Trajectory Optimization for Proximity Operations Around Tumbling Geometrical Constraints via Legendre Polynomials Conference Paper uri icon


  • © 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. This paper presents the development of a optimization guidance algorithm capable of generating three-dimensional trajectories enabling a small free-flyer robotic spacecraft to maneuver in close proximity to translating and tumbling satellites. Specifically, the proximity guidance law parameterizes the velocity trajectory using Legendre polynomials and optimizes their coefficients in a two-step fashion. In the first step, a sub-optimal solution that satisfies the boundary conditions, dynamics constraints, and performance limitations is obtained. In the second step, time-permitting, the optimal solution which also minimizes the path length is obtained. The performance of the guidance law is evaluated in simulation results for a fly-around scenario of both a non-cooperative stationary and tumbling target satellite.

author list (cited authors)

  • Shi, J., Ulrich, S., Chamitoff, G. E., Morrell, B. J., & Allen, A.

citation count

  • 2

publication date

  • September 2016