CN-122020861-A - Aircraft wind tunnel test data consistency optimization method, system, equipment and medium

CN122020861ACN 122020861 ACN122020861 ACN 122020861ACN-122020861-A

Abstract

The invention relates to the technical field of aircraft wind tunnel tests and discloses a method, a system, equipment and a medium for optimizing the consistency of aircraft wind tunnel test data, wherein the method comprises the steps of acquiring wind tunnel force measurement data and wind tunnel pressure measurement data, performing cubic spline interpolation processing on the wind tunnel pressure measurement data, and calculating partial derivatives of pressure coefficients on an attack angle and a sideslip angle; the method comprises the steps of carrying out aerodynamic coefficient integration based on wind tunnel pressure measurement data and geometric parameters of a pressure measurement model to obtain a normal force coefficient and a lateral force coefficient of the wind tunnel pressure measurement data, carrying out a ratio of the normal force coefficient of the wind tunnel pressure measurement data to obtain a normal scale factor, carrying out a ratio of the lateral force coefficient of the wind tunnel pressure measurement data to obtain a lateral scale factor, constructing a double correction factor model for each pressure measurement point based on the normal scale factor, the lateral scale factor and partial derivatives of the pressure coefficient on an attack angle and a sideslip angle, and solving the corrected pressure coefficient. The invention can eliminate manual errors and improve data consistency.

Inventors

WU HONGYU
LIU QINGHANG
ZHAO ZHILU
ZHU JUN
Yu Qingsi

Assignees

四川腾盾科技有限公司
四川腾盾良远智能科技有限公司

Dates

Publication Date: 20260512
Application Date: 20260413

Claims (10)

1. The method for optimizing the consistency of the wind tunnel test data of the aircraft is characterized by comprising the following steps of: Acquiring wind tunnel force measurement data and wind tunnel pressure measurement data, performing cubic spline interpolation processing on the wind tunnel pressure measurement data, and calculating partial derivatives of pressure coefficients on an attack angle and a sideslip angle; Performing aerodynamic coefficient integration based on wind tunnel pressure measurement data and geometric parameters of a pressure measurement model to obtain a normal force coefficient and a lateral force coefficient of the wind tunnel pressure measurement data; the normal force coefficient of the wind tunnel force measurement data and the normal force coefficient of the wind tunnel pressure measurement data are subjected to ratio to obtain a normal scale factor, and the lateral scale factor is obtained by performing ratio on the lateral force coefficient of the wind tunnel force measurement data and the lateral force coefficient of the wind tunnel pressure measurement data; And constructing a double correction factor model for each pressure measuring point based on the normal scale factors, the lateral scale factors and the partial derivatives of the pressure coefficients on the attack angle and the sideslip angle, and solving the corrected pressure coefficients.
2. The method for optimizing the consistency of aircraft wind tunnel test data according to claim 1, wherein the steps of obtaining wind tunnel force measurement data and wind tunnel pressure measurement data comprise obtaining normal force coefficients through a wind tunnel force measurement test And lateral force coefficient Obtaining the pressure coefficient of the pressure measuring point of the whole machine through a wind tunnel pressure measuring test Wherein, the method comprises the steps of, In order to be the angle of attack, As the slip angle of the slide-in plate, Is the deflection of the pneumatic control surface, The pressure points are numbered.
3. The method for optimizing the consistency of the wind tunnel test data of the aircraft according to claim 2, wherein the performing cubic spline interpolation on the wind tunnel pressure measurement data, calculating partial derivatives of pressure coefficients on attack angles and sideslip angles, comprises: Wherein, the As a function of the pressure coefficient, As the partial derivative of the pressure coefficient with respect to the angle of attack, And the cubic spline interpolation processing adopts a natural boundary condition to lead the second order of the interpolation curve to be continuous and conductive.
4. The method for optimizing the consistency of the wind tunnel test data of the aircraft according to claim 3, wherein the step of integrating aerodynamic coefficients based on the wind tunnel pressure measurement data and the geometrical parameters of the pressure measurement model to obtain a normal force coefficient and a lateral force coefficient of the wind tunnel pressure measurement data comprises the following steps: Wherein, the Is the normal force coefficient of the wind tunnel pressure measurement data, The lateral force coefficient of the wind tunnel pressure measurement data is obtained; is the first The normal component of each pressure measurement point in the y-direction, Is the first The normal component of each pressure measurement point in the z direction, Is the first The corresponding areas of the pressure measuring points, Is the reference area of the whole machine, The pressure points are numbered.
5. The method for optimizing the consistency of the wind tunnel test data of the aircraft according to claim 4, wherein the step of obtaining the normal scaling factor by comparing the normal force coefficients of the wind tunnel force measurement data with the normal force coefficients of the wind tunnel force measurement data and obtaining the lateral scaling factor by comparing the lateral force coefficients of the wind tunnel force measurement data with the lateral force coefficients of the wind tunnel force measurement data comprises the steps of: Wherein, the As a normal scaling factor, the reference value, Is a lateral scaling factor.
6. The method for optimizing the consistency of the wind tunnel test data of the aircraft according to claim 5, wherein the constructing the dual correction factor model for each pressure measuring point based on the normal scale factor, the lateral scale factor and the partial derivatives of the pressure coefficient with respect to the attack angle and the sideslip angle comprises: Wherein, the Is the first The corrected pressure coefficient of each pressure measuring point, And Is a coefficient to be determined.
7. The method for optimizing the consistency of aircraft wind tunnel test data according to claim 6, wherein the solving the corrected pressure coefficient comprises: solving the coefficient to be determined by the coefficient to be determined method And Simultaneous equations: Solving the undetermined coefficients by simultaneous equations And Then substituting the obtained product into the dual correction factor model to solve the first Pressure coefficient after correction of each pressure measuring point 。
8. An aircraft wind tunnel test data consistency optimization system, comprising: The data acquisition and preprocessing module is configured to acquire wind tunnel force measurement data and wind tunnel pressure measurement data, perform cubic spline interpolation processing on the wind tunnel pressure measurement data, and calculate partial derivatives of pressure coefficients on an attack angle and a sideslip angle; the aerodynamic coefficient integration module is configured to integrate aerodynamic coefficients based on wind tunnel pressure measurement data and geometric parameters of the pressure measurement model to obtain normal force coefficients and lateral force coefficients of the wind tunnel pressure measurement data; The scale factor calculation module is configured to perform a ratio of normal force coefficients of the wind tunnel force measurement data to normal force coefficients of the wind tunnel pressure measurement data to obtain a normal scale factor, and perform a ratio of lateral force coefficients of the wind tunnel force measurement data to lateral force coefficients of the wind tunnel pressure measurement data to obtain a lateral scale factor; And the corrected pressure coefficient solving module is configured to construct a double-corrected factor model for each pressure measuring point based on the normal scale factor, the lateral scale factor and the partial derivatives of the pressure coefficient on the attack angle and the sideslip angle, and solve the corrected pressure coefficient.
9. A computer device comprising a memory and a processor, the memory storing a computer program, characterized in that the processor, when executing the computer program, implements the aircraft wind tunnel test data consistency optimization method of any of claims 1-7.
10. A computer readable storage medium storing a computer program, wherein the computer program when executed by a processor implements the aircraft wind tunnel test data consistency optimization method of any of claims 1-7.

Description

Aircraft wind tunnel test data consistency optimization method, system, equipment and medium Technical Field The invention relates to the technical field of aircraft wind tunnel tests, in particular to a method, a system, equipment and a medium for optimizing data consistency of an aircraft wind tunnel test. Background In the field of aeronautical sky aerodynamic study, wind tunnel tests are a core means for acquiring aerodynamic characteristics of an aircraft, wherein wind tunnel force tests and wind tunnel pressure tests are two basic and key test types. The wind tunnel force measurement test directly acquires aerodynamic force and moment parameters (including lift force, resistance, side force, pitching moment, rolling moment and yaw moment) of a wind tunnel model whole machine and key components through a high-precision mechanical measurement device (typical equipment is a multi-component strain force balance), the measurement result directly reflects the whole mechanical response of the model under specific incoming flow conditions, the wind tunnel force measurement test acquires surface pressure data of limited discrete points through a pressure sensor array (such as a miniature piezoresistive sensor and a piezoelectric sensor) preset on the surface of the model, and the aerodynamic force characteristic of the whole machine or the components is acquired through integral calculation by combining a model surface topological structure. However, in practical engineering application, two types of test results often have non-negligible systematic deviation, the core causes of the two types of test results comprise three aspects, namely, model processing and manufacturing errors, rigidity of a force measurement model is required to be ensured to avoid balance measurement interference, a sensor installation channel is required to be reserved in the force measurement model, inherent differences exist in geometric shapes (such as surface finish and key pneumatic component contours) and structural rigidity of the force measurement model, flow field bypass characteristics are inconsistent, measuring system precision differences, measuring precision of the force measurement balance is influenced by temperature drift and load coupling interference, a zero drift and dynamic response hysteresis exist in a pressure sensor, and the like, calibration standards of the two types of sensors are different from a traceability system, further data deviation is further aggravated, and third, test environment disturbance, incoming flow uniformity (such as turbulence degree and Mach number stability) of two tests, model installation posture (such as attack angle and sideslip angle calibration precision) and flow field boundary conditions (such as tunnel wall interference correction coefficient) exist in fine differences, so that a test state cannot be completely reproduced. At present, a main stream deviation correction method in engineering relies on a manual comparison correction method, namely, component force measurement data and pressure measurement integral data of corresponding components are compared point by independently developing component force measurement tests, and a correction factor matrix is established to carry out iterative correction on pressure measurement results. Although the method can reduce deviation to a certain extent, the method has obvious technical defects, and the method is specifically expressed as follows: 1. The test efficiency is low, an independent force measurement test scheme and model are designed for each key component such as a wing, a fuselage, a tail wing and the like, the multi-wheel tests such as full-machine force measurement, full-machine pressure measurement and multi-component force measurement are sequentially carried out for completing full-machine correction, the whole correction period is usually as long as several weeks or even months, and the high-efficiency requirement of the aerodynamic design iteration of the aircraft is difficult to meet. 2. The experience dependence is strong, the correction process needs to depend on the understanding degree of engineers on pneumatic flow mechanisms (such as shock wave position, boundary layer separation and vortex system interference), and the selection of correction factors and the iteration direction have strong subjectivity. For complex flow fields (such as a transonic flow and a large attack angle separation flow), experience judgment is easy to deviate, so that reliability and robustness of a correction result are insufficient. 3. The comprehensive cost is high, a great amount of materials and working hours are consumed for designing and processing the extra component force measuring model, and the wind tunnel test resources are occupied by the multi-round test, so that the test cost is greatly increased. Meanwhile, the manual correction process is required to be invested in a team of senior engineers, and the labor cost is fur