CN109540962A - A kind of heat-insulated efficiency characterizing method of heat insulation structural - Google Patents
A kind of heat-insulated efficiency characterizing method of heat insulation structural Download PDFInfo
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Abstract
The application belongs to aircaft configuration the field of test technology, the in particular to heat-insulated efficiency characterizing method of a kind of heat insulation structural.Include: step 1: choosing multiple heat insulation structurals as testpieces；Step 2: being thermally shielded performance test to multiple testpieces respectively, obtains the huyashi-chuuka (cold chinese-style noodles) temperature measuring point of each testpieces in the identical situation of hot-face temperature, reaches temperature T when stable statemaxAnd reach time t used in stable statemax；Step 3: the density p of each testpieces, ρ=m/v are calculated, wherein m is testpieces quality, and v is testpieces volume；Step 4: a testpieces is chosen as standard, the density of the testpieces is ρ0, temperature when reaching stable state is T0 maxAnd reach the time used in stable state for t0 max；Step 5: the heat-insulated efficiency A of each testpieces is calculated separately.The application can preferably go out the optimal heat insulation structural of heat-insulated efficiency, realize the purpose of design of heat insulation structural efficient and light weight, heat insulation structural design efficiency can be improved, easy to spread, have biggish practical value.
Description
Technical field
The application belongs to aircaft configuration the field of test technology, the in particular to heat-insulated efficiency characterization side of a kind of heat insulation structural
Method.
Background technique
Airplane structural parts positioned at high-temperature region, such as close to the equipment compartment of engine, since component outer temperature is higher,
For the function of realizing its internal unit, corresponding heat-insulated demand is proposed.Traditional aircraft heat insulation structural is all made of in inside configuration
Increase heat-barrier material to realize heat insulating function, i.e., is directly glued large area heat-barrier material when siding inside, design usually only
The heat-proof quality of heat insulation structural is considered, often ignores large area heat-barrier material and increases weight to aircaft configuration bring.Therefore it is badly in need of
It is a kind of can with the heat insulation structural efficiency characterizing method of the two factors of overall merit heat insulation structural heat-proof quality and weight loss effect, from
And design the heat insulation structural of efficient and light weight.
Thus, it is desirable to have a kind of technical solution overcomes or at least mitigates at least one drawbacks described above of the prior art.
Summary of the invention
There is provided a kind of heat-insulated efficiency characterizing methods of heat insulation structural for the purpose of the application, to solve prior art presence
At least one problem.
The technical solution of the application is:
A kind of heat-insulated efficiency characterizing method of heat insulation structural, comprising the following steps:
Step 1: multiple heat insulation structurals are chosen as testpieces；
Step 2: being thermally shielded performance test to multiple testpieces respectively, and the huyashi-chuuka (cold chinese-style noodles) temperature measuring point for obtaining each testpieces exists
In the identical situation of hot-face temperature, reach temperature T when stable statemaxAnd reach time t used in stable statemax；
Step 3: the density p of each testpieces, ρ=m/v are calculated, wherein m is testpieces quality, and v is testpieces volume；
Step 4: a testpieces is chosen as standard, the density of the testpieces is ρ0, temperature when reaching stable state is
T0 maxAnd reach the time used in stable state for t0 max；
Step 5: the heat-insulated efficiency A of each testpieces is calculated separately:
Optionally, further includes:
Step 6: the heat-insulated the smallest testpieces of efficiency A value is chosen as aircraft heat insulation structural.
Optionally, multiple heat insulation structurals are chosen in step 1 as testpieces includes:
S101, the higher heat-barrier material of heat-insulating efficiency is chosen；
S102, according to aircraft heat insulation structural design requirement, by the heat-barrier material of selection be designed to multiple and different configurations every
Heat structure.
Optionally, multiple heat insulation structurals are chosen in step 1 as testpieces further include:
S103, establish each various configuration heat insulation structural finite element model, to the heat insulation structural of each various configuration
Transient heat conduction finite element analysis is carried out, the heat-proof quality of the heat insulation structural of each various configuration is compared, chooses multiple thermal insulations
The higher heat insulation structural of energy is as testpieces.
Optionally, the higher heat-barrier material of heat-insulating efficiency is chosen in step S101 specifically:
According to formula
Choose the higher heat-barrier material of heat-insulating efficiency；
Wherein, ρ1Smaller with the product of k, the heat-insulating efficiency of heat-barrier material is higher；
m1For the quality of heat-barrier material, S is the area of heat-barrier material, ρ1For the density of heat-barrier material, k is heat-barrier material
Thermal conductivity, △ T are the temperature difference of heat-barrier material, and q is the heat flow density of heat-barrier material.
Optionally, the heat-barrier material of selection is designed to multiple in step S102 according to aircraft heat insulation structural design requirement
The heat insulation structural of various configuration specifically:
Different structure parameters are set, there are one or more different configurations between the heat insulation structural of the various configuration
Parameter.
Optionally, the structure parameters include: siding material, rib shape, heat-barrier material thickness, siding and heat-barrier material
Type of attachment.
Optionally, the heat-barrier material includes aeroge and high silicon oxygen heat insulation foam.
Optionally, the rib shape includes Z-type, T-type, L-type, Ω type.
Optionally, the type of attachment of the siding and heat-barrier material includes being glued, being mechanically connected, Hybrid connections.
At least there are following advantageous effects in invention:
The heat-insulated efficiency characterizing method of the heat insulation structural of the application, be a kind of overall merit heat insulation structural heat-proof quality and
The heat insulation structural efficiency of the two factors of weight loss effect can select the optimal heat insulation structural of heat-insulated efficiency, be the heat-insulated knot of aircraft
The type selecting of structure, choosing ginseng design phase provide foundation, and heat insulation structural design efficiency can be improved, easy to spread, have biggish practical
Value.
Detailed description of the invention
Fig. 1 is the flow chart of the heat-insulated efficiency characterizing method of the heat insulation structural of the application；
Fig. 2 is the heat insulation structural schematic diagram of one embodiment of the application.
Wherein:
1- heat-barrier material；2- siding；3- rib.
Specific embodiment
To keep the purposes, technical schemes and advantages of the application implementation clearer, below in conjunction in the embodiment of the present application
Attached drawing, technical solutions in the embodiments of the present application is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the application
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
In explanation the application, and it should not be understood as the limitation to the application.Based on the embodiment in the application, ordinary skill people
Member's every other embodiment obtained without creative efforts, shall fall in the protection scope of this application.Under
Face is described in detail embodiments herein in conjunction with attached drawing.
In the description of the present application, it is to be understood that term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown is merely for convenience of description the application and simplifies description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the application
The limitation of range.
1 to Fig. 2 the application is described in further details with reference to the accompanying drawing.
This application provides a kind of heat-insulated efficiency characterizing methods of heat insulation structural, comprising:
Step 1: multiple heat insulation structurals are chosen as testpieces；
Step 2: being thermally shielded performance test to multiple testpieces respectively, and the huyashi-chuuka (cold chinese-style noodles) temperature measuring point for obtaining each testpieces exists
In the identical situation of hot-face temperature, reach temperature T when stable statemaxAnd reach time t used in stable statemax；
Step 3: the density p of each testpieces, ρ=m/v are calculated, wherein m is testpieces quality, and v is testpieces volume；
Step 4: a testpieces is chosen as standard, the density of the testpieces is ρ0, temperature when reaching stable state is
T0 maxAnd reach the time used in stable state for t0 max；
Step 5: the heat-insulated efficiency A of each testpieces is calculated separately:
The heat-insulated efficiency characterizing method of the heat insulation structural of the application further include:
Step 6: the heat-insulated the smallest testpieces of efficiency A value is chosen as aircraft heat insulation structural.
In the embodiment of the application, multiple heat insulation structurals are chosen in step 1 as testpieces includes:
S101, the higher heat-barrier material of heat-insulating efficiency is chosen；
S102, according to aircraft heat insulation structural design requirement, by the heat-barrier material of selection be designed to multiple and different configurations every
Heat structure；
S103, establish each various configuration heat insulation structural finite element model, to the heat insulation structural of each various configuration
Transient heat conduction finite element analysis is carried out, the heat-proof quality of the heat insulation structural of each various configuration is compared, chooses multiple thermal insulations
The higher heat insulation structural of energy is as testpieces.
Main to consider two aspects when choosing the higher heat-barrier material of heat-insulating efficiency in step s101, one is limitation
Hot-fluid, the other is loss of weight problem.Simultaneous Fourier's therorem and density, relationship between quality formula, obtain heat-insulated material on unit area
Expect the relationship of quality and density and thermal conductivity, as follows:
The higher heat-barrier material of heat-insulating efficiency is chosen according to above formula；Wherein, ρ1It is smaller with the product of k, heat-barrier material every
The thermal efficiency is higher；
m1For the quality of heat-barrier material, S is the area of heat-barrier material, ρ1For the density of heat-barrier material, k is heat-barrier material
Thermal conductivity, △ T are the temperature difference of heat-barrier material, and q is the heat flow density of heat-barrier material.
In the present embodiment, heat-barrier material includes two kinds, and one is aeroge AIC-32AF-600, and one is high silicon oxygen is heat-insulated
Cotton SF-15, the heat-insulated efficiency of two kinds of materials relatively see the table below.
By calculating, ρ is selected1With the lesser aeroge AIC-32AF-600 of product of k.
According to aircraft heat insulation structural design requirement in step S102, the heat-barrier material of selection is designed to multiple and different configurations
Heat insulation structural specifically:
Different structure parameters are set, there are one or more different configuration ginsengs between the heat insulation structural of various configuration
Number.
The design requirement of heat insulation structural is as follows in the present embodiment:
Meet heat insulation structural height: lower than 20mm；
Meet heat insulation: a length of 3min when heat-insulated, adiabatic temperature are 424 DEG C → 85 DEG C；
Meet weight indicator: less than 4kg.
Wherein structure parameters include: the connection of siding material, rib shape, heat-barrier material thickness, siding and heat-barrier material
Form etc..
As shown in Fig. 2, according to design requirement and structure actual bearer situation, being examined in the embodiment of the application
Consider 2 stability of siding, heat-barrier material 1 selects aeroge, devises two kinds of structural configuration schemes altogether.
The first configuration is can choose muscle of different shapes outside the rib 3 of 15mm high plus based on the aeroge of 5mm
Item 3, including Z-type, T-type, L-type, Ω type.It is for second outside the rib 3 of 20mm high plus the aeroge of 20mm thickness.Wherein siding 2
Type of attachment with heat-barrier material 1 includes splicing, mechanical connection, Hybrid connections etc..
Further, the finite element model for then establishing each heat insulation structural configuration carries out each configuration using ABAQUS
Transient heat conduction finite element method (fem) analysis, and the heat-proof quality of each heat insulation structural configuration of preliminary comparison.
According to each heat insulation structural configuration scheme, designs and produces representative heat structural test part and is thermally shielded performance test,
Testpieces is having a size of 400mm × 400mm.Due to preferably to go out the best configuration of comprehensive heat-insulated efficiency, heat insulation structural is examined respectively
Heat-proof quality in low temperature (100 DEG C) and two kinds of high temperature (424 DEG C) is examined inside heat insulation structural in real time during test
Temperature.When due to low temperature, heat insulation structural internal temperature can reach stable state when being not up to 85 DEG C, so when examination time reference flight
It is long, it is determined as 3 hours.When high temperature, heat insulation structural internal temperature, which reaches 85 DEG C, can stop testing.
After test obtains the parameter of each testpieces, the heat-insulated efficiency A of each testpieces is calculated by formula, is chosen heat-insulated
The smallest testpieces of efficiency A value is as aircraft heat insulation structural.
The heat-insulated efficiency characterizing method of the heat insulation structural of the application provides a kind of effective heat-insulated efficiency calculating method,
It is capable of the heat insulation structural efficiency of the two factors of the heat-proof quality and weight loss effect of overall merit heat insulation structural, can selects heat-insulated
The optimal heat insulation structural of efficiency provides foundation for the type selecting of aircraft heat insulation structural, choosing ginseng design phase.
Heat-insulated demand of the application according to heat insulation structural is preferably gone out by being thermally shielded efficiency characterization to each heat insulation structural
The optimal heat insulation structural of heat-insulated efficiency, realizes the purpose of design of heat insulation structural efficient and light weight.Heat insulation structural design effect can be improved
Rate, it is easy to spread, there is biggish practical value.
The above, the only specific embodiment of the application, but the protection scope of the application is not limited thereto, it is any
Within the technical scope of the present application, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
Cover within the scope of protection of this application.Therefore, the protection scope of the application should be with the scope of protection of the claims
It is quasi-.
Claims (10)
1. a kind of heat-insulated efficiency characterizing method of heat insulation structural, which comprises the following steps:
Step 1: multiple heat insulation structurals are chosen as testpieces；
Step 2: being thermally shielded performance test to multiple testpieces respectively, obtains the huyashi-chuuka (cold chinese-style noodles) temperature measuring point of each testpieces in hot face
In the identical situation of temperature, reach temperature T when stable statemaxAnd reach time t used in stable statemax；
Step 3: the density p of each testpieces, ρ=m/v are calculated, wherein m is testpieces quality, and v is testpieces volume；
Step 4: a testpieces is chosen as standard, the density of the testpieces is ρ0, temperature when reaching stable state is T0 max
And reach the time used in stable state for t0 max；
Step 5: the heat-insulated efficiency A of each testpieces is calculated separately:
2. the heat-insulated efficiency characterizing method of heat insulation structural according to claim 1, which is characterized in that further include:
Step 6: the heat-insulated the smallest testpieces of efficiency A value is chosen as aircraft heat insulation structural.
3. the heat-insulated efficiency characterizing method of heat insulation structural according to claim 1, which is characterized in that chosen in step 1 more
A heat insulation structural includes: as testpieces
S101, the higher heat-barrier material of heat-insulating efficiency is chosen；
S102, according to aircraft heat insulation structural design requirement, the heat-barrier material of selection is designed to the heat-insulated knot of multiple and different configurations
Structure.
4. the heat-insulated efficiency characterizing method of heat insulation structural according to claim 3, which is characterized in that chosen in step 1 more
A heat insulation structural is as testpieces further include:
S103, establish each various configuration heat insulation structural finite element model, the heat insulation structural of each various configuration is carried out
Transient heat conduction finite element analysis compares the heat-proof quality of the heat insulation structural of each various configuration, choose multiple heat-proof qualities compared with
High heat insulation structural is as testpieces.
5. the heat-insulated efficiency characterizing method of heat insulation structural according to claim 4, which is characterized in that chosen in step S101
The higher heat-barrier material of heat-insulating efficiency specifically:
According to formula
Choose the higher heat-barrier material of heat-insulating efficiency；
Wherein, ρ1Smaller with the product of k, the heat-insulating efficiency of heat-barrier material is higher；
m1For the quality of heat-barrier material, S is the area of heat-barrier material, ρ1For the density of heat-barrier material, k is the thermal conductivity of heat-barrier material
Rate, △ T are the temperature difference of heat-barrier material, and q is the heat flow density of heat-barrier material.
6. the heat-insulated efficiency characterizing method of heat insulation structural according to claim 5, which is characterized in that basis in step S102
The heat-barrier material of selection, is designed to the heat insulation structural of multiple and different configurations by aircraft heat insulation structural design requirement specifically:
Different structure parameters are set, there are one or more different configuration ginsengs between the heat insulation structural of the various configuration
Number.
7. the heat-insulated efficiency characterizing method of heat insulation structural according to claim 6, which is characterized in that the structure parameters packet
It includes: siding material, rib shape, the type of attachment of heat-barrier material thickness, siding and heat-barrier material.
8. the heat-insulated efficiency characterizing method of heat insulation structural according to claim 7, which is characterized in that the heat-barrier material packet
Include aeroge and high silicon oxygen heat insulation foam.
9. the heat-insulated efficiency characterizing method of heat insulation structural according to claim 7, which is characterized in that the rib shape packet
Include Z-type, T-type, L-type, Ω type.
10. the heat-insulated efficiency characterizing method of heat insulation structural according to claim 7, which is characterized in that the siding with every
The type of attachment of hot material includes being glued, being mechanically connected, Hybrid connections.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110704946A (en) * | 2019-09-22 | 2020-01-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft cabin temperature calculation method |
| CN114813200A (en) * | 2022-07-01 | 2022-07-29 | 中国飞机强度研究所 | Device and method for measuring high-temperature characteristics of airplane component |
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| CN109540962B (en) | 2021-07-09 |
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