CN208860470U - A vibration detection device for non-contact aircraft tail - Google Patents
A vibration detection device for non-contact aircraft tail Download PDFInfo
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- CN208860470U CN208860470U CN201821621395.7U CN201821621395U CN208860470U CN 208860470 U CN208860470 U CN 208860470U CN 201821621395 U CN201821621395 U CN 201821621395U CN 208860470 U CN208860470 U CN 208860470U
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- aircraft tail
- vibration
- detection device
- aircraft
- vibration detection
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Abstract
本实用新型公开了一种非接触式飞机尾翼的振动检测装置，包括飞机尾翼本体部分、激励部分及振动检测部分及控制部分；所述飞机尾翼本体部分包括飞机尾翼结构，所述激励部分包括激振器、信号发生器及功率放大器，所述振动检测部分包括投影仪、加速度计及CCD相机，所述控制部分包括压电陶瓷驱动器、扭转模态驱动器、放大电路及D/A转换器；从而实现对飞机尾翼本体部分振动的测量与控制。
The utility model discloses a vibration detection device for a non-contact aircraft tail, comprising an aircraft tail body part, an excitation part, a vibration detection part and a control part; the aircraft tail body part includes an aircraft tail structure, and the excitation part includes an excitation part. A vibrator, a signal generator and a power amplifier, the vibration detection part includes a projector, an accelerometer and a CCD camera, and the control part includes a piezoelectric ceramic driver, a torsional mode driver, an amplifier circuit and a D/A converter; Realize the measurement and control of the vibration of the aircraft tail body part.
Description
Technical field
The utility model relates to the vibration control fields of aircraft tail, and in particular to a kind of vibration of contactless aircraft tail
Motion detection device.
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.
Utility model content
In order to overcome shortcoming and deficiency of the existing technology, the utility model provides a kind of contactless aircraft tail vibration
Motion detection device.
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 utility model adopts the following technical solution:
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.
The course of work of the invention:
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.
The utility model has the beneficial effects that
(1) the utility model forms multiple incident points, measurement dress in the front of aircraft tail structural model using projector
Multiple incident points in different location can be measured simultaneously by setting, and processing data are greatly to be conducive to reduce error；
(2) the utility model detects aircraft tail structural model using binocular vision system, compared to existing skill
Art, it is advantageous that: do not have to directly contact testee, so the dynamic property of testee is not influenced；System features in convenient,
Structure is uncomplicated；More incident points are detected simultaneously, can reduce experimental error, improve measurement accuracy etc.；
(3) the utility model uses vibration excitor as excitation input equipment, with bandwidth, efficient, energy conservation and distortion
The advantages that small is spent, 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 utility model embodiment；
Fig. 2 is the incident point distribution map of aircraft tail in the utility model embodiment；
Fig. 3 is the main view of the vibration detection device of the contactless aircraft tail of the utility model embodiment；
Fig. 4 is the top view of the vibration detection device of the contactless aircraft tail of the utility model embodiment；
Fig. 5 is the left view of the vibration detection device of the contactless aircraft tail of the utility model embodiment.
Specific embodiment
Below with reference to examples and drawings, the utility model is described in further detail, but the reality of the utility model
It is without being limited thereto to apply mode.
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 utility model:
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。
Above-described embodiment is the preferable embodiment of the utility model, but the embodiments of the present invention is not by described
The limitation of embodiment, it is made under other any spiritual essence and principles without departing from the utility model to change, modify, replacing
In generation, simplifies combination, should be equivalent substitute mode, is included within the protection scope of the utility model.
Claims (7)
1. a kind of vibration detection device of contactless aircraft tail, which is characterized in that including aircraft tail body part, excitation
Partially, vibration detecting part and control section；
The aircraft tail body part includes aircraft tail structure, and the aircraft tail structural vertical is fixed on experimental bench,
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 aircraft tail knot
The reverse side of structure, vibration excitor mandril are contacted with the reverse side of aircraft tail structure, and are located at free end, and it is defeated that signal generator generates signal
Enter power amplifier, further vibration excitor is driven 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 meter
Calculation machine, the projector are connect with computer, and 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 amplifies by charge
Device 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 drives
Piezoelectric ceramic actuator and torsion mode driver inhibit the vibration of aircraft tail structure.
2. vibration detection device according to claim 1, which is characterized in that further include camera head and sliding rail, the CCD
Camera is mounted on camera head, and camera head slides on the slide rail.
3. vibration detection device according to claim 1, which is characterized in that the piezoelectric ceramic actuator is by multi-disc piezoelectricity
Potsherd is constituted, and multi-disc piezoelectric ceramic piece is arranged at "-" type.
4. vibration detection device according to claim 1, which is characterized in that the torsion mode driver is by eight piezoelectricity
Piece is driven to constitute, four, every face, and be located at along the geometric dimension middle position of spanwise, two-sided antisymmetry connects and composes torsion
Mode driver.
5. vibration detection device according to claim 1, which is characterized in that subpoint is located at the upper of torsion mode driver
Side.
6. vibration detection device according to claim 1, which is characterized in that the vibration excitor is two, is located at winged
The left and right sides of tail wing structure free end, accelerometer are located at the free end left side edge of aircraft tail structure.
7. vibration detection device according to claim 1-6, which is characterized in that it further include detection platform, it is described
Projector and CCD camera are located at detection platform, and the front of aircraft tail structure is arranged in detection platform.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201821621395.7U CN208860470U (en) | 2018-09-30 | 2018-09-30 | A vibration detection device for non-contact aircraft tail |
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| CN201821621395.7U CN208860470U (en) | 2018-09-30 | 2018-09-30 | A vibration detection device for non-contact aircraft tail |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109186741A (en) * | 2018-09-30 | 2019-01-11 | 华南理工大学 | A kind of vibration detection device and method of contactless aircraft tail |
| CN114878296A (en) * | 2022-04-13 | 2022-08-09 | 重庆大学 | Transparent soil three-dimensional synchronous scanning test device and using method thereof |
-
2018
- 2018-09-30 CN CN201821621395.7U patent/CN208860470U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109186741A (en) * | 2018-09-30 | 2019-01-11 | 华南理工大学 | A kind of vibration detection device and method of contactless aircraft tail |
| CN114878296A (en) * | 2022-04-13 | 2022-08-09 | 重庆大学 | Transparent soil three-dimensional synchronous scanning test device and using method thereof |
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