Locking mechanism capable of achieving unlocking by utilizing internal pressure
A locking mechanism and unlocking technology, which is applied in the direction of offensive equipment, projectiles, self-propelled bombs, etc., can solve the problems of inability to inspect products, locking and unlocking performance and non-destructive testing
Active Publication Date: 2021-03-12
BEIJING INST OF ASTRONAUTICAL SYST ENG
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The above two schemes have certain defects: the locking and unlocking performance of the product cannot be tested non-destructively, which means that the design scheme can only be verified by means of design margins and random inspections, but cannot test the actual product used
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Embodiment Construction
[0020] The present invention will be further elaborated below in conjunction with embodiment.
[0021] The invention proposes a cabin locking mechanism, which uses internal pressure to unlock and separate. It can be applied to structures such as the pressure-suppressing separation cover, the small rocket blocking cover, etc. It is a mechanical product that can replace the pyrotechnic separation structure, replacing the undetectable and unmeasurable pyrotechnic separation structure with a mechanism that can be tested multiple times on the ground, can be quantitatively controlled, and can be commercialized.
[0022] locking mechanism, such as figure 1 , figure 2 As shown, it specifically includes a thrust plate 1, a thrust rod 2, a limit nut 3, a sleeve 4, a first slider 5, an unlocking spring 6, a second slider 7, an adjustment sleeve 8, a cover 9, and a second connecting rod 11. Ball lock 12, first connecting rod 13, locking spring 14, adjustment slider 15, adjustment nut ...
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The invention relates to a locking mechanism capable of achieving unlocking by utilizing internal pressure, and belongs to the field of rocket missile bay design. The locking mechanism comprises a thrust disc, a thrust rod, a limiting nut, a sleeve, a first sliding block, an unlocking spring, a second sliding block, an adjusting sleeve, a covering cap, a second connecting rod, a ball lock, a firstconnecting rod, a locking spring, an adjusting sliding block, an adjusting nut and a ball pin. The locking mechanism can achieve reliable locking under the condition that no internal pressure existsin a cabin, and is fixed to a mouth frame. Under the action of the internal pressure, reliable unlocking is achieved, and the locking mechanism is blown away from the mouth frame under the action of the internal pressure. According to the locking mechanism, the mechanism design is completely used, and no initiating explosive device or structural damage exists, so that non-destructive locking and unlocking tests can be carried out infinitely, and the locking and unlocking reliability of the whole mechanism can be visually represented; and the locking mechanism can replace a mechanism product ofa fire work separation structure, and the undetectable and unmeasurable fire work separation structure is replaced with the mechanism which can be subjected to multiple ground tests, can be quantitatively controlled and can be productized.
Description
technical field [0001] The invention belongs to the field of rocket and missile cabin design, and relates to a locking mechanism unlocked by internal pressure. Background technique [0002] Aircraft such as rockets (missiles) need to open holes on the surface and cover them with covers due to the requirements of flight conditions (finishing, thermal separation, etc.). The flap needs to open smoothly under the pressure inside the rocket (missile) compartment. [0003] At present, the design scheme of most of the unrepaired covers is to open weakening grooves at the bolt mounting holes. When the pressure in the cabin increases, the weakening grooves are torn, and the cover structure is deformed and blown away by the internal pressure. Most of the thermal separation covers use a line-type pyrotechnic separation device, and the installation structure of the cover is blown away by internal pressure after being exploded by pyrotechnics. The above two schemes have certain defects...
Claims
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Login to View More IPC IPC(8): F42B15/00F42B15/36
CPCF42B15/00F42B15/36
Inventor 郭岳闫冰黎汉华杨柳张超颖彭飞王世勋王群谭指高竹青匡格平孟德浩
Owner BEIJING INST OF ASTRONAUTICAL SYST ENG