Solar Panel Deployment Mechanism for Nano-Satellite

A new solar panel deployment mechanism for nano-satellites is developed and successfully deployed on-orbit with an objective of achieving modularity and optimization in terms of mass and volume. The modular hinge mechanism simplifies ground testing and can be operated in Earth’s gravity, thereby eliminating the need for gravity compensation system for solar panel deployment. The miniature hinge is configured without locking linkages and holds the panel by ensuring positive spring torque at the end of deployment. Similar existing miniature hinge mechanisms either lack indication switch or use fragile elements like tape springs. Hinge design presented in the paper addresses all such limitations. After hold down release, panel rotates by 90°, hits the stopper bracket of the hinge and rebounds. The panel oscillates few times before eventually settling down in the deployed state. Deployment dynamics of the solar panel is modeled in a multi-body dynamics tool, MSC ADAMS and analyzed to evaluate settling time. It is important to evaluate settling time as it governs the timeline of the sequence of mission critical events to be executed by satellite’s on board computer. The peak angular velocity of the satellite during deployment is evaluated using the developed dynamics model. The evaluated peak reaction body rates and deployment settling time are compared with the actual on-orbit observations for the nano-satellite.