迭代制导在月面上升段的应用研究
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摘要
针对迭代制导在月面上升段的应用开展研究。首先对迭代制导基本原理及其在运载火箭上的应用进行了回顾,给出了月面上升段的动力学模型和迭代制导算法模型。并通过对比应用场景,深入研究了垂直起飞段和迭代制导段的衔接,提出了针对月面上升段特点、兼顾工程可实现性和燃料最优的迭代制导应用方案。对发射点参数、目标轨道参数、迭代初值的获取方式进行了讨论。最后以阿波罗12号飞船载人月面返回的任务场景为算例,进行Monte Carlo模拟打靶数学仿真验证,表明迭代制导在月面上升段具有较高的入轨精度。
The application of iterative guidance in lunar ascent was studied.Firstly,the foundation of iterative guidance and its application in launch vehicle were reviewed,then the dynamic model and iterative guidance algorithm were proposed.By comparing the differences between the two scenes and considering the lunar characteristic,the application scheme of iterative guidance in lunar ascent,with the advantage of both engineering obtainable and fuel optimal,was proposed.The link up of the vertical ascent phase and iterative guidance phase was thoroughly studied.The way of acquiring initial launch point parameters,target orbital parameters and initial parameters of iterative guidance for lunar ascent was discussed.Finally,the iterative guidance was tested by Monte Carlo simulation under the scene of Apollo 12 manned spacecraft returning from lunar surface,which demonstrated a high insert precision.
The application of iterative guidance in lunar ascent was studied.Firstly,the foundation of iterative guidance and its application in launch vehicle were reviewed,then the dynamic model and iterative guidance algorithm were proposed.By comparing the differences between the two scenes and considering the lunar characteristic,the application scheme of iterative guidance in lunar ascent,with the advantage of both engineering obtainable and fuel optimal,was proposed.The link up of the vertical ascent phase and iterative guidance phase was thoroughly studied.The way of acquiring initial launch point parameters,target orbital parameters and initial parameters of iterative guidance for lunar ascent was discussed.Finally,the iterative guidance was tested by Monte Carlo simulation under the scene of Apollo 12 manned spacecraft returning from lunar surface,which demonstrated a high insert precision.
引文
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[11]Nolley J.W.Apollo 12(mission H-1)spacecraft dispersion analysis.Volume 7:Dispersion summary[R].NASA-TM-X-72099,1969.
[2]韩祝斋.用于大型运载火箭的迭代制导方法[J].宇航学报,1983,4(1):9-21.Han Zhuzhai.An Iterative Guidance Method for the Large Launch Vehicle[J].Journal of Astronautics,1983,4(1):9-21.(in Chinese)
[3]程国采.运载火箭显式制导方法研究[J].航天控制,1988,6(3):1-9.Cheng Guocai.Stduy on Explicit Guidance Method[J].Aerospace Control.1988,6(3):1-9.(in Chinese)
[4]陈新民,余梦伦.迭代制导在运载火箭上的应用研究[J].宇航学报,2003,24(5):484-501.Chen Xinmin,Yu Menglun.Study of iterative guidance application to launch vehicles[J].Journal of Astronautics,2003,24(5):484-501.(in Chinese)
[5]周国财.运载火箭迭代制导方法研究[D].西安:西北工业大学,2003.Zhou Guocai.Research on Iterative Guidance Method of Launch Vehicle[D].Xi’an:Northwestern Polytechnic University,2003.(in Chinese)
[6]李华滨,李伶.小型固体运载火箭迭代制导方法研究[J].航天控制,2002,20(2):29-37.Li Huabin,Li Ling.Iterative Explicit Guidance for Small Solid Launch Vehicle[J].Aerospace Control,2002,20(2):29-37.(in Chinese)
[7]吕新广,宋征宇.载人运载火箭迭代制导方法应用研究[J].载人航天,2009,15(1):9-14.Lv Xinguang,Song Zhengyu.Study of Iterative Guidance Engineering Application to Manned Launch Vehicle[J].Manned Spaceflight,2009,15(1):9-14.(in Chinese)
[8]宋征宇.从准确、精确到精益求精—载人航天推动运载火箭制导方法的发展[J].航天控制,2013,31(1):4-10.Song Zhengyu.From Accurate,Precise to Perfect—Manned Space Promotes the Development of Guidance Method on Launch Vehicle[J].Aerospace Control,2013,31(1):4-10.(in Chinese)
[9]宋征宇.采用敏捷发射和自由飞行技术提升运载火箭竞争力[J].航天控制,2013,31(6):3-9.Song Zhengyu.Smart Launch,Free Fly—The Effect of Control System on Elevating Competitiveness of Launch Vehicle[J].Aerospace Control,2013,31(6):3-9.(in Chinese)
[10]吕新广,宋征宇,巩庆海.运载火箭轨迹预测制导方法研究[J].载人航天,2013,19(6):20-24.Lv Xinguang,Song Zhengyu,Gong Qinghai.Research on Trajectory Prediction Guidance for Launch Vehicle[J].Manned Spaceflight,2013,19(6):20-24.(in Chinese)
[11]Nolley J.W.Apollo 12(mission H-1)spacecraft dispersion analysis.Volume 7:Dispersion summary[R].NASA-TM-X-72099,1969.