CN109186920A - A kind of ramjet engine air inlet restriction characteristic automation control wind tunnel test methods - Google Patents
A kind of ramjet engine air inlet restriction characteristic automation control wind tunnel test methods Download PDFInfo
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- CN109186920A CN109186920A CN201811035350.6A CN201811035350A CN109186920A CN 109186920 A CN109186920 A CN 109186920A CN 201811035350 A CN201811035350 A CN 201811035350A CN 109186920 A CN109186920 A CN 109186920A
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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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Abstract
The invention discloses a kind of ramjet engine air inlet restriction characteristic automation control wind tunnel test methods.Row's static pressure monitoring point is distributed along journey key position in air intake duct model in wind tunnel, real-time measurement and feedback are carried out to monitoring point using high-precision quick response pressure measurement sensor and acquisition system, according to Supersonic Flow not forward pass characteristic, it can determine whether terminal shock wave position by static pressure monitoring point value of feedback, it sends control instruction to back-pressure regulating system and increases or reduces back-pressure, to reach air intake duct expected flow state, then sends acquisition instructions and carry out full measuring point pressure data acquisition.It realizes and the automatic closed loop of back-pressure regulating system and data collection system is controlled, so that primary blowing can get the trystate lower ideal restriction characteristic curve.
Description
Technical field
The present invention relates to a kind of automation control wind tunnel test methods.
Background technique
Air intake duct is a critical component of airbreather, and the superiority and inferiority of performance directly influences engine or even flies
The overall performance of row device.Air intake duct wind tunnel test is the main means assessed inlet characteristic, obtain inlet characteristics parameter,
Middle discharge coefficient and total pressure recovery coefficient are most important two characterisitic parameters of air intake duct, and the main purpose of wind tunnel test is also to be
The complete rule changed with air intake port back-pressure both is obtained, to evaluate the workability under air intake duct difference work condition state
Energy.
The simulation of the back-pressure of air intake test outlet at present is all made of the form of throttling cone, and the method generallyd use is all to try
Testing the preceding tester that dries, rule of thumb position is bored in the several throttlings of manual setting by theory analysis, and test is pressed given in the process
Position carries out data acquisition.This results in a blowing test to be difficult to obtain an ideal restriction characteristic curve, can not capture
To the optimal performance parameter of air intake duct in this state, or even also need secondary wind of re-blowing.This conventional method not only increases wind
The accuracy of hole experimental test, also improves experimentation cost.
In face of the urgent need of current air intake duct technology development, the Research Ability of current air intake duct wind tunnel test technology has been shown
Deficiency, due to manually taking uncertainty a little during test, the development for being difficult to model provides the technical support of fining, instead
Pressure regulating system couples regulation technology with the automation of data collection system and highlights necessity.
Summary of the invention
The technical problems to be solved by the present invention are: overcome the deficiencies in the prior art, the present invention provides a kind of punching press hairs
Motivation air intake duct restriction characteristic automation control wind tunnel test methods pass through different control strategies according to different tests demand
It realizes and the automatic closed loop of air intake port back-pressure regulating system and data collection system is controlled, eliminate manual intervention and bring
Uncertain factor so that a blowing test can get ideal restriction characteristic curve under the state.
The technical scheme adopted by the invention is that: a kind of ramjet engine air inlet restriction characteristic automation control wind-tunnel examination
Proved recipe method, comprises the following steps that
(1) several static pressure monitoring points, static pressure are set along flow direction near ramjet engine air inlet test model venturi
Monitoring point is connect with static monitor system, for monitoring air intake duct inner flow passage flow regime；
(2) static pressure monitoring point pressure threshold α is set, when monitoring static pressure monitoring point pressure beyond static pressure monitoring point pressure threshold
When value α, pressure acquisition system carries out full measuring point pressure data acquisition；The regulations speed of back-pressure regulating system during testing is set
v；
(3) after Flow Field in Wind Tunnel is established and stablized, static monitor system collects and records the pressure of primary all static pressure monitoring points
Force data, a reference value as the variation judgement of packing pressure value；
(4) control back-pressure regulating system increases air intake port back-pressure according to the regulations speed v actuation of setting, to most lower
Trip static pressure monitoring point pressure value is acquired and is judged in real time, when most downstream static pressure monitoring point current pressure values are with respect to step (3)
When the variable quantity of a reference value exceeds static pressure monitoring point pressure threshold α, stop back-pressure and adjust, and carries out primary full measuring point pressure
Value acquisition, obtains the inlet characteristic parameter under the state, inlet characteristic parameter includes discharge coefficient and total pressure recovery coefficient；
(5) step (4) are repeated, all static pressure monitoring points is successively traversed by air intake duct downstream to upstream.
Along flow direction 6~10 static pressure of setting near ramjet engine air inlet test model venturi in the step (1)
Monitoring point.
The static monitor system acquires the static pressure force value of static pressure monitoring point in real time, and to monitor static pressure supervise
Whether measuring point pressure, which exceeds static pressure monitoring point pressure threshold α, is judged, processing frequency is greater than 10Hz.
Pressure acquisition system is used for the acquisition of the full measuring point pressure value of air intake test model in the step (2), and judges
Whether the acquisition of data to all static pressure monitoring points is completed.
To the different settable different static pressure monitoring point pressure thresholds in static pressure monitoring point in the step (2).
The advantages of the present invention over the prior art are that:
(1) present invention is adjusted using the automation that air intake duct aerodynamic characteristic itself realizes data collection system, is avoided
Manual intervention bring uncertain factor, improves the accuracy of experimental test.
(2) flow regime that corresponding air intake duct is triggered in the static pressure monitoring point set by the present invention has certain physics meaning
Justice, i.e., pressure data collected is virtual value, avoids the invalidated acquisitions bring wasting of resources, reduces experimentation cost.
(3) the method for the present invention does not need the restriction characteristic for analyzing air intake duct current state in advance, need to only set static pressure monitoring
Point change threshold and back-pressure regulating system regulations speed shorten artificial intervention time before test, improve test efficiency.
(4) the method for the present invention has incomparable advantage for the test of venturi variable geometry inlet, can be by once testing
The optimal characteristic of shutting off for obtaining air intake duct under each venturi height, largely improves relative to conventional admission road measuring technology
Test efficiency.
Detailed description of the invention
Fig. 1 is air intake duct wind tunnel test automation control experiment process figure of the present invention；
Fig. 2 is air intake test system structure schematic diagram of the present invention；
Fig. 3 is typical ramjet engine air inlet along journey static pressure distribution curve；
Fig. 4 is present invention gained air intake duct restriction characteristic curve；
Specific embodiment
Below in conjunction with attached drawing and specific implementation, the present invention will be further described in detail.
As shown in Figure 1, a kind of ramjet engine air inlet restriction characteristic automation control wind tunnel test methods, including step
It is as follows:
(1) along 6~10 static pressure monitoring points of flow direction setting, static pressure near ramjet engine air inlet test model venturi
Monitoring point is connect with static monitor system, for monitoring air intake duct inner flow passage flow regime；Static monitor system monitors static pressure
Point static pressure force value acquired in real time, and to monitor static pressure monitor point pressure whether exceed static pressure monitoring point pressure threshold
α is judged that processing frequency is greater than 10Hz.
(2) static pressure monitoring point pressure threshold α is set, when monitoring static pressure monitoring point pressure beyond static pressure monitoring point pressure threshold
When value α, pressure acquisition system carries out full measuring point pressure data acquisition；The regulations speed of back-pressure regulating system during testing is set
v；Pressure acquisition system is used for the acquisition of the full measuring point pressure value of air intake test model, and judges whether to complete to all static pressure
The acquisition of the data of monitoring point.Point pressure is monitored to the different settable different static pressure in static pressure monitoring point in the step (2)
Threshold value.
(3) after Flow Field in Wind Tunnel is established and stablized, static monitor system collects and records the pressure of primary all static pressure monitoring points
Force data, a reference value as the variation judgement of packing pressure value；
(4) control back-pressure regulating system increases air intake port back-pressure according to the regulations speed v actuation of setting, to most lower
Trip static pressure monitoring point pressure value is acquired and is judged in real time, when most downstream static pressure monitoring point current pressure values are with respect to step (3)
When the variable quantity of a reference value exceeds static pressure monitoring point pressure threshold α, stop back-pressure and adjust, and carries out primary full measuring point pressure
Value acquisition, obtains the inlet characteristic parameter under the state, inlet characteristic parameter includes discharge coefficient and total pressure recovery coefficient；
(5) step (4) are repeated, all static pressure monitoring points is successively traversed by air intake duct downstream to upstream.
Embodiment:
A kind of ramjet engine air inlet restriction characteristic automation control wind tunnel test methods, include the following steps:
(1) as shown in Fig. 2, first in the ramjet engine air inlet test model design phase, according to tested air intake duct
Restriction characteristic determines the design position along journey static pressure monitoring point number and respective place air intake duct side wall, in addition to this by normal
Advise air intake duct modelling processing.Monitoring point measurement sensor should have the characteristics that high-precision quick response, acquisition system should have
Real-time storage and transfer function.Other pressure measurements and the optional conventional admission road pressure-measuring system of acquisition system.Back-pressure is adjusted
The optional conventional admission road throttling cone regulating system of system.Static pressure monitoring point is connect with static monitor system all the way by three-way connection
For each measuring point pressure change of real-time monitoring, common measuring point is connected to normal pressures measurement module all the way and carries out pressure survey
Amount.
(2) test before according to test demand be arranged automation control policing parameter, specifically include that static pressure monitoring point number and
Sequentially, the real-time frequency acquisition in static pressure monitoring point, pressure acquisition system carry out data and acquire corresponding static pressure monitoring point pressure value variation
The regulations speed of condition and back-pressure regulating system.
(3) start wind tunnel test after completing parameter set by step (2), stablize to Flow Field in Wind Tunnel and establish, attitude angle machine
After structure drives air intake duct model to reach dbjective state, static monitor system acquires and saves primary all static pressure monitoring points pressure value
Data, a reference value as the variation judgement of packing pressure value.
(4) as shown in figure 3, back-pressure adjusts actuation air intake port back-pressure is slowly improved by minimum value, according to ultrasound
Speed flows not forward pass characteristic, and with increasing for air intake port back-pressure, terminal shock wave back to front successively supervise by inswept all static pressure
Measuring point, the static pressure monitoring point pressure value being only swept in the process mutate, and the pressure value not being swept is constant, the mistake
Cheng Zhongxian is acquired and is judged in real time to most downstream static pressure monitoring point pressure value, if its pressure value relative datum value variable quantity is super
The threshold value of setting is crossed, static monitor system sends a command to back-pressure regulating system first and it is made to stop adjusting, then sends and refer to
It enables to pressure acquisition system and carries out full measuring point pressure acquisition, air intake duct is " back-pressure 1 " corresponding flow regime, terminal shock wave at this time
In " arrow 1 " position.
(5) after one acquisition, the back-pressure regulating system that static monitor system sends a command to continues to increase back-pressure, repeats
Step (4) successively traverses all static pressure monitoring points by downstream to upstream, judges that all acquisitions terminate by pressure acquisition system
Afterwards, primary test is completed, and wind-tunnel attitude angle mechanism is returned to zero, cut-off.
Gained air intake duct restriction characteristic curve such as " ideal curve " in Fig. 4 is shown by the method for the invention, compared to routine
The isenthalp that air intake test obtains, can more accurately capture the critical state of air intake duct and stall margin under the state, together
Shi Buhui has the appearance of invalid measurement point.
The content being not described in detail in this specification belongs to the well-known technique of professional and technical personnel in the field.
Claims (5)
1. a kind of ramjet engine air inlet restriction characteristic automation control wind tunnel test methods, which is characterized in that including step
It is as follows:
(1) several static pressure monitoring points, static pressure monitoring are set along flow direction near ramjet engine air inlet test model venturi
Point is connect with static monitor system, for monitoring air intake duct inner flow passage flow regime；
(2) static pressure monitoring point pressure threshold α is set, when monitoring static pressure monitoring point pressure beyond static pressure monitoring point pressure threshold α
When, pressure acquisition system carries out full measuring point pressure data acquisition；The regulations speed v of back-pressure regulating system during testing is set；
(3) after Flow Field in Wind Tunnel is established and stablized, static monitor system collects and records the number pressure of primary all static pressure monitoring points
According to a reference value judged as the variation of packing pressure value；
(4) control back-pressure regulating system increases air intake port back-pressure according to the regulations speed v actuation of setting, quiet to most downstream
Pressure monitoring point pressure value is acquired and is judged in real time, when most downstream static pressure monitoring point current pressure values are with respect to described in step (3)
When the variable quantity of a reference value exceeds static pressure monitoring point pressure threshold α, stop back-pressure and adjust, and carries out primary full measuring point pressure value and adopt
Collection, obtains the inlet characteristic parameter under the state, inlet characteristic parameter includes discharge coefficient and total pressure recovery coefficient；
(5) step (4) are repeated, all static pressure monitoring points is successively traversed by air intake duct downstream to upstream.
2. a kind of ramjet engine air inlet restriction characteristic automation control wind tunnel test methods according to claim 1,
It is characterized by: quiet along flow direction setting 6~10 near ramjet engine air inlet test model venturi in the step (1)
Press monitoring point.
3. a kind of ramjet engine air inlet restriction characteristic automation control wind tunnel test side according to claim 1 or 2
Method, it is characterised in that: the static monitor system acquires the static pressure force value of static pressure monitoring point in real time, and to monitoring
Whether static pressure monitoring point pressure, which exceeds static pressure monitoring point pressure threshold α, is judged, processing frequency is greater than 10Hz.
4. a kind of ramjet engine air inlet restriction characteristic automation control wind tunnel test side according to claim 1 or 2
Method, it is characterised in that: pressure acquisition system is used for the acquisition of the full measuring point pressure value of air intake test model in the step (2),
And judge whether to complete the acquisition of the data to all static pressure monitoring points.
5. a kind of ramjet engine air inlet restriction characteristic automation control wind tunnel test methods according to claim 1,
It is characterized by: to the different settable different static pressure monitoring point pressure thresholds in static pressure monitoring point in the step (2).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811035350.6A CN109186920B (en) | 2018-09-06 | 2018-09-06 | Automatic control wind tunnel test method for throttling characteristic of ramjet inlet |
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|---|---|---|---|
| CN201811035350.6A CN109186920B (en) | 2018-09-06 | 2018-09-06 | Automatic control wind tunnel test method for throttling characteristic of ramjet inlet |
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| CN109186920A true CN109186920A (en) | 2019-01-11 |
| CN109186920B CN109186920B (en) | 2020-09-18 |
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Cited By (8)
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| CN110907122A (en) * | 2019-11-19 | 2020-03-24 | 中国人民解放军国防科技大学 | Laser sheet light deflection device and wind tunnel optical measurement experiment system |
| CN111076875A (en) * | 2019-12-09 | 2020-04-28 | 北京动力机械研究所 | Adjustable runner high temperature dynamic seal directly links test device |
| CN112432759A (en) * | 2020-11-10 | 2021-03-02 | 北京动力机械研究所 | Axial-symmetry double-channel air inlet channel outlet back pressure adjusting and flow field measuring device |
| CN112432760A (en) * | 2020-11-10 | 2021-03-02 | 北京动力机械研究所 | Axial-symmetry double-channel air inlet channel outlet back pressure adjusting and flow field measuring method |
| CN113945355A (en) * | 2021-09-21 | 2022-01-18 | 中国航空工业集团公司西安飞机设计研究所 | Air inlet duct wind tunnel test simulation system under shock wave |
| CN115371933A (en) * | 2022-10-24 | 2022-11-22 | 中国航发四川燃气涡轮研究院 | Method for testing aerodynamic coupling between air inlet channel and aircraft forebody |
| CN116448374A (en) * | 2023-06-15 | 2023-07-18 | 中国航空工业集团公司沈阳空气动力研究所 | Air inlet duct wind tunnel test method for simulating multiple interference |
| CN117890071A (en) * | 2024-03-15 | 2024-04-16 | 中国空气动力研究与发展中心高速空气动力研究所 | Ultrasonic wind tunnel air inlet channel and engine coupling test method |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110907122A (en) * | 2019-11-19 | 2020-03-24 | 中国人民解放军国防科技大学 | Laser sheet light deflection device and wind tunnel optical measurement experiment system |
| CN111076875A (en) * | 2019-12-09 | 2020-04-28 | 北京动力机械研究所 | Adjustable runner high temperature dynamic seal directly links test device |
| CN112432759A (en) * | 2020-11-10 | 2021-03-02 | 北京动力机械研究所 | Axial-symmetry double-channel air inlet channel outlet back pressure adjusting and flow field measuring device |
| CN112432760A (en) * | 2020-11-10 | 2021-03-02 | 北京动力机械研究所 | Axial-symmetry double-channel air inlet channel outlet back pressure adjusting and flow field measuring method |
| CN113945355A (en) * | 2021-09-21 | 2022-01-18 | 中国航空工业集团公司西安飞机设计研究所 | Air inlet duct wind tunnel test simulation system under shock wave |
| CN113945355B (en) * | 2021-09-21 | 2024-01-30 | 中国航空工业集团公司西安飞机设计研究所 | Air inlet channel wind tunnel test simulation system under shock wave |
| CN115371933A (en) * | 2022-10-24 | 2022-11-22 | 中国航发四川燃气涡轮研究院 | Method for testing aerodynamic coupling between air inlet channel and aircraft forebody |
| CN116448374A (en) * | 2023-06-15 | 2023-07-18 | 中国航空工业集团公司沈阳空气动力研究所 | Air inlet duct wind tunnel test method for simulating multiple interference |
| CN116448374B (en) * | 2023-06-15 | 2023-08-22 | 中国航空工业集团公司沈阳空气动力研究所 | Air inlet duct wind tunnel test method for simulating multiple interference |
| CN117890071A (en) * | 2024-03-15 | 2024-04-16 | 中国空气动力研究与发展中心高速空气动力研究所 | Ultrasonic wind tunnel air inlet channel and engine coupling test method |
| CN117890071B (en) * | 2024-03-15 | 2024-05-17 | 中国空气动力研究与发展中心高速空气动力研究所 | Ultrasonic wind tunnel air inlet channel and engine coupling test method |
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