CN111855132A - Flutter test safety protection system and method - Google Patents
Flutter test safety protection system and methodDownload PDFInfo
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- CN111855132A CN111855132ACN202010884824.5ACN202010884824ACN111855132ACN 111855132 ACN111855132 ACN 111855132ACN 202010884824 ACN202010884824 ACN 202010884824ACN 111855132 ACN111855132 ACN 111855132A
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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
- G01M9/02—Wind tunnels
- 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
- 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
- G01M9/02—Wind tunnels
- G01M9/04—Details
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Abstract
Description
Technical Field
The invention relates to a flutter test safety protection system and method, in particular to a test model and protection of internal parts of a wind tunnel, and belongs to the technical field of aero-pneumatic wind tunnel tests.
Background
The method is mainly used for safety protection of test models and wind tunnels. In the wind tunnel flutter test, as the violent critical state needs to be observed, the model is likely to be damaged, and a protective net is usually arranged at the downstream of a test section to prevent the falling model from damaging the wind tunnel. This patent utilizes active control's safety protection technique, judges the model state in real time through the acceleration sensor reading, in case the model vibration the trend of dispersing appears, then starts the safety protection system, protection test model and wind-tunnel, and is more convenient, high-efficient, reliable.
The invention aims to design a safety protection method for a flutter test for a wind tunnel, in the flutter test of the wind tunnel, along with the gradual increase of the Mach number, the amplitude and the vibration frequency of a test model are also gradually changed, under certain test conditions, model fracture (integral fracture from a model support position) or model damage (fracture of a certain part of the model) caused by overlarge vibration of the test model can occur, and then the whole or fragments of the dropped model are brought downstream by high-speed fluid in the wind tunnel to damage certain parts in the wind tunnel.
Disclosure of Invention
In order to solve the problems of model fracture or damage of the model to certain parts in the wind tunnel caused by overlarge vibration of a test model, the invention provides a flutter test safety protection system and a method, and the specific technical scheme is as follows:
the first scheme is as follows: the system comprises a test model, an acceleration sensor, a flow regulating valve, a safety protection device, a data acquisition and analysis module, an electromagnetic valve and a wind tunnel control module;
the wind tunnel control module, the data acquisition and analysis module and the electromagnetic valve are positioned outside the wind tunnel;
the flow regulating valve, the safety protection device, the acceleration sensor and the test model are all arranged in the wind tunnel;
the test model is provided with at least one acceleration sensor, the test model is fixed on the safety protection device, and the electromagnetic valve is electrically connected with the safety protection device;
the flow regulating valve is arranged at the air inlet of the wind tunnel and is arranged in parallel with the experimental model and the safety protection device;
the data acquisition and analysis module is also connected with the electromagnetic valve through wireless control, the data acquisition and analysis module is also remotely controlled with the acceleration sensor to establish wireless control, and the data acquisition and analysis module is connected to the wind tunnel control system through Ethernet;
the wind tunnel control module is also in wireless communication connection with the flow regulating valve.
Furthermore, the safety protection device is used for fixing the test model, and the test model is arranged in the safety protection device to jointly form a test section for wind tunnel control.
The second scheme is that the flutter test safety protection method is realized based on the system, and the specific method comprises the following steps:
the method comprises the following steps: the wind tunnel control module monitors the stable condition of the flow field through the data acquisition and analysis module when starting the test, and controls the valve to close the flow control if the flow field is unstable, otherwise, the test is continued;
step two: the wind tunnel control module sends an instruction, a test model to be tested is loosened through the data acquisition and analysis module, the data acquisition and analysis module acquires a plurality of signals, and whether the number of times required by the test is exceeded or not is judged through the acquired signals;
step three: if the times of the rated numerical value meet the requirements, the tester judges that the test is finished, otherwise, the pneumatic control module issues a control command to clamp the test model and close the valve, so that the flutter test safety protection is realized;
furthermore, the data acquisition and analysis system directly controls the clamping and the loosening of the safety protection device through a quick electromagnetic valve switch.
Further, the specific protection method in the step two comprises the following steps:
step two, firstly: before the wind tunnel test, the safety protection device is in a clamping state, and a tester sets a data acquisition and analysis module according to different test models and test states to acquire the number of channels, the sampling rate f, the sampling number n and the threshold k of each channel;
step two: after the wind tunnel test is started, on the premise that the wind tunnel control module judges that the flow field is stable, the safety protection device loosens the test model, and the data acquisition and analysis system starts to work according to an instruction sent by the wind tunnel control module, wherein the data acquisition, analysis and storage are included;
further, the specific protection method in step three comprises the following steps:
step three, firstly: the data acquisition and analysis module calculates the peak value | V in the data sampling number n acquired by the appointed channel each timei| is defined as Vi-1<Vi>Vi+1The number of the n-1 is larger than the number m of the set threshold values k, once m is larger than a set value of a tester, calculation is carried out immediately, and the wind tunnel control module sends an instruction to control the safety protection device to clamp the model;
step three: and sending a test stopping signal to the wind tunnel control module while sending a clamping signal to the data acquisition and analysis module so as to quickly reduce the flow speed in the wind tunnel to 0, and finishing the test.
Further, in order to avoid communication failure in the test process, a tester manually operates the clamping or loosening valve through the safety test device to realize emergency protection.
Furthermore, the data collected in real time and the data after calculation and analysis are displayed on the data collecting and analyzing module, and the recorded data are subjected to time calibration according to the state sent by the wind tunnel control module.
The invention has the beneficial effects that:
according to the invention, by monitoring the numerical value of the acceleration sensor on the test model and carrying out calculation and analysis, the safety protection is implemented on the model through the safety protection device in the flutter test process, so that the damage of the model or the internal components of the wind tunnel caused by the overlarge vibration of the test model is prevented.
The flight control device meets the requirements of wind tunnel virtual flight test tasks, can realize synchronous control of 1-10 steering engines, realize high-precision measurement of model attitude angles, design and download of flight control programs, acquisition of test parameter data, measurement of model attitude and attitude angular velocity, and wireless communication between equipment and an external computer, saves field manual operation of operators, reduces the control difficulty of an aircraft in a pneumatic simulation flight test, improves the control efficiency, solves the problems of large size of a development board, occupation of model space, effectively reduces the model weight and greatly reduces the development difficulty.
Drawings
FIG. 1 is a flow chart of a flutter test safety protection method;
FIG. 2 is a schematic diagram of the overall composition of the flutter test safety protection system;
FIG. 3 is a schematic view of a portion of a test piece of the flutter test safety shield system;
in the figure, atest model 1, anacceleration sensor 2, asafety protection device 3, a windtunnel control module 4, a data acquisition andanalysis module 5, a quick electromagnetic valve 6, aflow regulating valve 7 and atest section 8 are adopted.
Detailed Description
The first embodiment is as follows: a flutter test safety protection system comprises a test model, an acceleration sensor, a safety protection device, a wind tunnel control module, a data acquisition and analysis module, a quick electromagnetic valve, a flow regulating valve and a test section; the wind tunnel control module, the data acquisition and analysis module and the electromagnetic valve are positioned outside the wind tunnel; the flow regulating valve, the safety protection device, the acceleration sensor and the test model are all positioned in the wind tunnel;
the wind tunnel control module is in control connection with the data acquisition and analysis module, and one end of the wind tunnel control module is in wireless communication connection with the flow safety valve;
the flow safety valve is arranged at the air inlet of the wind tunnel and is arranged in the wind tunnel in parallel with the experimental model and the safety protection device;
the test model is provided with at least one acceleration sensor, the test model is fixed on the safety protection device, and the electromagnetic valve is electrically connected with the safety protection device;
the data analysis module remotely establishes wireless control with the acceleration sensor, and the other end of the data analysis module is connected with the electromagnetic valve through the wireless control.
The second embodiment is as follows: according to the system composition of the first embodiment, the implementation process of the flutter test safety protection specific method described in conjunction with fig. 1-3 is as follows:
by monitoring the numerical value of the acceleration sensor on the test model and carrying out calculation and analysis, the safety protection device is used for carrying out safety protection on the test model in the flutter test process, and the damage of the model or the internal components of the wind tunnel caused by the overlarge vibration of the test model is prevented.
Taking a certain test as an example, before the wind tunnel flutter test is started:
(a) mounting an acceleration sensor on the test model;
(b) the data acquisition and analysis module is connected to the wind tunnel control module through Ethernet and is connected to the safety protection device [3] through a quick electromagnetic valve;
(c) placing the safety protection device in a state of clamping the test model;
(d) according to the characteristics of the test model and the acceleration sensor and the early-stage ground test result, the data acquisition and analysis module is provided with acquisition channel parameters: the sampling rate f is 1000 Hz; the sampling number n is 100; the threshold k is 20; the maximum peak number m >3 is set.
After the preparation is finished, a wind tunnel flutter test is started, the wind tunnel control module controls the flow regulating valve, when the flow field in the flow channel is stable, the wind tunnel control module communicates with the data acquisition and analysis module through the Ethernet, then the data acquisition and analysis module controls the quick electromagnetic valve, and the safety protection device is loosened.
And the data acquisition and analysis module starts to acquire signals of the acceleration sensor and simultaneously stores the data.
According to the set sampling rate f and the sampling number n, the following results are obtained:
single point data sampling time:t 1/f 1ms
The time of a single acquisition cycle is: n × t is 100ms
Namely, the data acquisition and analysis module analyzes and processes 100 data obtained from the acceleration sensor in every 100ms, and the calculation method is repeated in a circulating way as follows:
taking i as 2,3 … … 99, and sequentially obtaining adjacent 3 points (V)i-1，Vi，Vi+1) Calculating viWhether or not it is a peak, i.e. Vi-1＜Vi＞Vi+1；
If ViIf it is a peak value, and if the threshold k is 20, it is determined whether V is presentiIf the condition is satisfied, the maximum number m of peaks is accumulated to be 1, namely m +1 is equal to m, otherwise, m is maintained unchanged.
Successive pairs of V2，V3，V4……Vn-1And judging, wherein once m is more than 3 obtained by accumulation at the ith point, the subsequent i +1, i +2 … … n-1 points are not calculated, and otherwise, the calculation is continued.
The third concrete implementation mode: according to the second specific implementation, the flutter test safety protection system further includes a system judgment for executing protection, and the process is as follows:
after the data calculation of one period is completed, the following process is carried out:
(a) when m is less than or equal to 3 and the wind tunnel control module does not send a test stopping signal to the data acquisition and analysis module, resetting m, and continuously acquiring 100 signals of the next period for calculation;
(b) when m is less than or equal to 3, the wind tunnel control module sends a test stopping signal to the data acquisition and analysis module, then the data acquisition and analysis module does not continue to acquire the test stopping signal, the data acquisition and analysis module controls the safety protection device to perform test model clamping operation through the quick electromagnetic valve, and meanwhile, the wind tunnel control module closes the flow regulating valve to stop the test.
(c) When m is larger than 3, the data acquisition and analysis module controls the safety protection device to perform test model clamping operation through the quick electromagnetic valve, and meanwhile, the data acquisition and analysis module sends the data acquisition and analysis module to the wind tunnel control module to close the flow regulating valve and stop the test.
According to the explanation of the above embodiment, the present invention is characterized in that:
(1) aiming at the problems that the test model is damaged due to overlarge vibration of the test model and the internal components of the wind tunnel are damaged, which may occur in a wind tunnel flutter test, the safety protection device is used for clamping or loosening the test model in the test process.
(2) In the flutter test process of the wind tunnel, the data acquisition and analysis module acquires the acceleration sensor data on the test model, synchronous real-time analysis and calculation are carried out according to the data (sampling number) in single-period sampling, once the number of peak values exceeds the threshold value, the residual data in the period sampling does not need to be calculated, and the safety protection device is immediately sent out an instruction to carry out clamping operation.
(3) And stopping the wind tunnel test while clamping the test model by the safety protection device.
The above embodiments are merely illustrative of the present patent and do not limit the scope of the patent, and those skilled in the art can make modifications to the parts thereof without departing from the spirit and scope of the patent.
Claims (8)
1. The utility model provides a experimental safety protection system of flutter which characterized in that: the device comprises a test model, an acceleration sensor, a flow regulating valve, a safety protection device, a data acquisition and analysis module, an electromagnetic valve and a wind tunnel control module;
the wind tunnel control module, the data acquisition and analysis module and the electromagnetic valve are positioned outside the wind tunnel;
the flow regulating valve, the safety protection device, the acceleration sensor and the test model are all arranged in the wind tunnel;
the test model is provided with at least one acceleration sensor, the test model is fixed on the safety protection device, and the electromagnetic valve is electrically connected with the safety protection device;
the flow regulating valve is arranged at the air inlet of the wind tunnel and is arranged in parallel with the experimental model and the safety protection device;
the data acquisition and analysis module is also connected with the electromagnetic valve through wireless control, the data acquisition and analysis module is also remotely controlled with the acceleration sensor to establish wireless control, and the data acquisition and analysis module is connected to the wind tunnel control system through Ethernet;
the wind tunnel control module is also in wireless communication connection with the flow regulating valve.
2. The flutter test safety protection system according to claim 1, wherein: the safety protection device is used for fixing the test model, and the test model is arranged in the safety protection device and jointly forms a test section for wind tunnel control.
3. A flutter test safety protection method realized on the basis of the system according to any one of claims 1-2, characterized in that: the method comprises the following specific steps:
the method comprises the following steps: the wind tunnel control module monitors the stable condition of the flow field through the data acquisition and analysis module when starting the test, and controls the valve to close the flow control if the flow field is unstable, otherwise, the test is continued;
step two: the wind tunnel control module sends an instruction, a test model to be tested is loosened through the data acquisition and analysis module, the data acquisition and analysis module acquires a plurality of signals, and whether the number of times required by the test is exceeded or not is judged through the acquired signals;
step three: if the times of the rated numerical value meet the requirements, the tester judges that the test is finished, otherwise, the pneumatic control module issues a control command to clamp the test model and close the valve, and the flutter test safety protection is realized.
4. The flutter test safety protection method according to claim 3, wherein: the data acquisition and analysis system directly controls the clamping and the loosening of the safety protection device through a quick electromagnetic valve switch.
5. The flutter test safety protection method according to claim 3, wherein: the specific protection method in the step two comprises the following steps:
step two, firstly: before the wind tunnel test, the safety protection device is in a clamping state, and a tester sets a data acquisition and analysis module according to different test models and test states to acquire the number of channels, the sampling rate f, the sampling number n and the threshold k of each channel;
step two: after the wind tunnel test is started, on the premise that the wind tunnel control module judges that the flow field is stable, the safety protection device loosens the test model, and the data acquisition and analysis system starts to work according to an instruction sent by the wind tunnel control module, including data acquisition, analysis and storage.
6. The flutter test safety protection method according to claim 3, wherein: the concrete protection method in the third step comprises the following steps:
step three, firstly: the data acquisition and analysis module calculates the peak value | V in the data sampling number n acquired by the appointed channel each timei| is defined as Vi-1<Vi>Vi+1The number of the n-1 is larger than the number m of the set threshold values k, once m is larger than a set value of a tester, calculation is carried out immediately, and the wind tunnel control module sends an instruction to control the safety protection device to clamp the model;
step three: and sending a test stopping signal to the wind tunnel control module while sending a clamping signal to the data acquisition and analysis module so as to quickly reduce the flow speed in the wind tunnel to 0, and finishing the test.
7. The flutter test safety protection method according to claim 3, wherein: in order to avoid communication failure in the test process, a tester manually operates the safety test device to clamp or loosen the valve to realize emergency protection.
8. The flutter test safety protection method according to claim 4, wherein: the data collected in real time and the data after calculation and analysis are displayed on the data collecting and analyzing module, and the recorded data are subjected to time calibration according to the state sent by the wind tunnel control module.
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113203538A (en)* | 2021-05-25 | 2021-08-03 | 中国航空工业集团公司哈尔滨空气动力研究所 | Device for inhibiting vibration of mirror image supporting rod |
| CN113432820A (en)* | 2021-06-01 | 2021-09-24 | 中国航空工业集团公司沈阳飞机设计研究所 | Flutter wind tunnel test system and method based on automation |
| CN113432821A (en)* | 2021-06-01 | 2021-09-24 | 中国航空工业集团公司沈阳飞机设计研究所 | Emergency method for flutter suppression in low-speed flutter wind tunnel test |
| CN115077852A (en)* | 2022-08-16 | 2022-09-20 | 中国航空工业集团公司沈阳空气动力研究所 | Dynamic measurement system and measurement method for continuous transonic wind tunnel |
| CN115791070A (en)* | 2023-02-08 | 2023-03-14 | 中国航空工业集团公司沈阳空气动力研究所 | Continuous wind tunnel flutter test safety device |
| CN117451306A (en)* | 2023-11-03 | 2024-01-26 | 中国空气动力研究与发展中心高速空气动力研究所 | Model protection device and test method for flutter wind tunnel test of aircraft skin panel |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106500950A (en)* | 2016-12-02 | 2017-03-15 | 中国航空工业集团公司哈尔滨空气动力研究所 | A kind of efficient large scale injection piping installation of air intake test |
| US20180067015A1 (en)* | 2016-08-04 | 2018-03-08 | Ahmad D. Vakili | Technology to Control a Model and Balance Support System's Dynamics and Isolate the Balance as Needed to Increase Test Facilities Productivity |
| CN108195543A (en)* | 2017-11-29 | 2018-06-22 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft wind tunnel model flutter blowing test system |
| CN109870289A (en)* | 2019-04-11 | 2019-06-11 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of T-type horizontal tail flutter model protective device and its application |
| CN109885854A (en)* | 2018-11-23 | 2019-06-14 | 南京航空航天大学 | Flutter boundary real-time prediction system and prediction method based on ARMA model |
| CN110686856A (en)* | 2019-09-30 | 2020-01-14 | 中国空气动力研究与发展中心低速空气动力研究所 | Vibration monitoring, early warning and safety protection system for wind tunnel test bed of helicopter 2 m-diameter rotor |
- 2020
- 2020-08-28CNCN202010884824.5Apatent/CN111855132A/enactivePending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20180067015A1 (en)* | 2016-08-04 | 2018-03-08 | Ahmad D. Vakili | Technology to Control a Model and Balance Support System's Dynamics and Isolate the Balance as Needed to Increase Test Facilities Productivity |
| CN106500950A (en)* | 2016-12-02 | 2017-03-15 | 中国航空工业集团公司哈尔滨空气动力研究所 | A kind of efficient large scale injection piping installation of air intake test |
| CN108195543A (en)* | 2017-11-29 | 2018-06-22 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft wind tunnel model flutter blowing test system |
| CN109885854A (en)* | 2018-11-23 | 2019-06-14 | 南京航空航天大学 | Flutter boundary real-time prediction system and prediction method based on ARMA model |
| CN109870289A (en)* | 2019-04-11 | 2019-06-11 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of T-type horizontal tail flutter model protective device and its application |
| CN110686856A (en)* | 2019-09-30 | 2020-01-14 | 中国空气动力研究与发展中心低速空气动力研究所 | Vibration monitoring, early warning and safety protection system for wind tunnel test bed of helicopter 2 m-diameter rotor |
Non-Patent Citations (1)
| Title |
|---|
| 徐朝阳: "大展弦比机翼颤振及状态监测研究", 《中国优秀博硕士学位论文全文数据库（硕士） 工程科技II辑》* |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113203538A (en)* | 2021-05-25 | 2021-08-03 | 中国航空工业集团公司哈尔滨空气动力研究所 | Device for inhibiting vibration of mirror image supporting rod |
| CN113432820A (en)* | 2021-06-01 | 2021-09-24 | 中国航空工业集团公司沈阳飞机设计研究所 | Flutter wind tunnel test system and method based on automation |
| CN113432821A (en)* | 2021-06-01 | 2021-09-24 | 中国航空工业集团公司沈阳飞机设计研究所 | Emergency method for flutter suppression in low-speed flutter wind tunnel test |
| CN113432820B (en)* | 2021-06-01 | 2022-05-06 | 中国航空工业集团公司沈阳飞机设计研究所 | Flutter wind tunnel test system and method based on automation |
| CN115077852A (en)* | 2022-08-16 | 2022-09-20 | 中国航空工业集团公司沈阳空气动力研究所 | Dynamic measurement system and measurement method for continuous transonic wind tunnel |
| CN115791070A (en)* | 2023-02-08 | 2023-03-14 | 中国航空工业集团公司沈阳空气动力研究所 | Continuous wind tunnel flutter test safety device |
| CN115791070B (en)* | 2023-02-08 | 2023-04-11 | 中国航空工业集团公司沈阳空气动力研究所 | Continuous type wind tunnel flutter test safety device |
| CN117451306A (en)* | 2023-11-03 | 2024-01-26 | 中国空气动力研究与发展中心高速空气动力研究所 | Model protection device and test method for flutter wind tunnel test of aircraft skin panel |
| CN117451306B (en)* | 2023-11-03 | 2024-09-06 | 中国空气动力研究与发展中心高速空气动力研究所 | Model protection device and test method for flutter wind tunnel test of aircraft skin panel |
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