CN105547618A - Modal analysis method based on folding control surface rudder system - Google Patents
Modal analysis method based on folding control surface rudder system Download PDFInfo
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- CN105547618A CN105547618A CN201510882194.7A CN201510882194A CN105547618A CN 105547618 A CN105547618 A CN 105547618A CN 201510882194 A CN201510882194 A CN 201510882194A CN 105547618 A CN105547618 A CN 105547618A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
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Abstract
The invention discloses a modal analysis method based on a folding control surface rudder system. The method comprises following steps: a modal test and analysis system comprising a vibration exciter support (1), a vibration exciter (2), a ground rack (3), a rudder piece (4), a force sensor (5), a rudder room (6), an accelerometer (7), a portable computer (8), a data acquisition device (10), a steering engine (11), a power amplifier (12), and a blower fan (13) is constructed; modal parameters of the rudder system are pre-estimated by a modal analysis module (9); the rubber system is stimulated by the vibration exciter (2), test data is collected by the data acquisition device (10), test results are interpreted by the modal analysis module (9), and the modal purity is verified by the modal analysis module (9). By use of the modal analysis method, the main modal of the rudder system can be accurately recognized and bending modals can be distinguished, modal parameters such as natural frequency, damping ratio, and vibration mode which describe dynamic characteristics of a structural system are determined, and modal recognition reliability and accuracy are increased.
Description
Technical field
The present invention relates to a kind of modal analysis method of guided missile rudder system, particularly a kind of modal analysis method based on folding rudder face rudder system.
Background technology
Current rudder system model analysis mainly adopts theoretical analysis method and experimental test procedures.Theoretical analysis method is generally carry out finite element modeling, stress and strain model and numerical solution, thus obtains natural frequency and the principal mode of structure.Experimental test procedures uses dynamic test to set up the physical parameter model of structure, is foundation, obtains the inherent characteristic of system with measured data.Theoretical analysis method modeling speed is fast, calculates easy, but not easily simulates due to driving-chain gap, boundary condition etc., causes result likely to depart from reality.Modal Experimental Analysis method carries out on-the-spot test for material object, and the modal parameter of thus trying to achieve extremely meets actual conditions in kind, but conventional test analytical approach is likely lost the primary modal of system or caused result decision errors because the vibration shape is not obvious.
Summary of the invention
The object of the invention is to provide a kind of modal analysis method based on folding rudder face rudder system, solves the problem that in rudder system model analysis, master mode is easily lost and judged by accident.
Based on a modal analysis method for folding rudder face rudder system, its concrete steps are:
The first step builds Modal testing and analysis system
Modal testing and analysis system comprises: exciter support, vibrator, track, rudder sheet, force snesor, rudder stock, accelerometer, portable computer, data collector, steering wheel, power amplifier and blower fan.Model analysis module is run on a portable computer, and model analysis module is used for carrying out mode preanalysis to rudder system and processing the data of data collector collection and verify.
Exciter support and rudder stock are separately fixed in track, rudder sheet is fixed on the output shaft of steering wheel, force snesor and accelerometer stick on rudder sheet, vibrator is fixed on exciter support, exciting rod and the force snesor of vibrator are fixed, and the thermovent of vibrator and the draft tube of blower fan are fixed by socket.
Portable computer and data collector are bi-directionally connected, the output terminal of data collector is connected with the input end of power amplifier, the output terminal of power amplifier is connected with the input end of vibrator, and the output terminal of force snesor is connected with the input end of data collector with the output terminal of accelerometer.
The modal parameter of second step model analysis module anticipation rudder system
Model analysis module sets up the finite element three-dimensional model of rudder system, carry out stress and strain model, and according to the boundary condition of the aerodynamic conditions initialization system model under missile flight state, boundary conditions is set to fixed constraint by bottom rudder system, rudder sheet has rotary freedom, according to finite element modal analysis result, read rudder system natural mode of vibration frequency and the vibration shape, natural mode of vibration frequency provides reference for the setting of test frequency scope, natural frequency is included within test frequency scope, whether Mode Shape test sensors is arranged reasonable, in the node avoiding the rudder sheet vibration shape when sensor adheres to.
3rd step vibrator excitation rudder system
Power amplifier, according to the exciting force parameter of portable computer, controls exciting force and the excited frequency of vibrator, and rudder system produces vibration after being subject to dynamic excitation, and blower fan dispels the heat to vibrator.
4th step data harvester collecting test data
After rudder system generation flutter, data collector is by being attached to force snesor and the accelerometer on rudder system surface, and gather exciting force size and rudder sheet vibration acceleration signal, the test data collected is uploaded to model analysis module by data collector.
6th step model analysis module interpretation test result
Data collector collecting test data also obtain rudder system frequency response function, by model analysis module analysis rudder system dynamic perfromance, find out single order torsion mode, obtain natural mode of vibration and the frequency of rudder system.
7th step model analysis module verification modal purity
Phase differential between model analysis module determination portable computer input signal and output signal and nondimensional indicator function InvMIF, when rudder system issues raw phase resonance in the excitation of certain first natural frequency, the imaginary part of rudder system frequency response function reaches maximal value, real part is zero, phase differential between input accumulation signal and output response signal is 90 °, and now, InvMIF functional value is 1, InvMIF functional value more close to 1, then under this rank natural frequency to survey modal purity higher.
Modal analysis method of the present invention can accurately identify rudder system master mode and distinguish bending mode, determines the modal parameters such as the natural frequency of description scheme system dynamic characteristic, damping ratio and the vibration shape, improves modal identification fiduciary level and accuracy.
Accompanying drawing explanation
Modal testing and analysis system mechanics schematic diagram described in a kind of modal analysis method based on folding rudder face rudder system of Fig. 1;
Modal testing and analysis system circuit diagram described in a kind of modal analysis method based on folding rudder face rudder system of Fig. 2.
1. exciter support 2. vibrator 3. track 4. rudder sheet 5. force snesor 6. rudder stock 7. accelerometer 8. portable computer 9. model analysis module 10. data collector 11. steering wheel 12. power amplifier 13. blower fan.
Embodiment
Based on a modal analysis method for folding rudder face rudder system, its concrete steps are:
The first step builds Modal testing and analysis system
Modal testing and analysis system comprises: exciter support 1, vibrator 2, track 3, rudder sheet 4, force snesor 5, rudder stock 6, accelerometer 7, portable computer 8, data collector 10, steering wheel 11, power amplifier 12 and blower fan 13.Model analysis module 9 operates on portable computer 8, and model analysis module 9 is for carrying out mode preanalysis and processing the data that data collector 10 gathers and verify to rudder system.
Exciter support 1 and rudder stock 6 are separately fixed in track 3, rudder sheet 4 is fixed on the output shaft of steering wheel 11, force snesor 5 and accelerometer 7 stick on rudder sheet 4, vibrator 2 is fixed on exciter support 1, exciting rod and the force snesor 5 of vibrator 2 are fixed, and the thermovent of vibrator 2 and the draft tube of blower fan 13 are fixed by socket.
Portable computer 8 and data collector 10 are bi-directionally connected, the output terminal of data collector 10 is connected with the input end of power amplifier 12, the output terminal of power amplifier 12 is connected with the input end of vibrator 2, and the output terminal of force snesor 5 is connected with the input end of data collector 10 with the output terminal of accelerometer 7.
The modal parameter of second step model analysis module 9 anticipation rudder system
Model analysis module 9 sets up the finite element three-dimensional model of rudder system, carry out stress and strain model, and according to the boundary condition of the aerodynamic conditions initialization system model under missile flight state, boundary conditions is set to fixed constraint by bottom rudder system, rudder sheet 4 has rotary freedom, according to finite element modal analysis result, read rudder system natural mode of vibration frequency and the vibration shape, natural mode of vibration frequency provides reference for the setting of test frequency scope, natural frequency is included within test frequency scope, whether Mode Shape test sensors is arranged reasonable, in the node avoiding rudder sheet 4 vibration shape when sensor adheres to.
3rd step vibrator 2 encourages rudder system
Power amplifier 12, according to the exciting force parameter of portable computer 8, controls exciting force and the excited frequency of vibrator 2, and rudder system produces vibration after being subject to dynamic excitation, and blower fan 13 dispels the heat to vibrator 2.
4th step data harvester 10 collecting test data
After rudder system generation flutter, data collector 10 is by being attached to force snesor 5 and the accelerometer 7 on rudder system surface, gather exciting force size and rudder sheet 4 vibration acceleration signal, the test data collected is uploaded to model analysis module 9 by data collector 10.
6th step model analysis module 9 interpretation test result
Data collector 10 collecting test data also obtain rudder system frequency response function, analyze rudder system dynamic perfromance, find out single order torsion mode by model analysis module 9, obtain natural mode of vibration and the frequency of rudder system.
7th step model analysis module 9 verifies modal purity
Model analysis module 9 determine portable computer 8 input signal and output signal between phase differential and nondimensional indicator function InvMIF, when rudder system issues raw phase resonance in the excitation of certain first natural frequency, the imaginary part of rudder system frequency response function reaches maximal value, real part is zero, phase differential between input accumulation signal and output response signal is 90 °, and now, InvMIF functional value is 1, InvMIF functional value more close to 1, then under this rank natural frequency to survey modal purity higher.
Claims (1)
1., based on a modal analysis method for folding rudder face rudder system, it is characterized in that concrete steps are:
The first step builds Modal testing and analysis system
Modal testing and analysis system comprises: exciter support (1), vibrator (2), track (3), rudder sheet (4), force snesor (5), rudder stock (6), accelerometer (7), portable computer (8), data collector (10), steering wheel (11), power amplifier (12) and blower fan (13); Model analysis module (9) operates on portable computer (8), and model analysis module (9) is for carrying out mode preanalysis and processing the data that data collector (10) gathers and verify to rudder system;
Exciter support (1) and rudder stock (6) are separately fixed in track (3), rudder sheet (4) is fixed on the output shaft of steering wheel (11), force snesor (5) and accelerometer (7) stick on rudder sheet (4), vibrator (2) is fixed on exciter support (1), the exciting rod of vibrator (2) and force snesor (5) are fixed, and the thermovent of vibrator (2) and the draft tube of blower fan (13) are fixed by socket;
Portable computer (8) and data collector (10) are bi-directionally connected, the output terminal of data collector (10) is connected with the input end of power amplifier (12), the output terminal of power amplifier (12) is connected with the input end of vibrator (2), and the output terminal of force snesor (5) is connected with the input end of data collector (10) with the output terminal of accelerometer (7);
The modal parameter of second step model analysis module (9) anticipation rudder system
Model analysis module (9) sets up the finite element three-dimensional model of rudder system, carry out stress and strain model, and according to the boundary condition of the aerodynamic conditions initialization system model under missile flight state, boundary conditions is set to fixed constraint by bottom rudder system, rudder sheet (4) has rotary freedom, according to finite element modal analysis result, read rudder system natural mode of vibration frequency and the vibration shape, natural mode of vibration frequency provides reference for the setting of test frequency scope, natural frequency is included within test frequency scope, whether Mode Shape test sensors is arranged reasonable, in the node avoiding rudder sheet (4) vibration shape when sensor adheres to,
3rd step vibrator (2) excitation rudder system
Power amplifier (12), according to the exciting force parameter of portable computer (8), controls exciting force and the excited frequency of vibrator (2), and rudder system produces vibration after being subject to dynamic excitation, and blower fan (13) dispels the heat to vibrator (2);
4th step data harvester (10) collecting test data
After rudder system generation flutter, data collector (10) is by being attached to force snesor (5) and the accelerometer (7) on rudder system surface, gather exciting force size and rudder sheet (4) vibration acceleration signal, the test data collected is uploaded to model analysis module (9) by data collector (10);
6th step model analysis module (9) interpretation test result
Data collector (10) collecting test data also obtain rudder system frequency response function, analyze rudder system dynamic perfromance, find out single order torsion mode, obtain natural mode of vibration and the frequency of rudder system by model analysis module (9);
7th step model analysis module (9) checking modal purity
Model analysis module (9) determine portable computer (8) input signal and output signal between phase differential and nondimensional indicator function InvMIF, when rudder system issues raw phase resonance in the excitation of certain first natural frequency, the imaginary part of rudder system frequency response function reaches maximal value, real part is zero, phase differential between input accumulation signal and output response signal is 90 °, now, InvMIF functional value is 1, InvMIF functional value more close to 1, then under this rank natural frequency to survey modal purity higher.
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107063608A (en) * | 2017-05-22 | 2017-08-18 | 北京强度环境研究所 | A kind of lossless rudder system modal test device |
| CN107727340A (en) * | 2017-08-18 | 2018-02-23 | 上海机电工程研究所 | The elastic vibration mode testing method of rotary missile |
| CN108267285A (en) * | 2018-04-22 | 2018-07-10 | 北京工业大学 | A kind of folded in three wing kinetic characteristics experimental provision using steering engine |
| CN108279109A (en) * | 2017-12-12 | 2018-07-13 | 中国航天空气动力技术研究院 | A kind of transmission exciting device for wing rudder face model |
| CN109238886A (en) * | 2018-09-20 | 2019-01-18 | 王瑞芳 | A kind of airvane rudder core exciting test method |
| CN109911244A (en) * | 2018-11-12 | 2019-06-21 | 中航通飞研究院有限公司 | A kind of large aircraft ground roll-out Analysis of Vibration Characteristic method |
| CN112859592A (en) * | 2020-12-29 | 2021-05-28 | 中国航空工业集团公司西安飞机设计研究所 | Method for controlling structural modal frequency of turboprop aircraft |
| CN113050596A (en) * | 2021-03-12 | 2021-06-29 | 北京强度环境研究所 | Method for accurately acquiring modal parameters of air rudder under random excitation |
| CN113408672A (en) * | 2021-08-19 | 2021-09-17 | 中国科学院力学研究所 | Key parameter identification method for aircraft modal test |
| CN113566657A (en) * | 2021-07-30 | 2021-10-29 | 北京机械设备研究所 | On-missile intelligent vibration control electric steering engine and control method |
| CN114235956A (en) * | 2021-12-16 | 2022-03-25 | 苏州智科源测控科技有限公司 | Automatic phase control compensation equipment and method for modal vibration exciter |
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Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107063608A (en) * | 2017-05-22 | 2017-08-18 | 北京强度环境研究所 | A kind of lossless rudder system modal test device |
| CN107727340A (en) * | 2017-08-18 | 2018-02-23 | 上海机电工程研究所 | The elastic vibration mode testing method of rotary missile |
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| CN108279109B (en) * | 2017-12-12 | 2019-12-20 | 中国航天空气动力技术研究院 | Transmission excitation device for wing rudder surface model |
| CN108267285A (en) * | 2018-04-22 | 2018-07-10 | 北京工业大学 | A kind of folded in three wing kinetic characteristics experimental provision using steering engine |
| CN109238886A (en) * | 2018-09-20 | 2019-01-18 | 王瑞芳 | A kind of airvane rudder core exciting test method |
| CN109911244A (en) * | 2018-11-12 | 2019-06-21 | 中航通飞研究院有限公司 | A kind of large aircraft ground roll-out Analysis of Vibration Characteristic method |
| CN112859592A (en) * | 2020-12-29 | 2021-05-28 | 中国航空工业集团公司西安飞机设计研究所 | Method for controlling structural modal frequency of turboprop aircraft |
| CN112859592B (en) * | 2020-12-29 | 2022-08-09 | 中国航空工业集团公司西安飞机设计研究所 | Method for controlling structural modal frequency of turboprop aircraft |
| CN113050596A (en) * | 2021-03-12 | 2021-06-29 | 北京强度环境研究所 | Method for accurately acquiring modal parameters of air rudder under random excitation |
| CN113566657A (en) * | 2021-07-30 | 2021-10-29 | 北京机械设备研究所 | On-missile intelligent vibration control electric steering engine and control method |
| CN113566657B (en) * | 2021-07-30 | 2022-11-01 | 北京机械设备研究所 | Missile-borne intelligent vibration control electric steering engine and control method |
| CN113408672A (en) * | 2021-08-19 | 2021-09-17 | 中国科学院力学研究所 | Key parameter identification method for aircraft modal test |
| CN114235956A (en) * | 2021-12-16 | 2022-03-25 | 苏州智科源测控科技有限公司 | Automatic phase control compensation equipment and method for modal vibration exciter |
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