CN109186741A - A kind of vibration detection device and method of contactless aircraft tail - Google Patents
A kind of vibration detection device and method of contactless aircraft tail Download PDFInfo
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- CN109186741A CN109186741A CN201811157592.2A CN201811157592A CN109186741A CN 109186741 A CN109186741 A CN 109186741A CN 201811157592 A CN201811157592 A CN 201811157592A CN 109186741 A CN109186741 A CN 109186741A
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- aircraft tail
- vibration
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- 238000001514 detection method Methods 0.000 title claims abstract description 45
- 238000000034 method Methods 0.000 title claims abstract description 14
- 239000000919 ceramic Substances 0.000 claims abstract description 22
- 230000005284 excitation Effects 0.000 claims description 5
- 238000005259 measurement Methods 0.000 abstract description 4
- 238000004519 manufacturing process Methods 0.000 description 8
- 239000000463 material Substances 0.000 description 7
- 238000011160 research Methods 0.000 description 6
- 230000008901 benefit Effects 0.000 description 5
- 244000145845 chattering Species 0.000 description 3
- 238000004134 energy conservation Methods 0.000 description 3
- 238000002474 experimental method Methods 0.000 description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- 229910052782 aluminium Inorganic materials 0.000 description 2
- 235000021170 buffet Nutrition 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 230000006378 damage Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000007689 inspection Methods 0.000 description 2
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- 230000003321 amplification Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 238000009960 carding Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
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- 230000000694 effects Effects 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
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- 238000003384 imaging method Methods 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
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- 230000002045 lasting effect Effects 0.000 description 1
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Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01H—MEASUREMENT OF MECHANICAL VIBRATIONS OR ULTRASONIC, SONIC OR INFRASONIC WAVES
- G01H9/00—Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves by using radiation-sensitive means, e.g. optical means
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Measurement Of Mechanical Vibrations Or Ultrasonic Waves (AREA)
Abstract
The invention discloses the vibration detection devices and method of a kind of contactless aircraft tail, including aircraft tail body part, driver unit and vibration detecting part and control section；The aircraft tail body part includes aircraft tail structure, the driver unit includes vibration excitor, signal generator and power amplifier, the vibration detecting part includes projector, accelerometer and CCD camera, and the control section includes piezoelectric ceramic actuator, torsion mode driver, amplifying circuit and D/A converter；To realize the measurement and control vibrated to aircraft tail body part.
Description
Technical field
The present invention relates to the vibration control fields of aircraft tail, and in particular to a kind of vibration inspection of contactless aircraft tail
Survey apparatus and method.
Background technique
Empennage is mounted in a kind of device of airplane tail group, for enhancing stability of the aircraft in flight course.Flying
One of the damage that aircraft tail faces during row is exactly the buffeting of empennage.Aircraft especially fighter plane air-flow in the big angle of attack passes through
That crosses fuselage and wing diffuses to form buffeting.The irregular oscillation for being defined as aircaft configuration caused by turbulent flow is buffeted, in aircraft
The high-intensitive vortex load that will form in flight course, this vortex will increase lift when passing through wing and fuselage, but when it is prominent
The turbulent flow that high-energy can be generated to tail structure when meeting aircraft tail impacts, and impact just forms aircraft tail structure for a long time
It is lasting to buffet.The chattering phenomenon of aircraft tail structure increases the structural stress that aircraft is born in flight course, for fighter plane
For, it also will affect the operation such as aiming, tracking of weapon system, weaken combat performance to a certain extent.It can be seen that buffeting
It is fatal to aircraft especially high-performance fighter aircraft bring harm；For in economic benefit, it is normal that buffeting increases aircraft
Maintenance cost during one's term of military service.Foreign countries are more early to the research starting of aircraft tail chattering phenomenon, detect aircraft using piezoelectric material
The method of empennage vibrational state is commonplace；The country is more rare to the research of aircraft buffeting, and Experiment Result is less, initially more collection
In be aircraft buffeting characteristic theoretical research.The nineteen ninety-five country reports the wind- tunnel investigation of L8 aircraft buffeting, which surveys
The relationship that aircaft configuration is separated with the relationship of buffet margin, the angle of attack with air-flow is tried.Hereafter gradually move towards specific from theoretical research
Experiment.
So far, the vibration detection device in mainstream for the research of aircraft tail chattering phenomenon is mainly using piezoelectric sensing
Device, this contact measurement method, since detection device is directly contacted with measured object, so load effect is certainly existed, thus
Experimental error is introduced, experimental precision is influenced.During the vibration detection of research aircraft empennage, vibration detection link department perceives quilt
The function of object vibrational state is surveyed, so vibration detection device and method have very important importance in selection and implementation.
Summary of the invention
In order to overcome shortcoming and deficiency of the existing technology, the present invention provides a kind of contactless aircraft tail vibration inspection
Survey apparatus and method.
The device uses vibration excitor exciting aircraft tail, and vibration detecting part detects the vibration letter of aircraft tail body part
Computer is sent to after breath, computer sends a signal to vibration control part after respective handling, and the latter is to aircraft tail sheet
Body portion is controlled, to realize the measurement and control vibrated to aircraft tail body part.
The present invention adopts the following technical scheme:
A kind of vibration detection device of contactless aircraft tail, including aircraft tail body part, driver unit, vibration
Detection part and control section；
The aircraft tail body part includes aircraft tail structure, and the aircraft tail structural vertical is fixed on experimental bench
On, fixed one end is known as fixing end, and the other end is free end；
The driver unit includes vibration excitor, signal generator and power amplifier, and the vibration excitor is arranged in airplane tail
The reverse side of wing structure, vibration excitor mandril are contacted with the reverse side of aircraft tail structure, and are located at free end, and signal generator generates letter
Number input power amplifier further drives vibration excitor to evoke aircraft tail structural vibration；
The vibration detecting part includes projector, accelerometer, a pair of of CCD camera, charge amplifier, A/D capture card
And computer, the projector are connect with computer, the front for being projected in aircraft tail structure forms multiple incident points；
The pair of CCD camera is used to detect the vibration information in multiple incident points and is sent to computer；
The accelerometer is mounted on the edge of aircraft tail structure free end, and the signal of accelerometer acquisition passes through charge
Amplifier and A/D capture card input computer；
The control section includes piezoelectric ceramic actuator, torsion mode driver, amplifying circuit and D/A converter；
The piezoelectric ceramic actuator is pasted onto the positive and negative of aircraft tail structure, and close to fixing end；
The torsion mode driver is pasted onto the positive and negative of aircraft tail structure；
The computer handles vibration information to obtain control signal, through D/A converter and amplifying circuit, further
Piezoelectric ceramic actuator and torsion mode driver are driven, the vibration of aircraft tail structure is inhibited.
It further include camera head and sliding rail, the CCD camera is mounted on camera head, and camera head is slided on the slide rail
It is dynamic.
The piezoelectric ceramic actuator is made of multi-disc piezoelectric ceramic piece, and multi-disc piezoelectric ceramic piece is arranged at "-" type.
The torsion mode driver is made of eight piezoelectric driving plates, four, every face, and is located at along the several of spanwise
What size middle position, two-sided antisymmetry connect and compose torsion mode driver.
Subpoint is located at the top of torsion mode driver.
The vibration excitor is two, is located at the left and right sides of aircraft tail structure free end, and accelerometer, which is located at, to fly
The free end left side edge of tail wing structure.
It further include detection platform, the projector and CCD camera are located at detection platform, and detection platform is arranged in aircraft tail
The front of structure.
A kind of method of contactless aircraft tail vibration detection device, includes the following steps:
The first step, signal generator generate signal, drive vibration excitor to evoke aircraft tail structure after power amplifier
Vibration；
Second step, computer control projector output, form multiple incident points in the front of aircraft tail structure；
Third step, the vibration information of a pair of of CCD camera detection subpoint, inputs computer；Accelerometer detects airplane tail
The vibration information of wing structure inputs computer by charge amplifier and A/D capture card；
4th step, computer handle vibration information to obtain control signal, and control signal is by D/A converter and puts
Big circuit amplification rear-guard moves piezoelectric ceramic actuator and torsion mode driver, inhibits the vibration of aircraft tail structure.
Beneficial effects of the present invention:
(1) present invention forms multiple incident points in the front of aircraft tail structural model using projector, and measuring device can
Multiple incident points in different location are measured simultaneously, and processing data are greatly to be conducive to reduce error；
(2) present invention detects aircraft tail structural model using binocular vision system, compared to the prior art,
Advantage is: do not have to directly contact testee, so the dynamic property of testee is not influenced；System features in convenient, structure
It is uncomplicated；More incident points are detected simultaneously, can reduce experimental error, improve measurement accuracy etc.；
(3) present invention uses vibration excitor as excitation input equipment, small with bandwidth, efficient, energy conservation and the distortion factor
The advantages that, the performance of the present apparatus can be effectively improved.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of the vibration detection device of the contactless aircraft tail of the embodiment of the present invention；
Fig. 2 is the incident point distribution map of aircraft tail in the embodiment of the present invention；
Fig. 3 is the main view of the vibration detection device of the contactless aircraft tail of the embodiment of the present invention；
Fig. 4 is the top view of the vibration detection device of the contactless aircraft tail of the embodiment of the present invention；
Fig. 5 is the left view of the vibration detection device of the contactless aircraft tail of the embodiment of the present invention.
Specific embodiment
Below with reference to examples and drawings, the present invention is described in further detail, but embodiments of the present invention are not
It is limited to this.
Embodiment
As Figure 1-Figure 5, a kind of vibration detection device of contactless aircraft tail, including aircraft tail body part
Point, driver unit and vibration detecting part and control section；
The aircraft tail body part includes aircraft tail structure 4, bottom plate 6 and experimental bench 5；The experimental bench is aluminium profiles
Material seat, plays a supportive role, and the bottom plate is two, and two bottom plates are fixed on experimental bench by spiral marking connection, two bottom panel sides
Aircraft tail structure is clamped on experimental bench by spiral marking connection, and it is made to keep vertical state, convenient for detection.
The driver unit includes vibration excitor 2, vibration excitor pedestal 1, signal generator 16 and power amplifier 15, and described two
Platform vibration excitor and vibration excitor pedestal are placed on the reverse side of aircraft tail structure, and specific two vibration excitors are located at aircraft tail structure
The left and right sides of free end, vibration excitor mandril are contacted with the surface of aircraft tail structure, and signal generator accesses after generating signal
Power amplifier, then vibration excitor evokes aircraft tail structural vibration.
The vibration detecting part includes projector 12, accelerometer 3 and binocular vision detection system, the binocular vision
Detection system and projector are arranged in detection platform 13, and the detection platform is aluminum profile seat, are used to support vibration detection
Part.
Computer control projector makes the front of aircraft tail structure form multiple subpoints, to examine to binocular vision system
It surveys.
The binocular vision detection system includes that a pair of of CCD camera 11, camera head 10 and sliding rail 9 are constituted, a pair of of CCD phase
Machine is mounted on camera head, and the knob and ball adapter for adjusting camera head can realize the function of fine tuning camera shooting angle
Can, camera head is installed on the slide rail, and the holder that moves on the slide rail just can change the camera site of camera.
CCD camera shoots the vibration information of multiple subpoints and is sent to computer.
The accelerometer 3 is mounted on the top edge of aircraft tail structure free end, and the signal of accelerometer acquisition passes through
Charge amplifier 20 amplifies, and A/D capture card 19 is transferred in computer 18 after acquiring；By repeatedly experiment can be counted accurately repeatedly
Calculate the vibrational state for obtaining aircraft tail body part；
The control section includes piezoelectric ceramic actuator 8, torsion mode driver 7, amplifying circuit 14 and D/A converter
17；
Piezoelectric ceramic actuator is made of multi-disc piezoelectric ceramic piece, front and reverse side positioned at aircraft tail structure, at
"-" type arrangement, positioned at the fixing end of aircraft tail structure.
Multiple torsion mode drivers are mounted in the middle part of the aircraft tail body structure surface, multiple torsion mode drivers are at one
Font arrangement, between subpoint and piezoelectric ceramic actuator.
Computer handles vibration information to obtain control signal, through D/A converter and amplifying circuit, further drives
Piezoelectric ceramic actuator and torsion mode driver, further suppress the vibration of aircraft tail structure.
The torsion mode driver is made of eight piezoelectric driving plates, four, every face, and is located at along the several of spanwise
What size middle position, two-sided antisymmetry connect and compose torsion mode driver.
Use vibration excitor as excitation input equipment, has many advantages, such as that bandwidth, efficient, energy conservation and the distortion factor are small, energy
Effectively improve the performance of the present apparatus.
The course of work of the invention:
Signal generator generates signal, and vibration excitor is driven to evoke the vibration of aircraft tail structure after power amplifier；
Computer controls projector output, forms multiple incident points in the front of aircraft tail structure；
The vibration information of a pair of of CCD camera detection subpoint, inputs computer；Accelerometer detects aircraft tail structure
Vibration information inputs computer by charge amplifier and A/D capture card；
Computer handles vibration information to obtain control signal, and control signal passes through D/A converter and amplifying circuit
Amplify rear-guard and move piezoelectric ceramic actuator and torsion mode driver, inhibits the vibration of aircraft tail structure.
In vibration processes, the binocular vision system detection of a pair of of CCD camera composition flies the aircraft tail structural model
The vibration information of tail wing structure model；The accelerometer detection vibration information is simultaneously to compare.Compared to existing empennage
Vibration detection mode of the structure based on piezoelectric transducer, it is advantageous that: the binocular vision detection mode based on more incident points, no
With testee is directly contacted, so do not influence the dynamic property of testee；System features in convenient, structure are uncomplicated；It is throw more
Exit point detects simultaneously, can reduce experimental error, improves measurement accuracy etc..
In the present embodiment, a length of 288mm in measurand aircraft tail structural model top, following a length of 720mm, it is a height of
460mm, with a thickness of 1mm, material selection aluminium alloy, density of material 2770kg/m3, Poisson's ratio 0.31, elasticity modulus is
193GPa。
Vibration excitor selects the HEV series vibration excitor of Nanjing Fo Neng Scientific and Technical Industry Co., Ltd production, the series excitation element
Product is small, light-weight.The vibration excitor of model HEV-50 is selected, maximum exciting force is 50N, and bandwidth range is 0~3000Hz, most
Large amplitude ± 5mm has many advantages, such as that efficient, energy conservation and the distortion factor are small.
Torsion mode driver length is 60mm, width 60mm, with a thickness of 0.5mm, material selection PZT-BM500 type；
Piezoelectric ceramic actuator length is 30mm, width 10mm, and with a thickness of 0.5mm, material type selects PZT-5H, and dielectric constant is
3200, piezoelectric charge coefficient 640pC/N, voltage constant -9.3 × 10-3V·m/N。
D/A converter selects the model ISL5857 type high-speed d/a converter of Intersil company production, resolution ratio
It is 12, maximum conversion ratio is 260MSPS, and voltage 3.3V, temperature range is -40 DEG C~85 DEG C；A/D capture card is selected
ISLA222S12 type speedy carding process ADC, resolution ratio be 12, maximum conversion ratio position 125MSPS, temperature range be -40 DEG C~
85℃。
Projector select Sony production model VPL-EX433 projector, resolution ratio be 1024 ×
768dpi；CCD camera selects the high speed camera of the equal electron rich Science and Technology Ltd. production in Shanghai, model FASTCAM Mini
WX100/WX50, image resolution ratio are 2048 × 2048 pixels, frame rate 1080fps；Camera lens selects Computar company raw
The industrial lens of production, model M1614-MP, lens focus 16mm, maximum imaging size are 8.8mm × 6.6mm, resolution ratio
For 100lpm, interface type is C- interface；Camera and camera lens gross weight 1.5kg.Camera head selects the special of Fei Mansi company production
With T1 spherical pan head, maximum can bear the camera of 8kg weight, be used to verify the levelness of platform equipped with level meter thereon；Sliding rail
The model Famous F8 PRO photography sliding rail of Fei Mansi company production is selected, sliding rail material is carbon fiber, light-weight, anti-tensile
Intensity is high, and gliding smoothing is smooth.CCD camera is mounted on holder, and the knob and ball adapter for adjusting holder can be realized micro-
The function of phase modifier shooting angle；Holder is installed on the slide rail, and mobile holder just can change the camera site of CCD camera.
Computer selects the IPC610 cabinet of Taiwan Advantech company production, PCA-6006 mainboard, Pentium IV
2.4G Intel CPU。
The above embodiment is a preferred embodiment of the present invention, but embodiments of the present invention are not by the embodiment
Limitation, other any changes, modifications, substitutions, combinations, simplifications made without departing from the spirit and principles of the present invention,
It should be equivalent substitute mode, be included within the scope of the present invention.
Claims (8)
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110053770A (en) * | 2019-05-29 | 2019-07-26 | 华南理工大学 | A kind of quadrotor wing flutter detection control apparatus and method based on multisensor |
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Application publication date: 20190111 |