CN103398835B - Based on gaseous film control transient heat flow test macro and the method for hypersonic gun wind tunnel - Google Patents
Based on gaseous film control transient heat flow test macro and the method for hypersonic gun wind tunnel Download PDFInfo
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- CN103398835B CN103398835B CN201310366654.1A CN201310366654A CN103398835B CN 103398835 B CN103398835 B CN 103398835B CN 201310366654 A CN201310366654 A CN 201310366654A CN 103398835 B CN103398835 B CN 103398835B
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Abstract
The invention discloses a kind of gaseous film control transient heat flow test macro based on hypersonic gun wind tunnel and method, this test macro comprises: for detecting the pressure transducer of wind-tunnel 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 amplification, and trigger pip generates the opportunity of gaseous film control jet flow for controlling to be located at gaseous film control model surface in Laboratory Module; Gaseous film control model surface is provided with heat flux sensor, and the output terminal of heat flux sensor connects computing machine through digital signal acquiring device; The control end of digital signal acquiring device is connected to isochronous controller, and digital signal acquiring device is according to the data of the work schedule collection of isochronous controller from heat flux sensor; Computing machine is used for the work schedule of control synchronization controller and stores the heat flow data of digital signal acquiring device collection.The present invention is that under the hypersonic inlet flow conditions of measurement, the transient heat flow data of gaseous film control provide condition.
Description
Technical field
The present invention relates to gaseous film control fields of measurement, especially, relate to a kind of gaseous film control transient heat flow test macro based on hypersonic gun wind tunnel and method.
Background technology
Gaseous film control is the one typical case flowing in supersonic speed/hypersonic research field, especially in optical imagery, has wider application.The effect of gaseous film control is normally assessed by measuring its heat flux distribution.The heat flux distribution measuring gaseous film control under ordinary atmosphere is comparatively simple, if but will in supersonic speed, or even then difficulty is larger to measure gaseous film control hot-fluid in hypersonic air-flow.Ground is carried out the heat flow measurement of hypersonic gaseous film control, need hypersonic wind tunnel equipment, transient heat flow measuring technique, and corresponding method of testing.Because hypersonic gun wind tunnel working time is millisecond magnitude, transient heat flow is measured except will solving the problem of measuring technology itself, also will consider the synchro control of the operation of wind tunnel operation, air film, heat flow measurement three.Because air film can work under different inlet flow conditions, such as hypersonic, supersonic speed, subsonic speed are even without situations such as flowings, and the gaseous film control studied under hypersonic condition is significant in Practical Project, are also one of difficult points of research at present simultaneously.Because most of hypersonic wind tunnel is impulse wind tunnel, working time is very short, so obviously, studies the heat flux distribution of gaseous film control under this condition, and the operation of air film and heat flux measurement system must 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 being arranged in test model surface excessively pre-cooled, thus measuring error when increasing wind tunnel operation.A set ofly accurately can control that air film is opened, heat flow measurement system is opened and the synchro control of wind tunnel operation and measuring system and method so must design.At present, there is no and can be used for gaseous film control transient heat flow method of testing in hypersonic gun wind tunnel and system.
Summary of the invention
The object of the invention is to provide a kind of gaseous film control transient heat flow test macro based on hypersonic gun wind tunnel and method, to solve the technical matters that gaseous film control transient heat flow in hypersonic gun wind tunnel environment is difficult to test.
For achieving the above object, the technical solution used in the present invention is as follows:
Based on a gaseous film control transient heat flow test macro for hypersonic gun wind tunnel, this hypersonic gun wind tunnel comprise connect successively high pressure section, film chamber, low pressure stage, jet pipe and Laboratory Module, this test macro comprises:
For detecting the pressure transducer of 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 amplification, and trigger pip generates the opportunity of gaseous film control jet flow for controlling to be located at gaseous film control model surface in Laboratory Module;
Gaseous film control model surface is provided with heat flux sensor, and the output terminal of heat flux sensor connects computing machine through digital signal acquiring device;
The control end of digital signal acquiring device is connected to isochronous controller, and digital signal acquiring device is according to the data of the work schedule collection of isochronous controller from heat flux sensor;
Computing machine is used for the work schedule of control synchronization controller and stores the heat flow data of digital signal acquiring device collection.
Further, the output terminal of isochronous controller is connected with the solid-state relay amplifying trigger pip, and solid-state relay is connected with the solenoid valve for opening or cut out gaseous film control jet flow.
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 multiple, forms heat flux sensor array at gaseous film control model surface.
According to a further aspect in the invention, a kind of gaseous film control transient heat flow method of testing based on hypersonic gun wind tunnel is also provided, comprises the following steps:
Open hypersonic gun wind tunnel;
Detect the force value in hypersonic gun wind tunnel film chamber;
When the force value in film chamber raises instantaneously, open gaseous film control jet flow is not later than hypersonic gun wind tunnel foundation with the cooling air film that the gaseous film control model surface making to be positioned at Laboratory Module is formed;
Measure the heat flow data of gaseous film control model surface.
Further, heat flow data is for measuring through heat flux sensor and being stored in computing machine.
Further, heat flux sensor is in running order before performing 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 multiple, forms heat flux sensor array, for measuring the heat flow data of the multiple position of synchronization gaseous film control model surface at gaseous film control model surface.
The present invention has following beneficial effect:
The present invention is based on gaseous film control transient heat flow test macro and the method for hypersonic gun wind tunnel, by measuring the force value in hypersonic gun wind tunnel film chamber, the start-up time of gaseous film control jet flow is set up in Flow Field in Wind Tunnel a little in advance, to ensure while Flow Field in Wind Tunnel is set up, cooling jet flow is also set up simultaneously, and owing to being triggered the foundation of cooling jet flow by the force value detected in wind-tunnel die cavity, avoid the operating overload that cooling jet flow opens the heat flux sensor caused too early in advance, thus be that under the hypersonic inlet flow conditions of measurement, the transient heat flow data of gaseous film control provide condition, and pass through the control of the work schedule of isochronous controller, ensure that wind tunnel operation, air film runs, and heat flow measurement three's is synchronous.
Except object described above, feature and advantage, the present invention also has other object, feature and advantage.Below with reference to figure, the present invention is further detailed explanation.
Accompanying drawing explanation
The accompanying drawing forming a application's part is used to provide a further understanding of the present invention, and schematic description and description of the present invention, for explaining the present invention, does not form inappropriate limitation of the present invention.In the accompanying drawings:
Fig. 1 is the three-dimensional structure schematic diagram of the preferred embodiment of the present invention based on the gaseous film control transient heat flow test macro 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 the principle schematic that gaseous film control jet flow of the present invention forms 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 gaseous film control transient heat flow method of testing of hypersonic gun wind tunnel;
Fig. 7 is the work schedule schematic diagram of the preferred embodiment of the present invention based on the gaseous film control transient heat flow method of testing of hypersonic gun wind tunnel.
Embodiment
Below in conjunction with accompanying drawing, embodiments of the invention are described in detail, 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 gaseous film control transient heat flow test macro based on hypersonic gun wind tunnel, this hypersonic gun wind tunnel comprise connect successively high pressure section 1, film chamber 7, low pressure stage 2, jet pipe 6 and Laboratory Module 9.This test macro comprises:
For detecting the pressure transducer 17 of pressure in film chamber 7;
Pressure transducer 17 is connected with isochronous controller 14 through amplifier 15, isochronous controller 14 generates trigger pip according to the pressure signal after amplifier 15 amplification, and trigger pip is for controlling to be located at the opportunity of gaseous film control model 100 Surface Creation gaseous film control jet flow in Laboratory Module 9;
Gaseous film control model 100 surface is 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 data of the work schedule collection of isochronous controller 14 from heat flux sensor 11;
The work schedule of computing machine 16 for control synchronization controller 14 and the heat flow data of storage digital signal acquiring device 12 collection.
The embodiment of the present invention is based on the gaseous film control transient heat flow test macro of hypersonic gun wind tunnel, by measuring the force value in hypersonic gun wind tunnel film chamber, the start-up time of gaseous film control jet flow is set up in Flow Field in Wind Tunnel a little in advance, to ensure while Flow Field in Wind Tunnel is set up, cooling jet flow is also set up simultaneously, triggered the start-up time of air film foundation by the force value detected in die cavity 7 simultaneously, the heat flux sensor operating overload that the start-up time avoiding air film causes too early, and cause when hypersonic air-flow comes model surface, heat flux sensor cannot the fault of Measurement accuracy.The embodiment of the present invention by detect wind-tunnel die cavity 7 in pressure and according to detect pressure activated air film set up opportunity, both ensure that gaseous film control 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 ensure heat flux sensor nonoverload, thus provide condition for accurately measuring the transient heat flow data of gaseous film control under hypersonic inlet flow conditions, and by the control of the work schedule of isochronous controller, ensure that wind tunnel operation, air film run and heat flow measurement three synchronous.
With reference to Fig. 2 and Fig. 3, in the present embodiment, hypersonic gun wind tunnel comprise connect successively high pressure section 1, film chamber 7, low pressure stage 2, jet pipe 6 and Laboratory Module 9, wherein film chamber 7 clamps two high pressure section diaphragms 4 by folder film machine 3 and is formed, being provided with for stopping low pressure stage 2 and the low pressure stage diaphragm 5 of jet pipe 6 through pressing from both sides film machine 3 between low pressure stage 2 and jet pipe 6, in low pressure stage 2, being 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 pressure needed for test, also certain pressure is inflated in film chamber 7, 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 film chamber 7 serves the pressure differential of balance high pressure section 1 and low pressure stage 2 high-low pressure gas; The gas in quick release film chamber 7, successively breaks under the pressure differential effect of two high pressure section diaphragms 4 in both sides, film chamber 7 between high pressure section 1 and low pressure stage 2.Now, 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 velocity is very fast, can form normal shock wave before lightweight piston 8.Launch when normal shock wave arrives low pressure stage diaphragm 5, run into the lightweight piston 8 of advance, shock wave reflection is carried out repeatedly, constantly compress low pressure stage 2 gas in pipelines, its pressure, temperature are improved, and 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 namely gaseous film control model 100 can carry out hypersonic aerodynamic experiment in Laboratory Module 9.
It should be noted that, the working time of hypersonic gun wind tunnel is determined by the gas in low pressure stage 2.Because this part gas enters jet pipe 6, Laboratory Module 9 as the medium of flowing.After these gases are finished, wind-tunnel and end of run.Typically the working time of this kind of wind-tunnel facilities is in millisecond magnitude, and the working time of the hypersonic gun wind tunnel in this programme is 20ms.Although macroscopically the working time of wind-tunnel is very short, enough for hypersonic flowing.The Time Created of usual Hypersonic Flow Field is 3 ~ 5ms.Here need clearly several concept, the wind tunnel operation time refers to the time of setting up rear wind-tunnel stable operation at Hypersonic Flow Field.And the foundation of Hypersonic Flow Field refers to that tunnel airstream reaches the design point of Flow Field in Wind Tunnel during this period of time from setting in motion, could stable operation after foundation.In addition, the Startup time of wind-tunnel refers to the moment (be exactly generally film chamber venting at that moment) of impelling wind-tunnel to open artificially, and starts to wind-tunnel stable operation from wind-tunnel and terminate its time overall length and be also only about 200ms.The so so short time proposes higher requirement for testing apparatus, and sequential that is sensitive and that measure sufficiently is controllable.Otherwise may measure and also not start, wind-tunnel just end of run, so just cannot measure the parameter in true flow field.So the measurement moment of testing apparatus must be just within the time of wind tunnel operation or a little in advance in wind tunnel operation.Hypersonic gun wind tunnel equipment is generally difficult to do long-play in addition.Therefore, in order to ensure to form cooling air film on the surface of gaseous film control model 100 while Hypersonic Flow Field is set up, then the start-up time of gaseous film control jet flow will 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 amplifying trigger pip, and solid-state relay 13 is connected with the solenoid valve for opening or cut out gaseous film control jet flow.When the pressure transducer 17 for detecting the force value in film chamber 7 detects that in film chamber 7, pressure raises suddenly, the output signal of pressure transducer 17 inputs isochronous controller 14 after amplifier 15 amplifies, isochronous controller 14 exports a low level trigger pip according to the sequential pre-set, this trigger pip triggers solenoid valve again and opens cooling jet flow after solid-state relay 13 boosts, from trigger pip to unlatching cooling jet flow, usually need 50ms, thus ensure that Hypersonic Flow Field and cool the synchronous of jet flow.
With reference to Fig. 4, in the present embodiment, the upstream design of gaseous film control model 100 has gaseous film control spout 10, and this gaseous film control spout 10 has the profile of first shrinking and expanding afterwards, air-flow can be accelerated to supersonic speed.And the source of air-flow by gas cylinder through gas path pipe enter before spout stay room again by this gaseous film control spout 10 accelerate ejection.In order to control the switch of air-flow, gas circuit is 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 exports trigger pip, solenoid valve is opened, form cooling jet flow B, meanwhile, Hypersonic Flow Field A is established through hypersonic gun wind tunnel, between Hypersonic Flow Field A and cooling jet flow B, forming very thin cooling air film, being arranged on the heat flux sensor 11 on gaseous film control model 100 surface for detecting the transient heat flow data 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 carrying out large area measurement; Another kind of is sensor-based heat flow measurement technology.Wherein, thermo-mapping technique comprises infrared chart, look heating figure, phase change thermograph and fluorescence thermal map etc.This kind of technology once tests the heat flux distribution that just can obtain whole audience scope, and without the need to punching on model, and display is relatively more directly perceived, is a kind of heat flow measurement method based on optical measuring technique.But this class methods measuring system is complicated, and price is high; Affect by imaging system, Curvature varying larger part meeting distortion; Look as indicator becomes, phase-change material spraying coating process is tighter.In general, the existing thermo-mapping technique response time is relatively long, be suitable for longer wind-tunnel working time, and the thermo-mapping technique of gun wind tunnel is still in conceptual phase.Sensor-based heat flow measurement technology utilizes the hot-fluid of thermal transfer sensors (as film thermal transfer sensors, thin-walled or heavy wall calorimeter etc.) also measure local point.This kind of Technical Development History is longer, comparative maturity, belong to classical measurement technology one class, although its test space limited precision, and sensor mounting hole to be beaten on model, how much change local geometric shape, thus introduction measuring error, but because its precision is high, response fast, testing apparatus is simple, is still widely adopted as main means of testing.
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 multiple bridge diagram parallel with one another.Bridge diagram be wheatstone bridge circuits, wherein arm resistance R, Rf, Rs is precision resistance, and 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, to make bridge diagram initial output at room temperature as far as possible little, avoid output voltage in testing to exceed 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:
Can be conversed the resistance of thin-film thermistor Rd by output voltage values Ui, and the resistance temperature relation of thin-film thermistor Rd has good linear within the specific limits, its relation can with representing:
In above formula, R0 is the resistance of thin-film thermistor 0 DEG C time, 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 multiple, forms heat flux sensor array on gaseous film control model 100 surface.Because the resistance of each heat flux sensor 11 is different, need to arrange bridge diagram respectively for each heat flux sensor 11.
According to a further aspect in the invention, also provide a kind of gaseous film control transient heat flow method of testing based on hypersonic gun wind tunnel, with reference to Fig. 6, comprise the following steps:
Step S10: open hypersonic gun wind tunnel;
In the present embodiment, will be filled with the gas of different pressures, and people is for impelling film chamber 7 Rapid degassing in the high pressure section 1 of hypersonic gun wind tunnel, low pressure stage 2 and film chamber 7, wind-tunnel starts.Cause the high pressure section diaphragm 4 near high pressure section 1 side to break because pressure reduction raises, the gases at high pressure in high pressure section 1 enter film chamber 7, and pressure in film chamber 7 is raised instantaneously.
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 detecting force value in film chamber 7, and when the force value in film chamber 7 raises instantaneously, pressure transducer 17 generates step signal.
Step S30: when the force value in film chamber 7 raises instantaneously, opens gaseous film control jet flow is not later than hypersonic gun wind tunnel foundation with the cooling air film that gaseous film control model 100 surface making to be positioned at Laboratory Module 9 is formed;
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 valve, and solenoid valve is positioned to be provided in the gas circuit of source of the gas to gaseous film control spout 10, and solenoid valve is for controlling conducting or the cut out of gas circuit.When the force value in film chamber 7 raises instantaneously, the step signal that pressure transducer 17 exports exports to isochronous controller 14 after amplifier 15 amplifies, and isochronous controller 14 generates trigger pip according to the work schedule preset.The embodiment of the present invention by detect wind-tunnel die cavity 7 in pressure and according to detect pressure activated air film set up opportunity, both ensure that gaseous film control 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 ensure heat flux sensor nonoverload, thus provide condition for accurately measuring the transient heat flow data of gaseous film control under hypersonic inlet flow conditions, and by the control of the work schedule of isochronous controller, ensure that wind tunnel operation, air film run and heat flow measurement three synchronous.In the present embodiment, the trigger pip voltage that isochronous controller 14 exports only has 5V, through solid-state relay 13, the voltage of trigger pip is promoted to 24V, opens to trigger solenoid valve, thus cooling jet flow B is formed at gaseous film control spout 10 place, cooling jet flow B covers the surface of air film cooling jig 100.
Step S40: the heat flow data measuring gaseous film control model 100 surface.
The surface of gaseous film control model 100 arranges heat flux sensor 11, and heat flux sensor 11 detects the heat flow data on gaseous film control model 100 surface.Preferably, individual in the present embodiment, there iing multiple heat flux sensor 11 respectively on gaseous film control model 100 surface, to form heat flux sensor array, for measuring the heat flow data of the surperficial multiple position of synchronization gaseous film control model 100.The output data of heat flux sensor array are stored in computing machine 16 for follow-up analysis through digital signal acquiring device 12.
Preferably, heat flux sensor 11 is in running order before execution step S10, like this, when Hypersonic Flow Field A is formed with cooling jet flow B, the transient heat flow data of gaseous film control under the hypersonic inlet flow conditions of heat flux sensor 11 energy Measurement accuracy, wherein, the start-up time of air film only shifts to an earlier date too much than the moment of setting up of supersonic speed gun wind tunnel, only need about 20ms more Zao than wind tunnel operation, avoid heat flux sensor 11 to transship.
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 gaseous film control transient heat flow method of testing of hypersonic gun wind tunnel.The present invention is based on gaseous film control transient heat flow test macro and the method for hypersonic gun wind tunnel, by measuring the force value in hypersonic gun wind tunnel film chamber 7, the start-up time of gaseous film control jet flow is set up in Flow Field in Wind Tunnel a little in advance, to ensure while Flow Field in Wind Tunnel is set up, cooling jet flow is also set up simultaneously, thus be that under the hypersonic inlet flow conditions of measurement, the transient heat flow data of gaseous film control provide condition, and ensure that heat flux sensor 11 nonoverload, accurately measure the transient heat flow data of gaseous film control under hypersonic inlet flow conditions.The embodiment of the present invention, by the control of the work schedule of isochronous controller 14, ensure that wind tunnel operation, air film run and heat flow measurement three synchronous.
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 amendment done, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (4)
1. the gaseous film control transient heat flow test macro based on hypersonic gun wind tunnel, described hypersonic gun wind tunnel comprise connect successively high pressure section (1), film chamber (7), low pressure stage (2), jet pipe (6) and Laboratory Module (9), it is characterized in that
Comprise the pressure transducer (17) for detecting the interior pressure of described film chamber (7);
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) amplification, and described trigger pip is used for the opportunity that described Laboratory Module (9) interior gaseous film control model (100) Surface Creation gaseous film control jet flow is located in control;
Described gaseous film control model (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 data of the work schedule collection of described isochronous controller (14) from described heat flux sensor (11);
Described computing machine (16) is for controlling the work schedule of described isochronous controller (14) and storing the heat flow data that described digital signal acquiring device (12) gathers.
2. the gaseous film control transient heat flow test macro 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) amplifying described trigger pip, and described solid-state relay (13) is connected with the solenoid valve for opening or cut out gaseous film control jet flow.
3. the gaseous film control transient heat flow test macro 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 gaseous film control transient heat flow test macro based on hypersonic gun wind tunnel according to claim 3, is characterized in that,
Described heat flux sensor (11), for multiple, forms heat flux sensor array on described gaseous film control model (100) surface.
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| FR2932883B1 (en) * | 2008-06-19 | 2010-08-20 | Airbus France | HYBRID METHOD FOR EVALUATING THE FLOOD EFFECT ON AN AIRCRAFT |
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