Adjustment and correction structure and aircraft original position ear hole positioning device using the same

Abstract

The present invention relates to the technical field of online maintenance of aircraft ear holes, and in particular to an adjustment and correction structure and an aircraft original position ear hole positioning device using the same. The present invention designs an adjustment and correction structure, and uses the cooperation of a drilling template and an auxiliary frame to press the drilling template on the auxiliary frame and have a certain degree of free movement with the auxiliary frame, so as to facilitate the correction of the drilling template; at the same time, a screw hole is provided on the auxiliary frame, and a through hole with a diameter larger than the screw hole is provided on the drilling template, so that the position of the drilling template can be adjusted and corrected when a bolt is installed, and then the drilling template and the auxiliary frame are fixed by tightening the bolt, which is simple and convenient to operate. The aircraft original position ear hole positioning device of the present invention relies on the auxiliary ear hole and the auxiliary joint to realize auxiliary rough positioning, and then positions the ear hole to be processed by adjusting the correction structure, thereby ensuring the coaxiality of the drill sleeve and the ear hole to be processed, and ensuring the position accuracy of the ear hole to be processed.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft ear hole online maintenance, in particular to an adjustment and correction structure and an aircraft original position ear hole positioning device using the structure. Background Art

[0002] In the field of aerospace manufacturing, the ear holes and press-fit bushings at the connection between the aircraft fuselage and the wing are usually assembled using cold extrusion strengthening technology. After a certain service period, the base holes of the ear holes are worn or even cracked due to insufficient initial interference. When the aircraft is repaired, the ear holes need to be expanded and new press-fit bushings need to be replaced. In order to ensure the assembly performance of the ear holes and the press-fit bushings, the ear holes need to be accurately positioned, and the stability of the expansion process needs to be ensured.

[0003] When the ear holes are expanded, they are repaired online and the parts cannot be removed. As a result, due to the limited processing space for the original position ear holes, the traditional tooling structure cannot meet the requirements of the wing-body for the ear hole processing accuracy, and there are situations where positioning is difficult and easy to shift, resulting in low processing quality. At present, no effective aircraft original position ear hole positioning device and method has been retrieved. Summary of the invention

[0004] Based on this, it is necessary to provide an adjustment and correction structure and an aircraft original position ear hole positioning device using the structure to address the problems of difficult positioning and easy displacement of existing aircraft ear holes during online maintenance.

[0005] The present invention is implemented by the following technical solutions:

[0006] In a first aspect, the present invention discloses an adjustment and correction structure for positioning an ear hole of an aircraft. The adjustment and correction structure comprises a drilling template, an auxiliary frame, a first bolt, and a second bolt.

[0007] The drilling template is used as a correction piece. A cylindrical portion is provided on one side of the drilling template, and the cylindrical portion forms a positioning hole 1 that passes through the drilling template. The diameter of the positioning hole 1 is φ m1 The drilling template is evenly arranged with several through holes around the positioning hole. The diameter of the through hole is φ m2 A plurality of arc grooves are evenly arranged on the outer edge of the drilling template.

[0008] The auxiliary frame is used as a mounting base for mounting and connecting with the drilling template. f1 The cylindrical part is inserted into the positioning hole 2 for adjusting and calibrating the drilling template and the auxiliary frame. The auxiliary frame is provided with two circles of mounting holes along the circumference of the positioning hole 2 on the side facing the drilling template, one of which is a plurality of screw holes 1 corresponding to a plurality of through holes 1, and the diameter of the screw holes 1 is φ f1Another circle of mounting holes is a plurality of screw holes 2 corresponding to the plurality of arc grooves 1. A plurality of through holes 2 are arranged along the circumference of the positioning holes 2 on one side of the auxiliary frame facing away from the drilling template, for mounting and fixing the auxiliary frame.

[0009] Among them, (φ f1 -φ m1 ) / φ f1 ∈[a%,b%],(φ m2 -φ f2 ) / φ f2 ∈[c%,d%], a, b, c, d are preset parameters.

[0010] The number of bolts 1 and screw holes 1 is the same and corresponds to each other. Bolts 1 are used to pass through corresponding screw holes 1 and corresponding through holes 1, and fix the drilling template and the auxiliary frame after the drilling template and the auxiliary frame are adjusted and calibrated.

[0011] The number of bolts 2 and screw holes 2 is the same and corresponds to each other. Bolts 2 are used to pass through the corresponding arc groove 1 and the corresponding screw hole 2, and further fix the drilling template and the auxiliary frame.

[0012] The adjustment and correction structure implements the method or process according to the embodiment of the present disclosure.

[0013] In a second aspect, the present invention provides an aircraft original position ear hole positioning device, including a positioning fixture frame, a bolt, a drill sleeve, an expansion bolt, a tapered sleeve, and two adjustment and correction structures of the first aspect.

[0014] The positioning fixture frame includes two frame plates with the same structure and spaced apart, and the frame plates are connected as one at the bottom. An auxiliary plate hole is provided at one end of the frame plate, and a guide hole is provided at the other end. The two auxiliary plate holes are concentric and form an auxiliary joint. The guide holes of the two frame plates are concentric and form a positioning joint. The frame plate is provided with a plurality of screw holes 3 corresponding to the plurality of through holes 2 along the circumferential direction around the guide hole, for installing the adjustment correction structure.

[0015] The number of bolts 3 is the same as that of through holes 2 and they correspond to each other. The bolts 3 pass through the corresponding through holes 2 and extend into the corresponding screw holes 3 to connect the adjustment and correction structure with the frame plate.

[0016] The two adjustment and correction structures include an adjustment structure 1 and an adjustment structure 2. The adjustment structure 1 and the adjustment structure 2 are respectively located on the mutually opposite sides of the two frame plates to ensure the coaxiality.

[0017] The tapered sleeve is used to cooperate with the ear hole to determine the correction position of the drilling template and the auxiliary frame;

[0018] The drill sleeve is connected to the drill template for subsequent cooperation with the tool. The expansion bolt is used to pass through the auxiliary joint for fixing.

[0019] The aircraft original position ear hole positioning device implements the method or process according to the embodiment of the present disclosure.

[0020] In a third aspect, the present invention provides a method for locating an original position ear hole of an aircraft, which is applied to the original position ear hole locating device of the second aspect. The original position ear hole of the aircraft includes auxiliary ear holes and ear holes to be processed that are arranged at intervals.

[0021] The method for locating the ear holes of the original position of the aircraft includes the following steps:

[0022] S1, move the original position ear hole positioning device of the aircraft to the original position ear hole position of the aircraft, so that the auxiliary ear hole is close to the auxiliary joint and is placed between the two auxiliary plate holes, and the ear hole to be processed is close to the positioning joint and is placed between the two guide holes;

[0023] S2, connect the auxiliary joint to the auxiliary ear hole through expansion bolts, and install gaskets between the auxiliary ear hole and the auxiliary plate hole; turn the expansion bolts to tighten the auxiliary joint, eliminate the installation gap and fix it;

[0024] S3, adjusting and correcting the adjustment structure 1, and then adjusting and correcting the adjustment structure 2;

[0025] Among them, the adjustment and correction method is:

[0026] S301, firstly, the drilling template is mounted on the auxiliary frame by bolt 1, and the degree of freedom is reserved so that the drilling template can move on the auxiliary frame;

[0027] S302, taking the center of the ear hole to be processed as a reference, inserting the end of the tapered sleeve with a smaller diameter into the positioning hole 1 of the drilling template of the adjustment structure 1, and passing the tapered sleeve through the ear hole to be processed;

[0028] S303, adjusting the tapered sleeve until it matches the lug hole to be processed;

[0029] S304, tighten bolt 1 to fix the drilling template of the adjustment structure 1 on the auxiliary frame of the adjustment structure 1;

[0030] S305, further fixing the drilling template of the adjustment structure 1 by bolt 2;

[0031] S306, taking out the tapered sleeve;

[0032] S307, fixing the drill sleeve of the adjustment structure 1 on the drill template of the adjustment structure 1, and then installing the tool rod of the tool in the drill sleeve and extending it out of the adjustment structure 2;

[0033] S308, adjusting the relative positions of the drilling template of the adjustment structure 2 and the auxiliary frame of the adjustment structure 2, so that the drill sleeve of the adjustment structure 2 can pass through the tool rod of the tool and be fixed on the drilling template of the adjustment structure 2;

[0034] S309, tighten bolt 1 to fix the drilling template of the adjustment structure 2 to the auxiliary frame of the adjustment structure 2;

[0035] S310, further fix the drilling template of the adjustment structure 2 by bolt 2.

[0036] The aircraft original position ear hole positioning method implements the method or process according to the embodiment of the present disclosure.

[0037] Compared with the prior art, the present invention has the following beneficial effects:

[0038] 1. The present invention designs an adjustment and correction structure, which utilizes a drilling template with a positioning hole one and an auxiliary frame with a positioning hole two, so that the drilling template is pressed on the auxiliary frame and has a certain free movement range with the auxiliary frame, which is convenient for adjusting and correcting the drilling template; at the same time, a screw hole one is set in the auxiliary frame, and a through hole one with a diameter larger than the screw hole one is set on the drilling template, so that the position of the drilling template can be adjusted and corrected when the bolt one is installed, and then the drilling template and the auxiliary frame are fixed by tightening the bolt one, which is simple and convenient to operate.

[0039] 2. The adjustment and correction structure of the present invention is applied to the positioning of the ear hole to be processed in the original position of the aircraft, and a new positioning device for the ear hole in the original position of the aircraft is designed. Under the condition of realizing auxiliary rough positioning by the auxiliary ear hole and the auxiliary joint, the ear hole to be processed is positioned by adjusting the correction structure, thereby ensuring the coaxiality of the positioning hole of the drilling template and the ear hole to be processed, and then ensuring the coaxiality of the drill sleeve and the ear hole to be processed, and ensuring the position accuracy of the ear hole to be processed. In addition, the tooling of the positioning device also has the advantages of simple structure and high positioning accuracy.

[0040] 3. The present invention utilizes auxiliary ear holes for auxiliary positioning. At the same time, a pair of bolts are designed in the adjustment and correction structure to axially fix the drilling template and a pair of bolts are designed to radially fix the drilling template. In addition, a clamping screw is used to fix the drill sleeve on the drilling template, thereby ensuring the stability of the tool during processing and effectively improving the processing accuracy of the ear holes to be processed. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] Figure 1 The aircraft original position ear piece hole positioning device using the adjustment and correction structure in embodiment 1 of the present invention;

[0042] Figure 2 for Figure 1 Schematic diagram of the aircraft original position ear hole positioning device when in use;

[0043] Figure 3 for Figure 1 A magnified view of the adjusted correction structure;

[0044] Figure 4 for Figure 3 Top view of the center drill template;

[0045] Figure 5 for Figure 4 Cross-section view in the AA direction;

[0046] Figure 6 for Figure 4 Cross-section along the middle BB direction;

[0047] Figure 7 for Figure 3 A top view of the middle auxiliary frame;

[0048] Figure 8 for Figure 7 Cross-section view in the AA direction;

[0049] Fig. 9 for Figure 7 Cross-section along the middle BB direction;

[0050] Fig.10 for Figure 3 The diagram of the use of the adjustment and correction structure and the tapered sleeve;

[0051] Fig.11 for Fig.10 Structural diagram of the middle tapered sleeve;

[0052] Fig.12 for Figure 1 Structural diagram of expansion bolts;

[0053] Fig.13 for Figure 2 A partial enlarged view of .

[0054] In the accompanying drawings, the components represented by the reference numerals are listed as follows:

[0055] 1. Positioning fixture, 2. Expansion bolt, 3. Gasket, 4. Spacer, 5. Drill sleeve, 6. Bolt three, 7. Auxiliary frame, 8. Drill template, 9. Bolt two, 10. Bolt one, 11. Pressing screw, 12. Support column, 13. Connecting frame, 14. Tapered sleeve, 31. Bolt rod, 32. Expansion sleeve, 33. Tapered nut, 34. Auxiliary rotating handle, 101. Auxiliary plate hole, 102. Guide hole, 103. Fixed joint, 104. Support plate. DETAILED DESCRIPTION

[0056] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0057] It should be noted that when a component is referred to as being "mounted on" another component, it may be directly on the other component or there may be a central component. When a component is considered to be "set on" another component, it may be directly set on the other component or there may be a central component at the same time. When a component is considered to be "fixed to" another component, it may be directly fixed on the other component or there may be a central component at the same time.

[0058] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as those commonly understood by those skilled in the art to which the present invention belongs. The terms used herein in the specification of the present invention are only for the purpose of describing specific embodiments and are not intended to limit the present invention. The term "or / and" used herein includes any and all combinations of one or more of the related listed items.

[0059] Please see Figure 1 , Figure 1 This is a structural diagram of the aircraft original position ear hole positioning device using the adjustment and correction structure in this embodiment. This embodiment discloses an aircraft original position ear hole positioning device using the adjustment and correction structure, and its application object is the aircraft original position ear hole, including the auxiliary ear hole and the ear hole to be processed arranged at intervals. Figure 2 , is an example of the use of the original position ear hole positioning device of this aircraft, Figure 2 In the middle, A is the auxiliary ear hole, and B is the ear hole to be processed.

[0060] See also Figure 1 The aircraft original position ear hole positioning device using the adjustment and correction structure includes a positioning fixture frame 1, a bolt three 6, a drill sleeve 5, an expansion bolt 2, a tapered sleeve 14, and two adjustment and correction structures.

[0061] like Figure 1 As shown, the positioning fixture frame 1 includes two spaced apart and identically structured frame plates, which are connected as one at the bottom. An auxiliary plate hole 101 is opened at one end of the frame plate, and a guide hole 102 is opened at the other end. The two auxiliary plate holes 101 are concentric and form an auxiliary joint. The two guide holes 102 are concentric and form a positioning joint.

[0062] The auxiliary joint is used to connect with the auxiliary ear hole, and the positioning joint is used to cooperate with the ear hole to be processed so that the adjustment and correction structure can be positioned with respect to the ear hole to be processed. It should be noted that the distance between the auxiliary ear hole and the ear hole to be processed is a part processing specification, which can be determined according to the drawing or directly measured, and the adapted positioning fixture 1 can be processed based on the obtained data.

[0063] Two adjustment and correction structures are used to position the aircraft ear holes, which are divided into adjustment structure 1 and adjustment structure 2. Figure 3 , is an enlarged view of the adjustment and correction structure. Adjustment structure 1 and adjustment structure 2 are located on the opposite sides of the two frame plates to ensure coaxiality.

[0064] The adjustment structure 1 and the adjustment structure 2 have the same structure, including a drilling template 8, an auxiliary frame 7, a bolt 10, and a bolt 2 9.

[0065] See also Figure 4 , Figure 5 , Figure 6 , is a structural diagram of the drilling template 8. The drilling template 8 is used as a correction piece. One side of the drilling template 8 is integrally formed with a cylindrical portion, and the cylindrical portion forms a positioning hole 1 that passes through the drilling template 8. The inner diameter of the positioning hole 1 is φ m1 The drilling template 8 has a plurality of through holes evenly opened around the positioning hole. The diameter of the through hole is φ m2 The outer edge of the drilling template 8 is evenly provided with a plurality of arc grooves.

[0066] See also Figure 7 , Figure 8 , Fig. 9 , which is a structural diagram of the auxiliary frame 7. The auxiliary frame 7 is used as a mounting base plate for mounting and connecting with the drilling template 8. The auxiliary frame 7 has a diameter of φ f1 The cylindrical part is inserted into the positioning hole 2 for adjusting and calibrating the drilling template 8 and the auxiliary frame 7. The auxiliary frame 7 has two circles of mounting holes on the side facing the drilling template 8 along the circumference around the positioning hole 2: one circle of mounting holes is a screw hole 1 corresponding to the through hole 1, and the diameter of the screw hole 1 is φ f2 The other circle of mounting holes is screw hole 2 corresponding to arc groove 1.

[0067] It should be noted that (φ f1 -φ m1 ) / φ f1 ∈[a%,b%],(φ m2 -φ f2 ) / φ f2 ∈[c%,d%], a, b, c, d are preset parameters. The recommended settings are: 5≤a≤8, 8≤b≤10, 3≤c≤5, 5≤d≤8. The above settings take into account the processing accuracy and matching accuracy of the equipment to ensure the adjustment accuracy.

[0068] In order to ensure the rigidity of the structure, it is recommended that the auxiliary frame 7 be made of 45 steel and the drilling template 8 be made of 40Cr.

[0069] In this embodiment, the drilling template 8 is processed into a rectangle, the positioning hole 1 is located at the center of the drilling template 8, and the arc grooves 1 are evenly arranged on the four sides of the drilling template 8, with one arc groove 1 on each side. The auxiliary frame 7 is also processed into a rectangle, and the positioning hole 2 is located at the center of the auxiliary frame 7. The design specification of the ear hole corresponding to the original position of the aircraft is φ m1 =50mm,φ f1 =60mm,φ m2 =8mm,φ f2 =5mm.

[0070] like Figure 3 As shown, the number of bolts 10 is the same as that of screw holes 1, and they correspond to each other. Bolt 10 is used to pass through the corresponding through hole 1, extend into the corresponding screw hole 1, and fix the drilling template 8 and the auxiliary frame 7 after the drilling template 8 and the auxiliary frame 7 are adjusted and calibrated. The number of bolts 2 9 is the same as that of screw holes 2, and they correspond to each other. Bolts 2 9 are used to pass through the corresponding arc groove 1, extend into the corresponding screw hole 2, and further fix the drilling template 8 and the auxiliary frame 7.

[0071] Referring to the above setting relationship, the cylindrical portion of the drilling template 8 is smaller than the second positioning hole, and the cylindrical portion is inserted into the second positioning hole. The drilling template 8 is pressed on the auxiliary frame 7 and has a certain free movement range with the auxiliary frame 7, which is convenient for adjusting and correcting the drilling template 8. Since the diameter of the through hole 1 is larger than the screw hole 1, the position of the drilling template 8 can be adjusted and corrected when the bolt 10 is installed, and the drilling template 8 can still be fixed to the auxiliary frame by tightening the bolt 10.

[0072] In this embodiment, it is recommended that bolt 10 be a flange bolt. After tightening bolt 10, the flange of bolt 10 can clamp through hole 1, thereby pressing the drilling template 8. Of course, bolt 10 can be a bolt with an outer end larger than through hole 1.

[0073] It should be emphasized that the bolt 2 9 should be a truncated cone bolt. The truncated cone bolt has a truncated cone-shaped outer end. In this way, during the tightening process, the outer end of the truncated cone bolt contacts the arc groove 1 to clamp the drilling template 8. In addition, the truncated cone bolt is also convenient for adjustment. Since it has a truncated cone-shaped outer end, the mutual gap with the arc groove 1 can be changed by screwing it in and out, thereby adapting to the adjustment of the drilling template 8.

[0074] See also Figure 7, the auxiliary frame 7 has a plurality of through holes 2 opened along the circumference of the positioning hole 2 on the side facing away from the drilling template 8, for installing and fixing the auxiliary frame 7. Correspondingly, the frame plate has a plurality of screw holes 3 corresponding to the plurality of through holes 2 opened along the circumference around the guide hole 102, for installing the adjustment and correction structure. In this way, the same number of bolts 3 6 as the number of through holes 2 are used to pass through the corresponding through holes 2 and extend into the corresponding screw holes 3, and the auxiliary frame 7 is connected to the frame plate, that is, the adjustment and correction structure is connected to the frame plate, such as Figure 3 shown.

[0075] In this embodiment, it is suggested that the bolt 3 6 adopts a countersunk bolt for easy installation. Of course, the bolt 3 can also adopt other types of bolts, as long as it can fix the auxiliary frame 7 and the frame plate.

[0076] See also Fig.10 , is a diagram for adjusting the use of the correction structure and the tapered sleeve. The tapered sleeve 14 is used to cooperate with the ear hole to determine the correction position of the drilling template 8 and the auxiliary frame 7. For details, see Fig.11 , Fig.11 1 is a structural diagram of the tapered sleeve 14. Since the tapered sleeve 14 is a well-known structure, its structure is briefly described below: the tapered sleeve 14 has a truncated cone structure with a large diameter at one end and a small diameter at the other end.

[0077] Specifically, the scenario in which the tapered sleeve 14 is used is that the ear hole to be processed is close to the positioning joint and is placed between the two guide holes 102. When adjusting and correcting, the drilling template 8 should be installed on the auxiliary frame 7 by bolts 10, and the degree of freedom should be retained so that the drilling template 8 can move on the auxiliary frame 7. Then, with the center of the ear hole to be processed as the reference, the end with a smaller diameter of the tapered sleeve 14 is inserted into the positioning hole 1 of the drilling template 8, and the tapered sleeve 14 is passed through the ear hole to be processed. Adjust the tapered sleeve 14 until it is matched with the ear hole to be processed. At this time, the drilling template 8 moves relative to the auxiliary frame 7, and the adjustment and correction is completed. Among them, the completion of the match means that the amount of the tapered sleeve 14 passing through no longer changes. Of course, before passing the tapered sleeve 14, a gasket 3 can also be installed between the ear hole to be processed and the positioning joint to eliminate the gap. Then tighten the bolts 10, and use the clamping force to fix the drilling template 8 on the auxiliary frame 7, that is, the positioning after adjustment and correction is completed. In order to strengthen fixing, bolt 2 can also be installed to further fix the drilling template 8. Finally, take out the tapered sleeve 14 and get final product.

[0078] Of course, the tapered sleeve 14 may also be replaced by other parts, such as a conical or truncated cone rod.

[0079] like Figure 3As shown, the drill sleeve 5 is installed and connected to the drill template 8 for subsequent cooperation with the tool to ensure the coaxiality of the tool and the ear hole. Specifically, the two are connected by a clamping screw. For the drill sleeve 5, one end is provided with a folded edge, and the other end extends into the positioning hole one. Since the folded edge is larger than the positioning hole one, the folded edge of the drill sleeve 5 will be stuck on the drill template 8. The outer edge of the folded edge is evenly opened with arc grooves two, and the drill template 8 is also circumferentially evenly processed with screw holes four around the positioning hole one, and the screw holes four correspond to the arc grooves two. Pass the clamping screw 11 through the arc groove two and extend it into the screw hole four, and tighten the clamping screw 11 to clamp the drill sleeve 5 and the drill template 8.

[0080] It should be noted that the drill sleeve 5 needs to be installed and connected to the drill template 8 after the adjustment and correction mechanism is adjusted and corrected.

[0081] See also Fig.12 , is a structural diagram of the expansion bolt 2. The expansion bolt 2 is used to pass through the auxiliary joint for fixing. Fig.12 Since the expansion bolt 2 is a known structure, its structure is briefly described below. The expansion bolt 2 includes a bolt rod 31, an expansion sleeve 32, a conical nut 33, and an auxiliary rotation handle 34. The expansion sleeve 32 in this embodiment is made of spring steel, and the maximum expansion degree is 2mm.

[0082] Specifically, the auxiliary ear hole is close to the auxiliary joint and placed between the two auxiliary plate holes 101. The expansion bolt 2 without the conical nut 33 is passed through the two auxiliary plate holes, and one end of the bolt rod 31 will be stuck in one of the auxiliary plate holes. Then the conical nut 33 is installed on the other end of the bolt rod 31, so that the auxiliary rotating handle 34 is turned to drive the conical nut 33 to move toward the auxiliary rotating handle 34 and against the frame plate, and expand with the expansion sleeve 32, so that the auxiliary joint and the auxiliary ear hole eliminate the installation gap and are fixed. Of course, it is also recommended to install a gasket 3 between the auxiliary ear hole and the auxiliary plate hole 101.

[0083] Based on the above-mentioned aircraft original position ear piece hole positioning device, this embodiment also provides an aircraft original position ear piece hole positioning method, which is applied to the above-mentioned aircraft original position ear piece hole positioning device.

[0084] The method for locating the ear holes of the original position of the aircraft includes the following steps:

[0085] S1, move the aircraft original position ear hole positioning device to the aircraft original position ear hole position, so that the auxiliary ear hole is close to the auxiliary joint and placed between the two auxiliary plate holes 101, and the ear hole to be processed is close to the positioning joint and placed between the two guide holes 102.

[0086] It should be noted that, since most of the aircraft's original position ear holes are at high positions, a lifting device is required to lift the aircraft's original position ear hole positioning device to the aircraft's original position ear hole position.

[0087] S2, connect the auxiliary joint to the auxiliary ear hole through the expansion bolt 2, and install the gasket 3 between the auxiliary ear hole and the auxiliary plate hole 101; rotate the expansion bolt 2 to tighten the auxiliary joint, eliminate the installation gap and fix it.

[0088] S3, adjusting and correcting the adjustment structure 1, and then adjusting and correcting the adjustment structure 2;

[0089] Among them, the adjustment and correction method is:

[0090] S301, firstly install the drilling template 8 on the auxiliary frame 7 by means of bolts 10, and retain the degree of freedom so that the drilling template 8 and the auxiliary frame 7 can move relative to each other;

[0091] S302, taking the center of the ear hole to be processed as a reference, inserting the end with a smaller diameter of the tapered sleeve 14 into the positioning hole 1 of the drilling template 8 of the adjustment structure 1, and passing the tapered sleeve 14 through the ear hole to be processed;

[0092] If necessary, before inserting the tapered sleeve 14 , install a gasket 3 between the ear hole to be processed and the positioning joint to eliminate the gap; the tapered sleeve 14 should also pass through the gasket 3 .

[0093] S303, adjusting the tapered sleeve 14 until it matches with the lug hole to be processed;

[0094] Specifically, the fitting is completed when the penetration amount of the tapered sleeve 14 no longer changes.

[0095] S304, tighten the bolt 10 to fix the drilling template 8 of the adjustment structure 1 on the auxiliary frame 7 of the adjustment structure 1;

[0096] S305, further fixing the drilling template 8 of the adjustment structure 1 by means of the second bolt 9;

[0097] S306, taking out the tapered sleeve 14;

[0098] It should be noted that if a gasket 3 is installed between the ear hole to be processed and the positioning joint, it should be retained.

[0099] S307, fixing the drill sleeve 5 of the adjustment structure 1 on the drill template 8 of the adjustment structure 1, and then installing the tool rod of the tool in the drill sleeve 5 and extending it out of the adjustment structure 2;

[0100] It should be noted that if a gasket 3 is installed between the ear hole to be processed and the positioning joint, the tool shaft of the tool should pass through the gasket 3.

[0101] S308, adjusting the relative positions of the drilling template 8 of the second adjustment structure and the auxiliary frame 7 of the second adjustment structure, so that the drill sleeve 5 of the second adjustment structure can pass through the tool rod of the tool and be fixed on the drilling template 8 of the second adjustment structure;

[0102] S309, tighten the bolt 10 to fix the drilling template 8 of the adjustment structure 2 on the auxiliary frame 7 of the adjustment structure 2;

[0103] S310, further fix the drilling template 8 of the second adjustment structure by means of the second bolt 9.

[0104] Of course, after the adjustment and correction of the adjustment and correction structures on both sides are completed, the coaxial line has been achieved, that is, the positioning of the ear hole to be processed is completed. Then, the tool can be rotated to expand the ear hole to be processed.

[0105] In this way, while relying on the auxiliary ear hole and the auxiliary joint to realize auxiliary rough positioning, the ear hole to be processed is positioned by adjusting the correction structure, ensuring the coaxiality of the positioning hole 1 of the drilling template 8 and the ear hole to be processed, thereby ensuring the coaxiality of the drill sleeve 5 and the ear hole to be processed, and ensuring the position accuracy of the ear hole to be processed. In addition, the auxiliary ear hole is used for auxiliary positioning, and at the same time, bolts 10 are designed in the adjustment and correction structure to axially fix the drilling template 8 and bolts 2 9 are designed to radially fix the drilling template 8. In addition, the clamping screw 11 is used to fix the drill sleeve 5 on the drilling template 8, which ensures the stability of the tool during the processing and effectively improves the processing accuracy of the ear hole to be processed.

[0106] In another embodiment:

[0107] The aircraft original position ear hole positioning device is also provided with an auxiliary fixing structure. The auxiliary fixing structure is provided on the side of the positioning joint away from the auxiliary joint, and is used to assist in fixing the positioning joint. This is because some of the aircraft original position ear holes are in special positions, and it is not convenient for the positioning joint to directly place the ear holes to be processed between the positioning holes 102 vertically, and when expanding the holes, due to the separation of the plates, there will be a situation where the components vibrate greatly, resulting in poor processing results.

[0108] See also Figure 3 The auxiliary fixing structure includes two auxiliary plates, a support pad 4, and a bolt 3 6. The two auxiliary plates are arranged at intervals and have the same structure. The two auxiliary plates are connected one-to-one with the two frame plates. The auxiliary plates are provided with fixing holes, the two fixing holes are concentric, and form a fixing joint 103. The support pad 4 is arranged between the two fixing holes to support the two auxiliary plates. The bolt 3 6 passes through the fixing joint 103 and penetrates the support pad 4 to fix the support pad 4 between the auxiliary plates.

[0109] It should be noted that the support pad 4 should be ensured to extend between the two auxiliary plates so as to effectively support the auxiliary plates.

[0110] Thus, for the above-mentioned aircraft original position ear hole positioning method, before S1, bolt three 6 and support pad 4 should be removed, so that a channel is left between the auxiliary plates, making it convenient to place the ear hole to be processed between the positioning holes 102 from the horizontal direction, thereby completing S1.

[0111] Of course, after S1, the support pad 4 should be reinstalled between the auxiliary plates through the bolts 3 6. During the subsequent hole expansion process, since the frame plates are connected at the positioning joints through the auxiliary fixing structure, large vibrations can be avoided. In addition, if necessary, a gasket 3 is installed between the support pad 4 and the auxiliary plate, wherein the thickness of the gasket 3 is selected to be thinner or to correspond to the cross section of the support pad 4, so as to ensure that the two auxiliary plates are supported by the support pad 4.

[0112] In addition, there is an example:

[0113] See also Figure 2 The aircraft original position ear hole positioning device is also provided with a support plate 104, a support column 12, and a connecting frame 13. The support plate 104 is connected to the bottom of the frame plate and can be designed in an L-shaped layer, such as Figure 1 As shown. The support column 12 is used to support the positioning fixture frame, and its bottom end can be placed on the ground or other supporting platforms, and its bottom end can be fixed when necessary. The connecting frame 13 is used to connect the support plate 104 and the support column 12. Fig.13 As shown, the support plate 104 and the support column 12 are connected by bolts, and the connecting frame 13 at the connecting part adopts fixed blocks that are connected to each other to ensure the stability of processing.

[0114] The above components are used to support the entire positioning device and the aircraft component where the lug hole is located. This is because the entire positioning device is connected to the lug hole, which is equivalent to hanging on the aircraft component where the lug hole is located. This is easy to cause overall shaking during processing, resulting in poor processing results.

[0115] Therefore, after S1, the support plate 104 is connected to the support column 12, and the bottom end of the support column 12 is placed on the support platform. If necessary, the bottom end is fixed. In this way, the support platform is used to support the components above it, which can reduce the shaking of the hole expansion processing caused by suspension.

[0116] See also Figure 2 The auxiliary ear hole (A in the figure) and the ear hole to be processed (B in the figure) are spaced up and down, so two support plates 104 can also be symmetrically arranged. If the auxiliary ear hole and the ear hole to be processed are reversed in up and down positions, the device can be turned over accordingly for installation and use.

[0117] The technical features of the above-described embodiments may be arbitrarily combined. To make the description concise, not all possible combinations of the technical features in the above-described embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0118] The above-mentioned embodiments only express several implementation methods of the present invention, and the descriptions thereof are relatively specific and detailed, but they cannot be understood as limiting the scope of the invention patent. It should be pointed out that, for ordinary technicians in this field, several variations and improvements can be made without departing from the concept of the present invention, and these all belong to the protection scope of the present invention. Therefore, the protection scope of the patent of the present invention shall be subject to the attached claims.

Claims

1. Adjustment and correction structure, used to locate the aircraft ear hole, characterized in that: The adjustment and correction structure comprises: A drilling template is used as a correction piece; one side of the drilling template is provided with a cylindrical portion, and the cylindrical portion forms a positioning hole 1 that passes through the drilling template, and the inner diameter of the positioning hole 1 is φ m1 The drilling template is evenly arranged with a number of through holes around the positioning hole, and the diameter of the through hole is φ m2 ; The outer edge of the drilling template is evenly provided with a plurality of arc grooves; The auxiliary frame is used as a mounting base plate for mounting and connecting with the drilling template; the auxiliary frame is provided with a diameter of φ f1 The cylindrical portion is inserted into the positioning hole 2 for adjusting and correcting the drilling template and the auxiliary frame; the auxiliary frame is provided with two circles of mounting holes along the circumference around the positioning hole 2 on one side facing the drilling template, wherein one circle of mounting holes is a plurality of screw holes 1 corresponding to the plurality of through holes 1, and the diameter of the screw holes 1 is φ f2 , another circle of mounting holes is a plurality of screw holes 2 corresponding to the plurality of arc-shaped grooves 1; a plurality of through holes 2 are arranged along the circumference of the positioning holes 2 on the side of the auxiliary frame facing away from the drilling template, for mounting and fixing the auxiliary frame; Among them, (φ f1 -φ m1 ) / φ f1 ∈[a%,b%],(φ m2 -φ f2 ) / φ f2 ∈[c%,d%], a, b, c, d are preset parameters; A bolt 1 corresponding to the plurality of screw holes 1, which is used to pass through the corresponding through hole 1, extend into the corresponding screw hole 1, and fix the drilling template and the auxiliary frame after the drilling template and the auxiliary frame are adjusted and calibrated; and The bolts 2 corresponding to the plurality of screw holes 2 are used to pass through the corresponding arc grooves 1, extend into the corresponding screw holes 2, and further fix the drilling template and the auxiliary frame.

2. The adjustment and correction structure according to claim 1, characterized in that: The drilling template is rectangular, the positioning hole is located in the center of the drilling template, and the arc grooves are evenly arranged on the four sides of the drilling template; Or / and, the auxiliary frame is rectangular, and the second positioning hole is located at the center of the auxiliary frame; Or / and, the first bolt is a flange bolt; the second bolt is a truncated cone bolt; Or / and, 5≤a≤8, 8≤b≤10, 3≤c≤5, 5≤d≤8.

3. The aircraft original position ear hole positioning device is characterized by: include: A positioning fixture frame, comprising two frame plates of the same structure arranged at intervals, the frame plates being connected as one at the bottom; an auxiliary plate hole is arranged at one end of the frame plate, and a guide hole is arranged at the other end; the auxiliary plate holes are concentric and constitute an auxiliary joint; the two guide holes are concentric and constitute a positioning joint; the frame plate is circumferentially provided with a plurality of screw holes three corresponding to the plurality of through holes two, for installing an adjustment and correction structure; The bolt three corresponding to the through hole two passes through the corresponding through hole two and extends into the corresponding screw hole three to connect the adjustment and correction structure to the frame plate; Two adjustment and correction structures as claimed in claim 1 or 2; the two adjustment and correction structures include an adjustment structure 1 and an adjustment structure 2; the adjustment structure 1 and the adjustment structure 2 are respectively located on the sides of two frames that are away from each other, for ensuring coaxiality; A tapered sleeve, which is used to cooperate with the ear hole to determine the correction position of the drilling template and the auxiliary frame; A drill sleeve, which is installed and connected to the drill template for subsequent cooperation with the tool; and Expansion bolts are used to pass through auxiliary joints for fixing.

4. The aircraft original position ear hole positioning device according to claim 3, characterized in that: The drill sleeve is connected to the drill template via a compression screw; One end of the drill sleeve is provided with a folded edge, and the other end extends into the first positioning hole; the outer edge of the folded edge is evenly provided with arc grooves 2; The drilling template is also circumferentially and evenly provided with screw holes four around the positioning hole one, and the screw holes four correspond to the arc groove two; the clamping screw passes through the arc groove two, extends into the screw hole four, and clamps the drill sleeve and the drilling template.

5. The aircraft original position ear hole positioning device according to claim 4, characterized in that: The aircraft original position ear hole positioning device also includes an auxiliary fixing structure, which is arranged on a side of the positioning joint away from the auxiliary joint and is used to assist in fixing the positioning joint; The auxiliary fixing structure comprises: Two auxiliary plates with the same structure and arranged at intervals; the auxiliary plates are connected to the frame plate; the auxiliary plates are provided with fixing holes, the two fixing holes are concentric and constitute a fixing joint; a supporting pad, which is disposed between the two fixing holes and is used to support the two auxiliary plates; and Bolt three passes through the fixing joint and the supporting pad, and is used to fix the supporting pad between the auxiliary plates.

6. The aircraft original position ear hole positioning device according to claim 5, characterized in that: A gasket is also provided between the supporting pad and the auxiliary plate; Or / and, the bolt three is a countersunk bolt.

7. The aircraft original position ear hole positioning device according to claim 5, characterized in that: The aircraft original position ear hole positioning device also includes: A support plate connected to the bottom of the frame plate; A support column, used to support the positioning fixture frame; and A connecting frame is used to connect the support plate and the support column.

8. A method for locating the ear holes of an aircraft in its original position, characterized in that: It is applied to the aircraft original position ear hole positioning device as claimed in claim 3, wherein the aircraft original position ear hole comprises auxiliary ear holes and ear holes to be processed which are arranged at intervals; The aircraft original position ear hole positioning method comprises: S1, moving the aircraft original position ear hole positioning device to the aircraft original position ear hole position, so that the auxiliary ear hole is close to the auxiliary joint and placed between the two auxiliary plate holes, and the ear hole to be processed is close to the positioning joint and placed between the two guide holes; S2, connecting the auxiliary joint to the auxiliary ear hole through the expansion bolt, and installing a gasket between the auxiliary ear hole and the auxiliary plate hole; turning the expansion bolt to tighten the auxiliary joint, eliminate the installation gap and fix it; S3, adjusting and correcting the adjustment structure 1, and then adjusting and correcting the adjustment structure 2; Among them, the adjustment and correction method is: S301, firstly install the drilling template on the auxiliary frame by means of the bolt 1, and retain the degree of freedom so that the drilling template can move on the auxiliary frame; S302, taking the center of the ear hole to be processed as a reference, inserting the end of the tapered sleeve with a smaller diameter into the positioning hole 1 of the drilling template of the adjustment structure 1, and passing the tapered sleeve through the ear hole to be processed; S303, adjusting the tapered sleeve until it matches the ear hole to be processed; S304, tightening the bolt 1 to fix the drilling template of the adjustment structure 1 on the auxiliary frame of the adjustment structure 1; S305, further fixing the drilling template of the adjustment structure 1 by means of the second bolt; S306, taking out the tapered sleeve; S307, fixing the drill sleeve of the adjustment structure 1 on the drill template of the adjustment structure 1, and then installing the tool rod of the tool in the drill sleeve and extending it out of the adjustment structure 2; S308, adjusting the relative positions of the drilling template of the second adjustment structure and the auxiliary frame of the second adjustment structure, so that the drill sleeve of the second adjustment structure can pass through the tool rod of the tool and be fixed on the drilling template of the second adjustment structure; S309, tightening the bolt 1 to fix the drilling template of the adjustment structure 2 on the auxiliary frame of the adjustment structure 2; S310, further fixing the drilling template of the second adjustment structure by means of the second bolt.

9. The method for locating the original position ear hole of an aircraft according to claim 8, characterized in that: The aircraft original position ear hole positioning device also includes an auxiliary fixing structure, which is arranged on a side of the positioning joint away from the auxiliary joint and is used to assist in fixing the positioning joint; The auxiliary fixing structure comprises: Two auxiliary plates with the same structure and arranged at intervals; the auxiliary plates are connected to the frame plate; the auxiliary plates are provided with fixing holes, the two fixing holes are concentric and constitute a fixing joint; a supporting pad, which is disposed between the two fixing holes and is used to support the two auxiliary plates; and Bolt three, which passes through the fixing joint and the supporting pad, and is used to fix the supporting pad between the auxiliary plates; The aircraft original position ear hole positioning method also includes: Before S1, remove the bolt 3 and the support pad; After S1, the support block is reinstalled between the auxiliary plates by bolt three.

10. The method for locating the original position ear hole of an aircraft according to claim 9, characterized in that: The aircraft original position ear hole positioning device also includes: A support plate connected to the bottom of the frame plate; A support column, used to support the positioning fixture frame; and A connecting frame, which is used to connect the support plate and the support column; The aircraft original position ear hole positioning method also includes: After S1, the support plate is connected to the support column, and the bottom end of the support column is placed on the support platform.

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