A note on calculation of modal parameters of flexible appendages from component modal matrices
Abstract
A Craig-Bampton approach-based method is presently used to generate substructuring in the dynamic analysis of spacecraft structures undergoing dynamic analysis. By these means, it is possible to calculate the momentum coefficients of deployed flexible appendages via component modal matrices. The modal parameters are as accurate as the finite-element model employed in the representation of the appendage.
- Publication:
-
Journal of Spacecraft Technology
- Pub Date:
- July 1992
- Bibcode:
- 1992JSpT....2...73B
- Keywords:
-
- Dynamic Structural Analysis;
- Flexible Bodies;
- Large Space Structures;
- Modal Response;
- Resonant Frequencies;
- Vibration Damping;
- Low Density Materials;
- Spacecraft Construction Materials;
- Structural Vibration;
- Vibration Tests;
- Structural Mechanics