多约束条件下高超声速飞行器级间分离抗冲击强鲁棒控制方法研究

For the hypersonic vehicle (HSV), a stable controller for the stage separation is an important part to carry out the flight missions. So, this project intends to carry out the research on a class of robust impact control method for the stage separation of hypersonic vehicle with multiple constraints. Firstly, we study the requirements of HSV robust impact control problem with high dynamic pressure, strong impulse and disturbance in the stage separation phase. The strong robust chattering-free sliding mode control method with unidirectional auxiliary surface will be presented, and it is combined with the nonlinear generalized predictive control method and adaptive disturbance observer technique to suppress the impact disturbance. Secondly, the HSV fast constrained control problem will be researched in the project with multiple constraints including the flight states, control surfaces and the limitation of adjustment time etc. Based on the new conjugate gradient anti-windup and high-order design method, a class of adaptive sliding mode positively invariant set with the low computational complexity is presented for the stage separation of hypersonic vehicle with constraints. Meanwhile, the terminal attractor is introduced to improve rapidity of the proposed control method. This project has an important theoretical significance to improve the robust flight impact control method with multiple constraints, enrich the connotation of stage separation research, and promote engineering applications for the control methods based on sliding mode positively invariant sets.

对于高超声速飞行器(HSV)而言，级间分离段的稳定控制是其成功执行飞行任务的前提与保障。因此，为确保HSV稳定分离，本项目拟对适用于该阶段的抗冲击强鲁棒约束控制方法展开研究。首先，分析高动压分离条件下强分离冲量、耦合气动干扰等对控制系统稳定性的影响，改进无抖振强鲁棒单向滑模控制方法，结合非线性广义预测控制方法和自适应干扰观测器技术，解决HSV分离段抗冲击强鲁棒控制问题。其次，研究飞行状态、控制舵面和分离调整时间等多约束条件下HSV快速稳定控制问题，提出含时间约束指标的自适应滑模正不变集控制方法，并结合新的共轭梯度anti-windup以及高阶滑模控制思想，发展运算量小、易于实现的正不变集约束控制理论，并引入终端吸引子来提高控制方法的快速性能。该项目对完善多约束条件下HSV抗冲击强鲁棒飞行控制方法，丰富级间分离控制的研究内涵，推动滑模正不变集控制理论的工程应用有着重要的理论意义。

本项目主要以高超声速飞行器为研究对象，对多约束条件下抗冲击强鲁棒控制系统进行研究。为了进一步提升研究成果的有效性和实际意义，在研究过程中采用轨道炮发射的高超声速弹丸相关文档为参考，建立了高超声速飞行器六自由度十二状态非线性模型。在控制方法方面，本项目中建立了单向滑模控制理论的基础框架，并提出了基于不稳定辅助面和非线性异型辅助面的强鲁棒无抖振单向滑模控制器设计思路；同时，考虑时间、姿态和落角等约束指标，将单向滑模与预设性能控制理论相结合，并引入backstepping、方案弹道制导、快速单向滑模干扰观测器等技术，设计了高超声速飞行器强鲁棒多约束控制系统；此外，本项目还对大过载高超声速飞行器姿态组合辨识技术进行了研究，为我国大过载高超声速制导弾箭的研制提供理论基础与技术支撑。