CN204775984U - Light aerocraft wing covering panel beating flap - Google Patents
Light aerocraft wing covering panel beating flap Download PDFInfo
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- CN204775984U CN204775984U CN201520431075.5U CN201520431075U CN204775984U CN 204775984 U CN204775984 U CN 204775984U CN 201520431075 U CN201520431075 U CN 201520431075U CN 204775984 U CN204775984 U CN 204775984U
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- lid
- covering
- panel beating
- aircraft wing
- flap
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Abstract
The utility model provides a light aerocraft wing covering panel beating flap, relates to light aerocraft wing structural design technique for the inside a large amount of system of light aerocraft wing and the maintenance of structure are long circle panel beating structure, flap body (1) beading formation crimp including flap body (1), flap body (1) is with aircraft wing covering (2) overlap joint and form the echelonment structure, and its height equals with the thickness of aircraft wing covering (2) that flap fixed orifices (3) and aircraft wing covering (2) fixed connection are passed through plate nut group (4) in flap body (1). The utility model provides a light aerocraft wing covering panel beating flap simple structure, it is convenient to make, need not to arrange the connector frame specially, has reduced the degree of difficulty of arranging, and pneumatic appearance has been guaranteed to appearance face and aircraft wing covering (2) appearance parallel and level, only uses one row of plate nut group (4) with the organism when being connected, has improved maintenance efficiency.
Description
Technical field
The utility model relates to technical field of aircraft structure design, in particular to a kind of light airplane wing using collaborative optimization covering panel beating lid.
Background technology
Aircraft wing structure inside has a large amount of systems and structure to need to safeguard, therefore wing cover need layout to safeguard lid, safeguard that the form that lid is commonly used has following several form: 1, flat lid, be placed in engine body exterior, the wing cover of this kind of form safeguards that lid advantage is that dismounting is simple, shortcoming needs in lid junction to arrange mouth frame, for connecting lid, this adds increased the difficulty of structural arrangement and structure design, increase structural weight, the region of lid can not arranged, adopt external lid, lid can give prominence to profile, impacts pneumatic; 2, flat lid, is placed in internal body, and the wing cover of this kind of form safeguards that the advantage of lid is lid junction, and without the need to arranging mouth frame, shortcoming has jump between lid and profile, impacts pneumatic; 3, body-packing ring-lid form, lid connects by two nails, body is connected with packing ring, packing ring is connected with lid again, the wing cover of this kind of form safeguards that the advantage of lid is easy accessibility, shortcoming cannot use in the region of space anxiety, or need lid size to reduce, and brings difficulty to maintenance.
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, install after and wing cover maintains an equal level, without the need to arranging mouth frame, can increasing the light airplane wing using collaborative optimization covering panel beating lid of lid size.
The purpose of this utility model is achieved through the following technical solutions: a kind of light airplane wing using collaborative optimization covering panel beating lid, and comprise lid body, lid body is Long Circle Sheet Metal Part, and the curved edge of lid body forms crimp; Opening shape centered by the center of lid body, on aircraft wing covering is border, part between border and crimp is bent to form step structure to the direction that crimp is bending and overlaps with aircraft wing covering, and the height of step structure is equal with the thickness of aircraft wing covering.
In such scheme preferably, lid body and aircraft wing covering overlap are provided with lid fixed orifice along aircraft wing covering opening shape circumference.
In above-mentioned either a program preferably, lid body is fixedly connected with aircraft wing covering through lid fixed orifice by plate nut group, and wherein, plate nut group is the unitized construction of screw bolt and nut.
In above-mentioned either a program preferably, the distance of the adjacent lid fixed orifice on lid body is 6-8d, and wherein, d is the diameter of bolt in plate nut group.
The beneficial effect of light airplane wing using collaborative optimization covering panel beating lid provided by the utility model is, structure is simple, easily manufactured, without the need to specific placement communication port frame, reduce the difficulty of layout, external surface is concordant with wing profile, ensure that aerodynamic configuration, uses row's fastener when being connected with body, improve maintenance efficiency, compared with traditional lid, especially the nervous region in space, considerably increases the size of lid.
Accompanying drawing explanation
Fig. 1 is the cross-sectional view of the embodiment 1 according to light airplane wing using collaborative optimization covering panel beating lid of the present utility model;
Fig. 2 is the schematic diagram of the embodiment illustrated in fig. 1 concrete enforcement according to light airplane wing using collaborative optimization covering panel beating lid of the present utility model.
Reference numeral:
1-lid body, 2-aircraft wing covering, 3-lid fixed orifice, 4-plate nut group.
Detailed description of the invention
In order to understand the light airplane wing using collaborative optimization covering panel beating lid according to the utility model scheme better, be further elaborated explanation below in conjunction with the preferred embodiment of accompanying drawing to light airplane wing using collaborative optimization covering panel beating lid of the present utility model.
Embodiment 1:
As shown in Figure 1-2, the light airplane wing using collaborative optimization covering panel beating lid that the utility model provides, comprise lid body 1, lid body 1 is Long Circle Sheet Metal Part, and lid body 1 curved edge forms crimp; Opening shape centered by the center of lid body 1, on aircraft wing covering 2 is border, part between border and crimp is bent to form step structure to the direction that crimp is bending and overlaps with aircraft wing covering 2, and the height of step structure is equal with the thickness of aircraft wing covering 2.Lid body 1 and aircraft wing covering 2 overlap are provided with lid fixed orifice 3 along aircraft wing covering 2 opening shape circumference.Lid body 1 is fixedly connected with aircraft wing covering 2 through lid fixed orifice 3 by plate nut group 4, and wherein, plate nut group 4 is the unitized construction of screw bolt and nut.The distance of the adjacent lid fixed orifice 3 on lid body 1 is 6d, and wherein, d is the diameter of bolt in plate nut group 4.
The cross-sectional view of the preferred embodiment of the light airplane wing using collaborative optimization covering panel beating lid that Fig. 1 provides for the utility model, in figure, left side lid body 1 is plate nut group 4 with the black shaded area of aircraft wing covering 2 overlap, and right cap body 1 does not relate to plate nut group 4 with the section of aircraft wing covering 2 overlap.
In concrete use procedure, the services aperture that under certain type aviette leading edge, covering place offers as shown in Figure 2, the light airplane wing using collaborative optimization covering panel beating lid that this services aperture adopts the utility model preferred embodiment to provide is closed, and institute's services aperture of opening is for safeguarding that Wing-Body Configurations connects strut joint.Services aperture is ellipsoidal structure.Make and safeguard lid with the ellipse of this services aperture mating shapes.Lid body 1 is placed in services aperture, the edge of lid body 1 is provided with crimp, the crimp of lid body 1 is placed on the inner side of aircraft wing covering 2, the thickness deviating from the concave portion of lid body 1 crimp side is identical with the thickness of aircraft wing covering 2, like this, light airplane wing using collaborative optimization covering panel beating lid and aircraft wing covering 2 that the utility model provides is observed outside aircraft wing, jump is not had between lid body more than 1 aircraft wing covering 2, so use the light airplane wing using collaborative optimization covering panel beating lid of the utility model preferred embodiment to carry out closing can not impact startup this place's services aperture.
The light airplane wing using collaborative optimization covering panel beating lid that the utility model preferred embodiment provides, for oval, is placed in the inner side of aircraft wing covering 2, arranges along services aperture circumference the connection that row's plate nut group 4 realizes lid and aircraft wing covering 2.Open lid: be separated by the bolts and nuts of plate nut group 4, lid inwardly pushed away body, and rotates, lid minor face is placed in the side, long limit of services aperture on aircraft wing covering 2, lid is taken out.Close lid: lid minor face one is placed on the inner side that lid is put into aircraft wing covering 2 by side, body opening long limit, rotate lid to installation site and will install plate nut group 4, tightening, lid is closed.
Embodiment 2:
With reference to light airplane wing using collaborative optimization covering panel beating lid described in embodiment 1, the distance of adjacent lid fixed orifice 3 that difference is on lid body 1 is with it 7d.
Embodiment 3:
With reference to light airplane wing using collaborative optimization covering panel beating lid described in embodiment 1, the distance of adjacent lid fixed orifice 3 that difference is on lid body 1 is with it 8d.
More than be described in detail in conjunction with specific embodiment of the utility model, but be not to restriction of the present utility model, as the distance etc. between lid fixed orifice 3 adjacent on lid body 1, 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 light airplane wing using collaborative optimization covering panel beating lid technical scheme of the present utility model.
Claims (4)
1. a light airplane wing using collaborative optimization covering panel beating lid, comprises lid body (1), it is characterized in that: described lid body (1) is Long Circle Sheet Metal Part, and described lid body (1) curved edge forms crimp; Opening shape centered by the center of described lid body (1), on aircraft wing covering (2) is for border, part between border and crimp is bent to form step structure to the direction that crimp is bending and overlaps with aircraft wing covering (2), and the height of step structure is equal with the thickness of aircraft wing covering (2).
2. light airplane wing using collaborative optimization covering panel beating lid as claimed in claim 1, is characterized in that: described lid body (1) and aircraft wing covering (2) overlap are provided with lid fixed orifice (3) along aircraft wing covering (2) opening shape circumference.
3. light airplane wing using collaborative optimization covering panel beating lid as claimed in claim 1 or 2, it is characterized in that: described lid body (1) is fixedly connected with described aircraft wing covering (2) through lid fixed orifice (3) by plate nut group (4), wherein, plate nut group (4) unitized construction that is screw bolt and nut.
4. light airplane wing using collaborative optimization covering panel beating lid as claimed in claim 3, it is characterized in that: the distance of the adjacent lid fixed orifice (3) on described lid body (1) is 6-8d, wherein, d is the diameter of bolt in described plate nut group (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520431075.5U CN204775984U (en) | 2015-06-19 | 2015-06-19 | Light aerocraft wing covering panel beating flap |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520431075.5U CN204775984U (en) | 2015-06-19 | 2015-06-19 | Light aerocraft wing covering panel beating flap |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204775984U true CN204775984U (en) | 2015-11-18 |
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ID=54516086
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520431075.5U Active CN204775984U (en) | 2015-06-19 | 2015-06-19 | Light aerocraft wing covering panel beating flap |
Country Status (1)
| Country | Link |
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| CN (1) | CN204775984U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106394860A (en) * | 2016-11-25 | 2017-02-15 | 中国工程物理研究院总体工程研究所 | Skin connecting structure capable of being disconnected after being stressed |
| CN111017186A (en) * | 2019-12-10 | 2020-04-17 | 中国特种飞行器研究所 | Flexible wing surface structure maintenance opening cover |
| CN114715376A (en) * | 2022-05-24 | 2022-07-08 | 北京航空航天大学 | Maintenance flap suitable for flexible skin wing |
-
2015
- 2015-06-19 CN CN201520431075.5U patent/CN204775984U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106394860A (en) * | 2016-11-25 | 2017-02-15 | 中国工程物理研究院总体工程研究所 | Skin connecting structure capable of being disconnected after being stressed |
| CN111017186A (en) * | 2019-12-10 | 2020-04-17 | 中国特种飞行器研究所 | Flexible wing surface structure maintenance opening cover |
| CN114715376A (en) * | 2022-05-24 | 2022-07-08 | 北京航空航天大学 | Maintenance flap suitable for flexible skin wing |
| CN114715376B (en) * | 2022-05-24 | 2022-09-06 | 北京航空航天大学 | Maintenance flap suitable for flexible skin wing |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |