Rigid-Flexible Coupled Dynamic and Control for Thermally Induced Vibration and Attitude Motion of a Spacecraft with Hoop-Truss Antenna
Source abstract
Abstract
As space exploration activities are developing rapidly, spacecraft with large antennas have gained wide acceptance in providing reliable telecommunications and astrophysical observations. In this paper, the dynamic responses and control strategy for a spacecraft with a large hoop-truss antenna under solar flux shock are studied. According to the momentum and angular momentum principle, the rigid-flexible coupled rotational dynamic equation and the translational dynamic equation of the system are established, which include the attitude motion of the rigid main body and the vibration of the antenna. Then, a finite element model of the antenna is established to analytically obtain the corresponding vibration modal shape matrix and natural frequencies. Last, the coupled responses for the attitude motion and vibration are investigated. The corresponding control strategy is designed based on a double-loop structure sliding mode control method. The Lyapunov method is used to demonstrate the global asymptotic stability of the system. Simulations verify the effectiveness of the proposed rigid-flexible coupled model and control strategy.
Source: crossref · Quality: baseline
Research context
OpenAlex topics: Dynamics and Control of Mechanical Systems · Structural Analysis and Optimization · Space Satellite Systems and Control
SciVX discovery tags are terminology-based. OpenAlex topics are source-provided classifications.
Affiliations
Beijing Key Laboratory of Nonlinear Vibrations and Strength of Mechanical Structures, Faculty of Materials and Manufacturing, Beijing University of Technology, Beijing 100124, China
DFH Satellite Co., Ltd., Beijing 100094, China
Funding
National Natural Science Foundation of China · Beijing Municipal Natural Science Foundation
References (33)
Show source-provided references
1. Effects of uncertainties and flexible dynamic contributions on the control of a spacecraft full-coupled model10.1016/j.actaastro.2012.08.018 ↗
2. Thermally-induced bending vibrations of a flexible rolled-up solar-array10.2514/3.25550 ↗
3. Thermally-induced bending-torsion coupling vibration of large scale space structures10.1007/s00466-006-0134-x ↗
4. Thermally induced dynamics of satellite solar panels10.2514/2.3633 ↗
5. Pelton, J.N., Madry, S., and Camacho-Lara, S. (2013). Handbook of Satellite Applications, Springer.10.1007/978-1-4419-7671-0 ↗
6. Small satellite remote sensing and applications—History, current and future10.1080/01431160801914945 ↗
7. Rigid-flexible coupling dynamic modeling and vibration control for flexible spacecraft based on its global analytical modes10.1007/s11431-017-9219-1 ↗
8. Dynamic characteristics of flexible spacecraft with double solar panels subjected to solar radiation10.1016/j.ijmecsci.2018.10.067 ↗
9. Dynamic modeling and vibration control of a coupled rigid-flexible high-order structural system: A comparative study10.1016/j.ast.2020.105875 ↗
10. Nonlinear dynamic modeling and decoupling for rigid-flexible coupled system of spacecraft with rapid maneuver10.1177/0954406219840378 ↗
11. Dynamic analysis of the flexible hub-beam system based on rigid-flexible coupling mechanism
12. Axisa, F. (2005). Modeling of Mechanical Systems—Structural Elements, Elsevier.10.1016/S1874-7051(05)80003-9 ↗
13. A new computer-oriented approach with efficient variables for multibody dynamics with motion constraints10.1016/j.actaastro.2012.06.019 ↗
14. Dynamics of a large scale rigid-flexible multibody system composed of composite laminated plates10.1007/s11044-011-9256-9 ↗
15. Three-dimensional formulation of rigid-flexible multibody systems with flexible beam elements10.1007/s11044-008-9103-9 ↗
16. Géradin, M., and Rixen, D.J. (2014). Mechanical Vibrations: Theory and Application to Structural Dynamics, John Wiley & Sons.
17. Rao, S.S., and Atluri, S.N. (1982). The Finite Element Method in Engineering, Pergamon Press.
18. Finite-elements with increased freedom in choosing shape functions10.1002/nme.1620200405 ↗
19. The extended free formulation of finite elements in linear elasticity10.1115/1.3176135 ↗
20. Thermal-structural dynamic analysis of a satellite antenna with the cable-network and hoop-truss supports10.1080/01495739.2019.1649613 ↗
21. A compendium of FEM integration formulas for symbolic work10.1108/02644400410554362 ↗
22. Thermally induced vibrations of solar panel and their coupling with satellite10.1142/S1758825113500312 ↗
23. Thermal-structural analysis of large deployable space antenna under extreme heat loads10.1080/01495739.2016.1189776 ↗
24. Thermoelastic-Structural Analysis of Space Thin-Walled Beam Under Solar Flux10.2514/1.J057793 ↗
25. Neural adaptive integral sliding mode control for attitude tracking of flexible spacecraft with signal quantisation and actuator nonlinearity10.1080/00207721.2020.1803441 ↗
26. Sliding mode maneuvering control and active vibration damping of three-axis stabilized flexible spacecraft with actuator dynamics10.1007/s11071-007-9274-6 ↗
27. Adaptive robust attitude control of a flexible spacecraft10.1002/rnc.1051 ↗
28. Networked flexible spacecraft attitude maneuver based on adaptive fuzzy sliding mode control10.1016/j.actaastro.2009.04.004 ↗
29. State observation and variable structure control of rotational maneuvers of a flexible spacecraft10.1016/0094-5765(89)90134-3 ↗
30. A composite control scheme for attitude maneuvering and elastic mode stabilization of flexible spacecraft with measurable output feedback10.1016/j.ast.2007.06.007 ↗
31. A new inclination cranking method for a flexible spinning solar sail10.1109/TAES.2015.140117 ↗
32. Input-output linearization minimum sliding-mode error feedback control for spacecraft formation with large perturbations
33. Flexible spacecraft attitude maneuver by application of sliding mode control10.1016/j.actaastro.2005.04.009 ↗