CN112834159A - Method for measuring heat flow inside wing rudder gap and rudder shaft - Google Patents
Method for measuring heat flow inside wing rudder gap and rudder shaft Download PDFInfo
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- CN112834159A CN112834159A CN202011623037.1A CN202011623037A CN112834159A CN 112834159 A CN112834159 A CN 112834159A CN 202011623037 A CN202011623037 A CN 202011623037A CN 112834159 A CN112834159 A CN 112834159A
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- G—PHYSICS
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
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Abstract
The invention relates to the technical field of heat flow measurement, in particular to a method for measuring heat flow inside a wing rudder gap and a rudder shaft. According to the technical scheme of the invention, by adopting a heat measuring method combining a phosphorescence chart and an integrated thermocouple, the heat flow distribution on the inner surface of the wing rudder gap and the heat flow peak value at the position of the rudder shaft are accurately measured, the data is rich, the heat flow distribution and the change trend of the upper surface and the lower surface in the wing rudder gap can be visually seen, and the heat flow transfer condition of the rudder shaft region to the inner part of the wing rudder gap is known.
Description
Technical Field
The invention relates to the technical field of heat flow measurement, in particular to a method for measuring heat flow inside a wing rudder gap and on a rudder shaft.
Background
The wing rudder is the most widely applied control scheme in stable flight and attitude control of the hypersonic maneuvering aircraft, and a certain gap is usually reserved between the wing rudder and the aircraft in order to enable the aircraft to change the rudder deflection angle and accommodate thermal expansion caused by temperature rise of a structure. The wing rudder is used as a bulge on the surface of the hypersonic aircraft, complex physical phenomena such as shock wave and boundary layer interference, shock wave and shock wave interference, boundary layer separation and reattachment and the like exist locally, so that local pneumatic heating is extremely complex, upstream high-speed fluid flows into a gap due to the appearance of a wing rudder gap structure, a plurality of separation reattachment lines appear on the surface near the gap, a vortex structure can be generated inside the gap, the thermal environment characteristics of the gap and an interference area are greatly changed, a plurality of local high-heat-flow zones are generated, and high wall temperatures are easy to appear on the upper wall surface and the lower wall surface inside the gap and near a rudder shaft, so that serious ablation is caused. In a plurality of flight test projects at home and abroad, the phenomena of serious ablation and peeling of heat-proof materials occur in wing rudder interference areas and other parts, and the flight test is even disqualified under partial conditions.
Due to the limitation of the size of the wind tunnel, a wind tunnel test in an aerodynamic thermal environment mostly adopts a scaling model according to a similar criterion, the traditional wind tunnel heat measurement method has the defects of limited measuring point positions, difficulty in capturing heat flow peak values and the like due to the limitation of the size of a sensor, wiring and the like, and the problem is more prominent because the internal size of a wing rudder gap is small.
Disclosure of Invention
The invention aims to provide a method for measuring heat flow inside a wing rudder gap and a rudder shaft, which accurately captures the position and the size of a heat flow peak value in a wing rudder gap interference area by combining point measurement and non-contact surface measurement, overcomes the difficulties of size limitation of a sensor and difficulty in capturing the heat flow peak value, and realizes accurate measurement of heat flow distribution and the heat flow peak value in a complex flow interference area of the wing rudder gap.
The invention provides a method for measuring heat flow inside a wing rudder gap and a rudder shaft, which comprises the following steps of:
s1, manufacturing a test model, wherein the test model comprises a flat plate and a wing rudder, the flat plate is connected with the wing rudder through a rudder shaft, the bottom of the wing rudder is made of microcrystalline mica ceramic, and the corresponding part of the flat plate and the wing rudder is made of organic glass;
s2, spraying a temperature-sensitive material on the outer side of the microcrystalline mica ceramic at the bottom of the wing rudder to form a temperature-sensitive coating, placing a test model in a wind tunnel test section to perform a wind tunnel test, wherein a wind tunnel observation window is arranged on the side surface of the wind tunnel test section, and an ultraviolet excitation light source and a high-speed camera are arranged outside the wind tunnel observation window;
s3, irradiating ultraviolet rays emitted by an ultraviolet excitation light source onto the temperature-sensitive coating through a wind tunnel observation window and organic glass to excite the temperature-sensitive coating to emit fluorescence, enabling high-speed airflow to pass through a gap between a flat plate and a wing rudder to enable the temperature-sensitive coating to generate temperature rise, recording the surface light intensity change of the temperature-sensitive coating by using a high-speed camera, comparing the surface light intensity distribution of each fluorescence image with the initial average light intensity distribution to obtain the surface light intensity distribution change rate, comparing the surface light intensity distribution change rate of a plurality of fluorescence images with a calibration curve to obtain the change data of the surface temperature along with time, and further calculating the surface heat flow outside the microcrystalline mica ceramic;
s4, spraying a temperature-sensitive material on the upper surface of the organic glass to form a temperature-sensitive coating, and repeating the step S3 to obtain surface heat flow on the upper surface of the organic glass;
and S5, distributing the integrated thermocouples in the area of the rudder shaft, obtaining the temperature of the rudder shaft, and calculating the surface heat flow of the rudder shaft.
Further, in step S1, a mounting hole is formed in the flat plate, and the rudder shaft is fixed to the mounting hole through a nut. The microcrystalline mica ceramic at the bottom of the wing rudder can obtain higher temperature change rate under the condition of high temperature rise, the measurement precision of heat flow in a wing rudder gap is improved, and ultraviolet rays emitted by an ultraviolet excitation light source penetrate through the organic glass on the flat plate to excite the temperature-sensitive coating so as to realize the measurement of the surface temperature of the temperature-sensitive coating;
further, in steps S2 and S4, the temperature-sensitive material is composed of phosphor powder and a binder, a mass ratio of the phosphor powder to the binder is 1:4.8-5.2, the binder is composed of tetraethylenepentamine and isopropanol, and a mass ratio of the isopropanol to the tetraethylenepentamine is 1: 2.8-3.2.
Further, in the step S2 and the step S4, the spraying is performed by a spraying pen, the caliber of the spraying pen is 0.25mm, the spraying times is 5-6 times, the thickness of the single spraying is 4-5 μm, and the thickness of the temperature-sensitive coating is 20-30 μm. The phosphor powder is a material capable of emitting phosphorescence, the product is commercially available, the temperature-sensitive material can be better bonded on the test model by the adhesive, the temperature-sensitive coating is ensured not to fall off in the test process, the temperature-sensitive material prepared by the phosphor powder and the adhesive has good viscosity and high uniformity, and the coating is prevented from being too thick and influencing the test result by adopting a spraying pen to pass through a small number of spraying modes for multiple times.
Further, in step S3, the wavelength of the ultraviolet light is 365nm, the initial average light intensity distribution is an average light intensity distribution of a fluorescence image of the test device in the wind tunnel test section before the test, and the number of the fluorescence image is 20. The method comprises the steps of spraying a temperature-sensitive material on the outer side of microcrystalline mica ceramics at the bottom of a wing rudder to form a temperature-sensitive coating, placing a test model in a wind tunnel test section, before a wind tunnel test, recording the surface light intensity distribution of the test model in the wind tunnel test section by using a high-speed camera, irradiating excitation light emitted by an ultraviolet excitation light source on the temperature-sensitive coating through a wind tunnel observation window and organic glass to excite the temperature-sensitive coating to emit fluorescence, recording the surface light intensity of the temperature-sensitive coating by using the high-speed camera to obtain a fluorescence image, wherein the number of the fluorescence image is 20, and performing arithmetic averaging on the surface light intensity distribution of the 20.
Further, in step S3, the calibration curve is a curve of a change rate of light intensity distribution on the surface of the temperature-sensitive coating changing with temperature, and a relational expression between the change rate of light intensity distribution on the surface of the temperature-sensitive coating and the temperature is:
wherein T is temperature, I is surface light intensity distribution of the temperature-sensitive coating after heating, and I is temperature0Is the surface light intensity distribution of the temperature sensitive coating at the beginning.
Further, the microcrystalline mica ceramic and the organic glass of the test model both satisfy the one-dimensional semi-infinite hypothesis. When parameter
And when the maximum test time is determined, the minimum wall thickness of the test model can be calculated by the formula, so that the substrate material meets the assumption of one-dimensional semi-infinite size, and is microcrystalline mica ceramic or organic glass, namely the thickness of the microcrystalline mica ceramic and the thickness of the organic glass are both greater than the minimum wall thickness.
Further, in step S4, a temperature sensitive material is sprayed on the upper surface of the organic glass to form a temperature sensitive coating, an ultraviolet excitation light source emits ultraviolet rays, the ultraviolet rays pass through the wind tunnel observation window and the organic glass and irradiate the temperature sensitive coating on the upper surface of the organic glass to excite the temperature sensitive coating to emit fluorescence, high-speed airflow passes through a gap between the flat plate and the wing rudder to cause the temperature rise of the temperature sensitive coating, a high-speed camera is used to record the surface light intensity change of the temperature sensitive coating, the surface light intensity distribution of each fluorescence image is compared with the initial average light intensity distribution to obtain the surface light intensity distribution change rate, the surface light intensity distribution change rate of a plurality of fluorescence images is compared with a calibration curve to obtain the change data of the surface temperature along with time, and then.
In step S4, the initial average light intensity distribution is an average light intensity distribution of a fluorescence image of the test device in the wind tunnel test section before the test, and the number of the fluorescence images is 20. Before the wind tunnel test, a high-speed camera is adopted to record the surface light intensity distribution of the test model in the wind tunnel test section, excitation light rays emitted by an ultraviolet excitation light source irradiate the temperature-sensitive coating on the upper surface of the organic glass to excite the temperature-sensitive coating to emit fluorescence through a wind tunnel observation window and the organic glass, the high-speed camera is used to record the surface light intensity of the temperature-sensitive coating to obtain a fluorescence image, the number of the fluorescence images is 20, and the surface light intensity distribution of the 20 fluorescence images is arithmetically averaged to obtain the initial average light intensity distribution.
Further, in steps S3 and S4, the surface heat flow calculation formula of the outside of the microcrystalline mica ceramic and the upper surface of the organic glass is as follows:
wherein q (T) is the surface heat flow rate, k is the thermal conductivity coefficient of the base material, ρ is the density of the base material, c is the specific heat of the base material, T is the effective test time, TWIn order to increase the temperature of the temperature-sensitive coating in the effective test time, the substrate material is microcrystalline mica ceramic or organic glass.
Further, in step S5, the rudder shaft is made of nichrome, a groove is formed in a windward position of the rudder shaft, the integrated thermocouple is bonded in the groove, the integrated thermocouple is preferably a high-resolution integrated thermocouple, the high-resolution integrated thermocouple is an E-type thermocouple, the anode of the E-type thermocouple is the rudder shaft, the cathode of the E-type thermocouple is constantan alloy, the diameter of a measuring point of the E-type thermocouple is 0.2mm, and the distance between the measuring points is 1 mm. The E-type thermocouple has the advantages of large thermoelectric potential, high sensitivity, good stability and the like, and the E-type thermocouple is used for measuring a rudder shaft area where a light path cannot be arranged, so that the condition that the rudder shaft transfers heat to the inside of a wing rudder gap is known, and the measurement of the local heat flow of the rudder shaft is realized by improving the measuring point density of the rudder shaft.
Further, in step S5, the calculation formula of the temperature at the rudder shaft is:
T(K)＝Ae+Be2+Ce3+De4
wherein T (K) is temperature, e is thermoelectric force, A, B, C, D is thermocouple constant, and the thermocouple constant is determined by rudder shaft material.
Further, in step S5, the calculation formula of the surface heat flow at the rudder shaft is:
wherein q (T) is a surface heat flow rate, T is a measurement temperature, k is a heat conduction coefficient of the base material, ρ is a density of the base material, c is a specific heat of the base material, T is an effective test time, and the base material is a rudder shaft.
Further, the heat flow outside the microcrystalline mica ceramic, the upper surface of the organic glass and the surface of the rudder shaft are analyzed and processed to obtain a heat flow distribution cloud chart inside the wing rudder gap and a heat flow peak value at the position of the rudder shaft. The heat flow distribution and the change trend inside the wing rudder gap can be more intuitively known through the heat flow distribution cloud picture, and the heat transfer condition from the rudder shaft area to the inside of the wing rudder gap can be known through the heat flow peak value at the rudder shaft.
Advantageous effects of the invention
1. The invention adopts the phosphorescence heat map technology to realize the measurement of large-area heat flows on the upper and lower surfaces of the gap between the flat plate and the wing rudder, obtains a heat flow distribution cloud picture in the gap of the wing rudder, is vivid and intuitive, has rich data, and can intuitively see the heat flow distribution and the change trend in the gap of the wing rudder.
2. The invention adopts the E-type thermocouple to measure the heat flux density at the rudder shaft, knows the heat transfer condition of the rudder shaft area to the inside of the wing rudder gap, and can obviously improve the capture precision of the heat flux peak value.
3. The invention adopts a high-speed camera to record the surface light intensity change of the temperature-sensitive coating, the obtained data is more detailed, and not only can the quantitative data of the heat flow be obtained, but also the distribution trend of the heat flow can be obtained.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a block diagram of a test model in an embodiment of the present invention;
FIG. 2 is a front view of a test model in an embodiment of the present invention.
Description of reference numerals:
in the figure: 1-flat plate, 2-organic glass, 3-mounting holes, 4-wing rudder, 5-microcrystalline mica ceramic, 6-E type thermocouple and 7-rudder shaft.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the following embodiments, and it should be understood that the described embodiments are some, but not all, embodiments of the present invention. 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 invention.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention.
In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise. Furthermore, the terms "mounted," "connected," and "connected" are to be construed broadly and may, for example, be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Examples
As shown in fig. 1 to 2:
a method for measuring heat flow inside a wing rudder gap and a rudder shaft comprises the following steps:
s1, manufacturing a test model, wherein the test model comprises a flat plate 1 and a wing rudder 4, a mounting hole 3 is formed in the flat plate 1, a rudder shaft 7 is fixed on the mounting hole 3 through a nut, the flat plate 1 is connected with the wing rudder 4 through the rudder shaft 7, the bottom of the wing rudder 4 is made of microcrystalline mica ceramic 5, organic glass 2 is made at the corresponding position of the flat plate 1 and the wing rudder 4, and the distance between the flat plate 1 and the wing rudder 4 after the rudder shaft 7 is fixed on the mounting hole 3 is the distance between the aircraft and the wing rudder on the surface of the aircraft;
s2, mixing the phosphor powder and the adhesive according to the mass ratio of 1:4.8-5.2 to prepare a temperature-sensitive material, wherein the adhesive consists of isopropanol and tetraethylenepentamine according to the mass ratio of 1:2.8-3.2, the temperature-sensitive material is sprayed on the outer side of the microcrystalline mica ceramic 5 at the bottom of the wing rudder 1 by a spraying pen with the caliber of 0.25mm, the spraying is carried out for 5-6 times, the thickness of the spraying is 4-5 mu m in a single time, a temperature-sensitive coating with the thickness of 20-30 mu m is formed, a test model is placed in a wind tunnel test section to carry out a test, an observation window is arranged on the side surface of the wind tunnel test section, and an ultraviolet excitation light source and a high-speed camera are;
s3, an ultraviolet excitation light source emits ultraviolet rays with the wavelength of 365nm, the ultraviolet rays irradiate the temperature-sensitive coating through the wind tunnel observation window and the organic glass 2 to excite the temperature-sensitive coating to emit fluorescence, high-speed airflow passes through a gap between the flat plate 1 and the wing rudder 4 to enable the temperature rise of the temperature-sensitive coating, the surface light intensity change of the temperature-sensitive coating is recorded by a high-speed camera, the surface light intensity distribution of each fluorescence image is compared with the initial average light intensity distribution to obtain the surface light intensity distribution change rate, the surface light intensity distribution change rate of a plurality of fluorescence images is compared with a calibration curve to obtain the change data of the surface temperature of the temperature-sensitive coating along with time, and then the surface heat flow outside the microcrystalline mica ceramic 5, namely the surface heat flow on the upper surface of the.
The initial average light intensity distribution is obtained by placing a test model in a wind tunnel test section before a wind tunnel test, recording a fluorescence image of the test model by a high-speed camera, and performing arithmetic average on the surface light intensity distribution of 20 fluorescence images in the time direction. The method comprises the steps of spraying a temperature-sensitive material on the outer side of microcrystalline mica ceramics at the bottom of a wing rudder to form a temperature-sensitive coating, placing a test model in a wind tunnel test section, before a wind tunnel test, recording the surface light intensity distribution of the test model in the wind tunnel test section by using a high-speed camera, irradiating excitation light emitted by an ultraviolet excitation light source on the temperature-sensitive coating through a wind tunnel observation window and organic glass to excite the temperature-sensitive coating to emit fluorescence, recording the surface light intensity of the temperature-sensitive coating by using the high-speed camera to obtain a fluorescence image, wherein the number of the fluorescence image is 20, and performing arithmetic averaging on the surface light intensity distribution of the 20.
The calibration curve is obtained by a calibration system, the calibration system comprises a heating flat plate, a red copper block, a microcrystalline mica ceramic plate, a high-speed camera, an ultraviolet excitation light source, a temperature acquisition module and a workstation, temperature-sensitive materials are sprayed on the microcrystalline mica ceramic plate, the microcrystalline mica ceramic plate is placed on the heating flat plate, the ultraviolet excitation light source is adopted to excite a temperature-sensitive coating, the heating flat plate starts to heat, the high-speed camera records the change of the light intensity distribution on the surface of the temperature-sensitive coating in the heating process, the temperature acquisition module obtains the real-time temperature, the workstation is adopted to store and process data, the relational expression of the change rate of the light intensity distribution on the surface of the temperature-sensitive coating and the,
wherein T is temperature, I is surface light intensity distribution of the temperature-sensitive coating after heating, and I is temperature0Is the surface light intensity distribution of the temperature sensitive coating at the beginning.
During the wind tunnel test, when the parameter is changed
When the longest test time is determined, the minimum wall thickness of the test model can be calculated by the formula, and the substrate material is ensured to meet the assumption of one-dimensional semi-infinite size, namely the substrate material is the microcrystalline mica ceramic 5, namely the thickness of the microcrystalline mica ceramic 5 is larger than the minimum wall thickness.
When the microcrystalline mica ceramic 5 satisfies the one-dimensional semi-infinite assumption, the calculation formula of the heat flow of the outer surface of the microcrystalline mica ceramic 5 is:
in the test, because the running time of the pulse wind tunnel is very short, the heat flow is not changed in the test process, and the formula (1) can be simplified as follows:
wherein k is the heat conduction coefficient of the substrate material, ρ is the density of the substrate material, c is the specific heat of the substrate material, T is the effective test time, TWIn order to increase the temperature of the temperature-sensitive coating in the effective test time, the substrate material is microcrystalline mica ceramic 5.
S4, mixing the phosphor powder and the adhesive according to the mass ratio of 1:4.8-5.2 to prepare the temperature-sensitive material, wherein the adhesive consists of isopropanol and tetraethylenepentamine according to the mass ratio of 1:2.8-3.2, spraying the temperature-sensitive material on the upper surface of the organic glass 2 by a spraying pen with the caliber of 0.25mm for 5-6 times, and spraying the temperature-sensitive material with the thickness of 4-5 microns once to form a temperature-sensitive coating with the thickness of 20-30 microns.
An ultraviolet excitation light source emits ultraviolet rays with the wavelength of 365nm, the ultraviolet rays irradiate the temperature-sensitive coating on the upper surface of the organic glass 2 through the wind tunnel observation window and the organic glass 2 to excite the temperature-sensitive coating to emit fluorescence, high-speed airflow passes through a gap between the flat plate 1 and the wing rudder 4 to enable the temperature rise of the temperature-sensitive coating, a high-speed camera is used for recording the surface light intensity change of the temperature-sensitive coating, the surface light intensity distribution of each fluorescence image is compared with the initial average light intensity distribution to obtain the surface light intensity distribution change rate, the surface light intensity distribution change rate of a plurality of fluorescence images is compared with a calibration curve to obtain the change data of the surface temperature of the temperature-sensitive coating along with time, and then the surface heat flow of the upper surface of the organic glass 2, namely.
The initial average light intensity distribution is obtained by placing a test model in a wind tunnel test section before a wind tunnel test, recording a fluorescence image of the test model by a high-speed camera, and performing arithmetic average on the surface light intensity distribution of 20 fluorescence images in the time direction. The method comprises the steps of spraying a temperature-sensitive material on the upper surface of organic glass to form a temperature-sensitive coating, placing a test model in a wind tunnel test section, before a wind tunnel test, recording the surface light intensity distribution of the test model in the wind tunnel test section by using a high-speed camera, irradiating excitation light emitted by an ultraviolet excitation light source on the temperature-sensitive coating on the upper surface of the organic glass through a wind tunnel observation window and the organic glass to excite the temperature-sensitive coating to emit fluorescence, recording the surface light intensity of the temperature-sensitive coating by using the high-speed camera to obtain a fluorescence image, wherein the number of the fluorescence image is 20, and performing arithmetic averaging on the surface light intensity distribution of the.
The calibration curve is obtained by a calibration system, the calibration system comprises a heating flat plate, a red copper block, an organic glass plate, a high-speed camera, an ultraviolet excitation light source, a temperature acquisition module and a workstation, a temperature-sensitive material is sprayed on the organic glass plate, the organic glass plate is placed on the heating flat plate, the ultraviolet excitation light source is adopted to excite a temperature-sensitive coating, the heating flat plate starts to be heated, the high-speed camera records the change of the light intensity distribution on the surface of the temperature-sensitive coating in the heating process, the temperature acquisition module obtains the real-time temperature, the workstation is adopted to store and process data, the relational expression of the change rate of the light intensity distribution on the surface of the temperature-sensitive coating,
wherein T is temperature, I is surface light intensity distribution of the temperature-sensitive coating after heating, and I is temperature0Is the surface light intensity distribution of the temperature sensitive coating at the beginning.
During the wind tunnel test, when the parameter is changed
Time, the temperature at time x can be considered asThe degree is not changed, a is the thermal diffusivity of the substrate material, tau is the test time, after the longest test time is determined, the minimum wall thickness of the test model can be calculated by the formula, the substrate material is ensured to meet the assumption of one-dimensional semi-infinite, and the substrate material is the organic glass 2, namely the thickness of the organic glass 2 is larger than the minimum wall thickness.
When the organic glass 2 satisfies the one-dimensional semi-infinite assumption, the surface heat flow calculation formula of the upper surface of the organic glass 2 is as follows:
wherein k is the heat conduction coefficient of the substrate material, ρ is the density of the substrate material, c is the specific heat of the substrate material, T is the effective test time, TWIn order to raise the temperature of the temperature-sensitive coating within the effective test time, the substrate material is organic glass 2.
S5, the rudder shaft 7 is made of nickel-chromium alloy, a groove is formed in the windward part of the rudder shaft 7, the E-shaped thermocouple 7 is bonded in the groove, the positive electrode of the E-shaped thermocouple is the rudder shaft, the negative electrode of the E-shaped thermocouple is constantan alloy, the diameter of a measuring point is 0.2mm, the distance between the measuring points is 1mm, an output signal of the E-shaped thermocouple 7 enters a computer through amplification and A/D conversion, the potential measured by the E-shaped thermocouple 7 is converted into temperature, and the calculation formula is as follows:
T(K)＝Ae+Be2+Ce3+De4
where, t (k) is temperature, e is thermoelectric potential, A, B, C, D is thermocouple constant, a is 17.022525, B is-2.209724 × 10-1，C＝5.4809314×10-3，D＝-5.7669892×10-5。
In the effective running time of the wind tunnel test, the E-type thermocouple 7 meets the semi-infinite expansion assumption of the one-dimensional heat conduction principle, the surface heat flow can be calculated through the temperature, and the calculation formula is as follows:
the following differential format is used when the data is actually processed by linear interpolation:
wherein q (T) is a surface heat flow rate, T is a measurement temperature, k is a heat conduction coefficient of the base material, ρ is a density of the base material, c is a specific heat of the base material, T is an effective test time, and the base material is the rudder shaft 7.
And S6, processing the obtained surface heat flows of the upper surface and the lower surface of the gap and the surface heat flow at the position of the rudder shaft to obtain a heat flow distribution cloud picture in the wing rudder gap and a heat flow peak value at the position of the rudder shaft.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.
Claims (10)
1. A wing rudder gap internal and rudder shaft heat flow measuring method is characterized in that: the method comprises the following steps:
s1, manufacturing a test model, wherein the test model comprises a flat plate and a wing rudder, the flat plate is connected with the wing rudder through a rudder shaft, the bottom of the wing rudder is made of microcrystalline mica ceramic, and the corresponding part of the flat plate and the wing rudder is made of organic glass;
s2, spraying a temperature-sensitive material on the outer side of the microcrystalline mica ceramic at the bottom of the wing rudder to form a temperature-sensitive coating, placing a test model in a wind tunnel test section to perform a wind tunnel test, wherein a wind tunnel observation window is arranged on the side surface of the wind tunnel test section, and an ultraviolet excitation light source and a high-speed camera are arranged outside the wind tunnel observation window;
s3, irradiating ultraviolet rays emitted by an ultraviolet excitation light source onto the temperature-sensitive coating through a wind tunnel observation window and organic glass to excite the temperature-sensitive coating to emit fluorescence, enabling high-speed airflow to pass through a gap between a flat plate and a wing rudder to enable the temperature-sensitive coating to generate temperature rise, recording the surface light intensity change of the temperature-sensitive coating by using a high-speed camera, comparing the surface light intensity distribution of each fluorescence image with the initial average light intensity distribution to obtain the surface light intensity distribution change rate, comparing the surface light intensity distribution change rate of a plurality of fluorescence images with a calibration curve to obtain the change data of the surface temperature along with time, and further calculating the surface heat flow outside the microcrystalline mica ceramic;
s4, spraying a temperature-sensitive material on the upper surface of the organic glass to form a temperature-sensitive coating, and repeating the step S3 to obtain surface heat flow on the upper surface of the organic glass;
and S5, distributing the integrated thermocouples in the area of the rudder shaft, obtaining the temperature of the rudder shaft, and calculating the surface heat flow of the rudder shaft.
2. The method for measuring the heat flow inside the wing rudder gap and the rudder shaft according to claim 1, wherein the method comprises the following steps: in the steps S2 and S4, the temperature-sensitive material is composed of phosphor powder and an adhesive, the mass ratio of the phosphor powder to the adhesive is 1:4.8-5.2, the adhesive is composed of tetraethylenepentamine and isopropanol, and the mass ratio of the isopropanol to the tetraethylenepentamine is 1: 2.8-3.2.
3. The method for measuring the heat flow inside the wing rudder gap and the rudder shaft according to claim 1, wherein the method comprises the following steps: in the steps S2 and S4, the spraying is carried out by a spraying pen, the caliber of the spraying pen is 0.25mm, the spraying times are 5-6 times, the thickness of single spraying is 4-5 microns, and the thickness of the temperature-sensitive coating is 20-30 microns.
4. The method for measuring the heat flow inside the wing rudder gap and the rudder shaft according to claim 1, wherein the method comprises the following steps: in step S3, the wavelength of the ultraviolet light is 365nm, the initial average light intensity distribution is an average light intensity distribution of a fluorescence image of the test device in the wind tunnel test section before the test, the number of the fluorescence image is 20, the calibration curve is a curve of a change rate of light intensity distribution on the surface of the temperature sensitive coating changing with temperature, and a relational expression between the change rate of light intensity distribution on the surface of the temperature sensitive coating and the temperature is:
wherein T is temperature, I is surface light intensity distribution of the temperature-sensitive coating after heating, and I is temperature0Is the surface light intensity distribution of the temperature sensitive coating at the beginning.
5. The method for measuring the heat flow inside the wing rudder gap and the rudder shaft according to claim 1, wherein the method comprises the following steps: the microcrystalline mica ceramic and the organic glass of the test model both meet the assumption of one-dimensional semi-infinite.
6. The method for measuring the heat flow inside the wing rudder gap and the rudder shaft according to claim 5, wherein the method comprises the following steps: in step S3 and step S4, the calculation formula of the surface heat flow of the outside of the microcrystalline mica ceramic and the upper surface of the organic glass is as follows:
wherein q (T) is the surface heat flow rate, k is the thermal conductivity coefficient of the base material, ρ is the density of the base material, c is the specific heat of the base material, T is the effective test time, TWIn order to increase the temperature of the temperature-sensitive coating in the effective test time, the substrate material is microcrystalline mica ceramic or organic glass.
7. The method for measuring the heat flow inside the wing rudder gap and the rudder shaft according to claim 1, wherein the method comprises the following steps: in step S5, the rudder shaft is made of nichrome, a groove is formed in the windward side of the rudder shaft, the integrated thermocouple is bonded in the groove, the integrated thermocouple is an E-type thermocouple, the positive electrode of the E-type thermocouple is the rudder shaft, the negative electrode of the E-type thermocouple is constantan alloy, the diameter of the measuring points of the E-type thermocouple is 0.2mm, and the distance between the measuring points is 1 mm.
8. The method for measuring the heat flow inside the wing rudder gap and the rudder shaft according to claim 1, wherein the method comprises the following steps: in step S5, the calculation formula of the temperature at the rudder shaft is as follows:
T(K)＝Ae+Be2+Ce3+De4
where T (K) is temperature, e is thermoelectric potential, and A, B, C, D is thermocouple constant.
9. The method for measuring the heat flow inside the wing rudder gap and the rudder shaft according to claim 1, wherein the method comprises the following steps: in step S5, the calculation formula of the surface heat flow at the rudder shaft is:
wherein q (T) is a surface heat flow rate, T is a measurement temperature, k is a heat conduction coefficient of the base material, ρ is a density of the base material, c is a specific heat of the base material, T is an effective test time, and the base material is a rudder shaft.
10. The method for measuring the heat flow inside the wing rudder gap and the rudder shaft according to claim 1, wherein the method comprises the following steps: and analyzing and processing the heat flow of the outer side of the microcrystalline mica ceramic, the upper surface of the organic glass and the surface of the rudder shaft to obtain a heat flow distribution cloud chart inside the wing rudder gap and a heat flow peak value at the position of the rudder shaft.
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