Solar Panel and Deorbiting Mechanism
The UW Orbital design team needs to increase the solar radiation exposure while in orbit to increase the electrical power capacity. To meet competition requirement, a deorbiting mechanism must be implemented to reduce space pollution.
Objective: Design a solar panel deployment mechanism which also acts as the deorbiting mechanism when the winding mechanism turns the satellite so the surface area of the solar panels creates drag to bring down the satellite in low earth orbit.
- Integrates easily into the CubeSAT without altering the design of the internal stackup
- Minimizes the material cut from the structural frame
- Smallest design as possible
- Deployment mechanism is as simple as possible
- Must perform in the space environment after launch conditions
Mechanical Design
Process
- Determined the deployment mechanism to be a preloaded torsion spring through research and a concept evaluation table.
- Developed the minimum size of parts through engineering judgement.
- Sourced the torsion spring through size and calculations.
- Considered mass, manufacturability, thermal coefficients, vibration loads, cold welding, fretting/galling, galvanic corrosion, and outgassing principles when designing the hinge assembly.
- Performed FEA simulations to ensure forces on solar panel and hinge are acceptable.
- The FEA and prototyping phases are still in progress.