Small Spacecraft Thermal Control Louvers

Project Overview

Thermal management is a crucial component to satellite missions. A system that provides heat rejection and insulation without consuming power is ideal. The product is a passive thermal management system for small satellites that uses louvers on a radiator.

Performance Review

Several tests and analyses were performed to verify the effectiveness of the system to fulfill customer requirements. The most important methods are outlined below.

Thermal Analysis –Computational methods were used to verify the 20x heat rejection and determine optimal surface coatings.

Spring Testing –Bimetal springs were tested to ensure 90°rotation over desired temp. range

Structural Analysis –Model tested in SolidWorks to ensure it could withstand 50G on all axes

Thermal Cycle Testing –Atmosphere testing performed on prototype over many thermal cycles to verify thermal performance.

Conclusion

Results

• Thermal and Structural analysis demonstrate model fulfills their respective requirements
• Spring testing demonstrates the spring’s ability to open over the correct range
• Thermal cycle testing was successful, though proving some assembly flaws

Lessons Learned

• More precision and quality control during assembly would greatly benefit the performance, particularly with the flap and spring bonding

Moving Forward

• Vacuum chamber testing to validate model
• Vibration testing to validate structural requirements, ensure launch survival