期刊文献+

空间绳系机器人的多次推力逼近策略研究

Multi-thrust Approach Strategy for Space Tethered Robot
下载PDF
导出
摘要 针对空间绳系机器人近距离逼近问题,提出了基于时间最优的一般N次推力机动策略及算法,由演化得到的等时间N次机动模式和等速度增量N次推力机动模式,能够将多次推力机动策略中复杂的多时间变量求值问题转化为有非线性约束的最小机动时间问题,并利用基于罚函数法的遗传算法进行求解,对空间绳系机器人的近距离逼近问题进行了仿真。仿真表明:一般N次推力机动策略及算法能够很好解决此类多时间变量求值问题;且不需要进行初始速度脉冲修正,相对于基于"时间倒流法"的N次推力策略和连续推力具有较小的机动时间,并在某些情形下相较于后两者以及双冲量机动具有较少的能耗或者较小的最大视界角,为绳系机器人推动逼近设计提供了依据。 Dealing with the multi -thrust approach maneuvers for space tethered robot. Firstly, a strategy of general N -thrust maneuvers based on time optimization was presented in this paper, which was handled by the ge- netic algorithm with penalty function and can be used to allow the issue for solving complicated multiple time variables to transform into the one for constrained nonlinear optimization. Then based on this strategy, two models of N - thrust maneuvers for equal time interval and equal velocity increment can be established, meanwhile two cases of multi - thrust approach maneuvers for space tethered robot were simulated in this paper. Simulation results show that: this strategy, which is no need for impulse correction of the initial velocity, can deal with the issue for solving multiple time variables very well and has several advantages compared with the other strategies of N - thrust maneuvers from the method of "time back" and the continuous -thrust maneuvers even the double impulsive maneuvers, such as smaller maneuvering time and less energy consumption under some situations.
出处 《计算机仿真》 CSCD 北大核心 2012年第8期64-67,158,共5页 Computer Simulation
基金 国家自然基金资助项目(60805034 61005062) 中国博士后基金(2010471640)
关键词 时间最优 有约束非线性最优化 遗传算法 Time optimization Constrained nonlinear optimization Genetic algorithm
  • 相关文献

参考文献8

二级参考文献32

  • 1沈琦,李泽民.具有线性等式约束非线性规划问题的一种新算法[J].重庆大学学报(自然科学版),2006,29(7):98-101. 被引量:3
  • 2杨乐平,朱彦伟,安雪滢.基于组合机动的空间V-bar交会策略[J].国防科技大学学报,2006,28(5):6-10. 被引量:6
  • 3周树德,孙增圻.分布估计算法综述[J].自动化学报,2007,33(2):113-124. 被引量:209
  • 4玄光男 程润伟.遗传算法与工程设计[M].北京:科学出版社,2000..
  • 5Yamanaka K,Andersen F. New State Transition Matrix for Relative Motion on an Arbitrary Elliptical Orbit [J]. Journal of Guidance, Control and Dynamics, 2002, 25 ( 1 ) : 60-66.
  • 6Inalhan G,Tillerson M, How J P. Relative Dynamics and Control of Spacecraft Formations in Eccentric Orbits [J]. Journal of Guidance, Control and Dynamics, 2002, 25 ( 1 ) : 48-59.
  • 7Phillips J M, Kavraki L E. Spacecraft Rendezvous and Docking with Real-Time Randomized Optimization [C]// AIAA Guidance, Navigation, and Control Conference and Exhibit, Austin, Texas, 2003.
  • 8Straight S D. Maneuver Design for Fast Satellite Circumnavigation [ D]. MS Thesis, Astronautical Engineering, Air Force Institute of Technology, AFIT/GA/ENY /04- M05, 2004.
  • 9朱仁璋.近地卫星平面内轨道维持的一种方法[J].宇航学报,1982,3.
  • 10Desplats E, Champetier C. Adaptive Guidance Techniques for HERMES Rendezvous, N92-24440.

共引文献144

相关作者

内容加载中请稍等...

相关机构

内容加载中请稍等...

相关主题

内容加载中请稍等...

浏览历史

内容加载中请稍等...
;
使用帮助 返回顶部