Mathematical modeling of a class of multibody flexible spacecraft structures
Abstract
A mathematical model for a general multibody flexible spacecraft is obtained. The generic spacecraft considered consists of a flexible central body to which a number of flexible multibody structures are attached. The coordinate systems used in the derivation allow effective decoupling of the translational motion of the entire spacecraft from its rotational motion about its center of mass. The derivation assumes that the deformations in the bodies are only due to elastic motions. The dynamic model derived is a closedform vectormatrix differential equation. The model developed can be used for analysis and simulation of many realistic spacecraft configurations.
 Publication:

NASA STI/Recon Technical Report N
 Pub Date:
 December 1994
 Bibcode:
 1994STIN...9520800K
 Keywords:

 Dynamic Models;
 Dynamic Structural Analysis;
 EulerLagrange Equation;
 Flexible Spacecraft;
 Kinematic Equations;
 Mathematical Models;
 Rotating Bodies;
 Spacecraft Motion;
 Spacecraft Structures;
 Coordinates;
 Decoupling;
 Differential Equations;
 Matrices (Mathematics);
 Potential Energy;
 Translational Motion;
 Spacecraft Design, Testing and Performance