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High-intensity quick-disassembly fastener for airplane covering cap

A high-strength, flap-cap technology, applied in the direction of threaded fasteners, locking fasteners, connecting components, etc., can solve the problems of failure of double-threaded bolt components, the inability of the aircraft to take off quickly, and the inability to achieve rapid installation. Fast unlocking, high shear strength, and the effect of avoiding failure

Active Publication Date: 2015-01-07
GUIZHOU HANGTAI PRECISION MFG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] At present, the connection of the aircraft cover is mainly a load-bearing quick-release lock with double threads, which can ensure the quick opening or closing of the cover. However, the force-bearing quick-release lock currently used has the failure of the stop washer and the lock failure during use. This phenomenon leads to the failure of the two-wire bolt assembly. It needs to be screwed in after a single piece of manual alignment, which will not achieve the effect of quick installation, delay unnecessary time, and the aircraft cannot take off quickly in an emergency

Method used

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  • High-intensity quick-disassembly fastener for airplane covering cap
  • High-intensity quick-disassembly fastener for airplane covering cap
  • High-intensity quick-disassembly fastener for airplane covering cap

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specific Embodiment approach

[0038] DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS The present invention is described in detail below according to the accompanying drawings:

[0039] Such as figure 1 , 2 As shown, a high-strength quick-release fastener for an aircraft cover is composed of a cylindrical nut assembly 1 with four-wire internal threads and a double-lug floating seat assembly 2 with four-wire external threads.

[0040] Such as image 3 , 4 As shown, the cylindrical nut assembly 1 with four-wire internal thread is composed of a four-wire thread cylindrical nut 3, a washer 4 and a retaining ring 5. When in use, the four-wire thread cylindrical nut 3 is passed through the hole of the upper sandwich plate, and then Put the washer 4 and the circlip 5 on the other side to prevent the four-wire threaded cylindrical nut 3 from falling off the upper sandwich plate.

[0041] Such as Figure 5 , 6 As shown, the double lug swimming base assembly 2 with four-wire external thread is composed of a b...

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Abstract

The invention discloses a high-intensity quick-disassembly fastener for an airplane covering cap, and the fastener is composed of a cylindrical nut component with an inner four-line screw thread and a double-lug moving base component with an outer four-line screw thread; the cylindrical nut component includes a cylindrical four-line screw thread nut, a washer and an elastic damping ring, the cylindrical four-line screw thread nut passes through a hole on an upper sandwich plate, the other side of the cylindrical four-line screw thread nut is successively sleeved with the washer and the elastic damping ring; the double-lug moving base component includes a bush, a four-line screw thread bolt, an outer spring, an inner spring, a first toothed washer, a second toothed washer and a support plate, the bush is successively provided with the second toothed washer, the first toothed washer, the outer spring and the inner spring from the bottom to the top; the four-line screw thread bolt is fixedly arranged on the upper part inside the bush; the bush is fixedly installed on the support plate. The fastener is quickly opened and privately designed, high in anti-shearing intensity, strong in anti-loosening performance, and excellent in corrosion resistance.

Description

technical field [0001] The invention relates to a high-strength quick-release fastener for an aircraft hatch. Background technique [0002] At present, the connection of the aircraft cover is mainly a load-bearing quick-release lock with double threads, which can ensure the quick opening or closing of the cover. However, the force-bearing quick-release lock currently used has the failure of the stop washer and the lock failure during use. This phenomenon leads to the failure of the two-wire bolt assembly. It needs to be screwed in after a single piece of manual alignment, which will not achieve the effect of quick installation, delay unnecessary time, and the aircraft cannot take off quickly in an emergency. Contents of the invention [0003] The problem to be solved by the present invention is to overcome the deficiencies in the above-mentioned prior art, provide a method to meet the functional requirements of the fast opening and fast closing of the aircraft flap panel, ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F16B35/00
CPCF16B37/08F16B39/24F16B41/00
Inventor 谢仁君
Owner GUIZHOU HANGTAI PRECISION MFG
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