This paper investigates a convex optimization based method that can rapidly generate the fuel optimal asteroid powered descent trajectory. The ultimate goal is to autonomously design the optimal powered descent trajectory on-board the spacecraft immediately prior to the descent burn. Compared to a planetary powered landing problem, the major difficulty is the complex gravity field near the surface of an asteroid that cannot be approximated by a constant gravity field. This paper uses relaxation techniques and a successive solution process that seeks the solution to the original nonlinear, nonconvex problem through the solutions to a sequence of convex optimal control problems.
Rapid Generation of Optimal Asteroid Powered Descent Trajectories Via Convex Optimization
AAS/AIAA Astrodynamics Specialist Conference ; 2015 ; Vail, CO, United States
2015-08-10
Conference paper
No indication
English
Rapid Generation of Time-Optimal Trajectories for Asteroid Landing via Convex Optimization
Online Contents | 2017
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