SWINT Euler code are also presented.

  7. Embedded Systems - Missile Detection/Interception

    Directory of Open Access Journals (Sweden)

    Luis Cintron

    2010-01-01

    Full Text Available Missile defense systems are often related to major military resources aimed at shielding a specific region from incoming attacks. They are intended to detect, track, intercept, and destruct incoming enemy missiles. These systems vary in cost, efficiency, dependability, and technology. In present times, the possession of these types of systems is associated with large capacity military countries. Demonstrated here are the mathematical techniques behind missile systems which calculate trajectories of incoming missiles and potential intercept positions after initial missile detection. This procedure involved the use of vector-valued functions, systems of equations, and knowledge of projectile motion concepts.

  8. Trajectory Optimization Design for Morphing Wing Missile

    Institute of Scientific and Technical Information of China (English)

    Ruisheng Sun; Chao Ming; Chuanjie Sun

    2015-01-01

    This paper presents a new particle swarm optimization ( PSO) algorithm to optimize the trajectory of morphing⁃wing missile so as to achieve the enlargement of the maximum range. Equations of motion for the two⁃dimensional dynamics are derived by treating the missile as an ideal controllable mass point. An investigation of aerodynamic characteristics of morphing⁃wing missile with varying geometries is performed. After deducing the optimizing trajectory model for maximizing range, a type of discrete method is put forward for taking optimization control problem into nonlinear dynamic programming problem. The optimal trajectory is solved by using PSO algorithm and penalty function method. The simulation results suggest that morphing⁃wing missile has the larger range than the fixed⁃shape missile when launched at supersonic speed, while morphing⁃wing missile has no obvious range increment than the fixed⁃shape missile at subsonic speed.

  9. Robust missile feedback control strategies

    NARCIS (Netherlands)

    Trottemant, E.J.; Scherer, C.W.; Weiss, M.; Vermeulen, A.

    2010-01-01

    The nature of the missile interception problem with two noncooperative players leads to the field of differential games. Introducing nonlinear uncertain models can potentially lead to nonexistence of game theoretic equilibrium strategies, computationally intractable problems, and/or highly reduced p

  10. Acceleration effects on missile aerodynamics

    CSIR Research Space (South Africa)

    Gledhill, Irvy MA

    2010-09-01

    Full Text Available Practical requirements are now arising in which significant acceleration takes place during flight; 5th generation missiles, such as A-Darter, execute turns at 100 g, where g is the acceleration due to gravity, and thrust from propulsion systems may...

  11. Iliotibial band friction syndrome after anterior cruciate ligament reconstruction using the transfix device: report of two cases and review of the literature.

    Science.gov (United States)

    Pelfort, Xavier; Monllau, Joan C; Puig, Lluís; Cáceres, Enric

    2006-06-01

    The use of hamstrings is increasing as a treatment for anterior cruciate ligament (ACL) injuries. There are a lot of new devices and techniques that try to fix the graft without causing further injury or increased morbidity. We report two cases in relation to the transfix device for reconstructing the ACL. The first case is a 38-year-old female who was treated with an autologous hamstring graft for chronic ACL instability brought on by a sport trauma. The patient developed iliotibial band friction syndrome 3 months after the operation. MRI showed incorrect positioning and a rupture of the femoral bio-absorbable cross-pin. The hamstring graft always had good fixation and did not produce instability of the knee. We removed the cross-pin fragment in a second surgery and the patient returned to her daily lifestyle after 3 weeks. The second case is a 52-year-old female with a painful and unstable knee due to a previous lateral meniscectomy and failure of an ACL reconstruction. We performed an ACL reconstruction with an autologous hamstring graft and a lateral meniscus transplantation. Some months after the procedure she also developed this syndrome. MRI showed the same features as shown in the first case and a second surgery was needed. To our knowledge this clinical and technical problem has not been previously described.

  12. Missile vascular injuries: 19-year experience.

    Science.gov (United States)

    Ahanger, Abdul Gani; Wani, Mohd Lateef; Lone, Reyaz Ahmad; Singh, Shyam; Hussain, Zahur; Mir, Ishtiyak A; Irshad, Ifat; Ashraf, Hakeem Zubair; Dar, Abdul Majeed; Lone, Ghulam Nabi; Bhat, Mohammad Akbar; Sharma, Mukand Lal

    2010-03-01

    Missile vascular injuries have reached an epidemic proportion in Kashmir valley since the eruption of militancy. The present study was undertaken to analyze the mode, pattern, presentation, and management of missile vascular injuries. A retrospective study of patients with missile vascular injury from January 1990 to October 2008 was undertaken. Five hundred eighty patients with missile vascular injury were studied. All patients with vascular injury due to causes other than missiles were excluded from the study. Most of the patients were treated by interpositional saphenous vein graft or end-to-end anastomosis. The most common complication was wound infection (22.7%) followed by graft occlusion (3.8%). The amputation rate was 3.3% and was higher in patients with a delay of >6 hours to revascularization and associated fractures. Missile vascular injury requires prompt resuscitation and revascularization. Preoperative angiography is seldom necessary. Doppler study may sometimes be needed to aid in the diagnosis.

  13. Electro-chemical batteries for guided missiles

    Directory of Open Access Journals (Sweden)

    H. S. Jaggi

    1966-05-01

    Full Text Available Electro-chemical batteries owing to their simplicity and ease of stowage form one of the sources of electrical power inside a missile. However, all batteries are not suited for this application. This article describes the special features required of a missile borne battery pack and discusses the characteristics of various types of batteries available today in the world. Conclusions have been drawn as to the most suitable types of batteries for missile applications.

  14. Countering Air and Missile Threats

    Science.gov (United States)

    2012-03-23

    carrying the CMs. (2) SLCMs and ground-launched cruise missiles ( GLCMs ) present opportunities for detection as well as challenges for surveillance...if possible, and engage them before they can navigate to their targets. (6) Training patterns or identifiable launch sequence events for GLCMs are...rarely observed or practiced in an overt environment. Consequently, the probability is small for conclusively identifying a GLCM TEL using current

  15. Soviet debate on missile defense

    Energy Technology Data Exchange (ETDEWEB)

    Parrott, B.

    1987-04-01

    Although the Strategic Defense Initiative (SDI) is meant to cope with the danger of a Soviet nuclear attack, the recent US debate over SDI has paid surprisingly little attention to Soviet views of ballistic missile defense. Despite the existence of a substantial body of pertinent scholarship, the debate has failed to take adequate account of major changes in Soviet ballistic missile defense policy since the mid-1960s. It has also neglected the links between current Soviet military policy and broader Soviet political and economic choices. The Soviets regard SDI not as a novel undertaking to reduce the risks of nuclear war but as an extension of the geopolitical competition between the superpowers. This competition has been dominated in the 1980s, in the Soviet view, by sharply increased US assertiveness and the decline of detente. Viewing SDI as a manifestation of these general trends, Soviet decision makers find the prospect of an unregulated race in ballistic missile defenses and military space technologies deeply unsettling. The deterioration of superpower relations has raised serious doubts in Moscow about the wisdom of Soviet external policy during the 1970s and has provoked sharp internal differences over policy toward the US. Already highly suspicious of the Reagan administration, the elite is united by a general conviction that SDI is an American gambit that may ultimately undercut past Soviet strategic gains and pose a grave new threat to Soviet security. 14 references.

  16. Missile Electro-Optical Countermeasures Simulation Laboratory

    Data.gov (United States)

    Federal Laboratory Consortium — This laboratory comprises several hardware-in-the-loop missile flight simulations designed specifically to evaluate the effectiveness of electro-optical air defense...

  17. Infrared Background and Missiles Signature Survey

    Directory of Open Access Journals (Sweden)

    D.V. Renuka

    2013-11-01

    Full Text Available The proliferation of the missile threats in the existing threat scenario for airborne platform is a serious point of consideration for any mission planning. Missile warning system is an electronic warfare support system which gives warning to the pilot when a missile is detected in the scenario. The airborne platform has to be installed with missile warning sensors to give a spherical coverage, so that the sensors can detect the IR intensity variation in the ground scenario. This IR intensity variation has to be further analysed to differentiate the raising missile intensity from the varying background clutter. In order to differentiate the threat from the background clutter, the system should have sufficient background data set for online comparison thereby having less false alarm rate. The efficiency and performance of any missile warning system is validated with respect to its probability of declaration against the false alarm rate. Hence, to realize an efficient functioning of missile warning system, building IR background data base and missile signature database are the primary task. This paper details the methodology to be adapted for the building of tactical missile IR signatures and background data.

  18. Infrared Background and Missiles Signature Survey

    Directory of Open Access Journals (Sweden)

    D.V. Renuka

    2013-12-01

    Full Text Available The proliferation of the missile threats in the existing threat scenario for airborne platform is a serious point of consideration for any mission planning. Missile warning system is an electronic warfare support system which gives warning to the pilot when a missile is detected in the scenario. The airborne platform has to be installed with missile warning sensors to give a spherical coverage, so that the sensors can detect the IR intensity variation in the ground scenario. This IR intensity variation has to be further analysed to differentiate the raising missile intensity from the varying background clutter. In order to differentiate the threat from the background clutter, the system should have sufficient background data set for online comparison thereby having less false alarm rate. The efficiency and performance of any missile warning system is validated with respect to its probability of declaration against the false alarm rate. Hence, to realize an efficient functioning of missile warning system, building IR background data base and missile signature database are the primary task. This paper details the methodology to be adapted for the building of tactical missile IR signatures and background data.Defence Science Journal, 2013, 63(6, pp.611-615, DOI:http://dx.doi.org/10.14429/dsj.63.5762

  19. Infrared ship/decoy/missile encounter model

    Science.gov (United States)

    Morin, Josee; Reid, Francoise; Morin, Andre

    1993-08-01

    Simulations of missile-ship-countermeasures engagements are used to determine the effective ways of defending a ship against infrared-guided missile threats. This paper describes one type of simulation that models the engagement of a ship deploying IR decoys by an infrared-guided seeker-head missile. This model was developed to assess the efficiency of IR decoys in protecting ships against these missiles. The simulation, Missile Infrared Decoy And Ship (MIDAS), is composed of three major blocks, the infrared scene generation, the seeker simulation and the missile dynamics simulation. The infrared scene generation block produces a three-dimensional IR scene from the target ship and flare models and transforms it into the two-dimensional IR image viewed by the seeker. The seeker simulation block is based on a generic conical scan seeker which uses a crossed-detector array for target detection. It processes the IR image to select a target and generates a steering command. The missile dynamics block computes the changes in missile trajectory according to the seeker steering command. The computations performed by each of the three blocks are explained in detail.

  20. The Cooperative Ballistic Missile Defence Game

    NARCIS (Netherlands)

    Evers, L.; Barros, A.I.; Monsuur, H.

    2013-01-01

    The increasing proliferation of ballistic missiles and weapons of mass destruction poses new risks worldwide. For a threatened nation and given the characteristics of this threat a layered ballistic missile defence system strategy appears to be the preferred solution. However, such a strategy involv

  1. Principles of Guided Missiles and Nuclear Weapons.

    Science.gov (United States)

    Naval Personnel Program Support Activity, Washington, DC.

    Fundamentals of missile and nuclear weapons systems are presented in this book which is primarily prepared as the second text of a three-volume series for students of the Navy Reserve Officers' Training Corps and the Officer Candidate School. Following an introduction to guided missiles and nuclear physics, basic principles and theories are…

  2. The Cooperative Ballistic Missile Defence Game

    NARCIS (Netherlands)

    Evers, L.; Barros, A.I.; Monsuur, H.

    2013-01-01

    The increasing proliferation of ballistic missiles and weapons of mass destruction poses new risks worldwide. For a threatened nation and given the characteristics of this threat a layered ballistic missile defence system strategy appears to be the preferred solution. However, such a strategy

  3. Discrete Deterministic Modelling of Autonomous Missiles Salvos

    Directory of Open Access Journals (Sweden)

    Momcilo Milinovic

    2014-09-01

    Full Text Available The paper deals with mathematical models of sequent salvos battle, of autonomous flight missiles (AFM organized in the groups of combatants. Tactical integration of AFM system distance-controlled weapon is considered by performances of simultaneous approaches on targets, and continual battle models of guerilla and direct fire, are redesigned to the discrete-continual mixed model, for checking missiles sudden, and further salvos, attack effects. Superiority parameters, as well as losses and strengths of full, or the part of salvo battle, for the missiles groups as technology sub-systems combatants’, is expressed by mathematical and simulation examples. Targets engagements capacities of the missiles battle unit, is conducted through designed scenarios and mathematically derived in the research. Model orientated on answers about employment of rapid reaction defending tactics, by distance missiles attacks.Defence Science Journal, Vol. 64, No. 5, September 2014, pp.471-476, DOI:http://dx.doi.org/10.14429/dsj.64.5791

  4. DDG-1000 Missile Integration: A Case Study

    Science.gov (United States)

    2014-03-01

    Effectiveness (Pk) ‐ Platform  Environment ‐ Interface Definition Requirements Flow Interface  Definition Legend Figure 28. DDG-1000 Requirements Flow (from...development specifications and gaps that still exist in requirements. 71 Legacy Missile Requirements Legend DDG1000 Missile...Office Consolidates Programs, Cuts Costs.” Sea Power, Navy League of the United States, Arlington VA. February 2004. Accessed July 2013. http

  5. Attacking the Theater Mobile Ballistic Missile Threat

    Science.gov (United States)

    1993-06-01

    and Record, �Theater Ballistic Missile Defense and US Contingency Operations,� 13. 43Greg Myre, Associated Press, �De Klerk Reveals South African...possession). ____. Briefing, subject: �WarBreaker.� 17 December 1992. Myre, Greg. Associated Press. �De Klerk Reveals South African Nuclear...April�3 May 1992, 1,44. Ordway, Frederick I. III and Ronald C. Wakeford. International Missile and Spacecraft Guide. New York: McGraw

  6. Ballistic Missile Defense. Past and Future

    Science.gov (United States)

    2010-04-01

    and deployed. These are the two big questions of the anti-ballistic missile ( ABM ) debate. It must be emphasized that the...is the extreme polarization of the opposing positions that have been taken. Consider this statement: “The whole ABM question touched off so intense...earlier that same year by the Washington Post and ABC News11 reported that 80 percent of the American population was in favor of building a missile

  7. Quality and Reliability of Missile System

    Directory of Open Access Journals (Sweden)

    Mr. Prahlada

    2002-01-01

    Full Text Available Missile system is a single-shot weapon system which requires very high quality and reliability. Therefore, quality and reliability have to be built into the system from designing to testing and evaluation. In this paper, the technological challenges encountered during development of operational missile system and the factors considered to build quality and reliability through the design, manufacture, assembly, testing and by sharing the knowledge with other aerospace agencies, industries and institutions, etc. have been presented.

  8. Acquisition of the Army Tactical Missile System Anti-Personnel/Anti-Materiel Block IA Program

    National Research Council Canada - National Science Library

    1998-01-01

    The Army Tactical Missile System Anti-PersonnellAnti-Materiel Block IA missile (Block IA) is a ground-launched missile system consisting of a surface-to-surface guided missile with an anti-personnel/anti-materiel warhead...

  9. Variable centroid control scheme over hypersonic tactical missile

    Institute of Scientific and Technical Information of China (English)

    Yl; Yan(易彦); ZHOU; Fengqi(周凤岐)

    2003-01-01

    This paper presents a brand-new tactical missile control scheme--variable centroid vector control according to the international highlight in the field of missile control and the research status of hypersonic missile control in China. Four critical problems related with the new control method are included: improving phase control in the spinning missile single-channel control; establishing variable centroid controlled spinning missile attitude dynamics equations; analyzing variable centroid control strategies and analyzing the stability of the controlled missile and implementing robust control. The achievements and results obtained are valuable and helpful to the theoretical explorations and engineering applications.

  10. Variable centroid control scheme over hypersonic tactical missile

    Science.gov (United States)

    Yi, Yan; Zhou, Fengqi

    2003-12-01

    This paper presents a brand-new tactical missile control scheme—variable centroid vector control according to the international highlight in the field of missile control and the research status of hypersonic missile control in China. Four critical problems related with the new control method are included: improving phase control in the spinning missile single-channel control; establishing variable centroid controlled spinning missile attitude dynamics equations; analyzing variable centroid control strategies and analyzing the stability of the controlled missile and implementing robust control. The achievements and results obtained are valuable and helpful to the theoretical explorations and engineering applications.

  11. Influence of Missile Fusillade Engagement Mode on Operation Efficiency

    Institute of Scientific and Technical Information of China (English)

    BU Xian-jin; REN Yi-guang; SHA Ji-chang

    2008-01-01

    Shoot efficiency is one of the most important evaluation indexes of the operation efficiency of weapon system. In this paper, based on definitions of the probability and the expected number of missed attacking missiles, the expected numbers of anti-missiles and attacking missiles hit by single anti-missile, fusillade mechanism of multi-missile is analyzed systematically. The weapon operation efficiency in various engagement patterns is also studied. The results show that double missiles fusillade is the most feasible manner for increasing the weapon operation efficiency.

  12. Missile captive carry monitoring using a capacitive MEMS accelerometer

    Science.gov (United States)

    Hatchell, Brian; Mauss, Fred; Santiago-Rojas, Emiliano; Amaya, Ivan; Skorpik, Jim; Silvers, Kurt; Marotta, Steve

    2010-03-01

    Military missiles are exposed to many sources of mechanical vibration that can affect system reliability, safety, and mission effectiveness. One of the most significant exposures to vibration occurs when the missile is being carried by an aviation platform, which is a condition known as captive carry. If the duration of captive carry exposure could be recorded during the missile's service life, several advantages could be realized. Missiles that have been exposed to durations outside the design envelop could be flagged or screened for maintenance or inspection; lightly exposed missiles could be selected for critical mission applications; and missile allocation to missions could be based on prior use to avoid overuse. The U. S. Army Aviation and Missile Research Development and Engineering Center (AMRDEC) has been developing health monitoring systems to assess and improve reliability of missiles during storage and field exposures. Under the direction of AMRDEC staff, engineers at the Pacific Northwest National Laboratory have developed a Captive Carry Health Monitor (CCHM) for the HELLFIRE II missile. The CCHM is an embedded usage monitoring device installed on the outer skin of the HELLFIRE II missile to record the cumulative hours the host missile has been in captive carry mode and thereby assess the overall health of the missile. This paper provides an overview of the CCHM electrical and package design, describes field testing and data analysis techniques used to identify captive carry, and discusses the potential application of missile health and usage data for real-time reliability analysis and fleet management.

  13. Missile Captive Carry Monitoring using a Capacitive MEMS Accelerometer

    Energy Technology Data Exchange (ETDEWEB)

    Hatchell, Brian K.; Mauss, Fredrick J.; Santiago-Rojas, Emiliano; Amaya, Ivan A.; Skorpik, James R.; Silvers, Kurt L.; Marotta, Steve

    2010-04-08

    Military missiles are exposed to many sources of mechanical vibration that can affect system reliability, safety, and mission effectiveness. One of the most significant exposures to vibration occurs when the missile is being carried by an aviation platform, which is a condition known as captive carry. If the duration of captive carry exposure could be recorded during the missile’s service life, several advantages could be realized. Missiles that have been exposed to durations outside the design envelop could be flagged or screened for maintenance or inspection; lightly exposed missiles could be selected for critical mission applications; and missile allocation to missions could be based on prior use to avoid overuse. The U. S. Army Aviation and Missile Research Development and Engineering Center (AMRDEC) has been developing health monitoring systems to assess and improve reliability of missiles during storage and field exposures. Under the direction of AMRDEC staff, engineers at the Pacific Northwest National Laboratory have developed a Captive Carry Health Monitor (CCHM) for the HELLFIRE II missile. The CCHM is an embedded usage monitoring device installed on the outer skin of the HELLFIRE II missile to record the cumulative hours the host missile has been in captive carry mode and thereby assess the overall health of the missile. This paper provides an overview of the CCHM electrical and package design, describes field testing and data analysis techniques used to identify captive carry, and discusses the potential application of missile health and usage data for real-time reliability analysis and fleet management.

  14. Theater Ballistic Missile Defense Policy, Missions and Programs: Current Status

    Science.gov (United States)

    2007-11-02

    destroy its target. A French-Italian program called SAMP/T (Sol-Air Moyenne Portee/ Terrestre ) is being considered for a point defense system; further...Patriot PAC-3 missile. The Multimode Missile includes semi-active track- via -missile guidance, improved propulsion and uses an aimed blast

  15. The effectiveness of the U.S. missile defense capabilities as a deterrent to the North Korean missile threat

    OpenAIRE

    Gipson, Issac G.

    2007-01-01

    Over the last five years, America has placed an ever-increasing emphasis on missile defense and currently spends nearly $10 billion annually on its development. The United States' current missile Defense system is integrated; it depends on the cooperation of defensive elements aboard ships, on land, in the air and space. The objective is to provide a layered defense with multiple opportunities to destroy an incoming missile. By investing heavily in missile defense technology, the United ...

  16. The new politics of missile proliferation

    Energy Technology Data Exchange (ETDEWEB)

    Karp, A. [Old Dominion Univ., Norfolk, VA (United States)

    1996-10-01

    The author addresses the most consequential proliferation battle of the 1990s which occurred in Washington over the interpretation of the long-term threat to the United States from ballistic missiles. In the early 1970s, the stabilization of the US-Soviet strategic relationship led to new disputes over the other side`s future intentions, seen most graphically in Western debates over the implications of the Soviet SS-18 and SS-20 missile programs. Today, in much the same way, proliferation politics has matured to the point that surprises are few and the most challenging problem is anticipating the more distant future. Washington`s ballistic missile proliferation battle was sparked by National Intelligence Estimate (NIE) 95-19, entitled {open_quotes}Emerging Threats to North America During the Next 15 Years,{close_quotes} released by the National Intelligence Council in November 1995. This document updated the evidence of regional missile programs reviewed in a similar report issued in 1993, and recapitulated the previous finding that {open_quotes}No country, other than the major declared nuclear powers, will develop or otherwise acquire a ballistic missile in the next 15 years that could threatened the contiguous 48 states or Canada.{close_quotes} The new report confirmed what several other studies of missile proliferation had already established: that besides the five nuclear-weapon states (the United States, Russia, China, France and Britain), only India, Israel and Japan are in a position to develop an ICBM during the foreseeable future, and while all have relevant capabilities, none are undertaking the steps necessary to develop an actual ICBM.

  17. Current Trends in Tactical Missile Guidance

    Directory of Open Access Journals (Sweden)

    S. Vathsal

    2005-07-01

    Full Text Available The problem of tactical missile guidance is very challenging and has been treated using several basic metlfodologies in the past four decades. Major techniques can be grouped underclassical guidance laws, modern guidance laws, l'aws for manoeuvring targets, predictive guidance for endgame scenario, and guidance laws based on intelligent control methods. Each technique has some advantages and disadvantages while implementing in a practical system. Guidance law selection is dictated by nature of flight profile like boost, midcourse, terminal homing, etc, and also miss-distance and a single-shot kill probability. This paper presents a brief survey of the existing techniques and current trends in tactical missile guidance.

  18. Air and Missile Defense Radar (AMDR)

    Science.gov (United States)

    2015-12-01

    March 8, 2016 11:04:34 UNCLASSIFIED 4 CAPT Seiko Okano 1333 Isaac Hull Ave , SE Washington, DC 20376-7101 seiko.okano@navy.mil Phone: 202-781-0461 Fax: DSN...to the combat system. AMDR will be deployed on the Guided Missile Destroyer (DDG) 51 Flight III. AMDR December 2015 SAR March 8, 2016 11:04:34...Abbreviations Ao - Operational Availability CMS - Combat Management System DDG - Guided Missile Destroyer kW - Kilowatt TTL - Training Task List AMDR December

  19. EFP Warhead Missile Fuze Analysis and Simulation

    Institute of Scientific and Technical Information of China (English)

    LI Wei; FAN Ning-jun; WANG Zheng-jie

    2008-01-01

    The explosive formed penetrator(EFP)warhead missile projects the blast fragments in one direction normal to the missile longitudinal axis.Through analyzing on the two restrictions of EFP warhead explosion:trajectory restriction and attitude requirement,the concept of fuse time-delay tolerance is presented to be the measurement of the time of the EFP warhead explosion.The calculation models of fuze time-delaY tolerance under two restrictions are provided.Some crucial parameters playing important roles in calculation under attitude requirements are simulated.The simulation results show that the engagement plane angle,roll rate and warhead attack standoff influence the tolerance dramatically.

  20. An analysis of Common Missile and TOW 2B using the Janus combat simulation

    OpenAIRE

    2002-01-01

    Approved for public release; distribution is unlimited. The US Army is currently developing a new close combat missile system, Common Missile, to replace the aging Tubelaunched, Optically-tracked, Wire-guided (TOW 2B) and HELLFIRE missile systems. The Common Missile will have a greater range and improved target acquisition capability over the current missile systems. The purpose of this thesis is to compare the performance of the Common Missile and the TOW 2B missile in a simulated ground ...

  1. Rationale for wind-borne missile criteria for DOE facilities

    Energy Technology Data Exchange (ETDEWEB)

    McDonald, J R; Murray, R

    1999-09-01

    High winds tend to pick up and transport various objects and debris, which are referred to as wind-borne missiles or tornado missiles, depending on the type of storm. Missiles cause damage by perforating the building envelope or by collapsing structural elements such as walls, columns or frames. The primary objectives of this study are as follows: (1) to provide a basis for wind-borne or tornado missile criteria for the design and evaluation of DOE facilities, and (2) to provide guidelines for the design and evaluation of impact-resistant missile barriers for DOE facilities The first objective is accomplished through a synthesis of information from windstorm damage documentation experience and computer simulation of missile trajectories. The second objective is accomplished by reviewing the literature, which describes various missile impact tests, and by conducting a series of impact tests at a Texas Tech University facility to fill in missing information.

  2. CRANIOCEREBRAL MISSILE INJURY A STATISTICAL REVIEW

    Directory of Open Access Journals (Sweden)

    ALI ALIMOHAMMADI

    1986-05-01

    Full Text Available A Statistical report of 912 battle casualtiesadmitted in a special unit of the neurological surgery department during 49 months of the recent war was given. Methods of their evaluation, operative categories, management poli¬cies including techniques of Missile and bullet removal, and their complications were discussed.

  3. Cruise missiles should not stop START

    Energy Technology Data Exchange (ETDEWEB)

    Tsipis, K.

    1988-11-01

    A method for verifying a cruise-missile agreement that would be acceptable to the military, industrial, and intelligence communities in both nations must be as unintrusive as possible, while remaining immune to cheating of any significance. This is the goal of the technical solutions outlined here. The elements of a verification regime described do not require routine, intrusive, on-site visits to naval vessels, aircraft, air bases, or weapons magazines where missiles may be stored. They do not interfere with the operational readiness of the missiles, and they protect legitimate military secrets of the inspected nation. If supported by competent national technical means of verification such as those both sides already employ, with a small number of on-site challenge inspections, a combination of technical solutions and procedures such as these could be effective. They would adequately safeguard the national security and sovereignty of the participating nations while providing policymakers with the option of a treaty that limits the number of long-range nuclear cruise missiles or eliminates them completely. As discussed, there are problems that remain to be addressed, but they should not be allowed to block a U.S.-Soviet agreement significantly reducing strategic nuclear arsenals.

  4. Integrated Air and Missile Defense (IAMD)

    Science.gov (United States)

    2015-12-01

    IBCS. The cruise missile surrogate, an MQM-107 Drone Target, flew a low altitude trajectory against an asset defended by an Army IAMD task force...FY 2048 The difference in the acquisition quantity of 443 and the sustainment quantity of 427 is due to 16 RDT&E prototypes that are not to be

  5. Minimum variation guidance laws for interceptor missiles

    NARCIS (Netherlands)

    Weiss, M.; Shima, T.

    2014-01-01

    This paper introduces a new approach to guidance law design using linear quadratic optimal control theory, minimizing throughout the engagement the variation of the control input as well as the integral control effort. The guidance law is derived for arbitrary order missile dynamics and target maneu

  6. 关节镜下横杆式固定重建膝前十字韧带的中期疗效观察%The mid-term results of arthroscopic anterior cruciate ligament reconstruction using Transfix technique

    Institute of Scientific and Technical Information of China (English)

    李卫平; 陈仲; 宋斌; 杨睿; 谭伟权

    2013-01-01

    目的 评价关节镜下自体腘绳肌腱移植、横杆式固定(transfix)重建膝关节前十字韧带(anterior cruciate ligament,ACL)的中期临床疗效.方法 自2002年8月至2003年12月对38例膝关节ACL断裂患者应用自体腘绳肌腱重建ACL、股骨端采用横杆式固定、胫骨端采用界面螺钉固定.男21例,女17例;年龄19~48岁,平均28.4岁;左膝24例,右膝14例.运动伤27例,交通伤2例,跌倒扭伤2例,余7例无明显外伤.急性损伤6例,陈旧性损伤32例.术前体检:前抽屉试验阳性35例,弱阳性1例,阴性2例;Lachman征阳性37例,弱阳性1例.以Lysholm评分评价中期临床疗效,以MRI及X线观察移植物以及骨隧道变化情况.结果 38例患者中36例获得随访(随访率94.7%),随访时间6.3~7.6年,平均6.8年.所有患者关节活动度正常,Lysholm评分由术前(64.4±4.52)分提高到(85.6±4.60)分,差异有统计学意义.X线及MRI发现3例股骨及胫骨隧道均扩大,5例股骨隧道扩大,3例胫骨隧道近端扩大.未见关节间隙变窄.1例患者在术后4年因外伤再次致ACL断裂,行关节镜下ACL翻修术,采用同种异体肌腱移植物,股骨端及胫骨端采用可吸收挤压钉固定.结论 应用腘绳肌腱、股骨侧横杆式、胫骨侧界面挤压螺钉固定重建膝关节ACL可以获得较为满意的关节活动度及关节稳定性,中期疗效佳.%Objective To evaluate the mid-term results of arthroscopic anterior cruciate ligament (ACL) reconstruction using Transfix technique.Methods From August 2002 to December 2003,38 patients (24 left knees and 14 right knees) with ACL ruptures underwent arthroscopic ACL reconstruction with hamstring tendon using Transfix femoral fixation and interference screws tibial fixation.There were 21 males and 17 females,aged from 19 to 48 years (average,28.4 years).The causes of injury included sports injury in 27 cases,traffic injury in 2 cases and fall injury in 2 cases,and 7 patients had no

  7. Modeling and Simulating Dynamics of Missiles with Deflectable Nose Control

    Institute of Scientific and Technical Information of China (English)

    Gao Yuan; Gu Liangxian; Pan Lei

    2009-01-01

    This article investigates the dynamic characteristics of deflectable nose missiles with rotary single-channel control. After introduction of effective attack and sideslip angles as well as quasi-body coordinates based on the spin characteristics of the missile's body, an integrated rigid kinetic model of missile with deflectable nose control is set up in the quasi-body coordinates considering the interaction between the missile's nose and body by using rootless multi-rigid-body system dynamics and is linearized. Then an analysis with simulation is conducted to investigate the coupling characteristics between the channels, the influences of nose deflection on the body and the dynamic characteristics of missile's body. The results indicate that various channels of missiles with deflectable nose control are coupled cross-linked; the nose deflection tends to make the body move in the opposite direction and, finally, evidences the correctness and reasonability of the kinetic model proposed by this article.

  8. Ballistic Missile Silo Door Monitoring Analysis

    Energy Technology Data Exchange (ETDEWEB)

    EDENBURN,MICHAEL W.; TROST,LAWRENCE C.

    2000-01-01

    This paper compares the cost and effectiveness of several potential options that may be used to monitor silo-based ballistic missiles. Silo door monitoring can be used to verify that warheads removed to deactivate or download silo-based ballistic missiles have not been replaced. A precedent for monitoring warhead replacement using reentry vehicle on site inspections (RV-OSIs) and using satellites has been established by START-I and START-II. However, other monitoring options have the potential to be less expensive and more effective. Three options are the most promising if high verification confidence is desired: random monitoring using door sensors; random monitoring using manned or unmanned aircraft; and continuous remote monitoring using unattended door sensors.

  9. Using NASTRAN to model missile inertia loads

    Science.gov (United States)

    Marvin, R.; Porter, C.

    1985-01-01

    An important use of NASTRAN is in the area of structural loads analysis on weapon systems carried aboard aircraft. The program is used to predict bending moments and shears in missile bodies, when subjected to aircraft induced accelerations. The missile, launcher and aircraft wing are idealized, using rod and beam type elements for solution economy. Using the inertia relief capability of NASTRAN, the model is subjected to various acceleration combinations. It is found to be difficult to model the launcher sway braces and hooks which transmit compression only or tension only type forces respectively. A simple, iterative process was developed to overcome this modeling difficulty. A proposed code modification would help model compression or tension only contact type problems.

  10. Ballistic Missile Defense: New Plans, Old Challenges

    Directory of Open Access Journals (Sweden)

    Elizabeth Zolotukhina

    2010-01-01

    Full Text Available On September 17, 2009—the 70th anniversary of the Soviet invasion of Poland in 1939 that marked the beginning of World War II—the Obama Administration announced its intention to shelve plans for the U.S. Ballistic Missile Defense (BMD that had been developed under former President George W. Bush. Pointing to a new intelligence assessment, President Obama argued that his predecessor's plan to deploy an X-band radar station outside of Prague, Czech Republic, and 10 two-stage interceptor missiles in Poland would not adequately protect America and its European allies from the Iranian threat and reiterated his opposition to utilizing unproven technology in any European BMD architecture.

  11. Reliability Simulation for a Missile Tank Under Random Loading

    Institute of Scientific and Technical Information of China (English)

    2001-01-01

    This paper presents a Monte-Carlo simulation method to calculate intensity relia- bility for a missile tank under random loading. The cumulative damage mathematical mod- el is established, and it adopts a direct simulation method to present random loading and o-riginal intensity for a missile tank. It can effectively predict intensity reliability for a missile tank in the environment of transport and flight.

  12. The Joint Cruise Missiles Project: An Acquisition History

    Science.gov (United States)

    1982-08-01

    his staff at the Air Force ALCM System Project Office. The authors are, of course , solely responsible for the accuracy and interpretation of the...meaning) Sea launched cruise missile (current meaning) SPOC System Project Officers Council SRAM Short range attack missile STCM Supersonic tactical...Council ( SPOC ), com- posed of the directors of the four major missile systems (consisting at that time of the GLCM, ship- and sub-launched SLCM, and the

  13. Theater Missile Defenses and U.S. Foreign Policy

    Science.gov (United States)

    1992-01-01

    and Joseph Rotblat (London: Macmillan Press, 1987), p. 171. 11 dowry " to alleviate European fears of being left defenseless as the U.S. retreated behind...surface missile, the design of which came from reverse-engineering of U.S. Nike-Hercules surface-to-air missiles. 59 India could be on the verge of...indigenous production with the testing of its Privthi missile. India has also demonstrated successful development of an indigenous space launch capacity

  14. On the Dynamic Stability of a Missile

    Directory of Open Access Journals (Sweden)

    K.C. Sharma

    1977-01-01

    Full Text Available The P-method given by Parks and Pritchard has been used to discuss the stability behaviour of a missile in free flight. General stability criteria for aerodynamic stabilisation have been obtained for slowly varying coefficients. The effect of pressure gradient on the stability of a coasting rocket has been explicitly examined. It is observed that the positive Magnus moment parameter ensures stability whereas a negative moment parameter would enhance the requirements of a larger stability margin.

  15. Cruise Missile Attack Are We Prepared

    Science.gov (United States)

    2007-03-09

    to be met to make its air and missile defense systems interoperable with others throughout the military because the requirements for SIAP [Single...Single Integrated Air Picture ( SIAP ) and Integrated Fire Control (IFC). SIAP “is the product of fused, near real-time and real-time data from...guidance of the Assistant Secretary of the Army for Acquisition, Logistics, and Technology (ASAALT), the Joint SIAP System Engineering Organization (JSSEO

  16. Sustainability Of The 21M Missile Maintainer

    Science.gov (United States)

    2016-02-16

    considering alternative career field models for missile maintenance officers. Benefits can include discovering lessons learned and best practices to improve...entire ICBM community in mitigating today’s problems and securing the confidence of the service and public. Introduction Mission failure has...which are applied to an alternative ICBM career field model . The paper closes in offering conclusions and recommendations about improving the health

  17. The Future of Theater Missile Defense

    Science.gov (United States)

    1994-06-01

    withERINT) 1,500 IVf 74C 1998 3.0 Navy Lower-Tier Defense 1,820 SO4 50* 1999° 3* THAAD(withTMD-GBR) 1,313 80 14 2001e 9.1 AdvaaoedCapabflitylMD Systems...Administration cannot, by itself, provide a sufficient buffer between theater and strategic missile defenses. Other limits must be included. Finally, the

  18. The Evolution of the Cruise Missile

    Science.gov (United States)

    1985-09-01

    device as a target in operations with the cartier Ranger in August, 1938. These and subqueat practice sessions revealed shockingly poor US Navy... market within a very short time." TIhe author speculated that the device could destroy an entire town as far as 100 miks away with no loss te the...downed 72.8 percent of the 125 missiles observed. Nevertheless, one flying bomb hit Smithfield Market on 8 March, causing 233 casualties.61 In all, the

  19. Intelligent Design and Implementation of Missile Fire Control System

    Institute of Scientific and Technical Information of China (English)

    XIE Chun-si; WANG Min-qing; LI Wei-hai; LIU Xi-zuo; JIN Liang-an

    2006-01-01

    Missile fire control system is the core of ship-based missile weapon system, whose safeguard levelhas direct relation with the attack ability of naval vessels. After a long period of deep investigation and research, it was found that, in one missile fire control system, there are such problems as single safeguard system, low ratio of cost to efficiency, etc. By adopting intelligent control techniques and many measures to multiple securities, the new type of assistant system is designed, some difficult problems are solved, such as fixed project channel and unitary means of missiles, which can make the equipment carry out combat mission reliably and continuously.

  20. Absolute and contrast infrared signatures from missile noses

    Science.gov (United States)

    Tofani, Alessandro

    1990-10-01

    The infrared radiant intensity and radiative contrast produced by the aerodynamic and solar heating of missile noses have been obtained by computer simulating the corresponding temperature distributions and by taking into account the effects of both atmosphere (absorption and self-emission) and target geometry (distance, aspect and elevation angles). Six target classes have been considered, including cruise missiles, air-to-air and surface-to-surface missiles, and ballistic missiles. The comparison between radiative quantities in the 3 to 5 μm and S to 12 μm atmospheric transmittance windows gives the optimum spectral band for target detection in each point of its trajectory.

  1. Trident II (D-5) Sea Launched Ballistic Missile UGM 133A (Trident II Missile)

    Science.gov (United States)

    2015-12-01

    on quality training and unscheduled down time on the rocket motor precision drilling machine . Trident II Missile December 2015 SAR March 17, 2016...chocks, Third Stage (TS) dollies and TS Motor Supports and completion of machining and welding for Aerospike Protective Caps; 2) Early delivery of

  2. Common Ada Missile Packages. Phase 2. (CAMP-2). Volume 2. 11th Missile Demonstration

    Science.gov (United States)

    1988-11-01

    bii t Ui< «i > i martial Sanaor Aaaaaibly 11th Miaaila Syatam Figure 1. 11th Missile Hardware Design TABLE 2. PROCESSORS AND THEIR FUNCTIONS...ualng Two Value Aretangant Coaputa Wander Ailauth Angle ualng Two Value Aretangant SUBTOTALS 132 14» 20 »003 North »olntlng HaTlgatlon » arta Coaputa

  3. Introduction of Women into Titan II Missile Operations.

    Science.gov (United States)

    1981-03-01

    areas (weapons system orientation: mnaintenance management. electronics principles , and technical publications. facility systems and missile Sfstents...Management. Electronics Principles . Technical Publications 97.00 2.63 94.04 5.27 2.31 Facility Systems 92.25 4.61 93.2) 5.80 -.62 Missile Systems 96.67 2.90

  4. Aerodynamic performances of cruise missile flying above local terrain

    Science.gov (United States)

    Ahmad, A.; Saad, M. R.; Che Idris, A.; Rahman, M. R. A.; Sujipto, S.

    2016-10-01

    Cruise missile can be classified as a smart bomb and also Unmanned Aerial Vehicle (UAV) due to its ability to move and manoeuvre by itself without a pilot. Cruise missile flies in constant velocity in cruising stage. Malaysia is one of the consumers of cruise missiles that are imported from other nations, which can have distinct geographic factors including their local terrains compared to Malaysia. Some of the aerodynamic performances of missile such as drag and lift coefficients can be affected by the local geographic conditions in Malaysia, which is different from the origin nation. Therefore, a detailed study must be done to get aerodynamic performance of cruise missiles that operate in Malaysia. The effect of aerodynamic angles such as angle of attack and side slip can be used to investigate the aerodynamic performances of cruise missile. Hence, subsonic wind tunnel testings were conducted to obtain the aerodynamic performances of the missile at various angle of attack and sideslip angles. Smoke visualization was also performed to visualize the behaviour of flow separation. The optimum angle of attack found was at α=21° and side slip, β=10° for optimum pitching and yawing motion of cruise missile.

  5. A History of Polish Anti-Missile Defenses

    Science.gov (United States)

    1994-01-01

    tanks, 1,750 armored personnel carriers, transport 11 aircraft, helicopters, and several naval craft.ŕ The WOPK provided air space management and...targets which included missile-related threats.90 Comunnication was an integral part of missile warning. Since Poland’s WOPK was part of the PVOS, Warsaw

  6. 保留胫骨残端及Transfix固定的前交叉韧带重建%Reconstruction of anterior cruciate ligament with preserved tibial remnants and Transfix fixation

    Institute of Scientific and Technical Information of China (English)

    孙磊; 宁廷民; 吴波; 张磊

    2012-01-01

    Objective To explore the outcomes of arthroscopic reconstruction of the anterior cruciate ligament (ACL) with preserved tibial remnants and Transfix fixation.Methods From October 2009 to October 2010,a total of 69 patients with ACL rupture were treated surgically in our department.The arthroscopy revealed the ruptured ACL had only a partial or remnant tibial end in 26 patients (26 knees) of them.They were 16 males and 10 females,19 to 42 years of age (average,27 years).Their main clinical manifestation was instability of the affected knee.The pivot shift test,Lachmen test and anterior drawer test all had positive results in the 26 patients.The time from injury to surgery varied from 8 to 50 weeks,with an average of 17 weeks.Arthroscopic ACL reconstruction was performed for the 26 knees using the modified transtibial technique without removal of the tibial remnants of ACL and single bundle grafting of autogenous quadrupled hamstring tendons,followed by Transfix fixation.Results No severe complication occurred in the early stage after operation in the 26 patients.All of them were followed up for 12 to 23 months,with an average of 16 months.All the patients returned to pre-injury work without obvious discomfort.Their mean Lysholm score was remarkably improved from 56.7 ± 9.5 points (from 46 to 75 points) preoperatively to 95.6 ± 6.2 (85 to 100 points) at the latest follow up ( t =17.496,P < 0.05).The anterior drawer test showed only 3 positive results (1 + ) but the pivot shift test and Lachmen test were both negative in all the patients.There was a significant improvement in the International Knee Documentation Committee,IKDC)score (grade C in 12 knees and grade D in 14 knees preoperatively versus grade A in 20 knees and grade B in 6 knees at the last follow-up) ( Z =4.565,P < 0.05 ).Conclusion Arthroscopic ACL reconstruction with preserved tibial remnants and Transfix fixation can lead to satisfactory clinical outcomes because it facilitates the biological

  7. The science, technology, and politics of ballistic missile defense

    Science.gov (United States)

    Coyle, Philip E.

    2014-05-01

    America's missile defense systems are deployed at home and abroad. This includes the Groundbased Missile Defense (GMD) system in Alaska and California, the Phased Adaptive Approach in Europe (EPAA), and regional systems in the Middle East and Asia. Unfortunately these systems lack workable architectures, and many of the required elements either don't work or are missing. Major review and reconsideration is needed of all elements of these systems. GMD performance in tests has gotten worse with time, when it ought to be getting better. A lack of political support is not to blame as the DoD spends about 10 billion per year, and proposes to add about 5 billion over the next five years. Russia objects to the EPAA as a threat to its ICBM forces, and to the extensive deployment of U.S. military forces in countries such as Poland, the Czech Republic and Romania, once part of the Soviet Union. Going forward the U.S. should keep working with Russia whose cooperation will be key to diplomatic gains in the Middle East and elsewhere. Meanwhile, America's missile defenses face an enduring set of issues, especially target discrimination in the face of attacks designed to overwhelm the defenses, stage separation debris, chaff, decoys, and stealth. Dealing with target discrimination while also replacing, upgrading, or adding to the many elements of U.S. missiles defenses presents daunting budget priorities. A new look at the threat is warranted, and whether the U.S. needs to consider every nation that possesses even short-range missiles a threat to America. The proliferation of missiles of all sizes around the world is a growing problem, but expecting U.S. missile defenses to deal with all those missiles everywhere is unrealistic, and U.S. missile defenses, effective or not, are justifying more and more offensive missiles.

  8. The science, technology, and politics of ballistic missile defense

    Energy Technology Data Exchange (ETDEWEB)

    Coyle, Philip E. [Center for Arms Control and Non-Proliferation, Washington, DC (United States)

    2014-05-09

    America's missile defense systems are deployed at home and abroad. This includes the Groundbased Missile Defense (GMD) system in Alaska and California, the Phased Adaptive Approach in Europe (EPAA), and regional systems in the Middle East and Asia. Unfortunately these systems lack workable architectures, and many of the required elements either don't work or are missing. Major review and reconsideration is needed of all elements of these systems. GMD performance in tests has gotten worse with time, when it ought to be getting better. A lack of political support is not to blame as the DoD spends about $10 billion per year, and proposes to add about $5 billion over the next five years. Russia objects to the EPAA as a threat to its ICBM forces, and to the extensive deployment of U.S. military forces in countries such as Poland, the Czech Republic and Romania, once part of the Soviet Union. Going forward the U.S. should keep working with Russia whose cooperation will be key to diplomatic gains in the Middle East and elsewhere. Meanwhile, America's missile defenses face an enduring set of issues, especially target discrimination in the face of attacks designed to overwhelm the defenses, stage separation debris, chaff, decoys, and stealth. Dealing with target discrimination while also replacing, upgrading, or adding to the many elements of U.S. missiles defenses presents daunting budget priorities. A new look at the threat is warranted, and whether the U.S. needs to consider every nation that possesses even short-range missiles a threat to America. The proliferation of missiles of all sizes around the world is a growing problem, but expecting U.S. missile defenses to deal with all those missiles everywhere is unrealistic, and U.S. missile defenses, effective or not, are justifying more and more offensive missiles.

  9. Recent Advances in Antitank Guided Missile Systems

    Directory of Open Access Journals (Sweden)

    N. R. Iyer

    1995-07-01

    Full Text Available The recent advances in tactical antitank guided missile (ATGM systems are discussed. The main driving factors for the technological advances towards realisation of third generation ATGM systems have been the more demanding operational needs of the user services and limitations of earlier generation ATGM systems. The tasks of system design, hardware realisation, integration, testing and qualification have become extremely challenging to meet these stringent operational requirements. The technologies required to be mobilised for meeting these operational requirements and performance envelope and satisfying the operational and logistics constraints are again very demanding. The high technology content and the high level of performance required out of the subsystems have led to the present generation missile systems. The evolution from the earlier generations to current systems has been briefly discussed. Imaging infrared (IIR and Millimetre wave (MMW guidance systems employed for achieving the fire and forget capability of the third generation ATGM are described with specific reference to progress achieved so far. Translating the mission requirements to preliminary system specifications is another area wherein an innovative approach only can lead to meet the multiple performance criteria. Performance growth profile and emerging trends in ATGM systems are also analysed.

  10. CT analysis of missile head injury

    Energy Technology Data Exchange (ETDEWEB)

    Besenski, N. [Dept. of Radiology, Zagreb Univ. Hospital Rebro (Croatia); Jadro-Santel, D. [Dept. of Neuropathology, Zagreb Univ. Hospital Rebro (Croatia); Jelavic-Koic, F. [Dept. of Radiology, General Hospital Sveti Duh, Zagreb (Croatia); Pavic, D. [Dept. of Neuropathology, Zagreb Univ. Hospital Rebro (Croatia); Mikulic, D. [Zagreb School of Medicine (Croatia); Glavina, K. [Dept. of Radiology, Clinical Hospital, Osijek (Croatia); Maskovic, J. [Dept. of Radiology, Clinical Hospital, Split (Croatia)

    1995-04-01

    Between August 1991 and December 1992, CT was performed in 154 patients who had suffered missile head injury during the war in the Republic of Croatia. In 54% CT was performed 1-24 h after injury, and in 27% follow-up CT was also obtained. The wounds were penetrating, tangential or perforating (45%, 34% and 21%, respectively). Haemorrhage was the most frequent lesion in the brain (84%). Follow-up CT evolution of haemorrhage, oedema, cerebritis, abscess, secondary vascular lesions, necrosis, encephalomalacia and hydrocephalus. The most dynamic changes occurred 7-14 days after injury. In 14% of cases, deep cerebral lesions were found in the corpus callosum, septum pellucidum periventricular region and pons, although bone and shell fragments were in a different part of the brain parenchyma. Such lesions were found in penetrating injuries only. CT proved very useful for assessing the extent and type of lesions. Although different mechanisms of brain damage in missile head injury are known, here they are, to the best of our knowledge, shown for the first time by CT. (orig.)

  11. Modelling cavitating flow around underwater missiles

    Directory of Open Access Journals (Sweden)

    Fabien Petitpas

    2011-12-01

    Full Text Available The diffuse interface model of Saurel et al. (2008 is used for the computation of compressible cavitating flows around underwater missiles. Such systems use gas injection and natural cavitation to reduce drag effects. Consequently material interfaces appear separating liquid and gas. These interfaces may have a really complex dynamics such that only a few formulations are able to predict their evolution. Contrarily to front tracking or interface reconstruction method the interfaces are computed as diffused numerical zones, that are captured in a routinely manner, as is done usually with gas dynamics solvers for shocks and contact discontinuity. With the present approach, a single set of partial differential equations is solved everywhere, with a single numerical scheme. This leads to very efficient solvers. The algorithm derived in Saurel et al. (2009 is used to compute cavitation pockets around solid bodies. It is first validated against experiments done in cavitation tunnel at CNU. Then it is used to compute flows around high speed underwater systems (Shkval-like missile. Performance data are then computed showing method ability to predict forces acting on the system.

  12. Gauging the Influence of Technology on Tactical Missiles of the Future(Short Communication

    Directory of Open Access Journals (Sweden)

    Mark L. Bundy

    2002-01-01

    Full Text Available Tactical missiles, carrying kinetic energy, high explosives, or multiple submunitions are an integral part of the current and future US Army weapons inventory. Naturally, the number of missiles that can be stowed on any mobile launch platform depends on the size of the missile. Advances in rocket propulsion efficiency and improvements in guidance systems may make it possible to reduce missile size without a proportionate decrease in effectiveness. A primitive I-DOF computer model is used here to show how advances in missile technology might allow smaller missiles in the future to carry out the mission of today's larger missiles. A scaled-down version of a typical current generation missile is taken as the next generation missile. Hypothetical improvements in this smaller missile are then chosen in four basic areas-propellant impulse, burn time, weight fraction, and aerodynamic drag.-with the effects on lethality reported in a nondimensional format.

  13. Innovation in Aerodynamic Design Features of Soviet Missiles

    Science.gov (United States)

    Spearman, M. Leroy

    2006-01-01

    Wind tunnel investigations of some tactical and strategic missile systems developed by the former Soviet Union have been included in the basic missile research programs of the NACA/NASA. Studies of the Soviet missiles sometimes revealed innovative design features that resulted in unusual or unexpected aerodynamic characteristics. In some cases these characteristics have been such that the measured performance of the missile exceeds what might have been predicted. In other cases some unusual design features have been found that would alleviate what might otherwise have been a serious aerodynamic problem. In some designs, what has appeared to be a lack of refinement has proven to be a matter of expediency. It is a purpose of this paper to describe some examples of unusual design features of some Soviet missiles and to illustrate the effectiveness of the design features on the aerodynamic behavior of the missile. The paper draws on the experience of the author who for over 60 years was involved in the aerodynamic wind tunnel testing of aircraft and missiles with the NACA/NASA.

  14. A Low-Visibility Force Multiplier: Assessing China’s Cruise Missile Ambitions

    Science.gov (United States)

    2014-04-01

    and ballistic missile force will be far less effective than its numbers would indicate. 18 Forensic data may not have been collected and analyzed for...and ballistic missiles; some has focused on Chinese efforts to develop an antiship ballistic missile that might tar- get U.S. aircraft carriers. One...electronically scanned array AIP air-independent propulsion ARM antiradiation missile ASAT antisatellite ASBM antiship ballistic missile ASCM antiship

  15. Strapdown inertial systems applications for tactical missiles (stand-off missiles)

    Science.gov (United States)

    Puech

    1986-06-01

    Strapdown Inertial Systems (SDIS) are particularly well suited for tactical standoff missile applications. This certainty was made clear by several years of theoretical design work and trials. Initial theoretical work made wide use of parameters giving detailed definition of missile trajectories and motions as obtained from measurements made on weapon systems then in development or production. Sensors (principally gyroscopes) were laboratory tested. These preliminary design efforts led to selection of various technologies such as the laser gyro and the mechanical gyro, each being adapted to the weapon system in question. Share-out of functions between various equipment items was defined. Comparison of the advantages and disadvantages of these technologies shows that today the laser gyro is principally retained for high and medium range levels of precision, with the mechanical (spin-stabilized) gyro serving in the medium and low precision range. Since requirements are ever increasing in the fields of dynamic performance and robustness, it is here that most progress is expected.

  16. TOW Missile Pallet MIL-STD-1660 Tests

    Science.gov (United States)

    1993-08-01

    0 DTICS ELECTE FEB 2 19941 FINAL REPORT C U ow AUGUST 1993 (V V Lfl3 NNE REPORT NO. 93-23 TOW MISSILE PALLET MIL- STD -1660 TESTS Prepared for...TITLE gOnakde Secwir Casaftedon) TOW Missile Pallet MIL- STD -1660 Tests 12. PERSONAL AUTHOR(S) Jason B. Solberg 13s. TYPE OF REPORT 13b. TIME COVERED...and Engineering Center (ARDEC) to test the TOW missile pallet. This report contains the procedures, results, and recommendations from the MIL- STD

  17. Research on ballistic missile laser SIMU error propagation mechanism

    Institute of Scientific and Technical Information of China (English)

    Wei Shihui; Xiao Longxu

    2008-01-01

    It is necessary that the laser inertial system is used to further improve the fire accuracy and quick reaction capability in the ballistic missile strapdown inertial navigation system. According to the guidance con-trolling method and the output and error model of ballistic missile laser SIMU, the mathematical model of error propagation mechanism is set up and any transfer environmental function of error coefficient that affects the fire accuracy is deduced. Also, the missile longitudinal/lateral impact point is calculated using MATLAB. These estab-lish the technical foundation for further researching the dispersion characteristics of impact point and reducing the laser guidance error.

  18. Missile antenna pattern coordinate system and data formats

    Science.gov (United States)

    1993-08-01

    Antenna performance data pertains to missile, space, and aerodynamic vehicles' transmitting or receiving antennas used with range data collection, missile trajectory measurements, impact predictions, communications, or flight termination systems. As used in this document, the terms missile space vehicle, airborne, and aerodynamic vehicle are synonymous. This standard is intended to cover antennas for telemetry, pulsed radar beacons, continuous wave (CW) transponders, communication transmitters and receivers, command control/flight termination, receivers/decoders, pseudo random noise (PRN) ranging systems, and the Global Positioning System.

  19. Aerodynamic heating of ballistic missile including the effects of gravity

    Indian Academy of Sciences (India)

    S N Maitra

    2000-10-01

    The aerodynamic heating of a ballistic missile due to only convection is analysed taking into consideration the effects of gravity. The amount of heat transferred to the wetted area and to the nose region has been separately determined, unlike A Miele's treatise without consideration of gravity. The peak heating ratesto the wetted area and to the nose of the missile are also investigated. Finally four numerical examples are cited to estimate the errors, in heat transfers and heating ratesto both wetted area and nose region of the missile, arising out of neglecting the gravitational forces.

  20. Regional Joint-Integrated Air and Missile Defense (RF-IAMD): An Operational Level Integrated Air and Missile Defense (IAMD) Command and Control (C2) Organization

    Science.gov (United States)

    2015-05-15

    the Naval Air and Missile Defense Command (NAMDC). NAMDC then began training field grade officers through a Weapons and Tactics Instructor ( WTI ...49 Integrated Air and Missile Defense (IAMD) Weapons and Tactics Instructor ( WTI ), Naval Air and Missile...and Missile Defense (IAMD) Weapons and Tactics Instructor ( WTI ). Accessed April 28, 2015. http://namdc.ahf.nmci.navy.mil/site%20pages/wti.htm

  1. Dynamic Simulation for Missile Erection System

    Institute of Scientific and Technical Information of China (English)

    2007-01-01

    In order to study the dynamic characteristics of the missile erection system, it can be considered as a rigid-flexible coupling multi-body system. Firstly, the actual system is abstracted as an equal and simplified one and then the forces applied to it are analyzed. Secondly, the rigid-flexible coupling dynamic simulation for erection system is accomplished by use of the system simulation software, for example Pro/E, ADAMS, ANSYS, MATLAB/Simulink, etc. Finally, having the aid of simulation results, the kinetic and dynamic characteristics of the flexible bodies in erection system are analyzed.The simulation considering the erection system as a rigid-flexible coupling system can provide valuable results to the research of its kinetic, dynamic and vibrational characteristics.

  2. 关节镜下横穿钉固定重建膝关节前交叉韧带的临床疗效分析%Curative effects analysis on arthroscopic anterior cruciate ligament reconstruction with autogenous hamstring or allograft tendon using cross-pin(Transfix) fixation

    Institute of Scientific and Technical Information of China (English)

    温亮; 张博; 王志为; 张晓冬; 曲铁兵; 林源

    2012-01-01

    [Objective] To observe the curative effects on arthroscopic anterior cruciate ligament (ACL) reconstruction with autogenous hamstring or allograft tendon using Transfix at the femoral side, Interference Screw and Spiked Ligament Staple at the tibial side. [ Method]The technique of TransFix fixation was used for reconstructing ACL in 117 cases, including 81 cases with autogenous hamstring and 36 cases with allograft tendon. Pre-and post-operative knee joint function and stability as well as X-ray photograph were evaluated according to the Lysholm scoring scale system. The reliability of the fixation and its short-term effect were analyzed. [ Result]Totally 103 cases were followed, the follow-up duration ranged from 12 to 26 months( average, 18 months) . Lysholm score were 57. 60 ± 5. 74 and 94. 55 ± 2. 38 , respectively before operation and at the time of follow-up( P < 0. 05 ) . Both groups obtained significant improvement of knee stability after operation, with no significant differences between the two groups. [ Conclusion ] Using Transfix for ACL reconstruction under arthroscopy is a safe technique and its clinical outcome has been assured. The autogenous hamstring and allograft tendon have the same clinical therapeutic effects in ACL reconstruction. The graft can be selected according to the traumatic condition and the requirements of patients.%[目的]观察关节镜下股骨侧应用横穿钉(Transfix)固定,胫骨侧界面螺钉(Interference)结合门型钉固定自体腘绳肌腱或同种异体肌腱重建膝关节前交叉韧带的临床疗效.[方法]膝关节前交叉韧带重建患者117例,所有患者均应用股骨侧横穿钉(Transfix)固定,胫骨侧界面螺钉(Interference)结合门型钉固定行前交叉韧带单束重建,其中使用自体胭绳肌腱患者81例,使用同种异体肌腱患者36例,观察此固定方法的可靠性及近期疗效,使用Lysholm评分及IKDC 2000评价手术前后膝关节功能.[结果]103例

  3. The Study of Tactical Missile's Airframe Digital Optimization Design

    Institute of Scientific and Technical Information of China (English)

    LUO Zhiqing; QIAN Airong; LI Xuefeng; GAO Lin; LEI Jian

    2006-01-01

    Digital design and optimal are very important in modern design. The traditional design methods and procedure are not fit for the modern missile weapons research and development. Digital design methods and optimal ideas were employed to deal with this problem. The disadvantages of the traditional missile's airframe design procedure and the advantages of the digital design methods were discussed. A new concept of design process reengineering (DPR) was put forward. An integrated missile airframe digital design platform and the digital design procedure, which integrated the optimization ideas and methods, were developed. Case study showed that the design platform and the design procedure could improve the efficiency and quality of missile's airframe design, and get the more reasonable and optimal results.

  4. Passive Acoustic Radar for Detecting Supersonic Cruise Missile

    Institute of Scientific and Technical Information of China (English)

    XIAO Feng; XIAO Hui

    2005-01-01

    A Passive Acoustic Radar is presented as a necessary complement to electromagnetic wave radar, which will be expected to be an effective means for detecting cruise missiles. Acoustic characteristics of supersonic flying projectiles with diverse shapes are expounded via experiment. It is pointed out that simulation experiment could be implemented using bullet or shell instead of cruise missile. Based on theoretical analysis and experiment, the "acoustic fingerprint" character of cruise missile is illustrated to identify it in a strong noise environment. After establishing a locating mathematical model,the technique of acoustic embattling is utilized to resolve a problem of confirming the time of early-warning, considering the fact that velocity of sound is much slower than that of light. Thereby, a whole system of passive acoustic radar for detecting supersonic cruise missile is formed.

  5. Vortex development on slender missiles at supersonic speeds

    Science.gov (United States)

    Allen, J. M.; Dillenius, M. F. E.

    1979-01-01

    A theoretical and experimental effort has been made to develop a vortex-prediction capability on circular and noncircular missiles at supersonic speeds. Predicted vortex patterns are computed by two linear-theory computer codes. One calculates the strengths and initial locations of the vortices, and the other calculates their trajectories. A short color motion picture has been produced from the calculations to illustrate the predicted vortex patterns on a typical missile. Experimental vapor-screen photographs are presented to show the longitudinal development of the vortices on a fin-control missile. Comparisons are made between these data and the predicted vortices to assess the accuracy of the theory. The theory appears to be fairly accurate in predicting the number, locations, and relative strengths of individual vortices which develop over the missile, but cannot predict vortex sheets or diffuse vorticity whenever they occur.

  6. Revolution in military affairs, missile defence and weapons in space ...

    African Journals Online (AJOL)

    Revolution in military affairs, missile defence and weapons in space: the US ... 1991 Gulf War that captured the imagination of military planners and policy makers, ... Firstly, very few countries have the financial and technological capability to ...

  7. Analysis of Nonlinear Missile Guidance Systems Through Linear Adjoint Method

    Directory of Open Access Journals (Sweden)

    Khaled Gamal Eltohamy

    2015-12-01

    Full Text Available In this paper, a linear simulation algorithm, the adjoint method, is modified and employed as an efficient tool for analyzing the contributions of system parameters to the miss - distance of a nonlinear time-varying missile guidance system model. As an example for the application of the linear adjoint method, the effect of missile flight time on the miss - distance is studied. Since the missile model is highly nonlinear and a time-varying linearized model is required to apply the adjoint method, a new technique that utilizes the time-reversed linearized coefficients of the missile as a replacement for the time-varying describing functions is applied and proven to be successful. It is found that, when compared with Monte Carlo generated results, simulation results of this linear adjoint technique provide acceptable accuracy and can be produced with much less effort.

  8. 77 FR 51970 - Renewal of Missile Defense Advisory Committee

    Science.gov (United States)

    2012-08-28

    ... configurations for the Ballistic Missile Defense System. The Committee shall be composed of not more than eleven... shall be comprised of no more than seven members. The primary focus of the Subcommittee is to conduct...

  9. Analysis and improvement of missile three-loop autopilots

    Institute of Scientific and Technical Information of China (English)

    Lin Defu; Fan Junfang; Qi Zaikang; Mou Yu

    2009-01-01

    characteristics from a two-loop autopilot with PI compensator.Both the two-loop and three-loop topologies can stabilize a static unstable missile.However,the finite actuator resource is the crucial factor dominating autopilot function.

  10. Design and Manufacturing Process for a Ballistic Missile

    Directory of Open Access Journals (Sweden)

    Zaharia Sebastian Marian

    2016-12-01

    Full Text Available Designing a ballistic missile flight depends on the mission and the stress to which the missile is subject. Missile’s requests are determined by: the organization of components; flight regime type, engine configuration and aerodynamic performance of the rocket flight. In this paper has been developed a ballistic missile with a smooth fuselage type, 10 control surfaces, 8 directional surfaces for cornering execution, 2 for maneuvers of execution to change the angle of incidence and 4 stabilizers direction. Through the technology of gluing and clamping of the shell and the use of titanium components, mass of ballistic missile presented a significant decrease in weight and a structure with high strength.

  11. Density Models for Velocity Analysis of Jet Impinged CEDM Missile

    Energy Technology Data Exchange (ETDEWEB)

    Jo, Won Ho; Kang, Tae Kyo; Cho, Yeon Ho; Chang, Sang Gyoon; Lee, Dae Hee [KEPCO EnC, Daejeon (Korea, Republic of)

    2015-05-15

    A control element drive mechanism (CEDM) can be a potential missile in the reactor head area during one of the postulated accidents. The CEDM is propelled by the high speed water jet discharged from a broken upper head nozzle. The jet expansion models to predict the missile velocity have been investigated by Kang et al. The previous work of Kang et al. showed a continuous increase in missile velocity as the CEDM missile travels. But it is not natural in that two phase flow from the nozzle break exit tends to disperse and the thrust force on the missile decreases along the distance of the travel. The jet flow also interacts with the air surrounding itself. Therefore, the density change has to be included in the estimation of the missile velocity. In this paper, two density change models of the water jet are introduced for the jet expansion models along with the distance from the nozzle break location. The first one is the direct approximation model. Two density approximation models are introduced to predict the CEDM missile velocity. For each model, the effects of the expanded jet area were included as the area ratio to the exit nozzle area. In direct approximation model, the results have showed rapid decrease in both density and missile velocity. In pressure approach model, the density change is assumed perfectly proportional to the pressure change, and the results showed relatively smooth change in both density and missile velocity comparing to the direct approximation model. Using the model developed by Kang et al.., the maximum missile velocity is about 4 times greater comparing to the pressure approach model since the density is constant as the jet density at the nozzle exit in their model. Pressure approach model has benefits in that this model adopted neither curve fitting nor extrapolation unlike the direct approximation model, and included the effects of density change which are not considered in the model developed by Kang et al. So, this model is

  12. Application of Computer Graphics to Performance Studies of Missile Warheads

    Directory of Open Access Journals (Sweden)

    K. Rama Rao

    1991-01-01

    Full Text Available Intercept geometry of target aircraft and missiles play an important role in determining the effectiveness of the warhead. Factors such as fragment spatial distribution profile, damage capabilities, target and missile characteristics have been considered and visualised through computer graphics and optimum intercept intercept angles have been arrived. Computer graphics has proved to be an important tool to enhance perception and conceptual design capabilities in the design environment.

  13. Patriot Advanced Capability-3 Missile Segment Enhancement (PAC-3 MSE)

    Science.gov (United States)

    2015-12-01

    sustainment reliability will exceed 20 hours MTBCMF. Will be demonstrated during Post Deployment Build -8 and Radar Digital Processor- Configuration...Technology and Logistics) PAC-3 MSE December 2015 SAR March 21, 2016 09:42:58 UNCLASSIFIED 4 COL John M. Eggert Lower Tier Project Office Building 5250...PAC-3 MSE) is a high velocity, hit-to-kill, surface -to-air missile capable of intercepting and destroying Tactical Ballistic Missiles (TBM) and air

  14. Information Management Principles Applied to the Ballistic Missile Defense System

    Science.gov (United States)

    2007-03-01

    of a BMDS. From this, the Army produced the Nike- Zeus system comprised of four radars, the Zeus missile, and a computer fire control system (General...made the Nike- Zeus our first National Missile Defense (NMD) system named Sentinel. The architecture was to cover 14 locations, 10 of which were...fostered the database system and representation of data in a hierarchy (Galliers & Leidner, 2003). Soon the limits of hierarchies were identified and

  15. 2014 Assessment of the Ballistic Missile Defense System (BMDS)

    Science.gov (United States)

    2015-03-23

    and necessary training aids and devices are not currently available and are not scheduled to become available for several years. Analyses of data...and Evaluation ( IOT &E) flight tests for the Aegis BMD 4.0 system and SM-3 Block IB missile. Outcome. INTERCEPT. The ship detected, tracked...missiles in a raid scenario. FTX-18 was the last of the three IOT &E test missions. Outcome. THREE SIMULATED INTERCEPTS. The ship detected, tracked

  16. Missile Defense Acquisition: Failure Is Not An Option

    Science.gov (United States)

    2016-01-26

    missile over Japan into the sea.1With the nation already possessing weapons of mass destruction (WMD), the test launch signaled their intention to...Korea stunned the world in 1998 with the launch of a Taepo Dong-1 ballistic missile over Japan into the sea.4With the nation already possessing nuclear...acquisition agility. MDA’s BMDS acquisition strategy must be timely, flexible, and agile or risk irrelevance. BMDS Layered Architecture Since the NMD

  17. The expectation of applying IR guidance in medium range air-to-air missiles

    Science.gov (United States)

    Li, Lijuan; Liu, Ke

    2016-10-01

    IR guidance has been widely used in near range dogfight air-to-air missiles while radar guidance is dominant in medium and long range air-to-air missiles. With the development of stealth airplanes and advanced electronic countermeasures, radar missiles have met with great challenges. In this article, the advantages and potential problems of applying IR guidance in medium range air-to-air missiles are analyzed. Approaches are put forward to solve the key technologies including depressing aerodynamic heating, increasing missiles' sensitivity and acquiring target after launch. IR medium range air-to-air missiles are predicted to play important role in modern battle field.

  18. Cooled and uncooled infrared detectors for missile seekers

    Science.gov (United States)

    Fraenkel, Rami; Haski, Jacob; Mizrahi, Udi; Shkedy, Lior; Shtrichman, Itay; Pinsky, Ephi

    2014-06-01

    Electro-optical missile seekers pose exceptional requirements for infrared (IR) detectors. These requirements include: very short mission readiness (time-to-image), one-time and relatively short mission duration, extreme ambient conditions, high sensitivity, fast frame rate, and in some cases small size and cost. SCD is engaged in the development and production of IR detectors for missile seeker applications for many years. 0D, 1D and 2D InSb focal plane arrays (FPAs) are packaged in specially designed fast cool-down Dewars and integrated with Joule-Thomson (JT) coolers. These cooled MWIR detectors were integrated in numerous seekers of various missile types, for short and long range applications, and are combat proven. New technologies for the MWIR, such as epi-InSb and XBn-InAsSb, enable faster cool-down time and higher sensitivity for the next generation seekers. The uncooled micro-bolometer technology for IR detectors has advanced significantly over the last decade, and high resolution - high sensitivity FPAs are now available for different applications. Their much smaller size and cost with regard to the cooled detectors makes these uncooled LWIR detectors natural candidates for short and mid-range missile seekers. In this work we will present SCD's cooled and uncooled solutions for advanced electro-optical missile seekers.

  19. Missile launch detection electric field perturbation experiment. Final report

    Energy Technology Data Exchange (ETDEWEB)

    Kane, R.J.; Rynne, T.M.

    1993-04-28

    The Lawrence Livermore National Laboratory and SARA Inc. participated in the ATMD missile launch activities that occurred at WSMR during January 1993. LLNL and SARA deployed sensors for monitoring of basic phenomena. An attempt was made to measure perturbations of the earth geo-potential during the launch of a Lance missile. The occurrence of the perturbation is expected from the conducting body of the missile and the exhaust plume. A set of voltage-probe antennas were used to monitor the local electric field perturbation from the launch at ranges of approximately 1 km. Examination of the data acquired during the launch period failed to show identifiable correlation of the field variations with the launch event. Three reasons are ascribed to this lack of event data: (1) The electric field potential variations have a limited spatial correlation length - the fields measured in one region have little correlation to measurements made at distances of a kilometer away. The potential variations are related to localized atmospheric disturbances and are generally unpredictable. A value for the spatial correlation length is also not known. (2) The conductivity of the plume and missile body are not adequate to produce a field perturbation of adequate magnitude. Phenomena related to the exhaust plume and missile may exist and be outside of the collection range of the equipment employed for these measurements. (3) The presence of 60 Hz power line noise was of sufficient magnitude to irreversibly contaminate measurements.

  20. Asia-Pacific Missile Defense Cooperation and the United States 2004-2005: A Mixed Bag

    Science.gov (United States)

    2005-02-01

    in cooperating with the United States on various missile defense -related programs. Such close friends and allies as South Korea and Taiwan have made...many local opponents of missile defense argue that the missile threat to Australia is quite low, particularly as North Korea does not yet possess any...2004 in cooperating with the United States. Overall, South Korea does not appear to regard the North Korean missile threat as very likely. Based on

  1. A Study of Age Demographics across the Aviation and Missile Materiel Enterprise

    Science.gov (United States)

    2016-03-31

    future Aviation and Missile ME may look like. The Defense Civilian Personnel Data System (DCPDS) Human Resource managers across the Aviation and...Missile ME use the Defense Civilian Personnel Data System (DCPDS) as the warehouse for storing employee information. Each of the five organizations...Aviation and Missile Life Cycle Management Command Public Affairs, 25 April 2016 AVIATION AND MISSILE MATERIEL ENTERPRISE DEMOGRAPHICS 2

  2. 76 FR 63541 - Design-Basis Hurricane and Hurricane Missiles for Nuclear Power Plants

    Science.gov (United States)

    2011-10-13

    ...-2010-0288] Design-Basis Hurricane and Hurricane Missiles for Nuclear Power Plants AGENCY: Nuclear... Hurricane Missiles for Nuclear Power Plants.'' This regulatory guide provides licensees and applicants with... hurricane and design-basis hurricane-generated missiles that a nuclear power plant should be designed...

  3. The analysis of a generic air-to-air missile simulation model

    Science.gov (United States)

    Kaplan, Joseph A.; Chappell, Alan R.; Mcmanus, John W.

    1994-01-01

    A generic missile model was developed to evaluate the benefits of using a dynamic missile fly-out simulation system versus a static missile launch envelope system for air-to-air combat simulation. This paper examines the performance of a launch envelope model and a missile fly-out model. The launch envelope model bases its probability of killing the target aircraft on the target aircraft's position at the launch time of the weapon. The benefits gained from a launch envelope model are the simplicity of implementation and the minimal computational overhead required. A missile fly-out model takes into account the physical characteristics of the missile as it simulates the guidance, propulsion, and movement of the missile. The missile's probability of kill is based on the missile miss distance (or the minimum distance between the missile and the target aircraft). The problems associated with this method of modeling are a larger computational overhead, the additional complexity required to determine the missile miss distance, and the additional complexity of determining the reason(s) the missile missed the target. This paper evaluates the two methods and compares the results of running each method on a comprehensive set of test conditions.

  4. High performance infrared fast cooled detectors for missile applications

    Science.gov (United States)

    Reibel, Yann; Espuno, Laurent; Taalat, Rachid; Sultan, Ahmad; Cassaigne, Pierre; Matallah, Noura

    2016-05-01

    SOFRADIR was selected in the late 90's for the production of 320×256 MW detectors for major European missile programs. This experience has established our company as a key player in the field of missile programs. SOFRADIR has since developed a vast portfolio of lightweight, compact and high performance JT-based solutions for missiles. ALTAN is a 384x288 Mid Wave infrared detector with 15μm pixel pitch, and is offered in a miniature ultra-fast Joule- Thomson cooled Dewar. Since Sofradir offers both Indium Antimonide (InSb) and Mercury Cadmium Telluride technologies (MCT), we are able to deliver the detectors best suited to customers' needs. In this paper we are discussing different figures of merit for very compact and innovative JT-cooled detectors and are highlighting the challenges for infrared detection technologies.

  5. Flexible missile autopilot design studies with PC-MATLAB/386

    Science.gov (United States)

    Ruth, Michael J.

    1989-01-01

    Development of a responsive, high-bandwidth missile autopilot for airframes which have structural modes of unusually low frequency presents a challenging design task. Such systems are viable candidates for modern, state-space control design methods. The PC-MATLAB interactive software package provides an environment well-suited to the development of candidate linear control laws for flexible missile autopilots. The strengths of MATLAB include: (1) exceptionally high speed (MATLAB's version for 80386-based PC's offers benchmarks approaching minicomputer and mainframe performance); (2) ability to handle large design models of several hundred degrees of freedom, if necessary; and (3) broad extensibility through user-defined functions. To characterize MATLAB capabilities, a simplified design example is presented. This involves interactive definition of an observer-based state-space compensator for a flexible missile autopilot design task. MATLAB capabilities and limitations, in the context of this design task, are then summarized.

  6. Evaluation of Impact Force of Missile Filled with Fluid

    Energy Technology Data Exchange (ETDEWEB)

    Lee, Hyuk-Kee [Hyundai, Yongin (Korea, Republic of); Kim, Seung-Eock [Sejong University, Seoul (Korea, Republic of)

    2016-10-15

    In this paper, the effect of the fluid on the impact force was evaluated using the commercial software LS-DYNA. In order to verify the proposed finite element (FE) models, the impact force and impulse of the missiles filled with the fluid (wet missile) were investigated, and the analysis results were compared with the force plate tests conducted by VTT laboratory in Finland. A parametric study was performed to evaluate the impulse as per the position filled with the fluid and the impact velocity. The impulses of the wet missiles obtained from the parametric study were compared with those calculated by the modified Riera function. The effect of the fluid on the impact force was evaluated in this study. Based on this study, the following conclusions have been obtained: (1) The impulse/momentum ratios of the wet missiles filled with fluid in the front part were larger than those filled with fluid in the middle part. The difference was 5.5%, 5.3%, 6.2%, 3.8%, 2.9% and 1.0% for the impact velocities of 100 m/s, 110 m/s, 120 m/s, 130 m/s, 140 m/s, and 150 m/s, respectively. (2) The impulse/momentum ratios of the wet missiles by the FE analysis was larger than those by the modified Riera function up to 23.1% and 20.8%, respectively, when the fluid was filled in the front and middle parts. The modified Riera function underestimated the impulses of the wet missiles.

  7. Electric Loading Simulation System for Missile Wings and Rudders

    Institute of Scientific and Technical Information of China (English)

    QI Rong; LIN Hui; CHEN Ming

    2006-01-01

    The design and the realization of missile wings and rudders loading simulation system based on digital signal processor (DSP) TMS320LF2407 and direct torque control (DTC) servo driver ACS600 are discussed. The structure and opration principle for the system are presented. Speediness and elimination of superabundant torque are two key difficulties for electric loading simulation system. The method which can eliminate the superabundant torque is researched. Test results show the airflow resistance when missile wings and rudders are spreading can be rapidly simulated with high accuracy.

  8. Terrain Contour Matching (TERCOM): A Cruise Missile Guidance Aid

    Science.gov (United States)

    Golden, Joe P.

    1980-12-01

    The Cruise Missile is guided by an inertial guidance system aided by an updating technique called Terrain Contour Matching (TERCOM). Chance-Vought first proposed the terrain correlation technique in the late 1950's. Since that time TERCOM has evolved into a reliable, accurate, all weather, day and night method of position fixing and updating for cruise missiles. A brief history of TERCOM development will be presented giving results where possible. A description of TERCOM and how is works will be discussed. A snapshot of the present TERCOM status and future planned developments will be addressed.

  9. A METHOD IN SYSTEM DESIGN OF EJECTING DEVICES OF MISSILES

    Institute of Scientific and Technical Information of China (English)

    DaiLongcheng; XuanYimin

    2002-01-01

    Anew method in system design of ejecting devices of missiles is first presented.Some important points are dis-cussed,which guid the research and development of new ejecting devices of missileg,amd provid the foundation flr thw design of mew ejecting device is provided.The system design includes the distribution of techmology specifica-tion,3-D solid modeling of ejecting devices of missiles im-ported from abroad,the design of pmeumatic device sys-tem,the design of ejecting mechanism system,the predic-tion of reliability and the experimental analysis,etc.

  10. Heat Transfer Between a Missile's Combustion Chamber and the Warhead

    Institute of Scientific and Technical Information of China (English)

    赵永涛; 张奇; 白春华; 闫华

    2003-01-01

    Under higher temperatures the charge within a warhead will be subjected to physical and chemical changes, which will influence the security of the warhead launching process. In this paper the problem is studied adopting finite difference method for the case of a rocket-powered missile. Temperature distribution tables are given through quadrature experiments, and the results fit the actual measured values very well. The results also show that to ensure the launching security of rocket-powered missiles having warhead charge critical temperature close to about 60 ℃, the designer can select appropriate heat insulation structural parameters.

  11. Robust control for snake maneuver design of missile

    Science.gov (United States)

    Kun, Ya; Chen, Xin; Li, Chuntao

    2017-01-01

    For the performance of missile with high Mach number and strongly nonlinear dynamics, this paper uses robust control to design maneuver controller. Robust servomechanism linear quadratic regulator (RSLQR) control is used to form the inner loop and proportional-plus-integral (PI) control is used to provide yawing tracking with no error. Contrast simulations under three types of deviation have been done to confirm robustness of the RSLQR-plus-PI control. Simulation results shows that RSLQR-plus-PI control would resist the disturbance and maintain the properties of the controller, guarantee the robustness and stability of missile more effectively than pure PI control.

  12. Consolidation of data base for Army generalized missile model

    Science.gov (United States)

    Klenke, D. J.; Hemsch, M. J.

    1980-01-01

    Data from plume interaction tests, nose mounted canard configuration tests, and high angle of attack tests on the Army Generalized Missile model are consolidated in a computer program which makes them readily accessible for plotting, listing, and evaluation. The program is written in FORTRAN and will run on an ordinary minicomputer. It has the capability of retrieving any coefficient from the existing DATAMAN tapes and displaying it in tabular or plotted form. Comparisons of data taken in several wind tunnels and of data with the predictions of Program MISSILE2 are also presented.

  13. Design and Implementation of One Missile Visual Simulation System Based on OpenGL

    Institute of Scientific and Technical Information of China (English)

    GAO Ying; ZHANG Pu-zhao; PENG Yu-xin; HUANG Jian-guo

    2007-01-01

    The implementation of a missile's visual simulation system is explained that is developed with OpenGL(open graphic library) and the flight path and flight carriage in different stages of the missile are displayed. The establishment problems of the 3D scene are circumstantiated including the construction and redeployment of the model, creation of the virtual scene, setting of the multi-viewports and multi-windows etc. The missile's data driver, system flow, the modules and their mutual relations of the missile visual simulation system are discussed. The missile flight simulation results and effect of the scenes are given.

  14. Research on image fusion of missile team based on multi-agent cooperative blackboard model

    Science.gov (United States)

    Sen, Guo; Munan, Li

    The target of cooperative engagement of missile teams is to furthest improve hit rate of target according to communication and cooperation among missiles. In this paper the problems of image fusion between missile teams in complex combat environment was analyzed, after which an muti-agent blackboard cooperative model was presented and a public information platform of missile team is built according to this model. Through these, the fusion of images taken from muti-sensor of missiles can be realized and the hit rate of attacking target will be improved. At last, an simulation experiment were performed, and the feasibility of the method is proved by simulation experiment.

  15. An analysis of the common missile and TOW 2B on the Stryker anti-tank guided missile platform, using the Janus simulation

    OpenAIRE

    2002-01-01

    Approved for public release; distribution in unlimited. The U.S. Army is beginning to field the first of six Stryker Brigade Combat Teams (SBCTs) and equip the organic Anti-Tank (AT) Company of the Brigade with the LAV III Anti-Tank Guided Missile (ATGM) Platform and the Tube-Launched, Optically-Tracked, Wire-Guided 2B (TOW 2B) missile system. A developmental effort is currently underway to replace the aging TOW 2B and Hellfire missile systems with a common missile that meets both ground...

  16. The Joint Cruise Missiles Project: An Acquisition History--Appendixes

    Science.gov (United States)

    1982-08-01

    21 TERCOM and Terrain Following Operation.......................22 DMA/JCMPO Organizational Interactions...50 MRASM (AGM-1091) Test Program................................52 Cruise Missile TERCOM and Survivability Flight Tests...data package TEL Transporter erector launcher T&E Test and evaluation TEMP Test and evaluation master plan TERCOM Terrain contour matching UFC Unit

  17. CMC occasional papers : a missile stability regime for South Asia.

    Energy Technology Data Exchange (ETDEWEB)

    Khan, Feroz Hassan (Pakistan Army, Islamabad, Pakistan); Vannoni, Michael Geoffrey; Rajen, Gaurav (Gaia Research Consulting, Albuquerque, NM)

    2004-06-01

    India and Pakistan have created sizeable ballistic missile forces and are continuing to develop and enlarge them. These forces can be both stabilizing (e.g., providing a survivable force for deterrence) and destabilizing (e.g., creating strategic asymmetries). Missile forces will be a factor in bilateral relations for the foreseeable future, so restraint is necessary to curtail their destabilizing effects. Such restraint, however, must develop within an atmosphere of low trust. This report presents a set of political and operational options, both unilateral and bilateral, that decreases tensions, helps rebuild the bilateral relationship, and prepares the ground for future steps in structural arms control. Significant steps, which build on precedents and do not require extensive cooperation, are possible despite strained relations. The approach is made up of three distinct phases: (1) tension reduction measures, (2) confidence building measures, and (3) arms control agreements. The goal of the first phase is to initiate unilateral steps that are substantive and decrease tensions, establish missiles as a security topic for bilateral discussion, and set precedents for limited bilateral cooperation. The second phase would build confidence by expanding current bilateral security agreements, formalizing bilateral understandings, and beginning discussion of monitoring procedures. The third phase could include bilateral agreements limiting some characteristics of national missile forces including the cooperative incorporation of monitoring and verification.

  18. Joint Air-to-Surface Standoff Missile (JASSM)

    Science.gov (United States)

    2015-12-01

    Defense Program ICE - Independent Cost Estimate IOC - Initial Operational Capability Inc - Increment JROC - Joint Requirements Oversight Council $K...penetrating warhead with a robust blast fragmentation capability. The missiles employ an IIR seeker system to attack fixed, point targets requiring precision

  19. 22 CFR 121.16 - Missile Technology Control Regime Annex.

    Science.gov (United States)

    2010-04-01

    ... missile systems, see § 121.1, Cat. VIII (a), target drones and reconnaissance drones (see § 121.1, Cat... (see § 121.1, Cat. IV(h)); (b) Reentry vehicles (see § 121.1, Cat. IV(g)), and equipment designed or modified therefor, as follows, except as provided in Note (1) below for those designed for...

  20. Health Management and Service Life for Air Force Missiles

    Science.gov (United States)

    2011-09-26

    prediction of performance will be conducted DISTRIBUTION STATEMENT A. Approved for public release; distribution is unlimited. PA# TBD 24 • Empiricism ...Strategic Missile A&S Approach Overview Empiricism DISTRIBUTION STATEMENT A. Approved for public release; distribution is unlimited. PA# TBD...Extrapolation Simulated Data 25 • Empiricism cannot always predict future state • Mechanistic method enables enhanced predictions • Mechanistic will not be

  1. Controlling The Spread of Land-Attack Cruise Missiles.

    Science.gov (United States)

    2007-11-02

    Debate in the ’New’ European Community," Arms Control Today 23, no. 2 (March 1993): 12. 38 Controlling the Spread of Land-Attack Cruise Missiles...of temperature, pressures or atmosphere in autoclaves or hydro- claves when used for the production of composites or partially processed composites

  2. A robust approach to the missile defence location problem

    NARCIS (Netherlands)

    Bloemen, A.A.F.; Evers, L.; Barros, A.I.; Monsuur, H.; Wagelmans, A.P.M.

    2011-01-01

    This paper proposes a model for determining a robust defence strategy against ballistic missile threat. Our approach takes into account a variety of possible future scenarios and different forms of robustness criteria, including the well-known absolute robustness criterion. We consider two problem

  3. White Sands Missile Range 2011 Drinking Water Quality Report

    Science.gov (United States)

    2012-01-01

    acerca de su agua potable . Haga que alguien lo traduzca para usted, o hable con alguien que lo entienda. Main Post White Sands Missile Range 2011...standards. What is This Water Quality Report? Este informe contiene informacion importante acerca de su agua potable . Haga que alguien lo traduzca

  4. Shipborne Laser Beam Weapon System for Defence against Cruise Missiles

    Directory of Open Access Journals (Sweden)

    J.P. Dudeja

    2000-04-01

    Full Text Available Sea-skim~ing cruise missiles pose the greatest threat to a surface ship in the present-day war scenario. The convenitional close-in-weapon-systems (CIWSs are becoming less reliable against these new challenges requiring extremely fast reaction time. Naval Forces see a high energy laser as a feasible andjeffective directed energy weapon against sea-skimming antiship cruise missiles becauseof its .ability to deliver destructive energy at the speed of light on to a distant target. The paper comparesthe technology and capability of deuterium fluoride (DF and chemical-oxygen-iodine laser (COIL in effectively performing the role of a shipborne CIWS altainst sea-skimming missiles. Out of these twolasers, it is argued that DF laser wo.uld be more effective a,s a shipborne weapon for defence against sea-skimmin,g cruise missiles. Besides the high energy laser as the primary (killing laser, othersub-systems required in the complete weapon system would be: A beacon laser to sense phase distor'ions in the primary laser, adaptive optics to compensate the atmospheric distortions, beam-directing optics, illuminating lasers, IRST sensors, surveillance and tracking radars, interfacing system, etc.

  5. A Prototype Fibre Optic Gyroscope for Missile Guidance Applications,

    Science.gov (United States)

    This paper describes the design of a prototype fibre optic gyro, which is intended for missile guidance applications. Important design constraints...beam-splitter. Serrodyne phase ramps are impressed on the light propagating round the fibre optic sensor coil connected to the integrated optics chip

  6. Hardware in Loop Simulation for Missile Guidance and Control Systems

    Directory of Open Access Journals (Sweden)

    S. K. Chaudhuri

    1997-07-01

    Full Text Available The purpose of the guidance law is to determine appropriate missile flight path dynamics to achieve mission objective in an efficient manner based on navigation information. Today, guided missiles which are aerodynamically unstable or non-linear in all or part of the flight envelopes need control systems for stability as well as for steering. Many classical guidance and control laws have been used for tactical missiles with varying degrees of performance, complexity and seeker/sensor requirements. Increased accuracy requirements and more dynamic tactics of modern warfare demand improvement of performance which is a trade-off between sophisticated hardware and more sophisticated software. To avoid increase in cost by hardware sophistication, today's trend is to exploit new theoretical methods and low cost high speed microprocessor techniques. Missile test flights are very expensive. The missile system with its sophisticated software and hardware is not reusable after a test launch. Hardware-in-loop Simulation (HILS facilities and methodology form a well integrated system aimed at transforming a preliminary guidance and control system design to flight software and hardware with trajectory right from lift-off till its impact. Various guidance and control law studies pertaining to gathering basket and stability margins, pre-flight, post-flight analyses and validation of support systems have been carried out using this methodology. Nearly full spectrum of dynamically accurate six-degrees-of-freedom (6-DOF model of missile systems has been realised in the HILS scenario. The HILS facility allows interconnection of missile hardware in flight configuration. Pre-flight HILS results have matched fairly well with actual flight trial results. It was possible to detect many hidden defects in the onboard guidance and control software as well as in hardware during HILS. Deficiencies in model, like tail-wag-dog (TWD, flexibility, seeker dynamics and defects in

  7. Joint Counterair and Theater Missile Defense Doctrine to Defend against Unmanned Aerial Vehicles and Cruise Missiles in Asymmetric Warfare

    Science.gov (United States)

    2009-02-12

    state lasers, and a megawatt-class Chemical Oxygen Iodine Laser (COIL) to detect, track, target, and destroy ballistic missiles shortly after launch... disproportionate cost tradeoff between threat weapon systems and the proposed interceptors. With a price tag of over $1M per interceptor such as Patriot

  8. Flight testing of the AIM/RIM-7M missile, preflight analysis

    Science.gov (United States)

    Hicks, W.; Greenberg, E.

    1981-11-01

    The AIM/RIM-7M missile is the most recent version of the AIM-7 missile series. It is in the preproduction phase and has completed most of the preproduction flight test evaluation. A description is presented of the preflight simulation techniques used, taking into account the value of the techniques in predicting the results of actual flights. The AIM/RIM-7M is a semiactive, radar-guided homing missile with sophisticated onboard digital processing. It may be launched from either an aircraft or a surface system. To a large degree, the AIM/RIM-7M represents problems typical of all guided missiles. The described techniques are directly applicable to radar-guided missiles and generically to all types of guided missiles. Attention is given to simulation bay activities, the anechoic chamber, aspects of RF control, the target array, computer models, aspects of preflight simulations, and the test setup.

  9. The proliferation of aerospace weapons technology: Ballistic missiles and the case of Brazil

    Science.gov (United States)

    Vossen, Terrence John

    1993-04-01

    The rationale behind the development of ballistic missile production in Brazil is examined by exploring the political, military, and economic determinants of ballistic missile demand in that country. To ascertain how Brazil developed missile production capabilities, the contributions of aerospace industries in industrialized states, the Brazilian space program, trade between less-developed countries, and illicit trade in missile technology are assessed. It is argued that missile development increasingly became a function of economic as opposed to security considerations, and that technologies transferred from developed country aerospace firms and Brazil's space program were primarily responsible for the creation of production capabilities. It is also contended that the proliferation of missile technology to Brazil was consistent with the workings of a system evident in the aerospace weapons technology market that sustains the horizontal spread of weapons production capabilities.

  10. Computer simulation of absolute and contrast infrared signatures from missile noses

    Science.gov (United States)

    Tofani, Alessandro

    1992-03-01

    A computer simulation was performed to obtain an estimate of the infrared radiant intensity and radiative contrast produced by missile noses. The temperature distribution on the nose was computed by taking into account the effects of aerodynamic and solar heating, sky irradiance, and radiative cooling. The corresponding absolute and contrast signatures were obtained by considering the influence of both atmosphere and target geometry, for six target classes, including cruise missiles, tactical ballistic missiles, and air-to-air and surface-to-surface missiles. Both radiant intensity and radiative contrast were computed as a function of missile altitude or missile distance for all targets. A comparison of radiative quantities in the 3- to 5-micron and 8- to 12-micron bands shows that usually the spectral region that gives the strongest signal is not the one that gives the highest contrast.

  11. Application of Pontryagin’s Minimum Principle in Optimum Time of Missile Manoeuvring

    Directory of Open Access Journals (Sweden)

    Sari Cahyaningtias

    2016-11-01

    Full Text Available Missile is a guided weapon and designed to protect outermost island from a thread of other country. It, commonly, is used as self defense. This research presented surface-to-surface missile in final dive manoeuvre for fixed target. Furthermore, it was proposed manoeuvring based on unmanned aerial vehicle (UAV, autopilot system, which needs accuration and minimum both time and thrust of missile while attacking object. This paper introduced pontryagin’s Minimum Principle, which is useable to solve the problem. The numerical solution showed that trajectory of the missile is split it up in three sub-intervals; flight, climbing, and diving. The numerical simulation showed that the missile must climb in order to satisfy the final dive condition and the optimum time of a missile depend on initial condition of the altitude and the terminal velocity

  12. Assessment of Containment Structures Against Missile Impact Threats

    Institute of Scientific and Technical Information of China (English)

    LI Q M

    2006-01-01

    In order to ensure the highest safety requirements,nuclear power plant structures (the containment structures,the fuel storages and transportation systems) should be assessed against all possible internal and external impact threats.The internal impact threats include kinetic missiles generated by the failure of high pressure vessels and pipes,the failure of high speed rotating machineries and accidental drops.The external impact threats may come from airborne missiles,aircraft impact,explosion blast and fragments.The impact effects of these threats on concrete and steel structures in a nuclear power plant are discussed.Methods and procedures for the impact assessment of nuclear power plants are introduced.Recent studies on penetration and perforation mechanics as well as progresses on dynamic properties of concrete-like materials are presented to increase the understanding of the impact effects on concrete containment structures.

  13. BTT autopilot design for agile missiles with aerodynamic uncer tainty

    Institute of Scientific and Technical Information of China (English)

    Yueyue Ma; Jie Guo; Shengjing Tang

    2015-01-01

    The approach to the synthesis of autopilot with aerody-namic uncertainty is investigated in order to achieve large maneu-verability of agile missiles. The dynamics of the agile missile with reaction-jet control system (RCS) are presented. Subsequently, the cascade control scheme based on the bank-to-turn (BTT) steering technique is described. To address the aerodynamic un-certainties encountered by the control system, the active distur-bance rejection control (ADRC) method is introduced in the autopi-lot design. Furthermore, a compound control er, using extended state observer (ESO) to online estimate system uncertainties and calculate derivative of command signals, is designed based on dynamic surface control (DSC). Nonlinear simulation results show the feasibility of the proposed approach and validate the robust-ness of the control er with severe unmodeled dynamics.

  14. Potential applications of video disc technology to missile guidance

    Science.gov (United States)

    Ormsby, C. C.; Long, H. S.

    1980-01-01

    An assessment of video disk data storage technology suggests the possibility of a missile-borne data storage system providing real-time access to a data base consisting of approximately 10 to the 11th bits, with readout rates of up to 200 Mbits/sec and average frame access time of 2-3 sec. The Direct Read After Write (DRAW) technology currently under development will also provide a data recording capability of 10 to the 7th - 10 to the 8th bits/sec. Five cruise missile applications of this technology are discussed: (1) Terrain Contour Matching (TERCOM) data base guidance; (2) target signature data base guidance; (3) terrain/obstacle files navigation; (4) preprogrammed route storage navigation; and (5) reconnaissance data recording.

  15. Design and development of Propulsion System for Antitank Guided Missile

    Directory of Open Access Journals (Sweden)

    T. Mohan Reddy

    1995-07-01

    Full Text Available A Propulsion system is designed and developed for the third generation antitank guided missile (ATGM. It consists of a separate booster and sustainer. Booster is ahead of sustainer, having four nozzles canted to the missile axis. Sustainer discharges through a supersonic blast tube. Low smoke, high energy nitramine propellant for this propulsion system developed by the High Energy Materials Research Laboratory (HEMRL, Pune, has been successfully flight-tested. The booster grain is tube-in-tube configuration with end inhibition and the sustainer grain is of end burning configuration. High strength aluminium alloy, HE-15, is used for rocket motor components. Glass-phenolic composite ablative material is used for thermal protection of motors and high density graphite is used for nozzle throats. The design considerations and approach, including grain configuration, nozzle, and ignitersare briefly discussed. The propulsion system has been extensively tested in static tests and in flights, establishing the satisfactory performance of the system.

  16. A Predictive Explicit Guidance Scheme for Ballistic Missiles

    Directory of Open Access Journals (Sweden)

    N. Prabhakar

    2013-09-01

    Full Text Available A new approach to the design of ballistic missile guidance is presented in this paper. The proposed method uses the missile model to predict the likely impact point at every guidance cycle and apply course corrections based on the predicted impact point (PIP deviations. The algorithm also estimates the in-flight thrust variation from nominal and accordingly updates the model to reduce the uncertainty in the prediction of the impact point. The performance of the algorithm is tested through 6-DOF simulation. The simulation results show excellent performance of the proposed guidance scheme in nominal & off nominal cases.Defence Science Journal, 2013, 63(5, pp.456-461, DOI:http://dx.doi.org/10.14429/dsj.63.2575

  17. Discrete Sliding Mode Control for Hypersonic Cruise Missile

    Directory of Open Access Journals (Sweden)

    Yong Hua Fan

    2016-01-01

    Full Text Available A discrete variable structure control (DVSC with sliding vector is presented to track the velocity and acceleration command for a hypersonic cruise missile. In the design an integrator is augmented to ensure the tracking with zero steady-state errors. Furthermore the sliding surface of acceleration is designed using the error of acceleration and acceleration rate to avoid the singularity of control matrix. A proper power rate reaching law is utilized in this proposal; therefore the state trajectory from any initial point can be driven into the sliding surface. Besides, in order to validate the robustness of controller, the unmolded dynamic and parameter disturbance of the missile are considered. Through simulation the proposed controller demonstrates good performance in tracking velocity and acceleration command.

  18. External Peer Review Report on the Missile Defense Agency Office of Internal Review

    Science.gov (United States)

    2015-05-14

    No. DODIG-2015-123 M A Y 1 4 , 2 0 1 5 External Peer Review Report on the Missile Defense Agency Office of Internal Review Report Documentation...3. DATES COVERED 00-00-2015 to 00-00-2015 4. TITLE AND SUBTITLE External Peer Review Report on the Missile Defense Agency Office of Internal... REVIEW SUBJECT: External Peer Review Report on the Missile Defense Agency Office of Internal Review (Report No. DODIG-2015-123) Attached is the

  19. Sea-Based Ballistic Missile Defense - Background and Issues for Congress

    Science.gov (United States)

    2009-12-22

    Aegis ships. The program involved modifying the SM-2 Block IV air-defense missile. The missile, as modified, was called the Block IVA version. The...system was designed to intercept descending missiles endo-atmospherically (i.e., within the atmosphere) and destroy them with the Block IVA missile’s...the SBX radar in Texas.52 SBX underwent sea trials and high- power radiation testing in the Gulf of Mexico in 2005. It was then moved by a heavy

  20. ARMS CONTROL: U.S. Efforts to Control the Transfer of Nuclear-Capable Missile Technology

    Science.gov (United States)

    2015-12-11

    risk of diversion is an important part of its analysis, Commerce focuses its reviews on certain countries that are developing nuclear-capable missiles...ogy to countries developing nuclear-capable missile systems. Our work was conducted in the United States at the Departments of State, Commerce , and...the MTCR in halting the transfer of MTCR-related systems and technology to countries developing nuclear-capable missile systems. The objectives, scope

  1. HOMA: Israel’s National Missile Defense Strategy (Abridged Version)

    Science.gov (United States)

    2007-11-02

    developed by Tadiran Electronics Systems), and the Hazelnut Tree launcher control center.28 Each battery is designed to track and counter —14 enemy...Communications center, (4) HAZELNUT TREE fire control center, (5) GREEN PINE radar antenna, (6) Radar control center, (7) Radar power unit, (8) Radar...cooling unit. A battery has four launch vehicles with six ready missiles each, a Tadiran Citron Tree launch control centre, a Hazelnut Tree fire

  2. Long-Range Ballistic Missile Defense in Europe

    Science.gov (United States)

    2010-04-26

    and another transportable radar to be deployed in a country closer to Iran (which was never publicly identified). Deployment of the GMD European...former Polish President Lech Walesa and former Czech Prime Minister Mirek Topolanek criticized the Obama administration’s policy toward the region.4...the Pacific missile test range, would have been refurbished and transported to a fixed site at a military training base in the Czech Republic. The

  3. System Architecture for Anti-Ship Ballistic Missile Defense (ASBMD)

    OpenAIRE

    Hobgood, Jean; Madison, Kimberly; Pawlowski, Geoffrey; Nedd, Steven.; Roberts, Michael; Rumberg, Paige

    2009-01-01

    Approved for public release; distribution is unlimited. Recent studies suggest that China is developing a new class of ballistic missiles that can be used against moving targets, such as ships. One such technology is anticipated to cover a range of 2,000 kilometers and operate at a speed of Mach 10. The threat is also capable of maneuvering both during the midcourse and terminal flight phases for the purposes of guidance, target acquisition, and countermeasures. This threat could greatl...

  4. Missile trajectory shaping using sampling-based path planning

    OpenAIRE

    Pharpatara, Pawit; Pepy, Romain; Hérissé, Bruno; Bestaoui, Yasmina

    2013-01-01

    International audience; This paper presents missile guidance as a complex robotic problem: a hybrid non-linear system moving in a heterogeneous environment. The proposed solution to this problem combines a sampling-based path planner, Dubins' curves and a locally-optimal guidance law. This algorithm aims to find feasible trajectories that anticipate future flight conditions, especially the loss of manoeuverability at high altitude. Simulated results demonstrate the substantial performance imp...

  5. 1997 Report to the Congress on Ballistic Missile Defense.

    Science.gov (United States)

    2007-11-02

    be modified to the Block IVA TBMD configuration. This area defense program will provide a lower-tier or endoatmospheric intercept capability. The...and ADCP completed operational testing and evaluation at White Sands Missile Range, New Mexico . A successful TMD demonstration was conducted as part of...UOES FY 99) Sea Lower PAC-3 Configuration Three (FUE FY 99) Navy Theater Wide TBMD AEGIS With SM-2 Block IVA (FUE FY 02; UOES Software

  6. The U.S. Navy and the Cuban Missile Crisis

    Science.gov (United States)

    1990-05-22

    floor of 1,200 feet, the Guidelines were photographed at Bahia Honda, Havana, La Coloma, Mariel, Matanzas , San Julian, and Cienfuegos. Photography of the...a sharp warning might deter the Soviets from deploying ballistic missiles to Cuba, but unwilling to go public with the evidence 68 available to date...p. 4; "United States Air Force Security Service: Performance During the Cuban Crisis, April- December 1962," n.d., NSACF, pp. 12, 68 ; "Air Force

  7. Space and Missile Systems Center Standard: Space Flight Pressurized Systems

    Science.gov (United States)

    2015-02-28

    pressure and vehicle structural loads. The main propellant tank of a launch vehicle is a typical example. Pressurized System: A system that...SPACE AND MISSILE SYSTEMS CENTER STANDARD SPACE FLIGHT PRESSURIZED SYSTEMS APPROVED FOR PUBLIC RELEASE...Space Flight Pressurized Systems 5a. CONTRACT NUMBER 5b. GRANT NUMBER 5c. PROGRAM ELEMENT NUMBER 6. AUTHOR(S) 5d. PROJECT NUMBER 5e. TASK NUMBER

  8. Open Architecture as an Enabler for FORCEnet Cruise Missile Defense

    Science.gov (United States)

    2007-09-01

    battlespace via the FORCEnet information network. Current capability gaps include a lack of common configuration and Fire Control Quality ( FCQ ...connectivity among platforms that is needed to achieve and maintain a robust cruise missile defense. FCQ is defined as data obtained with the sufficient...platform, or a combination of the two. With Fire Control Quality ( FCQ ) threat data from a remote sensor, the remote unit can initiate a launch

  9. Analyzing and designing object-oriented missile simulations with concurrency

    Science.gov (United States)

    Randorf, Jeffrey Allen

    2000-11-01

    A software object model for the six degree-of-freedom missile modeling domain is presented. As a precursor, a domain analysis of the missile modeling domain was started, based on the Feature-Oriented Domain Analysis (FODA) technique described by the Software Engineering Institute (SEI). It was subsequently determined the FODA methodology is functionally equivalent to the Object Modeling Technique. The analysis used legacy software documentation and code from the ENDOSIM, KDEC, and TFrames 6-DOF modeling tools, including other technical literature. The SEI Object Connection Architecture (OCA) was the template for designing the object model. Three variants of the OCA were considered---a reference structure, a recursive structure, and a reference structure with augmentation for flight vehicle modeling. The reference OCA design option was chosen for maintaining simplicity while not compromising the expressive power of the OMT model. The missile architecture was then analyzed for potential areas of concurrent computing. It was shown how protected objects could be used for data passing between OCA object managers, allowing concurrent access without changing the OCA reference design intent or structure. The implementation language was the 1995 release of Ada. OCA software components were shown how to be expressed as Ada child packages. While acceleration of several low level and other high operations level are possible on proper hardware, there was a 33% degradation of 4th order Runge-Kutta integrator performance of two simultaneous ordinary differential equations using Ada tasking on a single processor machine. The Defense Department's High Level Architecture was introduced and explained in context with the OCA. It was shown the HLA and OCA were not mutually exclusive architectures, but complimentary. HLA was shown as an interoperability solution, with the OCA as an architectural vehicle for software reuse. Further directions for implementing a 6-DOF missile modeling

  10. Joint Air-to-Surface Standoff Missile (JASSM)

    Science.gov (United States)

    2013-12-01

    Retrieval Dev Est - Development Estimate DoD - Department of Defense DSN - Defense Switched Network Econ - Economic Eng - Engineering Est...Missile Reliability (KSA) (CPD para 6.2.8) 4th Lot .91 4th Lot. 91 IOT &E .80 4th Lot .85 IOT &E .95 4th Lot .91 JASSM December 2013 SAR April 16, 2014 17...Acronyms and Abbreviations CPD - Capability Production Document IOT &E - Initial Operational Test and Evaluation KPP - Key Performance Parameter KSA - Key

  11. Quadrennial Defense Review and Ballistic Missile Defense Review

    Science.gov (United States)

    2010-03-11

    global defense posture 3 BMDR Highlights • Outlines a strategy and policy framework to – Defend the homeland against limited ballistic missile attack...abroad – Collaborate closely with allies and partners – Pursue a cooperative and tailored global defense posture – Strengthen US civilian capacity...reviews in 2010 – QDR and BMDR released February 1, 2010 – Nuclear Posture Review to be released this spring – Space Posture Review, with Director of

  12. Decoupling Control Method Based on Neural Network for Missiles

    Institute of Scientific and Technical Information of China (English)

    ZHAN Li; LUO Xi-shuang; ZHANG Tian-qiao

    2005-01-01

    In order to make the static state feedback nonlinear decoupling control law for a kind of missile to be easy for implementation in practice, an improvement is discussed. The improvement method is to introduce a BP neural network to approximate the decoupling control laws which are designed for different aerodynamic characteristic points, so a new decoupling control law based on BP neural network is produced after the network training. The simulation results on an example illustrate the approach obtained feasible and effective.

  13. Robust Hybrid Control for Ballistic Missile Longitudinal Autopilot

    Institute of Scientific and Technical Information of China (English)

    WAEL Mohsen Ahmed; QUAN Quana

    2011-01-01

    This paper investigates the boost phase's longitudinal autopilot of a ballistic missile equipped with thrust vector control.The existing longitudinal autopilot employs time-invariant passive resistor-inductor-capacitor (RLC) network compensator as a control strategy,which does not take into account the time-varying missile dynamics.This may cause the closed-loop system instability in the presence of large disturbance and dynamics uncertainty.Therefore,the existing controller should be redesigned to achieve more stable vehicle response.In this paper,based on gain-scheduling adaptive control strategy,two different types of optimal controllers are proposed.The first controller is gain-scheduled optimal tuning-proportional-integral-derivative (PID) with actuator constraints,which supplies better response but requires a priori knowledge of the system dynamics.Moreover,the controller has oscillatory response in the presence of dynamic uncertainty.Taking this into account,gain-scheduled optimal linear quadratic (LQ) in conjunction with optimal tuning-compensator offers the greatest scope for controller improvement in the presence of dynamic uncertainty and large disturbance.The latter controller is tested through various scenarios for the validated nonlinear dynamic flight model of the real ballistic missile system with autopilot exposed to external disturbances.

  14. Changing law of launching pitching angular velocity of rotating missile

    Institute of Scientific and Technical Information of China (English)

    Liu Guang; Xu Bin; Jiao Xiaojuan; Zhen Tiesheng

    2014-01-01

    In order to provide accurate launching pitching angular velocity (LPAV) for the exterior trajectory optimization design, multi-flexible body dynamics (MFBD) technology is presented to study the changing law of LPAV of the rotating missile based on spiral guideway. An MFBD virtual prototype model of the rotating missile launching system is built using multi-body dynamics modeling technology based on the built flexible body models of key components and the special force model. The built model is verified with the frequency spectrum analysis. With the flexible body contact theory and nonlinear theory of MFBD technology, the research is conducted on the influence of a series of factors on LPAV, such as launching angle change, clearance between launching canister and missile, thrust change, thrust eccentricity and mass eccentricity, etc. Through this research, some useful values of the key design parameters which are difficult to be measured in physical tests are obtained. Finally, a simplified mathematical model of the changing law of LPAV is presented through fitting virtual test results using the linear regression method and verified by physical flight tests. The research results have important significance for the exterior trajectory optimization design.

  15. Design and Simulation of TF and TA Controller for Missile

    Institute of Scientific and Technical Information of China (English)

    ZHA Xu; GUANG Cheng-qi; CUI Ping-yuan; LIU Yong-cai

    2005-01-01

    A nonlinear terrain following(TF) and terrain avoidance(TA) controller is proposed for missile control systems.Based on classical TF algorithm (adaptive angle method), a new method for TF controller is proposed by using angle of attack. A method of obtaining terrain outline data from digital elevation map (DEM) for TF control is discussed in order to save store space. A TA algorithm is proposed by using bank-to-turn technique. The block control model, which is suitable for backstepping design, is given for nonlinear model of missile. Making full use of the characteristics of the system and combining block control principle and backstepping technique, a robust controller design method is proposed. Uncertainties in every sub-block are allowed, and can be canceled by using the idea of nonlinear damping. It is proved that the state tracking errors are converged to a neighborhood of the origin exponentially. Finally, nonlinear six-degree-of-freedom simulation results for the missile model are presented to demonstrate the effectiveness of the proposed control law.

  16. Study on combat effectiveness of air defense missile weapon system based on queuing theory

    Science.gov (United States)

    Zhao, Z. Q.; Hao, J. X.; Li, L. J.

    2017-01-01

    Queuing Theory is a method to analyze the combat effectiveness of air defense missile weapon system. The model of service probability based on the queuing theory was constructed, and applied to analyzing the combat effectiveness of "Sidewinder" and "Tor-M1" air defense missile weapon system. Finally aimed at different targets densities, the combat effectiveness of different combat units of two types' defense missile weapon system is calculated. This method can be used to analyze the usefulness of air defense missile weapon system.

  17. Iranian Ballistic Missile Threat and a Phased, Adaptive Approach for Missile Defense in Europe: Perceptions, Policies and Scenarios

    Science.gov (United States)

    2010-09-15

    critical challenges that endanger peace. The institute has offices in New York, Brussels and Moscow. In May 2009, EWI published a report titled...Program: Treading Water in Shark -Infested Seas,” The Heritage Foundation, April 8, 2010, http://www.heritage.org/Research/Reports/2010/04/The-Obama...Administrations-Ballistic-Missile- Defense-Program-Treading-Water-in- Shark -Infested-Seas. 129 Ibid. 57 an ICBM until 2020 (using the SM-3 Block

  18. Ballistic Missile Defense System Transition and Transfer Process from Missile Defense Agency to the Army - Innovative or Dysfunctional?

    Science.gov (United States)

    2010-04-14

    initiating development of the nuclear-capable Nike Zeus ABM interceptor, intended to destroy an incoming enemy warhead with an airborne nuclear explosion. The...intercept an incoming warhead using the nuclear-tipped Nike Zeus missile. Although DoD cancelled the Nike Zeus system due to technical and operational...budgeting, and initiate issue resolution through the Army/MDA Board of Directors to ensure adequate representation of the Service’s interests

  19. Missiles for Asia The Need for Operational Analysis of U.S. Theater Ballistic Missiles in the Pacific

    Science.gov (United States)

    2016-01-01

    attack a skilled TEL force. During the Gulf War, Iraqi TELs were able to continue firing TBMs at Israel , Saudi Arabia, and Bahrain despite a concerted...1, 2015: http://www.defenseindustrydaily.com/agm-158-jassm-lockheeds- family-of-stealthy-cruise-missiles-014343/ Binnie, Jeremy, “ Israel , Syria...Secretary of the Army and was conducted within the RAND Arroyo Center’s Strategy, Doctrine, and Resources Program. RAND Arroyo Center, part of the RAND

  20. The Apache Longbow-Hellfire Missile Test at Yuma Proving Ground: Ecological Risk Assessment for Missile Firing

    Energy Technology Data Exchange (ETDEWEB)

    Jones, Daniel Steven [ORNL; Efroymson, Rebecca Ann [ORNL; Hargrove, William Walter [ORNL; Suter, Glenn [U.S. Environmental Protection Agency; Pater, Larry [ERDC-CERL

    2008-01-01

    A multiple stressor risk assessment was conducted at Yuma Proving Ground, Arizona, as a demonstration of the Military Ecological Risk Assessment Framework. The focus was a testing program at Cibola Range, which involved an Apache Longbow helicopter firing Hellfire missiles at moving targets, M60- A1 tanks. This paper describes the ecological risk assessment for the missile launch and detonation. The primary stressor associated with this activity was sound. Other minor stressors included the detonation impact, shrapnel, and fire. Exposure to desert mule deer (Odocoileus hemionus crooki) was quantified using the Army sound contour program BNOISE2, as well as distances from the explosion to deer. Few effects data were available from related studies. Exposure-response models for the characterization of effects consisted of human "disturbance" and hearing damage thresholds in units of C-weighted decibels (sound exposure level) and a distance-based No Observed Adverse Effects Level for moose and cannonfire. The risk characterization used a weight-of-evidence approach and concluded that risk to mule deer behavior from the missile firing was likely for a negligible number of deer, but that no risk to mule deer abundance and reproduction is expected.

  1. Zero-sum versus nonzero-sum differential game approach to missile guidance

    NARCIS (Netherlands)

    Trottemant, E.J.; Vermeulen, A.; Weiss, M.

    2007-01-01

    New developments and improvements on evasive missiles have led to a situation in which the current missile guidance laws have difficulties to intercept maneuvering targets. The nature of the interception problem with 2 non-cooperative players leads to the field of differential games. Recent studies

  2. Discussion of the target-missile control scheme with supersonic speed at minimum altitude

    Institute of Scientific and Technical Information of China (English)

    2006-01-01

    An antiship missile with supersonic speed at minimum altitude is an effective weapon to break through a defense line. The former Soviet Union was a leader in this field since it had developed several kinds of antiship missiles which obtained supersonic speed at minimum altitudes. To counter this kind of missile,many countries have been developing corresponding antimissiles. For the purpose of verifing the antimissile missile's effectiveness in intercepting antiship missiles, a target-missile is needed. A target-missle is cheaper and can imitate the main characteristics of antiship missiles with supersonic speed at minimum altitude. In this paper, the control scheme of a target missile flying with supersonic speed at minimum altitude is studied. To counter the problem of hedgehopping over the sea, a control scheme utilizing a SINS + altimeter was proposed.In this scheme, both the quick response ability of altitude control and the anti-jamming problem were considered. A simulation experiment shows that when an integrated altitude control system is used, the anti-disturbance ability of the integrated altitude is good and the response speed of altitude control system can be dramatically improved.

  3. 48 CFR 225.7016 - Restriction on Ballistic Missile Defense research, development, test, and evaluation.

    Science.gov (United States)

    2010-10-01

    ... 48 Federal Acquisition Regulations System 3 2010-10-01 2010-10-01 false Restriction on Ballistic Missile Defense research, development, test, and evaluation. 225.7016 Section 225.7016 Federal Acquisition... Acquisition 225.7016 Restriction on Ballistic Missile Defense research, development, test, and evaluation. ...

  4. A modular ducted rocket missile model for threat and performance assessment

    NARCIS (Netherlands)

    Mayer, A.E.H.J.; Halswijk, W.H.C.; Komduur, H.J.; Lauzon, M.; Stowe, R.A.

    2005-01-01

    A model was developed to predict the thrust of throttled ramjet propelled missiles. The model is called DRCORE and fulfils the growing need to predict the performance of air breathing missiles. Each subsystem of the propulsion unit of this model is coded by using engineering formulae and enables the

  5. Making sense of ballistic missile defense: an assessment of concepts and systems for U.S. boost-phase missile defense in comparison to other alternatives

    National Research Council Canada - National Science Library

    Division on Engineering and Physical Sciences; National Research Council; Naval Studies Board

    2012-01-01

    "The Committee on an Assessment of Concepts and Systems for U.S. Boost-Phase Missile Defense in Comparison to Other Alternatives set forth to provide an assessment of the feasibility, practicality, and affordability of U.S...

  6. Missile Sites, Former missile field for Whiteman., Published in 2005, 1:12000 (1in=1000ft) scale, Whiteman Air Force Base.

    Data.gov (United States)

    NSGIC GIS Inventory (aka Ramona) — This Missile Sites dataset, published at 1:12000 (1in=1000ft) scale, was produced all or in part from Field Survey/GPS information as of 2005. It is described as...

  7. Simulation Analysis of Wave Effect on Exceeding Water Gesture and Load of Submarine Launched Missile

    Directory of Open Access Journals (Sweden)

    Ke Zhao

    2014-02-01

    Full Text Available In this study, we have a research on wave action on the submarine launched missile water trajectory and gesture angles during the process between launch and exit from water. Infinite water depth plane wave was used as the wave model, mathematics models of missile exceeding water under different wave conditions were established based on ideal potential flow theory. The flow field velocity potential was obtained by solving the Laplace equation, thus can obtain missile surface pressure. Considering free surface effects, simple Green’s function was introduced to solve boundary value problems. Three-dimensional Fortran program and finite software ABAQUS were combined to complete the fluid-structure interaction simulation. The rules that wave level and phases effects on submarine-launched missile were finally obtained, which shows wave affect cannot be neglected. Simulation methods and results of this study have a certain reference value for the submarine-launched missile launching.

  8. RUPTURE OF THIN METAL TUBES BY NORMAL AND OBLIQUE IMPACT OF BLUNT CONICALNOSED MISSILES: EXPERIMENTS

    Institute of Scientific and Technical Information of China (English)

    Mu Jianchun; Zhang Tieguang

    2000-01-01

    Impact tests at both normal and oblique angles of incidence were .conducted on thin mild tubes using a moderate size of 90° conical-nosed missiles. Tne minimum impact speed that generated cracks through the thickness of the wall, termed the speed for rupture, was measured, and various modes of rupture were identified. For a thin tube hit by a missile at a normal angle of obliquity at the speed for rupture, the contact region spreads across the nose of the missile, and the transverse shear deformation is predominant in the final failure process. If the angle of obliquity is 30°, the missile pierces a hole through the wall of the tube. At the speed for rupture, the kinetic energy of the missile for oblique angle 30° is only about 45 % that required for plugging at a normal angle of obliquity.

  9. Ballistic Missile Defense System (BMDS) Programmatic Environmental Impact Statement

    Science.gov (United States)

    2007-01-01

    for decommissioning the BMDS to prot(lct the Uruted ~tatoo lU.~.J . ns depbyed forces . friends. and aUlas hom b~Uistic missile throats. The...intcr~contincmal balh:. tic 7) The President would, m reaffirm the entire L’l’- de\\’cl<I•Pmcn:, human rigl:ts ~;caic. leader the ratitlcatlon...aspi."Ct’< oft he Balli~ tic Miss1k DetCnsc (BMD) pwgrarn. Acid rain; The MDA ihcl:·noti..’S i:1 the ?EIS the pn:.sibility cfa..:id rain cuuseC

  10. Reserve lithium-thionyl chloride battery for missile applications

    Science.gov (United States)

    Planchat, J. P.; Descroix, J. P.; Sarre, G.

    A comparative performance study has been conducted for silver-zinc, thionyl chloride, and thermal batteries designed for such missile applications as ICBM guidance system power supplies. Attention is given to each of the three candidates' conformity to requirements concerning mechanical configuration, electrochemical design, electrolyte reservoir, external case, and gas generator. The silver-zinc and Li-SOCl2 candidates employ similar cell configurations and yield comparable performance. The thermal battery is found to be incapable of meeting battery case temperature-related requirements.

  11. Launch Stabilisation System for Vertical Launch of a Missile

    Directory of Open Access Journals (Sweden)

    K. Sreekumar

    2005-07-01

    Full Text Available The launch platform stabilisation control system is a roll-pitch stabilised platform for the vertical launch of a missile from a naval ship. Stabilisation of the launch platform is achievedwith the help of embedded controllers and electro-hydraulic servo control system. The launch platform is stabilised wrt true horizontal with a 2-axis (roll and pitch stabilisation systemconsisting of a gimbal and a set of three high-pressure servo hydraulic actuators. The control system uses rate gyro and tilt sensor feedbacks for stabilising the platform. This paper outlines the details of the launch platform stabilisation control system, results of digital simulation, and the performance during sea trials.

  12. Ballistic missile precession frequency extraction by spectrogram's texture

    Science.gov (United States)

    Wu, Longlong; Xu, Shiyou; Li, Gang; Chen, Zengping

    2013-10-01

    In order to extract precession frequency, an crucial parameter in ballistic target recognition, which reflected the kinematical characteristics as well as structural and mass distribution features, we developed a dynamic RCS signal model for a conical ballistic missile warhead, with a log-norm multiplicative noise, substituting the familiar additive noise, derived formulas of micro-Doppler induced by precession motion, and analyzed time-varying micro-Doppler features utilizing time-frequency transforms, extracted precession frequency by measuring the spectrogram's texture, verified them by computer simulation studies. Simulation demonstrates the excellent performance of the method proposed in extracting the precession frequency, especially in the case of low SNR.

  13. Thermal Battery As A Power Sources In Guided Missiles

    Directory of Open Access Journals (Sweden)

    S. S. Singh

    1973-10-01

    Full Text Available The battery based on low melting eutectic salt mixture electrolyte is thermally activated by raising the temperature of the electrolyte to its melting point. The battery is capable of discharging at very high rates for short duration. The battery employs a combination of elements with low electronegativity and capable of giving higher electrode potentials such as Ca or Mg as anode, a wide variety of eutectic salt electrolytes and various oxides, sulphates, silicates, phosphates, chromates as cathode depolarizers. Only those thermally activated systems which find application as potential power sources in guided missiles are reviewed.

  14. Year 2000 small engine technology payoffs in cruise missiles

    Science.gov (United States)

    Singh, B.; Benstein, E. H.

    1986-01-01

    A study has been conducted for advanced small (450-850 pounds thrust) gas turbine engines for a subsonic strategic cruise missile application, using projected year-2000 technology. Engine performance and configuration analyses were performed for two and three spool turbofan and propfan engine concepts. Mission and Life Cycle Cost (LCC) analyses were performed in which the candidate engines were compared to the baseline engine over a prescribed mission. The advanced technology engines reduced system LCC up to 41 percent relative to the baseline engine. The critical aerodynamic materials and mechanical systems necessary for turbine engine technology were identified.

  15. Renewable Energy Opportunities at White Sands Missile Range, New Mexico

    Energy Technology Data Exchange (ETDEWEB)

    Chvala, William D.; Solana, Amy E.; States, Jennifer C.; Warwick, William M.; Weimar, Mark R.; Dixon, Douglas R.

    2008-09-01

    The document provides an overview of renewable resource potential at White Sands Missile Range (WSMR) based primarily upon analysis of secondary data sources supplemented with limited on-site evaluations. The effort was funded by the U.S. Army Installation Management Command (IMCOM) as follow-on to the 2005 DoD Renewable Energy Assessment. This effort focuses on grid-connected generation of electricity from renewable energy sources and also ground source heat pumps (GSHPs) for heating and cooling buildings, as directed by IMCOM.

  16. Minimum Ballistic Factor Problem of Slender Axial Symmetric Missiles

    Directory of Open Access Journals (Sweden)

    V. B. Tawakley

    1979-01-01

    Full Text Available The problem of determining the geometry of slender, axisymmetric missiles of minimum ballistic factor in hypersonic flow has been solved via the calculus of variations under the assumptions that the flow is Newtonian and the surface averaged skin-friction coefficient is constant. The study has been made for conditions of given length and diameter, given diameter and surfacearea, and given surface area and length. The earlier investigations/sup 8/ where only regular shapes were determined has been extended to cover those class of bodies which consist of regular shapes followed or preceded by zero slope shapes.

  17. Active infrared systems: possible roles in ballistic missile defense?

    Science.gov (United States)

    Paleologue, A.

    2006-05-01

    Active Infra-Red (IR) systems developed in the past ten years are now available for missile defense applications. The main purpose of this paper is to describe the advantages an active IR system could offer to a ballistic missile defense (BMD). The active IR system considered in this paper is a LIDAR (LIght Detection And Ranging) system. Historically, the Lincoln Laboratory in the USA began using lasers in the early 1960's. The initial applications included the development of a LIDAR system enabling the measurement of the distance between the earth and the moon in 1962. Satellite tracking using LIDAR began early in 1973. Today, technological developments, with the miniaturization of systems and increased performance levels, have enabled new ambitious projects such as the Discrimination Interceptor Technology Program (DITP) program started in 1998 and the use of LIDAR to help in the discrimination of future exo-atmospheric interceptors within the framework of BMD. The first part of this paper presents the possible contribution of LIDAR to BMD: the main roles, objectives, and strategic advantages. The second part gives a brief overview of the technological features of a generic LIDAR instrument, rapidly addressing laser sources, detectors, optics and electronics. Finally, a modeling of an IR LIDAR system, limited solely to direct detection, and an estimation of performance levels will be presented. A list of possible IR active discriminators will be then presented on the basis of the previous analysis and proposed as new constraints in the design of discrete objects.

  18. Missile-Borne SAR Raw Signal Simulation for Maneuvering Target

    Directory of Open Access Journals (Sweden)

    Weijie Xia

    2016-01-01

    Full Text Available SAR raw signal simulation under the case of maneuver and high-speed has been a challenging and urgent work recently. In this paper, a new method based on one-dimensional fast Fourier transform (1DFFT algorithm is presented for raw signal simulation of maneuvering target for missile-borne SAR. Firstly, SAR time-domain raw signal model is given and an effective Range Frequency Azimuth Time (RFAT algorithm based on 1DFFT is derived. In this algorithm, the “Stop and Go” (SaG model is adopted and the wide radar scattering characteristic of target is taken into account. Furthermore, the “Inner Pulse Motion” (IPM model is employed to deal with high-speed case. This new RFAT method can handle the maneuvering cases, high-speed cases, and bistatic radar cases, which are all possible in the missile-borne SAR. Besides, this raw signal simulation adopts the electromagnetic scattering calculation so that we do not need a scattering rate distribution map as the simulation input. Thus, the multiple electromagnetic reflections can be considered. Simulation examples prove the effectiveness of our method.

  19. Estimation filters for missile tracking with airborne laser

    Science.gov (United States)

    Clemons, T. M., III; Chang, K. C.

    2006-05-01

    This paper examines the use of various estimation filters on the highly non-linear problem of tracking a ballistic missile during boost phase from a moving airborne platform. The aircraft receives passive bearing data from an IR sensor and range data from a laser rangefinder. The aircraft is assumed to have a laser weapon system that requires highly accurate bearing information in order to keep the laser on target from a distance of 100-200 km. The tracking problem is made more difficult due to the changing acceleration of the missile, especially during stage drop-off and ignition. The Extended Kalman Filter (EKF), Unscented Kalman Filter (UKF), 'bootstrap' Particle Filter (PF), and the Gaussian Sum Particle Filter (GSPF) are explored using different values for sensor accuracy in bearing and range, and various degrees of uncertainty of the target and platform dynamic. Scenarios were created using Satellite Toolkit © for trajectories from a Southeast Asia launch with associated sensor observations. MATLAB © code modified from the ReBEL Toolkit © was used to run the EKF, UKF, PF, and GSPF sensor track filters. Mean Square Error results are given for tracking during the period when the target is in view of the radar and IR sensors. This paper provides insight into the accuracy requirements of the sensors and the suitability of the given estimators.

  20. AIM-120 Advanced Medium Range Air-to-Air Missile (AMRAAM)

    Science.gov (United States)

    2015-12-01

    Selected Acquisition Report (SAR) RCS: DD-A&T(Q&A)823-185 AIM-120 Advanced Medium Range Air-to-Air Missile (AMRAAM) As of FY 2017 President’s...17, 2013 Program Information Program Name AIM-120 Advanced Medium Range Air-to-Air Missile (AMRAAM) DoD Component Air Force Joint Participants...December 2015 SAR March 23, 2016 16:04:24 UNCLASSIFIED 5 Mission and Description The Advanced Medium Range Air-to-Air Missile (AMRAAM) AIM-120

  1. Study on Missile Intelligent Fault Diagnosis System Based on Fuzzy NN Expert System

    Institute of Scientific and Technical Information of China (English)

    2001-01-01

    In order to study intelligent fault diagnosis methods based on fuzzy neural network (NN) expert systemand build up intelligent fault diagnosis for a type of mis-sile weapon system, the concrete implementation of a fuzzyNN fault diagnosis expert system is given in this paper. Based on thorough research of knowledge presentation, theintelligent fault diagnosis system is implemented with artificial intelligence for a large-scale missile weapon equipment.The method is an effective way to perform fuzzy fault diagnosis. Moreover, it provides a new way of the fault diagnosisfor large-scale missile weapon equipment.

  2. Analysis Of The Infrared Emission Due To Aerodynamic Heating Of Missile Domes

    Science.gov (United States)

    Tofani, Alessandro

    1989-09-01

    A computer simulation of head-on infrared emission from missile noses has been performed. Both cruise missiles and tactical ballistic missiles were considered; results indicate a strong dependence of the emitted radiation on physical and geometrical properties of aerodynamic surfaces, flow character in the boundary layer and atmospheric characteristics. The model allows to give an order-of-magnitude estimate of radiant intensity in the 8-12 μm and 3-5 μm spectral bands and to determine their relative merits as far as the target detection is concerned.

  3. A Game-Theoretic History of the Cuban Missile Crisis

    Directory of Open Access Journals (Sweden)

    Frank C. Zagare

    2014-01-01

    Full Text Available This study surveys and evaluates previous attempts to use game theory to explain the strategic dynamic of the Cuban missile crisis, including, but not limited to, explanations developed in the style of Thomas Schelling, Nigel Howard and Steven Brams. All of the explanations were judged to be either incomplete or deficient in some way. Schelling’s explanation is both empirically and theoretically inconsistent with the consensus interpretation of the crisis; Howard’s with the contemporary understanding of rational strategic behavior; and Brams’ with the full sweep of the events that define the crisis. The broad outlines of a more general explanation that addresses all of the foundational questions associated with the crisis within the confines of a single, integrated, game-theoretic model with incomplete information are laid out.

  4. Parametric control systems design with applications in missile control

    Institute of Scientific and Technical Information of China (English)

    DUAN GuangRen; YU HaiHua; TAN Feng

    2009-01-01

    This paper considers parametric control of high-order descriptor linear systems via proportional plus derivative feedback.By employing general parametric solutions to a type of so-called high-order Sylvester matrix equations,complete parametric control approaches for high-order linear systems are presented.The proposed approaches give simple complete parametric expressions for the feedback gains and the closed-loop eigenvector matrices,and produce all the design degrees of freedom.Furthermore,Important special cases are particularly treated.Based on the proposed parametric design approaches,a parametric method for the gain-scheduling controller design of a linear time-varying system is proposed and the design of a BTT missile autopilot is carried out.The simulation results show that the method is superior to the traditional one in sense of either global stability or system performance.

  5. Ballistic Missile Warhead Recognition based on Micro-Doppler Frequency

    Directory of Open Access Journals (Sweden)

    Sun Hui-Xia

    2008-11-01

    Full Text Available To elucidate the spinning-precession signatures of ballistic warhead, the model of spinning precessionfor ballistic missile warhead is established and the mathematics of micro-Doppler signatures caused by spinning-precession is derived. Then the micro-Doppler features are analysed using high-resolution time-frequencytransform, and the model predictions match the experimental data well. Based on  different mass of warheadsand decoys, the feature, which can reflect the mass of the targets, is extracted from the time-frequency plane,proving a new method for recognising warheads and discriminating these from decoys. Finally the validityof the feature extracted in this study is verified by computer simulations even with low signal-to-noise ratio.Defence Science Journal, 2008, 58(6, pp.705-709, DOI:http://dx.doi.org/10.14429/dsj.58.1697

  6. New digital-input transmitter for missile telemetry

    Science.gov (United States)

    Rieger, J. L.; Woodworth, P. H.

    It is pointed out that telemetry for aircraft and missiles has been in use by the military and its suppliers since the 1950's, using a variety of frequencies and formats. However, the techniques used in airborne telemetry have changed as a consequence of advances in electronic technology. Use of digital pulse-code modulation instead of the analog time-sampled pulse-amptitude modulation (PAM) produced by an analog commutator has advantages in noise performance in instances where the telemetry link is performing near the threshold of noise. The present investigation is concerned with a digital-input transmitter which accepts binary format directly from a TTL source and has applicability in both standard telemetry and encrypted systems. Attention is given to telemetry modulation systems, data encryption requirements, the modulation interface, and transmitter characteristics.

  7. Ogive Nose Hard Missile Penetrating Concrete Slab Numerical Simulation Approach

    Directory of Open Access Journals (Sweden)

    Qadir Bux

    2011-01-01

    Full Text Available Great demand exists for more efficient design to protect delicate and serious structures such as nuclear plants, Power plants, Weapon Industries, weapons storage places, water retaining structures, & etc, against impact of kinetic missiles generated both accidentally and deliberately such as dynamic loading, incident occurs in nuclear plants, terrorist attack, Natural disasters like tsunami and etc., in various impact and blast scenarios for both civilian and military activities. In many cases, projectiles can be treated as rigid bodies when their damage and erosion are not severe. Due to the intricacy of the local impact damages, investigations are generally based on experimental data. Conclusions of the experimental observations are then used to guide engineering models. Local damages studies normally fall into three categories, i.e. empirical formulae based on data fitting, idealised analytical models based on physic laws and numerical simulations based on computational mechanics and material models. In the present study, 2D asymmetrical numerical simulation have done on concrete slab against the impact of  ogive nose hard missile of 26.90mm and 76.20mm diameter with CRH ratio 2.0 and 6.0 respectively, for penetration by using Concrete Damaged Plasticity Model, and ABAQUS/Explicit dynamic analysis in ABAQUS. It is found that the strains/stresses are induced in the concrete slab and a very nicely propagation of the stresses inside the  concrete slab in the form of waves, which is a clear indication for vibrations of the concrete. The lack of failure criterion in concrete damaged plasticity model does not allow the removal of elements during the analyses. This means that spalling, scabbing, and perforation cannot be modelled with the Concrete Damage Plasticity Model. The penetration depth results shows that the deeper penetration requires higher critical impact kinetic energies, and comparison shows the simulation results are more accurate

  8. Robust Graded Sliding Mode Tracking Control for Low Speed Spinning Ballistic Missiles

    Institute of Scientific and Technical Information of China (English)

    ZHOU Jun; WANG Zhi; ZHOU Feng-qi

    2007-01-01

    The nonlinear dynamic model of spinning ballistic missiles is established during the first boosting phase of the missile. Based on the conventional backstepping sliding mode control and the assumption of a two time-scale separation of missile dynamics, a graded sliding mode controller is designed with two sub-sliding surfaces which have invariability to external disturbances and parameter perturbations, and a matrix which comprises three first order low pass filters is introduced to prevent "explosion of terms". Owing to the upper bounds of the uncertainties are difficult to obtain in advance,adaptive laws are introduced to estimate the values of the uncertainties in real-time. Eventually, the numerical simulation results given to show the proposed controller can ensure the steady flight of missiles.

  9. Radar signal analysis of ballistic missile with micro-motion based on time-frequency distribution

    Science.gov (United States)

    Wang, Jianming; Liu, Lihua; Yu, Hua

    2015-12-01

    The micro-motion of ballistic missile targets induces micro-Doppler modulation on the radar return signal, which is a unique feature for the warhead discrimination during flight. In order to extract the micro-Doppler feature of ballistic missile targets, time-frequency analysis is employed to process the micro-Doppler modulated time-varying radar signal. The images of time-frequency distribution (TFD) reveal the micro-Doppler modulation characteristic very well. However, there are many existing time-frequency analysis methods to generate the time-frequency distribution images, including the short-time Fourier transform (STFT), Wigner distribution (WD) and Cohen class distribution, etc. Under the background of ballistic missile defence, the paper aims at working out an effective time-frequency analysis method for ballistic missile warhead discrimination from the decoys.

  10. A Terminal Guidance Law Based on Motion Camouflage Strategy of Air-to-Ground Missiles

    Directory of Open Access Journals (Sweden)

    Chang-sheng Gao

    2016-01-01

    Full Text Available A guidance law for attacking ground target based on motion camouflage strategy is proposed in this paper. According to the relative position between missile and target, the dual second-order dynamics model is derived. The missile guidance condition is given by analyzing the characteristic of motion camouflage strategy. Then, the terminal guidance law is derived by using the relative motion of missile and target and the guidance condition. In the process of derivation, the three-dimensional guidance law could be designed in a two-dimensional plane and the difficulty of guidance law design is reduced. A two-dimensional guidance law for three-dimensional space is derived by bringing the estimation for target maneuver. Finally, simulation for the proposed guidance law is taken and compared with pure proportional navigation. The simulation results demonstrate that the proposed guidance law can be applied to air-to-ground missiles.

  11. Missile injuries to the external genitalia: a five year experience in Maiduguri, North Eastern Nigeria

    Directory of Open Access Journals (Sweden)

    Hassan Mohammed Dogo

    2016-07-01

    Conclusions: Genital missile injuries are on the increase with militarization of civilian population. Goals of treatment still remain cosmesis, preservation of erectile and voiding function. [Int J Res Med Sci 2016; 4(7.000: 2964-2966

  12. Seeing 2020: America’s New Vision for Integrated Air and Missile Defense

    Science.gov (United States)

    2015-01-01

    the U.S. Army Air Corps began Operation Crossbow, the Anglo-American bombing campaign against Adolf Hitler’s V-1 and V-2 missile forces and a...science of war and its weapons matured, the development of improved propulsion, guidance, and payloads in guns, artillery, rockets, mortars , aircraft...range of threats to include short- and intermediate-range ballistic missiles, bombers, and tactical weapons such as artillery, rockets, and mortars

  13. Missile Captive Carry Monitoring and Helicopter Identification Using a Capacitive Microelectromechanical Systems Accelerometer

    Energy Technology Data Exchange (ETDEWEB)

    Hatchell, Brian K.; Mauss, Fredrick J.; Amaya, Ivan A.; Skorpik, James R.; Silvers, Kurt L.; Marotta, Steve

    2012-03-27

    Military missiles are exposed to many sources of mechanical vibration that can affect system reliability, safety, and mission effectiveness. The U. S. Army Aviation and Missile Research Development and Engineering Center (AMRDEC) has been developing missile health monitoring systems to assess and improve reliability, reduce life cycle costs, and increase system readiness. One of the most significant exposures to vibration occurs when the missile is being carried by a helicopter or other aviation platform, which is a condition known as captive carry. Recording the duration of captive carry exposure during the missile’s service life can enable the implementation of predictive maintenance and resource management programs. Since the vibration imparted by each class of helicopter varies in frequency and amplitude, tracking the vibration exposure from each helicopter separately can help quantify the severity and harmonic content of the exposure. Under the direction of AMRDEC staff, engineers at the Pacific Northwest National Laboratory have developed a Captive Carry Health Monitor (CCHM) for the Hellfire II missile. The CCHM is an embedded usage monitoring device installed on the outer skin of the Hellfire II missile to record the cumulative hours the host missile has been in captive carry mode. To classify the vibration by class of helicopter, the CCHM analyzes the amplitude and frequency content of the vibration with the Goertzel algorithm to detect the presence of distinctive rotor harmonics. Cumulative usage data are accessible in theater from an external display; monthly usage histograms are accessible through an internal download connector. This paper provides an overview of the CCHM electrical and package design, describes field testing and data analysis techniques used to monitor captive carry identify and the class of helicopter, and discusses the potential application of missile health and usage data for real-time reliability analysis and fleet management.

  14. Steady Fault Characteristic Analysis of a Missile Power System Based on a Differential Evolution Algorithm

    Institute of Scientific and Technical Information of China (English)

    XU Zhi-gao; GUAN Zheng-xi; MA Jing

    2005-01-01

    The differential evolution (DE) algorithm is applied to solving the models' equations of a whole missile power system, and the steady fault characteristics of the whole system are analyzed. The DE algorithm is robust, requires few control variables, is easy to use and lends itself very well to parallel computation. Calculation results indicate that the DE algorithm simulates faults of a missile power system very well.

  15. Six-Degree-of-Freedom Digital Simulations for Missile Guidance and Control

    Directory of Open Access Journals (Sweden)

    Yongjie Xu

    2015-01-01

    Full Text Available Six-degree-of-freedom ballistic trajectory model can be used to verify design indicators, performance parameters, and correctness so they have been put forward in the missile argumentation and design process. Mathematical simulation is the basis of late semiphysical simulation and field firing testing, and it can greatly reduce the field shooting test time, which shortens the missile test cycle and so reduces costs.

  16. Defense Science Board Task Force on Defense Strategies for Advanced Ballistic and Cruise Missile Threats

    Science.gov (United States)

    2017-01-01

    REPORT OF THE DEFENSE SCIENCE BOARD TASK FORCE ON Defense Strategies for Advanced Ballistic and Cruise Missile Threats January 2017 Office of... Science Board (DSB). The DSB is a Federal Advisory Committee established to provide independent advice to the Secretary of Defense. Statements, opinions... Science Board Task Force on Defense Strategies for Advanced Ballistic and Cruise Missile Threats completed its information-gathering in February 2016

  17. The Impact on Strategic Stability of Ballistic Missile Defense in Eastern Europe

    Science.gov (United States)

    2009-06-12

    the final chapter of the Eastern European missile defense saga has yet to be written, this study can contribute to the field of knowledge even at...Canada at the USSR Academy of Sciences. This publication is invaluable in examining how strategic stability was viewed at the twilight of the Cold...the Czech Republic are carrying out deliberations and how Russia is reacting to each particular new wrinkle in the missile defense saga ; and

  18. A Strategic Conversation about National Missile Defense (Strategic Studies Quarterly, Winter 2008)

    Science.gov (United States)

    2008-01-01

    they were “producing missiles like sausages .” These quotes, and the overall tone of Reagan’s speech, indicate the specific historical context in which...in this article . LeFevre.indd 108 10/30/08 1:18:22 PM A Strategic Conversation about National Missile Defense Strategic  Studies  Quarterly...time.com/time/magazine/ article /0,9171,923443,00.html. 3. National Intelligence Council, “Iran: Nuclear Intentions and Capabilities,” National Intel- ligence

  19. Cooperative Monitoring Center Occasional Paper/9: De-Alerting Strategic Ballistic Missiles

    Energy Technology Data Exchange (ETDEWEB)

    Connell, Leonard W.; Edenburn, Michael W.; Fraley, Stanley K.; Trost, Lawrence C.

    1999-03-01

    This paper presents a framework for evaluating the technical merits of strategic ballistic missile de-alerting measures, and it uses the framework to evaluate a variety of possible measures for silo-based, land-mobile, and submarine-based missiles. De-alerting measures are defined for the purpose of this paper as reversible actions taken to increase the time or effort required to launch a strategic ballistic missile. The paper does not assess the desirability of pursuing a de-alerting program. Such an assessment is highly context dependent. The paper postulates that if de-alerting is desirable and is used as an arms control mechanism, de-alerting measures should satisfy specific cirteria relating to force security, practicality, effectiveness, significant delay, and verifiability. Silo-launched missiles lend themselves most readily to de-alerting verification, because communications necessary for monitoring do not increase the vulnerabilty of the weapons by a significant amount. Land-mobile missile de-alerting measures would be more challenging to verify, because monitoring measures that disclose the launcher's location would potentially increase their vulnerability. Submarine-launched missile de-alerting measures would be extremely challlenging if not impossible to monitor without increasing the submarine's vulnerability.

  20. Countermeasure effectiveness against an intelligent imaging infrared anti-ship missile

    Science.gov (United States)

    Gray, Greer J.; Aouf, Nabil; Richardson, Mark; Butters, Brian; Walmsley, Roy

    2013-02-01

    Ship self defense against heat-seeking anti-ship missiles is of great concern to modern naval forces. One way of protecting ships against these threats is to use infrared (IR) offboard countermeasures. These decoys need precise placement to maximize their effectiveness, and simulation is an invaluable tool used in determining optimum deployment strategies. To perform useful simulations, high-fidelity models of missiles are required. We describe the development of an imaging IR anti-ship missile model for use in countermeasure effectiveness simulations. The missile model's tracking algorithm is based on a target recognition system that uses a neural network to discriminate between ships and decoys. The neural network is trained on shape- and intensity-based features extracted from simulated imagery. The missile model is then used within ship-decoy-missile engagement simulations, to determine how susceptible it is to the well-known walk-off seduction countermeasure technique. Finally, ship survivability is improved by adjusting the decoy model to increase its effectiveness against the tracker.

  1. Surgical treatment of tibial nonunion after wounding by high velocity missile and external fixators: A case report

    OpenAIRE

    2012-01-01

    Introduction. The missiles of modern firearms can cause severe fractures of the extremity. High velocity missile fractures of the tibia are characterized by massive tissue destruction and primary contamination with polymorphic bacteria. Treatment of these fractures is often complicated by delayed healing, poor position healing, nonhealing and bone tissue infection. Case Outline. We present the management of tibial nonunion after wounding by high velocity missile and primary treatment by...

  2. Solar-blind ultraviolet optical system design for missile warning

    Science.gov (United States)

    Chen, Yu; Huo, Furong; Zheng, Liqin

    2015-03-01

    Solar-blind region of Ultraviolet (UV) spectrum has very important application in military field. The spectrum range is from 240nm to 280nm, which can be applied to detect the tail flame from approaching missile. A solar-blind UV optical system is designed to detect the UV radiation, which is an energy system. iKon-L 936 from ANDOR company is selected as the UV detector, which has pixel size 13.5μm x 13.5 μm and active image area 27.6mm x 27.6 mm. CaF2 and F_silica are the chosen materials. The original structure is composed of 6 elements. To reduce the system structure and improve image quality, two aspheric surfaces and one diffractive optical element are adopted in this paper. After optimization and normalization, the designed system is composed of five elements with the maximum spot size 11.988μ m, which is less than the pixel size of the selected CCD detector. Application of aspheric surface and diffractive optical element makes each FOV have similar spot size, which shows the system almost meets the requirements of isoplanatic condition. If the focal length can be decreased, the FOV of the system can be enlarged further.

  3. China and ballistic missile defense: 1955 to 2002 and beyond

    Energy Technology Data Exchange (ETDEWEB)

    Brad, Roberts

    2004-07-01

    China's opposition to U.S. ballistic missile defense was forcefully articulated officially and unofficially between 1991 and 2001. Vociferous opposition gave way to near silence following U.S. ABM Treaty withdrawal, raising a question about precisely whether and how China will respond to future U.S. deployments in both the political and military-operational realms. To gauge likely future responses, it is useful to put the experience of the 1991-2001 period into historical context. China's attitudes toward BMD have passed through a series of distinct phases since the beginning of the nuclear era, as China has been concerned alternately with the problems of strategic defense by both the Soviet Union and United States (and others) around its periphery. Throughout this era it has also pursued its own strategic defense capabilities. There are important elements of continuity in China's attitudes concerns about the viability of its own force and about strategic stability. These suggest the likelihood of significant responses to U.S. BMD even in the absence of sharp rhetoric. (author)

  4. An affinity-directed protein missile system for targeted proteolysis

    Science.gov (United States)

    Fulcher, Luke J.; Macartney, Thomas; Bozatzi, Polyxeni; Hornberger, Annika; Rojas-Fernandez, Alejandro

    2016-01-01

    The von Hippel–Lindau (VHL) protein serves to recruit the hypoxia-inducible factor alpha (HIF1α) protein under normoxia to the CUL2 E3 ubiquitin ligase for its ubiquitylation and degradation through the proteasome. In this report, we modify VHL to engineer an affinity-directed protein missile (AdPROM) system to direct specific endogenous target proteins for proteolysis in mammalian cells. The proteolytic AdPROM construct harbours a cameloid anti-green fluorescence protein (aGFP) nanobody that is fused to VHL for either constitutive or tetracycline-inducible expression. For target proteins, we exploit CRISPR/Cas9 to rapidly generate human kidney HEK293 and U2OS osteosarcoma homozygous knock-in cells harbouring GFP tags at the VPS34 (vacuolar protein sorting 34) and protein associated with SMAD1 (PAWS1, aka FAM83G) loci, respectively. Using these cells, we demonstrate that the expression of the VHL-aGFP AdPROM system results in near-complete degradation of the endogenous GFP-VPS34 and PAWS1-GFP proteins through the proteasome. Additionally, we show that Tet-inducible destruction of GFP-VPS34 results in the degradation of its associated partner, UVRAG, and reduction in levels of cellular phosphatidylinositol 3-phosphate. PMID:27784791

  5. Simulation Study on the Feasibility of Gun-Launched Missile Against Attack Helicopters

    Institute of Scientific and Technical Information of China (English)

    王狂飙; 张天桥

    2001-01-01

    The feasibility of providing the tank a limited anti-helicopterability with gun-launched missile is studied. A type of simulation model of gun-launched missile against attack helicopters is established. The simulation and the parameter optimization of missile control system under various circumstances are done. The gun-launched missile can directly hit the helicopters in the typical tracks, all the missdistances are less than 1 m and the maximum overload is less than available overload. Gun-launched missile is a feasible choice for tanks against attack helicopters.%研究通过炮射反坦克导弹赋予坦克有限反武装直升机能力的可行性.建立了一种炮射导弹与武装直升机对抗的仿真模型,并在各种情况下进行了系统仿真与导弹控制系统参数优化.经参数优化的炮射导弹在给定的武装直升机各种航迹下,均可直接命中,脱靶量均小于1m,最大过载不超过可用过载.仿真结果表明炮射导弹是坦克对抗武装直升机的一种可行的选择.

  6. Use of noise attenuation modeling in managing missile motor detonation activities.

    Science.gov (United States)

    McFarland, Michael J; Watkins, Jeffrey W; Kordich, Micheal M; Pollet, Dean A; Palmer, Glenn R

    2004-03-01

    The Sound Intensity Prediction System (SIPS) and Blast Operation Overpressure Model (BOOM) are semiempirical sound models that are employed by the Utah Test and Training Range (UTTR) to predict whether noise levels from the detonation of large missile motors will exceed regulatory thresholds. Field validation of SIPS confirmed that the model was effective in limiting the number of detonations of large missile motors that could potentially result in a regulatory noise exceedance. Although the SIPS accurately predicted the impact of weather on detonation noise propagation, regulators have required that the more conservative BOOM model be employed in conjunction with SIPS in evaluating peak noise levels in populated areas. By simultaneously considering the output of both models, in 2001, UTTR detonated 104 missile motors having net explosive weights (NEW) that ranged between 14,960 and 38,938 lb without a recorded public noise complaint. Based on the encouraging results, the U.S. Department of Defense is considering expanding the application of these noise models to support the detonation of missile motors having a NEW of 81,000 lb. Recent modeling results suggest that, under appropriate weather conditions, missile motors containing up to 96,000 lb NEW can be detonated at the UTTR without exceeding the regulatory noise limit of 134 decibels (dB).

  7. Signature analysis of ballistic missile warhead with micro-nutation in terahertz band

    Science.gov (United States)

    Li, Ming; Jiang, Yue-song

    2013-08-01

    In recent years, the micro-Doppler effect has been proposed as a new technique for signature analysis and extraction of radar targets. The ballistic missile is known as a typical radar target and has been paid many attentions for the complexities of its motions in current researches. The trajectory of a ballistic missile can be generally divided into three stages: boost phase, midcourse phase and terminal phase. The midcourse phase is the most important phase for radar target recognition and interception. In this stage, the warhead forms a typical micro-motion called micro-nutation which consists of three basic micro-motions: spinning, coning and wiggle. This paper addresses the issue of signature analysis of ballistic missile warhead in terahertz band via discussing the micro-Doppler effect. We establish a simplified model (cone-shaped) for the missile warhead followed by the micro-motion models including of spinning, coning and wiggle. Based on the basic formulas of these typical micro-motions, we first derive the theoretical formula of micro-nutation which is the main micro-motion of the missile warhead. Then, we calculate the micro-Doppler frequency in both X band and terahertz band via these micro-Doppler formulas. The simulations are given to show the superiority of our proposed method for the recognition and detection of radar micro targets in terahertz band.

  8. Wind Tunnel Experimental Investigation on the Aerodynamic Characteristics of the Multifin Rockets and Missiles

    Institute of Scientific and Technical Information of China (English)

    2005-01-01

    The transonic-supersonic wind tunnel experiment on the aerodynamics of the rockets and missiles that have four, six, eight flat or wrap-around fins is introduced. The experimental results show, while M∞<2.0, with the increase of the fins' number, the derivative of lift coefficient is increasing, the pressure center is shifting backwards, and the longitudinal static stability is augmenting. On the contrary, while the Mach number exceeds a certain supersonic value, the aerodynamic effectiveness of the eight-fin missiles would be lower than that of the six-fin missiles. For the low speed short-range missiles, by adopting six, eight or ten flat fins configuration, the lift effectiveness can be greatly increased, the pressure center can be shifted backwards, the static and dynamic stability can be obviously enhanced. For the high speed long-range large rockets and missiles launched from multi-tube launcher, the configuration adopting more than six fins can not be useful for increasing the stability but would make the rolling rate instable during the flight.

  9. An evaluation method for tornado missile strike probability with stochastic correction

    Energy Technology Data Exchange (ETDEWEB)

    Eguchi, Yuzuru; Murakami, Takahiro; Hirakuchi, Hiromaru; Sugimoto, Soichiro; Hattori, Yasuo [Nuclear Risk Research Center (External Natural Event Research Team), Central Research Institute of Electric Power Industry, Abiko (Japan)

    2017-03-15

    An efficient evaluation method for the probability of a tornado missile strike without using the Monte Carlo method is proposed in this paper. A major part of the proposed probability evaluation is based on numerical results computed using an in-house code, Tornado-borne missile analysis code, which enables us to evaluate the liftoff and flight behaviors of unconstrained objects on the ground driven by a tornado. Using the Tornado-borne missile analysis code, we can obtain a stochastic correlation between local wind speed and flight distance of each object, and this stochastic correlation is used to evaluate the conditional strike probability, QV(r), of a missile located at position r, where the local wind speed is V. In contrast, the annual exceedance probability of local wind speed, which can be computed using a tornado hazard analysis code, is used to derive the probability density function, p(V). Then, we finally obtain the annual probability of tornado missile strike on a structure with the convolutional integration of product of QV(r) and p(V) over V. The evaluation method is applied to a simple problem to qualitatively confirm the validity, and to quantitatively verify the results for two extreme cases in which an object is located just in the vicinity of or far away from the structure.

  10. Comparison of different lateral acceleration autopilots for a surface-to-surface missile

    Directory of Open Access Journals (Sweden)

    Danilo V. Ćuk

    2011-07-01

    Full Text Available This paper presents a comparison of three lateral acceleration autopilots for a surface-to-surface missile: three-loop conventional acceleration autopilot, and gamma-dot and three-loop acceleration autopilot based upon the inverse-dynamic control. The surface-to-surface missile motion is described by nonlinear differential equations whose parameters change rapidly over a very wide range due to variable velocity and altitude. The requirement for the accurate controlling of the missile in such an environment represents a challenge for the autopilot designer. The brief review of the calculation of the autopilot gains is given using the concept of the 'point' stability for the linear time-varying system with 'frozen' dynamic coefficients. The method of the inverse-dynamic control is presented in the next section for two types of the autopilots: gamma-dot and acceleration autopilot. Both of them require the design of the estimators for the variables used as inputs to the control law. Finally, six-degree-of-freedom simulation results of the missile response to the demanded command on the typical ballistic trajectory are presented. The comparison of three autopilots considers the steady state errors and the sensitivity of the response to the highly variable environment. It was shown that the inverse-dynamic control can be very effective in the controlling of the surface-to-surface missile.

  11. A Study of the Effects of Sensor Noise and Guidance Laws on SAM Effectiveness Against Cruise Missiles

    Science.gov (United States)

    2015-06-01

    k guidance acceleration command vector xviii THIS PAGE INTENTIONALLY LEFT BLANK xix EXECUTIVE SUMMARY Cruise missile (CM) technology is...Germany, Netherlands, UK, Denmark Turkey, Romania, Poland, and Spain ) contributed to the Maritime Theatre Missile Defence Forum to obtain an impressive

  12. 15 CFR 744.3 - Restrictions on Certain Rocket Systems (including ballistic missile systems and space launch...

    Science.gov (United States)

    2010-01-01

    ... Vehicles (including cruise missile systems, target drones and reconnaissance drones) End-Uses. 744.3... missile systems, target drones and reconnaissance drones) End-Uses. (a) General prohibition. In addition... transfer (in-country) you know that the item: (1) Will be used in the design, development, production...

  13. Digital Array Radar for Ballistic Missile Defense and Counter-Stealth Systems Analysis and Parameter Tradeoff Study

    Science.gov (United States)

    2006-09-14

    Missile BMD Ballistic Missile Defense CAS Computer Algebra System CDD Capability Development Document CONOPS Concept of Operations CONUS Continental...this section. Analysis and calculations described in this section were conducted using Waterloo Maple® 7 Computer Algebra System (CAS). Initially...When two or more electromagnetic waves combine, their electric fields are integrated vectorially at each point in space for any

  14. 77 FR 64564 - Implementation of Regulatory Guide 1.221 on Design-Basis Hurricane and Hurricane Missiles

    Science.gov (United States)

    2012-10-22

    ... COMMISSION Implementation of Regulatory Guide 1.221 on Design-Basis Hurricane and Hurricane Missiles AGENCY....221 on Design-Basis Hurricane and Hurricane Missiles.'' The purpose of this ISG is to supplement the guidance regarding the application of Regulatory Guide 1.221, ``Design-Basis Hurricane and...

  15. Guidance Law and Neural Control for Hypersonic Missile to Track Targets

    Directory of Open Access Journals (Sweden)

    Wenxing Fu

    2016-01-01

    Full Text Available Hypersonic technology plays an important role in prompt global strike. Because the flight dynamics of a hypersonic vehicle is nonlinear, uncertain, and highly coupled, the controller design is challenging, especially to design its guidance and control law during the attack of a maneuvering target. In this paper, the sliding mode control (SMC method is used to develop the guidance law from which the desired flight path angle is derived. With the desired information as control command, the adaptive neural control in discrete time is investigated ingeniously for the longitudinal dynamics of the hypersonic missile. The proposed guidance and control laws are validated by simulation of a hypersonic missile against a maneuvering target. It is demonstrated that the scheme has good robustness and high accuracy to attack a maneuvering target in the presence of external disturbance and missile model uncertainty.

  16. A Direct Multiple Shooting Method for Missile Trajectory Optimization with The Terminal Bunt Manoeuvre

    Directory of Open Access Journals (Sweden)

    S. Subchan Subchan

    2011-08-01

    Full Text Available Numerical solution of constrained nonlinear optimal control problem is an important field in a wide range of applications in science and engineering. The real time solution for an optimal control problem is a challenge issue especially the state constrained handling. Missile trajectory shaping with terminal bunt manoeuvre with state constaints is addressed. The problem can be stated as an optimal control problem in which an objective function is minimised satisfying a series of constraints on the trajectory which includes state and control constraints. Numerical solution based on a direct multiple shooting is proposed. As an example the method has been implemented to a design of optimal trajectory for a missile where the missile must struck the target by vertical dive. The qualitative analysis and physical interpretation of the numerical solutions are given.

  17. Improved manufacturing techniques for rf and laser hardening of missile domes, phase 1

    Science.gov (United States)

    Pawlewicz, W. T.; Mann, I. B.; Martin, P. M.; Hays, D. D.; Graybeal, A. G.

    1982-07-01

    The adaptation of an existing Pacific Northwest Laboratory (PNL) optical coating capability developed for high power fusion laser applications to the case of RF and laser hardening of plastic missile domes used by US Army (MICOM) is reported. RF hardening of Hellfire and Copperhead 1.06 micron missile domes by use of transparent conductive Indium Tin Oxide (ITO) coatings is demonstrated. The project involved adaptation of a coating material and process developed for flat glass components used in fusion lasers to the case of hemispherical or conical heat sensitive plastic domes used on laser guided missiles. Specific ITO coating property goals are an electrical sheet resistance of 10 ohms/square, a coated dome transmission of 80% or more at 1.06 micron wavelength (compared to 90% for a bare dome), and good adhesion. The sheet resistance goal of 10 ohms/square was expected to result in an RF attenuation of 30 dB at the frequencies of importance.

  18. A method for simulating the atmospheric entry of long-range ballistic missiles

    Science.gov (United States)

    Eggers, A J , Jr

    1958-01-01

    It is demonstrated with the aid of similitude arguments that a model launched from a hypervelocity gun upstream through a special supersonic nozzle should experience aerodynamic heating and resulting thermal stresses like those encountered by a long-range ballistic missile entering the earth's atmosphere. This demonstration hinges on the requirements that model and missile be geometrically similar and made of the same material, and that they have the same flight speed and Reynolds number (based on conditions just outside the boundary layer) at corresponding points in their trajectories. The hypervelocity gun provides the model with the required initial speed, while the nozzle scales the atmosphere, in terms of density variation, to provide the model with speeds and Reynolds numbers over its entire trajectory. Since both the motion and aerodynamic heating of a missile tend to be simulated in the model tests, this combination of hypervelocity gun and supersonic nozzle is termed an atmosphere entry simulator.

  19. Autopilot Design Method for the Blended Missile Based on Model Predictive Control

    Directory of Open Access Journals (Sweden)

    Baoqing Yang

    2015-01-01

    Full Text Available This paper develops a novel autopilot design method for blended missiles with aerodynamic control surfaces and lateral jets. Firstly, the nonlinear model of blended missiles is reduced into a piecewise affine (PWA model according to the aerodynamics properties. Secondly, based on the equivalence between the PWA model and mixed logical dynamical (MLD model, the MLD model of blended missiles is proposed taking into account the on-off constraints of lateral pulse jets. Thirdly, a hybrid model predictive control (MPC method is employed to design autopilot. Finally, simulation results under different conditions are presented to show the effectiveness of the proposed method, which demonstrate that control allocation between aerodynamic control surfaces and lateral jets is realized by adjusting the weighting matrix in an index function.

  20. Treatment of transfixing hepatic lesions with a hydrostatic balloon

    Directory of Open Access Journals (Sweden)

    Sérgio San Gregorio Fávero

    Full Text Available Os autores analisaram 13 doentes com ferimentos hepático transfixante tratados com a colocação de balão hidrostático no trajeto do ferimento. Cinco doentes apresentavam ferimento abdominal exclusivo, enquanto 8 eram toraco-abdominais. Em todos os casos houve acometimento do lobo direito e em três o acometimento foi bilobar. O tempo médio de permanência do balão insuflado foi de 9 dias. Dois doentes necessitavam reoperação para a retirada do balão em virtude de existência de aderências que impediam sua mobilização. Não foram observados casos de sangramento após a retirada do balão. A permanência hospitalar variou de 5 a 36 dias. São discutidas as indicações e as vantagens da colocação desse tipo de dispositivo em doentes com ferimentos hepáticos profundos, transfixantes e com sangramento abundante.

  1. Successful hardware-in-the-loop support of the Longbow/HELLFIRE modular missile system

    Science.gov (United States)

    Ray, Jerry A.; Larson, Gerald A.; Terry, John E.

    2000-07-01

    The Air-to-Ground Missiles Systems (AGMS) Project Management Office (PMO) chose to invest in hardware-in-the-loop (HWIL) simulation as an integral part of their Longbow/HELLFIRE (Helicopter Launched, Fire-and-Forget) Modular Missile System program throughout the development and production phases. This investment has resulted in two HWIL simulations, developed by the U.S. Army Aviation and Missile Command (AMCOM) Missile Research Development and Engineering Center, that have had unprecedented success in program support from the early development through production phases. The Millimeter Simulation System 1 (MSS-1) facility is capable of edge-of- the-envelope performance analysis and verification using high- fidelity target, background, and countermeasures signature modeling. The System Test/Acceptance Facility (STAF), developed in partnership with Redstone Technical Test Center, tests full-up missiles for production lot acceptance. Between these two facilities, HWIL simulation is responsible for pre- flight confidence testing of missile hardware and software, software independent verification and validation (IV&V) testing, comprehensive performance evaluation, component verification, production lot acceptance, and data gathering for the shelf life extension program. One payoff of the MSS-1 HWIL investment has been an extremely effective flight test program with MSS-1 receiving credit for saving three flight tests and documenting over 40 failure modes. With the advent of the Performance Based Specification, the MSS-1 has become involved in continuous verification of high level specifications since contractor controlled, low-level specifications are subject to change. The STAF has saved 8 million annually through providing a non-destructive lot acceptance-testing paradigm, and further benefited the production phase by discovering three production problems. This paper will highlight the innovative uses of HWIL simulation as utilized in the Longbow/HELLFIRE program and

  2. Integrated Guidance and Control of Homing Missiles Against Ground Fixed Targets

    Institute of Scientific and Technical Information of China (English)

    Hou Mingzhe; Duan Guangren

    2008-01-01

    This paper presents a scheme of integrated guidance and autopilot design for homing missiles against ground fixed targets. An in- tegrated guidance and control model in the pitch plane is formulated and further changed into a normal form by nonlinear coordinate transformation. By adopting the sliding mode control approach, an adaptive nonlinear control law of the system is designed so that the missile can hit the target accurately with a desired impact attitude angle. The stability analysis of the closed-loop system is also con- ducted. The numerical simulation has confirmed the usefulness of the proposed design scheme.

  3. NATO and U.S. Ballistic Missile Defense Programs: Divergent or Convergent Paths?

    Science.gov (United States)

    2008-12-01

    making framework. It is common for TMD systems to be developed and deployed via bilateral negotiations. The only TMD project that has been subject to...sol-air moyenne portée- terrestre , that is, a ground based surface- to-air medium-range missile. 52 “Aster 30 SAMP/T – Surface-to-Air Missile Platform...alone rather than via a joint development with Alliance members that have expressed interest. Additionally, some European members of the Alliance

  4. Key considerations in infrared simulations of the missile-aircraft engagement

    CSIR Research Space (South Africa)

    Willers, MS

    2012-09-01

    Full Text Available of these details are investigated in Section 6. The tactical missile system used against aircraft includes several subsystems: airframe, flight control, fuze, propulsion, telemetry, data link, warhead and seeker.4 The seeker of an imaging IR missile provides...://proceedings.spiedigitallibrary.org/ on 12/19/2012 Terms of Use: http://spiedl.org/terms /7 dual mode detectors view a scene in two separate bands of the spectrum. The seeker compares the spectral distribution ratio of the various targets in the field of view to a predefined threshold. If a...

  5. Pacific Missile Range Facility Intercept Test Support. Environmental Assessment/Overseas Environmental Assessment

    Science.gov (United States)

    2010-04-01

    Portable hair dryer 86 to 77 At 1 foot Vacuum cleaner 85 to 78 At 5 feet Long range airplane 80 to 70 Inside Conversation 60 Typical suburban...missile unstable, causing it to tumble and fall to the earth prior to reaching populated areas. Other strategies to cause a vehicle to tumble may also

  6. A Three-Pronged Strategy to Solve the Problem of Long-Range Missile Proliferation

    Science.gov (United States)

    1994-06-01

    One example is Brazil and its Sonda space launch vehicle (SLV) program. This SLV program, and others like it, are potentially dangerous to the U.S...because as a non-adherent to the MTCR, Brazil may transfer Sonda technology to rogue states or build offensive missiles capable of striking the U.S

  7. Treatment of open tibial fracture with bone defect caused by high velocity missiles: a case report.

    Science.gov (United States)

    Golubović, Zoran; Vukajinović, Zoran; Stojiljković, Predrag; Golubović, Ivan; Visnjić, Aleksandar; Radovanović, Zoran; Najman, Stevo

    2013-01-01

    Tibia fracture caused by high velocity missiles is mostly comminuted and followed by bone defect which makes their healing process extremely difficult and prone to numerous complications. A 34-year-old male was wounded at close range by a semi-automatic gun missile. He was wounded in the distal area of the left tibia and suffered a massive defect of the bone and soft tissue. After the primary treatment of the wound, the fracture was stabilized with an external fixator type Mitkovic, with convergent orientation of the pins. The wound in the medial region of the tibia was closed with the secondary stitch, whereas the wound in the lateral area was closed with the skin transplant after Thiersch. Due to massive bone defect in the area of the rifle-missile wound six months after injury, a medical team placed a reconstructive external skeletal fixator type Mitkovic and performed corticotomy in the proximal metaphyseal area of the tibia. By the method of bone transport (distractive osteogenesis), the bone defect of the tibia was replaced. After the fracture healing seven months from the secondary surgery, the fixator was removed and the patient was referred to physical therapy. Surgical treatment of wounds, external fixation, performing necessary debridement, adequate antibiotic treatment and soft and bone tissue reconstruction are essential in achieving good results in patients with the open tibial fracture with bone defect caused by high velocity missiles. Reconstruction of bone defect can be successfully treated by reconstructive external fixator Mitkovic.

  8. 78 FR 9768 - Bureau of International Security and Nonproliferation Imposition of Missile Sanctions on Two...

    Science.gov (United States)

    2013-02-11

    ... of International Security and Nonproliferation Imposition of Missile Sanctions on Two Chinese Foreign.... SUMMARY: A determination has been made that two foreign persons in China have engaged in activities that...) . Accordingly, the following sanctions are being imposed on these foreign persons for two years: (A) Denial of...

  9. Military aircraft and missile technology at the Langley Research Center: A selected bibliography

    Science.gov (United States)

    Maddalon, D. V.

    1980-01-01

    A compilation of reference material is presented on the Langley Research Center's efforts in developing advanced military aircraft and missile technology over the past twenty years. Reference material includes research made in aerodynamics, performance, stability, control, stall-spin, propulsion integration, flutter, materials, and structures.

  10. 76 FR 4322 - Availability of the Fiscal Year 2009 Missile Defense Agency Services Contracts Inventory Pursuant...

    Science.gov (United States)

    2011-01-25

    ... of the Secretary Availability of the Fiscal Year 2009 Missile Defense Agency Services Contracts... United States Code as amended by the National Defense Authorization Act for Fiscal Year 2008 (NDAA 08... Procurement and Acquisition Policy, Office of Strategic Sourcing (DPAP/SS) will make available to the public...

  11. Software Acquisition: Evolution, Total Quality Management, and Applications to the Army Tactical Missile System.

    Science.gov (United States)

    presents the concept of software Total Quality Management (TQM) which focuses on the entire process of software acquisition, as a partial solution to...software TQM can be applied to software acquisition. Software Development, Software Acquisition, Total Quality management (TQM), Army Tactical Missile

  12. 78 FR 42430 - Revisions to the Export Administration Regulations Based on the 2012 Missile Technology Control...

    Science.gov (United States)

    2013-07-16

    ... (Definitions of Terms as Used in the Export Administration Regulations) by amending the definition of the term... Definitions of terms as used in the Export Administration Regulations (EAR). * * * * * Payload... Administration Regulations Based on the 2012 Missile Technology Control Regime Plenary Agreements AGENCY:...

  13. ORAL HEALTH OF OPERATING FLEET BALLISTIC MISSILE SUBMARINE CREWS: A CROSS-SECTIONAL SURVEY.

    Science.gov (United States)

    A cross-sectional survey of two fleet ballistic missile submarine crews revealed no remarkable oral health factors. A close relationship was found...effects of FBM submarine service on oral health could be demonstrated; however, in view of the isolated nature of the FBM patrols great stress needs to

  14. The Effects of Fleet Ballistic Missile Submarine Patrols on Oral Health

    Science.gov (United States)

    Maintenance of optimum oral health for Fleet Ballistic Missile submarine personnel is a continuing effort. Information is required concerning oral ... health status and patrol effects on this status. Ninety-one crew members of the USS JOHN MARSHALL (SSBN 611 (Gold)) were evaluated predeployment, during

  15. Joint Theater Missile Defense in Taiwan: Protecting United States Interests and Friends

    Science.gov (United States)

    2007-11-02

    people in a disproportionately short period and where the consequences of its release overwhelms local responders. 67 APPENDIX A CHINESE BALLISTIC...2004, Ballistic Missile Defense. Airborne Laser The Airborne Laser (ABL) consists of a high-energy, chemical oxygen iodine laser (COIL) mounted

  16. Theoretical and Experimental Methods in the Solution of Missile Nonlinear Roll Problems

    Science.gov (United States)

    1978-03-01

    directed towvard improving the science of free flight missile dynamics by investigating the nonlinear rolling motion phenomena *exhibitcd by firned ...3 3 Schematic of Basic Finner Model ......................... 7 4 Induced Rolling Moment vs Roll Orientation Angle for Basic Finner Model Measured in...28 27 Rotational Characteristics of Cruciform Rectangular Fins ....... ............................. 29 28 Wind Tunnel Model (Naval Academy

  17. Dynamic attack zone of air-to-air missile after being launched in random wind field

    Institute of Scientific and Technical Information of China (English)

    Hui Yaoluo; Nan Ying; Chen Shaodong; Ding Quanxin; Wu Shengliang

    2015-01-01

    A new concept is presented for air-to-air missile which is dynamic attack zone after being launched in random wind field. This new concept can be used to obtain the 4-dimensional (4-D) information regarding the dynamic envelope of an air-to-air missile at any flight time aimed at different flight targets considering influences of random wind, in the situation of flight fighters coop-erated with missiles fighting against each other. Based on an air-to-air missile model, some typical cases of dynamic attack zone after being launched in random wind field were numerically simulated. Compared with the simulation results of traditional dynamic envelope, the properties of dynamic attack zone after being launched are as follows. The 4-D dynamic attack zone after being launched is inside traditional maximum dynamic envelope, but its forane boundary is usually not inside tra-ditional no-escape dynamic envelope;Traditional dynamic attack zone can just be reliably used at launch time, while dynamic envelope after being launched can be reliably and accurately used dur-ing any flight antagonism time. Traditional envelope is a special case of dynamic envelope after being launched when the dynamic envelope is calculated at the launch time;the dynamic envelope after being launched can be influenced by the random wind field.

  18. Passive FOG IMU for short-range missile application: from qualification toward series production

    Science.gov (United States)

    Trommer, Gert F.; Mueller, R.; Opitz, S.

    1996-11-01

    An inertial measurement unit (IMU) with angular rate, angular increment and linear acceleration measurement systems for short range missile application is described. It consists of a three axis fiber optic gyroscope (FOG) cluster, three linear vibrating beam accelerometers and an electronics device for signal evaluation and data transmission via a serial transputer link. The FOG cluster is realized by means of a passive all-fiber open loop configuration. Due to the inherent optical phase shift of 3 by 3 couplers, completely passive operation near the quadrature point is achieved without the need for a non- reciprocal optical phase modulation in the fiber loop. Basing on that concept more than 50 rugged IMUs have been built for implementation into a short range air to air missile. Verification tests for flight clearance with stresses simulating air carriage and missile free flight environments have been computed. The operation under extreme vibration and shock environments without the use of vibration isolator fixings due to very tight requirements on data time delay has been demonstrated. The first telemetered missile firings have been performed successfully. The line- setup for large quantity series production is progressing. The implementation of the workstations for the integration of the IMU is finished. The production equipment for calibration and acceptance testing of IMUs in parallel allowing for a rate of more than 150 unit per month has been installed and will be operational in autumn this year.

  19. Optical flow based guidance system design for semi-strapdown image homing guided missiles

    Directory of Open Access Journals (Sweden)

    Huang Lan

    2016-10-01

    Full Text Available This paper focuses mainly on semi-strapdown image homing guided (SSIHG system design based on optical flow for a six-degree-of-freedom (6-DOF axial-symmetric skid-to-turn missile. Three optical flow algorithms suitable for large displacements are introduced and compared. The influence of different displacements on computational accuracy of the three algorithms is analyzed statistically. The total optical flow of the SSIHG missile is obtained using the Scale Invariant Feature Transform (SIFT algorithm, which is the best among the three for large displacements. After removing the rotational optical flow caused by rotation of the gimbal and missile body from the total optical flow, the remaining translational optical flow is smoothed via Kalman filtering. The circular navigation guidance (CNG law with impact angle constraint is then obtained utilizing the smoothed translational optical flow and position of the target image. Simulations are carried out under both disturbed and undisturbed conditions, and results indicate the proposed guidance strategy for SSIHG missiles can result in a precise target hit with a desired impact angle without the need for the time-to-go parameter.

  20. Space radiation studies at the White Sands Missile Range Fast Burst Reactor

    Science.gov (United States)

    Delapaz, A.

    1972-01-01

    The operation of the White Sands Missile Range Fast Burst Reactor is discussed. Space radiation studies in radiobiology, dosimetry, and transient radiation effects on electronic systems and components are described. Proposed modifications to increase the capability of the facility are discussed.

  1. Synthesis of robust feedback missile control strategies by using LMI techniques

    NARCIS (Netherlands)

    Trottemant, E.J.; Weiss, M.; Vermeulen, A.

    2009-01-01

    Robust programming, and more specific LMI techniques, have proven to be an extremely effective tool for the synthesis of missile guidance laws. The advantage of this model-based approach is that a large class of uncertainties can be taken into account and a robust guidance law is obtained. In this p

  2. Optimal linear-quadratic missile guidance laws with penalty on command variability

    NARCIS (Netherlands)

    Weiss, M.; Shima, T.

    2015-01-01

    This paper proposes a new approach to the derivation of homing guidance laws for interceptor missiles that makes use of linear-quadratic optimal control in a different manner than the traditional approaches. Instead of looking only for the minimization of the miss distance and the integral square of

  3. 75 FR 20520 - Revisions to the Export Administration Regulations Based on the 2009 Missile Technology Control...

    Science.gov (United States)

    2010-04-20

    ... turbo-compound engines. Accordingly, turbo-compound engines are not meant to be included within the... describe these engines. Additionally, turbo- compound engines are not a missile proliferation concern. This... December 10, 2009 (74 FR 65662). DATES: Effective Date: This rule is effective: April 20, 2010....

  4. 75 FR 28587 - Taking and Importing Marine Mammals; Taking Marine Mammals Incidental to Missile Launch...

    Science.gov (United States)

    2010-05-21

    ... incidents (e.g., search-and-rescue, fire-fighting, adverse weather conditions), which may require... mission objectives; (2) the Navy must limit launch activities during other pinniped pupping seasons... launch trajectory necessary to meet mission objectives; (3) the Navy must not launch missiles from...

  5. Determination of an Achievable Materiel Availability for the Joint Air-to-Ground Missile

    Science.gov (United States)

    2009-07-01

    to meet applied TAT metrics (use of FedEx, DHL , etc.). Sup- ply chain variances emerge under organic support, which are out of the control of the...can be a low priority, will vary depending on the mode and frequency of trips. Missiles in particular cannot be shipped commercially (FedEx, DHL etc

  6. 75 FR 58365 - Taking and Importing Marine Mammals; Taking Marine Mammals Incidental to Missile Launch...

    Science.gov (United States)

    2010-09-24

    .... Placement of the cameras would cause minimal disturbance to pinnipeds and would focus on a subgroup of... forward looking infrared (FLIR) HS-324 Command thermal imaging cameras for nighttime monitoring of pinnipeds before, during, and after each missile launch. Previously, no cameras were available for...

  7. Near Term Command and Control of Homeland Air and Missile Defense

    Science.gov (United States)

    2003-01-01

    grounded the aircraft prior to take off. Special Operations forces might be best suited to eliminate a terrorist cell with minimal collateral 32 damage. We...Review. 27 March 2002. HAER No. ND-9 (Excerpt from Historic American Engineering Record,) Safeguard Ballistic Missile Defense Center ( BMDC ). Heller

  8. Navy Aegis Ballistic Missile Defense (BMD) Program: Background and Issues for Congress

    Science.gov (United States)

    2016-10-25

    developments in Australia, Japan , and South Korea. 93 Justin Doubleday, “MDA Looking to Integrate European Allies into Missile Defense Architecture ...12 Japan ................................................................................................................................. 12 Other...building, or are planning to build Aegis-equipped ships include Japan , South Korea, Australia, Spain, and Norway.2 Aegis BMD System3 Aegis ships

  9. Adaptive block dynamic surface control for integrated missile guidance and autopilot

    Institute of Scientific and Technical Information of China (English)

    Hou Mingzhe; Liang Xiaoling; Duan Guangren

    2013-01-01

    A novel integrated guidance and autopilot design method is proposed for homing missiles based on the adaptive block dynamic surface control approach.The fully integrated guidance and autopilot model is established by combining the nonlinear missile dynamics with the nonlinear dynamics describing the pursuit situation of a missile and a target in the three-dimensional space.The integrated guidance and autopilot design problem is further converted to a state regulation problem of a time-varying nonlinear system with matched and unmatched uncertainties.A new and simple adaptive block dynamic surface control algorithm is proposed to address such a state regulation problem.The stability of the closed-loop system is proven based on the Lyapunov theory.The six degrees of freedom (6DOF) nonlinear numerical simulation results show that the proposed integrated guidance and autopilot algorithm can ensure the accuracy of target interception and the robust stability of the closed-loop system with respect to the uncertainties in the missile dynamics

  10. Conventional Prompt Global Strike and Long Range Ballistic Missiles: Background and Issues

    Science.gov (United States)

    2017-02-03

    Christopher P. Caves, “Subs May Serve Attack, Guided Missile Functions,” Navy Times, October 15, 2011, http://www.navytimes.com/news/2011/10/navy- dual -use...preliminary results show that the HTV-2 achieved controlled flight in the atmosphere before telemetry was lost nine minutes after liftoff. 72 Media

  11. Conventional Prompt Global Strike and Long-Range Ballistic Missiles: Background and Issues

    Science.gov (United States)

    2016-02-24

    2011/10/navy- dual -use-submarines-attack-guided-missile-101511w/ 46 U.S. Department of Defense, Major Budget Decisions Briefing From the Pentagon...According to DARPA, its preliminary results show that the HTV-2 achieved controlled flight in the atmosphere before telemetry was lost nine minutes after

  12. 基于HLA的导弹仿真系统%Missile simulation system based on HLA

    Institute of Scientific and Technical Information of China (English)

    王利; 赵振南; 张亮

    2013-01-01

    计算机仿真是解决导弹装备研发过程中遇到难题的有效方法.设计了基于高层体系结构(HLA)分布式协议的仿真框架,给出了搭建系统的实施方案,具体介绍了系统联邦成员的构成及功能,分析设计了主要联邦成员的对象类和交互类,最后给出了整个系统的仿真流程及主要代码实现.该系统是一个模块化、通用化、易扩展、形象直观的导弹仿真系统,可以进行多种想定条件下导弹飞行仿真和性能评估,为导弹装备的论证、定型、验证提供了支撑平台.%The computer simulation is an effective way to solve the missile R&D process problems encountered.The article designs the simulation framework based on High Level Architecture (HLA),gives out the build system solutions,introduces the structure and function of the system of the federal member,analyzes and designs the main federal members of the object class and interaction class,finally present the simulation process and code implementation of the entire system.The system is a modular,extensible,general-purpose,image intuitive missile simulation system,can do many kinds of scenario conditions missile flight simulation and performance evaluation for missile equipment,provides support platform for missile equipment demonstration,qualitative and verify.

  13. Influence of transverse reinforcement on perforation resistance of reinforced concrete slabs under hard missile impact

    Energy Technology Data Exchange (ETDEWEB)

    Orbovic, Nebojsa, E-mail: nebojsa.orbovic@cnsc-ccsn.gc.ca; Sagals, Genadijs; Blahoianu, Andrei

    2015-12-15

    This paper describes the work conducted by the Canadian Nuclear Safety Commission (CNSC) related to the influence of transverse reinforcement on perforation capacity of reinforced concrete (RC) slabs under “hard” missile impact (impact with negligible missile deformations). The paper presents the results of three tests on reinforced concrete slabs conducted at VTT Technical Research Centre (Finland), along with the numerical simulations as well as a discussion of the current code provisions related to impactive loading. Transverse reinforcement is widely used for improving the shear and punching strength of concrete structures. However, the effect of this reinforcement on the perforation resistance under localized missile impact is still unclear. The goal of this paper is to fill the gap in the current literature related to this topic. Based on similar tests designed by the authors with missile velocity below perforation velocity, it was expected that transverse reinforcement would improve the perforation resistance. Three slabs were tested under almost identical conditions with the only difference being the transverse reinforcement. One slab was designed without transverse reinforcement, the second one with the transverse reinforcement in form of conventional stirrups with hooks and the third one with the transverse reinforcement in form of T-headed bars. Although the transverse reinforcement reduced the overall damage of the slabs (the rear face scabbing), the conclusion from the tests is that the transverse reinforcement does not have important influence on perforation capacity of concrete slabs under rigid missile impact. The slab with T-headed bars presented a slight improvement compared to the baseline specimen without transverse reinforcement. The slab with conventional stirrups presented slightly lower perforation capacity (higher residual missile velocity) than the slab without transverse reinforcement. In conclusion, the performed tests show slightly

  14. Cooperative Monitoring Center Occasional Paper/4: Missile Control in South Asia and the Role of Cooperative Monitoring Technology

    Energy Technology Data Exchange (ETDEWEB)

    Kamal, N.; Sawhney, P.

    1998-10-01

    The succession of nuclear tests by India and Pakistan in May 1998 has changed the nature of their missile rivalry, which is only one of numerous manifestations of their relationship as hardened adversaries, deeply sensitive to each other's existing and evolving defense capabilities. The political context surrounding this costly rivalry remains unmediated by arms control measures or by any nascent prospect of detente. As a parallel development, sensible voices in both countries will continue to talk of building mutual confidence through openness to avert accidents, misjudgments, and misinterpretations. To facilitate a future peace process, this paper offers possible suggestions for stabilization that could be applied to India's and Pakistan's missile situation. Appendices include descriptions of existing missile agreements that have contributed to better relations for other countries as well as a list of the cooperative monitoring technologies available to provide information useful in implementing subcontinent missile regimes.

  15. Integrated guidance and control design for missile with terminal impact angle constraint based on sliding mode control

    Institute of Scientific and Technical Information of China (English)

    Peng Wu; Ming Yang

    2010-01-01

    Aimed at the guidance requirements of some missiles which attack targets with terminal impact angle at the terminal point,a new integrated guidance and control design scheme based on variable structure control approach for missile with terminal impact angle constraint is proposed.First,a mathematical model of an integrated guidance and control model in pitch plane is established,and then nonlinear transformation is employed to transform the mathematical model into a standard form suitable for sliding mode control method design.A sufficient condition for the existence of linear sliding surface is given in terms of linear matrix inequalities(LMIs),based on which the corresponding reaching motion controller is also developed.To verify the effectiveness of the proposed integrated design scheme,the numerical simulation of missile is made.The simulation results demonstrate that the proposed guidance and control law can guide missile to hit the target with desired impact angle and desired flight attitude angle simultaneously.

  16. Ballistic Missile Defense: Actions Needed to Address Implementation Issues and Estimate Long-Term Costs for European Capabilities

    Science.gov (United States)

    2014-04-01

    forces, and allies against inbound threat missiles. In December 2011, DOD deployed the initial phase of a revised approach for Europe, with...the United States, U.S. forces, and allies around the world against inbound threat missiles. In 2009, the President announced a revised approach for...allocating resources. In addition, we reviewed the Army’s regulation on Integrated Logistic Support, which includes guidance on business-case analysis

  17. A study of the motion and aerodynamic heating of ballistic missiles entering the earth's atmosphere at high supersonic speeds

    Science.gov (United States)

    Allen, H Julian; Eggers, A J , Jr

    1958-01-01

    A simplified analysis of the velocity and deceleration history of ballistic missiles entering the earth's atmosphere at high supersonic speeds is presented. The results of this motion analysis are employed to indicate means available to the designer for minimizing aerodynamic heating. The heating problem considered involves not only the total heat transferred to a missile by convection, but also the maximum average and local time rates of convective heat transfer.

  18. Research of Short-range Missile Motion in Terms of Different Wind Loads

    Directory of Open Access Journals (Sweden)

    A. N. Klishin

    2015-01-01

    Full Text Available When modeling the aircraft motion it is advisable to choose a particular model of the Earth, depending both on the task and on the required accuracy of calculation. The article describes various models of the Earth, such as the flat Earth with a plane-parallel field of gravity, spherical and non-rotating Earth with a plane-parallel field of gravity, spherical and non-rotating Earth with a central gravitational field, spherical and non-rotating Earth, taking into account the polar flattening of the Earth, spherical Earth based compression and polar daily rotation. The article also considers the influence of these models on the motion of the selected aircraft.To date, there is technical equipment to provide highly accurate description of the Earthshape, gravitational field, etc. The improved accuracy of the Earth model description results in more correct description of the trajectory and motion parameters of a ballistic missile. However, for short ranges (10-20 km this accuracy is not essential, and, furthermore, it increases time of calculation. Therefore, there is a problem of choosing the optimal description of the Earth parameters.The motion in the model of the Earth, which takes into account a daily rotation of the planet and polar flattening, is discussed in more detail, and the geographical latitude impact on coordinates of the points of fall of a ballistic missile is analyzed on the basis of obtained graphs.The article individually considers a problem of the wind effect on the aircraft motion and defines dependences of the missile motion on the parameters of different wind loads, such as wind speed and height of its action.A mathematical model of the missile motion was built and numerically integrated, using the Runge-Kutta 4th order method, for implementation and subsequent analysis.Based on the analysis of the calculation results in the abovementioned models of the Earth, differences in impact of these models on the parameters of the

  19. Comparison of head-steered and aircraft-fixed infrared imagery for employing the AGM-65 Maverick missile

    Science.gov (United States)

    Osgood, Robert K.; Wells, Maxwell J.; Meador, Douglas P.

    1995-05-01

    Eight veteran USAF fighter pilots, experienced with AGM-65 Maverick air-to-ground missiles, flew a night, low-level ground attack mission in a flight simulator equipped with a helmet-mounted display (HMD). The mission was performed by delivering five Maverick missiles against ground vehicles using either an aircraft-fixed forward-looking infrared (FLIR) sensor image on a head-up display (HUD) or a head-steered FLIR as the missile aiming device. Additionally, the pilots employed their weapons by two methods: fixing and launching missiles singly or in varying numbers (multiple method). The purpose of the experiment was to determine what, if any, advantage there is to employing the AGM-65 using the HMD FLIR image to slew the missile seeker onto the target versus the conventional method of using the FLIR image displayed on the HUD. With a head-steered sensor (and fixing and launching weapons singly) subjects released their weapons quicker (14.6 second interval between launches vs. 17.1 sec.), at a higher altitude (1739 feet vs. 1603 ft.), and slightly farther from the target (3.42 nautical miles vs. 3.37 nm). Furthermore, data indicated the pilots looked farther off-boresight when searching for and locking the weapon onto a target, thereby more effectively using the full field-of-regard of the missile seeker. The participants also contributed their opinions of the advantages and disadvantages of the two mechanizations.

  20. Research on the Robustness of an Adaptive PID Control of a Kind of Supersonic Missile

    Directory of Open Access Journals (Sweden)

    Gangling Jiao

    2013-01-01

    Full Text Available In this study, the dynamic characteristic of missile system is viewed as a two-loop system, such as inner loop and outer loop and we design an adaptive PID control strategy for the pitch channel linear model of supersonic missile. The robustness of a double PID controller is analyzed by changing the aerodynamic coefficients. The control law is testified to be stable even the aerodynamic coefficients are changed between 0.7 and 1.7 times of its standard value and the control effect is compared with the sliding mode control strategy. Also the advantage and defect of both control strategy are summarized at the end of this study.

  1. A Study on Missile Reentry Control Based on the Method of Feedback Linearization

    Institute of Scientific and Technical Information of China (English)

    LIU Yu-xi; ZHOU Jun; ZHOU Feng-qi

    2007-01-01

    In the process of missile large attack angle reentry, there exist nonlinear, strong coupling uncertainty and multiinput-multi-output (MIMO) in the movement equations, so the traditional small disturbance faces difficulties. For such situations, the method of feedback linearization is adopted to control the complex system, and the control method based on the fuzzy adaptive nonlinear dynamic inversion decoupling control of missile is proposed in the paper. According to the principle of time-scale separation, the system is separated into fast loop and slow loop, the method of dynamic inversion is applied to them, and the method of adaptive fuzzy approach is adopted to compensate for the uncertainty of the fast loop.The simulation results denote the control method in the paper has a better tracing characteristic and robustness.

  2. 3D-Route Planning Method to Realize Missile Cruise Flight

    Institute of Scientific and Technical Information of China (English)

    WANG Zheng-jie; FAN Chen; ZHU Qun-Min; TANG Wei

    2007-01-01

    In order to increase the aircraft's survival in the flight mission, it is necessary to carry out flight mission planning, which includes TF/TA\\+2(terrain following/terrain avoidance/threat avoidance).An approach to 3D-route planning based on A* heuristic search algorithm was selected to determine the routes of fiber optic guidance missile's cruise segment.The cost function was discussed, which was mainly related to the physical obstacle, threat exposure, and aircraft performance characteristics.The digital map techniques were presented, which included setting "no-go" area according to fiber's safety requirement.The optimal or the sub-optimal route was obtained, while the cost function constraints were satisfied and the stored terrain obtained from a real terrain was digitized.The algorithm is validated through simulation and can fulfill the route planning task which focuses on the cruise segment of fiber optic guidance missile.

  3. Terrain-aided navigation of an unpowered tactical missile using autopilot-grade sensors

    Science.gov (United States)

    Longenbaker, W. E.

    1984-04-01

    The feasibility of applying a terrain-aided navigation concept (Sandia Inertial Terrain-Aided Navigation, or SITAN) to an unpowered tactical missile (USAF GBU-15) is considered. The brief flight time and predictable missile flight path dynamics lead to the definition of a velocity-based strap-down navigation algorithm that uses the existing autopilot-grade sensors. The navigation states are corrected by means of the error estimates of a Kalman filter. The filter makes use of frequent radar altimeter measurements and terrain slope information (derived from an on-board digitized map) to provide essentially continuous position updating. Covariance analysis and Monte Carlo simulation techniques are then applied to predict system performance. Results are obtained showing that the accuracy of this weapon/guidance combination is sufficient to defeat airfields with area munitions.

  4. Using Fractional-order Piλ Dμ Controller for Control of Aerodynamic Missile

    Institute of Scientific and Technical Information of China (English)

    ZHANG Bang-chu; ZHU Ji-hong; PAN Shu-shan; WANG Shao-feng

    2006-01-01

    A new type of PID controller is introduced and some properties are given. The novelty of the proposed controller consists in the extension of derivation and integration order from integer to non-integer order. The PIλDμ controller generally has three advantages when compared to the integerl-order controller: the first is that it has more degrees of freedom in the model; the second is that it has a memory in model, the memory insure the history and its impact to present and future, the third is it ensures the stability of missile. This approach provides a more flexible tuning strategy and therefore an easier achieving of control requirements. Flight dynamic model of an aerodynamic missile is taken into account in implementing the PIλDμ controller. Simulation results show that the PIλDμ controller is not sensitive to the changes of control parameters and the system parameters. Also, the controller has more flexible structure and stronger robustness.

  5. Average-passage simulation of counter-rotating propfan propulsion systems as applied to cruise missiles

    Science.gov (United States)

    Mulac, Richard A.; Schneider, Jon C.; Adamczyk, John J.

    1989-01-01

    Counter-rotating propfan (CRP) propulsion technologies are currently being evaluated as cruise missile propulsion systems. The aerodynamic integration concerns associated with this application are being addressed through the computational modeling of the missile body-propfan flowfield interactions. The work described in this paper consists of a detailed analysis of the aerodynamic interactions between the control surfaces and the propfan blades through the solution of the average-passage equation system. Two baseline configurations were studied, the control fins mounted forward of the counter-rotating propeller and the control fins mounted aft of the counter-rotating propeller. In both cases, control fin-propfan separation distance and control fin deflection angle were varied.

  6. A distributed cooperative guidance law for salvo attack of multiple anti-ship missiles

    Directory of Open Access Journals (Sweden)

    Zhang Youan

    2015-10-01

    Full Text Available The consensus problem of impact time is addressed for multiple anti-ship missiles. A new distributed cooperative guidance law with the form of biased proportional navigation guidance (BPNG is presented. The proposed guidance law employs the available measurements of relative impact time error as the feedback information to achieve the consensus of impact time among missiles and, by exploiting the special structure of the biased cooperative control term, it can handle the seeker’s field-of-view (FOV constraint. The proposed scheme ensures convergence to consensus of impact time under either fixed or switching sensing/communication network, and the topological requirements are less restrictive than those in the existing results. Numerical examples are provided to illustrate the effectiveness of the proposed guidance law.

  7. A distributed cooperative guidance law for salvo attack of multiple anti-ship missiles

    Institute of Scientific and Technical Information of China (English)

    Zhang Youan; Wang Xingliang; Wu Huali

    2015-01-01

    The consensus problem of impact time is addressed for multiple anti-ship missiles. A new distributed cooperative guidance law with the form of biased proportional navigation guidance (BPNG) is presented. The proposed guidance law employs the available measurements of relative impact time error as the feedback information to achieve the consensus of impact time among mis-siles and, by exploiting the special structure of the biased cooperative control term, it can handle the seeker’s field-of-view (FOV) constraint. The proposed scheme ensures convergence to consensus of impact time under either fixed or switching sensing/communication network, and the topological requirements are less restrictive than those in the existing results. Numerical examples are provided to illustrate the effectiveness of the proposed guidance law.

  8. Results from Sandia National Laboratories/Lockheed Martin Electromagnetic Missile Launcher (EMML).

    Energy Technology Data Exchange (ETDEWEB)

    Lockner, Thomas Ramsbeck; Skurdal, Ben (Lockheed Martin MS2, Baltimore, MD); Gaigler, Randy (Lockheed Martin MS2, Baltimore, MD); Basak, L (Lockheed Martin MS2, Baltimore, MD); Root, G (Lockheed Martin MS2, Baltimore, MD); Aubuchon, Matthew S.; Turman, Bobby N.; Floyd, Mendel D. (Lockheed Martin MS2, Baltimore, MD)

    2005-05-01

    Sandia national laboratories (SNL) and lockheed martin MS2 are designing an electromagnetic missile launcher (EMML) for naval applications. The EMML uses an induction coilgun topology with the requirement of launching a 3600 lb. missile up to a velocity of 40 m/s. To demonstrate the feasibility of the electromagnetic propulsion design, a demonstrator launcher was built that consists of approximately 10% of the propulsion coils needed for a tactical design. The demonstrator verified the design by launching a 1430 lb weighted sled to a height of 24 ft in mid-December 2004 (Figure 1). This paper provides the general launcher design, specific pulsed power system component details, system operation, and demonstration results.

  9. Backstepping design of missile guidance and control based on adaptive fuzzy sliding mode control

    Institute of Scientific and Technical Information of China (English)

    Ran Maopeng; Wang Qing; Hou Delong; Dong Chaoyang

    2014-01-01

    This paper presents an integrated missile guidance and control law based on adaptive fuzzy sliding mode control. The integrated model is formulated as a block-strict-feedback nonlinear system, in which modeling errors, unmodeled nonlinearities, target maneuvers, etc. are viewed as unknown uncertainties. The adaptive nonlinear control law is designed based on backstepping and sliding mode control techniques. An adaptive fuzzy system is adopted to approximate the coupling nonlinear functions of the system, and for the uncertainties, we utilize an online-adaptive control law to estimate the unknown parameters. The stability analysis of the closed-loop system is also conducted. Simulation results show that, with the application of the adaptive fuzzy sliding mode control, small miss distances and smooth missile trajectories are achieved, and the system is robust against system uncertainties and external disturbances.

  10. Comparative Analysis of Guidance Algorithms for the Hyper Velocity Missile and AFTI/F-16

    Science.gov (United States)

    1991-11-12

    latest Kalman Filter modeling tools to the problem of guiding this missile to a target. Capps and Nelson assumed a smart missile, with "a proportional...N \\ r~,sin(S)I Nx /4 p1M. rt rioi r.Di PIc2 i_e IM rm rM BIm Figure 3-7 Pursuit Algorithm Geometry From Figure 3-7 it is seen that: r, sin (8) (1...algorithm does. 4-25 101 I-\\ - - 00 I-’ c 4 o. 0) 000 < L L Z 0) LL zo 0 C!) * . 0 .D 0 0 ~ cu r- mn T CItI I’ II II I I I CUj 0 0) CD r- CD I) W m N ~ 4-2E

  11. Modular Open System Architecture for Reducing Contamination Risk in the Space and Missile Defense Supply Chain

    Science.gov (United States)

    Seasly, Elaine

    2015-01-01

    To combat contamination of physical assets and provide reliable data to decision makers in the space and missile defense community, a modular open system architecture for creation of contamination models and standards is proposed. Predictive tools for quantifying the effects of contamination can be calibrated from NASA data of long-term orbiting assets. This data can then be extrapolated to missile defense predictive models. By utilizing a modular open system architecture, sensitive data can be de-coupled and protected while benefitting from open source data of calibrated models. This system architecture will include modules that will allow the designer to trade the effects of baseline performance against the lifecycle degradation due to contamination while modeling the lifecycle costs of alternative designs. In this way, each member of the supply chain becomes an informed and active participant in managing contamination risk early in the system lifecycle.

  12. Design and Simulation of BTT Missile with High-Aspect-Ratio Wing Robust H∞ Autopilot

    Institute of Scientific and Technical Information of China (English)

    CUI Sheng-wang; LIU Li; MA Chun-yan

    2007-01-01

    For the strong coupling among the channels of bank-to-turn (BTT) missile with high-aspect-ratio wing,an autopilot is designed with a two loop control structure robust autopilot design methods.By the inner loop design,the question of pole-zero cancellation is solved,and the stabilization of structured uncertainty is achieved.Through the outer loop of H∞ controller design,the flying performance and robustness can be guaranteed.The nonlinear simulation results show that the autopilot designed has perfect time domain response,and can suppress bad influence of the inertial and kinematics couplings.It can make the missile fly stably in the large flying areas.The control is very effective.

  13. Indirect robust control of agile missile via Theta-D technique

    Directory of Open Access Journals (Sweden)

    Di Zhou

    2014-09-01

    Full Text Available An agile missile with tail fins and pulse thrusters has continuous and discontinuous control inputs. This brings certain difficulty to the autopilot design and stability analysis. Indirect robust control via Theta-D technique is employed to handle this problem. An acceleration tracking system is formulated based on the nonlinear dynamics of agile missile. Considering the dynamics of actuators, there is an error between actual input and computed input. A robust control problem is formed by treating the error as input uncertainty. The robust control is equivalent to a nonlinear quadratic optimal control of the nominal system with a modified performance index including uncertainty bound. Theta-D technique is applied to solve the nonlinear optimal control problem to obtain the final control law. Numerical results show the effectiveness and robustness of the proposed strategy.

  14. Crisis Stability and Long-Range Strike: A Comparative Analysis of Fighters, Bombers, and Missiles

    Science.gov (United States)

    2013-01-01

    affordable as we advance further into the 21st century. In fact , the risks in some confrontations may be comparable to what the United States expe- rienced...confrontation between nuclear- armed superpowers at the height of the Cold War. Given the immense stakes for both sides and the fact that it was resolved...and a secret promise to remove U.S. Jupiter missiles from Turkey. While this case is informative, and much has been made of it in previous crisis

  15. Prediction of Target Travel During Missile Time of Flight. A Computer Simulation

    Science.gov (United States)

    1978-06-01

    the second program, the subject had to decide if a gap between two covered areas was wide enough for a missile to be fired successfully. Functional...Program Display During "Time to Decide"....... . ............ 7 4. Gap Program Display ,howing Covered Areas and Dot Track ... .......... 7 5. Gap...18 17. SD of Decision Time As a Funcion of Target Speed and Relative Gap Size ....... .............................. 19 18. Mean Decision

  16. China and Proliferation of Weapons of Mass Destruction and Missiles: Policy Issues

    Science.gov (United States)

    2014-01-03

    Machinery and Electric Equipment Import and Export Co. - Wha Cheong Tai Co. - China Shipbuilding Trading Co. - CPMIEC - China Aero-Technology Import...Equipment Import Export Co. - CMEC Machinery and Electrical Import Export Co. - China Machinery and Electric Equipment Import Export Co. - Wha Cheong...ballistic missiles) September 23, 2004 for two years - Liaoning Jiayi Metals and Minerals Co. - Q.C. Chen - Wha Cheong Tai Co. Ltd. - Shanghai

  17. Another Brick in the Wall: The Israeli Experience in Missile Defense

    Science.gov (United States)

    2015-04-01

    the launch- ing of preemptive campaigns that would swiftly move the battles to the territory its enemies. The country did start cooperating with the...Israeli leaders opted for offensive doctrines, enabling the launching of preemptive campaigns that would swiftly move the battles to the territory of...it meant for Israeli analysts was that Saddam Hussein was using Scud missiles to strike Tehran as new means of compellence. This is now cor

  18. Deep intracerebral (basal ganglia) haematomas in fatal non-missile head injury in man.

    OpenAIRE

    Adams, J H; Doyle, D.; Graham, D I; Lawrence, A E; McLellan, D R

    1986-01-01

    Deep intracerebral (basal ganglia) haematomas were found post mortem in 63 of 635 fatal non-missile head injuries. In patients with a basal ganglia haematoma, contusions were more severe, there was a reduced incidence of a lucid interval, and there was an increased incidence of road traffic accidents, gliding contusions and diffuse axonal injury than in patients without this type of haematoma. Intracranial haematoma is usually thought to be a secondary event, that is a complication of the ori...

  19. Navy Ohio Replacement (SSBN[X]) Ballistic Missile Submarine Program: Background and Issues for Congress

    Science.gov (United States)

    2013-10-22

    Missile Submarine Program Congressional Research Service F. Woolf , discusses the SSBN(X) as an element of future U.S. strategic nuclear forces in the...Report RL33640, U.S. Strategic Nuclear Forces: Background, Developments, and Issues, by Amy F. Woolf . 3 In the designations SSN, SSGN, SSBN, and SSBN(X...missions than do SSN operations. For more on the Navy’s SSNs and SSGNs, see CRS Report RL32418, Navy Virginia (SSN-774) Class Attack Submarine

  20. Treatment of open tibial fracture with bone defect caused by high velocity missiles: A case report

    Directory of Open Access Journals (Sweden)

    Golubović Zoran

    2013-01-01

    Full Text Available Introduction .Tibia fracture caused by high velocity missiles is mostly comminuted and followed by bone defect which makes their healing process extremely difficult and prone to numerous complications. Case Outline. A 34-year-old male was wounded at close range by a semi-automatic gun missile. He was wounded in the distal area of the left tibia and suffered a massive defect of the bone and soft tissue. After the primary treatment of the wound, the fracture was stabilized with an external fixator type Mitkovic, with convergent orientation of the pins. The wound in the medial region of the tibia was closed with the secondary stitch, whereas the wound in the lateral area was closed with the skin transplant after Thiersch. Due to massive bone defect in the area of the rifle-missile wound six months after injury, a medical team placed a reconstructive external skeletal fixator type Mitkovic and performed corticotomy in the proximal metaphyseal area of the tibia. By the method of bone transport (distractive osteogenesis, the bone defect of the tibia was replaced. After the fracture healing seven months from the secondary surgery, the fixator was removed and the patient was referred to physical therapy. Conclusion. Surgical treatment of wounds, external fixation, performing necessary debridement, adequate antibiotic treatment and soft and bone tissue reconstruction are essential in achieving good results in patients with the open tibial fracture with bone defect caused by high velocity missiles. Reconstruction of bone defect can be successfully treated by reconstructive external fixator Mitkovic. [Projekat Ministarstva nauke Republike Srbije, br. III 41017 i br. III 41004

  1. Electromagnetic pulse (EMP): Exposure of missile 56 in EMP simulator sapiens

    Science.gov (United States)

    Dikvall, T.

    1985-06-01

    The effects on the electric field caused by the object (missile) in the SAPIENS electromagnetic pulse simulator were studied. A noticeable effect on the field strength is noted close to the object, due to the characteristics of the field. This effect also appears in real electromagnetic pulse environments. During these tests 200 pulses were distributed with good accuracy of reproduction. The SAPIENS is an outdoor device and tests carried out in winter show that weather has very little influence on results.

  2. Non-Slender Missile Geometries of Minimum Ballistic Factor via Calculus of Variations

    Directory of Open Access Journals (Sweden)

    Manak Singh

    1986-01-01

    Full Text Available The problem of determining the geometry of non-slender axisymmetric missile of minimum ballistic factor in hypersonic flow has been solved via calculus of variation under the assumption that the flow is Newtonian and the surface averaged skin friction coefficient is constant. The study has been made for conditions of given diameter and surface area. The results obtained have been compared with those obtained by the method of gradient technique.

  3. Complaint Regarding the Use of Audit Results on a $1 Billion Missile Defense Agency Contract

    Science.gov (United States)

    2014-09-12

    our scope and methodology. See Appendix B for the sequence of events. Background Missile Defense Agency MDA is a research , development, and...a $2.07 billion cost-plus-fixed/award-fee1 proposal submitted by a DoD contractor for the Ground-Based Midcourse Defense (GMD) Core Completion...negotiated, DCAA discontinued its audit of the GMD proposal. MDA Did Not Consider the DCAA Preliminary Audit Results DFARS Procedures, Guidance , and

  4. Navy Aegis Ballistic Missile Defense (BMD) Program: Background and Issues for Congress

    Science.gov (United States)

    2011-04-19

    many ships will be available; and how the alphabet- soup of U.S. and international commanders will work together in a crisis. [Admiral Mark...meeting outside of missile defense,” Campbell said during a Nov. 3 interview with Aviation Week. These include providing weapons and manpower for...would seem a natural mission for the Army to fund and field the land-based SM-3 mission as the lead service. Campbell notes that the Army has 10

  5. Application of fleet ballistic missile components/designs for expendable launch vehicles

    Science.gov (United States)

    Grizzell, Norman E.

    This paper describes the orbital performance and configuration attributes of an expendable launch vehicle (ELV) derived from flight-qualified components. Representative logistical and programmatic data are also provided. The backbone of the ELV program described is the cost-effective use of proven Fleet Ballistic Missile components/designs coupled with other high confidence 'off-the-shelf' equipment. The ELV defined can place over a thousand pounds (1000 lb) of spacecraft (payload) into Low Earth Orbit.

  6. INVESTIGATION OF TIGHTLY COUPLED SINS/GPS INTEGRATION MIDCOURSE GUIDANCE FOR AIR-TO-AIR MISSILES

    Institute of Scientific and Technical Information of China (English)

    1998-01-01

    The applied problems of SINS/GPS integration navigation system existing in midcourse guidance of air-to-air missiles have been investigated recently. In comparison with those investigations existing in current publications, a new tightly coupled SINS/GPS integration navigation system for air-to-air missiles, based on the decorrelated pseudo-range approach, is presented in this paper. Because of high jamming and dynamic of air-to-air missiles, inertial velocity aiding GPS receiver is used to provide a more accurate, jam-resistant measurement for midcourse guidance systems. A tracking error estimator is designed to distinguish the correlation that existed between pseudo-range measurements and inertial information. It is found better to regard inertial velocity aiding errors as the noise of which statistical properties are unknown. So using mixed Kalman/minimax filtering theory, one can obtain the new tracking error estimator with simple and robust algorithm through constructing a composite filter consisting of two parts: Kalman filter for the noise of known statistics and minimax filter for the unknown. In order to ensure this simple estimator stability, a new method is proposed to choose its parameters, based on Khargonekars work. Moreover, it is demonstrated that the given method also ensures the proposed estimator optimality. All the work mentioned above is involved in the tightly coupled SINS/GPS integration midcourse system design in which a set of low-accuracy inertial components is shared by SINS and autopilot. Simulation results of a certain type of air-to-air missile are presented. Due to decorrelation by the tracking error estimator, only small white noise of pseudo-range measurements remains. So it is shown that application of the new midcourse guidance system results in better guidance accuracy, higher jam-resistance.

  7. A qualitative analysis of future air combat with 'fire and forget' missiles

    Science.gov (United States)

    Shinar, J.; Davidovitz, A.

    1987-01-01

    A set of previous examples have demonstrated that the two-target game formulation is adequate for modeling air-to-air combat between two aggressively motivated fighter aircraft. The present paper describes such an engagement between two aircraft of different speed but equipped with the same 'fire and forget' type guided missiles. The results of the analysis suggest a new concept of air combat tactics for future scenarios.

  8. Ballistic Missile Defense in the European Theater: Political, Military and Technical Considerations

    Science.gov (United States)

    2007-04-15

    in a ground-based system, called the Sol-Air Moyen Portee/ Terrestre (SAMP/T) that uses the Aster 15 and the Aster 30 missiles with a range of up to...development processes “ via a spiral pathway culminating in an operator-in-the- 107 COL Tim Polaske Chief...Reentry Vehicle SAMP/T Sol-Air Moyen Portee/ Terrestre SBI Space Based Interceptor SBIRS Space Based Infrared Satellite SHAPE

  9. REVOLUTION IN MILITARY AFFAIRS, MISSILE DEFENCE AND WEAPONS IN SPACE: THE US STRATEGIC TRIAD

    OpenAIRE

    Joelien Pretorius

    2011-01-01

    American plans for Missile Defence (MD) and the weaponisation of space should be analysed in the larger framework of the contemporary Revolution in Military Affairs (RMA).1 Soviet military analysts have written about this revolution from as early as the 1970s, but it was the application of information age technology (IT) in the 1991 Gulf War that captured the imagination of military planners and policy makers, especially in the US. The US is actively pursuing an RMA, conceptualised as integra...

  10. Echoes That Never Were: American Mobile Intercontinental Ballistic Missiles, 1956-1983

    Science.gov (United States)

    2006-05-11

    the remains of three old launch facilities now surrounded by the ubiquitous ice plant and sweet-smelling wildflowers of the California chaparral...1956-1983 Steven Anthony Pomeroy Doctor of Philosophy, May 11, 2006 (M.A., California State University, 1994) (B.A., Pennsylvania State University...the humanities from the California State University. He has had extensive experience in missile and space launch operations, education, training

  11. Ground Based Free Electron Laser Technology Integration Experiment, White Sands Missile Range, New Mexico

    Science.gov (United States)

    1987-01-01

    would preclude interference with televisions , radios and computer equipment operated in the area around WSMR. Warning signs will be posted at the...canadensis mexicana ); (2) black-tailed prairie dog (Cynonmys ludovicianus); (3) Colorado chipmunk (Eutamias quadrivittatus australis); (4) White Sands pupfish...by GBFEL TIE equipment, it could disturb local television and radio receivers. Since the GBFEL TIE will be located on White Sands Missile Range (WSMR

  12. 40th Annual Armament Systems: Guns-Ammunition-Rockets-Missiles Conference and Exhibition

    Science.gov (United States)

    2005-04-28

    PM] Abraham Overview, Mr. Robert Daunfeldt, Bofors Defence Summary Overview of an Advanced 2.75 Hypervelocity Weapon, Mr. Larry Bradford, CAT Flight...Engineer Tank Ammunition Directorate - IMI Ammunition Group A105/120/125 mm PELE Firing Results, Dr. Lutz Börngen, Rheinmetall Wafe Munition Line Of Sight...Missiles & Rockets Critical Asset Defense - ABRAHAM Rocket Assisted Projectile Mr. Robert Daunfeldt, Bofors Defence Hypervelocity Propulsion System

  13. Focal Plane Array Sensor for Imaging Infrared Seeker of Antitank Guided Missile

    Directory of Open Access Journals (Sweden)

    A.V.R. Warrier

    1995-07-01

    Full Text Available Technological issues and Processes for fabrication of mercury cadmium telluride detector arrays, charge coupled device readout arrays and integration of these into a focal plane array sensor have been discussed. Mini arrays of 16 X 16 size have been realised and tested to prove the technology and process schedule with a view to scaling up this for larger arrays to be used in the antitank guided missile.

  14. Storage Reliability Missile Materiel Program. Storage Reliability Summary Report. Volume 2. Electromechanical Devices

    Science.gov (United States)

    1978-02-01

    these factors places great im- portance on selecting missile materiels which are capable of performing reliably in each of the environments. The... great variety of special features and construction, are available. Latching and time delay are common features, and the reed construction has advantages...represents a reliability study performed under contract to RADC in 1974. This source identified the type and quality grades for the devides , however

  15. The Unauthorized Movement of Nuclear Weapons and Mistaken Shipment of Classified Missile Components: An Assessment

    Science.gov (United States)

    2012-01-01

    nonnuclear warhead cruise missiles in the storage structures even though visually recognizing the difference between nuclear and nonnuclear requires...ratification on that promise. Michelle Spencer, Aadina Ludin, and Heather Nelson 38 House? There is a response to that stimuli or lack of stimuli ...Encouraging teamwork  Responsibility. Former Chairman of the Joint Chiefs of Staff General Maxwell D. Taylor stated, ―One expects a military

  16. Environmental Assessment (EA): Proposed Missile Storage Improvements, Utah Test and Training Range

    Science.gov (United States)

    2013-06-11

    Prevention Plan TTU Thermal Treatment Unit UAC Utah Administrative Code US United States (of America ) USAF United States Air Force USC United States Code...activities. Wider roads and new missile storage facilities would create a minor loss of habitat, displacing reptiles , avian species, and mammals. The...Photography Guidelines, National Park Service, 2011. US 2010: Treaty Between the United States of America and the Russian Federation on Measures for the

  17. A new guidance law for a tactical surface-to-surface missile

    Directory of Open Access Journals (Sweden)

    Danilo V. Ćuk

    2012-01-01

    Full Text Available Modern tactical surface-to-surface missiles, equipped with strapdown inertial navigation systems, achieve very good accuracy compared with free-flight rockets. The probable range dispersion mainly depends on instruments errors and longitudinal disturbances such as rocket motor total-impulse deviation as well as differences between the estimated and actual values of the axial force and head wind. This paper gives an extension of the correlated velocity concept for surface-to-surface missiles without a thrust-terminating mechanism. The calculated parameters of the correlated velocity are stored into the memory of an onboard guidance computer. On the basis of the correlated velocity concept, the modified proportional navigation with the adjustment of the time-to-go of the missile to the target was proposed. It is shown that the new guidance law can compensate for the longitudinal disturbances of different levels successfully. The effectiveness of the proposed guidance method was confirmed by means of the calculated probable range and lateral dispersion for the anticipated disturbances in the guidance system.

  18. Development of Empirical Prediction Formula for Penetration of Ogive Nose Hard Missile into Concrete Targets

    Directory of Open Access Journals (Sweden)

    Ahmad M.A. Zaidi

    2010-01-01

    Full Text Available Problem statement: Concrete is basic construction material used for most of structures. However, the typical vital structures have to be designed as self-protective such as nuclear plants, power plants, weapon industries, weapons storage places and water retaining structures, against any threats like natural disaster tragedy incident or intentionally produced by horrible incidents such as dynamic loading, incident occurs in nuclear plants, terrorist attack, missile attack tsunami and etc. Approach: In modern science, the impact energies are crucial way to study the local impact effects on concrete structures. Results: The way in which the kinetic energy is distributed through the concrete target is also noteworthy in determining its response, with the influence of dimensional analysis of the non dimensional numbers. This study is concentrate on development of empirical formula for predicting penetration depth of ogive nose hard missile in to the concrete structures, with the effects of different CRH ratios of missile (CRH = 2.0, CRH = 3.0, CRH = 4.5, CRH = 6.0 based on critical impact energies, by using curve fitting dimensional analysis of non-dimensional numbers. Conclusions/Recommendations: For the verification, the proposed developed empirical formula was compared with other established formulae such as Modified NDRC formula, Hughes formula, ACE formula, UKAEA formula. It is expected that the outcome of the proposed formulae can be applied in design recommendations and design procedures, especially for determining the dynamic reaction of the target to foil penetration in terms of critical impact kinetic energy.

  19. Improved manufacturing techniques for RF and laser hardening of missile domes. Phase I. Technical report

    Energy Technology Data Exchange (ETDEWEB)

    Pawlewicz, W.T.; Mann, I.B.; Martin, P.M.; Hays, D.D.; Graybeal, A.G.

    1982-07-01

    This report summarizes key results and accomplishements during the first year of a Manufacturing Methods and Technology project to adapt an existing Pacific Northwest Laboratory (PNL) optical coating capability developed for high-power fusion-laser applications to the case of rf and laser hardening of plastic missile domes used by the US Army (MICOM). The primary objective of the first year's work was to demonstrate rf hardening of Hellfire and Copperhead 1.06-micron missile domes by use of transparent conductive Indium Tin Oxide (ITO) coatings. The project thus involved adaptation of a coating material and process developed for flat glass components used in fusion lasers to the case of hemispherical or conical heat-sensitive plastic domes used on laser-guided missiles. Specific ITO coating property goals were an electrical sheet resistance of 10 Ohms/square, a coated-dome transmission of 80% or more at 1.06 micron wavelength (compared to 90% for a bare dome), and good adhesion. The sheet resistance goal of 10 Ohms/square was expected to result in an rf attenuation of 30 dB at the frequencies of importance.

  20. Raman studies for stockpile reliability of missiles by detecting degradation of propellant stabilizers

    Science.gov (United States)

    Farley, Carlton; Kassu, Aschalew; Mills, Jonathan; Bibb, Jonathan; Curley, Michael; Ruffin, Paul; Sharma, Anup; Rice, Jeremy; McDonald, Brian

    2016-09-01

    The objective of this study is to demonstrate a sensitive Raman technique for sensing degradation of propellant stabilizers like MNA and 2-NDPA that are commonly used in some missiles. The functionality of missiles and rockets are often evaluated by being fired or decomposed at routine time-intervals after prolonged storage. However, these destructive testing techniques for determining long-term rocket motor aging and shelf-life are extremely costly. If successful, the Raman technique could be utilized to determine the health of propellant stabilizers without dismantling the missiles as is commonly done at present. Raman technique is to measure concentrations of propellant stabilizers between 0.1-2% in glycerin. Two different lasers at 785 nm and 532 nm are used for developing this technique. A secondary objective is to develop a theoretical model that predicts temperature as a function of time and position inside the cylindrical storage container of MNA or 2-NDPA stabilizer. This model can help in understanding the thermal degradation of propellant stabilizers.

  1. Missile target interaction analysis of B747 aircraft using hydro code LSDYNA

    Energy Technology Data Exchange (ETDEWEB)

    Lee, Kyoung Soo; Hong, Jung Wuk [KAIST, Daejeon (Korea, Republic of)

    2012-10-15

    After the 11 September 2011, we newly recognized the importance of intentional aircraft impact on national critical infrastructure such as tall buildings, military facilities, and nuclear power plants. A lot of research has been performed to measure the capability of current nuclear power plants to withstand unusual impact loadings. As a result, Nuclear Regulatory Commission (NRC) concluded that the impact of a large, commercial aircraft is a beyond design basis event (BDBE). In this paper, we demonstrate the assessment of the impact load of large, commercial B747 aircraft by using the so called missile target interaction analysis method. The results of impact force is compared with the reported impact force time histories of B747. To perform the missile target interaction analysis, an FE mesh model of B747 is developed. Rigid wall impact tests are performed numerically using commercial Hydro code LS DYNA with FE model of B747 to demonstrate the accuracy and applicability of the rigorous missile target interaction analysis.

  2. Upper and lower extremity nerve injuries in pediatric missile wounds: a selective approach to management.

    Science.gov (United States)

    Stoebner, Andrew A; Sachanandani, Neil S; Borschel, Gregory H

    2011-06-01

    Nerve injuries from missile and gunshot wounds often produce significant disability, and their management is controversial. The role of the surgeon in cases of missile wounds with neurologic deficits is not well defined. Enhancing the trauma team's ability to recognize treatable nerve injuries will lead to improved outcomes. Further, raising awareness of the time-sensitive nature of these injuries will also improve results in these cases. We reviewed a consecutive series of 17 pediatric patients with peripheral nerve injuries caused by missile and gunshot wounds in a tertiary care children's hospital. We examined the indications for surgery, presence of associated injuries, mechanisms of injury, demographic characteristics and clinical outcomes. Urban victims were significantly more likely to have been intentionally assaulted than rural or suburban victims and they were also less likely to have completed follow-up care. High-energy weapons were more likely to require surgery compared with low-energy weapons. Patients presenting with tendon injuries were more likely to have a high-grade nerve injury requiring surgery. Patients presenting with tendon lacerations or high-energy mechanisms were significantly more likely to require surgery. Early exploration should be undertaken in cases where transection is likely to have occurred. Early decompression of common entrapment sites distal to repairs or injuries should be performed. Because follow-up is poor in this population, treatment should be prompt and thorough.

  3. Study on the Analytical Behaviour of Concrete Structure Against Local Impact of Hard Missile

    Directory of Open Access Journals (Sweden)

    Ahmad Mujahid Ahmad Zaidi

    2011-07-01

    Full Text Available Concrete is basic construction material used for almost all kind of structure. However, in the majority essential structures such as nuclear plants, Power plants, Weapon Industries, weapons storage places, water retaining structures like dams, highways barriers, bridges, & etc., concrete structures have to be designed as self-protective structure which can afford any disaster or consciously engendered unpleasant incidents such as incident occurs in nuclear plants, incident in any essential industry, terrorist attack, Natural disasters like tsunami and etc missile attack, and local impact damage generated by kinetic missiles dynamic loading (steel rods, steel pipes, turbine blades, etc.. This paper inquisitively is paying attention on verdict of the recent development in formulating analytical behavior of concrete and reinforced concrete structures against local impact effect generated by hard missile with and without the influence of dimensional analysis based on dominant non-dimensional parameters, various nose shape factors at normal and certain inclined oblique angles. The paper comprises the analytical models and methods for predicting penetration, and perforation of concrete and reinforced concrete. The fallout conquer from this study can be used for making design counsel and design procedures for seminal the dynamic retort of the concrete targets to foil local impact damage.

  4. A Direct Interception Missile Assignment Model in Firepower Planning of Double-Layer Anti-Missile Combat%直接分配到弹的双层反导火力规划模型

    Institute of Scientific and Technical Information of China (English)

    李龙跃; 刘付显; 杨国哲; 赵麟锋

    2014-01-01

    Firepower application is one of the core problem in anti-missile power construction,Firepower Planning of double-layer anti-missile combat in terminal phase is a Nondeterministic polynomial hard Mod-eling question.We analysis the problem,when to assign the interception missiles to the targets and give the model assumptions;Then we establish the direct interception missile assignment model in firepower planning of double-layer anti-missile combat This model break the research which targets only can be as-signed to the weapon system or fire units in the past,assigned the interception missiles to ballistic missiles one by one,it's a new idea about firepower planning.%反导作战火力运用是反导力量建设的核心内容之一,末段双层反导火力规划是一个复杂的不确定多约束条件优化问题,对火力规划进行了问题分析、弹-目分配时机分析和模型假设;分2个阶段建立了直接分配到弹的末段双层反导火力规划模型,模型重点考虑拦截目标与拦截弹杀伤时间窗口的对应关系,建立起武器系统拦截弹与来袭目标的弹-目对应分配关系,提供一种新的、快速的双层反导火力规划方法。

  5. The First Distance Constraint on the Renegade High Velocity Cloud Complex WD

    CERN Document Server

    Peek, J E G; Sana, Hugues; Roman-Duval, Julia; Tumlinson, Jason; Zheng, Yong

    2016-01-01

    We present medium-resolution, near-ultraviolet VLT/FLAMES observations of the star USNO-A0600-15865535. We adapt a standard method of stellar typing to our measurement of the shape of the Balmer epsilon absorption line to demonstrates that USNO-A0600-15865535 is a blue horizontal branch star, residing in the lower stellar halo at a distance of 4.4 kpc from the Sun. We measure the H & K lines of singly-ionized calcium and find two isolated velocity components, one originating in the disk, and one associated with high-velocity cloud complex WD. This detection demonstrated that complex WD is closer than ~4.4 kpc and is the first distance constraint on the +100 km/s Galactic complex of clouds. We find that Complex WD is not in corotation with the Galactic disk as has been assumed for decades. We examine a number of scenarios, and find that the most likely is that Complex WD was ejected from the solar neighborhood and is only a few kpc from the Sun.

  6. Renegade homeostatic cytokine responses in T1D: drivers of regulatory/effector T cell imbalance.

    Science.gov (United States)

    Gupta, Shipra; Cerosaletti, Karen; Long, S Alice

    2014-04-01

    Homeostatic cytokines contribute to the balance between regulatory and effector T cells (Tregs and Teffs respectively) and are necessary to maintain peripheral tolerance. These cytokines include IL-2 that supports Treg and IL-7 and IL-15 that drive Teff. In overt settings of lost tolerance (i.e. graft rejection), IL-2 Treg signatures are decreased while IL-7 and IL-15 Teff signatures are often enhanced. Similar cytokine profile imbalances also occur in some autoimmune diseases. In type 1 diabetes (T1D), there are underlying defects in the IL-2 pathway and Teff cytokine blockade can prevent and treat diabetes in NOD mice. In this review, we summarize evidence of IL-2, IL-7 and IL-15 genetic and cellular alterations in T1D patients. We then discuss how the combined effect of these cytokine profiles may together contribute to altered Treg/Teff ratios and functions in T1D. Implications for combination therapies and suggestions for integrated cytokine and Treg/Teff biomarker development are then proposed. Copyright © 2014 Elsevier Inc. All rights reserved.

  7. Digital Renegades in America: Changing Metaphors to Realize the Potential of Technology in Education

    Science.gov (United States)

    Smith, Thomas

    2013-01-01

    In 2001, Marc Prensky introduced a new metaphor to the educational landscape. He suggested that the rising generation were growing up in a time so filled with new media that they were "digital natives," while those born earlier were "digital immigrants." In this view, because the digital natives are growing up immersed in a sea…

  8. Simulacioni model sistema za upravljanje letom protivbrodske rakete / Model for simulating the flight control system of a antiship missile

    Directory of Open Access Journals (Sweden)

    Nebojša N. Gaćeša

    2007-04-01

    Full Text Available U radu je analiziran program za simulaciju sistema za upravljanje letom protivbrodske rakete sa radarskom glavom za samonavođenje. Analiziran je matematički model rakete, model autopilota i model cilja. Ovakvim pristupom dobijen je rezultat koji omogućava uspostavljanje realnijeg procesa praćenja leta konkretne protivbrodske rakete, budući da upravljanje letom rakete na celoj trajektoriji ima znatne prednosti u odnosu na nevođene projektile, pre svega zbog mogućnosti gađanja pokretnih ciljeva. Simulacioni model upravljanja letom rakete pruža mogućnosti za dalje proučavanje ove klase raketa. / The paper analyzes a program for simulating the flight control of an antiship missile with the radar seeker. The paper analyzes a mathematic missile model an autopilot model and a target model. Thus obtained results enable a more realistic process of flight tracking of a particular antiship missile as the missile guidance along the whole trajectory provides many advantages over unguided projectiles, primarily because of the possibility to fire at moving targets. The flight control simulation model enables further study of this missile class.

  9. U.S.S.R. disposed of nuclear mini reactors for missiles; L'URSS disposait de minireacteurs nucleaires pour missiles

    Energy Technology Data Exchange (ETDEWEB)

    Kempf, H

    2004-07-01

    A Byelorussian savant, Vassili Nesterenko, reveals that Moscow had developed, in the eighties years very light and mobile reactors to supply steps of fire of its missiles. The Chernobylsk accident has stopped this project. The realizations of these nuclear plants were called Pamir. In 200, it was question to launch again this project but for civil applications. In 2002, the Russian Minister of Atomic Energy has launched the idea of floating nuclear power plants that could be installed in the region of Arkhangelsk (North west of russia) and on the river banks of Tchoukotka (North east of the Siberia). The nuclear power plants would be constituted of two 35 MW reactors coming from ice-breakers and would cost 180 millions dollars. They would be installed on a big barge anchored near the coast. But this project has risen numerous notices because of their insufficient safety. (N.C.)

  10. Synergetic Optimization of Missile Shapes for Aerodynamic and Radar Cross-Section Performance Based on Multi- objective Evolutionary Algorithm

    Institute of Scientific and Technical Information of China (English)

    刘洪

    2004-01-01

    A multiple-objective evolutionary algorithm (MOEA) with a new Decision Making (DM) scheme for MOD of conceptual missile shapes was presented, which is contrived to determine suitable tradeoffs from Pareto optimal set using interactive preference articulation. There are two objective functions, to maximize ratio of lift to drag and to minimize radar cross-section (RCS) value. 3D computational electromagnetic solver was used to evaluate RCS, electromagnetic performance. 3D Navier-Stokes flow solver was adopted to evaluate aerodynamic performance. A flight mechanics solver was used to analyze the stability of the missile. Based on the MOEA, a synergetic optimization of missile shapes for aerodynamic and radar cross-section performance is completed. The results show that the proposed approach can be used in more complex optimization case of flight vehicles.

  11. Analysis of the Dryden Wet Bulb GLobe Temperature Algorithm for White Sands Missile Range

    Science.gov (United States)

    LaQuay, Ryan Matthew

    2011-01-01

    In locations where workforce is exposed to high relative humidity and light winds, heat stress is a significant concern. Such is the case at the White Sands Missile Range in New Mexico. Heat stress is depicted by the wet bulb globe temperature, which is the official measurement used by the American Conference of Governmental Industrial Hygienists. The wet bulb globe temperature is measured by an instrument which was designed to be portable and needing routine maintenance. As an alternative form for measuring the wet bulb globe temperature, algorithms have been created to calculate the wet bulb globe temperature from basic meteorological observations. The algorithms are location dependent; therefore a specific algorithm is usually not suitable for multiple locations. Due to climatology similarities, the algorithm developed for use at the Dryden Flight Research Center was applied to data from the White Sands Missile Range. A study was performed that compared a wet bulb globe instrument to data from two Surface Atmospheric Measurement Systems that was applied to the Dryden wet bulb globe temperature algorithm. The period of study was from June to September of2009, with focus being applied from 0900 to 1800, local time. Analysis showed that the algorithm worked well, with a few exceptions. The algorithm becomes less accurate to the measurement when the dew point temperature is over 10 Celsius. Cloud cover also has a significant effect on the measured wet bulb globe temperature. The algorithm does not show red and black heat stress flags well due to shorter time scales of such events. The results of this study show that it is plausible that the Dryden Flight Research wet bulb globe temperature algorithm is compatible with the White Sands Missile Range, except for when there are increased dew point temperatures and cloud cover or precipitation. During such occasions, the wet bulb globe temperature instrument would be the preferred method of measurement. Out of the 30

  12. Navy Air-Launched Missile Operating and Support Cost Estimating Model

    Science.gov (United States)

    1979-04-01

    same manner as the previous oneexcept that half of the missile poundage is shipped in dromedary units. All routes are calculated with Dual Driver...Protective Service. Dromedary Rate Min. Wt. Security Rate Factor Origin % ($/cwt) (thous.of ibs) ( )t. GIC NWS Yorktown 50.0 38.63 2,500 21.84 60.47 30.24...ll I I IIII • I I N i l ll II Hium-+ ii[ii~ i 1j 78 The preceding calculation refers only to the rates for the poundage shipped in dromedary units. To

  13. Space and Missile Systems Center Tailoring: Tailoring Instructions for MIL-STD-882E

    Science.gov (United States)

    2012-11-30

    Space Command SPACE AND MISSILE SYSTEMS CENTER TAILORING TAILORING INSTRUCTIONS FOR MIL- STD -882E APPROVED FOR PUBLIC RELEASE...for MIL- STD -882E 5a. CONTRACT NUMBER 5b. GRANT NUMBER 5c. PROGRAM ELEMENT NUMBER 6. AUTHOR(S) 5d. PROJECT NUMBER 5e. TASK NUMBER 5f. WORK UNIT...THIS PAGE unclassified Standard Form 298 (Rev. 8-98) Prescribed by ANSI Std Z39-18 SMC Tailoring of MIL- STD -882E, System Safety FOREWORD This

  14. Method of Designing Missile Controller Based on Multi-Objective Optimization

    Institute of Scientific and Technical Information of China (English)

    LIN Bo; MENG Xiu-yun; LIU Zao-zhen

    2006-01-01

    A method of designing robust controller based on genetic algorithm is presented in order to overcome the drawback of manual modification and trial in designing the control system of missile. Specification functions which reflect the dynamic performance in time domain and robustness in frequency domain are presented,then dynamic/static performance, control cost and robust stability are incorporated into a multi-objective optimization problem. Genetic algorithm is used to solve the problem and achieve the optimal controller directly.Simulation results show that the controller provides a good stability and offers a good dynamic performance in a large flight envelope. The results also validate the effectiveness of the method.

  15. Boost-Phase ballistic missile trajectory estimation with ground based radar

    Institute of Scientific and Technical Information of China (English)

    Tang Yuyan; Huang Peikang

    2006-01-01

    A conditional boost-phase trajectory estimation method based on ballistic missile (BM) information database and classification is developed to estimate and predict boos-phase BM trajectory. The main uncertain factors to describe BM dynamics equation are reduced to the control law of trajectory pitch angle in boost-phase. After the BM mass at the beginning of estimation, the BM attack angle and the modification of engine thrust denoting BM acceleration are modeled reasonably, the boost-phase BM trajectory estimation with ground based radar is well realized. The validity of this estimation method is testified by computer simulation with a typical example.

  16. Golf Balls, Boomerangs and Asteroids The Impact of Missiles on Society

    CERN Document Server

    Kaye, Brian H

    1996-01-01

    Exciting reading for anyone with a curious mind!. 'Walking one day by a golf course in Wisconsin, I was startled to hear a sharp bang as a golf ball narrowly missed my head and hit a tree. My companion cheerfully remarked, 'That could have killed you, you know.' I picked up the innocent looking little white ball and looked at it with new respect.'. Prompted by this perilous experience, Brian Kaye has written a delightful and informative book on the design and behavior of different kinds of missiles from golf balls, arrows, and slingshots to comets and rockets to outer space. You'll learn about

  17. Confronting the ’Essence of Decision’: Canada and the Cuban Missile Crisis

    Science.gov (United States)

    2010-11-01

    conflit . DRDC CORA TM 2010-250 i This page intentionally left blank. DRDC CORA TM 2010-250 ii Executive Summary Introduction...clés étaient perçus par les autres, principalement par les États-Unis. Le triste épisode de la gestion de la crise des missiles de Cuba par Ottawa...du prochain conflit . « L’essence de la décision » américaine, bien que loin d’être parfaite, reposait sur un effort de compréhension du contexte

  18. Ballistic missile precession frequency extraction based on the Viterbi & Kalman algorithm

    Science.gov (United States)

    Wu, Longlong; Xie, Yongjie; Xu, Daping; Ren, Li

    2015-12-01

    Radar Micro-Doppler signatures are of great potential for target detection, classification and recognition. In the mid-course phase, warheads flying outside the atmosphere are usually accompanied by precession. Precession may induce additional frequency modulations on the returned radar signal, which can be regarded as a unique signature and provide additional information that is complementary to existing target recognition methods. The main purpose of this paper is to establish a more actual precession model of conical ballistic missile warhead and extract the precession parameters by utilizing Viterbi & Kalman algorithm, which improving the precession frequency estimation accuracy evidently , especially in low SNR.

  19. Ballistic Missile Defense Organization, Advance Planning Briefing for Industry, Updated Agenda, Attendance Roster, Proceedings.

    Science.gov (United States)

    1994-03-01

    Registration) Updated Agenda 2 Attendance Roster 3 Program Overview 21 Biographies of the Principal Speakers 28 SLIDES: "The Worldwide Missile Threat...229-5800 x Mr. C. Lee Newton Sverdrup Technology Inc PO Box 1935, Bldg 260 Eglin A F B FL 32542-0935 (904) 678-2001 x Dv. David A. Nichols...922-7350 x Dr. Gary H. Weissman LNK Corporation» Inc. Suite 306 6811 Kenilworth Avenue Riverdale MD 20737-1333 (301) 927-3223 x Mr. Isaac

  20. Computational Comparison of the Interaction of a Lateral Jet on a Supersonic Generic Missile

    OpenAIRE

    Gnemmi, Patrick; Adeli, Reza; Longo, José Maria

    2008-01-01

    The paper deals with the comparison of computations made at DLR and ISL on the interaction between a lateral jet issuing from a generic missile body and the oncoming supersonic cross-flow. Steady-state numerical simulations are carried out by 3D, viscous, turbulent, Reynolds-Averaged Navier-Stokes Codes; at DLR, a hybrid mesh is used for the TAU calculation, whereas at ISL a hexahedral mesh is used for the CFX computation. Experimental data acquired in the DLR wind tunnel TMK in Cologne act a...

  1. Computer program for simulating the six-degree-of-freedom motion of missile debris fragments

    Science.gov (United States)

    Hemsch, M. J.

    1981-05-01

    The rational modeling and empirical correlations used to build a comprehensive computer code for simulating general six-degree-of-freedom motions of missile debris fragments are described. The approach is deterministic in that a number of possible generic fragment shapes were defined, methods were selected to describe the aerodynamic loads on these shapes, and the results were incorporated in a six-degree-of-freedom trajectory program. The method chosen is simple enough to avoid large computation times and yet represents coning and tumbling conditions as well as trimmed flight.

  2. Missile longitudinal autopilot design using the state-dependent Riccati equation method

    Energy Technology Data Exchange (ETDEWEB)

    Mracek, C.P.; Cloutier, J.R. [Air Force Armament Directorate, Eglin, FL (United States)

    1994-12-31

    A missile output feedback pitch autopilot is designed using the state-dependent Riccati equation (SDRE) approach presented in. The particular SDRE design methodology chosen for this paper is referred to as SDRE H{sub 2}. The SDRE H{sub 2} design structure is the same as that of linear H{sub 2}, except that the two Riccati equations are state-dependent. Hence, SDRE H{sub 2} design is a nonlinear extension of linear H{sub 2} design. The procedural steps in the SDRE H{sub 2} design process are presented along with design results.

  3. REALIZATION OF GPS/SST/SINS INTEGRATED NAVIGATION FILTER ALGORITHM FOR BALLISTIC MISSILE

    Institute of Scientific and Technical Information of China (English)

    KANGGuo-hua; LIUJian-ye; ZHUYan-hua; XIONGZhi

    2005-01-01

    Considering the domestic single navigation system of the ballistic missile, a new filter method is presented. The method integrates the information of the strapdown star tracker (SST) attitude, the position and the velocity of a high speed GPS with a strapdown inertial navigation system (SINS) information into one filter, thus improving the precision of the attitude, the velocity, and the position. Finally, the GPS/SST/SINS simulation platfornt is designed. Simulation results demonstrate that the filter is robust and reliable, and the precision rises to the comparative level abroad.

  4. Application of Extended Kalman Filter to Tactical Ballistic Missile Re-entry Problem

    CERN Document Server

    Bhowmik, Subrata

    2007-01-01

    The objective is to investigate the advantages and performance of Extended Kalman Filter for the estimation of non-linear system where linearization takes place about a trajectory that was continually updated with the state estimates resulting from the measurement. Here tactile ballistic missile Re-entry problem is taken as a nonlinear system model and Extended Kalman Filter technique is used to estimate the positions and velocities at the X and Y direction at different values of ballistic coefficients. The result shows that the method gives better estimation with the increase of ballistic coefficient.

  5. Remote control canard missile with a free-rolling tail brake torque system

    Science.gov (United States)

    Blair, A. B., Jr.

    1981-01-01

    An experimental wind-tunnel investigation has been conducted at supersonic Mach numbers to determine the static aerodynamic characteristics of a cruciform canard-controlled missile with fixed and free-rolling tail-fin afterbodies. Mechanical coupling effects of the free-rolling tail afterbody were investigated using an electronic/electromagnetic brake system that provides arbitrary tail-fin brake torques with continuous measurements of tail-to-mainframe torque and tail-roll rate. Results are summarized to show the effects of fixed and free-rolling tail-fin afterbodies that include simulated measured bearing friction torques on the longitudinal and lateral-directional aerodynamic characteristics.

  6. Low-Cost Phased Array Antenna for Sounding Rockets, Missiles, and Expendable Launch Vehicles

    Science.gov (United States)

    Mullinix, Daniel; Hall, Kenneth; Smith, Bruce; Corbin, Brian

    2012-01-01

    A low-cost beamformer phased array antenna has been developed for expendable launch vehicles, rockets, and missiles. It utilizes a conformal array antenna of ring or individual radiators (design varies depending on application) that is designed to be fed by the recently developed hybrid electrical/mechanical (vendor-supplied) phased array beamformer. The combination of these new array antennas and the hybrid beamformer results in a conformal phased array antenna that has significantly higher gain than traditional omni antennas, and costs an order of magnitude or more less than traditional phased array designs. Existing omnidirectional antennas for sounding rockets, missiles, and expendable launch vehicles (ELVs) do not have sufficient gain to support the required communication data rates via the space network. Missiles and smaller ELVs are often stabilized in flight by a fast (i.e. 4 Hz) roll rate. This fast roll rate, combined with vehicle attitude changes, greatly increases the complexity of the high-gain antenna beam-tracking problem. Phased arrays for larger ELVs with roll control are prohibitively expensive. Prior techniques involved a traditional fully electronic phased array solution, combined with highly complex and very fast inertial measurement unit phased array beamformers. The functional operation of this phased array is substantially different from traditional phased arrays in that it uses a hybrid electrical/mechanical beamformer that creates the relative time delays for steering the antenna beam via a small physical movement of variable delay lines. This movement is controlled via an innovative antenna control unit that accesses an internal measurement unit for vehicle attitude information, computes a beam-pointing angle to the target, then points the beam via a stepper motor controller. The stepper motor on the beamformer controls the beamformer variable delay lines that apply the appropriate time delays to the individual array elements to properly

  7. ASTEROFF: A Computer Code to Deflect NEOs by Missiles shot from L1 and L3 (Earth-Moon)

    Science.gov (United States)

    Maccone, C.

    We develop the mathematical theory for an automatic, space-based system to deflect NEOs by virtue of missiles shot from the Earth-Moon L1 and L3 Lagrangian Points. A patent application has been filed for the relevant code, dubbed ASTEROFF (= Asteroids OFF !). This code was already implemented, and a copyright for it was registered. In a paper published in Acta Astronautica, Vol. 50, No. 3, pp. 185-199 (2002), this author proved mathematically the following theorem (hereafter called the ``confocal conics theorem''): ``Within the sphere of influence of the Earth, any NEO could be hit by a missile at just an angle of 90 degrees, was the missile shot from Lagrangian Points L1 or L3 of the Earth-Moon system, rather than from the surface of the Earth''. As a consequence, the hitting missile would have move along a ``confocal ellipse'' (centered at the Earth) uniquely determined by the NEO's incoming hyperbola. Based on the above theorem, the author further shows in this paper that: The proposed defense system would be ideal to deflect NEOs that are small, i.e. less than one kilometer in diameter. Small NEOs are just the most difficult ones to be detected early enough and to such an orbital accuracy to be positively sure that they are indeed hazardous. The traditional theory of Keplerian orbits can successfully be applied to get an excellent first-order approximation of the (otherwise unknown) mathematical formulae of the energy/momentum requested to achieve the NEO deflection. Many engineering details about the missiles shot from L1 and L3, however, still have to be implemented into our simulations, partly because they are classified. Was one missile not enough to deflect the NEO completely, it is a great advantage of the ``confocal conics'' used here that the new, slightly deflected NEO's hyperbola would certainly be hit at nearly 90 degrees by another and slightly more eccentric elliptical missile trajectory. A sufficient number of missiles could thus be launched in a

  8. Protivoklopni vođeni projektili zapadne Evrope, Izraela i Indije / Anti-tank guided missiles of western Europe, Israel and India

    Directory of Open Access Journals (Sweden)

    Goran M. Lazić

    2010-10-01

    Full Text Available Protivoklopni vođeni projektili namenjeni su za uništavanje teško-oklopljenih tenkova, kao i drugih oklopnih vozila. Ovaj rad nudi istorijsko-tehnički pregled (razvoj projektila kroz generacije i osnovni podaci vezani za borbeno-operativno dejstvo ovih projektila ovog tipa naoružanja koje poseduju zemlje zapadne Evrope, Izraela i Indije. Pored osnovnih podataka navode se i cene nekih projektila ponaosob, kao i tendencije razvoja u ovoj grani naoružanja. / Anti-tank guided missiles are designed to hit and destroy heavily armored tanks and other armored fighting vehicles. This review offers a historical and technical overview (development of missiles throughout generations and basic data about combat and operational actions of this type of weapons in Western Europe, Israel and India. The review also offers prices of some missiles and tendencies of development in this branch. Anti-tank guided missiles are primarily designed to destroy armoured tanks as well as other armoured vehicles. Anti-tank guided systems differ in size, from small ones (shoulder-launched missile weapons carried by a single person to complex weapon systems (crewserved, vehicle-mounted and airborne systems. The first generation of anti-tank guided missiles is a manually guided MCLOS (Manual Command to Line of Sight projectile requiring an operator to guide and steer it to a target by a joystick. Vickers vigilant is a British anti-tank wire-guided missile, produced in 1956. The Bantam (Bofors Anti-Tank Missile or Robot 53 (RB 53 is a Swedish anti-tank wire-guided missile, produced in 1963. Cobra is a German - Swiss product which entered the operational use in 1956. It was replaced by Cobra 2000 and Mamaba systems, which are anti-tank guided missiles of the first generation, but with improved guidance and electronics. ENTAC (Engin téléguidé anti-char or MGM Petronor-32A is a French anti-tank wire-guided missile, widely spread and still in the operational use in many

  9. Using GPU convolutions to correct optical distortion in closed-loop real-time missile simulations

    Science.gov (United States)

    Fronckowiak, Thomas, Jr.

    2009-05-01

    U.S. Army Aviation and Missile Research, Development and Engineering Center (AMRDEC) has long been a leader in in-band high fidelity scientific scene generation. Recent efforts to harness and exploit the parallel power of the Graphics Processor Unit (GPU), for both graphics and general purpose processing, have been paramount. The emergence of sophisticated image generation software packages, such as the Common Scene Generator (CSG) and the Joint Signature Image Generator (JSIG), have lead to a sharp increase in the performance of digital simulations and signal injection and projection systems in both tactical and strategic programs. One area of missile simulations that benefits from this technology is real-time modeling of optical effects, such as seeker dome distortion, glint, blurring effects, and correcting for facility misalignment and distortion. This paper discusses the on-going research of applying convolution filters to the GPU multi-pass rendering process to compensate for spatial distortion in the optical projection path for synthetic environments.

  10. The role of maxillofacial radiologists in gunshot injuries: a hypothesized missile trajectory in two case reports

    Science.gov (United States)

    Sansare, K; Khanna, V; Karjodkar, F

    2011-01-01

    Gunshot injuries are an emerging form of trauma that oral radiologists increasingly have to deal with. There are two main types of gunshot injuries: high-velocity and low-velocity bullet injuries. The outcome of high-velocity gunshot injury is usually fatal; however, a non-fatal low-velocity injury to the maxillofacial region is more likely to be encountered by the oral and maxillofacial radiologist. It is therefore important to up-to-date knowledge of ballistic science and its implications in the field of maxillofacial radiology. The ability of oral and maxillofacial radiologists to predict the missile trajectory will aid the assessment and localization of the damage caused by the bullet and its splinters. Predicting the missile trajectory may also be of help to law enforcement agencies and forensic scientists in determining the type of firearm used and direction of fire. This article, which examines two cases, attempts to highlight to the oral radiologist this emerging form of trauma and its implications. PMID:21159916

  11. The Control of Asymmetric Rolling Missiles Based on Improved Trajectory Linearization Control Method

    Directory of Open Access Journals (Sweden)

    Huadong Sun

    2016-07-01

    Full Text Available According to motion characteristic of an asymmetric rolling missile with damage fin, a three-channel controlled model is established. The controller which is used to realize non-linear tracking and decoupling control of the roll and angle motion is introduced based on an improved trajector y linearization control method. The improved method is composed of the classic trajectory linearization control method and a compensation control law. The classic trajectory linearization control method is implemented in the time-scale separation principle. The Lipschitz non-linear state observer systematically obtained by solving the linear matrix inequality approach is provided to estimate state variables and unknown parameters, and then the compensation control law utilizing the estimated unknown parameters improves the TLC method. Simulation experiments show that the adaptive decoupling control ensure tracking performance, and the robustness and accuracy of missile attitude control are ensured under the condition of the system parameters uncertainty, random observation noise and external disturbance caused by damage fin.

  12. The Regional Dimension of Romania's Participation to the Anti-Missile Defense System

    Directory of Open Access Journals (Sweden)

    Florin Iftode

    2015-08-01

    Full Text Available The current security environment is characterized by a high degree of instability and unpredictability, through the manifestation of new risks and threats, especially those with asymmetrical nature, by redefining the relations between the great powers, and increasing freedom of action of the regional actors (state and non-state. At the international level, the end of the Cold War has led to a fragmentation of efforts in the security field, with direct implications on the need for further efforts of the international community coordination. In this era of profound change and transformation it is not possible the adoption of an isolationist policy of security, but only in a broader context of interdependencies and relationships between general trends, threats or challenges specific to a particular area or geographic areas. Swift operationalization of the anti-missile system will strengthen the national security both directly, through the protection it provides for the entire national territory, and indirectly, as the system will have a deterrent important role, able to mitigate risks of possible attacks by ballistic missiles. The role of deterrence will remove the risk of attack against any Allied territory on which, by virtue of membership in NATO and obligations involved according to article 5 of the Washington Treaty, Romania has also responsibilities.

  13. Optimization of three-loop missile autopilot gain under crossover frequency constraint

    Institute of Scientific and Technical Information of China (English)

    M.A. ABD-ELATIF; Long-jun QIAN; Yu-ming BO

    2016-01-01

    The open-loop crossover frequency is pointed as an important parameter for practical autopilot design. Since different gain designs may achieve the same open-loop crossover frequency, it should be neither considered as a performance objective of the optimal autopilot design-schemes nor neglected. Besides, the main assignment of the autopilot is to drive the missile to track the acceleration commands, so the autopilot gain design should be evaluated directly according to the resultant tracking performance. For this purpose, an optimal design methodology of the three-loop missile autopilot is introduced based on constraint optimization technique, where the tracking performance is established analytically as the design objective and the open-loop crossover frequency is formed as inequality constraint function, both are manipulated in terms of stable characteristic parameters of the autopilot closed-loop. The proposed technique is implemented with the assistance of a numerical optimization algorithm which automatically adjusts the design parameters. Finally, numerical simulation results are provided to demonstrate the effectiveness and feasibility of the proposed approach compared with that in some references.

  14. Adaptive critic autopilot design of bank-to-turn missiles using fuzzy basis function networks.

    Science.gov (United States)

    Lin, Chuan-Kai

    2005-04-01

    A new adaptive critic autopilot design for bank-to-turn missiles is presented. In this paper, the architecture of adaptive critic learning scheme contains a fuzzy-basis-function-network based associative search element (ASE), which is employed to approximate nonlinear and complex functions of bank-to-turn missiles, and an adaptive critic element (ACE) generating the reinforcement signal to tune the associative search element. In the design of the adaptive critic autopilot, the control law receives signals from a fixed gain controller, an ASE and an adaptive robust element, which can eliminate approximation errors and disturbances. Traditional adaptive critic reinforcement learning is the problem faced by an agent that must learn behavior through trial-and-error interactions with a dynamic environment, however, the proposed tuning algorithm can significantly shorten the learning time by online tuning all parameters of fuzzy basis functions and weights of ASE and ACE. Moreover, the weight updating law derived from the Lyapunov stability theory is capable of guaranteeing both tracking performance and stability. Computer simulation results confirm the effectiveness of the proposed adaptive critic autopilot.

  15. 33 CFR 334.1130 - Pacific Ocean, Western Space and Missile Center (WSMC), Vandenberg AFB, Calif.; danger zones.

    Science.gov (United States)

    2010-07-01

    ... Missile Center (WSMC), Vandenberg AFB, Calif.; danger zones. 334.1130 Section 334.1130 Navigation and Navigable Waters CORPS OF ENGINEERS, DEPARTMENT OF THE ARMY, DEPARTMENT OF DEFENSE DANGER ZONE AND..., Calif.; danger zones. (a) The Area. (1) The waters of the Pacific Ocean in an area extending...

  16. Environmental Impact Statement for BOMARC Missile Site, McGuire AFB, New Jersey. Volume 1, Sections 1 through 8

    Science.gov (United States)

    1992-05-22

    the site is an Urban Land Unit. By definition, the Urban Land Units are variable in their composition U and morphology . 3.2.8.3 Test Pit Data for...species present, particularly near missile Shelter 204 and the associated drainage swale, include members of the grass family (Gramineae or Poaceae

  17. 78 FR 76060 - Pacific Ocean off the Pacific Missile Range Facility at Barking Sands, Island of Kauai, Hawaii...

    Science.gov (United States)

    2013-12-16

    ... amendment to the regulation will not have a significant impact to the quality of the human environment and... activities, increases in force protection and other mission-essential evolutions without first obtaining...-essential evolutions. Residents and visitors who typically use these waters off Pacific Missile...

  18. Adaptive Control and Guidance for Tactical Missiles. Volume 1: Parts 1 and 2. Introduction and Adaptive Control Theory

    Science.gov (United States)

    varying airframe dynamics. Guidance techniques for tactical missiles are also reviewed and a number of steering laws, derived from optimal control ... theory , are evaluated. Quantitative comparisons are made between different guidance laws on the basis of intercept accuracy and control effort expended.

  19. Surgical treatment of tibial nonunion after wounding by high velocity missile and external fixators: A case report

    Directory of Open Access Journals (Sweden)

    Golubović Ivan

    2012-01-01

    Full Text Available Introduction. The missiles of modern firearms can cause severe fractures of the extremity. High velocity missile fractures of the tibia are characterized by massive tissue destruction and primary contamination with polymorphic bacteria. Treatment of these fractures is often complicated by delayed healing, poor position healing, nonhealing and bone tissue infection. Case Outline. We present the management of tibial nonunion after wounding by high velocity missile and primary treatment by external fixation in a 25-year-old patient. The patient was primarily treated with external fixation and reconstructive operations of the soft tissue without union of the fracture. Seven months after injury we placed a compression-distraction external fixator type Mitkovic and started with compression and distraction in the fracture focus after osteotomy of the fibula and autospongioplasty. We recorded satisfactory fracture healing and good functional outcome. Conclusion. Contamination and devitalization of the softtissue envelope increase the risk of infection and nonunion in fractures after wounding by high velocity missile. The use of the compression-distraction external fixator type Mitkovic may be an effective method in nonunions of the tibia after this kind of injury. [Projekat Ministarstva nauke Republike Srbije, br. III 41004

  20. Three-time rapid transfer alignment method of SINS/GPS navigation system of high-speed marine missile

    Institute of Scientific and Technical Information of China (English)

    WANG Si; DENG Zheng-long; SU Ling-feng

    2008-01-01

    The transfer alignment of SINS/GPS navigation system of a high-speed marine missile was investiga-ted. With the help of the big acceleration of a high-speed missile, the transfer alignment was changed into a three-time alignment. The azimuth alignment was coarsely finished in 10s in the first time alignment, the hori-zontal alignment was accurately and rapidly finished in the second time alignment, and the azimuth alignment was accurately finished in the third time alignment. Because the second time alignment and the third time align-ment were finished by GPS after the missile was launched, the horizontal alignment and the second azimuth a-lignment got rid of the influence of the warship body flexibility deforming. The precision and rapidity of the hori-zontal alignment were prominently increased due to the vertical launch of the marine missile with the big accel-eration. Simulation verifies the effectiveness of the proposed alignment method.

  1. Storage Reliability of Missile Materiel Program. Storage Reliability Analysis Summary Report. Volume 1. Electrical and Electronic Devices

    Science.gov (United States)

    1976-05-01

    Donald R. Earles .. FOR , HEADQUARTERS , U. S. ARMY MISSILE COMMAND REDSTONE ARSENAL, ALABAMA IN COMPLIANCE WITH CONTRACT NO. DAAHOI-74-C-0853 DATED 4...not available. Data storage failure modes is mucl . less extensive. A summary of the failure modes is shown in Table 4.1-2. 4.1.2 Non-Operational Failure

  2. Dynamic planning of navigation determinations of airspace and missile objects in an automated flight test control system

    Science.gov (United States)

    Lovtsov, D. A.; Karpov, D. S.

    2011-12-01

    This study considers an approach to planning navigation determinations of airspace and missile objects in the course of preparing for and carrying out an active flight test in an automated flight test control system. The approach is based on special information and mathematical software. The performance indices of the navigation determination subsystem are studied. Results of simulated modeling are provided.

  3. 78 FR 31614 - Implementation of Regulatory Guide 1.221 on Design-Basis Hurricane and Hurricane Missiles

    Science.gov (United States)

    2013-05-24

    ....221 on Design-Basis Hurricane and Hurricane Missiles AGENCY: Nuclear Regulatory Commission. ACTION... guidance regarding the application of Regulatory Guide (RG) 1.221, ``Design-Basis Hurricane and Hurricane... ML13015A688 Interim Staff Guidance-024 on Implementation of Regulatory Guide 1.221 on Design-Basis...

  4. 弹载共形遥测天线的设计%Design of conformal telemetry antenna on missiles

    Institute of Scientific and Technical Information of China (English)

    周旭冉; 高宝建; 伍捍东; 任宇辉

    2013-01-01

    In this paper, a microstrip antenna on missiles is proposed. The antenna is conformal with the curved surface of missile, and the convex height of radome is less than 8 mm. This proposal will not have any influence on both dynamic characteristics of the missile body and mechanical strength of the airframe. The antenna can obtain the high gain of 8.4dBi, its simulation pattern is almost consistent with the measured pattern results, and the antenna has the stable radiation characteristics in operating frequency range. Therefore it is very suitable to be fuze, telemetry antennas on missiles.%设计了一种弹载微带天线,该天线与弹体曲面共形,加上天线罩所凸出的曲面高度不超过8 mm,不仅不影响弹体的动力学特性,而且也不损伤弹体的机械强度.该天线具有较高的增益(8.4 dBi),仿真方向图与实测方向图吻合良好,且在整个工作频段内辐射特性稳定,非常适合作为弹载引信、遥测天线.

  5. Motion of a ballistic missile angularly misaligned with the flight path upon entering the atmosphere and its effect upon aerodynamic heating, aerodynamic loads, and miss distance

    Science.gov (United States)

    Allen, Julian H

    1957-01-01

    An analysis is given of the oscillating motion of a ballistic missile which upon entering the atmosphere is angularly misaligned with respect to the flight path. The history of the motion for some example missiles is discussed from the point of view of the effect of the motion on the aerodynamic heating and loading. The miss distance at the target due to misalignment and to small accidental trim angles is treated. The stability problem is also discussed for the case where the missile is tumbling prior to atmospheric entry.

  6. Data fusion control and guidance of surface-to-air missile under the complex circumstance based on neural-net technology

    Institute of Scientific and Technical Information of China (English)

    Zhou Deyun; Zhou Feng

    2008-01-01

    Under the complicated electromagnetism circumstance,the model of data fusion control and guidance of surface-to-air missile weapon systems is established.Such ways and theories as Elman-NN,radar tracking and niter's data fusion net based on the group method for data-processing (GMRDF) are applied to constructing the model of data fusion.The highly reliable state estimation of the tracking targets and the improvement in accuracy of control and guidance are obtained.The purpose is optimization design of data fusion control and guidance of surface-to-air missile weapon systems and improving the fighting effectiveness of surface-to-air missile weapon systems.

  7. Missile Aerodynamics

    Science.gov (United States)

    1979-02-01

    flow pictures that on such a wing the same type of flow is preserved up to large incidences, and that it devel- ops in a regular manner, at least as...flow spends in each orientation. Support for this point of view comes from surface pressure withno isc nibe vriaio n ts ndiion. Cark 1 ha alo ... Vera laval d’une mani’are quasi p4riodique. Las rdpercuaaiona de tela phdnam’anes sont assentiellement dea deux orcires - tout d’abard, induction de

  8. Experimental static aerodynamic forces and moments at high subsonic speeds on a missile model during simulated launching from the midsemispan location of a 45 degree sweptback wing-fuselage-pylon combination

    Science.gov (United States)

    Alford, William J; King, Thomas, Jr

    1957-01-01

    An investigation was made at high subsonic speeds in the Langley high-speed 7- by 10-foot tunnel to determine the static aerodynamic forces and moments on a missile model during simulated launching from the midsemispan location of a 45 degree sweptback wing-fuselage-pylon combination. The results indicated significant variations in all the aerodynamic components with changes in chordwise location of the missile. Increasing the angle of attack caused increases in the induced effects on the missile model because of the wing-fuselage-pylon combination. Increasing the Mach number had little effect on the variations of the missile aerodynamic characteristics with angle of attack except that nonlinearities were incurred at smaller angles of attack for the higher Mach numbers. The effects of finite wing thickness on the missile characteristics, at zero angle of attack, increase with increasing Mach number. The effects of the pylon on the missile characteristics were to causeincreases in the rolling-moment variation with angle of attack and a negative displacement of the pitching-moment curves at zero angle of attack. The effects of skewing the missile in the lateral direction relative to and sideslipping the missile with the wing-fuselage-pylon combination were to cause additional increments in side force at zero angle of attack. For the missile yawing moments the effects of changes in skew or sideslip angles were qualitatively as would be expected from consideration of the isolated missile characteristics, although there existed differences in theyawing-moment magnitudes.

  9. Tank segmentation of infrared images with complex background for the homing anti-tank missile

    Science.gov (United States)

    Zhou, Yulong; Gao, Min; Fang, Dan; Zhang, Baoquan

    2016-07-01

    In an effort to achieve fast and effective tank segmentation of infrared images under complex background for the homing anti-tank missile, the threshold of the maximum between-class variance method (i.e., the Otsu method) is experimentally analyzed, and the working mechanism of the Otsu method is revealed. Subsequently, a fast and effective method for tank segmentation under complex background is proposed based on the Otsu method by constraining the image background pixels and gray levels. Firstly, with the prior information of the tank, derive the equation to calculate the number of pixels of tank according to optical imaging principle, and then use the calculated tank size to constrain the image background pixels. Secondly, employ the golden section to restrict the background gray levels. Finally, use the Otsu method to implement the segmentation of the tank. Experimental results demonstrate that the proposed method can get as an ideal result as the manual segmentation with less running time.

  10. Sliding mode control for an aerodynamic missile based on backstepping design

    Institute of Scientific and Technical Information of China (English)

    Wenjin GU; Hongchao ZHAO; Changpeng PAN

    2005-01-01

    In order to solve the mismatched uncertainties of a class of nonlinear systems,a control method of sliding mode control (SMC) based on the backstepping design is proposed.It introduces SMC in to the last step of backstepping design to modify the backstepping algorithm.This combination not only enables the generalization of the backstepping design to be applied to more general nonlinear systems,but also makes the SMC method become effective in solving the mismatched uncertainties.The SMC based on the backstepping design is applied to the flight control system design of an aerodynamic missile.The control system is researched through simulation.The simulation results show the effectiveness of the proposed control method.

  11. Advanced technology payoffs for future rotorcraft, commuter aircraft, cruise missile, and APU propulsion systems

    Science.gov (United States)

    Turk, M. A.; Zeiner, P. K.

    1986-01-01

    In connection with the significant advances made regarding the performance of larger gas turbines, challenges arise concerning the improvement of small gas turbine engines in the 250 to 1000 horsepower range. In response to these challenges, the NASA/Army-sponsored Small Engine Component Technology (SECT) study was undertaken with the objective to identify the engine cycle, configuration, and component technology requirements for the substantial performance improvements desired in year-2000 small gas turbine engines. In the context of this objective, an American turbine engine company evaluated engines for four year-2000 applications, including a rotorcraft, a commuter aircraft, a supersonic cruise missile, and an auxiliary power unit (APU). Attention is given to reference missions, reference engines, reference aircraft, year-2000 technology projections, cycle studies, advanced engine selections, and a technology evaluation.

  12. Designing Integrated Fuzzy Guidance Law for Aerodynamic Homing Missiles Using Genetic Algorithms

    Science.gov (United States)

    Omar, Hanafy M.

    The Fuzzy logic controller (FLC) is well-known for robustness to parameter variations and ability to reject noise. However, its design requires definition of many parameters. This work proposes a systematic and simple procedure to develop an integrated fuzzy-based guidance law which consists of three FLC. Each is activated in a region of the interception. Another fuzzy-based switching system is introduced to allow smooth transition between these controllers. The parameters of all the fuzzy controllers, which include the distribution of the membership functions and the rules, are obtained simply by observing the function of each controller. Furthermore, these parameters are tuned by genetic algorithms by solving an optimization problem to minimize the interception time, missile acceleration commands, and miss distance. The simulation results show that the proposed procedure can generate a guidance law with satisfactory performance.

  13. Adaptive Sliding Mode BTT Autopilot for Cruise Missiles with Variable-Swept Wings

    Institute of Scientific and Technical Information of China (English)

    Wei-Ming Li; Rui-Sheng Sun; Hong-Yang Bai; Peng-Yun Liu

    2014-01-01

    In this paper, an adaptive sliding mode method was proposed for BTT autopilot of cruise missiles with variable-swept wings. To realize the whole state feedback, the roll angle, normal overloads and angular rates were considered as state variables of the autopilot, and a parametric sliding mode controller was designed via feedback linearization. A novel parametric adaptation law was put forward to estimate the nonlinear time-varying parameter perturbations in real time based on Lyapunov stability theory. A sliding mode boundary layer theory was adopted to smooth the discontinuity of control variables and eliminate the control chattering. The simulation was presented for the roll angle and overload commands tracking in different configuration schemes. The results indicated that the controlled system has robust dynamic tracking performance in condition of the large-scale aerodynamic parametric variety resulted from variable-swept wings.

  14. Global stabilizing controller design for linear time-varying systems and its application on BTT missiles

    Institute of Scientific and Technical Information of China (English)

    2008-01-01

    A parametric method for the gain-scheduled controller design of a linear time-varying system is given. According to the proposed scheduling method, the performance between adjacent characteristic points is preserved by the invariant eigenvalues and the gradually varying eigenvectors. A sufficient stability criterion is given by constructing a series of Lyapunov functions based on the selected discrete characteristic points. An important contribution is that it provides a simple and feasible approach for the design of gain-scheduled controllers for linear time-varying systems, which can guarantee both the global stability and the desired closed-loop performance of the resulted system. The method is applied to the design of a BTT missile autopilot and the simulation results show that the method is superior to the traditional one in sense of either global stability or system performance.

  15. Genetic algorithm to solve constrained routing problem with applications for cruise missile routing

    Science.gov (United States)

    Latourell, James L.; Wallet, Bradley C.; Copeland, Bruce

    1998-03-01

    In this paper the use of a Genetic Algorithm to solve a constrained vehicle routing problem is explored. The problem is two-dimensional with obstacles represented as ellipses of uncertainty surrounding each obstacle point. A route is defined as a series of points through which the vehicle sequentially travels from the starting point to the ending point. The physical constraints of total route length and maximum turn angle are included and appear in the fitness function. In order to be valid, a route must go from start to finish without violating any constraint. The effects that different mutation rates and population sizes have on the algorithm's computation speed and ability to find a high quality route are also explored. Finally, possible applications of this algorithm to the problem of route planning for cruise missiles are discussed.

  16. Biannual water-resources review, White Sands Missile Range, New Mexico, 1986 and 1987

    Science.gov (United States)

    Myers, Robert G.; Sharp, Steven C.

    1989-01-01

    Hydrologic data were collected at White Sands Missile Range, New Mexico in 1986 and 1987. The total groundwater withdrawal in 1986 was 565,462,500 gal and in 1987 it was 620,492,000 gal. The total groundwater withdrawal was 110,971,300 gal less in 1986 than in 1985, but 55,029,500 gal more in 1987 than in 1986. Water samples from five Post Headquarters water supply wells were collected for chemical analysis in 1986. In 1987, water samples were collected from four test wells in the Post Headquarters area for analysis of selected volatile organic compounds. Twenty-eight water samples from wells were collected for analysis of specific conductance in 1986 and 1987. (USGS)

  17. Simulation of Missile Autopilot with Two-Rate Hybrid Neural Network System

    Directory of Open Access Journals (Sweden)

    ASTROV, I.

    2007-04-01

    Full Text Available This paper proposes a two-rate hybrid neural network system, which consists of two artificial neural network subsystems. These neural network subsystems are used as the dynamic subsystems controllers.1 This is because such neuromorphic controllers are especially suitable to control complex systems. An illustrative example - two-rate neural network hybrid control of decomposed stochastic model of a rigid guided missile over different operating conditions - was carried out using the proposed two-rate state-space decomposition technique. This example demonstrates that this research technique results in simplified low-order autonomous control subsystems with various speeds of actuation, and shows the quality of the proposed technique. The obtained results show that the control tasks for the autonomous subsystems can be solved more qualitatively than for the original system. The simulation and animation results with use of software package Simulink demonstrate that this research technique would work for real-time stochastic systems.

  18. Real-time target motion animation for missile warning system testing

    Science.gov (United States)

    Perkins, Timothy; Sundberg, Robert; Cordell, John; Tun, Zaw; Owen, Mark

    2006-05-01

    The QUick Image Display (QUID) model accurately computes and displays radiance images of aircraft and other objects, generically called targets, at animation rates while the target undergoes unrestricted flight. Animation rates are obtained without sacrificing radiometric accuracy by using two important innovations. First, QUID has been implemented using the Open Scene Graph (OSG) library, an open-source, cross-platform 3-D graphics toolkit for the development of high performance graphics applications in the fields of visual simulation, virtual reality, scientific visualization and modeling. Written entirely in standard C++ and fully encapsulating OpenGL and its extensions, OSG exploits modern graphics hardware to perform the computationally intensive calculations such as hidden surface removal, 3-D transformations, and shadow casting. Second, a novel formulation for reflective/emissive terms enables rapid and accurate calculation of per-vertex radiance. The bi-directional reflectance distribution function (BRDF) is a decomposed into separable spectral and angular functions. The spectral terms can be pre-calculated for a user specified band pass and for a set of target-observer ranges. The only BRDF calculations which must be performed during target motion involves the observer-target-source angular functions. QUID supports a variety of target geometry files and is capable of rendering scenes containing high level-of-detail targets with thousands of facets. QUID generates accurate visible to LWIR radiance maps, in-band and spectral signatures. The newest features of QUID are illustrated with radiance and apparent temperature images of threat missiles as viewed by an aircraft missile warning system.

  19. Application of the Janus Combat Model for analysis of alternatives : a study of the operational effectiveness of the common missile as compared to the Hellfire

    OpenAIRE

    2002-01-01

    Approved for public release; distribution is unlimited By 2010, 100 percent of the existing stockpile of Hellfire and TOW 2A/2B missiles will reach their design shelf life. The stock of Hellfire missiles available to support Army air-to-ground combat will be depleted by 2015. Of particular interest to the Aviation community is the Comanche first unit equipped (FUE) in 2009, which will be significantly impacted by the scarcity and condition of this primary weapon. This research employs the ...

  20. Evaluation of the Transfer of International Traffic in Arms Regulations-Controlled Missile Defense Technology to the National Aeronautics and Space Administration (NASA)

    Science.gov (United States)

    2015-07-13

    approval from the U.S. Department of State, is prohibited.” 4 Category IV (i) is launch vehicles, guided missiles, ballistic missiles, rockets...computer forensic evidence, we were not able to prove or disprove his contention that he did not share the technical data with anybody. Also, as...a retransfer occurred. Our evaluation was limited based on NASA’s inability to provide historical email records and the lack of computer forensic

  1. Analysis of Rocket, Ram-Jet, and Turbojet Engines for Supersonic Propulsion of Long-Range Missles. II - Rocket Missile Performance

    Science.gov (United States)

    Huff, Vearl N.; Kerrebrock, Jack

    1954-01-01

    The theoretical performance of a two-stage ballistic rocket mis having a centerbody and two parallel boosters was investigated for J oxygen and ammonia-fluorine propellants. Both power-plant and missi parameters were optimized to give minimum cost on-the basis of the analysis for a range of 5500 nautical miles. After optimum values were found, each parameter was varied independently to determine its effect on performance of the missile. The missile using the ammonia-fluorine propellant weighs about one half as much as a missile using JP4-oxygen. Based on an expected unit cost of fluorine in quantity production, the ammonia-fluorine missile has a substantially lower relative cost than a JP4-oxygen missile. Optimum chamber pressures for both propellant systems and for both the centerbody and boosters were between 450 and 600 pounds per square inch. High design altitudes for the exhaust nozzle are desirable for both the centerbody and boosters. For the centerbody, the design altitude should be between 45,000 and 60,000 feet, with the value for ammonia-fluorine lower than that for JP4-oxygen. For the boosters, the design altitude should be 20,000 to 30,000 feet, with the value for the ammonia-fluorine. missile higher.

  2. 非定常导弹尾焰数值模拟%Numerical simulation of the Unsteady-state Missile Plume

    Institute of Scientific and Technical Information of China (English)

    李华; 王占学

    2012-01-01

    computations for a missile plumes flowfield were made using standard k-epsilon turbulence model in two parts. For one part, the mach number of the missile, as one of the missile model boundary conditions for computations, changes from 1.000 to 2.000. The another part, the missile plumes flowfield was simulated using the transient n (the static pressure ratio of missile nozzle exit to freestream) which changes from 1.000 to 11.000. The results can provide us the approximately data of missile plumes parameters under various operation conditions.%采用标准k-epsilon湍流模型对某型导弹高空飞行时的尾焰流场进行了模拟,对导弹飞行马赫数Ma由1.0变化为2.0和导弹尾喷管出口静压与大气静压比n由1.000变化为11.000的导弹尾焰流场分别进行了计算.分析了导弹飞行马赫数和静压比n对导弹尾焰产生的影响,并拟合出了相应的公式.

  3. Supersonic aerodynamic characteristics of a maneuvering canard-controlled missile with fixed and free-rolling tail fins

    Science.gov (United States)

    Blair, A. B., Jr.

    1990-01-01

    Wind tunnel investigations were conducted on a generic cruciform canard-controlled missile configuration. The model featured fixed or free-rolling tail-fin afterbodies to provide an expanded aerodynamic data base with particular emphasis on alleviating large induced rolling moments and/or for providing canard roll control throughout the entire test angle-of-attack range. The tests were conducted in the NASA Langley Unitary Plan Wind Tunnel at Mach numbers from 2.50 to 3.50 at a constant Reynolds number per foot of 2.00 x 10 to the 6th. Selected test results are presented to show the effects of a fixed or free-rolling tail-fin afterbody on the static longitudinal and lateral-directional aerodynamic characteristics of a canard-controlled missile with pitch, yaw, and roll control at model roll angles of 0 deg and 45 deg.

  4. Modeling and Simulation of Control Actuation System with Fuzzy-PID Logic Controlled Brushless Motor Drives for Missiles Glider Applications.

    Science.gov (United States)

    Muniraj, Murali; Arulmozhiyal, Ramaswamy

    2015-01-01

    A control actuation system has been used extensively in automotive, aerospace, and defense applications. The major challenges in modeling control actuation system are rise time, maximum peak to peak overshoot, and response to nonlinear system with percentage error. This paper addresses the challenges in modeling and real time implementation of control actuation system for missiles glider applications. As an alternative fuzzy-PID controller is proposed in BLDC motor drive followed by linkage mechanism to actuate fins in missiles and gliders. The proposed system will realize better rise time and less overshoot while operating in extreme nonlinear dynamic system conditions. A mathematical model of BLDC motor is derived in state space form. The complete control actuation system is modeled in MATLAB/Simulink environment and verified by performing simulation studies. A real time prototype of the control actuation is developed with dSPACE-1104 hardware controller and a detailed analysis is carried out to confirm the viability of the proposed system.

  5. Peeling the onion: an heuristic overview of hit-to-kill missile defense in the 21st century

    Science.gov (United States)

    LaCroix, Len; Kurzius, Shelby

    2005-03-01

    Researchers engaged in the development of infrared detector technologies may well benefit from a broader understanding of their products from the perspective of the end-user. An appreciation of how this technology is to be used by system designers, many of whom possess only a rudimentary understanding of quantum physics, is highly germane. Answers to questions like: "What device technology will be employed," "How will the device be used?" and "What are the impacts on signal-to-noise?" are of critical importance. In this paper, some of the fundamentals of hit-to-kill missile defense technology are examined in a largely non-mathematical context. From its "Star Wars" inception during the Reagan administration, to today"s Missile Defense Agency, the core requirement of missile defense has not changed - find the threat and destroy it before it reaches its destination. This fundamental requirement, while conceptually straightforward, is extraordinarily difficult to satisfy, and is almost exclusively dependent on our ability to detect and designate a relatively small, very fast-moving, room-temperature object, at great distances, and usually in a severe environment of shock and vibration further clouded by error and uncertainty. With an obvious bias toward passive IR detection and associated focal plane array characteristics, the flight of a fictitious interceptor is followed from launch to impact. At various points along the interceptor"s trajectory, a "peel the onion" approach is utilized to expose increasingly detailed layers of behavior, including the eventual release of the kinetic kill vehicle, and its autonomous flight to a body-to-body impact with its target. Various sources of error and their impact on the success of the mission are examined, and an overall understanding of the key features of the infrared seeker and its critical role in missile defense are ultimately developed.

  6. Preliminary Airworthiness Evaluation of the AH-1S (Modernized Cobra) with the HELLFIRE, TOW, and Stinger Missiles Installed

    Science.gov (United States)

    1984-10-01

    Evaluation (PAE) was to obtain limited handling qualities and performance data on the AH-IS(MC) with an in-house developed integrated HELLFIRE, TOW, and... integration of the HELLFIRE, TOW and Stinger missile systems for weapons firing. The three evaluations resulted in a logical progression of flight...testing in a cost effective manner. If at any timc the results of an evaluacion were unacceptable, the program could hive been stopped with minimum cost

  7. Navy Columbia Class (Ohio Replacement) Ballistic Missile Submarine (SSBN[X]) Program: Background and Issues for Congress

    Science.gov (United States)

    2016-10-03

    Navy Columbia Class (Ohio Replacement) Ballistic Missile Submarine (SSBN[X]) Program : Background and Issues for Congress Ronald O’Rourke...Specialist in Naval Affairs October 3, 2016 Congressional Research Service 7-5700 www.crs.gov R41129 Navy Columbia Class (Ohio Replacement) Program ...1,091.1 million in research and development funding for the Columbia class program , previously known as the Ohio replacement program (ORP) or SSBN(X

  8. Qualitative comparison of concurrent vertical optical turbulence profiles from an aircraft and balloons over White Sands Missile Range

    Science.gov (United States)

    Nowlin, Scott R.; Hahn, Ila L.; Hugo, Ronald J.; Bishop, Kenneth P.

    1999-08-01

    We report simultaneous balloon-borne thermosonde/airborne constant-current anemometer measurements made over a portion of White Sands Missile Range, NM. For the first time, vertical profiles of the refractive index structure parameter (Cn2) data generated from shallow slant aircraft flight paths are compared to the balloons vertical Cn2 distributions. We discuss possible adverse effects of meteorology and atmospheric velocity fluctuations. We present conclusions and make recommendations for future similar experimental efforts.

  9. The Impact of Czech Domestic Politics on Missile Defense Agreements Between the United States and the Czech Republic

    Science.gov (United States)

    2009-04-01

    EU membership, although the outspoken leader of the OSD, Vaclav Klaus was loudly critical of many aspects of the EU.23 The Czech leadership after...the parliamentarians required three elections43 and three rounds of balloting before the compromise appointment of ODS founder Vaclav Klaus as...defense6 and in June 2000 suggested to Czech President Vaclav Havel that the Czech Republic offer to host a US missile defense radar.7 Most

  10. The Politics of NATO Short-Range Nuclear Modernization 1983-1990: The Follow-On-to-Lance Missile Decisions

    Science.gov (United States)

    1991-06-01

    missiles stationed in Europe that relied on reduced blast and enhanced neutron flux (short duration radiation) for its killing effect.10 3 Branded the...Atlanticists, primarily CDU moderates including Helmut Kohl, Manfred Worner, and Volker Ruhe, who view the bipolar world as a given, generally support...that singularization was a myth: all West European states faced the same threat of Soviet nuclear attack.7" Volker Ruihe publicly responded to this

  11. Missile injuries in head — neck and maxillo-facial region — an experience in eastern nepal

    OpenAIRE

    2008-01-01

    Ballistic injuries to head-neck and maxillofacial region is quite common problem nowadays. Most of the time the injuries seem to be dreadful but the mechanism of the injuries caused by ballistics and the anatomical conditions of maxillofacial and head-neck region mitigate the severity of the injuries. Proper primary management followed by reconstruction and management of associated injuries decreases the mortality and morbidity of missile injuries in head-neck and maxillofacial region. Eleven...

  12. A Study on: Exploring U.S. Missile Defense Requirements in 2010: What Are the Policy and Technology Challenges?

    Science.gov (United States)

    1997-04-01

    military offi- cers, law enforcement personnel, and organized crime groups are willing to engage in illegal activ- ities for a price. This willingness...Interview with Gennady G. Yanpolsky, "A New Era for Russian Defense Export," Military Technology, December 1995, p. 33. Vago Muradian, "Russia Wants...34 that have hindered ballistic missile devel- opment in the past. For example, rocket- society papers on staging problems, discussions on guid- ance

  13. 导弹退化故障预测方法研究%A Method for Missile Degradation Fault Prediction

    Institute of Scientific and Technical Information of China (English)

    丛林虎; 徐廷学; 杨继坤; 董琪

    2014-01-01

    对导弹退化故障预测方法进行了研究,对测试数据进行统计推断,确定了测试数据的分布规律,并针对导弹测试数据分布参数存在小样本、非线性等特点,应用最小二乘支持向量机预测算法对测试数据的分布参数进行预测,确定了测试数据未来某一时刻的分布函数,进而建立了导弹退化故障预测模型,得出了导弹未来一段时间内的退化故障概率。通过实例分析,验证了退化故障预测模型的合理性。%The method for missile degradation fault prediction is studied .The distribution regularity of test data is obtained by statistical inference .Considering that the distribution parameters of missile test data have the features of small sample and nonlinearity,the prediction algorithm of least square support vector machine is used to predict the distribution parameters of test data in order to get the future distribution function . Further more,the degradation fault prediction model of missile is established to get the future degradation fault probability of missile .The results of example analysis validate the rationality of degradation fault prediction model.

  14. Industrial-hygiene-survey report of Martin Marietta Missile and Electronics Group, Orlando, Florida, April 25-27, 1988

    Energy Technology Data Exchange (ETDEWEB)

    Piacitelli, G.; Votaw, D.M.; Krishnan, E.R.

    1988-09-09

    A walk-through survey was made of the Martin Marietta Missile and Electronics Group, Orlando, Florida to evaluate worker exposure, protective equipment, and engineering controls used to reduce employee exposures to 2-methoxyethanol (2-ME), 2-methoxyethyl acetate (2-MEA), 2-ethoxyethanol (2-EE), and 2-ethoxyethyl-acetate (2-EEA). The facility was involved in the design, development, and production of missile and electro-optical systems used for aircraft and naval combat weapons programs. Of 38 field samples collected for each of the four target ethylene glycol ethers, only nine samples indicated the presence of any of the compounds and one sample indicated more than one to be present. Some skin protection was afforded by gloves, but the workers wore only ordinary street clothes and no respirators. Peak exposures to 2-EEA in the Hellfire area occurred during the spray painting of missiles. The authors recommend that local exhaust ventilation be installed at work stations in the Patriot area and that impermeable coveralls be given to workers in the Hellfire and Patriot areas.

  15. Extended nonlinear chirp scaling algorithm for highly squinted missile-borne synthetic aperture radar with diving acceleration

    Science.gov (United States)

    Liu, Rengli; Wang, Yanfei

    2016-04-01

    An extended nonlinear chirp scaling (NLCS) algorithm is proposed to process data of highly squinted, high-resolution, missile-borne synthetic aperture radar (SAR) diving with a constant acceleration. Due to the complex diving movement, the traditional signal model and focusing algorithm are no longer suited for missile-borne SAR signal processing. Therefore, an accurate range equation is presented, named as the equivalent hyperbolic range model (EHRM), which is more accurate and concise compared with the conventional fourth-order polynomial range equation. Based on the EHRM, a two-dimensional point target reference spectrum is derived, and an extended NLCS algorithm for missile-borne SAR image formation is developed. In the algorithm, a linear range walk correction is used to significantly remove the range-azimuth cross coupling, and an azimuth NLCS processing is adopted to solve the azimuth space variant focusing problem. Moreover, the operations of the proposed algorithm are carried out without any interpolation, thus having small computational loads. Finally, the simulation results and real-data processing results validate the proposed focusing algorithm.

  16. Robust sliding mode control with ESO for dual-control missile

    Institute of Scientific and Technical Information of China (English)

    Wei Shang; Shengjing Tang; Jie Guo; Yueyue Ma; Yuhang Yun

    2016-01-01

    This paper proposes a novel composite dual-control by combing the integral sliding mode control (ISMC) method based on the finite time convergence theory with extended state observer (ESO) for a tracking problem of a missile with tail fins and reaction-jet control system (RCS). First, the ISMC method based on finite time convergence is utilized to design the control law of tail fins and the pulse control of RCS for the dual-control system, ensuring the system with rapid response and high accuracy of tracking. Then, ESO is employed for the estimation of aerodynamic disturbances influenced by the airflow of thruster jets. With the characteristic of high accuracy estimation of ESO, the chattering free tracking performance of the attack angle command and the robustness of the control law are achieved. Meanwhile, the stability of the dual-control system is analyzed based on finite time convergence stability theorem and Lyapunov’s theorem. Final y, numerical sim-ulations demonstrate the effectiveness of the proposed design.

  17. Fast pattern recognizer for autonomous target recognition and tracking for advanced naval attack missiles

    Science.gov (United States)

    Hastbacka, Al

    2001-10-01

    A FPR System under development for the Naval Air Warfare Center, China Lake, CA is funded under a SBIR, Phase II contract as an automatic target recognizer and tracker candidate for Navy fast-reaction, subsonic and supersonic, stand-off weapons. The FPR will autonomously detect, identify, correlate, and track complex surface ship and land based targets in hostile, high-clutter environments in real time. The novel FPR system is proven technology that uses an electronic implementation analogous to an optical correlator system, where the Fourier transform of the incoming image is compared against known target images stored as matched filter templates. FPR demonstrations show that unambiguous target identification is achievable in a ninety-five percent fog obscuration for over ninety-percent of target images tested. The FPR technology employs an acoustic dispersive delay line (DDL) to achieve ultra-fast image correlations in 90 microseconds or 11,000 correlations per second. The massively scalable FPR design is capable of achieving processing speeds of an order of magnitude faster using available ASIC technology. Key benefits of the FPR are dramatically reduced power, size, weight, and cost with increased durability, robustness, and performance - which makes the FPR ideal for onboard missile applications.

  18. Strategic culture and ballistic missile defense: Russia and the United States. Master's thesis

    Energy Technology Data Exchange (ETDEWEB)

    Becker, M.D.

    1993-06-01

    This thesis examines U.S. and Russian history and current policy debates to advance understanding of: (1) the strategic cultures of these nations, particularly with respect to BMD policies in the recent past; and (2) whether and how their strategic cultures and approaches to BMD are changing and how that may affect future strategic BMD developments and the status of the ABM Treaty. The development of BMD strategies, including policies concerning the ABM Treaty, within the framework of the established American and Russian strategic cultures is studied, with due attention to the Soviet experience and legacy in the Russian case. U.S. strategic culture does not seem to have changed significantly with the end of the Cold War, but U.S. BMD priorities have been redefined to reflect a higher priority attached to regional and theater-level defenses. It is apparent that the Soviet experience did have a significant impact on Russian strategic culture. Faced with major changes in its international status, domestic political-military arrangements, and scope of national security concerns, Russian strategic culture is nonetheless moving beyond the old Soviet culture. Future Russian policies regarding the transfer of BMD technology, sharing early warning data, and participating in a global protective system are heavily dependent on domestic political developments. United States, Russia, USSR, Strategic culture, Ballistic missile defense, National strategy, Nuclear strategy, Strategic defense, ABM Treaty, Arms control, Strategic stability.

  19. Roll-pitch-yaw autopilot design for nonlinear time-varying missile using partial state observer based global fast terminal sliding mode control

    Institute of Scientific and Technical Information of China (English)

    Ahmed Awad; Wang Haoping

    2016-01-01

    The acceleration autopilot design for skid-to-turn (STT) missile faces a great challenge owing to coupling effect among planes, variation of missile velocity and its parameters, inexistence of a complete state vector, and nonlinear aerodynamics. Moreover, the autopilot should be designed for the entire flight envelope where fast variations exist. In this paper, a design of inte-grated roll-pitch-yaw autopilot based on global fast terminal sliding mode control (GFTSMC) with a partial state nonlinear observer (PSNLO) for STT nonlinear time-varying missile model, is employed to address these issues. GFTSMC with a novel sliding surface is proposed to nullify the integral error and the singularity problem without application of the sign function. The pro-posed autopilot consisting of two-loop structure, controls STT maneuver and stabilizes the rolling with a PSNLO in order to estimate the immeasurable states as an output while its inputs are missile measurable states and control signals. The missile model considers the velocity variation, gravity effect and parameters’ variation. Furthermore, the environmental conditions’ dynamics are mod-eled. PSNLO stability and the closed loop system stability are studied. Finally, numerical simula-tion is established to evaluate the proposed autopilot performance and to compare it with existing approaches in the literature.

  20. Present Development Status of Foreign Small Multi-Purpose Missile%国外小型多用途导弹发展现状

    Institute of Scientific and Technical Information of China (English)

    宋怡然; 蒋琪; 关世义

    2012-01-01

    On the basis of summarizing the characteristics of small multi-purpose missile,the six kinds of foreign small multi-purpose missile which are being developed or put into operations have been introduced,and the development present situation of small multi-purpose missile have been analyzed.Some proposals for the classification of small multi-purpose missile are provided.Based on analysis of the roles of small multi-purpose missile in recent and future non-traditional warfare,some development suggestions are put forward.%在总结小型多用途导弹特点的基础上,介绍了国外小型多用途导弹六个主要项目和型号的基本情况,同时分析了国外小型多用途导弹的发展现状,给出了小型多用途导弹分类建议。通过对小型多用途导弹在当前和未来非传统作战中作用的分析,提出了小型多用途导弹的后续发展建议。

  1. Roll-pitch-yaw autopilot design for nonlinear time-varying missile using partial state observer based global fast terminal sliding mode control

    Directory of Open Access Journals (Sweden)

    Awad Ahmed

    2016-10-01

    Full Text Available The acceleration autopilot design for skid-to-turn (STT missile faces a great challenge owing to coupling effect among planes, variation of missile velocity and its parameters, inexistence of a complete state vector, and nonlinear aerodynamics. Moreover, the autopilot should be designed for the entire flight envelope where fast variations exist. In this paper, a design of integrated roll-pitch-yaw autopilot based on global fast terminal sliding mode control (GFTSMC with a partial state nonlinear observer (PSNLO for STT nonlinear time-varying missile model, is employed to address these issues. GFTSMC with a novel sliding surface is proposed to nullify the integral error and the singularity problem without application of the sign function. The proposed autopilot consisting of two-loop structure, controls STT maneuver and stabilizes the rolling with a PSNLO in order to estimate the immeasurable states as an output while its inputs are missile measurable states and control signals. The missile model considers the velocity variation, gravity effect and parameters’ variation. Furthermore, the environmental conditions’ dynamics are modeled. PSNLO stability and the closed loop system stability are studied. Finally, numerical simulation is established to evaluate the proposed autopilot performance and to compare it with existing approaches in the literature.

  2. Chaff Centroid Jamming and Ship to Air Missile Anti-missile Cooperation Conflict Prediction%箔条质心干扰与舰空弹反导冲突预测问题研究

    Institute of Scientific and Technical Information of China (English)

    孙翼; 韩龙

    2015-01-01

    现代海战中箔条弹与舰空导弹综合使用中存在的电磁干扰冲突严重制约了舰艇的防空反导能力。论文重点针对电磁干扰冲突问题,提出了冲突预测判断原则,构建了冲突预测理论模型,并基于模型采取遍历运算方法对箔条质心干扰与舰空导弹冲突预测进行模拟仿真,对冲突判断模型进行了验证,其结果与实际相吻合。论文的研究可为提升箔条弹与舰空导弹协同作战效能,提高防空反导能力提供重要思路。%In the modern sea warfare ,the electromagnetic conflicts of using the Centroid Jamming and Ship to Air Missile se‐verely restricted the ability of air defence and antimissile .This paper forcused on the electromagnetic interference conflict question , proposed conflict prediction judgment principle ,constructed the conflict prediction model .And based on the model ,this paper used the traversal algorithm to simulate conflict prediction of the chaff centroid jamming and ship to air missile .The results were consist‐ent with the actual situation .The research could enhance the cooperative operation effectiveness of the chaff centroid jamming and ship to air missile ,and improve the ability of air defence and antimissile ,and provide an important idea .

  3. Improvement of Intercept Probability Algorithm for Anti-ship Missile Based on Search Theory%Improvement of Intercept Probability Algorithm for Anti-ship Missile Based on Search Theory

    Institute of Scientific and Technical Information of China (English)

    汪新刚; 谢晓方; 李雪

    2011-01-01

    Traditional intercept probability model has some drawbacks and can not meet the demands of command and control system. Aiming at this problem, a new calculation method based on search theory, terminal control area distribution function of antl-ship missile, target distribution function and missile's radar scan feature is proposed, Under the condition of common target distribution, an intercept probability model for present point attacking is determined. The simulation verifies its effectiveness and establishes the selecting model for aiming point when enemy ships evade in high speed.

  4. The reaction jet technology of air-to-air missiles%空空导弹直接力控制技术

    Institute of Scientific and Technical Information of China (English)

    高建军

    2011-01-01

    为了实现空空导弹大机动飞行,采用直接力控制技术。本文介绍了直接力控制技术在多种拦截弹上的使用情况,并分析了其各种关键技术,以利于将来大机动空空导弹的设计工作。%For the high maneuverability flight of air-to-air missiles, the reaction jet technology is used. In order to design the new air-to-air missiles of high maneuverability, it is introduced in this paper how the reaction jet technology is used in many missiles, and many key technologies about the reaction jet are analyzed in it.

  5. Some Considerations about the RIERA Approach and Missile-Structure Interaction Analysis Method in Aircraft Impact Assessment on Nuclear Power Plants

    Energy Technology Data Exchange (ETDEWEB)

    Jin, Byeong Moo; Kim, Young Jin [Daewoo E and C Co. Ltd., Suwon (Korea, Republic of); Jeon, Se Jin [Ajou Univ., Suwon (Korea, Republic of)

    2014-05-15

    In this paper, the classically preferred RIERA approach and the so-called missile-structure interaction (MSI) analysis methods which are indebted by the latest computing power are discussed about their inherent discrepancies. Studies on the safety assessments on the nuclear power plants against large civil aircraft crashes are ongoing actively. In this paper, the classically preferred RIERA approach and the so-called missile-structure interaction (MSI) analysis methods are discussed about their inherent discrepancies especially from the point of view energy balances. More advanced and simplified ways in the safety assessment of nuclear power plants against large civil aircrafts may be possible by understanding the inherent discrepancies of the RIERA approach method and the missile-structure interaction method and reducing the differences of structural responses.

  6. A COUPLING MODEL OF WATER FLOWS AND GAS FLOWS IN EXHAUSTED GAS BUBBLE ON MISSILE LAUNCHED UNDERWATER

    Institute of Scientific and Technical Information of China (English)

    2007-01-01

    The gas and water flows during an underwater missile launch are numerically studied. For the gas flow, the explicit difference scheme of Non-oscillation and Non-free-parameter Dissipation (NND) is utilized to solve the Euler equations for compressible fluids in the body-fitted coordinates. For the water flow, the Hess-Smith method is employed to solve the Laplace equation for the velocity potential of irrotational water flows based on the potential theory and the boundary element method. The hybrid Eulerian-Lagrangian formulation for the free boundary conditions is used to compute the changes of the free surface of the exhausted gas bubble in time stepping. On the free surface of the exhausted gas bubble, the matched conditions of both the normal velocities and pressures are satisfied. From the numerical simulation, it is found that the exhausted gas bubble grows more rapidly in the axial direction than in the radial direction and the bubble will shrink at its "neck" finally. Numerical results of the movement of the shock wave and the distribution of the Mach number and the gas pressure within the bubble were presented, which reveals that at some time, the gas flow in the Laval nozzle is subsonic and the gas pressure in the nozzle is very high. Influences of various initial missile velocities and chamber total pressures and water depths on both the time interval when the gas flow in the nozzle is subsonic and the peak of the gas pressure at the nozzle end were discussed. It was suggested that a reasonable adjustment of the chamber total pressure can improve the performance of the engine during the underwater launch of missiles.

  7. An ultrastructural study on indirect injury of dental pulp caused by high-speed missile projectile to mandible in dogs.

    Science.gov (United States)

    Ren, Changqun; Liu, Ruifeng; Tian, Lei; Chen, Peng; Zhou, Shuxia

    2008-12-01

    The aim of this study was to evaluate the characteristics of indirect injury of dental pulp caused by high-speed missile projectile to mandible in dogs. Eighteen dogs aged 12-13 months were divided equally into six groups (n = 3 in each group) with random allocation, then a high-speed missile projectile (a ball bearing of stainless steel, phi6.0 mm, 0.88 g) was shot at right mandible body (the wound tract was below the fourth premolar, 1 cm or so to the root tips) of each dog, but the teeth were not wounded directly. The dogs were killed 6 h (n = 3), 24 h (n = 3), 3 days (n = 3), 7 days (n = 3), 2 weeks (n = 3) and 4 weeks (n = 3) after the wound, respectively; then ultrastructural change of dental pulp of the fourth premolar and the second premolar of right mandible, and the second premolar of left mandible was observed through transmission electron microscope. The results showed that mean initial velocity of projectiles was 778.0 +/- 33.2 m s(-1) and mean projection energy was 266.1 +/- 19.1 J, which were in conformity with parameters of gunshot wound. On the wound side, dental pulp of the fourth mandibular premolar was injured seriously and irreversible necrosis happened in the end; yet, dental pulp of the second mandibular premolar was injured less seriously, reversibly; on the opposite side, dental pulp of the second mandibular premolar was injured slightly and temporarily. It may be concluded that there are several characteristics in indirect injury of dental pulp caused by high-speed missile projectile to dogs' mandible: the injured area is relatively extensive; traumatic degree decreases progressively and sharply with the distance to the wound tract increasing; ultrastructural change of nerval damage takes place in early stage after wound, etc.

  8. Research on Missile Separation Design Techniques%导弹分离设计技术研究

    Institute of Scientific and Technical Information of China (English)

    郭凤美; 余梦伦

    2014-01-01

    Separation system is an important subsystem of the missile. Its design is one of the keys of the missile system design and also a key process which affects the success of the missile flight. From the view of engineering practice, the design principles, design methods and test methods of separation system is researched and summarized. With respect to stage separation design technique, the requirements of coordination, environmental compatibility for separation system design and a method for separation sequence optimal design are proposed. Also some issues about separation system design which should be paid attention to are pointed out, providing some reference to the engineering design of separation system.%分离系统是导弹的一个重要分系统,分离系统设计是导弹总体设计的关键之一,也是影响导弹飞行成败的关键环节。从工程实际的角度,对分离系统设计原则、设计方法和试验方法等进行研究总结,围绕级间分离设计技术,提出分离系统设计协调性、环境适应性等要求和分离时序优化设计方法,并指出分离系统设计需关注的几个问题,对分离系统工程设计具有一定的参考意义。

  9. Anukalpana 2.0: A Performance Evaluation Software Package for Akash Surface to Air Missile System

    Directory of Open Access Journals (Sweden)

    G.S. Raju

    1997-07-01

    Full Text Available Abstract : "An air defence system is a complex dynamic system comprising sensors, control centres, launchers and missiles. Practical evaluation of such a complex system is almost impossible and very expensive. Further, during development of the system, there is a necessity to evaluate certain design characteristics before it is implemented. Consequently, need arises for a comprehensive simulation package which will simulate various subsystems of the air defence weapon system, so that performance of the system can be evaluated. With the above objectives in mind, a software package, called Anukalpana 2.0, has been developed. The first version of the package was developed at the Indian Institute of Science, Bangalore. This program has been subsequently updated. The main objectives of this package are: (i evaluation of the performance of Akash air defence system and other similar air defence systems against any specified aerial threat, (ii investigation of effectiveness of the deployment tactics and operational logic employed at the firing batteries and refining them, (iii provision of aid for refining standard operating procedures (SOPs for the multitarget defence, and (iv exploring the possibility of using it as a user training tool at the level of Air Defence Commanders. The design specification and the simulation/modelling philosophy adopted for the development of this package are discussed at length. Since Akash air defence system has many probabilistic events, Monte Carlo method of simulation is used for both threat and defence. Implementation details of the package are discussed in brief. These include: data flow diagrams and interface details. Analysis of results for certain input cases is also covered."

  10. Simulation of Thin Film Thermocouple for High Temperature Measurement Applicable to Missiles

    Directory of Open Access Journals (Sweden)

    Manoj Kumar Sonker

    2015-09-01

    Full Text Available Thermocouples have been extensively used for the measurement of temperature since the advent of seebeck effect. Numerous sensors have been developed for temperature measurement, yet measurement of high temperature flowing fluid has been a challenging task. For the measurement of static temperature the measuring device should travel with the fluid at the same speed without disturbing the flow, which is quite unrealistic. So indirect determination of static temperature of flowing fluid is done by using thermocouple exposed into the flowing fluid. Other sensors available for high temperature measurement may lead to problems like resistance in the flow path of fluid which changes the structural dynamics. Thin film thermocouple (TFTC based on W-W26Re for super high temperature measurement has been investigated which can be used in missiles for surface temperature measurement of nozzle and rocket interior surface. TFTC does not cause disruption in the flow path with maintaining structural integrity. The W-W26Re thermocouple offers advantage of higher seebeck coefficient at high temperature i.e. above 750 K, and usability in vacuum, inert and hydrogen atmosphere. Zirconia Fiber has been proposed as insulation protection material over thermocouple. Modelling and simulation of the TFTC for the temperature range 300 K - 2900 K has been presented. FEA model using PDE has been presented to implement heat equation, current balance  quation, Gauss theorem and Neumann boundary condition. The expected voltage production on exposed temperature gradient has been studied.

  11. 临近空间高超声速导弹红外特性研究%Study on infrared radiation feature of near space hypersonic missile

    Institute of Scientific and Technical Information of China (English)

    张海林; 周林; 左文博; 范奇; 谭西江

    2015-01-01

    研究临近空间高超声速导弹的红外辐射特性,对于反临近空间武器系统侦察监视临近空间目标具有重要意义。通过对临近空间高超声速导弹 X-51 A 试验飞行过程的研究,深入分析了高超声速导弹的红外辐射特征,并建立其红外辐射模型。以导弹蒙皮、发动机及尾喷焰作为高超声速导弹的主要红外辐射源,以 X-51 A 试验飞行器为参考,计算临近空间高超声速导弹在3~5μm 和8~14μm 波段在不同方向上的红外辐射强度,并针对计算结果进行了分析。%It is important for defending near space weapons and detecting near space targets to study the infrared radia-tion characteristics of near space hypersonic missiles.By studying the near space hypersonic missile X -51 A′s flight test,the infrared radiation characteristics of hypersonic missiles are analyzed,and its infrared radiation model is estab-lished.The missile skin,engine and tail flame are reguarded as the primary infrared radiation sources of hypersonic missile.Taking X -51 A test vehicle as a reference,the infrared radiation strength of near space hypersonic missiles is calculated at different directions in 3 ~5 μm and 8 ~1 4 μm waveband,and the calculation results are discussed.

  12. Stability and Control of Tactical Missile Systems Held in Ankara (Turkey) on 9-12 May 1988

    Science.gov (United States)

    1989-03-01

    Ankara. Turkey and for the facilities and personnel which made this meeting possible. Le Panel du Mecanique du Vol tient ii remercier les D6legucs...missile peut 6tre fournie soit par des outils de CAO, soit par des formulations analytiques . L~e premier exemple do calcul pr6sentA eat relatif i une...pr~sence doUne mecttudo cone qni rend le ilisposit i d’.tcti vation iso~lastique et qoi supprime la resonance mecanique do basculemeot. Coin

  13. A new method of passive counting of nuclear missile warheads -a white paper for the Defense Threat Reduction Agency

    Energy Technology Data Exchange (ETDEWEB)

    Morris, Christopher [Los Alamos National Lab. (LANL), Los Alamos, NM (United States); Durham, J. Matthew [Los Alamos National Lab. (LANL), Los Alamos, NM (United States); Guardincerri, Elena [Los Alamos National Lab. (LANL), Los Alamos, NM (United States); Bacon, Jeffrey Darnell [Los Alamos National Lab. (LANL), Los Alamos, NM (United States); Wang, Zhehui [Los Alamos National Lab. (LANL), Los Alamos, NM (United States); Fellows, Shelby [Los Alamos National Lab. (LANL), Los Alamos, NM (United States); Poulson, Daniel Cris [Los Alamos National Lab. (LANL), Los Alamos, NM (United States); Plaud-Ramos, Kenie Omar [Los Alamos National Lab. (LANL), Los Alamos, NM (United States); Daughton, Tess Marie [Los Alamos National Lab. (LANL), Los Alamos, NM (United States); Johnson, Olivia Ruth [Los Alamos National Lab. (LANL), Los Alamos, NM (United States)

    2015-07-31

    Cosmic ray muon imaging has been studied for the past several years as a possible technique for nuclear warhead inspection and verification as part of the New Strategic Arms Reduction Treaty between the United States and the Russian Federation. The Los Alamos team has studied two different muon imaging methods for this application, using detectors on two sides and one side of the object of interest. In this report we present results obtained on single sided imaging of configurations aimed at demonstrating the potential of this technique for counting nuclear warheads in place with detectors above the closed hatch of a ballistic missile submarine.

  14. 弹箭用先进复合材料研究进展%Research Progress of Advanced Composite in Rocket and Missile

    Institute of Scientific and Technical Information of China (English)

    马开宝; 高守臻; 李大勇; 辛全友; 罗长宏; 王晓立; 庞旭堂

    2012-01-01

    介绍了弹箭用先进复合材料的分类,分析了各类不同的轻质复合材料和热防护复合材料的应用现状及种类,结合弹箭武器应用阐明了先进复合材料的发展趋势.%Classifications of advanced composites in rocket and missile were described. The varieties of different lightweight composites and thermal insulating composites and their current situation of research and application were analyzed completely. Development trends of advanced composites in rocket and missile were introduced finally.

  15. Modeling and Simulation of Control Actuation System with Fuzzy-PID Logic Controlled Brushless Motor Drives for Missiles Glider Applications

    Science.gov (United States)

    Muniraj, Murali; Arulmozhiyal, Ramaswamy

    2015-01-01

    A control actuation system has been used extensively in automotive, aerospace, and defense applications. The major challenges in modeling control actuation system are rise time, maximum peak to peak overshoot, and response to nonlinear system with percentage error. This paper addresses the challenges in modeling and real time implementation of control actuation system for missiles glider applications. As an alternative fuzzy-PID controller is proposed in BLDC motor drive followed by linkage mechanism to actuate fins in missiles and gliders. The proposed system will realize better rise time and less overshoot while operating in extreme nonlinear dynamic system conditions. A mathematical model of BLDC motor is derived in state space form. The complete control actuation system is modeled in MATLAB/Simulink environment and verified by performing simulation studies. A real time prototype of the control actuation is developed with dSPACE-1104 hardware controller and a detailed analysis is carried out to confirm the viability of the proposed system. PMID:26613102

  16. Impact angle constrained three-dimensional integrated guidance and control for STT missile in the presence of input saturation.

    Science.gov (United States)

    Wang, Sen; Wang, Weihong; Xiong, Shaofeng

    2016-09-01

    Considering a class of skid-to-turn (STT) missile with fixed target and constrained terminal impact angles, a novel three-dimensional (3D) integrated guidance and control (IGC) scheme is proposed in this paper. Based on coriolis theorem, the fully nonlinear IGC model without the assumption that the missile flies heading to the target at initial time is established in the three-dimensional space. For this strict-feedback form of multi-variable system, dynamic surface control algorithm is implemented combining with extended observer (ESO) to complete the preliminary design. Then, in order to deal with the problems of the input constraints, a hyperbolic tangent function is introduced to approximate the saturation function and auxiliary system including a Nussbaum function established to compensate for the approximation error. The stability of the closed-loop system is proven based on Lyapunov theory. Numerical simulations results show that the proposed integrated guidance and control algorithm can ensure the accuracy of target interception with initial alignment angle deviation and the input saturation is suppressed with smooth deflection curves. Copyright © 2016 ISA. Published by Elsevier Ltd. All rights reserved.

  17. Modeling and Simulation of Control Actuation System with Fuzzy-PID Logic Controlled Brushless Motor Drives for Missiles Glider Applications

    Directory of Open Access Journals (Sweden)

    Murali Muniraj

    2015-01-01

    Full Text Available A control actuation system has been used extensively in automotive, aerospace, and defense applications. The major challenges in modeling control actuation system are rise time, maximum peak to peak overshoot, and response to nonlinear system with percentage error. This paper addresses the challenges in modeling and real time implementation of control actuation system for missiles glider applications. As an alternative fuzzy-PID controller is proposed in BLDC motor drive followed by linkage mechanism to actuate fins in missiles and gliders. The proposed system will realize better rise time and less overshoot while operating in extreme nonlinear dynamic system conditions. A mathematical model of BLDC motor is derived in state space form. The complete control actuation system is modeled in MATLAB/Simulink environment and verified by performing simulation studies. A real time prototype of the control actuation is developed with dSPACE-1104 hardware controller and a detailed analysis is carried out to confirm the viability of the proposed system.

  18. Research of Step-down Stress Accelerated Degradation Data Assessment Method of a Certain Type of Missile Tank

    Institute of Scientific and Technical Information of China (English)

    YAO Jun; XU Mingge; ZHONG Weiqiang

    2012-01-01

    The performance degradation rates of the missile tank are generally time-varying functions uneasily evaluated by general classical evaluation methods.This paper develops a segmented nonlinear accelerated degradation model (SNADM) based on the equivalent method of accumulative damage theory,which tackles the problem that product life is difficult to be determined with degradation rate being a function of the variable of time.A segmented expression of the function of population accumulative degradation is derived.And combined with nonlinear function,an accelerated degradation function,i.e.,SNADM is obtained.The parameters of the SNADM are identified by numerical iteration,and the statistical function of degradation track is extrapolated.The reliability function is determined through the type of random process of the degradation distribution.Then an evaluation of product storage life is undertaken by combining the statistical function of degradation track,reliability function and threshold.An example of a missile tank undergoes a step-down stress accelerated degradation test (SDSADT),in which the resuits with the SNADM and the classical method are evaluated and compared.The technology introduced is validated with the resultant coincidence of both evaluated and field storage lives.

  19. Numerical Investigation on Aerodynamic Characteristics of the Square Cross-section Missile Configuration%方形截面导弹气动特性数值研究∗

    Institute of Scientific and Technical Information of China (English)

    李剑; 李斌; 敬代勇

    2015-01-01

    文中为了研究方形截面导弹的气动特性,设计了舵面位于平面和舵面位于直角两种布局形式方形截面导弹,并通过CFD数值模拟方法分析比较了方形截面导弹和圆形截面导弹的气动特性。分析结果表明,方形截面导弹相比圆形截面导弹具有较大的法向力和横、侧向气动力,其中舵面位于平面布局与舵面位于直角布局的方形截面导弹相比较其横、侧向气动力要小一些。%In order to investigate aerodynamic characteristics of square cross-section missile, square cross-section missile with fin plane and, and then the aerodynamic characteristics of square and circular cross-section missile through CFD numerical simulation. The result in-dicates that the square cross-section missile can generate more normal force and lateral force and moment than the circular cross-section missile, and the square cross-section missile with fin plane can generate less lateral force and moment than the square cross-section missile with fin.

  20. Impact of coupling of lateral movement on missile stability margin%侧向运动耦合对导弹稳定裕度的影响

    Institute of Scientific and Technical Information of China (English)

    郭广明; 罗琴

    2013-01-01

    各通道间无耦合是工程上导弹控制系统设计的一个基本假设,但随着飞行速度及机动性的提高,导弹各通道间的气动与运动学耦合已不能忽略.以面对称导弹为研究对象,依据小扰动理论,通过建立偏航与滚转通道之间的耦合运动方程,定量分析了通道耦合对导弹控制系统稳定裕度的影响,所得结论可为面对称导弹的工程设计提供参考.%Abstract:No coupling between each channel is a basic assumption of the missile control system design on engineering,but with the flight speed and the mobility increased,aerodynamic and kinematic coupling between each channel of the missile can not be neglected.With plane symmetry missile as the research object,based on small perturbation theory and by establishing some coupled equations of motion between yaw and roll channels,this paper analyzes quantitatively the influence of channel coupling on stability margin.The conclusions can provide a reference for the engineering design of the plane symmetry missile.

  1. What to Do About That Pack of Wolves at the Door: A Binational Organization and Acquisitions Approach to Homeland Cruise Missile Defense

    Science.gov (United States)

    2016-04-04

    Russia’s desire for increased military power to counter US primacy. In order to codify the ways and means to this end, Russian President Vladimir Putin ...5 Russia ... Russia have enjoyed a largely uncontested duopoly on cruise missile employment, these increasingly accurate and lethal systems have proliferated widely

  2. Informationization Design of New Generation Antitank Missile Weapon%新一代反坦克导弹武器信息化设计

    Institute of Scientific and Technical Information of China (English)

    何亚娟; 孙亚平; 王小永; 王琨

    2012-01-01

    In order to improve the design level of anti-tank missile weapon in informationization warfare, a method of informative design of indirect aiming anti-tank missile weapon system is proposed. Based on the purpose and criterion of informative design, informative design flow of anti-tank missile weapon is presented. The design content of information system of anti-tank missile weapon is described in detail form 8 aspects. Simulation results show the advantage of this design method such as short design assessment cycle, clear and reasonable design flow, rapid reaction and strong resilience.%为了提高信息化战争中反坦克导弹武器系统的设计水平,提出了一种间瞄反坦克导弹武器系统信息化设计方法,以信息化设计的目的、设计准则为依据,给出了反坦克导弹武器系统信息化设计流程,从8个方面详细论述了反坦克导弹武器系统信息化设计的内容.仿真结果表明:该设计评估周期短,设计流程清晰、合理、反应迅速、抗毁性强.

  3. 印度导弹武器装备体系发展与前景分析%Analysis of Indian Missile Weapon System Development

    Institute of Scientific and Technical Information of China (English)

    张莹

    2012-01-01

    随着国际安全环境的重大变化,印度加紧了其军事战略的调整和军队建设的步伐,大力发展导弹武器体系建设,对周边国家和地区形成了安全威胁.在分析印度军事战略的基础上,重点阐述印度弹道导弹、巡航导弹、防空导弹和导弹防御系统等武器装备体系的建设情况,并分析了其发展趋势和未来前景.%With the tremendous changes of the international security environment, India promotes the military strategy adjustment and the military construction, and pays great attention to the development of missile weapon system, threatening to the security of neighboring countries and regions. Beginning with the Indian military strategy, this paper describes the Indian weapon system construction in depth, such as the ballistic missile, cruise missile, air defense system and ballistic missile defense system .ete. Finally future development trend and prospect are analyzed.

  4. Diode Pumped Alkaline Laser System: A High Powered, Low SWaP Directed Energy Option for Ballistic Missile Defense High-Level Summary - April 2017

    Energy Technology Data Exchange (ETDEWEB)

    Wisoff, P. J. [Lawrence Livermore National Lab. (LLNL), Livermore, CA (United States)

    2017-04-28

    The Diode-Pumped Alkali Laser (DPAL) system is an R&D effort funded by the Missile Defense Agency (MDA) underway at Lawrence Livermore National Laboratory (LLNL). MDA has described the characteristics needed for a Boost Phase directed energy (DE) weapon to work against ICBM-class threat missiles. In terms of the platform, the mission will require a high altitude Unmanned Aerial Vehicle (UAV) that can fly in the “quiet” stratosphere and display long endurance – i.e., days on station. In terms of the laser, MDA needs a high power, low size and weight laser that could be carried by such a platform and deliver lethal energy to an ICBM-class threat missile from hundreds of kilometers away. While both the military and industry are pursuing Directed Energy for tactical applications, MDA’s objectives pose a significantly greater challenge than other current efforts in terms of the power needed from the laser, the low size and weight required, and the range, speed, and size of the threat missiles. To that end, MDA is funding two R&D efforts to assess the feasibility of a high power (MWclass) and low SWaP (size, weight and power) laser: a fiber combining laser (FCL) project at MIT’s Lincoln Laboratory, and LLNL’s Diode-Pumped Alkali Laser (DPAL) system.

  5. A modified nasolabial flap for reconstruction of transfixing alar wing defects.

    Science.gov (United States)

    Bouhassira, J; Hersant, B; Noel, W; Aguilar, P; Niddam, J; Meningaud, J-P

    2017-08-22

    Reconstruction of an entire alar wing is a frequently encountered reconstructive challenge in onco-dermatologic surgery. The aim of this technical note was to describe a surgical technique total for reconstruction of the alar wing, with a modified nasolabial flap with an inferior pedicle associated with a cartilaginous graft. This rapid procedure seems to be a well alternative for elderly people and patients who do not want a forehead flap. The aesthetic and functional outcomes of the donor and recipient sites were satisfactory. Copyright © 2017 Elsevier Masson SAS. All rights reserved.

  6. 弹载飞行控制软件重用技术研究%Research on Software Reuse Technology of Missile Flight Control Sof tware

    Institute of Scientific and Technical Information of China (English)

    刘思思; 刘迪; 卢娥

    2015-01-01

    针对弹载飞行控制软件研制现状,探讨软件重用的目的、意义及技术途径;结合弹载飞行控制软件的组成和设计原则,分析可重用软件应满足的基本条件;提出一种基于领域工程的弹载飞行控制软件重用实施方法;从软件工程化要求、编码要求、软件测试要求和硬件设计要求等方面建立弹载飞行控制软件通用构件库的可重用构件选取标准。最后,用实例说明了弹载飞行控制软件重用的可操作性。%In view of the current status of Missile Flight Control Software ,this paper discusses the purpose and signifi‐cance of software reuse ,introduces the technical approaches of software reuse ;Combined with the composition and design principle of Missile Flight Control Software ,analysis of the basic conditions of software reuse should satisfy ;A kind of software reuse method through domain engineering on Missile Flight Control Software is proposed ;From these aspects , summed up criteria for the selection of Missile Flight Control Software of the general component library of reusable com‐ponents ,including requirements of software engineering ,the developer coding ,software testing and hardware designing . Finally ,an example is used to illustrate the operability of Missile Flight Control Software reuse .

  7. 弹道导弹威胁估计模型构建%Research on Model Building of Ballistic Missile Threat Assessment

    Institute of Scientific and Technical Information of China (English)

    朱艺; 肖兵; 林傲; 张锋; 王海燕

    2016-01-01

    简要分析了弹道导弹飞行3个阶段的不同特点及各阶段导弹预警探测手段的侧重点,结合威胁估计的特征构建了弹道导弹威胁估计模型结构框架,运用多阶段贝叶斯网络理论,构造了主动段、自由段和再入段威胁估计模型,并明确了三阶段间的转换时机。采用动态贝叶斯方法对弹道导弹作战全过程进行威胁估计仿真推理,仿真结果能够反映导弹在飞行过程中威胁程度的变化特点,为反导指挥员作出辅助决策提供智力支持。%This paper briefly introduces different features in three phases of ballistic missile and focuses in different detection methods of missile early warning according to the features of threat assessment ,It establishes the threat assessment model pattern of ballistic missile. Through applying multi-phase Bayesian theory ,it builds a assessment model which includes boost phase,free phase,and re-entry phase and clarifies proper transformation opportunity among three phases. Besides ,it reasons and simulates the whole battle process of ballistic missile so as to get threat assessment results which reveals the traits of missiles regarding to changes during the flight and to offer intelligent assistance working as auxiliary decisions to commanders.

  8. 高超声速巡航导弹攻防对抗仿真研究%Study about Hypersonic Cruise Missile Combat Engagement Simulation

    Institute of Scientific and Technical Information of China (English)

    郑祥品; 王志刚

    2012-01-01

    在当前复杂作战环境下,对导弹武器系统进行攻防对抗研究是非常有必要的.针对攻防对抗这一复杂的动态过程,建立了高超声速巡航导弹攻防对抗仿真模型.并在此模型中,分别给出了结果评判模型、作战环境模型和对抗仿真模型.并根据所建立的仿真模型,计算出高超声速巡航导弹的突防概率.仿真算例结果表明,减小高超声速巡航导弹的雷达反射截面积RCS和增大高超声速巡航导弹的巡航速度是提高其突防效能的重要手段.%During current complex combat conditions, investigation of combat engagement of a new technology missile weapon system is necessary. Aimed at the complex dynamic course of combat engagement, a framework for hypersonic cruise missile combat engagement simulation is established. The combat engagement models of offensive side and defensive side are established in this framework, as well as combat environment models and damage probability of the hypersonic cruise missile are computed. Finally, penetration effectiveness of the hypersonic cruise missile is given. The results show that reducing the RCS and increasing the cruise velocity of the hypersonic cruise missile are two important approaches to improve the penetration effectiveness.

  9. ROMANIA’S PARTICIPATION TO THE AEGIS BALLISTIC MISSILE DEFENSE SYSTEM AS REFLECTED BY ROMANIAN NEWSPAPERS’ EVALUATIVE DISCOURSE

    Directory of Open Access Journals (Sweden)

    Raluca Mihaela LEVONIAN

    2012-01-01

    Full Text Available This study aims to investigate Romanian media discourse on the current standing of the relations between Romania and the United States of America in the military fi eld. The main topic investigated is connected to Romania’s decision to host the land-based component of the Balllistic Missile Defense System on its ground, an event which attracted signifi cant media coverage during the year 2011. The corpus analyzed consisted of 37 news and opinion items and reports published on the site of three Romanian newspapers. The main research questions were to assess whether the evaluations of this event were positive or negative, who were the actors issuing these statements and what objects were discussed in association to this event. The results showed that positive evaluations were more common than negative evaluations and that the offi cial stances on this topic formed a very coherent perspective, endorsing the project.

  10. Demonstration of the Military Ecological Risk Assessment Framework (MERAF): Apache Longbow - Hell Missile Test at Yuma Proving Ground

    Energy Technology Data Exchange (ETDEWEB)

    Efroymson, R.A.

    2002-05-09

    This ecological risk assessment for a testing program at Yuma Proving Ground, Arizona, is a demonstration of the Military Ecological Risk Assessment Framework (MERAF; Suter et al. 2001). The demonstration is intended to illustrate how risk assessment guidance concerning-generic military training and testing activities and guidance concerning a specific type of activity (e.g., low-altitude aircraft overflights) may be implemented at a military installation. MERAF was developed with funding from the Strategic Research and Development Program (SERDP) of the Department of Defense. Novel aspects of MERAF include: (1) the assessment of risks from physical stressors using an ecological risk assessment framework, (2) the consideration of contingent or indirect effects of stressors (e.g., population-level effects that are derived from habitat or hydrological changes), (3) the integration of risks associated with different component activities or stressors, (4) the emphasis on quantitative risk estimates and estimates of uncertainty, and (5) the modularity of design, permitting components of the framework to be used in various military risk assessments that include similar activities. The particular subject of this report is the assessment of ecological risks associated with a testing program at Cibola Range of Yuma Proving Ground, Arizona. The program involves an Apache Longbow helicopter firing Hellfire missiles at moving targets, i.e., M60-A1 tanks. Thus, the three component activities of the Apache-Hellfire test were: (1) helicopter overflight, (2) missile firing, and (3) tracked vehicle movement. The demonstration was limited, to two ecological endpoint entities (i.e., potentially susceptible and valued populations or communities): woody desert wash communities and mule deer populations. The core assessment area is composed of about 126 km{sup 2} between the Chocolate and Middle Mountains. The core time of the program is a three-week period, including fourteen days of

  11. Brain injury after survived gunshot to the head: reactive alterations at sites remote from the missile track.

    Science.gov (United States)

    Oehmichen, M; Meissner, C; König, H G

    2001-01-15

    Gunshot wounds to the brain usually lead to acute respiratory arrest or death after a brief survival period, even in cases involving only slight direct tissue damage. It can be assumed therefore that the damage extends beyond the zone of recognizable destruction and hemorrhages. To determine the true extent of the tissue injury resulting from gunshot wounds to the brain, we carried out microscopic investigations for reactive changes (emigration of leukocytes and macrophages, axonal expression of beta-amyloid precursor protein (beta-APP) in 10 cases of gunshot wound to the narrow channel of the brain with survival times >2h. Demonstration of leukocytes expressing naphthol AS-D chloroacetate esterase activity in the brain tissue at the border of the missile track established the vitality of the gunshot effect. The presence of macrophages (CD68-epitope) allowed demarcation of a 1-2mm wide necrotic zone around the permanent cavity. Within this zone and beyond, beta-APP showed an initial increase followed by a decline in the number of injured axons. Three types of beta-APP positive staining could be differentiated. In the immediate vicinity of the missile track beta-APP positive neurons were present at a distance of 2-4mm from the margin of the permanent cavity (type 1) as a result of primary injured neuronal tissue by the gunshot itself. At longer distances from the narrow channel and the permanent cavity single beta-APP positive axons or axon fragments and two additional types were found; type 2 shows a parallel, wave-like arrangement of the damaged fibers, which suggests that the injury was produced by mechanical acceleration of the brain tissue created by the energy the projectile expended within the brain; irregular aggregation of beta-APP positive axons or axon fragments within a local edema represents type 3, which may be attributed to secondary ischemia or edema.

  12. Sheet thickness required for protection against the impact of a missile generated by a tornado; Espesor de chapa requerido para la proteccion contra el impacto de un misil generado por un tornado

    Energy Technology Data Exchange (ETDEWEB)

    Prats, F.; Fernandez, M. C.

    2010-07-01

    The tornado generated missiles are classified in three categories: piece of pipe, car and a solid sphere. These missiles can impact class structures outer areas of the plant, possibly causing damage. Specifically, can pierce tanks located within reach class and losing the required integrity of these structures. Therefore, in this paper we review the issue of the required thickness to ensure that no loss of integrity of the tanks. The paper focuses on the evaluation of the required thickness of steel sheets.

  13. Design and Simulation of Adaptive Backstepping Control Law for BTT Missile%BTT导弹自适应反演控制律设计与仿真

    Institute of Scientific and Technical Information of China (English)

    施敏良; 王凌艳; 李青山; 刘洪昌

    2012-01-01

    针对倾斜转弯(BTT)导弹控制中的多变量强耦合问题,研究了一种适用于BTT导弹的反演算法,以实现自动驾驶仪的自适应解耦控制.根据BTT导弹控制的基本特性,建立导弹的非线性控制模型,并将其转化为适合于反演设计的反馈块模型.在此模型上,基于反演的非线性控制系统综合设计方法,加入自适应神经网络逼近系统中存在的不确定性,利用Lyapunov稳定性定理推导了自适应调节律,设计了导弹控制律.通过仿真验证了该设计方法的有效性和可行性,该控制器能够实现控制解耦目的,且对指令信号跟踪效果良好.%In order to solve the problems of multiple variables and strong coupling in BIT (bank-to-turn) missile control, a backstepping algorithm suitable for the BTT missile autopilot controller was proposed. Based on the peculiarity of BTT missile,the nonlinear model of missile was built up. Then,the missile model was translated into a feedback block model to realize the backstepping design. A special nonlinear synthetical backstepping method was applied in design of the control law for BTT missile, which added neural networks to solve the uncertainties problems, and the adaptive tuning rules were derived using the Lyapunov stability theorem. This method can implement the decoupling design of controller and track the command signals well. Simulation was made to demonstrate the effectiveness of the proposed method.

  14. Software system requirements for the Army Tactical Missile System (ATACMS) End-To-End System using the Computer Aided Prototyping System (CAPS) multi-file approach

    OpenAIRE

    Angrisani, David Stuart; Whitbeck, George Steven.

    1996-01-01

    The Department of Defense (DOD) is seeking software system requirements for the Army Tactical Missile System (ATACMS) End to End System, which comprises both ATACMS and all sensors, links, and command centers which enable integration across system and service boundaries. The complexity, multiple interfaces, and joint nature of planned ATACMS operations demands accurate specification of software system requirements. DOD also desires automated tools capable of developing rapid prototypes to ass...

  15. Study on the Spline Filter Algorithm in Ballistic Missile Boost-phase%弹道导弹主动段样条滤波算法

    Institute of Scientific and Technical Information of China (English)

    张峰; 田康生

    2012-01-01

    对弹道导弹主动段进行跟踪是弹道导弹主动段防御中极其重要的任务,它是制导拦截的基础.针对传统方法在弹道导弹主动段跟踪能力不足,建立了弹道导弹主动段样条滤波算法.该滤波算法首先用样条函数建立了主动段运动模型,其次在此基础上将运动状态进行了解耦,建立了状态方程,最后基于解耦模型,应用Kalman滤波进行了状态估计,并且在估计中设计了模型更新方法,使算法具有很好的机动跟踪性能.仿真实验证明,该跟踪算法估计精度高于其它算法.%The tracking of ballistic missile under boost-phase is extremely important in the missile early defense program. It is the base of interception. In respect that traditional methods have essential deficiency on the tracking of ballistic missile under boost-phase, this paper introduces a filter algorithm based on spline modeling. First, a ballistic missile under boost-phase motion model is established based on spline function. Then movement state is decoupled. Equation of State is established. At last, based on the decoupling model, state is estimated by using Kalman Filter. This paper has designed a model updating method in order to make it capable of maneuver target tracking. The simulation result shows that this algorithm has high precision and good performance.

  16. Development of microprocessor-based laser velocimeter and its application to measurement of jet exhausts and flows over missiles at high angles of attack

    Science.gov (United States)

    Harwell, K. E.; Farmer, W. M.; Hornkohl, J. O.; Stallings, E.

    1981-03-01

    During the past three years, personnel have developed a unique three-component laser velocimeter for the in situ measurement of particle and/or gas velocities in flow fields produced behind bodies at high angles of attack and in jet exhaust plumes. This report describes the development of the laser velocimeter and its subsequent application of the measurement of the velocity distribution and vortex structure in free jets and in flows over missiles at high angles of attack.

  17. Supersonic aerodynamic characteristics of a low-aspect-ratio missile model with wing and tail controls and with tails in line and interdigitated

    Science.gov (United States)

    Graves, E. B.

    1972-01-01

    A study has been made to determine the aerodynamic characteristics of a low-aspect ratio cruciform missile model with all-movable wings and tails. The configuration was tested at Mach numbers from 1.50 to 4.63 with the wings in the vertical and horizontal planes and with the wings in a 45 deg roll plane with tails in line and interdigitated.

  18. Final Programmatic Environmental Impact Statement for Defense Threat Reduction Agency (DTRA) Activities on White Sands Missile Range, New Mexico. Volume 1

    Science.gov (United States)

    2007-03-01

    of test may cause minor cosmetic damage (e.g. broken windows, and cracked plaster) to a structure. Proposed mitigations would require that weather...Applied Microbiology and Biotechnology , 49(6): 751-757. Borg, E. 1991. Physiological and pathogenic effects of sound. Acta Oto-Laryngologica 381...breeding black-throated blue warblers. Ecology 73:357-372. Rodriguez, M. 2004. West Nile Virus found on WSMR. Missile Ranger (57)39:1. Rowson, K

  19. The Apache Longbow-Hellfire Missile Test at Yuma Proving Ground: Introduction and Problem Formulation for a Multiple Stressor Risk Assessment

    Energy Technology Data Exchange (ETDEWEB)

    Efroymson, Rebecca Ann [ORNL; Peterson, Mark J [ORNL; Jones, Daniel Steven [ORNL; Suter, Glenn [U.S. Environmental Protection Agency

    2008-01-01

    An ecological risk assessment was conducted at Yuma Proving Ground, Arizona, as a demonstration of the Military Ecological Risk Assessment Framework (MERAF). The focus of the assessment was a testing program at Cibola Range, which involved an Apache Longbow helicopter firing Hellfire missiles at moving targets, i.e., M60-A1 tanks. The problem formulation for the assessment included conceptual models for three component activities of the test, helicopter overflight, missile firing, and tracked vehicle movement, and two ecological endpoint entities, woody desert wash communities and desert mule deer (Odocoileus hemionus crooki) populations. An activity-specific risk assessment framework was available to provide guidance for assessing risks associated with aircraft overflights. Key environmental features of the study area include barren desert pavement and tree-lined desert washes. The primary stressors associated with helicopter overflights were sound and the view of the aircraft. The primary stressor associated with Hellfire missile firing was sound. The principal stressor associated with tracked vehicle movement was soil disturbance, and a resulting, secondary stressor was hydrological change. Water loss to washes and wash vegetation was expected to result from increased ponding, infiltrationand/or evaporation associated with disturbances to desert pavement. A plan for estimating integrated risks from the three military activities was included in the problem formulation.

  20. 导弹预防性检测系统设计%The Design of The System of Missile Precautionary Measurement

    Institute of Scientific and Technical Information of China (English)

    刘洪于; 方洋旺

    2012-01-01

    导弹贮存期间经历多次测试维修,检测数据繁杂,只有更好利用其现场数据才能更合理预测导弹寿命及检测时间。对此,结合装备失效率曲线,提出三种样本采集方案,设计了一套预防性检测系统,并以威布尔分布为例,进行了仿真验证,结果验证系统的正确性与实用性。%There is a lot of measurement and maintenance during missile storage.Due to the complexity of data test,only by using field data can the lifespan and test time of missiles be better forecasted.To solve the problem,three kinds of data acquisition schemes are given by considering the bathtub curve of disabled probability of equipment.The system of missile precautionary measurement is designed.The simulation experiment based on the data turns out to obey Weibull distribution.The result validates the effectiveness and practicability of the system.

  1. Study on Noise Environment Prediction of Missile Instrument Bay Base on NASTRAN%基于NASTRAN导弹仪器舱噪声环境预示研究

    Institute of Scientific and Technical Information of China (English)

    王亮; 商霖; 牛智玲; 李炳蔚

    2013-01-01

    Based on the FEM software MSC.Patran and Nastran, the prediction of the noise environment dynamics of the missile instrument bay is investigated. Firstly, the 3-D shell model of the instrument bay is established. Secondly, the sound press lever (SPL) of the missile during flight is studied based on trajectory data. And the Spectrum of SPL is presented, which is transferred to power spectral density function of pressure. At last, the dynamic environment of missile instrument bay is predicted.%  基于商用有限元软件 MSC.Patran 和 Nastran,研究某型导弹的仪器舱结构的噪声环境动力学预示.首先建立仪器舱的三维壳单元模型;根据弹道数据理论,研究导弹在飞行过程中遭受噪声的总声压级,给出噪声声压级谱,并转换为压力功率谱密度函数;最后预示了该仪器舱在压力功率谱的作用下的动力学环境.

  2. 舰载弹炮结合近程武器系统技术研究%Study on Shipped Missile-Gun Integrated Defense Weapon System

    Institute of Scientific and Technical Information of China (English)

    白奕

    2014-01-01

    现代高性能反舰导弹是舰艇末端防御的最大威胁,而舰载弹炮结合近程武器系统为舰艇的末端防御提供了一种有效的途径。分析了舰载弹炮结合近程武器系统的作战使用和主要特点,针对海上空袭武器的特点,重点研究了增强系统抗饱和攻击能力的设计方法,并探讨了舰载弹炮结合近程武器系统在现代海战中的使用方向。%Modern high-powered antiship missile is the main threaten of ship,and shipped missile-gun integrated defense weapon system is an effective way to the terminal defense of ship. This paper first analyzes the combat operation and main characteristic of missile-gun integrated defense weapon system,then studies the key factor of designing a system. At last the system usage is discussed in the modern sea war.

  3. 舵机负载模拟器惯量失配加载补偿方法%Missile Actuator Load Simulator Inertia Mismatch Compensation Methods

    Institute of Scientific and Technical Information of China (English)

    陶渝辉; 王战

    2012-01-01

    The compensation methods are discussed when load simulator inertia is greater than missile control surface inertia. Errors of missile actuator torque and deflection angle exist in simulation using compensation. The approaches are presented to improve simulation according to different errors. Analysis results show that the compensation method is useable and valuable to many missile actuator load simulations.%针对舵机负载力矩模拟器输出等效惯量大于被加载舵机舵面惯量的舵机加载试验情况,研究了其力矩加载补偿方法,分析了其力矩加载误差,提出了针对不同误差源的提高仿真精度的技术途径.分析结果表明,此力矩加载补偿方法现实可行,提高了试验资源的利用率,具有较好的经济效益和现实意义.

  4. 空空导弹冗余系统共模失效%Approach of Common Mode Failure Analysis in Redundant System of Air-to-Air Missile

    Institute of Scientific and Technical Information of China (English)

    王丽丽; 周光巍; 王俊华

    2011-01-01

    为避免空空导弹冗余系统产生共模失效,提高产品可靠性和安全性。在研究共模失效分析方法的基础上,结合空空导弹的研制特点,对某型空空导弹电源组件点火电路冗余系统共模故障进行了定性分析,识别了点火电路中的共模故障,分析了故障原因和耦合因素,并提出了相应的改进措施。%In order to avoiding common mode failure of the air-to-air missile, and improving the reliability and safety of the product, combine the developing character of the air-to-air missile, made a qualitative a- nalysis of the common mode failure in the redundant system of a type air-to-air missile power supply module igniting circuit based on the study of the method of common mode failure analysis, identified the com- mon mode failure of the equipment, analyzed the cause of failure and the coupling factor, put forward improvement measures.

  5. The Application of ANSYS Software on Missile Packing Design%ANSYS软件在导弹包装箱设计中的应用研究

    Institute of Scientific and Technical Information of China (English)

    张鹏; 王文博; 王宏伟

    2015-01-01

    To consider in the design of missile packing in minimize weight, at the same time also need to satisfy the packing stacking, lifting, fork, long-distance transportation and use of mechanical environment. Based on the common packing of the framework outside missile, for example, the ANSYS software was used for ifnite element modeling and mechanical environment analyzing and researching, and formed a modeling and analysis method with ANSYS software for missile packing.%空空导弹包装箱在设计中要考虑减重措施,同时还需满足包装箱堆码、吊运、叉运、长途运输等使用力学环境。以常用的导弹外框架包装箱为例,采用ANSYS软件进行了有限元建模和力学环境分析研究,形成了应用ANSYS软件进行导弹包装箱有限元建模和分析的一般方法。

  6. Effects of variable trajectory on ramjet powered anti-ship missile%弹道变轨对冲压动力反舰导弹的影响

    Institute of Scientific and Technical Information of China (English)

    柳长安; 张蒙正

    2012-01-01

    With the development of the technology for defence against anti-ship missile,anti-ship missile is facing a new challenge.Therefore,the technologies of stealth,variable trajectory,electronic countermeasure and supersonic flight must be used to improve the penetration efficiency and strike effect,in which the variable trajectory and supersonic flight technologies are all affected by the propulsion equipment.The different variable trajectory methods are described.The ramjet constraint is analyzed.The influence of different parameters on the performance of anti-ship missile and some limiting factors to the propulsion device are discussed.%反舰导弹防御技术的发展使反舰导弹已面临新的挑战,迫切需要通过隐身技术、变轨技术、电磁对抗和超声速飞行等技术来提高突防和打击效能,而变轨技术和超声速飞行直接与冲压动力装置相关。在论述变轨技术的基础上对冲压动力约束问题进行了对比分析,讨论了不同参数的影响和动力装置的限制因素。

  7. 旋转导弹姿态稳定控制方法研究%The Attitude Stabilization Control Method for Spinning Missile

    Institute of Scientific and Technical Information of China (English)

    楼朝飞; 张锐; 陆宙斯

    2011-01-01

    旋转导弹往往采用初始静不稳定的结构形式使得在攻击目标时具有较大的过载能力,如何能够保证旋转导弹平稳地度过静不稳定段是导弹正常飞行的关键.采用姿态稳定控制方法对初始段进行控制,使导弹顺利度过静不稳定段,通过数学仿真及半实物仿真验证了该控制方法的有效性.基于正交试验设计的仿真试验表明,在各种气动干扰因素影响下,旋转导弹均能实现较高的姿态控制精度.%Spinning missile generally adopts initial unsteady structure to make it endure much higher overload. It is necessary for a spinning missile to get through the unsteady period successfully. The attitude stabilization control method is designed for spinning missile. The design of attitude stabilization control method is given and math simulation is completed. The availability is validated by simulation data at different interference backgrounds.

  8. An Onboard Transmitting Antenna of Cruise Missile%一种飞航导弹弹载发射天线设计

    Institute of Scientific and Technical Information of China (English)

    何兵; 刘刚; 南楠; 王园园

    2011-01-01

    以飞航导弹弹载数据链为应用背景,通过综合分析、比较、优化和仿真,设计了一种与飞航导弹共形、具有大角域覆盖能力的弹载发射天线。仿真结果说明了该天线性能满足飞航导弹卫星通信需求,在解决工程实际问题的同时,为此类应用提供了一种新型天线方案,为相关设计提供了一种思路。%In the paper,we designed a kind of onboard transmitting antenna of cruise missile through integrated comparison,analysis,optimization and simulation.The antenna is conformal with the cruise missile,and has wide coverage domain and certain anti-jamming capability.The simulation result shows that the designed antenna satisfies all requirements of satellite communication of cruise missile.The paper provides a new antenna designning method and new idea for similar application.

  9. 基于TOPSIS的战区高层反导威胁评估%Threat Assessment of the High Altitude Area Ballistic Missile Defense Based on TOPSIS

    Institute of Scientific and Technical Information of China (English)

    范学渊; 邢清华; 黄沛; 王小光

    2012-01-01

    Firstly, the characteristics of the high altitude area ballistic missile defense' s threat assessment are analyzed. Then the threat assessment's model index system is set up and quantitated, such as launch position of tactical ballistic missile (TBM) , forecasting impact point, range and so on. Finally, the theory of technique for order preference by similarity to idea solution (TOPSIS) based on weight of entropy is used to compute the model. The result shows that the threat assessment' s model and the algorithm is effective and useful for developing the battle manage of the high altitude area ballistic missile defense ' s.%在分析战区高层反导威胁评估特点的基础上,建立了以来袭TBM发射点、预测落点、射程等为核心的战区高层反导威胁评估模型指标体系并进行了相应的量化,然后利用基于熵值权重确定的TOPSIS理论对模型进行求解.通过实例证明所提出的战区高层反导威胁评估模型和算法的有效性,对研究美军的战区高层反导武器系统具有一定的借鉴意义.

  10. 基于Multi-Agent的防空导弹武器系统模型设计%Design of Multi-Agent Based Model on Air Defense Missile Weapon System

    Institute of Scientific and Technical Information of China (English)

    陈宝印; 栾立秋; 张成斌

    2011-01-01

    建立科学的结构模型是进行防空导弹武器系统仿真的基础和关键环节.针对防空导弹武器系统的特点,提出了基于Multi-Agent的防空导弹武器系统模型建模方法,设计了防空导弹武器系统模型结构.利用Multi-Agent建模技术,把防空导弹武器系统实体映射成相应的Multi-Agent系统,并以Agent的形式对防空导弹武器系统这一客观复杂系统进行了深刻的认识,为防空导弹武器系统建模仿真奠定了基础.%Forming a scientific system model is the key of Air Defense Missile Weapon System simulation. According to the characters of Air Defense Missile Weapon System, a modeling method of multi-agent based model on Air Defense Missile Weapon System is given. The framework on Air Defense Missile Weapon System is designed. Using the Multi-Agent modeling technology, maps the Air Defense Missile Weapon System entity the corresponding Multi-Agent system, and carries on the profound understanding by the Agent form to Air Defense Missile Weapon System this objective complicated, which will be helpful to realize the modeling simulation on Air Defense Missile Weapon System.

  11. 美国空射导弹拦截系统的作战应用分析%Analysis on Operational Applications of USA Air-launched Missile Interception System

    Institute of Scientific and Technical Information of China (English)

    宋文静; 曹泽阳; 张晋; 刘永兰

    2015-01-01

    Air-launched missile interception system is an interception mean of USA missile defense systems.Its main operational missions are analyzed, including missile defense mission, hypersonic speed missile interception mission in the air,multi-orbital air-craft interception mission and other defense missions.Taking missile defense mission as an example, its operational process is ana-lyzed, thus key links of air-launched missile anti-missile /anti-satellite system are given.Combined with main operational missions and operational process, special influence factors of its operational effectiveness are parsed.Studying on problems of its operational application, is benefit to improve operational effectiveness of the weapon equipment.%空射导弹拦截系统是美国弹道导弹防御体系的拦截手段之一,文中首先分析了空射导弹拦截系统的主要作战任务,包括弹道导弹防御任务、高超声速导弹空中截击任务、跨轨道飞行器拦截任务和其他防御任务;然后,以弹道导弹防御任务为例,对其作战过程进行了分析,进而给出了空射导弹反导/反卫拦截系统作战的关键环节;最后,结合主要作战任务和作战过程,剖析了其作战效能的特殊影响因素. 研究其作战应用问题,有益于提升该武器装备的作战效能.

  12. 导弹防御系统中红外光电识别技术分析%Analyses on infrared optoelectronics recognition technology in missile defense system

    Institute of Scientific and Technical Information of China (English)

    吴瑕; 周焰; 崔建; 杨龙坡

    2009-01-01

    目标识别问题是弹道导弹防御系统中的核心难题之一,针对弹道导弹突防中威胁目标群飞行各阶段呈现出的不同红外特性.介绍了天基红外系统和拦截弹的最新研究进展及其红外目标识别技术手段.在温度测量、测辐射强度、红外成像等关键技术方面,系统地论述了其在反导系统弹道目标识别中所运用的红外光电子学方法与技术,并且就相应的反红外识别手段--红外隐身与红外诱饵,进行了探讨.最后对导弹防御系统中红外目标识别与反识别的研究动向进行了展望,提出了进行导弹防御系统目标识别研究的总体建议.%The target recognition is one of the core difficult problems of ballistic missile defense system. According to the different infrared characteristics of all sorts of dangerous targets in the apiece phases of ballistic missile flying, the newest development and the technical means of infrared target recognition for SBIRS and kinetic kill vehicle were introduced. The means and technologies of infrared optoelectronics applying in target recognition were depicted systematically considering the development of some key technologies, such as infrared temperature measurement, radiant intensity test and infrared imaging. Infrared stealth and infrared decoy technique were also discussed, which were the relevant infrared target counter-recognition means and technologies during ballistic missile attacking. Finally, some new representative developments for infrared target recognition and counter-recognition in ballistics missile defense system were expected, and some general suggestions to develop target recognition in ballistic missile defense system were provided.

  13. 越肩发射空空导弹发射条件%A Research on Launching Opportunity of Over-the-shoulder(OTS)Missile

    Institute of Scientific and Technical Information of China (English)

    赵雨; 张斌; 李浩亮

    2014-01-01

    越肩发射的使用是有条件的,只有在保证安全的前提下才能使用越肩发射导弹攻击尾后目标,因此,载机攻击时要考虑目标威胁。通过威胁因子法分析空战中威胁载机安全的几个因素,确定各因素在目标总的威胁中所占权值,为载机正确决策提供依据;简要阐述了航迹正切规避法,并说明了使用场合;提出了越肩发射空空导弹的发射时机,基本原则是既能保证载机处于目标威胁区域之外,还要确保目标处于载机导弹的全向攻击区之内。仿真结果表明:载机被目标尾追攻击时做出正确决策可以在保证自身安全的同时将其击落。%Firing of the OTS missile is conditional,and only by ensuring safety can a fighter use the OTS missile to attack the rear target.Therefore,while attacking the rear target the pilot of the fighter should also consider the target's threats to the fighter.Firstly,this paper analyzes several factors those threaten to fighter's safety by a threat-factor method to determine the proportion of each factor,and provides evidences for the pilot to make correct choices.The paper also briefly describes the path tangent avoidance method and illustrates the situations for adopting the method.And then the paper presents a launching opportunity of over the shoulder missile.The basic principle is to ensure that the fighter is beyond the target's threat while the target still can be hit by the OTS missile.The simulation results show that it is necessary for a pilot to make decisions under the enemy's threat,and simultaneously commanding the opportunity of launching over-the-shoulder missile is of great importance to winning the air combat.

  14. Time-cooperative distributed guidance law design for multi-missiles%多导弹时间协同分布式导引律设计

    Institute of Scientific and Technical Information of China (English)

    马国欣; 张友安

    2014-01-01

    To achieve the cooperative attack against a same target for multi-missiles, an approach to design the time-cooperative distributed guidance law is proposed, which is applicable to the situation with or without angular constraint. With each missile subsystem as a homogeneous network node, the time-cooperative guidance model for multi-missiles is built, which takes each missile’s time-to-go plus designated bias as the outputs. The distributed control scheme of the system is designed to reduce the difference among the outputs of subsystems. The communication topology condition to guarantee the time-cooperativeness of multi-missiles is given by analyzing the features of the homing guidance of missile with consideration of the convergence condition of the general cooperative control system. Finally, simulation results show the effectiveness of the proposed approach.%为了实现多导弹协同攻击同一目标,提出一种时间协同分布式导引律设计方法,该方法对于无角度约束和有角度约束的情况均适用。首先,以各导弹子系统作为网络同构节点建立了多导弹时间协同制导模型,该模型以各导弹剩余时间信息附加预定偏置量为输出;然后,以调整子系统间输出误差为目的,设计了系统的分布式控制方案,并结合一般协同控制系统的收敛性条件,分析了导弹寻的导引的特殊性,给出了保证多导弹时间协同的通信拓扑条件;最后,通过仿真结果验证了所提出方法的有效性。

  15. On a New Six Degree of Freedom Modelling Method for Homing Missiles and its Application for Design/Analysis

    Directory of Open Access Journals (Sweden)

    R. N. Bhattacherjee

    1997-07-01

    Full Text Available Development of an accurate six-degree-of-freedom (6-DOF simulation model for homing missiles incorporating seeker servosystem detailed modelling is reported. A new modelling concept for seeker servosystem simulation, the Newtonian equivalent model (NEM has been evolved, where body motion coupling is modelled through forces and moments transformed to the seeker. The NEM-based modelling of seeker head and its integration in 6-DOF has been discussed. In the presence of body coupling, the simulation model for seeker tracking or pointing error, gimbal angles and inertial line of sight (LOS rates as measured by the seeker mounted rate gyros have been obtained through the new modelling method. A novel method of obtaining optimum pitch and yaw LOS rates for proportional navigation (PN guidance mechanisation is formulated based on synthesised sight line rates measured in the seeker inner gimbal axis. This new method has been validated through simulation studies using the 6-DOF model developed and by comparing the results with those obtained by the conventional method of generating LOS rates for PN guidance. Other important applications of the 6-DOF model discussed are guidance and control design validation/tuning seeker feedforward compensation design tuning of switchover point from open-loop to closed-loop PN guidance. Importance of the detailed 6-DOF simulation model as the ultimate performance evaluation tool for the weapon system in terms of both terminal performance and adequacy of seeker field of view, gimbal angle freedom, etc. has been brought out.

  16. The Apache Longbow-Hellfire Missile Test at Yuma Proving Ground: Ecological Risk Assessment for Helicopter Overflight

    Energy Technology Data Exchange (ETDEWEB)

    Efroymson, Rebecca Ann [ORNL; Hargrove, William Walter [ORNL; Suter, Glenn [U.S. Environmental Protection Agency

    2008-01-01

    A multi-stressor risk assessment was conducted at Yuma Proving Ground, Arizona, as a demonstration of the Military Ecological Risk Assessment Framework. The focus of the assessment was a testing program at Cibola Range, which involved an Apache Longbow helicopter firing Hellfire missiles at moving targets, M60-A1 tanks. This paper focuses on the wildlife risk assessment for the helicopter overflight. The primary stressors were sound and the view of the aircraft. Exposure to desert mule deer (Odocoileus hemionus crooki) was quantified using Air Force sound contour programs NOISEMAP and MR_NMAP, which gave very different results. Slant distance from helicopters to deer was also used as a measure of exposure that integrated risk from sound and view of the aircraft. Exposure-response models for the characterization of effects consisted of behavioral thresholds in sound exposure level or maximum sound level units or slant distance. Available sound thresholds were limited for desert mule deer, but a distribution of slant-distance thresholds was available for ungulates. The risk characterization used a weight-of-evidence approach and concluded that risk to mule deer behavior from the Apache overflight is uncertain, but that no risk to mule deer abundance and reproduction is expected.

  17. Back-stepping active disturbance rejection control design for integrated missile guidance and control system via reduced-order ESO.

    Science.gov (United States)

    Xingling, Shao; Honglun, Wang

    2015-07-01

    This paper proposes a novel composite integrated guidance and control (IGC) law for missile intercepting against unknown maneuvering target with multiple uncertainties and control constraint. First, by using back-stepping technique, the proposed IGC law design is separated into guidance loop and control loop. The unknown target maneuvers and variations of aerodynamics parameters in guidance and control loop are viewed as uncertainties, which are estimated and compensated by designed model-assisted reduced-order extended state observer (ESO). Second, based on the principle of active disturbance rejection control (ADRC), enhanced feedback linearization (FL) based control law is implemented for the IGC model using the estimates generated by reduced-order ESO. In addition, performance analysis and comparisons between ESO and reduced-order ESO are examined. Nonlinear tracking differentiator is employed to construct the derivative of virtual control command in the control loop. Third, the closed-loop stability for the considered system is established. Finally, the effectiveness of the proposed IGC law in enhanced interception performance such as smooth interception course, improved robustness against multiple uncertainties as well as reduced control consumption during initial phase are demonstrated through simulations.

  18. Wind Tunnel Application of a Pressure-Sensitive Paint Technique to a Faceted Missile Model at Subsonic and Transonic Speeds

    Science.gov (United States)

    Erickson, Gary E.

    2004-01-01

    A pressure-sensitive paint (PSP) technique was applied in a wind tunnel experiment in the NASA Langley Research Center 8-Foot Transonic Pressure Tunnel to quantify the vortex-induced surface static pressures on a slender, faceted missile model at subsonic and transonic speeds. Satisfactory global calibrations of the PSP were obtained at =0.70, 0.90, and 1.20, angles of attack from 10 degrees to 20 degrees, and angles of sideslip of 0 and 2.5 degrees using an in-situ method featuring the simultaneous acquisition of electronically-scanned pressures (ESP) at 57 discrete locations on the model. Both techniques clearly revealed the significant influence on the surface pressure distributions of the vortices shed from the sharp, chine-like leading edges. The mean error in the PSP measurements relative to the ESP data was approximately 0.6 percent at M infinity =0.70 and 2.6 percent at M infinity =0.90 and 1.20. The vortex surface pressure signatures obtained from the PSP and ESP techniques were correlated with the off-surface vortex cross-flow structures obtained using a laser vapor screen (LVS) flow visualization technique. The on-surface and off-surface techniques were complementary, since each provided details of the vortex-dominated flow that were not clear or apparent in the other.

  19. Changes of balance between proteinase and their inhibitors in blood of pigs with high-velocity missile wounds

    Institute of Scientific and Technical Information of China (English)

    周元国; 朱佩芳; 周继红; 李晓炎

    2003-01-01

    Objective: To study the effect of imbalance between lysosomal enzymes and their inhibitors in blood on disturbance of the local and whole body after trauma. Methods: The dynamic changes of lysosomal enzymes and proteinase inhibitors were studied in 12 pigs with femoral comminuted fractures in both hind limbs caused by high velocity missiles. Four normal pigs served as controls. Results: After injury, the activity of Cathepsin D in arterial plasma increased gradually and reached the highest level at 8 hours, acid phosphatase in serum began to increase at 12 hours and the value of serum elastase did not change significantly. The level of α1-antitrypsin, a proteinase inhibitor in plasma, decreased significantly in the early stage after injury [73.5%±6.4% and 81.0%±5.1% of the baseline value (1.67 μmol*ml-1*min-1± 0.29 μmol*ml-1*min-1) at l and 2 hours after injury, respectively, P<0.05], then increased gradually and was higher than the baseline value at 12 hours after injury. Conclusions: Imbalance between lysosomal enzymes and proteinase inhibitors occurs soon after injury, which might result in continuous tissue damage and play an important role in the disturbance of general reaction after injury.

  20. A design proposal of a certain missile tactical command system based on Beidou satellite communication and GPS positioning techniques

    Science.gov (United States)

    Ma, Jian; Hao, Yongsheng; Miao, Jian; Zhang, Jianmao

    2007-11-01

    This paper introduced a design proposal of tactical command system that applied to a kind of anti-tank missile carriers. The tactical command system was made up of embedded computer system based on PC104 bus, Linux operating system, digital military map, Beidou satellite communication equipments and GPS positioning equipments. The geographic coordinates was measured by the GPS receiver, the positioning data, commands and information were transmitted real-time between tactical command systems, tactical command systems and command center, by the Beidou satellite communication systems. The Beidou satellite communication equipments and GPS positioning equipments were integrated to an independent module, exchanging data with embedded computer through RS232 serial ports and USB ports. The decision support system software based on information fusion, calculates positioning data, geography information and battle field information synthetically, shows the position of allies and the position of enemy on the military map, and assesses the various threats of different enemy objects, educes a situation assessment and threat assessment.

  1. 某型导弹舵机限流电路分析%Missile Servo Current-limiting Circuit Analysis

    Institute of Scientific and Technical Information of China (English)

    王小波; 付克亚

    2016-01-01

    The current of current-limiting circuit frequently surpasses its nomial value in testing servo control circuit of a certain type missile.This paper analyses the working principle of current-limiting circuit,identifies its main influence factors,and brings forward the corresponding solution to solve such failure and promote the passing ratio of control circuit assembly test.The feasibility and effectiveness of the solution method is validat-ed in practice.%某型导弹舵机控制电路在测试时,经常出现限幅电流超差故障。该文从分析限流电路工作原理出发,查找出其主要影响因素,并有针对性的提出解决方法,以解决此类故障,提高控制电路装配测试合格率。通过生产实际,验证了这些解决方法的可行性和有效性。

  2. Buying for Armageddon: Factors influencing post-World War II weapons purchases since the Cuban Missile Crisis

    Energy Technology Data Exchange (ETDEWEB)

    Boies, J.L.

    1991-01-01

    The central problem of this study is the role that the economy and economic interests play in decisions about US weapons-systems acquisition. Despite a voluminous literature discussing the formation of military policy, journalistic accounts of business influence on military policy dominate the literature. A notable exception to this pattern is Griffin, Devine, and Wallace's use of time-series data on military expenditures to assess Baran and Sweezy's thesis that military expenditures are necessary to the good health of the monopoly sector of the US economy. Using similar techniques and an expanded data set, the effect of business political action and major economic forces on the quantity and types of weapons purchased since the Cuban Missile Crisis are investigated. Findings indicate that defense contractor rates of profit have a positive relationship to procurement expenditures of most types. This is opposite of the effect posited by most of the literature. Elite political mobilization, measured by the activity of the Committee on the Present Danger, a group at the core of the New Right Social Movement, has a positive effect on expenditures.

  3. Computer program for post-flight evaluation of the control surface response for an attitude controlled missile

    Science.gov (United States)

    Knauber, R. N.

    1982-01-01

    A FORTRAN IV coded computer program is presented for post-flight analysis of a missile's control surface response. It includes preprocessing of digitized telemetry data for time lags, biases, non-linear calibration changes and filtering. Measurements include autopilot attitude rate and displacement gyro output and four control surface deflections. Simple first order lags are assumed for the pitch, yaw and roll axes of control. Each actuator is also assumed to be represented by a first order lag. Mixing of pitch, yaw and roll commands to four control surfaces is assumed. A pseudo-inverse technique is used to obtain the pitch, yaw and roll components from the four measured deflections. This program has been used for over 10 years on the NASA/SCOUT launch vehicle for post-flight analysis and was helpful in detecting incipient actuator stall due to excessive hinge moments. The program is currently set up for a CDC CYBER 175 computer system. It requires 34K words of memory and contains 675 cards. A sample problem presented herein including the optional plotting requires eleven (11) seconds of central processor time.

  4. 国外舰载防空反导火控系统发展现状%Study on Overseas Development Conditions of Shipboard Aerial Defence Anti-Missile Fire System

    Institute of Scientific and Technical Information of China (English)

    王金云; 王孟军

    2013-01-01

    论述了国外舰载火控系统的发展状况,介绍了各国防空反导系统中防空导弹、火炮、弹、炮、箭相结合的防御方式及新概念武器发展现状及其特点分析,指出未来防空反导任务中,需在火控技术上采用新的机理(如多传感器信息融合、对机动目标滤波处理、火控解算等),火力配置上采用分层防御,各种武器系统协同作战,实现对来袭导弹有效拦截。%The paper discusses the development conditions of overseas shipboard weapon system, introduces aerial defence missile,gun,missile-gun,missile-rocket integrated defense mode and new concept weapon development status and characteristics analysis. Finally,it is necessary to study new fire control theory(multiple sensors information fusion,maneuvering targets filtering,fire control computation) in the future aerial defence anti-missile task,adopted layered defence mode for fire configuration,all kinds of weapon combination fight. It is available to hold up missile.

  5. Interception Times Model and Simulation of Surface to Air Missile%地空导弹反导作战拦截次数计算模型及仿真

    Institute of Scientific and Technical Information of China (English)

    吕超; 王光辉; 迟玉玮

    2011-01-01

    Based on studying the process of surface to air missile weapon system intercepting incoming targets, the interception rate model of surface to air missile is built by analyzing the depth of surface to air missile launching zone. The model can calculate the times of surface to air missile weapon system intercepting a single incoming target in the anti-block area. The simulation results reveal how the targets with different characteristics ( speed, altitude, route shortcut) influence the times of surface to air missile weapon system intercepting incoming targets.%在分析地空导弹武器系统拦截来袭目标过程的基础上,通过分析地空导弹发射区纵深建立了地空导弹武器系统可拦截次数模型.利用该模型可计算地空导弹武器系统对单个来袭目标在杀伤区内的拦截次数.仿真结果揭示了地空导弹武器系统在不同目标特性(速度、高度、航路捷径)下对目标的可拦截次数的影响.

  6. Air-launching Missile Trajectory Numeric Simulation for Intercepting Boosting/Ascending Stage Ballistic Missile%助推/上升段空射反导弹道仿真∗

    Institute of Scientific and Technical Information of China (English)

    郭晓楠; 李记新

    2015-01-01

    For antimissile interception of the boosting/ascending tactical missile, guidance system model is built, and numeric simulation is carried out. First, 4 guidance laws, including proportion navigation guidance( PNG)、instantaneous miss-distance based forecasting opti-mal guidance law( OGL)、line of sight acceleration guidance( AAG) and target acceleration compensated proportion navigation( APN) , are selected and applied to mid-course guidance to study the performance. According to the guidance performance analysis, 2 schemes are presented, and another two schemes are presented via exorbitant gravitation compensation ( EGC) . Finally,‘OGL+APN( EGC) ’ is dem-onstrated to be the best one, which behaves better in attack zone, launching restrictions and guidance performance.%针对空射导弹拦截助推/上升段战术弹道导弹制导问题进行制导系统建模和数字仿真。选取4种基本制导律进行中、末制导研究,包括:比例制导律( PNG)、基于瞬时脱靶量的一种最优制导律( OGL)、视线角加速度制导律(AAG)、目标加速度补偿比例制导律(APN)。据此提出2种中、末制导组合方案,通过重力过补偿优化中制导得到另2种方案。4种方案仿真对比得到“OGL+APN (重力过补偿)”方案。该方案攻击区较大,发射条件约束较宽松,具有较好的制导性能。

  7. Research on Guidance Law for Cooperative Attack of Multiple Missiles%多导弹协同作战制导律研究

    Institute of Scientific and Technical Information of China (English)

    王晓芳; 郑艺裕; 林海

    2014-01-01

    To enhance the penetration and hitting capacity of anti-ship missiles attacking the target cooperatively,a cooperative guidance law composed of a cooperative range-to-go guidance law and a guidance law making line-of-sight (LOS)angle-rate approach zero was proposed.The desired range-to-go was designed based on current range-to-go of each missile.Then the nonlinear relative motion model between missile and target on the basis of proportional navigation guidance law was built,and it was divided into a fast subsystem and a slow subsystem according to the time-scale separation method.Feedback linearization of two subsystems was realized based on dynamic inverse system theory.The guidance law that made multiple missiles’range-to-go approach and keep the desired range-to-go was designed adopting linear system theory.To ensure missiles to hit target precisely,another guidance law was proposed based on the finite time control theory,which made the angle-rate of LOS of every missile approach zero quickly in finite time while the range-to-go decreased gradually.Simulation results show that adopting the cooperative guidance law can make multiple missiles fly to the target synchronously and hit the target almost at the same time, and the cooperation of range-to-go and impact time are realized effectively.%为了增强多枚反舰导弹协同作战时的突防和打击能力,提出了一种由弹目距离协同制导律和视线角速度收敛制导律两部分组成的多导弹协同制导律。综合多枚导弹的弹目距离信息,设计了期望弹目距离。基于比例导引律建立了导弹目标相对运动非线性模型,采用时标分离原理将其分为快变子系统和慢变子系统,然后采用动态逆系统理论将2个子系统反馈线性化,基于线性系统理论设计了能够实现多弹弹目距离趋于期望弹目距离的制导律。为了保证各导弹顺利地协同攻击目标,在飞行末段,采用有限时间控制理论

  8. 导弹攻防对抗仿真中偶极子云建模和仿真%Modeling and Simulation of Chaff Cloud in Missile Attack-Defense Confrontation

    Institute of Scientific and Technical Information of China (English)

    颜如祥; 宦国杨; 方冰

    2012-01-01

    Principles of chaff clouds thrown by missiles are analyzed in the simulation of missile attack-defense confrontation. The flight path model of chaff clouds is built and effects of chaff clouds are researched. The modeling and simulation technologies give a guidance for building simulation system of the missile attack-defense confrontation.%从导弹攻防对抗仿真角度分析了弹道导弹抛撒偶极子云的工作原理,继而建立了偶极子云飞行轨迹模型。同时研究了偶极子云的作用效果。该建模和仿真技术对建立导弹攻防对抗仿真系统具有指导意义。

  9. The Trend of Missile-Gun Combined Weapon System for Aerial Defense%弹炮结合防空武器系统新趋势

    Institute of Scientific and Technical Information of China (English)

    陈薇; 王军

    2016-01-01

    Since the Kosovo War started to use a form of simple air raids and counter-air raids,a increasing number of wars use air raids to attack the enemy,so how to defense the enemy in the air become more and more important. Missile-Gun combined weapon system not only has a big air defense area but also has a high effective-cost,so it will become the trend of air defense weapon system. This paper describes the structure and classification of Missile-Gun combined weapon system,and analyzes the advantages and disadvantages of the current systems; finally the trend of Missile-Gun combined weapon system is proposed.%自从科索沃战争开创了单纯空袭作战与反空袭作战的先例之后,空袭就成为了战争的焦点,如何更好地抵御空中目标的来袭成为各国战争防御的主题。弹炮结合防空武器系统具有防空区域大、效费比高等优点,是防空武器系统的发展趋势之一。在分析现有典型弹炮结合防空武器系统的基础上,依据弹炮结合武器系统是否共用火控系统将其分为弹炮混编式和弹炮同控式两种形式;随后,结合现代空袭的特点提出了弹炮结合武器系统的发展趋势。

  10. Flow behavior during uncorking process of an underwater hot-launched missile%导弹水下热发射出筒过程流动特性

    Institute of Scientific and Technical Information of China (English)

    曹嘉怡; 鲁传敬; 陈鑫; 李杰; 陈瑛

    2011-01-01

    研究了导弹水下热发射出筒过程的流动特性.采用基于多相流Mixture模型的有限体积法求解RANS方程,考虑了流体的可压缩性、粘性、重力作用、气-水掺混效应和能量交换等各项因素,运用自编UDF模块结合动网格技术,对导弹水下发射出筒过程的轴对称流场进行了数值模拟.计算结果揭示了导弹水下热发射出筒过程中发动机喷管、发射筒内和潜艇外的复杂多相流动的演化、流场结构和流体动力特性.%Flow behavior during the uncorking process of an underwater hot-launched missile were investigated. Hie finite volume method based on the multiphase model was adopted to solve RANS equations, which took into account the effects of fluid compressibility, viscosity, gravity, mixing and energy exchange of water and combustion gas. The program UDF module combined with the dynamic mesh method was used to numerically simulate the axisvmmetric flow field of the launching process. The results reveal the evolution progress, flow field configuration and hydrodynamic characteristics of the complex unsteady multiphase flow in the missile engine nozzle, launching-tube and outside the vehicle during the hot launching process of underwater missile.

  11. Study on aerodynamic characteristics of tactical missile with morphing wings%可变形翼战术导弹气动特性研究

    Institute of Scientific and Technical Information of China (English)

    张公平; 段朝阳; 廖志忠

    2011-01-01

    为进一步拓宽现有战术导弹的性能包线,通过工程估算及实验数据校核,分析了一类典型轴对称基准弹的纵向气动特性.然后,分别针对变后掠角弹翼与变翼展弹翼,研究了这两种可变形翼导弹的升力、阻力及静稳定度特性,揭示了弹翼变形对全弹气动特性的影响机理.最后,根据不同变形方式的气动计算结果,提出一种可在导弹飞行过程中同时改善其升力及阻力特性的方法.结果表明,所提出的变后掠与变翼展方法均能有效提高战术导弹的升力,并降低阻力.%To extend performance envelop of the existing tactical missiles, we study the aerodynamic characteristics of a representative axisymmetric baseline missile based on the engineering estimating and test data verifying.Then, the lift and drag characteristics of two morphing missiles with variable-sweep wings and variable-span wings are researched respectively, and the impact mechanism of morphing wings on aerodynamic characteristics is explained. Finally, based on the aerodynamic data of the two different morphing modes, a method is presented to give consideration to the characteristics of lift and drag. The results show that the variable-sweep wings and variablespan wings can effectively increase lift and reduce drag.

  12. 带控制律导弹投放数值模拟%Missile separation simulation with control laws

    Institute of Scientific and Technical Information of China (English)

    周乃春; 李彬; 郑鸣; 邓有奇

    2013-01-01

    Using an overset unstructured grid,three dimensional URANS equations are applied to simulate the missile separation with control laws.The walls criterion is used in the automatic hole-cutting procedure.Arithmetic average method is used to get the value during the overset grids.Comparison computing of the trajectories of a wing/pylon/finned-store configuration with three different control laws is carried out with this method,and a complex separation problem is solved.%基于非结构重叠网格技术,耦合舵面控制律模块,采用非定常雷诺平均NS方程,建立了模拟控制律作用下导弹投放分离动态特性的CFD数值方法.非结构重叠网格生成技术以“物面相交”方法确定洞边界,在多套网格重叠部分采用算术平均进行物理量的计算传递.采用机翼/挂架/带舵外挂物模型,以及不同的舵面控制规律展开了对比计算,分析了结果.并比较了某导弹有无控制律作用时从某战斗机分离的动态特性,研究了增加控制律的必要性.

  13. Toward Armageddon: The proliferation of unconventional weapons and ballistic missiles in the Middle East. Occasional Paper No. 36

    Energy Technology Data Exchange (ETDEWEB)

    Miller, A.J.

    1989-12-01

    The author concludes that it is probable that unconventional weapons and their associated delivery systems will form a permanent part of future political and strategic calculations in the Middle East. Some possible consequences of this situation can be divided into three classes: intra-regional, inter-regional and extra-regional. There is no doubt that Israel, driven by the need for security,precipitated the proliferation of unconventional weapons and of surface-to-surface missiles in the Middle East. It will now be driven to secure itself from the new threat to its security posed by its regional opponents. The most significant extra-regional consequence of developments in the Middle East may be further complication of great power arms control negotiations. To the re-discovery by the United States and the Soviet Union of their obligations under the Non-Proliferation Treaty to reduce the level of their nuclear weapons must now be added the desire to reduce, if not entirely eliminate, their chemical weapons stockpiles in advance of a global ban. It is possible that lesser powers will learn from the evidence of the great powers behavior, although that contradicts much of what we know of the psychology of decision making in international politics. What is necessary, though not necessarily sufficient, is that the U.S. and the USSR as the two external powers with potentially the greatest leverage, work together toward the resolution of the underlying causes of conflict in a region marked by more than a generation of competition between them.

  14. 基于遗传算法的导弹编队攻击任务优化分配策略%Strategy of Task Optimization Allocation for Missile Group-attack Based on Genetic Algorithm

    Institute of Scientific and Technical Information of China (English)

    白军; 刘新学; 郭峰; 高娟

    2011-01-01

    导弹编队攻击目标时,在确定打击目标和需求导弹数量后,如何把发射任务科学合理、高效地分配给相应的发射器,完成对目标的打击,在控制自身火力消耗最小的情况下实现作战效能最大是一个组合优化问题。针对导弹编队攻击任务分配问题,提出了基于遗传算法的优化分配策略。在理论上为常规导弹编队攻击目标时任务分配提供策略支持,对提高导弹部队任务分配决策能力和作战效能具有实际意义。%While missile group-assault target after determining the attack target and the number of needed missile,how to allocate the launch task to launcher in scientific,reasonable and efficient pattern so as to complete the attack for target is a combination optimization problem that makes operation effect be maximum under the condition of minimum in controlling itself force consumption.Aimed at the puzzle of task allocation in missile group-assault,the paper proposed the optimization strategy based on genetic algorithm.It can theoretically provide the strategy support for task allocation while missile group-assault target,and it is of actual significance to improve the efficiency of decision making and missile launching.for conventional missile troops.

  15. NATO Missile Defense and the European Phased Adaptive Approach: The Implications of Burden Sharing and the Underappreciated Role of the U.S. Army

    Science.gov (United States)

    2013-10-01

    sys- tem. For example, Germany hosts a NATO BMD cell at Ramstein Air Base. The BMD cell’s multinational staff is currently 10 strong, with a plan to...contributions by the European allies, assuming complete coverage of allied territory is the objective.106 But part may also stem from the need to...Missile Defense Conference, Tel Aviv, Israel, July 25, 2011,” available from www.state.gov/t/ avc /rls/169023.htm. 103. Interview with two U.S. officials

  16. GPS轨迹测量系统在导弹飞行试验中的应用%Application of GPS trajectory measurement system in missile flight test

    Institute of Scientific and Technical Information of China (English)

    李东; 黄信安

    2014-01-01

    In the process of air-to-air missile development,a serial of tethered flight test must be done to improve the capa-bility of capturing and tracking the real goal of missile guidance system. The traditional tethered flight test results in great uncer-tainty for the flight test results because the test personnel on ground can not grasp the dynamic status of the drone aircraft in real time. With GPS widely used in the system,the target aircraft′s position and speed relative to fighter plane are calculated in com-bination the GPS information received from the airborne missile and target GPS pod,and displayed in the data processing soft-ware,so that the test personnel on ground obtain the relevant information of fighter plane and drone aircraft in real time and pro-vide reliable data for the test command. The practical application result shows that this system can greatly improve the success rate and the missile interception probability,and save the time and fund of the test.%空空导弹研制需要一系列空中系留飞行试验,以解决导弹制导系统对真实目标的截获跟踪能力。传统的系留试验由于地面试验人员无法实时掌握靶机和目标机的动态,给飞行试验结果造成了很大的不确定性;本系统利用日益广泛使用的GPS全球定位技术,从载机的导弹产品和目标机GPS吊舱接收下传的GPS信息,实时解算出目标机相对于载机位置、速度等信息,显示在数据处理软件上,从而使地面试验人员实时获取载机和目标机的相关信息,为试验指挥提供了可靠数据;实际应用结果表明,该系统大大提高了系留试验的成功率和导弹截获概率,为飞行试验节约了试验经费和时间,创造了良好的经济效益。

  17. 大攻角导弹控制的经典和现代方法比较%Comparisons on Classic and Modern Controls for High AOA Missiles

    Institute of Scientific and Technical Information of China (English)

    宋雪海; 侯明善; 熊飞

    2011-01-01

    Comparisons on precision and robustness of classic and modern controls for high Angle-of-Attack (AOA) are presented. Based on the nonlinear characteristics of the high AOA missile, two kinds of missile longitudinal autopilot are designed using classical three-loops configuration and dynamic inversion embedded pole placement technique respectively. Study on their command tracking precision and robustness have been conducted. It's proved by simulation that classic and modern controls are nearly identical in either rapidity of response or robustness, but modern control can obtain better tracking precision.%比较研究了大攻角导弹的经典和现代控制方法的精度和鲁棒性.基于大攻角非线性弹体动力学模型,根据经典三回路控制系统结构和动态逆双时标极点配置方法分别设计了控制器,研究了两种控制方法的指令跟踪精度和抗弹体气动参数摄动的鲁棒性.结果表明,传统控制方法的鲁棒性和快速性与现代方法基本一致,而现代方法则具有更好的稳态精度.

  18. Departures from plane-wave-like coupling to a Maverick missile in the radiating near-field region of a horn antenna

    Science.gov (United States)

    Voss, D. E.; Koslover, R. A.; Cremer, C. D.; Silvestro, J.; Miner, L. M.

    1990-05-01

    The High Power Microwaves (HPM) susceptibility testing often requires irradiating test objects at the highest fluences possible. For aperture antennas, the highest fluences are generally found in the radiating near field region. For valid effects testing, the energy coupled to the object interior must accurately replicate that which would occur in a true weapon environment (plane wave illumination). Some believe that valid testing requires object placement at distances from the aperture exceeding 2 D squared/lambda (D=antenna effective diameter). Many also believe testing at farther away than 2 D squared/lambda guarantees plane wave-like coupling conditions. Neither view is correct. Testing in the reactive field region (less than lambda from the aperture) is generally invalid due to dominance of reactive coupling. For testing in the radiating near field, determination of validity is less trivial. An investigation was performed quantifying deviations from plane wave coupling. The measurements, using an instrumented Maverick missile in an anechoic chamber, and supported by theory, indicate conditions for which testing the Maverick missile accurately simulates plane wave coupling.

  19. Radiological survey and evaluation of the fallout area from the Trinity test: Chupadera Mesa and White Sands Missile Range, New Mexico

    Energy Technology Data Exchange (ETDEWEB)

    Hansen, W.R.; Rodgers, J.C.

    1985-06-01

    Current radiological conditions were evaluated for the site of the first nuclear weapons test, the Trinity test, and the associated fallout zone. The test, located on White Sands Missile Range, was conducted as part of the research with nuclear materials for the World War II Manhattan Engineer District atomic bomb project. Some residual radioactivity attributable to the test was found in the soils of Ground Zero on White Sands Missile Range and the areas that received fallout from the test. The study considered relevant information including historical records, environmental data extending back to the 1940s, and new data acquired by field sampling and measurements. Potential exposures to radiation were evaluated for current land uses. Maximum estimated doses on Chupadera Mesa and other uncontrolled areas are less than 3% of the DOE Radiation Protection Standards (RPSs). Radiation exposures during visits to the US Army-controlled Ground Zero area are less than 1 mrem per annual visit or less than 0.2% of the RPS for a member of the public. Detailed data and interpretations are provided in appendixes. 14 figs., 45 tabs.

  20. Index Method for Evaluating the Fighting Ability of Missile Weapons%导弹武器战斗能力评估的指数方法

    Institute of Scientific and Technical Information of China (English)

    邓昌; 汪民乐; 谢涛

    2011-01-01

    根据导弹武器战斗能力量化评估的需要,分析了导弹武器战斗能力的影响因素,运用量纲分析理论,分层次建立起了战斗能力指数评定模型,并对各子指标的量化进行了分析.以这种评价方法得到的"指数",反映问题直观、简单,适合于敌我双方实力的对比,并且与指挥员习惯相一致.%According to the need of evaluating the fighting ability of missile weapons, the factors related to fighting ability of missile weapons are analyzed. By using the theory of dimensional analysis, a fighting ability assessment model, index model, is given and the quantitative analysis of each subindex is also briefly introduced. The index obtained by this kind of method reflects problems easily and visually. It is suitable for comparing the power of both sides in battle and keeping pace with the habits of commanders.

  1. Ometanje radarskih glava za samonavođenje amplitudno modulisanom metodom ometanja "cross eye" / Monopulse homing missile jamming with the amplitude modulated cross eye method

    Directory of Open Access Journals (Sweden)

    Bojan Milanović

    2008-07-01

    Full Text Available U radu je prikazan uticaj metode ometanja "Cross eye" na uspešno vođenje rakete monoimpulsnom radarskom glavom za samonavođenje. Analiza dobijenih rezultata pokazala je: da se maksimalna greška određivanja položaja cilja postiže kada ometači emituju koherentne signale čija je fazna razlika 180°, da je greška veća što je međusobno rastojanje između antena ometača veće, da je, suprotno očekivanju, efikasnost ometanja veća što je rastojanje između ometača i rakete koja se ometa manje. / This article shows the effect of the "Cross eye" jamming method on successful guidance of monopulse homing missiles. The analysis of the results has shown that the maximal tracking error is made if the jamming signals are coherent and out of phase, that a larger distance between jamming antennas causes a greater error, and that, opposite to expectations, a smaller distance between the jammer and the missile results in better jamming effects.

  2. 基于共生仿真的巡航导弹协同作战研究%Research on symbiotic simulation based cruise missile collaborative engagement

    Institute of Scientific and Technical Information of China (English)

    吴红; 杨峰; 王维平

    2012-01-01

    In order to response to complex and diverse battlefield environment, cruise missile needs to carry out task through dynamic collaboration. Nowadays, domestic and international researches which focus on cruise missile collaborative engagement have presented some dynamic cooperative modes, but all they have several drawbacks to some extent. Because of this, this paper puts forward a limited autonomy of central control of distributed collaboration, designs system business logic and analyzes system function in detail, then uses it as the background to carry out system architecture design of remote control collaboration based on symbiotic simulation.%为了应对体系对抗过程中复杂多变的战场环境,巡航导弹需通过动态协同执行作战任务.目前,国内外在巡航导弹协同作战的研究过程中,提出了几种动态协同模式,但都在一定程度上存在局限性.基于此,首先提出有限中央控制的分布式自主协同,对其系统业务逻辑进行了详细的设计和系统功能进行了详细的分析,并以此为背景开展基于共生仿真的远程控制协同系统体系结构设计.

  3. Study on Emergency Measures for Nuclear Accident of Missile Nuclear Weapon%导弹核武器核事故应急有关问题研究

    Institute of Scientific and Technical Information of China (English)

    高桂清; 毕义明

    2001-01-01

    The major task, characteristics, organizing and commending, and resource manipulation of the emergency measures for nuclear accident of missile nuclear weapon are probed into. The measures may be considered as a complex system engineering involving system of organization, personnel, equipment, technique and scientific theory, so on. Relevant problems of emergency measures are deliberately studied referring the practical situations. The results could provide the theoretical guidance to emergency measures for nuclear accident of missile nuclear weapon.%对导弹核武器核事故应急的主要任务、特点、组织指挥以及力量运用等问题进行了探讨,导弹核武器核事故的应急问题是一项涉及体制、人员、装备、技术、科学理论等方面的复杂系统工程,笔者结合实际,有针对性的研究了事故应急有关的问题,可为导弹核武器核事故应急提供理论指导。

  4. 大型导弹车工作模态识别研究及应用%Research and application on the operational modal identification of large missile launch vehicle

    Institute of Scientific and Technical Information of China (English)

    赵威; 张永杰; 王喆; 韦冰峰

    2013-01-01

    To solve some problems of the operational modal identification of large missile launch vehicle, a model reflecting the main dynamic characteristics of large missile launch vehicle was made. Modal experiments were conducted and dynamic characteristics of the model were identified using the Least Square Complex Exponent (LSCE) method. Modal identification results were compared and analyzed to evaluate the LSCE method. It was applied to the operational modal identification of large missile launch vehicle. It is of significance to provide references for the dynamic characteristics analysis of large missile launch vehicle.%针对大型导弹车在运输状态下的动态特性识别问题,设计制作了能够反映大型导弹车主要动力学特征的简化模型,使用最小二乘复指数法(LSCE)对简化模型进行了动态特性识别,对识别结果进行了分析和评估,并将最小二乘复指数法应用到真实大型导弹车运输状态的模态识别中。可为大型导弹车运输状态下的动力学特性分析提供参考。

  5. 美军舰空导弹协同制导技术及其能力分析%Analysis of Cooperative Guidance Technology of US Navy Ship-to-Air Missile and Its Capability

    Institute of Scientific and Technical Information of China (English)

    王国田; 王航宁; 石章松

    2012-01-01

    介绍了美军舰空导弹协同制导的发展概况。阐述了标准6导弹的协同制导作战流程,分析了舰空导弹协同制导技术的能力,以及实现协同制导的关键技术。协同制导为舰空导弹实现超视距拦截创造了条件,可提高系统的作战效能和可靠性。%The development survey of US navy ship-to-air missiles cooperative guidance was introduced in this paper.The cooperative guidance operational flowchart of SM-6 missile was presented.The capabilities of the cooperative guidance technology for ship-to-air missile and main key technologies for its implement were analyzed.The cooperative guidance would create the conditions for beyond-visual-range interception of ship-to-air missile,which could improve the combat effectiveness and reliability of the weapon system.

  6. Assessment of equipment operation network capability based on the anti-missile operation loops%基于反导作战环的装备作战网络能力评估

    Institute of Scientific and Technical Information of China (English)

    芦荻; 商慧琳

    2016-01-01

    考虑到以往装备体系的研究方法忽略了装备之间的配合关系,基于网络科学思想,建立反导作战网络模型。阐明了反导作战能力生成机制,并基于此提出了反导装备体系作战网络能力评估方法,最后通过示例对所提出的建模和评估方法进行展示,证明了该方法的可行性和有效性。%Considering the interactions between equipment that have been neglected in the earlier research on equipment system-of-systems, an exploration based on networks science is conducted. The paper presents a model of anti-missile operation network and illustrates the generation progress of anti-missile operation capability, based on which a capability assessment method of anti-missile equipment system-of-systems is examined. An example of anti-missile operation network is demonstrated to illuminate the feasibility and validity of the proposed method.

  7. The Peak of Rocket Production: The Designer of Ballistic Missiles V.F. Utkin (1923-2000)

    Science.gov (United States)

    Prisniakov, V.; Sitnikova, N.

    2002-01-01

    The main landmarks of the biography of the general designer of the most power missiles Vladimira Fe- dorovicha Utkina are stated. Formation of character of outstanding scientist of 20 century as the son of the Soviet epoch is shown. He belongs to that generation which had many difficulties and afflictions - hungry time, the heavy years of the second world war, post-war disruption, but also many happy days - the Victory above fascism, restoration of the country, pride of successes in conquest of Space. In June, 1941 Vladimir has finished school with honours certificate and since October, 1941 up to the end of the second world war was on various fronts. After the ending of Leningrad military-mechanical insti- tute the young engineer came in Southern engineering works in Dnipropetrovsk (Yugmach). Here for 40 years there was a dizzy ascent of the beginner-designer over a ladder of space-rocket's Olympus up to the chief designer and the general director of the biggest in the world of rocket concern (9000 high quality engineers of Design office Yugnoe (DOYu) and 60 thousand workers Yugmach). After death in 1971 to year of main designer M. Jangele V. F. Utkin has headed Design office Yugnoe. Under ma- nual of V. Utkin four strategic rocket complexes of new generation SS-17, SS-18 (three updatings with divided head parts with weight of 8 tons), SS-24 (railway and shaft basing) were developed and han- ded over on arms. Among development of academician V. Utkin there is a rocket-carrier "Zenit" which delivers to an orbit over 12 tons of a payload. This rocket is also a basis of the first stage of reusable transport space system "Energia-Buran". Under manual of V. Utkin were developed and used the con- version carrier-rockets "Ziclon" and "Kosmos", as well the effective satellites of a defensive, scientific and economic direction, among which family of satellites "Kosmos", the satellite "Ocean", equipped by a locator of the side observation too. Largest scientific

  8. Real-time simulation of missile efflux plasma based on Vega Prime & OpenGL%Vega Prime结合OpenGL的导弹尾焰实时模拟

    Institute of Scientific and Technical Information of China (English)

    李威; 杨峰; 程咏梅; 杨衍波

    2012-01-01

    It researches missile operational system simulation experiment, in view of the problem that when using Vega Prime' s particle system module for the simulation of missile efflux plasma which is moving with high speed, the particles are discrete that impact the simulation visualization effect. In order to solve the missile efflux plasma simulation problem, it proposes the solution that using Vega Prime together with OpenGL. It models the missile efflux plasma based on the particle system principle, applies OpenGL into Vega Prime according to the event issued subscription mechanism of Vega Prime. The efflux plasma that simulated by the proposed method is shape lifelike and sporty. It meets the demands of the instantaneity and authenticity in the simulation and solves the defect of simulating missile efflux plasma by Vega Prime.%研究基于Vega Prime的导弹作战系统仿真实验,针对使用Vega Prime的粒子特效模拟高速飞行导弹尾焰会出现尾焰不连续而影响仿真可视化效果的问题,提出将Vega Prime与OpenGL相结合的方法.基于粒子系统基本原理,对导弹尾焰进行建模;依据Vega Prime的事件发布订阅机制将OpenGL引入到Vega Prime中.模拟的尾焰形态逼真,动感十足,满足仿真实时性与真实性要求,解决了Vega Prime模拟导弹尾焰存在缺陷的问题.

  9. 弹道导弹SINS/CNS 组合导航系统建模与性能仿真%System Modeling and Performance Simulation on SINS/CNS Integrated Navigation System for Ballistic Missile

    Institute of Scientific and Technical Information of China (English)

    王鑫; 王新龙

    2015-01-01

    Combined with the characteristics of ballistic missile and the model error caused by uncer-tain noise characteristics in engineering practice, this paper proposes a SINS/CNS integrated navigation system suitable for ballistic missiles.This system, integrated some characteristics of simple combination models and overall optimal correction combination models, uses the adaptive Kalman filtering to ensure the stability and robustness of the filter.In the simulation, according to the missile trajectory, it establi-shes a reasonable, complete guide star catalog of missile.The simulation illustrates that this navigation scheme can improve the precision of navigation parameters of ballistic missile.%针对弹道导弹在工程实际中噪声特性的不确定性及其引起的模型误差,本文提出了一种适用于弹道导弹的 SINS/CNS 组合导航方案。该方案融合了简单组合模式和基于全面最优校正的组合模式特点,采用自适应卡尔曼滤波来保证滤波的稳定性和鲁棒性,并根据导弹的飞行弹道,建立了合理、完备的弹载导航星表。仿真验证结果表明,该导航方案可以达到全面提高弹道导弹导航参数精度的目的。

  10. 歼击机拦截巡航导弹拦截阵位研究%Research of Lineup of Heading off of Fighter Plane Heading off Cruise Missile

    Institute of Scientific and Technical Information of China (English)

    高晓冬; 于嘉晖; 吴杰; 吕超

    2013-01-01

    为研究歼击机拦截巡航导弹时的拦截阵位问题,构建了歼击机拦截阵位模型。在分析歼击机拦截来袭巡航导弹过程的基础上,根据歼击机的运动模型和歼击机接敌方法,确定了拦截阵位相关参数,并以机载导弹对巡航导弹杀伤概率为目标函数进行仿真研究。仿真结果找出了一定条件下歼击机的最优航向前置角范围,为反巡航导弹作战理论研究提供了参考。%For researching the lineup of the fighter plane heading off the cruise missile, the model of the fighter plane heading off the cruise missile lineup is established. Based on analyzing the process of the fighter plane heading off the cruise missile, the parameters of the lineup is confirmed according to the movement model and the adjacency enemy method of the fighter plane. Aiming at the probability of killing the cruise missile, the simulation is carried out. The best course pre-positive-angle range is found, which makes reference for the theory of the fighter plane heading off the cruise missile.

  11. 导弹虚拟战场环境设计与实现%Design and Implementation of A Missile's Virtual Battlefield Environment

    Institute of Scientific and Technical Information of China (English)

    赵海龙; 李佳泽; 郑重; 李朋飞

    2012-01-01

    为给某型导弹部队提供一个全新的演习、训练和战前要素熟悉平台,文中通过VC++6.0和该实验室自行开发的软件Deep Eye平台设计和实现了导弹虚拟战场环境演示系统.首先根据系统分析对系统整体结构进行了模块化设计,然后从场景生成和效果实现两方面对各模块进行开发,先后建立了天空模型、地形背景模型、战场实体模型,并对地形匹配、航迹规划、特殊效果实现、视点变换、交互接口设计等关键技术做了研究,最后实现了适合于导弹作战的虚拟战场环境模型.结果表明,该设计方案可行,仿真效果良好.%To give a certain type of missile units for a new exercise,training and pre-war elements familiar platform,the missile's virtual battlefield environment demo system is designed and achieved on VC++6.0 and Deep Eye in this paper. The system overall structure is a-dopted modular design according to the system analysis, and then from two aspects of the modular design scene generation and effect each module is developed,has established a model of the sky,the terrain background model,battlefield solid model and the key technology such as terrain matching,path planning,special effects to achieve, the focus transformation and interactive interface are researched. At last,achieve a suitable model of the virtual battlefield environment for missile combat. The results shows that the design scheme is feasible and the simulation result is good.

  12. Robust Terminal Guidance Law for Air-to-Air Missile of Adjustable Velocity%速度可调空空导弹鲁棒末制导律

    Institute of Scientific and Technical Information of China (English)

    史鲲; 梁晓庚

    2013-01-01

    针对采用变流量固体火箭冲压发动机的空空导弹速度可调的特点,提出了一种非线性鲁棒末制导律.将弹目相对速度与视线角速度一起作为被控状态,基于准平行接近原理,通过选择合适的李雅普诺夫函数,在保证了制导系统大范围渐近稳定的同时,结合非线性H∞鲁棒控制理论,推导出了鲁棒末制导律的表达式.数字仿真结果表明,该制导律不仅对目标的大范围机动具有较强的鲁棒性,命中精度较高,并且与传统末制导律相比,能够明显缩短导弹拦截时间,具有较大优势.%According to adjustable character of the velocity of air-to-air missile with variable-flow ducted rockets,a nonlinear terminal guidance law with robustness was proposed.The relative velocity of the missile and the target was taken as controlled state as well as the line-of-sight angular-velocity.Based on the principle of quasi constant bearing navigation,a proper Lyapunov function was chosen.The global asymptotic stability of the guidance system was ensured,and the expression of the robust terminal guidance law was obtained by means of the nonlinear H∞ robust control theory.Simulation results show that,for the missile intercepting a target with high maneuverability,the proposed terminal guidance law not only has strong robustness and excellent guidance precision,but also can shorten the interception time compared with the traditional one.

  13. Missile Maintenance Career Ladder

    Science.gov (United States)

    1994-01-01

    K696 INSPECT GENERAL PURPOSE EQUIPMENT 48 E176 LOCATE INFORMATION IN TOs 44 F235 PERFORM PREOPERATIONAL CHECKS ON MECHANICAL 42 MAINTENANCE SUPPORT...ON COLORIMETRIC GAS DETECTORS 24 27 TABLE 9 REPRESENTATIVE TASKS PERFORMED BY 2M052A PERSONNEL PERCENT MEMBERS PERFORMING TASKS (N=436) E176 LOCATE...AS STAFF MEETINGS, 67 BRIEFINGS, CONFERENCES, OR WORKSHOPS B30 CONDUCT PERFORMANCE FEEDBACK WORKSHEET SESSIONS 64 E176 LOCATE INFORMATION IN TOs 57

  14. Ballistic & Cruise Missile Threat

    Science.gov (United States)

    2013-01-01

    parade in 2009 and is currently deployed with the Second Artillery Corps. lacm Torgos MUPSOW SS-N-21 AS-4 AS-15 APACHE Popeye Turbo Storm Shadow...less than 300 2013+ ISRAEL Popeye Turbo Air Conventional 300+ 2002 PAKISTAN RA’AD Air Conventional or nuclear 350 Undetermined Babur Ground

  15. Tactical Missile Conceptual Design,

    Science.gov (United States)

    1980-09-01

    isa plot of these values. The wing alone lift curve slope, (C L) is determined from thin airfoil theory or experiment. The lift curve slope of delta...x rtU to Go M t* C3 Q -i 0 co zo La o r, F.to to C V. C4 . . .C~ .. . . . . . . . . . 3: r 8 11 r- r4- .4.r1.4.4 r Go co co Go c o 000 cc I -V to go

  16. Feature extraction of micro-motion frequency and the maximum wobble angle in a small range of missile warhead based on micro-Doppler effect

    Science.gov (United States)

    Li, M.; Jiang, Y. S.

    2014-11-01

    Micro-Doppler effect is induced by the micro-motion dynamics of the radar target itself or any structure on the target. In this paper, a simplified cone-shaped model for ballistic missile warhead with micro-nutation is established, followed by the theoretical formula of micro-nutation is derived. It is confirmed that the theoretical results are identical to simulation results by using short-time Fourier transform. Then we propose a new method for nutation period extraction via signature maximum energy fitting based on empirical mode decomposition and short-time Fourier transform. The maximum wobble angle is also extracted by distance approximate approach in a small range of wobble angle, which is combined with the maximum likelihood estimation. By the simulation studies, it is shown that these two feature extraction methods are both valid even with low signal-to-noise ratio.

  17. Influence of seeker disturbance rejection rate on missile guidance system%平台导引头隔离度对导弹制导系统影响

    Institute of Scientific and Technical Information of China (English)

    宋韬; 林德福; 王江

    2013-01-01

    Spring torque and damping torque are two main factors which cause seeker disturbance rejection rate problems, for studying the influence of seeker disturbance rejection rate on the guidance system of missile, a model of the guidance system which contains seeker disturbance rejection rate parasitical loop was established; the rela-tionship between the disturbance rejection rate and the stabilization of the guidance system was analyzed on basis of the model;under the typical noise input condition of radar seeker, the simulation gave the miss distances of missile corresponding to different seeker disturbance rejection rates. The results show that the guidance system parameters greatly affect the parasitical loop stability zone; the larger the disturbance rejection rate caused by spring torque, following the reduction of the distance between missile and target, the earlier the radiation of the guidance system. The larger the disturbance rejection rate caused by damping torque, the later the radiation of the guidance system;under the condition of seeker noise input, the larger the disturbance rejection rate caused by spring torque, the lar-ger the miss distance. The larger the disturbance rejection rate caused by damping torque, the smaller the miss dis-tance. The conclusion may provide theoretical instruction for the general missile design and the demonstration for the relevant indices of seeker.%弹簧力矩和阻尼力矩是平台导引头产生隔离度问题的主要因素,为了研究平台导引头隔离度对导弹制导系统的影响,建立了包含隔离度寄生回路的制导系统模型;在此模型的基础上,分析了隔离度与制导系统稳定性的关系;在雷达导引头典型噪声输入条件下,仿真得出了不同隔离度时对应的导弹脱靶量。结果表明:制导系统主要参数的变化会引起隔离度寄生回路稳定域的变化;弹簧力矩引起的隔离度越大,随着弹目距离接近制导系统越早

  18. 弹载计算机CPU数字模型系统开发%CPU Numerical Model System of the Embedded Computer in Airborne Missile

    Institute of Scientific and Technical Information of China (English)

    罗阳; 侯俊刚

    2012-01-01

    提出弹载计算机数字模型系统的研制需求,在此基础上,分析了该系统的功能组成,然后从COFF文件解析、DSP软核、指令解析执行三个方面详细介绍了该系统的具体开发过程,最后给出应用结论。%The studying demand of numerical model system of the embedded computer in airborne missile is adverted in this article. On basis of this, the system composition is analyzed, and the develop- ment process of the numerical model system is introduced particularly in three ways, that is analysis of COFF file, DSP soft core and parsing command execution. Lastly, the applied conclusion is gained.

  19. A Flight Investigation of the Damping in Roll and Rolling Effectiveness Including Aeroelastic Effects of Rocket Propelled Missile Models Having Cruciform, Triangular, Interdigitated Wings and Tails

    Science.gov (United States)

    Hopko, R. N.

    1951-01-01

    The damping in roll and rolling effectiveness of two models of a missile having cruciform, triangular, interdigitated wings and tails have been determined through a Mach number range of 0.8 to 1.8 by utilizing rocket-propelled test vehicles. Results indicate that the damping in roll was relatively constant over the Mach umber range investigated. The rolling effectiveness was essentially constant at low supersonic speeds and increased with increasing mach numbers in excess of 1.4 over the Mach number range investigated. Aeroelastic effects increase the rolling-effectiveness parameters pb/2V divided by delta and decrease both the rolling-moment coefficient due to wing deflection and the damping-in-roll coefficient.

  20. Determining the Probability of Violating Upper-Level Wind Constraints for the Launch of Minuteman Ill Ballistic Missiles At Vandenberg Air Force Base

    Science.gov (United States)

    Shafer, Jaclyn A.; Brock, Tyler M.

    2013-01-01

    The 30th Operational Support Squadron Weather Flight (30 OSSWF) provides comprehensive weather services to the space program at Vandenberg Air Force Base (VAFB) in California. One of their responsibilities is to monitor upper-level winds to ensure safe launch operations of the Minuteman Ill ballistic missile. The 30 OSSWF requested the Applied Meteorology Unit (AMU) analyze VAFB sounding data to determine the probability of violating (PoV) upper-level thresholds for wind speed and shear constraints specific to this launch vehicle, and to develop a graphical user interface (GUI) that will calculate the PoV of each constraint on the day of launch. The AMU suggested also including forecast sounding data from the Rapid Refresh (RAP) model. This would provide further insight for the launch weather officers (LWOs) when determining if a wind constraint violation will occur over the next few hours, and help to improve the overall upper winds forecast on launch day.