Test data processing method for multi-control-surface hinge moment wind tunnel test

Abstract

The invention discloses a test data processing method for a multi-control-surface hinge moment wind tunnel test, and belongs to the technical field of wind tunnel test data processing. In order to improve the accuracy and efficiency of data processing, the method comprises the following steps: constructing a hinge moment balance coordinate system, a control surface reference coordinate system, a control surface pneumatic data coordinate system and a control surface pneumatic data normalization coordinate system under a wind tunnel test model body axis coordinate system; establishing a relationship between a wind tunnel test model body axis coordinate system and each coordinate system; establishing a rotation matrix and a translation matrix between the coordinate systems; establishing a transformation method of balance force and moment in each coordinate system; a wind tunnel test model body axis coordinate system is used as a middle coordinate system, balance forces and moments are converted in different coordinates between any control surfaces through conversion of a rotation matrix and a translation matrix, and calculated coordinate system data results are obtained; and converting the force vector and the torque vector into dimensionless aerodynamic force and torque coefficients for data processing and analysis comparison based on a unified standard.

Description

Technical Field

[0001] The invention belongs to the technical field of wind tunnel test data processing, and in particular relates to a test data processing method for a multi-control surface hinge moment wind tunnel test. Background Art

[0002] The refinement of modern aircraft design places increasingly higher demands on the accuracy of wind tunnel test data. Accurate evaluation of control surface hinge torque is of great support significance for the selection of aircraft control surface servos, aircraft structure design, and aircraft control system design.

[0003] As the diameter of the wind tunnel increases, the corresponding model size and aerodynamic load also increase synchronously, and the number of control surfaces that can simultaneously measure the hinge torque in the wind tunnel test also increases. Because each control surface is located in a different part of the wind tunnel test model, the balance form, balance strain element number, and control surface angle change method used for each control surface may be different.

[0004] First, in the traditional control surface hinge moment wind tunnel test process, the hinge moment data of each control surface is established and processed separately based on a single control surface, and multiple control surfaces are realized through a simple repetitive process, resulting in the differences in characteristics between the control surfaces and their contribution to the overall aerodynamic characteristics of the aircraft cannot be evaluated under a unified system.

[0005] Secondly, the traditional serial data processing flow requires frequent re-establishment of data transmission relationships when there are many control surface hinge torque balances with different forms, which significantly increases the workload of data processing and the probability of error. Summary of the invention

[0006] The problem to be solved by the present invention is to obtain the test data of each control surface under a unified standard during a wind tunnel test of multiple control surfaces, improve the accuracy and efficiency of data processing, and propose a test data processing method for a wind tunnel test of multiple control surfaces.

[0007] To achieve the above object, the present invention is implemented through the following technical solutions: A test data processing method for a multi-control surface hinge moment wind tunnel test comprises the following steps: S1. Coordinate system of the model body axis in the wind tunnel test Next, for the The hinge moment balance coordinate system is constructed for each control surface , control surface reference coordinate system , control surface aerodynamic data coordinate system , control surface aerodynamic data normalized coordinate system ; S2. Establish the relationship between the wind tunnel test model body axis coordinate system and the coordinate systems constructed in step S1: Determine the axis coordinate system of the wind tunnel test model Transform to the hinge moment balance coordinate system The rotation matrix , determine the wind tunnel test model body axis coordinate system Transform to the control surface reference coordinate system The rotation matrix , determine the wind tunnel test model body axis coordinate system To the control surface aerodynamic data coordinate system The rotation matrix , determine the wind tunnel test model body axis coordinate system To the control surface aerodynamic data normalized coordinate system The rotation matrix ; S3. Establish the rotation matrix and translation matrix between the coordinate systems constructed in step S1: The wind tunnel test model body axis coordinate system As the intermediate coordinate system, construct the rotation matrix and translation matrix between the coordinate systems constructed in step S1; S4. Establish the transformation method of balance force and moment in each coordinate system: During the test, the hinge moment balance strain signal is calculated and collected to obtain the hinge moment balance coordinate system The force vector under and the moment vector Based on the rotation matrix and translation matrix obtained in step S3, the control surface reference coordinate system Projection is performed to obtain the control surface reference coordinate system The force vector under and the moment vector ;Will and In the control surface aerodynamic data coordinate system Projection is performed to obtain the control surface aerodynamic data coordinate system The force vector under and the moment vector ;Will and Normalized coordinate system of control surface aerodynamic data Projection is performed to obtain the normalized coordinate system of the control surface aerodynamic data The force vector under and the moment vector ; S5. According to the above steps S1-S4, the wind tunnel test model body axis coordinate system is used. It is an intermediate coordinate system. For any control surface, each balance force and moment are converted in different coordinates through the conversion of rotation matrix and translation matrix to obtain the data results of each coordinate system after solution. S6. According to the solved data results of each coordinate system, the reference area and reference length cited by different coordinate systems, the force vector and moment vector are converted into dimensionless aerodynamic force and moment coefficients for data processing and analysis and comparison based on unified standards.

[0008] Furthermore, in step S1, the hinge moment balance coordinate system , control surface reference coordinate system In the wind tunnel test model body axis coordinate system Determine the coordinate system direction vector and origin coordinates.

[0009] Furthermore, in step S4, the hinge moment balance coordinate system The force vector under and the moment vector It is obtained by iteratively solving the hinge moment balance formula.

[0010] Furthermore, in step S6, the dimensionless aerodynamic force and moment coefficient are calculated by using the actual Mach number of the wind tunnel flow field, the static pressure of the wind tunnel test section flow field, and the reference area and reference length of the control surface.

[0011] Beneficial effects of the present invention: The test data processing method for the hinge moment wind tunnel test of multiple control surfaces described in the present invention does not need to deduce the data processing process for different control surfaces during the test preparation process, but only needs to be processed in the wind tunnel test model reference system. Provided below: Coordinate system used by hinge moment balance for each control surface The coordinate origin and the unit vector of the coordinate axis direction, the reference coordinate system of each control surface The coordinate origin and the unit vector of the coordinate axis direction, the aerodynamic data coordinate system of each control surface The coordinate origin and the unit vector of the coordinate axis direction, and the aerodynamic data of each control surface are normalized to the coordinate system The coordinate origin and the unit vector of the coordinate axis direction can be obtained through the wind tunnel test model reference system Rotation matrices between coordinate systems and translation matrix , each control surface is connected through a hinge torque balance on the control surface hinge torque balance using the coordinate system The force measured under and torque , converted to the normalized coordinate system of each control surface aerodynamic data , the experimental data processing of the multi-control surface hinge moment wind tunnel test is realized through the coordinate system transformation of Euclidean space. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 The present invention is a flow chart of a test data processing method for a multi-control surface hinge moment wind tunnel test. DETAILED DESCRIPTION

[0013] In order to make the purpose, technical solution and advantages of the present invention more clear, the present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention, that is, the specific embodiments described are only part of the embodiments of the present invention, rather than all of the specific embodiments. The components of the specific embodiments of the present invention described and shown in the drawings herein can be arranged and designed in various different configurations, and the present invention can also have other embodiments.

[0014] Therefore, the following detailed description of the specific embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention claimed for protection, but merely represents the selected specific embodiments of the present invention. Based on the specific embodiments of the present invention, all other specific embodiments obtained by those skilled in the art without making creative work are within the scope of protection of the present invention.

[0015] In order to further understand the content, features and effects of the present invention, the following specific implementation methods are given as examples, and the attached Figure 1 The detailed instructions are as follows:

[0016] Embodiment 1: A test data processing method for a multi-control surface hinge moment wind tunnel test comprises the following steps: S1. Coordinate system of the model body axis in the wind tunnel test Next, for the The hinge moment balance coordinate system is constructed for each control surface , control surface reference coordinate system , control surface aerodynamic data coordinate system , control surface aerodynamic data normalized coordinate system ; Furthermore, the specific implementation method of step S1 includes the following steps: S1.1. Setting the wind tunnel test model body axis coordinate system As a global reference coordinate system; The origin of the wind tunnel test model body axis coordinate system : Fixed at the reference point; The vertical axis of the wind tunnel test model body axis coordinate system : Parallel to the fuselage axis or wing root chord, pointing forward; The horizontal axis of the wind tunnel test model body axis coordinate system : perpendicular to the aircraft reference plane (fuselage symmetry plane), pointing to the right; The vertical axis of the wind tunnel test model body axis coordinate system : Located in the aircraft reference plane, vertical Point downwards; S1.2. Constructing the hinge moment balance coordinate system ; The origin of the hinge moment balance coordinate system : The torque measurement reference point of the balance; The vertical axis of the hinge moment balance coordinate system : Along the center line of the Tianping Plain piece pointing to the model end; The horizontal axis of the hinge moment balance coordinate system : points upwards in the longitudinal symmetry plane of the balance; Vertical axis of the hinge moment balance coordinate system : Perpendicular to , determined based on the right-hand coordinate rule; S1.3. Constructing the control surface reference coordinate system ; Origin of the control surface reference coordinate system : The intersection position of the control surface hinge axis and the section where the average aerodynamic chord of the control surface is located; The longitudinal axis of the control surface reference coordinate system : The vertical hinge axis in the control surface reference plane points to the incoming flow direction; The horizontal axis of the control surface reference coordinate system : coincides with the control surface hinge axis in the control surface reference plane; Vertical axis of the control surface reference coordinate system : Perpendicular to , determined based on the right-hand coordinate rule; Further, the control surface reference plane is fixedly connected to the control surface, passes through the control surface hinge axis, and is parallel to the characteristic chord line, and the characteristic chord line is the control surface root chord line or the section chord line of the fixed wing surface where the control surface root chord is located; the control surface deflection angle is set to be the angle of deflection of the control surface around its hinge axis, and usually the positive deflection of the control surface generates a negative control torque; S1.4. Constructing the control surface aerodynamic data coordinate system ; The origin of the control surface aerodynamic data coordinate system : The intersection position of the control surface hinge axis and the section where the average aerodynamic chord of the control surface is located; The vertical axis of the control surface aerodynamic data coordinate system : When the control surface deflection angle is 0°, the vertical hinge axis in the control surface reference plane points to the incoming flow. When the control surface deflection angle is not equal to 0°, it rotates around the hinge axis by a corresponding angle; The horizontal axis of the control surface aerodynamic data coordinate system : coincides with the control surface hinge axis in the control surface reference plane; Vertical axis of the control surface aerodynamic data coordinate system : Perpendicular to Plane, determined based on the right-hand coordinate rule; S1.5. Constructing a normalized coordinate system for control surface aerodynamic data ; For the right control surface of the model, the coordinate system Aerodynamic data coordinate system of control surface completely consistent; For the left control surface of the model, the coordinate system The X and Z axis definitions are The Y axis is opposite to it; S2. Establish the relationship between the wind tunnel test model body axis coordinate system and the coordinate systems constructed in step S1: Determine the axis coordinate system of the wind tunnel test model Transform to the hinge moment balance coordinate system The rotation matrix , determine the wind tunnel test model body axis coordinate system Transform to the control surface reference coordinate system The rotation matrix , determine the wind tunnel test model body axis coordinate system To the control surface aerodynamic data coordinate system The rotation matrix , determine the wind tunnel test model body axis coordinate system To the control surface aerodynamic data normalized coordinate system The rotation matrix ; Furthermore, the specific implementation method of step S2 includes the following steps: S2.1. Coordinate system of the body axis of the wind tunnel test model To the hinge moment balance coordinate system : The wind tunnel test model body axis coordinate system is obtained by establishing a coordinate system in the digital model To the hinge moment balance coordinate system Euler angles of rotation in the order YZX: yaw angle , Pitch angle , Roll Angle ; Set the hinge moment balance coordinate system The coordinates of the origin in the wind tunnel test model body axis coordinate system , then the wind tunnel test model body axis coordinate system Transform to the hinge moment balance coordinate system The rotation matrix The calculation is as follows: ; in, The coordinate system of the wind tunnel test model is Transform to the hinge moment balance coordinate system Roll angle, pitch angle, yaw angle; S2.2. For wind tunnel test model body axis coordinate system To the control surface reference coordinate system : Obtaining the wind tunnel test model body axis coordinate system by measuring the digital model To the control surface reference coordinate system Euler angles of rotation in the order YZX: yaw angle , Pitch angle , Roll Angle ; Set the control surface reference coordinate system The coordinates of the origin in the wind tunnel test model body axis coordinate system , then the wind tunnel test model body axis coordinate system To the control surface reference coordinate system The rotation matrix The calculation is as follows: ; Among them, the wind tunnel test model body axis coordinate system Transform to the control surface reference coordinate system The Euler angles rotated in the order of YZX are: yaw angle , Pitch angle , Roll Angle ; S2.3. For wind tunnel test model body axis coordinate system To the control surface aerodynamic data coordinate system : Obtain the axis coordinate system of the wind tunnel test model by measuring the digital model To the control surface aerodynamic data coordinate system according to YZX Euler angles of sequential rotation: yaw angle , Pitch angle , Roll Angle ; Set the control surface aerodynamic data coordinate system The coordinates of the origin in the wind tunnel test model body axis coordinate system , then the wind tunnel test model body axis coordinate system To the control surface aerodynamic data coordinate system The rotation matrix The calculation is as follows: ; Among them, the wind tunnel test model body axis coordinate system To the control surface aerodynamic data coordinate system The Euler angles rotated in the order of YZX are: yaw angle , Pitch angle , Roll Angle ; S2.4. For wind tunnel test model body axis coordinate system To the control surface aerodynamic data normalized coordinate system : For the right control surface of the model, the wind tunnel test model body axis coordinate system To the control surface aerodynamic data normalized coordinate system The rotation matrix and equal; For the left control surface of the model, the wind tunnel test model body axis coordinate system To the control surface aerodynamic data normalized coordinate system The rotation matrix ; S3. Establish the rotation matrix and translation matrix between the coordinate systems constructed in step S1: The wind tunnel test model body axis coordinate system As the intermediate coordinate system, construct the rotation matrix and translation matrix between the coordinate systems constructed in step S1; Furthermore, the specific implementation method of step S3 includes the following steps: S3.1. Constructing the hinge moment balance coordinate system To the control surface reference coordinate system The rotation matrix and translation matrix of : Hinge moment balance coordinate system To the control surface reference coordinate system The rotation matrix ,in for Transpose a matrix; Hinge moment balance coordinate system To the control surface reference coordinate system The origin of the coordinate system points to the vector ; Hinge moment balance coordinate system To the control surface reference coordinate system The coordinate origin points to the vector in the control surface reference coordinate system The median coordinates are as follows: ; ; in, for The value of the i-th row and j-th column of They are In the control surface reference coordinate system The mid-coordinate decomposition is x, y, z; Hinge moment balance coordinate system To the control surface reference coordinate system Additional torque ; Hinge moment balance coordinate system To the control surface reference coordinate system The translation matrix ; S3.2. Constructing the control surface reference coordinate system To the control surface aerodynamic data coordinate system The rotation matrix and translation matrix of : Control surface reference coordinate system To the control surface aerodynamic data coordinate system The rotation matrix ; Control surface reference coordinate system To the control surface aerodynamic data coordinate system The origin of the coordinate system points to the vector ; Control surface reference coordinate system To the control surface aerodynamic data coordinate system The coordinate origin points to the vector in the control surface aerodynamic data coordinate system The median coordinates are as follows: ; ; in, for No. Row, No. Column value; They are In the control surface aerodynamic data coordinate system The mid-coordinate decomposition is x, y, z; Control surface aerodynamic data coordinate system and Control surface reference coordinate system The origin is the same, the control surface reference coordinate system To the control surface aerodynamic data coordinate system Additional torque ;Control surface reference coordinate system To the control surface aerodynamic data coordinate system The translation matrix ; S3.3. Constructing the control surface aerodynamic data coordinate system To the control surface aerodynamic data normalized coordinate system The rotation matrix and translation matrix of : For the right control surface of the model, the control surface aerodynamic data coordinate system To the control surface aerodynamic data normalized coordinate system Rotation Matrix ; Control surface aerodynamic data coordinate system To the control surface aerodynamic data normalized coordinate system Additional torque ;Control surface aerodynamic data coordinate system To the control surface aerodynamic data normalized coordinate system The translation matrix ; For the control surface on the left side of the model, the control surface aerodynamic data coordinate system To the control surface aerodynamic data normalized coordinate system Rotation Matrix ; Control surface aerodynamic data coordinate system To the control surface aerodynamic data normalized coordinate system Additional torque ;Control surface aerodynamic data coordinate system To the control surface aerodynamic data normalized coordinate system The translation matrix ; S4. Establish the transformation method of balance force and moment in each coordinate system: During the test, the hinge moment balance strain signal is calculated and collected to obtain the hinge moment balance coordinate system The force vector under and the moment vector Based on the rotation matrix and translation matrix obtained in step S3, the control surface reference coordinate system Projection is performed to obtain the control surface reference coordinate system The force vector under and the moment vector ;Will and In the control surface aerodynamic data coordinate system Projection is performed to obtain the control surface aerodynamic data coordinate system The force vector under and the moment vector ;Will and Normalized coordinate system of control surface aerodynamic data Projection is performed to obtain the normalized coordinate system of the control surface aerodynamic data The force vector under and the moment vector ; Furthermore, the specific implementation method of step S4 includes the following steps: S4.1. Calculation of hinge moment balance coordinate system To the control surface reference coordinate system The force vector and torque vector of ; Based on hinge moment balance coordinate system Downward force , torque , after rotation transformation to the control surface reference coordinate system The force , after rotation transformation to the control surface reference coordinate system Torque , after translation transformation to the control surface reference coordinate system Additional torque ; Get the reference coordinate system of the control surface after rotation and translation The torque under ; S4.2. Calculation of control surface reference coordinate system To the control surface aerodynamic data coordinate system The force vector and torque vector of ; Based on the solution results of step S4.1, set the control surface reference coordinate system Downward force , torque , after rotation transformation to the control surface aerodynamic data coordinate system The force , after rotation transformation to the control surface aerodynamic data coordinate system Torque , after translation transformation to the control surface aerodynamic data coordinate system Additional torque ; Get the aerodynamic data coordinate system of the control surface after rotation and translation The torque under ; S4.3. Calculation of control surface aerodynamic data coordinate system To the control surface aerodynamic data normalized coordinate system The force vector and torque vector of ; Based on the S4.2 solution results, set the control surface aerodynamic data coordinate system Downward force , torque , after rotation transformation to the control surface aerodynamic data normalized coordinate system back , after rotation transformation to the control surface aerodynamic data normalized coordinate system Torque , after translation transformation to the normalized coordinate system of the control surface aerodynamic data Additional torque ; Get the normalized coordinate system of the control surface aerodynamic data after rotation and translation Torque ; S5. According to the above steps S1-S4, the wind tunnel test model body axis coordinate system is used. It is an intermediate coordinate system. For any control surface, each balance force and moment are converted in different coordinates through the conversion of rotation matrix and translation matrix to obtain the data results of each coordinate system after solution. S6. According to the solved data results of each coordinate system, the reference area and reference length cited by different coordinate systems, the force vector and moment vector are converted into dimensionless aerodynamic force and moment coefficients for data processing and analysis and comparison based on unified standards.

[0017] Furthermore, the specific implementation method of step S6 includes the following steps: S6.1. Calculation of hinge moment coefficients ; in, is the hinge moment, in Nm, corresponding to the stress moment vector Quantity , ; is the incoming flow pressure, unit: Pa; is the characteristic area of ​​the control surface, in units ; is the characteristic chord length of the control surface, in m; S6.2. Calculation of Normal Force Coefficient ; in, is the normal force, unit , corresponding to the stress vector Quantity , ; S6.3. Calculation of Axial Force Coefficient ; in, is the axial force, unit , corresponding to the stress vector Quantity ; S6.4. Calculation of Lateral Force Coefficient ; in, is the axial force, unit , corresponding to the stress vector Quantity ; S6.5. Calculation of rolling moment coefficient ; in, is the rolling moment, unit , corresponding to the stress vector Quantity ; is the characteristic extension of the control surface, in units ； S6.6. Calculation of Yawing Moment Coefficient ; in, is the yaw moment, in units of , corresponding to the stress vector Quantity .

[0018] It should be noted that relational terms such as "first" and "second" are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the existence of other identical elements in the process, method, article or device including the elements.

[0019] Although the present application has been described above with reference to specific embodiments, various modifications may be made thereto and parts thereof may be replaced with equivalents without departing from the scope of the present application. In particular, as long as there is no structural conflict, the various features in the specific embodiments disclosed in the present application may be used in combination with each other in any manner, and the fact that these combinations are not exhaustively described in this specification is only for the sake of omitting space and saving resources. Therefore, the present application is not limited to the specific embodiments disclosed herein, but includes all technical solutions falling within the scope of the claims.

Claims

1. A test data processing method for a multi-control surface hinge moment wind tunnel test, characterized in that: The following steps are involved: S1. Coordinate system of the model body axis in the wind tunnel test Next, for the The hinge moment balance coordinate system is constructed for each control surface , control surface reference coordinate system , control surface aerodynamic data coordinate system , control surface aerodynamic data normalized coordinate system ; S2. Establish the relationship between the wind tunnel test model body axis coordinate system and the coordinate systems constructed in step S1: Determine the axis coordinate system of the wind tunnel test model Transform to the hinge moment balance coordinate system The rotation matrix , determine the wind tunnel test model body axis coordinate system Transform to the control surface reference coordinate system The rotation matrix , determine the wind tunnel test model body axis coordinate system To the control surface aerodynamic data coordinate system The rotation matrix , determine the wind tunnel test model body axis coordinate system To the control surface aerodynamic data normalized coordinate system The rotation matrix ; S3. Establish the rotation matrix and translation matrix between the coordinate systems constructed in step S1: The wind tunnel test model body axis coordinate system As the intermediate coordinate system, construct the rotation matrix and translation matrix between the coordinate systems constructed in step S1; S4. Establish the transformation method of balance force and moment in each coordinate system: During the test, the hinge moment balance strain signal is calculated and collected to obtain the hinge moment balance coordinate system The force vector under and the moment vector Based on the rotation matrix and translation matrix obtained in step S3, the control surface reference coordinate system Projection is performed to obtain the control surface reference coordinate system The force vector under and the moment vector ;Will and In the control surface aerodynamic data coordinate system Projection is performed to obtain the control surface aerodynamic data coordinate system The force vector under and the moment vector ;Will and Normalized coordinate system of control surface aerodynamic data Projection is performed to obtain the normalized coordinate system of the control surface aerodynamic data The force vector under and the moment vector ; S5. According to the above steps S1-S4, the wind tunnel test model body axis coordinate system is used. It is an intermediate coordinate system. For any control surface, each balance force and moment are converted in different coordinates through the conversion of rotation matrix and translation matrix to obtain the data results of each coordinate system after solution. S6. According to the solved data results of each coordinate system, the reference area and reference length cited by different coordinate systems, the force vector and moment vector are converted into dimensionless aerodynamic force and moment coefficients for data processing and analysis and comparison based on unified standards.

2. The test data processing method for a multi-control surface hinge moment wind tunnel test according to claim 1, characterized in that: Hinge moment balance coordinate system in step S1 , control surface reference coordinate system In the wind tunnel test model body axis coordinate system Determine the coordinate system direction vector and origin coordinates.

3. The test data processing method for a multi-control surface hinge moment wind tunnel test according to claim 2, characterized in that: Hinge moment balance coordinate system in step S4 The force vector under and the moment vector It is obtained by iteratively solving the hinge moment balance formula.

4. The test data processing method for a multi-control surface hinge moment wind tunnel test according to claim 3, characterized in that: In step S6, the dimensionless aerodynamic force and moment coefficient are calculated by using the actual Mach number of the wind tunnel flow field, the static pressure of the wind tunnel test section flow field, and the reference area and reference length of the control surface.

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