CN111130392B - Heat protection structure with bearing/heat-proof/power supply integrated function - Google Patents
Heat protection structure with bearing/heat-proof/power supply integrated function Download PDFInfo
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- CN111130392B CN111130392B CN201911281996.7A CN201911281996A CN111130392B CN 111130392 B CN111130392 B CN 111130392B CN 201911281996 A CN201911281996 A CN 201911281996A CN 111130392 B CN111130392 B CN 111130392B
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- 239000011159 matrix material Substances 0.000 claims description 7
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- 238000010248 power generation Methods 0.000 claims description 4
- 229910000838 Al alloy Inorganic materials 0.000 claims description 3
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims description 3
- 229910044991 metal oxide Inorganic materials 0.000 claims description 3
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- TWNQGVIAIRXVLR-UHFFFAOYSA-N oxo(oxoalumanyloxy)alumane Chemical compound O=[Al]O[Al]=O TWNQGVIAIRXVLR-UHFFFAOYSA-N 0.000 description 2
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Classifications
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02N—ELECTRIC MACHINES NOT OTHERWISE PROVIDED FOR
- H02N11/00—Generators or motors not provided for elsewhere; Alleged perpetua mobilia obtained by electric or magnetic means
- H02N11/002—Generators
-
- 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)
- Laminated Bodies (AREA)
Abstract
本发明公开了一种具有承载/防热/供电一体化功能的热防护结构，热防护结构单元由热防护单元及间隙热防护组件组成；热防护单元包含承载框架、热电层及限位窝芯，间隙热防护组件包含防热层、隔热层、结构接口层及控温层；热电层包含高温热电层和中温热电层；所述承载框架与飞行器壁面通过螺钉连接，其余结构部件间均通过耐高温胶连接。本发明的集成热电转换功能的热防护结构，将热电材料及控温材料引入热防护结构设计中，通过合理设计热防护单元与间隙热防护组件，在满足承载功能与热防护功能的前提下，利用热电材料层的温差进行发电，对于在严峻热环境中长时间工作的飞行器减重及飞行器内部空间使用率的提升具有重要意义。
The invention discloses a thermal protection structure with integrated functions of bearing/heat protection/power supply. The thermal protection structural unit is composed of a thermal protection unit and a gap thermal protection component; the thermal protection unit includes a bearing frame, a thermoelectric layer and a limit socket core , the gap thermal protection component includes a heat protection layer, a thermal insulation layer, a structural interface layer and a temperature control layer; the thermoelectric layer includes a high temperature thermoelectric layer and a medium temperature thermoelectric layer; the carrier frame and the aircraft wall are connected by screws, and the rest of the structural components are connected between All connected by high temperature resistant glue. The thermal protection structure with integrated thermoelectric conversion function of the present invention introduces thermoelectric materials and temperature control materials into the design of the thermal protection structure. Using the temperature difference of the thermoelectric material layer to generate electricity is of great significance for the weight reduction of aircraft that work in severe thermal environments for a long time and the improvement of the utilization rate of the internal space of the aircraft.
Description
Technical Field
The invention belongs to the field of overall design of aerospace aircrafts and design of multifunctional structural materials, and relates to a thermal protection structure with a bearing/heat prevention/power supply integrated function.
Background
The hypersonic cruise aircraft needs to work for a long time in a severe geothermal environment, the heat is taken away through ablation or heat resistance is achieved by utilizing the property of a material in the traditional aircraft heat protection system design, the long-time working requirement of the aircraft is not met, the requirement for a carried power supply is increased inevitably when the aircraft works for a long time, the internal space of the aircraft is occupied, and the weight of the aircraft is increased.
Therefore, the design idea of the original thermal protection system is urgently needed to be broken through, from the thermal management perspective, the blocking is changed into the dredging, the waste is changed into the using, the thermal energy is converted into the electric energy, and an innovative thermal protection structure which comprehensively considers the integrated functions of bearing, heat prevention and power supply is adopted; meanwhile, a complete theoretical system is established to describe different functions and corresponding index parameters, and the problem of realizing the integrated structural design and optimization integrating bearing, heat protection and power supply is urgently needed to be solved.
Disclosure of Invention
The invention aims to provide a thermal protection structure with a bearing/heat prevention/power supply integrated function, which can replace part of power supply carried by an aircraft, save the internal space of the aircraft and convert pneumatic heat into electric energy through thermoelectric materials on the premise of ensuring the basic function of a thermal protection system on the wall surface of the aircraft, thereby realizing the bearing/heat prevention/power supply integrated design based on the thermal protection structure of the aircraft.
In order to achieve the purpose, the technical scheme adopted by the invention is as follows:
a thermal protection structure with integrated functions of bearing, heat prevention and power supply comprises a temperature control layer, a thermal protection unit and a gap thermal protection assembly, wherein the temperature control layer is arranged on one side of an aircraft wall structure, the thermal protection unit is arranged on the other side of the aircraft wall structure, and the gap thermal protection assembly is arranged on the periphery of the thermal protection unit;
the thermal protection unit comprises a bearing frame and a thermoelectric layer, and the thermoelectric layer is arranged on the bearing frame; the thermoelectric layer is divided into a first thermoelectric layer and a second thermoelectric layer, the first thermoelectric layer is arranged on the second thermoelectric layer, and the second thermoelectric layer is arranged on the bearing frame; the working temperatures of the first thermoelectric layer and the second thermoelectric layer form temperature difference power generation;
the heat protection assembly comprises a heat-proof layer, a heat-insulating layer and a structural interface layer, wherein the heat-proof layer and the heat-insulating layer, the heat-insulating layer and the structural interface layer, and the structural interface layer and the temperature control layer are connected through glue;
the structural interface layer of the clearance thermal protection assembly, the bearing frame of the thermal protection unit and the aircraft wall surface structure are fixed through fasteners.
Optionally, the thermoelectric layer includes alumina ceramic layer and thermoelectric material, and three alumina ceramic layers stack in proper order, wherein set up a plurality of thermoelectric layer unit cells between two adjacent alumina ceramic layers from top to bottom and form first thermoelectric layer and second thermoelectric layer, and a plurality of thermoelectric layer unit cells loop through the conducting strip electricity and connect.
Optionally, the thermoelectric layer unit cell comprises a cylindrical thermoelectric material and a limiting nest core, the cylindrical thermoelectric material is embedded in the limiting nest core, and the conductive sheet connects the thermoelectric material in series.
Optionally, the thermoelectric material and the spacing nest core are filled with a fiber heat insulating material.
Optionally, the working temperature of the thermoelectric material of the first thermoelectric layer is higher than that of the thermoelectric material of the second thermoelectric layer.
Optionally, the outer side of the whole body of the limiting nest core is connected with the inner side of the whole body of the bearing frame through glue, and the aluminum oxide ceramic layer is connected with the conducting plate through glue.
Optionally, a circle of high temperature resistant rubber bushing is arranged around the fastener, and a layer of heat insulation material is arranged between the heat protection unit and the wall surface of the aircraft.
Optionally, the bearing frame and the nest core are made of one of metals or metal alloys such as titanium, titanium alloy, aluminum alloy, deformed high-temperature alloy and the like; the thermoelectric material adopted by the thermoelectric layer is one of metal alloy and semiconductor metal oxide.
Optionally, the heat-proof layer is made of one of an ablation type composite material and a non-ablation type composite material; the heat insulation layer is made of one of a heat reflection material, a porous material or a vacuum material; the temperature control layer can be a packaged composite phase change material or a temperature control material.
Optionally, the thermal protection units are arranged on the aircraft wall surface structure in a matrix form, the gap thermal protection assembly is a layered structure with grid array holes, and the thermal protection units are arranged in the grid array holes of the gap thermal protection assembly.
Compared with the prior art, the structure of the application has the following advantages:
the invention provides a thermal protection structure with integrated functions of bearing, heat prevention and power supply, which can be used as a design scheme of an aircraft thermal protection structure. The thermoelectric material and the temperature control material are introduced into the aircraft thermal protection structure, on the premise of meeting the thermal protection requirement, pneumatic heat is converted into electric energy, partial energy requirements of the long-endurance high-speed cruise aircraft during working are met, partial onboard power supplies can be replaced, and the utilization rate of the internal space of the aircraft is improved. The thermal protection structure with the integrated bearing/heat-proof/power supply function has the advantages of standard mechanical interface and electrical interface, strong expansibility, reusability and low test and use cost, and outputs the structural form and the structural size according to the bearing environment and the power supply requirement of the service working condition. According to the thermal protection structure integrating the thermoelectric conversion function, the thermoelectric material and the temperature control material are introduced into the design of the thermal protection structure, and the thermal protection unit and the gap thermal protection assembly are reasonably designed, so that the temperature difference of the thermoelectric material layer is utilized to generate electricity on the premise of meeting the bearing function and the thermal protection function, and the thermal protection structure has important significance for reducing the weight of an aircraft working in a severe thermal environment for a long time and improving the utilization rate of the space in the aircraft.
Drawings
Fig. 1 is a schematic view of a thermal protection structure with integrated functions of load bearing, heat protection and power supply, which is provided by the invention and applied to a wall surface of an aircraft in a matrix unit form.
Fig. 2 is a schematic view of a thermal protection structure with integrated functions of load bearing, heat protection and power supply.
Fig. 3 is an assembly schematic diagram of the invention with integrated bearing/heat protection/power supply function.
FIG. 4 is an assembly schematic of a thermal protection unit provided by the present invention.
Fig. 5 is a schematic cross-sectional view of the middle part of a thermal protection structure with integrated load bearing/heat protection/power supply function (refer to the cross-section of fig. 1) provided by the invention.
FIG. 6 is a detail view of a pyroelectric layer unit cell of the thermal protection unit provided by the present invention.
In the figure:
0. a high temperature resistant glue layer; 1. a gap thermal protection assembly; 2. a thermal protection unit; 3. an aircraft wall structure; 11. a heat shield layer; 12. a thermal insulation layer; 3. an aircraft wall structure; 4. a temperature control layer; 5. fastening screws; 6. a high temperature resistant rubber bushing; 21. an alumina ceramic layer; 22. a limiting nest core; 23. a conductive sheet; 241. a high temperature thermoelectric material; 242. a medium temperature thermoelectric material; 25. a load-bearing frame.
Detailed Description
In order to make those skilled in the art better understand the technical solution of the present invention, the technical solution in the embodiment of the present invention will be clearly and completely described below with reference to the drawings in the embodiment of the present invention, and it is obvious that the described embodiment is only a part of the embodiment of the present invention, and not all embodiments. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, shall fall within the scope of protection of the present invention.
It will be understood that when an element is referred to as being "disposed on" another element, it can be directly on the other element or intervening elements may also be present. When an element is referred to as being "connected" to another element, it can be directly connected to the other element or intervening elements may also be present. The terms "vertical," "horizontal," "left," "right," and the like as used herein are for illustrative purposes only and do not denote a single embodiment.
Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. The terminology used in the description of the invention herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items.
As shown in fig. 1 to 6, the thermal protection structure with integrated functions of load bearing, heat protection and power supply of the present invention is formed by arranging a plurality of periodic structural units in a matrix form, wherein each periodic structural unit is composed of a thermal protection unit 2 and a gap thermal protection assembly 1.
The thermal protection unit 2 mainly comprises a bearing frame 25, a thermoelectric layer, a limiting nest core 22 and a temperature control layer 4; the clearance heat protection assembly mainly comprises a heat-proof layer 11, a heat-insulating layer 12, a structure interface layer and a temperature control layer 4.
The thermoelectric layer of thermal protection unit divide into high temperature thermoelectric layer and medium temperature thermoelectric layer according to thermoelectric material work temperature range, every thermoelectric layer comprises aluminium oxide ceramic layer 21, conducting strip and thermoelectric material, the conducting strip welds with the both ends of spreading layer serial ports connected mode and thermoelectric material, the conducting strip passes through high temperature resistant glue with the aluminium oxide ceramic layer and is connected, thermoelectric material inlays in spacing nest core, spacing nest core 22 space packing thermal-insulated fibre. Finally, the thermoelectric layer comprises three alumina ceramic laminates, two types of thermoelectric materials, four layers of conducting strips and the like.
The side surface of the limiting nest core 22 of the thermal protection unit, the side surface of the alumina ceramic laminate in the thermoelectric layer and the bearing frame are connected through high-temperature-resistant glue.
The structure interface layer of the clearance thermal protection assembly 1, the bearing frame 25 of the thermal protection unit 2 and the aircraft wall structure 3 are fixed through twelve fastening screws 5, wherein a layer of heat insulation material is arranged between the bearing frame 25 and the aircraft wall structure 3, a circle of high-temperature resistant rubber bushing is arranged around the fastening screws 5, and the above structural design form is mainly used for relieving the high-temperature stress concentration condition of the rigid connection structure and improving the anti-vibration characteristic.
The heat-proof layer 11 and the heat-insulating layer 12, the heat-insulating layer 12 and the structure interface layer, and the structure interface layer and the temperature control layer 4 of the gap heat protection assembly are all connected through high-temperature-resistant glue, and the heat-proof layer 11 and the inner side surface of the temperature control layer 4 and the outer side surface of the wall surface of the bearing frame 25 of the heat protection unit are connected through high-temperature-resistant glue.
The bearing frame 25 and the limiting nest core 22 in the thermal protection unit can be made of one of metals or metal alloys such as titanium, titanium alloy, aluminum alloy, deformed high-temperature alloy and the like; the thermoelectric material adopted by the thermoelectric layer can be one of metal alloy and semiconductor metal oxide; the material of the temperature control layer 4 can be one of a packaged composite Phase Change Material (PCM) and a Temperature Control Material (TCM).
The heat-proof layer 11 in the gap thermal protection component 1 can be made of one of an ablative composite material and a non-ablative composite material; the material of the thermal insulation layer 12 may be one of a heat reflection material, a porous material or a vacuum material.
The limiting socket core 22 of the thermal protection unit 2 is integrally formed by material increase manufacturing technology, namely a three-dimensional CAD model of a part generated in a computer is adopted, three-dimensional data information of the part is converted into a series of two-dimensional outline information, materials are stacked layer by layer according to an outline track by a laser cladding method, and finally a three-dimensional solid part is formed.
The invention is based on the traditional thermal protection structure, multifunctional structure, thermoelectric material-based thermoelectric power generation structure and the like of an aircraft, the design of a thermal protection unit bearing frame is completed by utilizing the characteristics of high bending resistance, torsion resistance, high connection strength and the like of a flange structure, a cylindrical thermoelectric material is embedded in a honeycomb core, and heat insulation fibers are filled in gaps, so that the torque and bending moment borne by the thermoelectric material are relieved, the thermoelectric material has certain vibration resistance, the connection of a plurality of thermoelectric material power supply serial ports and a plurality of thermoelectric material power supply serial ports is realized by utilizing a printed circuit board type conducting strip, and the temperature difference between the cold end and the hot end of the thermoelectric material; in addition, for the interface clearance of thermal protection unit and aircraft wall connection, use for reference traditional thermal protection system design experience, adopt "heat protection layer + insulating layer + structural layer + accuse temperature layer" design theory, satisfy the requirement of thermal protection system.
The thermoelectric material has good thermoelectric conversion performance, electric energy can be generated through temperature difference, the optimal temperature ranges of different types of thermoelectric materials are different, the thermal protection structure with the integrated functions of bearing, heat prevention and power supply is possible by designing the thermal protection unit with the layered thermoelectric material and large temperature difference between the hot end and the cold end, the designed thermal protection unit is designed to enable the thermoelectric material to bear the load as small as possible and the temperature difference between the cold end and the hot end of the thermoelectric material to be as large as possible in consideration of weak bearing capacity of the thermoelectric material, and the temperature difference between the cold end and the hot end of the thermoelectric material can be remarkably improved by using the temperature control material.
The design and guidance of the thermal protection units are high in bending resistance and torsion resistance, the thermal protection units are arranged on the wall surface structure of the aircraft in a matrix arrangement mode, gaps exist at mechanical interfaces connected with the wall surface of the aircraft, the thermal protection structure design is also carried out on the gaps, and the design of the gap thermal protection system is completed under the guidance of improving the thermoelectric efficiency, meeting the system requirements and reducing the quality.
Compared with the traditional structure, the thermal protection unit has more applied material types and higher requirements on the material, the bearing material has excellent specific strength/specific rigidity at the service temperature, and the inherent property of the thermoelectric material influences the thermoelectric conversion efficiency and the power generation power of the structure; the heat protection unit uses a large amount of high-temperature-resistant glue, and the property of the high-temperature-resistant glue has direct influence on the inherent characteristics, mechanical property and reliability of the heat protection unit.
Examples
The invention relates to a thermal protection structure with integrated functions of load bearing, heat protection and power supply, which is a periodic unit of the thermal protection structure as shown in fig. 2, 3 and 5, and can be arranged and installed in a matrix form when being specifically applied to the wall surface of a flight vehicle; the thermal protection component comprises a heat-proof layer 11, a heat-insulating layer 12, a mechanical interface between a thermal protection unit 2 and an aircraft wall surface structure 3 and the like, wherein the thermal protection unit 2 and the thermal protection component 1 share a temperature control layer 4; the thermal protection unit 2 is fixed with the aircraft wall structure 3 through a fastening screw 5, and the fastening screw 5 is sleeved with a high-temperature-resistant rubber bushing 6.
The invention provides a heat protection structure with a bearing/heat prevention/power supply integrated function, which is applied to a certain aircraft wall surface, for example, as shown in fig. 1, a plurality of heat protection units 2 arranged in a matrix form are fixed on an aircraft wall surface structure 3, a gap heat protection component 1 designed for the aircraft wall surface covers a gap between the aircraft wall surface structure 3 and the heat protection units 2, and an electrical interface of the heat protection unit 2 is connected by adopting a serial port.
The thermal protection unit 2 of the present invention is shown in fig. 4 and fig. 6, wherein the thermoelectric layer is divided into a high temperature thermoelectric layer and a medium temperature thermoelectric layer; specifically, the high-temperature thermoelectric layer and the medium-temperature thermoelectric layer can tolerate the relative temperature up and down, and actually mean that the temperature resistance of the high-temperature thermoelectric layer is higher than that of the medium-temperature thermoelectric layer, and the high-temperature thermoelectric layer and the medium-temperature thermoelectric layer are not a specific limitation of high temperature and low temperature.
Wherein, high temperature thermoelectric layer contains alumina ceramic layer 21, high temperature thermoelectric material 241 and conducting strip 23, and conducting strip 23 is prefabricated layer formula conducting strip that spreads, and the conducting strip is with thermoelectric material serial ports connection to the end welding will be drawn forth in high temperature thermoelectric material 241 terminal surface, conducting strip 23 and alumina ceramic layer 21 are connected through high temperature resistant glue 0, and cylindric high temperature thermoelectric material 241 inlays in spacing nest core 22. The fiber heat insulation material is filled in the gap between the high-temperature thermoelectric material 241 and the spacing nest core 22, the outer side of the whole body of the spacing nest core 22 is connected with the inner side of the whole body of the bearing frame 25 through high-temperature-resistant glue, the structural form of the middle-temperature thermoelectric layer is similar to that of the high-temperature thermoelectric layer, the middle-temperature thermoelectric layer and the high-temperature thermoelectric layer share one aluminum oxide ceramic layer, and the relation among all the parts in the thermoelectric layer can be clearly seen with.
In the thermal protection structure, except for the conducting strip, the other conducting materials (metal materials) are coated with the high-temperature-resistant insulating layer.
The limiting nest core in the thermal protection unit 2 provided by the invention is subjected to three-dimensional CAD modeling and transmits model data to a 3D printer, and the model is prepared by adopting an additive manufacturing technology, for example, titanium alloy is selected as a material.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered to be within the scope of the present invention, and the technical solutions and the inventive concepts thereof according to the present invention should be equivalent or changed within the technical scope of the present invention.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention, and all equivalent changes and modifications made within the scope of the present invention should be considered as the technical scope of the present invention.
Claims (6)
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| Application Number | Priority Date | Filing Date | Title |
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| CN201911281996.7A CN111130392B (en) | 2019-12-13 | 2019-12-13 | Heat protection structure with bearing/heat-proof/power supply integrated function |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201911281996.7A CN111130392B (en) | 2019-12-13 | 2019-12-13 | Heat protection structure with bearing/heat-proof/power supply integrated function |
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| CN111130392A CN111130392A (en) | 2020-05-08 |
| CN111130392B true CN111130392B (en) | 2021-06-01 |
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| CN201911281996.7A Expired - Fee Related CN111130392B (en) | 2019-12-13 | 2019-12-13 | Heat protection structure with bearing/heat-proof/power supply integrated function |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112580236B (en) * | 2020-11-30 | 2023-08-01 | 中国运载火箭技术研究院 | A Fast Analytical Method for Nonlinear Dynamic Response of Thermal Protection Connecting Structure |
| CN113562202B (en) * | 2021-08-24 | 2022-07-29 | 北京理工大学 | Integrated dot matrix thermal protection system is born to thermal-insulated heat-proof of multilayer based on phase change material |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5445861A (en) * | 1992-09-04 | 1995-08-29 | The Boeing Company | Lightweight honeycomb panel structure |
| CN105515448A (en) * | 2016-01-19 | 2016-04-20 | 哈尔滨工业大学 | Hypersonic speed aircraft skin cooling and semiconductor thermoelectric power generation integrated system |
| CN109941423A (en) * | 2019-03-25 | 2019-06-28 | 西北工业大学 | A Modular Multifunctional Heat-Proof Structure for Hypersonic Vehicles |
| CN110065618A (en) * | 2019-03-25 | 2019-07-30 | 西北工业大学 | A kind of multifunction structure device and its working method for hypersonic aircraft |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2929746B1 (en) * | 2008-04-07 | 2010-09-03 | Hutchinson | ACOUSTIC INSULATION PANEL |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5445861A (en) * | 1992-09-04 | 1995-08-29 | The Boeing Company | Lightweight honeycomb panel structure |
| CN105515448A (en) * | 2016-01-19 | 2016-04-20 | 哈尔滨工业大学 | Hypersonic speed aircraft skin cooling and semiconductor thermoelectric power generation integrated system |
| CN109941423A (en) * | 2019-03-25 | 2019-06-28 | 西北工业大学 | A Modular Multifunctional Heat-Proof Structure for Hypersonic Vehicles |
| CN110065618A (en) * | 2019-03-25 | 2019-07-30 | 西北工业大学 | A kind of multifunction structure device and its working method for hypersonic aircraft |
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| CN111130392A (en) | 2020-05-08 |
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