A device for controlling the step chamfer of an aircraft external accessory and method of use

Abstract

The present application relates to the technical field of aircraft assembly, in particular to a device for controlling the step chamfer of an aircraft external accessory and a use method. The device for controlling the step chamfer of an aircraft external accessory comprises a first ring, a shell and a base. The first ring is used for sleeving a sander. The top surface of the base is provided with a toothed rack and a sliding surface which are inclined and parallel to each other. The bottom surface of the shell is slidingly connected to the sliding surface. The shell is provided with a through hole. The first ring is rotationally connected to the through hole. The outer wall of the first ring is provided with a gear which corresponds to the toothed rack. The first ring can rotate to drive the shell to slide along the sliding surface so that the sander approaches the aircraft external accessory to be polished. The shell is further provided with a scale and a brake. The scale is used for identifying the rotation angle of the first ring relative to the shell. The brake is used for limiting the sliding distance of the shell and the base. By using the device, the chamfer is formed, and the chamfer width is ensured to be within a specified range, thereby meeting the high-precision and high-efficiency requirements of aircraft assembly.

Description

Technical Field

[0001] This invention relates to the field of aircraft assembly technology, and in particular to a device and method for controlling the chamfering of external aircraft accessories. Background Technology

[0002] Aircraft external components generally refer to the aircraft skin or covers. During aircraft assembly, it is necessary to ensure that there are no or minimal step differences between external components, that is, to avoid height differences caused by the accumulation of assembly and manufacturing errors, which would affect the aircraft's aerodynamic and stealth performance. However, in actual assembly, due to assembly errors, tooling errors, and worker operation, assembly step differences of external components are unavoidable. Therefore, it is necessary to grind off these step differences. The current method is to install the external component on the aircraft, measure the step difference, and then have a worker use a hand-held grinder to grind it to the appropriate chamfer width. The chamfer width needs to be calculated based on the step difference height using a corresponding conversion ratio, and different aircraft have different conversion ratios. The chamfer width equals the step difference height multiplied by a corresponding coefficient. Furthermore, it is difficult to control the chamfer width within the specified range when manually grinding with a hand-held grinder. Summary of the Invention

[0003] The purpose of this invention is to overcome the problem in the prior art that it is difficult to control the chamfer width within the specified range when manually hand-held grinders, and to provide a device and method for controlling the chamfer of aircraft external accessories.

[0004] To achieve the above-mentioned objectives, the present invention provides the following technical solution:

[0005] A device for controlling the chamfering of aircraft external accessories includes a first ring sleeve, a housing, a base, and a braking component. The first ring sleeve is fitted onto the neck of a grinder. The top surface of the base has an inclined rack and an inclined sliding surface, which are parallel to each other. The bottom surface of the housing is slidably connected to the sliding surface. The housing has a through hole, and the first ring sleeve is rotatably connected to the through hole. The outer wall of the first ring sleeve has a gear that can mesh with the rack. The first ring sleeve can rotate to drive the housing to slide along the sliding surface, thereby moving the grinder away from or closer to the aircraft external accessory. The sliding of the housing along the sliding surface can drive the first ring sleeve to rotate and bring the grinder closer to the aircraft external accessory. The housing is also provided with a scale and a braking component. The scale is used to indicate the rotation angle of the first ring sleeve relative to the housing, and the braking component is used to limit the sliding distance between the housing and the base or the rotation angle of the first ring sleeve.

[0006] The first ring is circular and fits onto the neck of the grinder. Before grinding the step difference of the aircraft external accessory, the first ring must be positioned appropriately on the rack, with the gear on the first ring meshing with the rack. After attaching the first ring to the top of the grinder and installing the device, the first ring moves along the rack towards the aircraft external accessory due to gravity. The first ring drives the grinder to move, causing it to grind the aircraft external accessory until the braking element contacts and brakes the first ring, thus completing the chamfering of the aircraft external accessory step difference.

[0007] The gear on the first ring and the rack on the base allow the first ring to move along the rack during rotation. A through-hole in the outer shell allows the grinder to pass through the device. The meshing of the gear and rack not only prevents slippage between the grinder and the assembly step to be processed, but also ensures that the grinder's setting point is at the same height as the processing point on the aircraft external accessory during the pressing process. This guarantees that the gear's displacement on the rack corresponds to the chamfer of the assembly step, thus ensuring the accuracy and efficiency of the chamfering process. The sliding surface setting angle allows the first ring to move downwards along the sliding surface due to gravity, minimizing effort. The scale indicates the rotation angle of the first ring relative to the outer shell, indicating the magnitude of the first ring's displacement along the rack, thereby determining the width of the aircraft external accessory chamfer.

[0008] By using this device to control the chamfering of aircraft external accessories, a grinder is driven to grind the steps of the aircraft external accessories, forming a chamfered edge and ensuring that the chamfer width is within the specified range. Furthermore, it does not rely excessively on the skill level and experience of the grinding personnel, improving work efficiency and reducing errors that may be caused by judgment or operational mistakes by the grinding personnel, thus ensuring the high precision and efficiency requirements of the aircraft assembly process.

[0009] Preferably, the outer shell has a strip-shaped hole, the extension direction of the strip-shaped hole is parallel to the movement direction of the first ring, and the scale includes positioning holes, with a plurality of positioning holes arranged along the strip-shaped hole.

[0010] By using a strip-shaped hole on the outer shell parallel to the direction of movement of the first ring sleeve, the gear transmission of the first ring sleeve can be observed, thereby determining the magnitude of the displacement of the first ring sleeve on the rack, and thus determining the width of the step chamfer of the aircraft's external accessories. Furthermore, several positioning holes are arranged along the strip-shaped hole; positioning holes at different positions represent different step conversion ratios, thereby controlling the width of the step chamfer.

[0011] Preferably, the outer casing also includes a fixing device for securing the first ring.

[0012] By fixing the first ring sleeve with a fixing device, it can be ensured that the gear transmission process of the first ring sleeve is located inside the outer shell as much as possible, and that each chamfer formed by each gear transmission process is completely constructed, which is conducive to meeting the high precision and high efficiency requirements of the aircraft assembly process.

[0013] Preferably, the outer casing is provided with hinges, which are used to adjust the opening and closing of the fixing device.

[0014] Hinges are used to adjust the opening and closing of the fixing device, facilitating the installation of this device.

[0015] Preferably, it also includes a second ring sleeve, the first ring sleeve is provided with a guide rod located in the strip hole, the second ring sleeve is provided with a limiting member corresponding to the positioning hole, the second ring sleeve has a thread inside, and the guide rod has a thread on the outside corresponding to the thread inside the second ring sleeve.

[0016] The shape of the limiting component is determined by the shape of the positioning hole. A guide rod is provided on the first ring sleeve, and the guide rod is located inside the strip-shaped hole. The guide rod is used to move the first ring sleeve, facilitating machining. Because the internal thread of the second ring sleeve corresponds to the external thread of the guide rod, the vertical position of the second ring sleeve can be adjusted and it is easy to fix. Before the chamfering of the aircraft external accessories, the guide rod is placed in the corresponding position, and the second ring sleeve is rotated to the predetermined position so that the limiting component connects with the positioning hole, fixing the initial position of the guide rod. This ensures that the guide rod remains in its corresponding position before machining, preventing any adverse effects on the subsequent chamfering process and facilitating the meeting of the high-precision requirements of the aircraft assembly process.

[0017] Preferably, the location of the positioning hole on the outer shell is an arc, and the center of the arc is the same as the center of the first ring.

[0018] The concentric circles ensure that the limiting parts and positioning holes on the second ring can make accurate contact.

[0019] Preferably, it also includes a hydraulic mechanism that ensures the limiting member is located within the positioning hole.

[0020] Because of the threads, the limiting part and the positioning hole may not correspond. In this case, the hydraulic mechanism can apply a load to make them correspond and ensure fixation to guarantee accuracy.

[0021] Preferably, the base has a protrusion on its top for mounting the rack.

[0022] The protrusion raises the position of the rack, preventing the grinder from being obstructed and ensuring the accuracy of the work.

[0023] Preferably, the braking element is a limiting block and is located at the top of the rack.

[0024] The limit block is located at the top of the rack, which facilitates braking, avoids over-machining, and ensures machining accuracy.

[0025] A method for machining step chamfers on aircraft external accessories, employing the aforementioned device for controlling step chamfers on aircraft external accessories, includes the following steps:

[0026] S1. Measure the step difference of aircraft external accessories;

[0027] S2. Fix the guide rod to the corresponding position: Rotate the guide rod to the corresponding position, adjust the second ring to the corresponding height and fix it; place the limiting member in the positioning hole;

[0028] S3. Processing the step chamfer of aircraft external accessories: Install the first ring on the neck of the grinder, install the device for controlling the step chamfer of aircraft external accessories, place the part of the aircraft external accessory to be ground at the corresponding scale, release the first ring, and the brake will engage, thus completing the processing of the step chamfer of the aircraft external accessory.

[0029] The braking mechanism indicates that the grinding process is complete. The braking mechanism prevents over-machining and ensures the accuracy of the chamfering process.

[0030] By using the chamfering process for aircraft external accessories, the step difference of the aircraft external accessories is compressed to form a chamfer, ensuring that the chamfer width is within the specified range. This method does not overly rely on the skill level and experience of the grinding personnel, improving work efficiency and reducing errors that may be caused by misjudgments by the grinding personnel, thus ensuring the high precision and efficiency requirements of the aircraft assembly process.

[0031] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0032] By using this device to control the chamfering of aircraft external accessories, a grinder is driven to grind the steps of the aircraft external accessories, forming a chamfered edge and ensuring that the chamfer width is within the specified range. Furthermore, it does not rely excessively on the skill level and experience of the grinding personnel, improving work efficiency and reducing errors that may be caused by judgment or operational mistakes by the grinding personnel, thus ensuring the high precision and efficiency requirements of the aircraft assembly process. Attached Figure Description

[0033] Figure 1 This is a cross-sectional view of a device for controlling the chamfering of aircraft external accessories in Embodiment 1;

[0034] Figure 2 This is a side view of a device for controlling the chamfering of aircraft external accessories in Embodiment 1;

[0035] Figure 3This is a three-dimensional view of a device for controlling the chamfering of aircraft external accessories in Example 1;

[0036] Figure 4 This is a schematic diagram of the operation of a device for controlling the chamfering of aircraft external accessories in Example 1;

[0037] Figure 5 This is a flowchart of a processing method for step chamfering of an aircraft external accessory in Example 2.

[0038] The markings in the diagram are: 1-first ring sleeve, 11-gear, 12-guide rod, 13-brake component, 2-locking device, 3-outer shell, 31-positioning hole, 32-strip hole, 33-hinge, 4-second ring sleeve, 41-limiting component, 5-base, 51-rack, 52-sliding surface, 53-aircraft external accessory, 54-grinder. Detailed Implementation

[0039] The present invention will be further described in detail below with reference to experimental examples and specific embodiments. However, this should not be construed as limiting the scope of the above-mentioned subject matter of the present invention to the following embodiments; all technologies implemented based on the content of the present invention fall within the scope of the present invention. Example 1:

[0040] like Figure 1-3As shown, a device for controlling the chamfering of aircraft external accessories includes a first ring sleeve 1, a housing 3, a base 5, and a brake element 13. The first ring sleeve 1 is fitted onto the neck of a grinder 54. The top surface of the base 5 has an inclined rack 51 and an inclined sliding surface 52, which are parallel to each other. The bottom surface of the housing 3 is slidably connected to the sliding surface 52. The housing 3 has a through hole, and the first ring sleeve 1 is rotatably connected to the through hole. The outer wall of the first ring sleeve 1 has a gear 11, which is connected to the rack 51. The first ring sleeve 1 can be engaged, allowing the outer casing 3 to rotate and slide along the sliding surface 52, thereby moving the grinder 54 away from or closer to the aircraft external accessory 53. The sliding of the outer casing 3 along the sliding surface 52 causes the first ring sleeve 1 to rotate and brings the grinder 54 closer to the aircraft external accessory 53 for grinding. The outer casing 3 is also equipped with a scale and a braking element 13. The scale is used to indicate the rotation angle of the first ring sleeve 1 relative to the outer casing 3, and the braking element 13 is used to limit the sliding distance between the outer casing 3 and the base 5 or the rotation angle of the first ring sleeve 1. The outer casing 3 has a strip-shaped hole 32, the extension direction of which is parallel to the movement direction of the first ring sleeve 1. The scale includes positioning holes 31, with several positioning holes 31 arranged along the strip-shaped hole 32. The number and shape of the positioning holes 31 are determined according to specific circumstances. In this embodiment, each scale uses one circular positioning hole 31 on each side of the strip-shaped hole 32. The positioning holes 31 are located on the outer casing 3 in an arc shape, with the center of the arc being the same as the center of the first ring sleeve 1. The outer casing 3 also includes a locking device 2, which is used to restrict the first ring 1 from being located inside the outer casing 3. The braking element 13 is a limiting block and is located on top of the rack 51. The locking device 2 uses an outer clamp. The outer casing 3 is provided with a hinge 33, which is used to adjust the opening and closing of the locking device 2, such as... Figure 3 As shown.

[0041] It also includes a second ring sleeve 4. The first ring sleeve 1 is provided with a guide rod 12, which is located inside the strip hole 32. The second ring sleeve 4 is provided with a limiting member 41 corresponding to the positioning hole 31. The second ring sleeve 4 has internal threads, and the guide rod 12 has external threads corresponding to the internal threads of the second ring sleeve 4.

[0042] The base 5 has a protrusion on its top, which is used to mount the rack 51.

[0043] It also includes a hydraulic mechanism that ensures that the limiting member 41 is located within the positioning hole 31.

[0044] During sanding, the specific construction process is as follows: Figure 4 The part of the aircraft's external accessory 53 that needs to be polished is the part on the right in the picture. Example 2:

[0045] like Figure 5As shown, a method for processing step chamfers on aircraft external accessories, using a device for controlling step chamfers on aircraft external accessories as described in Example 1, includes the following steps:

[0046] S1. Measure the step difference of aircraft external accessory 53;

[0047] S2. Fixing the guide rod 12: Rotate the guide rod 12 to the corresponding position, adjust the second ring 4 to the corresponding height and fix it; place the limiting member 41 in the positioning hole 31;

[0048] S3. Processing the step chamfer of aircraft external accessory 53: Install the first ring 1 onto the neck of the grinder 54, install the device controlling the step chamfer of aircraft external accessory 53, place the part of aircraft external accessory 53 to be ground at the corresponding scale, release the first ring 1, and the brake 13 engages, thus completing the processing of the step chamfer of aircraft external accessory 53. Figure 4 As shown, the part that needs to be polished is the aircraft external accessory 53 on the right side of the picture.

[0049] When fixing the guide rod 12, the limiting member 41 is placed inside the positioning hole 31. Releasing the first ring sleeve 1 requires placing the limiting member 41 outside the positioning hole 31.

[0050] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A device for controlling the chamfering of external aircraft accessories, characterized in that, The device comprises a first ring sleeve (1), a housing (3), a base (5), and a brake (13). The first ring sleeve (1) is fitted onto the neck of a grinder (54). The top surface of the base (5) has an inclined rack (51) and an inclined sliding surface (52), which are parallel to each other. The bottom surface of the housing (3) is slidably connected to the sliding surface (52). The housing (3) has a through hole, and the first ring sleeve (1) is rotatably connected to the through hole. The outer wall of the first ring sleeve (1) has a gear (11), which meshes with the rack (51). The shell (3) can be rotated to slide along the sliding surface (52), thereby moving the polisher (54) away from or closer to the aircraft external accessory (53). The sliding of the shell (3) along the sliding surface (52) can drive the first ring (1) to rotate and make the polisher (54) closer to polish the aircraft external accessory (53). The shell (3) is also provided with a scale and the brake (13). The scale is used to mark the rotation angle of the first ring (1) relative to the shell (3). The brake (13) is used to limit the sliding distance between the shell (3) and the base (5) or the rotation angle of the first ring (1).

2. The device for controlling the chamfering of aircraft external accessories as described in claim 1, characterized in that, The outer shell (3) has a strip hole (32), the extension direction of the strip hole (32) is parallel to the movement direction of the first ring (1), the scale includes a positioning hole (31), and a plurality of the positioning holes (31) are arranged along the strip hole (32).

3. The device for controlling the chamfering of aircraft external accessories as described in claim 2, characterized in that, The outer casing (3) also includes a locking device (2) for fixing the first ring sleeve (1).

4. The device for controlling the chamfering of aircraft external accessories as described in claim 3, characterized in that, The outer casing (3) is provided with a hinge (33), which is used to adjust the opening and closing of the locking device (2).

5. The device for controlling the chamfering of aircraft external accessories as described in claim 2, characterized in that, It also includes a second ring sleeve (4), the first ring sleeve (1) is provided with a guide rod (12), the guide rod (12) is located inside the strip hole (32), the second ring sleeve (4) is provided with a limiting member (41) corresponding to the positioning hole (31), the second ring sleeve (4) has a thread inside, and the guide rod (12) has a thread outside that corresponds to the thread inside the second ring sleeve (4).

6. The device for controlling the chamfering of aircraft external accessories as described in claim 5, characterized in that, The location of the positioning hole (31) on the outer shell (3) is an arc, and the center of the arc is the same as the center of the first ring (1).

7. The device for controlling the chamfering of aircraft external accessories as described in claim 6, characterized in that, It also includes a hydraulic mechanism that ensures that the limiting member (41) is located within the positioning hole (31).

8. The device for controlling the chamfering of aircraft external accessories as described in claim 1, characterized in that, The base (5) has a protrusion on its top, which is used to mount the rack (51).

9. The device for controlling the chamfering of aircraft external accessories as described in claim 1, characterized in that, The braking element (13) is a limiting block and is located on top of the rack (51).

10. A method for machining step chamfers on aircraft external accessories, employing a device for controlling step chamfers on aircraft external accessories as described in any one of claims 5-7, characterized in that, It includes the following steps: S1. Measure the step difference of the aircraft's external accessories (53); S2. Fix the guide rod (12) to the corresponding position: rotate the guide rod (12) to the corresponding position, adjust the second ring (4) to the corresponding height and fix it; place the limiting member (41) in the positioning hole (31); S3. Processing the step chamfer of the aircraft external accessory (53): Install the first ring (1) of the step chamfering device on the neck of the grinder (54), install the device for controlling the step chamfer of the aircraft external accessory (53), place the part of the aircraft external accessory (53) to be ground on the corresponding scale, release the first ring (1), and brake (13) brakes, thus completing the processing of the step chamfer of the aircraft external accessory (53).

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