Efficient development and processing of thermal math models of very large space truss structuresAs the spacecraft moves along the orbit, the truss members are subjected to direct and reflected solar, albedo and planetary infra-red (IR) heating rates, as well as IR heating and shadowing from other spacecraft components. This is a transient process with continuously changing heating loads and the shadowing effects. The resulting nonuniform temperature distribution may cause nonuniform thermal expansion, deflection and stress in the truss elements, truss warping and thermal distortions. There are three challenges in the thermal-structural analysis of the large truss structures. The first is the development of the thermal and structural math models, the second - model processing, and the third - the data transfer between the models. All three tasks require considerable time and computer resources to be done because of a very large number of components involved. To address these challenges a series of techniques of automated thermal math modeling and efficient processing of very large space truss structures were developed. In the process the finite element and finite difference methods are interfaced. A very substantial reduction of the quantity of computations was achieved while assuring a desired accuracy of the results. The techniques are illustrated on the thermal analysis of a segment of the Space Station main truss.
Document ID
19930046991
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Warren, Andrew H. (Grumman Corp. Space and Electronics Group, Bethpage, NY, United States)
Arelt, Joseph E. (NASA Headquarters Washington, DC United States)
Lalicata, Anthony L. (Grumman Corp. Space Station Integration Div., Reston, VA, United States)
Date Acquired
August 16, 2013
Publication Date
February 1, 1993
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 93-1104
Meeting Information
Meeting: AIAA, AHS, and ASEE, Aerospace Design Conference