Optimal Closed-Loop Guidance for Cruise Missiles Based on Pseudospectral Method

doi:10.16182/j.issn1004731x.joss.201809030

Abstract

Abstract: Cruise missiles facing complex constraints are prone to deviation from the intended trajectory due to disturbances and unexpected situations in flight. Based on solving the optimal control problem of trajectory optimization with pseudospectral method, the optimal closed-loop guidance is realized by continuous on-line trajectory reconstruction using the rolling time-domain strategy. The simulation experiments are also undertaken for the unexpected events and disturbances that may be encountered during flight to verify the capability and feasibility. Simulation results show that this method can meet the requirements of real-time and accuracy, and has good adaptability to different interference errors and task modification forms.

Key words: cruise missiles, trajectory optimization, pseudospectral method, optimal closed-loop guidance

CLC Number:

TJ765.3

Liao Ying, Ji Haiyu, Xue Gaoxiong. Optimal Closed-Loop Guidance for Cruise Missiles Based on Pseudospectral Method[J]. Journal of System Simulation, 2018, 30(9): 3464-3471.

References

[1] 周伟, 李毅, 张亚迪. 外军巡航导弹发展态势分析[J]. 航天电子对抗, 2015, 31(1): 1-5.
Zhou W, Li Y, Zhang Y D. nalysis of the Development Situation of Foreign Military Cruise Missiles[J]. Aerospace Electronic Competition, 2015, 31(1): 1-5.
[2] 杨希祥, 杨慧欣, 王鹏. 伪谱法及其在飞行器轨迹优化设计领域的应用综述[J]. 国防科技大学学报, 2015(4):1-8.
Yang X X, Yang H X, Wang P.Overview of pseudo-spectral method and its application in trajectory optimum design for flight vehicles[J]. Journal of National University of Defense Technology, 2015(4):1-8.
[3] Ross I M, Fahroo F.A Unified Computational Framework for Real-Time Optimal Control[C]// Proceedings of the 42nd IEEE Conierence on Decision and Control. Maui, Hawaii USA: IEEE Press, 2003: 2210-2215.
[4] Ross I M, Sekhavat P, Fleming A, et al.Optimal Feedback Control: Foundations, Examples,and Experimental Results for a New Approach[J]. Journal of Guidance,Control and Dynamics (S0731-5090), 2008, 31(2): 1307-1321.
[5] Tian B, Zong Q.Optimal guidance for reentry vehicles based on indirect Legendre pseudospectral method[J]. Acta Astronautica (S0094-5765), 2011, 68(7/8): 1176-1184.
[6] 黄诘, 张友安, 刘永新, 等. 基于Radau伪谱方法的轨迹优化[J]. 海军航空工程学院学报, 2015, 30(4): 315-320.
Huang J, Zhang Y A, Liu Y X, et al.Trajectory optimization based on Radau pseudospectral method[J]. Journal of Naval Aeronautical Engineering Institute, 2015, 30(4): 315-320.
[7] 明超, 孙瑞胜, 白宏阳, 等. 基于hp自适应伪谱法的多脉冲导弹弹道优化设计[J]. 固体火箭技术, 2015(2):151-155.
Ming C, Sun R S, Bai H Y, et al.Ballistic optimization design of multi-pulse missile based on hp adaptive pseudospectral method[J]. Solid State Rocket Technology, 2015(2): 151-155.
[8] Peng H, Gao Q, Wu Z, et al.Optimal guidance based on receding horizon control for low-thrust transfer to libration point orbits[J]. Advances in Space Research, 2013, 51(11): 2093-2111.
[9] Darby C L, Hager W W, Rao A V.Direct trajectory optimization using a variable low-order adaptive pseudospectral method[J]. Journal of Spacecraft and Rockets (S0022-4650). 2011, 48(3): 433-445.
[10] Lu P.Closed-form control laws for linear time-varying systems[J]. Automatic Control (S0018-9286), IEEE Transactions on, 2000, 45(3): 537-542.
[11] 吴森堂. 飞航导弹制导控制系统随机鲁棒分析与设计[M]. 北京: 国防工业出版社, 2010: 39-200.
WU Sentang.Tochastic robustness analysis and design for guid-ance and control systemof winged missile[M]. Beijing: NationalDefense Industry Press, 2010: 39-200.
[12] 韩祖南. 国外著名导弹解析[M]. 北京: 国防工业出版社, 2013: 198-203.
Han Z N.Analysis of famous foreign missiles[M]. Beijing: National Defence Industry Press, 2013: 198-203.