一种卫星分离装置、运载火箭、设计方法和电子设备
By vertically setting n sub-separation devices on the outer periphery of the satellite, each containing m single springs, and adjusting their number and position, the problem of complex satellite surface structure or limited push contact length was solved, and the stability of the satellite's attitude after separation was achieved.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- AEROSPACE SCI & IND KET TECH CO LTD
- Filing Date
- 2023-02-10
- Publication Date
- 2026-07-17
AI Technical Summary
In existing technologies, satellite-rocket separation devices are difficult to distribute evenly when the push contact length is limited or the satellite surface structure is complex, resulting in unstable satellite attitude after separation.
Design a satellite separation device, in which n sub-separation devices are vertically arranged along the outer periphery of the satellite. Each sub-separation device contains m single springs. By adjusting the number and position of the sub-separation devices, the resultant separation torque of the separation force relative to the center of mass of the satellite is made zero, ensuring the stability of the satellite's attitude after separation.
Through combined design, the angular velocity of the satellite after separation is minimized, ensuring the satellite's attitude stability after separation and adapting to the separation of complex structure satellites from rockets.
Smart Images
Figure CN116424582B_ABST