CN109738144A - A kind of prominent wind response ground simulation experiment method - Google Patents
A kind of prominent wind response ground simulation experiment method Download PDFInfo
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- CN109738144A CN109738144A CN201811286428.1A CN201811286428A CN109738144A CN 109738144 A CN109738144 A CN 109738144A CN 201811286428 A CN201811286428 A CN 201811286428A CN 109738144 A CN109738144 A CN 109738144A
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Abstract
The invention discloses a kind of prominent wind to respond ground simulation experiment method, by on aircaft configuration placement sensor to test the response signal of structure to be tested, unsteady aerodynamic force caused by structural vibration is calculated by aerodynamics evaluation module using the response signal of structure to be tested, it introduces prominent wind and motivates model, the excitation of prominent wind is superimposed with caused unsteady aerodynamic force is vibrated, it is applied in structure to be tested by vibration excitor, for the accurate load for guaranteeing aerodynamic force, closed-loop control is carried out to the power output of vibration excitor, pass through the test condition of given test, the dynamic respond signal of interrecord structure is the response under prominent wind excitation.Test is not limited by structure size to be tested, can be carried out in actual airplane structure, compared to Finite element analysis results, the test result confidence level is higher；The test can be arranged on a small quantity after Ground Vibration Test and sensor arrangement after directly carry out, trystate adjusting can be directly arranged in software, and test operation is easy, can shorten the test period.
Description
Technical field
This method belongs to aeroelastic effect test field, in particular to a kind of prominent wind responds ground simulation experiment method, mainly
The ground simulation and test that prominent wind for aircaft configuration responds.
Background technique
Prominent wind response is response of the aircaft configuration in air turbulence effect lower body, since prominent wind response is for ride comfort
Property have an important influence, therefore prominent wind response analysis and verifying are a necessary links in Ci vil Aircraft Design type-approval process.For
Civil aircraft structures are designed with the sound for slowing down control, needing to aircaft configuration under wind load action of dashing forward of optimization and prominent wind
It should be assessed, the main means used in current engineering have simulation analysis and two kinds of wind tunnel test, and commonly used in pneumatic
Since air turbulence experimental condition is uncontrollable, test is difficult to carry out the flight test of elasticity verifying.Finite element analysis has cost
Advantage low, the period is short, but since model and actual airplane structure have differences, and can not consider the non-thread of aircaft configuration
Property etc. factors influence, cause analysis error it is larger；Wind tunnel model aerodynamic simulation precision is higher, but due to scale model
It is had differences with actual airplane structure, there is some difference with truth for test, while wind tunnel test is costly, processing
The period of model is longer.In view of the deficiency of above-mentioned means, a kind of prominent wind project of the aircaft configuration based on Ground Vibration Test is proposed
Ground simulation experiment method simulates the unsteady aerodynamic pressure distribution that aircaft configuration is subject to by the concentrated force of vibration excitor, can be with needle
Experimental test is carried out to actual airplane structure, the confidence level of test result is higher.
Summary of the invention
Goal of the invention
It is an object of the invention to propose a kind of prominent wind response ground simulation experiment method, to improve under prominent wind load action
Aircaft configuration response precision of prediction, while reduce cost, shorten predetermined period, thus for civil aircraft structures protrusion-dispelling wind design with
And prominent wind load slow down control design case provide before to data guidance.
Inventive technique solution
In order to achieve the above-mentioned object of the invention, the present invention uses following technical solutions:
A kind of prominent wind responds ground simulation experiment method, by structure to be tested placement sensor it is to be tested to test
The response signal of structure calculates structural vibration to be tested by aerodynamic force reconstructed module using the response signal of structure to be tested and draws
The unsteady aerodynamic force risen, the prominent wind of introducing motivate model, and the excitation of prominent wind is superimposed with caused unsteady aerodynamic force is vibrated, is passed through
Vibration excitor is applied in structure to be tested, for the accurate load for guaranteeing aerodynamic force, carries out closed-loop control to the power output of vibration excitor,
By the test condition of given test, the dynamic respond signal for recording structure to be tested is the response dashed forward under wind excitation.
Preferably, the sensor uses acceleration and displacement sensor, and speed signal passes through integrated acceleration or displacement
Differential obtains indirectly.
Preferably, a kind of prominent wind of the invention responds ground simulation experiment method, includes the following steps: step 1: for
Structure is tested, carries out prominent wind response analysis using finite element method, obtains the prominent wind response under basic flight reference and excitation
Analyze result；Step 2: using the result of step 1 as the objective function of optimization, optimized variable is the position of vibration excitor and sensor
And quantity, it is optimized using genetic algorithm, obtains the arrangement of optimal vibration excitor and sensor；Step 3: utilizing step
The arrangement of 2 vibration excitors obtained and sensor carries out depression of order processing to power interpolation and response interpolating matrix, by unsteady gas
Multiply power interpolating matrix after multiplying response interpolating matrix before dynamic effect system matrix, obtains the frequency-domain model of aerodynamic force after depression of order；Step
4: being fitted in time domain using the frequency-domain model that minimum state method obtains step 3, obtain the Model in Time Domain of aerodynamic force；Step 5:
The vibration excitor and sensor positioning scheme obtained according to step 2 is installed, and is coupled to each subsystem；Step 6: passing through half
Matter simulating system applies pumping signal to power amplifier, and test vibration excitor acts on the response in structure to be tested, and sets
Controller is counted, the design method of controller is based on H referring to Chinese patent CN201310303375.0∞The excitation of robust control
Force control system design method；Step 7: the state of flight that structure to be tested is arranged in aerodynamic force reconstructed module downloads model
It to semi-matter simulating system and is tested, records the dynamic respond signal of structure to be tested, compared with analysis result.
Preferably, state of flight includes height, Mach number in step 7.
Preferably, each subsystem includes: semi-matter simulating system (hardware realization for signal source), power in step 5
Amplifier, vibration excitor, force snesor, structure to be tested generate voltage signal, benefit by the signal source in semi-matter simulating system
Power amplification is carried out with the voltage signal driving power amplifier, driving vibration excitor applies excitation to structure to be tested, utilizes cloth
The amplitude for setting the force snesor record exciting force between vibration excitor and structure to be tested, acquires signal using data collection system
Source signal and excitation force signal are used for Model Distinguish and controller design.
Advantages of the present invention
The present invention has the advantages that
Test is not limited by structure size to be tested, can be carried out in actual airplane structure, compared to finite element analysis
As a result the test result confidence level is higher；It tests the equipment used and vibration test is almost the same, it is only necessary to increase a small amount of sensor
And HWIL simulation equipment, compared to wind tunnel test, cost is relatively low for the test；The test can carry out after Ground Vibration Test
It is directly carried out after a small amount of setting and sensor arrangement, trystate adjusting can be directly arranged in software, test operation letter
Just, the test period can be shortened.
Detailed description of the invention
Fig. 1 is the functional block diagram that a kind of prominent wind of the invention responds ground simulation experiment method.
Fig. 2 is the plate wing structure scale diagrams as structure to be tested.
Fig. 3 is excitation point and pick-up point position optimum results schematic diagram.
Fig. 4 is the wing gas bullet system emulation figure of prominent wind excitation.
Fig. 5 is the test point response results comparison diagram of depression of order front and back structure to be tested.
Fig. 6 is simulation result schematic diagram.
Fig. 7 is experimental test result schematic diagram.
In figure: 1- structure to be tested, 2- semi-matter simulating system, 3- aerodynamic force reconstructed module, the control of 4-MIMO exciting force
Module, 5- sensor, 6- power amplifier, 7- vibration excitor, 8- force snesor.
Specific embodiment
In conjunction with summary of the invention general introduction and attached drawing, the specific embodiment that the present invention will be described in detail.
A kind of prominent wind responds ground simulation experiment method, by structure 1 to be tested placement sensor 5 it is to be measured to test
The response signal for trying structure 1 calculates structural vibration by aerodynamic force reconstructed module 3 using the response signal of structure 1 to be tested and draws
The unsteady aerodynamic force risen, the prominent wind of introducing motivate model, and the excitation of prominent wind is superimposed with caused unsteady aerodynamic force is vibrated, is passed through
Vibration excitor 7 is applied in structure 1 to be tested, for the accurate load for guaranteeing aerodynamic force, carries out closed loop control to the power output of vibration excitor 7
System, by the test condition of given test, the dynamic respond signal of interrecord structure is the response under prominent wind excitation.
The sensor uses acceleration and displacement sensor, and speed signal is indirect by integrated acceleration or displacement differential
It obtains.
A kind of prominent wind response ground simulation experiment method of the invention includes the following steps:
Step 1: being directed to structure to be tested, carry out prominent wind response analysis using finite element method, obtain basic flight reference
With the analysis result of the prominent wind response under excitation；
Step 2: using the result of step 1 as the objective function of optimization, optimized variable is the position of vibration excitor 7 and sensor 5
It sets and quantity, is optimized using genetic algorithm, obtain the arrangement of optimal vibration excitor 7 and sensor 5；
Step 3: the arrangement of the vibration excitor 7 and sensor 5 that are obtained using step 2, to power interpolation and response interpolation square
Battle array carries out depression of order processing, is to multiply power interpolating matrix after multiplying response interpolating matrix before matrix by unsteady aerodynamic force influence, is dropped
The frequency-domain model of aerodynamic force after rank；
Step 4: be fitted in time domain using the frequency-domain model that minimum state method obtains step 3, obtain aerodynamic force when
Domain model；
Step 5: the vibration excitor 7 and 5 arrangement of sensor obtained according to step 2 is installed, and presses Fig. 1 to each subsystem
Coupled；
Step 6: pumping signal being applied to power amplifier 6 by semi-matter simulating system 2, test vibration excitor 7 acts on
Response in structure 1 to be tested, and design controller；
Step 7: model is downloaded to half material object by the state of flight that structure 1 to be tested is arranged in aerodynamic force reconstructed module 3
Analogue system 2 is simultaneously tested, and the dynamic respond signal of structure 1 to be tested is recorded, and is compared with analysis result.State of flight
Including height, Mach number.
Using attached plate wing structure shown in Fig. 2 as structure 1 to be tested, pass through the vibration excitor 7 and sensing of optimum option
The position of device 5 is as shown in Fig. 3, chooses the allocation plan of 4 sets of vibration excitor 7 and 4 set sensors 5, wherein triangle is denoted as exciting
7 position of device, dot are denoted as 5 position of sensor, and sensor 5 uses acceleration transducer and displacement sensor.
Frequency domain aerodynamic reduced order model is established using the allocation plan after above-mentioned optimization, is fitted, is built by minimum state method
The attached simulation model shown in Fig. 4 of Liru, structure 1 to be tested under Aerodynamic Model and Primordial Qi dynamic model after comparison optimization act on
Response, as a result as shown in Fig. 5.Primordial Qi dynamic model acts on Aerodynamic Model after flowering structure response (Fig. 5 solid line) and depression of order
It acts on flowering structure and responds (Fig. 5 dotted line) curve co-insides, model equivalent effect is preferable before and after illustrating depression of order.
The model of loading system is established, while designing controller, by Aerodynamic Model and controller and structure to be tested 1
According to attached drawing 1 logical relation composition ground dash forward wind response test system, including semi-matter simulating system 2, power amplifier 6,
Vibration excitor 7, force snesor 8, structure to be tested 1；Semi-matter simulating system 2 includes aerodynamic force reconstructed module 3 and MIMO exciting force
Control module 4；Sensor 5 is arranged in structure 1 to be tested, and sensor 5 is connected to aerodynamic force reconstructed module 3, aerodynamic force reconstruct
Module 3 is connected to MIMO exciting force control module 4, and MIMO exciting force control module 4 is connected to power amplifier 6, power amplification
Device 6 is connected to vibration excitor 7, and force snesor 8 is respectively connected to MIMO exciting force control module 4, vibration excitor 7 and structure to be tested 1；
Voltage signal is generated by the signal source in semi-matter simulating system 2, carries out function using the voltage signal driving power amplifier 6
Rate amplification, driving vibration excitor 7 applies excitation to structure 1 to be tested, using being arranged between vibration excitor 7 and structure to be tested 1
Force snesor 8 records the amplitude of exciting force, is used for model using data collection system acquisition signal source signal and excitation force signal
Identification and controller design.By setting test mode parameter, tested, the test point in the structure to be tested 1 of acquisition
Response results are shown in Fig. 7；Simulation result is shown in Fig. 6.By emulating and the structural response under former Aerodynamic force action it can be seen from test result
The response curve match result of test point is preferable after (Fig. 6 and Fig. 7 solid line) and depression of order, and the two relative error is less than 10%, in work
In journey tolerance interval.
The present invention allows to simulate using the discrete force of a small amount of vibration excitor 7 and sensor 5 by the depression of order of aerodynamic force
Distributed unsteady aerodynamic force；Frequency domain aerodynamic force is fitted to time domain using minimum state method, to obtain emulation and test
Available aerodynamics evaluation model.By combining two above step, can fly in the sky in ground device prominent
Wind environment, to realize the test of the prominent wind response in ground.
By introducing System Discrimination and robust control, guarantee that vibration excitor can be according to the correct load of instruction, so as to protect
The precision demonstrate,proving the simulation precision of aerodynamic force and finally testing.
Claims (5)
1. a kind of prominent wind responds ground simulation experiment method, which is characterized in that by structure to be tested placement sensor with
The response signal for testing structure to be tested calculates structure by aerodynamic force reconstructed module using the response signal of structure to be tested and shakes
Unsteady aerodynamic force caused by dynamic, the prominent wind of introducing motivate model, and the excitation of prominent wind is superimposed with caused unsteady aerodynamic force is vibrated,
It is applied in structure to be tested by vibration excitor, for the accurate load for guaranteeing aerodynamic force, closed loop is carried out to the power output of vibration excitor
Control, by the test condition of given test, the dynamic respond signal of interrecord structure is the response under prominent wind excitation.
2. a kind of prominent wind as described in claim 1 responds ground simulation experiment method, which is characterized in that the sensor uses
Acceleration and displacement sensor, speed signal are obtained indirectly by integrated acceleration or displacement differential.
3. a kind of prominent wind as described in claim 1 responds ground simulation experiment method, which comprises the steps of:
Step 1: being directed to structure to be tested, carry out prominent wind response analysis using finite element method, obtain basic flight reference and swash
The analysis result of prominent wind response under encouraging；
Step 2: using the result of step 1 as the objective function of optimization, optimized variable is the position sum number of vibration excitor and sensor
Amount, is optimized using genetic algorithm, obtains the arrangement of optimal vibration excitor and sensor；
Step 3: the arrangement of the vibration excitor and sensor that are obtained using step 2 carries out power interpolation and response interpolating matrix
Unsteady aerodynamic force influence is to multiply power interpolating matrix after multiplying response interpolating matrix before matrix, obtains gas after depression of order by depression of order processing
The frequency-domain model of power；
Step 4: being fitted in time domain using the frequency-domain model that minimum state method obtains step 3, obtain the time-domain mode of aerodynamic force
Type；
Step 5: the vibration excitor and sensor positioning scheme obtained according to step 2 is installed, and is coupled to each subsystem；
Step 6: pumping signal being applied to power amplifier by semi-matter simulating system 2, test vibration excitor acts on to be tested
Response in structure, and design controller；
Step 7: model is downloaded to HWIL simulation system by the state of flight that structure to be tested is arranged in aerodynamics evaluation module
It unites and is tested, record the dynamic respond signal of structure 1 to be tested, compared with analysis result.
4. a kind of prominent wind as claimed in claim 3 responds ground simulation experiment method, which is characterized in that flight shape in step 7
State includes height, Mach number.
5. a kind of prominent wind as claimed in claim 3 responds ground simulation experiment method, which is characterized in that each subsystem in step 5
System includes: semi-matter simulating system, power amplifier, vibration excitor, force snesor, structure to be tested, passes through HWIL simulation system
Signal source in system generates voltage signal, carries out power amplification using the voltage signal driving power amplifier, drives vibration excitor
Apply to structure to be tested and motivate, utilizes the width for the force snesor record exciting force being arranged between vibration excitor and structure to be tested
Value is used for Model Distinguish and controller design using data collection system acquisition signal source signal and excitation force signal.
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| CN201811286428.1A CN109738144B (en) | 2018-10-31 | 2018-10-31 | Gust response ground simulation test method |
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| CN201811286428.1A CN109738144B (en) | 2018-10-31 | 2018-10-31 | Gust response ground simulation test method |
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Cited By (2)
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| CN113310695A (en) * | 2021-05-28 | 2021-08-27 | 中国商用飞机有限责任公司 | Aircraft engine windmill load ground simulation method and system |
| CN114818550A (en) * | 2022-06-30 | 2022-07-29 | 中国飞机强度研究所 | Time-varying aerodynamic load ground equivalent simulation method in airplane vibration test |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113310695A (en) * | 2021-05-28 | 2021-08-27 | 中国商用飞机有限责任公司 | Aircraft engine windmill load ground simulation method and system |
| CN114818550A (en) * | 2022-06-30 | 2022-07-29 | 中国飞机强度研究所 | Time-varying aerodynamic load ground equivalent simulation method in airplane vibration test |
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