CN109941423B - Modular multifunctional heat-proof structure for hypersonic aircraft - Google Patents
Modular multifunctional heat-proof structure for hypersonic aircraft Download PDFInfo
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- CN109941423B CN109941423B CN201910228106.XA CN201910228106A CN109941423B CN 109941423 B CN109941423 B CN 109941423B CN 201910228106 A CN201910228106 A CN 201910228106A CN 109941423 B CN109941423 B CN 109941423B
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- 239000000463 material Substances 0.000 claims abstract description 28
- 239000000956 alloy Substances 0.000 claims description 5
- 239000011810 insulating material Substances 0.000 claims description 4
- 238000010438 heat treatment Methods 0.000 abstract description 3
- 238000012423 maintenance Methods 0.000 abstract description 2
- 230000008878 coupling Effects 0.000 description 3
- 238000010168 coupling process Methods 0.000 description 3
- 238000005859 coupling reaction Methods 0.000 description 3
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 239000000919 ceramic Substances 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000012774 insulation material Substances 0.000 description 2
- 230000005678 Seebeck effect Effects 0.000 description 1
- 238000007792 addition Methods 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 229910052738 indium Inorganic materials 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000011148 porous material Substances 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Thermal Insulation (AREA)
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Abstract
The invention discloses a modularized multifunctional heat-proof structure for a hypersonic aircraft, which comprises a heat-proof layer, a honeycomb layer cover plate, a thermoelectric material, a frame and a bottom cover plate, wherein the honeycomb layer is arranged on the bottom cover plate; the honeycomb layer is arranged in the frame, the thermoelectric material is arranged in the accommodating space of the honeycomb layer, and a honeycomb layer cover plate is arranged on the honeycomb layer; the heat-proof layer is arranged on the honeycomb layer cover plate, the bottom cover plate is arranged below the frame, and the honeycomb layer and the thermoelectric material are fixed into a modular structure through fasteners by the heat-proof layer and the bottom cover plate. When the aircraft is subjected to severe pneumatic heating, the structure can protect the structure of the aircraft body from being damaged, and convert part of pneumatic heat energy into electric energy to be supplied to the aircraft, so that the use and maintenance cost of the aircraft is effectively reduced. Meanwhile, the developed modularization and splicing scheme are convenient to install and use on the aircraft, and have certain universality.
Description
Technical Field
The invention relates to the field of thermal protection design of a hypersonic aircraft, in particular to a modular multifunctional heat-proof structure for the hypersonic aircraft.
Background
When the hypersonic aerocraft flies in the atmosphere, a serious pneumatic heating phenomenon can be generated, and a thermal protection system is required to be used for protecting the structure of the aerocraft. The existing aircraft is usually designed with a thermal protection system and a bearing structure separately, the mechanical property of a heat-proof structure is weaker, the load of a fuselage structure cannot be shared, the connection mode is mostly bonding, and the maintainability is poor. Traditional aircraft heat protection structure includes ceramic heat protection tile, ceramic heat insulation felt and metal heat protection tile etc. to prevent insulating against heat as the main objective, efficiency is lower, for this reason each country's researcher has developed the novel heat protection structure who contains multiple functions such as bearing, heat protection, power supply. As shown In FIG. 1, Banapalli et al, In reference 1 "Banapalli. S.K.analysis and Design of Corrugated-Core Sandwich Panels for Thermal Protection Systems of Space Vehicles [ C ]. In Proceedings of the47th AIAA Structures, Structural Dynamics and Materials Conference, 2006", have established a load/heat resistant integrated structure based on a Corrugated Sandwich structure, which is highly efficient, has high toughness and good impact resistance.
Disclosure of Invention
The invention aims to provide a modular multifunctional heat-proof structure which can be suitable for a hypersonic aircraft, improves the existing heat protection design concept, and utilizes pneumatic heat as energy. The modularized multifunctional heat-proof structure provided by the invention is used for providing a necessary heat-proof effect for the hypersonic aircraft, and has power supply and carrying capacities.
In order to realize the task, the invention adopts the following technical solution:
a modularized multifunctional heat-proof structure for a hypersonic aircraft comprises a heat-proof layer, a honeycomb layer cover plate, a thermoelectric material, a frame and a bottom cover plate;
the honeycomb layer is arranged in the frame, the thermoelectric material is arranged in the accommodating space of the honeycomb layer, and a honeycomb layer cover plate is arranged on the honeycomb layer;
the heat-proof layer is arranged on the honeycomb layer cover plate, the bottom cover plate is arranged below the frame, and the honeycomb layer and the thermoelectric material are fixed into a modular structure through fasteners by the heat-proof layer and the bottom cover plate.
Thermoelectric materials are placed in the honeycomb layer and thermal insulation materials are filled in the honeycomb layer.
The fastener is a connecting stud.
The heat-proof layer is made of C/C-SiC material.
The honeycomb layer is made of TC4 alloy materials, an insulating layer is coated on a bottom plate of the honeycomb layer, and electrodes for leading out electric energy are welded on the bottom plate of the honeycomb layer.
The splicing assembly is used for splicing a plurality of modular structures;
the modular structure is provided with a splicing groove matched with the splicing component.
The splicing assembly comprises a corner splicing assembly, a side splicing assembly and a center splicing assembly,
the corner edge splicing assembly comprises an L-shaped main body and a first inserting edge which is used for being inserted into the splicing groove, and the first inserting edge is arranged along the edges of two surfaces of the L-shaped main body;
the side splicing assembly comprises a T-shaped main body and a second inserting edge which is used for being inserted into the splicing groove, and the second inserting edge is arranged along the edges of three surfaces of the T-shaped main body;
the central splicing assembly comprises a cross-shaped main body and a third inserting edge used for being inserted into the splicing groove, and the third inserting edge is arranged along the edges of four surfaces of the cross-shaped main body.
Compared with the prior art, the invention has the following advantages:
the invention provides a thermoelectric power generation structure with multiple layers of materials and multiple functions based on thermoelectric materials, wherein a heat-proof layer is the outer surface of the multifunctional structure, the thermoelectric materials are placed in a honeycomb layer, and a frame is used for providing support for the multifunctional structure, so that the multifunctional structure for bearing/preventing heat/supplying power for a hypersonic aircraft is formed, and a modular scheme and a splicing scheme for easy installation are provided. The modular multifunctional heat-proof structure for the hypersonic aircraft is designed for the hypersonic aircraft. When the aircraft is subjected to severe pneumatic heating, the structure can protect the body structure from being damaged, and a part of pneumatic heat energy is converted into electric energy to be supplied to the aircraft, so that the use and maintenance cost of the aircraft is effectively reduced. Meanwhile, the developed modularization and splicing scheme are convenient to install and use on the aircraft, and have certain universality.
Drawings
FIG. 1 is a schematic diagram of a corrugated sandwich structure designed by Bapanaralli.
Fig. 2 is a schematic view of the multifunctional heat-proof structure of the present invention.
Fig. 3 is an exploded view of the multifunctional heat-proof structure of the present invention.
Fig. 4 is a schematic diagram of the multi-functional heat-proof structure of the present invention after splicing.
FIG. 5 is a schematic view of three splice assemblies of the present invention.
In the figure: 1 is a heat-proof layer; 2 is a connecting stud; 3 is a honeycomb layer cover plate; 4 is a thermoelectric material; 5 is a frame; 6 is a bottom cover plate; 7 is a corner edge splicing component; 8 is a side splicing component; 9 is a central splicing component; 10 is a honeycomb layer; 11 is a splicing component; 12 is a splicing groove; 13 is an L-shaped main body; 14 is a first inserting edge; 15 is a T-shaped main body; 16 is a second inserting edge; 17 is a cross-shaped main body; and 18 is a third inserting edge.
Detailed Description
The invention is described in further detail below with reference to the figures and the detailed description.
As shown in fig. 2 to 5, the invention provides a modular multifunctional heat-proof structure, which can convert heat energy into electric energy to supply to an aircraft power supply system through the temperature difference between two ends of a thermoelectric material based on the seebeck effect of the thermoelectric material while completing the heat-proof function, and has a certain bearing capacity to prevent the structure from being damaged.
The heat-insulating honeycomb structure mainly comprises a heat-insulating layer 1, a honeycomb layer 10, a honeycomb layer cover plate 3, thermoelectric materials 4, heat-insulating materials, a frame 5, a bottom cover plate 6, connecting studs 2 and a splicing assembly 11.
As shown in fig. 3, the honeycomb layer 10 is arranged in the frame 5, the thermoelectric material 4 is arranged in the accommodating space of the honeycomb layer 10, and the honeycomb layer cover plate 3 is arranged on the honeycomb layer 10; the heat-proof layer 1 is arranged on the honeycomb layer cover plate 3, the bottom cover plate 6 is arranged below the frame 5, and the honeycomb layer 10 and the thermoelectric material 4 are fixed into a modular structure by the heat-proof layer 1 and the bottom cover plate 6 through fasteners.
Preferably, the honeycomb layer 10 is filled with an insulating material and a thermoelectric material 4 is disposed therein. The fastener is a connecting stud 2.
The honeycomb layer 10 is made of TC4 alloy material, and an insulating layer is coated on the bottom plate of the honeycomb layer 10 and welded with electrodes for leading out electric energy.
The heat-proof layer 1 is the outer surface of the multifunctional structure; thermoelectric materials are placed in the honeycomb layer 10, and heat insulation materials are filled in the honeycomb layer; the frame 5 is used for providing support for the honeycomb layer 10; the connecting stud 2 is used for connecting the whole structure; the splicing assembly 11 is used to splice the modular structures into a desired shape.
The heat shield layer 1 uses C/C-SiC, or similar high temperature resistant material, to maintain the geometry of the structure under high temperature conditions.
The honeycomb layer 10 is made of TC4 alloy or similar high-temperature-resistant alloy material and is used for placing thermoelectric materials and limiting, and meanwhile, the load-bearing capacity of the structure is guaranteed. In addition, the bottom plate of the honeycomb layer 10 needs to be coated with an insulating layer and welded with electrodes for leading out electric energy.
The honeycomb layer cover plate 3 is used for transition between the heat-proof layer 1 and the honeycomb layer 10, and the situation of overlarge thermal stress is prevented.
As shown in fig. 4 and 5, the splicing assembly 11 is used for splicing a plurality of modular structures; the modular structure is provided with a splicing groove 12 matched with the splicing component 11. The splicing assembly 11 has three forms, and can be used for splicing the multifunctional structure into a required shape in a plane, if a more complex shape is required, different splicing assemblies 11 can be designed according to requirements. The splicing component 11 comprises a corner splicing component 7, a side splicing component 8 and a center splicing component 9,
the corner edge splicing assembly 7 comprises an L-shaped main body 13 and a first inserting edge 14 used for being inserted into the splicing groove 12, and the first inserting edge 14 is arranged along two surface edges of the L-shaped main body 13.
The side splicing assembly 8 comprises a T-shaped main body 15 and a second inserting edge 16 used for being inserted into the splicing groove 12, and the second inserting edge 16 is arranged along the edges of three surfaces of the T-shaped main body 15.
The central splicing component 9 comprises a cross-shaped main body 17 and a third inserting edge 18 used for being inserted into the splicing groove 12, and the third inserting edge 18 is arranged along the edges of four faces of the cross-shaped main body 17.
As shown in fig. 4, the structural layers of the present invention can be assembled separately and finally assembled in a unified manner.
For the heat-shielding layer 1, since there is only one cover plate, no additional operation is required.
For the honeycomb layer 10, the insulating treatment of the base plate and the welding of the electrodes should be first completed, and then the thermoelectric material 4 is welded on the base plate 6 and the remaining pores are filled with the insulating material, and then the cover plate 3 is installed and sealed.
And connecting the two layers of structures by using a connecting stud 2 to complete the assembly of the multifunctional heat-proof structure.
When a plurality of multifunctional structure assemble, can be by the center to assembling all around, use central coupling assembling 9 earlier promptly, can modify multifunctional structure's shape at the marginal part according to the shape to use angle limit coupling assembling 7 and side coupling assembling 8 to accomplish the concatenation at edge, and carry out handles such as encapsulating according to the demand.
The above-described embodiments are merely illustrative of implementations of the invention that enable persons skilled in the art to make or use the invention, and the description is not limiting. Therefore, the present invention should not be limited to the embodiments shown herein, and all additions and equivalents made to the technical features of the present invention are intended to fall within the scope of the present application.
Claims (4)
1. A modularized multifunctional heat-proof structure for a hypersonic aircraft is characterized by comprising a heat-proof layer (1), a honeycomb layer (10), a honeycomb layer cover plate (3), a thermoelectric material (4), a frame (5) and a bottom cover plate (6);
the honeycomb layer (10) is arranged in the frame (5), the thermoelectric material (4) is arranged in the accommodating space of the honeycomb layer (10), and the honeycomb layer cover plate (3) is arranged on the honeycomb layer (10);
the heat-proof layer (1) is arranged on the honeycomb layer cover plate (3), the bottom cover plate (6) is arranged below the frame (5), and the honeycomb layer (10) and the thermoelectric material (4) are fixed into a modular structure by the heat-proof layer (1) and the bottom cover plate (6) through fasteners;
the thermoelectric material (4) is placed in the honeycomb layer (10) and is filled with a heat insulating material;
the heat-proof layer (1) is made of C/C-SiC material;
the honeycomb layer (10) is made of TC4 alloy materials, an insulating layer is coated on a bottom plate of the honeycomb layer (10), and electrodes for leading out electric energy are welded on the bottom plate.
2. The modular multifunctional heat protection architecture for hypersonic aircraft according to claim 1, characterized in that said fasteners are connecting studs (2).
3. The modular multifunctional heat protection architecture for hypersonic aircraft according to claim 1, characterized in that it further comprises a splicing assembly (11) for splicing a plurality of modular structures;
the modular structure is provided with a splicing groove (12) matched with the splicing component (11).
4. The modular multifunctional heat protection structure for hypersonic aircraft according to claim 3, characterized in that said splicing modules (11) comprise corner splicing modules (7), side splicing modules (8) and central splicing modules (9),
the corner edge splicing assembly (7) comprises an L-shaped main body (13) and a first inserting edge (14) used for being inserted into the splicing groove (12), and the first inserting edge (14) is arranged along the edges of two surfaces of the L-shaped main body (13);
the side edge splicing assembly (8) comprises a T-shaped main body (15) and a second inserting edge (16) used for being inserted into the splicing groove (12), and the second inserting edge (16) is arranged along the edges of three surfaces of the T-shaped main body (15);
the center splicing assembly (9) comprises a cross-shaped main body (17) and a third inserting edge (18) used for being inserted into the splicing groove (12), and the third inserting edge (18) is arranged along the edges of four surfaces of the cross-shaped main body (17).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910228106.XA CN109941423B (en) | 2019-03-25 | 2019-03-25 | Modular multifunctional heat-proof structure for hypersonic aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910228106.XA CN109941423B (en) | 2019-03-25 | 2019-03-25 | Modular multifunctional heat-proof structure for hypersonic aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN109941423A CN109941423A (en) | 2019-06-28 |
| CN109941423B true CN109941423B (en) | 2022-05-31 |
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| CN201910228106.XA Expired - Fee Related CN109941423B (en) | 2019-03-25 | 2019-03-25 | Modular multifunctional heat-proof structure for hypersonic aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111130392B (en) * | 2019-12-13 | 2021-06-01 | 西北工业大学 | Heat protection structure with bearing/heat-proof/power supply integrated function |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5154373A (en) * | 1988-09-26 | 1992-10-13 | Rockwell International Corporation | Integral structure and thermal protection system |
| CN101722687A (en) * | 2009-12-30 | 2010-06-09 | 哈尔滨工业大学 | Metal alloy cover board for hypersonic speed flying vehicle thermal protection system |
| CN101927585B (en) * | 2009-12-30 | 2012-11-28 | 哈尔滨工业大学 | Cover plate consisting of metal honeycomb structure and ceramics for thermal protection system |
| JP6022419B2 (en) * | 2013-07-09 | 2016-11-09 | 株式会社Kelk | Thermoelectric module |
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Granted publication date: 20220531 |