The invention relates to the technical field of spacecrafts, and discloses a four-redundancy firer mechanism lock which comprises a lock body assembly and a pressing assembly which are matched with each other, and the lock body assembly comprises an igniter, an ignition shell, a pin rod, a seat body, a structural upper plate and a hinge module; the pressing assembly comprises a ball pad seat, a pressing rod, a pulling rod module and a structure lower plate; a hinging module is arranged in an inner cavity of the seat body; the ignition shell is arranged on the seat body, and two groups of ignition cylinders are oppositely formed; two groups of pin rods are respectively arranged in each group of ignition cylinders, the pin rods are movably matched with the hinge modules, and igniters communicated with the inner cavities are arranged on the side surfaces of the ignition cylinders; a ball cushion seat is arranged on the structure lower plate, a pulling rod module is arranged at one end of the pressing rod, and the other end of the pressing rod penetrates through the ball cushion seat and is movably matched with the hinging module. The four sets of unlocking executing mechanisms which are completely independent are adopted, unlocking can be achieved when any unlocking executing mechanism normally works, and therefore the working reliability of the firer mechanism lock is improved.
本发明涉及航天器技术领域,公开一种四冗余火工机构锁,包括相互配合的锁体组件和压紧组件,锁体组件包括点火器、点火壳、销杆、座体、结构上板和铰合模块;压紧组件包括球垫座、压紧杆、拔杆模块和结构下板;所述座体内腔设置有铰合模块;所述点火壳设置在所述座体上,并相对形成有两组点火筒体;每组所述点火筒体内分别设置两组销杆,所述销杆与所述铰合模块活动配合,所述点火筒体的侧面设置与内腔连通的点火器;所述结构下板上设置有球垫座,所述压紧杆的一端设置拔杆模块,另一端穿过球垫座也与所述铰合模块活动配合。本发明采用完全独立的四套解锁执行机构,任一解锁执行机构正常工作均可以实现解锁,从而提高了火工机构锁的工作可靠性。
Four-redundancy firer mechanism lock
一种四冗余火工机构锁
2024-01-09
Patent
Elektronische Ressource
Chinesisch
IPC: | B64G Raumfahrt , COSMONAUTICS |
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