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针对火星大气制动降轨过程中稀薄流区大气受季节和昼夜等因素影响而存在较大动态误差的问题,建立气动力作用下的轨道动力学方程,研究探测器稀薄流气动参数计算方法,分析大气参数动态误差对气动力及制动降轨效果的影响。结合火星探测应用,仿真分析火星大气制动过程中的探测器气动特性以及轨道变化特性。为保证探测器制动过程中的安全和持续时间要求,给出了理想的大气制动降轨走廊范围及导航精度需求,具有一定的工程参考价值。
Aiming at the large dynamic error of the atmosphere in the thin flow area due to the influence of season, day and night in the course of the orbital descent of Mars atmospheric braking, the orbital dynamics equation under aerodynamic force is established, the calculation method of the aerodynamic parameters of the lean flow field of the detector is studied, The influence of the dynamic error of atmospheric parameters on the aerodynamic force and the effect of braking orbit reduction is analyzed. Combining with the Mars exploration application, the aerodynamic characteristics and orbit characteristics of the detector during the atmospheric braking of Mars are simulated. In order to ensure the safety and duration requirements of the detector during braking, the ideal range of atmospheric braking and landing corridor and navigation accuracy are given, which has certain engineering reference value.