基于轨道倾角约束的小行星探测弹、轨道拼接设计研究

设计一个完整的小行星探测轨道方案需要分别对整条轨迹中的弹道段和轨道段进行优化并拼接。目前拼接设计方法中对弹道段终点约束考虑不足、设计效率低。基于实际弹道运算数据计算了指定运载火箭发射弹道对停泊轨道倾角的约束形式，并研究了火箭偏航能力和射向变化对弹道-轨道拼接后无量纲运载能力的影响。结果表明，算例中的健神星探测窗口不适合低轨道倾角发射弹道。考虑一般情况，高轨道倾角发射弹道可以更好适应飞出地球引力影响球的深空探测类任务需求。根据研究结果，提出了对未来深空探测运载火箭的设计需求。

Research on Ballistic-orbit Splicing in Asteroid Exploration Mission Based on Orbital Inclination Constraint

Ballistic optimization and orbit optimization are both required when designing a complete asteroid exploration orbital scheme.In view of insufficient consideration of terminal constraint of ballistic section and low design efficiency in current splicing design method,constraint form of designated launching trajectory to LEO is calculated based on actual ballistic calculation data.Influence of yaw ability and launching direction angle todimensionless carrying capacity are studied.Results show that detection window of Hygiea is unsuitable for loworbital inclination launch trajectory.Highorbital inclination launch trajectory can better adapt to the requirements of deep-space exploration tasks that fly out of Earth's sphere of influence.According to research results,design requirements for future deep space exploration launch vehicles are proposed.