Aircraft skin drilling and sliding pit guiding tool

Abstract

The utility model provides an aircraft skin drilling and sliding pit guiding tool which comprises two guiding blocks arranged in the first direction. Each guide block is provided with a first end and a second end which are opposite in the second direction, and the first ends of the two guide blocks are rotationally connected; the guide block is provided with a first through hole penetrating in the second direction, and the axis of the first through hole passes through the middle position of the end face of the second end in the first direction. The first through hole is provided with a first hole part and a second hole part which are respectively opened on the end surfaces of the first end and the second end; the two first pins are detachably arranged in the second hole parts of the two guide blocks respectively, and second through holes penetrating in the second direction are formed in the first pins; when the first pin is arranged in the second hole part, the second through hole and the first hole part form a confirmation hole channel, a pin rod of the first pin is located in the second hole part, and a pin cap is located outside the second end. The second pin is detachably arranged in the confirmation hole channel; the locking bolt assembly comprises a bolt and a locking nut which are inserted into the first through hole or the confirmation hole channel.

Description

Technical Field

[0001] This disclosure relates to the field of aircraft manufacturing equipment technology, and in particular to an aircraft skin drilling and rudder guidance tooling. Background Technology

[0002] During aircraft manufacturing, two holes need to be drilled at designated locations on the aircraft skin according to maintenance and modification requirements. After drilling, the holes also need to be grouted. Aircraft skin is a regular arc surface, and both drilling and grooving require alignment with the arc surface normal at the designated location. However, the existing drilling process for aircraft skin makes it difficult to meet the alignment requirements of the drilling and grooving processes, and it is impossible to guarantee the smoothness and regularity of the hole's outline. Summary of the Invention

[0003] A primary objective of this disclosure is to overcome at least one of the deficiencies of the prior art described above, and to provide a drilling and dredging guide tooling for aircraft skin that can ensure alignment of the arc surface normal at a specified position during drilling and dredging processes.

[0004] To achieve the above objectives, the present disclosure adopts the following technical solution:

[0005] According to one aspect of this disclosure, an aircraft skin drilling and sliding guide fixture is provided, comprising two guide blocks, two first pins, a second pin, and two sets of locking bolt assemblies; the two guide blocks are arranged along a first direction; each guide block has a first end and a second end opposite to each other in a second direction perpendicular to the first direction, the first ends of the two guide blocks are rotatably connected, and the axis of rotation extends along a third direction perpendicular to both the first and second directions; each guide block is provided with a first through hole extending along the second direction, the axis of the first through hole passing through the end face of the second end at a midpoint in the first direction; the first through hole has a first hole portion and a second hole portion connected together, one end of the first hole portion opening onto the end face of the first end, and one end of the second hole portion opening onto the... The end face of the second end has a second hole diameter larger than the first hole diameter; two first pins are detachably disposed in the second holes of the two guide blocks, each first pin having a second through hole extending along the second direction, the diameter of the second through hole being equal to the diameter of the first hole; when the first pin is disposed in the second hole, the second through hole is coaxial with the first hole and together forms a confirmation channel, the pin shank of the first pin is located in the second hole, and its pin cap is located outside the second end; the second pin is detachably disposed in the confirmation channel; the locking bolt assembly includes a bolt and a locking nut, the bolt being used to be inserted into the first through hole or the confirmation channel from one side of the second end, and the locking nut being located on one side of the first end and threadedly engaged with the bolt.

[0006] According to one embodiment of this disclosure, the end face of the second end is rectangular, and the axis of the first through hole passes through the geometric center of the end face of the second end.

[0007] According to one embodiment of this disclosure, the first end is provided with a pivot portion, and the two guide blocks are rotatably connected via the two pivot portions; wherein, the guide fixture further includes an adjusting bolt passing through the two pivot portions for locking or unlocking the two guide blocks.

[0008] According to one embodiment of this disclosure, one end of the adjusting bolt is provided with an operating handwheel.

[0009] According to one embodiment of this disclosure, when the second pin is disposed in the confirmation channel, the pin rod of the second pin passes through the second through hole and the first hole respectively, and the pin cap of the second pin is located on the side of the pin cap of the first pin away from the pin rod, or the pin cap of the second pin is located outside the first end.

[0010] According to one embodiment of this disclosure, an annular clearance groove is provided on the wall of the second hole at the end away from the first hole.

[0011] According to one embodiment of this disclosure, the outer diameter of the pin shank of the first pin is larger than the diameter of the second hole, so that the first pin is tightly fitted when it is disposed in the second hole.

[0012] According to one embodiment of this disclosure, the outer diameter of the pin of the second pin is larger than the diameter of the second through hole, so that the second pin is tightly fitted when it is disposed in the second through hole.

[0013] According to one embodiment of this disclosure, the bolts of the locking bolt assembly are provided with push-pull rings.

[0014] According to one embodiment of this disclosure, the bore diameter of the aircraft skin is 1 inch, and the outer diameter of the bolt of the locking bolt assembly is 0.25 inches.

[0015] As can be seen from the above technical solution, the advantages and positive effects of the aircraft skin drilling and rudder guidance tooling proposed in this disclosure are as follows:

[0016] The aircraft skin drilling and sliding guide fixture disclosed herein includes two guide blocks, two first pins, a second pin, and two sets of locking bolt assemblies: the two guide blocks are arranged along a first direction; the guide blocks have first and second ends opposite in a second direction, and the first ends of the two guide blocks are rotatably connected; the guide blocks are provided with a first through hole extending along the second direction, the axis of the first through hole passing through the middle position of the end face of the second end in the first direction; the first through hole has a first and a second hole portion opening onto the end faces of the first and second ends respectively, the diameter of the second hole portion being larger than that of the first hole portion; the two first pins are detachably disposed in the second hole portions of the two guide blocks respectively, and the first pins are provided with a second through hole extending along the second direction; when the first pin is disposed in the second hole portion, the second through hole and the first hole portion form a confirmation channel, the pin shank of the first pin is located in the second hole portion, and its pin cap is located outside the second end; the second pin is detachably disposed in the confirmation channel; each set of locking bolt assemblies includes a bolt inserted into the first through hole or the confirmation channel and a locking nut. Through the above structural design, since the axis of the first through hole passes through the middle position of the second end face in the first direction, this disclosure can ensure that the axis of the first through hole and the confirmed channel coincides with the normal of the skin drilling position based on the principle of "drawing the normal line from the perpendicular bisector of the chord length of the arc". Therefore, during drilling, sliding, and other processes using this guide fixture, it can ensure that the axes of the first pin, the second pin, and the locking bolt assembly coincide with the normal of the skin drilling position, and simultaneously ensure that the process axes of other fixtures such as drilling fixtures and sliding fixtures that cooperate with this guide fixture coincide with the normal of the skin drilling position. Accordingly, using the guide fixture proposed in this disclosure in the drilling and sliding processes of aircraft skin can meet the normal alignment requirements in the relevant processes, ensuring the smoothness and regularity of the machined hole's outline. Attached Figure Description

[0017] The various objectives, features, and advantages of this disclosure will become more apparent from the following detailed description of preferred embodiments of the disclosure taken in conjunction with the accompanying drawings. The drawings are merely illustrative illustrations of the disclosure and are not necessarily drawn to scale. In the drawings, the same reference numerals always denote the same or similar parts. Wherein:

[0018] Figure 1 This is a three-dimensional structural schematic diagram of an aircraft skin drilling and swivel guide tool according to an exemplary embodiment.

[0019] Figure 2 yes Figure 1 A schematic diagram of the three-dimensional structure from another perspective;

[0020] Figure 3 yes Figure 1 The front view;

[0021] Figure 4 yes Figure 1 Top view;

[0022] Figure 5 It is along Figure 4 A sectional view of line AA in the diagram;

[0023] Figure 6 yes Figure 1 An exploded three-dimensional schematic diagram of a portion of the structure of the aircraft skin drilling and swivel guide tooling.

[0024] Figure 7 and Figure 8 They are Figure 1 The diagram shows a three-dimensional structural schematic of the aircraft skin drilling and swivel guidance tooling from two different perspectives in an application scenario.

[0025] Figures 9 to 17 They are Figure 1 The diagram shows a cross-sectional view of the aircraft skin drilling and rudder guidance tooling in multiple process steps of an application scenario.

[0026] The annotations in the attached figures are explained as follows:

[0027] 100. Guiding fixture; 130. Second pin;

[0028] 110. Guide block; 141. Bolt;

[0029] 111. First end; 1411. Push-pull ring;

[0030] 1111. Pivot joint; 142. Locking nut;

[0031] 112. Second end; 150. Adjusting bolt;

[0032] 113. First through hole; 151. Operating handwheel;

[0033] 1131. First hole; 200. Skin;

[0034] 1132. Second hole section; 210. Process transition hole;

[0035] 1133. Annular clearance groove; 220. Machined hole;

[0036] 114. Confirm the borehole; 300. Second drilling fixture;

[0037] 120. First pin; 400. Slipper tooling;

[0038] 121. Second through hole; L. Rotation axis. Detailed Implementation

[0039] Typical embodiments embodying the features and advantages of this disclosure will be described in detail in the following description. It should be understood that this disclosure can have various variations in different embodiments without departing from the scope of this disclosure, and the descriptions and drawings therein are illustrative in nature and not intended to limit this disclosure.

[0040] In the following description of various exemplary embodiments of this disclosure, reference is made to the accompanying drawings, which form part of this disclosure, and which illustrate by way of example different exemplary structures, systems, and steps that can implement various aspects of this disclosure. It should be understood that other specific embodiments of the components, structures, exemplary devices, systems, and steps may be used, and structural and functional modifications may be made without departing from the scope of this disclosure. Furthermore, while the terms “above,” “between,” “within,” etc., may be used in this specification to describe different exemplary features and elements of this disclosure, these terms are used herein only for convenience, such as the orientation according to the examples described in the accompanying drawings. Nothing in this specification should be construed as requiring a specific three-dimensional orientation of the structure to fall within the scope of this disclosure.

[0041] See Figure 1 This illustration represents a three-dimensional structural diagram of the aircraft skin drilling and rutting guidance fixture (hereinafter referred to as guidance fixture 100) proposed in this disclosure. In this exemplary embodiment, the guidance fixture 100 proposed in this disclosure is described using the hydrostatic drilling and rutting process applied to the aircraft skin 200 as an example. It will be readily understood by those skilled in the art that various modifications, additions, substitutions, deletions, or other changes may be made to the following specific embodiments in order to apply the relevant designs of this disclosure to other types of drilling and rutting, and these changes are still within the scope of the principles of the guidance fixture 100 proposed in this disclosure.

[0042] like Figure 1 As shown, in one embodiment of this disclosure, the guiding fixture 100 includes two guiding blocks 110, two first pins 120, a second pin 130, and two sets of locking bolt assemblies. The accompanying drawings only illustrate the device structure of the guiding fixture 100 in a specific process step within a particular application scenario, and do not limit the device structure of the guiding fixture 100 in other process steps, such as the assembly relationship of components. See also... Figures 2 to 6 , Figure 2 China representatively shows Figure 1 A schematic diagram of the three-dimensional structure from another perspective; Figure 3 China representatively shows Figure 1 The front view; Figure 4 China representatively shows Figure 1 Top view; Figure 5 The middle section represents the direction along Figure 4A sectional view of line AA in the diagram; Figure 6 The figure shows a representative exploded perspective view of part of the structure of the guide fixture 100, specifically showing the exploded structure of the two guide blocks 110 and the adjusting bolt 150. The structure, connection method, and functional relationship of the main components of the guide fixture 100 proposed in this disclosure will be described in detail below with reference to the above-mentioned figures.

[0043] like Figures 1 to 5 As shown, in one embodiment of this disclosure, two guide blocks 110 are arranged along a first direction, which can be referred to as direction D1 shown in the figures. Each guide block 110 has a first end 111 and a second end 112 opposite to each other in a second direction, which can also be referred to as direction D2 shown in the figures, and is perpendicular to the first direction. The first ends 111 of the two guide blocks 110 are rotatably connected, and the rotation axis L of the rotatably connected joint extends along a third direction, which can be referred to as direction D3 shown in the figures, and is perpendicular to both the first and second directions. Each guide block 110 is provided with a first through hole 113 extending along the second direction, the axis of which passes through the end face of the second end 112 at a midpoint in the first direction. The first through hole 113 has a first hole portion 1131 and a second hole portion 1132 connected to each other. One end of the first hole portion 1131 opens onto the end face of the first end 111, and one end of the second hole portion 1132 opens onto the end face of the second end 112. The diameter of the second hole portion 1132 is larger than the diameter of the first hole portion 1131. Two first pins 120 are detachably disposed in the second hole portions 1132 of the two guide blocks 110. Each first pin 120 has a second through hole 121 extending along a second direction. The diameter of the second through hole 121 is equal to the diameter of the first hole portion 1131. Accordingly, when the first pin 120 is disposed in the second hole portion 1132, the second through hole 121 and the first hole portion 1131 are coaxial and together form a confirmation channel 114. Furthermore, the pin shank of the first pin 120 is located in the second hole portion 1132, and its pin cap is located outside the second end 112. The second pin 130 is detachably disposed in the confirmation channel 114. Each locking bolt assembly includes a bolt 141 and a locking nut 142, the bolt 141 being inserted from one side of the second end 112 into the first through hole 113 (e.g., corresponding to...). Figures 10 to 13 The bolt 141 shown on the left side) or the confirmation hole 114 (e.g., corresponding to) Figures 13 to 17The bolt 141 shown on the right side has a locking nut 142 located on one side of the first end 111 and threadedly engaged with the bolt 141. It should be noted that in the above description of the first pin 120 or the second pin 130, the so-called pin shank is the part where the pin is inserted into the corresponding hole and positioned, and the so-called pin cap is the part outside the hole that limits the position of the pin, and the outer diameter of the pin cap is larger than the outer diameter of the pin shank. Through the above structural design, since the axis of the first through hole 113 passes through the middle position of the end face of the second end 112 in the first direction, this disclosure can ensure that the axis of the first through hole 113 and the confirmation channel 114 coincides with the normal of the drilling position of the skin 200 based on the principle of "drawing the normal line from the perpendicular bisector of the chord length of the arc". Therefore, during drilling, cambering, and other processes using the guide fixture 100, it can be ensured that the axes of the first pin 120, the second pin 130, and the locking bolt assembly coincide with the normal of the drilling position of the skin 200, respectively. Simultaneously, it ensures that the process axes of other fixtures such as the drilling fixture and cambering fixture 400 that cooperate with the guide fixture 100 coincide with the normal of the drilling position of the skin 200. Accordingly, using the guide fixture 100 proposed in this disclosure in the drilling and cambering processes of the aircraft skin 200 can meet the normal alignment requirements in the relevant processes, ensuring the smoothness and regularity of the outer contour of the machined hole 220.

[0044] Specifically, refer to Figure 10 The guide block 110 contacts the aircraft skin 200 with its second end 112. Based on this, for any guide block 110, when it contacts the skin 200, since the skin 200 is arc-shaped, the end face of the second end 112 of the guide block 110 actually contacts the skin 200 with its two ends edges in the first direction. Accordingly, along the first direction, the portion of the skin 200 located between the two ends of the end face of the second end 112 can be regarded as an arc, and the end face of the second end 112 of the guide block 110 can be regarded as a chord corresponding to the arc. Therefore, by utilizing the structural design that "the axis of the first through hole 113 passes through the middle position of the end face of the second end 112 in the first direction", this disclosure can ensure that the axis of the first through hole 113 coincides with the normal of the middle position (e.g., the vertex) of the aforementioned arc. As a result, each channel structure processed during the process (e.g., the process transition hole 210, the machining hole 220, etc.) can ensure that the axis of the channel coincides with the normal of the drilling position of the skin 200.

[0045] like Figure 1 and Figure 4As shown, in one embodiment of this disclosure, the end face of the second end 112 of the guide block 110 can be rectangular, and the axis of the first through hole 113 can pass through the geometric center of the end face of the second end 112. In other words, based on the premise that "the axis of the first through hole 113 passes through the middle position of the end face of the second end 112 in the first direction", the axis of the first through hole 113 can also pass through the middle position of the end face of the second end 112 in the third direction.

[0046] like Figure 6 As shown, in one embodiment of this disclosure, the first end 111 of the guide block 110 may be provided with a pivot portion 1111, and the two guide blocks 110 are rotatably connected via the two pivot portions 1111. Based on this, the guide fixture 100 proposed in this disclosure may further include an adjusting bolt 150 passing through the two pivot portions 1111, which can lock or release the two guide blocks 110. Accordingly, when it is necessary to adjust the relative opening and closing position (e.g., included angle) of the two guide blocks 110, the adjusting bolt 150 can be turned to release the two guide blocks 110; when rotated to the desired opening and closing position, the adjusting bolt 150 can be turned again to lock the two guide blocks 110. In other embodiments of this disclosure, other adjustable positioning structures may also be used to achieve adjustment and locking of the two guide blocks 110 at different opening and closing positions, and this disclosure is not limited to this embodiment.

[0047] like Figure 6 As shown, based on the structural design of the guide fixture 100 including the adjusting bolt 150, in one embodiment of this disclosure, a control handwheel 151 can be provided at one end of the adjusting bolt 150. Through the above structural design, this disclosure enables the operator to operate the adjusting bolt 150 to rotate using the control handwheel 151, which is more labor-saving.

[0048] like Figure 3 and Figure 5As shown, in one embodiment of this disclosure, when the second pin 130 is disposed in the confirmation channel 114, the pin rod of the second pin 130 can pass through the second through hole 121 and the first hole portion 1131 respectively, and the pin cap of the second pin 130 can be located on the side of the first pin 120 away from the pin rod. Through the above structural design, when the second pin 130 is inserted, it can be made to have the same insertion direction as the first pin 120, that is, the second pin 130 is inserted into the confirmation channel 114 from one side of the second end 112 of the guide block 110. Accordingly, the insertion steps of the first pin 120 and the second pin 130 can be performed on the same side of the skin 200, further reducing the process complexity and facilitating operation. In some other embodiments of this disclosure, when the second pin 130 is disposed in the confirmation channel 114, the pin cap of the second pin 130 may also be located outside the first end 111, that is, the second pin 130 may be inserted into the confirmation channel 114 from one side of the first end 111 of the guide block 110, and is not limited to this embodiment.

[0049] like Figure 5 and Figure 6 As shown, in one embodiment of this disclosure, the wall of the second hole 1132 at the end away from the first hole 1131 may be provided with an annular clearance groove 1133. Through the above structural design, this disclosure can utilize the annular clearance groove 1133 to provide a clearance function, avoiding slippage during the process (e.g., see [reference]). Figure 12 (As shown in the process state) The sliding tool 400 collided with the hole wall of the first hole 1131, damaging the structure of the guide block 110, thus ensuring the stability and service life of the guide tool 100 during use.

[0050] In one embodiment of this disclosure, the outer diameter of the first pin 120 can be larger than the diameter of the second hole 1132, so that the first pin 120 is tightly fitted when it is placed in the second hole 1132. Through the above structural design, this disclosure enables a more secure fit when the first pin 120 is inserted into the second hole 1132, further improving the stability and reliability of the first pin 120 in coaxiality verification and bolt 141 insertion, and further meeting the alignment requirements in drilling and slipforming processes.

[0051] In one embodiment of this disclosure, the outer diameter of the pin shank of the second pin 130 can be larger than the diameter of the second through hole 121, so that the second pin 130 is tightly fitted when it is disposed in the second through hole 121. Through the above structural design, this disclosure can make the fit when the second pin is inserted into the confirmation hole 114 more secure, further improve the stability and reliability of the second pin 130 when participating in coaxiality confirmation, and further meet the alignment requirements in drilling and slippage processes.

[0052] like Figure 1 and Figure 3As shown, in one embodiment of this disclosure, the bolt 141 of the locking bolt assembly may be provided with a push-pull ring 1411. Through the above structural design, this disclosure allows the operator to push and pull the bolt 141 using the push-pull ring 1411, making it easier to apply force.

[0053] In one embodiment of this disclosure, the bore diameter of the aircraft skin 200 (i.e., the diameter of the machined hole 220) can be 1 inch, and the outer diameter of the bolt 141 of the locking bolt assembly (i.e., the diameter of the process transition hole 210) can be 0.25 inches. In other embodiments of this disclosure, depending on the manufacturing needs of different aircraft, the bore diameter of the skin 200 can also be other sizes, and the outer diameter of the bolt 141 can be adjusted accordingly, as long as the outer diameter of the bolt 141 is smaller than the bore diameter.

[0054] Based on the detailed description of the above-described exemplary embodiments of the aircraft skin drilling and rudder guidance tooling proposed in this disclosure, the following will be combined with Figures 7 to 17 The present invention describes a specific application example of the guide tooling 100 proposed in this disclosure in drilling and rutting of the skin 200 in an application scenario.

[0055] See Figures 7 to 17 , Figure 7 and Figure 8 The text represents the characteristics of each element. Figure 1 The diagram shows a three-dimensional structural schematic of the guide fixture 100 from two different perspectives in an application scenario. Figures 9 to 17 The text represents the characteristics of each element. Figure 1 The diagram shows a cross-sectional view of the guide fixture 100 during multiple process steps. It should be noted that, for ease of illustration and understanding, the skin 200 shown in the related figures is only a partial structure.

[0056] like Figure 7 and Figure 17 As shown, when the guide fixture 100 proposed in this disclosure is used in the drilling and cambering processes of the skin 200, a large portion of the guide fixture 100 (e.g., two guide blocks 110) is located on one side surface of the skin 200 (the aforementioned second direction is approximately the thickness direction of the skin 200). Furthermore, when the first pin 120 is inserted into the second hole 1132, the pin cap of the first pin 120 is located on the other side surface of the skin 200; when the second pin 130 is inserted into the confirmation hole 114, the pin cap of the second pin 130 is located on the other side surface of the skin 200 (specifically, outside the pin cap of the first pin 120); when the bolt 141 passes through the confirmation hole 114 (or through the first through hole 113, for example, corresponding to...), it is considered a bolt. Figures 10 to 13 The bolt 141 shown on the left side has its nut portion located outside the nut of the first pin 120 (or on the other side surface of the skin 200).

[0057] As described above, the general process steps for drilling and denting the aircraft skin 200 are as follows:

[0058] like Figure 9 As shown, the first process transition hole 210 is drilled at a designated position on the skin 200. Specifically, the drilling process can be carried out using the first drilling tool.

[0059] like Figure 10 As shown, the guide fixture 100 proposed in this disclosure is fixed to the skin 200. Specifically, the main structure of the guide fixture 100 (i.e., the two guide blocks 110) is fixed to the skin 200 by a set of locking bolt assemblies. The bolts 141 of the locking bolt assembly pass through the first process transition hole 210, and at this time, the bolts 141 are inserted into the first through hole 113 of one of the guide blocks 110. By manipulating the adjusting bolt 150, the two guide blocks 110 are released, and their opening and closing states are adjusted so that the end faces of the second ends 112 of the two guide blocks 110 are in contact with the skin 200. Then, the adjusting bolt 150 is manipulated to lock the two guide blocks 110. Then, using the first hole 1131 of the first through hole 113 of another guide block 110 as the guide hole, a second process transition hole 210 is drilled on the skin 200 using a drilling tool. This drilling tool can be the first drilling tool mentioned above for drilling the first process transition hole 210, or it can be another drilling tool.

[0060] like Figure 11 As shown, using the second process transition hole 210 as a reference, the second drilling fixture 300 further drills in the process transition hole 210 to form the first machining hole 220. Specifically, during the drilling process of the second drilling fixture 300, the second process transition hole 210 and the first hole portion 1131 of the guide block 110 can provide a guiding function.

[0061] like Figure 12 As shown, the sliding tool 400 is used to perform sliding treatment on the skin 200 at the position of the first machining hole 220. Specifically, during the sliding treatment process of the sliding tool 400, the first hole portion 1131 of the guide block 110 can provide a guiding function. Accordingly, the first machining hole 220 after sliding treatment is obtained.

[0062] like Figure 13As shown, a first pin 120 and a second pin 130 are respectively installed into the right guide block 110 (at this time, the left guide block 110 is still fixed to the skin 200 by the first set of locking bolts). Specifically, the first pin 120 passes through the first machined hole 220 and is inserted into the second hole 1132 of the right guide block 110, and the second through hole 121 of the first pin 120 and the first hole 1131 together form a confirmation channel 114, in which the second pin 130 is inserted. This achieves the confirmation of the coaxiality of the first machined hole 220.

[0063] like Figure 14 As shown, pull out the second pin 130, leaving the first pin 120 in place. Pass the bolt 141 of the other set of locking bolt assemblies through the confirmation hole 114, and then tighten it using the lock nut 142. At this time, the guide fixture 100 is fixed to the first machining hole 220 of the skin 200 by the second set of locking bolt assemblies and the first pin 120. Of course, when the first set of locking bolt assemblies is not removed, the guide fixture 100 is simultaneously fixed to the first process transition hole 210 of the skin 200 by the same first set of locking bolt assemblies.

[0064] like Figure 15 As shown, the first set of locking bolts is removed. Then, using the first process transition hole 210 as a reference, a second machining hole 220 is formed by further drilling in the process transition hole 210 using the second drilling fixture 300. Specifically, during the drilling process of the second drilling fixture 300, the first process transition hole 210 and the first hole portion 1131 of the guide block 110 can provide a guiding function.

[0065] like Figure 16 As shown, the sliding tool 400 is used to perform sliding treatment on the skin 200 at the position of the second machining hole 220. Specifically, during the sliding treatment process of the sliding tool 400, the first hole portion 1131 of the guide block 110 can provide a guiding function. Accordingly, the second machining hole 220 after sliding treatment is obtained.

[0066] like Figure 17 As shown, a second first pin 120 (the first first pin 120 is still fixed at the first machining hole 220) and a second pin 130 are respectively installed into the left guide block 110 (at this time, the right guide block 110 is still fixed to the skin 200 by the second set of locking bolts). Specifically, the first pin 120 passes through the second machining hole 220 and is inserted into the second hole 1132 of the left guide block 110, and the second through hole 121 of the first pin 120 and the first hole 1131 together form a confirmation channel 114, in which the second pin 130 is inserted. This achieves the confirmation of the coaxiality of the second machining hole 220.

[0067] Finally, the second set of locking bolt assemblies is removed, along with two first pins 120 and one second pin 130, thereby removing the guide fixture 100 (e.g., two guide blocks 110) from the skin 200, thus achieving the disassembly and detachment of the guide fixture 100 from the skin 200. At this point, the basic process of drilling and denting the two machining holes 220 of the skin 200 is essentially complete.

[0068] It should be noted that the aircraft skin drilling and swivel guide tooling shown in the accompanying drawings and described in this specification are merely a few examples of the many guide tooling 100 capable of employing the principles of this disclosure. It should be clearly understood that the principles of this disclosure are by no means limited to any detail or component of the aircraft skin drilling and swivel guide tooling shown in the accompanying drawings or described in this specification.

[0069] In summary, the aircraft skin drilling and rudder guidance fixture disclosed herein includes two guide blocks 110, two first pins 120, a second pin 130, and two sets of locking bolt assemblies: the two guide blocks 110 are arranged along a first direction. Each guide block 110 has first and second ends 112 opposite to each other in a second direction, and the first ends 111 of the two guide blocks 110 are rotatably connected. Each guide block 110 has a first through hole 113 extending along the second direction, the axis of which passes through the middle position of the end face of the second end 112 in the first direction. The first through hole 113 has first and second hole portions 1132 respectively opening onto the end faces of the first and second ends 112, the diameter of the second hole portion 1132 being larger than that of the first hole portion 1131. The two first pins 120 are detachably disposed in the second hole portions 1132 of the two guide blocks 110, and each first pin 120 has a second through hole 121 extending along the second direction. When the first pin 120 is located in the second hole 1132, the second through hole 121 and the first hole 1131 form a confirmation channel 114. The pin shank of the first pin 120 is located in the second hole 1132, and its pin cap is located outside the second end 112. The second pin 130 is detachably located in the confirmation channel 114. Each set of locking bolt assemblies includes a bolt 141 inserted into the first through hole 113 or the confirmation channel 114 and a locking nut 142. Through the above structural design, since the axis of the first through hole 113 passes through the middle position of the end face of the second end 112 in the first direction, this disclosure can ensure that the axis of the first through hole 113 and the confirmation channel 114 coincides with the normal of the drilling position of the skin 200 based on the principle of "drawing the normal line from the perpendicular bisector of the chord length of the arc". Therefore, during drilling, cambering, and other processes using the guide fixture 100, it can be ensured that the axes of the first pin 120, the second pin 130, and the locking bolt assembly coincide with the normal of the drilling position of the skin 200, respectively. Simultaneously, it ensures that the process axes of other fixtures such as the drilling fixture and cambering fixture 400 that cooperate with the guide fixture 100 coincide with the normal of the drilling position of the skin 200. Accordingly, using the guide fixture 100 proposed in this disclosure in the drilling and cambering processes of the aircraft skin 200 can meet the normal alignment requirements in the relevant processes, ensuring the smoothness and regularity of the outer contour of the machined hole 220.

[0070] The foregoing has described and / or illustrated exemplary embodiments of the aircraft skin drilling and rudder guidance tooling proposed in this disclosure. However, the embodiments of this disclosure are not limited to the specific embodiments described herein; rather, components and / or steps of each embodiment may be used independently and separately from other components and / or steps described herein. Each component and / or step of one embodiment may also be used in combination with other components and / or steps of other embodiments. In describing the elements / components / etc. described and / or illustrated herein, the terms “a,” “an,” and “the above” are used to indicate the presence of one or more elements / components / etc. The terms “comprising,” “including,” and “having” are used to indicate an open-ended inclusion and mean that additional elements / components / etc. may exist in addition to those listed. Furthermore, the terms “first” and “second,” etc., in the claims and specification are used only as illustrative marks and are not intended to limit the numerical scope of the subject matter.

[0071] Although the aircraft skin drilling and rudder guidance tooling proposed in this disclosure has been described with respect to different specific embodiments, those skilled in the art will recognize that modifications may be made to the implementation of this disclosure within the spirit and scope of the claims.

Claims

1. A tooling for drilling holes and guiding rudders in aircraft skin, characterized in that, include: Two guide blocks (110) are arranged along a first direction; each guide block (110) has a first end (111) and a second end (112) opposite to each other in a second direction perpendicular to the first direction. The first ends (111) of the two guide blocks (110) are rotatably connected, and the axis of rotation (L) extends along a third direction perpendicular to both the first and second directions. Each guide block (110) is provided with a first through hole (113) extending along the second direction. The axis of the first through hole (113) passes through the end face of the second end (112) at the middle position in the first direction; the first through hole (113) has a first hole portion (1131) and a second hole portion (1132) connected to each other, one end of the first hole portion (1131) is open to the end face of the first end (111), one end of the second hole portion (1132) is open to the end face of the second end (112), and the diameter of the second hole portion (1132) is larger than the diameter of the first hole portion (1131); Two first pins (120) are detachably disposed in the second holes (1132) of the two guide blocks (110). The first pin (120) is provided with a second through hole (121) extending along the second direction. The diameter of the second through hole (121) is equal to the diameter of the first hole (1131). When the first pin (120) is disposed in the second hole (1132), the second through hole (121) and the first hole (1131) are coaxial and together form a confirmation channel (114). The pin of the first pin (120) is located in the second hole (1132), and its pin cap is located outside the second end (112). A second pin (130) is detachably disposed in the confirmation channel (114); Two sets of locking bolt assemblies, each including a bolt (141) and a locking nut (142), wherein the bolt (141) is used to be inserted into the first through hole (113) or the confirmation channel (114) from the second end (112) side, and the locking nut (142) is located on the first end (111) side and is threadedly engaged with the bolt (141).

2. The aircraft skin drilling and sliding guide fixture according to claim 1, characterized in that, The end face of the second end (112) is rectangular, and the axis of the first through hole (113) passes through the geometric center of the end face of the second end (112).

3. The aircraft skin drilling and sliding guide fixture according to claim 1, characterized in that, The first end (111) is provided with a pivot (1111), and the two guide blocks (110) are rotatably connected via the two pivots (1111); wherein, the guide fixture (100) further includes an adjusting bolt (150) passing through the two pivots (1111) for locking or unlocking the two guide blocks (110).

4. The aircraft skin drilling and sliding guide fixture according to claim 3, characterized in that, One end of the adjusting bolt (150) is provided with an operating handwheel (151).

5. The aircraft skin drilling and sliding guide fixture according to claim 1, characterized in that, When the second pin (130) is disposed in the confirmation channel (114), the pin rod of the second pin (130) passes through the second through hole (121) and the first hole (1131) respectively, and the pin cap of the second pin (130) is located on the side of the pin cap of the first pin (120) away from the pin rod, or the pin cap of the second pin (130) is located outside the first end (111).

6. The aircraft skin drilling and rudder guidance fixture according to claim 1, characterized in that, The second hole (1132) has an annular clearance groove (1133) on the end of the hole away from the first hole (1131).

7. The aircraft skin drilling and sliding guide fixture according to claim 1, characterized in that, The outer diameter of the first pin (120) is larger than the diameter of the second hole (1132) so that the first pin (120) is tightly fitted when it is placed in the second hole (1132).

8. The aircraft skin drilling and sliding guide fixture according to claim 1, characterized in that, The outer diameter of the pin of the second pin (130) is larger than the diameter of the second through hole (121) so that the second pin (130) is tightly fitted when it is placed in the second through hole (121).

9. The aircraft skin drilling and sliding guide fixture according to claim 1, characterized in that, The bolt (141) of the locking bolt assembly is provided with a push-pull ring (1411).

10. The aircraft skin drilling and rudder guidance fixture according to claim 1, characterized in that, The bore diameter of the aircraft skin (200) is 1 inch, and the outer diameter of the bolt (141) of the locking bolt assembly is 0.25 inches.

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