A computational formulation for the dynamic analysis of spacecraft with deploying appendages is presented. The appendage model is based on a geometrically nonlinear beam formulation which accurately accounts for large rotational and large deformation motions. A moving finite element reference grid is incorporated within the nonlinear beam formulation to model the deployment motion. Hamilton's Law is used to formulate the general equations of motion, and a transient integration solution procedure is derived from a space-time finite element discretization of the Hamiltonian variational statement. Computational results of the methodology are presented for a classical gravity gradient stabilized satellite configuration.
Dynamics of spacecraft with deploying flexible appendages
AIAA Dynamics Specialists Conference ; 1992 ; Dallas, TX, United States
1992-01-01
Conference paper
No indication
English
Approximate Solutions for Attitude Dynamics of a Spacecraft with Deploying Flexible Appendages
British Library Conference Proceedings | 1997
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