CN114872924B - Repair type frame for aircraft structure - Google Patents
Repair type frame for aircraft structure Download PDFInfo
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- CN114872924B CN114872924B CN202210670379.1A CN202210670379A CN114872924B CN 114872924 B CN114872924 B CN 114872924B CN 202210670379 A CN202210670379 A CN 202210670379A CN 114872924 B CN114872924 B CN 114872924B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/40—Maintaining or repairing aircraft
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
The invention relates to the field of aviation equipment manufacturing, and particularly discloses an aircraft structure repair type frame which comprises a front landing gear longitudinal beam positioning unit, a central wing box positioning support unit and a fuselage rear positioning support unit which are connected in sequence; the front landing gear longitudinal beam positioning unit comprises a front landing gear longitudinal beam positioning assembly and a first fixed support, the central wing box positioning support unit comprises a front support seat of the machine body, a second fixed support and a central wing box positioning support seat, and the rear positioning support unit of the machine body comprises a connecting support seat, a third fixed support, a rear auxiliary support seat of the machine body and a tail mooring ring positioning support seat. The aircraft nose landing gear longitudinal beam positioning assembly is simple in structure, can accurately position and reliably fix the aircraft through the central wing box positioning support and the aircraft tail mooring ring positioning support, and can accurately position the nose landing gear longitudinal beam assembly of the aircraft, so that the time for an operator to overhaul or replace the nose landing gear longitudinal beam assembly of the aircraft is saved, and the structural repair quality of the aircraft is also ensured.
Description
Technical Field
The invention relates to the field of aviation equipment manufacturing.
Background
With the increasing abundance of people's life development, pursuing new life style becomes necessary, the aircraft has become the main mode that people went on a journey gradually, because aviation equipment manufacturing's development, the equipment and the maintenance business of aircraft are also increasing day by day, accurate location and reduction aircraft nose landing gear's mounted position guarantee the assembly accuracy of changing nose landing gear longeron subassembly etc. is an important work, current aircraft repair type frame is mostly too heavy and can not carry out accurate location to the aircraft, when leading to aircraft structural repair, it is laborious to take time to change nose landing gear longeron subassembly, and the accuracy is difficult to guarantee. In order to solve the problems, a novel aircraft structure repair type frame is researched and designed, and the problems existing in the existing aircraft structure repair type frame are very necessary to overcome.
Disclosure of Invention
In order to solve the problems of the prior repair type frame for the airplane structure, the invention provides the repair type frame for the airplane structure.
The technical scheme adopted by the invention for achieving the purpose is as follows: an aircraft structure repair type frame comprises a front landing gear longitudinal beam positioning unit, a central wing box positioning support unit and a fuselage rear positioning support unit which are connected in sequence;
the nose landing gear longitudinal beam positioning unit comprises a nose landing gear longitudinal beam positioning assembly and a first fixed bracket, the nose landing gear longitudinal beam positioning assembly is connected to the upper end of the first fixed bracket in a sliding manner, and the nose landing gear longitudinal beam positioning assembly corresponds to the nose landing gear at the bottom of the airplane in position;
the central wing box positioning support unit comprises a front support seat of the machine body, a second fixed support and a central wing box positioning support seat, wherein the front support seat of the machine body is arranged at the upper end of the second fixed support, the front support seat of the machine body corresponds to the position of a partition frame at the bottom of the aircraft, one end of the second fixed support is connected with the first fixed support, the central wing box positioning support seat is connected with the other end of the second fixed support, and the central wing box positioning support seat corresponds to the position of a central wing box at the bottom of the aircraft;
the fuselage rear portion location supporting unit includes connection support, third fixed bolster, fuselage rear portion auxiliary support seat and tail mooring ring location supporting seat, connection support one end with central wing box location support is connected, and the other end is connected with third fixed bolster, fuselage rear portion auxiliary support seat with central wing box location support all set up in the upper end of third fixed bolster, the position of fuselage rear portion auxiliary support seat and aircraft rear portion bulkhead is corresponding, tail mooring ring location supporting seat is corresponding with the position of aircraft tail mooring ring.
Preferably, the nose landing gear longitudinal beam positioning assembly comprises a movable platform, a lifting platform, a first bottom plate, a second bottom plate and a rotating platform, wherein the movable platform is connected with the first fixed support through a sliding rail, the lifting platform is arranged at the upper end of the movable platform, the second bottom plate is connected with the upper end of the lifting platform through the first bottom plate, and the rotating platform is arranged at the upper end of the second bottom plate and can rotate in the horizontal direction relative to the second bottom plate.
Preferably, an external frame is further arranged at the upper end of the movable platform, and the external frame is arranged at the left side and the right side of the lifting platform.
Preferably, the upper end of the rotary platform is sequentially provided with a main supporting plate positioning piece for installing a supporting plate, an auxiliary supporting plate positioning piece for installing the supporting plate for installing a foldable supporting rod and an auxiliary supporting plate positioning piece for installing the foldable supporting rod from front to back, and the main supporting plate positioning piece for installing the supporting plate, the auxiliary supporting plate positioning piece for installing the supporting plate for installing the foldable supporting rod, the main supporting plate positioning piece for installing the foldable supporting rod and the auxiliary supporting plate positioning piece for installing the foldable supporting rod are two and symmetrically arranged along the central axis of the rotary platform.
Preferably, the rotary platform is further provided with four longitudinal beam web supports, and the four longitudinal beam web supports are respectively arranged at four corners of the rotary platform and are used for supporting longitudinal beam webs of the aircraft.
Preferably, the machine body positioning auxiliary comprises a machine body positioning auxiliary, positioning pin holes and clamping parts are formed in two ends of the machine body positioning auxiliary, a positioning guide frame, positioning pins and positioning clamps are arranged at the upper end of the central wing box positioning support, the positioning guide frame is a Y-shaped frame provided with an opening, the shape of the opening corresponds to that of the machine body positioning auxiliary, the outer diameter of the positioning pins is identical to the inner diameter of the positioning pin holes, and the positioning clamps are used for clamping the clamping parts of the machine body positioning auxiliary.
Preferably, the positioning pin is connected with the central wing box positioning support through a positioning pin seat, and an adjusting gasket is arranged between the positioning pin seat and the machine body positioning auxiliary.
Preferably, the tail mooring ring positioning support seat is connected with the third fixing support through a lifting device, a groove corresponding to the shape of the aircraft tail mooring ring is formed in the upper end of the tail mooring ring positioning support seat, and a locking clamp is further arranged on the tail mooring ring positioning support seat and used for clamping the aircraft tail mooring ring.
Preferably, the adjustable support leg is an L-shaped support, the lower ends of the first fixed support, the second fixed support, the central wing box positioning support, the connecting support and the third fixed support are all provided with adjustable support leg mounting plates, the adjustable support leg is connected with the adjustable support leg mounting plates through bolts, the vertical section of the adjustable support leg is connected with the adjustable support leg mounting plates through bolts, the adjustable support leg mounting plates are also provided with horizontal adjustment locking sleeves, the horizontal section of the adjustable support leg is provided with connecting rods, the outer diameters of the connecting rods are the same as the inner diameters of the horizontal adjustment locking sleeves, the connecting rods can penetrate through the horizontal adjustment locking sleeves and are locked by nuts, and the horizontal section of the adjustable support leg is further provided with bolt holes and is connected with the ground.
Preferably, the first fixed support, the second fixed support, the central wing box positioning support, the connecting support and the lower end of the third fixed support are all provided with movable casters, and the movable casters are provided with brakes.
The aircraft structure repair type frame is simple in overall structure, convenient to assemble and disassemble, and capable of accurately positioning and reliably fixing an aircraft through the central wing box positioning support and the tail mooring ring positioning support seat, so that the nose landing gear longitudinal beam positioning assembly can accurately position the nose landing gear longitudinal beam assembly of the aircraft, the time for overhauling or replacing the nose landing gear longitudinal beam assembly of the aircraft by an operator is saved, and the aircraft structure repair quality is also ensured.
Drawings
FIG. 1 is a schematic view of an aircraft structure repair type frame in accordance with an embodiment of the present invention;
FIG. 2 is a schematic view of a front view of an aircraft structure repair type frame according to an embodiment of the present invention;
FIG. 3 is a schematic illustration of a nose landing gear stringer positioning unit of an embodiment of the present invention;
FIG. 4 is a schematic view of the structure of a central wing box positioning and supporting unit according to an embodiment of the present invention;
FIG. 5 is a schematic illustration of the structure of a center box positioning support of an embodiment of the present invention;
FIG. 6 is a schematic view of a tail mooring ring positioning support seat according to an embodiment of the invention.
In the figure: 1. the device comprises a first fixed support, 2, a sliding rail, 3, a movable platform, 4, a lifting platform, 5, a first bottom plate, 6, a second bottom plate, 7, a rotary platform, 8, an outer frame, 9, a pillar installation support main positioning piece, 10, a pillar installation support auxiliary positioning piece, 11, a foldable support rod installation support main positioning piece, 12, a foldable support rod installation support auxiliary positioning piece, 13, a longitudinal beam web support, 14, a front support seat of a machine body, 15, a second fixed support, 16, a central wing box positioning support, 17, a machine body positioning auxiliary piece, 17-1, a positioning pin hole, 17-2, a clamping part, 18, a positioning guide frame, 19, a positioning pin, 20, a positioning clamp, 21, a positioning pin seat, 22, an adjusting gasket, 23, a connecting support, 24, a machine body rear body auxiliary support seat, 25, a machine tail mooring ring positioning support seat, 26, a lifting device, 27, a third fixed support, 28, a locking clamp, 29, an adjustable support, 30, an adjustable support foot, 31, a horizontal adjusting sleeve, 32, a connecting rod, a locking castor, 33 and a caster.
Detailed Description
Embodiments of the present invention are described in further detail below with reference to the accompanying drawings and examples. The following examples are illustrative of the invention but are not intended to limit the scope of the invention.
In the description of the present invention, it should be noted that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, only for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the apparatus or elements to be referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying relative importance, but rather the terms "mounted," "connected," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art. Furthermore, in the description of the present invention, unless otherwise indicated, the meaning of "a plurality" is two or more.
An aircraft structure repair type frame of the embodiment is shown in fig. 1 and 2, and comprises a nose landing gear longitudinal beam positioning unit, a central wing box positioning support unit and a fuselage rear positioning support unit which are sequentially connected, wherein the nose landing gear longitudinal beam positioning unit comprises a nose landing gear longitudinal beam positioning component and a first fixed bracket 1, the nose landing gear longitudinal beam positioning component is slidably connected to the upper end of the first fixed bracket 1, and corresponds to the position of a nose landing gear at the bottom of an aircraft, and is used for supporting and overhauling the nose landing gear at the bottom of the aircraft so as to ensure the assembly accuracy of replacing a nose landing gear longitudinal beam component, a No. 1 frame, a skin and the like; the central wing box positioning and supporting unit comprises a front supporting seat 14 of the airplane body, a second fixed bracket 15 and a central wing box positioning support 16, wherein the front supporting seat 14 of the airplane body is arranged at the upper end of the second fixed bracket 15, the front supporting seat 14 of the airplane body corresponds to the position of a bottom bulkhead of the airplane and is used for supporting the bottom bulkhead of the airplane, one end of the second fixed bracket 15 is connected with the first fixed bracket 1, the central wing box positioning support 16 is connected with the other end of the second fixed bracket 15, and the central wing box positioning support 16 corresponds to the position of a central wing box at the bottom of the airplane and is used for supporting the central wing box at the bottom of the airplane; the fuselage rear portion location supporting unit includes connecting support 23, third fixed bolster 26, fuselage rear portion auxiliary support seat 24 and tail mooring ring location supporting seat 25, connecting support 23 one end is connected with central wing box location support 16, the other end is connected with third fixed bolster 27, fuselage rear portion auxiliary support seat 24 and central wing box location support 16 all set up in the upper end of third fixed bolster 27, fuselage rear portion auxiliary support seat 24 corresponds with the position of aircraft rear bulkhead for support aircraft rear bulkhead, tail mooring ring location supporting seat 25 corresponds with the position of aircraft tail mooring ring for support and fastening aircraft tail mooring ring.
As shown in fig. 3, the nose landing gear longitudinal beam positioning assembly comprises a movable platform 3, a lifting platform 4, a first bottom plate 5, a second bottom plate 6 and a rotating platform 7, wherein the movable platform 3 is connected with the first fixed support 1 through a sliding rail 2, two sliding rails 2 can be arranged for enabling the movable platform 3 to slide more smoothly and stably, and the movable platform 3 can move back and forth along the two sliding rails 2 so as to drive the whole nose landing gear longitudinal beam positioning assembly to move back and forth. The elevating platform 4 sets up in the upper end of movable platform 3, in addition, the upper end of movable platform 3 still can be equipped with external frame 8, and external frame 8 sets up in the left and right sides of elevating platform 4, and elevating platform 4 can reciprocate in external frame 8 to realize the accurate positioning to nose gear longeron locating component. The second bottom plate 6 is connected with the upper end of the lifting platform 4 through the first bottom plate 5, six adjusting and positioning screws are respectively arranged at the edges of two sides of the second bottom plate 6, the transverse adjustment and the height adjustment of the second bottom plate 6 can be realized, the rotating platform 7 is arranged at the upper end of the second bottom plate 6 and can rotate in the horizontal direction relative to the second bottom plate 6, one positioning screw (four positioning screws in total) is respectively arranged in the middle of four sides of the rotating platform 7, and after the rotation angle of the rotating platform 7 meets the requirement, the four positioning screws can be screwed to position the rotating platform 7. The upper end of the rotary platform 7 is sequentially provided with a main supporting plate positioning piece 9 for installing a supporting plate, an auxiliary supporting plate positioning piece 10 for installing the supporting plate for installing a foldable supporting rod, a main supporting plate positioning piece 11 for installing the foldable supporting rod and an auxiliary supporting plate positioning piece 12 for installing the foldable supporting rod from front to back, and the main supporting plate positioning piece 9 for installing the supporting plate, the auxiliary supporting plate positioning piece 10 for installing the supporting plate for installing the foldable supporting rod, the main supporting plate positioning piece 11 for installing the foldable supporting rod and the auxiliary supporting plate positioning piece 12 for installing the foldable supporting rod are two and symmetrically arranged along the central axis of the rotary platform 7. The rotary platform 7 is further provided with four stringer web supports 13, and the four stringer web supports 13 are respectively arranged at four corners of the rotary platform 7 and are used for supporting stringer webs of the aircraft.
As shown in fig. 4 and 5, the aircraft body positioning auxiliary 17 further comprises an aircraft body positioning auxiliary 17, the aircraft body positioning auxiliary 17 can penetrate through a central wing box of an aircraft body, 2 preset bolts (not fastened and screwed by hand) are respectively used at two ends through corresponding mounting holes at two ends of the upper surface of the central wing box of the aircraft body, the aircraft body positioning auxiliary 17 is mounted on the central wing box of the aircraft, positioning pin holes 17-1 and clamping parts 17-2 are respectively arranged at two ends of the aircraft body positioning auxiliary 17, a positioning guide frame 18, positioning pins 19 and positioning clamps 20 are arranged at the upper end of a positioning support 16 of the central wing box, the positioning guide frame 18 is a Y-shaped frame with openings, the shapes of the openings correspond to the shapes of the aircraft body positioning auxiliary 17, the outer diameters of the positioning pins 19 are the same as the inner diameters of the positioning pin holes 17-1, the positioning clamps 20 are used for clamping the clamping parts 17-2 of the aircraft body positioning auxiliary 17, the positioning pins 19 are connected with the positioning support 16 through positioning pin seats 21, and adjusting gaskets 22 are arranged between the positioning pin seats 21 and the aircraft body positioning auxiliary 17.
As shown in fig. 6, the tail mooring ring positioning support seat 25 is connected with the third fixing bracket 27 through the lifting device 26, a groove corresponding to the shape of the aircraft tail mooring ring is formed at the upper end of the tail mooring ring positioning support seat 25, and the tail mooring ring positioning support seat 25 is further provided with a locking clamp 28, wherein the locking clamp 28 is used for clamping the aircraft tail mooring ring.
As shown in fig. 1-6, an adjustable support 29 is further provided, the adjustable support 29 is an L-shaped support, the first fixing support 1, the second fixing support 15, the central wing box positioning support 16, the connecting support 23 and the lower end of the third fixing support 27 are all provided with an adjustable support mounting plate 30, the adjustable support 29 is connected with the adjustable support mounting plate 30 through bolts, the vertical section of the adjustable support 29 and the adjustable support mounting plate 30 are all provided with a plurality of bolt holes, the adjustable support mounting plate 30 is also provided with a horizontal adjusting locking sleeve 31, the horizontal section of the adjustable support 29 is provided with a connecting rod 32, the outer diameter of the connecting rod 32 is the same as the inner diameter of the horizontal adjusting locking sleeve 31, the connecting rod 32 can penetrate through the horizontal adjusting locking sleeve 31 and is locked by nuts, the horizontal section of the adjustable support 29 is also provided with bolt holes, and the bolts penetrate through the bolt holes, so that the whole device is connected with the ground. The lower ends of the first fixing bracket 1, the second fixing bracket 15, the central wing box locating support 16, the connecting support 23 and the third fixing bracket 27 are respectively provided with a movable castor 33, and the movable castor 33 is provided with a brake 34.
When in installation:
1. the first fixing bracket 1, the second fixing bracket 15, the central wing box locating support 16, the connecting support 23 and the third fixing bracket 27 are sequentially connected, the movable castor 33 is locked, the movable castor 33 is symmetrical about the central axis of the whole device, the movable castor 33 can be arranged according to the specific specification of the device, the adjustable support 29 is arranged on the adjustable support mounting plate 30, 14 adjustable support mounting plates 30 can be arranged, 7 adjustable support mounting plates are arranged on the left and right sides and symmetrically arranged along the central axis of the device, and 28 bolts can be used for connection;
2. the infrared level meter is used for emitting vertical laser rays, and the first fixing support 1, the second fixing support 15, the central wing box locating support 16, the connecting support 23 and the third fixing support 27 are calibrated, so that the central axes of the first fixing support 1, the second fixing support 15, the central wing box locating support 16, the connecting support 23 and the third fixing support 27 are on the same vertical plane;
3. according to the size of the machine body, the axial position of the machine tail mooring ring positioning support seat 25 is adjusted, so that the machine tail mooring ring positioning support seat 25 is positioned at a proper position;
4. after the 14 adjustable feet 29 are secured to the ground with expansion bolts, the entire frame is horizontally aligned and the height of each adjustable foot 29 is adjusted depending on the situation to ensure that all of the casters 33 have been lifted off the ground. The horizontal laser lines emitted by the infrared level meter are matched with the bubble level to perform horizontal calibration on the first fixing support 1, the second fixing support 15, the central wing box locating support 16, the connecting support 23 and the third fixing support 27, wherein the horizontal calibration is divided into longitudinal calibration and transverse calibration. Bubble level bars are respectively placed on the horizontal datum planes of the first fixing support 1, the second fixing support 15, the central wing box locating support 16, the connecting support 23 and the third fixing support 27 along the longitudinal direction and the transverse direction, the supports are positioned horizontally by horizontally adjusting the fastening positions of the locking sleeve 31 and the connecting rod 32 of the adjustable support leg 29 at the adjusting position 14, and the adjacent horizontal datum planes of the supports are ensured to be at the same horizontal height (the error is less than 2 mm). The adjusting sequence is the second fixed bracket 15, the central wing box positioning support 16, the first fixed bracket 1, the connecting support 23 and the third fixed bracket 27. And (3) injection: after the horizontal calibration is completed, the movable castor 33 should be checked to confirm that it is lifted off the ground, otherwise, the adjustment should be performed again to ensure that the adjustable leg 29 is the main bearing member;
5. after the adjustment is completed, the horizontal adjustment locking sleeve 31 and the connecting rod 32 of the adjustable support leg 29 are locked by nuts, and bolts in bolt holes of the adjustable support leg 29 are locked.
When in use, the utility model is characterized in that:
1. the machine body positioning auxiliary 17 passes through a central wing box of the airplane body, 2 preset bolts (not fastened and screwed by hand) are respectively used at two ends of the machine body positioning auxiliary 17 through corresponding mounting holes at two ends of the upper surface of the central wing box of the airplane body, the machine body positioning auxiliary 17 is mounted on the central wing box, a crane (or equivalent equipment) is used for moving the airplane body above the device, the airplane body is controlled to slowly descend, the machine body positioning auxiliary 17 is aligned with an opening of a positioning guide frame 18, and clamping parts 17-2 at two ends of the machine body positioning auxiliary 17 are aligned with positioning clamps 20;
2. optionally adjusting the lateral position of the tail mooring ring positioning support seat 25 to enable the tail mooring ring to be aligned with a groove at the upper end of the tail mooring ring positioning support seat 25, optionally adjusting the front support seat 14 of the airplane body and the auxiliary support seat 24 of the rear body of the airplane, and lightly putting down the airplane;
3. the aircraft fuselage is leveled on the device, the air bubble level is placed on the upper surface of a central wing box in the fuselage during horizontal axis leveling, the number of adjusting gaskets 22 on the positioning pins 19 at the left end and the right end of the fuselage positioning auxiliary 17 is increased or decreased according to the condition, so that the air bubble level is positioned at the center, two leveling screws positioned at the left front side window of the fuselage are partially screwed out during vertical axis leveling, the air bubble level is placed on the heads of the two leveling screws, and the height of the tail mooring ring positioning support seat 25 is adjusted according to the condition, so that the air bubble level is positioned at the center. After the leveling is completed, a limit bolt is installed on the tail mooring ring positioning support seat 25, a locking nut is fastened, and a mooring ring locking clamp 28 is installed. The forward fuselage support pedestal 14 and the aft fuselage support pedestal 24 are raised to contact the lower fuselage surface and bear a small portion of the support force as a static support assist to improve the stability of the fuselage. The main bearing points of the fuselage structure are checked and confirmed on the central wing box locating support 16 and the tail mooring ring locating support 25 so as to avoid deformation of the fuselage structure caused by improper stress of the supports. Optionally adjusting the height of the positioning clamp 20 of the body positioning aid 17, locking the positioning clamp 20, fastening the body positioning aid 17, and tightening a preset bolt of the body positioning aid 17;
4. the front landing gear longitudinal beam positioning assembly moves to a proper position along the sliding rail 2, the lifting platform 4 is adjusted to ascend and move to a corresponding position, the main positioning piece 9 of the installation support post installation support plate, the auxiliary positioning piece 10 of the support post installation support plate, the main positioning piece 11 of the foldable support rod installation support plate and the auxiliary positioning piece 12 of the foldable support rod installation support plate are installed, and the position of the second bottom plate 6 is adjusted to ensure that the longitudinal axis of the second bottom plate 6 coincides with the longitudinal axis of the whole device. Six adjusting and positioning screws are respectively arranged at the edges of two sides of the second bottom plate 6, so that the transverse adjustment and the height adjustment of the second bottom plate 6 can be realized, and the positions of 8 positioning pieces on the rotating platform 7 are adjusted. So that the positions of the 8 positioning members coincide with the positions of the strut mounting brackets and the foldable strut mounting bracket mounting holes of the aircraft, and if not, the rotary platform 7 can be rotated as appropriate.
5. After the adjustment is completed, the disassembly work of the longitudinal beam of the front landing gear of the airplane body and the positioning work of the new longitudinal beam of the front landing gear of the airplane body can be performed.
The embodiments of the invention have been presented for purposes of illustration and description, and are not intended to be exhaustive or limited to the invention in the form disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art. The embodiments were chosen and described in order to best explain the principles of the invention and the practical application, and to enable others of ordinary skill in the art to understand the invention for various embodiments with various modifications as are suited to the particular use contemplated.
Claims (8)
1. The aircraft structure repair type frame is characterized by comprising a front landing gear longitudinal beam positioning unit, a central wing box positioning support unit and a fuselage rear positioning support unit which are connected in sequence;
the nose landing gear longitudinal beam positioning unit comprises a nose landing gear longitudinal beam positioning assembly and a first fixed bracket (1), wherein the nose landing gear longitudinal beam positioning assembly is connected to the upper end of the first fixed bracket (1) in a sliding manner, and the nose landing gear longitudinal beam positioning assembly corresponds to the position of the nose landing gear at the bottom of the aircraft;
the nose landing gear longitudinal beam positioning assembly comprises a movable platform (3), a lifting platform (4), a first bottom plate (5), a second bottom plate (6) and a rotating platform (7), wherein the movable platform (3) is connected with the first fixed support (1) through a sliding rail (2), the lifting platform (4) is arranged at the upper end of the movable platform (3), the second bottom plate (6) is connected with the upper end of the lifting platform (4) through the first bottom plate (5), and the rotating platform (7) is arranged at the upper end of the second bottom plate (6) and can rotate in the horizontal direction relative to the second bottom plate (6);
the central wing box positioning and supporting unit comprises a front body supporting seat (14), a second fixing bracket (15) and a central wing box positioning support (16), wherein the front body supporting seat (14) is arranged at the upper end of the second fixing bracket (15), the front body supporting seat (14) corresponds to the position of a bottom bulkhead of the aircraft, one end of the second fixing bracket (15) is connected with the first fixing bracket (1), the central wing box positioning support (16) is connected with the other end of the second fixing bracket (15), and the central wing box positioning support (16) corresponds to the position of a central wing box at the bottom of the aircraft;
the rear positioning support unit of the aircraft comprises a connecting support (23), a third fixed support (27), an auxiliary support seat (24) of the rear of the aircraft and a positioning support seat (25) of a tail mooring ring, wherein one end of the connecting support (23) is connected with the central wing box positioning support (16), the other end of the connecting support is connected with the third fixed support (27), the auxiliary support seat (24) of the rear of the aircraft and the positioning support seat (16) of the central wing box are both arranged at the upper end of the third fixed support (27), the auxiliary support seat (24) of the rear of the aircraft corresponds to the position of a rear partition frame of the aircraft, and the positioning support seat (25) of the tail mooring ring corresponds to the position of the tail mooring ring of the aircraft;
the tail mooring ring positioning support seat (25) is connected with the third fixing support (27) through the lifting device (26), a groove corresponding to the shape of the aircraft tail mooring ring is formed in the upper end of the tail mooring ring positioning support seat (25), the tail mooring ring positioning support seat (25) is further provided with a locking clamp (28), and the locking clamp (28) is used for clamping the aircraft tail mooring ring.
2. The aircraft structure repair type frame according to claim 1, wherein an outer frame (8) is further provided at an upper end of the movable platform (3), and the outer frame (8) is provided at left and right sides of the lifting platform (4).
3. The aircraft structure repair type frame according to claim 1, wherein the upper end of the rotary platform (7) is sequentially provided with a main strut installation supporting plate positioning member (9), an auxiliary strut installation supporting plate positioning member (10), a main strut installation supporting plate positioning member (11) and an auxiliary strut installation supporting plate positioning member (12) from front to back, and the main strut installation supporting plate positioning member (9), the auxiliary strut installation supporting plate positioning member (10), the main strut installation supporting plate positioning member (11) and the auxiliary strut installation supporting plate positioning member (12) are two and are symmetrically arranged along the central axis of the rotary platform (7).
4. An aircraft structure repair jig according to claim 1, characterized in that the rotary platform (7) is further provided with four stringer web supports (13), the four stringer web supports (13) being arranged at the four corners of the rotary platform (7) respectively for supporting the stringer web of an aircraft.
5. The aircraft structure repair type frame according to claim 1, further comprising a body positioning auxiliary (17), wherein positioning pin holes (17-1) and clamping portions (17-2) are formed in two ends of the body positioning auxiliary (17), a positioning guide frame (18), positioning pins (19) and positioning clamps (20) are arranged at the upper end of the central wing box positioning support (16), the positioning guide frame (18) is a Y-shaped frame provided with openings, the shapes of the openings correspond to those of the body positioning auxiliary (17), the outer diameters of the positioning pins (19) are identical to the inner diameters of the positioning pin holes (17-1), and the positioning clamps (20) are used for clamping the clamping portions (17-2) of the body positioning auxiliary (17).
6. An aircraft structure repair jig according to claim 5, characterized in that the locating pin (19) is connected to the central wing box locating support (16) by a locating pin seat (21), an adjustment shim (22) being provided between the locating pin seat (21) and the fuselage positioning aid (17).
7. The aircraft structure repair type frame according to claim 1, characterized in that an adjustable support leg (29) is further provided, the adjustable support leg (29) is an L-shaped support, the first fixed support (1), the second fixed support (15), the central wing box positioning support (16), the connecting support (23) and the lower end of the third fixed support (27) are all provided with an adjustable support leg mounting plate (30), the adjustable support leg (29) is connected with the adjustable support leg mounting plate (30) through bolts, the vertical section of the adjustable support leg (29) and the adjustable support leg mounting plate (30) are all provided with a plurality of bolt holes, the adjustable support leg mounting plate (30) is further provided with a horizontal adjustment locking sleeve (31), the horizontal section of the adjustable support leg (29) is provided with a connecting rod (32), the outer diameter of the connecting rod (32) is the same as the inner diameter of the horizontal adjustment locking sleeve (31), and the connecting rod (32) can penetrate through the horizontal adjustment locking sleeve (31) and use locking nuts, and the horizontal section of the adjustable support leg (29) is further provided with a plurality of bolt holes for connection with the ground.
8. An aircraft structure repair jig according to claim 1, characterized in that the first fixed bracket (1), the second fixed bracket (15), the central wing box positioning support (16), the connecting support (23) and the third fixed bracket (27) are each provided with a movable castor (33) at their lower ends, and the movable castor (33) is provided with a brake (34).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202210670379.1A CN114872924B (en) | 2022-06-15 | 2022-06-15 | Repair type frame for aircraft structure |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210670379.1A CN114872924B (en) | 2022-06-15 | 2022-06-15 | Repair type frame for aircraft structure |
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| CN114872924A CN114872924A (en) | 2022-08-09 |
| CN114872924B true CN114872924B (en) | 2023-07-07 |
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| CN202210670379.1A Active CN114872924B (en) | 2022-06-15 | 2022-06-15 | Repair type frame for aircraft structure |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115675911A (en) * | 2022-10-11 | 2023-02-03 | 北京山太公务机维修技术有限公司 | Aircraft wing maintenance device and method thereof |
| CN117533516B (en) * | 2024-01-09 | 2024-03-19 | 山西禧佑源民机完工中心有限公司 | Aircraft wing maintenance ladder assembly |
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| CN114872924A (en) | 2022-08-09 |
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