The problem of spacecraft trajectory optimization

Research output: Chapter in Book/Report/Conference proceedingChapter

Abstract

Introduction The subject of spacecraft trajectory optimization has a long and interesting history. The problem can be simply stated as the determination of a trajectory for a spacecraft that satisfies specified initial and terminal conditions, that is conducting a required mission, while minimizing some quantity of importance. The most common objective is to minimize the propellant required or equivalently to maximize the fraction of the spacecraft that is not devoted to propellant. of course, as is common in the optimization of continuous dynamical systems, it is usually necessary to provide some practical upper bound for the final time or the optimizer will trade time for propellant. There are also spacecraft trajectory problems where minimizing flight time is the important thing, or problems, for example those using continuous thrust, where minimizing flight time and minimizing propellant use are synonymous. Except in very special (integrable) cases, which reduce naturally to parameter optimization problems, the problem is a continuous optimization problem of an especially complicated kind.

Original languageEnglish (US)
Title of host publicationSpacecraft Trajectory Optimization
PublisherCambridge University Press
Pages1-15
Number of pages15
ISBN (Electronic)9780511778025
ISBN (Print)9780521518505
DOIs
StatePublished - Jan 1 2010

ASJC Scopus subject areas

  • Engineering(all)

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