亚轨道飞行器无动力自动着陆的横侧向控制  

The Unpowered Autolanding Lateral Control Design for Sub-orbital Reusable Launch Vehicle

作　　者：赵志芳[1] 倪少波[1] 贾志强[1] 穆晓敏[1] 

机构地区：[1]北京航天自动控制研究所,北京100854

出　　处：《航天控制》2014年第6期30-33,39,共5页Aerospace Control

摘　　要：针对重复使用亚轨道飞行器无动力自动着陆的横侧向控制,偏航通道根据状态反馈和输出反馈理论将"偏航角速度+偏航角"反馈转换成适于工程应用的"偏航角速度+侧向过载"控制方式;滚转通道设计了"滚转角速度+滚转角"控制方式,在此基础上首次推导了BTT控制方式侧偏距回路的稳定性分析原理,并据此理论设计了横侧向回路的控制参数。仿真结果表明所设计的横侧向控制器能够快速消除侧滑角,有效消除侧偏距,并且对平稳风和切变风有较强的鲁棒性。The unpowered autolanding lateral controller of sub - orbital reusable launch vehicle （SRLV） is designed. Firstly, based on input feedback and output feedback theory, the yaw rate and yaw controller of yaw loop are converted into yaw rate and overload controller for SRLV is designed. Secondly, the roll channel controller of roll rate and roll is completed, and then according to the stability analysis principles of lateral deviation loop for BTT control which has been evolved for the first time, the feedback controller parameters of the deviated distance and deviated rate are established. The simulation results show that the controller designed not only can eliminate the lateral deviation effectively and but also can control the side slip to zero rapidly. Most importantly, the robustness to steady wind and wind shear has been verified by the simulation.

关 键 词：无动力自动着陆 横侧向控制 BTT 侧偏距回路稳定性 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]