Continuum Modeling and Boundary Control of a Satellite with a Large Space Truss Structure
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| Published in: | Aerospace vol. 11, no. 1 (2024), p. 54 |
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| Other Authors: | , |
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MDPI AG
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| Online Access: | Citation/Abstract Full Text + Graphics Full Text - PDF |
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| 024 | 7 | |a 10.3390/aerospace11010054 |2 doi | |
| 035 | |a 2918503825 | ||
| 045 | 2 | |b d20240101 |b d20241231 | |
| 084 | |a 231330 |2 nlm | ||
| 100 | 1 | |a Cao, Shilei |u School of Instrumentation Science and Engineering, Harbin Institute of Technology, Harbin 150001, China; <email>liujian@hit.edu.cn</email> | |
| 245 | 1 | |a Continuum Modeling and Boundary Control of a Satellite with a Large Space Truss Structure | |
| 260 | |b MDPI AG |c 2024 | ||
| 513 | |a Journal Article | ||
| 520 | 3 | |a Due to its advantages of easy deployment and high stiffness-to-mass ratio, the utilization of truss structures for constructing large satellites presents an appealing solution for modern space missions, including Earth observation and astronomy. However, the dimensions of the traditional finite element model for a satellite with a large space truss structure become exceedingly large as the structure’s size increases. The control system design process based on the finite element model is complex and time-consuming. This paper employs the continuum modeling method to represent the truss structure as a continuous entity. The bending vibrations of the truss structure are encapsulated by a simplified partial differential equation (PDE), as opposed to the more intricate traditional finite element model. Simultaneously, the satellite’s attitude motion is characterized by an ordinary differential equation (ODE). Building upon this coupled PDE-ODE model, a boundary control law that only requires sensors/actuators at the boundary is formulated to effectively mitigate structural vibrations and regulate the satellite’s attitude. The exponential stability of this closed-loop system is scrutinized using Lyapunov’s direct method. The simulation results affirm that the continuum modeling method is indeed well-suited for satellites endowed with substantial truss structures, and the proposed boundary law proves to be highly effective in both attitude tracking and vibration suppression. | |
| 653 | |a Finite element method | ||
| 653 | |a Smart materials | ||
| 653 | |a Astronomy | ||
| 653 | |a Control systems | ||
| 653 | |a Investigations | ||
| 653 | |a Boundary control | ||
| 653 | |a Vibration control | ||
| 653 | |a Systems design | ||
| 653 | |a Continuum modeling | ||
| 653 | |a Closed loops | ||
| 653 | |a Modelling | ||
| 653 | |a Performance evaluation | ||
| 653 | |a Fuzzy logic | ||
| 653 | |a Vibration | ||
| 653 | |a Simulation | ||
| 653 | |a Control theory | ||
| 653 | |a Partial differential equations | ||
| 653 | |a Space missions | ||
| 653 | |a Control systems design | ||
| 653 | |a Attitude stability | ||
| 653 | |a Genetic algorithms | ||
| 653 | |a Sensors | ||
| 653 | |a Controllers | ||
| 653 | |a Design | ||
| 653 | |a Mathematical models | ||
| 653 | |a Satellites | ||
| 653 | |a Trussed structures | ||
| 653 | |a Satellite tracking | ||
| 653 | |a Feedback control | ||
| 653 | |a Actuators | ||
| 700 | 1 | |a Yang, Man |u HIT Satellite Technology Co., Ltd., Harbin 150001, China; <email>yangman0503@163.com</email> | |
| 700 | 1 | |a Liu, Jian |u School of Instrumentation Science and Engineering, Harbin Institute of Technology, Harbin 150001, China; <email>liujian@hit.edu.cn</email> | |
| 773 | 0 | |t Aerospace |g vol. 11, no. 1 (2024), p. 54 | |
| 786 | 0 | |d ProQuest |t Advanced Technologies & Aerospace Database | |
| 856 | 4 | 1 | |3 Citation/Abstract |u https://www.proquest.com/docview/2918503825/abstract/embedded/7BTGNMKEMPT1V9Z2?source=fedsrch |
| 856 | 4 | 0 | |3 Full Text + Graphics |u https://www.proquest.com/docview/2918503825/fulltextwithgraphics/embedded/7BTGNMKEMPT1V9Z2?source=fedsrch |
| 856 | 4 | 0 | |3 Full Text - PDF |u https://www.proquest.com/docview/2918503825/fulltextPDF/embedded/7BTGNMKEMPT1V9Z2?source=fedsrch |