The invention provides a low-impact satellite-rocket separation mechanism which is suitable for connection and separation release of a satellite and a carrier rocket. The device mainly comprises a locking seat assembly, a separation spring assembly and a bottom plate, the bottom plate is fixed to a rocket body, and the four locking base assemblies and the four separating spring assemblies are installed at the four corner points of the bottom plate in a four-point arrangement mode. The locking seat assembly comprises a satellite butt joint seat connected with a satellite cabin plate, a satellite and a carrier rocket are stably connected before orbit injection in the mode that locking bolts are matched with memory metal separation nuts, and controllable unlocking is achieved after orbit injection. After unlocking, a separation spring in the separation spring assembly pushes away the satellite deck, and the satellite is separated from the rocket at a certain relative speed. According to the satellite and rocket separation mechanism, unlocking is driven through the memory metal separation nut, the actuation impact is small, and an additional buffering and vibration reduction structure is not needed; pollutants are not generated in the separation process, and sensitive components are not influenced; the mechanical interface is simple, wide in application range and high in reliability.
本发明提供一种低冲击星箭分离机构,适用于卫星与运载火箭的连接和分离释放。主要包括锁紧座组件、分离弹簧组件和底板;底板固定在火箭箭体上,锁紧座组件和分离弹簧组件分别设置四套,以四点式布置方式安装在底板的四个角点;锁紧座组件包括与卫星舱板连接的卫星对接座,通过锁紧螺栓配合记忆金属分离螺母的方式在入轨前稳固连接卫星与运载火箭,并在入轨后可控解锁;解锁后,分离弹簧组件中的分离弹簧将卫星舱板推离,并使卫星以一定的相对速度与火箭分离。本发明的星箭分离机构,通过记忆金属分离螺母驱动解锁,作动冲击小,无需额外的缓冲减振结构;分离过程不产生污染物,不影响敏感元器件;机械接口简单,应用范围广,可靠性高。
Low-impact satellite-rocket separation mechanism
一种低冲击星箭分离机构
2023-02-28
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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