2006•Unpublished venueRequires access

Optimal Orbit Design of Lunar Modules Soft Landing

Zhou Jing-Yang, Di Zhou, Guang‐Ren Duan

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.

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Available abstract

Key concepts: Soft landing, Moon landing, Lunar orbit, Orbit (dynamics), Trajectory, Aerospace engineering, Optimal control, Computer science