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文章主要研究载人登月舱动力下降段应急返回轨道设计问题。针对应急返回对等待时间的需求,改进了同心椭圆返回轨道方案。将显式制导法应用于应急返回上升段控制中,充分利用了登月舱的剩余速度,得到了满足要求的入轨精度。根据仿真结果确定了利用下降级推力器完成上升段应急返回的准则。在上升段仿真的基础上设计了跟踪段过渡椭圆轨道,显著缩短了登月舱在停泊轨道的等待时间。文中的方法和结论可以为载人登月工程应急返回提供一定的参考价值。
The article mainly studies the design of emergency return orbit of descending section of manned lunar module. For the return of emergency response to the need of waiting time, the concentric elliptical return trajectory scheme has been improved. The explicit guidance method is applied to the control of the emergency return ascent section, which makes full use of the remaining velocity of the lunar module and obtains the orbit accuracy to meet the requirements. According to the simulation results, the criterion of using the downgrade thruster to complete the emergency return of ascending section was determined. The elliptical orbit of the tracking section is designed on the basis of the ascending section simulation, which significantly shortens the waiting time of the lunar module in the docked orbit. The method and conclusion in this paper can provide certain reference value for manned lunar landing emergency return.