CN106828871A - A kind of heat insulation structural - Google Patents
A kind of heat insulation structural Download PDFInfo
- Publication number
- CN106828871A CN106828871A CN201710128812.8A CN201710128812A CN106828871A CN 106828871 A CN106828871 A CN 106828871A CN 201710128812 A CN201710128812 A CN 201710128812A CN 106828871 A CN106828871 A CN 106828871A
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- CN
- China
- Prior art keywords
- fuselage
- heat insulation
- bearing
- rotating shaft
- installation base
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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)
- Thermal Insulation (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
A kind of heat insulation structural, is arranged on the fuselage and rotating shaft of aircraft, and heat insulation structural is included：Body, it has body through-holes, has fuselage installation base and lug boss around body through-holes, and body is arranged on fuselage by fuselage installation base, and lug boss stretches into the concave part on fuselage；, be installed on body for rotating shaft by the bearing by multiple bearings, and the end of rotating shaft is located in the rotating shaft through hole of fuselage；Multiple bearing baffles, it is fixedly mounted on body, between bearing and fuselage, for limiting bearing movement；Thermal insulation board, it is set in around the fuselage installation base of body, between body and fuselage；Heat insulation loop, it is set on the lug boss of body, between the lug boss of body and the concave part of fuselage.The present invention is convenient to be implemented, saves space, aircraft machine inner structural member temperature rise rate can be effectively reduced in small space, it is ensured that the flutter allowance of aerofoil when structural member rigidity and high-speed flight.
Description
Technical field
The present invention relates to the anti-thermal technology of Flight Vehicle Structure, and in particular to one kind is in aircraft fuselage small space using pre-
Stay gap, the heat insulation structural of filling low thermal conductivity material.
Background technology
Aerodynamic loading and aerofoil bending load are awing born by the executing agency of aircraft.Hypersonic aircraft flies
Middle fuselage Aerodynamic Heating is harsh, 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 control mechanism rigidity meets use requirement.
The content of the invention
The present invention provides a kind of heat insulation structural, convenient to implement, save space, effectively can reduce aircraft in small space
Machine inner structural member temperature rise rate, it is ensured that 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, and it is arranged on the fuselage and rotating shaft of aircraft,
There is concave part, concave part middle setting has rotating shaft through hole, multiple mounting holes are provided with the fuselage around concave part on fuselage
With multiple location holes, the heat insulation structural includes：
Body, it has body through-holes, has fuselage installation base and lug boss around body through-holes, by fuselage installation base
Body is arranged on fuselage, lug boss stretches into the concave part on fuselage；
, be installed on body for rotating shaft by the bearing by multiple bearings, and the end of rotating shaft is located in the rotating shaft through hole of fuselage；
Multiple bearing baffles, it is fixedly mounted on body, between bearing and fuselage, for limiting bearing movement；
Thermal insulation board, it is set in around the fuselage installation base of body, between body and fuselage；
Heat insulation loop, it is set on the lug boss of body, between the lug boss of body and the concave part of fuselage.
Described body is also included：
Multiple bearing baffles install groove, and it is located on lug boss, for installing bearing baffle.
Described body is also included：
Multiple mounting holes, it is arranged on fuselage installation base, and position is corresponding with the mounting hole on fuselage, for connecting machine
Body；
Multiple location holes, its position is corresponding with the location hole on fuselage, is positioned for connecting.
Described thermal insulation board is also included：
Through hole, its shape is matched with the fuselage installation base of body, thermal insulation board is just set in fuselage installation base week
Enclose.
Described thermal insulation board is also included：
Location hole, its position is corresponding with the location hole on fuselage, is positioned for connecting.
Described heat insulation loop is also included：
Multiple grooves, its position is corresponding with the bearing baffle installation groove on body, for installing bearing baffle.
Described fuselage uses titanium alloy material, body to use aluminum alloy materials, rotating shaft and bearing baffle to use stainless steel
Material, thermal insulation board uses 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 described bearing baffle is more than bearing, makes the presence of gap between bearing and fuselage.
Positioning link realizes this through location hole, the location hole on location hole and fuselage on thermal insulation board on body
Body is positioned with the installation of fuselage；Connector fixes body and fuselage through the mounting hole on the mounting hole and fuselage on body
Connection.
Bearing baffle is arranged on the bearing baffle of body and installed in groove by bearing baffle connector.
The present invention, by reducing structural member metal contact area, increases gap on the premise of without structure space is increased,
Increase the measures such as asbestos insulation pad, the vagcor steel heat insulation loop of lower thermal conductivity, reduce the heat of fuselage to machine inner structural member
Conduction, slow down mechanism's temperature rise rate, be a kind of convenient implementation, the heat insulation structural of space-saving, can effectively reduce aircraft machine
Inner structural member temperature rise rate, it is ensured that the flutter allowance of aerofoil when structural member rigidity and high-speed flight.
Brief description of the drawings
Fig. 1 is the inner side 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 that the present invention is provided.
Fig. 4 is a kind of heat insulation structural of present invention offer along the cross section view of rotating shaft.
Fig. 5 is the structural representation of body.
Fig. 6 is the structural representation of thermal insulation board.
Fig. 7 is the structural representation of heat insulation loop.
Specific embodiment
Below according to Fig. 1~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 rotating 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, concave part 10-3 middle settings have rotating shaft through hole 10-4, concave part 10-3
Multiple mounting hole 10-2 and multiple location hole 10-1 are provided with the fuselage of surrounding.
As shown in Figure 3 and Figure 4, described heat insulation structural is specifically included：
Body 1, it has body through-holes 106, has fuselage installation base 101 and lug boss 102 around body through-holes 106, leads to
Cross fuselage installation base 101 body 1 is arranged on fuselage 10, lug boss 102 stretches into the concave part 10-3 on fuselage 10；
, be installed on body 1 for rotating shaft 2 by the bearing 3 by multiple bearings 3, and the end of rotating shaft 2 is located at the rotating shaft through hole of fuselage 10
In 10-4；
Multiple bearing baffles 4, it is fixedly mounted on body 1, between bearing 2 and fuselage 10, is moved for limiting bearing 2
It is dynamic；
Thermal insulation board 6, it is set in around the fuselage installation base 101 of body 1, between body 1 and fuselage 10；
Heat insulation loop 5, it is set on the lug boss 102 of body 1, positioned at the lug boss 102 and the concave part of fuselage 10 of body 1
Between 10-3.
As shown in figure 5, described body 1 is also included：
Multiple bearing baffles install groove 103, and it is located on lug boss 102, for installing bearing baffle 4；
Multiple mounting holes 105, it is arranged on fuselage installation base 101, and position is corresponding with the mounting hole 10-2 on fuselage, is used
In connection fuselage 10；
Multiple location holes 104, its position is corresponding with the location hole 10-1 on fuselage 10, is positioned for connecting.
As shown in fig. 6, described thermal insulation board 6 is also included：
Through hole 601, its shape is matched with the fuselage installation base 101 of body 1, thermal insulation board 6 is just set in fuselage and is pacified
Around dress boss 101；
Location hole 602, its position is corresponding with the location hole 10-1 on fuselage 10, is positioned for connecting.
As shown in fig. 7, described heat insulation loop 5 is also included：
Multiple grooves 501, its position is corresponding with the bearing baffle installation groove 103 on body 1, for installing bearing baffle 4.
As shown in Figure 3 and Figure 4, positioning link 9 through location hole 104, the positioning on thermal insulation board 6 on body 1 is used
Location hole 10-1 on hole 602 and fuselage 10, realizes that body 1 is positioned with the installation of fuselage 10.Body 1 is passed through using connector 7
On mounting hole 105 and fuselage 10 on mounting hole 10-2, body 1 is fixedly connected with fuselage 10.Connected using bearing baffle
Bearing baffle 4 is arranged on the bearing baffle of body 1 and installed in groove 103 by part 8.
To meet aircraft lightweight small form factor requirements, fuselage 10 is titanium alloy material, and body 1 uses aluminum alloy materials, is turned
Axle 2 and bearing baffle 4 use stainless steel material, and rotating shaft 2 is installed on body 1 by bearing 3, and bearing baffle 4 is arranged on body
Bearing baffle install in groove 103, limitation bearing 3 is outer to be moved, and is contacted in the inwall after installation with fuselage 10, by rotating shaft 2 and
The outer power moved of bearing 3 is transferred on fuselage 10, uniform on bearing circumferencial direction using four bearing baffles 4 in the present embodiment,
Make the presence of gap between bearing 3 and the inwall of fuselage 10, reduce the contact area of bearing 3 and fuselage 10, slow down bearing temperature rise speed,
The height of bearing baffle 4 is more than bearing 3 simultaneously, makes the presence of gap between bearing 3 and fuselage 10, reduces contact of the bearing with fuselage
Area, reduces the heat that fuselage is transferred to bearing, reduces bearing temperature rise speed.
There are two contact surfaces in body 1, first is plane with fuselage 10, be used to support rotating shaft 2, and second is fuselage 10
Concave part 10-3 and body 1 lug boss 102 formed anchor ring, be used to the moment of flexure load transitions of rotating shaft 2 to body 1 and machine
Body 10, is provided with thermal insulation board 6 on flat contact surface, and heat insulation loop 5 is provided with annular face contacts face, then body 1 and fuselage 10
Only there is direct metal contact at fuselage installation base 101, substantially reduce the contact area of body 1 and fuselage 10, contract
Small heat transfer pathway of the fuselage 10 to body 1, while the thermal insulation board 6 that the asbestos material of lower thermal conductivity is made reduces body 1
With the metal contact area between fuselage 10, and the heat insulation loop 5 that the vagcor steel of lower thermal conductivity high compression-strength is made
The heat for avoiding fuselage 10 is transferred directly to body 1.
The present invention, by reducing structural member metal contact area, increases gap on the premise of without structure space is increased,
Increase the measures such as asbestos insulation pad, the vagcor steel heat insulation loop of lower thermal conductivity, reduce the heat of fuselage to machine inner structural member
Conduction, slow down mechanism's temperature rise rate, be a kind of convenient implementation, the heat insulation structural of space-saving, can effectively reduce aircraft machine
Inner structural member temperature rise rate, it is ensured that the flutter allowance of aerofoil when structural member rigidity and high-speed flight.
Although present disclosure is discussed in detail by 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 the above, for of the invention
Various 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, it is arranged on the fuselage and rotating shaft of aircraft, fuselage（10）It is upper that there is concave part（10-3）, it is recessed
Groove portion（10-3）Middle setting has rotating shaft through hole（10-4）, concave part（10-3）Multiple mounting holes are provided with the fuselage of surrounding
（10-2）With multiple location holes（10-1）, it is characterised in that the heat insulation structural is included：
Body（1）, it has body through-holes（106）, body through-holes（106）Surrounding has fuselage installation base（101）And projection
Portion（102）, by fuselage installation base（101）By body（1）Installed in fuselage（10）On, lug boss（102）Stretch into fuselage
（10）On concave part（10-3）；
Multiple bearings（3）, by the bearing（3）By rotating shaft（2）It is installed to body（1）On, rotating shaft（2）End be located at fuselage
（10）Rotating shaft through hole（10-4）In；
Multiple bearing baffles（4）, it is fixedly mounted on body（1）On, positioned at bearing（2）And fuselage（10）Between, for limiting
Bearing（2）It is mobile；
Thermal insulation board（6）, it is set in body（1）Fuselage installation base（101）Around, positioned at body（1）And fuselage（10）It
Between；
Heat insulation loop（5）, it is set in body（1）Lug boss（102）On, positioned at body（1）Lug boss（102）And fuselage
（10）Concave part（10-3）Between.
2. heat insulation structural as claimed in claim 1, it is characterised in that described body（1）Also include：
Multiple bearing baffles install groove（103）, it is located at lug boss（102）On, for installing bearing baffle（4）.
3. heat insulation structural as claimed in claim 2, it is characterised in that described body（1）Also include：
Multiple mounting holes（105）, it is arranged on fuselage installation base（101）On, the mounting hole on position and fuselage（10-2）Phase
Correspondence, for connecting fuselage（10）；
Multiple location holes（104）, its position and fuselage（10）On location hole（10-1）It is corresponding, positioned for connecting.
4. heat insulation structural as claimed in claim 1, it is characterised in that described thermal insulation board（6）Also include：
Through hole（601）, its shape and body（1）Fuselage installation base（101）Matching, makes thermal insulation board（6）Can just be arranged
In fuselage installation base（101）Around.
5. heat insulation structural as claimed in claim 4, it is characterised in that described thermal insulation board（6）Also include：
Location hole（602）, its position and fuselage（10）On location hole（10-1）It is corresponding, positioned for connecting.
6. heat insulation structural as claimed in claim 1, it is characterised in that described heat insulation loop（5）Also include：
Multiple grooves（501）, its position and body（1）On bearing baffle install groove（103）It is corresponding, for installing bearing
Baffle plate（4）.
7. heat insulation structural as claimed in claim 1, it is characterised in that described fuselage（10）Using titanium alloy material, body
（1）Using aluminum alloy materials, rotating shaft（2）And bearing baffle（4）Using stainless steel material, thermal insulation board（6）Using lower thermal conductivity
Asbestos material, heat insulation loop（5）Using the vagcor steel of lower thermal conductivity high compression-strength.
8. heat insulation structural as claimed in claim 1, it is characterised in that described bearing baffle（4）Height be more than bearing
（3）, make bearing（3）With fuselage（10）Between there is gap.
9. the heat insulation structural as described in claim 3 or 5, it is characterised in that positioning link（9）Through body（1）On determine
Position hole（104）, thermal insulation board（6）On location hole（602）And fuselage（10）On location hole（10-1）, realize body（1）With machine
Body（10）Installation positioning；Connector（7）Through body（1）On mounting hole（105）And fuselage（10）On mounting hole（10-
2）, by body（1）And fuselage（10）It is fixedly connected.
10. heat insulation structural as claimed in claim 2, it is characterised in that bearing baffle connector（8）By bearing baffle（4）Peace
Mounted in body（1）Bearing baffle install groove（103）It is interior.
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 true CN106828871A (en) | 2017-06-13 |
| CN106828871B 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) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114275145A (en) * | 2021-12-30 | 2022-04-05 | 湖北三江航天红阳机电有限公司 | Hot air flow blocking structure |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1905979A2 (en) * | 2006-09-29 | 2008-04-02 | JTEKT Corporation | Turbocharger |
| 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 |
| CN105507962A (en) * | 2014-10-14 | 2016-04-20 | 博格华纳公司 | Heat shield with centering features |
-
2017
- 2017-03-06 CN CN201710128812.8A patent/CN106828871B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1905979A2 (en) * | 2006-09-29 | 2008-04-02 | JTEKT Corporation | Turbocharger |
| 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 |
| CN105507962A (en) * | 2014-10-14 | 2016-04-20 | 博格华纳公司 | Heat shield with centering features |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114275145A (en) * | 2021-12-30 | 2022-04-05 | 湖北三江航天红阳机电有限公司 | Hot air flow blocking structure |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106828871B (en) | 2019-07-26 |
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