摘要
针对以RCS系统为姿态控制方式的飞行器,给出了一种简易的RCS系统姿控喷管布局方案,降低了系统的姿控喷管数量,通过姿控喷管的不同开关组合能够产生三通道的控制力矩。针对该布局方案存在的三通道耦合影响问题,提出了一种易于工程实现的姿控喷管开关逻辑策略并设计了控制律,实现了三通道姿态的稳定控制。通过仿真验证了布局方案和控制方案的合理性和有效性。
For flight vehicles with reaction control system(RCS),a simple nozzle location method for RCS is presented,which may significantly reduce the number of the attitude control nozzles,through the different switch combinations of nozzle,the three-channel control moment can be generated.A new switch logic which is easy to be achieved on engineering and a corresponding control law are presented to restrain the coupling effects of the three–channel control.A numerical example is given to verify the rationality and validity of the proposed approach.
作者
张磊
马奥家
李亚辉
高峰
王辰琳
Zhang Lei;Ma Ao-jia;Li Ya-hui;Gao Feng;Wang Chen-lin(China Academy of Launch Vehicle Technology,Beijing,100076)
出处
《导弹与航天运载技术》
CSCD
北大核心
2020年第5期62-66,共5页
Missiles and Space Vehicles
关键词
RCS系统
姿态控制
开关逻辑
reaction control system
attitude control
switch logic
