迭代制导情况下姿态控制系统稳定性分析方法研究

为了提高火箭的入轨精度和轨道适应能力,我国在新一代运载火箭末级中采用了迭代制导技术,俯仰、偏航程序角根据火箭运动状态和目标轨道参数实时变化,目前工程设计中仍按照固定程序角方式开展稳定性分析。本文推导出迭代制导程序角与火箭速度、位置之间的线性关系式,在国内首次提出了迭代制导情况下的稳定性分析方法,并以新一代运载火箭为例进行了实例计算,结果表明此分析方法正确、可行,具有一定的参考价值。

The Research on Stability Analysis of Attitude Control System in the Case of Iterative Guidance

Aiming at the improvement of in-orbit precision and orbit adaptability,the iterative guidance technology is adopted in new generation launch vehicle of China.The pitch and yaw program attitude angles are changed,which are based on launch vehicle movement states and target orbit parameters in real time,but the stability analysis is still developed according to the form of fixed program attitude angles in today’s engineer design.In this paper,the linear relation functions of iterative guidance program angles and launch vehicle velocity and position are deduced,and the method of stability analysis in the case of iterative guidance is presented firstly in China.Then,the calculation example of new generation launch vehicle is demonstrated.The results indicate that the analysis method is correct and advisable,which has fair reference value.