| 引用本文: | 张万里,王常虹,夏红伟,解伟男.连续小推力航天器轨道交会问题的制导律设计[J].哈尔滨工业大学学报,2012,44(1):36.DOI:10.11918/j.issn.0367-6234.2012.01.008 |
| ZHANG Wan-li,WANG Chang-hong,XIA Hong-wei,XIE Wei-nan.Guidance law of spacecraft for continuous low-thrusts orbital rendezvous problem[J].Journal of Harbin Institute of Technology,2012,44(1):36.DOI:10.11918/j.issn.0367-6234.2012.01.008 |
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| 摘要: |
| 使用高比冲的小推力推进系统为执行机构,设计空间交会问题的燃料最优时间连续制导律.首先给出轨道交会问题的数学模型,并给出最优控制问题的目标函数和约束条件;然后利用直接法将控制变量离散化,通过参数寻优得到对应燃料最优的控制变量参数和转移时间常数;最后针对点火时刻误差问题,分析了实际轨迹与名义最优轨迹的偏差,并利用微分代数工具求取部分控制变量的修正值,以保证航天器满足轨道交会的终端位置约束. |
| 关键词: 空间交会 制导律设计 微分代数 连续小推力 控制变量修正 |
| DOI：10.11918/j.issn.0367-6234.2012.01.008 |
| 分类号:V448.23 |
| 基金项目:哈尔滨工业大学优秀青年教师培养计划资助项目(HITQNJS.2009.007) |
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| Guidance law of spacecraft for continuous low-thrusts orbital rendezvous problem |
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ZHANG Wan-li1,2, WANG Chang-hong3, XIA Hong-wei4, XIE Wei-nan5
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1.Space Control and Inertial Technology Research Center,Harbin Institute of Technology,150001 Harbin,China,;2.China Airborne Missile Academy,471009 Henan Luoyang,China;3.Space Control and Inertial Technology Research Center,Harbin Institute of Technology,150001 Harbin,China;4.Space Control and Inertial Technology Research Center,Harbin Institute of Technology,150002 Harbin,China;5.Space Control and Inertial Technology Research Center,Harbin Institute of Technology,150003 Harbin,China
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| Abstract: |
| The hypothesis of pulse thrust cannot be always satisfied for the short-range stage of space rendezvous.In this article,High isp low-thrust is applied as actuators to solve the fuel optimal control problem of spacecraft rendezvous condition.First,we gave the mathematical models of the orbital rendezvous problem,the performance index function and constraints equations are also presented.Then,we used the direct method to discrete the control variables,though parameter optimization algrithm to get the optimal control variable and rendezvous time constants.Finally,aimed at the fire time deviation,we analyzed the error between the actual trajectory and the nominal trajectory,and obtained the correction value of control variables.Using this correction values,the spacecraft can satisfy the final position constraints and avoid the complex optimization computing process. |
| Key words: space rendezvous guidance law design differential algebraic continuous low-thrust correction of control variables |
