闭路制导在小型固体运载火箭中的应用

固体运载火箭发动机推力偏差和秒耗量偏差大,导致关机点时间偏差也大,因此偏差轨道和按标称值飞行的标准轨道之间偏差大,传统的摄动制导难以满足对卫星高入轨精度的要求。针对固体运载火箭的上述特点,本文提出具有工程意义的闭路制导方法。实现闭路制导的关键之一是需要速度的求解。本文根据运载火箭的实时飞行状态和卫星轨道元素之间的关系推导出简单实用的需要速度,并应用于发射近圆轨道卫星的小型固体运载火箭的闭路制导控制中。经过数学仿真验证,证明本文中的方法在各种干扰下均具有较高的精度。

Application of Closed Loop Guidance in Small Solid Launch Vehicle

The error of thrust and fuel wastage per second of solid launch vehicle engine is quite different from the parameters which are fixed before,thus the time of engine shutdown is deviated from which of standard trajectory.Because the error trajectory deviates from the standard trajectory,the precision of satellite trajectories can not be satisfied when using traditional perturbation guidance.Aiming at the charcateristics of solid launch vehicle,this article presents a closed loop guidance precept.The calculation of required velocity is one of the keys to realize closed loop guidance.On the basis of real-time flight conditions of launch vehicle and satellite trajectories,simple and practical required velocity is deduced in this article.And this method has been used in closed loop guidance system in small solid launch vehicle to launch rather rounded satellite.Simulation results show that the method in this article has comparatively high precision when considering different disturbance.