Publication: Analysis for the structural integrity of deployable truss
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Date
2008-04-01
Authors
Yu, Kok Hwa
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Abstract
The purpose of this project is to design an ideal single module deployable truss structure for space application. It is a structure which capable of large configuration changes in an autonomous way. The configuration can changes from a packaged, compact state to a deployed, large state. There are several structural aspects were taken into consideration, i.e. geometry, stiffness, loading, weight, rigidity and stability, in order to design an optimum deployable truss. In this final year project, it outlines the methodology to design, model, analyse and obtain an ideal deployable truss through optimization. The designed truss structure should be able to support two solar arrays weighted 1000kg each in the space environment and able to retract for easy storage. Stress and buckling analysis were conducted using Finite Element Method for simplified model before complicated three-dimensional model were analysed in widely used computer-aided software like MSC. PATRAN with MSC. NASTRAN. A MATLAB program implementing Direct Stiffness Method is established for analytical and computational verification. An optimum design structure is obtained through parametric optimization in the latter part of design process. Hopefully, this multi purpose structural element will be a crucial structure element in the future for the benefit of mankind.