CN111950079A - Aerodynamic modeling and full-aircraft flutter analysis method based on wind tunnel test response - Google Patents
Aerodynamic modeling and full-aircraft flutter analysis method based on wind tunnel test response Download PDFInfo
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Abstract
The application provides a pneumatic 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, the unsteady aerodynamic model is identified through wind tunnel test data, the unsteady aerodynamic model is obtained, the unsteady aerodynamic coefficient of the scaled wind tunnel model is converted to the full-aircraft model through a similarity law, and flutter analysis is carried out on the full-aircraft model by using the converted aerodynamic model, so that a flutter boundary is obtained. This application compares in comparing in prior art and utilizes flight test data's flutter analysis, and its response data that uses wind tunnel test model carries out aerodynamic modeling, because in the wind tunnel test, it is relatively easy to bury the sensor, consequently can obtain more effective data based on the test data of wind tunnel, and aerodynamic model is more accurate for flutter analysis result is more credible, especially transonic velocity district's aerodynamic modeling.
Description
Technical Field
The application belongs to the technical field of aeroelasticity analysis and test of an aerocraft, and particularly relates to an aerodynamic modeling and full-aircraft flutter analysis method based on wind tunnel test response.
Background
Simulation analysis, wind tunnel test and flutter flight test are usually required in the design process of the airplane, but the relationship between the current wind tunnel test and the flutter analysis is not tight. At present, data after wind tunnel test is mainly applied to the process of verification and confirmation of flutter analysis algorithm, flutter generation form and the like, and wind tunnel test data is not well utilized.
Disclosure of Invention
The application aims to provide a pneumatic modeling and full-aircraft flutter analysis method based on wind tunnel test response, so as to solve the problem of low precision of pneumatic modeling in the prior art.
The technical scheme of the application is as follows: a aerodynamic modeling and full-aircraft flutter analysis method based on wind tunnel test response comprises the following steps:
determining flutter analysis parameters of the real airplane according to the full-airplane analysis typical working condition points of the real airplane;
constructing a wind tunnel test model for flutter analysis by utilizing a similarity criterion, wherein the wind tunnel test model has the same aerodynamic appearance and vibration form as a real airplane;
setting wind tunnel test conditions under the conditions identical to the flutter analysis parameters, carrying out wind tunnel test on a wind tunnel test model for flutter analysis under the wind tunnel test conditions, and measuring the vibration response of the wind tunnel test model at a preset incoming flow speed;
obtaining a mass array and a stiffness array of the wind tunnel test model through finite element analysis, obtaining a state space mathematical model of the wind tunnel test model through conversion, stripping the state space model from the flutter system mathematical model, and dividing the state space model by test dynamic pressure to obtain an unsteady aerodynamic model;
the flutter analysis parameters are the same according to a model similarity law, at the moment, the similarity proportion coefficient corresponding to the generalized aerodynamic influence coefficient is 1, the unsteady aerodynamic model obtained in the step is the full-aerodynamic influence coefficient of the real aircraft, and the generalized unsteady aerodynamic model of the real aircraft can be obtained by multiplying the full-aerodynamic influence coefficient by the flight dynamic pressure of the real aircraft;
establishing a full-aircraft structure model of a real aircraft, converting a kinetic equation into a generalized coordinate, forming a flutter analysis system state space mathematical model together with the generalized unsteady aerodynamic model established in the step, and performing characteristic value analysis on the flutter analysis system state space mathematical model to obtain full-aircraft flutter boundary information including flutter speed and frequency.
In an embodiment of the present application, the flutter analysis parameters include, but are not limited to, mach number, reynolds number, atmospheric specific heat, gravity parameters, and reduction frequency.
In an embodiment of the application, in the wind tunnel test process of a wind tunnel test model for flutter analysis under the wind tunnel test condition, pulse excitation disturbance is applied to the wind tunnel test model to improve the vibration response magnitude of the model in a subcritical state.
In an embodiment of the application, in the process of performing a wind tunnel test on a wind tunnel test model for flutter analysis under the wind tunnel test condition, the vibration response magnitude of the model in the subcritical state is improved in a manner of performing sweep frequency excitation by an exciter built in the wind tunnel test model.
In an embodiment of the application, the vibration response of the wind tunnel test model at a predetermined incoming flow speed is obtained by a response measurement device of a pre-embedded acceleration sensor or an external vibration deformation field measurement system.
The application carries out the discernment of unsteady aerodynamic force model through wind-tunnel test data to obtain unsteady aerodynamic force model, and convert the unsteady aerodynamic force coefficient of scaling wind-tunnel model to on the full quick-witted model through similar law, and utilize the aerodynamic force model after the conversion to carry out flutter analysis to the full quick-witted model, so that obtain the border that flutters. Compared with flutter analysis in the prior art, the method makes full use of data tested by a wind tunnel test, and the aerodynamic force model is more accurate, so that the flutter analysis result is more credible, and particularly, the aerodynamic force modeling in a transonic speed region is realized; meanwhile, compared with aerodynamic modeling of a flight test, the wind tunnel test has the characteristic of higher economy, and can research the influence of different parameters on flutter characteristics, so that the application range is wider.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
Fig. 1 is a schematic view of an exhaust pipe mounting structure according to the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
In order to further excavate data of a wind tunnel test and fully utilize the test means of the wind tunnel test, the application provides a structural unsteady aerodynamic modeling and flutter analysis method based on model response in the wind tunnel test, a model established by the method can be converted through a similarity relation and is applied to flutter analysis of a full-aircraft model, and in view of the fact that a structural dynamics model is accurate, main factors influencing flutter analysis results are the precision of the unsteady aerodynamic model, and the aerodynamic model established through the wind tunnel test meets the similarity relation and is tested under a real environment, so that the model precision is obviously improved compared with a traditional analysis method.
As shown in fig. 1, the aerodynamic modeling and full-aircraft flutter analysis method based on wind tunnel test response provided by the present application includes:
s1: determining flutter analysis parameters such as Mach number, Reynolds number, atmospheric specific heat, gravity parameter, reduction frequency and the like by planning a full-aircraft flutter analysis typical working condition point of a real aircraft.
And S2, constructing and processing a wind tunnel test model for flutter analysis by using a similar criterion, wherein the wind tunnel test model has the same aerodynamic shape and vibration form as a real airplane.
S3, simultaneously, according to the requirements that the flutter analysis parameters such as Mach number, Reynolds number, atmospheric specific heat ratio, gravity parameter, shrinkage reduction frequency and the like are the same, the wind tunnel test condition is worked out.
And carrying out wind tunnel test on the wind tunnel test model under the formulated wind tunnel test condition to obtain the vibration response data of the wind tunnel test model under a certain test incoming flow speed condition.
It should be noted that, in order to improve the accuracy of the test, in some embodiments of the present application, the magnitude of the vibration response of the model in the subcritical state may be improved by applying pulse excitation disturbance to the wind tunnel test model. Or the vibration response magnitude of the model in the subcritical state is improved in a mode of carrying out frequency sweep excitation by arranging an exciter in the wind tunnel test model.
And measuring the vibration response of the wind tunnel test model by using vibration response measuring equipment or a device. The vibration response of the wind tunnel test model can be measured in a mode of embedding an acceleration sensor in the wind tunnel test model. It should be noted that, when the sensor cannot be embedded due to overweight in the wind tunnel test model, a non-contact sensor may be used for vibration response measurement, or an external vibration deformation field measurement system may be used for vibration response measurement, such as an optical camera system.
S4, obtaining a mass array and a stiffness array of the wind tunnel test model through finite element analysis, obtaining a state space mathematical model of the wind tunnel test model through conversion, stripping the state space mathematical model from a flutter system mathematical model, and obtaining an unsteady aerodynamic force model by dividing the test dynamic pressure in the wind tunnel test;
s5, according to the model similarity law, if the Mach number, the Reynolds number, the atmospheric specific heat ratio, the gravity parameter and the reduction frequency are the same, the similarity proportion coefficient corresponding to the generalized aerodynamic influence coefficient is 1, the unsteady aerodynamic model obtained in the step S4 can be used as the full-aircraft aerodynamic influence coefficient of the real aircraft, and the generalized unsteady aerodynamic model is obtained by multiplying the coefficient by the flight dynamic pressure of the real aircraft;
s6, establishing a full-aircraft structure model of the real aircraft, converting a kinetic equation into a generalized coordinate, forming a flutter analysis system state space mathematical model together with the generalized unsteady aerodynamic model established in the step S5, and performing characteristic value analysis on the flutter analysis system state space mathematical model to obtain flutter boundary information such as full-aircraft flutter speed, frequency and the like of the real aircraft.
It should be noted that, in the design process of the flutter wind tunnel test model, the design is usually performed according to the similar criterion, so that the requirement of the similar law is usually satisfied, the method can be directly used, if part of parameters cannot completely satisfy the similar criterion, the aerodynamic force model can be corrected by a certain correction method, and the specific correction method can be corrected by referring to the related content of the flutter test of the wind tunnel model in the prior art.
The application carries out the discernment of unsteady aerodynamic force model through wind-tunnel test data, obtains unsteady aerodynamic force model to on unsteady aerodynamic force coefficient with scaling wind-tunnel model converts whole quick-witted model to through similar law, and utilize the aerodynamic force model after the conversion to carry out flutter analysis to whole quick-witted model, so that obtain the border that flutters.
Compared with the flight test data in the prior art, the aerodynamic force modeling is carried out by using the response data of the wind tunnel test model, the data of the wind tunnel test are fully utilized, and because the embedded sensor is relatively easy in the wind tunnel test, more effective data can be obtained based on the test data of the wind tunnel, so that the aerodynamic force model is more accurate, the flutter analysis result is more credible, and especially the aerodynamic force modeling in a transonic speed region is realized. Meanwhile, compared with aerodynamic modeling of a flight test, the wind tunnel test has the characteristic of higher economy, and can research the influence of different parameters on flutter characteristics, so that the application range is wider.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (5)
1. A aerodynamic modeling and full-aircraft flutter analysis method based on wind tunnel test response is characterized by comprising the following steps:
determining flutter analysis parameters of the real airplane according to the full-airplane analysis typical working condition points of the real airplane;
constructing a wind tunnel test model for flutter analysis by utilizing a similarity criterion, wherein the wind tunnel test model has the same aerodynamic appearance and vibration form as a real airplane;
setting wind tunnel test conditions under the conditions identical to the flutter analysis parameters, carrying out wind tunnel test on a wind tunnel test model for flutter analysis under the wind tunnel test conditions, and measuring the vibration response of the wind tunnel test model at a preset incoming flow speed;
obtaining a mass array and a stiffness array of the wind tunnel test model through finite element analysis, obtaining a state space mathematical model of the wind tunnel test model through conversion, stripping the state space model from the flutter system mathematical model, and dividing the state space model by test dynamic pressure to obtain an unsteady aerodynamic model;
the flutter analysis parameters are the same according to a model similarity law, at the moment, the similarity proportion coefficient corresponding to the generalized aerodynamic influence coefficient is 1, the unsteady aerodynamic model obtained in the step is the full-aerodynamic influence coefficient of the real aircraft, and the generalized unsteady aerodynamic model of the real aircraft can be obtained by multiplying the full-aerodynamic influence coefficient by the flight dynamic pressure of the real aircraft;
establishing a full-aircraft structure model of a real aircraft, converting a kinetic equation into a generalized coordinate, forming a flutter analysis system state space mathematical model together with the generalized unsteady aerodynamic model established in the step, and performing characteristic value analysis on the flutter analysis system state space mathematical model to obtain full-aircraft flutter boundary information including flutter speed and frequency.
2. The method of claim 1, wherein the flutter analysis parameters include but are not limited to mach number, reynolds number, atmospheric specific heat, gravity parameters, and reduction frequency.
3. The aerodynamic modeling and full-aircraft flutter analysis method based on wind tunnel test response according to claim 2, wherein in the wind tunnel test process of a wind tunnel test model for flutter analysis under the wind tunnel test condition, the vibration response magnitude of the model in the subcritical state is improved by applying pulse excitation disturbance to the wind tunnel test model.
4. The aerodynamic modeling and full-aircraft flutter analysis method based on wind tunnel test response as claimed in claim 2, wherein in the wind tunnel test process of a wind tunnel test model for flutter analysis under the wind tunnel test condition, the vibration response magnitude of the model in the subcritical state is improved by means of frequency sweep excitation of a built-in exciter in the wind tunnel test model.
5. The aerodynamic modeling and full-aircraft flutter analysis method based on wind tunnel test response as claimed in claim 1, wherein the vibration response of the wind tunnel test model at the predetermined incoming flow velocity is obtained by a response measurement device of a pre-embedded acceleration sensor or an outer vibration deformation field measurement system.
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| CN112611538A (en) * | 2020-11-24 | 2021-04-06 | 中国航空工业集团公司沈阳飞机设计研究所 | Design parameter control method for transonic flutter wind tunnel model processing |
| CN113945357A (en) * | 2021-10-28 | 2022-01-18 | 南京航空航天大学 | Method and device for predicting flutter critical wind speed of wind turbine blade |
| CN114608795A (en) * | 2022-05-11 | 2022-06-10 | 中国飞机强度研究所 | Wind tunnel system resonance boundary determining method for airplane blowing test |
| CN117290960A (en) * | 2023-10-18 | 2023-12-26 | 天目山实验室 | Resistance rudder wing flutter analysis method considering unsteady aerodynamic force correction |
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| CN117290960A (en) * | 2023-10-18 | 2023-12-26 | 天目山实验室 | Resistance rudder wing flutter analysis method considering unsteady aerodynamic force correction |
| CN117290960B (en) * | 2023-10-18 | 2024-07-26 | 天目山实验室 | Resistance rudder wing flutter analysis method considering unsteady aerodynamic force correction |
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