›› 2013, Vol. 33 ›› Issue (2): 54-60.doi: 10.3780/j.issn.1000-758X.2013.02.009

• 技术交流 • 上一篇    下一篇

登月舱上升段最优轨迹设计

马克茂, 陈海朋   

  1. (哈尔滨工业大学控制与仿真中心,哈尔滨 150080)
  • 收稿日期:2012-08-20 修回日期:2012-09-28 出版日期:2013-04-25 发布日期:2013-04-25
  • 作者简介:马克茂 1970年生,1998年获哈尔滨工业大学飞行器控制、制导与仿真专业博士学位, 现为哈尔滨工业大学航天学院教授。研究方向为非线性控制、飞行器制导控制。
  • 基金资助:

    国家自然科学基金(61174001,61203185)资助项目

Optimal Trajectory Design for the Lunar Module in Ascent Stage

MA  Ke-Mao, CHEN  Hai-Peng   

  1. Control and Simulation Center, Harbin Institute of Technology, Harbin 150080
  • Received:2012-08-20 Revised:2012-09-28 Online:2013-04-25 Published:2013-04-25

摘要: 为了实现登月舱上升段轨迹的优化,建立了上升段登月舱动力学模型,用单位归一化技术建立了最优控制模型,并以燃料消耗为最优指标,利用Pontryagin极小值原理,将问题转化为时间自由的两点边值问题 TPBVP 。采用了一种基于初值预估方法和向前扫描法求解TPBVP,从而设计出登月舱上升段最优轨迹,并进行了数值仿真。仿真结果表明所设计的算法收敛速度快、可靠性高。

关键词: 离月段轨道, 轨迹设计, 最优控制, 两点边值问题, 登月舱

Abstract: To realize the trajectory optimization of the lunar module in ascent stage, the dynamical model of the lunar module was established and nondimensionalized to construct the optimal control-oriented model. Based on Pontryagin's minimal principle and taking the fuel consumption as the optimizing index, the optimal problem was converted into a time free two-point boundary value problem ( TPBVP) . Using one of initial value hypothesizing methods, combined with the forward sweep algorithm, the TPBVP was solved and the optimized trajectory was obtained. Numerical simulation was conducted. The simulation results justify the rapid convergence rate and high reliability of the proposed method.

Key words: Lunar departure trajectory , Trajectory design , Optimal control, Two-point boundary value problem, Lunar module