脉冲式干扰下高超声速飞行器的有限时间状态受限控制

项目名称： 脉冲式干扰下高超声速飞行器的有限时间状态受限控制

项目编号： No.61503100

项目类型： 青年科学基金项目

立项/批准年度： 2016

项目学科： 自动化技术、计算机技术

项目作者： 谭峰

作者单位： 哈尔滨工业大学

项目金额： 20万元

中文摘要： 高超声速飞行器工作状态突变时，如助推分离、发动机点火与熄火，控制系统会受到短时、大幅值的干扰，容易引发飞行器姿态震荡，威胁飞行安全。我们将这种典型干扰描述为脉冲式干扰，研究该类干扰下高超声速飞行器的有限时间状态受限控制问题。首先提出基于迭代凸优化的在线轨迹优化算法，通过修正制导轨迹来减小脉冲式干扰的影响；其次，基于该优化轨迹得到飞行器姿态系统的线性时变模型，采用连续椭球估计的思想推导系统的鲁棒有限时间稳定性条件；最后，基于凸优化算法解决输入受限系统的有限时间镇定和干扰下的输入状态有限时间镇定控制问题。课题的研究结果将应用于高超声速飞行器助推分离、点火熄火等关键飞行段的分析和设计，为高超声速飞行器的研究和研制提供理论支撑和设计参考。

中文关键词： 鲁棒控制；状态约束；有限时间稳定；凸优化；高超声速飞行器

英文摘要： The control system of hypersonic vehicles would experience short-time and high-amplitude disturbances when there is a sudden change of operation modes, like stage separation, engine turn-on or turn-off. In many cases, this kind of disturbance, which is called impulsive disturbance in this project, tends to cause serious problems. This project focuses on the study of finite-time state constrained control methods of hypersonic vehicles under impulsive disturbances. Firstly, an online trajectory optimization algorithm is proposed based on iterative convex optimization to reduce the influence of impulsive disturbances. Then according to the optimal trajectory, a linear time-varying model of the attitude control system is built and sequential ellipsoidal approximations are used to derive robust finite-time stability conditions of the system. Finally, the input-constrained finite-time stabilization and input-state finite-time stabilization problems are solved using convex optimization. The results of this project can be used to solve the stage separation problem, the engine on and off impact problem and so on, which will provide theoretical supports and design references for the research and development of hypersonic vehicles.

英文关键词： robust control;state constraints;finite-time stability;convex optimization;hypersonic vehicles