空间交会对接最终平移段直线制导律研究

Straight line guidance strategy design for the final translation of space rendezvous and docking

针对空间交会对接最终平移段追踪器沿视线作受迫接近运动问题,基于相对运动动力学特性研究V-bar、R-bar直线接近制导方法,设计了采用脉冲式匀速和有限推力式变速直线制导律,获得了燃料最省的制导条件。最后进行了仿真验证与对比分析,仿真结果表明,设计的制导律简单有效,其中V-bar直线制导的脉冲式实现与有限推力式实现燃料消耗相同,但有限推力式转移时间较长;而R-bar直线制导的有限推力式实现与脉冲式实现相比,燃料消耗更多,转移时间也更长。设计的V-bar、R-bar脉冲式和有限推力式直线制导律适合不同推进器配置下的工程应用。

Aimed at the problem of forced motion along Line of sight of final translation phase of space rendezvous and docking,straight line guidance algorithms of V-bar and R-bar based on C-W equation are investigated,the guidance laws used impulsive propulsion and finite thrust are designed,and the guidance conditions for optimal-fuel are obtained.Simulation is done to illustrate and analyze the guidance algorithms,and siumlation results show that the proposed approaches are simple and efficient,and the V-bar guidance law used impulsive thrust has the same fuel consumption with the law used finite thrust,but less transfer time,and for R-bar guidance,the law used impulsive thrust has less fuel and time consumption than the law used finite thrust.