针对一种两级固体探空火箭的落点位置及倾角散布控制问题,提出了二级点火时刻控制与闭路制导相结合的解决方案。利用探空火箭射程、射向相对固定的特点,将地球自转、地球形状、大气阻力对弹道的综合影响视为系统性误差进行补偿,获得了简化的弹道转移制导模型。设计了基于二级助推前后椭圆弹道交会点的二级点火时刻自适应控制律以及给定虚拟目标点速度大小的免能量耗散、免迭代二级闭路制导算法。蒙特卡洛仿真结果表明,当落点位置偏差小于2.2km,落点弹道倾角偏差小于0.5°时,满足探空火箭试验任务需求。

To solve the problem of impact point position and inclination angle dispersion control of a two stage solid sounding rocket, a method using both adaptive ignition time control and second stage closeloop guidance is put forward in this paper. Taking advantage of that the rocket's range and launching direction are relatively fixed, affecting factors such as atmospheric drag, spin and shape of the earth, are treated as systematic error and equivalently compensated, thus a simplified trajectory transfer guidance model is obtained. On this basis, an adaptive ignition time control algorithm based on rendezvous point of the two ellipse trajectories before and after second stage boosting is designed. A second stage closeloop guidance algorithm with no energy dissipation nor iteration calculation but given velocity of the virtual target is derived as well. MonteCarlo simulation result shows that the sounding rocket's flight test requirements are met well, with impact point position error less than 2.2 km and inclination angle error less than 0.5°.