月球着陆器过渡轨道的数值仿真

针对月球背面着陆器过渡轨道的选择问题,选择南极艾德肯盆地SPA作为登陆位置,设计了月球正面远月点100km高程,背面SPA为近月点10km高程的椭圆型过渡轨道,利用动力学方法和月球高阶重力场模型GRGM660PRIM,对该轨道进行了仿真分析.结果表明,着陆器的在轨时间接近7d,其中近月点在SPA中心平坦区域的时间超过3d.较长的在轨时间有利于后续着陆决策操作的准备,说明该设计的初始轨道根数具有一定的实际意义,可为着陆器的成功登陆提供一定程度的参考.

Numerical Simulation of the Transition Orbit of Lunar Lander

As to the lander''s transition orbit on the farside of the moon, this paper proposes an elliptic orbit with an apogee of 100 km on the nearside and a perigee over the South Pole-Aitken SPA basin. Employing the dynamic method and the recent high precision gravity field model GRGM660PRIM, we make a simulation and an analysis of this transition orbit. The results indicate that the lander on such an orbit can keep running for approximately 7 days and, especially, remain over the flat region of the SPA for more than 3 days, which is favorable for landing decision. The initial Kepler orbit elements suggested here may be of great help for the lander''s successful landing.