Aircraft cabin door anti-sinking mechanism
A technology for anti-sinking and cabin doors, which is applied in the field of aircraft doors, and can solve problems such as complex structures and poor load-bearing conditions of single-point locking mechanisms
Active Publication Date: 2021-04-09
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology
[0005] The purpose of the present invention is: the embodiment of the present invention provides an aircraft door anti-sinking mechanism to solve the problems of the existing anti-sinking mechanism, such as the poor load-bearing condition of the single-point locking mechanism and the need for special configuration of the two-point locking mechanism. The problem of complex structure caused by the movement mechanism
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[0029] In order to make the purpose, technical solution and advantages of the present invention more clear, the embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings. It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined arbitrarily with each other.
[0030] The following specific embodiments provided by the present invention can be combined with each other, and the same or similar concepts or processes may not be repeated in some embodiments.
[0031] It has been explained in the above-mentioned background technology that after the upward and outward flipped open blocking hatch door completes the lifting movement, it must be able to be safely and reliably locked in the lifting posture. The anti-sinking mechanism is a set of devices that realize the locking posture of the hatch door. The important functional sub-organizati...
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The invention discloses an aircraft cabin door anti-sinking mechanism. An aircraft cabin door comprises a cabin door structure, a suspension rocker arm and a cabin door mechanism. The aircraft cabin door anti-sinking mechanism is arranged in the cabin door structure and comprises a lock hook arranged on the inner side of the cabin door structure, two sets of supporting rod assemblies arranged on the inner side of the cabin door structure and a lock pin arranged on the side, close to the cabin door structure, of the suspension rocker arm; the lock hook is fixedly installed in the middle of the upper part of the cabin door structure, the two sets of supporting rod assemblies are correspondingly arranged on the two sides of the lock hook, and the lock pin is arranged on the inner side of the suspension rocker arm and used in cooperation with the lock hook; and in the cabin door lifting movement process, the cabin door structure and the suspension rocker arm are locked through locking fit between the lock pin and the lock hook and locking fit between each set of supporting rod assembly and the suspension rocker arm after movement. The aircraft cabin door anti-sinking mechanism solves the problem that the structure is complex due to the fact that in an existing anti-sinking mechanism, the force bearing condition of a single-point locking mechanism is poor, and a two-point locking mechanism needs to be specially provided with a movement mechanism.
Description
technical field [0001] The invention relates to but not limited to the technical field of aircraft doors, in particular to an aircraft door anti-sinking mechanism. Background technique [0002] At present, the anti-sinking mechanism of the plugged hatch that is turned upwards and outwards is usually in the form of single-point locking or two-point locking. [0003] Among the above two locking methods, the anti-sinking mechanism of the single-point locking method is simple, but due to the limitation of the layout of other mechanisms of the hatch, the installation position is located on one side of the hatch, and the load-bearing condition is not good. [0004] In the anti-sinking mechanism of the two-point locking method, the two locking points are arranged symmetrically with respect to the cabin door. In order to limit the degree of freedom of rotation around the line connecting the two points, a relatively complex kinematic mechanism is required to realize its function. C...
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IPC IPC(8): E05D3/06E05D5/00E05D5/06B64C1/14
CPCE05D3/06E05D5/00E05D5/06B64C1/1407E05Y2900/502E05Y2900/531
Inventor 甘亚东
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA