CN114323545A - High-precision synchronization control device for impulse wind tunnel jet flow interference test - Google Patents
High-precision synchronization control device for impulse wind tunnel jet flow interference test Download PDFInfo
- Publication number
- CN114323545A CN114323545A CN202210234666.8A CN202210234666A CN114323545A CN 114323545 A CN114323545 A CN 114323545A CN 202210234666 A CN202210234666 A CN 202210234666A CN 114323545 A CN114323545 A CN 114323545A
- Authority
- CN
- China
- Prior art keywords
- wind tunnel
- jet flow
- test
- electromagnetic valve
- control device
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Landscapes
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention belongs to the technical field of hypersonic pulse wind tunnel tests and discloses a high-precision synchronization control device for a pulse wind tunnel jet flow interference test. The gas storage pipe of the jet system of the synchronous control device is a Ludwigsh pipe; the quick electromagnetic valve is connected to the downstream end of the gas storage pipe of the jet system; the test model is connected with the outlet of the rapid electromagnetic valve; the sensor is arranged at the position of the low-pressure section of the pulse wind tunnel, which is close to the diaphragm of the high-low pressure section; the input interface of the delay trigger is connected with the sensor; the input interface of the signal generator is connected with the output interface of the delay trigger; the input interface of the quick relay is connected with the output interface of the signal generator, and the quick relay is conducted after receiving the output signal of the signal generator; the conventional power supply is connected with the quick electromagnetic valve through an electric wire. When the rapid relay is switched on, the rapid electromagnetic valve is switched on, and high-pressure gas in the gas storage pipe of the jet flow system flows out rapidly and forms stable jet flow synchronous with the main flow of the wind tunnel on the surface of the test model.
Description
Technical Field
The invention belongs to the technical field of hypersonic pulse wind tunnel tests, and particularly relates to a high-precision synchronization control device for a pulse wind tunnel jet flow interference test.
Background
When a high-orbit aircraft or a reentry aircraft flies at middle and high altitude, the air density is low, the dynamic pressure is low, the control efficiency of the traditional pneumatic rudder is low, the control requirement of the aircraft cannot be met by the pneumatic rudder alone, and in order to meet the requirement of high-altitude quick pneumatic control, the aircraft such as a non-lift reentry aircraft (such as a ship returning cabin), 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) adopt an engine plume and a Reaction Control System (RCS) to replace or assist the pneumatic rudder for control. The RCS jet flow and the incoming flow can generate strong interference, so that the heat flow peak value of an interference area of the RCS jet flow on the surface of the aircraft is increased by multiple times or even tens of times, and great challenges are brought to the prediction and heat protection design of the thermal environment on the surface of the aircraft.
In order to reduce the development risk of a cross-domain aircraft using an attitude and orbit control engine and improve people's knowledge of jet interference phenomena and aerodynamic/thermal influence rules of the aircraft, a pulse wind tunnel jet interference test technology and related test research work need to be developed on the ground urgently.
The high-mach-number pulse wind tunnel jet flow interference test is usually carried out in a pulse type wind tunnel with the test time of only millisecond magnitude, and the key technology for carrying out the jet flow interference test in the pulse wind tunnel is that a jet flow field and a pulse wind tunnel main flow field are required to be synchronously established within tens of milliseconds.
At present, a high-precision synchronization control device for a jet flow disturbance test of a pulse wind tunnel needs to be developed.
Disclosure of Invention
The invention aims to provide a high-precision synchronization control device for a jet flow interference test of a pulse wind tunnel.
The invention relates to a high-precision synchronous control device for a pulse wind tunnel jet interference test, which is characterized by comprising a jet system gas storage pipe, a quick electromagnetic valve, a test model, a sensor, a delay trigger, a signal generator, a quick relay and a conventional power supply, wherein the jet system gas storage pipe, the quick electromagnetic valve, the test model, the sensor, the delay trigger, the signal generator, the quick relay and the conventional power supply are arranged in a pulse wind tunnel body;
the pulse wind tunnel comprises a high-pressure section, a high-low pressure section diaphragm, a low-pressure section, a throat two-channel diaphragm, a Laval nozzle and a test section which are sequentially connected along the direction of test airflow, and is used for generating a test flow field with test time of about tens of milliseconds in the test section;
the gas storage pipe of the jet flow system is a Ludwigshi pipe;
the quick electromagnetic valve is connected to the downstream end of the gas storage pipe of the jet system through a pipe threaded interface and a metal gas pipe with the drift diameter matched with the pipe threaded interface;
the test model is connected with the outlet of the rapid electromagnetic valve through a high-pressure hose;
the sensor is arranged at the position of the low-pressure section of the pulse wind tunnel, which is close to the high-low pressure section diaphragm;
the input interface of the delay trigger is connected with the sensor through a coaxial signal line;
the input interface of the signal generator is connected with the output interface of the delay trigger through a coaxial signal line;
the input interface of the rapid relay is connected with the output interface of the signal generator through a coaxial signal wire, and the rapid relay is conducted after receiving the output signal of the signal generator;
the conventional power supply is connected with the rapid electromagnetic valve through an electric wire, and the rapid relay is positioned in a live wire circuit of the conventional power supply; when the quick relay is switched on, the conventional power supply provides voltage required by work for the quick electromagnetic valve, and the quick electromagnetic valve is switched on quickly, so that high-pressure gas in the gas storage pipe of the jet flow system flows out quickly and forms stable jet flow on the surface of the test model.
Furthermore, the gas storage pipe of the jet flow system is filled with jet flow gas media through a direct high-pressure gas source or a high-pressure gas bottle set, and the pressure range of the high-pressure gas source or the high-pressure gas bottle set is 5 MPa-16 MPa.
Furthermore, the quick electromagnetic valve is a normally closed two-position two-way valve; the quick electromagnetic valve is in a pilot gas type or a non-pilot gas type.
Furthermore, the test model is a cross-domain aircraft scale model with a reaction control system, or a flat plate, cone and column simplified model abstracted from the local jet flow interference position of the aircraft.
Further, the sensor is a pressure sensor or a temperature sensor.
Furthermore, the delay trigger has signal conversion and delay functions.
Further, the signal generator presets and outputs a pulse, square wave or step voltage signal according to the test requirement.
Further, the conventional power supply is a 220 volt alternating current power supply, or a direct current power supply.
The hypersonic pulse wind tunnel applicable to the high-precision synchronous control device for the pulse wind tunnel jet flow interference test comprises a shock wave wind tunnel, an expansion pipe wind tunnel and a gun wind tunnel.
The high-precision synchronous control device for the pulse wind tunnel jet flow interference test enables the pulse wind tunnel main flow and the jet flow field to achieve high-precision synchronization, the time difference of simultaneous establishment of the pulse wind tunnel main flow and the jet flow field is not more than 4ms, and the duration time of the jet flow field exceeds the effective test time of the pulse wind tunnel main flow.
The high-precision synchronous control device for the impulse wind tunnel jet flow interference test can enable a jet flow system to provide a jet flow field with high reliability, good repeatability and accurate test parameters, and is particularly suitable for ground simulation tests of jet flow interference on measurement and evaluation of the thermal environment of a cross-domain aircraft surface interference area.
Drawings
Fig. 1 is a schematic overall layout diagram of a high-precision synchronization control device for a pulsed wind tunnel jet flow disturbance test according to the present invention.
In the figure, 1, a pulse wind tunnel; 2. a jet system gas storage tube; 3. a fast electromagnetic valve; 4. a test model; 5. a sensor; 6. a delay trigger; 7. a signal generator; 8. a fast relay; 9. a conventional power supply;
101. a high pressure section; 102. a high and low pressure section diaphragm; 103. a low-pressure section; 104. a second diaphragm of the throat; 105. a laval nozzle; 106. and (5) testing.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and examples.
As shown in FIG. 1, the high-precision synchronous control device for the impulse wind tunnel jet interference test comprises a jet system gas storage pipe 2 arranged in a body of an impulse wind tunnel 1, a quick electromagnetic valve 3, a test model 4, a sensor 5, a delay trigger 6, a signal generator 7, a quick relay 8 and a conventional power supply 9;
the impulse wind tunnel 1 comprises a high-pressure section 101, a high-low pressure section diaphragm 102, a low-pressure section 103, a second throat diaphragm 104, a Laval nozzle 105 and a test section 106 which are sequentially connected along the direction of test airflow, and the impulse wind tunnel is used for generating a test flow field with test time of about tens of milliseconds in the test section 106;
the gas storage pipe 2 of the jet flow system is a Ludwigshi pipe;
the rapid electromagnetic valve 3 is connected to the downstream end of the gas storage pipe 2 of the jet system through a pipe threaded interface and a metal gas pipe with the drift diameter matched with the pipe threaded interface;
the test model 4 is connected with the outlet of the rapid electromagnetic valve 3 through a high-pressure hose;
the sensor 5 is arranged at the position of a low-pressure section 103 of the pulse wind tunnel 1 close to a high-low pressure section diaphragm 102;
the input interface of the delay trigger 6 is connected with the sensor 5 through a coaxial signal line;
the input interface of the signal generator 7 is connected with the output interface of the delay trigger 6 through a coaxial signal line;
an input interface of the rapid relay 8 is connected with an output interface of the signal generator 7 through a coaxial signal wire, and the rapid relay 8 is conducted after receiving an output signal of the signal generator 7;
the conventional power supply 9 is connected with the rapid electromagnetic valve 3 through an electric wire, and the rapid relay 8 is positioned in a live wire circuit of the conventional power supply 9; when the quick relay 8 is switched on, the conventional power supply 9 provides voltage required by work for the quick electromagnetic valve 3, and the quick electromagnetic valve 3 is switched on quickly, so that high-pressure gas in the gas storage pipe 2 of the jet flow system flows out quickly and forms stable jet flow on the surface of the test model 4.
Further, the gas storage pipe 2 of the jet system is filled with jet flow gas media through a direct supply high-pressure gas source or a high-pressure gas cylinder set, and the pressure range of the high-pressure gas source or the high-pressure gas cylinder set is 5 MPa-16 MPa.
Further, the fast electromagnetic valve 3 is a normally closed two-position two-way valve; the rapid electromagnetic valve 3 is of a pilot gas type or a non-pilot gas type.
Further, the test model 4 is a cross-domain aircraft scaling model with a reaction control system, or a simplified model of a flat plate, a cone and a column abstracted from the local jet flow interference position of the aircraft.
Further, the sensor 5 is a pressure sensor or a temperature sensor.
Further, the delay flip-flop 6 has signal conversion and delay functions.
Further, the signal generator 7 outputs a pulse, square wave or step voltage signal according to the test requirement.
Further, the conventional power supply 9 is a 220 volt alternating current power supply, or a direct current power supply.
Example 1
In the embodiment, the pulse wind tunnel 1 is a shock wave wind tunnel driven by high-pressure helium, wherein a mixed gas of helium with a molar concentration of 90% and nitrogen with a molar concentration of 10.5MPa is filled in the high-pressure section 101, pure nitrogen with a molar concentration of 0.125MPa is filled in the low-pressure section 103, and a Laval nozzle 105 adopts a nozzle with an outlet diameter of 2 meters and a Mach number of 12; the gas storage pipe 2 of the jet flow system is a Ludwigshi pipe with the inner diameter of 80mm, the outer diameter of 89mm and the total length of 14m, and pure CF with the pressure of 4MPa is filled in the pipe4A gas; the fast electromagnetic valve 3 adopts a high-temperature and high-pressure resistant fast electromagnetic valve with model number XYGW-15P-250G of Shanghai Xin valve Co., Ltd; the test model 4 adopts a triangular wedge metal model with an RCS transverse spray pipe; sensingThe device 5 adopts a piezoelectric type quick response pressure sensor which is self-made by a shock tunnel laboratory of the ultra-high speed aerodynamic research institute of China and is numbered V1001-210802; the delay trigger 6 adopts a speed measuring trigger device with a charge input voltage output function and a delay function; the signal generator 7 adopts a pulse signal generator which has an external trigger function and is adjustable in pulse width, high level, time period and rising edge; the rapid relay 8 adopts a single-phase solid state relay SSR-40DD for controlling direct current by direct current; the conventional power supply 9 adopts a direct-current power supply with adjustable stable output voltage.
The time from the beginning of the rupture of the high-low pressure section membrane 102 to the stable establishment of the free flow field in the test section 106 of the shock tunnel is about 45ms, the stable duration time of the free flow field is about 19ms, the establishment time of the surface jet flow field of the test model 4 is about 41ms, and the stable duration time of the jet flow is about 50ms, so that the time difference between the stable establishment of the surface jet flow of the test model 4 and the stable establishment of the main flow of the shock tunnel test section is not more than 4ms, and the high-precision synchronous control effect is achieved.
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 high-precision synchronous control device for a pulse wind tunnel jet flow interference test is characterized by comprising a jet flow system gas storage pipe (2), a quick electromagnetic valve (3), a test model (4), a sensor (5), a delay trigger (6), a signal generator (7), a quick relay (8) and a conventional power supply (9), wherein the jet flow system gas storage pipe is arranged beside a pulse wind tunnel (1) body;
the pulse wind tunnel (1) comprises a high-pressure section (101), a high-pressure section diaphragm (102), a low-pressure section (103), a second throat diaphragm (104), a Laval nozzle (105) and a test section (106) which are sequentially connected along the direction of test airflow, and the pulse wind tunnel is used for generating a test flow field with test time of tens of milliseconds in the test section (106);
the gas storage pipe (2) of the jet flow system is a Ludwigshi pipe;
the rapid electromagnetic valve (3) is connected to the downstream end of the jet system gas storage pipe (2) through a pipe threaded interface and a metal gas pipe with the drift diameter matched with the pipe threaded interface;
the test model (4) is connected with the outlet of the rapid electromagnetic valve (3) through a high-pressure hose;
the sensor (5) is arranged at the position, close to the high-low pressure section diaphragm (102), of the low pressure section (103) of the pulse wind tunnel (1);
the input interface of the delay trigger (6) is connected with the sensor (5) through a coaxial signal line;
the input interface of the signal generator (7) is connected with the output interface of the delay trigger (6) through a coaxial signal line;
an input interface of the rapid relay (8) is connected with an output interface of the signal generator (7) through a coaxial signal line, and the rapid relay (8) is conducted after receiving an output signal of the signal generator (7);
the conventional power supply (9) is connected with the rapid electromagnetic valve (3) through an electric wire, and the rapid relay (8) is positioned in a live wire circuit of the conventional power supply (9); when the quick relay (8) is conducted, the conventional power supply (9) provides voltage required by work for the quick electromagnetic valve (3), and the quick electromagnetic valve (3) is conducted, so that high-pressure gas in the gas storage pipe (2) of the jet flow system flows out and jet flow is formed on the surface of the test model (4).
2. The high-precision synchronous control device for the impulse wind tunnel jet flow interference test according to claim 1, wherein the jet flow system gas storage pipe (2) is filled with jet flow gas media through a direct supply high-pressure gas source or a high-pressure gas bottle set, and the pressure range of the high-pressure gas source or the high-pressure gas bottle set is 5 MPa-16 MPa.
3. The high-precision synchronous control device for the impulse wind tunnel jet flow disturbance test according to claim 1, wherein the quick electromagnetic valve (3) is a normally closed two-position two-way valve; the rapid electromagnetic valve (3) is in a pilot gas type or a non-pilot gas type.
4. The high-precision synchronous control device for the impulse wind tunnel jet flow interference test according to claim 1, wherein the test model (4) is a cross-domain aircraft scale model with a reaction control system, or a simplified model of a flat plate, a cone and a column abstracted from a local jet flow interference position of an aircraft.
5. A high-precision synchronous control device for a pulsed wind tunnel jet disturbance test according to claim 1, characterized in that the sensor (5) is a pressure sensor or a temperature sensor.
6. The high-precision synchronization control device for the impulse wind tunnel jet flow disturbance test according to claim 1, wherein the delay trigger (6) has signal conversion and delay functions.
7. A high-precision synchronous control device for a pulse wind tunnel jet flow disturbance test according to claim 1, characterized in that the signal generator (7) is preset to output a pulse, square wave or step voltage signal according to test requirements.
8. A high precision synchronous control device for impulse wind tunnel jet disturbance test according to claim 1, characterized in that said regular power supply (9) is 220 volt alternating current power supply or direct current power supply.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210234666.8A CN114323545A (en) | 2022-03-11 | 2022-03-11 | High-precision synchronization control device for impulse wind tunnel jet flow interference test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210234666.8A CN114323545A (en) | 2022-03-11 | 2022-03-11 | High-precision synchronization control device for impulse wind tunnel jet flow interference test |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114323545A true CN114323545A (en) | 2022-04-12 |
Family
ID=81033903
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210234666.8A Pending CN114323545A (en) | 2022-03-11 | 2022-03-11 | High-precision synchronization control device for impulse wind tunnel jet flow interference test |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114323545A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117386830A (en) * | 2023-12-13 | 2024-01-12 | 中国空气动力研究与发展中心超高速空气动力研究所 | Quick response pneumatic needle valve suitable for pulse wind tunnel and application method thereof |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108398272A (en) * | 2017-12-14 | 2018-08-14 | 中国航天空气动力技术研究院 | A kind of fuel system and method for the experiment of shock tunnel super burn engine inlets |
| CN108709713A (en) * | 2017-04-11 | 2018-10-26 | 通用电气公司 | Skin support still air data testing system with automatic dependent surveillance verifying broadcasts |
| CN110542532A (en) * | 2019-09-10 | 2019-12-06 | 中国空气动力研究与发展中心超高速空气动力研究所 | Wind tunnel helium gas reuse device |
| CN113884267A (en) * | 2021-12-07 | 2022-01-04 | 中国空气动力研究与发展中心超高速空气动力研究所 | Transient jet flow test device for pulse wind tunnel |
| CN113899516A (en) * | 2021-09-30 | 2022-01-07 | 中国空气动力研究与发展中心超高速空气动力研究所 | Ground simulation device and method for rocket engine jet flow interference effect |
-
2022
- 2022-03-11 CN CN202210234666.8A patent/CN114323545A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108709713A (en) * | 2017-04-11 | 2018-10-26 | 通用电气公司 | Skin support still air data testing system with automatic dependent surveillance verifying broadcasts |
| CN108398272A (en) * | 2017-12-14 | 2018-08-14 | 中国航天空气动力技术研究院 | A kind of fuel system and method for the experiment of shock tunnel super burn engine inlets |
| CN110542532A (en) * | 2019-09-10 | 2019-12-06 | 中国空气动力研究与发展中心超高速空气动力研究所 | Wind tunnel helium gas reuse device |
| CN113899516A (en) * | 2021-09-30 | 2022-01-07 | 中国空气动力研究与发展中心超高速空气动力研究所 | Ground simulation device and method for rocket engine jet flow interference effect |
| CN113884267A (en) * | 2021-12-07 | 2022-01-04 | 中国空气动力研究与发展中心超高速空气动力研究所 | Transient jet flow test device for pulse wind tunnel |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117386830A (en) * | 2023-12-13 | 2024-01-12 | 中国空气动力研究与发展中心超高速空气动力研究所 | Quick response pneumatic needle valve suitable for pulse wind tunnel and application method thereof |
| CN117386830B (en) * | 2023-12-13 | 2024-02-02 | 中国空气动力研究与发展中心超高速空气动力研究所 | Quick response pneumatic needle valve suitable for pulse wind tunnel and application method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN114354124B (en) | High-precision synchronous control method for jet flow interference test of pulse wind tunnel | |
| CN102507203B (en) | Shockwave wind tunnel-based self-starting test device for hypersonic air inlet channel | |
| Hannemann et al. | The high enthalpy shock tunnel Göttingen of the German aerospace center (DLR) | |
| Gildfind et al. | Performance considerations for expansion tube operation with a shock-heated secondary driver | |
| Liu et al. | Aerodynamic control of NACA 0021 airfoil model with spark discharge plasma synthetic jets | |
| CN114323545A (en) | High-precision synchronization control device for impulse wind tunnel jet flow interference test | |
| Grossir | Longshot hypersonic wind tunnel flow characterization and boundary layer stability investigations | |
| Wang et al. | Aerodynamic characteristics research on wide-speed range waverider configuration | |
| Chinske et al. | Visualization and Measurement of Transverse Jet Injection on a 7 Degree Half-Angle Cone in Hypersonic Quiet Flow | |
| CN113027613B (en) | Supersonic mixed pressure type air inlet starting device based on plasma synthetic jet | |
| Peters et al. | An evaluation of jet simulation parameters for nozzle/afterbody testing at transonic Mach numbers | |
| Anfimov | TsNIIMASH capabilities for aerogasdynamical and thermal testing of hypersonic vehicles | |
| Marsh et al. | Experimental investigation of the hypersonic'Air Spike'inlet at Mach 10 | |
| Nonaka et al. | Vertical landing aerodynamics of reusable rocket vehicle | |
| Verma et al. | Cold gas dual-bell tests in high-altitude simulation chamber | |
| Prasad et al. | Impingement of supersonic jets on an axisymmetric deflector | |
| Landsbaum | Contour nozzles | |
| Diankai et al. | PIV experiment study on interaction between pulsed laser plasma and normal shock | |
| Juhany et al. | AT0 Ludwieg tube wind tunnel at KAU | |
| Bougas et al. | Design and experimental validation of a propulsion duct for a jet propelled low observable scaled UAV demonstrator | |
| Mahapatra et al. | Effect of counterflow argon plasma jet on aerodynamic drag of a blunt body at hypersonic Mach numbers | |
| Rizkalla et al. | Use of an expansion tube to examine scramjet combustion at hypersonic velocities | |
| Liu et al. | Turbine Based Combined Cycle Inlet Mode Transition at Different Operation Conditions | |
| DOSANJH et al. | Experiments with Two-Dimensional, Transversely Impinging Jets | |
| Hsu et al. | Simulation of multiple shock-shock interference patterns on a cylindrical leading edge |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20220412 |
|
| WD01 | Invention patent application deemed withdrawn after publication |