CN106314758B - A kind of end cap thermal resistance attachment device - Google Patents
A kind of end cap thermal resistance attachment device Download PDFInfo
- Publication number
- CN106314758B CN106314758B CN201610863502.6A CN201610863502A CN106314758B CN 106314758 B CN106314758 B CN 106314758B CN 201610863502 A CN201610863502 A CN 201610863502A CN 106314758 B CN106314758 B CN 106314758B
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- China
- Prior art keywords
- end cap
- pinboard
- metal shell
- sealing ring
- front deck
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- 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
Abstract
The invention discloses a kind of end cap resistive thermal devices, it includes end cap, first pinboard, second pinboard, first sealing ring and the second sealing ring, the tapered tubular of end cap, its big end is provided with mounting flange face and seal groove, second sealing ring is mounted in end cap seal groove, and the second sealing ring is tightly attached to the endface of the anti-thermal insulation layer of front deck metal shell Surface mulch simultaneously, end cap step surface is provided on the end face of end cap big end, the step surface that the endface of the end cap step surface and anti-thermal insulation layer is arranged fits, end cap is fixedly connected by mounting flange face with the first pinboard, second pinboard is fixed at front deck metal shell head end, first pinboard and the second pinboard are affixed, seal groove is provided at front deck metal shell head end, first sealing ring is installed in the seal groove.Apparatus of the present invention can effectively prevent the heat transfer to bay section, guarantee cabin temperature in anti-Design on thermal insulation claimed range.
Description
Technical field
The invention belongs to the anti-heat insulation structural design fields of aircraft bay section, are related to a kind of for aircraft end cap and bay section
Between anti-heat-proof device.
Background technique
During aircraft supersonic flight, the heating of end cap partial pneumatic is serious, need to carried out at this structure it is anti-every
Thermal design.Meanwhile the high temperature on end cap can also be transmitted into cabin, harsh thermal environment will affect or destroy in cabin single machine and
Equipment.Specifically, high temperature can be passed to bay section metal by heat transfer if end cap shell is directly contacted with bay section metal shell
Enclosure interior causes stand-alone device in metal shell strength failure or cabin to destroy.
For this reason, it is necessary to design a kind of end cap thermal resistance attachment device, it is connect meeting end cap with bay section metal shell
While, prevent the high temperature in end cap from conducting into bay section metal shell and cabin.
Summary of the invention
Aiming at the above defects or improvement requirements of the prior art, the present invention provides a kind of end cap thermal resistance attachment device,
Its object is to which end the rear part cabin heat transfer is effectively reduced by resistive thermal device, guarantee that the temperature at resistive thermal device reduces
It connect, is conducted so as to avoid high temperature into bay section metal shell and cabin, energy of the present invention to after OK range, then with front deck shell
The heat transfer to bay section is effectively reduced, guarantees cabin temperature within the scope of design requirement.
To achieve the above object, according to one aspect of the present invention, a kind of end cap resistive thermal device is provided, the device is whole
Surface mulch, which is arranged in, in body has at the front deck metal shell head end of anti-thermal insulation layer comprising end cap, the first pinboard,
Two pinboards, the first sealing ring and the second sealing ring,
The end cap material is heat-resisting material, and tapered tubular is provided with mounting flange face in its big end, at this
The endface of big end is provided with seal groove, and the second sealing ring is mounted in the seal groove, and second sealing ring is tight simultaneously
It is attached to the endface of the anti-thermal insulation layer of front deck metal shell Surface mulch, close to end cap outer wall on the end face of end cap big end
Place is provided with end cap step surface, and the step surface of the endface setting of the end cap step surface and anti-thermal insulation layer fits,
The end cap is fixedly connected by mounting flange face with first pinboard, is arranged on first pinboard
Multiple boss,
Second pinboard is fixed at front deck metal shell head end, is also equipped on second pinboard more
A boss with mounting hole, first pinboard and second pinboard are by respective boss face paste and and use standard
Part is fixedly connected,
It is provided with seal groove at the front deck metal shell head end, the first sealing ring, institute are installed in the seal groove
The boss that itself is higher by the outer ring of the first pinboard is stated, the outer ring of first pinboard can be made to compress first sealing
Circle.
By the above inventive concept and demand, end cap thermal resistance attachment device is designed, passes through the switching of two pinboards,
Avoid the direct heat transfer between end cap and metal shell.Meanwhile using step surface fitting step surface to form " L " type labyrinth
Structure, and combine the first sealing ring, the second sealing ring point sealing, can effectively prevent out of my cabin Aerodynamic Heating high temperature conducted into cabin.
Further, the end cap material is that tungsten seeps copper.
Further, mounting flange face is provided at the front deck metal shell inner wall, before second pinboard passes through
The mounting flange face being arranged at the metal shell inner wall of cabin is fixed at front deck metal shell head end.
Further, after the step surface that the endface of the end cap step surface and anti-thermal insulation layer is arranged fits, two
Gap is formed between step surface, the width in the gap is 1.0mm, and end cap is being avoided directly to contact reduction heat with the anti-thermal insulation layer of front deck
Conduction simultaneously, coordinates thermal stress deformation between the two.
In general, through the invention it is contemplated above technical scheme is compared with the prior art, it is following by that can obtain
The utility model has the advantages that
1, the present invention passes through the switching of two pinboards, avoids the direct heat transfer between end cap and metal shell, has
Effect avoids metal shell temperature is excessively high stand-alone device in strength failure and cabin is caused to destroy.
2, the thermal resistance connection structure material is common, and structure is simple, and design and installation are convenient, and good heat-insulation effect can be used for flying
In the anti-heat insulation structural design of row device, there is higher use value.
Detailed description of the invention
Fig. 1 is a kind of structural schematic diagram of end cap thermal resistance attachment device in the embodiment of the present invention；
Fig. 2 is L-type labyrinth seal structure schematic diagram in the end cap thermal resistance attachment device of the embodiment of the present invention；
Fig. 3 is end cap structural schematic diagram of the present invention, and the first pinboard, seal groove installation are equipped on mounting flange face
There is the second sealing ring；
Fig. 4 (a), Fig. 4 (b) they are the first pinboard and the second adapter plate structure schematic diagram of the embodiment of the present invention respectively, the
One pinboard is connected by plain bolt with end cap, and outer ring is higher by compressible first sealing ring of circular bosses, the second pinboard
It is connect with front deck metal shell, is contacted between pinboard using multiple circular bosses upper surfaces, connected with screw.
Fig. 5 is the front deck metal shell front end face of the embodiment of the present invention, and ring flange is connect with the second pinboard, seal groove
The first sealing ring of interior installation.
In all the appended drawings, identical appended drawing reference is used to denote the same element or structure, in which:
1 is end cap, and 2 be the first pinboard, and 3 be the second switching, and 4 be front deck metal shell, and 5 be anti-thermal insulation layer, and 6 be the
One sealing ring, 7 be the second sealing ring.
Specific embodiment
In order to make the objectives, technical solutions, and advantages of the present invention clearer, with reference to the accompanying drawings and embodiments, right
The present invention is further elaborated.It should be appreciated that the specific embodiments described herein are merely illustrative of the present invention, and
It is not used in the restriction present invention.As long as in addition, technical characteristic involved in the various embodiments of the present invention described below
Not constituting a conflict with each other can be combined with each other.
End cap thermal resistance attachment device disclosed by the invention, including end cap, the first pinboard, the second pinboard, first
Sealing ring and the second sealing ring further include some necessary fasteners.End cap material is high temperature structural materials, typical material
If tungsten seeps copper, pneumatic thermogenetic high temperature when being mainly used for being resistant to aircraft supersonic flight.First pinboard and the second switching
Plate is for example steel, and the first pinboard is connect with end cap, and the second pinboard is connect with front deck metal shell front end frame, first
Pinboard is connect with the second pinboard, and design has for example gap 1.0mm between end cap and front deck metal shell, which has
Multi-pass bending is labyrinth seal structure, and the first sealing ring and the second sealing ring are mounted in maze-type structure gap, are used for
Preventing inside and outside cabin is heat-insulated.Front deck metal housing materials are metal material, and typical material is for example aluminium alloy.Aircraft supersonic speed flies
When row, the outer temperature of end cap is connected up to 1000 ° or more by the thermal resistance of pinboard, can be by the second pinboard and front deck metal
The temperature of housing junction is greatly lowered, so that meeting metal shell uses temperature requirement.
The end cap material is heat-resisting material, if tungsten seeps copper, for bearing high temperature when aircraft supersonic flight,
The metal housing materials are metal, and such as aluminium alloy is difficult to be resistant to high temperature, and high temperature be easy to cause single machine in strength failure and cabin
It destroys, there is anti-thermal insulation layer in outer surface.The switching plate material is general steel plate, wherein the first pinboard is connect with end cap,
Second pinboard is connect with metal shell, and the first pinboard is connect with the second pinboard, and connector is plain bolt standard component.
Have the gap 1mm between the end cap and front deck metal shell, the anti-thermal insulation layer in front deck outer surface, avoid end cap with
The conduction of metal shell direct contact heat, gap are L-type labyrinth structure, are set at end cap and front deck metal shell or anti-thermal insulation layer
Be equipped with the first sealing ring, the second sealing ring, for prevent out of my cabin Aerodynamic Heating high temperature conducted into cabin.
When aircraft supersonic flight, pneumatic thermal environment is harsh, and the end cap is subjected to 1000 ° or so high temperature.And it is golden
Category shell energy bearing temperature is lower, and aluminum alloy materials are about 200 ° or less.When end cap is connect with bay section metal shell, need effective
High temperature heat transfer is reduced, avoids metal shell temperature beyond its use scope, guarantees that air themperature is used in stand-alone device in cabin
In temperature range.
Fig. 1 is that a kind of structural schematic diagram of end cap thermal resistance attachment device, Fig. 2 are implementation of the present invention in the embodiment of the present invention
L-type labyrinth seal structure schematic diagram in the end cap thermal resistance attachment device of example；Fig. 3 is end cap structural schematic diagram of the present invention,
First pinboard is installed, seal groove is equipped with the second sealing ring on its mounting flange face；Fig. 4 (a), Fig. 4 (b) are this hair respectively
First pinboard of bright embodiment and the second adapter plate structure schematic diagram, before Fig. 5 is the front deck metal shell of the embodiment of the present invention
End structure illustration.
By above more figures it is found that the device is integrally provided in 4 head of front deck metal shell that Surface mulch has anti-thermal insulation layer 5
Endface comprising end cap 1, the first pinboard 2, the second pinboard 3, the first sealing ring 6 and the second sealing ring 7, wherein
1 material of end cap is heat-resisting material, and tapered tubular is provided with mounting flange face (in the inner wall of big end in its big end
Place), it is provided with seal groove in the endface of the big end, the second sealing ring 7 is mounted in the seal groove, and second sealing
Circle 7 is tightly attached to the endface of the anti-thermal insulation layer 5 of 4 Surface mulch of front deck metal shell simultaneously, leans on the end face of 1 big end of end cap
End cap step surface, the step of the endface setting of the end cap step surface and anti-thermal insulation layer 5 are provided at the head cap outer wall of proximal end
Face fits, and the end cap 1 is fixedly connected by mounting flange face with first pinboard 2, on first pinboard 2
Provided with multiple boss.Mounting flange face is provided at 4 inner wall of front deck metal shell, second pinboard 3 passes through front deck gold
Belong to the mounting flange face being arranged at 4 inner wall of shell to be fixed at 4 head end of front deck metal shell.On second pinboard 3
Multiple boss are also equipped with, have mounting hole, first pinboard 2 and second pinboard 1 to pass through on boss respective convex
The standard components such as platform screw are fixedly connected, and are provided with seal groove at 4 head end of front deck metal shell, peace in the seal groove
Equipped with the first sealing ring 6, the boss of itself is higher by the outer ring of first pinboard 2, first pinboard 2 can be made
Outer ring compresses first sealing ring 6.
A in one embodiment of the invention, 1 material of end cap is for example that tungsten seeps copper.The end cap step surface and anti-
After the step surface of the endface setting of thermal insulation layer 5 fits, gap is formed between two step surfaces, the thickness in the gap is for example
1.0mm。
In the present invention, the anti-thermal insulation layer 5 is mounted on front deck metal shell outer surface 4, for front deck prevent it is heat-insulated.End
1 rear end face of cap and front deck metal shell 4,5 front end face of anti-thermal insulation layer have 1mm labyrinth gap, to avoid end cap 1 and metal
Direct contact heat conduction between shell 4, anti-thermal insulation layer 5, coordinates thermal stress deformation, while salable.
In the present invention, the first sealing ring is for example quartz fibre casing, is mounted on end cap 1 and the anti-thermal insulation layer 5 of front deck
Between gap, for heat-insulated.Second sealing ring 7 is for example silicon rubber, heat-insulated for the second inside and outside cabin.Meanwhile by end
At L-shaped maze-type structure is designed in cap 1 and anti-5 gap of thermal insulation layer of front deck, to reduce conduction of the high temperature into cabin out of my cabin.
As an improvement of the present invention, the different material of heat resistance can be used in two switching plate materials, such as the first pinboard
Heat resistance is stronger than the second pinboard, such design, so that heat-conductive characteristic is variant, formation temperature gradient, to improve
Thermal resistance effect.
According to aircraft flight operating condition, in conjunction with aeroheating analysis, end cap during aircraft supersonic flight most
High-temperature is 1060 DEG C, and maximum temperature of the anti-thermal insulation layer in flight course is about 1700 DEG C outside front deck, after thermal resistance connects,
Local maximum temperature of the metal shell in flight course is less than 160 DEG C, and air themperature is able to satisfy less than 70 DEG C in front deck cabin
Stand-alone device requirement in the strength of materials and cabin prevents heat-insulated and connection purpose to reach.
As it will be easily appreciated by one skilled in the art that the foregoing is merely illustrative of the preferred embodiments of the present invention, not to
The limitation present invention, any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should all include
Within protection scope of the present invention.
Claims (4)
1. a kind of end cap resistive thermal device, which is characterized in that the device is integrally provided in front of Surface mulch has anti-thermal insulation layer (5)
At cabin metal shell (4) head end comprising end cap (1), the first pinboard (2), the second pinboard (3), the first sealing
Enclose (6) and the second sealing ring (7), wherein
End cap (1) material is heat-resisting material, and tapered tubular is provided with mounting flange on the inner wall of its big end
Face is provided with seal groove in the endface of the big end, and the second sealing ring (7) is mounted in the seal groove, and described second close
Seal (7) is tightly attached to the endface of the anti-thermal insulation layer (5) of front deck metal shell (4) Surface mulch simultaneously, in end cap (1) big end
End face on end cap step surface, the end face of the end cap step surface and anti-thermal insulation layer (5) are provided at the end cap outer wall
The step surface of place's setting fits,
The end cap (1) is fixedly connected by mounting flange face with first pinboard (2), first pinboard (2)
It is upper to be provided with multiple boss,
Second pinboard (3) is fixed at front deck metal shell (4) head end, also sets on second pinboard (3)
Multiple boss are equipped with, first pinboard (2) is fixedly connected with second pinboard (3) by respective boss,
It is provided with seal groove at front deck metal shell (4) head end, the first sealing ring (6) are installed in the seal groove,
The boss of itself is higher by the outer ring of first pinboard (2), can make described in the outer ring compression of first pinboard (2)
First sealing ring (6).
2. a kind of end cap resistive thermal device as described in claim 1, which is characterized in that end cap (1) material is tungsten infiltration
Copper.
3. a kind of end cap resistive thermal device as claimed in claim 1 or 2, which is characterized in that before the front deck metal shell (4)
There is mounting flange face at the inner wall of end face, second pinboard (3) passes through the installation at front deck metal shell (4) front end face inner wall
Flange face is fixed at front deck metal shell (4) head end.
4. a kind of end cap resistive thermal device as claimed in claim 1 or 2, which is characterized in that the end cap step surface and anti-
After the step surface of the endface setting of thermal insulation layer (5) fits, gap is formed between two step surfaces, the width in the gap is
1.0mm。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610863502.6A CN106314758B (en) | 2016-09-29 | 2016-09-29 | A kind of end cap thermal resistance attachment device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610863502.6A CN106314758B (en) | 2016-09-29 | 2016-09-29 | A kind of end cap thermal resistance attachment device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106314758A CN106314758A (en) | 2017-01-11 |
| CN106314758B true CN106314758B (en) | 2019-01-04 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610863502.6A Active CN106314758B (en) | 2016-09-29 | 2016-09-29 | A kind of end cap thermal resistance attachment device |
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| Country | Link |
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| CN (1) | CN106314758B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113086224B (en) * | 2021-03-17 | 2023-01-17 | 北京机电工程研究所 | Equipment fixing heat bridge restraines structure |
| CN113978696B (en) * | 2021-11-08 | 2024-04-09 | 湖北航天技术研究院总体设计所 | Spacecraft and thermal resistance type end cap mounting structure thereof |
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| DE102004011183A1 (en) * | 2004-03-08 | 2005-09-29 | Airbus Deutschland Gmbh | Aircraft electrical cable mount, has two sections made of plastic, and connecting unit supporting plate-shaped unit, where both units are made up of more heat resistant or fire-resistant material |
| US7584582B1 (en) * | 2006-02-14 | 2009-09-08 | Physical Systems, Inc. | Adhesive bonded attachment assembly for an insulation blanket |
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| CN202358306U (en) * | 2011-09-28 | 2012-08-01 | 湖北航天技术研究院总体设计所 | Thermal protection structure for tail segment of aircraft |
| CN202593852U (en) * | 2012-04-28 | 2012-12-12 | 湖北航天技术研究院总体设计所 | Connecting device for high-low temperature driving component |
| CN105083528A (en) * | 2015-09-07 | 2015-11-25 | 哈尔滨工业大学 | Thermal protection device |
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2016
- 2016-09-29 CN CN201610863502.6A patent/CN106314758B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102004011183A1 (en) * | 2004-03-08 | 2005-09-29 | Airbus Deutschland Gmbh | Aircraft electrical cable mount, has two sections made of plastic, and connecting unit supporting plate-shaped unit, where both units are made up of more heat resistant or fire-resistant material |
| US7584582B1 (en) * | 2006-02-14 | 2009-09-08 | Physical Systems, Inc. | Adhesive bonded attachment assembly for an insulation blanket |
| CN201566844U (en) * | 2009-11-10 | 2010-09-01 | 湖北航天技术研究院总体设计所 | Flexible connecting structure for optical dome |
| CN202130570U (en) * | 2011-05-16 | 2012-02-01 | 湖北航天技术研究院总体设计所 | Aircraft cowling shell |
| CN202358306U (en) * | 2011-09-28 | 2012-08-01 | 湖北航天技术研究院总体设计所 | Thermal protection structure for tail segment of aircraft |
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| Publication number | Publication date |
|---|---|
| CN106314758A (en) | 2017-01-11 |
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