Damaged airplane repairing tool

Abstract

The invention discloses a damaged aircraft repairing tool, which belongs to the technical field of aircraft maintenance and comprises a ground platform, a jack, a cabin clamping and fixing tool, an inclined frame fixing tool, a lower half frame appearance fixing tool, a front undercarriage supporting tool, a main undercarriage supporting tool and a 38 frame fixing tool. After a ground platform is leveled, a jack is used for adjusting an airplane to be in a horizontal state, a front undercarriage supporting tool and a main undercarriage supporting tool are used for replacing the jack to support the airplane to keep the airplane in the horizontal state, a 38-frame fixing tool is used for supporting the 38-frame position of a rear fuselage, and an inclined frame fixing tool is used for fixing an inclined frame structure. The lower half frame appearance fixing tool is used for fixing a lower equipment cabin skin and a stringer, and the cabin clamping and fixing tool is used for clamping and fixing an aircraft cabin opening frame beam, a rear wall plate, a central floor and a four-frame upper half frame. The device has the three functions of aircraft horizontal adjustment, aircraft position fixing and supporting and aircraft cockpit replacement component clamping and fixing at the same time, and an aircraft can be kept in a horizontal parking state in the repairing process.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft maintenance, and in particular relates to a damaged aircraft repair tool. Background Art

[0002] During the repair process of a certain type of aircraft, the aircraft must be kept in a horizontal parking state. During the removal and replacement of aircraft cabin components, the installation position of each replacement component must be clamped and fixed, and the position must not be shifted due to external forces.

[0003] In order to ensure the smooth progress of repairs on a certain type of aircraft, it is necessary to design a set of combined tooling that has three functions: aircraft horizontal adjustment, aircraft position fixation support, and aircraft cabin component clamping and fixation. Summary of the invention

[0004] In order to solve the above problems existing in the background technology, the present invention provides a damaged aircraft repair tool.

[0005] The technical solution adopted by the present invention is as follows:

[0006] A damaged aircraft repair tool, comprising a ground platform, a jack 1, a cockpit clamping and fixing tool 4, an inclined frame fixing tool 5, a lower half frame shape fixing tool 6, a front landing gear supporting tool 7, a main landing gear supporting tool 8 and a 38 frame fixing tool 9. The ground platform is used for the horizontal installation of the entire damaged aircraft repair tool. The jack 1 is installed on the ground platform to adjust the overall level of the aircraft. The front landing gear supporting tool 7 and the main landing gear supporting tool 8 replace the jack 1 after the aircraft is adjusted to be level, and the aircraft is rigidly bound to the ground platform to avoid changes in the position of the aircraft. The 38 frame fixing tool 9 is used to support the position of the rear fuselage 38 frame after the aircraft is adjusted to be level. The inclined frame fixing tool 5 is used to fix the inclined frame structure 1 after the aircraft is adjusted to be level, to ensure that the remaining structure of the radar cabin is stable and relatively positioned after the upper half of the 4 frames are disassembled. The position of the nose cone axis will not deviate, the lower half frame shape fixing tool 6 is used for the inner bracket to lift and fix the lower equipment compartment skin and long stringers, to ensure that after the cockpit floor, the left and right side panels of the lower equipment compartment and the lower half frame of the (4-9) frame are disassembled, they can still be stably fixed in the position before disassembly, and the lower skin contour will not be deformed or the position will change. The cockpit clamping and fixing tool 4 is installed above the upper and lower half frame shape fixing tool 6 of the three-dimensional flexible welding platform 3, and is used for clamping and fixing the aircraft cockpit frame beam, rear wall panel, central floor and the upper half frame of the 4 frames after the aircraft is adjusted to the level.

[0007] The specific structure of the damaged aircraft repair tool is as follows:

[0008] The ground platform uses two welding platforms, a heavy welding platform 2 and a three-dimensional flexible welding platform 3, according to the different positions of the parked aircraft and the tooling carried.

[0009] The heavy-duty welding platform 2 is integrally cast, with three triangularly arranged ones for supporting the fixing jack 1, 38 frame fixing tool 9, main landing gear support tool 8 and front landing gear support tool 7; the three-dimensional flexible welding platform 3 is integrally cast, with one for supporting the lower half frame shape fixing tool 6, the inclined frame fixing tool 5 and the cockpit clamping fixing tool 4. The outer surface of each heavy-duty welding platform 2 and three-dimensional flexible welding platform 3 is evenly spaced with a number of mounting holes; the bottom surface of each heavy-duty welding platform 2 and three-dimensional flexible welding platform 3 is evenly distributed with a number of leveling points 10, the top of the leveling point 10 is installed in the mounting hole, and the bottom is provided with anchor bolts, and the anchor bolts are adjusted through the mounting holes to ensure the overall leveling of the ground platform.

[0010] There are three jacks 1 in total, which are fixed on three heavy welding platforms 2 respectively, and are used to adjust the level of the aircraft.

[0011] After the aircraft is adjusted to be level, the front landing gear support tool 7 replaces the jack 1 at the front landing gear and is fixed to the front landing gear mounting point of the aircraft 16 frame to support the fuselage 16 frame.

[0012] The front landing gear support tooling 7 includes a frame connecting fork 11, a column 12, a reinforcing rib 13, a flange 14 and a diagonal tie rod 15. The flange 14 is located at the bottom and is used to be fixedly connected to the heavy welding platform 2. The column 12 is fixed at the center of the upper surface of the flange 14, and its height is set according to the actual support height after the aircraft is adjusted horizontally. Four reinforcing ribs 13 are fixedly installed at the lower part of the column 12, and a supporting foot is installed at the bottom of the reinforcing rib 13 to adjust the gap when the fixed tooling is installed. The diagonal tie rod 15 is installed on the column 12, one end of which is connected to the column 12 through a half clamp structure, and the other end refers to the installation form of the aircraft landing gear actuator through the end head The threaded pin and nut are connected and fastened to the original landing gear actuator connection point to ensure that the front landing gear support tooling 7 does not move with the landing gear connection point as the axis; the frame connecting fork 11 is fixed to the top of the column 12, and is arranged as an inverted triangular support structure with a horizontal top according to the 16-frame shape. Referring to the front landing gear connection method, a groove is arranged on the top of the frame connecting fork 11 to match the structure of the aircraft's front landing gear installation point, and pin shaft sleeves are arranged on both sides of the groove. Adjustment bolts (left-handed and right-handed threads) are installed in the pin shaft sleeves to be fastened to the front landing gear installation point on the aircraft 16 frame, wherein the adjustment bolts are manufactured according to the size of the original aircraft assembly bolts to ensure that the gap is the same as the original state.

[0013] The main landing gear support fixtures 8 are provided with two symmetrical arrangements, which are used to replace the two jacks 1 at the main landing gear to support the fuselage, and the top is fixed to the main landing gear installation point of the aircraft.

[0014] The main landing gear support fixture 8 also includes a frame connecting fork 11, a column 12, a reinforcing rib 13, a flange 14 and a diagonal rod 15, wherein the column 12, the flange 14 and the diagonal rod 15 are the same as the front landing gear support fixture 7, the reinforcing rib 13 is connected between the column 12 and the flange 14, the frame connecting fork 11 is fixed to the top of the column 12, and is set to a triangular structure with reference to the main landing gear connection method, and the mounting surface is an inclined surface. The mounting surfaces of the frame connecting forks 11 on the two main landing gear support fixtures 8 are opposite, and grooves are made at the mounting surfaces to match the structure of the aircraft main landing gear mounting point. Pin shaft sleeves are arranged on both sides of the grooves, and adjusting bolts (left-handed and right-handed threads) are installed in the pin shaft sleeves to be fastened to the aircraft main landing gear mounting point, wherein the adjusting bolts are manufactured according to the assembly bolt size of the original aircraft to ensure that the gap is the same as the original aircraft state.

[0015] The 38 frame fixing tool 9 is used to support the position of the rear fuselage 38 frame after the aircraft is adjusted to the level, and includes a wooden support 16, a main frame 17, and an adjusting screw 18.

[0016] The bottom of the main frame 17 is a mounting plate for fixed installation on the ground, a frame structure is fixed on the mounting plate, a support seat is arranged on the top of the frame structure for installing the wooden support 16; there are two wooden support 16, which are installed side by side on the support seat, and the top thereof is arc-shaped, and the size of the arc is set according to the shape of the aircraft air inlet skin. A double layer of protection of canvas and felt is installed on the top of the wooden support 16 to prevent damage to the aircraft air inlet skin, and a U-shaped groove structure is used to fix the wooden support 16 around to prevent shaking and displacement of the wooden support 16; a sleeve is provided on the frame structure at the bottom of the wooden support 16, and an adjusting screw 18 is installed in the sleeve to meet the height and angle adjustment on the XZ axis plane, and is locked after being adjusted into place to prevent sliding back and other phenomena from damaging the existing position of the aircraft.

[0017] The inclined frame fixing tool 5 is used to fix the inclined frame structure after the aircraft is adjusted to the level, to ensure that the remaining structure of the radar cabin is stable after the upper half of the frame 4 is disassembled, and the relative position and the position of the nose cone axis will not deviate, and its bottom is fixedly connected to the three-dimensional flexible welding platform 3.

[0018] The inclined frame fixing tool 5 includes a frame connecting plate 20, a support frame 19, and a locking pin; the frame connecting plate 20 is arranged in a ring shape to reserve a working space, and the frame connecting plate 20 is fastened to the inclined frame of the aircraft 1 by a locking pin, and the position of the locking pin mounting hole is set according to the actual position of the inclined frame of the aircraft 1; the flange structure is installed at the lower end of the support frame 19 and is fixedly connected to the three-dimensional flexible welding platform 3, and its top is fixed to the frame connecting plate 20, and the inclined surface where the support frame 19 and the frame connecting plate 20 are installed is set according to the inclination of the inclined frame of the aircraft 1 to ensure the original installation position of the aircraft, and the support frame 19 reserves a working position while ensuring overall stability.

[0019] The lower half frame shape fixing tool 6 is installed next to the inclined frame fixing tool 5 on the three-dimensional flexible welding platform 3, and is used for the inner bracket to lift and fix the lower equipment compartment skin and long stringers to ensure that after the cockpit floor, the left and right side panels of the lower equipment compartment and the lower half frame of the (4-9) frame are disassembled, they can still be stably fixed in the position before disassembly, and the lower skin contour will not be deformed or the position will change. The lower half frame shape fixing tool 6 includes 4 frame brackets 21, 9 frame brackets 22, a base frame 24, a mouth frame beam bracket 23, a bow clamp and an inclined tie rod; the base frame 24 is a frame structure, which reserves a working position while ensuring overall stability, and a flange structure is provided at the bottom thereof for fixed connection with the three-dimensional flexible welding platform 3; the 4 frame brackets 21 and the 9 frame brackets 22 are both installed on the top of the base frame 24, and the two are arranged in parallel, and there are two mouth frame beam brackets 23, which are supported side by side between the 4 frame brackets 21 and the 9 frame brackets 22, and the upper surfaces of the 4 frame brackets 21, the 9 frame brackets 22 and the two mouth frame beam brackets 23 are It is an arc surface, which is set according to the shape of the aircraft air inlet skin. A 1mm thick rubber plate is bonded to the arc surface to prevent damage to the aircraft air inlet skin. The 4-frame bracket 21, the 9-frame bracket 22 and the two mouth frame beam brackets 23 are provided with bow clamps, which are detachable structures for clamping the brackets and the skin. The installation positions of the bow clamps are all in the grooves at the aircraft skin cover, and the rubber vulcanization process is carried out at the clamping points, which will not cause damage to the skin; the diagonal tie rods are installed at the chassis columns under the 4-frame brackets 21 and the 9-frame brackets 22. The diagonal tie rods are detachable structures, which can reserve working positions for repair work while stabilizing the tooling structure.

[0020] The cockpit clamping and fixing tool 4 is installed above the upper and lower frame shape fixing tool 6 of the three-dimensional flexible welding platform 3, and is used to clamp and fix the aircraft cockpit frame beam, rear wall panel, central floor and the upper half of the four frames after the aircraft is adjusted to the level.

[0021] The cockpit clamping fixture 4 is a three-axis movable gantry structure, including a gantry frame 25, an X-axis adjustment beam 27, a Y-axis adjustment beam 28, a lifting mechanism 29 and a protective sling 26; the gantry frame 25 is a detachable structure, and a bottom plate is installed at the bottom of the gantry column for fixed connection with the three-dimensional flexible welding platform 3, and a reinforcing rib plate is arranged between the bottom plate and the gantry column; the Y-axis adjustment beam 28 is provided with two, which are installed in parallel between the gantry columns, and the installation height of the two, that is, along the Z-axis direction, can be adjusted according to the actual position requirements; the X-axis adjustment beam 27 is provided with two, which are installed in parallel on the two Y-axis The X-axis adjustment beam 27 and the Y-axis adjustment beam 28 are connected to each other, and the installation position can be adjusted along the Y-axis adjustment beam 28, forming an adjustment mechanism for the XY-axis plane. The X-axis adjustment beam 27 and the Y-axis adjustment beam 28 together form an XYZ three-dimensional mobile structure; the hoisting mechanism 29 is provided in plurality, the top of which is fixedly mounted on the X-axis adjustment beam 27, and the installation position can be adjusted along the X-axis adjustment beam 27, and the bottom is a C-type clamp, which is used to clamp and fix the parts that need to be replaced and positioned in the cockpit at the installation position, and the repair process is ensured to be carried out in sequence by adjusting the hoisting position; the two ends of the protective sling 26 are connected to the crossbeam of the gantry frame 25, which is used to fix the nose.

[0022] The beneficial effects of the present invention are as follows: the present invention has three functions: horizontal adjustment of the aircraft, fixed support of the aircraft position, and clamping and fixing of aircraft cabin replacement components. The present invention can keep the aircraft in a horizontal parking state during the repair process. At the same time, during the process of disassembly and replacement of aircraft cabin components, each replacement component can be clamped and fixed in the installation position without position displacement due to external forces. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 This is the overall schematic diagram of the damaged aircraft repair tooling.

[0024] Figure 2 This is the structural diagram of the heavy welding platform.

[0025] Figure 3 This is the structural diagram of the three-dimensional flexible welding platform.

[0026] Figure 4 This is the structural diagram of the front landing gear support tooling.

[0027] Figure 5 Main landing gear support tooling structure diagram.

[0028] Figure 6 This is a schematic diagram of the 38-frame fixed tooling structure.

[0029] Figure 7 This is a schematic diagram of the inclined frame fixing tooling structure.

[0030] Figure 8 This is a schematic diagram of the tooling structure for fixing the lower half frame shape.

[0031] Fig. 9 This is a schematic diagram of the fixture clamping for fixing the lower half frame shape.

[0032] Fig.10 This is a schematic diagram of the cockpit clamping and fixing tooling structure.

[0033] Fig.11 Schematic diagram of the stiffener plate.

[0034] Fig.12 Schematic diagram of a lifting mechanism, where (a) and (b) are schematic diagrams of lifting mechanisms with two different structures.

[0035] Fig.13 This is a schematic diagram of the fixed installation of the lifting mechanism.

[0036] In the figure: 1- jack; 2- heavy welding platform; 3- three-dimensional flexible welding platform; 4- cockpit clamping fixture; 5- inclined frame fixing fixture; 6- lower half frame shape fixing fixture; 7- front landing gear support fixture; 8- main landing gear support fixture; 9- 38 frame fixing fixture; 10- leveling point; 11- frame connecting fork; 12- column; 13- reinforcing rib; 14- flange; 15- inclined rod; 16- wooden support; 17- main frame; 18- adjusting screw; 19- supporting frame; 20- frame connecting plate; 21- 4 frame bracket; 22- 9 frame bracket; 23- mouth frame beam bracket; 24- bottom frame; 25- gantry frame; 26- protective sling; 27- X-axis adjustment beam; 28- Y-axis adjustment beam; 29- hoisting mechanism. DETAILED DESCRIPTION

[0037] In order to make the purpose, technical solution and advantages of the present invention more clearly understood, the specific implementation methods of the present invention will be described in detail below with reference to the technical solution.

[0038] This embodiment provides a damaged aircraft repair tool, which includes a ground platform, a jack 1, a cockpit clamping and fixing tool 4, an inclined frame fixing tool 5, a lower half frame shape fixing tool 6, a front landing gear supporting tool 7, a main landing gear supporting tool 8 and a 38 frame fixing tool 9. Figure 1 shown.

[0039] 1. Ground platform

[0040] The ground platform is used for the horizontal installation of the entire damaged aircraft repair tooling. According to the different positions of the parked aircraft and the fixed tooling, the heavy welding platform 2 and the three-dimensional flexible welding platform 3 are selected. Figure 2 and Figure 3 shown.

[0041] The heavy welding platform 2 is provided with three triangular arrangements, which are used to support the fixed jack 1, the 38 frame fixing tool 9, the main landing gear support tool 8 and the front landing gear support tool 7 respectively. The heavy welding platform 2 is integrally cast from a high-precision 2m×3m HT-300 cast iron platform, with a single-point load-bearing weight of not less than 10t, which can meet the needs of aircraft repair and ensure safe and reliable support.

[0042] The three-dimensional flexible welding platform 3 is provided in total, which is used to support and fix the lower half frame shape fixing fixture 6, the inclined frame fixing fixture 5 and the cockpit clamping fixing fixture 4, and is integrally cast by a high-precision (2×4)m HT-300 cast iron platform.

[0043] The outer surface of each heavy-duty welding platform 2 and three-dimensional flexible welding platform 3 is equipped with φ28mm round holes evenly distributed at intervals of 100mm, which are used to connect and position various tooling. The hole spacing size error of any hole is ±0.05mm; each platform bottom surface is evenly distributed with 12 leveling points 10, the top of the leveling point 10 is installed in the mounting hole, and the bottom is provided with anchor bolts. The anchor bolts are adjusted through the mounting holes to ensure the overall adjustment level of the platform.

[0044] After the ground platform is placed at the installation location, the ground platform is leveled by using a level ruler and a level gauge, etc. through 12 leveling points 10 at the bottom of the platform.

[0045] (ii) Jack 1

[0046] There are three jacks 1 in total, which are fixed on three heavy welding platforms 2 respectively. The aircraft is connected to the jacks 1 for leveling the aircraft.

[0047] (III) Front landing gear support tooling 7

[0048] The front landing gear support tool 7 is used to replace the jack 1 at the front landing gear to support the fuselage 16 frame after the aircraft is adjusted horizontally; it includes a frame connecting fork 11, a column 12, a reinforcing rib 13, a flange 14 and a diagonal rod 15, which are welded together as shown in FIG. Figure 4As shown; the flange 14 is located at the bottom, which is a Q235A steel plate with a thickness of δ20mm and is provided with 8 φ28mm mounting holes, and is fixedly connected to the heavy welding platform 2; the column 12 is fixed at the center of the upper surface of the flange 14, and is made of Q235A / (G152×12)mm cold-drawn steel pipe, and its height is set according to the actual support height after the aircraft is adjusted horizontally, and 4 reinforcing ribs 13 are fixedly installed at the lower part of the column 12, which are made of No. 6 Q235A channel steel, and a supporting foot is installed at the bottom of the reinforcing rib 13 for adjusting the gap during the installation of the fixed tooling, and a diagonal tie rod 15 is installed on the column 12, one end of which is connected to the column 12 through a half clamp structure, and the other end is fastened to the landing gear through a terminal threaded pin and a nut with reference to the installation form of the aircraft landing gear actuator. The original actuator connection point is used to ensure that the front landing gear support tooling 7 does not move with the landing gear connection point as the axis; the frame connecting fork 11 is welded and fixed to the top of the column 12, and is set as an inverted triangular support structure with a horizontal top according to the 16-frame shape. It is welded with Q235A / δ30mm steel plate. Referring to the front landing gear connection method, a groove is set on the top of the frame connecting fork 11 to match the structure of the aircraft's front landing gear installation point. Pin sleeves are set on both sides of the groove. The pin sleeves are made of (G65×10)mm steel pipes to ensure that their rigidity meets the use requirements. Adjustment bolts (left-handed and right-handed threads) are installed in the pin sleeves and fastened to the front landing gear installation point on the aircraft 16 frame. Among them, the adjustment bolts are manufactured according to the size of the original aircraft assembly bolts to ensure that the gap is the same as the original state.

[0049] After the frame connecting fork 11 of the front landing gear supporting tooling 7 is connected to the corresponding installation part of the aircraft, the jack 1 is used to adjust the spatial position of the aircraft. After the aircraft is adjusted to be level, the height of the column 12 is adjusted according to the actual height position of the frame connecting fork 11, and then the remaining parts are welded and assembled; the four reinforcing ribs 13 support the ground feet to adjust the installation gap and then fix the flange 14 to the ground platform. The installation hole position of the flange 14 connecting the heavy welding platform 2 is drilled on-site according to the actual installation position and then secured with bolts.

[0050] (IV) Main landing gear support tooling 8

[0051] The main landing gear support fixture 8 is provided with two symmetrical arrangements, which are used to replace the two jacks 1 at the main landing gear to support the fuselage after the aircraft is adjusted to the level, and the top is fixed to the main landing gear installation point of the aircraft. The main landing gear support fixture 8 also includes a frame connecting fork 11, a column 12, a reinforcing rib 13, a flange 14 and a diagonal rod 15, which are assembled and welded as shown in FIG. Figure 5As shown, the column 12, flange 14 and inclined rod 15 are the same as those of the front landing gear support fixture 7, the reinforcing rib 13 is connected between the column 12 and the flange 14, the frame connecting fork 11 is fixed to the top of the column 12, and is set as a triangular structure with reference to the main landing gear connection method. It is welded with Q235A / δ30mm steel plate, and the mounting surface is an inclined surface. The mounting surfaces of the frame connecting forks 11 on the two main landing gear support fixtures 8 are opposite, and grooves are made at the mounting surfaces to match the structure of the main landing gear mounting point of the aircraft. Pin shaft sleeves are set on both sides of the grooves, and the pin shaft sleeves are also the same as the pin shaft sleeves in the front landing gear support fixture 7.

[0052] After the frame connecting fork 11 of the main landing gear support tooling 8 is connected to the corresponding installation part of the aircraft, the jack 1 is used to adjust the spatial position of the aircraft. After the aircraft is adjusted to be level, the height of the column 12 is configured according to the actual height position of the frame connecting fork 11, and then the remaining parts are welded and assembled. The installation hole position of the flange 14 connected to the heavy welding platform 2 is drilled on-site according to the actual installation position, and then secured with bolts.

[0053] (V) 38 frame fixed tooling 9

[0054] The 38 frame fixing tool 9 is used to support the rear fuselage 38 frame position after the aircraft is adjusted horizontally, and includes a wooden support 16, a main frame 17, and an adjusting screw 18. After the assembly is assembled, Figure 6 shown.

[0055] The bottom of the main frame 17 is equipped with a δ20mm thick Q235A steel plate as a mounting plate for fixed installation on the ground. The mounting plate is fixed with a frame structure made of Q235A / (130×130×10)mm cold-drawn square steel pipe. A support seat made of Q235A / (200×120×12)mm rectangular steel pipe is installed on the top for installing the wooden support 16; the wooden support 16 is installed side by side on the support seat in total of two, and the material is a δ200mm pine board, the top of which is arc-shaped, and the arc size is set according to the shape of the aircraft air inlet skin. The top of the wooden support 16 is installed with military green canvas and felt. Double-layer protection prevents damage to the aircraft air inlet skin. The U-groove structure of Q235A / δ10mm steel plate is used to fix the wooden support 16 around it to prevent the wooden support 16 from shaking and displacement. A sleeve is provided on the frame structure at the bottom of the wooden support 16, and an adjusting screw 18 is installed in the sleeve. The adjusting screw 18 uses a Tr60 trapezoidal thread screw and a matching handwheel. When in use, the handwheel is adjusted to meet the height and angle adjustment on the XZ axis plane, which is convenient for adjustment and fitting according to the actual position of the aircraft. A top screw is provided in the sleeve. After adjusting it into place, the top screw is rotated to lock the position of the adjusting screw 18 to prevent sliding back and other phenomena from damaging the current position of the aircraft.

[0056] After the aircraft is adjusted to be level, the height of the wooden support 16 is adjusted using a hand wheel until the top arc of the wooden support 16 is completely in contact with the lower wall panel of the engine compartment to complete the installation.

[0057] (VI) Inclined frame fixed support tooling

[0058] It is used to fix the inclined frame structure after the aircraft is adjusted to the level, to ensure that the remaining structure of the radar cabin is stable after the upper half of the 4 frames are disassembled, and the relative position and the position of the nose cone axis will not deviate. It includes a frame connecting plate 20, a support frame 19, and a locking pin. Since the work on the 4 frames and the radar cabin of the aircraft needs to be completed at the nose of the aircraft, a working space is reserved for the workers in the tooling structure design, such as Figure 7 shown.

[0059] The frame connecting plate 20 is set in an annular shape, and the inner hole is used as a working space. It is made of LY12-CZ / δ50mm thick aluminum alloy plate. The frame connecting plate 20 is fastened to the aircraft 1 inclined frame through four locking pins. Its overall size, process hole (avoiding the existing protruding parts of the inclined frame 1), locking pin installation hole position and the actual position of the aircraft 1 inclined frame are set on site and at the corresponding position of the aircraft during the tooling manufacturing process; the support frame 19 is made of Q235A / (100×100×8)mm steel square tube welding, and the lower end is installed A flange structure made of δ20mm thick Q235A steel plate is fixedly connected to the three-dimensional flexible welding platform 3, and its top is fixed to the frame connecting plate 20. The inclined surface of the support frame 19 and the frame connecting plate 20 is set according to the inclination of the inclined frame of the aircraft 1 to ensure the original installation position of the aircraft. The support frame 19 reserves a working position while ensuring overall stability; mounting holes are made on the flange structure, and the three-dimensional flexible welding platform 3 is fixedly connected through the mounting holes, and the mounting holes are not processed for the time being, and will be drilled after the overall position of the inclined frame fixed support tooling is determined.

[0060] During installation, the frame connecting plate 20 is fitted and fixed to the inclined frame of aircraft 1, and the four locking pins on the frame connecting plate 20 are connected and fastened to the inclined frame of aircraft 1. The support frame 19 is ground on site according to the actual measured height and inclination angle of the frame connecting plate 20. After the four legs of the support frame 19 intersect with the three-dimensional flexible welding platform 3, the excess part is removed, the flange structure is installed, and the position is recalibrated. After confirming that the position of the inclined frame 1 has not been offset due to processing, the flange structure and the three-dimensional flexible welding platform 3 are connected and fixed.

[0061] (VII) Lower half frame shape fixing tool 6

[0062] The lower half frame shape fixing tool 6 is installed beside the inclined frame fixing tool 5 on the three-dimensional flexible welding platform 3, and is used for the inner bracket to lift and fix the lower equipment compartment skin and long stringer, ensuring that after the cockpit floor, the left and right side panels of the lower equipment compartment and the (4-9) frame lower half frame are disassembled, they can still be stably fixed in the position before disassembly, and the lower skin contour will not be deformed or the position will change. It includes 4 frame brackets 21, 9 frame brackets 22, bottom frame 24, mouth frame beam bracket 23, bow clamps and oblique tie bars, and the structure is as follows Figure 8 shown.

[0063] The base frame 24 is a frame structure, which is welded by Q235A / (160×100×8)mm steel rectangular tubes. While ensuring the overall stability, a working position is reserved. A flange structure is provided at the bottom for fixed connection with the three-dimensional flexible welding platform 3. The 4-frame bracket 21 and the 9-frame bracket 22 are both installed on the top of the base frame 24, and the two are arranged in parallel. There are two frame beam brackets 23, which are supported side by side between the 4-frame bracket 21 and the 9-frame bracket 22. The 4-frame bracket 21 and the 9-frame bracket 22 are connected to the base frame 24. The upper surfaces of the two mouth frame beam brackets 23 are all cambered surfaces, which are set according to the shape of the aircraft air inlet skin. A 1mm thick rubber sheet is bonded to the cambered surface to prevent damage to the aircraft air inlet skin. The materials of the 4 frame brackets 21, 9 frame brackets 22 and the two mouth frame beam brackets 23 are all made of pine boards (the digital model is established by photographic technology, the shape is processed by CNC with aluminum materials, and the shape accuracy can be controlled by affixing aviation cloth for protection). The 4 frame brackets 21, 9 frame brackets 22 and the two mouth frame beam brackets 23 are provided with 6 bow clips, such as Fig. 9 As shown, it is a detachable structure for clamping the bracket and the skin. The installation positions of the bow clamps are all in the grooves of the aircraft skin cover, and the rubber vulcanization process is carried out at the clamping points, which will not cause damage to the skin; the diagonal tie bars include those installed at the chassis columns under the 4-frame bracket 21 and the 9-frame bracket 22. The diagonal tie bars are detachable structures, which can reserve a working position for repair work while stabilizing the tooling structure.

[0064] During installation, after the upper surfaces of the 4-frame brackets 21, 9-frame brackets 22 and two mouth frame beam brackets 23 on the aircraft (4-9) frame and the lower half frame shape fixing tool 6 are fitted, the brackets and the skin are clamped by 6 bow-shaped clamps. The installation reference position is as follows Fig. 9 shown.

[0065] (VIII) Cockpit clamping fixture 4

[0066] The cockpit clamping and fixing tool 4 is installed above the upper and lower half frame shape fixing tool 6 of the three-dimensional flexible welding platform 3, and is used to clamp and fix the aircraft cockpit port frame beam, rear wall plate, central floor and the upper half frame of the four frames by adjusting the lifting position after the aircraft is adjusted horizontally. It includes a gantry frame 25, an X-axis adjustment beam 27, a Y-axis adjustment beam 28, a lifting mechanism 29 and a protective strap 26. After the assembly is installed, Fig.10 As shown; the overall inner dimensions of the gantry frame 25 are (3800×3000×4600) mm, and are made of Q235A / (160×160×12) mm square steel pipes. Bolts are used to connect the gantry columns to the crossbeams. The entire frame is a detachable structure for easy transportation. A Q235A sheet with a thickness of δ20 mm is installed at the bottom of the gantry column as a bottom plate for fixed connection with the three-dimensional flexible welding platform 3. Four reinforcing rib plates made of Q235A plates with a thickness of δ12 mm are welded between each bottom plate and the gantry column, such as Fig.11 As shown, multiple φ5mm process holes of different heights are processed on the top of the gantry column (drilling is performed according to the actual size of the bolts during installation). After the gantry frame 25 is built, inclined braces can be installed according to the stability. One end of the inclined braces is screwed to the gantry column, and the other end is fastened to the ground platform. There are two Y-axis adjustment beams 28, which are installed in parallel between the gantry columns. The two are made of rectangular steel pipes of Q235A / (200×150×8)mm. The flange structures made of Q235A / δ12mm steel plates at both ends are fixedly connected to the gantry columns through process holes. By connecting with process holes of different heights, the height along the Z-axis direction can be adjusted according to the actual position requirements. Multiple φ5mm installation holes are prefabricated in the horizontal direction on the Y-axis adjustment beam 28 according to the actual working position. There are two X-axis adjustment beams 27, which are installed in parallel between the two Y-axis adjustment beams 28. It is made of Q235A / (150×75×10)mm rectangular steel pipe, and the flange structure made of Q235A / δ12mm steel plate is welded at both ends of the beam and connected to the Y-axis adjustment beam 28 through the mounting holes. The mounting position is adjusted along the Y-axis adjustment beam 28 by connecting different mounting holes to form an adjustment mechanism in the XY-axis plane. The X-axis adjustment beam 27 and the Y-axis adjustment beam 28 together form an XYZ three-dimensional mobile structure. The X-axis adjustment beam 27 prefabricates a plurality of φ5mm process holes in the horizontal direction according to the actual working requirements for the installation of the hoisting mechanism 29; the hoisting mechanism 29 is provided with a plurality of them, and the material is all Q235A steel. The top is fixedly installed on the process hole of the X-axis adjustment beam 27, and the mounting position is adjusted along the X-axis adjustment beam 27 by connecting the process holes at different positions. The bottom is a C-type clamp, which is used to clamp and fix the components that need to be replaced and positioned in the cockpit at the installation position, such as Fig.12 As shown; the protective sling 26 is made of synthetic fiber round sling, which is made of high-strength polyester filament and has the characteristics of soft texture, light weight, large lifting force, large safety factor, non-conductive, strong wear resistance, etc. It will not cause scratches on the surface of the aircraft. The two ends of the protective sling 26 are connected to the crossbeam of the gantry frame 25 to fix the nose.

[0067] During installation, when the gantry frame 25 is mounted, all beams and gantry columns of the gantry frame 25 are laser calibrated at any time with reference to the coordinate system after the aircraft is adjusted horizontally to ensure their horizontality and verticality; the two ends of the protective sling 26 are connected to the beams of the gantry frame 25, and the length is adjusted to fix the aircraft head; after the position of the lifting mechanism 29 is determined, threaded holes are drilled at the corresponding positions of the X-axis, and then bolts are used to connect, such as Fig.13 shown.

[0068] The installation and use process of the damaged aircraft repair tool is as follows:

[0069] Step 1. After the ground platform is placed at the installation position, place a level ruler around the upper plane, place an infrared high-precision level on the ground, and keep it on the same basis as the industrial camera. Adjust the level of each platform through the level adjustment point 10 at the bottom of the platform so that the bubble at each level ruler remains in the middle position and the infrared ray can pass completely through the upper horizontal plane.

[0070] Step 2: After the ground platform is adjusted to be level, place the aircraft body and the jack 1 on the ground platform, connect the frame connecting fork 11 of the front landing gear support fixture 7 and the main landing gear support fixture 8 to the corresponding installation position of the aircraft, and use the jack 1 to adjust the aircraft level. During the installation process, the aircraft position is monitored by the MPS industrial photogrammetry system to prevent installation deviation.

[0071] Step 3, after the aircraft is adjusted to be level, the height of the column 12 of the front landing gear support fixture 7 and the main landing gear support fixture 8 is configured according to the actual height position of each frame connecting fork 11, and the remaining parts are welded and assembled, wherein the front landing gear support fixture 7 uses the four reinforcing ribs 13 connected to its column 12 to support the ground to adjust the installation gap, and the front landing gear support fixture 7 and the main landing gear support fixture 8 are both equipped with on-site drilling installation holes on the flange 14 according to the actual installation position, and then firmly connected to the ground platform with bolts, and the verticality of the column 12 after the fixture is installed is calibrated by laser.

[0072] Step 4, after the aircraft is adjusted to be level, the height of the wooden support 16 is adjusted using the hand wheel of the adjusting screw 18 in the 38 frame fixing tool 9, until the top arc of the wooden support 16 is completely in contact with the lower wall panel of the engine compartment to complete the installation.

[0073] Step 5, fit the frame connecting plate 20 of the inclined frame fixing support tooling to the aircraft 1 inclined frame and fix them with four locking pins, grind the support frame 19 on site according to the actual measured height and inclination angle of the frame connecting plate 20, remove the excess part after the four legs of the support frame 19 intersect with the ground platform, install the flange structure at the bottom, recalibrate the position, and make sure that the position of the inclined frame 1 has not shifted due to processing, then connect and fix the flange structure to the ground platform.

[0074] Step 6, after the 4-frame brackets 21, 9-frame brackets 22 and two mouth frame beam brackets 23 on the lower half frame shape fixing tooling 6 are attached to the aircraft air inlet skin, the brackets and the skin are clamped by 6 bow clamps.

[0075] Step 7, install the cockpit clamping and fixing tooling 4. During the installation process of the gantry frame 25, laser calibration is performed on all the beams and gantry columns of the gantry frame 25 at any time with reference to the coordinate system after the aircraft is adjusted to the horizontal level to ensure their horizontality and verticality; connect the two ends of the protective sling 26 to the crossbeams of the gantry frame 25, and adjust the length to fix the nose; after the position of the lifting mechanism 29 is determined, drill threaded holes at the corresponding positions of the X-axis, and then use bolts to connect, and the C-type clamps will clamp and fix the parts in the cockpit that need to be replaced and positioned in the installation position.

Claims

1. A damaged aircraft repair tool, characterized in that: The damaged aircraft repair tooling comprises a ground platform, a jack (1), a cockpit clamping and fixing tooling (4), an inclined frame fixing tooling (5), a lower half frame shape fixing tooling (6), a front landing gear supporting tooling (7), a main landing gear supporting tooling (8) and a 38 frame fixing tooling (9); the ground platform is used for horizontal installation of the entire damaged aircraft repair tooling, the jack (1) is installed on the ground platform to adjust the overall level of the aircraft, the front landing gear supporting tooling (7) and the main landing gear supporting tooling (8) are arranged on the ground platform, and the front landing gear supporting tooling (7) and the main landing gear supporting tooling (8) are arranged on the ground platform. After the aircraft is leveled, the jack (1) is replaced to rigidly bind the aircraft to the ground platform. The 38-frame fixing tool (9) is used to support the position of the rear fuselage 38 frame after the aircraft is leveled. The inclined frame fixing tool (5) is used to fix the inclined frame structure after the aircraft is leveled. The lower half frame shape fixing tool (6) is used to lift and fix the lower equipment compartment skin and long stringers. The cockpit clamping and fixing tool (4) is used to clamp and fix the aircraft cockpit door frame beam, rear wall panel, central floor and the upper half of the 4 frames after the aircraft is leveled.

2. A damaged aircraft repair tool according to claim 1, characterized in that: The ground platform comprises a heavy welding platform (2) and a three-dimensional flexible welding platform (3); the heavy welding platform (2) is provided with three triangularly arranged ones for supporting a fixed jack (1), a 38-frame fixing tool (9), a main landing gear supporting tool (8) and a front landing gear supporting tool (7); the three-dimensional flexible welding platform (3) is provided with one one for supporting a lower half frame shape fixing tool (6), an inclined frame fixing tool (5) and a cockpit clamping fixing tool (4); the outer surface of each heavy welding platform (2) and three-dimensional flexible welding platform (3) is evenly spaced with a plurality of mounting holes; the bottom surface of each heavy welding platform (2) and three-dimensional flexible welding platform (3) is evenly spaced with a plurality of leveling points (10) for adjusting the ground platform to an overall level.

3. A damaged aircraft repair tool according to claim 1, characterized in that: A total of three jacks (1) are provided, which are fixed on the ground platform respectively and are used to adjust the level of the aircraft.

4. A damaged aircraft repair tool according to claim 1, characterized in that: The front landing gear support tooling (7) replaces the jack (1) at the front landing gear after the aircraft is adjusted to be level, and is fixed to the front landing gear mounting point of the aircraft frame 16, comprising a frame connecting fork (11), a column (12), a reinforcing rib (13), a flange (14) and a diagonal rod (15). The flange (14) is located at the bottom and is used for fixed connection with the ground platform. The column (12) is fixed at the center of the upper surface of the flange (14), and its height is set according to the actual support height after the aircraft is adjusted to be level. The column (12) Four reinforcing ribs (13) are fixedly installed at the bottom, and a supporting foot is installed at the bottom of the reinforcing rib (13) for adjusting the gap when the fixed tooling is installed. A diagonal tie rod (15) is installed on the column (12), one end of which is connected to the column (12) through a half clamp structure, and the other end is connected and fastened to the original landing gear cylinder connection point; the frame connecting fork (11) is fixed to the top of the column (12), and is set as an inverted triangle support structure with a horizontal top according to the shape of the 16-frame, and is used to be fastened to the front landing gear installation point on the aircraft 16 frame; The main landing gear support fixture (8) is provided with two symmetrical arrangements, which are used to replace the two jacks (1) at the main landing gear and fix with the aircraft main landing gear installation point, and also includes a frame connecting fork (11), a column (12), a reinforcing rib (13), a flange (14) and a diagonal rod (15), wherein the column (12), the flange (14) and the diagonal rod (15) are the same as the front landing gear support fixture (7), the reinforcing rib (13) is connected between the column (12) and the flange (14), the frame connecting fork (11) is fixed on the top of the column (12), and is set as a triangular structure, and the mounting surface is an inclined surface, and the mounting surfaces of the frame connecting forks (11) on the two main landing gear support fixtures (8) are opposite to each other, and are used to be fastened with the aircraft main landing gear installation point.

5. The damaged aircraft repair tool according to claim 1, characterized in that: The 38-frame fixing tool (9) is used to support the position of the rear fuselage 38 frame after the aircraft is adjusted to be level, and includes a wooden support (16), a main frame (17), and an adjusting screw (18); the bottom of the main frame (17) is a mounting plate for fixed installation on the ground, a frame structure is fixed on the mounting plate, and a support seat is arranged on the top of the frame structure for installing the wooden support (16); there are two wooden supports (16) installed side by side on the support seat, and the top thereof is arc-shaped, and the arc size is set according to the shape of the aircraft air inlet skin, and the adjusting screw (18) is installed on the frame structure at the bottom of the wooden support (16) to meet the height and angle adjustment on the XZ axis plane.

6. A damaged aircraft repair tool according to claim 1, characterized in that: The inclined frame fixing tool (5) comprises a frame connecting plate (20) and a support frame (19); the frame connecting plate (20) is arranged in a ring shape to reserve a working space, and the frame connecting plate (20) is tightly connected to the inclined frame of the aircraft 1; the lower end of the support frame (19) is fixedly connected to the ground platform, and the top of the support frame (19) is fixed to the frame connecting plate (20), and the inclined surface on which the support frame (19) and the frame connecting plate (20) are installed is arranged according to the inclination of the inclined frame of the aircraft 1.

7. The damaged aircraft repair tool according to claim 1, characterized in that: The lower half frame shape fixing tool (6) comprises a 4-frame bracket (21), a 9-frame bracket (22), a base frame (24), and a mouth frame beam bracket (23); the bottom of the base frame (24) is fixedly connected to the ground platform; the 4-frame bracket (21) and the 9-frame bracket (22) are both installed on the top of the base frame (24), and the two are arranged in parallel. There are two mouth frame beam brackets (23) in total, which are supported side by side between the 4-frame bracket (21) and the 9-frame bracket (22). The upper surfaces of the 4-frame bracket (21), the 9-frame bracket (22) and the two mouth frame beam brackets (23) are all arc surfaces, which are arranged according to the shape of the aircraft air inlet skin. The 4-frame bracket (21), the 9-frame bracket (22) and the two mouth frame beam brackets (23) are detachably provided with bow clips for clamping the brackets and the skin.

8. The damaged aircraft repair tool according to claim 1, characterized in that: The cockpit clamping fixture (4) is a three-axis movable gantry structure, comprising a gantry frame (25), an X-axis adjustment beam (27), a Y-axis adjustment beam (28), a hoisting mechanism (29) and a protective sling (26); the bottom of the gantry column of the gantry frame (25) is fixedly connected to the bottom platform; two Y-axis adjustment beams (28) are provided, which are installed in parallel between the gantry columns, and the installation heights of the two are adjusted according to actual position requirements; the X-axis adjustment beams (27) are provided Two are provided, which are installed in parallel between two Y-axis adjustment beams (28), and can adjust the installation position along the Y-axis adjustment beam (28); the described lifting mechanism (29) is provided in plurality, the top of which is fixedly installed on the X-axis adjustment beam (27), and can adjust the installation position along the X-axis adjustment beam (27), and the bottom of which is a C-shaped clamp, which is used to clamp and fix the parts in the cockpit that need to be replaced and positioned at the installation position; the two ends of the described protective sling (26) are connected to the crossbeam of the gantry frame (25) and are used to fix the head.

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