CN105857569B - A kind of port cover structure of aircraft maintenance - Google Patents
A kind of port cover structure of aircraft maintenance Download PDFInfo
- Publication number
- CN105857569B CN105857569B CN201610203707.1A CN201610203707A CN105857569B CN 105857569 B CN105857569 B CN 105857569B CN 201610203707 A CN201610203707 A CN 201610203707A CN 105857569 B CN105857569 B CN 105857569B
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- CN
- China
- Prior art keywords
- cover plate
- hole
- matched
- lock shaft
- positive stop
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
- B64C1/1407—Doors; surrounding frames
- B64C1/1446—Inspection hatches
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Casings For Electric Apparatus (AREA)
- Connection Of Plates (AREA)
Abstract
A kind of port cover structure of aircraft maintenance, contain aircraft skin, strengthen mouth frame, cover plate, positive stop, bolt component and lock shaft, there is a countersunk head lockhole centre of cover plate, there is conductive rubber strip to be matched with the L-type groove of cover plate, there is sagging hole the centre of positive stop, there is conductive rubber ring to be matched with the hole of sinking, described bolt component is made up of dead bolt and screw-thread bush, described lock shaft is a self-locking screw rod, cover plate is connected by lock shaft with bolt component, the endoporus for strengthening mouth frame is the crimp hole of a varus, a sagging step matched with cover plate L-type groove is formed between crimp hole and covering.
Description
Technical field
The invention belongs to field of airplane structure, it is related to a kind of maintenance mouth with electromagnetic protection function of aircraft
Lid.
Background technology
Passage of the lid as equipment detection, replacing and maintenance on aircraft, it is related to the working service of aircraft.Lid
More, then the open rate of aircraft is high, and its working service performance is also better, but increasingly complicated electromagnetic environment causes lid border
Gap be coupled into the passage of interior of aircraft as electromagnetic wave, and then the electronic equipment around lid is impacted.Thus
During lid designs, the quick-detachment function of lid should be considered, ensure that lid has electromagnetic protection function again.
The lid on aircraft is typically by the way of the connection of screw plate nut or the connection of quick-release bearing lock at present, in lid
Marine glue, which is scribbled, with the lap-joint of mouth frame carries out water-proofing treatment.When in use, it is necessary to open screw one by one with instrument or quick-release is held
Power is locked, and reduces the agility used.Meanwhile marine glue causes lid to have certain waterproof ability, but also increase lid
With the gap of mouth frame so that this gap turns into the main thoroughfare of electromagnetic coupled.
The content of the invention
, can not only it is an object of the invention to propose a kind of port cover structure of the aircraft maintenance with electromagnetic protection function
Enough using the quick and easy carry out disassembly and installation of general utility tool, and there is electromagnetic protection function, and self structure can be passed through
Form prevents from losing, and can meet the working service requirement of lid well.
A kind of airplane hatch cover structure, containing aircraft skin, strengthen mouth frame, cover plate, positive stop, bolt component and lock shaft,
It is characterized in that the cover plate front and aircraft theory form fit, there are a countersunk head lockhole, the reverse side side of cover plate in the centre of cover plate
Edge has sagging L-type groove, has conductive rubber strip to be matched with the L-type groove, described positive stop is groove shape part, is riveted on cover plate
Reverse side, there is sagging hole the centre of positive stop, has conductive rubber ring to be matched with the hole of sinking, described bolt component is by dead bolt
Formed with screw-thread bush, there is a connecting hole at the center of dead bolt, and tight fit has a screw-thread bush in connecting hole, described lock shaft be one from
Screw rod is locked, the termination of self-locking screw rod is the flat recess countersunk head matched with the countersunk head lockhole of cover plate, and self-locking screw rod serves as a contrast with above-mentioned screw thread
Set coordinates, and cover plate is connected by lock shaft with bolt component, and the endoporus for strengthening mouth frame is the crimp hole of a varus, crimp hole and covering
Between formed a sagging step matched with cover plate L-type groove.
The advantage of the invention is that：Drive bolt component to be secured to by single lock shaft to strengthen on mouth frame, realize lid
Be rapidly assembled and disassembled；It is sunk the conductive rubber ring at hole by the conductive rubber strip on cover plate L-type groove and positive stop,
Realize the electromagnetic protection function of lid；By positive stop and strengthen connecting on mouth frame by chain assemblies, effectively anti-seam
Losing of cover, and convenient use is safeguarded, realizes error-preventive design.
Accompanying drawing is described in further detail to the application with reference to embodiments.
Brief description of the drawings
Fig. 1 is a kind of aircraft maintenance lid schematic diagram with electromagnetic protection function
Fig. 2 is Fig. 1 explosive view
Fig. 3 is central rotation fore shaft lid sectional structure
Fig. 4 is cover plate schematic diagram
Fig. 5 is positive stop schematic diagram
Fig. 6, Fig. 7 are bolt component schematic diagrames
Fig. 8 is lock shaft schematic diagram
Numbering title in figure：1st, cover plate；2nd, positive stop；3rd, bolt component；4th, lock shaft；5th, chain；6th, mouth frame is strengthened；7、
Conductive rubber ring；8th, conductive rubber strip；9th, covering；10th, split pin；11st, countersunk head lockhole；12nd, L-type groove；21st, spacing crimp；22、
Sagging hole；31st, dead bolt；32nd, screw-thread bush；33rd, long tongue piece；34th, short tongue piece；35th, connecting hole；36th, interior self-locking thread；41st, one
Word groove countersunk head；42nd, outer self-locking thread；43rd, pin-and-hole；51st, chain link；52nd, angle section；61st, crimp hole
Embodiment
As illustrated, the present invention has the aircraft maintenance port cover structure of electromagnetic protection function, containing aircraft skin 9, strengthen
Mouth frame 6, cover plate 1, positive stop 2, bolt component 3 and lock shaft 4, the front of cover plate 1 and the covering matching of aircraft theory profile,
There is a countersunk head lockhole 11 centre of cover plate 1, and the opposite longitudinal side edge of cover plate 1 has sagging L-type groove 12, separately there is conductive rubber strip 8 and the L
Type groove 12 matches, and described positive stop 2 is groove shape part, is riveted on the reverse side of cover plate 1, and the both sides limited location of positive stop is curved
There is sagging hole 22 side 21, the centre of positive stop 2, separately have conductive rubber ring 7 to be matched with the hole 22 of sinking, described bolt component
3 are made up of dead bolt 31 and screw-thread bush 32, and there are connecting hole 35, the tongue piece length of dead bolt both sides, side in the center of dead bolt 31
Long tongue piece 33, the short tongue piece 34 of opposite side, the upper side of tongue piece is an inclined-plane, is matched with reinforcing frame stepped hole.It is tight in connecting hole
Screw-thread bush 32 is combined with, is interior self-locking thread 36 in the interstitial hole of screw-thread bush 32, after screw-thread bush 32 is by liquid nitrogen cold-shrinkage
It is pressed into the centre bore 35 of dead bolt 31.Described lock shaft 4 is a self-locking screw rod, and the termination of self-locking screw rod is the countersunk head with cover plate
The flat recess countersunk head 41 of lockhole matching, the interior self-locking thread 36 of the outer self-locking thread 42 of self-locking screw rod and above-mentioned screw-thread bush 32 are matched somebody with somebody
Close, and pin-and-hole 43 is formed with the outer end of self-locking thread 42, cover plate 1 is connected by lock shaft 4 with bolt component 3, and it is a metal plate to strengthen mouth frame 6
Golden thin plate, its endoporus are the crimp holes 61 of a varus, and form one between crimp hole 61 and covering 9 matches with cover plate L-type groove
Sagging step.
In order to prevent cover plate from sliding, implement cover plate and be connected by a flexible chain with strengthening mouth frame.The flexible chain
55 be to be linked to form by multiple chain links 51, and its one end is riveted to by angle section 52 to be strengthened on mouth frame 6, and the other end is screwed to limiting block
On block 2.
When implementing, strengthen mouth frame 6 and be riveted on covering 9, strengthen the intensity of its surrounding structure, the opening size of covering 9
(border) smaller 0~0.5mm than the size of cover plate 1, but the size than strengthening crimp hole 61 on mouth frame is big, ensures lid border and mouth
Frame has enough amounts of lap (generally, amount of lap is less than 6mm).Conductive rubber ring 7 is put into the sagging hole 22 of positive stop 2
Place, hole 22 of sinking are directed at the countersunk head lockhole 11 of cover plate 1, and postive stop baffle 2 is riveted to the centre of cover plate 1.The insertion lid of lock shaft 4
In the countersunk head lockhole 11 of plate 1, then bolt component 3 screwed in into lock shaft 4 so that the outer self-locking thread 42 of lock shaft 4 and bolt component 3
Interior self-locking thread 36 is engaged, and is then penetrated in the pin-and-hole 43 on lock shaft 4 split pin 10, is pulled open afterbody and fix.It will finally lead
Electric sealing joint strip 8 is pasted onto on the L-type groove 12 of cover plate 1, and positive stop 2 and reinforcement mouth frame 6 are linked together with chain 5.
The center latch assembled rotation lid is sideling put into and strengthens (the long tongue piece 33 in bolt component 3 first being put into reinforcement in mouth frame 6
In mouth frame 6, then short tongue piece 34 is put into and strengthened in mouth frame 6), by rotating lock shaft 4 so that bolt component 3 is in positive stop 2
It can not be rotated under position-limiting action, can only be maintained in the stroke of design and move along a straight line, until bolt component 3 is with strengthening mouth frame 6
Strengthen crimp contact, lid locking.In addition, in implementation process, it also should ensure that bolt component 3 is screwing in lock shaft 4, and use opening
After pin 10 and positive stop 3 are spacing, bolt component 3 can not rotate.
A kind of central rotation fore shaft with Spark gap function is covered after being installed on aircraft, lock shaft 4 and dead bolt
The self-locking thread engagement of component 3, it ensure that the reliable locking of lid；The L-type groove 12 of cover plate 1 and the sagging hole 22 of positive stop 2
Double conductive seal measures at place, ensure that the electromagnetic protection function of lid；Positive stop 2 is connected to by chain 5 with strengthening mouth frame 6
Together, effectively prevent lid during maintenance of equipment from losing problem.
Claims (3)
1. a kind of port cover structure of aircraft maintenance, containing aircraft skin, strengthen mouth frame, cover plate, positive stop, bolt component and
Lock shaft, it is characterised in that the cover plate front matches with aircraft configuration, and there are a countersunk head lockhole, the reverse side side of cover plate in the centre of cover plate
Edge has sagging L-type groove, has conductive rubber strip to be matched with the L-type groove, described positive stop is groove shape part, is riveted on cover plate
Reverse side, there is sagging hole the centre of positive stop, has conductive rubber ring to be matched with the hole of sinking, described bolt component is by dead bolt
Formed with screw-thread bush, there is a connecting hole at the center of dead bolt, and tight fit has a screw-thread bush in connecting hole, described lock shaft be one from
Screw rod is locked, the termination of self-locking screw rod is the flat recess countersunk head matched with the countersunk head lockhole of cover plate, and self-locking screw rod serves as a contrast with above-mentioned screw thread
Set coordinates, and cover plate is connected by lock shaft with bolt component, and the endoporus for strengthening mouth frame is the crimp hole of a varus, crimp hole and covering
Between formed a sagging step matched with cover plate L-type groove.
2. the port cover structure of aircraft maintenance as claimed in claim 1, it is characterised in that described cover plate is soft by one
Property chain with strengthen mouth frame be connected.
3. the port cover structure of aircraft maintenance as claimed in claim 1, it is characterised in that the tongue piece of described dead bolt both sides
Length, side tongue piece length and opposite side tongue piece, the upper side of tongue piece is an inclined-plane, is matched with reinforcing frame stepped hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610203707.1A CN105857569B (en) | 2016-04-01 | 2016-04-01 | A kind of port cover structure of aircraft maintenance |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610203707.1A CN105857569B (en) | 2016-04-01 | 2016-04-01 | A kind of port cover structure of aircraft maintenance |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105857569A CN105857569A (en) | 2016-08-17 |
| CN105857569B true CN105857569B (en) | 2018-04-03 |
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ID=56626881
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610203707.1A Active CN105857569B (en) | 2016-04-01 | 2016-04-01 | A kind of port cover structure of aircraft maintenance |
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| CN (1) | CN105857569B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107054618A (en) * | 2017-03-23 | 2017-08-18 | 西安飞机工业（集团）有限责任公司 | The electromagnetic protection method and conductive seal bar of a kind of airplane hatch cover |
| CN110816808A (en) * | 2019-12-04 | 2020-02-21 | 中国直升机设计研究所 | Non-closed waterproof opening cover assembly |
| CN110901879A (en) * | 2019-12-04 | 2020-03-24 | 中国直升机设计研究所 | Ventilation rainproof cover |
| CN111017226A (en) * | 2019-12-24 | 2020-04-17 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft sewage service panel structure |
| CN113525665B (en) * | 2021-08-08 | 2024-06-11 | 中国航空工业集团公司沈阳飞机设计研究所 | Self-opening aircraft flap structure |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201357942Y (en) * | 2009-03-13 | 2009-12-09 | 贵州航天精工制造有限公司 | Quick release force bearing lock of airplane hatch cover |
| CN101519119B (en) * | 2009-03-13 | 2013-05-22 | 贵州航天精工制造有限公司 | Fast-disassembly method of aeroplane access cover and bearing lock |
| DE102011085269A1 (en) * | 2011-10-27 | 2013-05-02 | Airbus Operations Gmbh | Cover plate, door cover and aircraft or spacecraft |
| CN203581389U (en) * | 2013-11-28 | 2014-05-07 | 江西洪都航空工业集团有限责任公司 | Error prevention limiting device for outboard switch of aircraft |
| CN103786892B (en) * | 2014-01-18 | 2016-02-10 | 成都飞机工业（集团）有限责任公司 | Many subdivisions fuel tank shares the topping up device of oil filling port |
| 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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2016
- 2016-04-01 CN CN201610203707.1A patent/CN105857569B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN105857569A (en) | 2016-08-17 |
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Address after: No. 710089 in Shaanxi province Xi'an city Yanliang District West Avenue Patentee after: AVIC Xi'an Aircraft Industry Group Co.,Ltd. Address before: 1 No. 710089 Shaanxi province Xi'an city Yanliang District West Avenue Patentee before: AVIC AIRCRAFT Corp. |
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| TR01 | Transfer of patent right |
Effective date of registration: 20210616 Address after: 1 No. 710089 Shaanxi province Xi'an city Yanliang District West Avenue Patentee after: AVIC AIRCRAFT Corp. Address before: 1 No. 710089 Shaanxi province Xi'an city Yanliang District West Avenue Patentee before: XI'AN AIRCRAFT BRANCH OF XI'AN AIRCRAFT INTERNATIONAL Corp. |