Design optimization of the support structure of a nanosatellite

The satelhte needs to meet strict mechanical requirements in order to survive the harsh launch environment. The key challenges include satisfying constraints on the rigidity, mass and center of gravity of the satellite apart from survivability during vibration qualification testing. The objective of the study is to design the support structure for the payload to satisfy the requirements imposed by the launch vehicle. Owing to the high mass (8kg) and the field-of-view requirements of the payload, a design involving a unique truss frame that supports the payload is proposed for the satellite support structure. Panels embedded in the truss frame support the subsystem PCBs on it. The satellite structure has to be structurally optimized for maximizing the natural frequency while keeping the mass minimum. This was carried out using the FEA software ABAQUS. Finally the optimized frame was subjected to quasi-static loading, random, harmonic and shock vibrations experienced during launch. A structural mock-up is being fabricated to test it for launch vibrations.