CN108341073A - Airplane flutter hot test image measurement method - Google Patents
Airplane flutter hot test image measurement method Download PDFInfo
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- CN108341073A CN108341073A CN201810172977.XA CN201810172977A CN108341073A CN 108341073 A CN108341073 A CN 108341073A CN 201810172977 A CN201810172977 A CN 201810172977A CN 108341073 A CN108341073 A CN 108341073A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G7/00—Simulating cosmonautic conditions, e.g. for conditioning crews
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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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- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
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- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
In order to overcome the problems, such as that the prior art can not determine climax velocity of sound airplane flutter characteristic in the case of a high temperature,The present invention provides airplane flutter hot test image measurement methods,This method respectively installs two high speed cameras and infrared or laser side distance meter above and below aircraft wing,And respectively it is horizontally mounted a high speed camera in wing front and back given position,All high speed cameras and infrared or laser side distance meter synchronous control,By being demarcated to each high speed camera group after fixed CCD field angles,Determine that wing is front and back along perspective view boundary and forefront crest line figure,Pixel position of each monitoring point in two high speed cameras above or below wing,Ground experiment wing is heated and carries out exciting,The immediate data obtained according to infrared or laser side distance meter,The position of pixel in high speed camera image,Leading edge perspective view boundary and forefront crest line figure change over time data,The image of wing tip changes over time data,It can estimate flutter of aerofoil parameter with fusion method,Amplitude and frequency,It solves the problems, such as to determine climax velocity of sound airplane flutter characteristic test under high-temperature condition.
Description
Technical field
The present invention relates to the safe ground comprehensive testing methods of the aircraft flights such as civil aircraft, fighter plane, unmanned plane, especially
It is related to airplane flutter hot test image measurement method, belongs to Aero-Space test and information technology field.
Background technology
Flutter is that elastic construction is occurred in uniform air flow by the coupling of air force, elastic force and inertia force
A kind of violent oscillatory motion phenomenon.For aircraft, it can awing be vibrated by after uncertain disturbance.At this point, by
In the effect of air-flow, the elastic construction such as wing, empennage or control surface of aircraft will will produce Additional pneumatic power；As a kind of exciting
Power, Additional pneumatic power will aggravate the vibration of structure.Air attempts to reduce vibration again to the damping force of aircaft configuration simultaneously；In low speed
When flight, since damping force is dominant, the vibration after disturbance fades away；It quivers when reaching the i.e. flutter critical speed of a certain flying speed
It shakes behind boundary, exciting force is dominant, and equilbrium position unstability will generate violent oscillatory motion, aircraft is caused to disintegrate in a few seconds, leads to calamity
Difficulty consequence；It can be said that from that day that aircraft industry is started to walk, flutter is always just the popular problem of aeronautical chart research.
To avoid flutter accident from occurring, new machine development is subjected to flutter test link, and flutter test does not occur with determination
Stabilized flight envelope curve；Carry out Flutter Problem research there are two main classes approach, first, numerical computations：This need to analysis object into
Row mathematical modeling, this process need to introduce certain hypothesis in structure, pneumatic etc., it is difficult to consider the various non-of necessary being
The influence of linear factor and modeling error, analysis result has certain reference value, but may have with actual conditions larger
Deviation；Second is that research technique：Experiment related with flutter mainly has wind tunnel test and flight test.Gas can be considered in wind tunnel test
Dynamic effect, but the method requires subjects carrying out contracting than design, scale model and real structure there are certain difference,
And since the interference aerodynamics of wind tunnel wall and holder are inevitably distorted；Situations such as further for high speed, thermal environment, wind tunnel test mould
Quasi- somewhat expensive and performance difficulty.Flight test can simulation test object completely real operating environments, but the condition tested
It is limited, costly and risk is big, flutter once occurs in the air for aircraft, can disintegrate within several seconds even shorter time, fly
It is substantially zeroed to escape probability almost without Deal with Time by member.
Flutter simulation experiment exactly a kind of flutter that can effectively make up insufficient, the great vitality of traditional experiment in ground is ground
Study carefully method.Ground experiment is using aircraft ground flutter test system as research object, with multidisciplinary design optimization theory research
Core is intimately associated the engineering characteristic of aircraft ground flutter test system, and it is distributed to break through equivalent test modeling method, multiple spot
The key technologies such as Unsteady Aerodynamic Modeling and control, flutter test integrated detection method put forth effort to solve aircraft flutter aerodynamic force mould
The problems such as type difficulty is realized, multi-point exciting power can not accurately control, flutter test result can not play back repeatedly improves master-plan water
It is flat.
Although aeronautical chart, mechanics circle are relatively early to avoiding the problem that flutter is studied, current research or primary
Stage does not form the theory and method system of a system；Existing method lacks aircraft equivalence ground flutter test method
And evaluation；Especially prior art do not provide how under the high-temperature condition more than 1000 degree to aircraft wing flutter into
Row energization is tested, to determine Hypersonic Aircraft buffet characteristic.
Invention content
In order to overcome the problems, such as that the prior art can not determine climax velocity of sound airplane flutter characteristic in the case of a high temperature, the present invention
Airplane flutter hot test image measurement method is provided, this method respectively installs two high speed phases above and below aircraft wing
Machine and infrared or laser side distance meter, and respectively it is horizontally mounted a high speed camera, Suo Yougao in wing front and back given position
Fast camera and infrared or laser side distance meter synchronous control, by being demarcated to each high speed camera group after fixed CCD field angles,
Monitoring point each above or below perspective view boundary and forefront crest line figure, wing is in two high speed phases before and after determining wing
Ground experiment wing is heated and carries out exciting in pixel position in machine, is obtained according to infrared or laser side distance meter direct
In data, high speed camera image the position of pixel, leading edge perspective view boundary and forefront crest line figure change over time data,
The image of wing tip changes over time data, can estimate flutter of aerofoil parameter, amplitude and frequency with fusion method, solve high temperature
In the case of determine climax velocity of sound airplane flutter characteristic test problem.
The present invention solve its technical problem the technical solution adopted is that, a kind of airplane flutter hot test image measurement side
Method, feature include the following steps：
（1）Fastening aircraft fuselage, using airframe shafting, it is that zero degree, the i.e. body shafting longitudinal axis keeps water to make aircraft pitch angle
Flat, each monitoring point of wing upper and lower is in airframe shafting position it is known that being carried out with the high speed camera group of four synchronous controls
Test；One high speed camera group respectively installs two high speed cameras above and below aircraft wing, and two high speed cameras can bow
Depending on or look up wing detection part, by the two high speed camera CCD chips installed above wing same assigned altitute water
Plane and two high speed camera CCD chip centers and centre-to-centre spacing are it is known that the two high speed camera CCD cores installed below wing
Known to horizontal plane and two high speed camera CCD chip centers and centre-to-centre spacing of the piece in same assigned altitute；Meanwhile in aircraft
It is corresponded to the infrared or laser side distance meter of underface installation and high speed camera synchronous control, acquisition right over each monitoring point of wing
Monitoring point position perpendicular to the ground, meanwhile, it is respectively horizontally mounted a high speed camera in wing front and back given position, makes two
A high speed camera center is parallel with the airframe shafting longitudinal axis with wing tip line and can observe that wing is laterally whole, often
The distance signal that the image and infrared or laser side distance meter that a high speed camera obtains obtain can synchronous control, and each high speed phase
Unit all carries out the anti-high wind glass-encapsulated of high temperature resistance；
（2）Each high speed camera group is demarcated after fixed CCD field angles：It is determined by the high speed camera installed in front of wing
Leading edge perspective view boundary and forefront crest line figure, the high speed camera installed by wing rear are determined after wing along perspective view
Boundary and finally along crest line figure, according to right over aircraft wing and the infrared or laser side distance meter of underface installation obtains wing
The infrared or laser testing distance of each monitoring point of upper and lower, meanwhile, according to four installed above and below aircraft wing
High speed camera obtains position of each monitoring point of wing upper and lower above with pixel in the high speed camera image of lower section two, according to
Two high speed camera CCD chip centre-to-centre spacing of the same level installed above or below wing, it may be determined that above wing or
Pixel position of each monitoring point in lower section in two high speed cameras, by taking i-th of wing monitoring point as an example, by two high speed phases
Machine CCD chip center and i-th of wing monitoring location determine a plane, due in two high speed camera CCD chips
The heart is away from position of i-th of wing monitoring point in two high speed camera images in the case of, fixed CCD field angles it is known that i-th of machine
Wing monitoring point and the angle of two high speed camera CCD chip center lines can be determined；
After being demarcated to each high speed camera group, according to the actual flying tests such as Hypersonic Aircraft obtain related data,
Ground experiment wing is heated and carries out exciting so that ground experiment wing generates flutter at a given temperature；
（3）Four high speed camera groups of synchronous control, each frame image of each high speed camera acquisition, infrared or laser side distance meter obtain
Each distance signal taken is time synchronization, each monitoring point of wing upper and lower that infrared or laser side distance meter obtains
Distance changes over time data and can be used for flutter of aerofoil analysis；According to four high speeds installed above and below aircraft wing
Camera obtains position of each monitoring point of wing upper and lower above with pixel in the high speed camera image of lower section two and becomes at any time
Changing data can be used for flutter of aerofoil analysis；Leading edge perspective view side can be obtained by the high speed camera installed in front of wing
Boundary and forefront crest line figure change over time data, and the high speed camera installed by wing rear can obtain after wing along perspective view
Boundary and data finally are changed over time along crest line figure, and the amplitude and frequency of wing tip can be obtained；According to infrared or laser
Position, leading edge perspective view boundary and the forefront crest line of pixel in immediate data that side distance meter obtains, high speed camera image
Figure changes over time data, the image of wing tip changes over time data, can estimate flutter of aerofoil parameter, amplitude with fusion method
And frequency.
The present invention beneficial outcomes be：Two high speed cameras and infrared or laser are respectively installed above and below aircraft wing
Side distance meter, an and high speed camera is respectively horizontally mounted in wing front and back given position, all high speed cameras and it is infrared or
Laser side distance meter synchronous control, by being demarcated to each high speed camera group after fixed CCD field angles, before and after determining wing
Pixel point of each monitoring point in two high speed cameras above or below perspective view boundary and forefront crest line figure, wing
It sets, exciting is heated and carried out to ground experiment wing, according to the immediate data of infrared or laser side distance meter acquisition, high speed camera figure
As in pixel position, leading edge perspective view boundary and forefront crest line figure change over time data, wing tip image at any time
Between delta data, fusion method estimation flutter of aerofoil parameter, amplitude and frequency can be used, solve and determine climax under high-temperature condition
Velocity of sound airplane flutter characteristic test problem.
It elaborates to the present invention with reference to example.
Specific implementation mode
（1）Fastening aircraft fuselage, using airframe shafting, it is that zero degree, the i.e. body shafting longitudinal axis is protected to make aircraft pitch angle
Water holding is flat, and each monitoring point of wing upper and lower is in airframe shafting position it is known that camera selects Luxima companies
1000 frames/second may be implemented in the camera of LUX2100-CMOS chips composition, the chip under 1920 × 1080 colour resolutions
Image Acquisition and record；It is tested with the high speed camera group of four synchronous controls；One high speed camera group is in aircraft wing
Above and below two high speed cameras are respectively installed, wing detection part can be overlooked or be looked up to two high speed cameras, by wing
Horizontal plane and two high speed camera CCD chip centers of the two high speed camera CCD chips of top installation in same assigned altitute
Position and centre-to-centre spacing it is known that the two high speed camera CCD chips installed below wing same assigned altitute horizontal plane and two
Known to a high speed camera CCD chip center and centre-to-centre spacing；Meanwhile right over each monitoring point of aircraft wing and underface
The infrared or laser side distance meter of installation and high speed camera synchronous control obtains corresponding monitoring point position perpendicular to the ground, meanwhile,
Wing front and back given position is respectively horizontally mounted a high speed camera, makes two high speed camera centers and wing tip line
It is parallel with the airframe shafting longitudinal axis and can observe wing laterally all, image that each high speed camera obtains and it is infrared or
The distance signal that laser side distance meter obtains can synchronous control, and each high speed camera group carries out the anti-high wind glass envelope of high temperature resistance
Dress；
（2）Each high speed camera group is demarcated after fixed CCD field angles：It is determined by the high speed camera installed in front of wing
Leading edge perspective view boundary and forefront crest line figure, the high speed camera installed by wing rear are determined after wing along perspective view
Boundary and finally along crest line figure, according to right over aircraft wing and the infrared or laser side distance meter of underface installation obtains wing
The infrared or laser testing distance of each monitoring point of upper and lower, meanwhile, according to four installed above and below aircraft wing
High speed camera obtains position of each monitoring point of wing upper and lower above with pixel in the high speed camera image of lower section two, according to
Two high speed camera CCD chip centre-to-centre spacing of the same level installed above or below wing, it may be determined that above wing or
Pixel position of each monitoring point in lower section in two high speed cameras, by taking i-th of wing monitoring point as an example, by two high speed phases
Machine CCD chip center and i-th of wing monitoring location determine a plane, due in two high speed camera CCD chips
The heart is away from position of i-th of wing monitoring point in two high speed camera images in the case of, fixed CCD field angles it is known that i-th of machine
Wing monitoring point and the angle of two high speed camera CCD chip center lines can be determined；
After being demarcated to each high speed camera group, according to the actual flying tests such as Hypersonic Aircraft obtain related data,
Ground experiment wing is heated and carries out exciting so that ground experiment wing generates flutter at a given temperature；
（3）Four high speed camera groups of synchronous control, each frame image of each high speed camera acquisition, infrared or laser side distance meter obtain
Each distance signal taken is time synchronization, each monitoring point of wing upper and lower that infrared or laser side distance meter obtains
Distance changes over time data and can be used for flutter of aerofoil analysis；According to four high speeds installed above and below aircraft wing
Camera obtains position of each monitoring point of wing upper and lower above with pixel in the high speed camera image of lower section two and becomes at any time
Changing data can be used for flutter of aerofoil analysis；Leading edge perspective view side can be obtained by the high speed camera installed in front of wing
Boundary and forefront crest line figure change over time data, and the high speed camera installed by wing rear can obtain after wing along perspective view
Boundary and data finally are changed over time along crest line figure, and the amplitude and frequency of wing tip can be obtained；According to infrared or laser
Position, leading edge perspective view boundary and the forefront crest line of pixel in immediate data that side distance meter obtains, high speed camera image
Figure changes over time data, the image of wing tip changes over time data, can estimate flutter of aerofoil parameter, amplitude with fusion method
And frequency.
Claims (1)
1. a kind of airplane flutter hot test image measurement method, feature include the following steps：
（1）Fastening aircraft fuselage, using airframe shafting, it is that zero degree, the i.e. body shafting longitudinal axis keeps water to make aircraft pitch angle
Flat, each monitoring point of wing upper and lower is in airframe shafting position it is known that being tested with the phase unit of four synchronous controls；
One phase unit respectively installs two cameras above and below aircraft wing, and wing detection can be overlooked or be looked up to two cameras
Part, by the two camera CCD chips installed above wing in the horizontal plane of same assigned altitute and two camera CCD chips
Heart position and centre-to-centre spacing it is known that the two camera CCD chips installed below wing same assigned altitute horizontal plane and two
Known to camera CCD chip center and centre-to-centre spacing；Meanwhile right over each monitoring point of aircraft wing and underface installation with
The infrared or laser side distance meter of camera synchronous control obtains corresponding monitoring point position perpendicular to the ground, meanwhile, in front of wing and
Rear given position is respectively horizontally mounted a camera, makes two image centers and wing tip line and the airframe shafting longitudinal axis
It is parallel and can observe wing laterally all, the distance letter that the image and infrared or laser side distance meter that each camera obtains obtain
Number can synchronous control, and each phase unit carries out the anti-high wind glass-encapsulated of high temperature resistance；
（2）Each phase unit is demarcated after fixed CCD field angles：Leading edge is determined by the camera installed in front of wing
Perspective view boundary and forefront crest line figure, the camera installed by wing rear are determined after wing along perspective view boundary and last edge
Crest line figure obtains wing upper and lower and each supervises according to right over aircraft wing with the infrared or laser side distance meter of underface installation
The infrared or laser testing distance of measuring point, meanwhile, obtain wing according to four cameras installed above and below aircraft wing
The each monitoring point of the upper and lower position with pixel in the camera image of lower section two above, according to what is installed above or below wing
Two camera CCD chip centre-to-centre spacing of same level, it may be determined that each monitoring point is in two cameras above or below wing
In pixel position, by taking i-th of wing monitoring point as an example, by two camera CCD chip centers and the monitoring of i-th wing
Point one plane of location determination, due to i-th of wing monitoring in the case of two camera CCD chip centre-to-centre spacing, fixed CCD field angles
Position o'clock in two camera images it is known that i-th wing monitoring point and two camera CCD chip center lines folder
Angle can be determined；
After being demarcated to each phase unit, according to the related data that the actual flying tests such as Hypersonic Aircraft obtain, over the ground
Interview tests wing and heats and carry out exciting so that ground experiment wing generates flutter at a given temperature；
（3）Four phase units of synchronous control, each frame image of each camera acquisition, infrared or laser side distance meter obtain each
A distance signal is all time synchronization, and each monitoring point distance of the wing upper and lower that infrared or laser side distance meter obtains is at any time
Between delta data can be used for flutter of aerofoil analysis；Wing is obtained according to four cameras installed above and below aircraft wing
The each monitoring point of upper and lower changes over time data with the position of pixel in the camera image of lower section two above and can be used for
Flutter of aerofoil is analyzed；Leading edge perspective view boundary and forefront crest line figure can be obtained at any time by the camera installed in front of wing
Between delta data, the camera installed by wing rear can obtain after wing along perspective view boundary and finally along crest line figure at any time
Delta data, and the amplitude and frequency of wing tip can be obtained；According to the immediate data of infrared or laser side distance meter acquisition, camera
In image the position of pixel, leading edge perspective view boundary and forefront crest line figure change over time data, wing tip image with
Time-variable data can estimate flutter of aerofoil parameter, amplitude and frequency with fusion method.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111222544A (en) * | 2019-12-22 | 2020-06-02 | 同济大学 | Ground simulation test system for influence of satellite flutter on camera imaging |
| CN115979157A (en) * | 2022-12-31 | 2023-04-18 | 同济大学 | Road surface structure performance evaluation method and system based on remote laser vibration measurement |
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| US20020069040A1 (en) * | 2000-12-05 | 2002-06-06 | Hideo Omotani | Flutter test model |
| CN102539099A (en) * | 2012-02-02 | 2012-07-04 | 北京航空航天大学 | Measuring device for 1400 DEG C high-temperature modal test of wing helm structure of hypersonic aircraft |
| CN104443427A (en) * | 2014-10-15 | 2015-03-25 | 西北工业大学 | Aircraft flutter prediction system and method |
| CN105716837A (en) * | 2014-12-03 | 2016-06-29 | 中国飞行试验研究院 | Airborne rotor motion measurement method based on PSD optical imaging |
| US20160355278A1 (en) * | 2015-06-04 | 2016-12-08 | The Boeing Company | Systems and methods for analyzing flutter test data using damped sine curve fitting with the closed form shape fit |
| CN107168398A (en) * | 2017-06-16 | 2017-09-15 | 华南理工大学 | Flexible wing vibration detection and control device and method based on high speed camera |
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2018
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020069040A1 (en) * | 2000-12-05 | 2002-06-06 | Hideo Omotani | Flutter test model |
| CN102539099A (en) * | 2012-02-02 | 2012-07-04 | 北京航空航天大学 | Measuring device for 1400 DEG C high-temperature modal test of wing helm structure of hypersonic aircraft |
| CN104443427A (en) * | 2014-10-15 | 2015-03-25 | 西北工业大学 | Aircraft flutter prediction system and method |
| CN105716837A (en) * | 2014-12-03 | 2016-06-29 | 中国飞行试验研究院 | Airborne rotor motion measurement method based on PSD optical imaging |
| US20160355278A1 (en) * | 2015-06-04 | 2016-12-08 | The Boeing Company | Systems and methods for analyzing flutter test data using damped sine curve fitting with the closed form shape fit |
| CN107168398A (en) * | 2017-06-16 | 2017-09-15 | 华南理工大学 | Flexible wing vibration detection and control device and method based on high speed camera |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111222544A (en) * | 2019-12-22 | 2020-06-02 | 同济大学 | Ground simulation test system for influence of satellite flutter on camera imaging |
| CN111222544B (en) * | 2019-12-22 | 2023-05-02 | 同济大学 | Ground simulation test system for influence of satellite flutter on camera imaging |
| CN115979157A (en) * | 2022-12-31 | 2023-04-18 | 同济大学 | Road surface structure performance evaluation method and system based on remote laser vibration measurement |
| CN115979157B (en) * | 2022-12-31 | 2023-09-12 | 同济大学 | Method and system for evaluating pavement structure performance based on remote laser vibration measurement |
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