CN106828871B - A kind of heat insulation structural - Google Patents
A kind of heat insulation structural Download PDFInfo
- Publication number
- CN106828871B CN106828871B CN201710128812.8A CN201710128812A CN106828871B CN 106828871 B CN106828871 B CN 106828871B CN 201710128812 A CN201710128812 A CN 201710128812A CN 106828871 B CN106828871 B CN 106828871B
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- CN
- China
- Prior art keywords
- fuselage
- ontology
- heat insulation
- bearing
- lug boss
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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.)
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Classifications
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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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Thermal Insulation (AREA)
Abstract
A kind of heat insulation structural, is arranged on the fuselage and shaft of aircraft, and heat insulation structural includes: ontology, it is with body through-holes, there is fuselage installation base and lug boss around body through-holes, ontology is mounted on fuselage by fuselage installation base, lug boss protrudes into the concave part on fuselage；Shaft is installed on ontology by multiple bearings by the bearing, and the end of shaft is located in the rotary shaft through hole of fuselage；Multiple bearing baffles are fixedly mounted on the body, mobile for limiting bearing between bearing and fuselage；Thermal insulation board is set in around the fuselage installation base of ontology, between ontology and fuselage；Heat insulation loop is set on the lug boss of ontology, between the lug boss of ontology and the concave part of fuselage.The present invention facilitates implementation, saves space, and aircraft machine inner structural member temperature rise rate can be effectively reduced in small space, guarantees the flutter allowance of aerofoil when structural member rigidity and high-speed flight.
Description
Technical field
The present invention relates to the anti-thermal technologies of Flight Vehicle Structure, and in particular to one kind is in aircraft fuselage small space using pre-
The heat insulation structural for staying gap, filling low thermal conductivity material.
Background technique
Aerodynamic loading and aerofoil bending load awing bear in the executing agency of aircraft.Hypersonic aircraft flight
Middle fuselage Aerodynamic Heating is harsh, and machine inner structural member quick heating drives the transmission mechanism Stiffness of aerofoil, reduces the gas of aerofoil
Dynamic flutter allowance.Therefore solar heat protection measure need to be taken, the temperature rise speed of fuselage inner structural member is reduced, so that aircraft is in flight course
Middle servo mechanism rigidity meets requirement.
Summary of the invention
The present invention provides a kind of heat insulation structural, facilitates implementation, saves space, aircraft can be effectively reduced in small space
Machine inner structural member temperature rise rate guarantees the flutter allowance of aerofoil when structural member rigidity and high-speed flight.
In order to achieve the above object, the present invention provides a kind of heat insulation structural, is arranged on the fuselage and shaft of aircraft,
There is concave part on fuselage, be provided with rotary shaft through hole among concave part, multiple mounting holes are provided on the fuselage around concave part
With multiple location holes, which includes:
Ontology has fuselage installation base and lug boss around body through-holes, is installed by fuselage with body through-holes
Ontology is mounted on fuselage by boss, and lug boss protrudes into the concave part on fuselage；
Shaft is installed on ontology by multiple bearings by the bearing, and the end of shaft is located in the rotary shaft through hole of fuselage；
Multiple bearing baffles are fixedly mounted on the body, mobile for limiting bearing between bearing and fuselage；
Thermal insulation board is set in around the fuselage installation base of ontology, between ontology and fuselage；
Heat insulation loop is set on the lug boss of ontology, between the lug boss of ontology and the concave part of fuselage.
The ontology also includes:
Multiple bearing baffle installation grooves are located on lug boss, for installing bearing baffle.
The ontology also includes:
Multiple mounting holes are arranged on fuselage installation base, and position is corresponding with the mounting hole on fuselage, for connecting
Fuselage；
Multiple location holes, position is corresponding with the location hole on fuselage, for connecting positioning.
The thermal insulation board also includes:
Through-hole, shape are matched with the fuselage installation base of ontology, make thermal insulation board just and can be set in fuselage installation convex
Around platform.
The thermal insulation board also includes:
Location hole, position is corresponding with the location hole on fuselage, for connecting positioning.
The heat insulation loop also includes:
Multiple grooves, position is corresponding with the bearing baffle installation groove on ontology, for installing bearing baffle.
The fuselage uses titanium alloy material, and ontology uses aluminum alloy materials, and shaft and bearing baffle use stainless steel
Material, thermal insulation board use the asbestos material of lower thermal conductivity, and heat insulation loop uses the vagcor steel of lower thermal conductivity high compression-strength.
The height of the bearing baffle is greater than bearing, makes between bearing and fuselage that there are gaps.
Positioning link passes through the location hole on ontology, the location hole on location hole and fuselage on thermal insulation board, realizes this
The installation of body and fuselage positions；Connector passes through the mounting hole on mounting hole and fuselage on ontology, and ontology and fuselage are fixed
Connection.
Bearing baffle is mounted in the bearing baffle installation groove of ontology by bearing baffle connector.
The present invention, by reduction structural member metal contact area, increases gap under the premise of no increase structure space,
Increase the measures such as asbestos insulation pad, the vagcor steel heat insulation loop of lower thermal conductivity, reduces the heat of fuselage to machine inner structural member
Conduction, slows down mechanism temperature rise rate, is a kind of heat insulation structural for facilitating implementation, space-saving, can effectively reduce aircraft machine
Inner structural member temperature rise rate guarantees the flutter allowance of aerofoil when structural member rigidity and high-speed flight.
Detailed description of the invention
Fig. 1 is the inside schematic diagram of airframe structure.
Fig. 2 is the outside schematic diagram of airframe structure.
Fig. 3 is a kind of schematic diagram of heat insulation structural provided by the invention.
Fig. 4 is a kind of cross section view of the heat insulation structural provided by the invention along shaft.
Fig. 5 is the structural schematic diagram of ontology.
Fig. 6 is the structural schematic diagram of thermal insulation board.
Fig. 7 is the structural schematic diagram of heat insulation loop.
Specific embodiment
Below according to FIG. 1 to FIG. 7, presently preferred embodiments of the present invention is illustrated.
The present invention provides a kind of heat insulation structural, is arranged on the fuselage and shaft of aircraft, realizes structural heat-insulation.Such as Fig. 1
With shown in Fig. 2, there is concave part 10-3 on fuselage 10, is provided with rotary shaft through hole 10-4, concave part 10-3 among concave part 10-3
Multiple mounting hole 10-2 and multiple location hole 10-1 are provided on the fuselage of surrounding.
As shown in Figure 3 and Figure 4, the heat insulation structural specifically includes:
Ontology 1 has fuselage installation base 101 and lug boss around body through-holes 106 with body through-holes 106
102, ontology 1 is mounted on fuselage 10 by fuselage installation base 101, lug boss 102 protrudes into the concave part 10- on fuselage 10
3；
Shaft 2 is installed on ontology 1 by multiple bearings 3 by the bearing 3, and the end of shaft 2 is located at the shaft of fuselage 10
In through-hole 10-4；
Multiple bearing baffles 4, are fixedly mounted on ontology 1, between bearing 2 and fuselage 10, for limiting bearing 2
It is mobile；
Thermal insulation board 6 is set in around the fuselage installation base 101 of ontology 1, between ontology 1 and fuselage 10；
Heat insulation loop 5 is set on the lug boss 102 of ontology 1, positioned at the lug boss 102 of ontology 1 and the groove of fuselage 10
Between portion 10-3.
As shown in figure 5, the ontology 1 also includes:
Multiple bearing baffle installation grooves 103 are located on lug boss 102, for installing bearing baffle 4；
Multiple mounting holes 105 are arranged on fuselage installation base 101, and position is opposite with the mounting hole 10-2 on fuselage
It answers, for connecting fuselage 10；
Multiple location holes 104, position is corresponding with the location hole 10-1 on fuselage 10, for connecting positioning.
As shown in fig. 6, the thermal insulation board 6 also includes:
Through-hole 601, shape are matched with the fuselage installation base 101 of ontology 1, make thermal insulation board 6 that can just be set in machine
Around body installation base 101；
Location hole 602, position is corresponding with the location hole 10-1 on fuselage 10, for connecting positioning.
As shown in fig. 7, the heat insulation loop 5 also includes:
Multiple grooves 501, position is corresponding with the bearing baffle installation groove 103 on ontology 1, for installing bearing rib
Plate 4.
As shown in Figure 3 and Figure 4, the location hole 104 on ontology 1, the positioning on thermal insulation board 6 are passed through using positioning link 9
Location hole 10-1 on hole 602 and fuselage 10 realizes that the installation of ontology 1 and fuselage 10 positions.Ontology 1 is passed through using connector 7
On mounting hole 105 and fuselage 10 on mounting hole 10-2, ontology 1 is fixedly connected with fuselage 10.It is connected using bearing baffle
Bearing baffle 4 is mounted in the bearing baffle installation groove 103 of ontology 1 by part 8.
To meet aircraft lightweight small form factor requirements, fuselage 10 is titanium alloy material, and ontology 1 uses aluminum alloy materials, is turned
Axis 2 and bearing baffle 4 use stainless steel material, and shaft 2 is installed on ontology 1 by bearing 3, and bearing baffle 4 is mounted on ontology
Bearing baffle installation groove 103 in, move, and contacted after installation with the inner wall of fuselage 10 outside limitation bearing 3, by shaft 2 and
The power moved outside bearing 3 is transferred on fuselage 10, uniformly distributed on bearing circumferencial direction using four bearing baffles 4 in the present embodiment,
Making there are gap between 10 inner wall of bearing 3 and fuselage, the contact area of reduction bearing 3 and fuselage 10 slows down bearing temperature rise speed,
The height of bearing baffle 4 is greater than bearing 3 simultaneously, makes between bearing 3 and fuselage 10 to reduce contact of the bearing with fuselage there are gap
Area reduces the heat that fuselage is transferred to bearing, reduces bearing temperature rise speed.
There are two contact surfaces, first is plane for ontology 1 and fuselage 10, and to support shaft 2, second is fuselage 10
Concave part 10-3 and ontology 1 the anchor ring that is formed of lug boss 102, to by the moment of flexure load transitions of shaft 2 to ontology 1 and machine
Body 10 is equipped with thermal insulation board 6 on flat contact surface, and heat insulation loop 5 is equipped on annular face contacts face, then ontology 1 and fuselage 10
Only there are direct metal contacts at fuselage installation base 101, substantially reduce the contact area of ontology 1 and fuselage 10, contracting
Small heat transfer pathway of the fuselage 10 to ontology 1, while thermal insulation board 6 made of the asbestos material of lower thermal conductivity reduces ontology 1
With the metal contact area between fuselage 10, and heat insulation loop 5 made of the vagcor steel of lower thermal conductivity high compression-strength
The heat for avoiding fuselage 10 is transferred directly to ontology 1.
The present invention, by reduction structural member metal contact area, increases gap under the premise of no increase structure space,
Increase the measures such as asbestos insulation pad, the vagcor steel heat insulation loop of lower thermal conductivity, reduces the heat of fuselage to machine inner structural member
Conduction, slows down mechanism temperature rise rate, is a kind of heat insulation structural for facilitating implementation, space-saving, can effectively reduce aircraft machine
Inner structural member temperature rise rate guarantees the flutter allowance of aerofoil when structural member rigidity and high-speed flight.
It is discussed in detail although the contents of the present invention have passed through above preferred embodiment, but it should be appreciated that above-mentioned
Description is not considered as limitation of the present invention.After those skilled in the art have read above content, for of the invention
A variety of modifications and substitutions all will be apparent.Therefore, protection scope of the present invention should be limited to the appended claims.
Claims (10)
1. a kind of heat insulation structural, is arranged on the fuselage and shaft of aircraft, there is concave part on fuselage, set among concave part
It is equipped with rotary shaft through hole, multiple mounting holes and multiple location holes are provided on the fuselage around concave part, which is characterized in that this is heat-insulated
Structure includes:
Ontology has fuselage installation base and lug boss around body through-holes, passes through fuselage installation base with body through-holes
Ontology is mounted on fuselage, lug boss protrudes into the concave part on fuselage；
Shaft is installed on ontology by multiple bearings by the bearing, and the end of shaft is located in the rotary shaft through hole of fuselage；
Multiple bearing baffles are fixedly mounted on the body, mobile for limiting bearing between bearing and fuselage；
Thermal insulation board is set in around the fuselage installation base of ontology, between ontology and fuselage；
Heat insulation loop is set on the lug boss of ontology, between the lug boss of ontology and the concave part of fuselage.
2. heat insulation structural as described in claim 1, which is characterized in that the ontology also includes:
Multiple bearing baffle installation grooves are located on lug boss, for installing bearing baffle.
3. heat insulation structural as claimed in claim 2, which is characterized in that the ontology also includes:
Multiple mounting holes are arranged on fuselage installation base, and position is corresponding with the mounting hole on fuselage, for connecting machine
Body；
Multiple location holes, position is corresponding with the location hole on fuselage, for connecting positioning.
4. heat insulation structural as claimed in claim 3, which is characterized in that the thermal insulation board also includes:
Through-hole, shape are matched with the fuselage installation base of ontology, and fuselage installation base week can be set in by making thermal insulation board just
It encloses.
5. heat insulation structural as claimed in claim 4, which is characterized in that the thermal insulation board also includes:
Location hole, position is corresponding with the location hole on fuselage, for connecting positioning.
6. heat insulation structural as claimed in claim 2, which is characterized in that the heat insulation loop also includes:
Multiple grooves, position is corresponding with the bearing baffle installation groove on ontology, for installing bearing baffle.
7. heat insulation structural as described in claim 1, which is characterized in that the fuselage uses titanium alloy material, and ontology uses
Aluminum alloy materials, shaft and bearing baffle use stainless steel material, and thermal insulation board uses the asbestos material of lower thermal conductivity, and heat insulation loop is adopted
With the vagcor steel of lower thermal conductivity high compression-strength.
8. heat insulation structural as described in claim 1, which is characterized in that the height of the bearing baffle is greater than bearing, makes axis
Hold between fuselage that there are gaps.
9. heat insulation structural as claimed in claim 5, which is characterized in that positioning link passes through the location hole, heat-insulated on ontology
The location hole on location hole and fuselage on plate realizes that the installation of ontology (1) and fuselage positions；Connector passes through the peace on ontology
The mounting hole on hole and fuselage is filled, ontology is fixedly connected with fuselage.
10. heat insulation structural as claimed in claim 2, which is characterized in that bearing baffle is mounted on this by bearing baffle connector
In the bearing baffle installation groove of body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710128812.8A CN106828871B (en) | 2017-03-06 | 2017-03-06 | A kind of heat insulation structural |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710128812.8A CN106828871B (en) | 2017-03-06 | 2017-03-06 | A kind of heat insulation structural |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106828871A CN106828871A (en) | 2017-06-13 |
| CN106828871B true CN106828871B (en) | 2019-07-26 |
Family
ID=59138788
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710128812.8A Active CN106828871B (en) | 2017-03-06 | 2017-03-06 | A kind of heat insulation structural |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106828871B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114275145B (en) * | 2021-12-30 | 2023-10-20 | 湖北三江航天红阳机电有限公司 | Hot air flow blocking structure |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4826417B2 (en) * | 2006-09-29 | 2011-11-30 | 株式会社ジェイテクト | Supercharger |
| CN101571194A (en) * | 2009-06-02 | 2009-11-04 | 上海师范大学 | Shaft hole heat insulation sealing device |
| CN201488930U (en) * | 2009-08-13 | 2010-05-26 | 上海诺甲仪器仪表有限公司 | Low-heat transmission spindle of mooney viscometer rotor |
| US9988977B2 (en) * | 2014-10-14 | 2018-06-05 | Borgwarner Inc. | Heat shield with centering features |
-
2017
- 2017-03-06 CN CN201710128812.8A patent/CN106828871B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN106828871A (en) | 2017-06-13 |
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