Guidance Solutions for Spacecraft Planar Rephasing and Rendezvous Using Input Shaping

摘要

The results presented in this Note demonstrate that input-shaping theory can be exploited to derive a general analytical guidance solution for relative orbital maneuvering as a function of shaper delay Δt and thrust angle α. The computed solutions allow a spacecraft to move from an initial location along its orbit to a desired position on the same course, as well as to fly around a desired point placed ahead or behind its initial position. It is worth remarking that the derived trajectories bring the spacecraft from an equilibrium configuration to a new equilibrium one, where equilibrium means a nondrifting relative state.