A radome replacement device and method

Abstract

The application provides an antenna cover replacement device, comprising: a lead hole base with a thin end and a thick end, the thin end of the lead hole base being provided with a body support nut limiting hole; a hollow screw installed in the body support nut limiting hole, the hollow screw being used for installing the lead hole base on a body structure; a drill template having a drill template hole coaxial with the body support nut limiting hole; wherein the drill template is connected with the lead hole base; a drill jig arranged in the drill template hole, the drill jig being used for drilling a hole on the antenna cover; and a process screw connected with the hollow screw through the drill template hole, the process screw being used for fixing the antenna cover on the body structure; meanwhile, the application also provides an antenna cover replacement method; and the application is convenient to use and has high hole drilling accuracy.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aircraft assembly manufacturing, and particularly relates to an antenna cover replacement device and method. BACKGROUND

[0002] The antenna cover is one of important components of an aircraft, is a structure for protecting an antenna system from external environment, and includes, but is not limited to, wind, rain, hail, sand, solar radiation, severe cold and heat, and the like. In addition, the antenna cover can reduce wear, corrosion and aging of the antenna system, and prolong the service life of the antenna system. The antenna cover has good electromagnetic wave penetration characteristics in electrical performance, so as to ensure the working performance of the antenna system.

[0003] In the process of scientific research and production, task flight and aircraft overhaul, the antenna cover is scrapped due to unqualified test parameters of the antenna cover body or damage of the antenna cover caused by external force impact. Currently, a new antenna cover is replaced by the following process method: removing the old antenna cover, removing the skin surface pressure adhesive layer, removing the support plate nut on the aircraft structure, clamping the new antenna cover according to the assembly hole positioning, drilling holes from the inside of the aircraft body to the antenna cover, disassembling the antenna cover, twice riveting the support plate nut, trial assembling the antenna cover and adjusting the state, disassembling the antenna cover, cleaning the excess, antenna cover pressure adhesive shaping, and antenna cover and aircraft body screwing.

[0004] When the rivet on the support plate nut is removed, the rivet hole is enlarged, the connection strength of the second riveting is sharply reduced, and the production cost is increased due to the replacement of the support plate nut. When holes are drilled from the inside of the aircraft body to the outside of the antenna cover, the drill bit will scratch the aircraft bolt hole wall. In a small space, the guide hole cannot be drilled vertically to the antenna cover. If the hole is drilled from the outside of the antenna cover, the accuracy is low, the error is large, the hole drilling is difficult, and the risk is high. The production cycle is long by using the replacement method, and the excess in the aircraft is not easy to control. SUMMARY

[0005] The application avoids the insufficient connection strength caused by the second disassembly of the support plate nut in the process of replacing the new antenna cover, avoids the scratching of the aircraft bolt hole wall when the hole is drilled, improves the hole drilling quality on the antenna cover, and provides an antenna cover replacement assembly device and method which are convenient to use and have high hole drilling accuracy.

[0006] In a first aspect, the application provides an antenna cover replacement device, which comprises:

[0007] The hole guide base has a thin end and a thick end, and the thin end of the hole guide base is provided with an aircraft support plate nut limiting hole.

[0008] A hollow screw is installed in the body bracket nut limiting hole, and the hollow screw is used to install the guide hole base on the body structure; wherein the sum of the thickness of the thin end of the guide hole base and the thickness of the head of the hollow screw is equal to the thickness of the body surface rubber layer; the hollow screw is coaxial with the body bracket nut limiting hole;

[0009] A drill template is provided with a drill hole, and the drill hole is coaxial with the body bracket nut limiting hole; wherein the drill template is connected with the guide hole base;

[0010] A drill is arranged in the drill hole, and the drill is used to drill holes on the radome;

[0011] A process screw is connected with the hollow screw through the drill hole, and the radome is fixed on the body structure.

[0012] Preferably, the thick end of the guide hole base is provided with a threaded hole, the drill template also has a thick end and a thin end, the drill hole is arranged in the thin end of the drill template, and the thick end of the drill template is provided with a through hole.

[0013] Preferably, the device further comprises:

[0014] A gasket is arranged between the threaded hole and the through hole, and the gasket is used to adjust the drill template to ensure that the drill template is parallelly attached to the outer surface of the radome.

[0015] Preferably, the device further comprises:

[0016] A stud is connected with the threaded hole through the through hole at one end;

[0017] A nut is arranged at the other end of the stud, and the nut is used to lock the drill template on the guide hole base.

[0018] Preferably, the device further comprises:

[0019] A bushing is arranged on the stud.

[0020] In a second aspect, the application also provides a radome replacement method, and the method comprises:

[0021] Hoisting a new radome onto a working bracket;

[0022] Slowly moving the new radome to the surface of the body structure 50 cm away, adjusting the position of the assembly hole of the new radome, adding a 3mm plastic gasket between the new radome and the body surface, and fixing the new radome on the body surface with a process bolt;

[0023] The stud is screwed on the pilot hole base, the height of the drilling template is adjusted by the gasket to ensure that the drilling template is parallel to the new radome outer surface, the drilling template is installed on the stud, the extension amount of the thread is adjusted by the bushing, and the nut is tightened. The fitting surface of the product needs to be protected by adhesive tape;

[0024] The installation position accuracy and bolt margin of the new radome are checked, the bracket is loosened and readjusted until the margin is appropriate.

[0025] A φ4mm alloy steel drill bit is used to drill the new radome pilot hole in the drilling template hole on the drilling template, and then the drilling template is tightened on the pilot hole device with M4 light rod bolts. All bolt pilot holes are made in the same way.

[0026] The bracket is loosened, the new radome and the pilot hole device are removed, the bolt hole is reamed and drilled with a φ4mm guide rod reamer and reamer according to the technical conditions, and then deburring and chamfering are performed.

[0027] The fitting surface and the surrounding environment are cleaned, the new radome and the body structure surface are pressed and glued, the temperature for applying glue is 15-30°C, the relative humidity is 35-80%, and the glue layer is shaped when the hardness reaches Shore hardness 30.

[0028] The new radome is screwed onto the body structure surface with product bolts to complete the replacement of the radome.

[0029] Preferably, before the new radome is hoisted onto the working bracket, it further comprises:

[0030] The scrapped radome is removed, and the glue layer on the body structure surface is cleaned with a glue scraping plate;

[0031] The hollow screw is fixed to the surface of the body structure through the pilot hole base with a screwdriver, and adhesive tape is applied to the fitting surface of the product to protect the product surface from being scratched. The pilot hole device is placed along the normal direction of the radome;

[0032] The outer packaging of the new radome is opened, its appearance is inspected, the history book is checked, and the non-construction surface is protected.

[0033] Preferably, the method further comprises:

[0034] Before drilling, the operator needs to wear a one-piece dustproof suit and a dustproof mask to avoid harm to the human body caused by fibers.

[0035] The beneficial technical effects of the present application are:

[0036] The application provides a hole guiding device and a method for replacing a radome without dismounting a bracket nut inside a body structure, a hole guiding base, a hollow screw, a stud and a drill template, a drill template and a drill jig are matched as H7 / g6, coaxialities of shaft parts are all ≯0.01mm, perpendicularity of the stud and the hole guiding base after installation is ≯0.01mm, and finally coaxiality of the hollow screw axis and the drill jig axis after assembly is ≯0.02mm. The use of the drill jig to drill a φ4mm initial hole better ensures perpendicularity and coaxiality of the bolt hole, alloy steel cutters are used for drilling the radome bolt hole, the service life of the cutters is improved, and the quality of the bolt hole is improved.

[0037] The research scheme of the radome replacement method solves the quality defects of insufficient bolt connection strength, bolt hole wall scratch and low accuracy of line drawing and hole guiding in a narrow space caused by secondary dismounting of the bracket nut, improves the replacement efficiency of the radome, reduces the production cost, and improves the installation quality of the radome. BRIEF DESCRIPTION OF DRAWINGS

[0038] Figure 1 It is a structural exploded view of the hole guiding device;

[0039] Figure 2 It is a structural view of the hole guiding device;

[0040] Figure 3 It is a structural cross-sectional view of the hole guiding device;

[0041] Figure 4 It is a use structure schematic view of the radome replacement process;

[0042] Figure 5 It is a use structure local enlarged view of a single hole guiding device;

[0043] Figure 6 It is a use structure cross-sectional view of the radome replacement process;

[0044] Figure 7 It is a use structure local cross-sectional enlarged view of the hole guiding device;

[0045] Wherein: 1, hole guiding base; 2, gasket; 3, drill template; 4, stud; 5, bushing; 6, nut; 7, process screw; 8, drill jig; 9, hollow screw; 10, radome; 11, body structure; 12, bracket nut. DETAILED DESCRIPTION

[0046] The application belongs to the technical field of aviation manufacturing and assembly, and relates to an assembly coordination technology for replacing a radome. The application aims to ensure coaxiality requirements of radome bolt holes, body structure bolt holes and bracket nuts, and formulates a corresponding technical scheme, including determination of the technical scheme, design of a hole guiding device and formulation of a process flow.

[0047] The hollow screw of the hole guiding device, the hole guiding base, the drilling template, and the drilling jig ensure the coaxiality requirement of the bolt hole of the radome and the bolt hole of the machine body structure, the bolt hole is reamed according to the technical condition by the reaming drill with a diameter of 4mm and the reamer after the initial hole is drilled, and the assembly quality requirement of the radome is met.

[0048] The method for replacing the radome is changed, the coordination accuracy of the bolt hole of the radome and the machine body structure is improved, the technical scheme is reasonable, the process method is feasible, and the hole guiding device and the assembly scheme can meet the technical requirement of the radome replacement through practice verification.

[0049] The radome is assembled through the following technical scheme.

[0050] When a new radome is replaced, the problems of secondary disassembly of the supporting plate nut and the scratch of the hole wall and the difficulty in hole drilling in a narrow space are solved by arranging a special hole guiding device between the machine body structure and the radome.

[0051] As shown in Figure 1 , Figure 2 , Figure 3 The special hole guiding device comprises nine parts, namely a hole guiding base 1, a gasket 2, a drilling template 3, a stud 4, a bushing 5, a nut 6, a process screw 7, a drilling jig 8, and a hollow screw 9.

[0052] The hole guiding base 1 is a stepped structure part made of 45# steel through mechanical processing, the thickness of the thin end is 1.5mm, there is a φ8H7mm hole in the center of the front surface, the distance from the end head edge is 10mm, the thickness of the thick end is 13mm, there are two threaded holes M6 in the center of the front surface, the distance between the two holes is greater than 30mm, the stability of the drilling template can be ensured, and the perpendicularity of the threaded hole and the end surface is ≯0.01mm.

[0053] The gasket 2 can be selected according to the different thicknesses of the radomes, and is used for adjusting the drilling template to ensure parallel fitting with the outer surface of the radome.

[0054] The drilling template 3 is a stepped structure part made of 45# steel through mechanical processing, the thickness of the thin end is 10mm, there is a φ10H7 hole in the center of the front surface, the distance from the end head edge is 10mm, the hole is convenient for the smooth insertion of the working part of the drilling jig and does not shake, the perpendicularity of the hole and the end surface is ≯0.01mm, the thickness of the thick end is 20mm, there are two holes with a diameter of φ6H7 in the center of the front surface, the hole positions are matched with the hole guiding base 1, and the coaxiality of the axis of the hollow screw and the axis of the drilling jig after assembly is ≯0.02mm.

[0055] Wherein, the stud 4 is a shaft part, the two ends are made of m6 thread, the middle guiding part is φ6g6 in diameter, and the material is 45 steel processed by mechanical processing and quenched. After the two studs are screwed with the drill jig base plate, the drill jig plate can slide along the axis of the stud.

[0056] Wherein, the thickness of the bushing 5 is selected according to the protruding amount of the stud rod after the drill jig plate is installed, so that the drill jig plate can be clamped after the nut 6 is tightened.

[0057] Wherein, the nut 6 is a process nut of M6, which can be tightened or disassembled by means of a ratchet wrench.

[0058] Wherein, the process screw 7 is an appropriate M4 screw with a light rod according to the thickness of the hole device and the antenna cover, which can ensure that the antenna cover can be fixed and clamped on the machine structure.

[0059] Wherein, the drill jig 8 is a stepped shaft part, the small diameter is matched with the drill jig hole diameter of the drill jig plate, which is φ10H7 / g6, the thickness is 10mm, the diameter of the large diameter part is φ10mm, the side surface is processed by knurling, which is convenient for operators to hold and process, the thickness is 8mm, a φ4mm through hole is made at the center of the drill jig, and the coaxiality of the axis is ≯0.01mm.

[0060] Wherein, the hollow screw 9 is a stepped shaft part, the tail of the screw is threaded, the size is matched with the size of the machine structure support plate nut, the length of the screw is selected to ensure that the hole base can be accurately fixed and clamped on the surface of the machine structure, the diameter of the head of the screw is φ16mm, the thickness is 1.5mm, and the sum of the thicknesses after the screw is screwed with the hole base is just the thickness of the adhesive layer, a depth 1mm through slot is made at the center of the end face, which can be tightened or disassembled by means of a screwdriver. An M4 threaded hole is made at the center of the screw, so that the process screw can be smoothly screwed in and fixed.

[0061] In other embodiments of the present application, a process flow provided by the present application is as follows:

[0062] a. Screw the hole base to the surface of the machine structure with the hollow screw;

[0063] b. Position the antenna cover on the surface of the hollow screw according to the assembly hole of the antenna cover;

[0064] c. Assemble the hole device;

[0065] d. Make a φ4mm initial hole on the antenna cover and fix it with the process screw;

[0066] e. After the hole is made, disassemble the antenna cover and the hole device;

[0067] f. Expand the initial hole of the antenna cover to the final hole with an expansion drill with a φ4mm guide rod according to the drawing and technical requirements.

[0068] This invention provides a pre-drilling device and a method for replacing an radome without removing the internal support plate nuts of the fuselage structure. The pre-drilling base and hollow screw, stud and drill template, and drill template and drill jig all have an H7 / g6 fit. The coaxiality of the shaft parts is ≤0.01mm, and the perpendicularity of the stud to the pre-drilling base after installation is ≤0.01mm. Ultimately, the coaxiality between the hollow screw axis and the drill jig axis after assembly is guaranteed to be ≤0.02mm. Using a drill jig to drill a φ4mm initial hole better ensures the perpendicularity and coaxiality of the bolt holes. Alloy steel tools are used to drill the radome bolt holes, which improves tool life and the quality of the bolt holes.

[0069] The research scheme of the antenna radome replacement method of the present invention solves the quality defects caused by the secondary disassembly and assembly of the support plate and nut, such as insufficient bolt connection strength, scratches on the bolt hole wall, and low accuracy of drawing lines and drilling in narrow spaces. It improves the replacement efficiency of the antenna radome, reduces production costs, and improves the installation quality of the antenna radome.

[0070] In other embodiments of this application, such as Figure 1 As shown, the present invention provides a special drilling device, which consists of nine parts: a drilling base 1, a gasket 2, a drill template 3, a stud 4, a bushing 5, a nut 6, a process screw 7, a drill jig 8, and a hollow screw 9.

[0071] The pilot hole base 1 is a stepped structure part, made of 45 steel and machined. Its thin end is 1.5mm thick, and there is an 8mm hole at the center of the front side, 10mm from the edge of the end. The thickness of the thick end is 13mm. There are two M6 threaded holes at the center of the front side, and the distance between the two holes is greater than 30mm, which can ensure the stability of the drilling template. The perpendicularity of the threaded hole to its end face is ≤0.01mm.

[0072] Among them, the shim 2 can be selected according to the different thicknesses of the radome, and is used to adjust the drill template to ensure that it is parallel and in contact with the outer surface of the radome.

[0073] The drill template 3 is a stepped structure part, made of 45 steel and machined. Its thin end is 10mm thick and has a φ10H7 hole at the center of the front side. The hole is 10mm away from the edge of the end, which facilitates the smooth insertion of the working part of the drill template without shaking. The perpendicularity of the hole to its end face is ≤0.01mm. The thickness of the thick end is 20mm. There are two holes with a diameter of φ6H7 at the center of the front side. The hole positions are matched with the pilot hole base 1 to ensure that the coaxiality of the hollow screw axis and the drill template axis is ≤0.02mm after assembly.

[0074] Among them, stud 4 is a shaft-type part with m6 threads at both ends and a diameter of φ6g6 for the middle guide part. It is made of 45 steel, machined and then quenched. After the two studs are screwed to the drill jig base plate, the drill jig template can slide along the stud axis.

[0075] The thickness of bushing 5 is selected based on the amount of protrusion of the stud rod after the drill template is installed, ensuring that the drill template can be clamped after the nut 6 is tightened.

[0076] Nut 6 is an M6 process nut, which can be tightened or loosened with the aid of a ratchet wrench. Process screw 7 is an M4 screw with a smooth rod, selected according to the thickness of the interlayer of the pilot hole device and the radome, to ensure that the radome can be fixedly clamped to the body structure.

[0077] Among them, the drill jig 8 is a stepped shaft part. Its minor diameter matches the drill jig hole diameter of the drill template with a size of φ10H7 / g6. It has a thickness of 10mm and a major diameter of φ10mm. The sides are knurled for easy hand-held processing by the operator. It has a thickness of 8mm and a φ4mm through hole at the center of the drill jig. The coaxiality of its axis is ≯0.01mm.

[0078] Among them, the hollow screw is a 9-step stepped shaft part. The screw tail is threaded, and its size matches the size of the nut on the machine body structure. The length of the screw must be selected to ensure that the pilot hole base is accurately fixed and clamped to the surface of the machine body structure. The screw head diameter is φ16mm and the thickness is 1.5mm. After screwing with the pilot hole base, the sum of the thicknesses is exactly the thickness of the adhesive layer. A 1mm deep through groove is cut on its end face through the center, which can be tightened or loosened with the aid of a screwdriver. The center of the screw has an M4 threaded through hole to facilitate the easy screwing of the process screw for fixation.

[0079] Please see Figure 4 , Figure 5 , Figure 6 , Figure 7 As shown, in one feasible implementation, the specific operation process provided by this application is as follows:

[0080] ① Manufacture all parts of the pilot hole device according to the drawings and technical specifications;

[0081] ② Remove the scrapped antenna cover and clean the adhesive layer on the surface of the fuselage structure with a scraper.

[0082] ③ Use a screwdriver to pass the hollow screw through the pilot hole base and fix it to the surface of the machine body structure. The contact surface with the product should be protected with tape to avoid scratching the product surface. The pilot hole device should be placed along the normal direction of the radome (do not install it in the mounting holes of the radome).

[0083] ④ Open the outer packaging of the new radome, inspect its appearance, check the record book, protect the non-construction surface, and then hoist the radome onto the work bracket.

[0084] ⑤ Slowly move the radome to a position 50cm from the surface of the fuselage structure, adjust the position of the radome mounting holes, add 3mm plastic shims between the radome and the fuselage surface, and fix the radome to the fuselage surface with process bolts.

[0085] ⑥ Screw the studs into the pilot hole base, adjust the height of the drill template with shims to ensure that the drill template is parallel and in contact with the outer surface of the radome, install the drill template on the studs, adjust the thread extension with bushings, and tighten it with nuts. The contact surface with the product needs to be protected with tape.

[0086] ⑦ Check the accuracy of the antenna radome's installation position and the bolt spacing. Loosen the brackets and readjust any parts with improper spacing until the spacing is correct.

[0087] ⑧ Before drilling, the operator must wear a full-body dust suit and a dust mask to avoid damage to the body from fibers;

[0088] 9. Using a φ4mm alloy steel drill bit, drill the initial hole of the radome in the drill jig hole on the drill template. Then, use an M4 bolt with a smooth rod to tighten the drill jig onto the pilot hole device. Use the same method to make all the initial holes for the bolts.

[0089] ⑩ Loosen the bracket, remove the antenna cover and the hole-opening device, and use a 4mm guide rod reamer and a reamer to ream the bolt holes according to the technical specifications. Then deburr and chamfer.

[0090] 11. Clean the bonding surface and surrounding environment, apply adhesive to the surface of the antenna radome and the body structure, the temperature of the adhesive application is 15℃~30℃, the relative humidity is 35%~80%, and the adhesive layer can be shaped only when the hardness of the adhesive reaches Shore hardness 30.

[0091] 12. Use product bolts to screw the radome onto the surface of the machine body structure to complete the replacement of the radome.

Claims

1. A method for replacing an radome, comprising an radome replacement device, the device comprising: A pilot hole base has a thin end and a thick end, and an organic support plate nut limiting hole is provided on the thin end of the pilot hole base; A hollow screw is installed in the limiting hole of the machine body plate nut. The hollow screw is used to install the pilot hole base on the machine body structure. The thickness of the thin end of the pilot hole base and the thickness of the head of the hollow screw are equal to the thickness of the adhesive layer on the surface of the machine body. The hollow screw is coaxial with the limiting hole of the machine body plate nut. A drilling template has a drilling hole, which is coaxial with the limiting hole of the machine body support plate nut; wherein, the drilling template is connected to the pilot hole base; A drill jig, disposed in the drill jig hole, the drill jig being used to drill holes in the radome; The process screw passes through the drill hole and connects with the hollow screw to fix the radome to the body structure; The thick end of the pilot hole base is provided with a threaded hole, and the drill template also has a thick end and a thin end. The drill hole is provided at the thin end of the drill template, and the thick end of the drill template is provided with a through hole. A shim is disposed between the threaded hole and the through hole. The shim is used to adjust the drill template to ensure that the drill template is parallel and in contact with the outer surface of the radome. A stud, one end of which passes through the through hole and connects to the threaded hole; A nut is provided at the other end of the stud, and the nut is used to lock the drill template onto the pilot hole base; A bushing is provided on the stud; The method is characterized by comprising: Hoist the new radome onto the work bracket; Slowly move the new radome to a position 50cm from the surface of the fuselage structure, adjust the position of the mounting holes of the new radome, add 3mm plastic shims between the new radome and the surface of the fuselage, and fix the new radome to the surface of the fuselage with process bolts. Screw the studs into the pilot hole base, adjust the height of the drill template with shims to ensure that the drill template is parallel and in contact with the outer surface of the new radome, install the drill template on the studs, adjust the thread extension with bushings, and tighten it with nuts. The contact surface with the product needs to be protected with tape. Check the accuracy of the new radome's installation position and the bolt spacing. Loosen the brackets and readjust any parts with improper spacing until the spacing is correct. Using a φ4mm alloy steel drill bit, drill a new initial hole for the radome in the drill jig hole on the drill template. Then, use an M4 bolt with a smooth rod to tighten the drill jig onto the pilot hole device. Use the same method to make all the initial holes for the bolts. Loosen the bracket, remove the new antenna cover and the pilot hole device, and use a 4mm guide rod reamer and a reamer to enlarge the bolt holes according to the technical specifications. Then deburr and chamfer. Clean the bonding surface and surrounding environment, apply adhesive to the new radome and the surface of the body structure, the temperature of the adhesive application is 15℃~30℃, the relative humidity is 35%~80%, and the adhesive layer can be shaped only when the hardness of the adhesive reaches Shore hardness 30. Use the product bolts to screw the new radome onto the surface of the aircraft structure to complete the radome replacement.

2. The method according to claim 1, characterized in that, Before hoisting the new radome onto the work bracket, the process also includes: Remove the scrapped antenna cover and clean the adhesive layer on the surface of the fuselage structure with a scraper. Use a screwdriver to pass the hollow screw through the pilot hole base and fix it to the surface of the body structure. The contact surface with the product should be protected with tape to avoid scratching the product surface. The pilot hole device should be placed along the normal direction of the radome. Open the outer packaging of the new radome, inspect its appearance, check its history, and protect the non-construction surfaces.

3. The method according to claim 2, characterized in that, The method further includes: Before drilling, operators must wear full-body dust suits and dust masks to avoid damage to the body from fibers.

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