Genetic programming of near-minimum-time spacecraft attitude maneuvers

  • Authors:

  • Brian Howley

  • Affiliations:

  • Lockheed Martin Missiles and Space Co, Sunnyvale, CA

  • Venue:
  • GECCO '96 Proceedings of the 1st annual conference on Genetic and evolutionary computation
  • Year:
  • 1996

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Abstract

Genetic programming is used to discover near optimal control laws for the minimum time reorientation of a spacecraft. Two types of acceleration limited maneuvers are considered: maneuvers with zero initial and final angular velocities, and rate limited maneuvers with non-zero initial and terminal velocities. An indexed terminal set was devised to enforce symmetry over the three degrees of freedom. Results for the zero initial and final rate maneuvers are within 2% of published numerical solutions to the problem. The non-zero initial and final rate solution outperforms a manual solution but does not generalize to arbitrary maneuvers.