Optimal Orbit Transfer For Continuous Thrust Spacecraft Using Sequential Convex Programming

Trajectory optimization is a fundamental problem for spacecraft missions.The key is to calculate the trajectory and control signal at the same time using a fast method.Based on impulse thrust,constant thrust and viable thrust,there are a large amount of work have been done.Complex dynamic model make the problem more challenging.The work is focused on orbit transfer problem of changeable thrust spacecraft and its sequentil convex solution with convex optimization method.This thesis provide the convex formulation for fixed-final-time coplanar optimal orbit transfer.The efficiency of sequential convex optimization programming is validated.Within this frame,the ability of fixed time orbit rephrasing is studied.Based on fixed final transfer angle orbit transfer problem,free-final-time coplanar orbit transfer problem is studied,with examples in free-final-time fuel optimal coplanar orbit transfer.Influence of final time constraint on final fuel consumption index is analyzed.Spatial orbit transfer problem is studied,with a formulation for convex optimization proposed to solve the problem.Examples demonstrate the effectiveness of the proposed formulation.