Development of the science and technology satellite ⅲ structure with composite sandwich constructions

Abstract

Composite sandwich constructions are widely employed in the space applications, because composite sandwich panels have high specific stiffness and high specific bending strength compared to solid panels. Also, the choice for the satellite primary structure materials has shifted from almost exclusively metallic structures to full composite utilization. In this thesis, the monocoque satellite structure of Korean Science and Technology Satellite III (STSAT III) was developed with the composite sandwich constructions to improve the rigidity of the satellite structures and to reduce structural mass. In the monocoque satellite structural design, many composite sandwich panels were joined each other with a newly designed I-shape side insert which was bonded to the composite sandwich panel with the adhesive. For the reliable joining of the composite satellites structure in this study, four kinds of joining parts, such as between the composite face and aluminum honeycomb panel, between the composite face and the aluminum I-shape side insert, between the composite sandwich panel and the partial insert, and between the composite panels with T-shape joints, were investigated by different experiments such as flatwise tensile and compressive test, cleavage peel test, insert pull out and shear test and composite sandwich T-joint static test. The finite element model of the composite sandwich T-joint with the I-shape side insert was developed from experimental results of the impulse response tests and composite sandwich T-joint static tests. From the quasi-static, modal analysis and vibration test of the monocoque composite sandwich satellite structure, their structural reliability was verified. The thermal analysis has been performed to evaluate thermal effect on a monocoque satellite structure in LEO (Low Earth Orbit) environment and to control the temperature ranges in equipments, and payload for the orbit specified. The thermal conductivity of the composite honey...