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Aerodynamic modeling and full-aircraft flutter analysis method based on wind tunnel test response

A flutter analysis and aerodynamic technology, applied in CAD numerical modeling, computer-aided design, special data processing applications, etc., can solve the problems of low accuracy of aerodynamic modeling, achieve reliable flutter analysis results, and aerodynamic The effect of accurate model and wide application range

Active Publication Date: 2020-11-17
CHINA AIRPLANT STRENGTH RES INST
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Problems solved by technology

[0003] The purpose of this application is to provide an aerodynamic modeling based on wind tunnel test response and whole-machine flutter analysis method to solve the problem of low accuracy of aerodynamic modeling in the prior art

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  • Aerodynamic modeling and full-aircraft flutter analysis method based on wind tunnel test response

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Embodiment Construction

[0018] In order to make the purpose, technical solution and advantages of the application more clear, the technical solution in the embodiment of the application will be described in more detail below in conjunction with the drawings in the embodiment of the application.

[0019] In order to further excavate the data of the wind tunnel test and make full use of the testing method of the wind tunnel test, this application proposes a structural unsteady aerodynamic modeling and flutter analysis method based on the model response in the wind tunnel test. The model established by the method can be converted through the similarity relationship and applied to the flutter analysis of the whole machine model. In view of the accuracy of the structural dynamics model, the main factor affecting the flutter analysis results is the accuracy of the unsteady aerodynamic model. Through the wind tunnel The aerodynamic model established by the test satisfies the similarity relationship and is te...

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Abstract

The invention provides an aerodynamic modeling and full-aircraft flutter analysis method based on wind tunnel test response, and belongs to the technical field of aircraft design. According to the method, an unsteady aerodynamic model is identified through wind tunnel test data, the unsteady aerodynamic model is obtained, an unsteady aerodynamic coefficient of a scaling wind tunnel model is converted to the full-aircraft model through the similarity law, and flutter analysis is made on the full-aircraft model by using a converted aerodynamic model so as to obtain a flutter boundary. Compared with flutter analysis by using flight test data in the prior art, aerodynamic modeling is performed by using the response data of the wind tunnel test model, and since sensors are relatively easy to embed in the wind tunnel test, more effective data can be obtained based on the test data of the wind tunnel, the aerodynamic model is more accurate, and the reliability of the aerodynamic model is improved. Thus, the flutter analysis result is more credible, especially aerodynamic modeling of a transonic interval.

Description

technical field [0001] The application belongs to the technical field of aeroelastic analysis and testing of aviation vehicles, and in particular relates to an aerodynamic modeling based on wind tunnel test response and a method for flutter analysis of the whole aircraft. Background technique [0002] Simulation analysis, wind tunnel test and flutter flight test are usually required in the process of aircraft design, but the relationship between wind tunnel test and flutter analysis is not close at present. At present, the data after the wind tunnel test are mainly used in the process of verifying and confirming the flutter analysis algorithm and the form of the flutter, and the wind tunnel test data has not been well utilized. Contents of the invention [0003] The purpose of this application is to provide an aerodynamic modeling based on wind tunnel test response and whole-machine flutter analysis method to solve the problem of low accuracy of aerodynamic modeling in the...

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Application Information

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IPC IPC(8): G06F30/15G06F30/23G06F30/28G06F119/14G06F113/08G06F111/10
CPCG06F30/15G06F30/23G06F30/28G06F2119/14G06F2113/08G06F2111/10Y02T90/00
Inventor 宋巧治王彬文李晓东牟让科
Owner CHINA AIRPLANT STRENGTH RES INST
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