This thesis presents a method and analysis for performing the mechanical qualification for the Joint Australian Engineering Satellite (JAESAT), being built at the Queensland University of Technology, though applicable to many other situations as well.
A method for controlling and recording errors and assumptions is detailed, which complements the finite element analysis used, and examines the differences between the model and reality. The method provides a formal criterion to accept or reject a given model, and provides a record of each assumption and error introduced into the analysis.
Finite Element analysis of relevant components of the satellite are performed, and the error control system is applied to this analysis to determine stress patterns and dynamic behaviour of these components. One of the aerials on the satellite (the receiver antenna) is found to not pass qualification, necessitating a review of the design.