Wing strength testing device

Abstract

The utility model discloses a wing strength testing device, and relates to the technical field of wing strength testing, the device comprises a fixing frame, a clamping assembly is arranged at the top of the fixing frame, the clamping assembly is used for fixing a wing, and a bottom plate used for placing a balancing weight is arranged at the bottom of the fixing frame. According to the scheme, the wing strength testing device comprises the fixing frame, the clamping assembly, the bottom plate and the balancing weight, the testing device is simple in overall structure, convenient to install and low in cost, meanwhile, wing strength testing can be rapidly carried out, the deformation amount is accurate, and the testing device can be suitable for carrying out loading tests on wings of different models.

Description

Technical Field

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

[0002] One of the contents of structural testing is to observe and study the strength, stiffness, stress and deformation distribution of aircraft structures or components under static loads. It is an important means to verify the structural strength of aircraft and the correctness of static analysis. The loading system of full-scale structural static testing is relatively complex. At the same time, the wing strength testing devices currently on the market have the disadvantages of being inconvenient to install and unable to perform load-bearing tests on different wings, and their applicability is generally low. Utility Model Content

[0003] In order to solve the technical problems existing in the above-mentioned prior art, the utility model provides a wing strength testing device, which includes a fixing frame, a clamping assembly is provided on the top of the fixing frame, the clamping assembly is used to fix the wing, and a base plate for placing a counterweight is provided at the bottom of the fixing frame.

[0004] The technical solution of the utility model is as follows: the wing strength testing device of the solution comprises a fixing frame, a clamping assembly and a counterweight block, the clamping assembly for fixing the wing is fixed on the top of the fixing frame, the counterweight block is placed on the bottom plate at the bottom of the fixing frame, and then a weight is added to the corresponding position of the wing to carry out a loading test on the wing, so as to obtain the test data we need, namely the deformation and the load it can withstand, and to visually observe whether there are cracks in the wing, and the counterweight block is to prevent the fixing frame from tipping over.

[0005] As an optional technical solution, the clamping assembly includes a support beam, one end of which is connected to the top of the fixed frame, and the other end of which is connected to the base, a first fixed plate is connected to the base, and lifting assemblies are installed on both sides of the first fixed plate, the bottom of the lifting assembly is connected to the base, and the top of the lifting assembly is connected to the second fixed plate.

[0006] As an optional technical solution, the lifting assembly includes a hydraulic pump and a telescopic rod, the bottom of the hydraulic pump is connected to the base, the top of the hydraulic pump is connected to the bottom of the telescopic rod, and the top of the telescopic rod is connected to the second fixed plate.

[0007] As an optional technical solution, the support beam is connected to the top of the fixing frame by bolts.

[0008] As an optional technical solution, a plurality of slide grooves are arranged on the first fixed plate at equal intervals, each slide groove is provided with a fixing column, and the fixing column is slidably connected to the slide groove.

[0009] As an optional technical solution, a groove corresponding to the slide groove is provided on a surface of the second fixing plate close to the first fixing plate, and a depth of the groove is greater than a height of the fixing column.

[0010] As an optional technical solution, the fixing frame and the base plate are integrated.

[0011] One or more technical solutions provided by the utility model have at least the following technical effects or advantages:

[0012] The utility model provides a wing strength testing device, comprising a fixing frame, a clamping assembly, a bottom plate and a counterweight. The testing device has not only a simple overall structure, convenient installation and low cost, but also can quickly perform wing strength testing, has a relatively accurate deformation amount, and can be suitable for loading tests on wings of different models. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] The drawings described herein are used to provide a further understanding of the embodiments of the present utility model, constitute a part of the present utility model, and do not constitute a limitation on the embodiments of the present utility model;

[0014] Figure 1 It is a structural schematic diagram of a wing strength testing device in the utility model;

[0015] Figure 2 It is a front view of a wing strength testing device in the utility model;

[0016] Figure 3 It is an enlarged schematic diagram of the clamping component part in the utility model;

[0017] Figure 4 It is a top view of the first fixing plate in the utility model;

[0018] Figure 5 It is a top view of the second fixing plate in the utility model.

[0019] Among them, 1-fixed frame, 2-wing, 3-bottom plate, 4-counterweight, 5-support beam, 6-base, 7-first fixed plate, 8-second fixed plate, 9-hydraulic pump, 10-telescopic rod, 11-fixed column, 12-slide groove, 13-groove. DETAILED DESCRIPTION

[0020] In order to more clearly understand the above-mentioned purpose, features and advantages of the utility model, the utility model is further described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be noted that the embodiments of the utility model and the features in the embodiments can be combined with each other without conflict.

[0021] In the following description, many specific details are set forth to facilitate a full understanding of the present invention. However, the present invention may also be implemented in other ways different from those within the scope of this description. Therefore, the protection scope of the present invention is not limited to the specific embodiments disclosed below.

[0022] Please refer to Figure 1 to Figure 5 , Figure 1 It is a structural schematic diagram of a wing strength testing device in the utility model; Figure 2 It is a front view of a wing strength testing device in the utility model; Figure 3 It is an enlarged schematic diagram of the clamping component part in the utility model;

[0023] Figure 4 It is a top view of the first fixing plate in the utility model; Figure 5 The device comprises a fixing frame 1, a clamping assembly is arranged on the top of the fixing frame 1, and the clamping assembly is used to fix the wing 2, and a bottom plate 3 for placing a counterweight 4 is arranged at the bottom of the fixing frame 1.

[0024] The specific embodiments of the utility model are as follows: a clamping assembly is fixed on the top of a fixing frame 1, the clamping assembly is used to fix the wing 2, a counterweight 4 is placed on a bottom plate 3 at the bottom of the fixing frame 1, and then a weight is added to the corresponding position of the wing 2 to perform a loading test on the wing 2, so as to obtain the test data we need, that is, the deformation and the load it can withstand, and to visually observe whether there are cracks in the wing 2. The counterweight 4 is to prevent the fixing frame 1 from tipping over.

[0025] A possible implementation method of the clamping assembly fixing the wing 2 is as follows: the clamping assembly includes a support beam 5, one end of the support beam 5 is connected to the top of the fixing frame 1, the other end of the support beam 5 is connected to the base 6, the first fixing plate 7 is connected to the base 6, and hydraulic pumps 9 are installed on both sides of the first fixing plate 7. The bottom of the hydraulic pump 9 is connected to the base 6, the top of the hydraulic pump 9 is connected to the bottom of the telescopic rod 10, and the top of the telescopic rod 10 is connected to the second fixing plate 8. The first fixing plate 7 is provided with a plurality of slide grooves 12, each of which is slidably connected with a fixing column 11, and the second fixing plate 8 is provided with a groove 13 corresponding to the slide groove, and the depth of the groove 13 is greater than the height of the fixing column 11. When the wing 2 needs to be fixed, a plurality of openings are generally provided on one side of the wing 2 (the wing 2 is fixed to the aircraft through these openings), but the openings on one side of the wing 2 of different models also have differences. In this scheme, the fixing column 11 is adjusted by the slide groove 12, so that the adjusted plurality of fixing columns 11 can match the openings of the wing 2. Then, the hydraulic pump 9 is started to shorten the telescopic rod 10, and the telescopic rod 10 drives the second fixing plate 8 to descend. Since the depth of the groove 13 on the second fixing plate 8 is greater than the height of the fixing column 11, the wing 2 can be effectively fixed by the first fixing plate 7, the fixing column 11, the second fixing plate 8 and its groove 13.

[0026] The wing strength testing device in this scheme not only has a simple overall structure, is easy to install and has low cost, but can also quickly perform wing strength tests and can be applied to loading tests on wings of different models.

[0027] Among them, the clamping assembly includes a support beam 5, one end of the support beam 5 is connected to the top of the fixed frame 1, and the other end of the support beam 5 is connected to the base, a first fixed plate 7 is connected to the base 6, and lifting assemblies are installed on both sides of the first fixed plate 7, the bottom of the lifting assembly is connected to the base 6, and the top of the lifting assembly is connected to the second fixed plate 8.

[0028] The lifting assembly includes a hydraulic pump 9 and a telescopic rod 10 , the bottom of the hydraulic pump 9 is connected to the base 6 , the top of the hydraulic pump 9 is connected to the bottom of the telescopic rod 10 , and the top of the telescopic rod 10 is connected to the second fixed plate 8 .

[0029] The first fixing plate 7 is provided with a plurality of slide grooves 12 at equal intervals, each slide groove 12 is provided with a fixing column 11 , and the fixing column 11 is slidably connected to the slide groove 12 .

[0030] A groove 13 corresponding to the slide groove 12 is formed on the surface of the second fixing plate 8 close to the first fixing plate 7 , and the depth of the groove 13 is greater than the height of the fixing column 11 .

[0031] When the wing 2 needs to be fixed, a plurality of openings are generally provided on one side of the wing 2 (through which the wing 2 is fixed to the aircraft), but the openings on one side of the wing 2 of different models are also different. In this solution, the fixing column 11 is adjusted by the slide groove 12 so that the adjusted fixing columns 11 can match the openings of the wing 2. Then the hydraulic pump 9 is started to work, driving the telescopic rod 10 to shorten, and the telescopic rod 10 drives the second fixing plate 8 to descend. Since the depth of the groove 13 on the second fixing plate 8 is greater than the height of the fixing column 11, the first fixing plate 7, the fixing column 11, the second fixing plate 8 and its groove 13 can effectively fix the wing 2. After the fixing is completed, a weight is added to the corresponding position of the wing 2 to perform a loading test on the wing, thereby obtaining test data.

[0032] The support beam 5 is connected with the top of the fixing frame 1 by bolts. The bolt connection makes installation and disassembly more convenient.

[0033] The fixing frame 1 and the bottom plate 3 are integrated into one piece, which improves the overall rigidity of the wing strength test device.

[0034] Although the preferred embodiments of the present invention have been described, those skilled in the art may make other changes and modifications to these embodiments once they have learned the basic creative concept. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments and all changes and modifications falling within the scope of the present invention.

[0035] Obviously, those skilled in the art can make various changes and modifications to the present invention without departing from the spirit and scope of the present invention. Thus, if these modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include these modifications and variations.

Claims

1. A wing strength testing device, characterized in that: The device includes a fixing frame, a clamping assembly is provided on the top of the fixing frame, the clamping assembly is used to fix the wing, and a bottom plate for placing a counterweight is provided at the bottom of the fixing frame; the clamping assembly includes a support beam, one end of the support beam is connected to the top of the fixing frame, and the other end of the support beam is connected to the base, a first fixing plate is connected to the base, lifting assemblies are installed on both sides of the first fixing plate, the bottom of the lifting assembly is connected to the base, and the top of the lifting assembly is connected to the second fixing plate.

2. A wing strength testing device according to claim 1, characterized in that: The lifting assembly includes a hydraulic pump and a telescopic rod, the bottom of the hydraulic pump is connected to the base, the top of the hydraulic pump is connected to the bottom of the telescopic rod, and the top of the telescopic rod is connected to the second fixing plate.

3. A wing strength testing device according to claim 1, characterized in that: The support beam is connected to the top of the fixing frame by bolts.

4. A wing strength testing device according to claim 1, characterized in that: The first fixed plate is provided with a plurality of slide grooves at equal intervals, each slide groove is provided with a fixing column, and the fixing column is slidably connected to the slide groove.

5. A wing strength testing device according to claim 4, characterized in that: A groove corresponding to the slide groove is formed on a surface of the second fixing plate close to the first fixing plate, and a depth of the groove is greater than a height of the fixing column.

6. A wing strength testing device according to claim 1, characterized in that: The fixing frame and the bottom plate are integrated.

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