Robust nonlinear attitude control of spacecraft with flexible structures

Yiing-Yuh Lin, Gern Liang Lin

Research output: Chapter in Book/Report/Conference proceedingConference contribution

3 Citations (Scopus)

Abstract

An approach incorporating the input-output feedback linearization and the sliding mode control is presented in this paper for the simultaneous multiaxis reorientation of a rigid spacecraft with flexible structures. Modeling of the dynamic system gives a set of coupled ordinary and partial differential equations, which describe the attitude dynamics of the spacecraft and the motions of the flexible structures, respectively. To apply the proposed attitude control law, the set of nonlinear equations governing the attitude motions were transformed into modified Rodrigues parameters(MRP) representation. Deformations of the flexible structures are assumed small under the control efforts and the governing equations are simplified by applying the mode-shape functions. The attitude feedback gain considering structure stabilization and system uncertainties is further determined by the use of Lyapunov function which ensures the control system to be stable and robust. Major advantage of the method is that only three attitude torque actuators in the hub are required for the proposed control law. Attitude detumbling to reorientation of a model spacecraft was tested and the simulation results were included.

Original languageEnglish
Title of host publicationAstrodynamics Specialist Conference
Pages454-464
Number of pages11
Publication statusPublished - 2000
EventAstrodynamics Specialist Conference 2000 - Dever, CO, United States
Duration: 2000 Aug 142000 Aug 17

Other

OtherAstrodynamics Specialist Conference 2000
CountryUnited States
CityDever, CO
Period00-08-1400-08-17

Fingerprint

attitude control
Flexible structures
Attitude control
Spacecraft
spacecraft
Feedback linearization
retraining
Sliding mode control
Lyapunov functions
Set theory
Nonlinear equations
Ordinary differential equations
spacecraft models
spacecraft motion
Partial differential equations
Dynamical systems
Actuators
Torque
Stabilization
Liapunov functions

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Astronomy and Astrophysics

Cite this

Lin, Y-Y., & Lin, G. L. (2000). Robust nonlinear attitude control of spacecraft with flexible structures. In Astrodynamics Specialist Conference (pp. 454-464)
Lin, Yiing-Yuh ; Lin, Gern Liang. / Robust nonlinear attitude control of spacecraft with flexible structures. Astrodynamics Specialist Conference. 2000. pp. 454-464
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Lin, Y-Y & Lin, GL 2000, Robust nonlinear attitude control of spacecraft with flexible structures. in Astrodynamics Specialist Conference. pp. 454-464, Astrodynamics Specialist Conference 2000, Dever, CO, United States, 00-08-14.

Robust nonlinear attitude control of spacecraft with flexible structures. / Lin, Yiing-Yuh; Lin, Gern Liang.

Astrodynamics Specialist Conference. 2000. p. 454-464.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

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N2 - An approach incorporating the input-output feedback linearization and the sliding mode control is presented in this paper for the simultaneous multiaxis reorientation of a rigid spacecraft with flexible structures. Modeling of the dynamic system gives a set of coupled ordinary and partial differential equations, which describe the attitude dynamics of the spacecraft and the motions of the flexible structures, respectively. To apply the proposed attitude control law, the set of nonlinear equations governing the attitude motions were transformed into modified Rodrigues parameters(MRP) representation. Deformations of the flexible structures are assumed small under the control efforts and the governing equations are simplified by applying the mode-shape functions. The attitude feedback gain considering structure stabilization and system uncertainties is further determined by the use of Lyapunov function which ensures the control system to be stable and robust. Major advantage of the method is that only three attitude torque actuators in the hub are required for the proposed control law. Attitude detumbling to reorientation of a model spacecraft was tested and the simulation results were included.

AB - An approach incorporating the input-output feedback linearization and the sliding mode control is presented in this paper for the simultaneous multiaxis reorientation of a rigid spacecraft with flexible structures. Modeling of the dynamic system gives a set of coupled ordinary and partial differential equations, which describe the attitude dynamics of the spacecraft and the motions of the flexible structures, respectively. To apply the proposed attitude control law, the set of nonlinear equations governing the attitude motions were transformed into modified Rodrigues parameters(MRP) representation. Deformations of the flexible structures are assumed small under the control efforts and the governing equations are simplified by applying the mode-shape functions. The attitude feedback gain considering structure stabilization and system uncertainties is further determined by the use of Lyapunov function which ensures the control system to be stable and robust. Major advantage of the method is that only three attitude torque actuators in the hub are required for the proposed control law. Attitude detumbling to reorientation of a model spacecraft was tested and the simulation results were included.

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Lin Y-Y, Lin GL. Robust nonlinear attitude control of spacecraft with flexible structures. In Astrodynamics Specialist Conference. 2000. p. 454-464