CN113955077B - Head surface heat insulation structure of hypersonic aircraft - Google Patents
Head surface heat insulation structure of hypersonic aircraft Download PDFInfo
- Publication number
- CN113955077B CN113955077B CN202111299914.9A CN202111299914A CN113955077B CN 113955077 B CN113955077 B CN 113955077B CN 202111299914 A CN202111299914 A CN 202111299914A CN 113955077 B CN113955077 B CN 113955077B
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- CN
- China
- Prior art keywords
- honeycomb
- heat insulation
- layer
- insulation layer
- lead
- 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.)
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Links
- 238000009413 insulation Methods 0.000 title claims abstract description 76
- 239000000155 melt Substances 0.000 claims abstract description 4
- 238000007789 sealing Methods 0.000 claims description 9
- 239000004593 Epoxy Substances 0.000 claims description 8
- 239000004952 Polyamide Substances 0.000 claims description 8
- 239000000853 adhesive Substances 0.000 claims description 8
- 230000001070 adhesive effect Effects 0.000 claims description 8
- 229920002647 polyamide Polymers 0.000 claims description 8
- 239000000463 material Substances 0.000 claims description 6
- 239000011204 carbon fibre-reinforced silicon carbide Substances 0.000 claims description 5
- 229910007948 ZrB2 Inorganic materials 0.000 claims description 4
- VWZIXVXBCBBRGP-UHFFFAOYSA-N boron;zirconium Chemical compound B#[Zr]#B VWZIXVXBCBBRGP-UHFFFAOYSA-N 0.000 claims description 4
- 230000001413 cellular effect Effects 0.000 claims 3
- 239000011810 insulating material Substances 0.000 claims 1
- 230000000694 effects Effects 0.000 abstract description 6
- 239000012774 insulation material Substances 0.000 description 4
- 238000009835 boiling Methods 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 238000002844 melting Methods 0.000 description 2
- 230000008018 melting Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000005457 optimization Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- WABPQHHGFIMREM-UHFFFAOYSA-N lead(0) Chemical compound [Pb] WABPQHHGFIMREM-UHFFFAOYSA-N 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000000859 sublimation Methods 0.000 description 1
- 230000008022 sublimation Effects 0.000 description 1
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
- B64C30/00—Supersonic type aircraft
Abstract
The invention provides a heat insulation structure for the head surface of an ultra-high sonic aircraft, which comprises an outer surface lead structure layer and a honeycomb heat insulation layer, wherein the honeycomb heat insulation layer is connected with the head surface of the aircraft; the lead structure layer on the outer surface comprises a honeycomb framework and a lead layer, wherein the lead layer covers the honeycomb of the honeycomb framework and can flow out along the groove honeycomb when the lead layer melts; the honeycomb framework is connected with the honeycomb heat insulation layer. The invention ensures that the heat insulation layer on the head surface of the hypersonic aircraft has better heat insulation effect.
Description
Technical Field
The invention relates to the technical field of aircraft heat insulation, in particular to a heat insulation structure for the head surface of an ultra-high-speed aircraft.
Background
Ultra-high speed aircraft are relatively common today, but the temperature of the head can rise to 1500-2000 ℃ instantaneously during the flight, so that the heat insulation of the head is particularly important in order to protect the head structure and internal instruments of the aircraft and ensure normal flight. At present, the use of the high-temperature-resistant heat insulation layer is common, but the heat insulation layer still has the room for optimization and improvement, so that the heat insulation layer has better heat insulation effect.
At present, a good heat insulation layer adopts a honeycomb structure, and on the basis of a high-temperature-resistant heat insulation material, the honeycomb structure enables air to enter holes, so that heat conduction and thermal resistance are increased, and a better heat insulation effect is achieved. At present, the heat insulation material applied to the high-temperature aviation field is zirconium diboride generally, and the material can resist the high temperature of 3246 ℃, and has the characteristics of high strength at the low temperature and the high temperature, good heat shock resistance, small resistance, oxidation resistance at the high temperature and the like. However, the existing heat insulation layer has the disadvantage that if the new heat insulation strength needs to be met, a new high-temperature resistant material needs to be found. And the difficulty and cost of processing the honeycomb structure are considered. Optimization of the insulation structure is required.
Disclosure of Invention
Aiming at the defects existing in the prior art, the invention provides the heat insulation structure for the head surface of the hypersonic aircraft, so that the heat insulation layer of the head surface of the hypersonic aircraft has a better heat insulation effect.
The present invention achieves the above technical object by the following means.
The heat insulation structure comprises an outer surface lead structure layer and a honeycomb heat insulation layer, wherein the honeycomb heat insulation layer is connected with the surface of the head of the aircraft; the lead structure layer on the outer surface comprises a honeycomb framework and a lead layer, wherein the lead layer covers the honeycomb of the honeycomb framework and can flow out along the groove honeycomb when the lead layer melts; the honeycomb framework is connected with the honeycomb heat insulation layer.
Further, the honeycomb heat insulation layer comprises a honeycomb inner core, a honeycomb heat insulation layer lower panel, an outer sealing layer and a honeycomb heat insulation layer upper panel; the honeycomb inner core is sealed and wrapped by a honeycomb heat insulation layer lower panel, an outer sealing layer and a honeycomb heat insulation layer upper panel; the honeycomb heat insulation layer lower panel is bonded with the surface of the head of the aircraft through an epoxy polyamide adhesive; the lower surface of the honeycomb framework is bonded with the upper panel of the honeycomb heat insulation layer through an epoxy polyamide adhesive.
Further, the honeycomb inner core is formed by closely arranging a plurality of hexahedral core cells to form densely distributed cavities.
Further, the side length of the core lattice of the honeycomb inner core is 6-10 mm, and the thickness of the honeycomb inner core is 200-300 mm.
Further, the material of the honeycomb inner core is zirconium diboride.
Further, the cells of the honeycomb inner core are filled with heat insulation materials.
Further, the honeycomb framework is made of C/SiC.
Further, the honeycomb framework is formed by closely arranging a plurality of hexahedral core lattices to form densely distributed cavities, lead layers are covered in the cavities, and the side length of the core lattice of the honeycomb framework is 4-6 mm.
The invention has the beneficial effects that:
according to the heat insulation structure for the head surface of the hypersonic aircraft, in the flying process of a hypersonic aircraft, the surface is rubbed with the atmosphere to generate a large amount of heat, the temperature of the head can be instantaneously raised to 1500-2000 ℃, the deformation of the head of the aircraft caused by high temperature can influence the stability and safety of the aircraft to a certain extent, in order to avoid the occurrence of the situation, the heat insulation layer of the head is optimized, a layer of lead is attached on the basis of the original honeycomb heat insulation layer, and the boiling point of the lead is 1740 ℃. In the flight process of the aircraft, lead is sublimated instantly due to the high temperature of the head, and a large amount of heat can be taken away by sublimation, so that the heat insulation effect is greatly enhanced. Lead is embedded into the C/SiC honeycomb skeleton, so that molten lead is ensured to flow out along the grooves, and the flying is not influenced by splashing everywhere.
Drawings
Fig. 1 is a cross-sectional view of a hypersonic aircraft head surface insulation structure in accordance with the present invention.
Fig. 2 is a schematic view of a honeycomb core according to the present invention.
In the figure:
1-a honeycomb skeleton; 2-epoxy polyamide adhesive; 3-cellular core; 4-a honeycomb insulation layer; 5-honeycomb insulation layer lower panel; 6-an outer sealing layer; 7-honeycomb insulation layer upper panel; 9-lead layer.
Detailed Description
The invention will be further described with reference to the drawings and the specific embodiments, but the scope of the invention is not limited thereto.
Embodiments of the present invention are described in detail below, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to like or similar elements or elements having like or similar functions throughout. The embodiments described below by referring to the drawings are illustrative and intended to explain the present invention and should not be construed as limiting the invention.
In the description of the present invention, it should be understood that the terms "center," "longitudinal," "transverse," "length," "width," "thickness," "upper," "lower," "axial," "radial," "vertical," "horizontal," "inner," "outer," and the like indicate orientations or positional relationships based on the orientation or positional relationships shown in the drawings, merely to facilitate describing the present invention and simplify the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature. In the description of the present invention, the meaning of "a plurality" is two or more, unless explicitly defined otherwise.
In the present invention, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
As shown in fig. 1 and 2, the heat insulation structure for the head surface of the hypersonic aircraft comprises an outer surface lead structural layer and a honeycomb heat insulation layer 4, wherein the honeycomb heat insulation layer 4 is connected with the head surface of the aircraft; the lead structure layer on the outer surface comprises a honeycomb framework 1 and a lead layer 9, wherein the lead layer 9 is covered in a honeycomb of the honeycomb framework 1, and when the lead layer 9 is melted, the lead can flow out along the honeycomb, so that the melted lead is prevented from splashing everywhere to influence the flight; the honeycomb framework 1 is connected with the honeycomb heat insulation layer 4. The honeycomb framework 1 is made of C/SiC. The honeycomb framework 1 is formed by closely arranging a plurality of hexahedral core lattices to form densely distributed cavities, lead layers 9 are covered in the cavities, and the side length of the core lattice of the honeycomb framework 1 is 4-6 mm.
The honeycomb heat insulation layer 4 comprises a honeycomb inner core 3, a honeycomb heat insulation layer lower panel 5, an outer sealing layer 6 and a honeycomb heat insulation layer upper panel 7; the honeycomb inner core 3 is sealed and wrapped by a honeycomb heat insulation layer lower panel 5, an outer sealing layer 6 and a honeycomb heat insulation layer upper panel 7; the honeycomb heat insulation layer lower panel 5 is bonded with the surface of the head of the aircraft through the epoxy polyamide adhesive 2; the lower surface of the honeycomb framework 1 is bonded with the upper panel 7 of the honeycomb heat insulation layer through the epoxy polyamide adhesive 2. The honeycomb inner core 3 is formed by closely arranging a plurality of hexahedral core cells to form densely distributed cavities. The side length of the cell of the honeycomb inner core 3 is 6-10 mm, and the thickness of the honeycomb inner core 3 is 200-300 mm. The material of the honeycomb inner core 3 is zirconium diboride. The cells of the honeycomb inner core 3 can be filled with heat insulation materials, so that heat insulation can be further realized.
Working principle:
the invention mainly takes away pneumatic heat according to the change of the state of the metallic lead. When the flight speed of the aircraft is low, the temperature of the head of the aircraft is lower than the melting point temperature of lead, the thermal load of the head of the aircraft is small, the stability of the aircraft cannot be affected, and the heat insulation structure can meet the heat insulation requirement of the head of the aircraft; when the aircraft flies at a high speed, the temperature of the head of the aircraft is higher than the melting point temperature of lead and lower than the boiling point temperature of lead, at the moment, the lead in the honeycomb heat insulation layer absorbs heat and melts, and the melted lead flows out through the honeycomb channels to take away heat, so that the temperature reduction function of the head of the aircraft is realized; when the aircraft flies at the hypersonic speed, the temperature of the head of the aircraft is instantaneously increased, lead is changed from a solid state to a gaseous state, a large amount of heat is absorbed, the gaseous lead flows out through the honeycomb flow channels, and a large amount of heat generated by friction with air is taken away, so that the temperature of the surface 7 is reduced, and the heat insulation pressure is reduced. Meanwhile, the outer sealing layer 6 is added on the basis of the honeycomb inner core 3, and the outer sealing layer 6 is bonded with the honeycomb inner core 3 through the epoxy polyamide adhesive 2, so that the liquid lead melted by the lead layer can flow into the gaps of the honeycomb structure, thereby affecting the heat insulation effect of the heat insulation layer. In order not to splash the melted lead everywhere, the lead layer 9 is fixed by the C/SiC honeycomb skeleton 1, and the melted lead liquid flows out along the honeycomb.
It should be understood that although the present disclosure has been described in terms of various embodiments, not every embodiment is provided with a separate technical solution, and this description is for clarity only, and those skilled in the art should consider the disclosure as a whole, and the technical solutions in the various embodiments may be combined appropriately to form other embodiments that will be understood by those skilled in the art.
The above list of detailed descriptions is only specific to practical embodiments of the present invention, and they are not intended to limit the scope of the present invention, and all equivalent embodiments or modifications that do not depart from the spirit of the present invention should be included in the scope of the present invention.
Claims (7)
1. The heat insulation structure for the head surface of the hypersonic aircraft is characterized by comprising an outer surface lead structure layer and a honeycomb heat insulation layer (4), wherein the honeycomb heat insulation layer (4) is connected with the head surface of the aircraft; the outer surface lead structure layer comprises a honeycomb framework (1) and a lead layer (9), wherein the lead layer (9) is covered in a honeycomb of the honeycomb framework (1), and can flow out along a ditch honeycomb when the lead layer (9) melts; the honeycomb framework (1) is connected with the honeycomb heat insulation layer (4); the honeycomb framework (1) is formed by closely arranging a plurality of hexahedral core lattices to form densely distributed cavities, and lead layers (9) are covered in the cavities;
the honeycomb heat insulation layer (4) comprises a honeycomb inner core (3), a honeycomb heat insulation layer lower panel (5), an outer sealing layer (6) and a honeycomb heat insulation layer upper panel (7); the honeycomb inner core (3) is sealed and wrapped by a honeycomb heat insulation layer lower panel (5), an outer sealing layer (6) and a honeycomb heat insulation layer upper panel (7); the honeycomb heat insulation layer lower panel (5) is bonded with the surface of the head of the aircraft through an epoxy polyamide adhesive (2); the lower surface of the honeycomb framework (1) is bonded with the upper panel (7) of the honeycomb heat insulation layer through an epoxy polyamide adhesive (2).
2. The heat insulation structure for the head surface of an hypersonic flight vehicle according to claim 1 wherein the cellular inner core (3) is formed by closely arranging a plurality of hexahedral core cells to form densely packed cavities.
3. The heat insulation structure for the head surface of the hypersonic flight vehicle according to claim 2 is characterized in that the side length of the core lattice of the honeycomb inner core (3) is 6-10 mm, and the thickness of the honeycomb inner core (3) is 200-300 mm.
4. The structure according to claim 1, characterized in that the cells of the cellular core (3) are filled with a heat insulating material.
5. The hypersonic aircraft head surface insulation structure as claimed in claim 1, characterized in that the material of the cellular core (3) is zirconium diboride.
6. The hypersonic aircraft head surface insulation structure as claimed in claim 1, characterized in that the material of the honeycomb skeleton (1) is C/SiC.
7. The heat insulation structure for the head surface of the hypersonic flight vehicle according to claim 1 is characterized in that the side length of the core lattice of the honeycomb framework (1) is 4-6 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111299914.9A CN113955077B (en) | 2021-11-04 | 2021-11-04 | Head surface heat insulation structure of hypersonic aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111299914.9A CN113955077B (en) | 2021-11-04 | 2021-11-04 | Head surface heat insulation structure of hypersonic aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113955077A CN113955077A (en) | 2022-01-21 |
| CN113955077B true CN113955077B (en) | 2024-03-19 |
Family
ID=79469206
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111299914.9A Active CN113955077B (en) | 2021-11-04 | 2021-11-04 | Head surface heat insulation structure of hypersonic aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113955077B (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1331266A (en) * | 1969-10-17 | 1973-09-26 | Hexcel Corp | Cells of structural honeycomb with fibrous material |
| JP2002228348A (en) * | 2001-01-31 | 2002-08-14 | Tokyo Electron Ltd | Heat-insulating structure |
| JP2004009740A (en) * | 1994-04-13 | 2004-01-15 | Nikkiso Co Ltd | Honeycomb laminated structure |
| DE102011008574A1 (en) * | 2010-10-12 | 2012-04-12 | Ec Technik Gmbh | Composite panel for e.g. fixed-wing aircraft for ballistic protection against surface-to-air missiles, has splinter protective layer integrated in panel, arranged between core layer and cover layer and firmly connected with cover layer |
| JP2017187098A (en) * | 2016-04-05 | 2017-10-12 | 東洋インキＳｃホールディングス株式会社 | Laminate heat insulation film and heat insulation cover |
| CN212046202U (en) * | 2020-03-19 | 2020-12-01 | 湖南云顶智能科技有限公司 | Phase-change heat-insulation composite thermal protection structure of hypersonic aircraft |
| CN212685893U (en) * | 2020-07-02 | 2021-03-12 | 中南大学 | Hypersonic aircraft prevents thermal-insulated integral structure |
| CN213832089U (en) * | 2020-10-13 | 2021-07-30 | 镇江市逸帆航空部件有限公司 | Honeycomb-based insulating panel for aircraft cabins |
-
2021
- 2021-11-04 CN CN202111299914.9A patent/CN113955077B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1331266A (en) * | 1969-10-17 | 1973-09-26 | Hexcel Corp | Cells of structural honeycomb with fibrous material |
| JP2004009740A (en) * | 1994-04-13 | 2004-01-15 | Nikkiso Co Ltd | Honeycomb laminated structure |
| JP2002228348A (en) * | 2001-01-31 | 2002-08-14 | Tokyo Electron Ltd | Heat-insulating structure |
| DE102011008574A1 (en) * | 2010-10-12 | 2012-04-12 | Ec Technik Gmbh | Composite panel for e.g. fixed-wing aircraft for ballistic protection against surface-to-air missiles, has splinter protective layer integrated in panel, arranged between core layer and cover layer and firmly connected with cover layer |
| JP2017187098A (en) * | 2016-04-05 | 2017-10-12 | 東洋インキＳｃホールディングス株式会社 | Laminate heat insulation film and heat insulation cover |
| CN212046202U (en) * | 2020-03-19 | 2020-12-01 | 湖南云顶智能科技有限公司 | Phase-change heat-insulation composite thermal protection structure of hypersonic aircraft |
| CN212685893U (en) * | 2020-07-02 | 2021-03-12 | 中南大学 | Hypersonic aircraft prevents thermal-insulated integral structure |
| CN213832089U (en) * | 2020-10-13 | 2021-07-30 | 镇江市逸帆航空部件有限公司 | Honeycomb-based insulating panel for aircraft cabins |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113955077A (en) | 2022-01-21 |
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