基于预测校正法的高超声速飞行器再入制导

王青; 冉茂鹏; 赵洋

基于预测校正法的高超声速飞行器再入制导

北京航空航天大学自动化科学与电气工程学院, 北京 100191

基金项目: 国家自然科学基金资助项目（61074027）；国防预研基金资助项目（9140C48020212HK0101）

详细信息

中图分类号: V448.234
计量
- 文章访问数: 1723
- HTML全文浏览量: 168
- PDF下载量: 791
- 被引次数: 0
出版历程
- 收稿日期: 2013-03-13
- 网络出版日期: 2013-12-30

Reentry guidance for hypersonic vehicle based on predictor-corrector method

School of Automation Science and Electrical Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 针对新一代高超声速飞行器在制导方法的精度及抗干扰能力上的要求，提出了一种基于能量的预测校正制导方法.建立了以能量为自变量的三自由度运动学方程，给出再入过程中的主要约束条件，在此基础上分别设计纵向制导律和侧向制导律.在纵向制导律中，不断预测剩余航程相对理论目标点之间的偏差，并以此偏差作为模糊校正器的输入，输出合适的侧倾角更新值，从而达到校正效果，保证纵向制导精度；在侧向制导律中，设计了一种基于横程偏差的侧倾角反转逻辑，当横程偏差超过所设定的边界条件时，侧倾角便进行一次反转，从而保证侧向制导精度.分别在标准初始条件下和存在偏差条件下进行了数值仿真，仿真结果验证了所设计的制导律的有效性.
- 高超声速飞行器 /
- 再入制导 /
- 预测校正
Abstract: An energy-based predictor-corrector guidance algorithm was proposed to handle the need for high precision and robustness of reentry guidance for hypersonic vehicle. A detailed derivation of three degrees of freedom reentry kinematic equations based on energy was conducted, and the path constraints and terminal constraints were also included. Based on the derivation, the longitudinal and lateral guidance law was designed. For the longitudinal part, longitudinal range errors were repeatedly calculated, and a fuzzy corrector was designed to eliminate the errors which guarantee the accuracy of the longitudinal guidance; for the lateral guidance law, a cross-range error based lateral reversal logic was designed, whenever the cross-range exceeds the sited boundaries, a bank reversal was conducted. Simulation results on both standard and deviation conditions verified the effectiveness of the proposed guidance law.
- hypersonic vehicle /
- reentry guidance /
- predictor-corrector

HTML全文

参考文献(10)

[1]	Xu Mingliang, Chen Kejun, Liu Luhua, et al.Quasi-equilibrium glide adaptive guidance for hypersonic vehicles[J].Science China-Technological Sciences, 2012, 55(3):856-866
[2]	Gamble J D, Cerimele C J, Moore T E.Atmospheric guidance concepts for an aeroassisted flight experiment[J].The Journal of the Astronautical Science, 1988, 36(1):45-71
[3]	Braun R D, Powell R W.Predictor-corrector guidance algorithm for use in high-energy aerobraking system studies[J].Journal of Guidance, Control, and Dynamics, 1992, 15(3):672-678
[4]	Lu Ping.Predictor-corrector entry guidance for low-lifting vehicles[J].Journal of Guidance, Control, and Dynamics, 2008, 31(4):1067-1075
[5]	Xue Songhai, Lu Ping.Constrained predictor-corrector entry guidance[J].Journal of Guidance, Control, and Dynamics, 2010, 33(4): 1273-1281
[6]	李惠峰, 谢陵.基于预测校正方法的RLV再入制导律设计[J].北京航空航天大学学报, 2009, 35(11):1344-1348 Li Huifeng, Xie Ling.Reentry guidance law design for RLV based on predictor-corrector method[J].Journal of Beijing University of Aeronautics and Astronautics, 2009, 35(11):1344-1348 (in Chinese)
[7]	雍恩米, 唐国金, 陈磊.高超声速无动力远程滑翔飞行器多约束条件下的轨迹快速生成[J].宇航学报, 2008, 29(1):46- 52 Yong Enmi, Tang Guojin, Chen Lei.Rapid trajectory planning for hypersonic empowered long-range reentry vehicles with multi-constraints[J].Journal of Astronautics, 2008, 29(1):46-52 (in Chinese)
[8]	Shen Zuojun, Lu Ping.Dynamic lateral guidance logic[J].Journal of Guidance, Control, and Dynamics, 2004, 27(6):949-959
[9]	John D S, Jason R H.In-flight entry trajectory optimization for reusable launch vehicles[C]//AIAA Guidance, Navigation, and Control Conference and Exhibit.San Francisco, California, USA:AIAA, 2005:1-18
[10]	Hanson J M, Jones R E.Test results for entry guidance methods for space vehicles[J].Journal of Guidance, Control, and Dynamics, 2004, 27(6):960-966