CN106248322A - A kind of wing-box assay device of curved scissors loading - Google Patents
A kind of wing-box assay device of curved scissors loading Download PDFInfo
- Publication number
- CN106248322A CN106248322A CN201610529962.5A CN201610529962A CN106248322A CN 106248322 A CN106248322 A CN 106248322A CN 201610529962 A CN201610529962 A CN 201610529962A CN 106248322 A CN106248322 A CN 106248322A
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- 238000003556 assay Methods 0.000 title abstract 4
- 238000010008 shearing Methods 0.000 claims abstract description 11
- 238000012360 testing method Methods 0.000 claims description 38
- 238000005452 bending Methods 0.000 claims description 36
- 230000003014 reinforcing effect Effects 0.000 claims description 8
- 238000003032 molecular docking Methods 0.000 claims description 7
- 238000012546 transfer Methods 0.000 claims description 4
- 238000010586 diagram Methods 0.000 description 8
- 210000001503 joint Anatomy 0.000 description 6
- 230000005540 biological transmission Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 239000006185 dispersion Substances 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000013001 point bending Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M5/00—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings
- G01M5/0016—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings of aircraft wings or blades
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention discloses the wing-box assay device of a kind of curved scissors loading.The wing-box assay device of described curved scissors loading includes: the first bottom girder, and it has a supporting surface；Charger, its one end is arranged on the supporting surface of described first bottom girder；First loads clamping device, and it is connected with the other end of described charger, and described first loads clamping device has a bare terminal end；Second bottom girder, it has a supporting surface；Support means, its one end is arranged on the supporting surface of described second bottom girder；Second loads clamping device, and it is connected with the other end of described support means, and described second loads clamping device has a bare terminal end；Stopping means, its one end is arranged on the supporting surface of described second bottom girder, and the other end loads clamping device with described second and is connected.The wing-box assay device of the curved scissors loading in the present invention utilizes " lever " principle to be supported and load, and loading is " moment of flexure " or " moment of flexure+shearing ".
Description
Technical Field
The invention relates to the technical field of airplane strength tests, in particular to a wing box section test device in a bending shear loading mode.
Background
The wing box of the wing is used as a main bearing part of an airplane structure, and the load mainly comprises: airfoil aerodynamics, inertial forces (including loads) of the wing and other components, and concentrated loads transferred by the landing gear during takeoff and landing. The internal forces on the cross section are mainly: bending moment, shear force and torque. In the development stage, a certain section of the wing box is usually selected to simulate a real wing box for strength examination through appropriate simplification. For the wing box section test with the loading form of bending moment or bending moment plus shearing force, the test is carried out by a device consisting of a bearing wall, a supporting clamp, a test piece and a loading clamp in the prior art, the bending moment load is applied by mainly utilizing the beam four-point bending principle, and the shearing force cannot be applied.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
It is an object of the present invention to provide a wing box test apparatus in the form of a curved shear load which overcomes or at least alleviates at least one of the above-mentioned disadvantages of the prior art.
In order to achieve the above object, the present invention provides a bending shear loaded wing box section testing device, which comprises: a first bottom beam having a support surface; one end of the loading device is arranged on the supporting surface of the first bottom beam; the first loading clamping device is connected with the other end of the loading device and is provided with a clamping end; a second bottom beam having a support surface; one end of the supporting device is arranged on the supporting surface of the second bottom beam; the second loading clamping device is connected with the other end of the supporting device and is provided with a clamping end; one end of the limiting device is arranged on the supporting surface of the second bottom beam, and the other end of the limiting device is connected with the second loading clamping device; the clamping end of the first loading clamping device is opposite to the clamping end of the second loading clamping device and is used for clamping the wing box section to be tested between the two clamping ends; the loading device is used for providing loading force for the wing box section to be tested, so that the wing box section to be tested is subjected to bending moment or bending moment and shearing force at the same time; the limiting device is used for limiting the first loading clamping device to move in the connecting direction of the first loading clamping device, the wing box section to be tested and the second loading clamping device.
Preferably, the loading device comprises two sets of cylinders, and the two sets of cylinders are sequentially arranged in the connecting direction of the first loading clamping device, the wing box to be tested and the second loading clamping device.
Preferably, each set of cylinders comprises two cylinders 21.
Preferably the cylinder of each ram is hinged to the first sill; and a piston rod of the actuating cylinder is hinged with the first loading clamping device.
Preferably, the first loading fixture comprises: a first loading box section connected with the loading device; a first docking plate disposed at one end of the first load cassette section; the first adapter plate is connected with the first butt plate, and one face of the first adapter plate is a connecting face and is used for being connected with a wing box section to be tested.
Preferably, the second loading fixture comprises: the second loading box section is connected with the supporting device and the limiting device; a second docking plate disposed at one end of the second load box section; and one surface of the second adapter plate is arranged to be a connecting surface and is used for being connected with a wing box section to be tested.
Preferably, the wing box section test device in the bending shear loading mode further comprises a pad beam, and the supporting device is connected with the second loading box section through the pad beam.
Preferably, the limiting device comprises: stop device body to and spacing angle box subassembly, spacing angle box subassembly includes: the limiting angle box comprises two intersected plate-shaped bodies, a reinforcing rib is arranged between the two plate-shaped bodies, and the reinforcing rib divides the two plate-shaped bodies into two accommodating spaces; the hinged support is arranged in the accommodating space and is provided with a concave part; the convex hinge structure is provided with a protruding part which is arranged in the concave part of the hinge support and is connected with the hinge support; the convex hinge structure is connected with the second loading box section.
Preferably, the limiting device body comprises two crossed supporting beams, wherein one supporting beam is perpendicular to the other supporting beam, and a reinforcing plate is arranged between the two supporting beams.
The wing box section test device in the bending shear loading mode utilizes the lever principle to support and load, and the loading mode is bending moment or bending moment plus shearing force, so that the problem that the bending moment and the shearing force cannot be applied simultaneously in the prior art is solved.
Drawings
Fig. 1 is a schematic structural diagram of a wing box test device in a bending shear loading mode according to an embodiment of the invention.
Fig. 2 is a schematic structural diagram of a limit angle box in the wing box section testing device in the bending shear loading mode shown in fig. 1.
Fig. 3 is a schematic view of the hinge mount in the wing box test apparatus in the form of a curved shear load shown in fig. 1.
Fig. 4 is a schematic structural diagram of a convex hinge structure in the wing box testing device in a bending shear loading mode shown in fig. 1.
Fig. 5 is a schematic structural diagram of a limiting device body in the wing box section testing device in the bending shear loading mode shown in fig. 1.
Reference numerals
| 1 | First bottom beam | 32 | First butt joint plate |
| 2 | Loading device | 33 | First adapter plate |
| 3 | First loading clamping device | 61 | Second load cassette section |
| 4 | Second bottom beam | 62 | Second butt joint plate |
| 5 | Supporting device | 63 | Second adapter plate |
| 6 | Second loading clamping device | 9 | Pad beam |
| 7 | Limiting device | 71 | Limiting device body |
| 8 | Wing box section to be tested | 72 | Limit corner box |
| 21 | Actuating cylinder | 73 | Hinged support |
| 31 | First loading box section | 74 | Convex hinge structure |
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting 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. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present invention and for simplifying the description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the scope of the present invention.
Fig. 1 is a schematic structural diagram of a wing box test device in a bending shear loading mode according to an embodiment of the invention. Fig. 2 is a schematic structural diagram of a limit angle box in the wing box section testing device in the bending shear loading mode shown in fig. 1. Fig. 3 is a schematic view of the hinge mount in the wing box test apparatus in the form of a curved shear load shown in fig. 1. Fig. 4 is a schematic structural diagram of a convex hinge structure in the wing box testing device in a bending shear loading mode shown in fig. 1. Fig. 5 is a schematic structural diagram of a limiting device body in the wing box section testing device in the bending shear loading mode shown in fig. 1.
The wing box test device in the bending shear loading mode shown in fig. 1 comprises a first bottom beam 1, a loading device 2, a first loading clamping device 3, a second bottom beam 4, a supporting device 5, a second loading clamping device 6 and a limiting device 7.
Referring to fig. 1, in the present embodiment, an i-beam is used as the first base beam 1, one of two sides of the i-beam is used as a support and can be placed on a base, the other side is used as a support surface, and one end of the loading device 2 is arranged on the support surface of the first base beam 1; the first loading clamping device 3 is connected with the other end of the loading device 2, and the first loading clamping device 3 is provided with a clamping end.
Referring to fig. 1, the second bottom beam is an i-beam, one of two sides of the i-beam is used as a support and can be placed on the base, and the other side of the i-beam is used as a support surface. One end of the supporting device 5 is arranged on the supporting surface of the second bottom beam 4; a second loading gripping device 6 is connected to the other end of the support device 5, the second loading gripping device 6 having a gripping end. One end of the limiting device 7 is arranged on the supporting surface of the second bottom beam 4, and the other end of the limiting device is connected with the second loading clamping device 6; the clamping end of the first loading clamping device 3 is opposite to the clamping end of the second loading clamping device 6, and is used for clamping the wing box section 8 to be tested between the two clamping ends; the loading device 2 is used for providing loading force for the wing box section 8 to be tested, so that the wing box section 8 to be tested is subjected to bending moment or bending moment and shearing force at the same time; the limiting device 7 is used for limiting the displacement of the first loading fixture 3 in the connection direction of the first loading fixture, the wing box under test and the second loading fixture (the connection direction is the direction indicated by the arrow in fig. 1).
The wing box section test device in the bending shear loading mode utilizes the lever principle to support and load, and the loading mode is bending moment or bending moment plus shearing force, so that the problem that the bending moment and the shearing force cannot be applied simultaneously in the prior art is solved.
Referring to fig. 1, in the present embodiment, the loading device includes two sets of cylinder groups, which are sequentially disposed in a connection direction of the first loading fixture, the wing box under test, and the second loading fixture. When the actuator is used, one group of actuating cylinders applies force in one direction, and the other group of actuating cylinders applies force in the opposite direction, so that bending moment and/or shearing force can be formed.
In the present embodiment, each cylinder group includes two cylinders 21.
Referring to fig. 1, in the present embodiment, the cylinder of each ram is hinged to the first bottom beam; the piston rod of the actuating cylinder is hinged with the first loading clamping device. The articulated mode is adopted, a certain amount of deformation can be generated during force bearing, and the damage of the connection position or the influence on the test effect due to rigid connection is prevented.
Referring to fig. 1, in the present embodiment, the first loading clamping device 3 includes a first loading box section 31, a first butt plate 32 and a first transfer plate 33, the first loading box section 31 is connected with the loading device; the first butt plate 32 is disposed at one end of the first loading cassette section 31; the first adapter plate 33 is connected to the first docking plate 32, and one surface of the first adapter plate 33 is provided as a connection surface for connecting to the wing box 8 to be tested.
Referring to fig. 1, in the present embodiment, the second loading clamping device 6 includes a second loading box section 61, a second docking plate 62 and a second adapter plate 63, and the second loading box section 61 is connected to the supporting device 5 and the limiting device 7; the second butt plate 62 is arranged at one end of the second loading box section 61; the second adapter plate 63 is connected to the second adapter plate 62, and one surface of the second adapter plate 63 is set as a connection surface for connecting to the wing box 8 to be tested.
In this embodiment, the first loading box section and the second loading box section have the same structure and are both welded parts.
The first butt joint plate and the second butt joint plate are of the same structure.
The first adapter plate and the second adapter plate are of the same structure.
The same structure is adopted for the above structure, and the advantage is that the force transmission is uniform, and the force dispersion problem caused by the structure is avoided.
It can be understood that the first loading box section is connected with the first butt plate through bolts, and the number of the bolts is more than 10.
It can be understood that the first butt plate and the first transfer plate are connected through bolts, and the number of the bolts is more than 10.
It can be understood that the second loading box section is connected with the second butt plate through bolts, and the number of the bolts is more than 10.
It can be understood that the second docking plate and the second adapter plate are connected through bolts, and the number of the bolts is more than 10.
Because in the test process, first loading box section, first butt joint board, first keysets, second loading box section, second butt joint board and second keysets are the load-bearing part, consequently, the bolt quantity that adopts should be no less than 10, prevents that the junction from splitting.
Referring to fig. 1, in the present embodiment, the wing box test device in the form of a bending shear load further includes a pad beam 9, and the support device 5 is connected with the second loading box 61 through the pad beam 9. The pad beams are adopted for connection, so that the contact area can be increased, and stress concentration is prevented.
Referring to fig. 1 to 5, in the present embodiment, the limiting device 7 includes a limiting device body 71 and a limiting angle box assembly, the limiting angle box assembly includes a limiting angle box 72, a hinge support 73 and a convex hinge structure 74, the limiting angle box 72 includes two intersecting plate-shaped bodies, a reinforcing rib is disposed between the two plate-shaped bodies, and the reinforcing rib separates the two plate-shaped bodies into two accommodating spaces; the hinge support 73 is disposed in the accommodating space, the hinge support 73 having a concave portion; the male hinge 74 has a protrusion disposed in a recess of the hinge support 74, and the male hinge 74 is coupled to the hinge support 73; the male hinge structure 74 is connected to the second cassette section 61.
Referring to fig. 5, in this embodiment, the spacing device body 71 includes two intersecting support beams, one of which is disposed perpendicular to the other, with a reinforcing plate disposed between the two support beams. By adopting the structure, the strength of the limiting device body can be increased.
Finally, it should be pointed out that: the above examples are only for illustrating the technical solutions of the present invention, and are not limited thereto. Although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (9)
1. The utility model provides a wing box test device of curved shear loading form which characterized in that, the wing box test device of curved shear loading form includes:
-a first bottom beam (1), said first bottom beam (1) having a support surface;
the loading device (2), one end of the loading device (2) is arranged on the supporting surface of the first bottom beam (1);
the first loading clamping device (3), the first loading clamping device (3) is connected with the other end of the loading device (2), and the first loading clamping device (3) is provided with a clamping end;
-a second bottom beam (4), said second bottom beam (4) having a support surface;
one end of the supporting device (5) is arranged on a supporting surface of the second bottom beam (4);
a second loading clamping device (6), wherein the second loading clamping device (6) is connected with the other end of the supporting device (5), and the second loading clamping device (6) is provided with a clamping end;
one end of the limiting device (7) is arranged on the supporting surface of the second bottom beam (4), and the other end of the limiting device (7) is connected with the second loading clamping device (6); wherein,
the clamping end of the first loading clamping device (3) is opposite to the clamping end of the second loading clamping device (6) and is used for clamping the wing box section (8) to be tested between the two clamping ends;
the loading device (2) is used for providing loading force for the wing box section (8) to be tested, so that the wing box section (8) to be tested is subjected to bending moment or bending moment and shearing force at the same time;
the limiting device (7) is used for limiting the first loading clamping device (3) to move in the connecting direction of the first loading clamping device, the wing box section to be tested and the second loading clamping device.
2. The wing box test device in the bending shear loading form according to claim 1, wherein the loading device comprises two sets of cylinders, and the two sets of cylinders are sequentially arranged in a connection direction of the first loading clamping device, the wing box to be tested and the second loading clamping device.
3. Wing box test unit in bent shear loaded form according to claim 2, characterized in that each set of cylinders comprises two cylinders (21).
4. A wing box test rig in the form of a curved shear load as claimed in claim 3, wherein the cylinder of each ram is hinged to the first sill; and a piston rod of the actuating cylinder is hinged with the first loading clamping device.
5. Wing box test unit in the form of a curved shear load according to claim 2, characterized in that the first loading clamp (3) comprises:
a first loading cassette section (31), the first loading cassette section (31) being connected to the loading device;
a first butt plate (32), the first butt plate (32) being disposed at one end of the first loading box section (31);
the first transfer plate (33) is connected with the first butt plate (32), and one face of the first transfer plate (33) is set as a connection face and used for being connected with a wing box section (8) to be tested.
6. Wing box test unit in the form of a curved shear load according to claim 5, characterized in that the second loading clamp (6) comprises:
a second loading box section (61), wherein the second loading box section (61) is connected with the supporting device (5) and the limiting device (7);
a second docking plate (62), the second docking plate (62) being disposed at one end of the second load cassette section (61);
the second adapter plate (63) is connected with the second adapter plate (62), and one surface of the second adapter plate (63) is arranged to be a connecting surface and used for being connected with a wing box section (8) to be tested.
7. The wing box test device in a bending shear loading form according to claim 6, characterized in that the wing box test device in a bending shear loading form further comprises a bolster (9), and the supporting device (5) is connected with the second loading box (61) through the bolster (9).
8. The bending shear loaded form of wing box test device according to claim 7, characterized in that the limiting device (7) comprises:
a stopper body (71), and
spacing angle box subassembly, spacing angle box subassembly includes:
the limiting angle box (72) comprises two crossed plate-shaped bodies, a reinforcing rib is arranged between the two plate-shaped bodies, and the reinforcing rib divides the two plate-shaped bodies into two accommodating spaces;
a hinge support (73), the hinge support (73) being disposed in the accommodating space, the hinge support (73) having a recess;
a male hinge structure (74), the male hinge structure (74) having a protrusion disposed within a recess of the hinge support (74), the male hinge structure (74) being connected to the hinge support (73);
the male hinge structure (74) is connected to the second cassette section (61).
9. Wing box test unit in bent shear loading form according to claim 8, characterized in that the stop body (71) comprises two intersecting support beams, one of which is arranged perpendicular to the other, between which a stiffening plate is arranged.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610529962.5A CN106248322B (en) | 2016-07-05 | 2016-07-05 | A kind of wing-box experimental rig of curved scissors loading |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610529962.5A CN106248322B (en) | 2016-07-05 | 2016-07-05 | A kind of wing-box experimental rig of curved scissors loading |
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| Publication Number | Publication Date |
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| CN106248322A true CN106248322A (en) | 2016-12-21 |
| CN106248322B CN106248322B (en) | 2018-11-13 |
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| CN201610529962.5A Active CN106248322B (en) | 2016-07-05 | 2016-07-05 | A kind of wing-box experimental rig of curved scissors loading |
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Cited By (6)
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|---|---|---|---|---|
| CN109738300A (en) * | 2018-10-31 | 2019-05-10 | 中国飞机强度研究所 | A kind of curved scissors combination test apparatus of pin shaft base part |
| CN110243701A (en) * | 2019-07-05 | 2019-09-17 | 山东科技大学 | A kind of Bolted Rock Masses torsional shear test device and method |
| CN110346223A (en) * | 2019-07-03 | 2019-10-18 | 中国商用飞机有限责任公司 | Bending shear coupling test device |
| CN110758768A (en) * | 2019-10-15 | 2020-02-07 | 中国直升机设计研究所 | Loading device for stiffness test of flexible beam of bearingless rotor wing |
| CN113371226A (en) * | 2021-07-14 | 2021-09-10 | 中国飞机强度研究所 | Static strength test structure for connecting part of Y-shaped wing outer wing and rear support box section thereof |
| CN113514212A (en) * | 2021-04-20 | 2021-10-19 | 中国飞机强度研究所 | Shear support rigidity simulation device |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109738300A (en) * | 2018-10-31 | 2019-05-10 | 中国飞机强度研究所 | A kind of curved scissors combination test apparatus of pin shaft base part |
| CN110346223A (en) * | 2019-07-03 | 2019-10-18 | 中国商用飞机有限责任公司 | Bending shear coupling test device |
| CN110346223B (en) * | 2019-07-03 | 2021-08-10 | 中国商用飞机有限责任公司 | Bending shear coupling test device |
| CN110243701A (en) * | 2019-07-05 | 2019-09-17 | 山东科技大学 | A kind of Bolted Rock Masses torsional shear test device and method |
| CN110243701B (en) * | 2019-07-05 | 2022-02-01 | 山东科技大学 | Torsion shear test device and method for anchored rock mass |
| CN110758768A (en) * | 2019-10-15 | 2020-02-07 | 中国直升机设计研究所 | Loading device for stiffness test of flexible beam of bearingless rotor wing |
| CN113514212A (en) * | 2021-04-20 | 2021-10-19 | 中国飞机强度研究所 | Shear support rigidity simulation device |
| CN113514212B (en) * | 2021-04-20 | 2023-09-05 | 中国飞机强度研究所 | Shear support rigidity simulation device |
| CN113371226A (en) * | 2021-07-14 | 2021-09-10 | 中国飞机强度研究所 | Static strength test structure for connecting part of Y-shaped wing outer wing and rear support box section thereof |
| CN113371226B (en) * | 2021-07-14 | 2024-01-30 | 中国飞机强度研究所 | Static strength test structure for connecting part of outer wing and rear supporting box section of Y-shaped wing |
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| CN106248322B (en) | 2018-11-13 |
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