Initial Guess Structure for the Optimal Lunar Landing Trajectory

摘要：

Generally, the lunar landing stage is divided intotwo distinct phases: de-orbit and descent, and this descent phase is usually divided into two sub-phases: braking and approach. And the optimization problem of minimal energy is usually focused on descent phases. In these approaches, the optimal control approaches are usually used to design the minimal fuel landing trajectory. These optimal control problem can be solved by using parameter optimization techniques such as SQP, PSO etc.. However, to find these initial co-state values to satisfied boundary conditions, the numerical approaches have some difficulty to choosing the initial guess. Sometimes the solvers cannot be converged to the optimal solution by choosing the unsuitable initial guessing. Therefore, the initial guess problem is important For this initial guessing, in this paper, the initial guess structure will be suggested.

关键词： lunar landing optimal trajectory initial guess structure

作者: Cho Donghyun Lee Donghun Bang Hyochoong

作者单位: Division of Aerospace Engineering, School of Mechanical, Aerospace and Systems Engineering,KAIST,Daejeon 305701, KOREA

会议类型: 国际会议

会议名称: 2010 Asia-Pacific International Symposium on Aerospace Technology(2010 亚太航空航天技术研讨会 APISAT 2010)

会议地点: 西安

会议语种:英文

页码: 640-643

在线出版日期: 2010-09-01（万方平台首次上网日期，不代表论文的发表时间）