Spacecraft on-orbit coupled loads analysis
Abstract
A method is presented for coupled loads analysis of on-orbit spacecraft systems. Discrete models are coupled then reduced using the Craig-Bampton technique. Coupled system transient response is determined as well as substructure interface forces and center-of-gravity accelerations. Typical results are presented for a spacecraft system having three components and being subjected to rocket motor thrust.
- Publication:
-
AIAA/ASME/ASCE/AHS/ASC 34th Structures, Structural Dynamics, and Materials Conference
- Pub Date:
- April 1993
- Bibcode:
- 1993ssdm.conf..144T
- Keywords:
-
- Center Of Gravity;
- Dynamic Loads;
- Finite Element Method;
- Rocket Thrust;
- Spacecraft Orbits;
- Cyclic Loads;
- Spacecraft Design;
- Transient Response;
- Spacecraft Design, Testing and Performance