CN104267062A - Method for converting cold wall heat flux into hot wall heat flux in aerodynamic heat simulating test - Google Patents
Method for converting cold wall heat flux into hot wall heat flux in aerodynamic heat simulating test Download PDFInfo
- Publication number
- CN104267062A CN104267062A CN201410568947.2A CN201410568947A CN104267062A CN 104267062 A CN104267062 A CN 104267062A CN 201410568947 A CN201410568947 A CN 201410568947A CN 104267062 A CN104267062 A CN 104267062A
- Authority
- CN
- China
- Prior art keywords
- hot
- sheet metal
- fluid
- temperature
- heat flux
- 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.)
- Granted
Links
Abstract
The invention provides a method for converting cold wall heat flux into hot wall heat flux in an aerodynamic heat simulating test. The method comprises the following steps: firstly, calculating a temperature change curve for the surface of a thin metal plate according to a cold wall heat flux boundary condition; secondly, heating the thin metal plate test piece according to the calculated temperature curve, and recording a hot wall heat flux curve for the surface of a heat flux sensor in the same plane of the thin metal plate under the temperature condition, namely by a combined method of theoretical calculation and an experimental test, finally obtaining a hot wall heat flux boundary condition which corresponds to the cold wall heat flux boundary condition and is difficultly determined by a computer. The invention provides a practicable hot wall heat flux determining method for a radiant aerodynamic heat simulating test on a high-speed aircraft.
Description
Technical field
The present invention relates to cold wall hot-fluid in a kind of Aerodynamic Heating simulation test and be converted to the method for hot wall hot-fluid, belong to high-speed aircraft aerothermodynamics experiment field.Particularly when using the Aerodynamic Heating environment of the high-speed aircrafts such as radiation mode simulated missile, the cold wall hot-fluid boundary condition obtained by theory calculate is converted to the hot wall hot-fluid boundary condition needed for reality.
Background technology
The aircraft such as guided missile, high-speed aircraft will there will be very serious " thermal boundary " problem when High Mach number flies.Can up to 1.2Mw/m with the transient heat flow density in the antenna house tapering, front end of the hypersonic aircraft of 6 Mach number
2, stagnation temperature will more than 1200 DEG C.When space shuttle gets through the earth's atmosphere, the temperature in most of region such as its body, wing, vertical fin is between 750 DEG C ~ 1450 DEG C, and the positions such as inner cone end and air intake duct even there will be the district of localized hyperthermia close to 1800 DEG C.So exceedingly odious high-temperature hot environmental baseline, make the thermal protection of high velocity of sound aircraft material and structure and hot strength problem become concerning development success or failure key issue.This is because the high temperature that Aerodynamic Heating serious during high-speed flight produces, significantly can reduce the strength degree of hypersonic aircraft material and the load-bearing capacity of Flight Vehicle Structure, make structure produce thermal deformation, destroy the aerodynamic configuration of parts and affect the security performance of Flight Vehicle Structure.For ensureing the safety of high-speed aircraft, confirming the thermal ablation that the materials and structures of aircraft produces when whether can stand high-speed flight and high-temperature hot stress rupture, Aerodynamic Heating simulation test must be carried out to high-speed aircraft materials and structures.The heating status of simulated flight materials and structures when high-speed flight, observation analysis is the mechanical property of material and the force-bearing situation of structure under thermal environment and mechanical environment effect, thus research and analyse structure load-bearing capacity at high temperature further, this work has very important meaning for the thermal protection of the aircraft such as guided missile, high-speed aircraft and safe design.
When carrying out radiant type heat test, the mode of simulation heating environment is divided into hot-fluid boundary condition simulation and temperature boundary to simulate two kinds of modes.For the structure of surface with ablative heat shield protecting, produce physics or the chemical changes such as burning, gasification, decomposition, stripping due to heating process floating coat, surface temperature is difficult to Measurement accuracy; Nonmetallic materials are owing to being subject to the impact of material behavior and the factor such as surface state and sensor installation in addition, and the reliable and stable measurement of its surface temperature is also very difficult.Therefore often can not adopt temperature boundary analog form for ablator and nonmetallic materials, but need to adopt hot-fluid boundary condition simulation mode to carry out Aerodynamic Heating simulation test.
When calculating outer wall heat-flux conditions, outer wall surface temperature constantly can change along with the change of heat time, is formed so-called " hot wall ".And the uncertain hot wall boundary condition of this continuous change, make the calculating of hot wall hot-fluid become very difficult.Therefore in calculation of aerodynamic heating, often take simplified way, namely suppose that Coated Surface Temperature is constant at initial temperature constant, and the heat flow density calculated under this kind of assumed condition is referred to as " cold wall " hot-fluid.Although carry out heat test according to the cold wall hot-fluid calculated not meet actual conditions, but when being difficult to measurements and calculations surface temperature, from the angle of the thermal protective performance or inspection coating process quality of studying or screen heat insulation material and structure, there is certain reference function (list of references: Zhang Yu, thermo-structural experiment technology [M], Yuhang Publishing House, 1993,28-29).
And carry out with radiation mode Aerodynamic Heating simulation test time, what obtain due to the heat resistance heat flow meter used in Measurement & Control process is hot wall hot-fluid, and cold wall hot-fluid has no idea to be obtained by test measurement in radiant type aerothermodynamics experiment.Therefore, when simulating pneumatic thermal environment, the cold wall hot-fluid boundary condition calculated must be converted to hot wall hot-fluid boundary condition.And then the thermal environmental test carried out based on hot wall hot-fluid boundary condition, before the test or the work converting cold wall hot-fluid to hot wall hot-fluid in process of the test extremely important, and implement very difficult.
Someone proposed in heat test process, first input cold wall heat flow data, the wall surface temperature obtained according to measurement again converts the method (list of references: Wang Zhiyong of hot wall hot-fluid in real time to, huge sub-hall, Huang Shiyong. cold wall hot-fluid boundary condition simulation technique study [J] in thermo-structural experiment. Spacecraft Environment Engineering, 2008,25 (1): 33-35).But there is conflicting problem in the method because will in transfer process measured surface temperature, and by its corrected Calculation value.And when determining originally to adopt hot-fluid boundary condition simulation environment, exactly because the temperature on ablation test part or nonmetallic materials testpieces surface is difficult to Measurement accuracy in heating process.Can not the boundary temperature data of Measurement accuracy go the method revising cold wall heat flow data feasible if use now, just the method for direct serviceability temperature measurement can test originally, and hot-fluid mode need not be used to test.Adopt inaccurate temperature data to go to revise cold wall heat flow data in addition, accuracy and the reliability of its result all have problems.
Although said method has certain problem, also illustrate that the necessity and the difficulty that in aerothermodynamics experiment simulation, cold wall hot-fluid boundary condition are converted to hot wall hot-fluid boundary condition.And the work cold wall hot-fluid being converted to hot wall hot-fluid has important using value for high-speed aircraft Aerodynamic Heating simulation test.
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome the deficiencies in the prior art, cold wall hot-fluid in a kind of Aerodynamic Heating simulation test is provided to be converted to the method for hot wall hot-fluid, when using the Aerodynamic Heating environment of the high-speed aircrafts such as radiation mode simulated missile, the cold wall hot-fluid obtained by theory calculate is converted to the hot wall hot-fluid needed for reality in radiation heating test, for high-speed aircraft ground pneumatic thermal modeling test provides a kind of thermal environment boundary condition defining method of practicality.
Technical solution of the present invention is: in a kind of Aerodynamic Heating simulation test, cold wall hot-fluid is converted to the method for hot wall hot-fluid, it is characterized in that measuring with test the method combined by theory calculate, cold wall hot-fluid boundary condition is converted to the hot wall hot-fluid boundary condition needed for reality in radiation heating test, its concrete steps are as follows:
Step a: determine the material of experimental test sheet metal, planar dimension and thickness.
Because in high-temperature hot test, hot-fluid and temperature have correlativity, generally the surface temperature of the large generation of hot-fluid is also high, some sheet metal very easily produces buckling deformation after being subject to high temperature, therefore need the material of the refractory metal thin plate according to maximum hot-fluid scope determination experimental test, and can be within usable range by the deformation condition of verification experimental verification sheet metal; Deflection after the sheet metal that planar dimension is larger is heated is often larger, and therefore the planar dimension of sheet metal can not be excessive, but planar dimension can not select too little, otherwise three-dismensional effect can become very large; If the thickness of sheet metal is excessive in addition, the appearance of the heat of sheet metal is made to become very large, slow for the reaction time of fast-changing hot-fluid environment during heating, obvious thermal hysteresis can be produced.Therefore must consider the material of sheet metal, the relation between planar dimension and thickness, rational sheet metal is surveyed in choosing, and is added their confirmation by test.
In described step a, sheet metal material is Ni-based stainless steel 1Cr18Ni9Ti, and its fusing point is about 1450 DEG C, has high temperature resistant, the feature that non-deformability is strong; Plate thickness is taken between 1.0mm-2.0mm, because the very thin thermal response speed of thickness of slab is very fast, the length of side of the planar dimension of sheet metal is 100mm-120mm, the ratio of its length of side and thickness is between 60:1 to 120:1, due to wide, thickness rate is very large, can become two-dimensional plane state by sufficient approximation, the impact of the three-dismensional effect of this big flakiness ratio thin plate boundary can be ignored.
Step b: the temperature variation curve calculating metal sheet surface according to cold wall heat flow meter.
If cold wall hot-fluid acts on sheet metal heating surface, first determine the initial temperature condition of sheet metal and the boundary condition such as the convection heat transfer between radiating surface and external environment condition and radiation heat transfer, then according to the cold wall hot-fluid-time changing curve of heating surface, the Temperature-time change curve being solved sheet metal front surface by the Unsteady Heat Transfer differential equation.
Step c: according to said temperature curve establishment thermal environmental test control program.
Both by being calculated " Temperature-time " data of metal sheet surface by cold wall heat flow meter stored in computing machine, as the preset value of control program.
Steps d: according to the temperature curve calculated, heating is controlled to sheet metal.
The sheet metal testpieces identical with the material in computation process, planar dimension and thickness is adopted to carry out heat test, the closed-loop control system that heat test system is made up of parts such as quartz lamp infrared radiation array, temperature sensor, signal amplifier, A/D converter, computing machine, D/A number converter, controllable silicon regulators.The front surface of sheet metal is welded with thermocouple sensor, thermal control system is measured showing temperature before sheet metal, the temperature data measured in real time using thermocouple sensor is as value of feedback, compare to the temperature preset value in above-mentioned corresponding moment of calculating, the departure obtained provides regulating and controlling amount after machine computing as calculated, the operating voltage on quartz lamp infrared radiator is changed, " Temperature-time " thermal environment of trace simulation metal sheet surface by controllable silicon regulator.Sheet metal is in distance quartz lamp infrared radiation heating array 50-70mm part.
Step e: in sheet metal heating process, record the hot wall hot-fluid arriving wooden partition face.
Heat flux sensor is arranged near sheet metal, and making the front surface of the front surface of heat flux sensor and sheet metal in the same plane, the hot wall heat flow value therefore arriving sheet metal front surface in heating process is the same with the heat flow value size arriving heat flux sensor front surface.When quartz lamp infrared radiation array heats sheet metal according to the metal sheet surface temperature curve calculated by cold wall heat flow meter, the dynamic changing process of the hot wall hot-fluid of sheet metal front surface just can be arrived under real time record with sheet metal heat flux sensor in the same plane.
The front surface of heat flux sensor and sheet metal front surface are arranged in same flat heated, ensure that the hot wall hot-fluid of the heat flux sensor surface hot wall hot-fluid of perception and the front surface of sheet metal has good consistance.
Step f: establishment hot wall hot-fluid computer heating control program.
" hot wall hot-fluid-time " data by the metal sheet surface under heat flux sensor survey record are inputted computing machine, as the preset value of hot-fluid Boundary Condition Control program.
Step g: by hot wall hot-fluid boundary condition, radiation heating test is carried out to actual experimental part.
The hot wall hot-fluid boundary condition using the actual experimental part that heat control system effects on surface has ablative heat shield protecting or nonmetallic materials to be converted to according to above-mentioned " cold wall hot-fluid " → " temperature " → " hot wall hot-fluid " carries out radiation heating test.
Principle of the present invention is: during because of the Aerodynamic Heating simulation test adopting radiation mode to carry out, and cold wall hot-fluid cannot be obtained by test measurement.So the cold wall hot-fluid boundary condition with approximation calculated must be converted to the hot wall hot-fluid boundary condition that more tallies with the actual situation to carry out thermal environmental test.Fixing corresponding relation is there is based between cold wall heat flow versus temperature-hot wall hot-fluid, first the temperature variation curve of metal sheet surface is calculated according to cold wall hot-fluid boundary condition, then according to the temperature curve calculated, heating is controlled to sheet metal, record the hot wall heat flow curve recorded of the heat flux sensor under this temperature conditions simultaneously, by the method that theory calculate combines with experimental test, obtain the hot wall hot-fluid boundary condition corresponding to cold wall hot-fluid, realize the radiant type heat test that surface has ablative heat shield protecting or nonmetallic materials structure necessary hot wall hot-fluid boundary condition.
The present invention's advantage is compared with prior art:
The surface temperature of some material is difficult to measure, such as: surface is with the structure of ablative heat shield protecting, and produce physics or the chemical changes such as burning, gasification, decomposition, stripping due to coating, surface temperature is difficult to Measurement accuracy; Nonmetallic materials are owing to being subject to the impact of material behavior and the factor such as surface state and sensor installation in addition, and the reliable and stable measurement of its surface temperature is very difficult.Therefore for the mode that ablator and nonmetallic materials often can not adopt temperature boundary to simulate, and need to use hot wall hot-fluid boundary condition to carry out thermal environmental test.The variation relation of hot wall hot-fluid and temperature is close, because the change of ablator and non-metal material surface temperature is difficult to determine, in hot wall hot-fluid calculates, just lacked an important temperature parameter, therefore the hot-fluid of the hot wall accurately boundary condition of ablator and nonmetallic materials is difficult to be obtained by theory calculate.Traditional method is in unavoidable situation, first suppose that the surface temperature of testpieces does not change in heating process, remain on a fixed temperature (although this does not meet actual conditions), then calculate so-called " cold wall (surface temperature does not change) " hot-fluid.Due in radiant type Aerodynamic Heating simulation test, cold wall hot-fluid cannot be obtained by measurement, therefore hot wall hot-fluid boundary condition must first be converted to during test, owing to showing temperature before ablator in heating process all the time in continuous change, and be difficult to determine, therefore " cold wall " hot-fluid is converted to the job very difficult of hot wall hot-fluid.Fixing corresponding relation is there is in the present invention according between cold wall heat flow versus temperature-hot wall hot-fluid, adopt the method that theory calculate combines with experimental test, cold wall hot-fluid boundary condition is converted to the hot wall hot-fluid boundary condition needed for reality, it also avoid in test to the temperature survey of the front surface of ablator and nonmetallic materials instability simultaneously.The method accurately and reliably, for high-speed aircraft radiant type Aerodynamic Heating simulation test provides a kind of hot-fluid ambient boundary condition determination method of practicality, has important engineer applied and is worth
Accompanying drawing explanation
Fig. 1 is the process flow diagram that cold wall hot-fluid of the present invention is converted to hot wall hot-fluid method;
Fig. 2 is the process schematic that cold wall hot-fluid of the present invention is converted to hot wall hot-fluid method.
Embodiment
As shown in Figure 1, the specific embodiment of the present invention is as follows:
1, sheet metal selects high temperature resistant Ni-based stainless steel 1Cr18Ni9Ti, and fusing point is 1450 DEG C, and this material non-deformability is at high temperature relatively good; Sheet metal thickness scope is chosen as 1.0-2.0mm, because too thick thermal capacitance is large, the reaction time for fast-changing thermal environment is long, and thermal hysteresis is serious.Too thin easy distortion, determines between 1.0-2.0mm proper after test.It is 100mm-120mm that the planar dimension of sheet metal is chosen as monolateral length, because area is not too large, outside face after being heated, deflection is within usable range, the length of side of this sheet metal and the ratio of thickness are between 60:1 to 120:1, it is wide, thickness rate is very large, therefore can be similar to and become two-dimensional plane state, the impact of the three-dismensional effect of boundary can be ignored.
2, the temperature variation curve of metal sheet surface is calculated according to cold wall heat flow meter:
If sheet metal initial temperature is t
0, thickness is h, and the side of sheet metal is heated, and its heat flow density is q.When the peripheral boundaries of sheet metal is adiabatic condition substantially, in planar range, sheet metal temperature difference is little, the main through-thickness transmission of heat.If any time, sheet metal interior temperature distribution function was t (x, τ), x is the coordinate (0≤x≤h) along sheet metal thickness direction, and τ is time variable, sheet metal internal temperature t (x, τ) is determined by the Unsteady Heat Transfer differential equation:
K is the coefficient of heat conductivity of sheet metal, and ρ is the density of sheet metal, c
pfor the specific heat capacity of sheet metal.
According to the initial temperature condition of the differential equation [1] and the cold wall hot-fluid of heating surface, the boundary condition such as convection heat transfer and radiation heat transfer between radiating surface and external environment condition, the Temperature Distribution of any time sheet metal through-thickness can be solved, and then obtain the change curve of sheet metal front surface temperature and time.
The concrete solution procedure of the time dependent curve of temperature of sheet metal front surface is as follows:
(1) initial temperature condition is determined.
When time variable τ=0, initial temperature t (x, τ)=t (x, the 0)=t of sheet metal
0.
(2) boundary condition of sheet metal heating surface and radiating surface is determined.
At heating surface, sheet metal is subject to the heating that size is the heat flow density of q.Then the thermal boundary condition of the heating surface of sheet metal can be described as:
At radiating surface (x=h place), consider that the radiating surface of sheet metal is in the face of open space outerpace, be made up of surface radiation heat transfer two parts with natural convection air heat exchange and surface and environment with the heat interchange of space outerpace.
At radiating surface (x=h place), total heat flow density q of sheet metal is described below:
q＝q
h+q
r [3]
In formula, q
hfor heat transfer free convection heat flow density, q
rfor radiation heat transfer heat flow density.
At sheet metal radiating surface, heat transfer free convection hot-fluid q
hfor:
q
h＝h(t(h,τ)-t
α) [4]
In formula: h is convection transfer rate, t (h, τ) is the temperature of τ moment sheet metal radiating surface, t
αfor exterior space temperature.
NATURAL CONVECTION COEFFICIENT OF HEAT h, is determined by formula [5]:
Wherein λ is air conduction coefficient, and H is the length of side of sheet metal testpieces.Nu is Nusselt number, and from physical significance, it is nondimensional convection transfer rate.
Sheet metal testpieces is vertically placed, and radiating surface and air pass through heat transfer free convection.Nusselt number Nu adopts the test correlation of the large space free convection heat transfer of even wall temperature boundary condition:
Nu＝C(GrPr)
n [6]
Gr is grashof number, and be the one tolerance of buoyancy lift and viscous force ratio in heat transfer free convection process, the gas physical parameter used when calculating grashof number is relevant with the qualitative temperature of gas; Pr is Prandtl number, is the temperature variant physical parameter of fluid itself; C with n is the constant relevant with natural convection fluidised form.
The heat transfer free convection heat flow density q in metal-plate radiating face can be solved by formula [4]-Shi [6]
h.And the radiation heat transfer heat flow density q of sheet metal radiating surface and space outerpace
rfor:
Wherein, ε is the emissivity of sheet metal radiating surface; σ is blackbody radiation constant, and its value is 5.67 × 10
-8w/ (m
2k
4); T (h, τ) is sheet metal radiating surface temperature, t
αfor exterior space temperature.
Through type [4] and formula [7], can determine the thermal boundary condition of sheet metal at radiating surface.
(3) discretize of the Unsteady Heat Transfer differential equation
Plate thickness is divided into n-1 part, obtains n-1 and calculate subregion and n computer memory node; M-1 part will be divided into computing time, obtain m timing node.Behind zoning and the division of computing time, each moment can be obtained, the ermal physics amounts such as the temperature on each space nodes, specific heat capacity.According to the ermal physics amount of space nodes each on plate thickness direction, adopt difference method, by the Unsteady Heat Transfer differential equation [1] discretize, obtain discrete equation group.
(4) discrete equation group is solved
The thermal boundary condition of above sheet metal initial temperature condition and heating surface and radiating surface is substituted into discrete equation group, by this discrete equation group of solution by iterative method, the temperature value of not each space nodes in the same time can be obtained in heating process.In order to calculate the temperature of front surface, the coordinate x of through-thickness was taken as 0 (x=0 represents the position of sheet metal heating surface), sheet metal front surface temperature curve t (x, τ) over time can be obtained.
3, " temperature " and " time " data corresponding with it that are calculated sheet metal front surface by cold wall heat flow meter are placed among 2 arrays respectively, input computing machine " Temperature-time " preset value as control program, to be formed the temperature variation environment of the metal sheet surface mutually corresponding with cold wall hot-fluid by heat control system.
4, sheet metal testpieces is positioned in distance quartz lamp infrared radiation heating array 50-70mm place, and the thermocouple sensor of a thermometric is welded in the centre of sheet metal front surface, the temperature variation on the full surface of real-time measurement sheet metal, during test by thermocouple sensor continually varying metal sheet surface temperature value adopted into, after signal amplifies, become digital signal from A/D converter.After again the temperature value measured and preset value being compared, deviation is sent into control program, computing machine calculates controlled quentity controlled variable by control algolithm to sampled data, and through D/A switch rear drive power of controlled silicon regulator, regulate the electric power on infrared radiation heating device, thus complete the Dynamic controlling of sheet metal front surface preset temperature.
5, in order to the hot wall heat flow data of the front surface of sheet metal can be arrived in the process of test heating under real time record, and make the hot wall hot-fluid of heat flux sensor surface perception consistent with the hot wall heat flow data of sheet metal front surface, the front surface of heat flux sensor and metal sheet surface are arranged in same flat heated, when quartz lamp infrared radiation array heats sheet metal according to preset temperature curve, the heat flux sensor in the same plane with sheet metal will record the dynamic changing process of the hot wall hot-fluid arriving sheet metal front surface.
6, " hot wall hot-fluid-time " data by the metal sheet surface under heat flux sensor survey record in above-mentioned test are inputted computing machine, as the preset data of hot wall hot-fluid Boundary Condition Control program.
7, the present invention obtains corresponding relation between hot wall hot-fluid and cold wall hot-fluid by the method that the theory calculate of " cold wall hot-fluid " → " temperature " → " hot wall hot-fluid " as shown in Figure 2 combines with experimental test, wherein the corresponding relation of " cold wall hot-fluid " → " temperature " adopts the method for theory calculate, the corresponding relation of " temperature " → " hot wall hot-fluid " adopts the method for experimental test, finally obtains the hot wall hot-fluid boundary condition of ablator and the nonmetallic materials being difficult to obtain.When using Transient Aerodynamic heat test simulation system to carry out heat insulation test to nonmetallic materials or surface with ablative heat shield protecting testpieces, just can control heating process according to hot wall hot-fluid.The present invention be high-speed aircraft radiant type Aerodynamic Heating simulation test provide a kind of can the hot wall hot-fluid defining method of practical application.For the heat insulation potency test checking of the high speed aircraft materials such as guided missile and security and Reliability Design is significant and practical engineering application is worth.
Non-elaborated part of the present invention belongs to techniques well known.
Claims (4)
1. in Aerodynamic Heating simulation test, cold wall hot-fluid is converted to a method for hot wall hot-fluid, it is characterized in that comprising the following steps:
Step a: consider the material of sheet metal, the relation between planar dimension and thickness, select sheet metal, make sheet metal be approximately two dimensional surface testpieces, the high temperature of the thousands of degree of ability, in heating process, do not produce large plane warping distortion, and added their confirmation by test;
Step b: cold wall hot-fluid is acted on sheet metal heating surface, and determine the boundary condition of the initial temperature condition of sheet metal and the convection heat transfer between radiating surface and external environment condition and radiation heat transfer, obtain " cold wall hot-fluid-time " change curve of sheet metal heating surface; Then according to " cold wall hot-fluid-time " change curve of sheet metal heating surface, " Temperature-time " change curve being calculated sheet metal front surface by the Unsteady Heat Transfer differential equation, and by " Temperature-time " change curve data of sheet metal front surface stored in computing machine, as the preset value of thermal control program;
Step c: utilize the material determined by step a, the sheet metal of thickness and planar dimension is as testpieces, heating is controlled to " Temperature-time " change curve that sheet metal calculates according to step b, the front surface of sheet metal is welded with the thermocouple sensor of thermometric, thermal control system heats sheet metal, sheet metal front surface temperature is measured in real time simultaneously, using measuring tempeature data as value of feedback, compare to the preset value in above-mentioned corresponding moment of calculating, regulating and controlling amount is obtained through Computing after obtaining departure, the operating voltage on quartz lamp infrared radiation array is adjusted in real time by controllable silicon regulator, " Temperature-time " thermal environment of the metal sheet surface that simulation is preset,
Steps d: heat flux sensor is arranged near sheet metal, and make the front surface of the front surface of heat flux sensor and sheet metal in the same plane, ensure that the hot wall heat flow value arriving sheet metal front surface in heating process is in the same size with the heat flow value arriving heat flux sensor front surface; Quartz lamp infrared radiation array is used to heat sheet metal according to the metal sheet surface temperature curve calculated by cold wall heat flow meter, and by arriving the dynamic changing process of hot wall hot-fluid of sheet metal front surface under heat flux sensor real time record, it can be used as hot wall hot-fluid boundary condition;
Step e: " hot wall hot-fluid-time " relation data by the metal sheet surface under heat flux sensor survey record is inputted computing machine, as the preset value of hot-fluid boundary condition computer heating control program;
Step f: use heat control system to carry out radiation heating test to the actual experimental part that nonmetallic materials or surface have ablative heat shield protecting according to the above-mentioned hot wall hot-fluid boundary condition be converted to by " cold wall hot-fluid " → " temperature " → " hot wall hot-fluid ".
2. in a kind of Aerodynamic Heating simulation test according to claim 1, cold wall hot-fluid is converted to the method for hot wall hot-fluid, and it is characterized in that: in described step a, sheet metal material is Ni-based stainless steel 1Cr18Ni9Ti, and its fusing point is about 1450 DEG C; Plate thickness is taken between 1.0mm-2.0mm, and the length of side of the planar dimension of sheet metal is 100mm-120mm, and the ratio of its length of side and thickness is between 60:1 to 120:1.
3. in a kind of Aerodynamic Heating simulation test according to claim 1, cold wall hot-fluid is converted to the method for hot wall hot-fluid, it is characterized in that: the sheet metal in described step c is in distance quartz lamp infrared radiation heating array 50-70mm part.
4. in a kind of Aerodynamic Heating simulation test according to claim 1, cold wall hot-fluid is converted to the method for hot wall hot-fluid, it is characterized in that: in described steps d, the front surface of heat flux sensor and sheet metal front surface are arranged in same flat heated, ensure that the hot wall hot-fluid of the heat flux sensor surface hot wall hot-fluid of perception and the front surface of sheet metal has good consistance.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410568947.2A CN104267062B (en) | 2014-10-22 | 2014-10-22 | A kind of method that in Aerodynamic Heating simulated test, cold wall hot-fluid is converted to hot wall hot-fluid |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410568947.2A CN104267062B (en) | 2014-10-22 | 2014-10-22 | A kind of method that in Aerodynamic Heating simulated test, cold wall hot-fluid is converted to hot wall hot-fluid |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104267062A true CN104267062A (en) | 2015-01-07 |
| CN104267062B CN104267062B (en) | 2016-08-24 |
Family
ID=52158603
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410568947.2A Expired - Fee Related CN104267062B (en) | 2014-10-22 | 2014-10-22 | A kind of method that in Aerodynamic Heating simulated test, cold wall hot-fluid is converted to hot wall hot-fluid |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104267062B (en) |
Cited By (23)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105203591A (en) * | 2015-09-24 | 2015-12-30 | 中国航天空气动力技术研究院 | Measurement method of hot wall heat flux density of spacecraft test model |
| CN105301048A (en) * | 2015-11-17 | 2016-02-03 | 中国航天科技集团公司第四研究院第四十一研究所 | Thermocouple pre-embedded thermal insulation coating test-piece interface temperature testing method |
| CN106248216A (en) * | 2016-07-29 | 2016-12-21 | 西安空间无线电技术研究所 | A kind of big temperature difference system of large-scale deployable antenna builds and method of testing |
| CN106407562A (en) * | 2016-09-19 | 2017-02-15 | 北京精密机电控制设备研究所 | A determining method for the heat insulation effect of a thermal protective layer in thermal vacuum environment |
| CN106840465A (en) * | 2016-12-29 | 2017-06-13 | 中国航天空气动力技术研究院 | A kind of Miniature water card heat-flow meter |
| CN106885634A (en) * | 2017-01-03 | 2017-06-23 | 浙江大学 | Unsteady wall heating heat flux distribution measuring method based on infrared thermal imagery thermometry |
| CN106960089A (en) * | 2017-03-14 | 2017-07-18 | 清华大学 | Temperature field and hot-fluid containing internal complex boundary structure are while reconstructing method |
| CN107525975A (en) * | 2017-07-17 | 2017-12-29 | 湖北航天技术研究院总体设计所 | Missile-borne Antenna electric performance test system under one kind simulation Aerodynamic Heating environment |
| CN107843405A (en) * | 2016-09-21 | 2018-03-27 | 北京空天技术研究所 | The acquisition methods of testpieces and engine gas to aircraft bottom radiant heat flux |
| CN107944065A (en) * | 2016-10-12 | 2018-04-20 | 北京空天技术研究所 | The test data world conversion method of aircraft gap flowing Aerodynamic Heating assessment |
| CN108120612A (en) * | 2016-11-29 | 2018-06-05 | 北京机电工程研究所 | A kind of processing method of heat test high temperature peak |
| CN109029907A (en) * | 2018-07-18 | 2018-12-18 | 大连理工大学 | A kind of parameter similar method of pneumatic thermal environmental test simulated conditions |
| CN109540962A (en) * | 2018-11-30 | 2019-03-29 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of heat-insulated efficiency characterizing method of heat insulation structural |
| CN110826272A (en) * | 2019-10-26 | 2020-02-21 | 复旦大学 | Heat rotating device simultaneously suitable for conduction, convection and radiation |
| CN110826266A (en) * | 2019-10-01 | 2020-02-21 | 复旦大学 | Thermal rotator device designed based on conversion thermal radiation and heat conduction theory |
| CN112197932A (en) * | 2020-12-07 | 2021-01-08 | 中国空气动力研究与发展中心低速空气动力研究所 | Surface temperature correction method and measurement method for airplane anti-icing and deicing test model |
| CN112326730A (en) * | 2020-10-21 | 2021-02-05 | 北京航空航天大学 | Experimental method and device for measuring heat release rate pulsation by adopting multiple microphones |
| CN112697365A (en) * | 2020-12-03 | 2021-04-23 | 北京机电工程研究所 | Thermal vibration testing device and testing method based on form and position equivalent backstepping control |
| CN114637277A (en) * | 2022-05-20 | 2022-06-17 | 中国飞机强度研究所 | All-range heat flux density measurement and control system and measurement and control method for aerospace plane test experiment |
| CN114647959A (en) * | 2022-05-24 | 2022-06-21 | 中国飞机强度研究所 | Method for constructing test piece heat flow density distribution calculation model in airplane test and application |
| CN114722543A (en) * | 2022-06-09 | 2022-07-08 | 中国飞机强度研究所 | Design method for heat reflecting screen in structural heat strength test of hypersonic aircraft |
| CN115356372A (en) * | 2022-10-24 | 2022-11-18 | 中国空气动力研究与发展中心计算空气动力研究所 | Time-varying thermal response test method and system for novel material in flight test |
| CN116383974A (en) * | 2023-06-06 | 2023-07-04 | 西安现代控制技术研究所 | Aircraft axial force correction method considering pneumatic heating effect |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH11174009A (en) * | 1997-12-09 | 1999-07-02 | Shimadzu Corp | Thermal analyzer |
| US5953924A (en) * | 1991-06-17 | 1999-09-21 | Y. T. Li Engineering, Inc. | Apparatus, process and system for tube and whip rod heat exchanger |
| JP2003279512A (en) * | 2002-03-26 | 2003-10-02 | Koji Ono | Method and apparatus for estimation of compressive strength of concrete |
| CN202393503U (en) * | 2011-12-01 | 2012-08-22 | 北京遥测技术研究所 | Round foil heat flux sensor |
| CN103512919A (en) * | 2013-10-16 | 2014-01-15 | 中国航天空气动力技术研究院 | Method for determining backing quantity at highest heat flow position in tilt wing front edge ablation test |
-
2014
- 2014-10-22 CN CN201410568947.2A patent/CN104267062B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5953924A (en) * | 1991-06-17 | 1999-09-21 | Y. T. Li Engineering, Inc. | Apparatus, process and system for tube and whip rod heat exchanger |
| JPH11174009A (en) * | 1997-12-09 | 1999-07-02 | Shimadzu Corp | Thermal analyzer |
| JP2003279512A (en) * | 2002-03-26 | 2003-10-02 | Koji Ono | Method and apparatus for estimation of compressive strength of concrete |
| CN202393503U (en) * | 2011-12-01 | 2012-08-22 | 北京遥测技术研究所 | Round foil heat flux sensor |
| CN103512919A (en) * | 2013-10-16 | 2014-01-15 | 中国航天空气动力技术研究院 | Method for determining backing quantity at highest heat flow position in tilt wing front edge ablation test |
Non-Patent Citations (1)
| Title |
|---|
| 王智勇等: ""结构热试验中冷壁热流边界模拟方法研究"", 《航天器环境工程》 * |
Cited By (40)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105203591A (en) * | 2015-09-24 | 2015-12-30 | 中国航天空气动力技术研究院 | Measurement method of hot wall heat flux density of spacecraft test model |
| CN105203591B (en) * | 2015-09-24 | 2018-09-18 | 中国航天空气动力技术研究院 | The measurement method of spacecraft testing model hot wall heat flow density |
| CN105301048A (en) * | 2015-11-17 | 2016-02-03 | 中国航天科技集团公司第四研究院第四十一研究所 | Thermocouple pre-embedded thermal insulation coating test-piece interface temperature testing method |
| CN105301048B (en) * | 2015-11-17 | 2018-01-09 | 中国航天科技集团公司第四研究院第四十一研究所 | A kind of heat insulating coat test specimen interface temperature method of testing of pre-buried thermocouple |
| CN106248216A (en) * | 2016-07-29 | 2016-12-21 | 西安空间无线电技术研究所 | A kind of big temperature difference system of large-scale deployable antenna builds and method of testing |
| CN106248216B (en) * | 2016-07-29 | 2019-04-09 | 西安空间无线电技术研究所 | A kind of big temperature difference system of large size deployable antenna constructs and test method |
| CN106407562A (en) * | 2016-09-19 | 2017-02-15 | 北京精密机电控制设备研究所 | A determining method for the heat insulation effect of a thermal protective layer in thermal vacuum environment |
| CN106407562B (en) * | 2016-09-19 | 2019-11-29 | 北京精密机电控制设备研究所 | A kind of determination method of the thermal protection shield heat insulation under hot vacuum environment |
| CN107843405A (en) * | 2016-09-21 | 2018-03-27 | 北京空天技术研究所 | The acquisition methods of testpieces and engine gas to aircraft bottom radiant heat flux |
| CN107944065A (en) * | 2016-10-12 | 2018-04-20 | 北京空天技术研究所 | The test data world conversion method of aircraft gap flowing Aerodynamic Heating assessment |
| CN107944065B (en) * | 2016-10-12 | 2021-08-10 | 北京空天技术研究所 | Test data space-ground conversion method for aerodynamic heat evaluation of aircraft gap flow |
| CN108120612A (en) * | 2016-11-29 | 2018-06-05 | 北京机电工程研究所 | A kind of processing method of heat test high temperature peak |
| CN106840465A (en) * | 2016-12-29 | 2017-06-13 | 中国航天空气动力技术研究院 | A kind of Miniature water card heat-flow meter |
| CN106840465B (en) * | 2016-12-29 | 2023-11-10 | 中国航天空气动力技术研究院 | Miniature water card heat flow meter |
| CN106885634A (en) * | 2017-01-03 | 2017-06-23 | 浙江大学 | Unsteady wall heating heat flux distribution measuring method based on infrared thermal imagery thermometry |
| CN106960089B (en) * | 2017-03-14 | 2019-05-21 | 清华大学 | Temperature field and hot-fluid containing internal complex boundary structural body while reconstructing method |
| CN106960089A (en) * | 2017-03-14 | 2017-07-18 | 清华大学 | Temperature field and hot-fluid containing internal complex boundary structure are while reconstructing method |
| CN107525975A (en) * | 2017-07-17 | 2017-12-29 | 湖北航天技术研究院总体设计所 | Missile-borne Antenna electric performance test system under one kind simulation Aerodynamic Heating environment |
| WO2020015375A1 (en) * | 2018-07-18 | 2020-01-23 | 大连理工大学 | Parameter similarity method for aerodynamic heat environment test simulation condition |
| CN109029907A (en) * | 2018-07-18 | 2018-12-18 | 大连理工大学 | A kind of parameter similar method of pneumatic thermal environmental test simulated conditions |
| US11454566B2 (en) | 2018-07-18 | 2022-09-27 | Dalian University Of Technology | Parameter similarity method for test simulation conditions of aerodynamic heating environment |
| CN109540962B (en) * | 2018-11-30 | 2021-07-09 | 中国航空工业集团公司沈阳飞机设计研究所 | Heat insulation efficiency characterization method of heat insulation structure |
| CN109540962A (en) * | 2018-11-30 | 2019-03-29 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of heat-insulated efficiency characterizing method of heat insulation structural |
| CN110826266A (en) * | 2019-10-01 | 2020-02-21 | 复旦大学 | Thermal rotator device designed based on conversion thermal radiation and heat conduction theory |
| CN110826266B (en) * | 2019-10-01 | 2023-05-30 | 复旦大学 | Heat rotator device based on heat radiation conversion and heat conduction theory design |
| CN110826272A (en) * | 2019-10-26 | 2020-02-21 | 复旦大学 | Heat rotating device simultaneously suitable for conduction, convection and radiation |
| CN110826272B (en) * | 2019-10-26 | 2023-05-30 | 复旦大学 | Heat rotating device suitable for conduction, convection and radiation simultaneously |
| CN112326730A (en) * | 2020-10-21 | 2021-02-05 | 北京航空航天大学 | Experimental method and device for measuring heat release rate pulsation by adopting multiple microphones |
| CN112697365A (en) * | 2020-12-03 | 2021-04-23 | 北京机电工程研究所 | Thermal vibration testing device and testing method based on form and position equivalent backstepping control |
| CN112697365B (en) * | 2020-12-03 | 2022-05-31 | 北京机电工程研究所 | Thermal vibration testing device and testing method based on form and position equivalent backstepping control |
| CN112197932A (en) * | 2020-12-07 | 2021-01-08 | 中国空气动力研究与发展中心低速空气动力研究所 | Surface temperature correction method and measurement method for airplane anti-icing and deicing test model |
| CN114637277B (en) * | 2022-05-20 | 2022-08-02 | 中国飞机强度研究所 | All-range heat flux density measurement and control system and measurement and control method for aerospace plane test experiment |
| CN114637277A (en) * | 2022-05-20 | 2022-06-17 | 中国飞机强度研究所 | All-range heat flux density measurement and control system and measurement and control method for aerospace plane test experiment |
| CN114647959A (en) * | 2022-05-24 | 2022-06-21 | 中国飞机强度研究所 | Method for constructing test piece heat flow density distribution calculation model in airplane test and application |
| CN114722543B (en) * | 2022-06-09 | 2022-08-12 | 中国飞机强度研究所 | Design method for heat reflecting screen in structural heat strength test of hypersonic aircraft |
| CN114722543A (en) * | 2022-06-09 | 2022-07-08 | 中国飞机强度研究所 | Design method for heat reflecting screen in structural heat strength test of hypersonic aircraft |
| CN115356372A (en) * | 2022-10-24 | 2022-11-18 | 中国空气动力研究与发展中心计算空气动力研究所 | Time-varying thermal response test method and system for novel material in flight test |
| CN115356372B (en) * | 2022-10-24 | 2023-03-10 | 中国空气动力研究与发展中心计算空气动力研究所 | Time-varying thermal response testing method and system for novel material in flight test |
| CN116383974A (en) * | 2023-06-06 | 2023-07-04 | 西安现代控制技术研究所 | Aircraft axial force correction method considering pneumatic heating effect |
| CN116383974B (en) * | 2023-06-06 | 2023-09-01 | 西安现代控制技术研究所 | Aircraft axial force correction method considering pneumatic heating effect |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104267062B (en) | 2016-08-24 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104267062B (en) | A kind of method that in Aerodynamic Heating simulated test, cold wall hot-fluid is converted to hot wall hot-fluid | |
| Liu et al. | Numerical and experimental study on thermal shock damage of CVD ZnS infrared window material | |
| Kumar et al. | Laser based calibration technique of thin film gauges for short duration transient measurements | |
| Fu et al. | Gardon gauge measurements of fast heat flux transients | |
| CN113495486A (en) | Model prediction control method based on extended state observer for structural thermal test | |
| Markan et al. | Measuring heat flux to a porous burner in microgravity | |
| Polanka et al. | Determination of Cooling Parameters for a High-Speed, True-Scale, Metallic Turbine Vane | |
| Miller et al. | Temperature dependent performance of Schmidt–Boelter heat flux sensors | |
| RU2676385C1 (en) | Method for thermal control during heat tests of antenna domes of missiles | |
| Alam et al. | Radiation based calibration of thin film gauge for transient measurement | |
| Wu et al. | Study on the thermal protection performance of superalloy honeycomb panels in high-speed thermal shock environments | |
| Houtz et al. | A finite element thermal simulation of a microwave blackbody calibration target | |
| Kandula et al. | Three-dimensional thermal boundary layer corrections for circular heat flux gauges mounted in a flat plate with a surface temperature discontinuity | |
| Hirschen et al. | Infrared thermography and pitot pressure measurements of a scramjet nozzle flowfield | |
| Zhao et al. | Development of Hypersonic Aerothermodynamic Technologies | |
| Wanqing et al. | Research and development of surface heat flux sensor for high speed aircraft | |
| Zhu et al. | Long-duration heat load measurement approach by novel apparatus design and highly efficient algorithm | |
| Zhong et al. | Investigation of heating characteristics of domestic gas cookers via a methodology of infrared thermography | |
| Manjhi et al. | Assessments of surface heat flux from rapid temperature sensors at various angles of attack over a plate | |
| Sivamurugan et al. | Aerothermal design, qualification and flight performance | |
| Wadhams et al. | Experimental Space Shuttle Orbiter Studies to Acquire Data for Code and Flight Heating Model Validation | |
| Koç | Experimental and numerical investigation of film cooling effectiveness for rectangular injection holes | |
| Shams et al. | Comparative study of heat flux instrumentation for hypersonic ground test facilities | |
| Barth et al. | Advanced flight analysis of SHEFEX-I | |
| Xing et al. | Thermal modeling and analysis of a radiometer for thermal control coatings in situ measurement |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160824 Termination date: 20171022 |