Research on Design, Simulation, and Experiment of Separation Mechanism for Micro-Nano Satellites

The separation mechanism is a critical device that transports and releases satellites during launch on-orbit. However, as become smaller more compact, the traditional belt-locking or pyrotechnic release cannot meet micro-nano satellite’s requirements. A novel kinematic system was designed, analyzed, experimentally verified to achieve non-interference non-pyrotechnic of from vehicle while maintaining initial attitude. First, an overall structural strategy for kinematics proposed based on MF (product code satellite) properties. characteristics were also confirmed by principle energy conservation. Then, finite element model dynamic coupling between satellite deployment constructed, along with analysis mechanical simulation. Finally, dependability using ground vibration test test. prototype results demonstrate process essentially identical numerical simulation can be deployed successfully without interference, attitude fully satisfying designed technical indexes.