Dynamics of spacecraft with deploying flexible appendagesA 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.
Document ID
19920053035
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Downer, Janice D. (Wisconsin, University Madison, United States)
Park, K. C. (Colorado, University Boulder, United States)