CN110666714A - Wing anchor clamps and wing test system - Google Patents
Wing anchor clamps and wing test system Download PDFInfo
- Publication number
- CN110666714A CN110666714A CN201910923643.6A CN201910923643A CN110666714A CN 110666714 A CN110666714 A CN 110666714A CN 201910923643 A CN201910923643 A CN 201910923643A CN 110666714 A CN110666714 A CN 110666714A
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- clamping
- support
- wing
- frame
- clamping support
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B11/00—Work holders not covered by any preceding group in the subclass, e.g. magnetic work holders, vacuum work holders
-
- 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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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
A wing clamp and wing test system, the wing clamp comprising: a first clamping bracket and a second clamping bracket; one end of the first clamping support is connected with one end of the second clamping support, the other end of the first clamping support is connected with the other end of the second clamping support, and the middle of the first clamping support and the middle of the second clamping support form an airfoil clamping part. The wing to be tested is clamped and fixed through the wing clamping part, so that the swing of the wing to be tested in the testing process is avoided, and the accuracy of the experiment is guaranteed.
Description
Technical Field
The invention relates to the technical field of aircraft wing testing, in particular to a wing clamp and a wing testing system with the same.
Background
The method for testing whether the structural strength meets the design requirements or not by applying loads according to different working conditions during the static test of the aircraft wing structure is an indispensable important link in the aircraft development process. With the rapid development of the aviation industry, the structure, materials, the processing technology and the like of the airplane are more and more complex, and the loading system is more and more huge, so that the deduction calculation of the testing machine and the test loading system and the determination of the deduction scheme are necessarily involved.
The weight deduction means that the weight of the wing structure and the weight of test equipment are deducted when static force/fatigue test of the airplane wing structure is carried out, so that the wing is in a zero-weight state during the test, and the test load can simulate flight load more truly.
During a wing loading test, the loading fixture is generally formed by assembling a plurality of I-shaped beams through bolts, and the bottoms of the I-shaped beams are connected with the loading actuating cylinders through single-lug or double-lug connecting sheets. The loading direction of the test load is defined as the chord plane after the wing deforms under the corresponding load working condition and is perpendicular to the limit load condition.
In the loading process, the action point of the load loading clamp is always far away from the chord plane of the wing section, and a plurality of sections are often loaded together during loading.
Disclosure of Invention
The invention aims to provide a wing clamp which avoids the friction influence of the clamp on the surface of a wing in the loading process and does not generate extra additional bending moment.
To solve the above problems, the present invention provides a wing clip, comprising: a first clamping bracket and a second clamping bracket; one end of the first clamping support is connected with one end of the second clamping support, the other end of the first clamping support is connected with the other end of the second clamping support, and the middle of the first clamping support and the middle of the second clamping support form an airfoil clamping part.
Furthermore, the middle part of the first clamping support protrudes towards the direction away from the second clamping support to form a first protruding part, and the first protruding part and the middle part of the second clamping support form the wing clamping part.
Further, a first clamping pad is arranged in the middle of one side, close to the second clamping support, of the first clamping support; and/or a second clamping pad is arranged in the middle of one side, close to the first clamping support, of the second clamping support.
Furthermore, one surface of the first clamping pad, which is far away from the first clamping support, is of an arc surface structure; and/or one surface of the second clamping cushion, which is far away from the second clamping support, is of an arc surface structure.
Further, the first clamping pad is made of a flexible material; and/or the second clamping pad is made of a flexible material.
Furthermore, one end of the first clamping bracket is detachably connected with one end of the second clamping bracket through a first connecting piece; and/or the other end of the first clamping support is detachably connected with the other end of the second clamping support through a second connecting piece.
Furthermore, the clamping device further comprises a rotating support frame, and two sides of the first clamping support frame are respectively connected with two ends of the rotating support frame in a rotating mode.
Furthermore, the straight lines of two points where the rotating support frame is rotatably connected with the first clamping support frame coincide with the chord line of the wing to be tested.
Furthermore, two connecting pins are symmetrically arranged on two sides of the first clamping support, and jacks matched with the connecting pins are arranged at two ends of the rotating support frame; the two sides of the first clamping support are inserted into the insertion holes through the connecting pins and are rotatably connected with the two ends of the rotating support frame.
The invention provides a wing test system, which comprises the wing clamp in any technical scheme.
The wing clamp and the wing test system have the beneficial effects that:
(1) the wing to be tested is clamped and fixed through the wing clamping part, so that the swing of the wing to be tested in the testing process is avoided, and the accuracy of the experiment is guaranteed;
(2) the first clamping pad and/or the second clamping pad can play a role in buffering, so that abrasion and the like to the wing to be tested are avoided;
(3) the rotary support frame is rotatably connected with the first clamping support, so that the first clamping support and the second clamping support can rotate in the wing testing process, and the testing requirements are met;
(4) because the straight lines of the two points of the rotary support frame and the first clamping support frame in rotary connection coincide with the chord line of the wing to be tested, the load acts on the wing chord plane (the plane in the middle of the wing) in each loading, and the extra bending moment load and the surface friction force to the wing generated by the rotation of the clamp are avoided.
Drawings
FIG. 1 is a schematic view of a wing clip according to the present invention;
figure 2 is an exploded view of the wing clip of the present invention.
Reference numerals:
1. the clamping device comprises a first clamping support, a second clamping support, a first clamping pad, a second clamping pad, a first connecting piece, a second connecting piece, a rotating support frame, a first gasket, a second gasket, a first clamping support, a second clamping pad, a second clamping support;
11. a connecting pin;
71. a support plate 72, a support bar;
711. a plug hole 712, and a cylinder loading portion.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail with reference to the accompanying drawings in conjunction with the following detailed description. It should be understood that the description is intended to be exemplary only, and is not intended to limit the scope of the present invention. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present invention.
First embodiment
FIG. 1 is a schematic view of a wing clip according to the present invention; figure 2 is an exploded view of the wing clip of the present invention.
A wing clamp comprises a first clamping bracket 1 and a second clamping bracket 2; the first clamping bracket 1 is provided with two end parts, namely one end and the other end; the second clamping bracket 2 has two end parts, one end and the other end respectively; one end of the first clamping support 1 is connected with one end of the second clamping support 2, the other end of the first clamping support 1 is connected with the other end of the second clamping support 2, and the middle of the first clamping support 1 is not in contact with the middle of the second clamping support 2, so that an airfoil clamping part is formed. When the test device is used, the wing to be tested is clamped and fixed through the wing clamping part.
In this embodiment, the middle of the first clamping bracket 1 protrudes in a direction away from the second clamping bracket 2 to form a first protruding portion, and the first protruding portion and the middle of the second clamping bracket 2 form the wing clamping portion.
Specifically, the whole wing clamp is of a rectangular frame structure. The first clamping support 1 is composed of three frames in a linear structure, namely a first frame, a second frame and a third frame, one end of the first frame is fixedly connected with one end of the second frame, the other end of the second frame is connected with one end of the third frame, and the first frame and the third frame are parallel to each other and located on one side of the second frame. In actual manufacturing, the first frame, the second frame and the third frame are of an integrated structure. The second clamping bracket 2 is a fourth frame in a linear structure. And clamping the wing to be tested through the second frame and the fourth frame.
The first clamping bracket 1 and the second clamping bracket 2 can be made into different specifications and sizes according to different wings and different wing sections.
In another possible embodiment, the first frame, the second frame, the third frame and the fourth frame are of a one-piece structure.
When the clamping device is applied specifically, the first clamping bracket 1 and the second clamping bracket 2 are both made of metal and can be made of square steel, channel steel or I-shaped beams; in order to avoid damage to the wing to be tested when clamping the wing, a first clamping pad 3 is additionally arranged on the first clamping bracket 1. Specifically, the first clamping pad 3 is a strip-shaped structure and is disposed on one surface of the second frame, which is close to the fourth frame. The first clamping pad 3 may be attached to the second rim by gluing or by fasteners.
A second clamping pad 4 is added to the second clamping bracket 2. Specifically, the second clamping pad 4 is a strip-shaped structure and is disposed on a surface of the fourth frame close to the second frame. The second clamping pad 4 may be connected to the fourth rim by gluing or by fasteners.
The first and second clamping pads 3, 4 are each made of a flexible material, such as foam or rubber.
In a preferred embodiment, a first spacer 8 is added between the first clamping pad 3 and the second rim, and a second spacer 9 is added between the second clamping pad 4 and the fourth rim.
The first gasket 8 is connected with the second frame through a fastener, and the first clamping pad 3 is adhered to the first gasket 8; the second gasket 9 is connected with the fourth frame through a fastener, and the second clamping pad 4 is adhered to the second gasket 9.
Because the appearance of wing is the arc structure, for the convenience of carrying out the centre gripping to the wing that awaits measuring through first centre gripping pad 3 and second centre gripping pad 4, set the cambered surface structure to the one side that is close to second centre gripping pad 4 with first centre gripping pad 3, also set the cambered surface structure to the one side that is close to first centre gripping pad 3 with second centre gripping pad 4. The cambered surface structure is arranged to be matched with the shape of the airfoil surface of the wing to be tested, so that the wing to be tested can be clamped conveniently, and the clamping force exerted on the wing to be tested by the first clamping pad 3 and the second clamping pad 4 can be ensured to be more uniform.
The first and second clamping pads 3, 4 may be made in a number of sizes for clamping different wings. The dimensions of the first clamping pad 3 and the second clamping pad 4 can be made in various manners, and the cambered surface structures can be made in various manners.
Preferably, one end of the first clamping bracket 1 is detachably connected with one end of the second clamping bracket 2 through a first connecting piece 5. Specifically, the other end of the first frame (the end far away from the second frame) is detachably connected with one end of the fourth frame through a first connecting piece 5. The first connecting piece 5 is in a right-angle shape, and two right-angle edges of the first connecting piece are respectively connected with the other end of the first frame and one end of the fourth frame; fasteners are often selected for attachment.
The other end of the first clamping support 1 is detachably connected with the other end of the second clamping support 2 through a second connecting piece 6. Specifically, the other end of the third frame (the end far away from the second frame) is detachably connected with the other end of the fourth frame through a second connecting piece 6. The second connecting piece 6 is in a right-angle shape, and two right-angle edges of the second connecting piece are respectively connected with the other end of the third frame and the other end of the fourth frame; fasteners are often selected for attachment.
In the specific application, the first connecting piece 5 and the second connecting piece 6 are also made of metal.
In a preferred embodiment, a rotating support frame 7 is further added, and two sides of the first clamping support 1 are respectively and rotatably connected with two ends of the rotating support frame 7.
Specifically, the rotating support frame 7 includes two support plates 71 and a support rod 72, the two support plates 71 are parallel to each other and are spaced apart from each other, and two ends of the support rod 72 are detachably connected to the two support plates 71, respectively. The two support plates 71 are rotatably connected to the first frame and the third frame, respectively.
One insertion hole 711 is formed in each support plate 71, the central axis of the insertion hole 711 is perpendicular to the longitudinal direction of the support plate 71, and the two insertion holes 711 in the two support plates 71 are coaxial. A connecting pin 11 matched with the jack is arranged on the outer side of the first frame (namely, the side far away from the third frame), a connecting pin 11 matched with the jack is arranged on the outer side of the third frame (namely, the side far away from the first frame), and the two connecting pins 11 arranged on the first frame and the third frame are coaxial. Each connecting pin 11 is inserted into one of the insertion holes 711 for rotatably connecting the rotary support frame 7 with the first clamping bracket 1.
In the installation, the connecting pin 11 is first inserted into one insertion hole 711, and the two support plates 71 are connected by the support rod 72.
Two ends of the support rod 72 are respectively provided with a connecting piece, and the connecting pieces and the support plate 71 can be connected through fasteners.
The central axis of the receptacle 711 coincides with the chord of the airfoil to be tested.
In particular applications, the support plate 71 and the support rod 72 are made of metal.
The first and second holding brackets 1 and 2 are rotatable on the rotating support frame 7 about two connecting pins 11. The protection scope of the present invention is not limited to the positions of the first and second clamping brackets 1 and 2 and the rotating support 7 shown in the drawings, and the support rod 72 may be rotated to the lower side of the second clamping bracket 2.
In another embodiment, the two sides of the first clamping bracket 1 are respectively connected with the two ends of the rotating support frame 7 in a rotating manner through rotating shafts. Specifically, a rotating shaft matched with the jack may be disposed on an outer side of the first frame (i.e., a side far away from the third frame), a rotating shaft matched with the jack may be disposed on an outer side of the third frame (i.e., a side far away from the first frame), and the two rotating shafts disposed on the first frame and the third frame are coaxial. The shaft is inserted into the insertion hole 711.
The support plate 71 is provided with a cylinder connecting portion 712 for connecting the cylinder. The ram connecting portion 712 may be provided on both support plates 71, and the central axes of the two ram loading portions 712 may be coaxial.
Second embodiment
A wing testing system comprising a wing clamp according to the first embodiment.
It is to be understood that the above-described embodiments of the present invention are merely illustrative of or explaining the principles of the invention and are not to be construed as limiting the invention. Therefore, any modification, equivalent replacement, improvement and the like made without departing from the spirit and scope of the present invention should be included in the protection scope of the present invention. Further, it is intended that the appended claims cover all such variations and modifications as fall within the scope and boundaries of the appended claims or the equivalents of such scope and boundaries.
Claims (10)
1. A wing clamp, characterized by: the method comprises the following steps: a first clamping bracket (1) and a second clamping bracket (2);
one end of the first clamping support (1) is connected with one end of the second clamping support (2), the other end of the first clamping support (1) is connected with the other end of the second clamping support (2), and the middle of the first clamping support (1) and the middle of the second clamping support (2) form an airfoil clamping part.
2. The wing clamp of claim 1, wherein: the middle part of the first clamping support (1) protrudes towards the direction far away from the second clamping support (2) to form a first protruding part, and the middle parts of the first protruding part and the second clamping support (2) form the wing clamping part.
3. The wing clamp of claim 1, wherein: a first clamping pad (3) is arranged in the middle of one side, close to the second clamping bracket (2), of the first clamping bracket (1); and/or a second clamping pad (4) is arranged in the middle of one side, close to the first clamping support (1), of the second clamping support (2).
4. The wing clamp of claim 3, wherein: one surface of the first clamping pad (3) far away from the first clamping support (1) is of an arc surface structure; and/or one surface of the second clamping pad (4) far away from the second clamping support (2) is of an arc surface structure.
5. The wing clamp of claim 3, wherein: the first clamping pad (3) is made of a flexible material; and/or the second clamping pad (4) is made of a flexible material.
6. The wing clamp of claim 1, wherein: one end of the first clamping bracket (1) is detachably connected with one end of the second clamping bracket (2) through a first connecting piece (5); and/or the other end of the first clamping support (1) is detachably connected with the other end of the second clamping support (2) through a second connecting piece (6).
7. The wing clamp of claim 1, wherein: the clamping device is characterized by further comprising a rotating support frame (7), wherein two sides of the first clamping support frame (1) are respectively connected with two ends of the rotating support frame (7) in a rotating mode.
8. The wing clamp of claim 7, wherein: the straight lines of two points where the rotary supporting frame (7) is rotatably connected with the first clamping support (1) coincide with the chord line of the airfoil section to be tested.
9. The wing clamp of claim 7, wherein: two connecting pins (11) are symmetrically arranged on two sides of the first clamping support (1), and inserting holes (711) matched with the connecting pins (11) are formed in two ends of the rotating support frame (7); two sides of the first clamping support (1) are inserted into the insertion holes (711) through the connecting pins (11) and are rotatably connected with two ends of the rotating support frame (7).
10. A wing test system characterized by: comprising a wing clamp as claimed in any of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910923643.6A CN110666714A (en) | 2019-09-27 | 2019-09-27 | Wing anchor clamps and wing test system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910923643.6A CN110666714A (en) | 2019-09-27 | 2019-09-27 | Wing anchor clamps and wing test system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110666714A true CN110666714A (en) | 2020-01-10 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910923643.6A Pending CN110666714A (en) | 2019-09-27 | 2019-09-27 | Wing anchor clamps and wing test system |
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| CN (1) | CN110666714A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112276808A (en) * | 2020-09-18 | 2021-01-29 | 余华云 | Aircraft wing processing maintenance positioner |
| CN112461644A (en) * | 2020-11-19 | 2021-03-09 | 航天彩虹无人机股份有限公司 | Clamping device for testing electrical performance of sensor antenna under static deformation of wing |
| CN113602524A (en) * | 2021-08-11 | 2021-11-05 | 北京航空航天大学 | Test platform for performance of flexible skin of trailing edge variable camber wing |
| CN114379814A (en) * | 2022-01-10 | 2022-04-22 | 电子科技大学 | Clamping and positioning device for movable wing |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112276808A (en) * | 2020-09-18 | 2021-01-29 | 余华云 | Aircraft wing processing maintenance positioner |
| CN112461644A (en) * | 2020-11-19 | 2021-03-09 | 航天彩虹无人机股份有限公司 | Clamping device for testing electrical performance of sensor antenna under static deformation of wing |
| CN113602524A (en) * | 2021-08-11 | 2021-11-05 | 北京航空航天大学 | Test platform for performance of flexible skin of trailing edge variable camber wing |
| CN113602524B (en) * | 2021-08-11 | 2024-01-30 | 北京航空航天大学 | Test platform for flexible skin performance of trailing edge camber wing |
| CN114379814A (en) * | 2022-01-10 | 2022-04-22 | 电子科技大学 | Clamping and positioning device for movable wing |
| CN114379814B (en) * | 2022-01-10 | 2023-08-11 | 电子科技大学 | Clamping and positioning device for movable wing |
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Application publication date: 20200110 |