载人火星任务气动捕获段轨道初步设计

Preliminary Aerocapture Trajectories Design for Manned Mars Mission

以载人火星探测任务为背景,建立了气动捕获段轨道的三自由度动力学模型。给出了满足任务要求的约束条件,求解了进入走廊,并分析了相关参数对轨道的影响。在此基础上采用遗传算法与序列二次规划相结合的串行优化策略,分析了通过侧倾角控制可达的航程范围。研究表明,气动捕获相对于直接减速入轨在能量需求上有显著优势,且具备一定的机动能力,是一种较为可行的载人火星飞船入轨方式。

In view of human exploration of Mars,the three-degree-of-freedom dynamic model of aerocapture trajectory was established. The constraints which satisfy the mission requirements were listed,and the entry corridor was obtained. The influence of some parameters on the trajectory shape was analyzed. A pipelining optimization approach of Genetic Algorithm（GA） and Sequential Quadratic Programming（SQP） were introduced to analyze the attainable region of flight through bank angle control. The results indicate that,compared with direct deceleration by retro-rocket,aerocapture mode is highly advantageous in energy requirement,and has good maneuver ability. It is a feasible approach for manned spacecraft to insert into Mars orbit.