论文部分内容阅读
根据推进方式和是否采用金星借力,火星转移轨道分为大推力直接转移轨道、大推力金星借力转移轨道、小推力直接转移轨道和小推力金星借力转移轨道4类。传统的轨道设计方法只是针对某一类特定的转移方案进行轨道优化,而并未针对不同的转移方案进行详细对比分析。文章以2020/2022年发射窗口为例,针对4类基本火星转移轨道进行研究。首先,基于不同轨道初始设计方法,对4类轨道进行了初始设计,得到了每类转移方案的能量最优转移轨道。然后,基于设计结果和能耗对4类转移方案进行了横向对比分析,得到了不同策略下的转移轨道的特性。基于小推力的火星探测任务轨道对发射能量要求低;大推力直接转移和借力金星的发射窗口交替分布,可以互为备份;基于小推力推进的探测器采用金星借力转移策略相比直接转移能够减少10%的能耗,优势十分明显。
According to the mode of propulsion and whether or not to use Venus, Mars transfer orbit is divided into large thrust direct transfer orbit, large thrust Venus levitation transfer orbit, small thrust direct transfer orbit and small thrust Venus levitation transfer orbit 4 categories. The traditional orbit design method is only for a particular type of transfer program orbit optimization, but not for different transfer programs for a detailed comparative analysis. Taking the launch window of 2020/2022 as an example, the paper studies the four types of basic Mars orbitals. Firstly, based on the initial design of different orbits, the initial design of four kinds of orbits has been done, and the optimal energy transfer orbit for each type of transfer scheme has been obtained. Then, based on the design results and energy consumption, the four types of transfer schemes are compared horizontally, and the characteristics of transfer orbits under different strategies are obtained. The small orbit-thrust Mars orbit has low requirements on the launch energy; the large thrust direct transfer and the leveraging Venus emission window are alternately distributed and can back up each other; the detector based on small thrust propulsion uses the Venus levitation transfer strategy compared to the direct transfer Can reduce energy consumption by 10%, the advantage is very obvious.