CN204775985U - Aircraft flap hinge structure - Google Patents
Aircraft flap hinge structure Download PDFInfo
- Publication number
- CN204775985U CN204775985U CN201520430403.XU CN201520430403U CN204775985U CN 204775985 U CN204775985 U CN 204775985U CN 201520430403 U CN201520430403 U CN 201520430403U CN 204775985 U CN204775985 U CN 204775985U
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- China
- Prior art keywords
- lid
- hinge
- bearing
- housing construction
- rocker bar
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Abstract
The utility model provides an aircraft flap hinge structure, relates to aircraft structural design technical field for being connected of flap and organism on the aircraft, covering, organism structure support pass through the fastener with the flap frame to be connected, and the hinge body passes through organism structure pivot with organism structure support to be connected, and the rocker bar bearing passes through the bolt fastening and is in on the flap, the hinge body passes through the cooperation of hinge body pivot with the rocker bar bearing and is connected. The utility model provides an aircraft flap hinge structure rotates the unipolar and changes the biax rotation into through to the hinge design, has increaseed the flap and has opened the angle to satisfy the maintainability requirement.
Description
Technical field
The utility model relates to technical field of aircraft structure design, in particular to a kind of airplane hatch cover hinge arrangement.
Background technology
Current in-service airplane hatch cover and body connection mode mainly contain two kinds, and one is that border is connected with housing construction by quick-detachable lock, and another kind is that side is connected through the hinge that all the other are connected by quick-detachable lock.
Border is by quick-release institute connection mode.After lid is opened, lid entirety is separated with housing construction.There is drawback in this version, along with the growth of aircraft Years Of Service, lid local deformation strengthens, and lid does not have positioning datum to be difficult in statu quo install after taking off, at this moment may occur in outfield forcing assembling, hide some dangers for the follow-up military service of aircraft.
Side is connected through the hinge all the other by quick-detachable lock connection mode.After lid is opened, lid is connected with housing construction by hinge, and outfield technical attendant completes after line inspection is safeguarded and can restore to the original state very soon, but this mode affects larger by lid position.When very moment drop cloth is put nearer apart from ground, the design of lid open angle seems particularly important.Sometimes for meeting maintainability needs, lid position being raised, at this moment causing the chain reactions such as weight increase.For this reason to sacrifice minimum weight, exchange the maximum angle that lid opens for and just seem particularly important.
The rotating shaft of tradition lid is fixed rotating shaft, and under rotating shaft fixing situation, lid open angle is definite value.The problem that present stage needs solution badly how under the prerequisite not increasing animal economy weight, lid to be opened larger angle.
Utility model content
The purpose of this utility model be solve above-mentioned deficiency of the prior art, provide a kind of simple and reasonable, under the prerequisite not increasing animal economy weight by lid open angle increase airplane hatch cover hinge arrangement.
The purpose of this utility model is achieved through the following technical solutions: a kind of airplane hatch cover hinge arrangement, for the connection of aircraft upper flap and body, lid circumference is provided with lid frame, lid is fixedly connected with by quick-detachable lock with lid frame, comprise rocker bar bearing, hinge bodies, housing construction bearing, housing construction pivot pin, hinge bodies pivot pin, wherein, covering, housing construction bearing is connected by fastener with lid frame, hinge bodies and housing construction bearing are connected, rocker bar bearing is fixed in lid by fastener, hinge bodies and rocker bar bearing are connected.
, housing construction bearing is ears permanent seat in such scheme preferably, and one end that hinge bodies and housing construction bearing are connected is monaural structure, and the two is dynamically connected by housing construction pivot pin axle.
In above-mentioned either a program preferably, rocker bar bearing is monaural permanent seat, and one end that hinge bodies and rocker bar bearing are connected is ears structure, and the two is dynamically connected by hinge bodies pivot pin axle.
The beneficial effect of airplane hatch cover hinge arrangement provided by the utility model is, structure is simple, by designing hinge-increase rotating shaft at hinge place, change to double-axle rotation by traditional single axle rotation, increase lid open angle, thus improve the maintainability of equipment compartment.
Accompanying drawing explanation
Fig. 1 is the integral structure scheme of installation of the preferred embodiment according to airplane hatch cover hinge arrangement of the present utility model;
Fig. 2 is housing construction bearing, hinge bodies connection structure schematic diagram embodiment illustrated in fig. 1 according to airplane hatch cover hinge arrangement of the present utility model;
Fig. 3 is rocker bar bearing, hinge bodies connection structure schematic diagram embodiment illustrated in fig. 1 according to airplane hatch cover hinge arrangement of the present utility model.
Reference numeral:
1-covering, 2-lid, 3-rocker bar bearing, 4-hinge bodies, 5-housing construction bearing, 6-housing construction pivot pin, 7-hinge bodies pivot pin, 8-lid frame.
Detailed description of the invention
In order to understand the airplane hatch cover hinge arrangement according to the utility model scheme better, be further elaborated explanation below in conjunction with the preferred embodiment of accompanying drawing to the utility model airplane hatch cover hinge arrangement.
As Figure 1-3, the airplane hatch cover hinge arrangement that the utility model provides, for the connection of aircraft upper flap 2 with body, lid 2 circumference is provided with lid frame 8, lid 2 is fixedly connected with by quick-detachable lock with lid frame 8, comprise rocker bar bearing 3, hinge bodies 4, housing construction bearing 5, housing construction pivot pin 6, hinge bodies pivot pin 7, wherein, covering 1, housing construction bearing 5 is connected by fastener with lid frame 8, hinge bodies 4 is connected with housing construction bearing 5, rocker bar bearing 3 is fixed in lid 2 by fastener, hinge bodies 4 and rocker bar bearing 3 are connected.Housing construction bearing 5 is ears permanent seat, and one end that hinge bodies 4 and housing construction bearing 5 are connected is monaural structure, and the two is dynamically connected by housing construction pivot pin 6 axle.Rocker bar bearing 3 is monaural permanent seat, and one end that hinge bodies 4 and rocker bar bearing 3 are connected is ears structure, and the two is dynamically connected by hinge bodies pivot pin 7 axle.
The rotating shaft of tradition lid is fixed rotating shaft, and under rotating shaft fixing situation, lid open angle is definite value.The utility model, by designing hinge, increases rotating shaft at hinge place, changes to double-axle rotation and rotates, thus increase lid open angle by traditional single axle rotation.Finally exchange lid unlatching maximum angle for sacrifice minimum weight, thus improve the maintainability of equipment compartment.
In concrete use procedure, lid 2 arranges two groups of rocker bar bearings 3, is bolted to connection between rocker bar bearing 3 and lid 2.The peripheral circumference of lid 2 is provided with lid frame 8, and covering 1 with lid frame 8 are equipped with two groups of housing construction bearings 5 with rocker bar bearing 3, and housing construction bearing 5 and covering 1, lid frame 8 are bolted to connection.Often organize rocker bar bearing 3 to be connected by hinge bodies 4 with between housing construction bearing 5.Hinge bodies 4 and housing construction bearing 5 coupling end are monaural structure, and housing construction bearing 5 is ears bearing.Hinge bodies 4 and rocker bar bearing 3 coupling end are ears structure, and rocker bar bearing 3 is monaural bearing.
Hinge bodies 4 and housing construction bearing 5 are connected by housing construction pivot pin 6 and by locking wire lock extremely, are fixed on housing construction bearing 5 by the monaural end of hinge bodies 4; Hinge bodies 4 and rocker bar bearing 3 are connected by hinge bodies pivot pin 7 and dead with locking wire lock, and hinge bodies 4 is fixed on rocker bar bearing 3.Like this, hinge bodies 4 with housing construction bearing 5 for fixed point, housing construction pivot pin 6 rotate around housing construction pivot pin 6 for rotating shaft.In addition, lid 2 can the ears end of hinge bodies 4 for fixed point, hinge bodies pivot pin 7 is axis of rotation.Rotated around housing construction bearing 5 by hinge bodies 4, lid 2 around hinge bodies 4 rotate the opening angle of lid 2 can be increased greatly, enable staff more convenient, have larger space to keep in repair equipment compartment.
Specific embodiment more than in conjunction with the utility model airplane hatch cover hinge arrangement is described in detail, but be not to restriction of the present utility model, everyly according to technical spirit of the present utility model, technical scope of the present utility model is all belonged to any simple modification made for any of the above embodiments, also it should be noted that, comprise the combination in any between each part mentioned above according to the category of airplane hatch cover hinge arrangement technical scheme of the present utility model.
Claims (3)
1. an airplane hatch cover hinge arrangement, for the connection of aircraft upper flap (2) with body, lid (2) circumference is provided with lid frame (8), lid (2) is fixedly connected with by quick-detachable lock with lid frame (8), it is characterized in that: comprise rocker bar bearing (3), hinge bodies (4), housing construction bearing (5), housing construction pivot pin (6), hinge bodies pivot pin (7), wherein, covering (1), housing construction bearing (5) is connected by fastener with lid frame (8), hinge bodies (4) is connected with described housing construction bearing (5), rocker bar bearing (3) is fixed in described lid (2) by fastener, hinge bodies (4) and rocker bar bearing (3) are connected.
2. airplane hatch cover hinge arrangement as claimed in claim 1, it is characterized in that: described housing construction bearing (5) is ears permanent seat, one end that described hinge bodies (4) and described housing construction bearing (5) are connected is monaural structure, and the two is dynamically connected by housing construction pivot pin (6) axle.
3. airplane hatch cover hinge arrangement as claimed in claim 1, it is characterized in that: rocker bar bearing (3) is monaural permanent seat, one end that hinge bodies (4) and rocker bar bearing (3) are connected is ears structure, and the two is dynamically connected by hinge bodies pivot pin (7) axle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520430403.XU CN204775985U (en) | 2015-06-19 | 2015-06-19 | Aircraft flap hinge structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520430403.XU CN204775985U (en) | 2015-06-19 | 2015-06-19 | Aircraft flap hinge structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204775985U true CN204775985U (en) | 2015-11-18 |
Family
ID=54516087
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520430403.XU Active CN204775985U (en) | 2015-06-19 | 2015-06-19 | Aircraft flap hinge structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204775985U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106184702A (en) * | 2016-09-23 | 2016-12-07 | 江西洪都航空工业集团有限责任公司 | Waterproof quick-release combination lid |
| CN106428515A (en) * | 2016-09-23 | 2017-02-22 | 江西洪都航空工业集团有限责任公司 | Foldable cabin door |
| CN109606616A (en) * | 2018-11-07 | 2019-04-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of double-axle rotation quick-release lid |
| CN110462067A (en) * | 2017-04-04 | 2019-11-15 | 日本制铁株式会社 | The heating device and heating means of torpedo hot metal mixer car |
| CN110984742A (en) * | 2019-11-27 | 2020-04-10 | 天津爱思达新材料科技有限公司 | Hinge for aircraft |
| CN113320713A (en) * | 2021-04-29 | 2021-08-31 | 中国电子科技集团公司第二十九研究所 | Pod large-opening-face quick-release maintenance opening cover device and design method |
-
2015
- 2015-06-19 CN CN201520430403.XU patent/CN204775985U/en active Active
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106184702A (en) * | 2016-09-23 | 2016-12-07 | 江西洪都航空工业集团有限责任公司 | Waterproof quick-release combination lid |
| CN106428515A (en) * | 2016-09-23 | 2017-02-22 | 江西洪都航空工业集团有限责任公司 | Foldable cabin door |
| CN106428515B (en) * | 2016-09-23 | 2019-07-09 | 江西洪都航空工业集团有限责任公司 | A kind of foldable hatch door |
| CN110462067A (en) * | 2017-04-04 | 2019-11-15 | 日本制铁株式会社 | The heating device and heating means of torpedo hot metal mixer car |
| CN109606616A (en) * | 2018-11-07 | 2019-04-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of double-axle rotation quick-release lid |
| CN110984742A (en) * | 2019-11-27 | 2020-04-10 | 天津爱思达新材料科技有限公司 | Hinge for aircraft |
| CN113320713A (en) * | 2021-04-29 | 2021-08-31 | 中国电子科技集团公司第二十九研究所 | Pod large-opening-face quick-release maintenance opening cover device and design method |
| CN113320713B (en) * | 2021-04-29 | 2023-03-24 | 中国电子科技集团公司第二十九研究所 | Quick-release maintenance covering cap device for large opening surface of nacelle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |