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.
Spacecraft on-orbit coupled loads analysis
1993-01-01
Conference paper
No indication
English
SPACECRAFT ON-ORBIT COUPLED LOADS ANALYSIS
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