CN109738144B - Gust response ground simulation test method - Google Patents
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Abstract
The invention discloses a gust response ground simulation test method, which comprises the steps of arranging a sensor on an airplane structure to test a response signal of a structure to be tested, utilizing the response signal of the structure to be tested to calculate unsteady aerodynamic force caused by structure vibration through an aerodynamic force calculation module, introducing a gust excitation model, superposing gust excitation and unsteady aerodynamic force caused by vibration, applying the gust excitation and the unsteady aerodynamic force on the structure to be tested through a vibration exciter, carrying out closed-loop control on the output force of the vibration exciter to ensure accurate loading of the aerodynamic force, and recording a displacement response signal of the structure, namely a response under the gust excitation through given test conditions of the test. The test is not limited by the size of the structure to be tested, can be carried out on the real airplane structure, and has higher reliability compared with a finite element analysis result; the test can be carried out after a small amount of setting and sensor arrangement are carried out after the ground vibration test, the test state adjustment can be directly set in software, the test operation is simple and convenient, and the test period can be shortened.
Description
Technical Field
The method belongs to the field of aeroelasticity tests, and particularly relates to a gust response ground simulation test method which is mainly used for ground simulation and test of gust response of an airplane structure.
Background
The gust response is the response of the aircraft body of the aircraft structure under the action of atmospheric turbulence, and because the gust response has important influence on riding comfort, the gust response analysis and verification are a necessary link in the design and shaping process of civil aircraft. In order to design and optimize a civil aircraft structure and slow down and control sudden wind, the response of the aircraft structure under the action of sudden wind load needs to be evaluated, the current engineering adopts two main means of simulation analysis and wind tunnel test, and the flight test usually used for aeroelasticity verification is difficult to implement due to uncontrollable atmospheric turbulence test conditions. Finite element analysis has the advantages of low cost and short period, but because the model is different from a real airplane structure and the influence of factors such as nonlinearity of the airplane structure cannot be considered, the analysis error is larger; the wind tunnel model has higher aerodynamic simulation precision, but the scaled model is different from a real airplane structure, so that the test and the real situation have certain difference, and meanwhile, the wind tunnel test has higher cost and longer period for processing the model. In view of the defects of the means, the ground vibration test-based ground simulation test method for the aircraft structure gushing project is provided, unsteady distribution aerodynamic force borne by the aircraft structure is simulated through the concentrated force of the vibration exciter, the test can be performed on the real aircraft structure, and the reliability of the test result is high.
Disclosure of Invention
Object of the Invention
The invention aims to provide a gust response ground simulation test method to improve the prediction precision of airplane structure response under the effect of a gust load, reduce the cost and shorten the prediction period, thereby providing forward data guidance for the anti-gust design and the gust load alleviation control design of civil airplane structures.
Technical solution of the invention
In order to achieve the purpose, the invention adopts the following technical scheme:
a gust response ground simulation test method includes the steps that a sensor is arranged on a structure to be tested to test a response signal of the structure to be tested, the response signal of the structure to be tested is utilized to calculate unsteady aerodynamic force caused by vibration of the structure to be tested through an aerodynamic force reconstruction module, a gust excitation model is introduced, gust excitation and unsteady aerodynamic force caused by vibration are superposed and applied to the structure to be tested through a vibration exciter, closed-loop control is conducted on output force of the vibration exciter to guarantee accurate loading of the aerodynamic force, and a displacement response signal of the structure to be tested is recorded through given test conditions of the test, namely response under the gust excitation.
Preferably, the sensors are acceleration and displacement sensors, and the speed signal is indirectly obtained through acceleration integral or displacement differential.
Preferably, the gust response ground model of the inventionThe test method comprises the following steps: step 1: aiming at the structure to be tested, carrying out gust response analysis by using a finite element method to obtain an analysis result of gust response under a given flight state and excitation; step 2: taking the result of the step 1 as an optimized objective function, optimizing variables to the positions and the number of the vibration exciters and the sensors, and optimizing by adopting a genetic algorithm to obtain an optimal arrangement scheme of the vibration exciters and the sensors; and step 3: reducing the order of the force interpolation and response interpolation matrix by using the arrangement scheme of the vibration exciter and the sensor obtained in the step 2, multiplying the front of the unsteady aerodynamic influence system matrix by the response interpolation matrix and then multiplying the back by the force interpolation matrix to obtain a frequency domain model of aerodynamic force after the order is reduced; and 4, step 4: fitting the frequency domain model obtained in the step 3 into a time domain by using a minimum state method to obtain a time domain model of aerodynamic force; and 5: installing according to the vibration exciter and sensor arrangement scheme obtained in the step 2, and connecting the subsystems; step 6: applying an excitation signal to the power amplifier through a semi-physical simulation system, testing the response of the vibration exciter on the structure to be tested, and designing a controller, wherein the design method of the controller refers to Chinese patent CN201310303375.0 based on H∞A design method of a robust control multipoint excitation force control system; and 7: and setting the flight state of the structure to be tested in the aerodynamic force reconstruction module, downloading the model to a semi-physical simulation system, testing, recording a displacement response signal of the structure to be tested, and comparing the displacement response signal with an analysis result.
Preferably, the flight state in step 7 includes altitude and mach number.
Preferably, in step 5, each subsystem includes: the system comprises a semi-physical simulation system (used for realizing hardware of a signal source), a power amplifier, a vibration exciter, a force sensor and a structure to be tested, wherein a signal source in the semi-physical simulation system generates a voltage signal, the voltage signal is used for driving the power amplifier to amplify power, the vibration exciter is driven to apply excitation to the structure to be tested, the force sensor arranged between the vibration exciter and the structure to be tested is used for recording the amplitude of excitation force, and a data acquisition system is used for acquiring the signal source signal and the excitation force signal to be used for model identification and controller design.
THE ADVANTAGES OF THE PRESENT INVENTION
The invention has the advantages that:
the test is not limited by the size of the structure to be tested, can be carried out on the real airplane structure, and has higher reliability compared with a finite element analysis result; the equipment used in the test is basically consistent with the vibration test, only a small amount of sensors and semi-physical simulation equipment are needed to be added, and compared with the wind tunnel test, the test cost is lower; the test can be carried out after a small amount of setting and sensor arrangement are carried out after the ground vibration test, the test state adjustment can be directly set in software, the test operation is simple and convenient, and the test period can be shortened.
Drawings
FIG. 1 is a schematic block diagram of a gust response ground simulation test method of the present invention.
Fig. 2 is a schematic size diagram of a flat-plate airfoil structure as a structure to be tested.
FIG. 3 is a diagram illustrating the result of optimizing the positions of the excitation point and the vibration pickup point.
FIG. 4 is a simulation of a gust excited wing aeroelastic system.
FIG. 5 is a comparison graph of the detection point response results of the structures to be tested before and after the reduction.
Fig. 6 is a diagram illustrating simulation results.
FIG. 7 is a graph showing the results of the test.
In the figure: the system comprises a structure to be tested 1, a semi-physical simulation system 2, a aerodynamic force reconstruction module 3, a 4-MIMO excitation force control module, a sensor 5, a power amplifier 6, a vibration exciter 7 and a force sensor 8.
Detailed Description
The detailed description of the embodiments of the present invention is provided in conjunction with the summary of the invention and the accompanying drawings.
A gust response ground simulation test method includes the steps that a sensor 5 is arranged on a structure 1 to be tested to test a response signal of the structure 1 to be tested, the response signal of the structure 1 to be tested is utilized, an unsteady aerodynamic force caused by structure vibration is calculated through an aerodynamic force reconstruction module 3, a gust excitation model is introduced, gust excitation and the unsteady aerodynamic force caused by vibration are superposed and applied to the structure 1 to be tested through a vibration exciter 7, closed-loop control is conducted on the output force of the vibration exciter 7 to guarantee accurate loading of the aerodynamic force, and the displacement response signal of the structure is recorded through given test conditions, namely the response under the gust excitation.
The sensor adopts acceleration and displacement sensors, and the speed signal is indirectly obtained through acceleration integral or displacement differential.
The invention relates to a gust response ground simulation test method, which comprises the following steps:
step 1: aiming at the structure to be tested, carrying out gust response analysis by using a finite element method to obtain an analysis result of gust response under a given flight state and excitation;
step 2: taking the result of the step 1 as an optimized objective function, optimizing the positions and the number of the vibration exciters 7 and the sensors 5 by using a genetic algorithm to obtain an optimal arrangement scheme of the vibration exciters 7 and the sensors 5;
and step 3: reducing the order of the force interpolation and response interpolation matrix by using the arrangement scheme of the vibration exciter 7 and the sensor 5 obtained in the step 2, multiplying the front of the unsteady aerodynamic influence system matrix by the response interpolation matrix and then multiplying the back by the force interpolation matrix to obtain a frequency domain model of the aerodynamic force after the order reduction;
and 4, step 4: fitting the frequency domain model obtained in the step 3 into a time domain by using a minimum state method to obtain a time domain model of aerodynamic force;
and 5: installing the vibration exciter 7 and the sensor 5 according to the arrangement scheme obtained in the step 2, and connecting the subsystems according to the figure 1;
step 6: applying an excitation signal to a power amplifier 6 through a semi-physical simulation system 2, testing the response of a vibration exciter 7 acting on a structure to be tested 1, and designing a controller;
and 7: and setting the flight state of the structure 1 to be tested in the aerodynamic force reconstruction module 3, downloading the model to the semi-physical simulation system 2 for testing, recording the displacement response signal of the structure 1 to be tested, and comparing the displacement response signal with the analysis result. The flight state includes altitude and Mach number.
The flat plate wing structure shown in the attached drawing 2 is used as a structure 1 to be tested, the positions of the vibration exciters 7 and the sensors 5 are optimized and are shown in the attached drawing 3, the configuration scheme of 4 sets of vibration exciters 7 and 4 sets of sensors 5 is selected, wherein triangles are marked as the positions of the vibration exciters 7, round points are marked as the positions of the sensors 5, and the sensors 5 adopt acceleration sensors and displacement sensors.
And (3) establishing a frequency domain aerodynamic reduced-order model by utilizing the optimized configuration scheme, establishing a simulation model shown in the attached figure 4 by fitting through a minimum state method, and comparing the response of the optimized aerodynamic model and the response of the structure to be tested 1 under the action of the original aerodynamic model, wherein the result is shown in the attached figure 5. The structural response (solid line in figure 5) under the action of the original aerodynamic model and the structural response (dotted line in figure 5) under the action of the aerodynamic model after the order reduction are superposed, which shows that the equivalent effect of the model before and after the order reduction is better.
Establishing a model of a loading system, designing a controller at the same time, and forming a ground gust response test system by the aerodynamic force model, the controller and the structure to be tested 1 according to the logical relation shown in the attached drawing 1, wherein the ground gust response test system comprises a semi-physical simulation system 2, a power amplifier 6, a vibration exciter 7, a force sensor 8 and the structure to be tested 1; the semi-physical simulation system 2 comprises a aerodynamic force reconstruction module 3 and an MIMO excitation force control module 4; the sensor 5 is arranged on the structure to be tested 1, the sensor 5 is connected to the aerodynamic force reconstruction module 3, the aerodynamic force reconstruction module 3 is connected to the MIMO excitation force control module 4, the MIMO excitation force control module 4 is connected to the power amplifier 6, the power amplifier 6 is connected to the vibration exciter 7, and the force sensors 8 are respectively connected to the MIMO excitation force control module 4, the vibration exciter 7 and the structure to be tested 1; the method comprises the steps of generating a voltage signal through a signal source in a semi-physical simulation system 2, driving a power amplifier 6 to amplify power by using the voltage signal, driving a vibration exciter 7 to apply excitation to a structure 1 to be tested, recording the amplitude of excitation force by using a force sensor 8 arranged between the vibration exciter 7 and the structure 1 to be tested, and collecting the signal source signal and the excitation force signal by using a data acquisition system for model identification and controller design. Testing is carried out by setting the test state parameters, and the response result of the detection point on the structure to be tested 1 is shown in figure 7; the simulation results are shown in fig. 6. As can be seen from simulation and test results, the coincidence effect of the structural response (solid lines in figures 6 and 7) under the action of the original pneumatic force and the response curve of the detection point after the reduction of the order is good, the relative error between the two is less than 10%, and the two is within an acceptable range of engineering.
According to the invention, through the reduction of the aerodynamic force, the distributed unsteady aerodynamic force can be simulated by using a small amount of discrete forces of the vibration exciters 7 and the sensor 5; and fitting the frequency domain aerodynamic force to the time domain by using a minimum state method, thereby obtaining an aerodynamic force calculation model which can be used for simulation and experiment. By combining the two steps, the gust environment of the aircraft flying in the air can be simulated on the ground, so that the test of the ground gust response is realized.
By introducing system identification and robust control, the vibration exciter can be correctly loaded according to instructions, so that the simulation precision of aerodynamic force and the precision of a final test can be guaranteed.
Claims (3)
1. A gust response ground simulation test method is characterized in that a sensor is arranged on a structure to be tested to test a response signal of the structure to be tested, the response signal of the structure to be tested is utilized to calculate unsteady aerodynamic force caused by structure vibration through an aerodynamic force reconstruction module, a gust excitation model is introduced, gust excitation and unsteady aerodynamic force caused by vibration are superposed and applied to the structure to be tested through a vibration exciter, closed-loop control is carried out on the output force of the vibration exciter for ensuring accurate loading of the aerodynamic force, and the displacement response signal of the structure is recorded as the response under the gust excitation through the test condition of a given test;
the method comprises the following steps:
step 1: aiming at the structure to be tested, carrying out gust response analysis by using a finite element method to obtain an analysis result of gust response under a given flight state and excitation;
step 2: taking the result of the step 1 as an optimized objective function, optimizing variables to the positions and the number of the vibration exciters and the sensors, and optimizing by adopting a genetic algorithm to obtain an optimal arrangement scheme of the vibration exciters and the sensors;
and step 3: reducing the order of the force interpolation and response interpolation matrix by using the arrangement scheme of the vibration exciter and the sensor obtained in the step 2, multiplying the front part of the unsteady aerodynamic influence coefficient matrix by the response interpolation matrix and then multiplying the rear part by the force interpolation matrix to obtain a frequency domain model of aerodynamic force after the order is reduced;
and 4, step 4: fitting the frequency domain model obtained in the step 3 into a time domain by using a minimum state method to obtain a time domain model of aerodynamic force;
and 5: installing according to the vibration exciter and sensor arrangement scheme obtained in the step 2, and connecting the subsystems; each subsystem comprises: the system comprises a semi-physical simulation system, a power amplifier, a vibration exciter, a force sensor and a structure to be tested, wherein a signal source in the semi-physical simulation system generates a voltage signal, the voltage signal is used for driving the power amplifier to amplify power and driving the vibration exciter to apply excitation to the structure to be tested, the force sensor arranged between the vibration exciter and the structure to be tested is used for recording the amplitude of excitation force, and a data acquisition system is used for acquiring the signal source signal and the excitation force signal for model identification and controller design;
step 6: applying an excitation signal to the power amplifier through the semi-physical simulation system (2), testing the response of the vibration exciter on the structure to be tested, and designing a controller;
and 7: and setting the flight state of the structure to be tested in the aerodynamic force reconstruction module, downloading the model to a semi-physical simulation system, testing, recording a displacement response signal of the structure (1) to be tested, and comparing the displacement response signal with an analysis result.
2. The method of claim 1, wherein the sensors are acceleration and displacement sensors, and the velocity signal is obtained indirectly by acceleration integration or displacement differentiation.
3. The method of claim 1, wherein the flight conditions in step 7 include altitude and mach number.
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| CN113310695B (en) * | 2021-05-28 | 2023-01-31 | 中国商用飞机有限责任公司 | Aircraft engine windmill load ground simulation method and system |
| CN114818550B (en) * | 2022-06-30 | 2022-09-13 | 中国飞机强度研究所 | Time-varying aerodynamic load ground equivalent simulation method in airplane vibration test |
| CN114970402B (en) * | 2022-06-30 | 2024-12-03 | 中国飞机强度研究所 | Aerodynamic load simulation calculation system and method in aircraft ground vibration test |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101793591A (en) * | 2010-03-26 | 2010-08-04 | 北京航空航天大学 | Aircraft aero-servo-elasticity ground simulating test system |
| CN103364170A (en) * | 2013-07-05 | 2013-10-23 | 北京航空航天大学 | Ground simulation predicting method and system for aeroelasticity stability |
| CN103592091A (en) * | 2013-11-14 | 2014-02-19 | 北京航空航天大学 | System and method for flutter ground test of aircraft control surface |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101793591A (en) * | 2010-03-26 | 2010-08-04 | 北京航空航天大学 | Aircraft aero-servo-elasticity ground simulating test system |
| CN103364170A (en) * | 2013-07-05 | 2013-10-23 | 北京航空航天大学 | Ground simulation predicting method and system for aeroelasticity stability |
| CN103592091A (en) * | 2013-11-14 | 2014-02-19 | 北京航空航天大学 | System and method for flutter ground test of aircraft control surface |
Non-Patent Citations (4)
| Title |
|---|
| 地面颤振模拟试验中的非定常气动力模拟;许云涛等;《航空学报》;20121125;第33卷(第11期);第1947-1957页 * |
| 宋巧治等.平板翼颤振地面模拟试验机理研究.《结构强度研究》.2016,(第1期),第1-7页. * |
| 带操纵面机翼气动弹性地面试验仿真系统中的气动力降阶方法;胡巍等;《西北工业大学学报》;20131031;第31卷(第5期);第810-815页 * |
| 平板翼颤振地面模拟试验机理研究;宋巧治等;《结构强度研究》;20161231(第1期);第1-7页 * |
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