CN109540962B - Heat insulation efficiency characterization method of heat insulation structure - Google Patents
Heat insulation efficiency characterization method of heat insulation structure Download PDFInfo
- Publication number
- CN109540962B CN109540962B CN201811452672.0A CN201811452672A CN109540962B CN 109540962 B CN109540962 B CN 109540962B CN 201811452672 A CN201811452672 A CN 201811452672A CN 109540962 B CN109540962 B CN 109540962B
- Authority
- CN
- China
- Prior art keywords
- heat insulation
- test piece
- heat
- efficiency
- selecting
- 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.)
- Active
Links
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N25/00—Investigating or analyzing materials by the use of thermal means
- G01N25/20—Investigating or analyzing materials by the use of thermal means by investigating the development of heat, i.e. calorimetry, e.g. by measuring specific heat, by measuring thermal conductivity
Landscapes
- Physics & Mathematics (AREA)
- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Chemical & Material Sciences (AREA)
- Analytical Chemistry (AREA)
- Biochemistry (AREA)
- General Health & Medical Sciences (AREA)
- General Physics & Mathematics (AREA)
- Immunology (AREA)
- Pathology (AREA)
- Building Environments (AREA)
- Investigating Or Analyzing Materials Using Thermal Means (AREA)
Abstract
The application belongs to the technical field of aircraft structure testing, and particularly relates to a heat insulation efficiency characterization method of a heat insulation structure. The method comprises the following steps: the method comprises the following steps: selecting a plurality of heat insulation structures as test pieces; step two: testing the heat insulation performance of the test pieces respectively to obtain the temperature T when the temperature of the cold surface temperature measuring point of each test piece reaches the steady state under the condition that the temperature of the hot surface is the samemaxAnd the time t taken to reach steady statemax(ii) a Step three: calculating the density rho of each test piece, wherein rho is m/v, m is the mass of the test piece, and v is the volume of the test piece; step four: selecting a test piece as a reference piece, wherein the density of the test piece is rho0The temperature at which steady state is reached is T0 maxAnd the time taken to reach steady state is t0 max(ii) a Step five: and respectively calculating the heat insulation efficiency A of each test piece. This application can optimize out thermal-insulated efficiency optimum thermal-insulated structure, realizes thermal-insulated structure light efficient design purpose, can improve thermal-insulated structural design efficiency, easily promotes, has great practical value.
Description
Technical Field
The application belongs to the technical field of aircraft structure testing, and particularly relates to a heat insulation efficiency characterization method of a heat insulation structure.
Background
Aircraft structural components located in high temperature regions, such as equipment compartments near engines, present a corresponding thermal insulation requirement for the function of their internal equipment due to the high external temperature of the components. The traditional aircraft heat insulation structure adopts the structure with heat insulation materials added inside to realize the heat insulation function, namely large-area heat insulation materials are directly glued on the inner side of a wall plate, the heat insulation performance of the heat insulation structure is usually considered during design, and the weight increment of the aircraft structure caused by the large-area heat insulation materials is usually ignored. Therefore, a method for representing the efficiency of the heat insulation structure, which can comprehensively evaluate two factors of the heat insulation performance and the weight reduction effect of the heat insulation structure, is urgently needed, so that a light and efficient heat insulation structure is designed.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The present application is directed to a method for characterizing the thermal insulation effectiveness of a thermal insulation structure, so as to solve at least one problem of the prior art.
The technical scheme of the application is as follows:
a method of characterizing the insulation effectiveness of an insulation structure, comprising the steps of:
the method comprises the following steps: selecting a plurality of heat insulation structures as test pieces;
step two: testing the heat insulation performance of the test pieces respectively to obtain the temperature T when the temperature of the cold surface temperature measuring point of each test piece reaches the steady state under the condition that the temperature of the hot surface is the samemaxAnd the time t taken to reach steady statemax；
Step three: calculating the density rho of each test piece, wherein rho is m/v, m is the mass of the test piece, and v is the volume of the test piece;
step four: selecting a test piece as a reference piece, wherein the density of the test piece is rho0The temperature at which steady state is reached is T0 maxAnd the time taken to reach steady state is t0 max；
Step five: and respectively calculating the heat insulation efficiency A of each test piece:
optionally, the method further comprises:
step six: and selecting the test piece with the minimum heat insulation efficiency A value as the heat insulation structure of the airplane.
Optionally, the selecting a plurality of insulation structures as the test piece in the first step includes:
s101, selecting a heat insulation material with high heat insulation efficiency;
s102, designing the selected heat insulation materials into a plurality of heat insulation structures with different configurations according to the design requirements of the heat insulation structure of the airplane.
Optionally, the selecting a plurality of insulation structures as the test piece in the first step further includes:
s103, establishing a finite element model of each heat insulation structure with different configurations, carrying out transient heat conduction finite element analysis on each heat insulation structure with different configurations, comparing the heat insulation performance of each heat insulation structure with different configurations, and selecting a plurality of heat insulation structures with higher heat insulation performance as test pieces.
Optionally, the step S101 of selecting a heat insulating material with high heat insulating efficiency specifically includes:
according to the formula
Selecting a heat insulation material with higher heat insulation efficiency;
where ρ is1The smaller the product of k and k, the higher the heat insulation efficiency of the heat insulation material;
m1is the mass of the insulation material, S is the area of the insulation material, ρ1Is the density of the heat insulating material, k is the heat conductivity of the heat insulating material, Δ T is the temperature difference of the heat insulating material, and q is the heat flow density of the heat insulating material.
Optionally, in step S102, according to the design requirement of the aircraft insulation structure, designing the selected insulation material into a plurality of insulation structures with different configurations specifically includes:
different configuration parameters are set, and one or more different configuration parameters exist among the different-configuration heat insulation structures.
Optionally, the configuration parameters include: wallboard materials, rib shapes, heat insulation material thickness and connection forms of the wallboard and the heat insulation materials.
Optionally, the insulation material comprises aerogel and high silica insulation cotton.
Optionally, the rib shape comprises a Z shape, a T shape, an L shape and an omega shape.
Optionally, the connection form of the wall plate and the heat insulation material comprises glue joint, mechanical connection and mixed connection.
The invention has at least the following beneficial technical effects:
the heat insulation efficiency characterization method of the heat insulation structure is a heat insulation structure efficiency comprehensively evaluating two factors of the heat insulation performance and the weight reduction effect of the heat insulation structure, can select the heat insulation structure with the optimal heat insulation efficiency, provides basis for the model selection and parameter selection design stages of the airplane heat insulation structure, can improve the design efficiency of the heat insulation structure, is easy to popularize, and has great practical value.
Drawings
FIG. 1 is a flow chart of a method of thermal insulation effectiveness characterization of the thermal insulation structure of the present application;
FIG. 2 is a schematic view of an insulation structure according to an embodiment of the present application.
Wherein:
1-heat insulating material; 2-wall plate; 3-ribs.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The present application is described in further detail below with reference to fig. 1-2.
The application provides a heat insulation efficiency characterization method of a heat insulation structure, which comprises the following steps:
the method comprises the following steps: selecting a plurality of heat insulation structures as test pieces;
step two: testing the heat insulation performance of the test pieces respectively to obtain the temperature T when the temperature of the cold surface temperature measuring point of each test piece reaches the steady state under the condition that the temperature of the hot surface is the samemaxAnd the time t taken to reach steady statemax；
Step three: calculating the density rho of each test piece, wherein rho is m/v, m is the mass of the test piece, and v is the volume of the test piece;
step four: selecting a test piece as a reference piece, wherein the density of the test piece is rho0The temperature at which steady state is reached is T0 maxAnd the time taken to reach steady state is t0 max；
Step five: and respectively calculating the heat insulation efficiency A of each test piece:
the method for characterizing the thermal insulation effectiveness of the thermal insulation structure further comprises the following steps:
step six: and selecting the test piece with the minimum heat insulation efficiency A value as the heat insulation structure of the airplane.
In one embodiment of the present application, the selecting a plurality of insulation structures as the test piece in the first step comprises:
s101, selecting a heat insulation material with high heat insulation efficiency;
s102, designing the selected heat insulation materials into a plurality of heat insulation structures with different configurations according to the design requirements of the heat insulation structure of the airplane;
s103, establishing a finite element model of each heat insulation structure with different configurations, carrying out transient heat conduction finite element analysis on each heat insulation structure with different configurations, comparing the heat insulation performance of each heat insulation structure with different configurations, and selecting a plurality of heat insulation structures with higher heat insulation performance as test pieces.
When selecting the heat insulating material having high heat insulating efficiency in step S101, two main considerations are to limit the heat flow and to reduce the weight. And (3) obtaining the relationship between the mass of the heat-insulating material and the density and the heat conductivity in unit area by combining Fourier theorem and a relational formula between the density and the mass, wherein the relationship comprises the following steps:
selecting a heat insulation material with higher heat insulation efficiency according to the formula; where ρ is1The smaller the product of k and k, the higher the heat insulation efficiency of the heat insulation material;
m1is the mass of the insulation material, S is the area of the insulation material, ρ1Is the density of the heat insulating material, k is the heat conductivity of the heat insulating material, Δ T is the temperature difference of the heat insulating material, and q is the heat flow density of the heat insulating material.
In this example, the insulation material includes two types, one is aerogel AIC-32AF-600, and one is high silica insulation cotton SF-15, and the thermal insulation effectiveness of the two materials is compared as shown in the following table.
Through calculation, rho is selected1Aerogel AIC-32AF-600 with a smaller product of k.
In step S102, according to the design requirements of the aircraft heat insulation structure, the selected heat insulation material is designed into a plurality of heat insulation structures with different configurations, specifically:
different configuration parameters are set, and one or more different configuration parameters exist among the heat insulation structures with different configurations.
The design requirements of the thermal insulation structure in the embodiment are as follows:
satisfy thermal-insulated structure height: less than 20 mm;
the heat insulation effect is satisfied: the heat insulation time is 3min, and the heat insulation temperature is 424 ℃→ 85 ℃;
the weight index is satisfied: less than 4 kg.
Wherein the configuration parameters comprise: wall board material, rib shape, heat insulation material thickness, connection form of the wall board and the heat insulation material and the like.
As shown in fig. 2, in one embodiment of the present application, two structural configurations are designed according to the design requirement and the actual load bearing condition of the structure, taking the stability of the wall plate 2 into consideration, and the aerogel is selected as the insulating material 1.
The first configuration is mainly that aerogel with the thickness of 5mm is added outside the ribs 3 with the height of 15mm, and the ribs 3 with different shapes can be selected, including Z-shaped, T-shaped, L-shaped and omega-shaped. The second is 20mm high ribs 3 externally plus 20mm thick aerogel. The connection form of the wall plate 2 and the heat insulating material 1 includes glue joint, mechanical connection, mixed connection and the like.
Further, a finite element model of each heat insulation structure configuration is established, ABAQUS is adopted to carry out transient heat conduction finite element calculation analysis of each configuration, and the heat insulation performance of each heat insulation structure configuration is compared preliminarily.
According to each heat insulation structure configuration scheme, a typical heat insulation structure test piece is designed and manufactured to carry out a heat insulation performance test, and the size of the test piece is 400mm multiplied by 400 mm. As the configuration with the best comprehensive heat insulation efficiency is preferably selected, the heat insulation performance of the heat insulation structure under two conditions of low temperature (100 ℃) and high temperature (424 ℃) is examined respectively, and the internal temperature of the heat insulation structure is examined in real time in the test process. Because the stable state can be achieved when the internal temperature of the heat insulation structure does not reach 85 ℃ at low temperature, the examination time is determined as 3 hours by referring to the flight time. When the temperature is high, the test can be stopped when the internal temperature of the heat insulation structure reaches 85 ℃.
After parameters of each test piece are obtained through tests, the heat insulation efficiency A of each test piece is calculated through a formula, and the test piece with the minimum heat insulation efficiency A value is selected as an airplane heat insulation structure.
The heat insulation efficiency characterization method of the heat insulation structure provides an effective heat insulation efficiency calculation method, can comprehensively evaluate the heat insulation performance of the heat insulation structure and the heat insulation structure efficiency of the weight reduction effect, can select the heat insulation structure with the optimal heat insulation efficiency, and provides a basis for the model selection and parameter selection design stages of the aircraft heat insulation structure.
This application is according to thermal-insulated demand of thermal-insulated structure, through carrying out thermal-insulated efficiency characterization to each thermal-insulated structure, selects the thermal-insulated structure that thermal-insulated efficiency is optimal, has realized the design purpose of thermal-insulated structure light weight efficient. Can improve the design efficiency of the heat insulation structure, is easy to popularize and has great practical value.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. A method for characterizing the thermal insulation efficiency of a thermal insulation structure is characterized by comprising the following steps:
the method comprises the following steps: selecting a plurality of heat insulation structures as test pieces;
step two: the heat insulation performance test is respectively carried out on a plurality of test pieces,obtaining the temperature T when the cold surface temperature measuring point of each test piece reaches the steady state under the condition that the hot surface temperature is the samemaxAnd the time t taken to reach steady statemax；
Step three: calculating the density rho of each test piece, wherein rho is m/v, m is the mass of the test piece, and v is the volume of the test piece;
step four: selecting a test piece as a reference piece, wherein the density of the test piece is rho0The temperature at which steady state is reached is T0 maxAnd the time taken to reach steady state is t0 max；
Step five: and respectively calculating the heat insulation efficiency A of each test piece:
2. the method for characterizing the insulating effectiveness of an insulating structure according to claim 1, further comprising:
step six: and selecting the test piece with the minimum heat insulation efficiency A value as the heat insulation structure of the airplane.
3. The method for characterizing the insulation effectiveness of an insulation structure according to claim 1, wherein the step one of selecting a plurality of insulation structures as test pieces comprises:
s101, selecting a heat insulation material with high heat insulation efficiency;
s102, designing the selected heat insulation materials into a plurality of heat insulation structures with different configurations according to the design requirements of the heat insulation structure of the airplane.
4. The method for characterizing the insulation effectiveness of an insulation structure according to claim 3, wherein the step of selecting a plurality of insulation structures as test pieces further comprises:
s103, establishing a finite element model of each heat insulation structure with different configurations, carrying out transient heat conduction finite element analysis on each heat insulation structure with different configurations, comparing the heat insulation performance of each heat insulation structure with different configurations, and selecting a plurality of heat insulation structures with higher heat insulation performance as test pieces.
5. The method for characterizing the heat insulation efficiency of the heat insulation structure according to claim 4, wherein the heat insulation material with higher heat insulation efficiency selected in step S101 is specifically:
according to the formula
Selecting a heat insulation material with higher heat insulation efficiency;
where ρ is1The smaller the product of k and k, the higher the heat insulation efficiency of the heat insulation material;
m1is the mass of the insulation material, S is the area of the insulation material, ρ1Is the density of the heat insulating material, k is the heat conductivity of the heat insulating material, Δ T is the temperature difference of the heat insulating material, and q is the heat flow density of the heat insulating material.
6. The method for characterizing the heat insulation efficiency of a heat insulation structure according to claim 5, wherein in step S102, the selected heat insulation material is designed into a plurality of heat insulation structures with different configurations according to the design requirements of the aircraft heat insulation structure, specifically:
different configuration parameters are set, and one or more different configuration parameters exist among the different-configuration heat insulation structures.
7. The method for characterizing the insulating effectiveness of an insulating structure according to claim 6, wherein the configuration parameters include: wallboard materials, rib shapes, heat insulation material thickness and connection forms of the wallboard and the heat insulation materials.
8. The method for characterizing the insulating effectiveness of an insulating structure according to claim 7, wherein the insulating material comprises aerogel and high silica insulating cotton.
9. The method of claim 7, wherein the ribs are Z-shaped, T-shaped, L-shaped, or Ω -shaped.
10. The method for characterizing the insulating effectiveness of an insulating structure according to claim 7, wherein the connection between the wall panels and the insulating material is a glue connection, a mechanical connection or a hybrid connection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811452672.0A CN109540962B (en) | 2018-11-30 | 2018-11-30 | Heat insulation efficiency characterization method of heat insulation structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811452672.0A CN109540962B (en) | 2018-11-30 | 2018-11-30 | Heat insulation efficiency characterization method of heat insulation structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109540962A CN109540962A (en) | 2019-03-29 |
| CN109540962B true CN109540962B (en) | 2021-07-09 |
Family
ID=65851458
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811452672.0A Active CN109540962B (en) | 2018-11-30 | 2018-11-30 | Heat insulation efficiency characterization method of heat insulation structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109540962B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110704946B (en) * | 2019-09-22 | 2023-04-07 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft cabin temperature calculation method |
| CN114813200B (en) * | 2022-07-01 | 2022-10-04 | 中国飞机强度研究所 | Device and method for measuring high-temperature characteristics of airplane component |
Citations (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7155377B2 (en) * | 2001-08-23 | 2006-12-26 | Wisconsin Alumni Research Foundation | Method and system for calculating the spatial-temporal effects of climate and other environmental conditions on animals |
| CN1900705A (en) * | 2006-07-12 | 2007-01-24 | 上海市房地产科学研究院 | In site detecting method for building wall heat transfer coefficient |
| WO2008081911A1 (en) * | 2007-01-05 | 2008-07-10 | Toyota Jidosha Kabushiki Kaisha | Heat insulation cell for fuel cell and method of producing the same |
| CN101302396A (en) * | 2008-06-27 | 2008-11-12 | 中材高新材料股份有限公司 | High temperature-resistant flame-retardant insulating paint and preparation thereof |
| CN101344384A (en) * | 2008-08-25 | 2009-01-14 | 苏州大学 | Depth detection method for steel surface hardening layer |
| CN101556256A (en) * | 2009-05-11 | 2009-10-14 | 天津科技大学 | Dual-flat plate thermal conductivity coefficient measuring instrument of thermal insulation materials |
| CN102199042A (en) * | 2011-03-28 | 2011-09-28 | 航天材料及工艺研究所 | Lightweight rigid ceramic heat-insulation tile and manufacture method thereof |
| CN102288641A (en) * | 2011-08-18 | 2011-12-21 | 中国飞机强度研究所 | Method for measuring high temperature thermal conductivity coefficient |
| RU2478936C1 (en) * | 2011-11-07 | 2013-04-10 | Федеральное государственное образовательное учреждение высшего профессионального образования "Казанский государственный архитектурно-строительный университет" КазГАСУ | Method of determining thermal conductivity coefficient of super-thin liquid heat-insulating coatings |
| CN106508022B (en) * | 2010-12-31 | 2014-09-10 | 上海机电工程研究所 | A kind of ablation thermal protection struc ture Analysis of Three-Dimensional Temperature computational methods |
| CN104215658A (en) * | 2014-08-20 | 2014-12-17 | 中国科学院力学研究所 | High-temperature heat conduction calibration method and high-temperature heat conduction calibration device |
| CN104267062A (en) * | 2014-10-22 | 2015-01-07 | 北京航空航天大学 | Method for converting cold wall heat flux into hot wall heat flux in aerodynamic heat simulating test |
| CN106971015A (en) * | 2016-01-13 | 2017-07-21 | 南京航空航天大学 | A kind of re-entry space vehicle thermal protection system is quickly analyzed and design method |
| CN207045657U (en) * | 2017-08-08 | 2018-02-27 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of heat structure with thermal protection function |
| CN108009336A (en) * | 2017-11-28 | 2018-05-08 | 北京航空航天大学 | A kind of micro- truss structure carrying and the Multipurpose Optimal Method of thermal protection structure |
| CN108052711A (en) * | 2017-11-29 | 2018-05-18 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of coupled thermal mechanical method of parallel combination engine installation structure |
| CN108088869A (en) * | 2017-11-30 | 2018-05-29 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of thermal protection system Heat-Insulation Test device |
| CN108116002A (en) * | 2017-12-07 | 2018-06-05 | 航天特种材料及工艺技术研究所 | A kind of sandwich thermally protective materials and its manufacturing method with high slab strength |
| CN108333215A (en) * | 2017-11-15 | 2018-07-27 | 北京空天技术研究所 | A kind of analysis of thermal conductivity method of aerogel heat-proof layer in integral type T PS |
| CN108610086A (en) * | 2018-06-01 | 2018-10-02 | 哈尔滨工业大学 | A kind of preparation method of three-dimensional network shape porous fibre matter heat-barrier material |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103091189B (en) * | 2013-01-10 | 2014-09-24 | 湘潭大学 | Tester for simulating service environment of thermal barrier coating and detecting failure of thermal barrier coating in real time |
| CN105702641B (en) * | 2016-03-18 | 2018-06-26 | 中国科学院长春光学精密机械与物理研究所 | The variable high power device radiator of spacecraft |
| CN105972854B (en) * | 2016-07-06 | 2018-04-20 | 福州幻科机电科技有限公司 | A kind of one side is heated the self cooling plate in the back side and its manufacture method |
-
2018
- 2018-11-30 CN CN201811452672.0A patent/CN109540962B/en active Active
Patent Citations (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7155377B2 (en) * | 2001-08-23 | 2006-12-26 | Wisconsin Alumni Research Foundation | Method and system for calculating the spatial-temporal effects of climate and other environmental conditions on animals |
| CN1900705A (en) * | 2006-07-12 | 2007-01-24 | 上海市房地产科学研究院 | In site detecting method for building wall heat transfer coefficient |
| WO2008081911A1 (en) * | 2007-01-05 | 2008-07-10 | Toyota Jidosha Kabushiki Kaisha | Heat insulation cell for fuel cell and method of producing the same |
| CN101302396A (en) * | 2008-06-27 | 2008-11-12 | 中材高新材料股份有限公司 | High temperature-resistant flame-retardant insulating paint and preparation thereof |
| CN101344384A (en) * | 2008-08-25 | 2009-01-14 | 苏州大学 | Depth detection method for steel surface hardening layer |
| CN101556256A (en) * | 2009-05-11 | 2009-10-14 | 天津科技大学 | Dual-flat plate thermal conductivity coefficient measuring instrument of thermal insulation materials |
| CN106508022B (en) * | 2010-12-31 | 2014-09-10 | 上海机电工程研究所 | A kind of ablation thermal protection struc ture Analysis of Three-Dimensional Temperature computational methods |
| CN102199042A (en) * | 2011-03-28 | 2011-09-28 | 航天材料及工艺研究所 | Lightweight rigid ceramic heat-insulation tile and manufacture method thereof |
| CN102288641A (en) * | 2011-08-18 | 2011-12-21 | 中国飞机强度研究所 | Method for measuring high temperature thermal conductivity coefficient |
| RU2478936C1 (en) * | 2011-11-07 | 2013-04-10 | Федеральное государственное образовательное учреждение высшего профессионального образования "Казанский государственный архитектурно-строительный университет" КазГАСУ | Method of determining thermal conductivity coefficient of super-thin liquid heat-insulating coatings |
| CN104215658A (en) * | 2014-08-20 | 2014-12-17 | 中国科学院力学研究所 | High-temperature heat conduction calibration method and high-temperature heat conduction calibration device |
| CN104267062A (en) * | 2014-10-22 | 2015-01-07 | 北京航空航天大学 | Method for converting cold wall heat flux into hot wall heat flux in aerodynamic heat simulating test |
| CN106971015A (en) * | 2016-01-13 | 2017-07-21 | 南京航空航天大学 | A kind of re-entry space vehicle thermal protection system is quickly analyzed and design method |
| CN207045657U (en) * | 2017-08-08 | 2018-02-27 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of heat structure with thermal protection function |
| CN108333215A (en) * | 2017-11-15 | 2018-07-27 | 北京空天技术研究所 | A kind of analysis of thermal conductivity method of aerogel heat-proof layer in integral type T PS |
| CN108009336A (en) * | 2017-11-28 | 2018-05-08 | 北京航空航天大学 | A kind of micro- truss structure carrying and the Multipurpose Optimal Method of thermal protection structure |
| CN108052711A (en) * | 2017-11-29 | 2018-05-18 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of coupled thermal mechanical method of parallel combination engine installation structure |
| CN108088869A (en) * | 2017-11-30 | 2018-05-29 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of thermal protection system Heat-Insulation Test device |
| CN108116002A (en) * | 2017-12-07 | 2018-06-05 | 航天特种材料及工艺技术研究所 | A kind of sandwich thermally protective materials and its manufacturing method with high slab strength |
| CN108610086A (en) * | 2018-06-01 | 2018-10-02 | 哈尔滨工业大学 | A kind of preparation method of three-dimensional network shape porous fibre matter heat-barrier material |
Non-Patent Citations (3)
| Title |
|---|
| Expermental study on heat insulation performance of functionally graded metal/ceramic coatings and their fracture behavior at high surface temperatures;Hua Ping Xiong 等;《SCIENCE @ DIRECT》;20040911;第194卷;203-214 * |
| 航天飞机防热结构温度场的数值计算研究;耿为群 等;《空气动力学报》;19920930;第10卷(第3期);367-372 * |
| 飞机隔热结构热桥效应分析与实验;夏甜 等;《航空材料学报》;20170331;第37卷(第3期);91-96 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109540962A (en) | 2019-03-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109540962B (en) | Heat insulation efficiency characterization method of heat insulation structure | |
| Zhang et al. | Avoiding thermal runaway propagation of lithium-ion battery modules by using hybrid phase change material and liquid cooling | |
| Yu et al. | Thermal analysis and two-directional air flow thermal management for lithium-ion battery pack | |
| Zhang et al. | A novel hybrid battery thermal management system with fins added on and between liquid cooling channels in composite phase change materials | |
| CN104925269B (en) | The assay device of a kind of high hypervelocity aircraft cabin section thermal environment and method | |
| CN102152902B (en) | Composite vacuum heat preservation box for energy storage sodium sulfur battery module | |
| CN103488850A (en) | Method for positioning and homogenizing residual stress of thermal shock compounding | |
| CN204575355U (en) | A kind of vacuum simulation test device with reduction of blood pressure in high-speed and explosive decompression function | |
| Palladino et al. | Preliminary studies of a regional aircraft with hydrogen-based hybrid propulsion | |
| CN111487136A (en) | Aluminum honeycomb panel rigidity testing arrangement based on external environment simulation | |
| Mahek et al. | Effects of control volume outlet variation on axial air cooling of lithium-ion batteries | |
| Lyu et al. | Enclosed aisle effect on cooling efficiency in small scale data center | |
| Gao et al. | Research on regeneration characteristics of diesel particulate filter based on fluid-thermal-solid coupling | |
| CN102661972B (en) | measurement method of heat insulating property of gas turbine heat shield | |
| CN110972561B (en) | Calculation method for realizing optimization of thickness of thermal insulation layer of fuel compartment of high-speed aircraft | |
| Chen et al. | Heat transfer characteristics of straw-core paper honeycomb plates (beetle elytron plates) I: Experimental study on horizontal placement with hot-above and cold-below conditions | |
| CN113148108A (en) | Double-layer corrugated sandwich heat-insulation/bearing integrated heat protection structure | |
| WO2014007681A1 (en) | Environmental testing apparatus and method for using same (variants) | |
| Zhu et al. | Coupling simulation of the cooling air duct and the battery pack in battery energy storage systems | |
| Li et al. | Experimental study on ventilation and thermal performance of exterior sandwich wall based on hot box method | |
| CN116244921A (en) | Building external wall insulation material thickness optimization method based on full life cycle | |
| CN108536913A (en) | Water film type packing cools down number simplified calculation method | |
| CN107738755A (en) | It is a kind of to adapt to efficiently main passive heat management system and its design method that the world comes and goes | |
| Niu et al. | Model study of relationship between local temperature and artificial heat release | |
| Chen et al. | Evaluation model of energy-economy-environment (3E) system coordinating degree: empirical analysis on china regionally |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |