CN113884267A - Transient jet flow test device for pulse wind tunnel - Google Patents
Transient jet flow test device for pulse wind tunnel Download PDFInfo
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- CN113884267A CN113884267A CN202111479106.0A CN202111479106A CN113884267A CN 113884267 A CN113884267 A CN 113884267A CN 202111479106 A CN202111479106 A CN 202111479106A CN 113884267 A CN113884267 A CN 113884267A
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- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
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- G—PHYSICS
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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Abstract
The invention discloses a transient jet flow test device for a pulse wind tunnel. The transient jet flow test device comprises a jet flow test model, an air source supply system, a rapid synchronous control system and a jet flow parameter measuring device; the jet flow test model sprays stable jet flow; the air source supply system provides a stable air source required by stable jet flow, and the rapid synchronous control system ensures that the forming time of the stable jet flow is synchronous with the forming time of the main flow of the pulse wind tunnel; meanwhile, the air source supply system ensures that the duration time of the stable jet flow exceeds the effective test time of the main flow of the pulse wind tunnel, and the rapid synchronous control system automatically closes the air source supply system after the set duration time of the stable jet flow is reached; the jet flow parameter measuring device is used for measuring the flow field parameters of the stable jet flow ejected by the fixed model before the jet flow test. The transient jet flow test device can provide jet flow with accurate parameters and good stability and repeatability so as to evaluate the influence of jet flow interference on the aerodynamic characteristics of an aircraft, can quickly complete jet flow preparation and accurately control the jet flow time.
Description
Technical Field
The invention belongs to the field of hypersonic pulse wind tunnel test equipment, and particularly relates to a transient jet flow test device for a pulse wind tunnel.
Background
The lateral jet flow control is a control method for carrying out attitude control on an aircraft or providing direct power by means of jet flow reaction force and interference force generated by interaction of jet flow and incoming flow. Compared with the traditional pneumatic rudder control, the transverse jet flow control is suitable for a full speed domain and a full airspace, has the remarkable characteristics of quick response and high efficiency, and is beneficial to reducing the pneumatic control surface of an aircraft, reducing the weight and reducing the resistance. The transverse jet flow control technology is used on aircraft such as a non-lift reentry aircraft (such as a returning capsule of an airship), a lift reentry aircraft (such as a space shuttle, X-37B, X-38, HTV-2 and the like) and a high-speed interception missile (such as PAC-3, THAAD and the like).
However, in the hypersonic flight process, the RCS jet flow and the aircraft circumfluence interfere with each other, the thermal environment of the interference area is very complex, and local high heat flow is generated, so that the thermal environment prediction and heat protection design are difficult. Due to the complexity of jet flow interference, wind tunnel test simulation is a necessary research means.
In a hypersonic pulse wind tunnel, jet flow interference simulation is not a mature conventional test technology, and the key technology is to design and form a jet flow generating device which meets the simulation requirement, has stable and reliable parameters and can be synchronous with the wind tunnel test airflow with the effective time of only millisecond.
Currently, there is a need to develop a transient jet test device for impulse wind tunnel.
Disclosure of Invention
The invention aims to provide a transient jet flow test device for a pulse wind tunnel.
The invention discloses a transient jet flow test device for a pulse wind tunnel, which is characterized by comprising a jet flow test model, an air source supply system, a rapid synchronous control system and a jet flow parameter measuring device; the jet flow test model sprays stable jet flow; the air source supply system provides a stable air source required by stable jet flow, and the rapid synchronous control system ensures that the forming time of the stable jet flow is synchronous with the forming time of the main flow of the pulse wind tunnel; meanwhile, the air source supply system ensures that the duration time of the stable jet flow exceeds the effective test time of the main flow of the pulse wind tunnel, and the rapid synchronous control system automatically closes the air source supply system after the set stable jet flow duration is reached; the jet flow parameter measuring device is used for measuring the flow field parameters of stable jet flow sprayed by the fixed model before a jet flow test;
the jet flow test model is arranged in a test section of the pulse wind tunnel, and comprises a model body and a Laval nozzle arranged in the model body, wherein the outlet of the Laval nozzle is in smooth transition with the surface of the model body, the inlet of the Laval nozzle is connected with an air hose of an air source supply system, and the Laval nozzle sprays the ultrasonic stable jet flow with the required Mach number;
the air source supply system comprises an air bottle group, an air storage pipe, a small-caliber breather pipe and a breather hose which are sequentially connected in the air flow direction, and also comprises an integrated control cabinet and a vacuum pump; the gas cylinder group and the gas storage pipe are positioned outside the testing section of the pulse wind tunnel, and the small-caliber breather pipe extends into the testing section through a flange on the side wall of the testing section; the gas storage pipe is provided with a pressure sensor for measuring the gas pressure in the gas storage pipe and a gas temperature sensor; the integrated control cabinet pumps residual gas in the gas storage pipe through a vacuum pump, and controls the pressure and the temperature of medium gas entering the gas storage pipe from the gas cylinder group through feedback signals of a pressure sensor and a temperature sensor so as to provide the medium gas required by stable jet flow;
the rapid synchronous control system comprises a trigger delayer, a signal generator, a rapid relay and a rapid electromagnetic valve which are connected through a cable; the quick electromagnetic valve is positioned near or inside the jet flow test model and is arranged between the small-caliber breather pipe and the breather hose of the air source supply system; the trigger delayer receives a charge signal from a piezoelectric sensor of the pulse wind tunnel shock tube, converts the charge signal into a voltage pulse signal, and adjusts delay time to control the starting time of a subsequent quick electromagnetic valve; the signal generator receives the voltage pulse signal from the trigger delayer, outputs a level signal with fixed pulse width and voltage, and is used for switching on and switching off the quick relay; the fast relay receives the level signal from the signal generator, switches on or off a switch circuit of the fast electromagnetic valve and controls the fast electromagnetic valve to be opened and closed;
the jet flow parameter measuring device is fixed on a jet flow test model before a pulse wind tunnel jet flow test, and outlet airflow parameters of the Laval nozzle are measured through a Pitot pressure probe and a static pressure probe.
Furthermore, L-shaped measuring supports of the jet flow parameter measuring device are symmetrically fixed on two sides of an outlet of the spray pipe, horizontal feet of the L-shaped measuring supports are fixed on the surface of the jet flow test model, and the vertical support is perpendicular to the surface of the jet flow test model; the bracket beam is supported on the vertical pillar, the wedge-shaped sensor support is fixed on the bracket beam, and the wedge-shaped wedge of the sensor support is over against the outlet of the spray pipe; a pressure sensor is arranged in the sensor support, and the rear end of each probe is connected with one pressure sensor in the sensor support; a protective cover is sleeved at the rear part of the sensor support; the front end of the probe extends downwards out of the sensor support and is opposite to the outlet of the spray pipe; a cable of the pressure sensor extends upwards out of the protective cover to be connected with the pulse wind tunnel measurement and control system; the probe comprises a pitot pressure probe for fixedly measuring the total pressure of the supersonic velocity airflow at the outlet of the spray pipe after the shock wave and a static pressure measuring probe for fixedly measuring the static pressure at the outlet of the spray pipe.
Furthermore, the sensor support of the jet flow parameter measuring device transversely moves through the support beam to measure jet flow parameters at different radial positions of the nozzle outlet; the vertical pillar of the L-shaped measuring support of the jet flow parameter measuring device and the support beam are provided with corresponding track sliding block mechanisms, the support beam drives the sensor support to slide up and down through the track sliding block mechanisms, and the height between the pitot pressure probe or the static pressure probe and the outlet of the spray pipe is adjusted.
Furthermore, the gas cylinder group is provided with a pressure reducing valve and a safety pressure relief valve, and is connected to the integrated control cabinet through a stainless steel high-pressure pipe, the integrated control cabinet monitors through a control cabinet panel, and the gas cylinder group is operated to inflate and deflate, so that gas media in the gas cylinder group are kept to have stable gas pressure and temperature parameters.
Further, the gas medium in the gas cylinder group is one of nitrogen, air or helium.
Furthermore, the inflation control valve, the deflation control valve and the evacuation control valve of the gas storage pipe are arranged in the integrated control cabinet, and the gas storage pipe is operated to inflate, deflate and evacuate through a control cabinet panel, so that the gas medium in the gas storage pipe is monitored and kept to have stable gas pressure and temperature parameters.
Further, the rapid relay is a solid-state rapid relay, and a 220V alternating current circuit is connected within 1ms, so that a power supply of the rapid electromagnetic valve is connected, the rapid electromagnetic valve is opened, and stable jet flow of the jet flow test model is started.
Further, the rapid electromagnetic valve is a pilot type normally closed rapid electromagnetic valve which is automatically triggered and has a preset time length, and the valve opening action time is less than 15 ms.
The gas storage pipe in the transient jet flow test device for the pulse wind tunnel utilizes the working principle of the Ludwigshi pipe, after a quick electromagnetic valve at the outlet end is opened, airflow in the pipe flows out from the outlet end, an expansion wave which reversely propagates is formed in the pipe, a wave head of the expansion wave is reflected at the bottom end of the gas storage pipe and then propagates to the outlet end, in the period from the formation of the first expansion wave to the arrival at the outlet end after the reflection, the pressure and the temperature of the airflow after the first expansion wave are kept unchanged, and the airflow in the pipe at the section is defined as a region 1 and serves as a jet flow gas supply source. And when the reflection expansion wave head reaches the outlet end, the effective gas supply time is finished. The gas storage pipe with larger diameter is adopted, which is beneficial to reducing the Mach number of the airflow in the 1 region
Thereby reducing the deviation of the total temperature and pressure of the jet from the initial inflation state.
The invention discloses a jet flow test model applicable to a transient jet flow test device for a pulse wind tunnel, which comprises a wedge model, a cone model, a flat plate model or other pneumatic thermal jet flow test models. Suitable hypersonic pulse wind tunnels comprise a gun wind tunnel, a shock wave wind tunnel and an expansion pipe wind tunnel.
The stable jet flow formed by the transient jet flow test device for the impulse wind tunnel can be synchronously established with the main flow of the wind tunnel, the duration time exceeds the effective test time of the main flow of the wind tunnel, and the stable jet flow is automatically closed after the set jet flow duration, so that a complex flow field structure formed by mutual interference of transverse jet flow formed when a reaction control system of an aircraft works and the peripheral flow of the aircraft can be simulated, and the device is particularly suitable for simulating the aerodynamic thermal environment of the surface of the aircraft with the transverse jet flow.
The transient jet flow test device for the pulse wind tunnel can provide jet flow with accurate parameters and good stability and repeatability so as to evaluate the influence of jet flow interference on the aerodynamic characteristics of an aircraft. Meanwhile, the preparation of a jet flow system can be quickly realized, the jet flow injection time can be accurately controlled, and the time and the cost of a wind tunnel test are saved.
Drawings
FIG. 1a is a schematic structural view (front view) of a wedge-shaped jet test model in a transient jet test device for a pulsed wind tunnel according to the present invention;
FIG. 1b is a schematic structural diagram (top view) of a wedge-shaped jet test model in the transient jet test device for an impulse wind tunnel according to the present invention;
FIG. 1c is a schematic structural diagram (partial sectional view) of a Laval nozzle of a wedge-shaped jet test model in a transient jet test device for a pulsed wind tunnel according to the present invention;
FIG. 2a is a schematic structural diagram (front view) of a transient jet test device for an impulse wind tunnel according to the present invention;
FIG. 2b is a schematic structural diagram (top view) of the transient jet test device for impulse wind tunnel according to the present invention;
FIG. 3a is a schematic structural view (perspective view) of a jet parameter measuring device of the transient jet test device for impulse wind tunnel according to the present invention;
FIG. 3b is a schematic structural diagram (cross-sectional view) of a jet parameter measuring device of the transient jet test device for impulse wind tunnel according to the present invention;
FIG. 3c is a schematic structural view (side view) of a jet parameter measuring device of the transient jet testing device for impulse wind tunnel according to the present invention;
FIG. 4a is a schematic structural view (front view) of a static pressure measurement probe of a jet parameter measurement device in a transient jet test device for a pulsed wind tunnel according to the present invention;
FIG. 4b is a schematic structural diagram (cross-sectional view) of a static pressure measuring probe of the jet parameter measuring device in the transient jet test device for impulse wind tunnel according to the present invention;
FIG. 5 is a schematic view of the operation principle of the gas storage pipe in the transient jet test device for impulse wind tunnel according to the present invention;
FIG. 6 is a diagram of the operation process of the transient jet test device for impulse wind tunnel according to the present invention;
FIG. 7 is a pitot pressure time curve and a static pressure time curve measured by a jet flow parameter measuring device in the transient jet flow testing device for a pulsed wind tunnel according to the present invention;
fig. 8 is a curve for synchronously debugging the timing sequence of the steady jet flow and the jet flow test model obtained by the transient jet flow test device for the impulse wind tunnel according to the present invention.
In the figure, 1, an air storage pipe; 2. a small-caliber breather pipe; 3. a fast electromagnetic valve; 4. an air hose; 5. a laval nozzle; 6. a jet flow test model; 7. a jet flow parameter measuring device;
701. a measuring support; 702. a nozzle outlet; 703. a pitot pressure probe; 704. a bracket beam; 705. a sensor support; 706. a pressure sensor; 707. a protective cover; 708. a static pressure measurement probe.
Detailed description of the preferred embodiments
The present invention will be described in detail below with reference to the accompanying drawings and examples.
The transient jet flow test device for the pulse wind tunnel comprises a jet flow test model 6, a gas source supply system, a rapid synchronous control system and a jet flow parameter measuring device 7; the jet flow test model 6 jets out stable jet flow; the air source supply system provides a stable air source required by stable jet flow, and the rapid synchronous control system ensures that the forming time of the stable jet flow is synchronous with the forming time of the main flow of the pulse wind tunnel; meanwhile, the air source supply system ensures that the duration time of the stable jet flow exceeds the effective test time of the main flow of the pulse wind tunnel, and the rapid synchronous control system automatically closes the air source supply system after the set stable jet flow duration is reached; the jet flow parameter measuring device 7 is used for measuring the flow field parameters of the stable jet flow ejected by the fixed model before the jet flow test;
as shown in fig. 1a, 1b and 1c, the jet flow test model 6 is installed in a test section of a pulse wind tunnel, and comprises a model body and a laval nozzle 5 installed inside the model body, an outlet of the laval nozzle 5 is in smooth transition with the surface of the model body, an inlet of the laval nozzle 5 is connected with an air hose 4 of an air source supply system, and the laval nozzle 5 jets a stable supersonic jet flow with a required mach number;
as shown in fig. 2a and 2b, the air supply system includes an air cylinder group, an air storage pipe 1, a small-caliber vent pipe 2 and a vent hose 4 which are connected in sequence in the air flow direction, and further includes an integrated control cabinet and a vacuum pump; the gas cylinder group and the gas storage pipe 1 are positioned outside a test section of the pulse wind tunnel, and the small-caliber breather pipe 2 extends into the test section through a flange on the side wall of the test section; the gas storage pipe 1 is provided with a pressure sensor for measuring the gas pressure in the gas storage pipe 1 and a temperature sensor for measuring the gas temperature; the integrated control cabinet sucks residual gas in the gas storage pipe 1 through a vacuum pump, and controls the pressure and the temperature of medium gas entering the gas storage pipe 1 from the gas cylinder group through feedback signals of a pressure sensor and a temperature sensor so as to provide the medium gas required by stable jet flow;
the rapid synchronous control system comprises a trigger delayer, a signal generator, a rapid relay and a rapid electromagnetic valve 3 which are connected through a cable; the rapid electromagnetic valve 3 is positioned near or inside the jet flow test model 6 and is arranged between the small-caliber breather pipe 2 and the breather hose 4 of the air source supply system; the trigger delayer receives a charge signal from a piezoelectric sensor of the pulse wind tunnel shock tube, converts the charge signal into a voltage pulse signal, and adjusts delay time to control the starting time of the subsequent rapid electromagnetic valve 3; the signal generator receives the voltage pulse signal from the trigger delayer, outputs a level signal with fixed pulse width and voltage, and is used for switching on and switching off the quick relay; the fast relay receives the level signal from the signal generator, switches on or off the switching circuit of the fast electromagnetic valve 3, and controls the fast electromagnetic valve 3 to be opened and closed;
the jet flow parameter measuring device 7 is fixed on the jet flow test model 6 before the pulse wind tunnel jet flow test, and measures the outlet airflow parameter of the Laval nozzle 5 through the Pitot pressure probe 703 and the static pressure probe.
Further, as shown in fig. 3a, 3b, and 3c, the L-shaped measuring brackets 701 of the jet parameter measuring device 7 are symmetrically fixed on both sides of the nozzle outlet 702, the horizontal feet of the L-shaped measuring brackets 701 are fixed on the surface of the jet test model 6, and the vertical pillars are perpendicular to the surface of the jet test model 6; a bracket beam 704 is supported on a vertical pillar, a wedge-shaped sensor support 705 is fixed on the bracket beam 704, and a wedge-shaped wedge of the sensor support 705 is opposite to a spray pipe outlet 702; a pressure sensor 706 is arranged in the sensor support 705, and the rear end of each probe is connected with one pressure sensor 706 in the sensor support 705; a protective cover 707 is sleeved on the rear part of the sensor support 705; the front end of the probe extends downwards out of the sensor support 705 and is opposite to the nozzle outlet 702; a cable of the pressure sensor 706 extends upwards out of the protective cover 707 to be connected with a pulse wind tunnel measurement and control system; the probes comprise a pitot pressure probe 703 for fixedly measuring the total pressure after the supersonic gas flow shock wave at the nozzle outlet 702 and a static pressure measurement probe 708 for fixedly measuring the static pressure at the nozzle outlet 702 as shown in fig. 4a and 4 b.
Further, the sensor support 705 of the jet parameter measuring device 7 moves transversely through the support beam 704 to measure jet parameters of different radial positions of the nozzle outlet 702; the vertical pillar of the L-shaped measuring bracket 701 of the jet flow parameter measuring device 7 and the bracket beam 704 are provided with corresponding track slider mechanisms, and the bracket beam 704 drives the sensor support 705 to slide up and down through the track slider mechanisms to adjust the height between the pitot pressure probe 703 or the static pressure probe and the nozzle outlet 702.
Furthermore, the gas cylinder group is provided with a pressure reducing valve and a safety pressure relief valve, and is connected to the integrated control cabinet through a stainless steel high-pressure pipe, the integrated control cabinet monitors through a control cabinet panel, and the gas cylinder group is operated to inflate and deflate, so that gas media in the gas cylinder group are kept to have stable gas pressure and temperature parameters.
Further, the gas medium in the gas cylinder group is one of nitrogen, air or helium.
Further, the inflation control valve, the deflation control valve and the evacuation control valve of the gas storage pipe 1 are installed in the integrated control cabinet, and the gas storage pipe 1 is operated to inflate, deflate and evacuate through a control cabinet panel, so that the gas medium in the gas storage pipe 1 is monitored and maintained to have stable gas pressure and temperature parameters.
Further, the rapid relay is a solid-state rapid relay, and a 220V alternating current circuit is connected within 1ms, so that the power supply of the rapid electromagnetic valve 3 is switched on, the rapid electromagnetic valve 3 is opened, and the stable jet flow of the jet flow test model 6 is started.
Further, the fast electromagnetic valve 3 is a pilot type normally closed fast electromagnetic valve which is automatically triggered and has a preset time length, and the valve opening action time is less than 15 ms.
Example 1
In this embodiment, the gas cylinder group supplied by the gas source is 4 bottles of nitrogen gas in 13MPa and 40L bottles, and 2 bottles of helium gas in 13MPa and 40L bottles; the gas cylinder group is connected to the gas storage pipe 1 through a stainless steel high-pressure pipe, and an integrated control cabinet is arranged between the gas cylinder group and the gas storage pipe; each gas cylinder is provided with a pressure reducing valve, a communicating pipeline between the gas cylinders is provided with a safety pressure reducing valve, and a main pipeline is communicated with a stainless steel high-pressure gas pipe of the gas storage pipe 1 and used for inflating the gas storage pipe 1. Meanwhile, a bottle of high-pressure air is independently used in the air bottle group to provide an air guide source for the rapid electromagnetic valve 3.
The material of the gas storage pipe 1 is 304 stainless steel, the inner diameter is 90mm, the length is 10m, the stable gas supply time is about 60ms when nitrogen is used, and the outlet end of the gas storage pipe 1 enters the test section through the side wall flange of the test section and is connected with the small-caliber vent pipe 2 made of metal; the other end of the small-caliber breather pipe 2 is connected to a quick electromagnetic valve 3. The quick electromagnetic valve 3 is connected with an air hose 4, and the other end of the air hose 4 is connected with the inlet of a Laval nozzle 5 in the model.
The quick relay is a direct current control alternating current Solid State Relay (SSR), and the response time is less than 1 ms. The quick electromagnetic valve 3 is MAC 56C-37-122BA, the equivalent flow aperture is about 12mm, and the full opening action time is about 12 ms. The material of the Laval nozzle 5 is 304 stainless steel, the diameter of an inlet is 20mm, the diameter of a throat is 8.6mm, the diameter of an outlet is 30mm, the length is 116mm, and the Mach number of the designed outlet is 4.0. The jet flow test model 6 is a wedge-shaped model and is made of 30 CrMnSiA. The laval nozzle 5 extends from the interior of the wedge-shaped model to the inner wall of the wedge surface of the wedge-shaped model and is fixed by using screws from inside to outside. The material of the air hose 4 between the Laval nozzle 5 and the rapid electromagnetic valve 3 is a high-pressure rubber pipe, and the joint of the two ends is clamped by a large-caliber pipe hoop.
The integrated control cabinet consists of an air inlet pipeline, an air supply pipeline, an evacuation pipeline, a pressure gauge, a temperature display screen, a manual stop valve, a pressure release valve, a quick relay, a trigger control switch and the like. The integrated control cabinet is used as a master control system for evacuating, inflating and deflating the gas storage pipe 1, and simultaneously monitors the pressure and the temperature of the gas storage pipe 1 and controls the on-off of the trigger signal.
The gas storage pipe 1 is a section of stainless steel high-pressure round pipe with the length designed according to the required gas supply time.
The vacuum pump is used for replacing gas in the gas storage pipe 1 or sucking gas containing water vapor in the pipe, and the vacuum pump with corresponding power is configured according to the volume of the gas storage pipe 1 and the limited evacuation time.
The fast synchronous control system is composed of a trigger delayer, a signal generator, a fast relay, a fast electromagnetic valve 3 and the like, and is characterized in that the fast electromagnetic valve 3 can be triggered by a pressure signal of wind tunnel operation, an air source supply system is started, and stable jet flow is formed synchronously with a wind tunnel jet flow test model 6 around a flow field. And the trigger delayer receives the charge signal from the piezoelectric sensor of the shock tube, converts the charge signal into a voltage pulse signal, and can adjust the delay time to control the starting time of the subsequent quick electromagnetic valve 3. And the signal generator receives the voltage pulse signal from the trigger delayer, outputs a level signal with a certain pulse width and a certain voltage, and is used for switching on and off the air rapid relay. And the quick relay receives a level signal with a certain pulse width from the signal generator, and switches on or off the switching circuit of the quick electromagnetic valve 3 within the time of 1ms magnitude, so that the opening and the closing of the quick electromagnetic valve 3 are controlled. The rapid electromagnetic valve 3 adopts a pilot type normally closed rapid electromagnetic valve, the upper limit of the working pressure is about 1MPa, the action time of the complete opening is about 12ms, and the rapid electromagnetic valve is in a normally closed state when the power is off. A fast relay controlled by a signal generator is used as a control switch thereof. The pilot gas of the quick electromagnetic valve 3 is supplied by a gas cylinder, the quick electromagnetic valve 3 is connected by a single ventilation hose through a quick plug connector, and the power supply of the quick electromagnetic valve 3 is connected to a quick relay. The inlet end of a quick electromagnetic valve 3 communicated with the gas storage pipe 1 is connected with a metal gas supply pipe 2, and the outlet end of the quick electromagnetic valve 3 communicated with a Laval nozzle 5 is connected with a ventilation hose 4. The fast solenoid valve 3 is fixed in a position close to the model.
The air hose 4 is a metal hose with a smooth inner wall or a rubber hose with certain hardness, one end of the air hose is connected with the spray pipe, the other end of the air hose is connected with the outlet of the rapid electromagnetic valve 3, and the inner diameter of the air hose is equivalent to that of the inlet of the spray pipe.
The Laval nozzle 5 determines the Mach number of stable jet flow, is a contraction-expansion type Laval nozzle, is designed by adopting a characteristic line method and a boundary layer correction method, determines the size of an outlet according to the simulation requirement of a wind tunnel test, and determines the throat size of the nozzle and the shape of the inner wall surface of the nozzle according to the size of the outlet and the Mach number of the jet flow.
The L-shaped measuring bracket 701 of the jet flow parameter measuring device 7 is used for installing and fixing a pitot pressure probe 703 or a static pressure measuring probe 708, and ensures that the pressure measuring probe is opposite to jet flow by combining with the local shape design of the model. The measurement mount 701 is mounted and secured using heat measurement, pressure measurement holes or custom mounting holes on the mold. The pitot pressure probe 703 or the static pressure measurement probe 708 can be measured by movement of the gantry beam 704 to obtain the pressure distribution along the radial direction of the nozzle outlet cross-section. Meanwhile, the height of the bracket beam 704 along the measuring bracket 701 is adjustable, so that the pitot pressure probe 703 can just measure the pitot pressure of the section of the outlet of the spray pipe, and the needle head and the measuring hole of the static pressure measuring probe 708 are both positioned in the effective uniform area of the flow field of the outlet of the spray pipe.
The pitot pressure probe 703 is similar to a pitot pressure measurement probe of a conventional hypersonic flow field, and is composed of a pressure measurement pipe and a pressure sensor 706, wherein the pressure after the air flow stagnates in the pressure measurement pipe forms a normal shock wave rear pressure of the supersonic air flow, namely the pitot pressure of the flow field, and is measured by the pressure sensor 706 arranged at the rear end of the pressure measurement pipe.
The static pressure measurement probe 708 is a slender pointed conical cylindrical probe, the pressure measurement holes are arranged in a cylindrical section, the reasonable range of the ratio of the distance from the measurement holes to the pointed end to the diameter of the probe is 8-15, and a larger value is preferably selected under the condition of permitted size. The pressure sensor 706 is disposed at the rear end of the probe and avoids the effect of the increased diameter at which the pressure sensor 706 is mounted on the pressure distribution at the surface of the upstream column section. And correcting the direct measurement result according to the comparison between the surface pressure at the measuring point of the probe column section and the free flow static pressure.
The working process of the transient jet flow test device for the impulse wind tunnel of the embodiment is as follows:
s1, determining parameter ranges such as the Mach number of a Laval nozzle, jet static pressure, jet momentum and the like of a jet test model 6 according to pulse wind tunnel operation parameters and transient jet test requirements, and determining steady-state jet duration;
s2, designing and processing an air storage pipe;
the gas storage pipe 1 is a stainless steel high-pressure round pipe, two ends of the gas storage pipe are provided with dynamic pressure sensors, and the middle section of the gas storage pipe is provided with a static pressure gauge and a thermocouple thermometer; the total length of the gas storage pipe 1 is determined according to the required duration of stable jet flow;
the gas storage pipe 1 has region 1 shown in figure 5, and the gas flow Mach number of region 1
：
Wherein the content of the first and second substances,
the inner diameter of the gas storage pipe is mm;
the valve equivalent diameter of the rapid electromagnetic valve 3 is mm;
the specific heat ratio of the gas in the gas storage pipe is;
total temperature, total pressure and Mach number of air flow in zone 1 of air storage pipe 1
The following relationship is satisfied:
wherein the content of the first and second substances,
is the total temperature of the air flow in the area 1, K;
is the initial temperature of the gas storage pipe, K;
the total pressure Pa of the air flow in the area 1;
is the initial pressure of the gas storage pipe, Pa;
stable gas supply time
The calculation formula is as follows:
wherein the content of the first and second substances,
the total length of the gas storage pipe is m;
the velocity of airflow sound in the initial state of the gas storage pipe is m/s;
s3, mounting a jet flow test model 6, and debugging each system;
installing a jet flow test model 6 in a pulse wind tunnel test section, connecting an air source supply system with the jet flow test model 6, and debugging the air source supply system and a rapid synchronous control system;
s4, measuring airflow parameters of the outlet 702 of the spray pipe;
a jet flow parameter measuring device 7 is arranged at the position of a jet pipe outlet 702 of the jet flow test model 6; opening an air source supply system, spraying air flow out of the spray pipe outlet 702, and measuring the jet flow pitot pressure and jet flow static pressure by a jet flow parameter measuring device 7; computing jet Mach number
：
Wherein the content of the first and second substances,
jet pitot pressure, kPa;
jet static pressure, kPa;
jet Mach number;
is the specific heat ratio of the jet flow medium;
s5, carrying out a pulse wind tunnel transient jet flow test;
as shown in fig. 6, the transient jet device is initialized, and waits for the impulse wind tunnel to start; the pulse wind tunnel is started, the membrane of the membrane cavity of the shock tube is broken, a charge signal is sent to a trigger delayer of the rapid synchronous control system, the trigger delayer starts timing, after the preset delay time is reached, a signal generator outputs a level signal with fixed pulse width and voltage, a rapid relay is switched on, a rapid electromagnetic valve 3 is opened, and the medium gas of the gas storage tube 1 of the gas source supply system flows out of a Laval nozzle 5 of a jet flow test model 6 to form stable jet flow; meanwhile, the main flow of the pulse wind tunnel reaches a test section, a model bypass is established, and the effect of synchronizing the stable jet flow forming time and the pulse wind tunnel main flow forming time is achieved; the method comprises the steps that a pulse wind tunnel measurement and control system obtains jet flow-disturbed flow interference test data; after the main flow of the pulse wind tunnel is finished, the rapid synchronous control system automatically closes the air source supply system after the set stable jet flow duration is reached; and finishing the transient jet flow test of the pulse wind tunnel.
Fig. 7 is a pitot pressure curve and a static pressure curve measured by the jet flow parameter measuring device 7. In FIG. 7, at about time 706ms, the jet nozzle outlet 702 begins to emit a jet of gas, and the pressure begins to rise; at about 733ms, the pitot pressure began to stabilize, indicating that a steady jet had been established; at about 786ms, the pitot pressure begins to decrease, indicating that the fast solenoid valve 3 has closed. In short, the measurement results shown in fig. 7 indicate that the transient jet device achieves a rapid establishment of a stable jet, an effective duration of about 53ms, a good pressure plateau, and stable jet parameters.
Fig. 8 is a timing sequence synchronous debugging curve of a stable jet flow and a main flow of a test, a solid line is a heat flow curve of a measuring point on the surface of the model outside a jet flow interference area on the jet flow test model 6, and the solid line reflects the arrival of the main flow of the wind tunnel and the establishment, stabilization and termination processes of the model bypass flow formed by the main flow of the wind tunnel. Meanwhile, the measured jet flow pitot pressure curve also reaches a stable state at the arrival time of the main flow of the wind tunnel, and the duration of the stable jet flow completely covers the model flow-surrounding stable time. In short, the measurement result shows that the jet flow device can realize the synchronization of the stable jet flow and the wind tunnel main flow, and the duration of the stable jet flow is enough to meet the wind tunnel test requirement.
Although the embodiments of the present invention have been disclosed above, it is not limited to the applications listed in the description and the embodiments, but it can be applied to various fields suitable for the present invention. Additional modifications and refinements of the present invention will readily occur to those skilled in the art without departing from the principles of the present invention, and therefore the present invention is not limited to the specific details and illustrations shown and described herein without departing from the general concept defined by the claims and their equivalents.
Claims (8)
1. A transient jet flow test device for a pulse wind tunnel is characterized by comprising a jet flow test model (6), an air source supply system, a rapid synchronous control system and a jet flow parameter measuring device (7); the jet flow test model (6) sprays stable jet flow; the air source supply system provides a stable air source required by stable jet flow, and the rapid synchronous control system ensures that the forming time of the stable jet flow is synchronous with the forming time of the main flow of the pulse wind tunnel; meanwhile, the air source supply system ensures that the duration time of the stable jet flow exceeds the effective test time of the main flow of the pulse wind tunnel, and the rapid synchronous control system automatically closes the air source supply system after the set stable jet flow duration is reached; the jet flow parameter measuring device (7) is used for measuring the flow field parameters of the stable jet flow ejected by the fixed model before the jet flow test;
the jet flow test model (6) is arranged at a test section of the pulse wind tunnel, and comprises a model body and a Laval nozzle (5) arranged in the model body, wherein an outlet of the Laval nozzle (5) is in smooth transition with the surface of the model body, an inlet of the Laval nozzle (5) is connected with an air hose (4) of an air source supply system, and the Laval nozzle (5) sprays ultrasonic stable jet flow with required Mach number;
the air source supply system comprises an air bottle group, an air storage pipe (1), a small-caliber air pipe (2) and an air hose (4) which are sequentially connected in the air flow direction, and further comprises an integrated control cabinet and a vacuum pump; the gas cylinder group and the gas storage pipe (1) are positioned outside a test section of the pulse wind tunnel, and the small-caliber breather pipe (2) extends into the test section through a side wall flange of the test section; the gas storage pipe (1) is provided with a pressure sensor for measuring the gas pressure in the gas storage pipe (1) and a temperature sensor for measuring the gas temperature; the integrated control cabinet sucks residual gas in the gas storage pipe (1) through a vacuum pump, and controls the pressure and the temperature of medium gas entering the gas storage pipe (1) from the gas cylinder group through feedback signals of a pressure sensor and a temperature sensor to provide the medium gas required by stable jet flow;
the rapid synchronous control system comprises a trigger delayer, a signal generator, a rapid relay and a rapid electromagnetic valve (3) which are connected through a cable; the rapid electromagnetic valve (3) is positioned near or inside the jet flow test model (6) and is arranged between the small-caliber breather pipe (2) and the breather hose (4) of the air source supply system; the trigger delayer receives a charge signal from a piezoelectric sensor of the pulse wind tunnel shock tube, converts the charge signal into a voltage pulse signal, and adjusts delay time to control the starting time of a subsequent quick electromagnetic valve (3); the signal generator receives the voltage pulse signal from the trigger delayer, outputs a level signal with fixed pulse width and voltage, and is used for switching on and switching off the quick relay; the rapid relay receives the level signal from the signal generator, switches on or off a switching circuit of the rapid electromagnetic valve (3), and controls the rapid electromagnetic valve (3) to be opened and closed;
the jet flow parameter measuring device (7) is fixed on the jet flow test model (6) before the pulse wind tunnel jet flow test, and outlet airflow parameters of the Laval nozzle (5) are measured through the Pitot pressure probe (703) and the static pressure probe.
2. The transient jet test device for the impulse wind tunnel according to claim 1, characterized in that the L-shaped measuring brackets (701) of the jet parameter measuring device (7) are symmetrically fixed at two sides of the nozzle outlet (702), the horizontal feet of the L-shaped measuring brackets (701) are fixed on the surface of the jet test model (6), and the vertical pillars are perpendicular to the surface of the jet test model (6); a bracket beam (704) is supported on a vertical pillar, a wedge-shaped sensor support (705) is fixed on the bracket beam (704), and a wedge-shaped wedge of the sensor support (705) is opposite to a spray pipe outlet (702); a pressure sensor (706) is arranged in the sensor support (705), and the rear end of each probe is connected with one pressure sensor (706) in the sensor support (705); a protective cover (707) is sleeved on the rear part of the sensor support (705); the front end of the probe extends downwards out of the sensor support (705) and is opposite to the nozzle outlet (702); a cable of the pressure sensor (706) extends upwards out of the protective cover (707) to be connected with the pulse wind tunnel measurement and control system; the probe comprises a pitot pressure probe (703) for fixedly measuring the total pressure after the supersonic gas flow shock wave of the nozzle outlet (702), and a static pressure measuring probe (708) for fixedly measuring the static pressure of the nozzle outlet (702).
3. The transient jet test device for the impulse wind tunnel according to claim 2, characterized in that a sensor support (705) of the jet parameter measuring device (7) is transversely moved through a support beam (704) to measure jet parameters of different positions of a nozzle outlet (702) in the radial direction; a vertical pillar of an L-shaped measuring support (701) of the jet flow parameter measuring device (7) and a support beam (704) are provided with corresponding track sliding block mechanisms, the support beam (704) drives a sensor support (705) to slide up and down through the track sliding block mechanisms, and the height between a pitot pressure probe (703) or a static pressure probe and a spray pipe outlet (702) is adjusted.
4. The transient jet flow test device for the impulse wind tunnel according to claim 1, wherein the gas cylinder set is provided with a pressure reducing valve and a safety pressure relief valve, and is connected to the integrated control cabinet through a stainless steel high-pressure pipe, the integrated control cabinet monitors through a control cabinet panel, and operates the inflation and deflation of the gas cylinder set to keep the gas medium in the gas cylinder set to have stable gas pressure and temperature parameters.
5. The transient jet test device for the impulse wind tunnel according to claim 1, wherein the gas medium in the gas cylinder group is one of nitrogen, air or helium.
6. The transient jet test device for the pulse wind tunnel according to claim 1, wherein the inflation control valve, the deflation control valve and the evacuation control valve of the gas storage pipe (1) are installed in an integrated control cabinet, and the gas storage pipe (1) is operated to inflate, deflate and evacuate through a control cabinet panel, so that the gas medium in the gas storage pipe (1) is monitored and maintained to have stable gas pressure and temperature parameters.
7. The transient jet flow test device for the pulse wind tunnel according to claim 1, wherein the rapid relay is a solid-state rapid relay, a 220V alternating current circuit is connected within 1ms, so that a power supply of the rapid solenoid valve (3) is connected, the rapid solenoid valve (3) is opened, and the stable jet flow of the jet flow test model (6) is started.
8. The transient jet test device for the impulse wind tunnel according to claim 1, wherein the fast solenoid valve (3) is a pilot type normally closed fast solenoid valve which is automatically triggered and has a preset time length, and the valve opening action time is less than 15 ms.
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| CN114354124A (en) * | 2022-03-11 | 2022-04-15 | 中国空气动力研究与发展中心超高速空气动力研究所 | High-precision synchronous control method for impulse wind tunnel jet flow interference test |
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