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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Veröffentlicht in:	Aerospace science and technology Jg. 45; S. 449 - 461
Hauptverfasser:	Feng, Weiming, Zhao, Di, Shi, Lei, Yang, Kun, Zhao, Junfeng
Format:	Journal Article
Sprache:	Englisch
Veröffentlicht:	Elsevier Masson SAS 01.09.2015
Schlagworte:	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
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Abstract	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.
AbstractList	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. 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.
Author	Feng, Weiming Shi, Lei Zhao, Di Zhao, Junfeng Yang, Kun
Author_xml	– sequence: 1 givenname: Weiming surname: Feng fullname: Feng, Weiming email: fwm@sdu.edu.cn organization: Department of Engineering Mechanics, Shandong University, Jinan, 260062, China – sequence: 2 givenname: Di surname: Zhao fullname: Zhao, Di organization: Department of Engineering Mechanics, Shandong University, Jinan, 260062, China – sequence: 3 givenname: Lei orcidid: 0000-0002-7854-0328 surname: Shi fullname: Shi, Lei organization: Department of Mechanical Engineering & Materials Science, Washington University in St. Louis, St. Louis, 63130, United States – sequence: 4 givenname: Kun surname: Yang fullname: Yang, Kun organization: Department of Engineering Mechanics, Shandong University, Jinan, 260062, China – sequence: 5 givenname: Junfeng surname: Zhao fullname: Zhao, Junfeng organization: Department of Engineering Mechanics, Shandong University, Jinan, 260062, China
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Keywords	Particle swarm and differential evolution hybrid algorithm Cooperative rendezvous Sequential quadratic programming method Active–passive rendezvous Optimization control
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SubjectTerms	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)
Title	Optimization control for the far-distance rapid cooperative rendezvous of spacecraft with different masses
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