运载火箭推力矢量/非线性复合控制方法研究  

Thrust Vector/Nonlinear Composite Control Method for Launch Vehicle

作　　者：周如好 张卫东[2] 胡存明 张飞 

机构地区：[1]上海航天控制技术研究所,上海201109 [2]上海航天技术研究院,上海201109

出　　处：《上海航天》2016年第B05期81-85,共5页Aerospace Shanghai

摘　　要：针对俯仰偏航单台发动机推力矢量控制、滚动非线性喷管控制新型液体运载火箭,燃气滚控力矩偏小,发动机摇摆对滚动通道产生干扰大的问题,建立了考虑箭体质心横移和风向变化的一体化动力学模型,提出了一种推力矢量/非线性复合控制方法,在三通道姿态解耦控制基础上,采用先控制稳定性,再控制精度的滚动控制策略。数学仿真结果表明:在箭体质心横移及恶劣风场条件下,可实现运载火箭精确稳定控制。For the pitch/yaw thrust vector control,rolling nonlinear nozzle control model of liquid rocket,gas rolling control moment was too small and easily disturbed by engine swing.The dynamic model was built considering the centroid offset and wind direction.A thrust vector/composite nonlinear control method was proposed in the paper.The stability and accuracy of rolling control strategy was adopted based on the decoupling control of three channels.The simulation results showed that the method could achieve rocket attitude stable and precise control under centroid offset and adverse wind condition.

关 键 词：复合控制 燃气滚控 最小路径 参数评估 质心横移 姿态控制 解耦控制 运载火箭 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]