CN113602523A - Loading system for wing load calibration test and using method thereof - Google Patents
Loading system for wing load calibration test and using method thereof Download PDFInfo
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- CN113602523A CN113602523A CN202110824556.2A CN202110824556A CN113602523A CN 113602523 A CN113602523 A CN 113602523A CN 202110824556 A CN202110824556 A CN 202110824556A CN 113602523 A CN113602523 A CN 113602523A
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- 238000012360 testing method Methods 0.000 title claims abstract description 62
- 238000000034 method Methods 0.000 title claims abstract description 11
- 239000003550 marker Substances 0.000 claims abstract description 5
- 238000006073 displacement reaction Methods 0.000 claims abstract description 4
- 239000003921 oil Substances 0.000 claims description 26
- 239000010720 hydraulic oil Substances 0.000 claims description 3
- 238000009434 installation Methods 0.000 abstract description 11
- 238000005259 measurement Methods 0.000 description 4
- 238000013461 design Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000010354 integration Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000010276 construction Methods 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
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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
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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
- G01N3/08—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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Abstract
The invention discloses a loading system for a wing load calibration test and a using method thereof, belonging to the field of airplane 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 a long hole of the T-shaped groove plate to perform 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, the air cushion module is connected with an air cushion controller through an air pressure pipeline, and the integral platform can be suspended when the air cushion module is inflated. The whole set of test equipment is suspended and moved quickly through the air cushion module, and then is positioned through the laser line marker; and meanwhile, the liftable module is arranged, so that the safety distance is preset when the test equipment loads the wings in the test debugging and formal test stages, and the test installation precision and safety are improved.
Description
Technical Field
The invention relates to the field of airplane structure tests, in particular to a loading system for an airplane wing load calibration test and a using method thereof.
Background
At present, in the field of airplane structure tests, wing load calibration tests are carried out until loading is carried out through a hydraulic coordination loading system, for example, in the prior art, patent CN104925270A discloses an invention patent named as 'a method, a pull load test system, a pressure load test system and a debugging assembly', when the wing load calibration tests are carried out, the whole system is fixed on the lower surface of a wing through an actuator cylinder base fixing device, and due to the fact that hydraulic actuator cylinders and auxiliary equipment are large in number, the problems of large field installation workload, large installation difficulty, low installation precision, disordered equipment arrangement 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 a wing load calibration test in the prior art, and provides a loading system of the wing load calibration test and a using method thereof, so that the test period is shortened, and the calibration efficiency is improved.
In order to achieve the above object, the technical solution of the present invention is as follows:
a loading system for a 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 direction and the width direction of a long hole of the T-shaped groove plate to perform 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, the air cushion module is connected with an air cushion controller through an air pressure pipeline, and the integral platform can be suspended when the air cushion module is inflated.
Furthermore, an oil distributor and a coordinated loading control system cabinet are arranged on the integral platform, the oil distributor is connected with the hydraulic actuating cylinder through a hydraulic pipeline, and the coordinated loading control system cabinet is connected with the hydraulic actuating cylinder and the force sensor through control cables.
Furthermore, three laser line marking instruments are arranged on the integral platform and used for enabling the integral platform and the wing horizontal measuring point to be focused by emitting vertical laser points.
Furthermore, the coordinated loading control system cabinet is connected with the control computer, and the oil separator is connected with the hydraulic substation through a hydraulic pipeline.
Furthermore, the lifting module is a manual-automatic screw rod, and the upper end of the lifting module is connected with the base of the hydraulic actuating cylinder through a screw rod seat.
Furthermore, each hydraulic oil circuit connected to the oil separator can be provided with a pressure valve to realize independent pressure value setting.
Furthermore, 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 use method of the loading system for the wing load calibration test, and the method comprises the following steps of:
step S1, moving the airplane to a test position and installing and fixing the airplane;
step S2, connecting the air cushion controller with an air source or an air compressor, controlling the air cushion module to inflate to enable the whole platform to suspend, moving or rotating the whole platform to the lower part of the wing, opening the laser line marker, ensuring the alignment of the three laser points through the vertical laser point and the horizontal measurement point focusing of the wing, then closing the air cushion controller, and putting down the whole platform;
s3, adjusting the vertical position of the lifting module to be minimized, performing test debugging, operating the hydraulic actuator cylinder and the force sensor and coordinating and loading a 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 step S4, after debugging is completed, lifting the lifting module to a proper position, and entering a formal test.
According to the loading system, the air cushion module realizes integral suspension of the whole set of test equipment, quickly moves to the test position on the lower surface of the wing, and positions the whole set of test equipment through a coordinate positioning system, namely a laser line marker, so that the installation position is accurately determined; and meanwhile, the liftable module is arranged, so that the safe distance is preset and the limit is set when the test equipment loads the wings in the test debugging and formal test stages, and the test loading system is ensured to be safely implemented.
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 tidy and ordered;
2. according to the loading system, the integral platform is provided with the air cushion module, so that the integral 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 line marking instrument, the measurement precision can reach +/-1 mm through laser point positioning, and the field installation precision is ensured;
4. the loading system is provided with the lifting module, the lifting module can adjust the vertical distance of the hydraulic actuating cylinder, and the loading range of the actuating cylinder is limited through mechanical limit; each hydraulic oil adjusting circuit on the oil separator can independently set a pressure value, so that the loading of the actuating cylinder is not over-limit, and the safety of the test is ensured by the two measures;
5. the lifting module is connected with the hydraulic actuator cylinder base through the manual screw rod base, the hydraulic actuator cylinder can be adjusted to lift in the vertical direction, the T-shaped groove plate is matched with the long-strip-shaped hole design, the unfolding direction adjustment and the course direction adjustment can be realized, and the lifting module and the T-shaped groove plate are combined to form the hydraulic actuator cylinder, so that the function of adjusting the positions in three coordinate directions can be realized, and the application range is expanded.
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 view of a T-slot plate configuration;
FIG. 5 is a view of an integral platform frame construction;
FIG. 6 is a structural diagram of a liftable module;
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, a force sensor, 3, a hydraulic actuator cylinder, 4, a railing, 5, an oil separator, 6, an integral platform, 7, a T-shaped trough plate, 8, a lifting module, 9, an air cushion controller, 10, an air cushion module, 11, a laser striping machine, 12, a coordinated loading control system cabinet, 13, a frame, 14, a safety fence, 15 and wings.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. The components of 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 present invention, 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 derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
In the description of the present invention, it should be noted that the terms "upper", "vertical", "inside", "outside", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, or orientations or positional relationships that are conventionally arranged when the products of the present invention are used, or orientations or positional relationships that are conventionally understood by those skilled in the art, and are used for convenience of description and simplification of description, but do not indicate or imply that the devices or elements that are referred to must have specific orientations, be constructed in specific orientations, and be operated, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and the like are used merely to distinguish one description from another, and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "disposed," "mounted," and "connected" are to be construed broadly, e.g., as meaning fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled 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 lifting module 8, each lifting module 8 can move along the length direction and the width direction of a long hole of the T-shaped groove plate 7 to perform displacement fine adjustment, and a hydraulic actuating cylinder 3, a force sensor 2 and a wing 15 loading block are arranged on each lifting 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.
Further, an oil separator 5 and a coordinated loading control system cabinet 12 are arranged on the integral platform 6, the oil separator 5 is connected with the hydraulic actuator cylinder 3 through a hydraulic pipeline, and the coordinated loading control system cabinet 12 is connected with the hydraulic actuator cylinder 3 and the force sensor 2 through control cables.
Furthermore, three laser striping machines 11 are arranged on the integral platform 6, and the three laser striping machines 11 are used for focusing the horizontal measuring points of the integral platform 6 and the wings 15 by emitting vertical laser points.
The integral platform 6 is provided with the air cushion module 10, so that the integral platform 6 is integrally moved, turned and installed in place, and the test installation time is shortened; the device is provided with a laser line marking instrument 11, the measurement precision can reach +/-1 mm through laser point positioning, and the field installation precision is ensured. The equipped lifting module 8 can adjust the vertical distance of the hydraulic actuating cylinder 3, and limit the loading range of the actuating cylinder through mechanical limit; each oil path on the oil separator 5 can be independently provided with a pressure value, so that the loading of the actuating cylinder is not over-limit, and the two measures ensure the safety of the test. Meanwhile, the integral platform 6 realizes the integration of resources, so that the whole system looks more tidy and ordered.
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, the frame 13 of the integrated platform 6 is constructed. A safety fence 14 is arranged on the outer side of the integral platform 6, 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, the T-shaped groove plates 7 are provided with lifting modules 8 and hydraulic actuating cylinders 3 which are the same in number, and the hydraulic actuating cylinders 3 are connected with force sensors 2 and wing 15 loading blocks.
As shown in fig. 6, the lifting module 8 is a manual-automatic screw rod, the upper end of the lifting module is connected with the base of the hydraulic actuator cylinder 3 through a screw rod seat for realizing the lifting adjustment of the hydraulic actuator cylinder 3 in the vertical direction, the T-shaped trough plate 7 is matched with the design of the long strip hole thereof for realizing the unfolding direction adjustment and the course direction adjustment, and the combination of the two realizes the function of the hydraulic actuator cylinder 3 for realizing the position adjustment in three coordinate directions, thereby expanding the application range.
The integral platform 6 is provided with an oil separator 5, and the oil separator 5 is provided with a hydraulic pipeline connected with the hydraulic actuating 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 connected with the hydraulic actuating cylinders 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 when the air cushion module 10 is inflated, the integral platform 6 moves upwards to float, so that the whole integral platform 6 can be conveniently moved, turned and displaced, and the labor intensity of workers is greatly reduced.
The embodiment also provides a use method of the loading system for the wing load calibration test, which comprises the following steps:
the method comprises the following steps: and (4) moving the airplane to a test position, and installing and fixing the airplane.
Step two: the air cushion controller 9 is connected with an air source or an air compressor to control 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 line marker 11 is opened, the horizontal measuring point (reference point) of the wing 15 is focused through the vertical laser point, the alignment of the three laser points is ensured, 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 coordinated loading control system cabinet 12 is connected with a loading control computer.
Step four: and adjusting the vertical position of the lifting module 8 to be minimized, 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 separator. After debugging is finished, the lifting module 8 is lifted to a proper position (based on the predicted deformation in the wing 15 test), and a formal test is carried out.
While the present invention has been described in detail with reference to the illustrated embodiments, it should not be construed as limited to the scope of the present patent. Various modifications and changes may be made by those skilled in the art without inventive step within the scope of the appended claims.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention in any way, and all simple modifications and equivalent variations of the above embodiments according to the technical spirit of the present invention are included in the scope of the present invention.
Claims (8)
1. The loading system for the wing load calibration test is characterized by comprising 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 lifting module (8), each lifting module (8) can move along the length direction and the width direction of a long hole of each T-shaped groove plate (7) to perform displacement fine adjustment, and a hydraulic actuating cylinder (3), a force sensor (2) and a wing (15) loading block are arranged on each lifting 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.
2. The loading system for the wing load calibration test according to claim 1, wherein an oil separator (5) and a coordinated loading control system cabinet (12) are arranged on the integral platform (6), the oil separator (5) is connected with the hydraulic actuator cylinder (3) through a hydraulic pipeline, and the coordinated loading control system cabinet (12) is connected with the hydraulic actuator cylinder (3) and the force sensor (2) through control cables.
3. The loading system for the wing load calibration test according to claim 1 or 2, characterized in that three laser striping machines (11) are arranged on the integral platform (6), and the three laser striping machines (11) are used for focusing the integral platform (6) and the horizontal measuring point of the wing (15) by emitting vertical laser spots.
4. The loading system for wing load calibration test according to claim 2, wherein the coordinated loading control system cabinet (12) is connected with the control computer, and the oil separator (5) is connected with the hydraulic substation through a hydraulic pipeline.
5. The loading system for wing load calibration test according to claim 1, wherein the lifting module (8) is a manual-automatic screw rod, and the upper end of the lifting module is connected with the base of the hydraulic actuator cylinder (3) through a screw rod seat.
6. The loading system for the wing load calibration test is characterized in that each hydraulic oil path connected to the oil separator (5) can be configured with a pressure valve to realize an independent set pressure value.
7. The loading system for the wing load calibration test is characterized in that the integrated 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 integrated platform (6).
8. The use method of the loading system for the wing load calibration test according to claim 3, characterized by comprising the following steps:
step S1, moving the airplane to a test position and installing and fixing the airplane;
step S2, connecting an air cushion controller (9) with an air source or an air compressor, controlling an air cushion module (10) to inflate, enabling an integral platform (6) to suspend, moving or rotating the integral platform (6) to the lower part of a wing (15), opening a laser line marker (11), ensuring that the positions of three laser points are aligned through focusing of a vertical laser point and a horizontal measuring point of the wing (15), then closing the air cushion controller (9), and putting down the integral platform (6);
s3, adjusting the vertical position of the lifting module (8) to be 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 separator;
and step S4, after debugging is completed, lifting the lifting module (8) to a proper position, and entering a formal test.
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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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| 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 true CN113602523A (en) | 2021-11-05 |
| CN113602523B CN113602523B (en) | 2024-01-12 |
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Cited By (2)
| 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 |
| CN115791426A (en) * | 2023-02-07 | 2023-03-14 | 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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