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Light aircraft cockpit cover locking mechanism and use method

A light aircraft and cockpit technology, applied to aircraft doors, aircraft accessories, etc., can solve problems such as unreasonable structural design and complex locking mechanism of aircraft cockpit cover, so as to improve safety and stability, improve safety guarantee, and simplify unlocking structure effect

Pending Publication Date: 2022-05-13
HUNAN SUNWARD SCI & TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0008] The technical problem to be solved by the present invention is to provide a light aircraft cockpit cover locking mechanism for the complex and unreasonable structural design of the aircraft cockpit cover locking mechanism in the prior art

Method used

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  • Light aircraft cockpit cover locking mechanism and use method
  • Light aircraft cockpit cover locking mechanism and use method
  • Light aircraft cockpit cover locking mechanism and use method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0041] This embodiment provides a light-duty aircraft cockpit cover locking mechanism, which includes a locking part installed on the cockpit cover and a limiting part installed on the aircraft body.

[0042] The locking part includes the inner handle 5, the outer handle 1, the handle shaft 2, the rotating crank 4, the latch connecting rod 6 and the latch 10, and the inner side of the cockpit cover is fixed with the rotating shaft mounting seat 3, and the handle rotating shaft 2 and the rotating shaft mounting seat 3 pass through the centripetal Joint bearing connection, the inner handle 5 is fixedly connected with one end of the handle rotating shaft 2, the outer handle 1 is arranged on the outside of the cockpit cover, and is fixedly connected with the other end of the handle rotating shaft 2 through the cockpit cover, the inner handle 5 and the outer handle 1 Both can control the rotation of the handle rotating shaft 2 . The rotating crank 4 is provided with two shaft holes...

Embodiment 2

[0048] This embodiment provides a light-duty aircraft cockpit cover locking mechanism, which includes a locking part installed on the cockpit cover and a limiting part installed on the aircraft body.

[0049] The locking part includes the inner handle 5, the outer handle 1, the handle shaft 2, the rotating crank 4, the latch connecting rod 6 and the latch 10, and the inner side of the cockpit cover is fixed with the rotating shaft mounting seat 3, and the handle rotating shaft 2 and the rotating shaft mounting seat 3 pass through the centripetal Joint bearing connection, the inner handle 5 is fixedly connected with one end of the handle rotating shaft 2, the outer handle 1 is arranged on the outside of the cockpit cover, and is fixedly connected with the other end of the handle rotating shaft 2 through the cockpit cover, the inner handle 5 and the outer handle 1 Both can control the rotation of the handle rotating shaft 2 . The rotating crank 4 is provided with two shaft holes...

Embodiment 3

[0056] This embodiment provides a light-duty aircraft cockpit cover locking mechanism, which includes a locking part installed on the cockpit cover and a limiting part installed on the aircraft body.

[0057] The locking part includes the inner handle 5, the outer handle 1, the handle shaft 2, the rotating crank 4, the latch connecting rod 6 and the latch 10, and the inner side of the cockpit cover is fixed with the rotating shaft mounting seat 3, and the handle rotating shaft 2 and the rotating shaft mounting seat 3 pass through the centripetal Joint bearing connection, the inner handle 5 is fixedly connected with one end of the handle rotating shaft 2, the outer handle 1 is arranged on the outside of the cockpit cover, and is fixedly connected with the other end of the handle rotating shaft 2 through the cockpit cover, the inner handle 5 and the outer handle 1 Both can control the rotation of the handle rotating shaft 2 . The outer wall of the handle rotating shaft 2 is conn...

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PUM

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Abstract

The invention discloses a light aircraft cockpit cover locking mechanism and method.The light aircraft cockpit cover locking mechanism comprises a locking part installed on a cockpit cover and a limiting part installed on an aircraft body, the light aircraft cockpit cover locking mechanism comprises an inner handle, an outer handle, a rotating shaft, a rotating crank, a plug pin connecting rod and a plug pin, the handles are connected with the rotating shaft, and the rotating crank is connected with the rotating shaft and steers along with the rotating shaft; one end of the bolt connecting rod is connected with the rotating crank, the other end of the bolt connecting rod is connected with the bolt, the bolt is fixed to the edge of the cockpit cover through the guide block, the bolt is controlled through the inner handle and the outer handle, the function that a cockpit can be controlled to be opened and closed inside and outside a small aircraft is achieved, and locking safety and stability are improved; the problem that the cabin door cannot be opened in time in an emergency state is solved.

Description

technical field [0001] The invention relates to the technical field of light aircraft locking structures, and more specifically, to a light aircraft cockpit cover locking mechanism and a method of use. Background technique [0002] The entrance and exit of the cockpit in a small aircraft is through the opening of the hatch to realize the entry and exit of personnel. According to regulations, the emergency exit of the aircraft must be able to be opened from both inside and outside. The hatch is the only entrance and exit of a small aircraft. Security on and off. [0003] CN202110982316.5 An aircraft cabin cover opening and closing mechanism, an aircraft cabin mechanism and its opening and closing method disclose including a latch system, a push rod system and a tightening device; the latch system includes an elastic element and a latch, and the elastic element is inserted through On the bolt, the bolt includes a first end and a second end, and one end of the elastic element ...

Claims

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Application Information

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IPC IPC(8): B64C1/14
CPCB64C1/14B64C1/1423
Inventor 李孚右周志东赵轶
Owner HUNAN SUNWARD SCI & TECH