NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About Help Login
Back to Results
Spacecraft on-orbit coupled loads analysisA 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.
Document ID
19930049891
Document Type
Conference Paper
Authors
Tinker, Michael L. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Publication Information
Publication: In: AIAA(ASME)ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 34th and AIAA/ASME Adaptive Structures Forum, La Jolla, CA, Apr. 19-22, 1993, Technical Papers. Pt. 1 (A93-33876 1
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 93-1312
Accession Number
93A33888
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.

Related Records

IDRelationTitle19930049879Collected WorksAIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 34th and AIAA/ASME Adaptive Structures Forum, La Jolla, CA, Apr. 19-22, 1993, Technical Papers. Pts. 1-6
No Preview Available