CN116394199A - Aircraft flap dismounting device and aircraft flap dismounting method - Google Patents
Aircraft flap dismounting device and aircraft flap dismounting method Download PDFInfo
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- CN116394199A CN116394199A CN202310675836.0A CN202310675836A CN116394199A CN 116394199 A CN116394199 A CN 116394199A CN 202310675836 A CN202310675836 A CN 202310675836A CN 116394199 A CN116394199 A CN 116394199A
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- 238000007789 sealing Methods 0.000 description 2
- 238000013024 troubleshooting Methods 0.000 description 2
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- 230000002441 reversible effect Effects 0.000 description 1
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- 239000004636 vulcanized rubber Substances 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B27/00—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for
- B25B27/02—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for for connecting objects by press fit or detaching same
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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 embodiment of the application discloses an aircraft flap dismounting device and an aircraft flap dismounting method, which relate to the technical field of aircraft assembly and comprise a fixed support, a locating pin, a sliding optical axis and a lifting mechanism, wherein a first surface of the fixed support is provided with a mounting hole in the vertical direction; the locating pin is matched with the mounting hole, the locating pin is matched with the fixed support through a boss, the second end of the locating pin penetrates through the fixed support, a conical table is arranged at the second end of the locating pin, and the conical table is used for penetrating through a screw nest on the opening cover and is matched with the inner surface of the opening cover; the sliding optical axis movably penetrates through the fixed support, a first end of the sliding optical axis is positioned in the fixed support, and a second end of the sliding optical axis is positioned outside the fixed support; the lifting mechanism is used for lifting the vertical height of the second end of the sliding optical axis. The utility model discloses an utilize locating pin and screw nest cooperation, upwards lift the flap through lever principle, reduced the degree of difficulty of dismantling to do not pry, effectively avoid Li Ling part damage, ensured aircraft surface quality.
Description
Technical Field
The application relates to the technical field of aircraft assembly, in particular to an aircraft flap dismounting device and an aircraft flap dismounting method.
Background
The surface of the aircraft is designed with a large number of covers, so that an operation channel is provided for normal installation and later maintenance of parts such as finished products, pipes, cables and the like in the aircraft body, and various covers are required to be detached when daily maintenance and troubleshooting repair are carried out on the aircraft in the later stage.
The existing disassembly method is to use a straight screwdriver to pry the flap open through a gap between the flap and the skin flap frame, but the mode has the following defects: on the one hand, the gap is smaller, so that the disassembly difficulty is high and the time is long; on the other hand, the prizing mode can inevitably damage parts nearby the operation area, and the surface quality is seriously affected; therefore, a disassembly means with low operation difficulty and no damage is needed.
Disclosure of Invention
The utility model provides a main aim at provides an aircraft flap dismounting device and aircraft flap dismantlement method, aims at solving the problem that the means degree of difficulty of aircraft flap dismantlement is big and cause spare part damage easily among the prior art.
The technical scheme adopted by the application is as follows:
in a first aspect, embodiments of the present application provide an aircraft flap disassembly device, comprising:
the fixing support is provided with a mounting hole in the vertical direction on the first surface;
the locating pin is matched with the mounting hole, the locating pin is matched with the fixed support through a boss, the second end of the locating pin penetrates through the fixed support, a conical table is arranged at the second end of the locating pin, and the conical table is used for penetrating through a screw nest on the opening cover and is matched with the inner surface of the opening cover;
the sliding optical axis is horizontally arranged, the sliding optical axis movably penetrates through the fixed support, the first end of the sliding optical axis is positioned in the fixed support, and the second end of the sliding optical axis is positioned outside the fixed support;
and the lifting mechanism is used for lifting the vertical height of the second end of the sliding optical axis.
Optionally, the lifting mechanism includes universal foot cup and twist grip, wherein:
the rod part of the universal foot cup penetrates through the second end of the sliding optical axis, the axis of the universal foot cup is perpendicular to the axis of the sliding optical axis, the rod part of the universal foot cup is in threaded connection with the sliding optical axis, and the bottom of the universal foot cup is used for being abutted with a machine body near the opening cover;
the rotating handle is connected with the rod part of the universal foot cup and one end far away from the sliding optical axis, and the axis of the rotating handle is perpendicular to the axis of the universal foot cup.
Optionally, two sliding optical axes are arranged, and the two sliding optical axes are symmetrically arranged about the vertical axis of the fixed support;
the lifting mechanism further comprises a connecting block, two ends of the connecting block are respectively connected with a second end of the sliding optical axis, and the rod part of the universal foot cup is in threaded connection with the middle part of the connecting block.
Optionally, the device further comprises a flange linear bearing, wherein the flange linear bearing is arranged on the fixed support, and the sliding optical axis is matched with the flange linear bearing.
Optionally, the first end of sliding optical axis runs through the fixed support, and the first end of sliding optical axis sets up the stopper.
Alternatively, two positioning pins are provided, two mounting holes are provided, one positioning pin is respectively matched with one mounting hole, and the arrangement direction of the two positioning pins is perpendicular to the axis direction of the sliding optical axis.
Optionally, any one of the mounting holes is a bar-shaped hole, and an extending direction of the bar-shaped hole is perpendicular to an axial direction of the sliding optical axis.
Optionally, a limiting cover is arranged on the first surface of the fixed support, a bar-shaped notch is formed in the limiting cover, and the size of the bar-shaped notch is matched with the size of the mounting hole.
Optionally, the second surface of the fixed support is covered with a rubber pad.
In a second aspect, an embodiment of the present application provides an aircraft flap disassembling method, which adopts the aircraft flap disassembling device provided in any one of the first aspects of the embodiments of the present application, including the following steps:
disassembling the bolts on the opening cover, and enabling the second surface of the fixed support to be attached to the surface of the opening cover so as to enable the positioning pins to be aligned with the bolt sockets from which the bolts are disassembled;
penetrating the second end of the locating pin through the rubber pad interlayer until a conical table arranged on the second end of the locating pin reversely hooks the inner surface of the flap so as to tighten the flap;
moving the sliding optical axis to adjust the distance between the second end thereof and the fixed support;
and lifting the second end of the sliding optical axis by using a lifting mechanism so that the part of the cover, which is hooked by the conical table, is lifted upwards to finish the separation of the cover and the machine body.
Compared with the prior art, the beneficial effects of this application are:
according to the aircraft flap dismounting device and the aircraft flap dismounting method, the fixed support, the sliding optical axis and the lifting mechanism are arranged, a lever structure is formed to be favorable for applying upward lifting force to the flap, the lifting force is realized through the end part of the positioning pin, the end part of the positioning pin penetrates through the screw nest formed when the flap is mounted, the end part of the positioning pin is provided with the conical table, the conical table can reversely hook the inner surface of the flap after penetrating through the flap, the sliding optical axis can upwards lift the fixed support under the action of the lifting mechanism, the fixed support and the flap form a whole under the connection of the positioning pin, the flap can be lifted upwards by the position of the screw nest, the operation is simple and convenient, the quick dismounting of the flap can be realized, and parts can not be pried and extruded, so that damage is avoided, and the quality of the surface of the aircraft after the flap is dismounted is ensured.
Drawings
Fig. 1 is a schematic structural view of an aircraft flap removing device according to an embodiment of the present disclosure;
fig. 2 is a schematic structural view of an aircraft flap removing device in a bottom view according to an embodiment of the present application;
FIG. 3 is a schematic structural view of the aircraft door removal device according to the embodiment of the present application in use;
FIG. 4 is a schematic side view of an aircraft flap removal device according to an embodiment of the present disclosure;
FIG. 5 is a schematic cross-sectional view of an aircraft flap removal device provided in an embodiment of the present application;
FIG. 6 is a schematic view of a conical table mated with a flap in an aircraft flap removal device according to an embodiment of the present application;
FIG. 7 is a schematic view of a positioning pin in an aircraft door removal device according to an embodiment of the present disclosure;
FIG. 8 is a schematic structural view of a fixing support in an aircraft flap removal device according to an embodiment of the present disclosure;
fig. 9 is a schematic structural view of a limit cover in the aircraft flap disassembling device provided in the embodiment of the application;
FIG. 10 is a schematic view of a sliding optical axis in an aircraft flap removal device according to an embodiment of the present disclosure;
FIG. 11 is a schematic structural view of a flange linear bearing in an aircraft flap disassembly device according to an embodiment of the present disclosure;
fig. 12 is a schematic structural view of a connection block in the aircraft flap removing device according to the embodiment of the present application;
FIG. 13 is a schematic view of the structure of a universal cup in the aircraft door removal device provided in the embodiment of the present application;
FIG. 14 is a flow chart of a method for removing an aircraft flap according to an embodiment of the present disclosure;
the reference numerals in the drawings indicate:
the device comprises a positioning pin 1, a fixed support 2, a limit cover 3, a rubber pad 4, a flange linear bearing 5, a sliding optical axis 6, a connecting block 7, a rotating handle 8, a universal cup 9, a protection pad 10, a spring 11, a cover 12, a skin 13 and a rubber pad 14.
Detailed Description
The following description of the embodiments of the present application will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are only some, but not all, of the embodiments of the present application. All other embodiments, which can be made by one of ordinary skill in the art based on the embodiments herein without making any inventive effort, are intended to be within the scope of the present application.
It should be noted that all directional indicators (such as up, down, left, right, front, and rear … …) in the embodiments of the present application are merely used to explain the relative positional relationship, movement, etc. between the components in a specific posture (as shown in the drawings), and if the specific posture is changed, the directional indicator is correspondingly changed.
In the present application, unless explicitly specified and limited otherwise, the terms "coupled," "secured," and the like are to be construed broadly, and for example, "secured" may be either permanently attached or removably attached, or integrally formed; can be mechanically or electrically connected; either directly or indirectly, through intermediaries, or both, may be in communication with each other or in interaction with each other, unless expressly defined otherwise. The specific meaning of the terms in this application will be understood by those of ordinary skill in the art as the case may be.
In addition, if there is a description of "first", "second", etc. in the embodiments of the present application, the description of "first", "second", etc. is for descriptive purposes only and is not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In addition, the meaning of "and/or" as it appears throughout includes three parallel schemes, for example "A and/or B", including the A scheme, or the B scheme, or the scheme where A and B are satisfied simultaneously. In addition, the technical solutions of the embodiments may be combined with each other, but it is necessary to base that the technical solutions can be realized by those skilled in the art, and when the technical solutions are contradictory or cannot be realized, the combination of the technical solutions should be regarded as not exist and not within the protection scope of the present application.
The surface of the aircraft is designed with a large number of covers, so as to provide an operation channel for normal installation and later maintenance of parts such as finished products, pipes, cables and the like in the aircraft body. In order to improve the sealing performance of the flap structure and prevent the fuel leakage or the corrosion of rainwater to the internal structure of the machine body, when the modern aircraft flap is assembled, a common process method is to bond a rubber pad on the inner surface of the flap or vulcanize a rubber pad on site on a flap frame by using vulcanized sealant, and simultaneously, fill rubber and vulcanize gaps around the flap, thereby realizing the sealing of the structure.
When the aircraft is subjected to routine maintenance and troubleshooting repair in the later stage, various covers are required to be disassembled, and because the number of the covers is large, the shapes, the sizes and the screw intervals are all different, the existing disassembly method is to use a straight screwdriver to pry the covers open through gaps between the covers and the skin mouth frame, but series of defects exist in the construction by using the screwdriver: firstly, damage to a surface paint layer, a vulcanized rubber layer, a covering cap and the edges of skin parts at a gap cannot be avoided, and polishing repair and glue repair and paint repair operations are required to be carried out on the damaged parts during the recovery and installation; and secondly, under the long-term pressure of the screw, the inner surface of the cover is completely attached to the adhesive layer to form larger adhesive force, and the gap between the two layers is small, so that the disassembly difficulty is high, and the surface quality of the aircraft is seriously influenced while a large amount of time is consumed.
Therefore, in order to reduce the disassembly difficulty, not damage the parts and ensure the surface quality, the embodiment of the application provides an aircraft flap disassembly device, as shown in fig. 1-13, comprising: fixed support 2, locating pin 1, slip optical axis 6 and lifting mechanism, wherein: a first surface of the fixed support 2 is provided with a mounting hole in the vertical direction; the locating pin 1 is matched with the mounting hole, the locating pin 1 is matched with the fixed support 2 through a boss, the second end of the locating pin 1 penetrates through the fixed support 2, a conical table is arranged at the second end of the locating pin 1, and the conical table is used for penetrating through a screw nest on the flap 12 and matched with the inner surface of the flap 12; the sliding optical axis 6 is horizontally arranged, the sliding optical axis 6 movably penetrates through the fixed support 2, a first end of the sliding optical axis 6 is positioned inside the fixed support 2, and a second end of the sliding optical axis 6 is positioned outside the fixed support 2; the lifting mechanism is used to lift the vertical height of the second end of the sliding optical axis 6.
In this embodiment, the screw nest of seting up when utilizing design flap 12 carries out the dismantlement of flap 12, the quality hidden danger that the prying brought from the gap has effectively been avoided, through mounting support 2, slip optical axis 6 and lifting mechanism, form lever structure in order to be favorable to applying ascending pulling force to flap 12, this pulling force passes through the tip of locating pin 1 and realizes, the screw nest of seting up when the flap 12 is installed is passed to the tip of locating pin 1, owing to its tip is provided with the toper platform, can reverse hook the internal surface of flap 12 behind penetrating flap 12, under lifting mechanism's effect, slip optical axis 6 upwards lifts up the flap 12 that forms the integral connection with mounting support 2, from this can be lifted up flap 12 by screw nest place, easy and simple to handle degree of difficulty is low, can realize the quick dismantlement of flap 12, and can not pry the spare part, the damage has been avoided, the quality of aircraft surface after flap 12 dismantlement has been effectively guaranteed.
The purpose of the lifting mechanism is to lift the second end of the sliding optical axis 6 upwards, so that the flap 12 can be lifted, as in the embodiment of the present application, by rotating the universal cup 9, or by a telescopic rod driven by a cylinder or a motor, and the telescopic rod can lift the sliding optical axis 6 upwards when extending; or a tool such as a jack is adopted, so that the pressure can be slowly and stably applied, and the flap 12 can be stably lifted.
The outer structure of the positioning pin 1 is shown in fig. 7, the middle part of the positioning pin is provided with a stage for being matched with the first surface of the fixed support 2 when the positioning pin is inserted into the mounting hole, the positioning pin 1 enables the fixed support 2 and the cover 12 to form a whole under the condition that the conical stage tightens the cover 12, and the fixed support 2 is pried up and drives the cover 12 to lift up under the leverage effect. The internal structure of the locating pin 1 is shown in fig. 5 and 6, the first end of the locating pin can be pressed downwards, the spring 11 sleeved in the locating pin can be compressed, on one hand, the locating pin 1 can be spirally tightened, on the other hand, the upward elastic force of the spring 11 is used for controlling the length of the locating pin 1 inserted into a screw socket when the locating pin 1 is not screwed down, the conical table of the locating pin 1 is effectively prevented from entering a rubber pad interlayer 14 of the hole wall, in a covering 13 mouth frame and nut structure, the conical table is similar to an expansion bolt, the movement of the conical table when the conical table enters the screw socket is smooth, the diameter of the second end of the locating pin 1 can be enlarged when the conical table acts, and therefore, the conical table can hook the inner surface of a cover 12 when the locating pin 1 is reversely moved.
The description of the components in this embodiment is based on the use state shown in fig. 4, where the top end of the component is the first end thereof and the bottom end of the component is the second end thereof in the vertical direction; in the horizontal direction, one end of the component, which is positioned on the left side, is a first end of the component, and one end of the component, which is positioned on the right side, is a second end of the component; the top surface of the component is its first surface and the bottom surface of the component is its second surface.
In one example, as shown in fig. 1, 2 and 13, an embodiment of a lifting mechanism is provided, specifically: the lifting mechanism comprises a universal foot cup 9 and a rotary handle 8, wherein: the rod part of the universal foot cup 9 penetrates through the second end of the sliding optical axis 6, the axis of the universal foot cup 9 is perpendicular to the axis of the sliding optical axis 6, and the rod part of the universal foot cup 9 is in threaded connection with the sliding optical axis 6; the rotating handle 8 is connected with the rod part of the universal cup 9 and one end far away from the sliding optical axis 6, and the axis of the rotating handle 8 is perpendicular to the axis of the universal cup 9.
According to the above embodiment, the lifting mechanism which is convenient for field implementation and stable in lever is provided, after the fixed support 2 is connected with the flap 12, the rotating force is applied to the universal foot cup 9 through the rotating handle 8, so that the labor can be saved, the bottom of the universal foot cup 9 is abutted with the machine body, the universal foot cup cannot move downwards further, and the second end of the sliding optical axis 6 moves upwards relatively to realize lifting. Moreover, as the rod part and the bottom part in the structure of the universal foot cup 9 are connected through the ball hinge, the stress direction can be adjusted, even if the lever is inclined in the lifting process, the bottom part of the universal foot cup 9 can be tightly attached to the machine body, so that force application on different angle planes and curved surfaces can be realized, the bottom part of the universal foot cup 9 can be provided with a protection pad 10, and the force application surface is ensured not to be damaged. Based on the purpose similar to the protection pad 10, the second surface of the fixed support 2 can be covered with a rubber pad 4, and the rubber pad 4 is connected with the fixed support 2 in a cementing manner, so that the damage to the flap 12 or the skin 13 can be avoided when the flap is stressed, and the static friction force is further increased, thereby being beneficial to the detachment of the flap 12.
In an embodiment, as shown in fig. 1 and fig. 3, in order to make the lifting of the lever smoother and the stress more uniform, the sliding optical axes 6 are two, and the two sliding optical axes 6 are symmetrically arranged about the vertical axis of the fixed support 2, because the two sliding optical axes 6 are arranged, in order to realize synchronous lifting, a connecting block 7 is added for the lifting mechanism, two ends of the connecting block 7 are respectively connected with the second end of one sliding optical axis 6, on the basis, in order to avoid toppling to one side during lifting, the universal foot cup 9 is not connected with the sliding optical axes 6 in the embodiment, but only needs to be connected with the middle part of the connecting block 7 through threads of the rod part of the universal foot cup, and in order to ensure that enough operation adjustment space exists at the bottom of the universal foot cup 9, the connecting block can adopt an arch-shaped connecting block with a symmetrical structure as shown in fig. 12.
In an embodiment, as shown in fig. 2 and 11, a flange linear bearing 5 is added to the device, the flange linear bearing 5 is arranged on the fixed support 2, the sliding optical axis 6 is matched with the flange linear bearing 5, on one hand, the structure that the sliding optical axis 6 penetrates through the through hole forming part of the fixed support 2 is stabilized, on the other hand, sliding connection is formed between the sliding optical axis 6 and the flange linear bearing 5, when the arm of force is adjusted, namely, the distance between the second end of the sliding optical axis 6 and the fixed support 2 is adjusted, and the sliding optical axis 6 has stronger stability under the friction when moving along the through hole. Further, in order to avoid that the sliding optical axis 6 breaks away from the fixed support 2, the first end of the sliding optical axis 6 penetrates through the fixed support 2 and is provided with a limiting block, and the size of the limiting block is larger than that of the penetrating hole, so that further movement of the sliding optical axis 6 is effectively prevented.
In one embodiment, as shown in fig. 1, fig. 3 and fig. 8, in order to make the initial area smaller when the flap 12 is lifted, to form local pulling to damage the flap 12, two positioning pins 1 are provided, two mounting holes are correspondingly provided, one positioning pin 1 is respectively matched with one mounting hole, the arrangement direction of the two positioning pins 1 is perpendicular to the axis direction of the sliding optical axis 6, the two positioning pins 1 are respectively matched with one screw socket when working, and the part between the two screw sockets can be used as the lifting part of the initial flap 12. Further, since the aircraft flap has a plurality of shapes and sizes, the arrangement of the screw sockets is different, and therefore, any mounting hole is arranged as a strip hole as shown in fig. 8, and the extending direction of the strip hole is perpendicular to the axial direction of the sliding optical axis 6, so that the positioning pin 1 in the strip hole can move along the strip hole to be matched with the screw sockets with different distances.
In one embodiment, as shown in fig. 1 and fig. 9, a limiting cover 3 is arranged on a first surface of the fixed support 2, a bar-shaped notch is formed in the limiting cover 3, the size of the bar-shaped notch is matched with the size of the mounting hole, the limiting cover 3 can be fixed through bolts to limit the moving range of the positioning pin 1, the device is integrated, and the positioning pin 1 is convenient to replace when a problem occurs.
Based on the same inventive concept as the previous embodiments, the embodiments of the present application further provide a method for disassembling an aircraft flap, as shown in fig. 14, by adopting the method for disassembling an aircraft flap according to the embodiments of the present application, the method includes the following steps:
s10: positioning the device: the bolts on the flap 12 are removed and the second face of the fixing support 2 is fitted to the surface of the flap 12 so that the positioning pins 1 are aligned with the bolt sockets from which the bolts are removed.
S20: and (5) tensioning the mouth cover: the second end of the positioning pin 1 is penetrated through the rubber pad interlayer 14 until a tapered table provided on the second end of the positioning pin 1 is reversely hooked on the inner surface of the flap 12 to tighten the flap 12.
S30: arm of force adjusts: the sliding optical axis 6 is moved to adjust the distance between its second end and the fixed support 2.
S40: and (3) lifting a lever: the second end of the sliding optical axis 6 is lifted by the lifting mechanism, so that the part of the cover 12 hooked by the conical table is lifted upwards, and the cover 12 is separated from the machine body.
The principle and beneficial effects of the embodiment can refer to the embodiment of the aircraft flap dismounting device, under the simple operation, the difficulty of dismounting is greatly reduced, the quick dismounting of the flap 12 can be realized, and under the conditions of uniform applied force and in-place protective measures, the damage to parts can be hardly caused, and the surface quality is ensured.
In sum, the embodiment of the application provides an aircraft flap dismounting device and aircraft flap dismounting method, utilize the screw nest of seting up when designing the flap to carry out the dismantlement of flap, effectively avoided prying the quality hidden danger that brings from the gap, through the fixed bolster, sliding optical axis and lifting mechanism, form lever structure in order to be favorable to applying ascending pulling force to the flap, this pulling force passes through the tip realization of locating pin, the screw nest of seting up when the locating pin's tip passes the flap installation, owing to its tip is provided with the toper platform, can backward hook the internal surface of flap behind the penetrating flap, under lifting mechanism's effect, sliding optical axis upwards lifts up the flap that forms bulk connection with the fixed bolster, from this can upwards lift the flap by screw nest place, easy and simple to handle degree of difficulty is low, can realize the quick dismantlement of flap, and can pry, the extrusion to spare part, the damage has been avoided, the quality of aircraft surface after the flap dismantlement has been effectively guaranteed.
The foregoing description of the preferred embodiments of the present application is not intended to limit the invention to the particular embodiments of the present application, but to limit the scope of the invention to the particular embodiments of the present application.
Claims (10)
1. An aircraft flap removal device, comprising:
the fixing support is provided with a mounting hole in the vertical direction on the first surface;
the locating pin is matched with the mounting hole, the locating pin is matched with the fixed support through a boss, the second end of the locating pin penetrates through the fixed support, a conical table is arranged at the second end of the locating pin, and the conical table is used for penetrating through a screw nest on the opening cover and is matched with the inner surface of the opening cover;
the sliding optical axis is horizontally arranged, the sliding optical axis movably penetrates through the fixed support, the first end of the sliding optical axis is positioned in the fixed support, and the second end of the sliding optical axis is positioned outside the fixed support;
and the lifting mechanism is used for lifting the vertical height of the second end of the sliding optical axis.
2. The aircraft flap removal device of claim 1, wherein the lifting mechanism comprises a gimbaled cup and a swivel handle, wherein:
the rod part of the universal foot cup penetrates through the second end of the sliding optical axis, the axis of the universal foot cup is perpendicular to the axis of the sliding optical axis, the rod part of the universal foot cup is in threaded connection with the sliding optical axis, and the bottom of the universal foot cup is used for being abutted with a machine body near the opening cover;
the rotary handle is connected with the rod part of the universal foot cup and one end far away from the sliding optical axis, and the axis of the rotary handle is perpendicular to the axis of the universal foot cup.
3. The aircraft flap removal device of claim 2, wherein two of the sliding optical axes are provided, the two sliding optical axes being symmetrically disposed about a vertical axis of the fixed mount;
the lifting mechanism further comprises a connecting block, two ends of the connecting block are respectively connected with the second end of the sliding optical axis, and the rod portion of the universal foot cup is in threaded connection with the middle of the connecting block.
4. The aircraft flap removal device of claim 1, further comprising a flange linear bearing disposed on the fixed mount, the sliding optical axis mating with the flange linear bearing.
5. The aircraft flap removal device of claim 1, wherein a first end of the sliding optical axis extends through the fixed mount, the first end of the sliding optical axis being provided with a stopper.
6. The aircraft flap removing device according to claim 1, wherein two positioning pins are provided, two mounting holes are provided, one positioning pin is respectively engaged with one mounting hole, and an arrangement direction of the two positioning pins is perpendicular to an axis direction of the sliding optical axis.
7. The aircraft door removal device of claim 6, wherein any of the mounting holes is a bar-shaped hole extending in a direction perpendicular to an axis of the sliding optical axis.
8. The aircraft flap removal device of claim 1, wherein a retaining cap is disposed on the first face of the mounting bracket, the retaining cap is provided with a bar-shaped slot, and the size of the bar-shaped slot is matched with the size of the mounting hole.
9. The aircraft flap removal device of claim 1, wherein the second face of the stationary support is covered with a rubber pad.
10. Method for removing an aircraft flap, characterized in that an aircraft flap removing device according to any one of claims 1-9 is used, comprising the following steps:
disassembling a bolt on the opening cover, and attaching a second surface of the fixed support to the surface of the opening cover so as to align a positioning pin with a screw nest from which the bolt is disassembled;
penetrating the second end of the locating pin through the rubber pad interlayer until a conical table arranged on the second end of the locating pin reversely hooks the inner surface of the opening cover so as to tighten the opening cover;
moving the sliding optical axis to adjust the distance between the second end thereof and the fixed support;
and lifting the second end of the sliding optical axis by using the lifting mechanism so as to lift the part of the cover hooked by the conical table upwards, thereby completing the separation of the cover and the machine body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310675836.0A CN116394199B (en) | 2023-06-08 | 2023-06-08 | Aircraft flap dismounting device and aircraft flap dismounting method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN216035073U (en) * | 2021-08-12 | 2022-03-15 | 陕西飞机工业有限责任公司 | Detachable process maintenance covering cap capable of being used in aircraft cabin |
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| CN116394199B (en) | 2023-10-03 |
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