复杂多约束条件下高超声速飞行器三维非线性末制导方法研究

Hypersonic vehicle terminal guidance is a complicated control problem of a high nonlinear, fast time-varying system. In this project, the problem will be studied based on the modern nonlinear control theory, and special attention has been paid to the following aspects: motion coupling, multi-constraint, parameter perturbation, target movement and model mismatch. First of all, the equations of motion of the vehicle will be constructed, which provides technical support for guidance methods validation. Then based on nonlinear control theory, the guidance method will be studied by using stratified progressive method: (1) Three dimensional nonlinear guidance law will be designed, combined with parameter optimization and velocity control, to solve the motion coupling and multi-constraint guidance problem. (2)Three dimensional nonlinear sliding mode variable structure guidance law will be proposed to cope with the uncertainty of the guidance parameters due to target motion and parameter perturbation. (3)Three dimensional nonlinear model reference adaptive guidance law will be put forward to solve the problems of system instability or loss of accuracy because of the difference between the guidance model and practical system. Finally, the application of the guidance method will be studied, that is, in view of the characteristics of the guidance information data sequence, the filtering and estimation methods will be studied to strengthen the robustness and adaptive ability of the guidance information estimation and prediction. In conclusion, this project aims to solve the key problems in hypersonic vehicle terminal guidance and to provide a theoretical basis and technical support for its further development.

高超声速飞行器的末制导问题是一个复杂非线性、快时变系统的控制问题。需要重点考虑运动耦合、多约束制导、参数扰动、目标运动以及模型失配等情况。本项目将基于现代非线性控制理论开展研究。首先构建飞行器空间运动模型，为制导方法验证提供技术支撑。然后，采用分层递进的思路，基于非线性控制理论展开制导方法研究：（1）设计三维非线性制导律，并进行参数优化与速度控制研究，解决运动耦合和多约束制导问题；（2）设计三维非线性滑模变结构制导律，解决目标运动和参数扰动导致制导参数不确定的问题；（3）设计三维非线性模型参考自适应制导律，解决制导模型与实际系统存在差异导致系统失稳或精度降低的问题。最后，研究制导方法的应用问题，针对制导信息数据序列特点进行滤波与估计方法研究、增强制导信息估计和预测的鲁棒性和自适应能力。通过本项目的研究，旨在解决高超声速飞行器末制导的关键理论问题，为高超声速飞行器研制提供理论基础和技术支持。

高超声速飞行器的末制导问题是一个复杂非线性、快时变系统的控制问题。需要重点考虑运动耦合、多约束制导、参数扰动、目标运动以及模型失配等情况。本项目基于现代非线性控制理论开展了研究。首先构建了飞行器空间运动模型和仿真验证平台，能够为制导方法验证提供支撑。然后，采用分层递进的思路，基于非线性控制理论展开了制导方法研究：（1）提出了旋量理论框架，基于旋量方法，设计了三维非线性伪最优制导律，并提出了一种通用的自适应速度控制算法，解决了运动耦合和多约束制导问题；（2）将参数扰动和目标运动统一视为外部有界扰动，基于滑模变结构控制方法，设计三维非线性滑模变结构制导律，解决了由于目标运动和参数扰动导致制导参数不确定的问题；（3）面向参考制导模型与实际系统存在差异问题，设计了三维非线性模型参考自适应制导律，解决了模型失配导致系统失稳或精度降低的问题。最后，研究了制导方法的应用问题，针对制导信息数据序列特点进行了滤波方法研究，通过卡尔曼滤波实现了对飞行器位置信息的估计。本项目的研究成果，为高超声速飞行器研制提供了理论基础和技术积累。