Stress and Thermal Analysis of CubeSat Structure.
This paper presents the stress and thermal analysis on the CubeSat structure to study the survivability of the CubeSat during the launching process or operating condition at the orbit is presented.
This paper presents the stress and thermal analysis on the CubeSat structure to study the survivability of the CubeSat during the launching process or operating condition at the orbit is presented. Various design of mechanical structures were analyzed to determine the best design for different mission requirements.
A Cubesat is a 10x10x10 cm cubic satellite that weights no more than 1 kg and that is currently used in many countries and educational institutions as an easy access to space. The primary work to do would be the analysis of the orbit the satellite would perform.
Alternative Cubesat structure 3.1 Introduction and Background 3.2 Additional requirements 3.3 Materials 3.3.1 Metallic materials 3.3.2 Nonmetallic materials 3.3.3 Material evaluation 3.4 Manufacture processes 3.4.1 Metallic Materials: 3.4.2 Non-Metallic Materials 3.4.3 Joint Methods 3.5 Conceptual Study 3.6.
The 2011 CubeSat project teams were charged with designing the CubeSat according to specifications of the instrument. The major design constraints were a polar orbit, a tracking system that could pinpoint the sun with a high degree of accuracy, and a high power requirement to run the instrument.
Modular CubeSat Structures from 1U up to 8U based on the CubeSat standard. Side shear panels. Flight heritage since 2012.
The CubeSat structure was designed using AutoCAD Power Pack software to ensure that all components fit together without interference, and to aid in the finite element analysis. The detail drawing of CubeSat’s component made in AutoCAD can be seen in Appendix A. The exterior structure of CubeSat consists of six aluminum (AL-6061-T6) walls.
The preliminary design of Aluminum-ULTEM structure is fine-tuned for easy assembly and disassembly of the subsystems stacked inside the CubeSat structure. The finalized design model is needed to be analyzed to verify the structural integrity using finite element analysis (FEA) tool, ABAQUS.
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As a bonus, the best CubeSat projects deliver new capabilities to the space industry. Western Aerospace Launch Initiative, or WALI, is a student-run WMU organization; it began with high-altitude balloon launches and has now progressed to the design of an advanced CubeSat focused on spacecraft propulsion system monitoring and analysis.
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The modular 6-Unit Cubesat structure allows up to six 1-Unit stacks of PCBs, or other modules, to be mounted inside in two rows of three. For example a 3-Unit bus in combination with a 3-Unit imager.
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