火星探测器飞行轨道设计

Flight Orbit Design of Rover to the Mars

在一些基本假设的基础上,初步设计了从地球停泊轨道发射探测器到达火星的飞行轨道。运用圆锥曲线拼接法,设计了采用双共切和单共切两种不同的日心段转移方式时,探测器日心段、地心段和火星中心段的飞行轨道,并分析比较了这两种设计方法的特点。根据限制性二体问题动力学模型,仿真计算了探测器在不同轨道段的飞行轨迹,结果表明,探测器可以按照所设计的轨道飞行到达火星,并被其捕获,成为环绕火星飞行的卫星。

This paper designed a flight orbit from the Earth to the Mars on the basis of some assumptions.The geocentric and heliocentric orbits,and the orbit around the Mars were preliminarily designed by the method of Patched-Conic orbits,based on Hohmann and single-cotangent heliocentric transfer orbits,and the differences were analyzed.The designed trajectory was simulated according to the dynamics model of restricted two-body problem.The conclusion is that the Rover coued arrive at the Mars,and then become a satellite of the Mars along the designed orbits.