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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。
Based on some basic assumptions, a preliminary design of the orbit from the earth mooring orbit to launch the detector reaches Mars. The concentric curved splicing method is used to design the orbit of the center of the detector, the center of the earth and the center of the space of the Mars when two different methods are used, The characteristics of the design method. According to the dynamical model of the restricted two-body problem, the trajectory of the detector in different orbit sections is simulated. The result shows that the detector can fly to Mars according to the designed orbit and be captured as a satellite orbiting Mars.