CN107869960B - A kind of aircraft wing deformation measuring device, installation method and test method - Google Patents
A kind of aircraft wing deformation measuring device, installation method and test method Download PDFInfo
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- CN107869960B CN107869960B CN201711171317.1A CN201711171317A CN107869960B CN 107869960 B CN107869960 B CN 107869960B CN 201711171317 A CN201711171317 A CN 201711171317A CN 107869960 B CN107869960 B CN 107869960B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B11/00—Measuring arrangements characterised by the use of optical techniques
- G01B11/16—Measuring arrangements characterised by the use of optical techniques for measuring the deformation in a solid, e.g. optical strain gauge
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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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- Manufacturing & Machinery (AREA)
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- Aviation & Aerospace Engineering (AREA)
- Length Measuring Devices By Optical Means (AREA)
Abstract
The present invention relates to aircraft wing deformation measurement fields, and in particular to a kind of aircraft wing deformation measuring device, installation method and test method, including computer, speckle imaging system and gyroscope inertial navigation system；Speckle imaging system includes image collecting device and speckle pattern, and speckle pattern is arranged on wing, and image collector is arranged in tail, is transmitted to computer for acquiring the deformation information of speckle pattern, and by deformation information；Gyroscope inertial navigation system includes fibre optic gyroscope, and fibre optic gyroscope has several, several fibre optic gyroscopes are symmetrical with wing in fuselage, and fibre optic gyroscope is communicatively coupled to computer, for transmitting measured data information to computer；The deformation information and fibre optic gyroscope data measured information realization of set of computers speckle pattern determine wing deflection.It can in a dynamic environment, and the measurement wing of real-time high-precision deforms.
Description
Technical field
The present invention relates to aircraft wing deformation measurement fields, and in particular to a kind of aircraft wing deformation measuring device, installation
Method and test method.
Background technique
Aircraft, since effect has aerodynamic loading on wing, can generate biggish deformation in flight course, wing it is larger
Deformation can all generate adverse effect to the security performance and economic performance of aircraft, therefore have to aircraft wing progress deformation measurement
Significance.
Researcher's method common for wing deformation measurement is divided into two kinds at present: contact type measurement and contactless survey
Amount.Traditional contact measurement method such as foil gauge, displacement or acceleration transducer etc. can measure the deformation knot of degree of precision
Fruit, but there are the influences such as larger additional stress when this kind of device is installed to wing cover surface, and wing is caused to generate additional deformation,
In the presence of measurement large error, and this kind of measuring device is spot measurement, can not obtain the continuous deformation data of wing.Rather than
Contact measurement mostly uses greatly the deformation of visual pattern processing measurement method fast track aircraft key point or partial region, this kind of side
Although method is able to achieve non-contact measurement, avoid additional stress, and precision is also relatively high, but this method can not obtain the wing whole audience
Deformation is existed simultaneously and is deformed under the vertical current intelligence of tail so that image information collecting generates error.
In previous Aerofoil deformation measuring device, contact measurement method such as pastes foil gauge, can measure degree of precision
Deformation result, but this method can generate additional stress deformation to wing, there are larger measurement error, and this kind of measuring device
It is spot measurement, the continuous deformation data of wing can not be obtained, measurement effect is poor in the dynamic case for the method.It is non-contact
In measurement method, what domestic wing deformation measurement generallyd use is measuring method, and measuring system is complicated, and measurement cost is high,
It, can be with although domestic scholars achieve certain achievement in the technique study of visual pattern processing measurement wing deformation in recent years
It is able to achieve non-contact measurement, avoids additional stress, precision is also relatively high, but this method does not consider that the Zona transformans of fuselage comes
Combined influence, measurement result certainly will be influenced.
Summary of the invention
The purpose of the invention is to provide a kind of aircraft wing deformation measuring device, installation method and test method,
Can in a dynamic environment, the measurement wing of real-time high-precision deforms.
To realize the above-mentioned technical purpose, the technical scheme adopted by the invention is as follows, a kind of aircraft wing deformation measuring device wraps
Include computer, speckle imaging system and gyroscope inertial navigation system；Speckle imaging system includes image collecting device and speckle pattern
Case, speckle pattern are arranged on wing, and image collector is arranged in tail, for acquiring the deformation information of speckle pattern, and will
Deformation information is transmitted to computer；Gyroscope inertial navigation system includes fibre optic gyroscope, and fibre optic gyroscope has several, several
Fibre optic gyroscope is respectively arranged on fuselage and wing, and the fibre optic gyroscope being set on fuselage is with two sides wing geometric center
Connecting line is axial symmetry distribution, and the fibre optic gyroscope on wing is distributed by axial symmetry of fuselage axis；Fibre optic gyroscope is logical
Letter is connected to computer, for transmitting measured data information to computer；The deformation information of set of computers speckle pattern with
Fibre optic gyroscope data measured information realization determines wing deflection.
As the improved technical solution of the present invention, fibre optic gyroscope be respectively arranged in wing top and fuselage it is upper
Portion；And fibre optic gyroscope is when wing top is arranged, fibre optic gyroscope be arranged on wing selected covering geometric center
Locate, the fibre optic gyroscope quantity on the wing of two sides is equal and symmetrical；When back arranges fibre optic gyroscope, select
Odd number fibre optic gyroscope, odd number fibre optic gyroscope are equally spaced, and wherein the fibre optic gyroscope in middle position is arranged in two
The midpoint of side wing geometric center line.
As the improved technical solution of the present invention, image collector is set to CCD camera.
Another object of the present invention provides a kind of installation method of aircraft wing deformation measuring device, includes the following steps:
Step 1: obtaining the model and size of selected aircraft wing, speckle placement scheme figure is drawn, determines arrangement；
Step 2: the speckle pattern on the aircraft skin on wing top according to placement scheme figure arrangement for imaging；Step 3: determining
The fibre optic gyroscope of selected model arranges several fibre optic gyroscopes on the wing of two sides, guarantees that fibre optic gyroscope is located at wing
Top at the geometric center of selected covering, and quantity of the fibre optic gyroscope on the wing of two sides it is equal, along fuselage in symmetrical
Distribution；Step 4: arranging fibre optic gyroscope on fuselage, the midpoint of two sides wing geometric center line is first calculated on fuselage
At the projection in portion, a fibre optic gyroscope is arranged in the position, then alongst with aforementioned optical fibre gyro on fuselage
Instrument is that symmetrical centre symmetrically arranges remaining fibre optic gyroscope at equal intervals；It hangs down Step 5: CCD camera is fixed on wing tail
Place, is adjusted to horizontal position, guarantees its stability when doing dynamic experiment；Step 6: by CCD camera and fibre optic gyroscope point
It is not connect with computer, and adjusts all fibre optic gyroscope horizontal positions on wing and fuselage.
As the improved technical solution of the present invention, include the following steps:
Step 1: CCD camera is connect with computer respectively with fibre optic gyroscope, and adjusts on wing and fuselage and own
Fibre optic gyroscope horizontal position；Aircraft is placed in simulation dynamic environment and is tested；Step 2: in simulation stationary state
Under, the deformation of wing under static state is measured by the fibre optic gyroscope on wing first, extremely by data information transfer
In computer, the deformation curve for measuring wing under stationary state by fibre optic gyroscope on wing is fitted, the deformation of the wing is bent
Line, primary data and reference standard of the deformation curve of the wing as subsequent simulation dynamic experiment；Step 3: in simulation dynamic
In environmental experiment, the data information of wing deformation is measured by the fibre optic gyroscope on wing first, extremely by data information transfer
In computer, the deformation of two sides wing is obtained；Then the deformation data of fuselage is measured by the fibre optic gyroscope on fuselage
Information determines the vertical attitudes vibration of fuselage afterbody tail and CCD camera relative to wing by the information processing of computer
Visual angle change carries out error compensation by calculating, the initial state of correction CCD camera acquisition information；Pass through CCD camera again
The deformation information of speckle pattern on wing is collected, and the deformation information of acquisition is transmitted in computer, obtains speckle imaging
The wing deformation of system output；The information that two systems obtain is melted with related algorithm finally by computer
It closes, determines the deflection and dynamic changes of wing.
Beneficial effect
Device collection speckle imaging system that the present invention designs, gyroscope inertial navigation system combination, the advantages of both combining,
The two data information is merged, by the processing of computer, measures wing deflection of the aircraft wing in dynamic environment, this hair
It is bright to be also suitble to static lower wing deformation measurement；In addition, the fibre optic gyroscope size of model selected by the device is small, light-weight, arrangement
Number is few, and the influence generated to large scale wing and fuselage is negligible, passes through the measurement of gyroscope on fuselage and wing
The angular deformation of position, measurement are accurate.
Detailed description of the invention
Fig. 1 Aerofoil deformation measuring device schematic layout pattern；
Computer, speckle imaging system and gyroscope inertial navigation system connection relationship are shown in Fig. 2 Aerofoil deformation measuring device
It is intended to；In figure, 1- gyroscope inertial navigation system, 2- computer, 3- speckle imaging system；A1, A2, A3, A4 respectively represent arrangement
Four light gyroscopes on the wing of aircraft side；B1, B2, B3, B4, which are respectively represented, to be arranged on the wing of the aircraft other side
Four light gyroscopes；C1, C2, C3 represent three fibre optic gyroscopes being arranged on fuselage, and P represents CCD camera.
Specific embodiment
The present invention is described further with reference to the accompanying drawing.The label declaration of each section in schematic diagram: optical fibre gyro is used
Guiding systems 1, computer 2, speckle imaging system 3, four light gyroscopes on the wing of aircraft side be respectively A1, A2, A3,
A4, four light gyroscopes on the wing of the aircraft other side are respectively B1, B2, B3, B4, three fibre optic gyroscopes on fuselage
Respectively C1, C2, C3, CCD camera P.
As shown in Figure 1, a kind of aircraft wing deformation measuring device, including computer, speckle imaging system and optical fibre gyro
Inertial navigation system；Speckle imaging system includes image collecting device and speckle pattern, and speckle pattern is arranged on wing, Image Acquisition
Device is set to tail, is transmitted to computer for acquiring the deformation information of speckle pattern, and by deformation information；Optical fibre gyro inertial navigation
System includes fibre optic gyroscope, and fibre optic gyroscope has several, several fibre optic gyroscopes are symmetrical with wing in fuselage, light
Fiber gyroscope is communicatively coupled to computer, for transmitting measured data information to computer；Set of computers speckle pattern
Deformation information and fibre optic gyroscope data measured information realization determine wing deflection；Specific fibre optic gyroscope is arranged in wing
Top and fuselage top, measure the wing angular deformation of designated position；And fibre optic gyroscope is when wing top is arranged, light
Fiber gyroscope be arranged on wing at the geometric center of selected covering, the fibre optic gyroscope quantity on the wing of two sides it is equal and
It is symmetrical；When back arranges fibre optic gyroscope, odd number fibre optic gyroscope is selected, between odd number fibre optic gyroscope etc.
Away from arrangement, wherein the fibre optic gyroscope in middle position is arranged in the midpoint of two sides wing geometric center line；Wherein, image is adopted
Packaging is set to CCD camera.
For reasonable Arrangement measuring device, firstly, obtaining the model and size of selected aircraft wing, speckle layout side is drawn
Case figure, determines arrangement, and the speckle along upper surface of the airfoil direction according to the well-regulated arrangement of placement scheme for being imaged is in winged
On machine covering.The purpose of arrangement speckle pattern is that speckle deformation is observed for CCD camera, high-precision in order to effectively obtain
The speckle pattern deformation information of degree measures numerical value, so the just ranks number of necessary reasonable set speckle and the layout on wing
Position.
Then the fibre optic gyroscope for determining selected model arranges several fibre optic gyroscopes in selecting on the wing of two sides
At geometric center at covering, the gyroscope quantity on the wing of two sides is equal, is symmetric along fuselage.Then, on fuselage
When the position of selected arrangement fibre optic gyroscope, projection of the midpoint in back of two sides wing geometric center line is first calculated
Place arranges 1 fibre optic gyroscope C2 in the position, is then symmetrically equally spaced optical fiber along two side directions of head and the tail on fuselage
Then CCD camera P is fixed at the vertical identified position of wing tail, is adjusted to horizontal position, finally by gyroscope (C1, C3)
Fixed each device is adjusted, guarantees its stability when doing dynamic experiment.After speckle pattern arranges on wing, in wing
By the method for many experiments on tail is vertical, CCD camera is fixed at the vertical upper different location of wing tail, is observed in stationary state
Under, the imaging figure of speckle on the wing at different location observes the speckle roundness in image, place when roundness is best
Position is exactly at the position of the fixed CCD camera of the present invention.
Each fibre optic gyroscope is connected with CCD camera P and is connect with computer, checks each device (each fibre optic gyroscope
Whether can be worked normally with CCD camera P), adjust each fibre optic gyroscope (C1-C3, A1-A4, B1-B4) on wing and fuselage
Aircraft is placed in simulation dynamic environment and tests by horizontal position.
As depicted in figs. 1 and 2, under static state, first by four fibre optic gyroscopes of the side on wing (A1,
A2, A3, A4) and four fibre optic gyroscopes (B1, B2, B3, B4) of the other side measure the number that wing deforms under static state
It is believed that breath, by data information transfer into computer, fits and measures wing by fibre optic gyroscope on wing under stationary state
Deformation curve, primary data and reference standard of the deformation curve of the wing as subsequent simulation dynamic experiment.
In simulation dynamic environment experiment, Step 1: by four fibre optic gyroscopes of the side on wing (A1, A2,
A3, A4) and the other side four fibre optic gyroscopes (B1, B2, B3, B4) measure wing deformation data information, data information
It is transmitted in computer, obtains the data information of two sides wing deformation；
Step 2: measuring the data information of frame deflection by the fibre optic gyroscope (C1, C2, C3) on fuselage, pass through meter
The information processing of calculation machine determines the visual angle change of fuselage afterbody tail vertical attitudes vibration and CCD camera relative to wing, leads to
It crosses calculating and carries out error compensation, the initial state of correction CCD camera acquisition information；
Step 3: the change information for collecting the change information of speckle on wing by CCD camera, and speckle being acquired
It is transmitted in computer, obtains the wing deformation information of speckle imaging system output；
Step 4: the deformation that the data information and step 3 that are obtained step 1 with related algorithm by computer obtain
Information is merged, and determines the deflection and dynamic changes of wing.
A specific embodiment of the invention is elaborated in conjunction with attached drawing above, but these explanations cannot be understood to
The scope of the present invention is limited, protection scope of the present invention is limited by appended claims, any the claims in the present invention
On the basis of change belong to protection scope of the present invention.
Claims (4)
1. a kind of installation method of aircraft wing deformation measuring device, the aircraft wing deformation measuring device include computer,
Speckle imaging system and gyroscope inertial navigation system；Speckle imaging system includes image collecting device and speckle pattern, speckle pattern
Case is arranged on wing, and image collector is arranged in tail, is passed for acquiring the deformation information of speckle pattern, and by deformation information
Computer is transported to, image collector is set to CCD camera；Gyroscope inertial navigation system includes fibre optic gyroscope, fibre optic gyroscope
There are several, several fibre optic gyroscopes are respectively arranged on fuselage and wing, and the fibre optic gyroscope being set on fuselage is with two
The connecting line of side wing geometric center is axial symmetry distribution, and the fibre optic gyroscope on wing is using fuselage axis as axial symmetry point
Cloth；Fibre optic gyroscope is communicatively coupled to computer, for transmitting measured data information to computer；Set of computers speckle pattern
The deformation information and fibre optic gyroscope data measured information realization of case determine wing deflection；It is characterised in that it includes following step
It is rapid:
Step 1: obtaining the model and size of selected aircraft wing, speckle placement scheme figure is drawn, determines arrangement；Step
Two, the speckle pattern on the aircraft skin on wing top according to placement scheme figure arrangement for imaging；
Step 3: determining the fibre optic gyroscope of selected model, several fibre optic gyroscopes are arranged on the wing of two sides, guarantee optical fiber
Gyroscope be located at wing top at the geometric center of selected covering, and quantity phase of the fibre optic gyroscope on the wing of two sides
Deng, be symmetric along fuselage；
Step 4: arranging fibre optic gyroscope on fuselage, the midpoint of two sides wing geometric center line is first calculated on fuselage
At the projection in portion, a fibre optic gyroscope is arranged in the position, then alongst with aforementioned optical fibre gyro on fuselage
Instrument is that symmetrical centre symmetrically arranges remaining fibre optic gyroscope at equal intervals；
Locate Step 5: CCD camera to be fixed on wing tail and hang down, is adjusted to horizontal position, guarantees that it is steady when doing dynamic experiment
It is qualitative；
Step 6: CCD camera is connect with computer respectively with fibre optic gyroscope, and adjust all optical fiber on wing and fuselage
Gyrohorizon position.
2. the installation method of aircraft wing deformation measuring device according to claim 1, which is characterized in that fibre optic gyroscope
It is respectively arranged the top in wing and the top of fuselage；And fibre optic gyroscope is when wing top is arranged, fibre optic gyroscope
Be arranged on wing at the geometric center of selected covering, the fibre optic gyroscope quantity on the wing of two sides is equal and symmetrical；
When back arranges fibre optic gyroscope, odd number fibre optic gyroscope is selected, odd number fibre optic gyroscope is equally spaced,
The fibre optic gyroscope in middle middle position is arranged in the midpoint of two sides wing geometric center line at the projection of back.
3. a kind of test method of aircraft wing deformation measuring device, the aircraft wing deformation measuring device include computer,
Speckle imaging system and gyroscope inertial navigation system；Speckle imaging system includes image collecting device and speckle pattern, speckle pattern
Case is arranged on wing, and image collector is arranged in tail, is passed for acquiring the deformation information of speckle pattern, and by deformation information
Computer is transported to, image collector is set to CCD camera；Gyroscope inertial navigation system includes fibre optic gyroscope, fibre optic gyroscope
There are several, several fibre optic gyroscopes are respectively arranged on fuselage and wing, and the fibre optic gyroscope being set on fuselage is with two
The connecting line of side wing geometric center is axial symmetry distribution, and the fibre optic gyroscope on wing is using fuselage axis as axial symmetry point
Cloth；Fibre optic gyroscope is communicatively coupled to computer, for transmitting measured data information to computer；Set of computers speckle pattern
The deformation information and fibre optic gyroscope data measured information realization of case determine wing deflection；It is characterised in that it includes following step
It is rapid:
Step 1: CCD camera is connect with computer respectively with fibre optic gyroscope, and adjust all optical fiber on wing and fuselage
Gyrohorizon position；Aircraft is placed in simulation dynamic environment and is tested；
Step 2: in the case where simulating stationary state, wing is measured under static state by the fibre optic gyroscope on wing first
Deformation fits by data information transfer into computer and measures wing by fibre optic gyroscope on wing under stationary state
Deformation curve, the primary data and reference standard of the deformation curve of the wing as subsequent simulation dynamic experiment；
Step 3: the data of wing deformation are measured by the fibre optic gyroscope on wing first in simulation dynamic environment experiment
Information obtains the deformation of two sides wing by data information transfer into computer；
Then the deformation data information of fuselage is measured by the fibre optic gyroscope on fuselage, by the information processing of computer, really
Determine the visual angle change of fuselage afterbody tail vertical attitudes vibration and CCD camera relative to wing, carries out error benefit by calculating
It repays, the initial state of correction CCD camera acquisition information；
The deformation information of speckle pattern on wing is collected by CCD camera again, and the deformation information of acquisition is transmitted to meter
In calculation machine, the wing deformation of speckle imaging system output is obtained；It is by two with related algorithm finally by computer
The information that system obtains is merged, and determines the deflection and dynamic changes of wing.
4. the test method of aircraft wing deformation measuring device according to claim 3, which is characterized in that fibre optic gyroscope
It is respectively arranged the top in wing and the top of fuselage；And fibre optic gyroscope is when wing top is arranged, fibre optic gyroscope
Be arranged on wing at the geometric center of selected covering, the fibre optic gyroscope quantity on the wing of two sides is equal and symmetrical；
When back arranges fibre optic gyroscope, odd number fibre optic gyroscope is selected, odd number fibre optic gyroscope is equally spaced,
The fibre optic gyroscope in middle middle position is arranged in the midpoint of two sides wing geometric center line at the projection of back.
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| JP6741716B2 (en) | 2018-04-09 | 2020-08-19 | 株式会社Ｓｕｂａｒｕ | Aircraft management system |
| CN109502052A (en) * | 2018-12-12 | 2019-03-22 | 西北工业大学 | One kind is test bed for Variable Geometry Wing deformation parameter |
| CN112393862A (en) * | 2020-09-23 | 2021-02-23 | 东南大学 | Wing deformation measuring device based on FBG (fiber Bragg Grating) and total station and high-precision fitting method |
| WO2021139837A2 (en) * | 2021-04-07 | 2021-07-15 | 郑州航空工业管理学院 | Wing swing amplitude testing device for airplane during dutch roll |
| CN113815897B (en) * | 2021-11-24 | 2022-02-18 | 中国飞机强度研究所 | Method for measuring deformation of airplane body under wide-range temperature rise |
| CN113819853B (en) * | 2021-11-24 | 2022-02-08 | 中国飞机强度研究所 | Method for measuring deformation of airplane body in extreme cold climate test |
| CN114619838A (en) * | 2022-03-14 | 2022-06-14 | 青岛海尔空调器有限总公司 | Overhead type air conditioner and control method thereof |
| CN117048848B (en) * | 2023-10-12 | 2024-01-05 | 中国飞机强度研究所 | Space attitude and deformation testing method for full-size airplane test |
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