CN219416625U - Rigidity detection equipment of aircraft wing - Google Patents

Abstract

The utility model relates to the technical field of wing stiffness detection, in particular to a stiffness detection device for aircraft wings, comprising a placement plate, two fixed mounts are arranged symmetrically on the upper surface of the placement plate, mounting plates are fixed on the upper surfaces of the two fixed mounts, two hydraulic cylinders are symmetrically installed on the lower end of the mounting plate, tension sensors are connected to the output ends of the two hydraulic cylinders, a clamping piece is arranged on the lower surface of the tension sensor, a biaxial motor is installed inside the clamping piece, and a screw rod is connected to the output shaft of the dual shaft motor. A movable plate is connected to the outer wall, and a guide rod is arranged on one side of the movable plate. The utility model can drive the clamping part to move through the hydraulic cylinder arranged on the mounting plate, and can detect the pulling force of the hydraulic cylinder through the tension sensor arranged at the output end of the hydraulic cylinder, and obtain the stiffness of the wing after calculation by the computer, thereby completing the detection and being convenient for people to use.

Description

A device for testing the stiffness of an aircraft wing

technical field

The utility model relates to the technical field of wing stiffness detection, in particular to a stiffness detection device for an aircraft wing.

Background technique

Unmanned aircraft, referred to as "UAV", is an unmanned aircraft controlled by radio remote control equipment and self-contained program control device. When the wings are in the air, they provide lift for the aircraft. In view of the fact that the wings need to be bent up and down, the air is tilted upwards, and the ground is bent downwards. An important means of analyzing correctness.

For example, the publication number is CN218156829U, a kind of wing strength detection device for unmanned aerial vehicle manufacturing. This utility model discloses a kind of wing strength detection device for unmanned aerial vehicle manufacturing. The utility model can drive the rotating rod to rotate through the cooperating arrangement of the reduction motor, the worm and the worm wheel. The rotating rod can drive the two-way threaded rod to rotate through the cooperative setting of the No. 1 gear and the No. 2 gear. The bi-directional threaded rod can drive the two clips to move relative to each other and clamp and limit the UAV wing through the cooperating setting of the No. 1 gear and the No. 2 gear.

Based on the above, it can be seen that there are the following technical problems in the prior art: the existing testing equipment is inconvenient to adjust the clamping mechanism, and the clamping will be unstable, and the wing is prone to shake during the testing process, thereby reducing the clamping effect. Therefore, we provide a stiffness testing device for the aircraft wing.

Utility model content

The purpose of this utility model is to provide a stiffness detection device for aircraft wings to solve the problems raised in the above-mentioned background technology.

In order to solve the above-mentioned technical problems, the utility model adopts the following technical solutions:

A stiffness detection device for an aircraft wing, comprising a placement board, two fixed mounts are arranged symmetrically on the upper surface of the placement board, mounting plates are fixed on the upper surfaces of the two fixing mounts, two hydraulic cylinders are symmetrically installed on the lower end of the installation board, tension sensors are connected to the output ends of the two hydraulic cylinders, a clamp is arranged on the lower surface of the tension sensor, a biaxial motor is installed inside the clamp, a screw rod is connected to the output shaft of the dual shaft motor, the outer wall of the screw rod is connected to a movable plate, and one side of the movable plate is arranged With guide rod.

Preferably, the hydraulic cylinder and the mounting plate are connected by bolts, and a telescopic structure is formed between the tension sensor and the hydraulic cylinder, and the clamping member and the tension sensor are fixedly connected.

Preferably, a rotating structure is formed between the screw rod and the biaxial motor, and the screw rod penetrates into the movable plate, and the movable plate forms a sliding structure through the guide rod and the clamping member.

Preferably, the movable board is also provided with:

A connecting block is symmetrically arranged at both ends of the movable plate, and a clamping plate is arranged on one side of the connecting block.

Preferably, the connecting block and the movable plate are fixedly connected, and the clamping plate and the connecting block are integrally fixed.

Preferably, the holder is also provided with:

Fixed plates, which are respectively arranged on the inner walls of the two fixed frames, an adjusting screw is installed inside the fixed plate, a connecting rod is connected to the end of the adjusting screw, a bearing is arranged below the connecting rod, and a limiting plate is connected to the lower end of the bearing.

Preferably, the adjusting screw penetrates to the inside of the fixing plate, and the limiting plate forms a rotating structure between the bearing and the connecting rod and the adjusting screw.

It can be seen from the above description that the technical problem to be solved in the present application must be solved through the above technical solution of the present application.

At the same time, through the above technical solutions, the utility model at least has the following beneficial effects:

The utility model can drive the clamping part to move through the hydraulic cylinder provided on the mounting plate, and can detect the pulling force of the hydraulic cylinder through the tension sensor provided at the output end of the hydraulic cylinder, and obtain the stiffness of the wing after calculation by the computer, thereby completing the detection, which is convenient for people to use; the dual-axis motor can drive the screw to rotate, and with the cooperation of the guide rod, the movable plate can be moved to adjust the clamping mechanism, which is convenient for clamping and limiting the wings of different sizes, reducing the situation of clamping instability and improving the detection effect;

The utility model drives the clamping plate to move when the movable plate moves through the provided connecting block, thereby clamping and limiting the wing, which is convenient for subsequent detection operations; by twisting the adjusting screw on the fixed plate, the limiting plate can be driven to move, the lower surface of the limiting plate contacts the upper surface of the wing, and with the cooperation of the bearing, the connecting rod can normally move vertically, thereby pushing the limiting plate to move and limiting the wing.

Description of drawings

Fig. 1 is a schematic diagram of the three-dimensional structure of the utility model;

Fig. 2 is the schematic cross-sectional structure diagram of the clamping part of the present invention;

Fig. 3 is a partial enlarged schematic diagram of place A in Fig. 2 of the utility model;

Fig. 4 is a schematic diagram of the three-dimensional structure of the fixing plate of the present invention.

In the figure: 1. Placement plate; 2. Fixed frame; 3. Mounting plate; 4. Hydraulic cylinder; 5. Tension sensor; 6. Clamping member; 7. Biaxial motor; 8. Screw rod;

Detailed ways

In order to make the purpose, technical solution and advantages of the utility model clearer, the utility model will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the utility model, and are not intended to limit the utility model.

Implementation Case 1

As shown in accompanying drawing 1-Fig. 3, the utility model provides a kind of technical scheme: a kind of rigidity detection equipment of aircraft wing, comprises placing plate 1, and the upper surface of placing plate 1 is symmetrically provided with two fixed mounts 2, and the upper surface of two fixed mounts 2 is all fixed with mounting plate 3, and the lower end of mounting plate 3 is symmetrically installed with two hydraulic cylinders 4, and the output end of two hydraulic cylinders 4 is all connected with tension sensor 5, and the lower surface of tension sensor 5 is provided with clamping member 6, and the interior of clamping member 6 is equipped with biaxial motor 7, the output shaft of biaxial motor 7 A screw rod 8 is connected, and a movable plate 9 is connected to the outer wall of the screw rod 8 , and a guide rod 10 is arranged on one side of the movable plate 9 .

Embodiment two

The solution in Embodiment 1 will be further introduced in combination with specific working methods below, see the following description for details:

As shown in Fig. 1, Fig. 2 and Fig. 3, as a preferred embodiment, on the basis of the above method, further, the hydraulic cylinder 4 and the mounting plate 3 are connected by bolts, and the tension sensor 5 and the hydraulic cylinder 4 form a telescopic structure, and the clamping part 6 and the tension sensor 5 are fixedly connected, the hydraulic cylinder 4 arranged on the mounting plate 3 can drive the clamping part 6 to move, and the tension sensor 5 provided at the output end of the hydraulic cylinder 4 can detect the pulling force of the hydraulic cylinder 4, and obtain the stiffness of the wing after calculation by the computer. The detection is completed, which is convenient for people to use; a rotating structure is formed between the screw rod 8 and the biaxial motor 7, and the screw rod 8 penetrates to the inside of the movable plate 9, and the movable plate 9 forms a sliding structure through the guide rod 10 and the clamping member 6. The biaxial motor 7 can drive the screw rod 8 to rotate.

As shown in Fig. 1, Fig. 2 and Fig. 4, as a preferred embodiment, on the basis of the above method, further, the connecting block 11 is symmetrically arranged at both ends of the movable plate 9, the connecting block 11 and the movable plate 9 are fixedly connected, and one side of the connecting block 11 is provided with a clamping plate 12, and the clamping plate 12 and the connecting block 11 are fixed in one structure. Through the provided connecting block 11, when the movable plate 9 moves, it drives the clamping plate 12 to move, thereby clamping and limiting the wing, which is convenient for subsequent detection operations Fixed plate 13, it is respectively arranged on the inwall of two fixed mounts 2, the inside of fixed plate 13 is equipped with adjusting screw rod 14, adjusting screw rod 14 runs through to the inside of fixed plate 13, the end of adjusting screw rod 14 is connected with connecting rod 15, the below of connecting rod 15 is provided with bearing 16, the lower end of bearing 16 is connected with limiting plate 17, limiting plate 17 forms a rotating structure through bearing 16 and connecting rod 15 and adjusting screw rod 14, by turning the adjusting screw rod 1 on the fixing plate 13 4. It can drive the limit plate 17 to move, the lower surface of the limit plate 17 is in contact with the upper surface of the wing, and under the cooperation of the bearing 16, the connecting rod 15 can normally move vertically, thereby pushing the limit plate 17 to move, and the wing is limited.

Based on the above, we can see that:

The utility model aims at the technical problem: the existing detection equipment is inconvenient to adjust the clamping mechanism, and the clamping will be unstable, and the wing is prone to shaking during the detection process, thereby reducing the clamping effect; the technical solutions of the above-mentioned embodiments are adopted. Simultaneously, the realization process of above-mentioned technical scheme is:

Before using the stiffness detection equipment of the aircraft wing, the placement plate 1 is first placed in a suitable position, through the openings on the two fixing frames 2, the wing to be detected is passed through the opening and placed on the placement plate 1, and then the adjusting screw 14 on the fixing plate 13 is rotated to drive the connecting rod 15 to move vertically, so that the lower surface of the limiting plate 17 is in contact with the upper surface of the wing. Vertical movement, thereby pushing the limit plate 17 to move, limit the wing, avoid the situation of displacement when the wing is detected, and then drive the clamping member 6 to move vertically through the hydraulic cylinder 4 provided on the mounting plate 3, so that the two groups of clamping plates 12 move to both sides of the wing respectively, and the biaxial motor 7 arranged in the clamping component 6 drives the screw rod 8 to rotate. Clamping and fixing facilitates the adjustment of the clamping mechanism, avoids unstable clamping, and improves the subsequent detection effect. After the clamping is completed, the set hydraulic cylinder 4 drives the clamping member 6 to rise. The tension sensor 5 provided at the output end of the hydraulic cylinder 4 can detect the pulling force of the hydraulic cylinder 4. After calculation by the computer, the stiffness of the wing can be obtained, so as to complete the detection and facilitate people's use.

Through the above settings, the present application must be able to solve the above technical problems, and at the same time, achieve the following technical effects:

The utility model can drive the clamping part 6 to move through the hydraulic cylinder 4 provided on the mounting plate 3, and the tension sensor 5 provided at the output end of the hydraulic cylinder 4 can detect the pulling force of the hydraulic cylinder 4, and obtain the stiffness of the wing after calculation by the computer, thereby completing the detection and making it convenient for people to use; the dual-axis motor 7 can drive the screw rod 8 to rotate, and under the cooperation of the guide rod 10, the movable plate 9 can be moved, thereby adjusting the clamping mechanism, which is convenient for clamping and limiting the wings of different sizes, and reduces the occurrence of clamping Unstable situation, improve the detection effect;

The utility model is provided with the connecting block 11, so that when the movable plate 9 moves, it drives the clamping plate 12 to move, thereby clamping and limiting the wing, which is convenient for subsequent detection operations; by twisting the adjusting screw 14 on the fixed plate 13, the limiting plate 17 can be driven to move, and the lower surface of the limiting plate 17 is in contact with the upper surface of the wing.

Although the embodiments of the present invention have been shown and described, for those of ordinary skill in the art, it can be understood that various changes, modifications, replacements and modifications can be made to these embodiments without departing from the principle and spirit of the present invention, and the scope of the present invention is defined by the appended claims and their equivalents.

Claims (7)

1. A stiffness detection device of an aircraft wing, characterized in that it comprises: Place the board (1), the upper surface of the placement board (1) is symmetrically provided with two fixing frames (2), the upper surfaces of the two fixing frames (2) are fixed with mounting plates (3), the lower end of the mounting plate (3) is symmetrically installed with two hydraulic cylinders (4), the output ends of the two hydraulic cylinders (4) are connected to tension sensors (5), the lower surface of the tension sensor (5) is provided with a clamping piece (6), and a biaxial motor (7) is installed inside the clamping piece (6). The output shaft of the biaxial motor (7) is connected with a screw rod (8), the outer wall of the screw rod (8) is connected with a movable plate (9), and one side of the movable plate (9) is provided with a guide rod (10). 2. the stiffness detection equipment of a kind of aircraft wing according to claim 1, it is characterized in that, be bolt connection between described hydraulic cylinder (4) and mounting plate (3), and form telescopic structure between tension sensor (5) and hydraulic cylinder (4), and be fixedly connected between clamp (6) and tension sensor (5). 3. the stiffness detection equipment of a kind of aircraft wing according to claim 1, is characterized in that, constitutes rotating structure between described screw mandrel (8) and biaxial motor (7), and screw mandrel (8) penetrates to the inside of movable plate (9), and movable plate (9) constitutes sliding structure between guide rod (10) and clamp (6). 4. the stiffness detection equipment of a kind of aircraft wing according to claim 1, is characterized in that, described movable plate (9) is also provided with: A connecting block (11) is arranged symmetrically at both ends of the movable plate (9), and a clamping plate (12) is arranged on one side of the connecting block (11). 5. the stiffness detection equipment of a kind of aircraft wing according to claim 4, is characterized in that, be fixedly connected between described connection block (11) and movable plate (9), and between clamping plate (12) and connection block (11) One fixed structure. 6. the stiffness detection equipment of a kind of aircraft wing according to claim 1, is characterized in that, described fixed mount (2) is also provided with: Fixing plate (13), it is respectively arranged on the inner wall of two described fixed mounts (2), and the inside of described fixing plate (13) is equipped with adjusting screw rod (14), and the end of described adjusting screw rod (14) is connected with connecting rod (15), and the below of described connecting rod (15) is provided with bearing (16), and the lower end of described bearing (16) is connected limiting plate (17). 7. the stiffness detection equipment of a kind of aircraft wing according to claim 6, is characterized in that, described adjusting screw rod (14) penetrates to the inside of fixed plate (13), and limiting plate (17) constitutes rotating structure between bearing (16) and connecting rod (15) and adjusting screw rod (14).