卫星轨道圆化的有限推力点火控制策略

本文研究卫星轨道圆化的点火控制策略，发动机推力为有限常值，方向可调。考虑了燃料消耗引起的质量损失。假设圆轨道上有一飞行器在运动，称为虚拟轨道器。只要卫星与虚拟轨道器软交会，就完成了轨道圆化。文中给出了使卫星与虚拟轨道器软交会的推力方向控制策略和点火位置与关车位置的求取方法。仿真结果表明，本文方法与水平推力策略和切向推力策略相比，具有更高的控制精度，而且燃料消耗接近最优。

FINITE THRUST BURN SCHEDULING FOR SATELLITE ORBIT CIRCULARIZATION

Finite thrust burn scheduling for satellite orbit circularization is studied Thrust value is assumed to be constant,and the thrust direction steerable Change in the mass of satellite is considered as the propellant is depleted It is supposed that there exists a spacecraft called imaginary orbiter moving on the circular orbit Circularization of satellite orbit will be completed if rendezvous of the satellite with the imaginary orbiter is realized This paper presents thrust steering strategy and the method obtaining burn on and burn off position for rendezvous of satellite with the imaginary orbiter Simulation results show that the steering strategy gives higher control accuracy in comparison with transverse steering strategy and tangential steering strategy furthermore,fuel penalty is near optimal