Wing control surface gap detection device

Abstract

The utility model discloses a wing control surface gap detection device, which belongs to the technical field of wing control surface gap detection, and comprises positioning parts, and the positioning parts are arranged oppositely in pairs so as to compress and position a wing; the detection part comprises a driver, an upper pressing pin, a lower pressing pin and a displacement sensor, the upper pressing pin and the lower pressing pin tightly press the to-be-detected end of the wing, the driver drives the upper pressing pin and the lower pressing pin to move oppositely or reversely, the displacement sensor is located at the to-be-detected position of the wing, and the displacement sensor is located at the to-be-detected position of the wing. And determining the deformation displacement of the wing control surface. The wing control surface clearance detection device is simple in structure and convenient to disassemble and assemble, realizes clearance detection of the wing control surface under the matching action of the pressure sensor and the displacement sensor, can be compatible with control surface detection of wings of various specifications, is higher in universality, and is higher in detection precision and higher in efficiency compared with manual operation.

Description

Technical Field

[0001] The utility model belongs to the technical field of wing and control surface clearance detection, in particular to a wing and control surface clearance detection device. Background Art

[0002] The wing is one of the most important parts on an aircraft. After the aircraft wing is produced and processed, the clearance of the wing control surfaces needs to be tested to meet the use requirements of the aircraft wing. Currently, the common method for testing the control surfaces of aircraft wings is manual testing, that is, the operator applies tension to the wing and uses the micrometer reading for testing. This testing method requires a lot of manpower and high skills of the operator. In addition, manual operation has certain inaccuracies, which is time-consuming and labor-intensive. It cannot guarantee the consistency of the detection, is inefficient and lacks accuracy. Utility Model Content

[0003] The utility model overcomes the deficiencies of the prior art and provides a wing control surface clearance detection device to solve the problems existing in the prior art.

[0004] In order to achieve the above purpose, the technical solution adopted by the utility model is: a wing control surface clearance detection device, comprising

[0005] Positioning parts, the positioning parts are arranged in pairs and opposite to each other to press the wings tightly and position them;

[0006] The detection part includes a driver, an upper pressure pin, a lower pressure pin and a displacement sensor. The upper pressure pin and the lower pressure pin press the end of the wing to be measured. The driver drives the upper pressure pin and the lower pressure pin to move toward or in opposite directions. The displacement sensor is located at the position to be measured on the wing to determine the deformation displacement of the wing control surface.

[0007] In a preferred embodiment of the present invention, a bracket is further included, and the positioning part and the detection part are both installed on the bracket.

[0008] In a preferred embodiment of the present invention, the positioning portion includes a connecting frame and a positioning pressure platform, the connecting frame is detachably mounted on the bracket, and the positioning pressure platform is mounted on the connecting frame via a buffer spring.

[0009] In a preferred embodiment of the present invention, a pressure sensor is provided on the connecting frame to monitor the pressure of the positioning press platform on the wing.

[0010] In a preferred embodiment of the present invention, the upper pressing pin and the lower pressing pin are both connected to the driver via a motion frame, and the driver drives the upper pressing pin and the lower pressing pin via the motion frame.

[0011] In a preferred embodiment of the present utility model, the number of the upper pressing pins and the lower pressing pins is both two, and they are arranged in pairs correspondingly to clamp the end portion to be measured of the wing.

[0012] In a preferred embodiment of the present utility model, the displacement sensor is installed on the bracket and corresponds to the position to be measured of the wing.

[0013] In a preferred embodiment of the present utility model, the driver is a driving motor with a speed reducer.

[0014] The present utility model solves the defects existing in the background technology, and the present utility model has the following beneficial effects:

[0015] The wing rudder surface clearance detection device of the present utility model has a simple structure and is convenient for disassembly and assembly. With the cooperation of the pressure sensor and the displacement sensor, the clearance detection of the wing rudder surface is realized. It can be compatible with the rudder surface detection of various specifications of wings, has stronger versatility, and has higher detection accuracy and faster efficiency compared with manual operation. Description of the Drawings

[0016] The following further illustrates the present utility model in conjunction with the drawings and embodiments;

[0017] Figure 1 It is a schematic diagram of the overall structure of the preferred embodiment of the present utility model;

[0018] Figure 2 For Figure 1 The enlarged view of part A in

[0019] Figure 3 For Figure 1 The enlarged view of part B in

[0020] In the figure: 10, positioning part; 11, connecting frame; 12, positioning pressing table; 20, detecting part; 21, driver; 22, upper pressing pin; 23, lower pressing pin; 24, displacement sensor; 30, bracket; 40, buffer spring; 50, pressure sensor; 60, moving frame. Detailed Embodiment

[0021] The following will disclose multiple embodiments of the present utility model with diagrams. For the sake of clear description, many physical details will be described together in the following narrative. However, it should be understood that these physical details are not used to limit the present utility model. That is to say, in some embodiments of the present utility model, these physical details are unnecessary. In addition, for the purpose of simplifying the diagrams, some conventional structures and components will be shown in a simple schematic manner in the diagrams.

[0022] In addition, in the present utility model, descriptions such as "first" and "second" are only for descriptive purposes, and do not specifically refer to the meaning of order or sequence, nor are they used to limit the present utility model. They are merely used to distinguish components or operations described with the same technical terms, and cannot be understood as indicating or implying their relative importance or implicitly indicating the quantity of the indicated technical features. Thus, features defined with "first" and "second" may explicitly or implicitly include at least one such feature. In addition, the technical solutions between various embodiments can be combined with each other, but it must be based on the ability of those of ordinary skill in the art to implement. When the combination of technical solutions results in contradictions or cannot be implemented, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection required by the present utility model.

[0023] This embodiment provides a wing flap gap detection device. The wing flap gap detection device has a simple structure and is easy to disassemble and assemble. With the cooperation of the pressure sensor 50 and the displacement sensor 24, the detection of the gap of the wing flap is realized. It can be compatible with the flap detection of various specifications of wings, has stronger versatility, and has higher detection accuracy and faster efficiency compared with manual operation.

[0024] Combined with Figures 1 to 3 As shown, the wing flap gap detection device of this embodiment includes a positioning part 10 and a detection part 20. The positioning part 10 presses and positions the middle position of the wing, and the detection part 20 detects the gap at the position to be measured of the wing flap.

[0025] In this embodiment, the wing flap gap detection device further includes a bracket 30, and the positioning part 10 and the detection part 20 are both installed on the bracket 30.

[0026] Combined with Figure 1 And Figure 2 As shown, the positioning parts 10 in this embodiment are arranged in pairs and are relatively arranged. The positioning part 10 includes a connecting frame 11 and a positioning pressing table 12. The connecting frame 11 is detachably installed on the bracket 30, and the positioning pressing table 12 is installed on the connecting frame 11 through a buffer spring 40. The wing is pressed and positioned by two positioning pressing tables 12 from the front and the back of the wing for subsequent detection of the wing.

[0027] In this embodiment, a pressure sensor 50 is arranged on the connecting frame 11 to monitor the pressure of the positioning pressing table 12 on the wing. The presence of the pressure sensor 50 can more accurately control the pressure applied to the wing flap, avoid damaging the wing flap due to excessive applied force, and effectively avoid damage to the wing flap while ensuring the positioning and pressing of the wing.

[0028] Combined with Figure 1 And Figure 3As shown in the figure, the detection unit 20 of this embodiment includes a driver 21, an upper pressing pin 22, a lower pressing pin 23, and a displacement sensor 24. The upper pressing pin 22 and the lower pressing pin 23 clamp the end of the wing to be measured. The driver 21 drives the upper pressing pin 22 and the lower pressing pin 23 to move towards each other or in the opposite direction. The displacement sensor 24 is located at the position of the wing to be measured to determine the deformation displacement of the wing control surface. The deformation displacement of the wing control surface obtained by the displacement sensor 24 is transmitted to an external computer. Combining with the pressure data obtained by the pressure sensor 50, the clearance generated by the wing control surface under the current force condition can be obtained.

[0029] In this embodiment, both the upper pressing pin 22 and the lower pressing pin 23 are connected to the driver 21 through a moving frame 60. The driver 21 drives the upper pressing pin 22 and the lower pressing pin 23 through the moving frame 60. During the wing detection process, the upper pressing pin 22 and the lower pressing pin 23 move towards each other to squeeze the wing control surface. The displacement sensor 24 is installed on the bracket 30 and corresponds to the position of the wing to be measured. The deformation displacement of the wing control surface is obtained by the displacement sensor 24 for subsequent detection.

[0030] Furthermore, the number of both the upper pressing pin 22 and the lower pressing pin 23 is two, and they are arranged in pairs to clamp the end of the wing to be measured, so as to facilitate the displacement sensor 24 to monitor the deformation displacement of the wing control surface.

[0031] In this embodiment, the driver 21 is a drive motor with a speed reducer, and a pulling rope is used to pull the moving frame 60. On the premise of ensuring accurate control of the pulling force, the problem of the motor retreating during the shutdown state can be effectively avoided.

[0032] In actual use of the wing control surface clearance detection device of this embodiment, the positioning unit 10 positions the wing. The upper pressing pin 22 and the lower pressing pin 23 of the detection unit 20 move towards each other under the action of the driver 21 to squeeze the wing control surface. The displacement sensor 24 can obtain the deformation displacement of the wing control surface and transmit the data to an external computer. Combining with the data obtained by the pressure sensor 50, the computer calculates the clearance generated by the wing control surface under the current force condition.

[0033] All in all, the wing control surface clearance detection device of this embodiment has a simple structure and is easy to disassemble and assemble. With the cooperation of the pressure sensor 50 and the displacement sensor 24, the clearance detection of the wing control surface is realized. It can be compatible with the control surface detection of multiple specifications of wings, has stronger versatility, higher detection accuracy and faster efficiency compared with manual operation.

[0034] Although the present utility model has been described above with reference to various embodiments, it should be understood that many changes and modifications can be made without departing from the scope of the present utility model. That is to say, the methods, systems, devices, etc. discussed above are all examples. Various configurations can be appropriately omitted, replaced or added with various processes or components. For example, in an alternative configuration, the method can be executed in an order different from the described order, and / or various stages can be added, omitted and / or combined. Moreover, the features described with respect to certain configurations can be combined in various other configurations. Different aspects and elements of the configuration can be combined in a similar manner. In addition, with the development of technology, many elements are only examples and do not limit the scope of the present disclosure or the claims.

[0035] Specific details are given in the description to provide a thorough understanding of the exemplary configurations including the implementation. However, the configurations can be practiced without these specific details. For example, well-known circuits, processes, algorithms, structures and technologies have been shown without unnecessary details to avoid obscuring the configurations. The description only provides exemplary configurations and does not limit the scope, applicability or configuration of the claims. On the contrary, the foregoing description of the configurations will provide those skilled in the art with an enabling description for implementing the described technology. Various changes can be made to the functions and arrangements of the elements without departing from the spirit or scope of the present disclosure.

[0036] In addition, although each operation can be described as a sequential process, many operations can be performed in parallel or simultaneously. Additionally, the order of the operations can be rearranged. A process may have other steps. Moreover, examples of the method can be implemented by hardware, software, firmware, middleware, code, hardware description language or any combination thereof. When implemented in software, firmware, middleware or code, the program code or code segment for performing the necessary tasks can be stored in a non-transitory computer-readable medium such as a storage medium and executed by a processor to perform the described tasks.

[0037] In summary, it is intended that the above detailed description be considered illustrative rather than restrictive, and it should be understood that the claims (including all equivalents) are intended to define the spirit and scope of the present utility model. The above embodiments should be understood to be only for illustrating the present utility model and not for limiting the protection scope of the present utility model. After reading the content recorded in the present utility model, those skilled in the art can make various changes or modifications to the present utility model, and these equivalent changes and modifications also fall within the scope defined by the claims of the present utility model.

Claims

1. An aircraft wing control surface clearance detection device, characterized in that, including positioning parts (10), with the positioning parts (10) in pairs and arranged oppositely to press and position the wing detection part (20), the detection part (20) includes a driver (21), an upper pressing pin (22), a lower pressing pin (23) and a displacement sensor (24), the upper pressing pin (22) and the lower pressing pin (23) press the end part of the wing to be measured, the driver (21) drives the upper pressing pin (22) and the lower pressing pin (23) to move towards each other or move in the reverse direction, and the displacement sensor (24) is located at the position of the wing to be measured to determine the deformation displacement of the wing rudder surface 2. The wing flap clearance detection device according to claim 1, characterized in that, further including a bracket (30), and the positioning parts (10) and the detection part (20) are both installed on the bracket (30) 3. The wing rudder surface clearance detection device according to claim 2, characterized in that, the positioning part (10) includes a connecting frame (11) and a positioning pressing table (12), the connecting frame (11) is detachably installed on the bracket (30), and the positioning pressing table (12) is installed on the connecting frame (11) through a buffer spring (40) 4. The wing rudder surface clearance detection device according to claim 3, characterized in that, a pressure sensor (50) is arranged on the connecting frame (11) to monitor the pressure of the positioning pressing table (12) on the wing 5. The wing rudder surface clearance detection device according to claim 1, characterized in that, the upper pressing pin (22) and the lower pressing pin (23) are both connected to the driver (21) through a moving frame (60), and the driver (21) drives the upper pressing pin (22) and the lower pressing pin (23) through the moving frame (60) 6. The wing rudder surface clearance detection device according to claim 5, wherein the number of the upper pressing pins (22) and the lower pressing pins (23) is two, and they are arranged in pairs correspondingly to press the end part of the wing to be measured 7. The wing flap clearance detection device according to claim 3, wherein, the displacement sensor (24) is installed on the bracket (30) and corresponds to the position of the wing to be measured 8. The wing flap clearance detection device according to claim 1, characterized in that, the driver (21) is a driving motor with a speed reducer

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