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Design and Analysis of Medium and Higher-Tier Missile Guidance Law
|關鍵字:||Ballistic Target;彈道目標;Guidance Law;Control;Performance;導引律;控制;性能||出版社:||電機工程學系所||引用:|| M. Guelman, “A qualitative study of proportional navigation,” IEEE Trans. on Aerospace and Electronic System, vol. ASE-7, no. 4, pp. 637-643, 1971.  S. Gutman, “An optimal guidance for homing missile,” AIAA Journal of Guidance Control and Dynamics, vol. 2, no. 4, pp. 296-300, 1979.  F. Imado and T. Kuroda, “Optimal missile guidance system against a hypersonic targets.” AIAA Paper 92-4531, 1992.  T. Kuroda, and F. Imado, “Advanced missile guidance system against very high speed target.” AIAA Paper 88-4092, AIAA, Washington, D.C., U.S.A. , 1988.  K. Becker, “Closed-form solution of pure proportional navigation.” IEEE Trans. on Aerospace and Electronic Systems, vol. 26, pp. 526-533, 1990.  C. F. Lin, “Advanced control systems design,” Prentice-Hall, Englewood Cliffs, NJ, 1994.  G. W. Cherry, “A general explicit, optimizing guidance law for rocket-propellant spacecraft,” AIAA Paper 64-638, 1964.  C. L. Lin, H. Z. Hung, Y. Y. Chen, and B. S. Chen, “Development of an integrated fuzzy-logic-based missile guidance law against high speed target,” IEEE Trans. on Fuzzy Systems, vol. 12, no. 2, pp. 157-169, 2004.  C. L. Lin, K. M. Chen, M. Z. Wu, and S. W. Hwang, “Hybrid guidance law for interception of ballistic target,” IME Journal of Aerospace Engineering-Pt. G, vol. 220, pp. 525-536, 2006.  C. L. Lin, and T. L. Wang, “Fuzzy side force control for missile against hypersonic target,” IET Control Theory and Applications, vol. 1, no. 1, pp. 33-43, 2007.  K. R. Babu, I. G. Sarma, and K. N. Swamy, “Switched bias proportional navigation for homing guidance against highly maneuvering targets,” AIAA Journal of Guidance Control and Dynamics, vol. 6, no. 17, pp. 1357-1363, 1994.  王勝德，郭德盛，陳永耀，傅立成，馮蟻剛，”飛彈導控系統終端導引律之研究”，技術報告，NSC 87-0210-D-082-001，臺灣大學，2002年1月.  D. R. Taur, and J. S. Chern, “An optimal composite guidance strategy for dogfight air-to-air IR missile,” AIAA Journal of Guidance, Control, and Dynamics, vol. 1, pp. 662-671, 1999.  A. O. Danielson, “Integrated aerodynamic fin and stowable TVC vane system; Patent,” Department of Navy, Washington, DC., 1994.  M. D. Jacobson, “Droppable jet vane TVC; patent,” Department of Navy, Washington, DC, 1992,  Y. F. Kuang, H. H. Chien, and L. C. Fu, “Design of optimal midcourse guidance sliding-mode control for missiles with TVC,” IEEE Trans. on Aerospace and Electronic Systems, vol. 39, no. 3, pp. 824-837, 2003.  傅立成，郭德盛，推力向量控制應用，技術報告，NSC90-CS-7-082- 003，臺灣大學，2002年1月.  S. Gutman, “Applied min-max approach to missile guidance and control,” Progress in Astronautics and Aeronautics Series, 209, AIAA, 2005.  F. P. Adler, “Missile guidance by three dimensional proportional navigation,” Journal of Applied Physics, vol. 27, pp. 500-507, 1956  S. H. Song, and I. J. Ha, “A Lyapunov-like approach to performance analysis of 3-dimensional pure PNG laws,” IEEE Trans. on Aerospace and Electronic Systems, vol. 30, pp. 238-248, 1994.  J. H. Oh, and I. J. Ha, “Capturability of the 3-dimensional pure PNG law,” IEEE Trans. on Aerospace and Electronic Systems, vol. 35, pp. 491-503, 1999.  W. Gu, H. Zhao, and R. Zhang, “A three-dimensional proportional guidance law based on RBF neural network,” 7th World Congress on Intelligent Control and Automation, pp. 6978-6982, 2008.  C. D., Yang, and C. C. Yang, “Analytical solution of generalized 3D proportional navigation,” IEEE Conf. on Decision and Control, vol. 4, pp. 3974-3979, 1995.||摘要:||
The research issue regarding missile guidance law design of a medium and higher-tier anti-ballistic missile to intercept ballistic targets during their early reentry phase has been a major concern in the defense technology. The defense missile possessing two solid rocket stages with both stages based on thrust vector control is used as a reference model for developing the guidance law.
For the guidance law design, the missile trajectory is first shaped by directly controlling its flight path toward the incoming target. When the first-stage rocket burns out, the missile coasts toward to the target with inertia force until the second-stage rocket activates. After the second-stage rocket activates, the missile is guided by proportional navigation guidance law that the angular rates are provided by the ground control center. The modified proportional navigation guidance law, works after the seeker starts, is designed to account the missile's axial acceleration and target acceleration variation. The lateral acceleration command is applied to guide the missile engaging the ballistic target.
The guidance law is developed with the aim to increase the interception performance by incorporating a thrust vector control mechanism to enhance lateral maneuverability and the second stage of the missile fitted with small control fins to stabilize the missile body. The effect of the proposed design is verified via extensive numerical simulation to examine its engagement performance. Miss distance analysis is conducted and characterization of the 3-dimenaional defensible volume is constructed to verify the proposed design.
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