CN105571811A - Method of measuring aircraft actual attack angle value in wind tunnel experiment - Google Patents
Method of measuring aircraft actual attack angle value in wind tunnel experiment Download PDFInfo
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- CN105571811A CN105571811A CN201510975741.6A CN201510975741A CN105571811A CN 105571811 A CN105571811 A CN 105571811A CN 201510975741 A CN201510975741 A CN 201510975741A CN 105571811 A CN105571811 A CN 105571811A
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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
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B7/00—Measuring arrangements characterised by the use of electric or magnetic techniques
- G01B7/30—Measuring arrangements characterised by the use of electric or magnetic techniques for measuring angles or tapers; for testing the alignment of axes
Abstract
The invention discloses a method of measuring an aircraft actual attack angle value in a wind tunnel experiment, comprising: collecting a zero point voltage value and other attack angle voltage value corresponding to the zero DEG attack angle value and the non-zero DEG attack angle value of a platform installed on an attack angle mechanism; subtracting the zero point voltage value from the attack angle voltage value corresponding to each non-zero DEG attack angle value to obtain a plurality of adjusted attack angle voltage values; utilizing the adjusted attack angle voltage values and attack angle values to establish a base curve; adjusting the attack angle of an aircraft to be measured to be zero DEG, and obtaining the curve between the actual attack angle value of the aircraft to be measured and an attack angle voltage value according to the preset angle of the aircraft to be measured and the base curve; and according to the measured attack angle voltage value and the curve between the actual attack angle value and the attack angle voltage value, obtaining the actual attack angle value of the aircraft to be measured. The method can substantially reduce operation personnel workload, improve work efficiency, reduce an error rate, enhance the program applicability to different models, and obtain a model preset angle through program calculation.
Description
Technical field
The present invention relates to a kind of method measuring aerocraft real angle of attack value in wind tunnel experiment.
Background technology
In wind tunnel test, be test the guarantee carried out smoothly to the accurate control of model attitude angle, and the angle of attack angle of most important to be also the most basic controlled quentity controlled variable be exactly model in model attitude angle.The angle of attack is also the angle of attack of model, is the angle that model is formed in face of incoming flow and incoming flow.The angle of attack of model controls the very high precision of demand fulfillment, in general, reach ± 3 ° within.Model attitude angle controls primarily of attack angle mechanism, and attack angle mechanism is driven by driving arrangement (as motor), the angle of attack variation of band movable model in flow field.In the process that the angle of attack controls, have several factors can affect the control accuracy of Model angle of attack, wherein the prepackage angle of attack angle mechanism is the key factor affecting control accuracy.Model angle of attack value is not identical with the angle of attack angle mechanism, prepackage angle is the difference of Model angle of attack and attack angle mechanism angle value, different models may be installed with different elbow connections, different elbow connections will cause the huge deviation of Model angle of attack and the attack angle mechanism angle of attack, the mechanical clearance of attack angle mechanism and the difference of model deadweight all can cause presetting angle to change simultaneously, the deviation of this initial zero degree can be added in whole process of the test and go, and therefore must be eliminated before the test is conducted.
The method that tradition eliminates wind tunnel model prepackage angle is relatively complicated, general step is, after model and pole are installed on attack angle mechanism, the angle that the pole that elbow connection or band pre-install angle produces is input in program by staff, by program or manually Model angle of attack is transferred to zero degree, then use the angle of attack magnitude of voltage that programmed acquisition is current, program can to the zero-point voltage Taxonomic discussion of the angle of attack.Owing to not being generally linear relationship between the angle of attack and sensor output voltage, therefore in different zero-point voltage scopes, matching angle of attack voltage equation being distinguished, then go out the angle of attack value under different situations according to different formulae discovery.That is simulate different angle of attack voltage equation according to different zero-point voltage values and then carry out collection and control.The method drawback: if 1 increases Novel bent joint, prepackage angle will be different, will remeasure an angle of attack voltage data this time, and simulate a new angle of attack voltage curve; 2, the method cannot effectively be eliminated due to the different small angle of attack error caused of model deadweight, can only carry out the rude classification in angle for the pole of different elbow connections and band angle; 3, bothering during the method operating cost, needing operating personnel's repeated measurement Model angle of attack actual value because wanting the new angle of attack voltage equation of frequent matching; 4, want to obtain real model prepackage angle, first attack angle mechanism can only be gone to zero degree, measure with instruments such as quadrants, the precision of measurement is determined by survey crew experience, can not effectively be ensured.
Summary of the invention
An object of the present invention is to solve at least the problems referred to above, and the advantage will illustrated at least is below provided.
A further object of the invention is to provide an object and is to provide kind of the method measuring aerocraft real angle of attack value in wind tunnel experiment, it improves the method for Measurement & Control precision, adopt the method effectively can overcome the deficiency of classic method, can effectively improve angle of attack control accuracy, reduce worker workload.
In order to realize, according to these objects of the present invention and other advantage, providing a kind of method measuring aerocraft real angle of attack value in wind tunnel experiment, comprising:
Step one, a platform is installed on attack angle mechanism, zero-point voltage value corresponding when the angle of attack value of acquisition platform is 0 °, and when angle of attack value is not 0 °, angle of attack magnitude of voltage corresponding during the different angle of attack value of platform;
Step 2, angle of attack magnitude of voltage corresponding to each not 0 deg angle of attack value deduct zero-point voltage value, obtain multiple correction angle of attack magnitude of voltage;
Step 3, the multiple correction angle of attack magnitudes of voltage obtained according to step 2, and the angle of attack value corresponding to each correction angle of attack magnitude of voltage, set up the curve of angle of attack value and correction angle of attack magnitude of voltage, as datum curve;
Step 4, dismounting platform, be installed on attack angle mechanism by aircraft to be measured, the angle of attack value of aircraft to be measured be adjusted to 0 °, measure the angle of angle as the pre-angle setting of aircraft to be measured of now attack angle mechanism;
According to pre-angle setting and the datum curve of aircraft to be measured, matching obtains the actual angle of attack value of aircraft to be measured and the curve of angle of attack magnitude of voltage;
Step 5, measure aircraft to be measured and be arranged on angle of attack magnitude of voltage on attack angle mechanism, the actual angle of attack value of aircraft to be measured obtained according to the angle of attack magnitude of voltage measured and step 4 and the curve of angle of attack magnitude of voltage, obtain the actual angle of attack value of aircraft to be measured.
Preferably, in described measurement wind tunnel experiment aerocraft real angle of attack value method in, in described step one, attack angle mechanism is installed a platform, by the zero-point voltage value that incidence vane acquisition platform is corresponding when angle of attack value is 0 °, when not being 0 ° with angle of attack value, the angle of attack magnitude of voltage that platform is corresponding when different angle of attack value.
Preferably, in described measurement wind tunnel experiment aerocraft real angle of attack value method in, in described step 3, to correct angle of attack magnitude of voltage for Y-axis, with angle of attack value for X-axis, set up the curve of angle of attack value and correction voltage value.
Preferably, in described measurement wind tunnel experiment aerocraft real angle of attack value method in, in described step 3, adopt least square multistage method to set up the curve of angle of attack value and correction voltage value.
Preferably, in described measurement wind tunnel experiment aerocraft real angle of attack value method in, in described step 4, aircraft to be measured is installed to attack angle mechanism, the angle of attack value of aircraft to be measured is adjusted to 0 °, according to pre-angle setting and the datum curve of aircraft to be measured, matching obtains the actual angle of attack value of aircraft to be measured and the curve of angle of attack voltage, is specially:
If the pre-angle setting of aircraft to be measured be on the occasion of, then by datum curve along the preset angle value of translation under Y-axis, the curve after translation is the actual angle of attack value of aircraft to be measured and the curve of angle of attack magnitude of voltage;
If the pre-angle setting of aircraft to be measured is negative value, then by datum curve along the preset angle value of translation in Y-axis, the curve after translation is the actual angle of attack value of aircraft to be measured and the curve of angle of attack magnitude of voltage.
The present invention at least comprises following beneficial effect: the first, simplify measurement and control program algorithm; The second, enhance routine suitability, the method is applicable to various difference prepackage angle case, without the need to the formula that the prepackage angle matching in order to new is new; Three, the workload of operating personnel's repeated measurement angle of attack angle value is greatly reduced; Four, the reduction of manual measurement workload means that people is that the probability of makeing mistakes reduces greatly; Five, the method can effectively be revised because model is conducted oneself with dignity the prepackage angle slight error caused, thus improves the control accuracy of angle, apply theoretically the method angle of attack control accuracy can be controlled ± 1 ' within.
Part is embodied by explanation below by other advantage of the present invention, target and feature, part also will by research and practice of the present invention by those skilled in the art is understood
Accompanying drawing explanation
Fig. 1 is process flow diagram of the present invention.
Fig. 2 is be the method that tradition eliminates angle of attack prepackage angle, and different prepackage will distinguish the different curve of matching;
Fig. 3 be the method for the invention by fundamental curve and pre-angle setting, matching obtains aerocraft real angle of attack value to be measured and magnitude of voltage curve.
Embodiment
Below in conjunction with accompanying drawing, the present invention is described in further detail, can implement according to this with reference to instructions word to make those skilled in the art.
Should be appreciated that used hereinly such as " to have ", other element one or more do not allotted in " comprising " and " comprising " term or the existence of its combination or interpolation.
As shown in Figure 1, the invention provides a kind of method measuring aerocraft real angle of attack value in wind tunnel experiment, comprising:
Step one, a platform is installed on attack angle mechanism, zero-point voltage value corresponding when the angle of attack value of acquisition platform is 0 °, and when angle of attack value is not 0 °, angle of attack magnitude of voltage corresponding during the different angle of attack value of platform;
Step 2, angle of attack magnitude of voltage corresponding to each not 0 deg angle of attack value deduct zero-point voltage value, obtain multiple correction angle of attack magnitude of voltage;
Step 3, the multiple correction angle of attack magnitudes of voltage obtained according to step 2, and the angle of attack value corresponding to each correction angle of attack magnitude of voltage, set up the curve of angle of attack value and correction angle of attack magnitude of voltage, as datum curve;
Step 4, dismounting platform, be installed on attack angle mechanism by aircraft to be measured, the angle of attack value of aircraft to be measured be adjusted to 0 °, measure the angle of angle as the pre-angle setting of aircraft to be measured of now attack angle mechanism;
According to pre-angle setting and the datum curve of aircraft to be measured, matching obtains the actual angle of attack value of aircraft to be measured and the curve of angle of attack magnitude of voltage;
Step 5, measure aircraft to be measured and be arranged on angle of attack magnitude of voltage on attack angle mechanism, the actual angle of attack value of aircraft to be measured obtained according to the angle of attack magnitude of voltage measured and step 4 and the curve of angle of attack magnitude of voltage, obtain the actual angle of attack value of aircraft to be measured.
In one embodiment, in step one, attack angle mechanism is installed a platform, by the zero-point voltage value that incidence vane acquisition platform is corresponding when angle of attack value is 0 °, when not being 0 ° with angle of attack value, the angle of attack magnitude of voltage that platform is corresponding when different angle of attack value.
In one embodiment, in step 3, to correct angle of attack magnitude of voltage for Y-axis, with angle of attack value for X-axis, set up the curve of angle of attack value and correction voltage value.
In one embodiment, in step 3, the multistage method of least square is adopted to set up the curve of angle of attack value and correction voltage value.
In one embodiment, in step 4, aircraft to be measured is installed to attack angle mechanism, the angle of attack value of aircraft to be measured is adjusted to 0 °, according to pre-angle setting and the datum curve of aircraft to be measured, matching obtains the actual angle of attack value of aircraft to be measured and the curve of angle of attack voltage, is specially:
If the pre-angle setting of aircraft to be measured be on the occasion of, then by datum curve along the preset angle value of translation under Y-axis, the curve after translation is the actual angle of attack value of aircraft to be measured and the curve of angle of attack magnitude of voltage;
If the pre-angle setting of aircraft to be measured is negative value, then by datum curve along the preset angle value of translation in Y-axis, the curve after translation is the actual angle of attack value of aircraft to be measured and the curve of angle of attack magnitude of voltage.
In order to make those skilled in the art have a clear understanding of the technical program, now illustrate with instantiation:
1) when the attack angle mechanism of wind-tunnel does not install any model (aircraft to be measured), attack angle mechanism installs a platform, this platform is as the measuring table measuring attack angle mechanism angle.
2) one group of angle of attack magnitude of voltage is measured: the angle value of attack angle mechanism measured by application quadrant or other High-precision angle measuring equipments on platform, record corresponding incidence vane output voltage V simultaneously, form one group of corresponding angle of attack voltage data, in the process of record, the angle of attack voltage during suggestion record zero degree angle of attack, is designated as zero-point voltage (being interposed between within 2 ° between suggestion measurement data points).
3) according to the curve of this group data fitting zero crossing, so-called zero crossing refers to and angle of attack magnitude of voltage is all deducted zero-point voltage value, then with corresponding angle of attack value matching curve (carrying out matching with least square is multistage), this curve is zeroaxial curve (i.e. fundamental curve).
4) be recorded in program by the formula of this curve, what react due to this curve is the relation of angle of attack voltage V and attack angle mechanism angle of attack value, and therefore program can calculate the angle of attack value of current attack angle mechanism by gathering angle of attack voltmeter.
5) be installed on attack angle mechanism by model (aircraft to be measured), the model prepackage angle that the pole of using when no matter installing model and elbow connection produce is how many, by control motor or hand mode, the angle of attack of model is transferred to horizontal zero degree.
6) angle of current attack angle mechanism is calculated with programmed acquisition, now the angle value of attack angle mechanism is exactly the pre-angle setting of this model, this pre-angle setting had both contained the prepackage angle of model, and also contains the angular error that model deadweight produces, this pre-angle setting is recorded in computer by program.
7) program is when reality exports angle again through once calculating, and namely obtains current angle of attack value.
8) after completing above operation, it is disposable work that formula is demarcated, different tests, and angle of attack prepackage angle or pole have elbow connection to change, and now only need repeat the accurate angle of attack value that the 5th and the 6th step operation can obtain new mechanism.
Relation due to angle of attack voltage is not linear relationship, in order to ensure precision, original method is by model in wind-tunnel, after different presetting angles installed by model, just think that the angle of attack moving law of model there occurs change, therefore the angle of attack voltage equation different to the matching of difference pre-angle setting is needed, much more a kind of situation will many matchings curve, as shown in Figure 2, X-axis is magnitude of voltage, Y-axis is angle of attack value, and every bar curve represents one and installs the actual angle of attack value of model and the relation of magnitude of voltage after model.
In the present invention, although be not linear relationship between the angle of attack and output voltage, but for attack angle mechanism, because the physical construction of attack angle mechanism itself is without any change, therefore there is not any change in its rule run, and the angle between the angle of attack value of the angle of attack angle mechanism and model is a constant, this constant is exactly real pre-angle setting, and this pre-angle setting not only contains the differential seat angle of the mechanisms such as elbow connection, also comprise model to conduct oneself with dignity the differential seat angle caused, therefore be same curve coordinate translation in an angular direction in different prepackage situation, as shown in Figure 3, X-axis is magnitude of voltage, Y-axis is angle of attack value, intermediate curve is datum curve, its formula is α=f (v-v
0), α is angle of attack value, and v is the angle of attack magnitude of voltage of angle of attack value not corresponding to 0 °, v
0for zero degree magnitude of voltage, upper and lower two curves are according to presetting angle number, the curve that the actual angle of attack value of the model that upper and lower translation datum curve obtains is corresponding with magnitude of voltage, and wherein, the formula of the curve on the datum curve top be positioned in Fig. 2 is α=f (v-v
0)-α ', wherein α ' is pre-angle setting, and the formula of the curve of the datum curve bottom be positioned in Fig. 2 is α=f (v-v
0)-α ", wherein α " is pre-angle setting.
The present invention is based on the feature of attack angle mechanism to model Angle ambiguity, excavate the rule of Angle ambiguity, be different from the method that tradition collection calculates angle of attack value, although it is not linear relationship that method disclosed by the invention is seen between angle of attack angle and sensor output voltage, for attack angle mechanism, its moving law does not change to start with all the time and deals with problems.Adopt the method, greatly can reduce the workload of operating personnel, reduction error rate of increasing work efficiency, enhance the applicability of program to different model, and the presetting angle of model can be obtained with program computation.
Although embodiment of the present invention are open as above, but it is not restricted to listed in instructions and embodiment utilization, it can be applied to various applicable the field of the invention completely, for those skilled in the art, can easily realize other amendment, therefore do not deviating under the universal that claim and equivalency range limit, the present invention is not limited to specific details and illustrates here and the legend described.
Claims (5)
1. measure a method for aerocraft real angle of attack value in wind tunnel experiment, it is characterized in that, comprising:
Step one, a platform is installed on attack angle mechanism, zero-point voltage value corresponding when the angle of attack value of acquisition platform is 0 °, and when angle of attack value is not 0 °, angle of attack magnitude of voltage corresponding during the different angle of attack value of platform;
Step 2, angle of attack magnitude of voltage corresponding to each not 0 deg angle of attack value deduct zero-point voltage value, obtain multiple correction angle of attack magnitude of voltage;
Step 3, the multiple correction angle of attack magnitudes of voltage obtained according to step 2, and the angle of attack value corresponding to each correction angle of attack magnitude of voltage, set up the curve of angle of attack value and correction angle of attack magnitude of voltage, as datum curve;
Step 4, dismounting platform, be installed on attack angle mechanism by aircraft to be measured, the angle of attack value of aircraft to be measured be adjusted to 0 °, measure the angle of angle as the pre-angle setting of aircraft to be measured of now attack angle mechanism;
According to angle and the datum curve of the pre-angle setting of aircraft to be measured, matching obtains the actual angle of attack value of aircraft to be measured and the curve of angle of attack magnitude of voltage;
Step 5, measure aircraft to be measured and be arranged on angle of attack magnitude of voltage on attack angle mechanism, the actual angle of attack value of aircraft to be measured obtained according to the angle of attack magnitude of voltage measured and step 4 and the curve of angle of attack magnitude of voltage, obtain the actual angle of attack value of aircraft to be measured.
2. the method measuring aerocraft real angle of attack value in wind tunnel experiment as claimed in claim 1, it is characterized in that, in described step one, attack angle mechanism is installed a platform, by the zero-point voltage value that incidence vane acquisition platform is corresponding when angle of attack value is 0 °, when not being 0 ° with angle of attack value, the angle of attack magnitude of voltage that platform is corresponding when different angle of attack value.
3. the method measuring aerocraft real angle of attack value in wind tunnel experiment as claimed in claim 1, is characterized in that, in described step 3, to correct angle of attack magnitude of voltage for Y-axis, with angle of attack value for X-axis, set up the curve of angle of attack value and correction voltage value.
4. the method measuring aerocraft real angle of attack value in wind tunnel experiment as claimed in claim 3, is characterized in that, in described step 3, adopts the multistage method of least square to set up the curve of angle of attack value and correction voltage value.
5. the method for aerocraft real angle of attack value in the measurement wind tunnel experiment as described in claim 3 or 4, it is characterized in that, in described step 4, aircraft to be measured is installed to attack angle mechanism, the angle of attack value of aircraft to be measured is adjusted to 0 °, according to pre-angle setting and the datum curve of aircraft to be measured, matching obtains the actual angle of attack value of aircraft to be measured and the curve of angle of attack voltage, is specially:
If the pre-angle setting of aircraft to be measured be on the occasion of, then by datum curve along the preset angle value of translation under Y-axis, the curve after translation is the actual angle of attack value of aircraft to be measured and the curve of angle of attack magnitude of voltage;
If the pre-angle setting of aircraft to be measured is negative value, then by datum curve along the preset angle value of translation in Y-axis, the curve after translation is the actual angle of attack value of aircraft to be measured and the curve of angle of attack magnitude of voltage.
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Cited By (5)
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| CN106871779A (en) * | 2017-02-27 | 2017-06-20 | 中国科学院自动化研究所 | Minitype underground fin face incidence vane |
| CN108132131A (en) * | 2017-12-22 | 2018-06-08 | 郑州大学 | The device and method of the structures under wind experiment zero degree wind angle of attack is determined using garage's sailing |
| CN108414185A (en) * | 2018-02-08 | 2018-08-17 | 上海机电工程研究所 | Symmetrical flight device wind tunnel test data zero point error processing method |
| CN112393873A (en) * | 2021-01-11 | 2021-02-23 | 中国空气动力研究与发展中心低速空气动力研究所 | Attack angle matching method |
| CN114910240A (en) * | 2022-07-14 | 2022-08-16 | 中国空气动力研究与发展中心低速空气动力研究所 | Automatic calibration method and system for wind tunnel attack angle sensor |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112393873A (en) * | 2021-01-11 | 2021-02-23 | 中国空气动力研究与发展中心低速空气动力研究所 | Attack angle matching method |
| CN114910240A (en) * | 2022-07-14 | 2022-08-16 | 中国空气动力研究与发展中心低速空气动力研究所 | Automatic calibration method and system for wind tunnel attack angle sensor |
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