CN113602523B - Loading system for wing load calibration test and application method thereof - Google Patents
Loading system for wing load calibration test and application method thereof Download PDFInfo
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- CN113602523B CN113602523B CN202110824556.2A CN202110824556A CN113602523B CN 113602523 B CN113602523 B CN 113602523B CN 202110824556 A CN202110824556 A CN 202110824556A CN 113602523 B CN113602523 B CN 113602523B
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- 238000012360 testing method Methods 0.000 title claims abstract description 59
- 238000000034 method Methods 0.000 title claims abstract description 12
- 238000006073 displacement reaction Methods 0.000 claims abstract description 4
- 239000003921 oil Substances 0.000 claims description 25
- 238000010330 laser marking Methods 0.000 claims description 6
- 239000010720 hydraulic oil Substances 0.000 claims description 3
- 238000009434 installation Methods 0.000 abstract description 11
- 239000000725 suspension Substances 0.000 abstract description 2
- 238000010276 construction Methods 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000010354 integration Effects 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000001105 regulatory effect Effects 0.000 description 2
- 238000004891 communication Methods 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
Classifications
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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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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/02—Details
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
- G01N3/10—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces generated by pneumatic or hydraulic pressure
- G01N3/12—Pressure testing
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- Physics & Mathematics (AREA)
- Health & Medical Sciences (AREA)
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- Engineering & Computer Science (AREA)
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- Aviation & Aerospace Engineering (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention discloses a loading system for a wing load calibration test and a using method thereof, and belongs to the field of aircraft structure tests. The device comprises an integral platform, wherein a plurality of T-shaped groove plates are arranged on the integral platform, each T-shaped groove plate is independently connected with a liftable module, the liftable module can move along the length and width directions of long strip holes of the T-shaped groove plates to carry out displacement fine adjustment, and a hydraulic actuator, a force sensor and a wing loading block are arranged on the liftable module; an air cushion module is arranged below the integral platform and is connected with the air cushion controller through an air pressure pipeline, and the integral platform can be suspended when the air cushion module is inflated. The invention realizes the whole suspension and the rapid movement of the whole set of test equipment through the air cushion module, and then positions the whole set of test equipment through the laser striping machine; meanwhile, the lifting module is arranged, so that the preset safety distance is ensured when the test equipment loads the wing in the test debugging and formal test stage, and the test installation precision and safety are improved.
Description
Technical Field
The invention relates to the field of aircraft structure tests, in particular to a loading system for a wing load calibration test and a using method thereof.
Background
At present, in the field of aircraft structure test, the aerofoil load calibration test has been developed to implement loading through a hydraulic coordination loading system, for example, in the prior art, patent CN104925270a discloses an invention patent named as a method, a tensile load test system, a ballast load test system and a debugging assembly, and when the aerofoil load calibration test is performed, the whole system is fixed on the lower surface of the aerofoil through an actuator base fixing device, and because the number of hydraulic actuators and auxiliary equipment is large, the problems of large field installation workload, large installation difficulty, low installation precision, disordered equipment placement and the like exist.
Disclosure of Invention
The invention aims to solve the problems of low installation precision, long test period, low safety and the like of wing load calibration tests in the prior art, and provides a loading system for the wing load calibration test and a use method thereof, which shortens the test period and improves the calibration efficiency.
In order to achieve the above object, the present invention has the following technical scheme:
the loading system for the wing load calibration test comprises an integral platform, wherein a plurality of T-shaped groove plates are arranged on the integral platform, each T-shaped groove plate is independently connected with a liftable module, the liftable module can move along the length and width directions of a long hole of the T-shaped groove plate to carry out displacement fine adjustment, and a hydraulic actuator cylinder, a force sensor and a wing loading block are arranged on the liftable module; an air cushion module is arranged below the integral platform and connected with the air cushion controller through an air pressure pipeline, and the integral platform can be suspended when the air cushion module is inflated.
Furthermore, the integral platform is provided with an oil distributor and a coordination loading control system cabinet, the oil distributor is connected with the hydraulic actuator cylinder through a hydraulic pipeline, and the coordination loading control system cabinet is connected with the hydraulic actuator cylinder and the force sensor through a control cable.
Further, three laser strippers are arranged on the integral platform and are used for focusing the integral platform and the horizontal measurement point of the wing by emitting vertical laser points.
Further, the cabinet of the coordination loading control system is connected with the control computer, and the oil separator is connected with the hydraulic substation through a hydraulic pipeline.
Further, the liftable module is a manual-automatic screw rod, and the upper end of the liftable module is connected with the base of the hydraulic actuator cylinder through a screw rod seat.
Furthermore, each hydraulic oil way connected to the oil separator can be provided with a pressure valve to realize independent pressure value setting.
Further, the integral platform comprises a frame and a flat plate arranged above the frame, and a safety fence is further arranged on the periphery of the integral platform.
The invention also provides a using method of the loading system for the wing load calibration test, which is based on the loading system for the wing load calibration test, and comprises the following steps:
s1, moving an airplane to a test position and installing and fixing the airplane;
s2, connecting an air cushion controller with an air source or an air compressor, controlling the air cushion module to inflate, suspending, moving or rotating the whole platform below the wing, opening a laser marking instrument, focusing through a vertical laser point and a horizontal wing measuring point, ensuring that the three laser points are aligned, closing the air cushion controller, and putting down the whole platform;
s3, adjusting the vertical position of the liftable module to be the lowest, performing test debugging, operating the hydraulic actuator cylinder and the force sensor and coordinating with the loading control system cabinet, adjusting the pressure value of each oil way of the oil separator, and testing the operation condition of the oil separator;
and S4, after debugging is completed, lifting the liftable module to a proper position, and entering a formal test.
The loading system provided by the invention has the advantages that the air cushion module realizes the integral suspension of the whole set of test equipment, quickly moves to the test position of the lower surface of the wing, and positions the whole set of test equipment through the coordinate positioning system, namely the laser marking instrument, so as to accurately determine the mounting position; meanwhile, the lifting module is arranged, so that the safety distance is preset when the test equipment loads the wing in the test debugging and formal test stage, the limit is set, and the test loading system for safely implementing the test is ensured.
In summary, the invention has the following advantages:
1. according to the invention, the integration of resources is realized by arranging the integral platform, so that the whole system looks more neat and orderly;
2. according to the loading system, the whole platform is provided with the air cushion module, so that the whole platform is integrally moved, turned and installed in place, and the test installation time is shortened;
3. the loading system is provided with the laser marking instrument, and the measuring precision can reach +/-1 mm through laser point positioning, so that the field installation precision is ensured;
4. the loading system is provided with the liftable module, the liftable module can adjust the vertical distance of the hydraulic actuator cylinder, and the loading range of the actuator cylinder is limited through mechanical limiting; each hydraulic oil way on the equipped oil separator can be independently provided with a pressure value, so that the loading of the actuating cylinder is ensured not to exceed the limit, and the safety of the test is ensured by the two measures;
5. the liftable module is connected with the hydraulic actuator cylinder base through the manual screw rod seat, so that the hydraulic actuator cylinder can be vertically adjusted and lifted, the T-shaped groove plate is matched with the strip hole design, the direction of the expanding direction and the direction of the heading direction can be adjusted, the combination of the direction of the expanding direction and the direction of the heading direction can be realized, the hydraulic actuator cylinder can realize the function of adjusting the positions of three coordinate directions, and the application range is enlarged.
Drawings
FIG. 1 is a front view of a loading system for an aircraft wing load calibration test;
FIG. 2 is a top view of a loading system for an aircraft wing load calibration test;
FIG. 3 is an isometric view of a loading system for an aircraft wing load calibration test;
FIG. 4 is a construction view of a T-shaped channel plate;
FIG. 5 is a unitary platform frame construction;
FIG. 6 is a diagram of a liftable module configuration;
FIG. 7 is a diagram of an air cushion controller and air cushion module configuration.
In the figure:
1. the device comprises a wing loading block, 2, force sensors, 3, a hydraulic actuator cylinder, 4, a railing, 5, an oil distributor, 6, an integral platform, 7, a T-shaped groove plate, 8, a liftable module, 9, an air cushion controller, 10, an air cushion module, 11, a laser marking instrument, 12, a coordination loading control system cabinet, 13, a frame, 14, a safety fence, 15 and a wing.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention. The components of the embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the invention, as presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further definition or explanation thereof is necessary in the following figures.
In the description of the present invention, it should be noted that, directions or positional relationships indicated by terms such as "upper", "vertical", "inner", "outer", etc., are directions or positional relationships based on those shown in the drawings, or are directions or positional relationships conventionally put in place when the inventive product is used, or are directions or positional relationships conventionally understood by those skilled in the art, are merely for convenience of describing the present invention and for simplifying the description, and do not indicate or imply that the apparatus or element to be referred to must have a specific direction, be constructed and operated in a specific direction, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and the like, are used merely to distinguish between descriptions and should not be construed as indicating or implying relative importance.
In the description of the present invention, it should also be noted that, unless explicitly specified and limited otherwise, the terms "disposed," "mounted," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
Example 1
The embodiment provides a loading system for a wing load calibration test, as shown in fig. 1-3, the loading system for the wing load calibration test comprises an integral platform 6, wherein a plurality of T-shaped groove plates 7 are arranged on the integral platform 6, each T-shaped groove plate 7 is independently connected with a liftable module 8, the liftable module 8 can move along the length and width directions of long holes of the T-shaped groove plates 7 to carry out displacement fine adjustment, and a hydraulic actuator 3, a force sensor 2 and a wing 15 loading block are arranged on the liftable module 8; an air cushion module 10 is arranged below the integral platform 6, the air cushion module 10 is connected with an air cushion controller 9 through an air pressure pipeline, and the integral platform 6 can be suspended when the air cushion module 10 is inflated.
Furthermore, the integral platform 6 is provided with an oil separator 5 and a coordination loading control system cabinet 12, the oil separator 5 is connected with the hydraulic actuator cylinder 3 through a hydraulic pipeline, and the coordination loading control system cabinet 12 is connected with the hydraulic actuator cylinder 3 and the force sensor 2 through control cables.
Further, three laser graticules 11 are provided on the integral platform 6, and the three laser graticules 11 are used for focusing the horizontal measuring points of the integral platform 6 and the wing 15 by emitting vertical laser points.
The integral platform 6 is provided with the air cushion module 10, so that the integral movement, steering and installation of the integral platform 6 in place are realized, and the test installation time is shortened; the laser striping machine 11 is provided, and the measuring precision can reach +/-1 mm through laser point positioning, so that the field installation precision is ensured. The lifting module 8 is provided, the vertical distance of the hydraulic actuator cylinder 3 can be adjusted, and the loading range of the actuator cylinder is limited through mechanical limiting; each oil way on the equipped oil separator 5 can be independently provided with a pressure value, so that the loading of the actuating cylinder is ensured not to exceed the limit, and the safety of the test is ensured by the two measures. Meanwhile, the whole platform 6 realizes the integration of resources, so that the whole system looks more neat and orderly.
Example 2
The invention provides a loading system for a wing load calibration test, which comprises an integral platform 6, wherein the integral platform 6 mainly comprises a frame 13 and a flat plate arranged on the frame 13. As shown in fig. 5, a frame 13 of the integral platform 6 is constructed. The outside of the integral platform 6 is provided with a safety fence 14, so that the safety of the test environment is ensured.
The integral platform 6 is provided with a plurality of T-shaped groove plates 7, lifting modules 8 and hydraulic actuating cylinders 3 with the same number are arranged on the T-shaped groove plates 7, and the hydraulic actuating cylinders 3 are connected with a force sensor 2 and a wing 15 loading block.
As shown in fig. 6, the liftable module 8 is an automatic and manual screw rod, the upper end of the liftable module is connected with the base of the hydraulic actuator cylinder 3 through a screw rod seat, and the liftable module is used for realizing lifting adjustment of the hydraulic actuator cylinder 3 in the vertical direction, the T-shaped groove plate 7 is matched with the strip hole design of the liftable module, so that the direction of the unfolding direction and the direction of the heading direction can be adjusted, the combination of the two can be realized, the function of adjusting the positions of the three coordinate directions of the hydraulic actuator cylinder 3 is formed, and the application range is enlarged.
The integral platform 6 is provided with an oil distributor 5, and the oil distributor 5 is provided with a hydraulic pipeline connected with the hydraulic actuator cylinder 3 and used for providing hydraulic power.
The integral platform 6 is provided with a coordination loading control system cabinet 12, and the coordination loading control system cabinet 12 is provided with a control circuit and is connected with the hydraulic actuator cylinder 3.
As shown in fig. 7, the air cushion module 10 and the air cushion controller 9 are arranged below the integral platform 6, and after the air cushion module 10 is inflated, the integral platform 6 moves upwards to float, so that the integral platform 6 can be conveniently moved, turned and shifted, and the labor intensity is greatly reduced.
The laser striping machine 11 is arranged at three positions on the integral platform 6, the laser striping machine 11 can throw light beams, has a horizontal adjusting function, is calibrated through measurement before use, and ensures the installation accuracy by positioning the position of a horizontal measuring point (namely a datum point) of the wing 15 through a laser point.
The embodiment also provides a using method of the loading system for the wing load calibration test, which comprises the following steps:
step one: the aircraft is moved to the test position and is fixed.
Step two: the air cushion controller 9 is connected with an air source or an air compressor, controls the air cushion module 10 to work, the integral platform 6 is suspended, the integral platform 6 can be moved and rotated to the approximate position of the lower surface of the wing 15, the laser marking instrument 11 is opened, the alignment of the positions of the three laser points is ensured through focusing of the vertical laser points and the horizontal measuring points (datum points) of the wing 15, the air cushion controller 9 is closed, and the integral platform 6 is put down.
Step three: the oil separator 5 is connected with a hydraulic pipeline of the hydraulic substation, and the coordination loading control system cabinet 12 is connected with a loading control computer.
Step four: and the vertical position of the lifting module 8 is regulated to be reduced to the minimum, test and debugging are carried out, the hydraulic actuator cylinder 3, the force sensor 2 and the coordination loading control system cabinet 12 are operated, the pressure value of each oil way of the oil separator 5 is regulated, and the operation condition is tested. After the debugging is completed, the liftable module 8 is lifted to a proper position (based on the expected deformation in the wing 15 test) and enters a formal test.
Although specific embodiments of the invention have been described in detail with reference to the accompanying drawings, it should not be construed as limiting the scope of protection of the present patent. Various modifications and variations which may be made by those skilled in the art without the creative effort are within the scope of the patent described in the claims.
The foregoing description is only a preferred embodiment of the present invention, and is not intended to limit the present invention in any way, and any simple modification, equivalent variation, etc. of the above embodiment according to the technical matter of the present invention fall within the scope of the present invention.
Claims (3)
1. The application method of the loading system for the wing load calibration test is characterized in that the loading system comprises an integral platform (6), a plurality of T-shaped groove plates (7) are arranged on the integral platform (6), each T-shaped groove plate (7) is independently connected with a liftable module (8), the liftable module (8) can move along the length and width directions of a long hole of the T-shaped groove plate (7) to carry out displacement fine adjustment, and a hydraulic actuator (3), a force sensor (2) and a wing (15) loading block are arranged on the liftable module (8); an air cushion module (10) is arranged below the integral platform (6), the air cushion module (10) is connected with an air cushion controller (9) through an air pressure pipeline, and the integral platform (6) can be suspended when the air cushion module (10) is inflated;
the integrated platform (6) is provided with an oil separator (5) and a coordination loading control system cabinet (12), the oil separator (5) is connected with the hydraulic actuator cylinder (3) through a hydraulic pipeline, and the coordination loading control system cabinet (12) is connected with the hydraulic actuator cylinder (3) and the force sensor (2) through control cables; three laser strippers (11) are arranged on the integral platform (6), and the three laser strippers (11) are used for focusing the horizontal measuring points of the integral platform (6) and the wing (15) by emitting vertical laser points; the coordination loading control system cabinet (12) is connected with a control computer, and the oil separator (5) is connected with the hydraulic substation through a hydraulic pipeline; each hydraulic oil way connected with the oil separator (5) can be provided with a pressure valve to realize independent pressure value setting;
the using method is as follows:
s1, moving an airplane to a test position and installing and fixing the airplane;
s2, connecting an air cushion controller (9) with an air source or an air compressor, controlling an air cushion module (10) to inflate, suspending the whole platform (6), moving or rotating the whole platform (6) to the lower part of a wing (15), opening a laser marking instrument (11), focusing through a vertical laser point and a horizontal measuring point of the wing (15), ensuring that the three laser points are aligned, closing the air cushion controller (9), and putting down the whole platform (6);
s3, adjusting the vertical position of the liftable module (8) to be the lowest, performing test debugging, operating the hydraulic actuator cylinder (3), the force sensor (2) and the coordination loading control system cabinet (12), adjusting the pressure value of each oil way of the oil separator (5), and testing the operation condition of the oil way;
and S4, after debugging is completed, lifting the liftable module (8) to a proper position, and entering a formal test.
2. The method for using the loading system for the wing load calibration test according to claim 1, wherein the liftable module (8) is a manual-automatic screw rod, and the upper end of the liftable module is connected with the base of the hydraulic actuator cylinder (3) through a screw rod seat.
3. The method for using the loading system for the wing load calibration test according to claim 1, wherein the integral platform (6) comprises a frame (13) and a flat plate arranged above the frame (13), and a safety fence (14) is further arranged on the periphery of the integral platform (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202110824556.2A CN113602523B (en) | 2021-07-21 | 2021-07-21 | Loading system for wing load calibration test and application method thereof |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110824556.2A CN113602523B (en) | 2021-07-21 | 2021-07-21 | Loading system for wing load calibration test and application method thereof |
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| CN113602523A CN113602523A (en) | 2021-11-05 |
| CN113602523B true CN113602523B (en) | 2024-01-12 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115014746A (en) * | 2022-07-08 | 2022-09-06 | 大连理工大学 | Wing follow-up deformation loading device |
| CN115791426B (en) * | 2023-02-07 | 2023-04-11 | 四川炬原玄武岩纤维科技有限公司 | Basalt fiber composite pipe pressure testing device and method |
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