月球着陆器过渡轨道的数值仿真
Numerical Simulation of the Transition Orbit of Lunar Lander

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100 km高程，背面SPA为近月点10 km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7 d，其中近月点在SPA中心平坦区域的时间超过3 d.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.
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