带落角约束的高超声速飞行器一体化制导控制

Integrated guidance and control with terminal angular constraint for hypersonic vehicles

中文关键词  高超声速飞行器  一体化制导控制  自适应块动态面反演控制  一致最终有界

英文关键词  hypersonic vehicles  integrated guidance and control  adaptive block dynamic surface backstepping control  uniformly ultimately bounded

中文摘要

      本文针对高超声速飞行器高速俯冲过程中的质心运动与绕质心运动之间存在强耦合的特点, 提出了一种基于全量耦合模型的满足落角约束的一体化制导控制方法. 首先建立基于视线角的飞行器与目标的相对运动方程和绕质心运动方程, 通过微分同胚处理得到一体化制导控制模型. 接着采用自适应块动态面反演方法提出了一体化制导控制方法. 该方法充分考虑了飞行器质心运动与绕质心运动之间的耦合作用, 显著提高高超声速飞行器高速俯冲过程中的整体控制性能. 本文提出的一体化制导控制方法能使得飞行器闭环系统的状态一致最终有界, 且视线角速率的界可以达到任意小. 最后, 通过仿真结果验证了全量耦合一体化制导控制方法的有效性.

英文摘要

      Considering the strong coupling between the centroid motion and the attitude motion for hypersonic vehicles in dive phase, we propose a novel integrated guidance and control (IGC) with terminal angular constraint approach based on the complete model. In designing the control law, we build the complete coupling model by combining together the line-of-sight (LOS) equations describing the relative motion between the vehicle and the target, and the attitude motion equations. Furthermore, a corresponding IGC law is developed by using the adaptive block dynamic surface backstepping control method which takes the synergism between the guidance subsystem and the control subsystem into consideration to improve the accuracy and robustness. With the developed IGC law, all the signals of the closed-loop system of the vehicle are guaranteed to be uniformly ultimately bounded, and the bounds of the LOS rates can be made arbitrarily small. Finally, simulation results demonstrate the feasibility of the novel IGC approach.