Inspection device for aileron actuator support

Abstract

The utility model belongs to the technical field of aircraft component assembly, and discloses an aileron actuator support inspection device which comprises a positioning assembly, a locking assembly and an inspection assembly. The positioning assembly is provided with a positioning plane and a reference plane which are perpendicular to each other. The reference plane is provided with an inspection through hole. The locking assembly can lock the positioning assembly and the aileron actuator support, and when the positioning piece and the aileron actuator support are locked, the inspection through hole is aligned with a shaft hole of the aileron suspension connector. The inspection assembly comprises a first inspection piece and a second inspection piece, the first inspection piece can inspect the distance deviation between the first end face and the shaft hole, and the second inspection piece can inspect the spanwise deviation of the aileron suspension joint. The aileron actuator support inspection device provided by the utility model is simple to operate, reduces the time cost for inspecting the distance deviation between the aileron actuator support and the aileron suspension joint and the spanwise deviation of the aileron suspension joint, improves the assembly efficiency of an airplane, does not need station transfer operation, and reduces the labor burden of workers.

Description

Technical Field

[0001] This utility model relates to the field of aircraft component assembly technology, and in particular to an aileron actuator bracket inspection device. Background Technology

[0002] In the field of aerospace manufacturing, the manufacturing and assembly precision of aircraft components is crucial to flight safety and performance. Among them, the positioning precision of the aileron actuator bracket is particularly critical, directly affecting the effective stroke of the aileron actuator and the deflection angle of the aileron.

[0003] Currently, engineering numerical models have strict requirements for the spatial dimensions from the aileron actuator bracket to the aileron suspension joint. Existing technology allows for the measurement of these dimensions using a laser tracker, which offers high measurement accuracy. However, laser tracker measurements require preparatory work such as warming up the engine and establishing a coordinate system, resulting in a long preparation cycle, complex operation, and reduced aircraft production efficiency. Furthermore, measurements of different components require switching stations, increasing the workload for workers. Utility Model Content

[0004] The purpose of this invention is to provide an aileron actuator support inspection device to improve aircraft production efficiency and reduce the workload of workers.

[0005] To achieve this objective, the present invention adopts the following technical solution:

[0006] An aileron actuator support inspection device, comprising:

[0007] A positioning assembly includes a positioning element having mutually perpendicular positioning planes and a reference plane, the reference plane being provided with an inspection through hole;

[0008] A locking assembly capable of locking the positioning member and the aileron actuator bracket. The aileron actuator bracket has a first end face. When the positioning member is locked to the aileron actuator bracket, the positioning plane is in contact with the first end face and the inspection through hole is aligned with the shaft hole of the aileron suspension joint.

[0009] The inspection assembly includes a first inspection piece and a second inspection piece. The first inspection piece can be inserted through the inspection through hole to inspect the distance deviation between the first end face and the shaft hole. The second inspection piece can measure the distance between the reference plane and the second end face on the aileron suspension joint to inspect the spanwise deviation of the aileron suspension joint.

[0010] In the aforementioned aileron actuator bracket inspection device, the first inspection component is an inspection pin, which has a positioning part and an inspection part. The positioning part is transitionally fitted with the inspection through hole, and the inspection part can pass through the shaft hole.

[0011] The aforementioned aileron actuator support inspection device includes a positioning member comprising a positioning plate and a reference plate. The positioning plate has a positioning plane, and the reference plate has a reference plane. The positioning plate is perpendicularly connected to the reference plate.

[0012] The aforementioned aileron actuator support inspection device includes a reinforcing rib between the positioning plate and the reference plate.

[0013] The aforementioned aileron actuator bracket inspection device includes a positioning pin in the positioning component. The positioning plane has a positioning through hole, and the first end face has a reference hole. The positioning pin passes through the positioning through hole and the reference hole to limit the positioning component.

[0014] The aforementioned aileron actuator support inspection device includes a rectangular positioning plate with at least two positioning through holes spaced apart along the diagonal of the positioning plate.

[0015] The aforementioned aileron actuator bracket inspection device includes a locking assembly comprising two magnetic components, one of which is attracted to the positioning plane and the other is attracted to the aileron actuator bracket. The two magnetic components attract each other so that the positioning plane is attached to the first end face.

[0016] The aforementioned aileron actuator bracket inspection device includes a locking assembly comprising a locking bolt and a locking nut, which are screwed together to clamp the aileron actuator bracket and the positioning member, such that the positioning plane is in contact with the first end face.

[0017] The aforementioned aileron actuator bracket inspection device includes a locking assembly that further includes a pressure plate. The locking nut is located on the side of the aileron actuator bracket away from the positioning member, and the pressure plate is located between the locking nut and the aileron actuator bracket.

[0018] The aforementioned aileron actuator support inspection device, wherein the second inspection component is a vernier caliper.

[0019] The beneficial effects of this utility model are:

[0020] This utility model provides an aileron actuator bracket inspection device. During use, a locking assembly locks the positioning component and the aileron actuator bracket, ensuring the positioning plane is flush with the first end face and the inspection through-hole is aligned with the shaft hole of the aileron suspension joint. This prevents movement of the positioning component relative to the aileron actuator bracket, reducing inspection errors. A first inspection piece is inserted through the inspection through-hole. If the first inspection piece can be inserted into the shaft hole of the aileron suspension joint, the relative distance between the first end face and the aileron suspension joint meets the design requirements. If the first inspection piece cannot be inserted into the shaft hole of the aileron suspension joint, the relative distance between the first end face and the aileron suspension joint does not meet the design requirements. A second inspection piece measures the distance between the reference plane and the second end face to inspect the spanwise deviation of the aileron suspension joint. The aileron actuator bracket inspection device provided by this utility model is simple to operate, reduces the time cost of inspecting the relative distance deviation between the aileron actuator bracket and the aileron suspension joint, and the spanwise deviation of the aileron suspension joint, improves aircraft assembly efficiency, and eliminates the need for transfer operations, reducing the workload of workers. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of the positioning component provided in an embodiment of the present utility model;

[0022] Figure 2 This is a schematic diagram of the locking assembly provided in an embodiment of the present invention;

[0023] Figure 3 This is a schematic diagram of the structure of the first inspection piece provided in this embodiment of the utility model;

[0024] Figure 4 This is a first structural schematic diagram of the aileron actuator bracket inspection device, aileron actuator bracket, and aileron suspension joint provided in this embodiment of the utility model;

[0025] Figure 5 This is a second structural schematic diagram of the aileron actuator bracket inspection device, aileron actuator bracket, and aileron suspension joint provided in this embodiment of the utility model.

[0026] In the picture:

[0027] 1. Positioning assembly; 11. Positioning component; 111. Positioning plate; 1111. Positioning plane; 1112. Positioning through hole; 1113. First mounting through hole; 112. Reference plate; 1121. Reference plane; 1122. Inspection through hole; 113. Reinforcing rib; 12. Positioning pin;

[0028] 2. Locking assembly; 21. Locking bolt; 22. Locking nut; 23. Pressure plate;

[0029] 3. First inspection piece; 31. Positioning part; 32. Inspection part; 33. Grip part;

[0030] 100. Aileron actuator support;

[0031] 200. Aileron suspension joint. Detailed Implementation

[0032] The embodiments of this utility model are described in detail below. Examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar parts or parts having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this utility model, and should not be construed as limiting this utility model.

[0033] In the description of this utility model, unless otherwise explicitly specified and limited, the terms "connected," "linked," and "fixed" should be interpreted broadly. For example, they can refer to a fixed connection or a detachable connection; a mechanical connection or an electrical connection; a direct connection or an indirect connection through an intermediate medium; or the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0034] In the description of this utility model, unless otherwise expressly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0035] The technical solution of this utility model will be further described below with reference to the accompanying drawings and specific embodiments.

[0036] The aileron actuator support inspection device provided by this utility model is used to improve aircraft production efficiency and reduce the workload of workers.

[0037] like Figures 1-5As shown, the aileron actuator bracket inspection device includes a positioning assembly 1, a locking assembly 2, and an inspection assembly. The positioning assembly 1 includes a positioning element 11, which has a mutually perpendicular positioning plane 1111 and a reference plane 1121. The reference plane 1121 has an inspection through hole 1122. The locking assembly 2 can lock the positioning element 11 and the aileron actuator bracket 100. The aileron actuator bracket 100 has a first end face. When the positioning element 11 and the aileron actuator bracket 100 are locked, the positioning plane 1111 fits against the first end face, and the inspection through hole 1122 is aligned with the shaft hole of the aileron suspension joint 200. The inspection assembly includes a first inspection element 3 and a second inspection element. The first inspection element 3 can pass through the inspection through hole 1122 to inspect the distance deviation between the first end face and the shaft hole. The second inspection element can measure the distance between the reference plane 1121 and the second end face on the aileron suspension joint 200 to inspect the spanwise deviation of the aileron suspension joint 200.

[0038] This utility model provides an aileron actuator bracket inspection device. In use, the locking assembly 2 locks the positioning member 11 and the aileron actuator bracket 100, ensuring that the positioning plane 1111 is flush with the first end face and the inspection through hole 1122 is aligned with the shaft hole of the aileron suspension joint 200. This prevents the positioning member 11 from moving relative to the aileron actuator bracket 100, reducing inspection errors. A first inspection member 3 is inserted through the inspection through hole 1122. If the first inspection member 3 can be inserted into the shaft hole of the aileron suspension joint 200, the relative distance between the first end face and the aileron suspension joint 200 meets the design requirements. If the first inspection member 3 cannot be inserted into the shaft hole of the aileron suspension joint 200, the relative distance between the first end face and the aileron suspension joint 200 does not meet the design requirements. A second inspection member measures the distance between the reference plane 1121 and the second end face to inspect the spanwise deviation of the aileron suspension joint 200. The aileron actuator bracket inspection device provided by this utility model is simple to operate, reduces the time cost of inspecting the relative distance deviation between the aileron actuator bracket 100 and the aileron suspension joint 200 and the spanwise deviation of the aileron suspension joint 200, improves aircraft assembly efficiency, and eliminates the need for station transfer operations, thus reducing the labor burden on workers.

[0039] The positioning plane 1111 is perpendicular to the reference plane 1121. When the positioning plane 1111 is attached to the first end face, the direction of the reference plane 1121 is the spanwise direction of the aileron suspension joint 200, which is biased to check the spanwise deviation of the aileron suspension joint 200.

[0040] The positioning element 11 can be plate-shaped or block-shaped. In this embodiment, see... Figure 1 and Figure 2The positioning component 11 includes a positioning plate 111 and a reference plate 112. The positioning plate 111 has a positioning plane 1111, and the reference plate 112 has a reference plane 1121. The positioning plate 111 and the reference plate 112 are perpendicularly connected to ensure that the positioning plane 1111 and the reference plane 1121 are perpendicular to each other. The positioning plate 111 and the reference plate 112 have small spatial dimensions, which can reduce the weight.

[0041] The positioning plate 111 and the reference plate 112 can be connected by bolts or by insertion. Optionally, the positioning plate 111 and the reference plate 112 can be connected by bolts, with the positioning plate 111 and the reference plate 112 set perpendicularly and fixed by existing bolts. The bolt connection is convenient and secure.

[0042] In other embodiments, the positioning element 11 can also be cast, and the cast positioning element 11 has a positioning plane 1111 and a reference plane 1121 that are perpendicular to each other.

[0043] To improve the stability of the positioning plate 111 and reference plate 112 after connection, a reinforcing rib 113 is provided between the positioning plate 111 and reference plate 112 in this embodiment. The reinforcing rib 113 has two mutually perpendicular surfaces, one surface abutting against the positioning plate 111 and the other surface abutting against the reference plate 112. The reinforcing rib 113 can be fixed to the positioning plate 111 and reference plate 112 by welding, which is simple to operate. The reinforcing rib 113 can improve the stability of the positioning plate 111 and reference plate 112 after connection and ensure that the positioning plate 111 and reference plate 112 are perpendicular to each other.

[0044] In this embodiment, the positioning component 1 further includes a positioning pin 12. The positioning plane 1111 has a positioning through hole 1112 and the first end face has a reference hole. The positioning pin 12 passes through the positioning through hole 1112 and the reference hole to limit the positioning member 11 and ensure that the reference plane 1121 is parallel to the spanwise direction of the aileron suspension joint 200.

[0045] The number and size of the positioning pins 12 must correspond one-to-one with the number and size of the positioning through holes 1112 to ensure that the positioning pins 12 pass through the positioning through holes 1112 and the reference hole to limit the positioning component 11. The size of the positioning through holes 1112 can be the same or different, and can be designed with reference to the size of the reference hole on the aileron actuator bracket 100.

[0046] One or more positioning holes can be provided. For example, the positioning plate 111 is a rectangular plate, and at least two positioning through holes 1112 are provided and spaced apart along the diagonal of the positioning plate 111 to prevent the positioning plate 111 from rotating around the axis of the positioning pin 12 and improve positioning accuracy. In other embodiments, four positioning through holes 1112 can also be provided, distributed at the four corner points of the positioning plate 111.

[0047] Specifically, attend Figure 1 and Figure 2 Two positioning through holes 1112 of different diameters are formed on the positioning plate 111, distributed along the diagonal of the positioning plate 111. Bushings are placed inside the two positioning through holes 1112 to reduce friction and protect the hole walls. Positioning pins 12 are inserted into the bushings to fix the positioning plate 111 and the aileron actuator bracket 100. The bushings can be existing round bushings or oblong bushings. For example, an oblong bushing is used, and a positioning pin 12 and a pin are provided inside the oblong bushing. Using two pins on one side for positioning can prevent over-positioning, avoid stress concentration, and improve the service life of the positioning component 11.

[0048] The locking assembly 2 is used to lock the positioning component 11 and the aileron actuator bracket 100. Together with the positioning pin 12, it ensures that the reference plane 1121 is parallel to the spanwise direction of the aileron suspension joint 200, facilitating the inspection of the distance deviation between the first end face and the shaft hole, and the spanwise deviation of the aileron suspension joint 200. The locking assembly 2 can be a magnetic structure or a bolt and nut mechanism.

[0049] Optionally, the locking assembly 2 includes two magnetic components, one of which is attracted to the positioning plane 1111, and the other is attracted to the aileron actuator bracket 100. The two magnetic components attract each other, causing the positioning plane 1111 to fit against the first end face. The mutual attraction of the two magnetic components ensures that the aileron actuator bracket 100 and the positioning component 11 are tightly fitted together, facilitating operation.

[0050] Optionally, the locking assembly 2 includes a locking bolt 21 and a locking nut 22, which are screwed together to clamp the aileron actuator bracket 100 and the positioning member 11, so that the positioning plane 1111 fits against the first end face. This connection is convenient and has high connection strength. Specifically, the positioning plate 111 has a first mounting through hole 1113, through which the locking bolt 21 passes and through the first mounting through hole 1113 and the center hole of the aileron actuator bracket 100, and is screwed together with the locking nut 22.

[0051] To prevent the locking nut 22 from damaging the aileron actuator bracket 100, in this embodiment, see [reference needed]. Figure 2 The locking assembly 2 also includes a pressure plate 23. A locking nut 22 is located on the side of the aileron actuator bracket 100 away from the positioning member 11, and the pressure plate 23 is positioned between the locking nut 22 and the aileron actuator bracket 100. The pressure plate 23 increases the contact area with the aileron actuator bracket 100, reduces the force exerted by the locking nut 22 on the aileron actuator bracket 100, and improves the service life of the aileron actuator bracket 100. A second mounting through hole is provided on the pressure plate 23 for inserting a locking bolt 21.

[0052] The inspection assembly is used to inspect the distance deviation between the first end face and the shaft hole, and the spanwise deviation of the aileron suspension joint 200. The first inspection piece 3 may be cylindrical in shape to facilitate insertion into the inspection through hole 1122 and the shaft hole to inspect the distance deviation between the first end face and the shaft hole. For example, see... Figure 3 The first inspection piece 3 is an inspection pin, which has a positioning part 31 and an inspection part 32. The positioning part 31 is transitionally fitted with the inspection through hole 1122, and the inspection part 32 can be inserted into the shaft hole.

[0053] The shaft diameter of the positioning part 31 is the same as the shaft diameter of the inspection through hole 1122, and the shaft diameter of the inspection part 32 is smaller than the shaft diameter of the positioning part 31. Specifically, multiple first inspection pieces 3 can be manufactured, for example, three first inspection pieces 3 can be processed, and the shaft diameter of the inspection part 32 of the three first inspection pieces 3 is 0.4 mm, 0.5 mm and 0.6 mm smaller than the shaft diameter of the positioning part 31, respectively.

[0054] In use, to facilitate gripping the first inspection piece 3, the first inspection piece 3 also includes a gripping part 33 for easy insertion and removal. The positioning part 31 is inserted into the inspection through hole 1122 to improve positioning accuracy, and the inspection part 32 is inserted into the shaft hole. First, insert the first inspection piece 3 with a shaft diameter of medium into the positioning part 31. If it cannot be inserted, replace it with a first inspection piece 3 with a smaller shaft diameter. For example, first insert the first inspection piece 3 with a diameter 0.5mm smaller. If it can be inserted, it means that the distance deviation between the first end face and the shaft hole is less than 0.25mm. If it cannot be inserted, it means that the distance deviation between the first end face and the shaft hole is greater than 0.25mm. In this case, the first inspection piece 3 with a diameter 0.4mm smaller can be used to perform the inspection again.

[0055] The second inspection piece is used to inspect the spanwise deviation of the aileron suspension joint 200. The second inspection piece is a vernier caliper, which is convenient for measuring the gap distance. The distance between the reference plane 1121 and the end face of the aileron suspension joint 200 is measured multiple times using the second inspection piece, and the average value of multiple sets of distances is the spanwise deviation of the aileron suspension joint 200.

[0056] In other embodiments, the second inspection piece 3 may also be a laser rangefinder or a feeler gauge.

[0057] The aileron actuator support inspection device provided by this utility model, when in use, refers to... Figure 4 and Figure 5The positioning component 11 is installed on the aileron actuator bracket 100 and positioned by the positioning pin 12. The positioning component 11 and the aileron actuator bracket 100 are locked by the locking assembly 2 to prevent the positioning component 11 from rotating relative to the aileron actuator bracket 100, ensuring that the reference plane 1121 and the spanwise direction of the aileron suspension joint 200 are parallel. The first inspection component 3 is inserted into the inspection through hole 1122 and the shaft hole to inspect the distance deviation between the first end face on the aileron actuator bracket 100 and the shaft hole on the aileron suspension joint 200. The distance between the reference plane 1121 and the end face of the shaft hole on the aileron suspension joint 200 is measured using the second inspection component to inspect the spanwise deviation of the aileron suspension joint 200.

[0058] 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 other variations or modifications based on the above description. It is neither necessary nor possible to exhaustively list all possible implementations 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 device for inspecting aileron actuator brackets, characterized in that, include: The positioning component (1) includes a positioning element (11), which has a positioning plane (1111) and a reference plane (1121) that are perpendicular to each other, and the reference plane (1121) is provided with an inspection through hole (1122). Locking assembly (2), the locking assembly (2) is capable of locking the positioning member (11) and the aileron actuator bracket (100), the aileron actuator bracket (100) has a first end face, when the positioning member (11) is locked with the aileron actuator bracket (100), the positioning plane (1111) is in contact with the first end face and the inspection through hole (1122) is aligned with the shaft hole of the aileron suspension joint (200); The inspection component includes a first inspection piece (3) and a second inspection piece. The first inspection piece (3) can be inserted through the inspection through hole (1122) to inspect the distance deviation between the first end face and the shaft hole. The second inspection piece can measure the distance between the reference plane (1121) and the second end face on the aileron suspension joint (200) to inspect the spanwise deviation of the aileron suspension joint (200).

2. The aileron actuator support inspection device according to claim 1, characterized in that, The first inspection piece (3) is an inspection pin, which has a positioning part (31) and an inspection part (32). The positioning part (31) is transitionally fitted with the inspection through hole (1122), and the inspection part (32) can pass through the shaft hole.

3. The aileron actuator support inspection device according to claim 1, characterized in that, The positioning component (11) includes a positioning plate (111) and a reference plate (112). The positioning plate (111) has the positioning plane (1111), and the reference plate (112) has the reference plane (1121). The positioning plate (111) and the reference plate (112) are perpendicularly connected.

4. The aileron actuator support inspection device according to claim 3, characterized in that, A reinforcing rib (113) is provided between the positioning plate (111) and the reference plate (112).

5. The aileron actuator support inspection device according to claim 3, characterized in that, The positioning component (1) further includes a positioning pin (12), the positioning plane (1111) is provided with a positioning through hole (1112), the first end face is provided with a reference hole, and the positioning pin (12) passes through the positioning through hole (1112) and the reference hole to limit the positioning component (11).

6. The aileron actuator support inspection device according to claim 5, characterized in that, The positioning plate (111) is a rectangular plate, and at least two positioning through holes (1112) are provided and are distributed at intervals along the diagonal of the positioning plate (111).

7. The aileron actuator support inspection device according to claim 1, characterized in that, The locking assembly (2) includes two magnetic components, one of which is attracted to the positioning plane (1111) and the other is attracted to the aileron actuator bracket (100). The two magnetic components attract each other so that the positioning plane (1111) is attached to the first end face.

8. The aileron actuator support inspection device according to claim 1, characterized in that, The locking assembly (2) includes a locking bolt (21) and a locking nut (22), which are screwed together to clamp the aileron actuator bracket (100) and the positioning member (11), such that the positioning plane (1111) fits against the first end face.

9. The aileron actuator support inspection device according to claim 8, characterized in that, The locking assembly (2) further includes a pressure plate (23), the locking nut (22) is disposed on the side of the aileron actuator bracket (100) away from the positioning member (11), and the pressure plate (23) is disposed between the locking nut (22) and the aileron actuator bracket (100).

10. The aileron actuator support inspection device according to any one of claims 1-9, characterized in that, The second inspection item is a vernier caliper.

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