Detection device

Abstract

The utility model discloses a detection device, and relates to the technical field of wing detection. The detection device comprises a first detection assembly arranged in an outer flap cabin and detachably connected with a first suspension joint; the first detection assembly comprises a first detection assembly which is arranged on the side, close to the outer flap cabin, of the triangular area and is matched with the shape of the side, close to the outer flap cabin, of the triangular area; a first preset distance and a second preset distance exist between the first inspection assembly and the triangular area; the second detection assembly is arranged in the inner flap cabin and is detachably connected with the second suspension joint; the second detection assembly comprises a second detection assembly which is arranged on one side, close to the inner flap cabin, of the triangular area and is matched with the shape of the side, close to the inner flap cabin, of the triangular area; and a third preset distance and a fourth preset distance exist between the second inspection assembly and the triangular area. The detection device is used for reducing the task load in the detection working process, improving the detection efficiency and reducing the detection error at the same time.

Description

Technical Field

[0001] This utility model relates to the field of wing inspection technology, and in particular to an inspection device. Background Technology

[0002] There is a triangular area between the inner and outer flaps of the new regional jet, which is part of the wing trailing edge flap nacelle. After the wing box section is assembled and removed from the rack, the triangular area is an important reference area for the installation of the inner and outer flaps. Its shape quality directly affects the positioning of the inner and outer flaps and the accuracy of their spanwise and heading, as well as other design requirements. Therefore, the shape of the triangular area needs to be effectively inspected and controlled.

[0003] In existing technologies, digital measurement techniques are typically used to measure and evaluate the shape of the triangular region, such as using a laser tracker.

[0004] However, there are many shortcomings in using digital measurement technology. For example, the equipment needs to be warmed up and coordinate system needs to be established in advance. This not only increases the workload of the staff and delays the project, but may also lead to measurement errors due to manual operation. Utility Model Content

[0005] The purpose of this invention is to provide a detection device that reduces the workload in the detection process, improves detection efficiency, and reduces detection errors.

[0006] To achieve this objective, the present invention adopts the following technical solution:

[0007] This utility model provides a detection device for detecting the shape of the triangular region of an aircraft wing. The wing has an outer flap nacelle, a triangular region, and an inner flap nacelle arranged sequentially along its spanwise direction. A first suspension connector is provided on the outer flap nacelle, and a second suspension connector is provided on the inner flap nacelle. The detection device includes: a first detection component, detachably connected to the first suspension connector; the first detection component includes a first inspection assembly, located on the side of the triangular region near the outer flap nacelle, and adapted to the shape of the side of the triangular region near the outer flap nacelle; in the spanwise direction of the wing, the first inspection... A first preset distance exists between the first inspection assembly and the triangular area; a second preset distance exists between the first inspection assembly and the triangular area in the Z-axis direction; a second detection component is detachably connected to the second suspension joint; the second detection component includes a second inspection assembly, disposed on the side of the triangular area near the inner flap nacelle, and adapted to the shape of the side of the triangular area near the inner flap nacelle; a third preset distance exists between the second inspection assembly and the triangular area in the spanwise direction of the wing; and a fourth preset distance exists between the second inspection assembly and the triangular area in the Z-axis direction.

[0008] In some embodiments, the first detection component further includes: a first main frame, disposed parallel to the upper skin of the wing, the first main frame being located on the side of the triangular region near the outer flap nacelle; a first inspection assembly fixedly connected to the first main frame; a first positioning assembly fixedly connected to the first main frame and detachably connected to the first suspension joint; the first positioning assembly being capable of positioning the first main frame in the heading and spanwise directions of the wing; the second detection component further includes: a second main frame, disposed parallel to the upper skin of the wing, the second main frame being located on the side of the triangular region near the inner flap nacelle; a second inspection assembly fixedly connected to the second main frame; a second positioning assembly fixedly connected to the second main frame and detachably connected to the second suspension joint; the second positioning assembly being capable of positioning the second main frame in the heading and spanwise directions of the wing.

[0009] In some embodiments, the outer flap nacelle is further provided with a third suspension joint, and the inner flap nacelle is further provided with a fourth suspension joint; the first detection component further includes a third positioning assembly, which is fixedly connected to the first main frame and detachably connected to the third suspension joint; the third positioning assembly is capable of positioning the first main frame in the heading and spanwise directions of the wing; the second detection component further includes a fourth positioning assembly, which is fixedly connected to the second main frame and detachably connected to the fourth suspension joint; the fourth positioning assembly is capable of positioning the second main frame in the heading and spanwise directions of the wing.

[0010] In some embodiments, the first suspension joint, the second suspension joint, the third suspension joint, and the fourth suspension joint have the same structure; the first positioning assembly, the second positioning assembly, the third positioning assembly, and the fourth positioning assembly have the same structure.

[0011] In some embodiments, the first suspension joint has a positioning groove; the first positioning assembly includes a connector, a positioning member, and a fixing shaft; one end of the connector is fixedly connected to the first main frame, and the other end is fixedly connected to the positioning member; the other end of the positioning member is inserted into the positioning groove; and the fixing shaft passes through the side wall of the positioning groove and the positioning member.

[0012] In some embodiments, the outer flap pod is provided with a first flap arm, and the inner flap pod is provided with a second flap arm; the first detection assembly further includes a third inspection assembly, one end of which is fixedly connected to the first main frame, and the other end of which is at a fifth preset distance from the end of the first flap arm away from the first main frame in the spanwise direction of the wing; the second detection assembly further includes a fourth inspection assembly, one end of which is fixedly connected to the second main frame, and the other end of which is at a sixth preset distance from the end of the second flap arm away from the second main frame in the spanwise direction of the wing.

[0013] In some embodiments, the third inspection assembly includes a first connecting rod and a first inspection pin; one end of the first connecting rod is fixedly connected to the first main frame, and the other end has a first inspection hole; the end of the first flap arm away from the first main frame has a second inspection hole; the first inspection pin is used to pass through the first inspection hole and the second inspection hole to check the coaxiality of the first inspection hole and the second inspection hole. When the first inspection pin passes through both the first inspection hole and the second inspection hole simultaneously, it indicates that the coaxiality meets the inspection requirements. The fourth inspection assembly includes a second connecting rod and a second inspection pin; one end of the second connecting rod is fixedly connected to the second main frame, and the other end has a third inspection hole; the end of the second flap arm away from the second main frame has a fourth inspection hole; the second inspection pin is used to pass through the third inspection hole and the fourth inspection hole to check the coaxiality of the third inspection hole and the fourth inspection hole. When the second inspection pin passes through both the third inspection hole and the fourth inspection hole simultaneously, it indicates that the coaxiality meets the inspection requirements.

[0014] In some embodiments, the first detection component further includes a first support assembly fixedly connected to the first main frame; the first support assembly is adjustable in the Z-axis direction to adjust the distance between the first main frame and the upper skin of the wing; the second detection component further includes a second support assembly fixedly connected to the second main frame; the second support assembly is adjustable in the Z-axis direction to adjust the distance between the second main frame and the upper skin of the wing.

[0015] In some embodiments, the first positioning assembly includes a positioning member and a fixing shaft. The positioning member has an oblong hole that extends along the Z-axis direction. The fixing shaft passes through the oblong hole along the spanwise direction of the wing.

[0016] In some embodiments, both the first detection component and the second detection component are provided with a hoisting component.

[0017] The beneficial effects of this utility model are:

[0018] This invention provides a detection device. It comprises a first detection assembly including a first inspection component and a second detection assembly including a second inspection component. The first detection component is disposed on the outer flap nacelle of an aircraft wing and detachably connected to a first suspension connector on the outer flap nacelle. The second detection component is disposed on the inner flap nacelle of the aircraft wing and detachably connected to a second suspension connector on the inner flap nacelle. Simultaneously, the first inspection component is positioned on the side of the triangular region near the outer flap nacelle of the wing, and its shape is adapted to the shape of the side of the triangular region near the outer flap nacelle. The second inspection component is positioned on the side of the triangular region near the inner flap nacelle of the wing, and its shape is adapted to the shape of the side of the triangular region near the inner flap nacelle of the wing. In the spanwise direction of the wing, the first and second inspection components are respectively positioned at a first preset distance and a third preset distance from the triangular region of the wing. In the Z-axis direction of the wing, the first and second inspection components are respectively positioned at a second preset distance and a fourth preset distance from the triangular region of the wing. This allows for the following process when inspecting the shape of the triangular region of the wing: In the spanwise direction of the wing, there are first and second inspection assemblies with the triangular region, representing first and third actual distances; in the Z-axis direction, there are second and fourth actual distances. These first, second, third, and fourth actual distances are compared one-to-one with first, second, third, and fourth preset distances to determine if they match. This comparison confirms the triangular region's shape is acceptable, thus completing the inspection. This process eliminates the need for preliminary preparation, reduces steps, and simplifies the operation, improving efficiency. Furthermore, transforming the "measurement operation" into a "comparison operation" reduces inspection errors. Attached Figure Description

[0019] Figure 1 This is a structural diagram of a wing provided in a specific embodiment of the present utility model;

[0020] Figure 2 This is a structural diagram of a wing and a detection device provided in a specific embodiment of the present invention;

[0021] Figure 3 This is a structural diagram of a detection device provided in a specific embodiment of this utility model;

[0022] Figure 4 yes Figure 3 An enlarged structural diagram of region A in the structure shown;

[0023] Figure 5 This is a structural diagram from another perspective of a detection device provided in a specific embodiment of this utility model;

[0024] Figure 6 This is a structural diagram of a wing and a first detection component provided in a specific embodiment of this utility model;

[0025] Figure 7 yes Figure 6 An enlarged structural diagram of region B in the structure shown;

[0026] Figure 8 yes Figure 7 An enlarged structural diagram of region B1 in the structure shown;

[0027] Figure 9 yes Figure 7 An enlarged structural diagram of region B2 in the structure shown;

[0028] Figure 10 yes Figure 7 An enlarged structural diagram of region B3 in the structure shown;

[0029] Figure 11 This is a structural diagram of a wing and a second detection component provided in a specific embodiment of this utility model;

[0030] Figure 12 yes Figure 11 An enlarged structural diagram of region C in the structure shown;

[0031] Figure 13 yes Figure 12 An enlarged structural diagram of region C1 in the structure shown;

[0032] Figure 14 yes Figure 12 An enlarged structural diagram of region C2 in the structure shown;

[0033] Figure 15 yes Figure 12 An enlarged structural diagram of region C3 in the structure shown.

[0034] In the picture:

[0035] 1. First inspection assembly; 11. First inspection unit; 111. First inspection clamping plate; 1111. Inspection section; 112. Second inspection clamping plate; 12. First main frame; 13. First positioning assembly; 131. Connecting piece; 132. Positioning piece; 133. Fixed shaft; 14. Third positioning assembly; 15. Third inspection assembly; 151. First connecting rod; 152. First inspection pin; 153. First inspection hole; 16. First support assembly;

[0036] 2. Second inspection assembly; 21. Second inspection assembly; 211. Third inspection clamping plate; 212. Fourth inspection clamping plate; 22. Second main frame; 23. Second positioning assembly; 24. Fourth positioning assembly; 25. Fourth inspection assembly; 251. Second connecting rod; 252. Second inspection pin; 253. Third inspection hole; 26. Second support assembly;

[0037] 3, First suspension joint; 31, Positioning groove; 4, Second suspension joint; 5, Third suspension joint; 6, Fourth suspension joint; 7, First flap arm; 71, Second inspection hole; 8, Second flap arm; 81, Fourth inspection hole; 9, Lifting assembly; 10, Triangular area; 101, Outer flap nacelle; 102, Inner flap nacelle.

[0038] Z, the Z-axis direction. Detailed Implementation

[0039] The present invention will now be described in further detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present invention and not intended to limit it. Furthermore, it should be noted that, for ease of description, the accompanying drawings show only the parts relevant to the present invention, not the entire structure.

[0040] In the description of this utility model, unless otherwise explicitly specified and limited, the terms "connected", "linked", and "fixed" should be interpreted broadly. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0041] In this invention, unless otherwise expressly specified and limited, the first feature being "above" or "below" the second feature may include direct contact between the first and second features, or contact between the first and second features not being in direct contact but through another feature between them.

[0042] In the description of this embodiment, the terms "upper," "lower," "left," and "right," etc., refer to the orientation or positional relationship shown in the accompanying drawings. They are used only for ease of description and simplification of operation, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model. In addition, the terms "first" and "second" are only used for distinction in description and have no special meaning.

[0043] This embodiment provides a detection device for detecting the shape of the triangular region 10 of an airfoil. Combined with... Figures 1 to 15As shown, the wing includes an outer flap 101, a triangular area 10, and an inner flap 102 arranged sequentially along the spanwise direction of the wing (i.e., the direction of wing extension). A first suspension joint 3 is provided on the outer flap 101 of the wing, and a second suspension joint 4 is provided on the inner flap 102 of the wing.

[0044] Combination Figure 1 , Figure 2 As shown, the detection device includes a first detection component 1 and a second detection component 2.

[0045] The first detection component 1 is located on the outer flap nacelle 101 of the aforementioned wing and is detachably connected to the first suspension joint 3 provided on the outer flap nacelle 101. The detachable connection between the two can be achieved, for example, by bolt connection, pin connection, or snap-fit ​​connection.

[0046] Combination Figures 1 to 3 As shown, the first inspection component 1 includes a first inspection assembly 11. This first inspection assembly 11 is located on the side of the triangular area 10 near the outer flap nacelle 101 of the wing, that is, to... Figure 2 Taking the shown perspective as an example, the first detection component 1 is located on the left side of the triangular area 10. The shape of the first detection component 1 is adapted to the side of the triangular area 10 near the wing's outer flap nacelle 101. It is easy to understand that "adapted" here means that the sidewall of the first detection component 1 near the triangular area 10 and the sidewall of the triangular area 10 near the first detection component 1 have the same outline, size, and direction of extension. In other words, if the sidewall of the first detection component 1 near the triangular area 10 is brought into contact with the sidewall of the triangular area 10 near the first detection component 1, the two sidewalls can fit tightly together. In the spanwise direction of the wing, there is a first preset distance between the first detection component 11 and the triangular area 10; in the Z-axis direction Z, there is a second preset distance between the first detection component 11 and the triangular area 10. The first and second preset distances here refer to the standard distances between the first inspection component 1 and the triangular area 10 in the spanwise direction of the wing and in the Z-axis direction Z, after the first inspection component 11 is placed on the side of the triangular area 10 near the outer flap 101 of the wing, provided that the shape of the triangular area 10 of the wing is qualified.

[0047] Combination Figures 1 to 3 As shown, the second detection component 2 is located in the inner flap pod 102 of the wing and is detachably connected to the second suspension connector 4 provided on the inner flap pod 102. The detachable connection between the two can be achieved, for example, by bolt connection, pin connection, or snap-fit ​​connection.

[0048] The aforementioned second inspection component 2 includes a second inspection assembly 21. This second inspection assembly 21 is located on the side of the triangular area 10 near the inner flap nacelle 102 of the wing, that is, to... Figure 2 Taking the shown perspective as an example, the second detection component 2 is located on the right side of the triangular area 10. The shape of this second detection component 2 is adapted to the shape of the side of the triangular area 10 closest to the inner flap 102 of the wing. It is easy to understand that the term "adapted" here has the same meaning as the "adapted" in the previous description of "the shape of the first detection component 1 is adapted to the shape of the side of the triangular area 10 closest to the outer flap 101 of the wing," and will not be repeated here. In the spanwise direction of the wing, there is a third preset distance between the second detection component 21 and the triangular area 10; in the Z-axis direction Z, there is a fourth preset distance between the second detection component 21 and the triangular area 10. The third and fourth preset distances here refer to the standard distances between the second detection component 2 and the triangular area 10 in the spanwise direction and in the Z-axis direction Z, after the shape of the triangular area 10 of the wing is qualified, and after placing the second detection component 21 on the side of the triangular area 10 closest to the inner flap 102 of the wing.

[0049] For example, in combination Figure 2 , Figure 3 , Figure 4 As shown, the first inspection assembly 11 includes a first inspection clamp 111 and a second inspection clamp 112, and the second inspection assembly 21 includes a third inspection clamp 211 and a fourth inspection clamp 212. In the spanwise direction of the wing, the first inspection clamp 111 and the second inspection clamp 112 are located on one side of the triangular area 10, and the third inspection clamp 211 and the fourth inspection clamp 212 are located on the other side of the triangular area 10. Figure 4 As shown, it can be understood that inspection sections 1111 are provided on the first inspection plate 111, the second inspection plate 112, the third inspection plate 113, and the fourth inspection plate 114. Each inspection section 1111 includes two inspection walls arranged perpendicularly to each other, located on the side of the triangular area 10 in the spanwise direction and on the side in the Z-axis direction Z, respectively. In the spanwise direction of the wing, the distance between the inspection sections 1111 on the first inspection plate 111 and the second inspection plate 112 and the triangular area 10 is a first preset distance, and the distance between the inspection sections 1111 on the third inspection plate 211 and the fourth inspection plate 212 and the triangular area 10 is a third preset distance. In the Z-axis direction Z, the distance between the inspection sections 1111 on the first inspection plate 111 and the second inspection plate 112 and the triangular area 10 is a second preset distance, and the distance between the inspection sections 1111 on the third inspection plate 211 and the fourth inspection plate 212 and the triangular area 10 is a fourth preset distance.

[0050] For example, in the Z-axis direction Z, the first inspection plate 111, the second inspection plate 112, the third inspection plate 113, and the fourth inspection plate 114 all have a 10mm gap between themselves and the outer shape of the upper wall panel of the triangular area 10 (i.e., the second preset distance and the fourth preset distance are both 10mm), which is used to detect the shape quality of the upper wall panel of the triangular area 10; in the spanwise direction of the wing, the first inspection plate 111 and the second inspection plate 112 have a 10mm or 20mm gap between themselves and the side wall panel of the triangular area 10 (i.e., the first preset distance is 10mm or 20mm), while the third inspection plate 113 and the fourth inspection plate 114 have a 10mm gap between themselves and the side wall panel of the triangular area 10 (i.e., the third preset distance is 10mm), which is used to detect the accuracy of the spanwise position of the triangular area 10.

[0051] Therefore, this embodiment provides a detection device, which includes a first detection component 1 including a first inspection assembly 11 and a second detection component 2 including a second inspection assembly 21. The first detection component 1 is disposed on the outer flap 101 of the wing and is detachably connected to the first suspension connector 3 disposed on the outer flap 101. The second detection component 2 is disposed on the inner flap 102 of the wing and is detachably connected to the second suspension connector 4 disposed on the inner flap 102. At the same time, the first inspection assembly 11 is disposed on the side of the triangular area 10 near the outer flap 101 of the wing and is adapted to the shape of the side of the triangular area 10 near the outer flap 101 of the wing. The second inspection assembly 21 is disposed on the side of the triangular area 10 near the inner flap 102 of the wing and is adapted to the shape of the side of the triangular area 10 near the inner flap 102 of the wing. In the spanwise direction of the wing, there are a first preset distance and a third preset distance between the first inspection assembly 11 and the second inspection assembly 21 and the triangular area 10 of the wing. In the Z-axis direction Z of the wing, there are a second preset distance and a fourth preset distance between the first inspection assembly 11 and the second inspection assembly 21 and the triangular area 10 of the wing. This allows for the following: when inspecting the shape of the triangular region 10 of the wing, there are first and third actual distances between the first inspection assembly 11 and the second inspection assembly 21 and the triangular region 10 in the spanwise direction of the wing; and second and fourth actual distances between the first inspection assembly 11 and the second inspection assembly 21 and the triangular region 10 in the Z-axis direction of the wing. These first, second, third, and fourth actual distances are compared one-to-one with first, second, third, and fourth preset distances to determine if they match. This allows for the assessment of whether the shape of the triangular region 10 is acceptable, thus completing the inspection of the triangular region 10's shape. In this process of inspecting the shape of the triangular region 10, no preliminary preparation work is required, the operation steps are few, and the process is simple, improving inspection efficiency. Furthermore, changing the "measurement operation" to a "comparison operation" in the inspection process reduces inspection errors.

[0052] In some embodiments, such as Figure 3 As shown, the first detection component 1 also includes a first main frame 12 and a first positioning assembly 13.

[0053] The first main frame 12 is a frame structure composed of multiple rod-like structures (such as square or rectangular tubes, channel steel, etc.) connected to each other (e.g., by welding or threaded connection). For example, the main frame is a rectangular frame structure formed by welding four square steel tubes end-to-end. The first main frame 12 is arranged parallel to the upper skin of the wing; in other words, the first main frame 12 is located on the upper side of the wing and parallel to the outer surface of the wing. The first main frame 12 is located on the side of the aforementioned triangular area 10 near the outer flap 101 of the wing, i.e., with... Figure 2 Taking the shown perspective as an example, the first main frame 12 is located on the left side of the triangular area 10. The aforementioned first inspection assembly 11 is fixedly connected to the first main frame 12, and the two are fixedly connected in a manner such as welding or bolting.

[0054] Combination Figures 5 to 10 As shown, the first positioning assembly 13 is fixedly connected to the first main frame 12. This fixed connection is achieved, for example, by welding or by bolts. Furthermore, the first positioning assembly 13 is detachably connected to the first suspension joint 3 provided on the wing outer flap nacelle 101, also detachably connected, for example, by bolts. This first positioning assembly 13 can position the first main frame 12 in the wing's heading and spanwise directions.

[0055] like Figure 3 As shown, the second detection component 2 also includes a second main frame 22 and a second positioning assembly 23.

[0056] The second main frame 22 is also a frame structure composed of multiple interconnected rods. For example, the structure of the second main frame 22 is the same as that of the first main frame 12; that is, the second main frame 22 is also a rectangular frame structure formed by welding four square steel pipes end to end. This second main frame 22 is parallel to the upper skin of the wing; in other words, it is located on the upper side of the wing and parallel to the outer surface of the wing. This second main frame 22 is located on the side of the aforementioned triangular area 10 near the inner flap 102 of the wing. Figure 2 Taking the shown perspective as an example, the second main frame 22 is located on the right side of the triangular area 10. The aforementioned second inspection assembly 21 is fixedly connected to the second main frame 22, and the two are fixedly connected in a manner such as welding or bolting.

[0057] Combination Figures 11 to 15As shown, the second positioning assembly 23 is fixedly connected to the second main frame 22, for example, by welding or by bolts. The second positioning assembly 23 is also detachably connected to the second suspension joint 4 on the wing inner flap nacelle 102, for example, by bolts. This second positioning assembly 23 can position the second main frame 22 in the wing's heading and span.

[0058] In the aforementioned detection device, the first detection component 1 is configured to include a first main frame 12 and a first positioning assembly 13 fixedly connected to the first main frame 12, and the second detection component 2 is configured to include a second main frame 22 and a second positioning assembly 23 fixedly connected to the second main frame 22. The first positioning assembly 13 is detachably connected to the first suspension connector 3 on the outer flap 101, and the second positioning assembly 23 is detachably connected to the second suspension connector 4 on the inner flap 102. This allows the first main frame 12 to be positioned on the outer flap 101 using the cooperation of the first positioning assembly 13 and the first suspension connector 3, and the second main frame 22 to be positioned on the inner flap 102 using the cooperation of the second positioning assembly 23 and the second suspension connector 4. This design is simple to operate and convenient to use. Furthermore, since the relative positions of the first suspension joint 3 on the outer flap 101 and the second suspension joint 4 on the inner flap 102 on the wing have been fixed, the first main frame 12, with the first suspension joint 3 as the positioning reference and the second main frame 22, with the second suspension joint 4 as the positioning reference, can indirectly position the first inspection assembly 11, which is fixedly connected to the first main frame 12, and the second inspection assembly 21, which is fixedly connected to the second main frame 22. This fixes the relative positions of the first inspection assembly 11 and the wing triangle 10, and the second inspection assembly 21 and the wing triangle 10. Consequently, errors can be avoided when detecting the first actual distance and the second actual distance between the first inspection assembly 11 and the wing triangle 10, as well as the third and fourth actual distances between the second inspection assembly 21 and the wing triangle 10, ensuring the accuracy of the detection device when detecting the shape of the triangle 10.

[0059] In some embodiments, combined with Figure 2 as well as Figures 6 to 15As shown, a third suspension connector 5 is also provided on the outer flap nacelle 101 of the aforementioned wing, and a fourth suspension connector 6 is also provided on the inner flap nacelle 102 of the aforementioned wing. The aforementioned first detection assembly 1 also includes a third positioning assembly 14. The third positioning assembly 14 is fixedly connected to the aforementioned first main frame 12 and is detachably connected to the third suspension connector 5. The fixed connection method of the third positioning assembly 14 to the first main frame 12 and the detachable connection method to the third suspension connector 5 are, for example, the same as the arrangement method of the first positioning assembly 13 described above, and will not be described in detail here. The third positioning assembly 14 can also position the first main frame 12 in the wing's heading and span.

[0060] like Figure 14 As shown, the second detection component 2 also includes a fourth positioning assembly 24. This fourth positioning assembly 24 is fixedly connected to the second main frame 22 and detachably connected to the fourth suspension connector 6. The method of fixing the fourth positioning assembly 24 to the second main frame 22 and the method of detachably connecting it to the fourth suspension connector 6 are, for example, the same as the method of setting the second positioning assembly 23 described above, and will not be described further here. This fourth positioning assembly 24 can also position the second main frame 22 in the wing's heading and span.

[0061] In the aforementioned testing device, a third positioning assembly 14 is added to the first testing component 1. This assembly is detachably connected to the third suspension joint 5 on the outer wing flap 101 and can also position the first main frame 12 in the wing's heading and spanwise directions. Similarly, a fourth positioning assembly 24 is added to the second testing component 2. This assembly is detachably connected to the fourth suspension joint 6 on the inner wing flap 102 and can also position the second main frame 22 in the wing's heading and spanwise directions. This enhances the positioning effect of the first main frame 12 on the outer wing flap 101 and the second main frame 22 on the inner wing flap 102, further ensuring the accuracy of testing the shape of the triangular area 10 using this device. Furthermore, by simultaneously providing two positioning assemblies in one testing component, the synergistic effect of the two positioning assemblies ensures that if one positioning assembly fails, the other can continue to perform its positioning function, improving the reliability of the positioning.

[0062] In some embodiments, the first suspension joint 3, the second suspension joint 4, the third suspension joint 5, and the fourth suspension joint 6 provided on the wing have the same structure. The first positioning assembly 13, the second positioning assembly 23, the third positioning assembly 14, and the fourth positioning assembly 24 in the first detection assembly 1 and the second detection assembly 2 have the same structure. This arrangement reduces the design and manufacturing cost of the detection device, improves the interchangeability of the components, and facilitates maintenance and repair.

[0063] In some embodiments, such as Figure 8 As shown, the first suspension joint 3 is provided with a positioning groove 31. The opening of the positioning groove 31 faces the first positioning assembly 13.

[0064] like Figure 8 As shown, the first positioning assembly 13 includes a connector 131, a positioning element 132, and a fixing shaft 133. The connector 131 is, for example, a connecting rod or a connecting plate. One end of the connector 131 is fixedly connected to the first main frame 12, for example, by welding or bolting. The other end of the connector 131 is fixedly connected to the positioning element 132, and the other end of the positioning element 132 is inserted into the positioning groove 31. The positioning element 132 is, for example, a rectangular plate structure, and the opening shape of the positioning groove 31 is rectangular to match the positioning element 132. The fixing shaft 133 passes through the side wall of the positioning groove 31 and the positioning element 132. Specifically, the positioning member 132 has a positioning hole for the fixed shaft 133 to pass through, and positioning holes are also provided on both side walls of the positioning groove 31. These three through holes (positioning holes) are coaxially arranged, allowing the fixed shaft 133 to pass through all three through holes simultaneously (i.e., through the side wall of the positioning groove 31 and the positioning member 132). This arrangement enables a detachable connection between the first positioning member 13 and the first suspension connector 3, resulting in a simple structure and convenient use.

[0065] In addition, it is easy to understand that after the positioning member 132 in the first positioning assembly 13 is inserted into the positioning groove 31 on the first suspension joint 3, a plug can be inserted between the side wall of the positioning member 132 and the side wall of the groove 31 to fill the gap that may be caused by the manufacturing process, prevent shaking, and thus ensure the accuracy of positioning of the entire first main frame 12.

[0066] In some embodiments, combined with Figures 1 to 15 As shown, the outer flap nacelle 101 of the aforementioned wing is equipped with a first flap support arm 7, and the inner flap nacelle 102 of the aforementioned wing is equipped with a second flap support arm 8. The first flap support arm 7 and the second flap support arm 8 are used to connect the outer flap nacelle 101 and the inner flap nacelle 102 to the wing, respectively, to ensure that the outer flap nacelle 101 and the inner flap nacelle 102 can be smoothly deployed or retracted. The installation position of the first flap support arm 7 and the second flap support arm 8 will affect the clearance between the outer flap nacelle 101 and the inner flap nacelle 102 and the triangular area 10. Therefore, in order to further ensure the accuracy of the installation positioning of the outer flap nacelle 101 and the inner flap nacelle 102, it is necessary to check the installation position of the first flap support arm 7 and the second flap support arm 8.

[0067] The aforementioned first detection component 1 also includes a third inspection assembly 15, one end of which is fixedly connected to the first main frame 12 (the two are fixedly connected by means of welding or bolts, for example), and the other end is at a fifth preset distance from the end of the first flap arm 7 away from the first main frame 12 in the spanwise direction of the wing.

[0068] The second detection component 2 also includes a fourth inspection assembly 25. One end of the fourth inspection assembly 25 is fixedly connected to the second main frame 22 (the two are fixedly connected by means of welding or bolts, for example), and the other end is at a sixth preset distance from the end of the second flap arm 8 away from the second main frame 22 in the spanwise direction of the wing.

[0069] The fifth and sixth preset distances here refer to the standard distances between the third inspection assembly 15 and the first flap arm 7, and the standard distance between the fourth inspection assembly 25 and the second flap arm 8 in the spanwise direction of the wing, provided that the first inspection assembly 1 is installed in the outer flap pod 101 and the second inspection assembly 2 is installed in the inner flap pod 102, provided that the first flap arm 7 and the second flap arm 8 are installed in the correct installation.

[0070] For example, in the spanwise direction of the wing, there is a 6mm gap between the third inspection assembly 15 and the first flap arm 7 (i.e., the fifth preset distance is 6mm), and a 6mm gap between the fourth inspection assembly 25 and the second flap arm 8 (i.e., the sixth preset distance is 6mm), which is used to detect the spanwise shape of the outer flap pod 101 and the inner flap pod 102 (i.e., the installation position in the spanwise direction of the wing).

[0071] In the aforementioned testing device, by adding a third inspection assembly 15, one end of which is fixedly connected to the first main frame 12, to the first testing assembly 1, and adding a fourth inspection assembly 25, one end of which is fixedly connected to the second main frame 22, to the second testing assembly 2, a fifth preset distance exists between the other end of the third inspection assembly 15 and the end of the first flap arm 7 away from the first main frame 12 in the spanwise direction of the wing. A sixth preset distance exists between the other end of the fourth inspection assembly 25 and the end of the second flap arm 8 away from the second main frame 22. This allows for the following: when it is necessary to inspect the installation position of the first flap arm 7 and the second flap arm 8 in the spanwise direction of the flap, there is a fifth actual distance between the third inspection assembly 15 and the first flap arm 7, and a sixth actual distance between the fourth inspection assembly 25 and the second flap arm 8. These fifth and sixth actual distances are compared one-to-one with the fifth and sixth preset distances, respectively. By determining whether multiple actual distances match multiple preset distances, it can be concluded that the installation position of the first flap arm 7 and the second flap arm 8 is qualified, thus completing the inspection of the installation position of the first flap arm 7 and the second flap arm 8 in the spanwise direction of the wing. In the above inspection process, no preliminary preparation work is required, the operation steps are few, the operation process is simple, and the inspection efficiency is improved; at the same time, changing the "measurement operation" in the inspection process into a "comparison operation" can reduce inspection errors.

[0072] In some embodiments, such as Figure 10 As shown, the aforementioned third inspection assembly 15 includes a first connecting rod 151 and a first inspection pin 152. One end of the first connecting rod 151 is fixedly connected to the aforementioned first main frame 12 (the two are fixedly connected by means such as welding or bolts), and the other end has a first inspection hole 153. It is easy to understand that the first inspection hole 153 should be adapted to the first inspection pin 152, that is, the opening shape of the first inspection hole 153 is the same as the cross-sectional shape of the first inspection pin 152 (the cross-sectional direction is perpendicular to the axis of the first inspection pin 152), and the inner diameter of the first inspection hole 153 is the same as the outer diameter of the first inspection pin 152. A second inspection hole 71 is provided at the end of the aforementioned first flap arm 7 away from the first main frame 12, and the second inspection hole 71 should also be adapted to the first inspection pin 152. The first inspection pin 152 is used to pass through the first inspection hole 153 and the second inspection hole 71 to check the coaxiality of the first inspection hole 153 and the second inspection hole 71. When the first inspection pin 152 passes through both the first inspection hole 153 and the second inspection hole 71, it indicates that the coaxiality meets the inspection requirements. By checking the coaxiality of the first inspection hole 153 and the second inspection hole 71, it is possible to indirectly check whether the installation position of the first flap arm 7 in the Z-axis direction Z is qualified.

[0073] like Figure 15 As shown, the aforementioned fourth inspection assembly 25 includes a second connecting rod 251 and a second inspection pin 252. One end of the second connecting rod 251 is fixedly connected to the aforementioned second main frame 22 (the two are fixedly connected by means such as welding or bolts), and the other end has a third inspection hole 253. The third inspection hole 253 should be adapted to the second inspection pin 252. For details, please refer to the description of "the first inspection hole 153 and the first inspection pin 152 are adapted" above, which will not be repeated here. A fourth inspection hole 81 is provided at the end of the aforementioned second flap arm 8 away from the second main frame 22. The fourth inspection hole 81 should also be adapted to the second inspection pin 252. The second inspection pin 252 is used to pass through the third inspection hole 253 and the fourth inspection hole 81 to check the coaxiality of the third inspection hole 253 and the fourth inspection hole 81. When the second inspection pin 252 passes through both the third inspection hole 253 and the fourth inspection hole 81, it indicates that the coaxiality meets the inspection requirements. By inspecting the coaxiality of the third inspection hole 253 and the fourth inspection hole 81, it is possible to indirectly verify whether the installation position of the second flap arm 8 in the Z-axis direction is qualified.

[0074] The first inspection pin 152 and the second inspection pin 252 mentioned above are, for example, grade pins.

[0075] In the above-mentioned testing device, the third inspection assembly 15 is configured with a first connecting rod 151 and a first inspection pin 152, one end of which is fixedly connected to the first main frame 12 and the other end of which has a first inspection hole 153. The fourth inspection assembly 25 is configured with a second connecting rod 251 and a second inspection pin 252, one end of which is fixedly connected to the second main frame 22 and the other end of which has a third inspection hole 253. At the same time, a second inspection hole 71 is opened at the end of the first flap support arm 7 away from the first main frame 12, and a fourth inspection hole 81 is opened at the end of the second flap support arm 8 away from the second main frame 22. This allows the coaxiality of the first inspection hole 153 and the second inspection hole 71 to be checked by simultaneously passing the first inspection pin 152 through the first inspection hole 153 and the second inspection hole 71, thereby indirectly checking whether the installation position of the first flap arm 7 in the Z-axis direction is qualified. Similarly, the coaxiality of the third inspection hole 253 and the fourth inspection hole 81 can be checked by simultaneously passing the second inspection pin 252 through the third inspection hole 253 and the fourth inspection hole 81, thereby indirectly checking whether the installation position of the second flap arm 8 in the Z-axis direction is qualified (i.e., if the first inspection pin 152 can smoothly pass through the first inspection hole 153, the installation position of the second flap arm 8 in the Z-axis direction is qualified). If the second inspection hole 71 of the first inspection pin 153 passes through the second inspection hole 71 of the first inspection hole 153, it indicates that the installation position of the first flap arm 7 in the Z-axis direction is qualified. If the first inspection pin 152 cannot pass through the second inspection hole 71 of the first inspection hole 153 at the same time, it indicates that the installation position of the first flap arm 7 in the Z-axis direction is unqualified. In the above-mentioned inspection process, there are few operation steps and the operation is simple. At the same time, the staff can directly visually inspect the inspection results, thereby improving the inspection efficiency. In addition, this inspection method changes the "measurement operation" into an "insertion operation" with only two results (i.e., insertion is possible or insertion is not possible), which can avoid inspection errors and improve the accuracy of inspection.

[0076] To avoid direct contact between the first main frame 12 and the upper skin of the wing, which could damage the upper skin, the first main frame 12 in the first detection assembly 1 and the second main frame 22 in the second detection assembly 2 should be positioned with a certain gap between them and the upper skin of the wing when using the aforementioned detection device. Furthermore, to ensure detection accuracy, the distance between the first main frame 12 and the upper skin of the wing, and the distance between the second main frame 22 and the upper skin of the wing, should be set to the same value, and uniformly set to a seventh preset distance.

[0077] In order to adjust the distance between the first main frame 12 and the second main frame 22 and the upper skin of the wing to a seventh preset distance during the inspection process. In some embodiments, such as Figure 3 , Figure 4As shown, the first detection component 1 further includes a first support assembly 16, which is fixedly connected to the first main frame 12. The first support assembly 16 is adjustable in the Z-axis direction Z to adjust the distance between the first main frame 12 and the upper skin of the wing.

[0078] For example, the first support assembly 16 includes a fixed plate and an adjustment assembly. One side of the fixed plate is fixedly connected to the first main frame 12, and the other side is rotatably connected to the adjustment assembly. The adjustment assembly includes an adjustment rod extending along the Z-axis direction Z and a support seat that contacts the upper skin of the wing. One end of the adjustment rod is threadedly connected to the support seat, while the rod body is rotatably connected to the fixed plate. Thus, when the other end of the adjustment rod is rotated, the threaded end of the adjustment rod connected to the support seat will move along the Z-axis direction Z under the action of the threaded engagement, thereby driving the first main frame 12 to move in the Z-axis direction Z, realizing the adjustment of the distance between the first main frame 12 and the upper skin of the wing.

[0079] like Figure 3 , Figure 5 As shown, the first detection component 1 further includes a second support assembly 26, which is fixedly connected to the second main frame 22. The second support assembly 26 is adjustable in the Z-axis direction Z to adjust the distance between the second main frame 22 and the upper skin of the wing. The structure of the second support assembly 26 is, for example, the same as that of the first support assembly 16, and will not be described again here.

[0080] In the aforementioned testing device, by setting the first support assembly 16 and the second support assembly 26, the distance between the first main frame 12 and the upper skin of the wing is adjustable, and the distance between the second main frame 22 and the upper skin of the wing is adjustable. This avoids direct contact between the first main frame 12 and the second main frame 22 and the upper skin of the wing, which could cause damage to the upper skin of the wing. At the same time, it also facilitates maintaining a uniform and fixed distance between the first main frame 12 and the second main frame 22 and the upper skin of the wing, thereby ensuring the accuracy of the testing.

[0081] In some embodiments, the positioning member 132 of the first positioning assembly 13 is provided with a waist-shaped hole, which extends along the Z-axis direction Z, and the fixing shaft 133 of the first positioning assembly 13 passes through the waist-shaped hole along the spanwise direction of the wing. With this arrangement, the distance between the first main frame 12 and the upper skin of the wing can be easily adjusted, ensuring that a uniform and fixed distance can be maintained between the first main frame 12 and the upper skin of the wing.

[0082] In some embodiments, such as Figure 3 , Figure 5As shown, both the first detection component 1 and the second detection component 2 are equipped with lifting components 9, such as lifting rings. It is easy to understand that there are multiple lifting components 9, evenly distributed on the first and second detection components 1 and 2. This arrangement allows the lifting components 9 on the first and second detection components to provide a lifting position for the hook of a lifting device (such as a gantry crane) when the detection device needs to be moved or installed, eliminating the need for manual handling, saving manpower, and improving the practicality of the detection device.

[0083] Finally, it should be noted that the "actual distance" mentioned in any of the embodiments above can be determined by inserting a feeler gauge or feeler block between the two components. This eliminates the need for measurement, is convenient and quick, and can reduce detection errors.

[0084] Obviously, the above embodiments of this utility model are merely examples for clearly illustrating the present utility model, and are not intended to limit the implementation of the present utility model. Those skilled in the art can make various obvious changes, readjustments, and substitutions without departing from the protection scope of this utility model. It is neither necessary nor possible to exhaustively describe all embodiments here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this utility model should be included within the protection scope of the claims of this utility model.

Claims

1. A detection device for detecting the shape of a triangular region (10) of an aircraft wing, wherein an outer flap nacelle (101), a triangular region (10), and an inner flap nacelle (102) are arranged sequentially along the spanwise direction of the wing; a first suspension connector (3) is provided on the outer flap nacelle (101), and a second suspension connector (4) is provided on the inner flap nacelle (102), characterized in that, The detection device includes: The first detection component (1) is detachably connected to the first suspension joint (3); the first detection component (1) includes a first inspection assembly (11), which is located on the side of the triangular area (10) near the outer flap nacelle (101) and is adapted to the shape of the side of the triangular area (10) near the outer flap nacelle (101); in the spanwise direction of the wing, there is a first preset distance between the first inspection assembly (11) and the triangular area (10), and in the Z-axis direction (Z), there is a second preset distance between the first inspection assembly (11) and the triangular area (10); The second detection component (2) is detachably connected to the second suspension joint (4); the second detection component (2) includes a second inspection assembly (21), which is located on the side of the triangular area (10) near the inner flap nacelle (102) and is adapted to the shape of the side of the triangular area (10) near the inner flap nacelle (102); in the spanwise direction of the wing, there is a third preset distance between the second inspection assembly (21) and the triangular area (10), and in the Z-axis direction (Z), there is a fourth preset distance between the second inspection assembly (21) and the triangular area (10).

2. The detection device according to claim 1, characterized in that, The first detection component (1) further includes: a first main frame (12) arranged parallel to the upper skin of the wing, the first main frame (12) being located on the side of the triangular area (10) near the outer flap wing pod (101); the first inspection assembly (11) being fixedly connected to the first main frame (12); The first positioning assembly (13) is fixedly connected to the first main frame (12) and detachably connected to the first suspension joint (3); the first positioning assembly (13) can position the first main frame (12) in the heading and span of the wing; The second inspection component (2) further includes: a second main frame (22) arranged parallel to the upper skin of the wing, the second main frame (22) being located on the side of the triangular area (10) near the inner flap wing pod (102); and the second inspection assembly (21) being fixedly connected to the second main frame (22). The second positioning assembly (23) is fixedly connected to the second main frame (22) and detachably connected to the second suspension joint (4); the second positioning assembly (23) is capable of positioning the second main frame (22) in the heading and span of the wing.

3. The detection device according to claim 2, characterized in that, The outer flap nacelle (101) is also provided with a third suspension joint (5), and the inner flap nacelle (102) is also provided with a fourth suspension joint (6). The first detection component (1) also includes a third positioning assembly (14), which is fixedly connected to the first main frame (12) and detachably connected to the third suspension joint (5). The third positioning assembly (14) can position the first main frame (12) in the heading and span of the wing. The second detection component (2) further includes a fourth positioning assembly (24), which is fixedly connected to the second main frame (22) and detachably connected to the fourth suspension joint (6); the fourth positioning assembly (24) is capable of positioning the second main frame (22) in the heading and span of the wing.

4. The detection device according to claim 3, characterized in that, The first suspension joint (3), the second suspension joint (4), the third suspension joint (5), and the fourth suspension joint (6) have the same structure; The first positioning assembly (13), the second positioning assembly (23), the third positioning assembly (14), and the fourth positioning assembly (24) have the same structure.

5. The detection device according to claim 1, characterized in that, The first suspension joint (3) has a positioning groove (31); The first positioning assembly (13) includes a connector (131), a positioning element (132), and a fixing shaft (133); one end of the connector (131) is fixedly connected to the first main frame (12), and the other end is fixedly connected to the positioning element (132); the other end of the positioning element (132) is inserted into the positioning groove (31); and the fixing shaft (133) is disposed through the side wall of the positioning groove (31) and the positioning element (132).

6. The detection device according to claim 1, characterized in that, The outer flap pod (101) is provided with a first flap arm (7), and the inner flap pod (102) is provided with a second flap arm (8); The first detection component (1) further includes a third inspection assembly (15), one end of which is fixedly connected to the first main frame (12), and the other end of which is at a fifth preset distance from the end of the first flap arm (7) away from the first main frame (12) in the spanwise direction of the wing. The second detection component (2) further includes a fourth inspection assembly (25), one end of which is fixedly connected to the second main frame (22), and the other end of which is at a sixth preset distance from the end of the second flap arm (8) away from the second main frame (22) in the spanwise direction of the wing.

7. The detection device according to claim 6, characterized in that, The third inspection assembly (15) includes a first connecting rod (151) and a first inspection pin (152); one end of the first connecting rod (151) is fixedly connected to the first main frame (12), and the other end is provided with a first inspection hole (153); the end of the first flap arm (7) away from the first main frame (12) is provided with a second inspection hole (71); the first inspection pin (152) is used to pass through the first inspection hole (153) and the second inspection hole (71) to inspect the coaxiality of the first inspection hole (153) and the second inspection hole (71). When the first inspection pin (152) passes through the first inspection hole (153) and the second inspection hole (71) at the same time, it indicates that the coaxiality meets the inspection requirements. The fourth inspection assembly (25) includes a second connecting rod (251) and a second inspection pin (252); one end of the second connecting rod (251) is fixedly connected to the second main frame (22), and the other end is provided with a third inspection hole (253); the second flap arm (8) is provided with a fourth inspection hole (81) at the end away from the second main frame (22); the second inspection pin (252) is used to pass through the third inspection hole (253) and the fourth inspection hole (81) to inspect the coaxiality of the third inspection hole (253) and the fourth inspection hole (81). When the second inspection pin (252) passes through the third inspection hole (253) and the fourth inspection hole (81) at the same time, it indicates that the coaxiality meets the inspection requirements.

8. The detection device according to claim 7, characterized in that, The first detection component (1) further includes a first support assembly (16), which is fixedly connected to the first main frame (12); the first support assembly (16) is adjustable in the Z-axis direction (Z) to adjust the distance between the first main frame (12) and the upper skin of the wing; The second detection component (2) further includes a second support assembly (26), which is fixedly connected to the second main frame (22); the second support assembly (26) is adjustable in the Z-axis direction (Z) to adjust the distance between the second main frame (22) and the upper skin of the wing.

9. The detection device according to claim 8, characterized in that, The first positioning assembly (13) includes a positioning member (132) and a fixing shaft (133). The positioning member (132) has an oblong hole that extends along the Z-axis direction (Z). The fixing shaft (133) passes through the oblong hole along the span of the wing.

10. The detection device according to any one of claims 1-9, characterized in that, Both the first detection component (1) and the second detection component (2) are equipped with a hoisting component (9).

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