DocumentCode
3215312
Title
Optimal Orbit Design of Lunar Modules Soft Landing
Author
Zhou Jing-yang ; Zhou Di ; Duan Guang-Ren
Author_Institution
Harbin Inst. of Technol., China
fYear
2006
fDate
7-11 Aug. 2006
Firstpage
2226
Lastpage
2229
Abstract
Precise three dimensional dynamics for lunar soft landing were presented. To realize the minimal fuel strategy, an optimal control law was proposed based on the maximum principle. By solving the two-point boundary value problem, the optimal trajectory of the lunar soft landing was obtained. Performance of the proposed control law was verified by simulation.
Keywords
aerospace control; boundary-value problems; fuel optimal control; maximum principle; position control; boundary value problem; lunar module soft landing; maximum principle; minimal fuel strategy; optimal control law; optimal orbit design; optimal trajectory; Boundary value problems; Control systems; Fuels; IEEE catalog; Moon; Optimal control; Lunar Module; Optimal Trajectory; Soft Lading;
fLanguage
English
Publisher
ieee
Conference_Titel
Control Conference, 2006. CCC 2006. Chinese
Conference_Location
Harbin
Print_ISBN
7-81077-802-1
Type
conf
DOI
10.1109/CHICC.2006.280951
Filename
4060499
Link To Document