CN109186920B - Automatic control wind tunnel test method for throttling characteristic of ramjet inlet - Google Patents
Automatic control wind tunnel test method for throttling characteristic of ramjet inlet Download PDFInfo
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- CN109186920B CN109186920B CN201811035350.6A CN201811035350A CN109186920B CN 109186920 B CN109186920 B CN 109186920B CN 201811035350 A CN201811035350 A CN 201811035350A CN 109186920 B CN109186920 B CN 109186920B
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Abstract
The invention discloses an automatic control wind tunnel test method for a throttling characteristic of an air inlet passage of a ramjet engine. A row of static pressure monitoring points are distributed at a key position along the way of an air inlet tunnel test model, a high-precision quick response pressure measuring sensor and an acquisition system are adopted to carry out real-time measurement and feedback on the monitoring points, the position of a tail shock wave can be judged through a feedback value of the static pressure monitoring points according to the characteristic that supersonic flow does not forward, a control instruction is sent to a back pressure adjusting system to increase or decrease back pressure so as to achieve the expected flow state of an air inlet, and then an acquisition instruction is sent to carry out full-measuring-point pressure data acquisition. Automatic closed-loop control over the back pressure regulating system and the data acquisition system is achieved, and an ideal throttling characteristic curve in the test state can be obtained by one-time blowing.
Description
Technical Field
The invention relates to an automatic control wind tunnel test method.
Background
The air intake duct is a key component of an air-breathing aircraft, and the performance of the air intake duct directly affects the overall performance of the engine and thus the aircraft. The air inlet channel wind tunnel test is a main means for evaluating the performance of an air inlet channel and obtaining characteristic parameters of the air inlet channel, wherein a flow coefficient and a total pressure recovery coefficient are two most main characteristic parameters of the air inlet channel, and the main purpose of the wind tunnel test is to obtain a complete rule that the flow coefficient and the total pressure recovery coefficient change along with the outlet back pressure of the air inlet channel so as to evaluate the working performance of the air inlet channel under different working conditions.
At present, the simulation of the back pressure of the test outlet of the air inlet channel adopts the form of a throttling cone, generally adopted methods are that before the test air blowing, a tester manually gives a plurality of throttling cone positions according to experience through theoretical analysis, and data collection is carried out according to the given positions in the test process. Therefore, an ideal throttling characteristic curve is difficult to obtain in a primary blowing test, the optimal performance parameters of the air inlet in the state cannot be captured, and even secondary supplementary blowing is needed. The traditional method not only improves the accuracy of the wind tunnel test, but also improves the test cost.
In the face of the urgent need of the current air inlet channel technology development, the research capability of the current air inlet channel wind tunnel test technology is obviously insufficient, fine technical support is difficult to provide for model development due to the uncertainty of manual point taking in the test process, and the automatic coupling adjustment technology of the back pressure adjustment system and the data acquisition system is obviously necessary.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the invention overcomes the defects of the prior art, and provides an automatic control wind tunnel test method for the throttling characteristic of the air inlet passage of the ramjet engine.
The technical scheme adopted by the invention is as follows: an automatic control wind tunnel test method for throttling characteristics of an air inlet passage of a ramjet engine comprises the following steps:
(1) arranging a plurality of static pressure monitoring points near a test model throat of the ramjet inlet along the flow direction, wherein the static pressure monitoring points are connected with a static pressure monitoring system and used for monitoring the flow state of a flow channel in the inlet;
(2) setting a pressure threshold alpha of a static pressure monitoring point, and when the pressure of the static pressure monitoring point exceeds the pressure threshold alpha of the static pressure monitoring point, acquiring pressure data of a full-measuring point by a pressure acquisition system; setting the regulating speed v of the back pressure regulating system in the test process;
(3) after the wind tunnel flow field is established to be stable, the static pressure monitoring system collects and records pressure data of all static pressure monitoring points at one time, and the pressure data is used as a reference value for judging the change of a subsequent pressure value;
(4) controlling a back pressure adjusting system to act according to a set adjusting rate v to increase the back pressure of an outlet of the air inlet, collecting and judging the pressure value of the downstream-most static pressure monitoring point in real time, stopping back pressure adjustment when the variation of the current pressure value of the downstream-most static pressure monitoring point relative to the reference value in the step (3) exceeds a pressure threshold value alpha of the static pressure monitoring point, and collecting a full-measuring-point pressure value once to obtain the performance parameters of the air inlet in the state, wherein the performance parameters of the air inlet comprise a flow coefficient and a total pressure recovery coefficient;
(5) and (5) repeating the step (4), and traversing all the static pressure monitoring points from the downstream to the upstream of the air inlet channel in sequence.
And (2) in the step (1), 6-10 static pressure monitoring points are arranged near the test model throat of the ramjet inlet along the flow direction.
The static pressure monitoring system collects static pressure values of the static pressure monitoring points in real time, judges whether the monitored pressure of the static pressure monitoring points exceeds a pressure threshold value alpha of the static pressure monitoring points or not, and the processing frequency is greater than 10 Hz.
And (3) the pressure acquisition system in the step (2) is used for acquiring the pressure values of all the measuring points of the air inlet channel test model and judging whether the data acquisition of all the static pressure monitoring points is finished.
And (3) setting different pressure thresholds of the static pressure monitoring points for different static pressure monitoring points in the step (2).
Compared with the prior art, the invention has the advantages that:
(1) the invention realizes the automatic adjustment of the data acquisition system by utilizing the pneumatic characteristic of the air inlet channel, avoids uncertain factors caused by manual intervention and improves the accuracy of test testing.
(2) The flow state of the air inlet channel corresponding to the triggering of the set static pressure monitoring point has certain physical significance, namely the acquired pressure data are all effective values, so that the resource waste caused by invalid acquisition is avoided, and the test cost is reduced.
(3) The method provided by the invention does not need to analyze the throttling characteristic of the current state of the air inlet channel in advance, and only needs to set the change threshold of the static pressure monitoring point and the adjustment rate of the back pressure adjusting system, so that the manual intervention time before the test is shortened, and the test efficiency is improved.
(4) The method has incomparable advantages for the throat-adjustable air inlet test, can obtain the optimal interception characteristic of the air inlet under each throat height through one test, and greatly improves the test efficiency compared with the conventional air inlet test technology.
Drawings
FIG. 1 is a flow chart of an automated control test for an air inlet tunnel test according to the present invention;
FIG. 2 is a schematic diagram of an inlet testing system according to the present invention;
FIG. 3 is an exemplary ramjet inlet on-path static pressure profile;
FIG. 4 is a graph of the air intake throttling characteristics obtained by the present invention;
Detailed Description
The invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
As shown in fig. 1, an automatic control wind tunnel test method for a throttling characteristic of an air inlet passage of a ramjet engine comprises the following steps:
(1) arranging 6-10 static pressure monitoring points near a test model throat of the ramjet inlet along the flow direction, wherein the static pressure monitoring points are connected with a static pressure monitoring system and used for monitoring the flow state of a flow channel in the inlet; the static pressure monitoring system collects the static pressure value of the static pressure monitoring point in real time, judges whether the monitored pressure of the static pressure monitoring point exceeds a pressure threshold value alpha of the static pressure monitoring point or not, and the processing frequency is more than 10 Hz.
(2) Setting a pressure threshold alpha of a static pressure monitoring point, and when the pressure of the static pressure monitoring point exceeds the pressure threshold alpha of the static pressure monitoring point, acquiring pressure data of a full-measuring point by a pressure acquisition system; setting the regulating speed v of the back pressure regulating system in the test process; the pressure acquisition system is used for acquiring pressure values of all measuring points of the air inlet channel test model and judging whether the acquisition of data of all static pressure monitoring points is finished or not. And (3) setting different pressure thresholds of the static pressure monitoring points for different static pressure monitoring points in the step (2).
(3) After the wind tunnel flow field is established to be stable, the static pressure monitoring system collects and records pressure data of all static pressure monitoring points at one time, and the pressure data is used as a reference value for judging the change of a subsequent pressure value;
(4) controlling a back pressure adjusting system to act according to a set adjusting rate v to increase the back pressure of an outlet of the air inlet, collecting and judging the pressure value of the downstream-most static pressure monitoring point in real time, stopping back pressure adjustment when the variation of the current pressure value of the downstream-most static pressure monitoring point relative to the reference value in the step (3) exceeds a pressure threshold value alpha of the static pressure monitoring point, and collecting a full-measuring-point pressure value once to obtain the performance parameters of the air inlet in the state, wherein the performance parameters of the air inlet comprise a flow coefficient and a total pressure recovery coefficient;
(5) and (5) repeating the step (4), and traversing all the static pressure monitoring points from the downstream to the upstream of the air inlet channel in sequence.
Example (b):
an automatic control wind tunnel test method for throttling characteristics of an air inlet passage of a ramjet engine comprises the following steps:
(1) as shown in fig. 2, firstly, in the design stage of the ramjet inlet test model, the number of on-way static pressure monitoring points and the design positions of the side walls of the inlet where the static pressure monitoring points are respectively located are determined according to the throttle characteristics of the tested inlet, and in addition, the design and processing are performed according to the conventional inlet model. The monitoring point measuring sensor has the characteristics of high precision and quick response, and the acquisition system has the functions of real-time storage and transmission. Other pressure measuring and collecting systems may be selected from conventional intake port pressure measuring systems. The back pressure regulating system can be selected from a conventional air inlet passage throttling cone regulating system. The static pressure monitoring points are connected with a static pressure monitoring system through a tee joint for monitoring pressure changes of all measuring points in real time, and one path of the static pressure monitoring points is connected with a conventional pressure measuring module to be used as a common measuring point for pressure measurement.
(2) Before the experiment, the automatic control strategy parameters are set according to the experiment requirements, and the method mainly comprises the following steps: the number and the sequence of the static pressure monitoring points, the real-time acquisition frequency of the static pressure monitoring points, the pressure change condition of the static pressure monitoring points corresponding to the data acquisition of the pressure acquisition system and the regulation rate of the back pressure regulation system.
(3) And (3) starting a wind tunnel test after the parameters set in the step (2) are completed, and collecting and storing pressure value data of all static pressure monitoring points once by the static pressure monitoring system as a reference value for subsequent pressure value change judgment after a wind tunnel flow field is stably established and the attitude angle mechanism drives the air inlet model to reach a target state.
(4) As shown in fig. 3, the backpressure regulation action causes the backpressure at the outlet of the air inlet channel to be slowly increased from the minimum value, according to the characteristic that the backpressure at the outlet of the ultrasonic flow is not forwarded, the tail shock wave sweeps all static pressure monitoring points from back to front in sequence along with the increase of the backpressure at the outlet of the air inlet channel, only the pressure value of the swept static pressure monitoring points is suddenly changed in the process, the pressure value which is not swept is unchanged, in the process, the pressure value of the static pressure monitoring point at the most downstream is collected and judged in real time, if the pressure value relative to the reference value variation exceeds the set threshold value, the static pressure monitoring system firstly sends an instruction to the backpressure regulation system to stop regulation, then sends an instruction to the pressure collection system to carry out pressure collection at all measuring points, at the moment, the air inlet channel is in a flowing.
(5) After the primary collection is finished, the static pressure monitoring system sends an instruction to the back pressure regulating system to continuously increase the back pressure, the step (4) is repeated, all static pressure monitoring points are traversed from the downstream to the upstream in sequence, after all collection points are judged by the pressure collection system, the primary test is finished, the wind tunnel attitude angle mechanism returns to zero, and the vehicle is shut down.
The air inlet throttling characteristic curve obtained by the method is shown as an 'ideal curve' in fig. 4, compared with a throttling curve obtained by a conventional air inlet test, the air inlet throttling characteristic curve can more accurately capture the critical state and the surge boundary of the air inlet in the state, and meanwhile, invalid measuring points cannot appear.
Those not described in detail in this specification are well known to those skilled in the art.
Claims (4)
1. An automatic control wind tunnel test method for throttling characteristics of an air inlet passage of a ramjet engine is characterized by comprising the following steps:
(1) arranging 6-10 static pressure monitoring points near a test model throat of the ramjet inlet along the flow direction, wherein the static pressure monitoring points are connected with a static pressure monitoring system and used for monitoring the flow state of a flow channel in the inlet;
(2) setting a pressure threshold alpha of a static pressure monitoring point, and setting a regulating speed v of a back pressure regulating system in the test process;
(3) after the wind tunnel flow field is established to be stable, the static pressure monitoring system collects and records pressure data of all static pressure monitoring points at one time, and the pressure data is used as a reference value for judging the change of a subsequent pressure value;
(4) controlling a back pressure adjusting system to act according to a set adjusting rate v to increase the back pressure of an outlet of the air inlet, collecting and judging the pressure value of the downstream-most static pressure monitoring point in real time, stopping back pressure adjustment when the variation of the current pressure value of the downstream-most static pressure monitoring point relative to the reference value in the step (3) exceeds a pressure threshold value alpha of the static pressure monitoring point, and collecting the pressure value of a full measuring point once by the pressure collecting system to obtain the performance parameters of the air inlet in the state, wherein the performance parameters of the air inlet comprise a flow coefficient and a total pressure recovery coefficient;
(5) and (5) repeating the step (4), and traversing all the static pressure monitoring points from the downstream to the upstream of the air inlet channel in sequence.
2. The automated control wind tunnel test method for the throttling characteristic of the inlet duct of the ramjet engine as claimed in claim 1, wherein: the static pressure monitoring system collects static pressure values of the static pressure monitoring points in real time, judges whether the variation of the monitored pressure values of the static pressure monitoring points relative to a reference value exceeds a pressure threshold value alpha of the static pressure monitoring points, and the processing frequency is greater than 10 Hz.
3. The automatic control wind tunnel test method for the throttling characteristic of the air inlet passage of the ramjet engine as claimed in claim 1 or 2, wherein: the pressure acquisition system is used for acquiring pressure values of all measuring points of the air inlet channel test model and judging whether the acquisition of data of all static pressure monitoring points is finished or not.
4. The automated control wind tunnel test method for the throttling characteristic of the inlet duct of the ramjet engine as claimed in claim 1, wherein: and (3) setting different pressure thresholds of the static pressure monitoring points for different static pressure monitoring points in the step (2).
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| CN112432760B (en) * | 2020-11-10 | 2023-05-12 | 北京动力机械研究所 | Axisymmetric double-channel inlet channel outlet counter pressure adjustment and flow field measurement method |
| 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 |
| CN114861364A (en) * | 2022-05-30 | 2022-08-05 | 中国空气动力研究与发展中心空天技术研究所 | Intelligent sensing and suction regulation and control method for air inlet flow field of air-breathing engine |
| CN115371933B (en) * | 2022-10-24 | 2023-03-24 | 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 |
| 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 |
| 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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