CN114860000B - Temperature rise and drop control device and method for airplane pneumatic thermal environment simulation test - Google Patents

Temperature rise and drop control device and method for airplane pneumatic thermal environment simulation test Download PDF

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CN114860000B
CN114860000B CN202210786192.8A CN202210786192A CN114860000B CN 114860000 B CN114860000 B CN 114860000B CN 202210786192 A CN202210786192 A CN 202210786192A CN 114860000 B CN114860000 B CN 114860000B
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air
temperature
box
tested piece
homogenizing
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CN114860000A (en
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陆林
王彬文
秦强
刘宁夫
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AVIC Aircraft Strength Research Institute
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AVIC Aircraft Strength Research Institute
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    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
    • G05D23/00—Control of temperature
    • G05D23/19—Control of temperature characterised by the use of electric means
    • G05D23/20—Control of temperature characterised by the use of electric means with sensing elements having variation of electric or magnetic properties with change of temperature
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/60—Testing or inspecting aircraft components or systems
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M99/00—Subject matter not provided for in other groups of this subclass
    • G01M99/002—Thermal testing
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M99/00—Subject matter not provided for in other groups of this subclass
    • G01M99/005—Testing of complete machines, e.g. washing-machines or mobile phones
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N25/00—Investigating or analyzing materials by the use of thermal means
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation

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Abstract

The invention discloses a temperature rise and drop control device and method for an aircraft pneumatic thermal environment simulation test, wherein the device comprises an air homogenizing box, an air conveying mechanism arranged at the upper part of the air homogenizing box and used for providing cold air, and a heating mechanism arranged at the lower part of the air homogenizing box and used for heating a tested piece, wherein a first temperature sensor used for collecting the temperature of the tested piece is arranged on the tested piece, so that the heating and cooling of the tested piece are realized, the surface temperature of the tested piece can be repeatedly and rapidly changed, and the true pneumatic thermal environment of the aircraft during hypersonic flight can be conveniently simulated. The method comprises the following steps: firstly, determining a temperature rise and drop control target curve of an airplane pneumatic thermal environment simulation test; secondly, performing an airplane pneumatic thermal environment simulation test; thirdly, heating operation; and fourthly, the temperature is reduced, so that the surface temperature of the tested piece is repeatedly adjusted and collected, and the accuracy and flexibility of the aircraft pneumatic thermal environment simulation test are enhanced.

Description

Temperature rise and drop control device and method for airplane pneumatic thermal environment simulation test
Technical Field
The invention belongs to the technical field of airplane pneumatic thermal environment simulation tests, and particularly relates to a temperature rise and drop control device and method for airplane pneumatic thermal environment simulation tests.
Background
When the aircraft flies at a high supersonic speed in the atmosphere, air is severely compressed and viscosity-retarded, airflow in a boundary layer of the surface of the aircraft generates strong friction, the airflow speed is reduced to a wall surface, kinetic energy is irreversibly converted into heat energy, so that the temperature in the boundary layer is rapidly increased, the surface temperature of the aircraft is increased, and the phenomenon is the phenomenon of aerodynamic heating of the high-speed aircraft.
In the process of simulating the aerodynamic thermal environment of the high-speed aircraft through a ground test, the temperature rise stage of a measured object can be well simulated at present, but the temperature reduction stage for simulating the measured object mainly depends on natural cooling, when the actual temperature reduction rate of the aircraft is too high, the natural cooling rate in the ground test is not enough to simulate the actual situation, effective tests cannot be carried out, the situation that the test result is incomplete easily occurs, and therefore whether the measured object fails in a real service state or not cannot be judged.
Therefore, a controllable temperature rise and fall device is needed to be designed, so that the temperature rise and fall links can be added conveniently in the ground test simulation process, and the ground test simulation can be as close to the real pneumatic thermal environment of the aircraft as possible.
Disclosure of Invention
The invention aims to solve the technical problem that the defects in the prior art are overcome, and provides a temperature rise and fall control device for an airplane pneumatic thermal environment simulation test.
In order to solve the technical problems, the invention adopts the technical scheme that: the utility model provides a pneumatic hot environmental simulation test of aircraft is with control device that heats up and cools down which characterized in that: the device comprises an air homogenizing box, an air conveying mechanism arranged at the upper part of the air homogenizing box and used for providing cold air, and a heating mechanism arranged at the lower part of the air homogenizing box and used for heating a tested piece, wherein a first temperature sensor used for collecting the temperature of the tested piece is arranged on the tested piece;
the gas homogenizing box is a bottomless hollow box, a first gas homogenizing plate, a second gas homogenizing plate and a fixing plate are sequentially arranged in the gas homogenizing box from bottom to top, the inner space of the gas homogenizing box is divided into a cooling layer positioned at the upper part and a gas transmission layer positioned at the lower part through the fixing plate, and the upper part of the gas homogenizing box is provided with exhaust holes for gas in the cooling layer to overflow;
the air conveying mechanism comprises an air exchange valve and a proportional valve which are arranged on the upper part of the air homogenizing box, the air exchange valve is connected with an air compressor, a first vent pipe used for conveying cold air to the cooling layer and a second vent pipe used for being connected with the proportional valve are arranged on the air exchange valve, and a third vent pipe used for conveying cold air to the air conveying layer is arranged on the proportional valve;
the heating mechanism comprises two wiring units and two quartz lamps, the wiring units are arranged on two sides of the gas homogenizing box respectively, the quartz lamps are arranged between the two wiring units, the quartz lamps are located on the lower portion of the gas homogenizing box, and the tested piece is located on the lower portion of the quartz lamps.
Foretell pneumatic hot environmental simulation of aircraft is with controlling means that heats up and cools down, its characterized in that: the third vent pipe conveys cold air into the air conveying layer through the air collecting box, the air collecting box is embedded in the center of the upper portion of the air homogenizing box, the upper end of the air collecting box extends out of the air homogenizing box and is communicated with the third vent pipe, the lower end of the air collecting box is open and extends into the air conveying layer, and an exhaust fan is arranged in the air collecting box.
The temperature rise and fall control device for the airplane pneumatic thermal environment simulation test is characterized in that: the first air homogenizing plate is provided with a plurality of first air homogenizing holes, the second air homogenizing plate is provided with a plurality of second air homogenizing holes, and the first air homogenizing holes and the second air homogenizing holes are distributed in a staggered mode.
Foretell pneumatic hot environmental simulation of aircraft is with controlling means that heats up and cools down, its characterized in that: the sum of the hole areas of the first air homogenizing holes and the sum of the hole areas of the second air homogenizing holes are smaller than the inner cross section area of the third air passing pipe.
The temperature rise and fall control device for the airplane pneumatic thermal environment simulation test is characterized in that: the wiring unit is in including being located the hollow copper pipe of even gas box lower part and setting on the hollow copper pipe and the wiring copper post that the power cable is connected, the wiring copper post is worn to establish on the even gas box and stretch out to the top of even gas box, a plurality of confessions have been seted up on the hollow copper pipe the mounting groove of quartz lamp installation, it is a plurality of the mounting groove is followed the length direction of hollow copper pipe is laid side by side.
The temperature rise and fall control device for the airplane pneumatic thermal environment simulation test is characterized in that: the utility model discloses a gas homogenizing box, including hollow copper pipe, water storage chamber, inlet tube, outlet pipe, even gas homogenizing box, mounting groove, the inside of hollow copper pipe is provided with the baffle and is located the water storage chamber of baffle top, still be provided with on the hollow copper pipe with communicating inlet tube in water storage chamber and outlet pipe, the inlet tube with the outlet pipe is all worn to establish just stretch out to on the even gas box the top of even gas box, the mounting groove is located the lower part of baffle.
The temperature rise and fall control device for the airplane pneumatic thermal environment simulation test is characterized in that: the tested piece is also provided with a second temperature sensor, the first temperature sensor is positioned in the center of the tested piece, and the second temperature sensor is positioned at the edge of the tested piece.
Meanwhile, the invention also discloses a method for controlling temperature rise and drop by using the temperature rise and drop control device for the aircraft pneumatic thermal environment simulation test, which has simple steps and convenient operation, realizes the repeated adjustment and collection of the surface temperature of the tested piece, and enhances the accuracy and flexibility of the aircraft pneumatic thermal environment simulation test, and is characterized by comprising the following steps:
step one, determining a temperature rise and drop control target curve of an airplane pneumatic thermal environment simulation test: determining a temperature rise and decrease control target curve of a tested piece in a pneumatic thermal environment simulation test according to the actual situation of the pneumatic thermal environment of the airplane in the flying process, wherein the temperature rise and decrease control target curve is a time-temperature curve, and the time-temperature curve is divided into a temperature rise section and a temperature decrease section;
step two, carrying out an airplane pneumatic thermal environment simulation test: heating and cooling the tested piece, and continuously acquiring a real-time temperature value on the tested piece through a first temperature sensor to enable the real-time temperature value to accord with a temperature value of corresponding time in the time-temperature curve;
when the test is carried out to the temperature rising section, executing a step three; when the test is carried out to the cooling section, executing the step four;
step three, heating operation: starting a quartz lamp, heating the tested piece, and changing the temperature rise speed of the tested piece by adjusting the power of the quartz lamp when the real-time temperature value has deviation with the temperature value of the corresponding time in the time-temperature curve, so that the real-time temperature value conforms to the temperature value of the corresponding time in the time-temperature curve;
meanwhile, the scavenging valve is adjusted, and cold air is continuously conveyed into the cooling layer of the air homogenizing box through the first vent pipe to cool the air homogenizing box;
step four, cooling operation: and closing the quartz lamp, adjusting the ventilation valve, conveying cold air into the air conveying layer of the air homogenizing box through the proportional valve, dispersing the cold air to the surface of the tested piece through the first air homogenizing plate and the second air homogenizing plate, cooling the tested piece, and when the real-time temperature value is deviated from the temperature value of the corresponding time in the time temperature curve, adjusting the opening degree of the proportional valve to further adjust the air pressure of the cold air in the air conveying layer and change the cooling speed of the tested piece, so that the real-time temperature value is in accordance with the temperature value of the corresponding time in the time temperature curve.
Compared with the prior art, the invention has the following advantages:
1. the tested piece is a testing piece of an airplane component, the heating mechanism is arranged to facilitate heating of the tested piece, so that the surface temperature of the tested piece is raised, the air conveying mechanism is arranged to facilitate conveying of cold air into the air homogenizing box, so that the cold air is conveyed to the surface of the tested piece as uniformly as possible through the air homogenizing box, the surface temperature of the tested piece is uniformly and rapidly reduced, the temperature rise and fall control in the airplane pneumatic thermal environment simulation test is realized, the simulation test is closer to the real pneumatic thermal environment when the airplane flies at hypersonic speed, and the use effect is good.
2. According to the invention, the fixed plate is arranged in the air homogenizing box, so that the internal space of the air homogenizing box is conveniently divided into the temperature reduction layer positioned at the upper part of the fixed plate and the air transmission layer positioned at the lower part of the fixed plate, when the temperature of the tested piece is required to be raised, the quartz lamp starts to work, at the moment, the air homogenizing box can also be subjected to the heat radiation of the quartz lamp, so that the temperature of the air homogenizing box is gradually raised, and the air exchange valve is arranged, so that the cold air is conveniently conveyed into the temperature reduction layer in the air homogenizing box through the first air pipe, the temperature of the air homogenizing box is favorably reduced, and the service life of the air homogenizing box is prolonged; when the tested piece needs to be cooled, the quartz lamp stops working, and the air exchange valve conveys cold air to the air conveying layer in the air homogenizing box, so that the cold air is blown to the tested piece as uniformly as possible, the device is reliable and stable, and the flexibility is strong.
3. The proportional valve is arranged, so that the size of cold air flow conveyed to the air collecting box can be controlled conveniently according to the temperature requirements of different stages in the test, the cold air is dispersed by the exhaust fan in the air collecting box, and the circulation speed of the cold air is increased, so that the cooling speed of the tested piece is increased, the test time is ensured, the control on the cooling speed of the tested piece is realized, and the test accuracy is improved.
4. According to the invention, through arranging the first air-homogenizing plate and the second air-homogenizing plate, the cold air is conveniently dispersed in the air conveying layer in the air-homogenizing box as uniformly as possible, and is blown to the surface of the tested piece from the lower part of the first air-homogenizing plate, so that the tested piece can uniformly receive the cold air as uniformly as possible, and thus the tested piece can be uniformly and rapidly cooled, the problem that the central temperature and the edge temperature of the tested piece are inconsistent is avoided, the aerodynamic heat condition of an airplane during hypersonic flight is better met, the accuracy and the authenticity of the test are effectively improved, and the practicability is strong.
5. The method provided by the invention has the advantages that the steps are simple, the operation is convenient and fast, the temperature of the tested piece is repeatedly adjusted by adjusting the lifting temperature control device, the real-time temperature value of the tested piece is continuously acquired by the first temperature sensor, the real-time temperature value of the tested piece changing along with time is convenient to determine to conform to a test lifting temperature control target curve, the simulation test is closer to the real pneumatic thermal environment when the airplane flies at hypersonic speed, the accuracy and flexibility of the simulation test of the pneumatic thermal environment of the airplane are enhanced, and the popularization and the use are convenient.
In summary, the lifting temperature control device adopted by the invention is convenient for heating the tested piece by arranging the heating mechanism so as to raise the surface temperature of the tested piece, and is convenient for uniformly and rapidly lowering the surface temperature of the tested piece by arranging the air transmission mechanism so as to simulate the real aerodynamic thermal environment of the airplane during hypersonic flight; the adopted temperature rise and fall control method has simple steps and convenient operation, realizes the repeated adjustment and collection of the surface temperature of the tested piece, enhances the accuracy and flexibility of the aircraft pneumatic thermal environment simulation test, and is convenient for popularization and use.
The technical solution of the present invention is further described in detail by the accompanying drawings and embodiments.
Drawings
FIG. 1 is a schematic structural diagram of a lift temperature control device according to the present invention.
Fig. 2 is a schematic view of the internal structure of the elevating temperature control device according to the present invention.
FIG. 3 is a block diagram of a method flow of the present invention.
Description of reference numerals:
1-homogenizing box; 2-a scavenging valve; 3-proportional valve;
4, a gas collecting box; 5-a first vent pipe; 6-a second vent pipe;
7-a third vent pipe; 8-a first gas homogenizing plate; 9-a first air homogenizing hole;
10-a second gas homogenizing plate; 11-second air homogenizing holes; 12, fixing a plate;
13-exhaust hole; 14-quartz lamp; 15-a piece under test;
16-hollow copper tube; 17-connecting copper columns; 18-a water inlet pipe;
19-water outlet pipe; 20, mounting a groove; 21-a partition plate;
22-a water storage cavity; 23-a handle; 24 — a first temperature sensor;
25-second temperature sensor.
Detailed Description
As shown in fig. 1 and 2, the temperature rise and decrease control device for aircraft pneumatic thermal environment simulation test of the present invention includes a gas homogenizing box 1, a gas transmission mechanism disposed on the upper portion of the gas homogenizing box 1 for providing cold gas, and a heating mechanism disposed on the lower portion of the gas homogenizing box 1 for heating a tested piece 15, wherein a first temperature sensor 24 for collecting the temperature of the tested piece 15 is disposed on the tested piece 15.
The gas homogenizing box 1 is a bottomless hollow box, a first gas homogenizing plate 8, a second gas homogenizing plate 10 and a fixing plate 12 are sequentially arranged in the gas homogenizing box 1 from bottom to top, the inner space of the gas homogenizing box 1 is divided into a cooling layer located at the upper part and a gas transmission layer located at the lower part through the fixing plate 12, and the upper part of the gas homogenizing box 1 is provided with a vent hole 13 for gas in the cooling layer to overflow and disperse.
The air delivery mechanism is including setting up scavenging valve 2 and proportional valve 3 on even gas box 1 upper portion, scavenging valve 2 is connected with the air compressor machine, be provided with on the scavenging valve 2 be used for to cooling layer carries air conditioning's first breather pipe 5 with be used for with the second breather pipe 6 that proportional valve 3 is connected, be provided with on the proportional valve 3 be used for to air delivery layer carries air conditioning's third breather pipe 7.
The heating mechanism comprises two wiring units which are respectively arranged at two sides of the gas homogenizing box 1 and a quartz lamp 14 which is arranged between the two wiring units, the quartz lamp 14 is positioned at the lower part of the gas homogenizing box 1, and the tested piece 15 is positioned at the lower part of the quartz lamp 14.
The tested piece 15 is a testing piece of an airplane part, the shape of the tested piece 15 is not limited, the tested piece 15 is convenient to heat by arranging the heating mechanism in a pneumatic thermal simulation test of the airplane part, the surface temperature of the tested piece 15 is increased, cold air is convenient to convey into the air homogenizing box 1 by arranging the air conveying mechanism, and therefore the cold air is conveyed to the surface of the tested piece 15 through the air homogenizing box 1 as uniformly as possible, the surface temperature of the tested piece 15 is uniformly and quickly reduced, the temperature rise and fall control in the pneumatic thermal environment simulation test of the airplane is realized, the simulation test is closer to the real pneumatic thermal environment of the airplane, and the use effect is good.
When the uniform gas box is actually used, the fixing plate 12 is arranged in the uniform gas box 1, so that the internal space of the uniform gas box 1 is conveniently divided into a cooling layer positioned at the upper part of the fixing plate 12 and a gas transmission layer positioned at the lower part of the fixing plate 12, when a tested piece 15 needs to be heated, the quartz lamp 14 starts to work, at the moment, the uniform gas box 1 can also receive the heat radiation of the quartz lamp 14, the temperature of the uniform gas box 1 is gradually increased, the ventilation valve 2 is arranged, so that the cold gas is conveniently conveyed to the cooling layer in the uniform gas box 1 through the first ventilation pipe 5, and the cold gas overflowing in the cooling layer is discharged through the exhaust hole 13, the temperature of the uniform gas box 1 is favorably reduced, and the service life of the uniform gas box 1 is prolonged; when the temperature of the tested piece 15 needs to be reduced, the quartz lamp 14 stops working, the air exchange valve 2 conveys cold air into the proportional valve 3 through the second vent pipe 6, the proportional valve 3 conveys the cold air into the air conveying layer in the air homogenizing box 1 through the third vent pipe 7, and therefore the cold air is blown to the tested piece 15 as uniformly as possible, the device is reliable and stable, and the flexibility is strong; wherein, the number of the exhaust holes 13 is at least four, and the four exhaust holes 13 are respectively positioned at four corners of the top of the air homogenizing box 1.
It should be noted that, handles 23 are respectively arranged on two opposite outer side walls of the gas homogenizing box 1, so that during testing, the handles 23 on two sides of the gas homogenizing box 1 are erected on the bracket, the gas homogenizing box 1 is separated from the test bed or the ground by a certain distance, and the tested piece 15 is placed on the test bed or the ground, so that the tested piece 15 is located below the quartz lamp 14.
In this embodiment, the third vent pipe 7 conveys cold air into the gas transmission layer through the gas collecting box 4, the gas collecting box 4 is embedded in the central position of the upper part of the gas homogenizing box 1, the upper end of the gas collecting box 4 extends out of the gas homogenizing box 1 and is communicated with the third vent pipe 7, the lower end of the gas collecting box 4 is open and extends into the gas transmission layer, and the gas collecting box 4 is internally provided with an exhaust fan.
During the in-service use, gas collection box 4 passes the upper portion and the fixed plate 12 of even gas box 1, air conditioning gets into gas collection box 4 back, send into the gas transmission layer of even gas box through the exhaust fan, through setting up proportional valve 3, be convenient for according to the temperature requirement of different stages in the experiment, the adjustment is carried to the air conditioning air current size of gas collection box 4, rethread exhaust fan in the gas collection box 4 makes the air conditioning dispersion, strengthen the speed that air conditioning circulates simultaneously, thereby both strengthened the cooling rate by test piece 15, the test time is guaranteed, realized the control to the cooling rate of test piece 15 again, the accuracy nature of experiment has been improved.
In this embodiment, the first gas homogenizing plate 8 is provided with a plurality of first gas homogenizing holes 9, the second gas homogenizing plate 10 is provided with a plurality of second gas homogenizing holes 11, and the plurality of first gas homogenizing holes 9 and the plurality of second gas homogenizing holes 11 are arranged in a staggered manner.
When in actual use, the plurality of first air homogenizing holes 9 are arranged on the first air homogenizing plate 8 in a plum blossom shape, the plurality of second air homogenizing holes 11 are arranged on the second air homogenizing plate 10, cold air in the air collecting box 4 is convenient to be conveyed between the second air homogenizing plate 10 and the first air homogenizing plate 8 through the plurality of second air homogenizing holes 11, the cold air is dispersed between the second air homogenizing plate 10 and the first air homogenizing plate 8, the concentration of the cold air is preliminarily reduced, the uniformity of the distribution is improved again when the cold air is conveyed to the outer side of the air homogenizing box 1 through the plurality of first air homogenizing holes 9 by arranging the plurality of first air homogenizing holes 9 on the first air homogenizing plate 8 and arranging the plurality of first air homogenizing holes 9 and the plurality of second air homogenizing holes 11 in a staggered manner, and the purpose of uniformly dispersing the cold air in the air conveying layer in the air homogenizing box 1 as uniformly as possible is achieved, and then make the surface of being tested piece 15 evenly receive air conditioning as far as possible to make and being tested piece 15 evenly and cool down fast, avoided air conditioning at the center of being tested piece 15 excessively concentrate, thereby avoid being tested piece 15 the central point put with marginal position cooling rate inconsistent, make the test result accord with the aerodynamic heating condition of aircraft when hypersonic flight more, effectively improved aerodynamic heating simulation test's accuracy and authenticity.
In this embodiment, the sum of the hole areas of the first air homogenizing holes 9 and the sum of the hole areas of the second air homogenizing holes 11 are both smaller than the inner cross section area of the third vent pipe 7, so that the pressure of the gas passing through the first air homogenizing holes 9 and the second air homogenizing holes 11 is greater than the pressure of the gas in the third vent pipe 7, thereby preventing the pressure of the cold gas from dropping after passing through the air homogenizing box 1, and reducing the cooling effect on the tested piece 15; wherein, the inner cross section of the third vent pipe 7 is circular.
In this embodiment, the wiring unit is in including being located the hollow copper pipe 16 of even gas box 1 lower part and setting the wiring copper post 17 that just supplies the cable to connect on the hollow copper pipe 16, wiring copper post 17 wears to establish just stretch out to on the even gas box 1's top, a plurality of confessions have been seted up on the hollow copper pipe 16 the mounting groove 20 of 14 installations of quartz lamp, it is a plurality of mounting groove 20 is followed hollow copper pipe 16's length direction lays side by side.
During the in-service use, the quantity of hollow copper pipe 16 is two, the cable is through wiring copper post 17 and hollow copper pipe 16 to quartz lamp 14 power supply, quartz lamp 14's quantity is a plurality of, a plurality of quartz lamps 14 are laid side by side between two hollow copper pipes 16, insert the both ends of quartz lamp 14 respectively in the mounting groove 20 of the hollow copper pipe 16 of even gas box 1 both sides, the realization is to quartz lamp 14's installation, through setting up a plurality of mounting grooves 20 along hollow copper pipe 16's length direction side by side, lay a plurality of quartz lamps 14 of being convenient for install, the work efficiency of heating mechanism is improved.
In this embodiment, a partition 21 and a water storage cavity 22 located above the partition 21 are disposed inside the hollow copper tube 16, the hollow copper tube 16 is further provided with a water inlet tube 18 and a water outlet tube 19 communicated with the water storage cavity 22, and the water inlet tube 18 and the water outlet tube 19 are both arranged on the gas homogenizing box 1 in a penetrating manner and extend out to the upper side of the gas homogenizing box 1.
During the in-service use, before the experiment begins to when the experiment finishes, continuously pour into the cooling water into in 22 to the water storage chamber through inlet tube 18, the cooling water that overflows in the rethread outlet pipe 19 discharge water storage chamber 22 makes the continuous circulation in 22 in the water storage chamber of process of the test have the cooling water, is convenient for reduce hollow copper pipe 16's temperature, has improved the security of technical staff operation.
It should be noted that the mounting groove 20 is located at the lower portion of the partition 21, that is, at the lower portion of the water storage cavity 22, so as to avoid affecting the water storage cavity 22.
In this embodiment, the device under test 15 is further provided with a second temperature sensor 25, the first temperature sensor 24 is located at the center of the device under test 15, and the second temperature sensor 25 is located at the edge of the device under test 15.
During the in-service use, through set up first temperature sensor 24 at the central point of being tested 15, be convenient for gather the temperature of the central point of being tested 15, through set up second temperature sensor 25 at the border position of being tested 15, be convenient for gather the temperature of the border position of being tested 15, be favorable to the technical staff to obtain the temperature of being tested 15 in the different positions of experimentation, be convenient for analysis test result, and through adjusting heating mechanism and gas transmission mechanism, make the temperature of being tested 15 each position all accord with experimental requirement.
As shown in fig. 3, a method for controlling the temperature of the aircraft by using the temperature raising and lowering control device for the aircraft pneumatic thermal environment simulation test includes the following steps:
step one, determining a temperature rise and drop control target curve of an airplane pneumatic thermal environment simulation test: the method comprises the steps that the pneumatic thermal environment of an airplane in the flying process changes along with the flying time, a temperature rise and fall control target curve of a tested piece 15 in a pneumatic thermal environment simulation test is determined according to actual conditions, the temperature rise and fall control target curve is a time temperature curve and represents the change of the temperature of the tested piece 15 in the test time, and the time temperature curve is divided into a temperature rise section and a temperature fall section.
Step two, carrying out an airplane pneumatic thermal environment simulation test: heating and cooling the tested piece 15, and continuously acquiring a real-time temperature value on the tested piece 15 through a first temperature sensor 24, so that the real-time temperature value conforms to a temperature value of corresponding time in the time-temperature curve; when the test is carried out to the temperature rising section, executing a step three; and when the test is carried out to the cooling section, executing the step four.
Step three, heating operation: and starting the quartz lamp 14, heating the tested piece 15, and when the real-time temperature value has deviation with the temperature value of the corresponding time in the time-temperature curve, changing the temperature rise speed of the tested piece 15 by adjusting the power of the quartz lamp 14 so as to enable the real-time temperature value to accord with the temperature value of the corresponding time in the time-temperature curve.
During actual operation, the real-time temperature value of the tested piece 15 and the temperature value corresponding to the time point in the time temperature curve are compared once every minute, the phenomenon that the deviation of the temperature value of the tested piece 15 is too large due to overlong interval time is avoided, and the power of the quartz lamp 14 is adjusted by changing the voltage of the cable connected with the wiring copper column 17.
Meanwhile, the ventilation valve 2 is adjusted to continuously convey cold air into the cooling layer of the air homogenizing box 1 through the first ventilation pipe 5, and the air homogenizing box 1 is cooled.
During the actual test, connect air compressor machine and scavenging valve 2, carry air conditioning to scavenging valve 2 through the air compressor machine, continuously carry air conditioning in the cooling layer of even gas box 1 through first breather pipe 5 to through the exhaust hole 13 on even gas box 1 upper portion excessive air conditioning in the cooling layer of discharging, make the cooling layer of even gas box 1 continuously play the effect that reduces even gas box 1 temperature, improved experimental security.
Step four, cooling operation: and closing the quartz lamp 14, adjusting the scavenging valve 2, conveying cold air into the air delivery layer of the air homogenizing box 1 through the proportional valve 3, dispersing the cold air to the surface of the tested piece 15 through the first air homogenizing plate 8 and the second air homogenizing plate 10, cooling the tested piece 15, and when the real-time temperature value has deviation with the temperature value of the corresponding time in the time temperature curve, adjusting the opening degree of the proportional valve 3 to further adjust the air pressure of the cold air in the air delivery layer, and changing the cooling speed of the tested piece 15 so that the real-time temperature value conforms to the temperature value of the corresponding time in the time temperature curve.
During actual test, the adjustment of cold air conveying capacity is realized by adjusting the opening degree of the proportional valve 3, so that the cold air quantity reaching the surface of the tested piece 15 is adjusted, the control of the cooling speed of the tested piece 15 is realized, and the change condition of the real-time temperature value of the tested piece 15 along with time is consistent with the temperature-time curve.
It should be noted that the real-time temperature value acquired by the first temperature sensor 24 is the real-time temperature value of the central position of the tested piece 15, and the real-time temperature value of the edge position of the tested piece 15 is continuously acquired by the second temperature sensor 25, so that a technician can compare the real-time temperature values of the central position and the edge position of the tested piece 15, adjust the test scheme, and obtain a more real and effective test result.
The invention realizes the repeated regulation and collection of the surface temperature of the tested piece 15, so that the real-time temperature value of the tested piece 15 changing along with time accords with the temperature rise and drop control target curve of the test, thereby realizing the aircraft pneumatic thermal environment simulation test of the tested piece of the aircraft component, and having strong test accuracy and flexibility.
In this embodiment, in step one, continuously pour into the cooling water into through inlet tube 18 in to the water storage chamber 22 in the hollow copper pipe 16, the cooling water that overflows in rethread outlet pipe 19 discharge water storage chamber 22 for the cooling water continuously circulates in the water storage chamber 22 in the hollow copper pipe 16, realizes the cooling to hollow copper pipe 16, avoids quartz lamp 14 during operation, and the temperature of hollow copper pipe 16 is too high, causes the potential safety hazard to technical staff.
And after the test time is met, the quartz lamp 14 and the air compressor are turned off, and the deformation condition of the tested piece 15 is observed, so that a preliminary test result of the aircraft pneumatic thermal environment simulation test is obtained.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and all simple modifications, changes and equivalent structural changes made to the above embodiment according to the technical spirit of the present invention still fall within the protection scope of the technical solution of the present invention.

Claims (8)

1. The utility model provides a pneumatic hot environmental simulation test of aircraft is with control device that heats up and cools down which characterized in that: the device comprises an air homogenizing box (1), an air conveying mechanism arranged at the upper part of the air homogenizing box (1) and used for providing cold air, and a heating mechanism arranged at the lower part of the air homogenizing box (1) and used for heating a tested piece (15), wherein a first temperature sensor (24) used for collecting the temperature of the tested piece (15) is arranged on the tested piece (15);
the gas homogenizing box (1) is a bottomless hollow box, a first gas homogenizing plate (8), a second gas homogenizing plate (10) and a fixing plate (12) are sequentially arranged in the gas homogenizing box (1) from bottom to top, the inner space of the gas homogenizing box (1) is divided into a cooling layer positioned at the upper part and a gas conveying layer positioned at the lower part through the fixing plate (12), and the upper part of the gas homogenizing box (1) is provided with a vent hole (13) for gas in the cooling layer to overflow;
the air delivery mechanism comprises a scavenging valve (2) and a proportional valve (3) which are arranged at the upper part of the air homogenizing box (1), the scavenging valve (2) is connected with an air compressor, a first vent pipe (5) used for delivering cold air to the cooling layer and a second vent pipe (6) used for being connected with the proportional valve (3) are arranged on the scavenging valve (2), and a third vent pipe (7) used for delivering cold air to the air delivery layer is arranged on the proportional valve (3);
heating mechanism includes that two set up respectively the wiring unit on even gas box (1) both sides is in with the setting two quartz lamp (14) between the wiring unit, quartz lamp (14) are located the lower part of even gas box (1), it is located to be tested piece (15) the lower part of quartz lamp (14).
2. The temperature rise and fall control device for the aircraft pneumatic thermal environment simulation test according to claim 1, wherein: the third vent pipe (7) conveys cold air to the air conveying layer through the air collecting box (4), the air collecting box (4) is embedded in the central position of the upper part of the air homogenizing box (1), the upper end of the air collecting box (4) extends out of the air homogenizing box (1) and is communicated with the third vent pipe (7), the lower end of the air collecting box (4) is open and extends into the air conveying layer, and an exhaust fan is arranged in the air collecting box (4).
3. The temperature rise and fall control device for the aircraft pneumatic thermal environment simulation test according to claim 1, wherein: a plurality of first air homogenizing holes (9) are formed in the first air homogenizing plate (8), a plurality of second air homogenizing holes (11) are formed in the second air homogenizing plate (10), and the first air homogenizing holes (9) and the second air homogenizing holes (11) are distributed in a staggered mode.
4. The temperature rise and fall control device for the aircraft pneumatic thermal environment simulation test according to claim 3, wherein: the sum of the hole areas of the first air homogenizing holes (9) and the sum of the hole areas of the second air homogenizing holes (11) are smaller than the inner cross section area of the third air passing pipe (7).
5. The temperature rise and fall control device for the aircraft pneumatic thermal environment simulation test according to claim 1, wherein: the wiring unit is in including hollow copper pipe (16) and the setting that are located even gas box (1) lower part hollow copper pipe (16) are gone up and supply wiring copper post (17) that the cable is connected, wiring copper post (17) are worn to establish go up and stretch out to even gas box (1) the top of even gas box (1), hollow copper pipe (16) are last to have seted up a plurality of confessions mounting groove (20) of quartz lamp (14) installation, and are a plurality of mounting groove (20) are followed the length direction of hollow copper pipe (16) is laid side by side.
6. The temperature rise and fall control device for the aircraft pneumatic thermal environment simulation test according to claim 5, wherein: the inside of hollow copper pipe (16) is provided with baffle (21) and is located water storage chamber (22) of baffle (21) top, hollow copper pipe (16) go up still be provided with communicating inlet tube (18) in water storage chamber (22) and outlet pipe (19), inlet tube (18) with outlet pipe (19) are all worn to establish even gas box (1) is gone up and is stretched out to the top of even gas box (1), mounting groove (20) are located the lower part of baffle (21).
7. The temperature rise and fall control device for the aircraft pneumatic thermal environment simulation test according to claim 1, wherein: the tested piece (15) is also provided with a second temperature sensor (25), the first temperature sensor (24) is positioned at the center of the tested piece (15), and the second temperature sensor (25) is positioned at the edge of the tested piece (15).
8. A method for controlling the temperature of a heating and cooling device for an aircraft aerodynamic thermal environment simulation test according to claim 1, the method comprising the steps of:
step one, determining a temperature rise and drop control target curve of an airplane pneumatic thermal environment simulation test: determining a temperature rise and fall control target curve of a tested piece (15) in a pneumatic thermal environment simulation test according to the actual situation of the pneumatic thermal environment of the airplane in the flying process, wherein the temperature rise and fall control target curve is a time-temperature curve, and the time-temperature curve is divided into a temperature rise section and a temperature fall section;
step two, carrying out an airplane pneumatic thermal environment simulation test: heating and cooling the tested piece (15), and continuously acquiring a real-time temperature value on the tested piece (15) through a first temperature sensor (24) to enable the real-time temperature value to be in accordance with a temperature value of corresponding time in the time-temperature curve;
when the test is carried out to the temperature rising section, executing a step three; when the test is carried out to the cooling section, executing the step four;
step three, heating operation: starting a quartz lamp (14), heating the tested piece (15), and when the real-time temperature value has deviation with the temperature value of the corresponding time in the time-temperature curve, changing the temperature rise speed of the tested piece (15) by adjusting the power of the quartz lamp (14) to make the real-time temperature value conform to the temperature value of the corresponding time in the time-temperature curve;
meanwhile, the air exchange valve (2) is adjusted, and cold air is continuously conveyed into the cooling layer of the air homogenizing box (1) through the first air pipe (5) to cool the air homogenizing box (1);
step four, cooling operation: the quartz lamp (14) is closed, the ventilation valve (2) is adjusted, cold air is conveyed to the air delivery layer of the air homogenizing box (1) through the proportional valve (3), then the cold air is dispersed to the surface of the tested piece (15) through the second air homogenizing plate (10) and the first air homogenizing plate (8) in sequence, the tested piece (15) is cooled, when the real-time temperature value is deviated from the temperature value of the corresponding time in the time temperature curve, the opening degree of the proportional valve (3) is adjusted, the air pressure of the cold air in the air delivery layer is further adjusted, the cooling speed of the tested piece (15) is changed, and the real-time temperature value is made to accord with the temperature value of the corresponding time in the time temperature curve.
CN202210786192.8A 2022-07-06 2022-07-06 Temperature rise and drop control device and method for airplane pneumatic thermal environment simulation test Active CN114860000B (en)

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