CN103398835A - System and method for testing transient air film cooling heat flow on basis of hypersonic-velocity gun air tunnel - Google Patents
System and method for testing transient air film cooling heat flow on basis of hypersonic-velocity gun air tunnel Download PDFInfo
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- CN103398835A CN103398835A CN2013103666541A CN201310366654A CN103398835A CN 103398835 A CN103398835 A CN 103398835A CN 2013103666541 A CN2013103666541 A CN 2013103666541A CN 201310366654 A CN201310366654 A CN 201310366654A CN 103398835 A CN103398835 A CN 103398835A
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Abstract
The invention discloses a system and a method for testing a transient air film cooling heat flow on the basis of a hypersonic-velocity gun air tunnel. The testing system comprises a pressure sensor, a synchronous controller, a heat flow sensor, a digital signal collector and a computer, wherein the pressure sensor is used for detecting pressure inside a cavity of the air tunnel and connected with the synchronous controller through an amplifier; the synchronous controller generates a triggering signal according to a pressure signal amplified by the amplifier, and the triggering signal is used for controlling the time for the surface of an air film cooling model inside an experimental cabin to generate an air film cooling jet stream; the heat flow sensor is arranged on the surface of the air film cooling model, and an output end of the heat flow sensor is connected with the computer through the digital signal collector; a control end of the digital signal collector is connected to the synchronous controller, and the digital signal collector collects data from the heat flow sensor according to the work sequence of the synchronous controller; and the computer is used for controlling the work sequence of the synchronous controller and storing heat flow data collected by the digital signal collector. The system and the method provide conditions for measuring transient air film cooling heat flow data under the hypersonic-velocity flow incoming condition.
Description
Technical field
The present invention relates to the cooling fields of measurement of air film, especially, relate to the cooling transient heat flow test macro of a kind of air film based on hypersonic gun wind tunnel and method.
Background technology
Air film is cooling is that a kind of typical case in supersonic speed/hypersonic research field is flowed, and especially aspect optical imagery, has wider application.The cooling effect of air film is normally assessed by measuring its heat flux distribution.Under conventional atmospheric environment, measure the cooling heat flux distribution of air film comparatively simple, but if in supersonic speed, or even difficulty is larger in hypersonic air-flow, to measure the air film heat flux.On ground, carry out the cooling heat flow measurement of hypersonic air film, hypersonic wind tunnel equipment need to be arranged, transient heat flow measuring technique, and corresponding method of testing.Because hypersonic gun wind tunnel is a millisecond magnitude working time, transient heat flow is measured except the problem that will solve measuring technology itself, also will consider that wind tunnel operation, air film move, heat flow measurement three's synchro control.Because air film can be worked under different inlet flow conditions, even without the situation such as flowing, and the air film of studying under hypersonic condition is cooling significant in Practical Project, is also simultaneously one of difficult point of research at present such as hypersonic, supersonic speed, subsonic speed.Because most of hypersonic wind tunnels are impulse wind tunnels, working time is very short, so obviously, the cooling heat flux distribution of research air film under this condition, the operation of air film and heat flux measurement system must be in advance in the foundation of Flow Field in Wind Tunnel.If before Flow Field in Wind Tunnel is set up, air film is opened too early, and the cooling effect of air film can make the heat flux sensor that is arranged in the test model surface excessively pre-cooled, thus the measuring error while increasing wind tunnel operation.A cover can accurately be controlled the air film unlatching, the heat flow measurement system is opened and synchro control and measuring system and the method for wind tunnel operation so must design.At present, there is no the cooling transient heat flow method of testing of the air film that can be used in hypersonic gun wind tunnel and system.
Summary of the invention
The object of the invention is to provide the cooling transient heat flow test macro of a kind of air film based on hypersonic gun wind tunnel and method, to solve the technical matters that in hypersonic gun wind tunnel environment, the cooling transient heat flow of air film is difficult to test.
For achieving the above object, the technical solution used in the present invention is as follows:
The cooling transient heat flow test macro of a kind of air film based on hypersonic gun wind tunnel, this hypersonic gun wind tunnel comprise high pressure section, film chamber, low pressure stage, jet pipe and the Laboratory Module that connects successively, and this test macro comprises:
Pressure transducer for detection of the film cavity pressure;
Pressure transducer is connected with isochronous controller through amplifier, and isochronous controller generates trigger pip according to the pressure signal after amplifier amplifies, and trigger pip is for controlling the opportunity of being located at the cooling jet flow of air film cooling jig Surface Creation air film in Laboratory Module;
Air film cooling jig surface is provided with heat flux sensor, and the output terminal of heat flux sensor connects computing machine through the digital signal acquiring device;
The control end of digital signal acquiring device is connected to isochronous controller, and the digital signal acquiring device is according to the work schedule collection of the isochronous controller data from heat flux sensor;
Computing machine is for the work schedule of controlling isochronous controller and the heat flow data of storing the collection of digital signal acquiring device.
Further, the output terminal of isochronous controller is connected with the solid-state relay that amplifies trigger pip, and solid-state relay is connected with for opening or cut out the solenoid valve of the cooling jet flow of air film.
Further, heat flux sensor comprises constant voltage power supply circuit and is located at the bridge diagram of constant voltage power supply circuit two ends for output voltage values, and at least one brachium pontis of bridge diagram is provided with thin-film thermistor.
Further, heat flux sensor is a plurality of, on air film cooling jig surface, forms the heat flux sensor array.
According to a further aspect in the invention, also provide a kind of air film based on hypersonic gun wind tunnel cooling transient heat flow method of testing, comprise the following steps:
Open hypersonic gun wind tunnel;
Detect the force value in hypersonic gun wind tunnel film chamber;
When the force value moment rising in the film chamber, open the cooling jet flow of air film so that be positioned at the foundation that the cooling air film of the air film cooling jig surface formation of Laboratory Module is not later than hypersonic gun wind tunnel;
Measure the heat flow data on air film cooling jig surface.
Further, heat flow data is for to measure and to be stored in computing machine through heat flux sensor.
Further, heat flux sensor is in running order before carrying out the step of opening hypersonic gun wind tunnel.
Further, heat flux sensor comprises constant voltage power supply circuit and is located at the bridge diagram of constant voltage power supply circuit two ends for output voltage values, and at least one brachium pontis of bridge diagram is provided with thin-film thermistor.
Further, heat flux sensor is a plurality of, on air film cooling jig surface, forms the heat flux sensor array, be used to measuring the heat flow data of a plurality of positions, synchronization air film cooling jig surface.
The present invention has following beneficial effect:
the present invention is based on the cooling transient heat flow test macro of air film and the method for hypersonic gun wind tunnel, by measuring the force value in hypersonic gun wind tunnel film chamber, make the start-up time of the cooling jet flow of air film in Flow Field in Wind Tunnel, set up a little in advance, to guarantee when Flow Field in Wind Tunnel is set up, cooling jet flow is also set up simultaneously, and due to the force value by in detection wind-tunnel die cavity, trigger the foundation of cooling jet flow, avoided cooling jet flow to open in advance the operating overload of the heat flux sensor that causes too early, thereby provide condition for measuring the cooling transient heat flow data of air film under hypersonic inlet flow conditions, and pass through the control of the work schedule of isochronous controller, guaranteed wind tunnel operation, the air film operation, and the heat flow measurement three's is synchronous.
Except purpose described above, feature and advantage, the present invention also has other purpose, feature and advantage.Below with reference to figure, the present invention is further detailed explanation.
The accompanying drawing explanation
The accompanying drawing that forms the application's a part is used to provide a further understanding of the present invention, and schematic description and description of the present invention the present invention does not form inappropriate limitation of the present invention for explaining.In the accompanying drawings:
Fig. 1 is the three-dimensional structure schematic diagram of the preferred embodiment of the present invention based on the cooling transient heat flow test macro of the air film of hypersonic gun wind tunnel;
Fig. 2 is the principle schematic of hypersonic gun wind tunnel in the preferred embodiment of the present invention;
Fig. 3 is the planar structure schematic diagram of Fig. 1;
Fig. 4 is that the cooling jet flow of air film of the present invention forms the principle schematic of cooling air film under the environment of hypersonic jet flow;
Fig. 5 is the circuit theory diagrams of preferred embodiment of the present invention heat flux sensor;
Fig. 6 is the flow chart of steps of the preferred embodiment of the present invention based on the cooling transient heat flow method of testing of the air film of hypersonic gun wind tunnel;
Fig. 7 is the work schedule schematic diagram of the preferred embodiment of the present invention based on the cooling transient heat flow method of testing of the air film of hypersonic gun wind tunnel.
Embodiment
Below in conjunction with accompanying drawing, embodiments of the invention are elaborated, but the multitude of different ways that the present invention can be defined by the claims and cover is implemented.
With reference to Fig. 1 and Fig. 3, the preferred embodiments of the present invention provide a kind of air film based on hypersonic gun wind tunnel cooling transient heat flow test macro, and this hypersonic gun wind tunnel comprises high pressure section 1, film chamber 7, low pressure stage 2, jet pipe 6 and the Laboratory Module 9 that connects successively.This test macro comprises:
Air film cooling jig 100 surfaces are provided with heat flux sensor 11, and the output terminal of heat flux sensor 11 connects computing machine 16 through digital signal acquiring device 12;
The control end of digital signal acquiring device 12 is connected to isochronous controller 14, and digital signal acquiring device 12 is according to the work schedule collection of isochronous controller 14 data from heat flux sensor 11;
the embodiment of the present invention is based on the cooling transient heat flow test macro of the air film of hypersonic gun wind tunnel, by measuring the force value in hypersonic gun wind tunnel film chamber, make the start-up time of the cooling jet flow of air film in Flow Field in Wind Tunnel, set up a little in advance, to guarantee when Flow Field in Wind Tunnel is set up, cooling jet flow is also set up simultaneously, by the force value that detects in die cavity 7, trigger the start-up time that air film is set up simultaneously, the heat flux sensor operating overload of having avoided the start-up time of air film to cause too early, and cause when hypersonic air-flow is come model surface, heat flux sensor can't Measurement accuracy fault.The embodiment of the present invention is by the pressure in the die cavity 7 that detects wind-tunnel setting up opportunity according to the pressure activated air film that detects, both guaranteed the air film coolant flow field early than or be synchronized with the foundation in supersonic flow flow field, avoid again the too early foundation of air film to guarantee the heat flux sensor nonoverload, thereby provide condition for accurately measuring the cooling transient heat flow data of air film under hypersonic inlet flow conditions, and pass through the control of the work schedule of isochronous controller, guaranteed wind tunnel operation, air film operation, reached the synchronous of heat flow measurement three.
With reference to Fig. 2 and Fig. 3, in the present embodiment, hypersonic gun wind tunnel comprises high pressure section 1, film chamber 7, low pressure stage 2, jet pipe 6 and the Laboratory Module 9 that connects successively, wherein film chamber 7 is formed by two high pressure section diaphragms 4 of folder film machine 3 clampings, between low pressure stage 2 and jet pipe 6, through folder film machine 3, be provided be used to stopping the low pressure stage diaphragm 5 of low pressure stage 2 and jet pipe 6, in low pressure stage 2, be provided with lightweight piston 8.Hypersonic gun wind tunnel mainly for generation of high hypersonic air flow to carry out wind tunnel experiment, concrete principle of work is as follows: during test, gas in high pressure section 1 and low pressure stage 2 is charged to the required pressure of test, in film chamber 7, also be inflated to certain pressure, guarantee that the high pressure section diaphragm 4 between high pressure section 1 and film chamber 7 does not break, high pressure section diaphragm 4 between film chamber 7 and low pressure stage 2 does not break, and the pressure differential of balance high pressure section 1 with low pressure stage 2 high-low pressure gases played in film chamber 7; The gas in release film chamber 7, break in two high pressure section diaphragms 4 priority under the pressure differential effect between high pressure section 1 and low pressure stage 2 of 7 both sides, film chamber fast.At this moment, gases at high pressure enter into rapidly low pressure stage 2 and promote lightweight piston 8 and advance to the right, and under the effect of high pressure, lightweight piston 8 movement velocitys are very fast, can be at the front formation normal shock wave of lightweight piston 8.When arriving low pressure stage diaphragm 5, launches normal shock wave, run into the lightweight piston 8 that advances, shock wave reflection is carried out repeatedly, low pressure stage 2 gas in pipelines are constantly compressed, its pressure, temperature are improved, pressure is brought up to a certain degree, low pressure stage diaphragm 5 breaks, high temperature and high pressure gas enters jet pipe 6 and expands, and reaches required hypersonic air-flow and enters Laboratory Module 9, and air film cooling jig 100 can namely can carry out hypersonic aerodynamic experiment in Laboratory Module 9.
It should be noted that, be to be determined by the gas in low pressure stage 2 working time of hypersonic gun wind tunnel.Because this part gas enters jet pipe 6, Laboratory Module 9 as the medium that flows.After these gases were finished, wind-tunnel was end of run.Typically the working time of this class wind-tunnel facilities, be 20ms the working time of the hypersonic gun wind tunnel in this programme in the millisecond magnitude.Although on macroscopic view the working time of wind-tunnel very short, enough for hypersonic flow.Usually be 3～5ms the Time Created of Hypersonic Flow Field.Here need clear and definite several concept, the wind tunnel operation time refers to the time of wind-tunnel stable operation after Hypersonic Flow Field is set up.And the foundation of Hypersonic Flow Field refers to that design point that tunnel airstream reaches Flow Field in Wind Tunnel from setting in motion during this period of time, could stable operation after setting up.In addition, the Startup time of wind-tunnel refers to the moment (being exactly generally to exit at that moment in the film chamber) of impelling artificially wind-tunnel to open, and start to wind-tunnel stable operation from wind-tunnel, finishes its time overall length also only for about 200ms.So so the short time has proposed higher requirement for testing apparatus, and sensitive and sequential that measure that must be enough is controllable.Otherwise may also measure, do not start, wind-tunnel is end of run just, so just can't measure the parameter in true flow field.So the measurement of testing apparatus constantly must be just within the time of wind tunnel operation or a little in advance in wind tunnel operation.Hypersonic gun wind tunnel equipment generally is difficult to do long-play in addition.Therefore, in order to guarantee on the surface of air film cooling jig 100, to form cooling air film when Hypersonic Flow Field is set up, the start-up time of the cooling jet flow of air film will be a little earlier in the foundation of Flow Field in Wind Tunnel.In the present embodiment, with reference to Fig. 3, the output terminal of isochronous controller 14 is connected with the solid-state relay 13 that amplifies trigger pip, and solid-state relay 13 is connected with for opening or cut out the solenoid valve of the cooling jet flow of air film.When the pressure transducer 17 of the force value for detection of in film chamber 7 detects film chamber 7 internal pressures and raises suddenly, the output signal of pressure transducer 17 is input isochronous controller 14 after amplifier 15 amplifies, isochronous controller 14 is according to the low level trigger pip of sequential output that sets in advance, this trigger pip triggers solenoid valve again and opens cooling jet flow after solid-state relay 13 boosts, from trigger pip to opening cooling jet flow, usually need 50ms, thereby guaranteed synchronizeing of Hypersonic Flow Field and cooling jet flow.
With reference to Fig. 4, in the present embodiment, the provided upstream of air film cooling jig 100 is in respect of air film cooled nozzle 10, and this air film cooled nozzle 10 has and first shrinks the profile of expanding afterwards, air-flow can be accelerated to supersonic speed.And ejection is accelerated by this air film cooled nozzle 10 in the chamber of staying before gas path pipe enters spout again by gas cylinder in the source of air-flow.In order to control the switch of air-flow, on gas circuit, be provided with solenoid valve, and the control signal wire of solenoid valve is connected to isochronous controller 14 through solid-state relay 13.When isochronous controller 14 output trigger pip, solenoid valve is opened, form cooling jet flow B, meanwhile, through hypersonic gun wind tunnel, set up Hypersonic Flow Field A, between Hypersonic Flow Field A and cooling jet flow B, form very thin cooling air film, be arranged on the transient heat flow data of the heat flux sensor 11 on air film cooling jig 100 surfaces for detection of the cooling jet flow B under Hypersonic Flow Field A effect.
Existing model surface heat flow measurement technology can be divided into two classes: a class is the thermo-mapping technique that carries out the large tracts of land measurement; The another kind of heat flow measurement technology that is based on sensor.Wherein, thermo-mapping technique comprises infrared chart, look heating figure, phase transformation thermal map and fluorescence thermal map etc.This class technology is once tested the heat flux distribution that just can obtain whole audience scope, and without on model, punching, and demonstration is more directly perceived, is a kind of method of heat flow measurement based on optical measuring technique.But this class methods measuring system complexity, price is high; Affected by imaging system, curvature changes larger part meeting distortion; Look as indicator becomes, the phase-change material spraying coating process is tighter.In general, the existing thermo-mapping technique response time is relatively long, be suitable for long wind-tunnel working time, and the thermo-mapping technique of gun wind tunnel still is in conceptual phase.Sensor-based heat flow measurement technology utilization heat transfer sensor (as film heat transfer sensor, thin-walled or heavy wall calorimeter etc.) is measured the hot-fluid of partial points.This class Technical Development History is longer, comparative maturity, belong to classical measurement technology one class, although its test space precision is limited, and will beat the installation of sensors hole on model, what have changed the local geometric shape, thereby introduction measuring error, but because its precision is high, the response fast, testing apparatus is simple, still as main means of testing, is widely adopted.
In the present embodiment, adopt sensor-based heat flow measurement technology, with reference to Fig. 5, the calorimetric circuit of heat flux sensor 11 comprises constant pressure source U0 and a plurality of bridge diagram parallel with one another.Bridge diagram be wheatstone bridge circuits, wherein arm resistance R, Rf, Rs are precision resistance, arm resistance Rs connects with thin-film thermistor Rd.Arm resistance Rf, Rs all arrange in pairs or groups according to thin-film thermistor Rd resistance at room temperature, so that bridge diagram initial output at room temperature is as far as possible little, in avoiding testing, output voltage surpasses the range of data acquisition system (DAS).Wherein, the pass between the output voltage values Ui of thin-film thermistor Rd and bridge diagram is:
By output voltage values Ui, can converse the resistance of thin-film thermistor Rd, and the resistance temperature relation of thin-film thermistor Rd has good linear within the specific limits, its relation can be with representing:
In following formula, R0 is the resistance of thin-film thermistor in the time of 0 ℃, and α is temperature-coefficient of electrical resistance, and Δ R is resistance change, and Δ T is temperature variation.
Preferably, heat flux sensor 11 is a plurality of, on air film cooling jig 100 surfaces, forms the heat flux sensor array.Due to the resistance difference of each heat flux sensor 11, need to bridge diagram be set respectively for each heat flux sensor 11.
According to a further aspect in the invention, also provide a kind of air film based on hypersonic gun wind tunnel cooling transient heat flow method of testing, with reference to Fig. 6, comprise the following steps:
Step S10: open hypersonic gun wind tunnel;
In the present embodiment, will in the high pressure section of hypersonic gun wind tunnel 1, low pressure stage 2 and film chamber 7, be filled with the gas of different pressures, and the people is for impelling film chamber 7 Rapid degassings, wind-tunnel starts.Because pressure reduction raises, cause the high pressure section diaphragm 4 near high pressure section 1 one sides to break, the gases at high pressure in high pressure section 1 enter film chamber 7, make the 7 internal pressure moment risings of film chamber.
Step S20: detect the force value in hypersonic gun wind tunnel film chamber 7;
Film chamber 7 is provided with the pressure transducer 17 for detection of film chamber 7 internal pressure values, and when force value moment in film chamber 7 raise, pressure transducer 17 generated step signals.
Step S30: when the force value moment rising in film chamber 7, open the cooling jet flow of air film so that be positioned at the foundation that the cooling air film of the air film cooling jig 100 surface formation of Laboratory Module 9 is not later than hypersonic gun wind tunnel;
In the present embodiment, pressure transducer 17 connects isochronous controller 14 through amplifier 15, the output terminal of isochronous controller 14 is through solid-state relay 13 connected electromagnetic valves, and solenoid valve is positioned to air film cooled nozzle 10 to be provided on the gas circuit of source of the gas, and solenoid valve is for controlling the conducting of gas circuit or cutting out.When the force value moment rising in film chamber 7, the step signal of pressure transducer 17 outputs is exported to isochronous controller 14 after amplifier 15 amplifies, and isochronous controller 14 generates trigger pip according to default work schedule.The embodiment of the present invention is by the pressure in the die cavity 7 that detects wind-tunnel setting up opportunity according to the pressure activated air film that detects, both guaranteed the air film coolant flow field early than or be synchronized with the foundation in supersonic flow flow field, avoid again the too early foundation of air film to guarantee the heat flux sensor nonoverload, thereby provide condition for accurately measuring the cooling transient heat flow data of air film under hypersonic inlet flow conditions, and pass through the control of the work schedule of isochronous controller, guaranteed wind tunnel operation, air film operation, reached the synchronous of heat flow measurement three.In the present embodiment, the trigger pip voltage of isochronous controller 14 outputs only has 5V, through solid-state relay 13, the voltage of trigger pip is promoted to 24V, to trigger solenoid valve, opens, thereby 10 places form cooling jet flow B at the air film cooled nozzle, and cooling jet flow B covers the surface of air film cooling jig 100.
Step S40: the heat flow data of measuring air film cooling jig 100 surfaces.
The surface of air film cooling jig 100 arranges heat flux sensor 11, and heat flux sensor 11 detects the heat flow data on air film cooling jig 100 surfaces.Preferably, individual in the present embodiment, on air film cooling jig 100 surfaces, a plurality of heat flux sensors 11 are being arranged respectively, to form the heat flux sensor array, be used to measuring the heat flow data of synchronization air film cooling jig 100 surperficial a plurality of positions.The output data of heat flux sensor array in digital signal acquiring device 12 is stored to computing machine 16 for follow-up analysis.
Preferably, heat flux sensor 11 is in running order before execution step S10, like this, when Hypersonic Flow Field A and cooling jet flow B formation, the cooling transient heat flow data of air film under the hypersonic inlet flow conditions of heat flux sensor 11 energy Measurement accuracy, wherein, the start-up time of air film only than the foundation of supersonic speed gun wind tunnel too much in advance constantly, only need the left and right than the Zao 20ms of wind tunnel operation, avoid heat flux sensor 11 overloads.
Preferably, the heat flux sensor 11 in the present embodiment comprises constant voltage power supply circuit and is located at the bridge diagram of constant voltage power supply circuit two ends for output voltage values, and at least one brachium pontis of bridge diagram is provided with thin-film thermistor.
Fig. 7 shows the work schedule schematic diagram of the preferred embodiment of the present invention based on the cooling transient heat flow method of testing of the air film of hypersonic gun wind tunnel.The present invention is based on the cooling transient heat flow test macro of air film and the method for hypersonic gun wind tunnel, by measuring the force value in hypersonic gun wind tunnel film chamber 7, make the start-up time of the cooling jet flow of air film in Flow Field in Wind Tunnel, set up a little in advance, to guarantee when Flow Field in Wind Tunnel is set up, cooling jet flow is also set up simultaneously, thereby provide condition for measuring the cooling transient heat flow data of air film under hypersonic inlet flow conditions, and guaranteed heat flux sensor 11 nonoverloads, accurately measured the cooling transient heat flow data of air film under hypersonic inlet flow conditions.The embodiment of the present invention, by the control of the work schedule of isochronous controller 14, has guaranteed wind tunnel operation, air film operation, has reached the synchronous of heat flow measurement three.
These are only the preferred embodiments of the present invention, be not limited to the present invention, for a person skilled in the art, the present invention can have various modifications and variations.Within the spirit and principles in the present invention all, any modification of doing, be equal to replacement, improvement etc., within all should being included in protection scope of the present invention.
Claims (9)
1. cooling transient heat flow test macro of the air film based on hypersonic gun wind tunnel, described hypersonic gun wind tunnel comprises high pressure section (1), film chamber (7), low pressure stage (2), jet pipe (6) and the Laboratory Module (9) that connects successively, it is characterized in that
Comprise the pressure transducer (17) for detection of described film chamber (7) internal pressure;
Described pressure transducer (17) is connected with isochronous controller (14) through amplifier (15), described isochronous controller (14) generates trigger pip according to the pressure signal after described amplifier (15) amplifies, and described trigger pip is for controlling the opportunity of being located at the cooling jet flow of the interior air film cooling jig of described Laboratory Module (9) (100) Surface Creation air film;
Described air film cooling jig (100) surface is provided with heat flux sensor (11), and the output terminal of described heat flux sensor (11) connects computing machine (16) through digital signal acquiring device (12);
The control end of described digital signal acquiring device (12) is connected to described isochronous controller (14), and described digital signal acquiring device (12) is according to the work schedule collection of described isochronous controller (14) data from described heat flux sensor (11);
Described computing machine (16) is be used to the work schedule of controlling described isochronous controller (14) and the heat flow data of storing described digital signal acquiring device (12) collection.
2. the cooling transient heat flow test macro of the air film based on hypersonic gun wind tunnel according to claim 1, is characterized in that,
The output terminal of described isochronous controller (14) is connected with the solid-state relay (13) that amplifies described trigger pip, and described solid-state relay (13) is connected with for opening or cut out the solenoid valve of the cooling jet flow of air film.
3. the cooling transient heat flow test macro of the air film based on hypersonic gun wind tunnel according to claim 1, is characterized in that,
Described heat flux sensor (11) comprises constant voltage power supply circuit and is located at the bridge diagram of described constant voltage power supply circuit two ends for output voltage values, and at least one brachium pontis of described bridge diagram is provided with thin-film thermistor.
4. the cooling transient heat flow test macro of the air film based on hypersonic gun wind tunnel according to claim 3, is characterized in that,
Described heat flux sensor (11) is a plurality of, on described air film cooling jig (100) surface, forms the heat flux sensor array.
5. the cooling transient heat flow method of testing of the air film based on hypersonic gun wind tunnel, is characterized in that, comprises the following steps:
Open hypersonic gun wind tunnel;
Detect the interior force value in film chamber (7) of hypersonic gun wind tunnel;
When the force value moment rising in described film chamber (7), open the cooling jet flow of air film so that be positioned at the foundation that the cooling air film of air film cooling jig (100) the surface formation of Laboratory Module (9) is not later than hypersonic gun wind tunnel;
Measure the heat flow data on described air film cooling jig (100) surface.
6. the cooling transient heat flow method of testing of the air film based on hypersonic gun wind tunnel according to claim 5, is characterized in that,
Described heat flow data is in computing machine (16) is measured and be stored to heat flux sensor (11).
7. the cooling transient heat flow method of testing of the air film based on hypersonic gun wind tunnel according to claim 6, is characterized in that,
Described heat flux sensor (11) is in running order before the step of carrying out the hypersonic gun wind tunnel of described unlatching.
8. the cooling transient heat flow method of testing of the air film based on hypersonic gun wind tunnel according to claim 6, is characterized in that,
Described heat flux sensor (11) comprises constant voltage power supply circuit and is located at the bridge diagram of described constant voltage power supply circuit two ends for output voltage values, and at least one brachium pontis of described bridge diagram is provided with thin-film thermistor.
9. the cooling transient heat flow method of testing of the air film based on hypersonic gun wind tunnel according to claim 6, is characterized in that,
Described heat flux sensor (11) is a plurality of, on described air film cooling jig (100) surface, forms the heat flux sensor array, be used to measuring the heat flow data of the surperficial a plurality of positions of the described air film cooling jig of synchronization (100).
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