Abstract
AbstractA direct transcription method is applied to the problem of multiple‐pass aeroassisted orbital transfer from geostationary orbit to low Earth orbit with a large inclination change. The objective is to provide minimum‐impulse requirements and corresponding optimal trajectories for a gliding vehicle with a high lift‐to‐drag ratio subject to constraints on heating rate, angle of attack, and transfer time. The multiple‐pass aeroassisted orbital transfer problem is set up as a multi‐phase optimal control problem. All relevant parameters, including de‐orbiting, intermediate, and circularizing impulses, are optimized. Copyright © 2002 John Wiley & Sons, Ltd.
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