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Integrated Design of Solar Panels Deployment Mechanism For a Three Unit Cubesat
| Content Provider | CiteSeerX |
|---|---|
| Author | Baig, Hamza |
| Abstract | CubeSats are a cost effective way to demonstrate scientific and technological experiments in space. One of the restraining factors is the limitation in generation of more power which restricts the fully utilization of the potential of CUBESATs. The generation of more power would mean increasing the life of the satellite and allowing more complicated power consuming instruments & equipments to be tested on-board. There is substantial research going on in developing cost effective methods to deploy solar panels to generate more power like miniature motors, Torsion spring and Shape Memory Alloys (SMAs). This paper will discuss in detail the design and successful implementation of Integrated Solar Panel Deployment Mechanism (ISPDM) using torsion springs and micro-levers. The design is not only in accordance with Cubesat Design Specifications (CDS) but also assures minimal extra mass and the best utilization of a three unit CUBESAT’s area. This design is equally applicable to a single and double unit CUBESAT. I. |
| File Format | |
| Access Restriction | Open |
| Subject Keyword | Solar Panel Deployment Mechanism Three Unit Cubesat Torsion Spring Successful Implementation Instrument Equipment Integrated Solar Panel Deployment Mechanism Complicated Power Technological Experiment Substantial Research Restraining Factor Double Unit Cubesat Cubesat Design Specification Unit Cubesat Area Miniature Motor Cost Effective Method Shape Memory Alloy Solar Panel Minimal Extra Mass Cost Effective Way |
| Content Type | Text |
| Resource Type | Article |
