Introduction of Clampbands in Spacecraft Structural Mathematical Models

摘要

Ariane and Thor Delta spacecraft adapter and clamp band stiffnesses are described, and simplified mathematical methods for investigating the influence of adapter and clamp band stiffnesses on the eigenfrequencies of spacecraft are presented. Methods of introducing clamp band and adapter stiffnesses in a finite element model are described. Modal coupling methods are illustrated using Giotto test data to show which data should be measured during a modal survey test to investigate the influence of adapter and clamp band stiffnesses on the modes and eigenfrequencies. The influence of pretension on clamp band mechanical properties is discussed.