A low-thrust guidance law based on Lyapunov feedback control and hybrid genetic algorithm

Purpose - This paper seeks to examine the development of the on-board guidance law for multi-revolutions orbit transfer spacecraft with low-thrust propulsion systems.Design methodology approach - In the research, first, a set of equinoctial elements is utilized to avoid the singularities in dynamica...

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Veröffentlicht in:Aircraft Engineering and Aerospace Technology Jg. 79; H. 2; S. 144 - 149
Hauptverfasser: Yuan, Ren, Pingyuan, Cui, Enjie, Luan
Format: Journal Article
Sprache:Englisch
Veröffentlicht: Bradford Emerald Group Publishing Limited 30.01.2007
Schlagworte:
Algorithms
Control systems
Control theory
Efficiency
Feedback
Feedback control
Genetic algorithms
Guidance (motion)
Liapunov functions
Performance enhancement
Performance indices
Propulsion system design
Singularities
Spacecraft
Spacecraft guidance
Stationkeeping
Studies
Trajectory optimization
China
Feedback
Algorithmic languages
ISSN:1748-8842, 0002-2667, 1758-4213
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Abstract Purpose - This paper seeks to examine the development of the on-board guidance law for multi-revolutions orbit transfer spacecraft with low-thrust propulsion systems.Design methodology approach - In the research, first, a set of equinoctial elements is utilized to avoid the singularities in dynamical equation of classical orbit elements. A thruster switch law is derived by analyzing the efficiency of the changing of each orbit elements. Second, by using the theory of Lyapunov feedback control, analytic expressions of thrust angles are derived. Finally, the weights of the Lyapunov function are adjusted by hybrid genetic algorithm to improve the performance of the guidance law.Findings - First, the dynamical equations of classical orbit elements are always singularity during the orbit transfer. By using modified equinoctial elements, these singularities could be avoided. Second, the trajectory is sensitive to the weights in Lyapunov function. With reasonable weights, the key parameters under the control of the guidance law presented in this paper are very close to that of optimal trajectory.Research limitations implications - In further research, some dynamical weights methods will be used in the control law to improve the performance index, and approach the optimal solution.Practical implications - The guidance law presented in this paper could be easily used as an on-board algorithm for the multi-revolutions orbit transfer or stationkeeping. Furthermore, it could also be utilized as an initial design method for low-thrust orbit transfer.Originality value - Providing a low-thrust guidance law by combining the concept of Lyapunov feedback control with hybrid genetic algorithm. This method has a super convergence and a low-computational cost.
AbstractList Purpose - This paper seeks to examine the development of the on-board guidance law for multi-revolutions orbit transfer spacecraft with low-thrust propulsion systems. Design/methodology/approach - In the research, first, a set of equinoctial elements is utilized to avoid the singularities in dynamical equation of classical orbit elements. A thruster switch law is derived by analyzing the efficiency of the changing of each orbit elements. Second, by using the theory of Lyapunov feedback control, analytic expressions of thrust angles are derived. Finally, the weights of the Lyapunov function are adjusted by hybrid genetic algorithm to improve the performance of the guidance law. Findings - First, the dynamical equations of classical orbit elements are always singularity during the orbit transfer. By using modified equinoctial elements, these singularities could be avoided. Second, the trajectory is sensitive to the weights in Lyapunov function. With reasonable weights, the key parameters under the control of the guidance law presented in this paper are very close to that of optimal trajectory. Research limitations/implications - In further research, some dynamical weights methods will be used in the control law to improve the performance index, and approach the optimal solution. Practical implications - The guidance law presented in this paper could be easily used as an on-board algorithm for the multi-revolutions orbit transfer or stationkeeping. Furthermore, it could also be utilized as an initial design method for low-thrust orbit transfer. Originality/value - Providing a low-thrust guidance law by combining the concept of Lyapunov feedback control with hybrid genetic algorithm. This method has a super convergence and a low-computational cost. [PUBLICATION ABSTRACT]
Purpose - This paper seeks to examine the development of the on-board guidance law for multi-revolutions orbit transfer spacecraft with low-thrust propulsion systems.Design methodology approach - In the research, first, a set of equinoctial elements is utilized to avoid the singularities in dynamical equation of classical orbit elements. A thruster switch law is derived by analyzing the efficiency of the changing of each orbit elements. Second, by using the theory of Lyapunov feedback control, analytic expressions of thrust angles are derived. Finally, the weights of the Lyapunov function are adjusted by hybrid genetic algorithm to improve the performance of the guidance law.Findings - First, the dynamical equations of classical orbit elements are always singularity during the orbit transfer. By using modified equinoctial elements, these singularities could be avoided. Second, the trajectory is sensitive to the weights in Lyapunov function. With reasonable weights, the key parameters under the control of the guidance law presented in this paper are very close to that of optimal trajectory.Research limitations implications - In further research, some dynamical weights methods will be used in the control law to improve the performance index, and approach the optimal solution.Practical implications - The guidance law presented in this paper could be easily used as an on-board algorithm for the multi-revolutions orbit transfer or stationkeeping. Furthermore, it could also be utilized as an initial design method for low-thrust orbit transfer.Originality value - Providing a low-thrust guidance law by combining the concept of Lyapunov feedback control with hybrid genetic algorithm. This method has a super convergence and a low-computational cost.
Design/methodology/approach - In the research, first, a set of equinoctial elements is utilized to avoid the singularities in dynamical equation of classical orbit elements. A thruster switch law is derived by analyzing the efficiency of the changing of each orbit elements. Second, by using the theory of Lyapunov feedback control, analytic expressions of thrust angles are derived. Finally, the weights of the Lyapunov function are adjusted by hybrid genetic algorithm to improve the performance of the guidance law. Findings - First, the dynamical equations of classical orbit elements are always singularity during the orbit transfer. By using modified equinoctial elements, these singularities could be avoided. Second, the trajectory is sensitive to the weights in Lyapunov function. With reasonable weights, the key parameters under the control of the guidance law presented in this paper are very close to that of optimal trajectory. Research limitations/implications - In further research, some dynamical weights methods will be used in the control law to improve the performance index, and approach the optimal solution. Practical implications - The guidance law presented in this paper could be easily used as an on-board algorithm for the multi-revolutions orbit transfer or stationkeeping. Furthermore, it could also be utilized as an initial design method for low-thrust orbit transfer. Originality/value - Providing a low-thrust guidance law by combining the concept of Lyapunov feedback control with hybrid genetic algorithm. This method has a super convergence and a low-computational cost.
Author Enjie, Luan
Pingyuan, Cui
Yuan, Ren
Author_xml – sequence: 1
  givenname: Ren
  surname: Yuan
  fullname: Yuan, Ren
  organization: Harbin Institute of Technology, Deep Space Exploration Research Center, Harbin, People's Republic of China
– sequence: 2
  givenname: Cui
  surname: Pingyuan
  fullname: Pingyuan, Cui
  organization: Harbin Institute of Technology, Deep Space Exploration Research Center, Harbin, People's Republic of China
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  givenname: Luan
  surname: Enjie
  fullname: Enjie, Luan
  organization: China National Space Administration, Beijing, People's Republic of China
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Cites_doi 10.3934/dcdsb.2002.2.57
10.2514/4.861543
10.2514/2.4344
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Snippet Purpose - This paper seeks to examine the development of the on-board guidance law for multi-revolutions orbit transfer spacecraft with low-thrust propulsion...
Purpose – This paper seeks to examine the development of the on‐board guidance law for multi‐revolutions orbit transfer spacecraft with low‐thrust propulsion...
Design/methodology/approach - In the research, first, a set of equinoctial elements is utilized to avoid the singularities in dynamical equation of classical...
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StartPage 144
SubjectTerms Algorithms
Control systems
Control theory
Efficiency
Feedback
Feedback control
Genetic algorithms
Guidance (motion)
Liapunov functions
Performance enhancement
Performance indices
Propulsion system design
Singularities
Spacecraft
Spacecraft guidance
Stationkeeping
Studies
Trajectory optimization
Title A low-thrust guidance law based on Lyapunov feedback control and hybrid genetic algorithm
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