Optimization control for the far-distance rapid cooperative rendezvous of spacecraft with different masses

In this study, the dynamics equation of orbital elements without singularities is used to describe the far-distance cooperative rendezvous of two spacecraft with different masses. The convergent costate vector is obtained using the particle swarm optimization with differential evolution (PSODE) hybr...

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Bibliographic Details
Published in:Aerospace science and technology Vol. 45; pp. 449 - 461
Main Authors: Feng, Weiming, Zhao, Di, Shi, Lei, Yang, Kun, Zhao, Junfeng
Format: Journal Article
Language:English
Published: Elsevier Masson SAS 01.09.2015
Subjects:
Active–passive rendezvous
Algorithms
Cooperative rendezvous
Fuel consumption
Mathematical analysis
Optimization
Optimization control
Particle swarm and differential evolution hybrid algorithm
Rendezvous
Sequential quadratic programming method
Spacecraft
Thrust
Vectors (mathematics)
Particle swarm and differential evolution hybrid algorithm
Cooperative rendezvous
Sequential quadratic programming method
Active–passive rendezvous
Optimization control
ISSN:1270-9638, 1626-3219
Online Access:Get full text
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Summary:In this study, the dynamics equation of orbital elements without singularities is used to describe the far-distance cooperative rendezvous of two spacecraft with different masses. The convergent costate vector is obtained using the particle swarm optimization with differential evolution (PSODE) hybrid algorithm to optimize the far-distance cooperative rendezvous process of the spacecraft. This vector is then used as the initial value for a sequential quadratic programming (SQP) algorithm to again optimize within a small range to obtain a convergent, stable solution. This study focuses on optimizing the control of the far-distance rapid cooperative rendezvous of spacecraft with different masses and explores the interactions between the magnitude of the thrust, the duration of the rendezvous, and the fuel consumption. Optimization simulation results indicate that when the rendezvous duration is limited to within a certain interval, the optimal process for the rendezvous of spacecraft with different masses is a cooperative manoeuvring type, and an increase in thrust will significantly save fuel. In the case of unrestricted rendezvous duration, as the thrust increases, the rendezvous time decreases, but there is little change in the total fuel consumption.
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ISSN:1270-9638
1626-3219
DOI:10.1016/j.ast.2015.06.015