CN101791880B - Cover plate formed by combining metal honeycomb structure and ceramics used for thermal protection system - Google Patents
Cover plate formed by combining metal honeycomb structure and ceramics used for thermal protection system Download PDFInfo
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- CN101791880B CN101791880B CN2009103127662A CN200910312766A CN101791880B CN 101791880 B CN101791880 B CN 101791880B CN 2009103127662 A CN2009103127662 A CN 2009103127662A CN 200910312766 A CN200910312766 A CN 200910312766A CN 101791880 B CN101791880 B CN 101791880B
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- thermal protection
- protection system
- honeycomb
- cover plate
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Abstract
The invention provides a cover plate formed by combining a metal honeycomb structure and ceramics used for a thermal protection system, which relates to the cover plate formed by combining the metal honeycomb structure and the ceramics. The invention aims at solving the problems that the existing thermal protection system using ceramic thermal protection tiles has the defects of crisp texture, easy obscission, water absorption, no rainproof effect and easy deformation, metal materials are unfavorable for gap sealing, the thermal protection system has little heat detained in the thermal protection system when heating the surface of an aircraft, and in addition, a large amount of heat is transmitted to the machine body of the aircraft. A lower layer plate is fixedly connected with a honeycomb body, each honeycomb cell of the honeycomb body is in a shape of a hexagon, each hexagon-shaped honeycomb cell is filled with phase-change materials arranged in a case, the honeycomb body, the phase-change materials and the case are combined for forming a honeycomb layer, the honeycomb body is fixedly connected with an upper layer plate, and a ceramic plate is fixedly connected with the upper layer plate. The invention is used for the thermal protection of disposable or reusable hypersonic speed aircrafts with the flight altitude between 30 km and 100 km and the flight speed between 3 M and 15 M.
Description
Technical field
The present invention relates to the cover plate that a kind of metal honeycomb structure combines with pottery.
Background technology
When being written into, spacecraft to get into atmosphere with very high speed; Under aerodynamic effect, be a significant slowdown; Its huge kinetic energy and potential energy are converted into huge heat energy simultaneously; And the effect of thermal protection system is exactly to reduce to get into the inner heat energy of spacecraft as far as possible, makes spacecraft body and internal part thereof operate as normal within the rational temperature scope.This shows that thermal protection system is the important component part of spacecraft.
The ceramic insulation tile serviceability temperature reaches 1250 ℃, and heat-proof quality is good, has satisfied the flight requirement of space shuttle basically, but its exist matter crisp, be prone to come off, absorb water, not rainproof, yielding, maintenance and change shortcoming such as difficulty; Metallic Thermal Protection Systems has the reliability height, good toughness, advantage such as do not absorb water, but service metal temperature is lower, generally is used for below 1000 ℃, thermal coefficient of expansion be ceramic tile 2-3 doubly, be unfavorable for the sealing in gap.Present thermal protection system heat when aircraft surface heats is trapped in the thermal protection system less, and heat transmits to the aircraft body in a large number.
Summary of the invention
The objective of the invention is for solve use in the existing thermal protection system ceramic insulation tile exist matter crisp, be prone to come off, absorb water, sealing that not rainproof, yielding and metal material is unfavorable for the gap and thermal protection system heat when aircraft surface heat be trapped in that less and heat has proposed a kind of metal honeycomb structure and ceramic cover plate that combines that is used for thermal protection system in a large number to the problem of aircraft body transmission in the thermal protection system.
The present invention solves the problems of the technologies described above the technical scheme of taking to be: said metal alloy cover board comprises honeycomb ceramics, top plate, lower plywood, phase-change material, shell and ceramic wafer; The upper surface of said lower plywood and the lower surface of honeycomb ceramics are affixed; Each honeycomb cell element of said honeycomb ceramics is a regular hexagon; Be filled with cased phase-change material in each regular hexagon honeycomb cell element; Said honeycomb ceramics and phase-change material and shell constitute keriotheca, and the upper surface of said honeycomb ceramics and the lower surface of top plate are affixed, and the lower surface of said ceramic wafer and the upper surface of top plate are affixed; The material of said honeycomb ceramics, top plate and lower plywood is Ni based high-temperature alloy, Fe based high-temperature alloy, Ni-Fe based high-temperature alloy, Co based high-temperature alloy or Nb based high-temperature alloy; The material of said ceramic wafer is SiO2, Al2O3 fibre reinforced materials or Al2O3 composite, and when said shell was Al2O3, said phase-change material was the Al-Si alloy; When said shell was SiO2, ZrO2 or Al2O3, said phase-change material was LiF.
The present invention has following beneficial effect: 1. the present invention combines pottery and metal alloy, and honeycomb ceramics as the structural member that carries, is reached the integrated design of thermal protection system and structural member, and whole machine body structural member gross weight is reduced 10-15%; Simultaneously structure difficult drop-off of the present invention, be difficult for suction, rainproof, not yielding and help the sealing in gap.2. fill cased phase-change material among the present invention in each honeycomb cell element; When temperature rises to or be higher than the phase-change material phase transition temperature; Phase-change material absorbs heat and undergoes phase transition; Variation greater than 20 ℃ does not take place in this cover plate temperature in the phase-change material phase transition process, the phase-change material phase transformation is accomplished back shroud and just continued to heat up; After aircraft surface stopped heating, when the cover plate temperature was lower than the phase-change material phase transition temperature, reverse phase transformation took place in phase-change material, emits heat.The operation principle of phase-change material makes thermal protection system more heats when aircraft surface heats be trapped in the thermal protection system; Reduce to the transmission of aircraft body; Compare with the thermal protection system of not filling phase-change material; This structure is thinner lighter, thereby bigger payload or cabin body space is provided.
Description of drawings
Fig. 1 is an overall structure sketch map of the present invention, and Fig. 2 is the A-A cutaway view of Fig. 1, and Fig. 3 is the B portion enlarged drawing of Fig. 1.
The specific embodiment
The specific embodiment one: combine Fig. 1 and Fig. 2 that this embodiment is described; The metal alloy cover board of this embodiment comprises honeycomb ceramics 1, top plate 2, lower plywood 3, phase-change material 4, shell 6 and ceramic wafer 7; The lower surface of the upper surface of said lower plywood 3 and honeycomb ceramics 1 is affixed; Each honeycomb cell element 1-1 of said honeycomb ceramics 1 is a regular hexagon; Be filled with the phase-change material 4 that is contained in the shell 6 in each regular hexagon honeycomb cell element 1-1; Said honeycomb ceramics 1 constitutes keriotheca 5 with phase-change material 4 and shell 6, and the lower surface of the upper surface of said honeycomb ceramics 1 and top plate 2 is affixed, and the upper surface of the lower surface of said ceramic wafer 7 and top plate 2 is affixed; The material of said honeycomb ceramics 1, top plate 2 and lower plywood 3 is Ni based high-temperature alloy, Fe based high-temperature alloy, Ni-Fe based high-temperature alloy, Co based high-temperature alloy or Nb based high-temperature alloy, and the material of said ceramic wafer 7 is SiO
2, Al
2O
3Fibre reinforced materials or Al
2O
3Composite, said shell 6 is Al
2O
3The time, said phase-change material 4 is the Al-Si alloy, said shell 6 is SiO
2, ZrO
2Or Al
2O
3The time, said phase-change material 4 is LiF;
Present embodiment can be used as heat sink structure, absorbs great amount of heat, reduces the temperature diffusivity of thermal protection system, reduces thermal protection system and thickness of structure.
The specific embodiment two: combine Fig. 1 and Fig. 2 that this embodiment is described, the wall thickness of each regular hexagon honeycomb cell element 1-1 of this embodiment is 0.05-0.1mm, and the length of side of each regular hexagon honeycomb cell element 1-1 is 2-10mm.Other composition and annexation are identical with the specific embodiment one.
The specific embodiment three: combine Fig. 1 and Fig. 2 that this embodiment is described, the height of the honeycomb ceramics 1 of this embodiment is 2-20mm.Other composition and annexation are identical with the specific embodiment one.
The specific embodiment four: combine Fig. 1 and Fig. 2 that this embodiment is described, the thickness of the ceramic wafer 7 of this embodiment is 0.1-20mm.Other composition and annexation are identical with the specific embodiment one.
The specific embodiment five: combine Fig. 1 and Fig. 2 that this embodiment is described, the thickness of the top plate 2 of this embodiment is 0.1-0.4mm.Other composition and annexation are identical with the specific embodiment one.
The specific embodiment six: combine Fig. 1 and Fig. 2 that this embodiment is described, the thickness of the lower plywood 3 of this embodiment is 0.1-0.4mm.Other composition and annexation are identical with the specific embodiment one.
The specific embodiment seven: combine Fig. 1 and Fig. 2 that this embodiment is described, the affixed form of the upper surface of the lower plywood 3 of this embodiment and the lower surface of honeycomb ceramics 1 is welding.Other composition and annexation are identical with the specific embodiment one.
The specific embodiment eight: combine Fig. 1 and Fig. 2 that this embodiment is described, the affixed form of the upper surface of the honeycomb ceramics 1 of this embodiment and the lower surface of top plate 2 is welding.Other composition and annexation are identical with the specific embodiment one.
The specific embodiment nine: combine Fig. 1 and Fig. 2 that this embodiment is described, the affixed form of the lower surface of the ceramic wafer 7 of this embodiment and the upper surface of top plate 2 is welding.
The specific embodiment ten: combine Fig. 1 and Fig. 2 that this embodiment is described, the lower surface of the ceramic wafer 7 of this embodiment and the affixed form of the upper surface of top plate 2 are that inorganic glue is bonding.
Operation principle: at first adopt the technology of high temperature vacuum brazing to connect into an integral body to honeycomb ceramics 1 and lower plywood 3; In each honeycomb cell element 1-1, fill then and be contained in the phase-change material 4 in the shell 6; Adopt high temperature vacuum brazing technology to be connected honeycomb ceramics 1 with top plate 2 again; Employing is affixed with ceramic wafer 7 and top plate 2 from spreading welding or inorganic glue technique for sticking, thereby the hypersonic vehicle that obtains filling phase-change material is with metal honeycomb structure and the ceramic honeycomb cover plate typical structure that combines.
Claims (10)
1. the cover plate that combines of metal honeycomb structure that is used for thermal protection system and pottery; It is characterized in that said cover plate comprises honeycomb ceramics (1), top plate (2), lower plywood (3), phase-change material (4), shell (6) and ceramic wafer (7); The lower surface of the upper surface of said lower plywood (3) and honeycomb ceramics (1) is affixed; Each honeycomb cell element (1-1) of said honeycomb ceramics (1) is a regular hexagon; Be filled with the phase-change material (4) that is contained in the shell (6) in each regular hexagon honeycomb cell element (1-1); Said honeycomb ceramics (1) constitutes keriotheca (5) with phase-change material (4) and shell (6), and the lower surface of the upper surface of said honeycomb ceramics (1) and top plate (2) is affixed, and the upper surface of the lower surface of said ceramic wafer (7) and top plate (2) is affixed; The material of said honeycomb ceramics (1), top plate (2) and lower plywood (3) is Ni based high-temperature alloy, Fe based high-temperature alloy, Ni-Fe based high-temperature alloy, Co based high-temperature alloy or Nb based high-temperature alloy, and the material of said ceramic wafer (7) is SiO
2, Al
2O
3Fibre reinforced materials or Al
2O
3Composite, said shell (6) is Al
2O
3The time, said phase-change material (4) is Al-Si alloy or LiF, said shell (6) is SiO
2And ZrO
2The time, said phase-change material (4) is LiF.
2. the cover plate that combines with pottery according to the said metal honeycomb structure that is used for thermal protection system of claim 1; The wall thickness that it is characterized in that said each regular hexagon honeycomb cell element (1-1) is 0.05-0.1mm, and the length of side of each regular hexagon honeycomb cell element (1-1) is 2-10mm.
3. according to claim 1 or the 2 said metal honeycomb structures and the ceramic cover plate that combines that are used for thermal protection system, the height that it is characterized in that said honeycomb ceramics (1) is 2-20mm.
4. the cover plate that combines with pottery according to the said metal honeycomb structure that is used for thermal protection system of claim 3, the thickness that it is characterized in that said ceramic wafer (7) is 0.1-20mm.
5. the cover plate that combines with pottery according to the said metal honeycomb structure that is used for thermal protection system of claim 4, the thickness that it is characterized in that said top plate (2) is 0.1-0.4mm.
6. the cover plate that combines with pottery according to the said metal honeycomb structure that is used for thermal protection system of claim 3, the thickness that it is characterized in that said lower plywood (3) is 0.1-0.4mm.
7. according to the said metal honeycomb structure and the cover plate that pottery combines that is used for thermal protection system of claim 1, it is characterized in that the upper surface of said lower plywood (3) and the affixed form of lower surface of honeycomb ceramics (1) are welding.
8. according to the said metal honeycomb structure and the cover plate that pottery combines that is used for thermal protection system of claim 1, it is characterized in that the upper surface of said honeycomb ceramics (1) and the affixed form of lower surface of top plate (2) are welding.
9. according to the said metal honeycomb structure and the cover plate that pottery combines that is used for thermal protection system of claim 1, it is characterized in that the lower surface of said ceramic wafer (7) and the affixed form of upper surface of top plate (2) are welding.
10. according to the said metal honeycomb structure and the cover plate that pottery combines that is used for thermal protection system of claim 1, it is characterized in that the lower surface of said ceramic wafer (7) and the affixed form of upper surface of top plate (2) are that inorganic glue is bonding.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009103127662A CN101791880B (en) | 2009-12-30 | 2009-12-30 | Cover plate formed by combining metal honeycomb structure and ceramics used for thermal protection system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009103127662A CN101791880B (en) | 2009-12-30 | 2009-12-30 | Cover plate formed by combining metal honeycomb structure and ceramics used for thermal protection system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101791880A CN101791880A (en) | 2010-08-04 |
| CN101791880B true CN101791880B (en) | 2012-11-28 |
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ID=42584893
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009103127662A Expired - Fee Related CN101791880B (en) | 2009-12-30 | 2009-12-30 | Cover plate formed by combining metal honeycomb structure and ceramics used for thermal protection system |
Country Status (1)
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| CN (1) | CN101791880B (en) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| TW201217096A (en) * | 2010-10-18 | 2012-05-01 | Metal Ind Res & Dev Ct | reducing weight and maintaining a certain flatness and rigidity to fast and accurately position to increase working efficiency |
| CN108102615A (en) * | 2018-01-24 | 2018-06-01 | 航天东方红卫星有限公司 | A kind of preparation method of the new sizing phase transformation thermal controls apparatus based on honeycomb |
| CN108758581A (en) * | 2018-08-09 | 2018-11-06 | 广东工业大学 | A kind of soaking plate applied to LED light group heat dissipation |
| CN111179896B (en) * | 2020-01-06 | 2022-06-14 | 苏州大学 | Honeycomb embedded coupling structure composite material and preparation method thereof |
| CN111532416B (en) * | 2020-05-12 | 2021-06-08 | 北京凌空天行科技有限责任公司 | Modular rigid ceramic tile assembly |
| CN115464226B (en) * | 2022-09-23 | 2023-10-24 | 中国航发哈尔滨东安发动机有限公司 | Vacuum brazing connection method for ceramics and Nb |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1623770A (en) * | 2004-12-17 | 2005-06-08 | 清华大学 | Metal/ceramic laminated composite material prevention plate |
| CN1746609A (en) * | 2005-10-17 | 2006-03-15 | 北京科技大学 | Composite bulletproof armour with steel honeycomb ceramic sandwich and manufacture thereof |
| CN101186134A (en) * | 2007-12-12 | 2008-05-28 | 哈尔滨工业大学 | Thermal barrier coating and preparation method thereof |
-
2009
- 2009-12-30 CN CN2009103127662A patent/CN101791880B/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1623770A (en) * | 2004-12-17 | 2005-06-08 | 清华大学 | Metal/ceramic laminated composite material prevention plate |
| CN1746609A (en) * | 2005-10-17 | 2006-03-15 | 北京科技大学 | Composite bulletproof armour with steel honeycomb ceramic sandwich and manufacture thereof |
| CN101186134A (en) * | 2007-12-12 | 2008-05-28 | 哈尔滨工业大学 | Thermal barrier coating and preparation method thereof |
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| Publication number | Publication date |
|---|---|
| CN101791880A (en) | 2010-08-04 |
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Granted publication date: 20121128 Termination date: 20131230 |