Finite Thrust Transfer Strategy Designing for Low Energy Moon Return Based on GPM/VSM

In a low energy moon return mission, due to the weak stability of the orbit, it is necessary to implement an accurate orbital maneuver to guarantee a successful return. During the process of getting the optimal thrust control with these two kinds of methods, it is hard to guess the initial value of...

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Bibliographic Details
Published inInternational journal of automation and computing Vol. 12; no. 5; pp. 490 - 496
Main Authors Yue, Liu, Jing, Wu-Xing, Xiao, Ying-Ying
Format Journal Article
LanguageEnglish
Published Beijing Institute of Automation, Chinese Academy of Sciences 01.10.2015
Springer Nature B.V
Subjects
and
CAE) and Design
Computer Applications
Computer-Aided Engineering (CAD
Control
Design
Energy
Engineering
Mathematical analysis
Mechatronics
Moon;trajectories;optimization
Optimal control
Orbital maneuvers
Orbital rendezvous
Orbital stability
Regular Paper
Robotics
Rocket launches
simulation;virt
Space rendezvous
Spacecraft
Spectral methods
Thrust control
Gauss pseudo-spectral method
Moon
optimization and simulation
virtual satellite method
trajectories
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Summary:In a low energy moon return mission, due to the weak stability of the orbit, it is necessary to implement an accurate orbital maneuver to guarantee a successful return. During the process of getting the optimal thrust control with these two kinds of methods, it is hard to guess the initial value of the co-states in the indirect method while a large amount of calculation is needed to insure the precision in the direct method. To solve the problem, in this paper a combined method is given which has the merit of both direct and indirect methods. In this method, the virtual satellite method(VSM) and the Gauss pseudo-spectral method(GPM)are applied, while the fuel optimal control strategy is computed with GPM to carry out a soft rendezvous between the spacecraft and a hypothetical virtual satellite running on the nominal low energy return orbit so that the spacecraft will enter the return orbit accurately. Compared with the direct and indirect methods, this combined method can avoid guessing the initial value of the co-states and the complexity of calculation is acceptable. According to the simulation results, the spacecraft is inserted to the target return orbit with a high accuracy and also the optimization is very effective.
Bibliography:Moon;trajectories;optimization and simulation;virt
Liu Yue;Wu-Xing Jing;Ying-Ying Xiao;Department of Astronautics Engineering, Harbin Institute of Technology
11-5350/TP
In a low energy moon return mission, due to the weak stability of the orbit, it is necessary to implement an accurate orbital maneuver to guarantee a successful return. During the process of getting the optimal thrust control with these two kinds of methods, it is hard to guess the initial value of the co-states in the indirect method while a large amount of calculation is needed to insure the precision in the direct method. To solve the problem, in this paper a combined method is given which has the merit of both direct and indirect methods. In this method, the virtual satellite method(VSM) and the Gauss pseudo-spectral method(GPM)are applied, while the fuel optimal control strategy is computed with GPM to carry out a soft rendezvous between the spacecraft and a hypothetical virtual satellite running on the nominal low energy return orbit so that the spacecraft will enter the return orbit accurately. Compared with the direct and indirect methods, this combined method can avoid guessing the initial value of the co-states and the complexity of calculation is acceptable. According to the simulation results, the spacecraft is inserted to the target return orbit with a high accuracy and also the optimization is very effective.
ISSN:1476-8186
2153-182X
1751-8520
2153-1838
DOI:10.1007/s11633-014-0869-3