CN203809465U - Anti-rotating bolt and nut subassembly for aircraft - Google Patents
Anti-rotating bolt and nut subassembly for aircraft Download PDFInfo
- Publication number
- CN203809465U CN203809465U CN201420226384.4U CN201420226384U CN203809465U CN 203809465 U CN203809465 U CN 203809465U CN 201420226384 U CN201420226384 U CN 201420226384U CN 203809465 U CN203809465 U CN 203809465U
- Authority
- CN
- China
- Prior art keywords
- bolt
- nut
- fixed base
- hollow slot
- aircraft
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
- 238000012856 packing Methods 0.000 claims description 10
- 230000002401 inhibitory effect Effects 0.000 claims description 8
- 238000005452 bending Methods 0.000 claims description 3
- 241000276425 Xiphophorus maculatus Species 0.000 abstract 2
- 238000012423 maintenance Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000000354 decomposition reaction Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
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- Connection Of Plates (AREA)
Abstract
The utility model relates to the field of structural design of connecting pieces for aircrafts, in particular to an anti-rotating bolt and nut subassembly for an aircraft. The anti-rotating bolt and nut subassembly for the aircraft comprises a bolt, a nut and a platy fixed base, wherein outer threads are formed at two ends of the bolt; the bolt penetrates in the fixed base; the two ends of the bolt are respectively positioned on two sides of the fixed base; a sunken groove is formed in a surface of the fixed base, and is in an optional geometrical shape except for a circle shape; a platy stopper is fixed in the middle of the bolt; the shape of the stopper is matched with that of the sunken groove; after the bolt is inserted in the fixed base, the stopper exactly drops in the sunken groove; one end of the bolt is fastened with the nut through a gasket; a detachable sleeving plate sleeves the other end of the bolt; and the outer side of the sleeving plate is fastened with the nut through a gasket. By using the anti-rotating bolt and nut subassembly for the aircraft, requirements on a mounting passage, space and tools can be reduced, and the maintainability of the aircraft is improved.
Description
Technical field
The utility model relates to aircraft connecting-piece structure design field, specifically, relates to a kind of aircraft rotation inhibiting bolt and nut component.
Background technique
Present generation aircraft often needs dismounting for ease of safeguarding certain structures, general demountable structure takes the bolt/nut of standard to be connected with fixed base, the problem of its existence is to need fixing one end, two instrument one end to tighten while installing, when practical set due to the restriction in path and space often at one end use instrument cause operating difficulties.
Model utility content
The purpose of this utility model is to overcome the deficiencies in the prior art, adapts to reality needs, and a kind of aircraft rotation inhibiting bolt and nut component is provided.
In order to realize the purpose of this utility model, the technical solution adopted in the utility model is:
A kind of aircraft rotation inhibiting bolt and nut component, comprise screw bolt and nut, also comprise a tabular fixed base, the two ends of described bolt are equipped with outside thread, described bolt-through fixed base, be the both sides that the two ends of bolt lay respectively at fixed base, a surface of described fixed base is provided with hollow slot, described hollow slot be shaped as the random geometry beyond circular, the middle part of bolt is fixed with a tabular block, the shape of described block and hollow slot matches, bolt inserts after fixed base, block just falls into hollow slot, one end of bolt is undertaken fastening by packing ring and nut, the other end outer cover is equipped with dismountable cage plate, cage plate outside is undertaken fastening by packing ring and nut.
Described hollow slot is polygonal groove.
The cross section of described hollow slot is the closed geometric shape that multistage combines, and each section of combination section middle part all bends or bending to the center of hollow slot.
The beneficial effects of the utility model are:
Be connected and compare with common bolt/nut, can reduce the requirement to path, space and instrument are installed, in regular maintenance, only need pull down in the outside of cage plate the nut in outside by instrument, take off cage plate, can safeguard aircraft, improve the maintenance of aircraft.
Brief description of the drawings
Fig. 1 is the decomposition texture schematic diagram of the each parts of the utility model;
Fig. 2 is the package assembly schematic diagram of each parts in Fig. 1;
Fig. 3 is the structural representation of hollow slot.
In figure, 1 is bolt, and 2 is nut, and 3 is fixed base, and 4 is hollow slot, and 5 is block, and 6 is packing ring, and 7 is cage plate.
Embodiment
Below in conjunction with drawings and Examples, the utility model is further illustrated:
Embodiment: referring to Fig. 1, Fig. 2, Fig. 3.
A kind of aircraft rotation inhibiting bolt and nut component, comprise bolt 1 and nut 2, it is characterized in that: also comprise a tabular fixed base 3, the two ends of described bolt 1 are equipped with outside thread, described bolt 1 runs through fixed base 3, be the both sides that the two ends of bolt lay respectively at fixed base 3, a surface of described fixed base 3 is provided with hollow slot 4, described hollow slot 4 be shaped as the random geometry beyond circular, the middle part of bolt 1 is fixed with a tabular block 5, described block 5 matches with the shape of hollow slot 4, bolt 1 inserts after fixed base 3, block 5 just falls into hollow slot 4, one end of bolt 1 is undertaken fastening by packing ring 6 and nut 2, the other end outer cover is equipped with dismountable cage plate 7, cage plate 7 outsides are undertaken fastening by packing ring 6 and nut 2.
In the technical solution of the utility model, fixed base 3 is fixed on the fuselage of aircraft, or this is as a part for fuselage, when assembling, bolt is passed from fixed base 3,5 of blocks in the middle of bolt just fall in hollow slot and to be blocked then left end packing ring 6 and nut 2 by it and carry out fasteningly, and right-hand member is inserted in after cage plate 7, fastening with packing ring 6 and nut 2 in outside.When dismounting, after can directly the nut of right-hand member 2, packing ring 6, cage plate 7 being pulled down, can carry out regular maintenance to aircraft.
In this case, hollow slot 4 can be the arbitrary shape except circular trough, as long as can be by smooth block 5 clamping.
As one preferred embodiment, described hollow slot 4 can be polygonal groove, and polygonal groove is easily processed.
As another preferred embodiment, the cross section of described hollow slot 4 is the closed geometric shape that multistage combines, and each section of combination section middle part all bends or bending to the center of hollow slot 4.
As shown in Figure 3, in the present embodiment, hollow slot 4 is made up of four arcs, and four arcs all bends to the center of hollow slot 4.Because bolt and nut component will be through repeatedly dismounting, polygonal hollow slot 4 is through wearing and tearing after repeatedly stressed, block 5 also can be in the corresponding rotation of the interior generation of hollow slot 4, of long duration even can skid, lose the such effect of hollow slot 4 and block 5 phase clampings, therefore, be designed to the structure of the present embodiment, can greatly extend the working life of the utility model bolt and nut component, hollow slot 4 will extend greatly with the time limit that block 5 skids due to wearing and tearing.
Claims (3)
1. an aircraft rotation inhibiting bolt and nut component, comprise screw bolt and nut, it is characterized in that: also comprise a tabular fixed base, the two ends of described bolt are equipped with outside thread, described bolt-through fixed base, be the both sides that the two ends of bolt lay respectively at fixed base, a surface of described fixed base is provided with hollow slot, described hollow slot be shaped as the random geometry beyond circular, the middle part of bolt is fixed with a tabular block, the shape of described block and hollow slot matches, bolt inserts after fixed base, block just falls into hollow slot, one end of bolt is undertaken fastening by packing ring and nut, the other end outer cover is equipped with dismountable cage plate, cage plate outside is undertaken fastening by packing ring and nut.
2. aircraft according to claim 1 rotation inhibiting bolt and nut component, is characterized in that: described hollow slot is polygonal groove.
3. aircraft according to claim 2 rotation inhibiting bolt and nut component, is characterized in that: the cross section of described hollow slot is the closed geometric shape that multistage combines, and each section of combination section middle part all bends or bending to the center of hollow slot.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420226384.4U CN203809465U (en) | 2014-05-06 | 2014-05-06 | Anti-rotating bolt and nut subassembly for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420226384.4U CN203809465U (en) | 2014-05-06 | 2014-05-06 | Anti-rotating bolt and nut subassembly for aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203809465U true CN203809465U (en) | 2014-09-03 |
Family
ID=51448222
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420226384.4U Expired - Lifetime CN203809465U (en) | 2014-05-06 | 2014-05-06 | Anti-rotating bolt and nut subassembly for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203809465U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104265745A (en) * | 2014-09-11 | 2015-01-07 | 贵州航太精密制造有限公司 | High-intensity quick-disassembly fastener for airplane covering cap |
-
2014
- 2014-05-06 CN CN201420226384.4U patent/CN203809465U/en not_active Expired - Lifetime
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104265745A (en) * | 2014-09-11 | 2015-01-07 | 贵州航太精密制造有限公司 | High-intensity quick-disassembly fastener for airplane covering cap |
| CN104265745B (en) * | 2014-09-11 | 2016-02-03 | 贵州航太精密制造有限公司 | A kind of high strength quick release fasteners for airplane hatch cover |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20140903 |