The invention relates to the technical field of aircraft component structure design, in particular to a spherical hinge type rope locking covering cap and a mounting method thereof.The spherical hinge type rope locking covering cap comprises a covering cap plate, a front end lug and a rear end lug are arranged on the covering cap plate, and limiting structures are arranged on the two sides of the covering cap plate respectively; a connecting unit is arranged on the front end lug; the connecting unit comprises a spherical hinge and an adjusting assembly. The rear end lug is provided with a non-concentric connection. According to the technical scheme, by arranging the non-concentric connecting hole, the adjusting assembly and the related limiting structure, the problems of gaps and jump in the prior art are perfectly solved, the jump between the locking covering cap and the aircraft front-end fuselage frame is eliminated through the internal adjusting assembly, and the gaps between the locking covering cap and the aircraft front-end fuselage frame are eliminated through the limiting structure; the step difference and the gap between the locking covering cap and the aircraft body frame at the rear end of the aircraft are eliminated through the obliquely upward fastening force of the rope, so that the step difference and the gap between the locking covering cap and the surrounding structure can be ensured to be within the design requirement range, and the flight safety cannot be influenced.
本发明涉及飞机部件结构设计技术领域,尤其涉及一种球铰式绳索锁紧口盖及其安装方法,包括口盖板,口盖板上设置有前端耳片和后端耳片,口盖板的两侧分别开设有限位结构;前端耳片上设置有连接单元;连接单元球形铰链和调节组件;后端耳上开设有非同心连接。本技术方案通过设置非同心连接孔、调节组件以及相关限位结构,完美解决现有技术所存在的间隙和阶差问题,锁紧口盖与飞机前端机身框的阶差通过内部调节组件消除,锁紧口盖与飞机前端机身框的间隙通过限位结构消除,锁紧口盖与飞机后端机身框的阶差和间隙通过绳索斜向上的系紧力消除,如此,锁紧口盖与周围结构的阶差间隙均可保证在设计要求范围之内,不会影响飞行安全。
Spherical hinge type rope locking covering cap and mounting method thereof
一种球铰式绳索锁紧口盖及其安装方法
2024-04-09
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
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