基于快速交会特殊点变轨策略的航天器发射窗口分析

Analysis of Launch Window in Short Rendezvous Mission Transferred at Special Points

快速交会任务将会随着未来航天任务的增加而成为主流形式,发射窗口的选择是快速交会任务完成的关键因素。当交会任务特殊点变轨策略确定后,若使整个变轨过程中追踪器达到最少燃料消耗,则需要目标器与追踪器初始时刻的相位差在一定范围内。利用交会任务的线性化方程组可以估算该相位差,经过遍历计算可以确定追踪器的相位窗口。另一方面,根据追踪器的异面变轨能力以及不同的发射策略可以确定周期性的平面窗口。本文综合相位窗口和平面窗口的选择方法,在测控等其他条件理想的情况下,得出追踪器最终发射窗口,是快速交会任务完成的必要条件。

With development of space exploration,short rendezvous technique will be widely used in the future. The launch window is very important for the accomplishment of short rendezvous mission.When designing transfer strategy at special points,the phase difference between the target spacecraft and the tracing spacecraft should be within the proper range,so the total fuel consumption will be the least. With the phase difference estimated by linearized equations,the phase launch window of tracing spacecraft can be obtained through traversal calculation,considering the state of target spacecraft. Additionally,the launch strategy and the limit of non-coplanar orbit transferring ability can influence the periodic plane launch window. Supposing the conditions of tracking telemetry and command( TT&C) are ideal,the final launch window will be obtained combining the phase window and the plane window in this issue,which is the essential condition of short rendezvous mission.