Nonlinear attitude dynamics and control for satellite tethered formation flying in three-dimensional free space

Insu Chang, Sang Young Park, Kyu Hong Choi

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

1 Citation (Scopus)

Abstract

The objective of the current research is to analyze the attitude dynamics and control of satellite tethered formation flying where the tethered units are modeled as extended rigid bodies. The three inline array system is used and the general formulation of the governing equations of motions of the system is obtained through a Lagrangian approach. In the research, attitude motions of the tethered satellite system are analyzed in the three-dimensional free space system to complement previous works. Centralized and decentralized approaches are applied to the dynamic system to compare the performance for controlling the attitude motion. The State-Dependent Riccati Equation (SDRE) controller is used to regulate the attitude errors. The stability region for the SDRE controlled tethered satellite system is estimated using a numerical method. The results show globally asymptotic stability for the control method.

Original languageEnglish
Title of host publicationSpace Flight Mechanics 2008 - Advances in the Astronautical Sciences, Proceedings of the AAS/AIAA Space Flight Mechanics Meeting
Pages779-798
Number of pages20
Volume130 PART 1
Publication statusPublished - 2008 Dec 1
Event18th Annual Space Flight Mechanics Meeting - Galveston, TX, United States
Duration: 2008 Jan 272008 Jan 31

Other

Other18th Annual Space Flight Mechanics Meeting
CountryUnited States
CityGalveston, TX
Period08/1/2708/1/31

Fingerprint

tethered satellites
formation flying
Riccati equations
Satellites
Riccati equation
Asymptotic stability
numerical method
Equations of motion
Numerical methods
Dynamical systems
rigid structures
complement
controllers
Controllers
equations of motion
formulations

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Space and Planetary Science

Cite this

Chang, I., Park, S. Y., & Choi, K. H. (2008). Nonlinear attitude dynamics and control for satellite tethered formation flying in three-dimensional free space. In Space Flight Mechanics 2008 - Advances in the Astronautical Sciences, Proceedings of the AAS/AIAA Space Flight Mechanics Meeting (Vol. 130 PART 1, pp. 779-798)
Chang, Insu ; Park, Sang Young ; Choi, Kyu Hong. / Nonlinear attitude dynamics and control for satellite tethered formation flying in three-dimensional free space. Space Flight Mechanics 2008 - Advances in the Astronautical Sciences, Proceedings of the AAS/AIAA Space Flight Mechanics Meeting. Vol. 130 PART 1 2008. pp. 779-798
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Chang, I, Park, SY & Choi, KH 2008, Nonlinear attitude dynamics and control for satellite tethered formation flying in three-dimensional free space. in Space Flight Mechanics 2008 - Advances in the Astronautical Sciences, Proceedings of the AAS/AIAA Space Flight Mechanics Meeting. vol. 130 PART 1, pp. 779-798, 18th Annual Space Flight Mechanics Meeting, Galveston, TX, United States, 08/1/27.

Nonlinear attitude dynamics and control for satellite tethered formation flying in three-dimensional free space. / Chang, Insu; Park, Sang Young; Choi, Kyu Hong.

Space Flight Mechanics 2008 - Advances in the Astronautical Sciences, Proceedings of the AAS/AIAA Space Flight Mechanics Meeting. Vol. 130 PART 1 2008. p. 779-798.

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

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N2 - The objective of the current research is to analyze the attitude dynamics and control of satellite tethered formation flying where the tethered units are modeled as extended rigid bodies. The three inline array system is used and the general formulation of the governing equations of motions of the system is obtained through a Lagrangian approach. In the research, attitude motions of the tethered satellite system are analyzed in the three-dimensional free space system to complement previous works. Centralized and decentralized approaches are applied to the dynamic system to compare the performance for controlling the attitude motion. The State-Dependent Riccati Equation (SDRE) controller is used to regulate the attitude errors. The stability region for the SDRE controlled tethered satellite system is estimated using a numerical method. The results show globally asymptotic stability for the control method.

AB - The objective of the current research is to analyze the attitude dynamics and control of satellite tethered formation flying where the tethered units are modeled as extended rigid bodies. The three inline array system is used and the general formulation of the governing equations of motions of the system is obtained through a Lagrangian approach. In the research, attitude motions of the tethered satellite system are analyzed in the three-dimensional free space system to complement previous works. Centralized and decentralized approaches are applied to the dynamic system to compare the performance for controlling the attitude motion. The State-Dependent Riccati Equation (SDRE) controller is used to regulate the attitude errors. The stability region for the SDRE controlled tethered satellite system is estimated using a numerical method. The results show globally asymptotic stability for the control method.

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Chang I, Park SY, Choi KH. Nonlinear attitude dynamics and control for satellite tethered formation flying in three-dimensional free space. In Space Flight Mechanics 2008 - Advances in the Astronautical Sciences, Proceedings of the AAS/AIAA Space Flight Mechanics Meeting. Vol. 130 PART 1. 2008. p. 779-798