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论文:2012,Vol:30,Issue(1):50-55 |
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引用本文： |
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刘睿, 周军, 刘莹莹. 载人登月舱动力下降段应急返回轨道设计[J]. 西北工业大学 |
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Liu Rui, Zhou Jun, Liu Yingying. Exploring Abort of Manned Lunar Module from Powered Descent Phase[J]. Northwestern polytechnical university |
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| 载人登月舱动力下降段应急返回轨道设计 |
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| 刘睿, 周军, 刘莹莹 |
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| 西北工业大学 精确制导与控制研究所,陕西 西安 710072 |
| 摘要: |
| 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。 |
| 关键词:
载人登月
应急返回
显式制导
过渡轨道
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| Exploring Abort of Manned Lunar Module from Powered Descent Phase |
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| Liu Rui, Zhou Jun, Liu Yingying |
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| Institute of Precision Guidance and Control,Northwestern Polytechnical University,Xi'an, 710072,China |
| Abstract: |
| Sections 1, 2 and 3 explain the exploration mentioned in the title.Tables 2, 4 and 5,and Figs.1 and4,present the results of our exploration,utilizing the published parameters of the Apollo 17; in addition,we ana-lyzed the results.The core of sections 1, 2 and 3 consists of: "We mainly focus on the orbit design of the mannedlunar module abort from powered descent phase.Firstly,in order to meet the requirements of the manned spacecraftaborting,an improved co-elliptic technique was proposed.Secondly,the expression of the explicit guidance law forascent phase in abort was deduced.Then, with the help of Simulink tools this guidance law was proved to be preciseenough when used in ascent phase,for the error in the height could be neglected and the error in the velocity waswithin a few meters per second.Finally,the height of apolune of the ellipse transfer orbit was designed based on theresult of the ascent phase,which effectively shortened the waiting time of lunar module.Only abort from the pre-phase of powered descent needs this technique."Section 4 presents our preliminary main conclusions,which maybe useful for the manned lunar project. |
| Key words:
algorithms
analysis
computer software
control
dynamics
design
energy conservation
errors
fu-els
lift
lunar missions
models
nonlinear systems
online systems
optimization
orbits
simulation
spacecraft
strategic planning
abort from descent
explicit guidance
manned lunar module
transfer orbit
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| 收稿日期: 2011-04-16
修回日期:
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| DOI: |
| 通讯作者:
Email： |
| 作者简介: 刘睿(1985-),女,西北工业大学助理工程师、博士研究生,主要从事航天器轨道动力学与控制的研究。
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| 相关功能 |
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| 作者相关文章 |
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| 刘睿 在本刊中的所有文章 |
| 周军 在本刊中的所有文章 |
| 刘莹莹 在本刊中的所有文章 |
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参考文献: |
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[2] Dole S H. Contingency Planning for Space-Flight Emergencies. AIAA 4th Annual Meeting and Technical Display，California，1967
[3] Bell J A. Planned Rendezvous Technique Following LM Abort from Powered Descent. NASA MSC Internal Note NO. 69-FM-46，1969
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[6] Hanssen Veit. Mission G Requirements for the RTCC: Nominal Ascent and Abort from Descent. NASA MSC Internal Note NO．68-FM-140, 1968
[7] Fridge E M. Logic and Equations for the Real-Time Calculations of the Powered Descent Abort Constants. NASA MSC InternalNote NO. 69-FM-225, 1969
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[10] Wolfer B M，Gatlin W P. Roles of the Ground and Flight Crew in Apollo Operations. AIAA Man's Role in Space Conference．Cocoa Beach，Florida, 1972 |
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