CN115659521B - Aerodynamic modeling method suitable for complex control surfaces of front spoiler and rear spoiler - Google Patents
Aerodynamic modeling method suitable for complex control surfaces of front spoiler and rear spoiler Download PDFInfo
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- CN115659521B CN115659521B CN202211453800.XA CN202211453800A CN115659521B CN 115659521 B CN115659521 B CN 115659521B CN 202211453800 A CN202211453800 A CN 202211453800A CN 115659521 B CN115659521 B CN 115659521B
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Abstract
The invention discloses an aerodynamic modeling method suitable for complex control surfaces of front and rear spoilers, which comprises the following steps: step 1, designing a front spoiler angle combination sample and a rear spoiler angle combination sample by adopting a DOE test; step 2, calculating sample point aerodynamic force data based on a CFD method of the unstructured grid; step 3, establishing a kriging model with the front spoiler and the rear spoiler as inputs and aerodynamic components as outputs; step 4, checking the precision of the kriging model, and repeating the steps 1 to 4 when the precision is insufficient; step 5, searching a series of front and rear spoiler combination pairs with the minimum rolling torque, and regarding the front and rear spoiler combination pairs as a combined control surface with a certain deflection angle; step 6, establishing a combined control surface aerodynamic force difference kriging model; step 7, establishing a basic aerodynamic force kriging model and a conventional control surface aerodynamic force kriging model; and 8, establishing a full-mechanical pneumatic model. The invention can establish an accurate aerodynamic model by using less aerodynamic calculation data for aircraft stability characteristic analysis and control law design.
Description
Technical Field
The invention relates to the field of aerodynamic modeling of aircrafts, in particular to an aerodynamic modeling method suitable for complex control surfaces of front and rear spoilers.
Background
The aircraft aerodynamic model is the basis for carrying out control effect evaluation and flight control law design, the conventional aircraft control surface coupling is not serious, and the requirements can be met by establishing a linear model aiming at each control surface. However, in the case of an aircraft with complex control surfaces, such as front and rear spoilers, aerodynamic interference between the control surfaces is severe, and when one control surface is deflected, the efficiency of the other control surface will change greatly. To simplify use, a combination of front and rear spoilers is often sought, which is used as a control surface. Because the front spoiler and the rear spoiler can not only generate yaw moment, but also generate roll moment and pitch moment, the triaxial coupling is serious. In order to maximize the efficiency of the control surface, a combination of a front spoiler and a rear spoiler needs to be found, and the rolling moment is as small as possible while the yawing moment is generated, so that the coupling effect is reduced.
Disclosure of Invention
The invention aims to provide an aerodynamic force modeling method suitable for complex control surfaces of front and rear spoilers, and an accurate aerodynamic force model is established by using less aerodynamic force calculation data so as to be used for analyzing the operational stability characteristics of an aircraft and designing a control law.
In order to achieve the purpose, the invention provides the following technical scheme:
an aerodynamic modeling method suitable for complex control surfaces of front and rear spoilers comprises the following steps:
step 1, designing a front spoiler angle combination sample and a rear spoiler angle combination sample by adopting a DOE (design of experiments), wherein the front spoiler angle combination sample comprises a modeling sample point and a checking sample point;
step 2, calculating sample point aerodynamic force data based on a CFD method of the unstructured grid;
step 3, establishing a kriging model with front and rear spoilers as input and each aerodynamic force component as output by taking the modeling sample points as basic data;
step 4, checking the precision of the kriging model, and repeating the steps 1 to 4 when the precision is insufficient;
step 5, taking a Kriging model of the rolling torque Cl of the front spoiler and the rear spoiler as a data source, obtaining a series of front spoiler and rear spoiler combined pairs with the minimum rolling torque by adopting a least square method, and regarding the front spoiler and the rear spoiler combined pairs as combined control surfaces with certain deflection angles;
step 6, obtaining aerodynamic force of the combined control surface by using an aerodynamic force component kriging model constructed by the front spoiler and the rear spoiler, carrying out difference on the aerodynamic force component kriging model and aerodynamic force data without a deflection angle of the control surface to obtain difference data, and establishing the aerodynamic force difference kriging model of the combined control surface by taking the deflection angle and the flight state of the combined control surface as variables and the aerodynamic force difference as output;
step 7, establishing a basic aerodynamic force kriging model and a conventional control surface aerodynamic force difference kriging model;
and 8, synthesizing the basic aerodynamic force kriging model, the conventional control surface aerodynamic force difference kriging model and the combined control surface aerodynamic force difference kriging model, and establishing the aerodynamic force model of the whole machine with the control surface and the combined control surface.
The invention has the beneficial effects that:
the method can realize the establishment of accurate front and rear spoiler kriging models by fewer sample points, can find out the front and rear spoiler combination pairs with smaller yaw control and roll control coupling degrees, and establishes the full-aerodynamic model for the stability operating characteristic analysis and control law design of the aircraft.
Drawings
FIG. 1 is a flow chart of an aerodynamic modeling method suitable for a complex control surface of a front spoiler and a complex control surface of a rear spoiler provided by the invention.
Detailed Description
The invention is described in further detail below with reference to the following figures and embodiments:
as shown in fig. 1, an aerodynamic modeling method suitable for complex control surfaces of front and rear spoilers includes the following steps:
step 1, designing a front spoiler angle combination sample and a rear spoiler angle combination sample by adopting a DOE (design of experiments), wherein the front spoiler angle combination sample comprises a modeling sample point and a checking sample point;
specifically, an orthogonal test design method is adopted, a modeling sample point and a checking sample point are designed by taking a front spoiler deflection angle, a rear spoiler deflection angle, an attack angle, a side slip angle, an M number and the like as variables.
Step 2, calculating sample point aerodynamic force data based on a CFD method of the unstructured grid;
step 3, establishing a kriging model with front and rear spoilers as input and each aerodynamic force component as output by taking the modeling sample points as basic data;
specifically, based on modeling sample points as basic data, a kriging model with a front spoiler deflection angle, a rear spoiler deflection angle, an attack angle, a side slip angle, M number and the like as variables is respectively established for aerodynamic coefficients including a lift coefficient CL, a resistance coefficient CD, a pitching moment coefficient Cm, a yawing moment coefficient Cn, a rolling moment coefficient Cl and a lateral force coefficient CY, and the kriging model is stored.
And 4, step 4: checking the precision of the kriging model, and repeating the steps 1 to 4 when the precision is insufficient;
specifically, the accuracy of the established kriging model is checked with the check of the sample point data as a standard. And (3) obtaining the input of each aerodynamic coefficient kriging model by taking the calculation condition of the check sample points as input, comparing the input with the check sample point data, solving the root mean square error, if the root mean square error value is more than 5% of the mean value of the check sample points, considering that the error is too large and the model precision is insufficient, increasing the modeling sample points, and repeating the steps 1 to 4 until the model precision is sufficient.
And 5: the Kriging model of the rolling torque Cl of the front spoiler and the rear spoiler is used as a data source, a series of front spoiler and rear spoiler combined pairs with the smallest rolling torque are obtained by adopting a least square method, and the front spoiler and the rear spoiler combined pairs are regarded as combined control surfaces with certain deflection angles;
specifically, M number, attack angle and side slip angle in a cruising state are selected, the deflection of a front spoiler is changed, a Kriging model of rolling torque Cl is used as a data source, the deflection of a rear spoiler when the absolute value of the rolling torque is minimum is obtained by adopting a least square method, a series of front and rear spoiler combination pairs are formed, and the deflection of the front spoiler is used as the deflection of a combined control surface.
Step 6: obtaining aerodynamic force of a combined control surface by using aerodynamic force component kriging models constructed by a front spoiler and a rear spoiler, performing difference on the aerodynamic force component kriging models and aerodynamic force data without a control surface deflection angle to obtain difference data, and establishing the aerodynamic force difference kriging models of the combined control surface by taking the combined control surface deflection angle and the flight state as variables and taking the aerodynamic force difference as output;
specifically, flight states of a front spoiler deflection angle, a rear spoiler deflection angle, a Ma number, an attack angle, a side slip angle and the like in the combined control surface are used as input, aerodynamic force data of the combined control surface are obtained by using an aerodynamic force component kriging model constructed by the front spoiler and the rear spoiler, the aerodynamic force data comprise a lift coefficient CL, a resistance coefficient CD, a pitching moment coefficient Cm, a yawing moment coefficient Cn, a rolling moment coefficient Cl and a lateral force coefficient CY, and the aerodynamic force data are subjected to difference when the control surface deflection angle is 0, so that aerodynamic force difference of the combined control surface is obtained. And constructing a Kriging model of each aerodynamic coefficient difference by taking the deflection angle, the Ma number, the attack angle and the sideslip angle of the combined control surface as variables.
And 7: establishing a basic aerodynamic force kriging model and a conventional control surface aerodynamic force difference kriging model;
specifically, all rudders are in zero as basic states, a DOE method is adopted to obtain sample points with the number of flying Ma, the incidence angle and the sideslip angle as input, aerodynamic force is calculated, and a basic aerodynamic force kriging model is established.
And obtaining sample points with the conventional control surface deflection angle, the flight Ma number, the attack angle and the sideslip angle as input by adopting a DOE (design of integration) method, calculating aerodynamic force, and carrying out difference with basic aerodynamic force data to establish a conventional control surface aerodynamic force difference kriging model.
And 8: synthesizing a basic aerodynamic force kriging model, a conventional control surface aerodynamic force difference kriging model and a combined control surface aerodynamic force difference kriging model, and establishing an aerodynamic force model of a whole machine with a control surface and a combined control surface;
specifically, a basic aerodynamic force kriging model, a conventional control surface aerodynamic force difference kriging model and a front spoiler and rear spoiler combined control surface aerodynamic force difference kriging model are combined into a full-mechanical aerodynamic force model, when the aerodynamic force under any flight state and any control surface deflection angle is calculated, the flight state is used as input, the basic aerodynamic force coefficient is obtained through the basic aerodynamic force kriging model, control surface aerodynamic force influence quantity data is obtained through the conventional control surface aerodynamic force difference kriging model, the control surface aerodynamic force difference kriging model is combined to obtain combined control surface aerodynamic force influence quantity data, and the combined control surface aerodynamic force influence quantity data is added to obtain full-mechanical aerodynamic force data.
The foregoing is merely an example of the present invention and common general knowledge in the art of designing and describing particular features and/or characteristics is not set forth herein in any greater detail. It should be noted that, for those skilled in the art, without departing from the technical solution of the present invention, several variations and modifications can be made, which should also be regarded as the protection scope of the present invention, and these will not affect the effect of the implementation of the present invention and the practicability of the patent. The scope of the claims of the present application shall be determined by the contents of the claims, and the description of the embodiments and the like in the specification shall be used to explain the contents of the claims.
Claims (1)
1. An aerodynamic modeling method suitable for complex control surfaces of front and rear spoilers is characterized by comprising the following steps:
step 1, designing a front spoiler angle combination sample and a rear spoiler angle combination sample by adopting a DOE (design of experiments), wherein the front spoiler angle combination sample comprises a modeling sample point and a checking sample point;
step 2, calculating sample point aerodynamic force data based on a CFD method of the unstructured grid;
step 3, establishing a kriging model with the front spoiler and the rear spoiler as input and each aerodynamic force component as output by taking the modeling sample points as basic data;
step 4, checking the precision of the kriging model, and repeating the steps 1 to 4 when the precision is insufficient;
step 5, taking a Kriging model of the rolling torque Cl of the front spoiler and the rear spoiler as a data source, obtaining a series of front spoiler and rear spoiler combined pairs with the minimum rolling torque by adopting a least square method, and regarding the front spoiler and the rear spoiler combined pairs as combined control surfaces with certain deflection angles;
step 6, obtaining aerodynamic force of the combined control surface by using an aerodynamic force component kriging model constructed by the front spoiler and the rear spoiler, carrying out difference on the aerodynamic force component kriging model and aerodynamic force data without a deflection angle of the control surface to obtain difference data, and establishing the aerodynamic force difference kriging model of the combined control surface by taking the deflection angle and the flight state of the combined control surface as variables and the aerodynamic force difference as output;
step 7, establishing a basic aerodynamic force kriging model and a conventional control surface aerodynamic force difference kriging model;
and 8, synthesizing the basic aerodynamic force kriging model, the conventional control surface aerodynamic force difference kriging model and the combined control surface aerodynamic force difference kriging model, and establishing the aerodynamic force model of the whole machine with the control surface and the combined control surface.
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