Abstract:The problem of finite-thrust small spacecraft minimum-fuel heat rateconstrained aeroassisted orbital transfer between two low-Earth orbits with inclination change is considered. The trajectory design for a vehicle of small mass and moderate thrust is described in detail and the aeroassisted orbital transfer is posed as a nonlinear optimal control problem. The optimal control problem is solved using a previously developed open-source pseudospectral optimal control software. It is found for heating rate-unconstr… Show more
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