CN107869960A - A kind of aircraft wing deformation measuring device, installation method and method of testing - Google Patents
A kind of aircraft wing deformation measuring device, installation method and method of testing Download PDFInfo
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- CN107869960A CN107869960A CN201711171317.1A CN201711171317A CN107869960A CN 107869960 A CN107869960 A CN 107869960A CN 201711171317 A CN201711171317 A CN 201711171317A CN 107869960 A CN107869960 A CN 107869960A
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- wing
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- optic gyroscope
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- fuselage
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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)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Length Measuring Devices By Optical Means (AREA)
Abstract
The present invention relates to aircraft wing deformation measurement field, and in particular to a kind of aircraft wing deformation measuring device, installation method and method of testing, 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 for gathering the deformation information of speckle pattern, and by deformation information to computer；Gyroscope inertial navigation system includes fibre optic gyroscope, and fibre optic gyroscope has several, and several fibre optic gyroscopes are symmetrical with wing in fuselage, and fibre optic gyroscope is communicatively coupled to computer, for data message measured by being transmitted to computer；The deformation information of set of computers speckle pattern determines wing deflection with fibre optic gyroscope data measured information realization.It can be under dynamic environment, the measurement wing deformation of real-time high-precision.
Description
Technical field
The present invention relates to aircraft wing deformation measurement field, and in particular to a kind of aircraft wing deformation measuring device, installation
Method and method of testing.
Background technology
Aircraft, because effect has aerodynamic loading on wing, can produce larger deformation in flight course, wing it is larger
Harmful effect can all be produced to the security performance and economic performance of aircraft by deforming, therefore be had to aircraft wing progress deformation measurement
Significance.
The method that researcher commonly uses for wing deformation measurement at present is divided into two kinds：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 the influence such as larger additional stress when this kind of device is installed to wing cover surface be present, cause wing to produce additional deformation,
In the presence of the larger error of measurement, and this kind of measurement apparatus is spot measurement, can not obtain the continuous deformation data of wing.Rather than
Contact measurement is mostly using the deformation of visual pattern processing measuring method fast track aircraft key point or subregion, this kind of side
Although method can realize non-contact measurement, additional stress is avoided, precision is also higher, and this method can not obtain the wing whole audience
Deformation, while exist and deformed under the vertical current intelligence of tail so that image information collecting produces error.
In conventional Aerofoil deformation measuring device, contact measurement method such as pastes foil gauge, can measure degree of precision
Deformation result, but this method can to wing produce additional stress deformation, have larger measurement error, and this kind of measurement apparatus
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 measuring method, domestic wing deformation measurement generally use is measuring method, and measuring system is complicated, and measurement cost is high,
Although recent year scholar achieves certain achievement in the technique study of visual pattern processing measurement wing deformation, can with
Non-contact measurement can be realized, avoids additional stress, precision is also higher, but this method does not consider that the Zona transformans of fuselage comes
Combined influence, measurement result certainly will be influenceed.
The content of the invention
The invention aims to provide a kind of aircraft wing deformation measuring device, installation method and method of testing, its
Can be under dynamic environment, the measurement wing deformation of real-time high-precision.
To realize above-mentioned technical purpose, the technical scheme that the present invention takes is a kind of aircraft wing deformation measuring device, bag
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 gathering 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 with the fibre optic gyroscope on wing, and on fuselage with both sides wing geometric center
Connecting line is distributed for axial symmetry, and the fibre optic gyroscope on wing is distributed by axial symmetry of fuselage axis；Fibre optic gyroscope leads to
Letter is connected to computer, for data message measured by being transmitted 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 scheme of the present invention, fibre optic gyroscope is respectively arranged in the upper of the top of wing and fuselage
Portion；And when fibre optic gyroscope is arranged on wing top, fibre optic gyroscope be arranged on wing selected covering geometric center
Locate, the fibre optic gyroscope quantity on the wing of both 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 the fibre optic gyroscope in wherein centre position is arranged in two
The midpoint of side wing geometric center line.
As the improved technical scheme of the present invention, image collector is set to ccd video camera.
Another object of the present invention provides a kind of installation method of aircraft wing deformation measuring device, comprises the following steps：
Step 1: the model and size of aircraft wing selected by obtaining, draw speckle placement scheme figure, determine arrangement；
Step 2: arrange the speckle pattern for imaging according to placement scheme figure on the aircraft skin on wing top；
Step 3: the fibre optic gyroscope of model selected by determining, arranges several fibre optic gyroscopes on the wing of both sides, ensure 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 both sides
Deng, be symmetric along fuselage；
Step 4: arranging fibre optic gyroscope on fuselage, the midpoint of both sides wing geometric center line is first calculated on fuselage
At the projection in portion, in one fibre optic gyroscope of the location arrangements, then alongst with foregoing optical fibre gyro on fuselage
Instrument is that symmetrical centre symmetrically arranges remaining fibre optic gyroscope at equal intervals；
Locate Step 5: ccd video camera to be fixed on wing tail and hang down, be adjusted to horizontal level, ensure that it is steady when doing dynamic experiment
It is qualitative；
Step 6: ccd video camera is connected with computer respectively with fibre optic gyroscope, and adjust all optical fiber on wing and fuselage
Gyrohorizon position.
As the improved technical scheme of the present invention, comprise the following steps：
Step 1: ccd video camera is connected with computer respectively with fibre optic gyroscope, and adjust all optical fiber on wing and fuselage
Gyrohorizon position；Aircraft is positioned in simulation dynamic environment and tested；
Step 2: in the case where simulating inactive state, wing is measured under static state by the fibre optic gyroscope on wing first
Deformation, by data information transfer into computer, fit and wing is measured by fibre optic gyroscope on wing under inactive state
Deformation curve, the deformation curve of the wing, the deformation curve of the wing as follow-up simulation dynamic experiment primary data and
Reference standard；
Step 3: in simulation dynamic environment experiment, the data of wing deformation are measured by the fibre optic gyroscope on wing first
Information, by data information transfer into computer, obtain the deformation of both sides wing；
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 the vertical attitudes vibration of fuselage afterbody tail and ccd video camera relative to wing, error benefit is carried out by calculating
Repay, the initial state of correction ccd video camera collection information；
The deformation information of speckle pattern on wing is collected by ccd video camera again, and the deformation information of collection 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 change situation of wing.
Beneficial effect
Device collection speckle imaging system that the present invention designs, gyroscope inertial navigation system combination, the advantages of combining the two, by two
Person's data message merges, and by the processing of computer, measures wing deflection of the aircraft wing in dynamic environment, the present invention
It is adapted to static lower wing deformation measurement；
In addition, the fibre optic gyroscope size of model selected by the device is small, in light weight, arrangement number is few, to large scale wing and
Influence can be neglected caused by fuselage, pass through the angular deformation of the measurement position of gyroscope on fuselage and wing, it is measured
Accurately.
Brief description of the drawings
Fig. 1 Aerofoil deformation measuring device schematic layout patterns；
Fig. 2 Aerofoil deformation measuring devices Computer, speckle imaging system and gyroscope inertial navigation system annexation are illustrated
Figure；
In figure, 1- gyroscope inertial navigation systems, 2- computers, 3- speckle imaging systems；A1, A2, A3, A4 are represented be arranged in respectively
Four light gyroscopes on the wing of aircraft side；B1, B2, B3, B4 represent four be arranged on aircraft opposite side wing respectively
Individual light gyroscope；C1, C2, C3 represent three fibre optic gyroscopes being arranged on fuselage, and P represents ccd video camera.
Embodiment
The present invention is described further below in conjunction with the accompanying drawings.The label declaration of each several part in schematic diagram：Optical fibre gyro is used to
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 aircraft opposite side wing are respectively B1, B2, B3, B4, three fibre optic gyroscopes on fuselage
Respectively C1, C2, C3, ccd video 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, IMAQ
Device is located at tail, is transmitted for gathering the deformation information of speckle pattern, and by deformation information to computer；Optical fibre gyro inertial navigation
System includes fibre optic gyroscope, and fibre optic gyroscope has several, and several fibre optic gyroscopes are symmetrical with wing in fuselage, light
Fiber gyroscope is communicatively coupled to computer, for data message measured by being transmitted to computer；Set of computers speckle pattern
Deformation information determines wing deflection with fibre optic gyroscope data measured information realization；Specific fibre optic gyroscope is arranged in wing
Top and fuselage top, measure the wing angular deformation of specified location；And when fibre optic gyroscope is arranged on wing top, light
Fiber gyroscope be arranged on wing at the geometric center of selected covering, the fibre optic gyroscope quantity on the wing of both sides it is equal and
It is symmetrical；When back arranges fibre optic gyroscope, from odd number fibre optic gyroscope, between odd number fibre optic gyroscope etc.
Away from arrangement, the fibre optic gyroscope in wherein centre position is arranged in the midpoint of both sides wing geometric center line；Wherein, image is adopted
Packaging is set to ccd video camera.
For reasonable Arrangement measurement apparatus, first, the model and size of aircraft wing selected by acquisition, speckle layout side is drawn
Case figure, determines arrangement, along upper surface of the airfoil direction according to the well-regulated speckle arranged for imaging of placement scheme in winged
On machine covering.The purpose of arrangement speckle pattern is to be used for ccd video camera observation speckle deformation, high-precision in order to effectively obtain
The speckle pattern deformation information measured value of degree, so the just ranks number of necessary reasonable set speckle and the layout on wing
Position.
It is then determined that the fibre optic gyroscope of selected model, arrange several fibre optic gyroscopes in selecting on the wing of both sides
At geometric center at covering, the gyroscope quantity on the wing of both sides is equal, is symmetric along fuselage.Then, on fuselage
During the position of selected arrangement fibre optic gyroscope, projection of the midpoint in back of both sides wing geometric center line is first calculated
Place, in 1 fibre optic gyroscope C2 of the location arrangements, then symmetrically it is equally spaced optical fiber along two side directions of head and the tail on fuselage
Gyroscope（C1、C3）, ccd video camera P is then fixed on the vertical identified opening position of wing tail, is adjusted to horizontal level, finally
The fixed each device of regulation, ensures 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 video camera is fixed at the vertical upper diverse location of wing tail, observed in inactive state
Under, the imaging figure of speckle on the wing at diverse location, observe the speckle roundness in image, place when roundness is optimal
Position, it is exactly the opening position of the fixed ccd video camera of the present invention.
Each fibre optic gyroscope is connected with ccd video camera P and is connected with computer, checks each device（Each fibre optic gyroscope
With ccd video camera P）Whether can normal work, adjust each fibre optic gyroscope on wing and fuselage（C1-C3, A1-A4, B1-B4）
Horizontal level, aircraft is positioned in simulation dynamic environment and tested.
As depicted in figs. 1 and 2, under static state, four fibre optic gyroscopes of the side on wing are passed through first（A1、
A2、A3、A4）And four fibre optic gyroscopes of opposite side（B1、B2、B3、B4）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 inactive state
Deformation curve, the deformation curve of the wing is as the follow-up primary data and reference standard for simulating dynamic experiment.
In simulation dynamic environment experiment, Step 1: four fibre optic gyroscopes for passing through the side on wing（A1、A2、
A3、A4）And four fibre optic gyroscopes of opposite side（B1、B2、B3、B4）Measure the data message of wing deformation, data message
Transmit into computer, obtain the data message of both sides wing deformation；
Step 2: pass through the fibre optic gyroscope on fuselage（C1、C2、C3、C4）The data message of frame deflection is measured, passes through calculating
The information processing of machine, determine that the vertical attitudes vibration of fuselage afterbody tail and ccd video camera relative to the visual angle change of wing, pass through
Calculate and carry out error compensation, the initial state of correction ccd video camera collection information；
Step 3: collecting the change information of speckle on wing by ccd video camera, and the change information for gathering speckle is transmitted
Into computer, the wing deformation information of speckle imaging system output is obtained；
Step 4: the deformation information obtained by computer with the data message that related algorithm obtains step 1 with step 3
Merged, determine the deflection and dynamic change situation of wing.
The embodiment of the present invention is elaborated above in association with accompanying drawing, but these explanations can not 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 (5)
1. a kind of aircraft wing deformation measuring device, it is characterised in that be used to including computer, speckle imaging system and optical fibre gyro
Guiding systems；Speckle imaging system includes image collecting device and speckle pattern, and speckle pattern is arranged on wing, image collector
Tail is arranged in, is transmitted for gathering the deformation information of speckle pattern, and by deformation information to computer；Optical fibre gyro inertial navigation system
System includes fibre optic gyroscope, and fibre optic gyroscope has several, and several fibre optic gyroscopes are respectively arranged on fuselage and wing, and
Fibre optic gyroscope on fuselage is distributed by axial symmetry of the connecting line of both sides wing geometric center, the optical fiber on wing
Gyroscope is distributed by axial symmetry of fuselage axis；Fibre optic gyroscope is communicatively coupled to computer, for being surveyed to computer transmission
Obtain data message；The deformation information of set of computers speckle pattern determines that wing becomes with fibre optic gyroscope data measured information realization
Shape amount.
2. a kind of aircraft wing deformation measuring device according to claim 1, it is characterised in that fibre optic gyroscope distinguishes cloth
It is placed in the top of wing and the top of fuselage；And when fibre optic gyroscope is arranged on wing top, fibre optic gyroscope is arranged in
On wing at the geometric center of selected covering, the fibre optic gyroscope quantity on the wing of both sides is equal and symmetrical；In fuselage
When fibre optic gyroscope is arranged on top, from odd number fibre optic gyroscope, odd number fibre optic gyroscope is equally spaced, wherein among
The fibre optic gyroscope of position is arranged in the midpoint of both sides wing geometric center line.
3. a kind of aircraft wing deformation measuring device according to claim 1, it is characterised in that image collector is set to
Ccd video camera.
A kind of 4. installation method of aircraft wing deformation measuring device as described in claim 1-3 is any, it is characterised in that bag
Include following steps：
Step 1: the model and size of aircraft wing selected by obtaining, draw speckle placement scheme figure, determine arrangement；
Step 2: arrange the speckle pattern for imaging according to placement scheme figure on the aircraft skin on wing top；
Step 3: the fibre optic gyroscope of model selected by determining, arranges several fibre optic gyroscopes on the wing of both sides, ensure 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 both sides
Deng, be symmetric along fuselage；
Step 4: arranging fibre optic gyroscope on fuselage, the midpoint of both sides wing geometric center line is first calculated on fuselage
At the projection in portion, in one fibre optic gyroscope of the location arrangements, then alongst with foregoing optical fibre gyro on fuselage
Instrument is that symmetrical centre symmetrically arranges remaining fibre optic gyroscope at equal intervals；
Locate Step 5: ccd video camera to be fixed on wing tail and hang down, be adjusted to horizontal level, ensure that it is steady when doing dynamic experiment
It is qualitative；
Step 6: ccd video camera is connected with computer respectively with fibre optic gyroscope, and adjust all optical fiber on wing and fuselage
Gyrohorizon position.
A kind of 5. method of testing of aircraft wing deformation measuring device as described in claim 1-3 is any, it is characterised in that bag
Include following steps：
Step 1: ccd video camera is connected with computer respectively with fibre optic gyroscope, and adjust all optical fiber on wing and fuselage
Gyrohorizon position；Aircraft is positioned in simulation dynamic environment and tested；
Step 2: in the case where simulating inactive state, wing is measured under static state by the fibre optic gyroscope on wing first
Deformation, by data information transfer into computer, fit and wing is measured by fibre optic gyroscope on wing under inactive state
Deformation curve, the primary data and reference standard of the deformation curve of the wing as follow-up simulation dynamic experiment；
Step 3: in simulation dynamic environment experiment, the data of wing deformation are measured by the fibre optic gyroscope on wing first
Information, by data information transfer into computer, obtain the deformation of both sides wing；
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 the vertical attitudes vibration of fuselage afterbody tail and ccd video camera relative to wing, error benefit is carried out by calculating
Repay, the initial state of correction ccd video camera collection information；
The deformation information of speckle pattern on wing is collected by ccd video camera again, and the deformation information of collection 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 change situation of wing.
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| CN201711171317.1A CN107869960B (en) | 2017-11-22 | 2017-11-22 | A kind of aircraft wing deformation measuring device, installation method and test method |
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Cited By (7)
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| 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 |
| US11155365B2 (en) | 2018-04-09 | 2021-10-26 | Subaru Corporation | Aircraft management system |
| CN113819853A (en) * | 2021-11-24 | 2021-12-21 | 中国飞机强度研究所 | Method for measuring deformation of airplane body in extreme cold climate test |
| CN113815897A (en) * | 2021-11-24 | 2021-12-21 | 中国飞机强度研究所 | Method for measuring deformation of airplane body under wide-range temperature rise |
| WO2021139837A3 (en) * | 2021-04-07 | 2022-02-10 | 郑州航空工业管理学院 | Wing swing amplitude testing device for airplane during dutch roll |
| CN117048848A (en) * | 2023-10-12 | 2023-11-14 | 中国飞机强度研究所 | Space attitude and deformation testing method for full-size airplane test |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11155365B2 (en) | 2018-04-09 | 2021-10-26 | Subaru Corporation | 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 |
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| WO2021139837A3 (en) * | 2021-04-07 | 2022-02-10 | 郑州航空工业管理学院 | Wing swing amplitude testing device for airplane during dutch roll |
| CN113819853A (en) * | 2021-11-24 | 2021-12-21 | 中国飞机强度研究所 | Method for measuring deformation of airplane body in extreme cold climate test |
| CN113815897A (en) * | 2021-11-24 | 2021-12-21 | 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 |
| CN117048848A (en) * | 2023-10-12 | 2023-11-14 | 中国飞机强度研究所 | Space attitude and deformation testing method for full-size airplane test |
| 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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| Publication number | Publication date |
|---|---|
| CN107869960B (en) | 2019-09-10 |
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