Accession Number : ADP003674

Title :   Application of Modal Synthesis Concepts to Spacecraft Design Verification,

Corporate Author : DEUTSCHE FORSCHUNGS- UND VERSUCHSANSTALT FUER LUFT- UND RAUMFAHRT E V GOETTINGEN (GERMANY F R)

Personal Author(s) : Bertram,A.

Report Date : 1984

Pagination or Media Count : 18

Abstract : A spacecraft never will be subjected to the flight environment for which it was designed until it is launched. To ensure safety and reliability of the structure, one is left to demonstrate that it can withstand all loads to be expected during launch and during its life in orbit prior one will risk to put it onto a launcher. The only argument the structural engineer is endowed with is a calculation of the dynamic response and of internal loads under certain specified dynamic environments. This is done using a mathematical model representing the dynamic characteristics of the structure - and certainly more or less realistically. The general way to model a complex structural system is the method to discretize it by means of large finite-element (FE) program systems.

Descriptors :   *Structural mechanics, *Mathematical models, *Finite element analysis, *Structural engineering, *Spacecraft, Dynamic response, Flight loads, Dynamic tests, Test methods

Distribution Statement : APPROVED FOR PUBLIC RELEASE