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Cabin door assembly of main undercarriage cabin of aircraft

A technology for landing gear compartments and hatches, which is applied to aircraft parts, aircraft accessories, and fuselages. It can solve the problems of failure to reach load limits and low utilization of rib materials, and achieve easy on-site assembly processes and high load transfer efficiency. , the effect of reducing the weight of the structure

Pending Publication Date: 2021-06-15
COMAC +1
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  • Summary
  • Abstract
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  • Claims
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Problems solved by technology

However, this arrangement of ribs makes the load of the ribs at most positions far less than the load limit that the material can bear, thus resulting in a low utilization rate of the rib material

Method used

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  • Cabin door assembly of main undercarriage cabin of aircraft
  • Cabin door assembly of main undercarriage cabin of aircraft
  • Cabin door assembly of main undercarriage cabin of aircraft

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Embodiment Construction

[0058] The present invention will be further described below in conjunction with specific embodiment and accompanying drawing, set forth more details in the following description so as to fully understand the present invention, but the present invention can obviously be implemented in many other ways different from this description, Those skilled in the art can make similar promotions and deductions based on actual application situations without violating the connotation of the present invention, so the content of this specific embodiment should not limit the protection scope of the present invention.

[0059] In an embodiment of the present invention, the "transverse direction" of the door panel is defined as the direction on the door panel that is substantially parallel to the axis of rotation of the door panel; the "longitudinal direction" of the door panel is defined as the direction on the door panel A direction substantially perpendicular to the axis of rotation of the door...

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Abstract

The invention relates to a cabin door assembly of an aircraft main undercarriage cabin, and the cabin door assembly comprises a cabin door panel which comprises a cabin door skin and a cabin door reinforcing rib, and the cabin door reinforcing rib is arranged on the side, facing the main undercarriage cabin, of the cabin door skin; the driving rocker arm is connected with the first side of the cabin door panel so that the cabin door panel can rotate around the pivot axis, the driving rocker arm is provided with a first connecting end and a second connecting end, and the first connecting end is fixedly connected to a cabin door reinforcing rib of the cabin door panel.

Description

technical field [0001] The disclosure relates to the technical field of an aircraft body structure, and in particular, the invention relates to a door assembly of an aircraft main landing gear compartment. Background technique [0002] Civilian airliners usually contain three landing gears, the nose gear located at the front of the fuselage and two main gears, specifically one under the left and right wings. The receiving compartment of the landing gear (hereinafter referred to as the landing gear compartment) is equipped with a corresponding follow-up hatch, which is used to maintain a good aerodynamic shape of the aircraft after the landing gear is retracted, so as to reduce the overall aerodynamic resistance of the aircraft. [0003] In the prior art, the door of the landing gear compartment mainly adopts the form of "integral machined panel + rocker arm or tie rod". Due to the previous production process, it is easier to align the drilling holes or directly combine with...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C25/16B64C1/14
CPCB64C25/16B64C1/1461
Inventor 周松官杨贵强薄晓莉
Owner COMAC
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