CN117740307B - Method for predicting performance of full-size rotor wing - Google Patents
Method for predicting performance of full-size rotor wing Download PDFInfo
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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Abstract
The invention discloses a method for predicting the performance of a full-size rotor wing, and belongs to the technical field of helicopter wind tunnel tests; the method mainly comprises the steps of carrying out helicopter model rotor wing tests, adopting helicopter model rotor wings with different diameters, and obtaining test results of different scale shrinkage ratio models; thus, full-size rotor performance calculation is established to obtain a full-size rotor performance prediction method; the invention provides a technical means for accurately predicting the performance of the full-size rotor wing of the helicopter. Through developing helicopter model rotor tests with different diameters, a model rotor hovering and forward flight test database is established and enriched, reliable data is provided for obtaining Reynolds number correction amounts of rotor model performances with different scale ratios, a data basis is provided for researching correlation between model rotor wind tunnel test results and calculation results, and accuracy of predicting helicopter rotor performances by using ground test data can be improved.
Description
Technical Field
The invention relates to a method for predicting performance of a full-size rotor wing, and belongs to the technical field of helicopter wind tunnel tests.
Background
The helicopter rotor wing model wind tunnel test is a main research means for researching the aerodynamic characteristics of a rotor wing and obtaining rotor wing aerodynamic performance data. The wind tunnel test of the helicopter rotor wing model is a dynamic high-lift test, and the Reynolds number of the wind tunnel test is 1-2 orders of magnitude lower than the real flying Reynolds number due to the limitation of the wind tunnel size, so that the wind tunnel test result cannot be directly used for a full-size rotor wing. Therefore, a wind tunnel test result correction method research must be carried out, a correction technology for solving the Reynolds number influence of the test result is adopted, the accuracy of predicting the performance and the load of the full-size rotor wing by using the model wind tunnel test result is improved, and design change caused by the fact that technical indexes caused by inaccurate prediction cannot meet the requirements is avoided, so that model development cost and period are greatly reduced, and the risk and period of a flight test are reduced.
Disclosure of Invention
The invention aims at: aiming at the problems, a method for predicting the performance of the full-size rotor wing is provided, the performance data of rotor wings of different scale scaling models are obtained through experiments, and the Reynolds number correction quantity of the performance of the rotor wings of different scale scaling models is obtained through conversion; calculating and obtaining the performance of the scaled rotor model with different scales after the Reynolds number correction according to the rotor parameters of the scaled model, the test conditions and the correlation result of the Reynolds number correction; on the basis, a full-size rotor performance prediction method is established according to full-size rotor flight conditions and parameters, and a basis is provided for predicting and evaluating the full-size rotor performance of the helicopter.
The technical scheme adopted by the invention is as follows:
a method of predicting performance of a full-size rotor of a helicopter, comprising the steps of:
Step 1, developing helicopter model rotor wing tests, and acquiring test results of different scale scaling models by adopting helicopter model rotor wings with different diameters;
step 2, acquiring Reynolds number correction quantity converted from the performance of the scaled rotor wing model to the performance of the full-size rotor wing according to the test structures of the scaled models with different scales acquired in the step 1;
Step 3, analyzing correlation results among Reynolds number correction amounts of rotor performance of different scale scaling models;
Step 4, calculating and obtaining the performance of the scaled rotor models with different scales after the Reynolds number correction according to the rotor parameters of the scaled model, the test conditions and the correlation results of the Reynolds number correction in step 3, and comparing whether the calculation results are matched with the test results;
And 5, on the basis of matching the calculation result in the step 4 with the test result, combining full-size rotor wing flight conditions and parameters, and establishing full-size rotor wing performance calculation to obtain a full-size rotor wing performance prediction method.
Further, in step 1, helicopter model rotor tests include hover tests and forward flight tests.
Further, the hovering test is carried out among hovering tests, and ventilation conditions around the hovering test are good.
Further, the helicopter model rotor to ground height should be greater than 1.2 rotor diameters to reduce the effects of ground effects.
Further, the distance from the helicopter model rotor to the top of the hover space should be greater than 1.5 rotor diameters to provide sufficient inflow distance above the blade.
Further, the forward flight test is performed in a wind tunnel, and the maximum diameter of the helicopter model rotor wing is determined according to the size of a wind tunnel test section.
Further, helicopter model rotor wind tunnel test conditions correspond to full-size rotor flight conditions, including rotor vertical component, horizontal component, flight speed.
Further, the vertical component force, the horizontal component force and the flying speed are converted into corresponding aerodynamic dimensionless coefficients, including the vertical force coefficient, the horizontal force coefficient and the forward ratio, so as to facilitate performance analysis and research
Further, in step1, the helicopter model rotor and the full-size rotor meet the conditions of geometric similarity, power similarity and motion similarity.
Further, the helicopter model rotor wing is proportional to the overall dimension of the full-size rotor wing, and the corresponding angles are consistent;
the helicopter model rotor wing is consistent with the tip Mach number of the full-size rotor wing;
The forward ratio of the helicopter model rotor to the full-size rotor corresponds to the corresponding steering angle.
In summary, due to the adoption of the technical scheme, the beneficial effects of the invention are as follows:
the method for predicting the performance of the full-size rotor wing provides a technical means for accurately predicting the performance of the full-size rotor wing of the helicopter. Through developing helicopter model rotor tests with different diameters, a model rotor hovering and forward flight test database is established and enriched, reliable data is provided for obtaining Reynolds number correction amounts of rotor model performances with different scale ratios, and a data base is provided for researching correlation between model rotor wind tunnel test results and calculation results. On the basis, a method for predicting the performance of the full-size rotor wing by using a model wind tunnel test result is established according to the flight condition and parameters of the full-size rotor wing. The method can improve the accuracy of predicting the performance of the helicopter rotor by using ground test data, and further improve the aerodynamic force research level of the helicopter rotor in China, thereby providing more powerful technical support for the development of helicopter models.
Drawings
The invention will now be described by way of example and with reference to the accompanying drawings in which:
Fig. 1 is a flow chart of the present invention.
Detailed Description
All of the features disclosed in this specification, or all of the steps in a method or process disclosed, may be combined in any combination, except for mutually exclusive features and/or steps.
Any feature disclosed in this specification may be replaced by alternative features serving the same or equivalent purpose, unless expressly stated otherwise. That is, each feature is one example only of a generic series of equivalent or similar features, unless expressly stated otherwise.
Examples
A method of predicting full-size rotor performance, as shown in fig. 1, comprising the steps of:
Step 1, developing helicopter model rotor wing tests, and acquiring test results of different scale scaling models by adopting helicopter model rotor wings with different diameters;
step 2, acquiring Reynolds number correction quantity converted from the performance of the scaled rotor wing model to the performance of the full-size rotor wing according to the test structures of the scaled models with different scales acquired in the step 1;
Step 3, analyzing correlation results among Reynolds number correction amounts of rotor performance of different scale scaling models;
Step 4, calculating and obtaining the performance of the scaled rotor models with different scales after the Reynolds number correction according to the rotor parameters of the scaled model, the test conditions and the correlation results of the Reynolds number correction in step 3, and comparing whether the calculation results are matched with the test results;
And 5, on the basis of matching the calculation result in the step 4 with the test result, combining full-size rotor wing flight conditions and parameters, and establishing full-size rotor wing performance calculation to obtain a full-size rotor wing performance prediction method.
In the design, particularly in the design of the step 1, the test database of the model rotor wing can be enriched, and a data basis is provided for researching the correlation between the wind tunnel test result and the calculation result of the model rotor wing. On the basis of establishing an experimental database, corresponding operation is further developed for further developing full-size helicopter rotor performance prediction, so that the full-size rotor performance prediction is more accurately realized.
In order to better realize the accuracy of prediction, more specifically, in the step 2, the specific conversion mode is that the performance of the small-scale scaled rotor model is converted to the Reynolds number correction amount of the performance of the large-scale scaled rotor model, and finally converted to the performance of the full-scale rotor, so that the performance and the geometric dimension can be more similar to those of the full-scale rotor. Specifically, for example, a model rotor with a diameter of 1 meter is converted to a model rotor with a diameter of 2 meters, and then converted to a model rotor with a diameter of 4 meters, and finally converted to a reynolds number correction amount for the performance of a full-sized rotor.
More specifically, in step 1, helicopter model rotor tests include hover tests and forward flight tests.
In a specific test process, a hover test is carried out in a hover test room, and ventilation conditions around the hover test room are good. In order to ensure the specific accuracy of the test, the helicopter model rotor wing is further specifically designed, and the height from the helicopter model rotor wing to the ground is larger than 1.2 times of the rotor wing diameter so as to reduce the influence of the ground effect; the distance from the helicopter model rotor to the top of the hover space should be greater than 1.5 rotor diameters to provide sufficient inflow distance above the blade.
As a more specific design, the forward flight test is carried out in a wind tunnel, and the maximum diameter of the helicopter model rotor wing is determined according to the size of a wind tunnel test section.
In the whole test process, the specific accuracy is considered, and the helicopter model rotor wing wind tunnel test conditions correspond to full-size rotor wing flight conditions, including rotor wing vertical component force, horizontal component force and flight speed. More specifically, the vertical component force, the horizontal component force and the flying speed are converted into corresponding aerodynamic dimensionless coefficients, including the vertical force coefficient, the horizontal force coefficient and the forward ratio, so that performance analysis and research can be conveniently carried out.
Based on the specific design, the more specific optimal design is realized, and in step 1, the helicopter model rotor wing and the full-size rotor wing meet the conditions of geometric similarity, power similarity and motion similarity.
More specifically, the geometric similarity is that the rotor wing of the helicopter model is proportional to the overall dimension of the full-size rotor wing, and the corresponding angles are consistent;
The power similarity is that the rotor of the helicopter model is consistent with the Mach number of the tip of the full-size rotor;
The motion similarity is the forward ratio of the helicopter model rotor wing to the full-size rotor wing, and the corresponding steering angles are consistent.
In summary, the method for predicting the performance of the full-size rotor wing of the helicopter provides a technical means for accurately predicting the performance of the full-size rotor wing of the helicopter. Through developing helicopter model rotor tests with different diameters, a model rotor hovering and forward flight test database is established and enriched, reliable data is provided for obtaining Reynolds number correction amounts of rotor model performances with different scale ratios, and a data base is provided for researching correlation between model rotor wind tunnel test results and calculation results. On the basis, a method for predicting the performance of the full-size rotor wing by using a model wind tunnel test result is established according to the flight condition and parameters of the full-size rotor wing. The method can improve the accuracy of predicting the performance of the helicopter rotor by using ground test data, and further improve the aerodynamic force research level of the helicopter rotor in China, thereby providing more powerful technical support for the development of helicopter models.
The invention is not limited to the specific embodiments described above. The invention extends to any novel one, or any novel combination, of the features disclosed in this specification, as well as to any novel one, or any novel combination, of the steps of the method or process disclosed.
Claims (10)
1. A method of predicting performance of a full-size rotor, comprising: the method comprises the following steps:
Step 1, developing helicopter model rotor wing tests, and acquiring test results of different scale scaling models by adopting helicopter model rotor wings with different diameters;
Step 2, according to the test structures of different scale scaling models obtained in the step 1, obtaining Reynolds number correction quantity of scaling rotor wing model performance converted to full-size rotor wing performance, wherein the specific conversion mode is that small scale scaling rotor wing model performance is converted to large scale scaling rotor wing model performance Reynolds number correction quantity, and finally converted to full-size rotor wing performance, so that performance and geometric dimension can be more approximate to full-size rotor wing;
Step 3, analyzing correlation results among Reynolds number correction amounts of rotor performance of different scale scaling models;
Step 4, calculating and obtaining the performance of the scaled rotor models with different scales after the Reynolds number correction according to the rotor parameters of the scaled model, the test conditions and the correlation results of the Reynolds number correction in step 3, and comparing whether the calculation results are matched with the test results;
And 5, on the basis of matching the calculation result in the step 4 with the test result, combining full-size rotor wing flight conditions and parameters, and establishing full-size rotor wing performance calculation to obtain a full-size rotor wing performance prediction method.
2. A method of predicting full-size rotor performance in accordance with claim 1, wherein: in step 1, helicopter model rotor tests include hover tests and forward flight tests.
3. A method of predicting full-size rotor performance in accordance with claim 2, wherein: the hover test is performed between hover tests, and ventilation is performed around the hover test.
4. A method of predicting full-size rotor performance in accordance with claim 3, wherein: the helicopter model rotor to ground height should be greater than 1.2 rotor diameters.
5. A method of predicting full-size rotor performance as claimed in claim 3 or 4, wherein: the distance from the helicopter model rotor to the top of the hover space should be greater than 1.5 rotor diameters.
6. A method of predicting full-size rotor performance in accordance with claim 2, wherein: the forward flight test is carried out in a wind tunnel, and the maximum diameter of the helicopter model rotor wing is determined according to the size of a wind tunnel test section.
7. A method of predicting full-size rotor performance in accordance with claim 6, wherein: the helicopter model rotor wing wind tunnel test conditions correspond to full-size rotor wing flight conditions, and comprise a rotor wing vertical component, a horizontal component and a flight speed.
8. A method of predicting full-size rotor performance in accordance with claim 7, wherein: the vertical component force, the horizontal component force and the flying speed are converted into corresponding aerodynamic dimensionless coefficients, including a vertical force coefficient, a horizontal force coefficient and an advancing ratio.
9. A method of predicting full-size rotor performance in accordance with claim 1, wherein: in step 1, the helicopter model rotor and the full-size rotor meet the conditions of geometric similarity, power similarity and motion similarity.
10. A method of predicting full-size rotor performance in accordance with claim 9, wherein: the helicopter model rotor wing is proportional to the overall dimension of the full-size rotor wing, and the corresponding angles are consistent;
the helicopter model rotor wing is consistent with the tip Mach number of the full-size rotor wing;
The forward ratio of the helicopter model rotor to the full-size rotor corresponds to the corresponding steering angle.
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