CN203189436U - Clamping device of plane interior trim panel - Google Patents
Clamping device of plane interior trim panel Download PDFInfo
- Publication number
- CN203189436U CN203189436U CN 201320060251 CN201320060251U CN203189436U CN 203189436 U CN203189436 U CN 203189436U CN 201320060251 CN201320060251 CN 201320060251 CN 201320060251 U CN201320060251 U CN 201320060251U CN 203189436 U CN203189436 U CN 203189436U
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- CN
- China
- Prior art keywords
- plane
- retaining part
- clamping
- aircraft
- center
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- 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
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Abstract
The utility model discloses a clamping device of a plane interior trim panel. The clamping device is of a double-8-shaped elastic clamping structure, the double-8-shaped elastic clamping device forms multi-point clamping on a plane interior trim part through an inner-side plane clamping portion (1) and an annular inner-side clamping portion (2) on the end portion, a plate type compression structure (3) is arranged on the side face of the double-8-shaped clamping structure, so that an elastic secondary clamping structure is formed on the outer side face of the inner-side plane clamping portion (1), and a semi-annular protrusion is arranged at the tail end of the plate type compression structure (3). The clamping device of the plane interior trim panel (5) is simple in structure, convenient to manufacture, reliable in installation and capable of achieving rapid disassembly and assembly of the plane interior trim panel, and has large practical value.
Description
Technical field
The utility model relates to aircraft interior trim device, relates in particular to a kind of aircraft trim panel holding device.
Background technique
The conventional airplane trim panel often adopts fastening piece to be connected with aircaft configuration, and perforate and/or pre-buried inserter often must be set on the aircraft trim panel, transplants a cutting with trim panel and hides fastening piece in the hope of reaching decorative effect preferably.But adopt the connecting means of this aircraft trim panel, perforate and/or pre-buried inserter must be set on the aircraft trim panel, the many and weightening finish of process.
The model utility content
The purpose of this utility model is: a kind of aircraft trim panel holding device is provided, and manufacturing process is simple, connects reliably, with low cost, and is used with other aircraft inside gadget connecting means and can makes the inside gadget fast assembling-disassembling.
The technical solution of the utility model is: a kind of aircraft trim panel holding device, this holding device is symplex structure, the resilient clamp structure that is two " 8 " shapes, comprise and constitute two " 8 " shape upper half part, be positioned at the plane retaining part of center of inside and constitute two " 8 " shape lower half portions, be positioned at and add the ring gripping position of holding the device end, two place's retaining parts form the multiple spot clamping to the aircraft inside gadget; Clevis is held the outer side surface of structure in two " 8 ", end is set has the board-like compressing structure of semi-circular projection to the outer side surface formation elasticity time clamping structure of its center of inside plane retaining part.
The beneficial effects of the utility model are: it is many and effect is relatively poor to overcome the installation process of fastening piece connecting means of traditional aircraft inside gadget, inside gadget can't fast assembling-disassembling problem, a kind of aircraft inside gadget holding device of novelty is provided, be used with other aircraft inside gadget connecting means, both can effectively improve decorative effect, and can make the inside gadget fast assembling-disassembling, this holding device manufacturing process is simple, connect reliable, with low cost.
Description of drawings
Fig. 1 is the utility model holding device axonometric drawing.
Fig. 2 is the utility model holding device front view.
Fig. 3 is that the utility model holding device is to the clamping schematic representation of aircraft inside gadget.
Embodiment
Below in conjunction with accompanying drawing the utility model is described in further detail:
As shown in Figure 1, 2, 3, the holding device that the utility model provides is symplex structure, the resilient clamp structure that roughly is two " 8 " shapes, comprise and constitute two " 8 " shape upper half part 1, be positioned at the plane retaining part 11 of center of inside and constitute two " 8 " shape lower half portions 2, be positioned at and add ring gripping position 22, two place's retaining parts of holding the device end aircraft inside gadget is formed the multiple spot clamping; Clevis is held the outer side surface of structure in two " 8 ", end is set has semi-circular protruding 31 board-like compressing structure 3 outer side surface of its center of inside plane retaining part is formed elasticity time clamping structure.
The holding device of two " 8 " shape is that highly resilient material is made, and its attachment face 4 is the plane, can be fixed on the structural member by methods such as splicing or riveted joints.
The plane retaining part that constitutes the center of inside of two " 8 " shape upper half part 1 has one section plane retaining part 11, and be held aircraft inside gadget formation face and contact, the ring gripping position of this surface of contact and end is in same plane with the line contact position that is held the aircraft inside gadget, and the end 12 outside perks of plane retaining part are avoided being held the scraping of aircraft inside gadget.
The ring gripping position that is positioned at the holding device end that constitutes two " 8 " shape lower half portions 2 is dual torus, the dual torus inner side surface forms " pilot pin " effect that is inserted with that 21 pairs of grooves are held the aircraft inside gadget, the dual torus retaining part forms line and contact with being held between the aircraft inside gadget, and is positioned at same plane with the surface of contact of the plane retaining part of the center of inside that constitutes pair " 8 " shape upper half part.
Arranged outside at the plane retaining part 11 of the center of inside that constitutes two " 8 " shape upper half part has the terminal outwards semiorbicular board-like compressing structure 3 of perk to be pressed on the outer side surface of plane retaining part, the plane retaining part is formed the hypoelasticity clamping structure, be the line contact between the two.
The resilient clamp structure of two " 8 " shape and other aircraft inside gadget 5 connecting means are used, and can realize the fast assembling-disassembling of aircraft inside gadget 5.
The utility model using method is as follows:
At first, two " 8 " clevis being held Unit Installation face 4 is fixed on the structural member by Placements such as splicing or riveted joints; Secondly, aircraft inside gadget 5 is inserted along the groove 21 that the what is called of holding device end plays " pilot pin " effect, the plane that enters the holding device center of inside up to the end of aircraft inside gadget 5 adds holds in the position 11.In addition, the other end of aircraft inside gadget 5 adopts other Placement to be fixed on the structural member, thereby realizes being connected between aircraft inside gadget 5 and the structural member.
Claims (5)
1. aircraft trim panel holding device, it is characterized in that, this holding device is symplex structure, the resilient clamp structure that is two " 8 " shapes, comprise and constitute two " 8 " shape upper half part (1), be positioned at the plane retaining part (11) of center of inside and constitute two " 8 " shape lower half portions (2), be positioned at and add the ring gripping position (22) of holding the device end, two place's retaining parts form the multiple spot clamping to the aircraft inside gadget; Clevis is held the outer side surface of structure in two " 8 ", end is set has the board-like compressing structure (3) of semi-circular projection (31) to the outer side surface formation elasticity time clamping structure of its center of inside plane retaining part.
2. device according to claim 1 is characterized in that, the holding device of two " 8 " shape is that highly resilient material is made, and its attachment face (4) is the plane, is fixed on the structural member by splicing or clinching method.
3. device according to claim 1, it is characterized in that, its plane retaining part that constitutes the center of inside of two " 8 " shape upper half part (1) has one section plane clamp face structure (11), and be held aircraft inside gadget formation face and contact, the ring gripping position of this surface of contact and end is in same plane with the line contact position that is held the aircraft inside gadget, and outwards perk of the end of plane retaining part (12).
4. device according to claim 1, it is characterized in that, the ring gripping position that is positioned at the holding device end that constitutes two " 8 " shape lower half portions (2) is dual torus, the dual torus inner side surface forms groove (21), the dual torus retaining part forms line and contact (22) with being held between the aircraft inside gadget, and is positioned at same plane with the surface of contact of the plane retaining part of the center of inside that constitutes pair " 8 " shape upper half part.
5. device according to claim 1, it is characterized in that, the arranged outside of the plane retaining part (11) of the center of inside that constitutes two " 8 " shape upper half part have end (31) outwards the semiorbicular board-like compressing structure (3) of perk be pressed on the outer side surface of plane retaining part, the plane retaining part is formed the hypoelasticity clamping structure, be the line contact between the two.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320060251 CN203189436U (en) | 2013-02-01 | 2013-02-01 | Clamping device of plane interior trim panel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320060251 CN203189436U (en) | 2013-02-01 | 2013-02-01 | Clamping device of plane interior trim panel |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203189436U true CN203189436U (en) | 2013-09-11 |
Family
ID=49106298
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201320060251 Expired - Lifetime CN203189436U (en) | 2013-02-01 | 2013-02-01 | Clamping device of plane interior trim panel |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203189436U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105416766A (en) * | 2015-09-14 | 2016-03-23 | 廖苔安 | Combined pallet |
| CN105947368A (en) * | 2015-04-14 | 2016-09-21 | 廖苔安 | Combined pallet |
| CN106015212A (en) * | 2016-07-28 | 2016-10-12 | 青岛海澄知识产权事务有限公司 | Flexible material fixing device |
| CN107989860A (en) * | 2017-11-08 | 2018-05-04 | 苏州固特斯电子科技有限公司 | A kind of metal plate shackle member |
| CN109322994A (en) * | 2018-11-02 | 2019-02-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of encapsulating method of aircraft trim panel |
| US10519992B2 (en) | 2017-11-30 | 2019-12-31 | Ford Global Technologies, Llc | Spring clip with a single resilient cantilevered leg |
-
2013
- 2013-02-01 CN CN 201320060251 patent/CN203189436U/en not_active Expired - Lifetime
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105947368A (en) * | 2015-04-14 | 2016-09-21 | 廖苔安 | Combined pallet |
| CN105947368B (en) * | 2015-04-14 | 2018-02-16 | 昆山亚比斯环保包装材料有限公司 | Combined pallet |
| CN105416766A (en) * | 2015-09-14 | 2016-03-23 | 廖苔安 | Combined pallet |
| CN105923236A (en) * | 2015-09-14 | 2016-09-07 | 廖苔安 | Combined pallet |
| CN105923236B (en) * | 2015-09-14 | 2018-12-04 | 昆山亚比斯环保包装材料有限公司 | Combined pallet |
| CN106015212A (en) * | 2016-07-28 | 2016-10-12 | 青岛海澄知识产权事务有限公司 | Flexible material fixing device |
| CN107989860A (en) * | 2017-11-08 | 2018-05-04 | 苏州固特斯电子科技有限公司 | A kind of metal plate shackle member |
| US10519992B2 (en) | 2017-11-30 | 2019-12-31 | Ford Global Technologies, Llc | Spring clip with a single resilient cantilevered leg |
| CN109322994A (en) * | 2018-11-02 | 2019-02-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of encapsulating method of aircraft trim panel |
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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 | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130911 |