CN202923884U - Connecting structure of heat insulation layer of aircraft bulkhead - Google Patents
Connecting structure of heat insulation layer of aircraft bulkhead Download PDFInfo
- Publication number
- CN202923884U CN202923884U CN 201220325656 CN201220325656U CN202923884U CN 202923884 U CN202923884 U CN 202923884U CN 201220325656 CN201220325656 CN 201220325656 CN 201220325656 U CN201220325656 U CN 201220325656U CN 202923884 U CN202923884 U CN 202923884U
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- CN
- China
- Prior art keywords
- heat
- insulating block
- insulated
- bulkhead
- adhesive tape
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Abstract
The utility model discloses a connecting structure of a heat insulation layer of an aircraft bulkhead, belongs to an aircraft bulkhead heat insulation layer structure technology, relates to an improvement on the laying of a heat insulation layer and is suitable for laying a heat insulation layer on a region composed of multiple bulkheads, a long purlin and a skin. The connecting structure comprises buckle groups 1,2,5,6, insulated blocks 3,7,9, a fastener 11 and adhesive tapes 14,15; the insulated blocks 3,7 are respectively laid at two sides of two adjacent frames 4,8, the insulated block 3 is fixed by using the buckle groups 1,2, and the insulated block 7 is fixed by using the buckle groups 5,6; the insulated block 9 is extruded in a region with the skin 10 laid between the insulated blocks 3,7, the side of the insulated block 9, clinging to the skin 10, is provided with a groove 13, the long purlin 12 is located in the groove 13, and the insulated block 9 is fixedly connected with the long purlin 12 through the fastener 11; and the adhesive tape 14 is adhered with the insulated blocks 3,9, and the adhesive tape 15 is adhered with the insulated blocks 7,9. The connecting structure is simple in form, high in reliability and capable of shortening the mounting and maintaining time and greatly improving the laying effect while reducing the cost.
Description
Technical field
The utility model belongs to aircraft bulkhead insulating structure technology, relates to the improvement that adiabatic layer is laid, and the adiabatic layer that is applicable to the many bulkheads of bulkhead, long purlin and covering compositing area lays.
Background technology
Traditional bulkhead adiabatic layer material stiffness is little, without the characteristic of controlling oneself, for prevent from coming off, the generation of the fault such as Joint failure, need large tracts of land to use fastener, hasp etc. to be connected.A large amount of fasteners that use run through clad and core body, have reduced the tear resistance of adiabatic layer, and steam is easier infiltration also, and the durability of adiabatic layer, life-span are significantly reduced, and weight increases, and outward appearance, the also purpose of out of reach fast assembling-disassembling, maintenance are laid in impact.
Summary of the invention
The purpose of this utility model is: the purpose of this invention is to provide a kind of maintainability good, lay bulkhead adiabatic layer connection structure attractive in appearance.
The technical solution of the utility model is: a kind of connection structure of aircraft bulkhead adiabatic layer, comprise the first hasp group 1, the second hasp group 2, the 3rd hasp group 5, the 4th hasp group 6, the first heat-insulating block 3, the second heat-insulating block 7, the 3rd heat-insulating block 9, fastener 11, the first adhesive tape 14, the second adhesive tape 15, it is characterized in that: the first heat-insulating block 3, the second heat-insulating block 7 be laid in respectively adjacent the first bulkhead 4 and the second bulkhead, 8 both sides, the first heat-insulating block 3 adopts the first hasp group 1, the second hasp group 2 is fixing, and the second heat-insulating block 7 adopts the 3rd hasp group 5, the 4th hasp group 6 is fixing; The 3rd heat-insulating block 9 pushes covering 10 zones that are laid between the first heat-insulating block 3, the second heat-insulating block 7, the 3rd heat-insulating block 9 has groove 13 being close to covering 10 1 sides, making long purlin 12 be positioned at groove 13, the three heat-insulating blocks 9 captives joint with long purlin 12 by fastener 11; The first adhesive tape 14 and the first heat-insulating block 3, the 3rd heat-insulating block 9 are bonding, and the second adhesive tape 15 and the second heat-insulating block 7, the 3rd heat-insulating block 9 are bonding.The beneficial effects of the utility model are: this connection structure form is simple, reliability is high, a large amount of uses of the too much perforate of housing construction and fastener have been avoided, shortened installation and maintenance time, delayed the adiabatic layer suction and become the tide cycle, when saving cost, greatly improved and laid effect.
Description of drawings
Fig. 1 is the connection structure scheme drawing of aircraft bulkhead adiabatic layer
Fig. 2 is the connection structure A-A face scheme drawing of aircraft bulkhead adiabatic layer
Wherein 1 is the first hasp group, and 2 is the second hasp group, and 3 is the first heat-insulating block, 4 is the first bulkhead, and 5 is the 3rd hasp group, and 6 is the 4th hasp group, 7 is the second heat-insulating block, and 8 is the second bulkhead, and 9 is the 3rd heat-insulating block, 10 is covering, 11 is fastener, and 12 are long purlin, and 13 is groove, 14 is the first adhesive tape, and 15 is the second adhesive tape.
The specific embodiment
Below in conjunction with accompanying drawing the utility model is described in further detail:
Please also refer to Fig. 1 and Fig. 2, a kind of connection structure of aircraft bulkhead adiabatic layer comprises self bonding nylon the first hasp group 1, the second hasp group 2, the 3rd hasp group 5, the 4th hasp group 6, the first heat-insulating block 3, the second heat-insulating block 7, the 3rd heat-insulating block 9, fastener 11, the first adhesive tape 14, the second adhesive tape 15, the first adhesive tape 14, the second adhesive tape 15, the first heat-insulating block 3, the second heat-insulating block 7 adjacent the first bulkhead 4 that is laid in respectively, the both sides of the second bulkhead 8, the first heat-insulating block 3 adopts the first hasp group 1, the second hasp group 2 is fixing, and the second heat-insulating block 7 adopts the 3rd hasp group 5, the 4th hasp group 6 is fixing.The 3rd heat-insulating block 9 pushes covering 10 zones that are laid between the first heat-insulating block 3, the second heat-insulating block 7, the 3rd heat-insulating block 9 has groove 13 being close to covering 10 1 sides, make long purlin 12 be positioned at groove 13, the setting of groove has namely guaranteed the adiabatic layer thickness of different laying areas, the accumulated error of installation process along the first bulkhead 4, the second bulkhead 8 directions eliminated in the gap requirement that has kept again adiabatic layer and covering simultaneously.The 3rd heat-insulating block 9 is captiveed joint with long purlin 12 by fastener 11; The first adhesive tape 14 and the first heat-insulating block 3, the second heat-insulating block 9 are bonding, and the second adhesive tape 15 and the second heat-insulating block 7, the 3rd heat-insulating block 9 are bonding.Fastener 11 by glue buckle, nylon staple and rivet form.
Claims (3)
1. the connection structure of an aircraft bulkhead adiabatic layer, comprise the first hasp group (1), the second hasp group (2), the 3rd hasp group (5), the 4th hasp group (6), the first heat-insulating block (3), the second heat-insulating block (7), the 3rd heat-insulating block (9), fastener (11), the first adhesive tape (14), the second adhesive tape (15), it is characterized in that: the first heat-insulating block (3), the first bulkhead (4) that the second heat-insulating block (7) is laid in respectively adjacent and the both sides of the second bulkhead (8), the first heat-insulating block (3) adopts the first hasp group (1), the second hasp group (2) is fixing, and the second heat-insulating block (7) adopts the 3rd hasp group (5), the 4th hasp group (6) is fixing; The 3rd heat-insulating block (9) pushes covering (10) zone that is laid between the first heat-insulating block (3), the second heat-insulating block (7), the 3rd heat-insulating block (9) has groove (13) being close to covering (10) one sides, make long purlin (12) be positioned at groove (13), the 3rd heat-insulating block (9) is captiveed joint with long purlin (12) by fastener (11); The first adhesive tape (14) and the first heat-insulating block (3), the 3rd heat-insulating block (9) are bonding, and the second adhesive tape (15) and the second heat-insulating block (7), the 3rd heat-insulating block (9) are bonding.
2. the connection structure of a kind of aircraft bulkhead adiabatic layer as claimed in claim 1 is characterized in that: first to fourth hasp group (1), (2), (5), (6) employing self bonding velcro.
3. the connection structure of a kind of aircraft bulkhead adiabatic layer as claimed in claim 1 is characterized in that: fastener (11) by glue buckle, nylon staple and rivet form.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220325656 CN202923884U (en) | 2012-07-06 | 2012-07-06 | Connecting structure of heat insulation layer of aircraft bulkhead |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220325656 CN202923884U (en) | 2012-07-06 | 2012-07-06 | Connecting structure of heat insulation layer of aircraft bulkhead |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202923884U true CN202923884U (en) | 2013-05-08 |
Family
ID=48213871
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220325656 Expired - Lifetime CN202923884U (en) | 2012-07-06 | 2012-07-06 | Connecting structure of heat insulation layer of aircraft bulkhead |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202923884U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106132829A (en) * | 2014-04-08 | 2016-11-16 | 埃尔塞乐公司 | The clamp device of heat shield panel |
-
2012
- 2012-07-06 CN CN 201220325656 patent/CN202923884U/en not_active Expired - Lifetime
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106132829A (en) * | 2014-04-08 | 2016-11-16 | 埃尔塞乐公司 | The clamp device of heat shield 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: 20130508 |