摘要
开展了运载火箭的姿态控制方案对最优制导的适应性研究,分析了运载火箭采用最优制导方法后,实时计算的程序角的平滑性易受发动机推力脉动的影响,导致发动机摆角输出不平稳,提出了一种"降带+增阻"的姿态控制方案,对没有速率陀螺的级段采用了捷联惯组角速率信号参与姿态控制,设计了程序角的带宽限幅器和系统阻尼的系数。仿真结果表明:该控制方案效果明显,提高了发动机摆角稳定性,极大改善了稳定控制的品质。
The adaptability of the attitude control for the optimal guidance of launuh vehicle was studied in this paper.Due to the rocket which was using the method of optimal guidance,the output angle which was sensitive to the thrust change would not be smooth.The attitude control method was introduced to reduce the guidance signal bandwidth and improve the damping of the system in this paper.By comparing with the traditional differential network control method,simulation results showed that this method improved the engine angular stable precision,ensured the engine angular stability and achieved the purpose of the launch vehicle attitude stability control.
出处
《上海航天》
2016年第B05期86-90,共5页
Aerospace Shanghai
