Research on Divert and Attitude Control System Technology of Ballistic Missile Midcourse Maneuver Penetration Warhead

Chenchao Dai; Hongfu Qiang; Xueren Wang

doi:10.54097/fcis.v3i1.6342

Authors

Chenchao Dai
Hongfu Qiang
Xueren Wang

DOI:

https://doi.org/10.54097/fcis.v3i1.6342

Keywords:

Autonomous maneuver penetration, Midcourse intercept, Kinetic kill vehicle, DACS, Gas valve

Abstract

With the continuous development of American midcourse interception technology, it is particularly important to promote the midcourse penetration capability construction of ballistic missiles. The use of maneuver penetration technology in the midcourse of ballistic missiles can effectively deal with the midcourse interception of foreign missiles. In order to promote the development of midcourse maneuver penetration technology, this paper takes the Divert and Attitude Control System (DACS) of maneuver penetration warhead as the starting point, refers to the development of DACS of Kinetic Kill Vehicle in the United States, and summarizes the research status of gas valve, the key structure of DACS. On this basis, combined with the structural characteristics of maneuver penetration warhead, the key technologies related to the construction of DACS of penetration warhead are summarized, which lays a foundation for the development of DACS of penetration warhead in the future.

Downloads

Download data is not yet available.

References

Qin Z J, Zhang Z M. Topol-M intercontinental ballistic missile of Russia [J]. Missiles and Space Vehicles, 2001 (01): 55-62.

Li L. Research on maneuver penetration of ballistic missile warhead [D]. Harbin Institute of Technology, 2011.

Wang Y Q, Ning G D, Wang X F, et al. Maneuver penetration strategy of near space vehicle based on differential game [J]. Acta Aeronautica ET Astronautica Sinica, 2020, 41 (S2): 69-78.

Wen D Y. Development status of orbit transfer and attitude control system for kinetic energy weapons in the United States [J]. Modern Defense Technology, 1995 (04): 32-37.

Wen D. The Development Status of US Kinetic Weapon Divert and Attitude Control System[J]. Modern Defense Technology, 1995(04):32-37.

Webber T E. GROUND TESTING KINETIC ENERGY PROJECTILES FOR THE LIGHTWEIGHT EXOZTMOSPHERIC PROJECTILE (LEAP) PROGRAM[J]. 2011.

Weiss A. Status of the first LEAP space flight test[J]. International Journal of Social Economics, 2013,37(October):951-969.

Smith F, Camp D J, Leister K K. Lightweight Exo-Atmospheric Projectile Space Test--LEAP 2 Flight[J]. aiaa journal, 1992.

Baker P, Funari A. Army Lightweight Exo-Atmospheric Projectile (LEAP)[J]. Aiaa Journal, 1992.

Ceng P, Zhong L W, Xiao L J, et al. Development status and trend of divert and attitude control power system of kinetic energy weapons abroad: 37th Technical Exchange Conference of China Aerospace Third Professional Information Network and 1st Joint Conference of Aerospace Power, Xi'an, Shaanxi, China, 2016 [C].

Zhang D X and Wang Z B. Solid propellant divert control and attitude control system of KKV [J]. Winged Missiles Journal, 2001 (02): 37-41.

Coon J, Yasuhara W. Solid propulsion approaches for terminal steering[J]. AIAA and SDIO, 2nd Annual Interceptor Technology Conference, 1993.

Prins W, Spencer A, Roberts J. SM-3 SDACS Flight Test Successes: 39th AIAA Joint Propulsion Conference, Huntsville, Alabama, 2003[C].

Xu D D, Kou Y, Wang J Y, et al. Research on American Solid Divert and attitude control Thrust System Technology [J]. Winged Missiles Journal, 2015 (07): 64-70.

Zhang Y, Ceng P, Zhong L W, et al. Research on Standard-3 Missile Solid Rocket Motor: 38th Technical Exchange Conference of China Aerospace Third Professional Information Network and 2nd Joint Conference on Aerospace Power, Dalian, Liaoning, China, 2017 [C].

Hou X, Fu P, Wu Y. Energy management technology of solid rocket motor and its new progress [J]. Journal of Solid Rocket Technology, 2017, 40 (01): 1-6.

Morrow D, Mcallister P, Evans R. High-performance graphite thruster valve system using a 4500 deg solid propellant gas generator: 9th Propulsion Conference, 1973[C].

Morrow D, Scottsdale A. Valve:

West L, Carlson R. Solid Divert Breakthroughs that Enable Mission Flexible TMD Interceptors[J]. Solid Divert Breakthroughs That Enable Mission Flexible Tmd Interceptors, 1998.

Napior J, Garmy V. Controllable Solid Propulsion for Launch Vehicle and Spacecraft Application, 2006[C].

Cover C L, Drendel A S. Rocket thruster comprising load-balanced pintle valve:

Yang Z. Research on solid attitude control system of KKV [D]. Beijing Institute of Technology, 2015.

Lu J, Li X H. Application Research of Negative Pressure Index Propellant in Solid Divert and attitude control system: The Third China Aerospace Propulsion Technology Forum, 2020 [C].

Wang Y L. Experimental study on the principle of pintle variable thrust solid motor [D]. Northwestern Polytechnical University, 2007.

Wei X G, He G Q, Li J, et al.Pressure response analysis of non-coaxial pintle variable thrust engine [J]. Journal of Solid Rocket Technology, 2009, 32 (04): 409-412.

Wu Y, He G Q, Sun L G, et al. Interior ballistic regulation characteristics of pintle variable thrust solid rocket motor [J]. Journal of Solid Rocket Technology, 2009, 32 (05): 511-513.

Li J, Wang Z L, Zheng K, et al. Numerical analysis of dynamic response characteristics of thrust adjustable solid rocket motor with pintle [J]. Journal of Solid Rocket Technology, 2009, 32 (01): 48-52.

Hua L H, Tian W P, Gan X S, et al.Numerical simulation of nozzle flow field of thrust adjustable thrust engine with pintle [J]. Journal of Solid Rocket Technology, 2008 (04): 344-349.

Cheng C. Thrust control method and performance simulation research of pintle solid variable thrust motor [D]. Northwestern Polytechnical University, 2017.

Wang J X, Wei Z J, Wang N F. Study on unsteady influencing factors of variable thrust solid rocket motor [J]. Transactions of Beijing Institute of Technology, 2011, 31 (09): 1018-1022.

Wang J X, Wei Z J, Wang N F. Test of pintle variable thrust solid rocket motor with high combustion temperature [J]. Journal of Propulsion Technology, 2012, 33 (01): 89-92.

Wang J X, Wei Z J, Wang N F. Analysis of influencing factors of pressure response rate of pintle engine [J]. Science & Technology Review, 2012, 30 (02): 18-21.

Huang P Q. Why did the United States Department of Defense replace MK12A with ABRV to equip MX missile [J]. Foreign Missile Technology, 1985 (03): 14-22.

Wu Q X, Zhang W H. Research on Midcourse Maneuver penetration of Ballistic Missile [J]. Journal of Astronautics, 2006 (06): 1243-1247.