CN105000166A - Heat insulation structure used for high-mach-number air vehicle - Google Patents
Heat insulation structure used for high-mach-number air vehicle Download PDFInfo
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- CN105000166A CN105000166A CN201510212722.8A CN201510212722A CN105000166A CN 105000166 A CN105000166 A CN 105000166A CN 201510212722 A CN201510212722 A CN 201510212722A CN 105000166 A CN105000166 A CN 105000166A
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- heat insulation
- insulation structural
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- supporting construction
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Abstract
The invention relates to a design principle of a heat insulation structure used for a high-mach-number air vehicle. When the heat insulation structure of the high-mach-number air vehicle is designed through the principle, the weight of the heat insulation structure can be reduced on the premise that the heat insulation effect is guaranteed. The principle is that heat is taken away through high-speed flowing air and discharged out of the air vehicle, and the heat insulation aim is achieved. The principle is mainly used for designing structures, requiring heat insulation parts, of the high-mach-number air vehicle.
Description
One, technical field
The present invention relates to a kind of heat insulation structural principle of design for high Mach aircraft, adopt the heat insulation structural of this principle design height Mach aircraft, heat insulation structural weight can be alleviated under the prerequisite ensureing effect of heat insulation, realize the overall loss of weight of aircraft further.Be mainly used in the structure design that high Mach aircraft needs heat insulation position.
Two, background technology
High Mach aircraft, when passing in and out atmospheric envelope, aircraft surface and air severe friction, can cause aircraft surface temperature sharply to raise.For 6 Mach of aircraft, the temperature of its nose cone, the leading edge of a wing reaches as high as 1600 DEG C, in order to ensure the normal function of flight inner components, its internal temperature control must be made in lower level, conventional low-speed operations device ordinary construction used is difficult to be competent at, and needs to adopt special heat insulation structural design.
The heat insulation structural of high Mach aircraft requires the weight alleviating structure while ensureing effect of heat insulation.Existing heat insulation structural principle of design be utilize thermal insulation material low thermal conductivity to realize heat insulating function, heat insulation felt or the method at paste outside rigidity thermal insulation tile 1 is pasted specifically in heat insulation structural inside, as shown in Figure 1, this mode is pasted onto on metal skin 2 by thermal insulation material by adhesion agent, fitting process is complicated, Joint strenght is lower, the more important thing is and this design introduces thermal insulation material, can increase the weight of whole aircraft.
The present invention adopts new heat insulation structural principle of design, abandons the thermal insulation material that orthodox method adopts, and utilizes swiftly flowing airstrip to walk heat to realize cooling to heat insulation structural, effectively can alleviate structural weight while guarantee effect of heat insulation.
Three, summary of the invention
The invention provides a kind of principle of design of high Mach aircraft heat insulation structural, utilize swiftly flowing airstrip walk heat and discharge aircraft exterior, reach heat insulation object.Basic skills is the hollow interlayer structure be designed to by heat insulation structural with gas cooling-gallery or pipeline, the cold air had neither part nor lot in driving engine in the cold air of burning or atmospheric envelope is incorporated in gas cooling-gallery, pressure cooling is carried out to heat insulation structural, finally high temperature air is discharged in air.
Advantage of the present invention
The invention provides a kind of principle of design of high Mach aircraft heat insulation structural, utilize swiftly flowing airstrip walk heat and discharge aircraft exterior, reach heat insulation object.Adopt this principle design height Mach aircraft heat insulation structural, abandoned the design of the filling stickup thermal insulation material that orthodox method adopts, used the hollow interlayer structure with gas cooling-gallery or pipeline instead, with implementation structure function integration.
The present invention, while guarantee effect of heat insulation, not only can simplify fitting process, improves structural strength, prior without the need to recharging or pasting thermal insulation material, significant emphatically to aircraft.
Four, accompanying drawing explanation
Fig. 1 is the schematic diagram of prior art heat insulation structural;
Fig. 2 is the schematic diagram of the modular design of heat insulation structural;
Fig. 3 is the schematic diagram of vertical plate type heat insulation structural;
Fig. 4 is the schematic diagram of the board-like heat insulation structural of triangle;
Fig. 5 is the schematic diagram of taper interlayer heat insulation structural;
1-heat insulation felt or rigidity thermal insulation tile, 2-metal skin, 3-module, 4-covering, 5-body, 6-supporting construction.
Five, detailed description of the invention
Detailed description of the invention is: design heat insulation structural according to the temperature traverse of aircraft and aerodynamic configuration, the hollow interlayer construction module 3 with gas cooling-gallery of different forms is designed for different positions, the serial or parallel connection between several module can be carried out, from driving engine or air, introduce cold air cool heat insulation structural, be finally discharged in air.
Concrete heat insulation structural is: described heat insulation structural comprises covering 4, the body 5 of aircraft and supporting construction 6, described supporting construction is supported between covering and the body of aircraft, cooling-gallery is formed by the body of covering, aircraft and supporting construction, described cooling-gallery communicates with cold air source, taken away the heat of covering by cold air, high Mach aircraft is dispelled the heat.
Be further: described supporting construction 6 is stay bearing plate or support post.
Be further: described body 5 is the position windward of aircraft.
Be further: cold air source is the cold air having neither part nor lot in burning in driving engine or the atmospheric envelope cold air be incorporated in described cooling-gallery.
Particularly, the heat insulation structural of modular high Mach aircraft, described heat insulation structural comprises multiple module, each module includes covering, the body of aircraft and supporting construction, described supporting construction is supported between covering and the body of aircraft, form cooling-gallery by the body of covering, aircraft and supporting construction, taken away the heat of covering by cold air, high Mach aircraft is dispelled the heat; Between each module, gas circuit communicates, and is combined to form a complete cooling gas circuit by modules, and the cooling-gallery of one of them module communicates with cold air source.
Particularly, the heat insulation structural of modular high Mach aircraft, described heat insulation structural comprises multiple module, each module includes covering, the body of aircraft and supporting construction, described supporting construction is supported between covering and the body of aircraft, form cooling-gallery by the body of covering, aircraft and supporting construction, taken away the heat of covering by cold air, high Mach aircraft is dispelled the heat; Separate between each module, each module forms separately a complete cooling gas circuit, and the cooling-gallery of each module all communicates with cold air source.
Described heat insulation structural has various structures, as described below:
1), riser interlayer heat insulation structural
1. select structural materials and project organization profile according to structure at the use position of aircraft.
2. adopt vertical plate type jacket gas cooling-gallery in inside configuration, as shown in Figure 3.
3. construction module is assembled to aircraft corresponding site.
4. introduce refrigerating gas and pressure cooling is carried out to structure.
2) triangle interlayer heat insulation structural
1. select structural materials and project organization profile according to structure at the use position of aircraft.
2. adopt triangle interlayer gas cold but passage in inside configuration, as shown in Figure 4.
3. construction module is assembled to aircraft corresponding site.
4. introduce refrigerating gas and pressure cooling is carried out to structure.
3) taper interlayer heat insulation structural
1. select structural materials and project organization profile according to structure at the use position of aircraft.
2. adopt cone to open gas cooling-gallery in inside configuration, as shown in Figure 5.
3. construction module is assembled to aircraft corresponding site.
4. introduce refrigerating gas and pressure cooling is carried out to structure.
4) honeycomb interlayer heat insulation structural
1. select structural materials and project organization profile according to structure at the use position of aircraft.
2. adopt honeycomb interlayer gas cooling-gallery in inside configuration.
3. construction module is assembled to aircraft corresponding site.
4. introduce refrigerating gas and pressure cooling is carried out to structure.
Claims (9)
1. the heat insulation structural of one kind high Mach aircraft, it is characterized in that: described heat insulation structural comprises covering, the body of aircraft and supporting construction, described supporting construction is supported between covering and the body of aircraft, cooling-gallery is formed by the body of covering, aircraft and supporting construction, described cooling-gallery communicates with cold air source, taken away the heat of covering by cold air, high Mach aircraft is dispelled the heat.
2. the heat insulation structural of high Mach aircraft according to claim 1, is characterized in that: described supporting construction is stay bearing plate or support post.
3. the heat insulation structural of high Mach aircraft according to claim 1 and 2, is characterized in that: described body is the position windward of aircraft.
4. the heat insulation structural of high Mach aircraft according to claim 1 and 2, is characterized in that: cold air source is the cold air having neither part nor lot in burning in driving engine or the atmospheric envelope cold air be incorporated in described cooling-gallery.
5. the heat insulation structural of high Mach aircraft according to claim 1 and 2, is characterized in that: described heat insulation structural is riser interlayer heat insulation structural, triangle interlayer heat insulation structural, taper interlayer heat insulation structural, honeycomb interlayer heat insulation structural.
6. the heat insulation structural of a modular high Mach aircraft, described heat insulation structural comprises multiple module, each module includes covering, the body of aircraft and supporting construction, described supporting construction is supported between covering and the body of aircraft, cooling-gallery is formed by the body of covering, aircraft and supporting construction, taken away the heat of covering by cold air, high Mach aircraft is dispelled the heat; Between each module, gas circuit communicates, and is combined to form a complete cooling gas circuit by modules, and the cooling-gallery of one of them module communicates with cold air source.
7. the heat insulation structural of high Mach aircraft according to claim 6, is characterized in that: described heat insulation structural is riser interlayer heat insulation structural, triangle interlayer heat insulation structural, taper interlayer heat insulation structural, honeycomb interlayer heat insulation structural.
8. the heat insulation structural of a modular high Mach aircraft, described heat insulation structural comprises multiple module, each module includes covering, the body of aircraft and supporting construction, described supporting construction is supported between covering and the body of aircraft, cooling-gallery is formed by the body of covering, aircraft and supporting construction, taken away the heat of covering by cold air, high Mach aircraft is dispelled the heat; Separate between each module, each module forms separately a complete cooling gas circuit, and the cooling-gallery of each module all communicates with cold air source.
9. the heat insulation structural of high Mach aircraft according to claim 8, is characterized in that: described heat insulation structural is riser interlayer heat insulation structural, triangle interlayer heat insulation structural, taper interlayer heat insulation structural, honeycomb interlayer heat insulation structural.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510212722.8A CN105000166A (en) | 2015-04-29 | 2015-04-29 | Heat insulation structure used for high-mach-number air vehicle |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510212722.8A CN105000166A (en) | 2015-04-29 | 2015-04-29 | Heat insulation structure used for high-mach-number air vehicle |
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| CN105000166A true CN105000166A (en) | 2015-10-28 |
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| CN201510212722.8A Pending CN105000166A (en) | 2015-04-29 | 2015-04-29 | Heat insulation structure used for high-mach-number air vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106197938A (en) * | 2016-06-28 | 2016-12-07 | 中国航天空气动力技术研究院 | Free jet dynamometer check model novel heat-insulation system |
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| US4671348A (en) * | 1985-05-21 | 1987-06-09 | Mcdonnell Douglas Corporation | Transverse flow edge heat pipe |
| US4786015A (en) * | 1986-12-31 | 1988-11-22 | Sundstrand Corporation | Structural cooling unit |
| JPH04271999A (en) * | 1991-02-25 | 1992-09-28 | Ishikawajima Harima Heavy Ind Co Ltd | Cooling structure body and manufacture thereof |
| US20030087049A1 (en) * | 2001-11-02 | 2003-05-08 | Dieter Hachenberg | Ventilated double-walled composite aircraft fuselage shell |
| US20090101755A1 (en) * | 2007-10-17 | 2009-04-23 | Lockheed Martin Corporation | System, method, and apparatus for leading edge structures and direct manufacturing thereof |
| CN101636314A (en) * | 2007-02-23 | 2010-01-27 | 空中客车德国有限公司 | Fuselage of an aircraft or spacecraft and method of activelyinsulating such a fuselage |
| US20110100747A1 (en) * | 2006-05-24 | 2011-05-05 | Airbus Operations Gmbh | Sandwich element for the sound-absorbing inner cladding of means of transport, especially for the sound-absorbing inner cladding of aircraft |
| CN102145747A (en) * | 2011-03-22 | 2011-08-10 | 北京航空航天大学 | Impact and micro straight channel cooling structure for front edge of hypersonic vehicle |
| CN102427936A (en) * | 2009-06-01 | 2012-04-25 | 波音公司 | Methods and apparatus for a micro-truss based structural insulation layer |
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2015
- 2015-04-29 CN CN201510212722.8A patent/CN105000166A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4671348A (en) * | 1985-05-21 | 1987-06-09 | Mcdonnell Douglas Corporation | Transverse flow edge heat pipe |
| US4786015A (en) * | 1986-12-31 | 1988-11-22 | Sundstrand Corporation | Structural cooling unit |
| JPH04271999A (en) * | 1991-02-25 | 1992-09-28 | Ishikawajima Harima Heavy Ind Co Ltd | Cooling structure body and manufacture thereof |
| US20030087049A1 (en) * | 2001-11-02 | 2003-05-08 | Dieter Hachenberg | Ventilated double-walled composite aircraft fuselage shell |
| US20110100747A1 (en) * | 2006-05-24 | 2011-05-05 | Airbus Operations Gmbh | Sandwich element for the sound-absorbing inner cladding of means of transport, especially for the sound-absorbing inner cladding of aircraft |
| CN101636314A (en) * | 2007-02-23 | 2010-01-27 | 空中客车德国有限公司 | Fuselage of an aircraft or spacecraft and method of activelyinsulating such a fuselage |
| US20090101755A1 (en) * | 2007-10-17 | 2009-04-23 | Lockheed Martin Corporation | System, method, and apparatus for leading edge structures and direct manufacturing thereof |
| CN102427936A (en) * | 2009-06-01 | 2012-04-25 | 波音公司 | Methods and apparatus for a micro-truss based structural insulation layer |
| CN102145747A (en) * | 2011-03-22 | 2011-08-10 | 北京航空航天大学 | Impact and micro straight channel cooling structure for front edge of hypersonic vehicle |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106197938A (en) * | 2016-06-28 | 2016-12-07 | 中国航天空气动力技术研究院 | Free jet dynamometer check model novel heat-insulation system |
| CN106197938B (en) * | 2016-06-28 | 2018-11-23 | 中国航天空气动力技术研究院 | Free jet dynamometer check model insulation system |
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Application publication date: 20151028 |