CN105015437A - Interior trim support for aircraft - Google Patents
Interior trim support for aircraft Download PDFInfo
- Publication number
- CN105015437A CN105015437A CN201510496368.6A CN201510496368A CN105015437A CN 105015437 A CN105015437 A CN 105015437A CN 201510496368 A CN201510496368 A CN 201510496368A CN 105015437 A CN105015437 A CN 105015437A
- Authority
- CN
- China
- Prior art keywords
- interior trim
- support
- aircraft
- rack body
- strip hole
- 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.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60R—VEHICLES, VEHICLE FITTINGS, OR VEHICLE PARTS, NOT OTHERWISE PROVIDED FOR
- B60R13/00—Elements for body-finishing, identifying, or decorating; Arrangements or adaptations for advertising purposes
- B60R13/02—Internal Trim mouldings ; Internal Ledges; Wall liners for passenger compartments; Roof liners
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60R—VEHICLES, VEHICLE FITTINGS, OR VEHICLE PARTS, NOT OTHERWISE PROVIDED FOR
- B60R13/00—Elements for body-finishing, identifying, or decorating; Arrangements or adaptations for advertising purposes
- B60R13/02—Internal Trim mouldings ; Internal Ledges; Wall liners for passenger compartments; Roof liners
- B60R2013/0293—Connection or positioning of adjacent panels
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Connection Of Plates (AREA)
Abstract
The invention relates to structural design technologies of interior trim supports for aircrafts and discloses an interior trim support for an aircraft. A support body is a U-type structural part formed integrally and is composed of a long side, short sides and a transverse side. The long side is parallel to a structural frame of the aircraft and is connected with a structural stringer through angle pieces. The short sides are of a flange structure and are provided with grooves and used for clamping spring clip supporting plate nuts. Long-strip holes are formed in the transverse side, and screws are matched with the spring clip supporting plate nuts to fixedly connect the transverse side with an interior trim plate. The interior trim support for the aircraft is simple in structure and good in technology feasibility and can be formed through sheet metal parts. The U-shaped structure facilitates support and interior trim plate positioning on an installing site and ensures installing precision; the long-strip holes in the support can effectively eliminate errors accumulated in the installing process, rapid adjustment on the installing site is achieved, working efficiency is improved, and the cost is lowered.
Description
Technical field
The present invention relates to technical field of aircraft structure design, in particular to a kind of aircraft interior trim support.
Background technology
Traditional aircraft interior trim support, lack actv. location measure and regulate surplus, cannot effectively eliminate the accumulated error produced in interior trim installation process, often cause original mounting hole on trim panel cannot to match with the hole on support, need scene distribution again, thus affect setting accuracy and effect, reduce work efficiency.Present urgent problem how to design a kind of interior trim support, can be eliminated the cumulative errors produced in interior trim installation process by structure design, avoids reseting mounting hole on trim panel thus the integral structure affecting trim panel, improves setting accuracy.
Summary of the invention
The object of the invention is to solve above-mentioned deficiency of the prior art, a kind of adjustment surplus when ensureing that trim panel is installed is provided, can effectively eliminates the error accumulated in installation process, the aircraft interior trim support of raising setting accuracy.
Object of the present invention is achieved through the following technical solutions: a kind of aircraft interior trim support, comprise rack body, gusset plate, the U-shaped framing member that rack body is formed in one, be made up of long limit, minor face, horizontal edge, wherein, long limit is paralleled with the structural frames of aircraft and is connected by the long purlin of gusset plate and structure; Horizontal edge offers strip hole, and horizontal edge is fixedly connected with trim panel through strip hole, trim panel coordinating with springclip holder crab bolt by screw; Minor face is turnup structure and is provided with groove, for clamp springs folder plate nut.
In such scheme preferably, horizontal edge and trim panel cambered surface profile match.
In above-mentioned either a program preferably, long limit is fixedly connected with by screw with gusset plate.
In above-mentioned either a program preferably, the external diameter of springclip holder crab bolt is identical with the width of strip hole, and the length of strip hole is greater than the diameter of screw.
In above-mentioned either a program preferably, rack body is metallic article.
In above-mentioned either a program preferably, gusset plate is metal metal plate comer pieces, and the metal plate bending angle of gusset plate and the long purlin of structure, long limit angulation match.
The beneficial effect of aircraft interior trim support provided by the present invention is, structure is simple, and easily manufactured, device stability is high, safe and reliable.
Accompanying drawing explanation
Fig. 1 is the package assembly schematic diagram of the preferred embodiment according to aircraft interior trim support of the present invention;
Fig. 2 is the partial groups assembling structure schematic diagram embodiment illustrated in fig. 1 according to aircraft interior trim support of the present invention;
Fig. 3 is the cross-sectional view of the rack body embodiment illustrated in fig. 1 according to aircraft interior trim support of the present invention.
Reference numeral:
The long limit of 1-rack body, 2-, 3-minor face, 4-horizontal edge, 5-trim panel, 6-groove, 7-strip hole, 8-springclip holder crab bolt, 9-gusset plate, 10-screw.
Detailed description of the invention
In order to understand the aircraft interior trim support according to the present invention program better, be further elaborated explanation below in conjunction with the preferred embodiment of accompanying drawing to aircraft interior trim support of the present invention.
As Figure 1-3, aircraft interior trim support provided by the invention, comprises rack body 1, gusset plate 9, the U-shaped framing member that rack body 1 is formed in one, be made up of long limit 2, minor face 3, horizontal edge 4, wherein, long limit 2 is paralleled with the structural frames of aircraft and is connected by the long purlin of gusset plate 9 and structure; Horizontal edge 4 offers strip hole 7, horizontal edge 4 is fixedly connected with trim panel 5 through strip hole 7, trim panel 5 coordinating with springclip holder crab bolt 8 by screw 10; Minor face 3 is turnup structure and is provided with groove 6, for clamp springs folder plate nut 8.Horizontal edge 4 and trim panel 5 cambered surface profile match.Long limit 2 is fixedly connected with by screw with described gusset plate 9.The external diameter of springclip holder crab bolt 8 is identical with the width of strip hole 7, and the length of strip hole 7 is greater than the diameter of screw 10.Rack body 1 is metallic article.Gusset plate 9 is metal metal plate comer pieces, and the metal plate bending angle of gusset plate 9 and the long purlin of structure, long limit 2 angulation match.
Aircraft interior trim support Design provided by the invention is U-shaped structure, and long limit 2 parallels with aircaft configuration frame, the location of rack body 1 when being convenient to install.Top, long limit 2 is connected with gusset plate 9, and gusset plate 9 is fixed on the long purlin of structure, can be used for connecting the trim panel 5 distant with structure.Minor face 3 is flange, plays structural strengthening effect.Minor face 3 offers groove 6, for clamp springs folder plate nut 8, horizontal edge 4 and trim panel 5 cambered surface profile match, and horizontal edge 4 have strip hole 7, fix trim panel 5 by springclip holder crab bolt 8 and screw 10.
In concrete use procedure, first gusset plate 9 is fixed on aircaft configuration, by screw, gusset plate 9 is fixedly connected with the long limit 2 of rack body 1, in installation process, guarantee that the long limit of rack body 1 parallels with aircaft configuration frame.The horizontal edge 4 of rack body 1 matches with the cambered surface profile of trim panel 5.
As Figure 1-Figure 2, springclip holder crab bolt 8 is clamped on strip hole 7 by the groove 6 on minor face 3 by springclip holder crab bolt 8, and trim panel 5 is fixed on strip hole 7 place of rack body 1 by the cooperation of screw 10, springclip holder crab bolt 8.The length of strip hole 7 is larger than the diameter of screw 10, so screw 10 can move along the length direction of strip hole 7, strip hole 7 and springclip holder crab bolt 8 with the use of guaranteeing that trim panel has certain adjustment surplus, effectively eliminate the error of accumulating in installation process.Minor face 3 is turnup structure, improves the overall construction intensity of rack body 1.
Long limit 2 is connected by gusset plate 9 with the long purlin of aircraft, load suffered by rack body 1 can be passed to housing construction by gusset plate 9, guarantees that rack body 1 can not be stressed and cause the damage of structure due to integral structure.Gusset plate 9 and rack body 1 are combined to form secondary support for fixed range rack body 1 trim panel 5 far away.
The horizontal edge of rack body 1 offers strip hole 7, screw 10 through strip hole 7, and coordinates with spring plank nut 8 and is fixed on rack body 1 by trim panel 5.The minor face 3 of rack body 1 is also provided with groove 6, and for clamp springs folder plate nut 8, groove 6 pairs of springclip holder crab bolts 8 carry out spacing, avoid springclip holder crab bolt 8 with rack body 1, relative displacement can not occur and change.
Rack body 1 integral structure of aircraft interior trim support provided by the invention is simple, technological feasibility is good, the mode utilizing can manufacturing can shaped support body 1. rack body 1 be integral type structure, and by machine up one-shot forming, long limit 2, minor face 3 are connected by horizontal edge 4.
Strip hole 7 is Long Circle hole, the two ends of strip hole 7 are semi-circular structure, and middle part is rectangular configuration, semicircular structure and rectangular configuration junction rounding off, semi-round diameter is identical with the external diameter of spring plank nut 8, and the length of rectangular configuration is greater than the radius length of screw 10.Screw 10 coordinates with spring plank nut 8, is fixed on the horizontal edge 4 of rack body 1 by spring plank nut 8.By the position of set screw 10 in strip hole 7, can avoid in the process of installing trim panel 5 because installation error accumulates the not corresponding problem in the position, hole of the rack body 1 caused.Long Circle is set to by being used for the fixed orifice of fixed support body 1 with trim panel 5, the installation error eliminating rack body 1 by adjustment screw 10 and the relative position of strip hole 7 accumulates, avoid carrying out secondary punching to rack body 1 or trim panel 5, ensure the integraty of the structure of body, on housing construction intensity without impact.In addition, when trim panel 5 is installed, by regulating in strip hole 7, the field erected time reduces, strip hole 7 and springclip holder crab bolt 8 with the use of guaranteeing that trim panel has certain adjustment surplus, the error of accumulating in effective elimination installation process, reduce the field erected time, installation effectiveness improves greatly.
The structure of rack body 1 is simple, and technological feasibility is good, utilizes sheet metal component and plastic.As shown in Figure 3, rack body 1 is U-shaped structure, comprises long limit 2, minor face 3, horizontal edge 4, horizontal edge 4 offers strip hole 7.Rack body 1 is conducive to the location of erecting stage rack body 1 and trim panel 5 for U-shaped structure, guarantees setting accuracy; Strip hole 7 on support can effectively eliminate the error of accumulating in the installation process of trim panel 5, realizes the quick adjustment of erecting stage, increases work efficiency and reduces costs.
More than be described in detail in conjunction with aircraft interior trim support specific embodiment of the present invention, but be not limitation of the present invention, everyly according to technical spirit of the present invention, technical scope of the present invention 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 aircraft interior trim support technology scheme of the present invention.
Claims (6)
1. an aircraft interior trim support, it is characterized in that: comprise rack body (1), gusset plate (9), the U-shaped framing member that rack body (1) is formed in one, be made up of long limit (2), minor face (3), horizontal edge (4), wherein
Long limit (2) is paralleled with the structural frames of aircraft and is connected with the long purlin of structure by gusset plate (9);
Horizontal edge (4) offers strip hole (7), horizontal edge (4) is fixedly connected with trim panel (5) through strip hole (7), trim panel (5) coordinating with springclip holder crab bolt (8) by screw (10);
Minor face (3) is for turnup structure and be provided with groove (6), for clamp springs folder plate nut (8).
2. aircraft interior trim support as claimed in claim 1, is characterized in that: described horizontal edge (4) and trim panel (5) cambered surface profile match.
3. aircraft interior trim support as claimed in claim 1, is characterized in that: described long limit (2) is fixedly connected with by screw with described gusset plate (9).
4. aircraft interior trim support as claimed in claim 1, it is characterized in that: the external diameter of described springclip holder crab bolt (8) is identical with the width of described strip hole (7), the length of described strip hole (7) is greater than the diameter of described screw (10).
5. aircraft interior trim support as claimed in claim 1, is characterized in that: described rack body (1) is metallic article.
6. aircraft interior trim support as claimed in claim 3, it is characterized in that: described gusset plate (9) is metal metal plate comer pieces, the metal plate bending angle of described gusset plate (9) and the long purlin of structure, described long limit (2) angulation match.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510496368.6A CN105015437B (en) | 2015-08-13 | 2015-08-13 | A kind of aircraft interior trim support |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510496368.6A CN105015437B (en) | 2015-08-13 | 2015-08-13 | A kind of aircraft interior trim support |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105015437A true CN105015437A (en) | 2015-11-04 |
| CN105015437B CN105015437B (en) | 2017-11-21 |
Family
ID=54405865
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510496368.6A Active CN105015437B (en) | 2015-08-13 | 2015-08-13 | A kind of aircraft interior trim support |
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| Country | Link |
|---|---|
| CN (1) | CN105015437B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109538619A (en) * | 2018-11-23 | 2019-03-29 | 航天精工股份有限公司 | A kind of fixing hoop cornual plate component |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5610412A (en) * | 1979-07-04 | 1981-02-02 | Kasai Kogyo Co Ltd | Method of press-molding interior finish parts for car |
| KR20110045266A (en) * | 2009-10-26 | 2011-05-04 | (주)진명이앤씨 | construction exterior structure of the bracket assembly |
| KR20120001592U (en) * | 2010-08-27 | 2012-03-07 | 구하경 | bracket with the elasticity |
| CN203390804U (en) * | 2013-06-25 | 2014-01-15 | 中国商用飞机有限责任公司 | Positioning tooling for installing top control plate of aircraft cockpit |
-
2015
- 2015-08-13 CN CN201510496368.6A patent/CN105015437B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5610412A (en) * | 1979-07-04 | 1981-02-02 | Kasai Kogyo Co Ltd | Method of press-molding interior finish parts for car |
| KR20110045266A (en) * | 2009-10-26 | 2011-05-04 | (주)진명이앤씨 | construction exterior structure of the bracket assembly |
| KR20120001592U (en) * | 2010-08-27 | 2012-03-07 | 구하경 | bracket with the elasticity |
| CN203390804U (en) * | 2013-06-25 | 2014-01-15 | 中国商用飞机有限责任公司 | Positioning tooling for installing top control plate of aircraft cockpit |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109538619A (en) * | 2018-11-23 | 2019-03-29 | 航天精工股份有限公司 | A kind of fixing hoop cornual plate component |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105015437B (en) | 2017-11-21 |
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