The invention provides a locking and releasing mechanism and method and an aircraft, the locking and releasing mechanism comprises a shell, an elastic piece fixing rod, a rotating shaft, a power-assisted elastic piece, a lock hook and a locking force-bearing element, the elastic piece fixing rod and the rotating shaft are fixedly arranged in a containing cavity at intervals, the power-assisted elastic piece is arranged in the containing cavity, one end of the power-assisted elastic piece is connected with the elastic piece fixing rod, and the other end of the power-assisted elastic piece is connected with the lock hook. The lock hook is arranged in the containing cavity, can rotate around the rotating shaft, is connected with the other end of the power-assisted elastic piece and comprises a first lock hook section, a second lock hook section and a third lock hook section which are sequentially connected, the locking force bearing element can move in the height direction of the shell, and the locking force bearing element can be selectively matched with the locking hole; the locking force-bearing element can abut against the first lock hook section so as to limit rotation of the first lock hook section. By the adoption of the technical scheme, the technical problems that in the prior art, a locking and releasing mechanism is too complex in structure and many in operation process, and the hanging device is difficult to disassemble quickly under the emergency condition are solved.
本发明提供了一种锁定释放机构、方法及飞行器,包括:壳体、弹性件固定杆、转轴、助力弹性件、锁钩和锁定承力元件,弹性件固定杆和转轴间隔固定设置在容纳腔内,助力弹性件设置在容纳腔内,助力弹性件的一端与弹性件固定杆连接,锁钩设置在容纳腔内,锁钩可绕转轴转动,锁钩与助力弹性件的另一端连接,锁钩包括依次相连接的第一锁钩段、第二锁钩段和第三锁钩段,锁定承力元件沿壳体的高度方向可移动,锁定承力元件可选择地与锁定孔相配合,锁定承力元件可与第一锁钩段相抵接以限制第一锁钩段转动。应用本发明的技术方案,以解决现有技术中锁定释放机构结构均过于复杂,操作流程多,在紧急情况下难以快速实现吊挂装置的拆卸的技术问题。
Locking and releasing mechanism, method and aircraft
锁定释放机构、方法及飞行器
2024-03-12
Patent
Electronic Resource
Chinese
European Patent Office | 2020
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