Wing static test tool

Abstract

The utility model relates to the technical field of wing test, and discloses a wing static test tool, which comprises a wing, one side of the wing is fixedly connected with a mounting plate, one side of the mounting plate is provided with a far-end pin hole, the inside of the far-end pin hole is connected with an L-shaped plate through a bolt, the bottom of the L-shaped plate is connected with a fixing frame through a bolt, and the fixing frame is connected with the wing through a bolt. A near-end pin hole is formed in the other side of the mounting plate, a bolt is arranged in the near-end pin hole, steel wire ropes are connected to the two ends of the bolt respectively, a crane scale is connected to the top ends of the steel wire ropes, a gantry crane is arranged at the top of the crane scale, and a rear edge is arranged on the other side of the wing. According to the utility model, the wing is fixed through the fixing frame, the force applied to the position of the wing is simulated during loading through the operation of the gantry crane, the loaded force is displayed through the operation of the crane scale, and the deformation of the wing can be read through the arrangement of the displacement measuring device, so that the static test can be carried out on the wing.

Description

Technical Field

[0001] The utility model relates to the technical field of wing testing, in particular to a wing static testing tool. Background Art

[0002] The wing is an important part of an aircraft. Its main function is to provide lift. Together with the tail, it ensures that the aircraft has good stability. When it has an upward dihedral angle, it can provide some lateral stability for the aircraft. At its trailing edge, there are generally ailerons and spoilers for lateral control. In order to improve the aerodynamic effect of the wing, various types of flaps, wing wraps and other lift-enhancing devices are increasingly installed at the front and rear of the wing to improve the take-off, landing or maneuverability of the aircraft. The wing static test is one of the contents of the structural test, which is used to observe and study the strength, stiffness, stress and deformation distribution of its structure or components under static loads. It is an important means to verify its structural strength and the correctness of static analysis.

[0003] Traditional wing static tests use an electronic computer-controlled electric hydraulic servo system with an automatic closed-loop coordinated loading system. It has hundreds of loaders, hundreds of loading points, hundreds of measurement channels, and thousands of strain gauges, and uses electronic computers for data collection and processing, which results in a high test cost. Utility Model Content

[0004] In order to make up for the above shortcomings, the utility model provides a wing static test tooling, aiming to improve the problem of high cost of traditional wing static test.

[0005] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: a wing static test tooling, comprising a wing, a mounting plate fixedly connected to one side of the wing, a distal pin hole provided on one side of the mounting plate, an L-plate connected to the inside of the distal pin hole by bolts, a fixing frame connected to the bottom of the L-plate by bolts, a proximal pin hole provided on the other side of the mounting plate, a bolt provided inside the proximal pin hole, steel wire ropes connected to both ends of the bolts, a crane scale connected to the top of the steel wire rope, a gantry crane provided on the top of the crane scale, a trailing edge provided on the other side of the wing, a leading edge provided on the side of the wing away from the trailing edge, and a displacement measuring device symmetrically provided on the bottom of the wing away from the mounting plate.

[0006] Preferably, the displacement measuring device includes a bracket, a steel ruler is provided on one side of the bracket, a pulley is symmetrically connected to one side of the top of the bracket through bolts, a cotton thread is slidably connected to one side of the pulley, and one end of the cotton thread is respectively connected to the trailing edge and the leading edge of the wing.

[0007] Preferably, the cotton thread is fixedly connected with a pointer near the outer wall of the steel ruler, and the bottom end of the cotton thread is fixedly connected with a plumb bob.

[0008] Preferably, anti-twist pins are symmetrically arranged on one side of the wing close to the mounting plate, and limit holes are symmetrically arranged on one side of the fixing frame close to the wing.

[0009] Preferably, the anti-twist pins match the limit holes of the fixing frame, and the anti-twist pins are located in the limit holes of the fixing frame.

[0010] Preferably, a threaded lifting platform is arranged at the bottom of the wing, and sandbags are evenly arranged on the top of the wing.

[0011] Preferably, the hanging scale and the gantry crane are located directly above the proximal pin hole.

[0012] Preferably, positioning holes are evenly arranged at the bottom of the periphery of the fixing frame.

[0013] The utility model has the following beneficial effects:

[0014] 1. In the utility model, the wing is fixed by the fixing frame. Through the operation of the gantry crane, the force applied to the wing here during loading is simulated. Through the operation of the hanging scale, the applied force is displayed. Through the setting of the displacement measuring device, the deformation amount of the wing can be read, so that the static test of the wing can be carried out. The tooling structure is simple, safe and firm, solving the problem of high cost of the traditional wing static test, facilitating the recording of the deformation amount, with convenient loading, accurate displacement amount, meeting the use of the loading conditions, and the tooling will not cause damage and injury to the experimental structure during use, with reliable performance, not easy to loosen, and in-place safety protection. Brief Description of the Drawings

[0015] Figure 1 is a schematic three-dimensional structure diagram of the wing static test tooling proposed by the utility model;

[0016] Figure 2 is a schematic diagram of the wing of the wing static test tooling proposed by the utility model;

[0017] Figure 3 is a schematic diagram of the displacement measuring device of the wing static test tooling proposed by the utility model.

[0018] Legend Explanation:

[0019] 1. Wing; 2. Proximal pin hole; 3. Distal pin hole; 4. Anti-twist pin; 5. Trailing edge; 6. Leading edge; 7. Sandbag; 8. Fixing frame; 9. L-shaped plate; 10. Gantry crane; 11. Hanging scale; 12. Threaded lifting platform; 13. Displacement measuring device; 14. Steel wire rope; 15. Steel tape; 16. Pointer; 17. Plumb bob; 18. Pulley; 19. Cotton thread; 20. Bracket. Detailed Embodiment

[0020] The technical solutions in the embodiments of the present utility model will be clearly and completely described below in conjunction with the accompanying drawings of the present utility model. Obviously, the described embodiments are only a part of the embodiments of the present utility model, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present utility model without creative efforts shall fall within the protection scope of the present utility model.

[0021] Referring to Figures 1-3 , an embodiment provided by the present utility model: an aircraft wing static test tooling, including an aircraft wing 1. One side of the aircraft wing 1 is fixedly connected with a mounting plate. One side of the mounting plate is provided with a distal pin hole 3. An L-shaped plate 9 is connected inside the distal pin hole 3 through a bolt. The bottom of the L-shaped plate 9 is connected with a fixing frame 8 through a bolt. The other side of the mounting plate is provided with a proximal pin hole 2. A bolt is arranged inside the proximal pin hole 2. Both ends of the bolt are respectively connected with a steel wire rope 14. The top end of the steel wire rope 14 is connected with a hanging scale 11. A gantry crane 10 is arranged on the top of the hanging scale 11. The other side of the aircraft wing 1 is provided with a trailing edge 5. One side of the aircraft wing 1 away from the trailing edge 5 is provided with a leading edge 6. Displacement measuring devices 13 are symmetrically arranged at the bottom of the aircraft wing 1 away from the mounting plate.

[0022] Specifically, the aircraft wing 1 is fixed on one side of the L-shaped plate 9 through the distal pin hole 3. The aircraft wing 1 is fixed on the top of the fixing frame 8 through the L-shaped plate 9. The steel wire ropes 14 are hung on both sides of the proximal pin hole 2 through bolts. Through the operation of the gantry crane 10, the force applied to this part of the aircraft wing 1 during loading is simulated. Through the operation of the hanging scale 11, the applied force is displayed. Through the setting of the displacement measuring devices 13, the deformation amount of the aircraft wing 1 can be read, so that the static test of the aircraft wing 1 can be carried out. The tooling has a simple structure, is safe and firm, and solves the problem of the high cost of traditional aircraft wing static tests.

[0023] The displacement measuring device 13 includes a bracket 20. One side of the bracket 20 is provided with a steel tape measure 15. On one side of the top of the bracket 20, pulleys 18 are symmetrically connected through bolts. A cotton thread 19 is slidably connected to one side of the pulley 18. One end of the cotton thread 19 is respectively connected to the trailing edge 5 and the leading edge 6 of the aircraft wing 1; a pointer 16 is fixedly connected to the outer wall of the cotton thread 19 close to the steel tape measure 15. A plumb bob 17 is fixedly connected to the bottom end of the cotton thread 19.

[0024] Specifically, by bonding the cotton thread 19 to the trailing edge 5 and the leading edge 6 of the aircraft wing 1, when the aircraft wing deforms during loading, it will drive the cotton thread 19 to move, thereby driving the pointer 16 to move. By calculating the indication data of the pointer 16 on the steel tape measure 15, the deformation amount of the aircraft wing 1 can be known, so that when the aircraft wing 1 is loaded, it is convenient to record its deformation amount, and the loading is convenient, the displacement amount is accurate, and it meets the use of the loading conditions.

[0025] On one side of the wing 1 close to the mounting plate, anti-twist pins 4 are symmetrically arranged. On one side of the fixing frame 8 close to the wing 1, limit holes are symmetrically arranged; the anti-twist pins 4 match the limit holes of the fixing frame 8, and the anti-twist pins 4 are located in the limit holes of the fixing frame 8; a threaded lifting platform 12 is arranged at the bottom of the wing 1, and sandbags 7 are evenly arranged on the top of the wing 1; the hanging scale 11 and the gantry crane 10 are located directly above the proximal pin hole 2; positioning holes are evenly arranged at the bottom around the fixing frame 8.

[0026] Specifically, the wing 1 is further limited through the limit holes on one side of the fixing frame 8 to prevent it from shifting during loading. Through the operation of the threaded lifting platform 12, the wing 1 can be supported. By placing the sandbags 7 on the wing 1 according to the corresponding requirements, and then through the operation of the threaded lifting platform 12, the threaded lifting platform 12 no longer contacts the wing 1, so that the loading on the wing 1 can be simulated. This tooling will not cause damage and injury to the experimental structure during use, and has reliable performance, is not easy to loosen, and has in-place safety protection.

[0027] Working principle: When using this tooling, first lock the positioning holes around the fixing frame 8 with ground expansion screws, then connect the L-shaped plate 9 to the fixing frame 8 with bolts. Then invert the wing 1 so that the lower skin faces up. Insert the two anti-twist pins 4 on one side of the wing 1 into the limit holes on the side of the fixing frame 8, and connect and fix the distal pin hole 3 and the L-shaped plate 9 with bolts. At this time, the wing 1 is constrained. Then push the gantry 10 to directly above the proximal pin hole 2, insert a bolt into the proximal pin hole 2, and hang the front and rear ends of the bolt with the steel wire rope 14 respectively. During loading, simulate the force applied to this part of the wing 1. Through the operation of the hanging scale 11, the magnitude of the applied force is displayed. Then, bond the cotton thread 19 to the trailing edge 5 and the leading edge 6 of the wing 1. When the wing deforms during loading, it will drive the cotton thread 19 to move, thereby driving the pointer 16 to move. By calculating the indication data of the pointer 16 on the steel scale 15, the deformation amount of the wing 1 can be obtained, so that it is convenient to record the deformation amount when the wing 1 is loaded. Before the wing 1 is loaded, a threaded lifting platform 12 needs to be placed at the bottom to ensure the safety and non-shaking of the wing 1 when stacking the sandbags 7. After the sandbags 7 are placed, adjust the threaded lifting platform 12 until it does not contact the wing 1. When the gantry crane 10 pulls the hanging scale 11 to reach the required force value, then read the measured value on the displacement measuring device 13, thus completing the static test of the wing.

[0028] Finally, it should be noted that the above are only the preferred embodiments of the present utility model and are not used to limit the present utility model. Although the present utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or perform equivalent replacements for some of the technical features. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present utility model shall be included within the protection scope of the present utility model.

Claims

1. Wing static test tooling, including a wing (1), characterized in that: One side of the wing (1) is fixedly connected with a mounting plate. One side of the mounting plate is provided with a distal pin hole (3). Inside the distal pin hole (3), an L-shaped plate (9) is connected by bolts. The bottom of the L-shaped plate (9) is connected with a fixing frame (8) by bolts. The other side of the mounting plate is provided with a proximal pin hole (2). Inside the proximal pin hole (2), there is a bolt. The two ends of the bolt are respectively connected with a steel wire rope (14). The top end of the steel wire rope (14) is connected with a hanging scale (11). The top of the hanging scale (11) is provided with a gantry crane (10). The other side of the wing (1) is provided with a trailing edge (5). One side of the wing (1) away from the trailing edge (5) is provided with a leading edge (6). Symmetrically arranged at the bottom of the wing (1) away from the mounting plate are displacement measuring devices (13).

2. The wing static test tooling according to claim 1, wherein: The displacement measuring device (13) includes a bracket (20). One side of the bracket (20) is provided with a steel tape rule (15). Symmetrically connected to the top side of the bracket (20) by bolts are pulleys (18). One side of the pulley (18) is slidably connected with a cotton thread (19). One end of the cotton thread (19) is respectively connected to the trailing edge (5) and the leading edge (6) of the wing (1).

3. The wing static test tooling according to claim 2, wherein: Fixedly connected to the outer wall of the cotton thread (19) close to the steel tape rule (15) is a pointer (16). The bottom end of the cotton thread (19) is fixedly connected with a plumb bob (17).

4. The wing static test tooling according to claim 1, characterized in that: Symmetrically arranged on one side of the wing (1) close to the mounting plate are anti-twist pins (4). Symmetrically arranged on one side of the fixing frame (8) close to the wing (1) are limit holes.

5. The wing static test tooling according to claim 4, characterized in that: The anti-twist pins (4) match the limit holes of the fixing frame (8), and the anti-twist pins (4) are located in the limit holes of the fixing frame (8).

6. The wing static test tooling according to claim 1, characterized in that: The bottom of the wing (1) is provided with a threaded lifting platform (12). Sandbags (7) are evenly arranged on the top of the wing (1).

7. The wing static test tooling according to claim 1, characterized in that: The hanging scale (11) and the gantry crane (10) are located directly above the proximal pin hole (2).

8. The wing static test tooling according to claim 1, wherein: Positioning holes are evenly arranged at the bottom around the fixing frame (8).

Images