CN109649635A - A kind of aircraft acoustical and thermal layer installation method - Google Patents
A kind of aircraft acoustical and thermal layer installation method Download PDFInfo
- Publication number
- CN109649635A CN109649635A CN201811306335.0A CN201811306335A CN109649635A CN 109649635 A CN109649635 A CN 109649635A CN 201811306335 A CN201811306335 A CN 201811306335A CN 109649635 A CN109649635 A CN 109649635A
- Authority
- CN
- China
- Prior art keywords
- acoustical
- plastic
- thermal layer
- staple bolt
- aircraft
- 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.)
- Pending
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/40—Sound or heat insulation, e.g. using insulation blankets
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/40—Sound or heat insulation, e.g. using insulation blankets
- B64C1/403—Arrangement of fasteners specially adapted therefor, e.g. of clips
Abstract
A kind of aircraft acoustical and thermal layer installation method, contain plastic staple bolt and plastic spacer, the rivet nut of the plastic staple bolt is equipped with rounded tabs, overhead structure is equipped in baffle side, multiple coaxial taper buckles are equipped in the rivet nut of the baffle other side, the diameter of the baffle is greater than the diameter of taper buckle, and the rivet nut between adjacent conical buckle forms annular slot, and the plastic spacer is equipped with the flexible hole with extension notch；The overhead structure end of plastic staple bolt is passed through to the connecting hole of airframe, the conic clamp end of thread of plastic staple bolt is passed through into acoustical and thermal layer, in the annular slot for the plastic staple bolt that the flexible hole of plastic spacer is socketed in outside acoustical and thermal layer again, acoustical and thermal layer is connect with airframe with plastic spacer and plastic staple bolt.
Description
Technical field
The application belongs to airplane design technical field, and in particular to aircraft acoustical and thermal layer installation method.
Background technique
Aircraft acoustical and thermal layer is typically mounted at aircraft skin inner surface, by the heat-proof quality and sound insulation effect of material,
The thermal environment in aircraft cabin is maintained to improve the noise radiation in cabin simultaneously.
The mounting hole that the installation of existing aircraft acoustical and thermal layer first passes through nylon staple tail end is riveted in aircraft stringer, then
Acoustical and thermal layer passes through nylon staple, finally by glue buckle into nylon staple tip, to fix acoustical and thermal layer.
On the one hand this installation form needs rivet nylon staple, on the other hand need fixed acoustical and thermal thickness degree
To be matched with the length of nylon staple.
Summary of the invention
The purpose of the present invention is to provide a kind of aircraft acoustical and thermal layer installation methods, can fix the sound insulation of different-thickness
Thermal insulation layer.
A kind of aircraft acoustical and thermal layer installation method, which is characterized in that 1) contain plastic staple bolt and plastic spacer, it is described
The rivet nut of plastic staple bolt is equipped with rounded tabs, is equipped with overhead structure in baffle side, is equipped in the rivet nut of the baffle other side
Multiple coaxial taper buckles, the diameter of the baffle are greater than the diameter of taper buckle, and the rivet nut between adjacent conical buckle is formed
Annular slot, the plastic spacer are equipped with the flexible hole with extension notch；2) sound insulation is laid on the inside of the covering of aircraft
Thermal insulation layer is equipped with the fixed connecting hole of acoustical and thermal layer on airframe；3) the overhead structure end of plastic staple bolt is passed through
The conic clamp end of thread of plastic staple bolt is passed through acoustical and thermal layer by the connecting hole of airframe, then by the flexible hole set of plastic spacer
It connects in the annular slot of the plastic staple bolt outside acoustical and thermal layer, with plastic spacer and plastic staple bolt by acoustical and thermal layer and aircraft
Body connection.
The plastic staple bolt can also be a two-way rivet nut structure, be again provided on the outside of overhead structure multiple coaxial
Taper buckle, have the acoustical and thermal layer in the two sides of aircraft body structure, on aircraft body structure be equipped with sound insulation
One end of the two-way plastic bail, is passed through the sound insulation of the connecting hole and connecting hole side by the fixed connecting hole of thermal insulation layer
Thermal insulation layer is socketed in the plastic staple bolt annular slot outside acoustical and thermal layer with the plastic spacer, then with two-way plastic card
The other end of nail passes through the acoustical and thermal layer of the connecting hole other side, then is socketed in outside the acoustical and thermal layer with a plastic spacer
In plastic staple bolt annular slot.
The beneficial effects of the present application are as follows: 1) plastic staple bolt carry barb, baffle and card slot locking structure, has installation fast
Prompt convenient advantage；2) on the housing construction frame or beam of aircraft the mounting hole of prefabricated acoustical and thermal layer can facilitate implementation to every
The installation of sound thermal insulation layer is fixed；3) it since plastic clip fourth is equipped with the different annular slot of multiple height, can fix not
The acoustical and thermal layer of stack pile.
Attached drawing is described in further detail the application with reference to embodiments.
Detailed description of the invention
Fig. 1 is that acoustical and thermal layer is fixed on schematic diagram in the stringer structure of airframe.
Fig. 2 is that acoustical and thermal layer is fixed on schematic diagram on the bulkhead structure of airframe.
Fig. 3 is two-way plastic bail structural schematic diagram.
Fig. 4 is unidirectional plastic clip fourth structural schematic diagram.
Fig. 5 is plastic spacer structural schematic diagram.
Explanation: 1 plastic staple bolt, 2 plastic spacers, 3 acoustical and thermal layers, 4 stringers, 5 coverings, 6 bulkheads, 7 tapers is numbered in figure
Buckle, 8 annular slots, 9 baffles, 10 overhead structures, 11 flexible holes.
Specific embodiment
Referring to attached drawing, aircraft acoustical and thermal layer installation method provided by the present application, containing plastic staple bolt 1 and plastic spacer 2,
The rivet nut of the plastic staple bolt 1 is equipped with rounded tabs 9, overhead structure 10 is equipped in 9 side of baffle, in 9 other side of baffle
Rivet nut be equipped with multiple coaxial tapers buckles 7, the diameter of the baffle 9 is greater than the diameter of taper buckle 7, adjacent conical buckle
Rivet nut between 7 forms annular slot 8, and the plastic spacer 2 is equipped with the flexible hole 11 with extension notch；In aircraft
It is laid with acoustical and thermal layer on the inside of covering 5, the fixed connecting hole of acoustical and thermal layer is equipped in the stringer 4 of airframe；3) will
The overhead structure end of plastic staple bolt 1 passes through the connecting hole in airframe stringer 4, and the taper of plastic staple bolt 1 is buckled 7 ends and is worn
Acoustical and thermal layer 3 is crossed, then the flexible hole 11 of plastic spacer 2 is socketed in the annular slot of 3 outside plastic staple bolt 1 of acoustical and thermal layer
In 8, acoustical and thermal layer 3 and the stringer of airframe are connected and fixed with plastic spacer 2 and plastic staple bolt 1.
Fixed acoustical and thermal layer 3, the plastic staple bolt 1 used can also be a two-way rivet nut knot at the bulkhead 6 of covering 5
Structure is again provided with multiple coaxial taper buckles 7 on the outside of overhead structure 10, has in the two sides of aircraft body structure bulkhead 6
The acoustical and thermal layer 3 is equipped with the fixed connecting hole of acoustical and thermal layer 3, by institute equally in 6 structure of airframe bulkhead
The one end for the two-way plastic bail stated passes through the acoustical and thermal layer 3 of the connecting hole and connecting hole side, with the plastic spacer 2
It is socketed in the plastic staple bolt annular slot 8 outside acoustical and thermal layer 3, then another across connecting hole with the other end of two-way plastic bail
The acoustical and thermal layer 3 of side, then the plastic staple bolt annular slot 8 outside the acoustical and thermal layer 3 is socketed in another plastic spacer 2
It is interior.
Claims (2)
1. a kind of aircraft acoustical and thermal layer installation method, which is characterized in that 1) contain plastic staple bolt and plastic spacer, the modeling
Expect that the rivet nut of bail is equipped with rounded tabs, is equipped with overhead structure in baffle side, is equipped in the rivet nut of the baffle other side more
A coaxial taper buckle, the diameter of the baffle are greater than the diameter of taper buckle, and the rivet nut between adjacent conical buckle forms ring
Shape card slot, the plastic spacer are equipped with the flexible hole with extension notch；2) on the inside of the covering of aircraft be laid with sound insulation every
Thermosphere is equipped with the fixed connecting hole of acoustical and thermal layer on airframe；3) the overhead structure end of plastic staple bolt is passed through and is flown
The conic clamp end of thread of plastic staple bolt is passed through acoustical and thermal layer, then the flexible hole of plastic spacer is socketed by the connecting hole of machine body
In the annular slot of the plastic staple bolt outside acoustical and thermal layer, with plastic spacer and plastic staple bolt by acoustical and thermal layer and aircraft machine
Body connection.
2. aircraft acoustical and thermal layer installation method as described in claim 1, which is characterized in that the plastic staple bolt is one
Two-way rivet nut structure is again provided with multiple coaxial taper buckles on the outside of overhead structure, equal in the two sides of aircraft body structure
There is the acoustical and thermal layer, the fixed connecting hole of acoustical and thermal layer is equipped on aircraft body structure, it will be described two-way
One end of plastic staple bolt passes through the acoustical and thermal layer of the connecting hole and connecting hole side, is socketed in sound insulation with the plastic spacer
In plastic staple bolt annular slot outside thermal insulation layer, then with the other end of two-way plastic bail pass through the sound insulation of the connecting hole other side every
Thermosphere, then be socketed in the plastic staple bolt annular slot outside the acoustical and thermal layer with a plastic spacer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811306335.0A CN109649635A (en) | 2018-11-02 | 2018-11-02 | A kind of aircraft acoustical and thermal layer installation method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811306335.0A CN109649635A (en) | 2018-11-02 | 2018-11-02 | A kind of aircraft acoustical and thermal layer installation method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109649635A true CN109649635A (en) | 2019-04-19 |
Family
ID=66110023
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811306335.0A Pending CN109649635A (en) | 2018-11-02 | 2018-11-02 | A kind of aircraft acoustical and thermal layer installation method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109649635A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP4289724A1 (en) * | 2022-06-09 | 2023-12-13 | SFS Group International AG | Component holder |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4208493A1 (en) * | 1992-03-17 | 1993-09-23 | Deutsche Aerospace Airbus | Retainer for fixture of insulating mat for heat insulation of aircraft cabin - is fixed to strip of hull and has holder pin connectable to insulating mat |
| CN101506036A (en) * | 2006-08-22 | 2009-08-12 | 空中客车德国有限公司 | Frame element, aircraft component assembly system and method of fitting a component in an aircraft |
| CN104169167A (en) * | 2012-01-10 | 2014-11-26 | 湾流航空航天公司 | Mounting assembly and method for mounting a sound-deadening body to a fuselage of an aircraft |
| CN104908924A (en) * | 2015-06-29 | 2015-09-16 | 中国商用飞机有限责任公司 | Fastener and method for mounting thermal-insulation and sound-insulation layer by virtue of fastener |
| CN106132822A (en) * | 2014-03-27 | 2016-11-16 | C&D佐迪阿克公司 | Closure system |
-
2018
- 2018-11-02 CN CN201811306335.0A patent/CN109649635A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4208493A1 (en) * | 1992-03-17 | 1993-09-23 | Deutsche Aerospace Airbus | Retainer for fixture of insulating mat for heat insulation of aircraft cabin - is fixed to strip of hull and has holder pin connectable to insulating mat |
| CN101506036A (en) * | 2006-08-22 | 2009-08-12 | 空中客车德国有限公司 | Frame element, aircraft component assembly system and method of fitting a component in an aircraft |
| CN104169167A (en) * | 2012-01-10 | 2014-11-26 | 湾流航空航天公司 | Mounting assembly and method for mounting a sound-deadening body to a fuselage of an aircraft |
| CN106132822A (en) * | 2014-03-27 | 2016-11-16 | C&D佐迪阿克公司 | Closure system |
| CN104908924A (en) * | 2015-06-29 | 2015-09-16 | 中国商用飞机有限责任公司 | Fastener and method for mounting thermal-insulation and sound-insulation layer by virtue of fastener |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP4289724A1 (en) * | 2022-06-09 | 2023-12-13 | SFS Group International AG | Component holder |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20190419 |