Design and application research of separable electrical interface for spacecraft based on laser displacement monitoring
Ziliang Zhang, Di Zhu, Lei Wang, Dongyang Luo, Tian Zhao, Fengping He · 2025
Addressing the power demand and reliability needs during the directly inserted high-capacity geostationary satellite (GEO) launch phase, a detachable satellite rocket electrical interface design method based on laser displacement monitoring technology is proposed. A satellite-rocket electrical interface system suitable for high-power satellite platforms is designed, and power supply topology, satellite battery configuration, and safety design are optimized. High precision laser displacement sensing signals are introduced to monitor the satellite rocket separation status in real time, meeting the requirements of power supply, command, and telemetry signal transmission channels for high-capacity synchronous orbit satellites and achieving reliable laser displacement satellite and rocket separation control signal acquisition functions. By optimizing contact allocation, signal partitioning, and electromagnetic compatibility design, thereby reducing the risk of short circuits and electromagnetic interference among different signals during the transfer orbit phase, achieving real-time diagnosis of separation actions and dynamic control of power supply switching. The application shows that this design enhances the satellite’s power efficiency, reliability, and handling during the challenging period of insertion.