一种直接上升式轨道转移计算仿真方法  

Study on Computation and Simulation for Direct Ascending Orbit Transformation Design

作　　者：吴启星 赵灵峰 王涛 WU Qi-xing;ZHAO Ling-feng;WANG Tao(Beijing Institute of Tracking and Communication Technology,Beijing 100094,China;Innovation Academy for Microsatellites of CAS,Shanghai 200120,China;School of Intelligent Systems Engineering,Sun Yat-Sen University,Guangzhou 510006,China)

机构地区：[1]北京跟踪与通信技术研究所,北京100094 [2]中国科学院微小卫星创新研究院,上海200120 [3]中山大学智能工程学院,广东广州510006

出　　处：《计算机仿真》2023年第4期48-51,共4页Computer Simulation

基　　金：国家自然科学基金(61975151)。

摘　　要：由于空间飞行器末制导段修正能力有限,助推段的制导精度将严重影响交会过程的最终制导精度。针对空间飞行器直接上升轨道转移实时快速性及容许制导交班误差的要求,提出了一种直接上升式轨道转移优化设计方法。假设空间飞行器助推段起始瞬间获得全部速度增量,并在该段的其余时间内作惯性飞行,给出一种满足时间约束和速度增量约束组合条件下的轨道转移优化方法,确定助推点火时刻和预计交会点,并在此基础上给出助推器推力矢量定向的方法。方法对空间交会轨道设计具有普适性,可用于非共面非共轴交会。Because of the limited capability of the space vehicles'terminal guidance corrections,the guidance precision of the boost phase will have a seriously bad effect on the guidance precisions in rendezvous.In order to fulfill the requirements of real-time rapidity and guidance precision for the space vehicle direct orbit transformation,This paper provides an optimization design for direct ascending orbit transformation.In this paper,assuming that the space vehicle obtains the full velocity increment at the beginning time of the boost phase,and then the vehicle enters inertial flight,an optimization algorithm based on the time and velocity constraints is proposed for the orbit transformation,and finds out the fire time of the boost phase and expected rendezvous point are found.On this basis,the thrust vector orientation of the boost phase can be determined.The method has its generality for space rendezvous including the non-coplanar and non-coaxial orbital rendezvous.

关 键 词：空间飞行器 有限末制导 轨道转移 优化 

分 类 号：V448.25[航空宇航科学与技术—飞行器设计]