火星探测器使命轨道捕获策略研究  

Analysis of Orbit Capture Method for Mars Vehicle

作　　者：闵学龙[1] 潘腾[1] 郭海林[1] 

机构地区：[1]北京空间飞行器总体设计部,北京100094

出　　处：《航天器工程》2008年第6期39-43,共5页Spacecraft Engineering

基　　金：国家重大科技专项工程

摘　　要：分析了火星探测器使命轨道捕获策略研究需求,给出了三种可用的典型捕获策略,建立了速度纵向平面内的飞行动力学方程,对三种典型策略进行了飞行动力学仿真,给出了各策略完成捕获所需速度增量、任务耗时及过。通过对仿真结果的分析比较,得出研究结论为:直接制动捕获任务耗时及过载较小,但速度增量需求较大;多次穿越后捕获任务耗时较长,但速度增量需求和过载较小;一次穿越后捕获速度增量需求较小且任务耗时较短,但过载较大。The research necessary of Mars Vehicle （MV） orbit capture is discussed. A comparison of 3 typical orbit capture methods for Mars vehicle--propulsive braking, aerobraking and aerocapture is presented. The study employs a presumptive performance for the Mars vehicle. The aerobraking and aeroca- pture flight databases were generated by a Matlab process based on 2-dirnensional dynamic model. A comparative orbit capture method performance analysis is performed using delta-v and duration, which allow method performances to be objectively compared. Propulsion for a tremendous delta-v is an unac- ceptable method. Aerobraking is an acceptable method for the low heat load and delta-v, but its duration is long. Aerocapture is preferred for the short duration and the delta-v is within a reasonable limit, but as for the high heat load, the vehicle needs thermal proteetion system

关 键 词：火星探测器轨道 捕获 推力制动 大气辅助捕获 

分 类 号：V476[航空宇航科学与技术—飞行器设计]