CN108082534A - A kind of lifting airscrew combined load test fiber arrangement and group bridge method - Google Patents
A kind of lifting airscrew combined load test fiber arrangement and group bridge method Download PDFInfo
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- CN108082534A CN108082534A CN201711256514.3A CN201711256514A CN108082534A CN 108082534 A CN108082534 A CN 108082534A CN 201711256514 A CN201711256514 A CN 201711256514A CN 108082534 A CN108082534 A CN 108082534A
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- optical fiber
- measurement optical
- load measurement
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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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- Aviation & Aerospace Engineering (AREA)
- Length Measuring Devices By Optical Means (AREA)
Abstract
The present invention relates to a kind of lifting airscrew combined load test fiber arrangements and group bridge method, belong to helicopter load field of measuring technique, it realizes load measurement of the optical fiber on rotary wing by the arrangement of the optical fiber measurement blade combined load more than present invention and group bridge method.The present invention can directly apply to the measurement of lifting airscrew combined load, compared with former measurement method, since its is smaller, cost is lower and longer service life, the consumptive material expense of lifting airscrew load measurement will be greatly decreased, the time is repaired in test and test original paper influences for the shape of the components such as blade optical fiber in the present invention.
Description
Technical field
The invention belongs to helicopter load field of measuring technique more particularly to a kind of lifting airscrew combined load test lights
Fibre arrangement and group bridge method.
Background technology
Rotor system is the prevailing lift of helicopter and steering force source, and the blade and propeller hub component in rotor system exist
In flight course, due to the effect of gas bullet coupling, the always working condition in alternating load.Therefore, pacify to improve helicopter
Quan Xing, it is necessary to real-time online measuring be carried out to the alternating load for acting on rotor system, and be the longevity of blade and propeller hub component
Life estimation accumulation data.
In measurement helicopter blade load strain, mainly the strain waved on section with edgewise direction is measured.
Resistance strain plate measurement rotor system load arrangement and group bridge schematic diagram are as shown in Figure 1.It is cutd open using foil gauge measurement blade
The load decoupling in face needs to arrange that 4 (1,2,3,4 positions in Fig. 1) wave direction foil gauge and 6-8 pieces are shimmy on the section
Direction (A, B, C, D, E, F, G, H position in Fig. 1) foil gauge.Direction loading is waved, from edgewise direction foil gauge, is chosen by dry
Disturb foil gauge of the foil gauge as edgewise direction of minimum combination.Foil gauge measures rotor system components ' load, exists
Foil gauge service life is short, the cycle of patch and calibration is long, can not achieve the limitations such as continuous load measurement.
Fiber-optic grating sensor measures helicopter rotor system load.Optical fiber appearance and size is thinner, and simple optical fiber can transmit
Multi channel signals, therefore overall routing is smaller to the Effect on Mechanical Properties of structure；Fiber optic materials tensile strength characteristics are larger, can survey
Measure the strain of large deformation；Single channel blade measures, and the cost of optical fiber is about 1st/1/10th to 20 of foil gauge cost；
The service life of foil gauge is about tens hours under big strained situation, and the theoretical service life of optical fiber is thousands of hours.
For the load measurement of large scale blade, since its shape is larger, in operational process suffered alternating load amount compared with
Greatly.Traditional resistance strain plate measurement, in service life etc., there is larger limitations.
The content of the invention
The object of the present invention is to provide a kind of lifting airscrew combined load test fiber arrangement and group bridge method, for solving
Certainly any of the above-described problem.
In order to achieve the above objectives, the technical solution adopted by the present invention is：A kind of lifting airscrew combined load tests optical fiber
Arrangement and group bridge method, including
1) fiber arrangement under combined load
Wave the arrangement of direction load measurement optical fiber：The multiple blades measured as needed are tested section and are waving direction survey
The grating sensor of the identical quantity of imprinting on optical fiber is measured, has what light deleted sensor to wave direction load measurement optical fiber along paddle imprinting
Leaf aerodynamic center line is arranged in blade surface；
The arrangement of edgewise direction load measurement optical fiber：Edgewise direction load measurement optical fiber is a plurality of and each parallel in pneumatic
Heart line is set, on every edgewise direction load measurement optical fiber imprinting have and wave quantity and position on the load measurement optical fiber of direction
The grating sensor of all same, wherein, an edgewise direction load measurement optical fiber between aerodynamic center line and blade leading edge,
Remaining edgewise direction load measurement optical fiber is between aerodynamic center line and blade trailing edge；And arrange that compensation passes in propeller shank
Sensor；
2) fibre strain group bridge
2.1) single section waves direction：It is sensed using the grating sensor waved on the load measurement optical fiber of direction and compensation
Device carries out a group bridge；
Single section edgewise direction：Using the edgewise direction load measurement light between aerodynamic center line and blade leading edge
In grating sensor on fibre and the one edgewise direction load measurement optical fiber between aerodynamic center line and blade trailing edge
Grating sensor carries out a group bridge；
2.2) repeat step 2.1 and obtain the fibre strain group bridge that multiple blades are tested under section.
Further, distance of the load measurement optical fiber away from aerodynamic center line between aerodynamic center line and blade trailing edge
It is integral multiple of the load measurement optical fiber away from aerodynamic center linear distance between aerodynamic center line and blade leading edge.
Further, it is temperature-compensating plate to compensate sensor.
Further, the light in the one edgewise direction load measurement optical fiber between aerodynamic center line and blade trailing edge is selected
The method of gate sensor is：
By wave direction load counterweight obtain grating sensor on a plurality of edgewise direction load measurement optical fiber measure should
Variate；
By edgewise direction load counterweight obtain grating sensor on a plurality of edgewise direction load measurement optical fiber measure should
Variate；
The edge grating sensor strain value that direction measures will be waved to make the difference with grating sensor strain value at trailing edge, with
And make the difference the edge grating sensor strain value that edgewise direction measures with grating sensor strain value at trailing edge, it will finally wave
The difference of the difference and edgewise direction of waving direction, which is done, to be compared, and one group of composition of ratio minimum waves the bridge in direction.
Further, the difference is absolute value.
The measuring method of the present invention can directly apply to the measurement of lifting airscrew combined load, with former measurement method phase
Than since its is smaller, cost is lower and longer service life lifting airscrew will be greatly decreased in the optical fiber in the present invention
The consumptive material expense of load measurement, test repair the time and test original paper to be influenced for the shape of the components such as blade, measures model
Enclose wider, economic benefit is more preferable, the advantages that using its longer life expectancy.
Description of the drawings
Attached drawing herein is merged in specification and forms the part of this specification, shows the implementation for meeting the present invention
Example, and the principle for explaining the present invention together with specification.
Fig. 1 measures rotor system load arrangement and group bridge schematic diagram for resistance strain plate；
Fig. 2 arranges schematic diagram for optical fiber measurement rotor system load；
Fig. 3 is favour stone half-bridge schematic diagram.
Specific embodiment
To make the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, the technical solution in the embodiment of the present invention is further described in more detail.
Exist in blade aerodynamic load detection process, aerofoil profile, Mass Distribution generally first against helicopter blade etc. propose blade
The load monitoring demand of specific section, including waving the alternating load with edgewise direction on blade.Determine rotor system
Load monitoring face and monitoring content propose specific scope and requirement to the location arrangements for measuring optical fiber.
For above-mentioned requirements, the present invention provides a kind of lifting airscrew combined load test fiber arrangement and group bridge method,
It includes：
1) fiber arrangement under combined load
It is carried out using grating (assembly of sensor and optical fiber is grating) according to the content of load measurement on rotor surface
It is laid with or pastes.
Optical fiber measurement rotor system load arrangement schematic diagram waves direction and edgewise direction as shown in Fig. 2, it is broadly divided into
Load measurement optical fiber, X-direction is edgewise direction in figure, and Y-direction waves direction.
1.1) direction load measurement optical fiber is waved：Waving direction load can be by the feelings of each section bending strain of blade
Condition is obtained by conversion.When blade works, the bending strain at the aerodynamic center of each section is maximum, and due to resemblance with
The coupling of edgewise direction is minimum, waves direction load measurement fiber arrangement on the intersection point of blade aerodynamic center line and each section,
That is measuring point 1.
1.2) edgewise direction load measurement optical fiber：The edgewise direction of propeller-blade section as shown in Fig. 2, blade front and rear edge due to outer
Shape characteristic, can not placement sensor.Suitable (better closer to leading edge) position cloth is selected between blade aerodynamic center and leading edge
Put a Sensor.3 measuring points are arranged between blade aerodynamic center and trailing edge for being waved and shimmy side to A points
To decoupling.Wherein measuring point A is with aerodynamic center linear distance if L, then measuring point B, C, D points and the distance of aerodynamic center line are then distinguished
For 3L, 4L, 5L.
1.3) temperature compensation characteristic：Since fiber-optic grating sensor has temperature-sensing property, the optical fiber light in different temperatures environment
Gate sensor has certain temperature drift (temperature drift).When arranging blade aerodynamic load measuring point, temperature-compensating plate need to be arranged.Edgewise direction
There are decoupling problem, measuring point can not increase temperature-compensating plate.Therefore direction arrangement temperature-compensating plate is being waved, temperature-compensating plate is set
Any position at blade root.
2nd, fibre strain bridge group bridge
Since resistance-type strains itself easily by interference such as electromagnetism, bridge mainly uses self-compensating favour stone full-bridge mould
Formula.Optical fiber has individually acquisition or measuring apparatus since its insulating properties is preferable, therefore uses favour stone half-bridge mode.Hui Si
Logical half-bridge schematic diagram is as shown in Figure 3.R1, R2 are work measuring point (being arranged in the measuring point on blade) in figure, and R3, R4 are measuring instrument
Device built-in resistor.
2.1) wave direction and a group bridge is carried out using half-bridge public compensation pattern：Blade during the work time, blade root to blade tip
In same environment, temperature difference is smaller.In bridge on direction is waved, a piece of public of temperature-compensating plate arrangement.
R1 measuring points are propeller-blade section and the measuring point 1 on aerodynamic center intersection point upper surface in Fig. 3, and R2 measuring points are the temperature being arranged at blade root
Sensor.
2.2) edgewise direction carries out a group bridge using half-bridge mode：R1 measuring points in Fig. 3 are edgewise direction group bridge blade leading edge
The point arranged between aerodynamic center, i.e. measuring point A in Fig. 2；Point of the R2 measuring points between blade aerodynamic center and blade trailing edge, i.e.,
Measuring point B, C, D point are more therein in Fig. 2.The intelligent acess test equipment that will have been pasted measures strain using A points and is converted to electricity
Resistance value, R3 and R4 resistance form bridge with B, C, D point in host computer respectively.
When selecting R2 measuring points, the point of coupled interference minimum is selected as R2 measuring points, and selection method is as follows：
A) edgewise direction (blade places loading vertically) loading counterweight records the strain value of A, B, C, D point；
B) direction (the horizontal positioned loading of blade) loading counterweight is waved, records the strain value of A, B, C, D point；
C) will subtract each other in step a) with strain value of the A points strain value respectively with B, C, D point under this state, such as UAa-
UBa、UAa-UCa、UAa-UDa；
D) will subtract each other in step b) with strain value of the A points strain value respectively with B, C, D point, such as UAb-UBb、UAb-UCb、
UAb-UDb；
E) difference obtained in step d, step c is divided by (wave/shimmy value), selects the point in the value of ratio minimum
As R2 measuring points, i.e., from (UAb-UBb)/(UAa-UBa)、(UAb-UCb)/(UAa-UCa)、(UAb-UDb)/(UAa-UDa) in selection numerical value
Minimum one group is selected a little from B, C, D as R2.
2.3) step 1 and 2 is repeated on remaining section, finds out the R2 measuring points on corresponding section.
By the arrangement of the optical fiber measurement blade combined load more than present invention and group bridge method, realize that optical fiber is revolved in rotation
Load measurement on the wing.The present invention can directly apply to the measurement of lifting airscrew combined load, compared with former measurement method,
Lifting airscrew load will be greatly decreased since its is smaller, cost is lower and longer service life in optical fiber in the present invention
The consumptive material expense of lotus measurement, test repair the time and test original paper to be influenced for the shape of the components such as blade.
The above is only the optimal specific embodiment of the present invention, but protection scope of the present invention is not limited thereto,
Any one skilled in the art in the technical scope disclosed by the present invention, the change or replacement that can be readily occurred in,
It should be covered by the protection scope of the present invention.Therefore, protection scope of the present invention should be with the protection model of the claim
Subject to enclosing.
Claims (5)
1. a kind of lifting airscrew combined load test fiber arrangement and group bridge method, which is characterized in that including
1) fiber arrangement under combined load
Wave the arrangement of direction load measurement optical fiber：The multiple blades measured as needed are tested section and are waving orientation measurement light
Imprinting is had what light deleted sensor to wave direction load measurement optical fiber along blade gas by the grating sensor of the identical quantity of imprinting on fibre
Dynamic center line is arranged in blade surface；
The arrangement of edgewise direction load measurement optical fiber：Edgewise direction load measurement optical fiber is a plurality of and each parallel to aerodynamic center line
Set, on every edgewise direction load measurement optical fiber imprinting have and wave quantity and the position on the load measurement optical fiber of direction homogeneous
With grating sensor, wherein, an edgewise direction load measurement optical fiber between aerodynamic center line and blade leading edge, remaining
Edgewise direction load measurement optical fiber is between aerodynamic center line and blade trailing edge；And arrange compensation sensing in propeller shank
Device；
2) fibre strain group bridge
2.1) single section waves direction：Using the grating sensor waved on the load measurement optical fiber of direction and compensation sensor into
Row group bridge；
Single section edgewise direction：Using on the edgewise direction load measurement optical fiber between aerodynamic center line and blade leading edge
Grating sensor and one edgewise direction load measurement optical fiber between aerodynamic center line and blade trailing edge in grating
Sensor carries out a group bridge；
2.2) repeat step 2.1 and obtain the fibre strain group bridge that multiple blades are tested under section.
2. lifting airscrew combined load test fiber arrangement according to claim 1 and group bridge method, which is characterized in that
Distance of the load measurement optical fiber away from aerodynamic center line between aerodynamic center line and blade trailing edge is aerodynamic center line and paddle
Integral multiple of the load measurement optical fiber away from aerodynamic center linear distance between leaf leading edge.
3. lifting airscrew combined load test fiber arrangement and group bridge method according to 1, which is characterized in that compensation sensing
Device is temperature-compensating plate.
4. lifting airscrew combined load test fiber arrangement and group bridge method according to 3, which is characterized in that selection is pneumatic
The method of the grating sensor in one edgewise direction load measurement optical fiber between center line and blade trailing edge is：
By obtaining grating sensor on a plurality of edgewise direction load measurement optical fiber and measuring strain value waving direction and load counterweight；
Strain value is measured by obtaining grating sensor on a plurality of edgewise direction load measurement optical fiber in edgewise direction loading counterweight；
The edge grating sensor strain value that direction measures will be waved to make the difference with grating sensor strain value at trailing edge and will
The edge grating sensor strain value that edgewise direction measures makes the difference with grating sensor strain value at trailing edge, finally will the side of waving
To difference and the difference of edgewise direction do and compare, one group of composition of ratio minimum waves the bridge in direction.
5. lifting airscrew combined load test fiber arrangement and group bridge method according to 4, which is characterized in that the difference
For absolute value.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711256514.3A CN108082534B (en) | 2017-12-03 | 2017-12-03 | Optical fiber arrangement and bridging method for helicopter rotor wing composite load test |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711256514.3A CN108082534B (en) | 2017-12-03 | 2017-12-03 | Optical fiber arrangement and bridging method for helicopter rotor wing composite load test |
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| CN108082534A true CN108082534A (en) | 2018-05-29 |
| CN108082534B CN108082534B (en) | 2021-03-30 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109580057A (en) * | 2019-01-09 | 2019-04-05 | 武汉理工大学 | Lifting airscrew load monitoring system and method based on Built-In Optical-Fiber Sensors Used |
| CN112432746A (en) * | 2020-10-21 | 2021-03-02 | 中国人民解放军总参谋部第六十研究所 | Method for determining swing load coupling degree of helicopter blade |
| CN113029405A (en) * | 2021-02-04 | 2021-06-25 | 南京航空航天大学 | Blade bending moment decoupling and calibrating method based on optical fiber strain combined bridge circuit |
| CN113942642A (en) * | 2021-11-19 | 2022-01-18 | 中国直升机设计研究所 | Helicopter blade with pneumatic pressure measuring sensor |
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| CN103698063A (en) * | 2013-12-02 | 2014-04-02 | 成都阜特科技股份有限公司 | Wind generating set blade load measurement device and measurement method thereof |
| CN104648688A (en) * | 2013-11-25 | 2015-05-27 | 中国直升机设计研究所 | Paddle strain gauge arranging and decoupling method |
| CN106338384A (en) * | 2015-07-15 | 2017-01-18 | 成都阜特科技股份有限公司 | Wind generating set blade full-spanwise load measuring method |
| CN107401986A (en) * | 2017-07-26 | 2017-11-28 | 北京航空航天大学 | A kind of wing based on fiber grating actual measurement strain presses heart load method of real-time |
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| CN102353487A (en) * | 2011-06-16 | 2012-02-15 | 上海理工大学 | Paster of multidimensional force sensor and bridging method |
| CN104648688A (en) * | 2013-11-25 | 2015-05-27 | 中国直升机设计研究所 | Paddle strain gauge arranging and decoupling method |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109580057A (en) * | 2019-01-09 | 2019-04-05 | 武汉理工大学 | Lifting airscrew load monitoring system and method based on Built-In Optical-Fiber Sensors Used |
| CN112432746A (en) * | 2020-10-21 | 2021-03-02 | 中国人民解放军总参谋部第六十研究所 | Method for determining swing load coupling degree of helicopter blade |
| CN112432746B (en) * | 2020-10-21 | 2022-11-11 | 中国人民解放军总参谋部第六十研究所 | Method for determining swing load coupling degree of helicopter blade |
| CN113029405A (en) * | 2021-02-04 | 2021-06-25 | 南京航空航天大学 | Blade bending moment decoupling and calibrating method based on optical fiber strain combined bridge circuit |
| CN113942642A (en) * | 2021-11-19 | 2022-01-18 | 中国直升机设计研究所 | Helicopter blade with pneumatic pressure measuring sensor |
| CN113942642B (en) * | 2021-11-19 | 2023-09-08 | 中国直升机设计研究所 | Helicopter blade with pneumatic pressure measurement sensor |
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