摘要
为了综合研究和分析载人飞船返回舱制导导航控制 (GNC)系统的性能 ,验证系统设计的正确性、合理性和可行性 ,提出了返回舱六自由度再入弹道仿真研究问题。根据返回舱 GNC系统的任务 ,建立了适用于包括风在内的各种干扰作用下六自由度再入弹道仿真数学模型 ,为半实物仿真奠定了基础。提出了基于标准轨道的再入制导律 ,严格推导了再入段总升力方向控制中滚动通道姿态控制信号的形成 ,并给出了工程应用中简化的方法。开发了综合仿真软件 ,仿真计算表明 ,GNC系统的设计及参数选择、总体设计是合理的、正确的和可行的。
In order to comprehensively study and analyze the performances of the guidance navigation control (GNC) system for manned spaceship's return module, and verify the validity, rationality and feasibility of the system design, the research on 6DOF reentry trajectory simulation for the return module is proposed. According to the GNC system function and task for it, the 6DOF simulative mathematical models of reentry trajectory are formulated under the action of a variety of disturbances including wind on it. Hence, a foundation is laid for the hardware in the loop simulation. The nominal trajectory based reentry guidance law is put forward. Then, the attitude control signal parameters of the roll channel in the process of reentry total lift control are rigorously derived, and the simplifying method for the engineering application is given according to the practical situation. A comprehensive simulation software is developed. By digital simulation, some conclusions, which have important theoretical significance and engineering application values, are made.
出处
《飞行力学》
CSCD
北大核心
2000年第3期80-84,共5页
Flight Dynamics
关键词
再入制导
升力控制
姿态控制
弹道仿真
载人飞船
reentry guidance
lift control
attitude control
navigation computation
6DOF trajectory simulation
