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Continuum Modeling and Boundary Control of a Satellite with a Large Space Truss Structure

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Publicado en:Aerospace vol. 11, no. 1 (2024), p. 54
Autor principal: Cao, Shilei
Otros Autores: Yang, Man, Liu, Jian
Publicado:
MDPI AG
Materias:
Finite element method
Smart materials
Astronomy
Control systems
Investigations
Boundary control
Vibration control
Systems design
Continuum modeling
Closed loops
Modelling
Performance evaluation
Fuzzy logic
Vibration
Simulation
Control theory
Partial differential equations
Space missions
Control systems design
Attitude stability
Genetic algorithms
Sensors
Controllers
Design
Mathematical models
Satellites
Trussed structures
Satellite tracking
Feedback control
Actuators
Acceso en línea:Citation/Abstract
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Resumen: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.
ISSN:2226-4310
DOI:10.3390/aerospace11010054
Fuente:Advanced Technologies & Aerospace Database