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

Abstract

A test data processing method for a multi-control-surface hinge moment wind tunnel test relates to the technical field of structural component testing, solves the problem that an existing control-surface hinge moment test data processing method does not include deformation correction, and comprises the steps of S1, coordinate system description, S2, ground preparation process, and S3, data processing. S3, establishing and converting an aerodynamic force and aerodynamic torque conversion relation; S4, calculating and correcting aerodynamic force and aerodynamic torque coefficients in consideration of a local Mach number condition; and S5, carrying out whole angle interpolation. According to the method, the influence of the elastic angle of the hinge moment balance, the torsion angle after the control surface is loaded, the difference of wind tunnel test models and the difference of the real Mach number and the nominal Mach number on the aerodynamic coefficient under the condition that the deflection angle of the control surface is large can be more accurately corrected.

Description

Technical Field

[0001] The present invention relates to the technical field of structural component testing, and particularly relates to a method for processing test data for a multi-control surface hinge moment wind tunnel test. Background Art

[0002] The refinement of modern aircraft design places increasingly high requirements on the accuracy of wind tunnel test data. The accurate evaluation of the hinge moment of the control surface is of great significance for the selection of the aircraft control surface actuator, the aircraft structural design, and the aircraft control system design.

[0003] With the increase in the wind tunnel diameter, the corresponding model size and aerodynamic load also increase synchronously. The bending and torsion deformation of the control surface after being loaded will have an obvious impact on the aerodynamic characteristics of the control surface.

[0004] First of all, during the use of the traditional control surface hinge moment balance, the bending and torsion deformation that occurs after the balance is loaded is ignored, resulting in an elastic angle. Since the control surface is fixedly connected to the balance, this deformation will also affect the true deflection angle of the control surface.

[0005] Secondly, in the traditional control surface hinge moment wind tunnel test, the deflection angles of each control surface are achieved through angle-changing blocks or other limiting structures with similar functions. During the test, the influence of the elastic deformation of the control surface itself after being loaded on the control surface angle is ignored. It is considered that the control surface itself is a rigid body and the nominal deflection angle of the control surface is the true deflection angle during the test process, so the measurement of the true angle is not carried out. This has a certain impact on the accuracy of the hinge moment test data of large-size wind tunnel models with large and thin control surfaces.

[0006] Finally, during the traditional hinge moment test process, the Mach number of the wind tunnel inflow is replaced by the nominal Mach number of the wind tunnel. For wind tunnel test models with different blockage ratios, the influence of the model blockage ratio on the far-field Mach number of the wind tunnel test is not fully considered. For some special control surface change angles, they can even be perpendicular to the wind tunnel inflow, which will cause a large change in the blockage ratio of the wind tunnel test model. In this case, the difference between the true inflow Mach number near the model and the nominal Mach number of the wind tunnel will have a certain impact on the dimensionless results of the test data.

[0007] The above three points will all affect the accuracy of the control surface hinge moment wind tunnel test data. Therefore, it is of great significance to establish a hinge moment test preparation and test data correction method that has a relatively small cost for additional measurement equipment in the wind tunnel and takes into account the elastic deformation of the balance and the control surface and the interference of the control surface deflection angle on the wind tunnel flow field to improve the accuracy of the hinge moment wind tunnel test data and the evaluation of the test data effect. Summary of the Invention

[0008] To solve the problem that the existing method for processing test data of control surface hinge moment does not include deformation correction, the present invention provides a method for processing test data of multi-control surface hinge moment wind tunnel test, including: S1. Under the body coordinate system of the wind tunnel test model, construct five types of coordinate systems for each control surface: the ground axis coordinate system of the hinge moment balance , the coordinate system used by the hinge moment balance , the reference coordinate system , the aerodynamic data coordinate system , and the aerodynamic data correction coordinate system ; ; S2. Perform ground preparation operations, including: S2.1. Arrange static pressure measurement points on the model surface of the fuselage to obtain the static pressure data of the measurement points; S2.2. By stepwise loading four geometric feature points on the control surface reference calibration block, measure their displacement changes and solve the Euler angles, establish the fitting relationship between the load and the bending and torsion angles of the balance, and obtain the elastic angle, rotation matrix and translation matrix ; S2.3. By pasting identification points on the wing and the control surface, use dual cameras to photograph and calibrate the conversion relationship between the camera coordinate system and the model coordinate system to obtain the calibration matrix to complete the reference calibration of the deformation measurement system; S2.4. By photographing the displacement differences of the identification points on the wing and the control surface in the windless and windy states with dual cameras, calculate the chordwise torsion angle of the wing and the spanwise bending angle of the wing , the chordwise torsion angle of the control surface and the spanwise bending angle of the control surface , and use the rotation matrix to deduct the associated influence of the wing deformation on the control surface, and finally obtain the change amount of the control surface relative to the root angle of the control surface rudder axis and the rotation matrix from the control surface coordinate system to the control surface correction coordinate system ; S3. Based on the output parameters of S2, convert the force vector and moment vector in the ground axis coordinate system of the hinge moment balance to the aerodynamic data correction coordinate system to obtain the force vector and moment vector in the aerodynamic data correction coordinate system; S4. Based on the static pressure data of the measurement points in S2.1, calculate the local Mach number and dynamic pressure, and realize the dimensionless correction of the force vector and moment vector in the aerodynamic data correction coordinate system in S3 to obtain the dimensionless aerodynamic coefficient; S5. Based on the change amount of the control surface relative to the root angle of the control surface rudder axis in S2.4, match the dimensionless aerodynamic coefficient to the nominal deflection angle by integer angle linear interpolation.

[0009] Furthermore, in S2.2, the elastic angles are obtained by: ; wherein, in the geocentric coordinate system of the hinge moment balance, is the elastic angle about the Z-axis, is the elastic angle about the Y-axis, is the elastic angle about the X-axis, is the normal force along the Y-axis, is the moment about the Z-axis, is the normal force along the Z-axis, is the moment about the Y-axis, is the moment about the X-axis, and the elastic angle coefficient is the elastic deformation constant corresponding to each element force and moment obtained by calculation; The rotation matrix is obtained by: ; wherein, is the rotation matrix about X, is the rotation matrix about Z, is the rotation matrix about Y; The translation matrix is obtained by: ; wherein, is the coordinate offset of the geocentric coordinate system of the hinge moment balance relative to the coordinate system used by the hinge moment balance.

[0010] Furthermore, S2.3 is specifically: Stick and paint identification points W1, W2, W3, W4 on the wing surface, and stick and paint identification points D1, D2, D3, D4 on the control surface. Use the high-definition camera 1 on the side wall and the high-definition camera 2 on the top of the wind tunnel test section to take pictures of the identification points on the wing and the control surface, and complete the reference calibration of the deformation measurement system by determining the conversion relationship between the camera coordinate system and the coordinate systems of the wing and the control surface.

[0011] Furthermore, in S2.4, the chordwise twist angle of the wing and the spanwise bending angle are obtained by: ; wherein, is the change amount of the W1 point perpendicular to the wing plane, is the change amount of the W2 point perpendicular to the wing plane, is the change amount of the W3 point perpendicular to the wing plane, is the change amount of W4 perpendicular to the wing plane, is the distance between the centers of W1, W2 and the centers of W3, W4, is the distance between the centers of W1, W3 and the centers of W2, W4, which can be obtained by digital model measurement; The chordwise torsion angle of the control surface and the spanwise bending angle of the control surface are obtained through: ; wherein, is the change amount of D1 perpendicular to the wing plane, is the change amount of D2 perpendicular to the wing plane, is the change amount of D3 perpendicular to the wing plane, is the change amount of D4 perpendicular to the wing plane, is the distance between the centers of D1, D2 and the centers of D3, D4, is the distance between the centers of D1, D3 and the centers of D2, D4, which can be obtained by digital model measurement; The change amount of the angle of the control surface relative to the root of the control surface rudder shaft is obtained through: ; wherein, is the chordwise torsion angle change amount of the control surface relative to the root of the control surface rudder shaft, is the spanwise bending angle change amount of the control surface relative to the root of the control surface rudder shaft; The rotation matrix of the control surface coordinate system to the corrected control surface coordinate system is obtained through: ; wherein,

[0012] The beneficial effects of the present invention: After adopting the method of the present invention, the influence of the elastic angle of the hinge moment balance, the torsion angle after the control surface is loaded, the difference of the wind tunnel test model, and the difference between the true Mach number and the nominal Mach number under the condition of a large deflection angle of the control surface on the aerodynamic coefficient can be corrected more accurately. Brief Description of the Drawings

[0013] Figure 1 is a schematic layout diagram of the elastic correction measurement points of the multi-coordinate system of the wind tunnel test aircraft model; In the figure: 1- upper panel of the test section, 2- lower panel of the test section, 3- high-definition camera 1, 4- high-definition camera 2, 5- model, 6- hinge torque balance, 7- control surface reference position, 8- position of the control surface after deflection, W1- wing deformation measurement point 1, W2- wing deformation measurement point 2, W3- wing deformation measurement point 3, W4- wing deformation measurement point 4, D1- control surface deformation measurement point 1, D2- control surface deformation measurement point 2, D3- control surface deformation measurement point 3, D4- control surface deformation measurement point 4; Figure 2 This is the principle diagram of the solution method for the hinge moment test in a continuous transonic wind tunnel. DETAILED DESCRIPTION

[0014] The technical solution of the present invention is further described below with reference to the embodiments, but is not limited thereto. Any modification or equivalent replacement of the technical solution of the present invention without departing from the spirit and scope of the technical solution of the present invention shall be included in the scope of protection of the present invention. The process equipment or devices not specifically noted in the following examples are all conventional equipment or devices in the art. Unless otherwise specified, the raw materials used in the examples of the present invention can be obtained commercially; unless otherwise specified, the technical means used in the examples of the present invention are all conventional means well known to those skilled in the art.

[0015] Example 1, combined Figure 1 This embodiment is described by Figure 1 It can be seen that a test data processing method for a multi-control surface hinge moment wind tunnel test includes: S1. In the wind tunnel test model body coordinate system Five types of coordinate systems are constructed for each control surface: hinge torque balance axis coordinate system , Coordinate system used by hinge moment balance , reference coordinate system , aerodynamic data coordinate system and aerodynamic data correction coordinate system ; S2. Perform ground preparation operations, including: S2.1. Arrange static pressure measuring points on the model surface on the fuselage and obtain static pressure data at the measuring points; S2.2. By step-loading the four geometric feature points on the control surface reference calibration block, measuring their displacement changes and solving the Euler angle, establishing the fitting relationship between the load and the balance bending and torsion angle, and obtaining the elastic angle and rotation matrix and translation matrices ; S2.3. Complete the benchmark calibration of the deformation measurement system by attaching marker points to the wings and control surfaces, using dual cameras to capture and calibrate the transformation relationship between the camera coordinate system and the model coordinate system, and obtaining the calibration matrix; S2.4. By taking pictures with dual cameras to obtain the displacement differences of the identification points on the wing and control surface in the windless and windy states, respectively calculate the chordwise twist angle of the wing and the spanwise bending angle of the wing , the chordwise twist angle of the control surface and the spanwise bending angle of the control surface , and use the rotation matrix to deduct the associated influence of the wing deformation on the control surface. Finally, obtain the angle change of the control surface relative to the root of the control surface rudder shaft and the rotation matrix from the control surface coordinate system to the corrected control surface coordinate system; S3. Based on the output parameters of S2, convert the force vector and moment vector in the ground axis coordinate system of the hinge moment balance to the aerodynamic data corrected coordinate system , and obtain the force vector and moment vector in the aerodynamic data corrected coordinate system; S4. Based on the static pressure data of the pressure measurement points described in S2.1, calculate the local Mach number and dynamic pressure, and realize the non-dimensional correction of the force vector and moment vector in the aerodynamic data corrected coordinate system described in S3 to obtain the non-dimensional aerodynamic coefficients; S5. Taking the angle change of the control surface relative to the root of the control surface rudder shaft described in S2.4 as the benchmark, match the non-dimensional aerodynamic coefficients to the nominal deflection angles through integer angle linear interpolation.

[0016] Specifically, S1 establishes the spatial transformation reference for aerodynamic force measurement and correction by constructing five types of coordinate systems. S2 makes detailed arrangements for the calibration of the balance elastic deformation, the installation of the video measurement system for measuring the elastic deformation of the control surface, and the airtightness inspection of the model monitoring pressure measurement points to meet the acquisition basis of the necessary parameters in this method. S3 According to the results of S2, in the form of matrix transformation, the force vector and moment vector in the ground axis system of the hinge moment balance are successively passed through the coordinate system used by the control surface hinge moment balance, the fixed end 1 coordinate system of the control surface hinge moment balance, the fixed end 2 coordinate system of the control surface hinge moment balance, the control surface reference coordinate system , and the control surface aerodynamic data coordinate system for axis system transformation, and finally obtain the force vector and moment vector in the control surface aerodynamic data corrected coordinate system. S4 measures the static pressure of the pressure measurement points on the surface of the typical model under the windy test conditions, combines with the total pressure of the free stream in the wind tunnel, calculates the local Mach number and local dynamic pressure, and realizes the correction of the non-dimensional parameters under the windy test conditions. S5 Based on the actual deflection angle of the control surface, aligns the nominal angle through interpolation to generate the mapping relationship between the standard aerodynamic coefficients and the rudder deflection angles.

[0017] Furthermore, in S2.2, the elastic angle is obtained by: ; is obtained, where, in the geodetic coordinate system of the hinge moment balance, is the elastic angle about the Z-axis, is the elastic angle about the Y-axis, is the elastic angle about the X-axis, is the normal force along the Y-axis, is the moment about the Z-axis, is the normal force along the Z-axis, is the moment about the Y-axis, is the moment about the X-axis, and the elastic angle coefficient is the elastic deformation constant corresponding to each element force and moment obtained by calculation; The rotation matrix is obtained by: ; where, is the rotation matrix about X, is the rotation matrix about Z, is the rotation matrix about Y; The translation matrix is obtained by: ; where, is the coordinate offset of the geodetic coordinate system of the hinge moment balance relative to the coordinate system used by the hinge moment balance of the hinge moment balance.

[0018] Specifically, during the preparation of the ground calibration table or the wind tunnel test model, outside the selected balance calibration center, four information measurement points A, B, C, and D with known position information on the control surface reference calibration block are selected, where the line AB is parallel to the axis of the control surface reference calibration block, and the line CD is perpendicular to the axis of the control surface reference calibration block.

[0019] Using measuring devices such as dial indicators or height gauges, simultaneously measure the displacement changes of these four points before and after loading in the form of stepped loading, and convert the displacement changes into the Euler angles of the rotation of the three coordinate axis vectors of the control surface hinge moment balance geodetic system Finally, an approximate fitting relationship between the load and the balance bending and torsion angles is established to determine the conversion relationship between the three coordinate axes of the control surface hinge moment balance geodetic system and the coordinate system used by the control surface hinge moment balance under the condition of wind after the control surface hinge moment balance is loaded.

[0020] The rotation matrix from the balance geodetic system to the balance body axis system ; Further, S2.3 is specifically as follows: Apply identification points W1, W2, W3, and W4 on the wing surface, and apply identification points D1, D2, D3, and D4 on the control surface. Use the high-definition cameras 1 on the side wall of the wind tunnel test section and the high-definition camera 2 on the top to photograph the identification points on the wing and the control surface. By determining the conversion relationship between the camera coordinate system and the wing and control surface coordinate systems, the reference calibration of the deformation measurement system is completed.

[0021] Specifically, Figure 1 Fig. shows the test layout of the aircraft model (5) in the wind tunnel test. The test section is composed of upper and lower wall plates (1, 2). The two high-definition cameras (3, 4) on both sides are used to capture the displacement changes of the wing deformation measurement points (W1 - W4) and the control surface measurement points (D1 - D4). The model is fixed by a hinge moment balance (6). The comparison between the reference position (7) and the deflected position (8) of the control surface presents the dynamic deflection of the rudder surface, and the enlarged area highlights the distribution details of the measurement points.

[0022] Further, in S2.4, the chordwise twist angle of the wing and the spanwise bending angle of the wing are obtained through: ; wherein, is the change amount of the perpendicular distance from point W1 to the wing plane, is the change amount of the perpendicular distance from point W2 to the wing plane, is the change amount of the perpendicular distance from point W3 to the wing plane, is the change amount of the perpendicular distance from point W4 to the wing plane, is the distance between the midpoints of W1, W2 and the midpoints of W3, W4, is the distance between the midpoints of W1, W3 and the midpoints of W2, W4, which can be obtained by digital mock-up measurement; The chordwise twist angle of the control surface and the spanwise bending angle of the control surface are obtained through: ; wherein, is the change amount of the perpendicular distance from point D1 to the wing plane, is the change amount of the perpendicular distance from point D2 to the wing plane, is the change amount of the perpendicular distance from point D3 to the wing plane, is the change amount of the perpendicular distance from point D4 to the wing plane, is the distance between the midpoints of D1, D2 and the midpoints of D3, D4, is the distance between the midpoints of D1, D3 and the midpoints of D2, D4, which can be obtained by digital mock-up measurement; The change amount of the angle of the control surface relative to the root of the control surface rudder shaft is obtained through: ; obtained, is the chordwise torsional angle change of the control surface relative to the root of the control surface hinge axis, is the spanwise bending angle change of the control surface relative to the root of the control surface hinge axis; The rotation matrix from the control surface coordinate system to the corrected control surface coordinate system is obtained through: ; obtained.

[0023] Specifically, Figure 2 shows the multi - level coordinate system conversion process of the hinge moment measurement data in the aircraft wind tunnel test: starting from the balance original earth axis coordinate system, passing through the body axis coordinate system, the control surface reference coordinate system, and the actual rudder deflection coordinate system in sequence, and finally mapping to the corrected coordinate system, clearly marking the rotation angles and rotation matrices around different axes at each link.

Claims

1. A method for processing test data of hinge moment of multiple control surfaces in a wind tunnel test, characterized in that Including: S1. In the body coordinate system of the wind tunnel test model , five types of coordinate systems are constructed for each control surface: the hinge moment balance earth axis coordinate system , the coordinate system used by the hinge moment balance , the reference coordinate system , the aerodynamic data coordinate system and the aerodynamic data correction coordinate system ; S2. Perform ground preparation operations, including: S2.

1. Arrange static pressure measurement points on the surface of the fuselage model to obtain the static pressure data of the measurement points; S2.

2. Manipulate the four geometric feature points on the control surface reference calibration block through stepped loading, measure their displacement changes and solve the Euler angles, establish the fitting relationship between the load and the balance bending and torsion angles, and obtain the elastic angle, rotation matrix and translation matrix ; S2.

3. By pasting identification points on the wing and control surface, using two cameras to take pictures and calibrate the conversion relationship between the camera coordinate system and the model coordinate system, obtain the calibration matrix to complete the reference calibration of the deformation measurement system; S2.

4. Use dual cameras to capture the displacement differences of the wing and control surface markers in windless and no-wind conditions, and calculate the chord-wise twist angles. Spanwise bending angle of the wing , control surface chordal twist angle Spanwise bending angle with control surface , and use the rotation matrix to deduct the collateral effect of wing deformation on the control surface, and finally obtain the angle change of the control surface relative to the control surface rudder axis root and the rotation matrix from the control surface coordinate system to the control surface correction coordinate system ; S3. Based on the output parameters of S2, convert the force vector and moment vector in the hinge moment balance earth axis coordinate system to the aerodynamic data correction coordinate system to obtain the force vector and moment vector in the aerodynamic data correction coordinate system; S4. Based on the static pressure data of the measurement points described in S2.1, calculate the local Mach number and dynamic pressure, and realize the non-dimensional correction of the force vector and moment vector in the corrected coordinate system of the aerodynamic data described in S3 to obtain the non-dimensional aerodynamic coefficients; S5. Taking the change amount of the relative angle of the control surface with respect to the root of the control surface rudder shaft described in S2.4 as the reference, match the non-dimensional aerodynamic coefficients to the nominal deflection angle through integer-angle linear interpolation.

2. The test data processing method for multi-control surface hinge moment wind tunnel test according to claim 1, wherein In S2.2, the elastic angle is obtained by: ； obtained, wherein, in the hinge moment balance earth axis coordinate system, is the elastic angle about the Z axis, is the elastic angle about the Y axis, is the elastic angle about the X axis, is the normal force along the Y axis, is the moment about the Z axis, is the normal force along the Z axis, is the moment about the Y axis, is the moment about the X axis, and the elastic angle coefficient is the elastic deformation constant corresponding to each element force and moment obtained by calculation; The rotation matrix by: ； obtained, where, is the rotation matrix about X, is the rotation matrix about Z, is the rotation matrix about Y; The translation matrix by: ； obtained, wherein, is the hinge moment balance earth axis coordinate system with respect to the coordinate system used by the hinge moment balance coordinate offset.

3. A test data processing method for multi-control surface hinge moment wind tunnel test according to claim 2, characterized in that S2.3 specifically is: Paste and paint identification points W1, W2, W3, W4 on the wing surface, paste and paint identification points D1, D2, D3, D4 on the control surface surface, use the high-definition camera 1 on the side wall of the wind tunnel test section and the high-definition camera 2 on the top to take pictures of the identification points on the wing and control surface, and complete the reference calibration of the deformation measurement system by determining the conversion relationship between the camera coordinate system and the wing and control surface coordinate systems.

4. A test data processing method for multi-control surface hinge moment wind tunnel test according to claim 3, characterized in that, In S2.4, the chordwise twist angle of the wing and the spanwise bending angle of the wing are obtained through: ； Obtained, where, is the change in the perpendicular distance of point W1 from the wing plane, is the change in the perpendicular distance of point W2 from the wing plane, is the change in the perpendicular distance of point W3 from the wing plane, is the change in the perpendicular distance of point W4 from the wing plane, is the distance between the center points of W1, W2 and the center points of W3, W4, is the distance between the center points of W1, W3 and the center points of W2, W4, which can be obtained by digital mock-up measurement; The chordwise twist angle of the control surface and the spanwise bending angle of the control surface are obtained by: ； Obtained, where is the change amount of point D1 perpendicular to the wing plane, is the change amount of point D2 perpendicular to the wing plane, is the change amount of point D3 perpendicular to the wing plane, is the change amount of point D4 perpendicular to the wing plane, is the distance between the center points of D1 and D2 and the center points of D3 and D4, is the distance between the center points of D1 and D3 and the center points of D2 and D4, which can be obtained by digital model measurement; The change amount of the relative angle of the control surface with respect to the root of the control surface rudder shaft is obtained by: ； Obtained is the chordwise torsional angle change amount of the control surface relative to the root of the control surface hinge axis is the spanwise bending angle change amount of the control surface relative to the root of the control surface hinge axis; Rotation matrix from control surface coordinate system to control surface corrected coordinate system By: ； Obtained.

Images