Modeling, Simulation, and Analysis of Flexible Satellite Dynamics in MATLAB and ADAMS and Design Verification for Attitude Control Applications
Document Type : Original Article
Author
K. N. Toosi University of Technology
Abstract
Flexible solar arrays are widely employed in satellites to generate electrical power. However, designing an attitude control law for satellites with large flexible components involves difficulties such as complex modeling and dynamics. This article investigates various flexible satellite modeling methods and proposes the finite element method for modal analysis. The study presents frequency mode analysis of the flexible satellite as a cantilever beam attached to a rigid body, including an analytical model implemented in MATLAB and finite element simulation. For this purpose, ADAMS, Patran/Nastran, and Abaqus are utilized for modeling, and the physical characteristics of the flexible satellite are determined based on Intelsat-5 parameters. A comparison between the modal analysis results and the satellite’s operational model shows a maximum relative error of 3.34%. This difference arises from the different meshing used for modal analysis in the simulation software. Finally, model verification is performed through a multidisciplinary simulation of the flexible satellite, demonstrating an acceptable relative error between the MATLAB and ADAMS simulations. The findings confirm the effectiveness of finite element models in modeling and solving the dynamic equations of flexible satellites, which can be used to design an attitude control law.
Keywords
Subjects
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Volume 6, Issue 1
September 2026Pages 132-149
- Receive Date 09 September 2025
- Revise Date 30 October 2025
- Accept Date 08 June 2026