Design of Midcourse Trajectory for Tactical Ballistic Missile Intercept on the Basis of Zero Effort Miss

Abstract:

Since the maneuverability of the tactical ballistic missile, the midcourse trajectory of interception missile needs design online. Firstly, this paper reasonably simplifies the models and explores the analytical expressions of their relative motion state to obtain a kind of rapid and high-precision computing method of zero effort miss. Secondly, it applies constant thrust for the interception missile, burns out shut-down solid engine, reflects on the index requirement of overloaded interception missile, and designs midcourse trajectory of the interception missile with Pontryagin maximal principle, in accordance with the analytical expressions of zero effort miss. Finally, with the simulating calculation, the prediction methods of zero effort miss and trajectory design method provided by this paper are applied to a situation simulation which is close to the fact as much as possible so as to verify the applicability in the interception of tactical ballistic missile.

• Periodical: Applied Mechanics and Materials (Volumes 397-400)
• Pages: 536-545
• DOI: https://doi.org/10.4028/www.scientific.net/AMM.397-400.536
• Online since: September 2013
• Authors: Luo Gang Li, Wu Xing Jing, Chang Sheng Gao
• Keywords: Analytical Solution, Interception, Tactical Ballistic Missile, Trajectory Design, Zero Effort Miss

References

[1] Song Eun-Jung. Three-dimensional midcourse guidance using neural networks for interception of ballistic targets[J]. IEEE Transactions on Aerospace and Electronic Systems, 2002, 38 (2): 404-414.

DOI: 10.1109/taes.2002.1008975

[2] Hull, David G. Missile sizing for ascent-phase intercept[J]. Journal of Spacecraft and Rockets, 1995, 32(3): 445-449.

DOI: 10.2514/3.26635

[3] Shinar, J. Nonorthodox guidance law development approach for intercepting maneuvering targets[J]. Journal of Guidance, Control, and Dynamics, 2002, 25(4): 658-666.

DOI: 10.2514/2.4960

[4] Yeh, Fu-Kuang. Design of optimal midcourse guidance sliding-mode control for missiles with TVC[J]. IEEE Transactions on Aerospace and Electronic Systems, 2003, 39(3): 824-837.

DOI: 10.1109/taes.2003.1238739

[5] Shtessel, Yuri B. Smooth second-order sliding modes: Missile guidance application[J]. Automatica, 2007, 43(8): 1470-1476.

DOI: 10.1016/j.automatica.2007.01.008

[6] Newman B． Spacecraft intercept guidance using zero effort miss steering[R]． AIAA 93-3890，(1993).

DOI: 10.2514/6.1993-3890

[7] Newman B． Robust conventional based midcourse guidance for spacecragt intercept[C]． The Amarican Control Confence，Seattle，Washington，June (1995).

[8] Newman B． Strategic intercept midcourse guidance using modified zero effort miss steering[J]． Journal of Guidance，Control，and Dynamics，1996，19(1): 107-112.

DOI: 10.2514/3.21586

[9] LIU Shi-yong. Research on Midcourse Guidance for Fue-Exhaustion-Shutoff exo-Atmospheric Interceptor [J]. Yuhang Xuebao/Journal of Astronautics, v 26, n 2, pp.156-163.

[10] Zheng, Li-Wei; Jing, Wu-Xing; Zhang. Zero effort miss formulation for longer range targeting, Source: Yuhang Xuebao/Journal of Astronautics, v 28, n 4, pp.865-869, July (2007).

[11] Chen, Feng; Xiao, Yelun; Chen. Guidance based on zero effort miss for super-range exoatmospheric intercept: Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica, v 30, n 9, pp.1583-1589, September 2009 Language: Chinese.

[12] Li, Yun-Qian; Qi, Nai-Ming. A zero-effort miss distance-based guidance law for endoatmoshperic interceptor, Yuhang Xuebao/Journal of Astronautics, v 31, n 7, pp.1768-1774, July (2010).

[13] Zhu, Shengying, Guidance law of impacting small bodies using Zero-Effort-Miss(ZEM) steering. 2008 2nd International Symposium on Systems and Control in Aerospace and Astronautics, ISSCAA 2008, 2008, 2008 2nd International Symposium on Systems and Control in Aerospace and Astronautics, ISSCAA (2008).

DOI: 10.1109/isscaa.2008.4776346

[14] Tang shan-tong. Summary of the vehicle trajectory optimazation and guidance law[J]. MODERN DEFENCE TECHNOLOGY.

[15] Li Luo-gang. Optimal orbit design of returning from moon[J]. Journal of Harbin institute of technology.

[16] HE Xing-suo. Optimal Design of Direct Soft-Landing Trajectory of Lunar Prospector[J]. Yuhang Xuebao/Journal of Astronautics.

[17] LIANG Xin-gang. Applying Nonlinear Programming to Solve Nonplanar Optimal Orbital Transfer Problem[J]. Yuhang Xuebao/Journal of Astronautics.

[18] ZHOU Jing-Yang, ZHOU Di. Precise Modeling and Optimal Orbit Design of Lunar Modules Soft Landing[J]. Yuhang Xuebao/Journal of Astronautics.

[19] LIANG Xin-gang. Applying Nonlinear Programming to Solve Nonplanar Optimal Orbital Transfer Problem[J]. Yuhang Xuebao/Journal of Astronautics.

[20] LIU Tao, HE Zhao-wei. Continuous-Thrust Orbit Maneuver Optimization Using Modified Robust Algorithm[J]. Yuhang Xuebao/Journal of Astronautics.

[21] JING Wu-xing, Li Luo-gang. Calculating Flight Program Data and Launch-Time Window in Missile Interception[J]. Systems Engineering and Electronics.