CN108516102B - Flexible general aircraft support tool - Google Patents
Flexible general aircraft support tool Download PDFInfo
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- CN108516102B CN108516102B CN201810400770.3A CN201810400770A CN108516102B CN 108516102 B CN108516102 B CN 108516102B CN 201810400770 A CN201810400770 A CN 201810400770A CN 108516102 B CN108516102 B CN 108516102B
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- jacking device
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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
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
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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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- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Conveying And Assembling Of Building Elements In Situ (AREA)
Abstract
The invention discloses a flexible general aircraft support tool, which comprises a aircraft nose jacking device for supporting a general aircraft at the aircraft nose of the general aircraft and a wing jacking device for supporting the general aircraft at the wing of the general aircraft, wherein the relative position and/or distance between the wing jacking device and the aircraft nose jacking device can be adjusted. The flexible general aircraft support tool disclosed by the invention realizes the control on the lifting of the general aircraft during the assembly and maintenance of the general aircraft, is convenient for the assembly and maintenance of the general aircraft, can be disassembled into a free state, is convenient to avoid obstacles and push into the bottom of the general aircraft, has a simple structure, is convenient to use, has low cost, is easy to maintain, and improves the working efficiency.
Description
Technical Field
The invention belongs to the technical field of general aviation auxiliary equipment, and particularly relates to a flexible general aircraft support tool.
Background
Along with the gradual release of the low-altitude airspace of China and the intensive release of the navigation related good policy, the navigation industry of China has burst development. The aircraft assembly is a technical work with large technical difficulty, wide subject and high comprehensive integration level, determines the final quality, manufacturing cost and period of the aircraft, is a huge obstacle restricting the quick development of the aircraft in China, and is a major bottleneck restricting the development of the aircraft assembly technology. Likewise, maintenance of a general-purpose aircraft is also affected by tooling development delays.
In the field of general aircraft assembly and maintenance, tools for lifting and supporting an aircraft are required. The existing general aircraft support tool is complex in structure, inconvenient to use, influences working efficiency and cannot ensure stability of the general aircraft in the assembly and maintenance processes.
Disclosure of Invention
The present invention aims to solve at least one of the technical problems existing in the prior art. Therefore, the invention provides a flexible general aircraft support tool, which aims to facilitate the assembly and maintenance of a general aircraft.
In order to achieve the above purpose, the technical scheme adopted by the invention is as follows: the flexible general aircraft support tool comprises a aircraft nose jacking device for supporting a general aircraft at the aircraft nose of the general aircraft and a wing jacking device for supporting the general aircraft at the wing of the general aircraft, wherein the relative position and/or distance between the wing jacking device and the aircraft nose jacking device are adjustable.
The flexible general aircraft support tool also comprises a first truss connected with the aircraft nose jacking device and the wing jacking device and a second truss connected with the first truss and the aircraft nose jacking device and used for enabling the aircraft nose jacking device and the wing jacking device to be kept relatively fixed.
The two wing jacking devices are connected with the aircraft nose jacking device through one first truss respectively, each first truss is connected with one second truss respectively, and the second trusses are detachably connected with the aircraft nose jacking device.
The machine head jacking device comprises a central base, a central supporting column movably arranged on the central base, a machine body bracket arranged on the central supporting column and used for supporting the general aircraft, and a binding belt connected with the machine body bracket and used for binding the machine head of the general aircraft.
The machine head jacking device further comprises a central hydraulic cylinder which is arranged on the central base and used for controlling the central support column to move along the vertical direction.
The central base comprises a central guide column, a first central supporting leg, a second central supporting leg and casters, wherein the central guide column is vertically arranged, the first central supporting leg and the second central supporting leg are connected with the central guide column, the casters are arranged on the first central supporting leg and the second central supporting leg, and the central supporting column and the central hydraulic cylinder are arranged in the central guide column.
The wing jacking device comprises a side base, a side support column movably arranged on the side base, a wing bracket arranged on the side support column and used for providing support for a general aircraft, and a side hydraulic cylinder arranged on the side base and used for controlling the side support column to move along the vertical direction.
The side base comprises a side guide column, a first side support leg, a second side support leg and a castor, wherein the side guide column is vertically arranged, the first side support leg and the second side support leg are connected with the side guide column, the castor is arranged on the first side support leg and the second side support leg, and the side support column and the side hydraulic cylinder are arranged in the side guide column.
The first end of the first truss is rotationally connected with the central base, the second end of the first truss is fixedly connected with the side base, and the second end of the first truss is rotationally connected with the second truss.
The first end of the second truss is detachably connected with the central base, and the second end of the second truss is rotatably connected with the second end of the first truss.
The flexible general aircraft support tool disclosed by the invention realizes the control on the lifting of the general aircraft during the assembly and maintenance of the general aircraft, is convenient for the assembly and maintenance of the general aircraft, can be disassembled into a free state, is convenient to avoid obstacles and push into the bottom of the general aircraft, has a simple structure, is convenient to use, has low cost, is easy to maintain, and improves the working efficiency.
Drawings
The present specification includes the following drawings, the contents of which are respectively:
FIG. 1 is a schematic structural view of a flexible general aircraft support tooling of the present invention;
FIG. 2 is a front view of the flexible general aircraft support tooling of the present invention;
FIG. 3 is a side view of the flexible universal aircraft support tooling of the present invention;
FIG. 4 is a top view of the flexible general aircraft support tooling of the present invention;
FIG. 5 is a cross-sectional view A-A of FIG. 2;
FIG. 6 is a cross-sectional view B-B of FIG. 3;
FIG. 7 is an enlarged view at A in FIG. 2;
FIG. 8 is an enlarged view at A in FIG. 2;
FIG. 9 is an enlarged view of FIG. 3 at B;
FIG. 10 is an enlarged view of FIG. 4 at C;
FIG. 11 is a schematic view of the structure of the first truss;
FIG. 12 is a schematic view of the structure of the second truss;
marked in the figure as: 1. casters; 2. a manual hydraulic pump; 3. a first truss; 301. a first cross beam; 302. a first stringer; 4. a second truss; 401. a second cross beam; 402. a third cross beam; 403. a second stringer; 404. a tab; 405. a connecting plate; 406. an avoidance groove; 5. a central hydraulic cylinder; 6. a first central leg; 601. a first connecting rod; 602. a second connecting rod; 603. a third connecting rod; 7. a second central leg; 8. a central guide post; 9. a limiting pin; 10. a central support column; 11. a cushion block; 12. a fuselage bracket; 13. a strap; 14. a side hydraulic cylinder; 15. a first side leg; 16. a second side leg; 17. a side guide post; 18. a side support column; 19. a wing bracket; 20. a first nut; 21. a first bolt; 22. a second bolt; 23. a second nut; 24. a gasket.
Detailed Description
The following detailed description of the embodiments of the invention, given by way of example only, is presented in the accompanying drawings to aid in a more complete, accurate and thorough understanding of the concepts and aspects of the invention, and to aid in its practice, by those skilled in the art.
As shown in fig. 1 to 12, the present invention provides a flexible general aircraft support tooling, comprising a nose jacking device for providing support to a general aircraft at the nose of the general aircraft and a wing jacking device for providing support to the general aircraft at the wing of the general aircraft, wherein the relative position and/or distance between the wing jacking device and the nose jacking device is adjustable.
Specifically, as shown in fig. 1 to 4, the number of the wings of the general aircraft is two, correspondingly, the number of the wing jacking devices is two, one aircraft nose jacking device is arranged, the two wing jacking devices respectively provide a supporting effect for one wing of the general aircraft, and one aircraft nose jacking device provides a supporting effect for the aircraft nose of the general aircraft, so that the control on lifting of the general aircraft is realized jointly when the general aircraft is assembled and maintained, and the assembly and maintenance of the general aircraft are facilitated. The two wing jacking devices are matched with one aircraft nose jacking device to form three-point support for the general aircraft, so that the general aircraft is ensured to be supported stably.
As shown in fig. 1 to 4, the flexible general aircraft support tool of the present invention further includes a first truss 3 connected to the aircraft nose jacking device and the wing jacking device, and a second truss 4 connected to the first truss 3 and the aircraft nose jacking device and used for maintaining the aircraft nose jacking device and the wing jacking device relatively fixed. Two wing jacking devices are connected with the aircraft nose jacking device through a first truss 3 respectively, each first truss 3 is connected with a second truss 4 respectively, the second trusses 4 are detachably connected with the aircraft nose jacking device, namely, the first trusses 3 and the second trusses 4 are both arranged two, the first end of the first truss 3 is rotationally connected with the aircraft nose jacking device, the second end of the first truss 3 is fixedly connected with the wing jacking device, the first end of the second truss 4 is detachably connected with the aircraft nose jacking device, the second end of the first truss 3 is rotationally connected with the second end of the first truss 3, and the rotation center line of the rotation connecting point of the first truss 3 and the rotation center line of the rotation connecting point of the second truss 4 and the first truss 3 is parallel and is positioned in a vertical plane. After the second truss 4 is dismounted with the aircraft nose jacking device, the second truss 4 and the aircraft nose jacking device can rotate relative to the first truss 3, so that the included angle between the two first trusses 3 is adjustable, the relative position and/or distance between the wing jacking device and the aircraft nose jacking device are/is adjustable, the supporting tool is opened to a free state, the space occupied by the whole supporting tool in moving and storing can be reduced, the whole supporting tool can be conveniently moved, the supporting tool can easily avoid obstacles such as an aircraft landing gear in the bottom process of being pushed into a general aircraft, the use is convenient, and the assembly and maintenance work efficiency can be improved.
As shown in fig. 1 to 4, 6 and 7, the head jacking device includes a central base, a central support column 10 movably provided on the central base, a body bracket 12 provided on the central support column 10 for providing support to the general aircraft, and a strap 13 connected to the body bracket 12 for tying up the head of the general aircraft. The central support column 10 is vertically arranged, the body bracket 12 is arranged above the central support column 10, the body bracket 12 is fixedly connected with the upper end of the central support column 10, the body bracket 12 provides a supporting effect for the aircraft nose of the general aircraft below the aircraft nose of the general aircraft, the lower end of the central support column 10 is inserted into the central base, the central support column 10 can move relative to the central base along the vertical direction, the central base provides a guiding effect for the central support column 10, and stable support for the general aircraft can be ensured. The binding belt 13 is fixedly connected with the machine body bracket 12, the binding belt 13 is arranged to encircle the machine head of the general aircraft and bind the machine head, so that the fixed connection between the machine head and the machine head jacking device is realized, the relative movement between the general aircraft and the supporting tool is avoided, and the safety and the reliability during assembly and maintenance work are improved.
As shown in fig. 1 to 4 and 6, the head jacking device further includes a central hydraulic cylinder 5 provided on the central base for controlling the central support column 10 to move in the vertical direction. The central hydraulic cylinder 5 is vertically arranged in the central base, the central hydraulic cylinder 5 is positioned below the central supporting column 10, the central hydraulic cylinder 5 is a hydraulic cylinder which can stretch along the vertical direction, the cylinder body of the central hydraulic cylinder 5 is connected with the central base, and the piston rod of the central hydraulic cylinder 5 is connected with the central supporting column 10. When the central hydraulic cylinder 5 stretches, the central support column 10 can be pushed to move upwards, and then the lifting of the universal aircraft nose can be realized. When the general aircraft is lifted in place, the central hydraulic cylinder 5 provides support for the central support column 10, so that the fuselage bracket 12 can provide support for the aircraft nose of the general aircraft, and the aircraft can slowly land once the hydraulic system leaks, so that the aircraft cannot be damaged to a higher degree due to hard impact to the ground. The central base is provided with a light manual hydraulic pump 2 for extending and contracting the central hydraulic cylinder 5, the manual hydraulic pump 2 is connected with the central hydraulic cylinder 5 through a hydraulic pipeline, the manual hydraulic pump 2 is used for converting manual mechanical energy into hydraulic energy, and an operator can realize lifting control of a general aircraft through manual operation of the manual hydraulic pump 2.
As shown in fig. 1 to 4, 6 and 7, the center base includes a center guide post 8 provided vertically, first and second center legs 6 and 7 connected to the center guide post 8, and casters 1 provided on the first and second center legs 6 and 7, and a center support post 10 and a center hydraulic cylinder 5 are provided inside the center guide post 8. The central guide column 8 is of a structure with an opening at the upper end and a hollow interior, the central hydraulic cylinder 5 is fixedly arranged in the inner cavity of the central guide column 8, the cylinder body of the central hydraulic cylinder 5 is connected with the lower end of the central guide column 8, the central support column 10 is inserted into the inner cavity of the central guide column 8, the central support column 10 can move along the vertical direction relative to the central guide column 8, and the machine body bracket 12 is positioned above the central guide column 8. The first central supporting leg 6 and the second central supporting leg 7 are fixedly connected with the central guide post 8, the first central supporting leg 6 and the second central supporting leg 7 are horizontally arranged, the first central supporting leg 6 and the second central supporting leg 7 are located at the same height, the length direction of the first central supporting leg 6 is perpendicular to the length direction of the second central supporting leg 7, the length direction of the body bracket 12 is parallel to the length direction of the second central supporting leg 7, and the second central supporting leg 7 is located below the body bracket 12. The central guiding column 8 is fixedly connected with the second central supporting leg 7 at the middle position of the second central supporting leg 7 in the length direction, one end of the first central supporting leg 6 is fixedly connected with the central guiding column 8, and the other end of the first central supporting leg 6 is connected with the second truss 4 and detachably connected with the second truss 4. The first central supporting leg 6 is provided with the truckle 1, the second central supporting leg 7 is provided with the two truckles 1, the two truckles 1 on the second central supporting leg 7 are respectively and fixedly arranged at one end of the second central supporting leg 7 in the length direction, namely, the central base is provided with the three truckles 1, the three truckles 1 are distributed in three points, the truckles 1 are in contact with the ground and can roll on the ground, and an operator can conveniently push and support the whole tool to move.
The first central supporting leg 6 and the second central supporting leg 7 are made of square steel, the central supporting column 10 and the central guide column 8 are cylindrical, and the formed central base is simple in structure, low in cost, high in strength, good in stability and easy to maintain. As shown in fig. 1 to 4, fig. 6 and fig. 7, the machine head jacking device further comprises a limiting pin 9 for limiting the central supporting column 10, the limiting pin 9 is located above the central guiding column 8, the central supporting column 10 is provided with limiting holes allowing the limiting pin 9 to pass through, the limiting holes are formed in a plurality, all the limiting holes are sequentially formed in the central supporting column 10 along the vertical direction and are equidistantly distributed, the limiting pin 9 can be selectively inserted into one of the limiting holes, the length of the limiting pin 9 is larger than the diameter of the upper end opening of the central guiding column 8, the limiting pin 9 is inserted into one limiting hole of the central guiding column 8, two ends of the limiting pin 9 extend out of the limiting holes, the central guiding column 8 is used for limiting the limiting pin 9 below the limiting pin 9, the limiting pin 9 can further serve for limiting the central supporting column 10 in the vertical direction, and damage caused by hard impact of a general plane to the ground due to failure of a hydraulic system during operation is avoided, and safety and reliability are improved.
As shown in fig. 1 and 6, preferably, the body bracket 12 is provided with a cushion block 11 for contacting with the general aircraft, the cushion block 11 is made of soft material, for example, the cushion block 11 is made of foam material, the body bracket 12 is made of metal material, and the body bracket 12 is not in direct contact with the nose of the general aircraft, but is in contact with the nose of the general aircraft through the cushion block 11, so that a supporting effect is provided for the general aircraft, and damage to the general aircraft can be avoided.
As shown in fig. 1 to 5, the wing jacking device includes a side base, a side support column 18 movably disposed on the side base, a wing bracket 19 disposed on the side support column 18 and used for providing support for the general aircraft, and a side hydraulic cylinder 14 disposed on the side base and used for controlling the side support column 18 to move in a vertical direction. The side support column 18 is vertical setting, and wing bracket 19 sets up in the upper end of side support column 18, wing bracket 19 and with the upper end fixed connection of side support column 18, side support column 18 provides the supporting role to the wing of general aircraft in general aircraft's wing below, and the inside of side base is inserted to the lower extreme of side support column 18, and side support column 18 can follow vertical direction for the side base and remove, and the side base provides the guiding role to side support column 18, ensures to provide stable support to general aircraft. The side hydraulic cylinder 14 is vertically arranged in the side base, the side hydraulic cylinder 14 is located below the side support column 18, the side hydraulic cylinder 14 is a hydraulic cylinder which is telescopic along the vertical direction, a cylinder body of the side hydraulic cylinder 14 is connected with the side base, and a piston rod of the side hydraulic cylinder 14 is connected with the side support column 18. When the side hydraulic cylinder 14 is extended, the side support column 18 can be pushed to move upwards, so that the lifting of the wing of the general aircraft can be realized. When the general aircraft is lifted in place, the side hydraulic cylinders 14 provide support for the side support columns 18, so that the wing brackets 19 can provide support for the wings of the general aircraft, and the hydraulic support is adopted, so that once the hydraulic system leaks, the aircraft can slowly land without being damaged to a higher degree due to hard impact to the ground. Be equipped with the light-duty manual hydraulic pump 2 that is used for side pneumatic cylinder 14 to stretch out and draw back on the side base, manual hydraulic pump 2 is connected with side pneumatic cylinder 14 through the hydraulic line, and manual hydraulic pump 2 is used for converting manual mechanical energy into hydraulic energy, and operating personnel can realize the lift control to general aircraft through manual operation manual hydraulic pump 2.
As shown in fig. 1 to 5, the side base includes a vertically disposed side guide column 17, first and second side legs 15 and 16 connected to the side guide column 17, and casters 1 disposed on the first and second side legs 15 and 16, and a side support column 18 and a side hydraulic cylinder 14 are disposed inside the side guide column 17. The side guide column 17 is an open-ended and hollow structure, the side hydraulic cylinder 14 is fixedly arranged in the inner cavity of the side guide column 17, the cylinder body of the side hydraulic cylinder 14 is connected with the lower end of the side guide column 17, the side support column 18 is inserted into the inner cavity of the side guide column 17, the side support column 18 can move along the vertical direction relative to the side guide column 17, and the wing bracket 19 is positioned above the side guide column 17. The first side support leg 15 and the second side support leg 16 are fixedly connected with the side guide column 17, the first side support leg 15 and the second side support leg 16 are horizontally arranged, the first side support leg 15, the second side support leg 16, the first central support leg 6 and the second central support leg 7 are all located at the same height, the second side support leg 16 is located below the first truss 3 and the second truss 4, and the length direction of the first side support leg 15 is perpendicular to the length direction of the second side support leg 16. The side guide post 17 is in the middle position department and the second side landing leg 16 fixed connection of the length direction of second side landing leg 16, the one end and the side guide post 17 fixed connection of first side landing leg 15, the other end of first central landing leg 6 is provided with a truckle 1, set up two truckles 1 on the second side landing leg 16, two truckles 1 on the second side landing leg 16 are fixed setting respectively in the length direction's of second side landing leg 16 one end, namely the side base has three truckles 1, three truckles 1 are three point distribution, truckle 1 and ground contact and can roll subaerial, the operating personnel of being convenient for promotes and supports the frock and wholly remove.
The first side support leg 15 and the second side support leg 16 are made of square steel, the side support column 18 and the side guide column 17 are cylindrical, and the formed side base is simple in structure, low in cost, high in strength, good in stability and easy to maintain. As shown in fig. 1 to 5 and 9, the wing jacking device further comprises a limiting pin 9 for limiting the side support column 18, the limiting pin 9 is located above the side guide column 17, the side support column 18 is provided with limiting holes allowing the limiting pin 9 to pass through, the limiting holes are formed in a plurality of positions, all the limiting holes are sequentially formed in the side support column 18 in the vertical direction and are equidistantly distributed, the limiting pin 9 can be selectively inserted into one of the limiting holes, the length of the limiting pin 9 is larger than the diameter of an upper end opening of the side guide column 17, the limiting pin 9 is inserted into one limiting hole of the side guide column 17, two ends of the limiting pin 9 extend out of the limiting holes, the side guide column 17 is used for limiting the limiting pin 9 below the limiting pin 9, the limiting pin 9 can further serve as a limiting effect on the side support column 18 in the vertical direction, and the phenomenon that a general plane is hard to impact to the ground due to failure of a hydraulic system during operation is avoided, and safety and reliability are improved.
Preferably, the wing bracket 19 is made of soft material, such as nylon material, the side support columns 18 are made of metal material, and the side support columns 18 are not in direct contact with the wings of the general aircraft, but are in contact with the wings of the general aircraft through the wing bracket 19, so that a supporting effect is provided for the general aircraft, and damage to the general aircraft can be avoided.
As shown in fig. 1 to 9, the first end of the first truss 3 is rotatably connected with the central base through a second fastener, the second end of the first truss 3 is fixedly connected with the side base, the second end of the first truss 3 is rotatably connected with the second end of the second truss 4 through a second fastener, the first end of the second truss 4 is detachably connected with the central base, and the first end of the second truss 4 is connected with the first central leg 6 through a first fastener. The first fastener mainly comprises a first bolt 21 and a first nut 20, the first nut 20 is sleeved on the first bolt 21 and is in threaded connection with the first bolt 21, the first bolt 21 is arranged along the vertical direction, and the second truss 4 and the machine head jacking device are required to be detached and separated, so that the first nut 20 is preferably a butterfly nut, the first nut 20 is positioned above the second truss 4, the screwing operation is facilitated, and the working efficiency is improved. After the first nut 20 is screwed down, the first nut 20 is matched with the first bolt 21, so that the second truss 4 is fixedly connected with the aircraft nose jacking device, and the aircraft nose jacking device is relatively fixed with the two wing jacking devices.
The second fastening piece mainly comprises a second bolt 22, a second nut 23 and a gasket 24, wherein the second nut 23 is sleeved on the second bolt 22 and is in threaded connection with the second bolt 22, and the second nut 23 is preferably a self-locking nut. As shown in fig. 8, the first end of the first truss 3 is connected with the central guide post 8 through a second fastener, the second bolt 22 is vertically arranged, the second nut 23 is located below the first truss 3, the gasket 24 is clamped between the hexagonal head of the second bolt 22 and the first truss 3, the first truss 3 and the central guide post 8 are provided with through holes for the second bolt 22 to pass through, and the axis of the second bolt 22 is the rotation center line at the rotation connection point of the first truss 3 and the head jacking device. As shown in fig. 5, the second end of the first truss 3 is connected with the second truss 4 through a second fastener, the second bolt 22 is vertically arranged, the second nut 23 is located below the first truss 3, the gasket 24 is clamped between the hexagonal head of the second bolt 22 and the second truss 4, the first truss 3 and the second truss 4 are provided with through holes for the second bolt 22 to pass through, and the axis of the second bolt 22 is the rotation center line at the rotation connection point of the first truss 3 and the second truss 4.
As shown in fig. 1 and 10, the first truss 3 includes a first cross beam 301 and a first longitudinal beam 302 that are connected, at least two first cross beams 301 are provided, at least one first longitudinal beam 302 is provided, the first cross beam 301 is horizontally provided and all the first cross beams 301 are sequentially provided along a vertical direction, the first longitudinal beam 302 is vertically provided, the first longitudinal beam 302 is located between two adjacent first cross beams 301 and the first longitudinal beam 302 is fixedly connected with the two first cross beams 301, and all the first longitudinal beams 302 are sequentially arranged along a length direction of the first cross beam 301. Preferably, the first cross beam 301 has an L-shaped structure, one end of the first cross beam 301 is rotatably connected with the central base, the other end of the first cross beam 301 is fixedly connected with the side base, and the end of the first cross beam 301 is rotatably connected with the second truss 4 through a second fastener. In this embodiment, two first cross beams 301 and six first longitudinal beams 302 are provided, the first cross beams 301 and the first longitudinal beams 302 are made of square steel, and the formed first truss 3 has high structural strength.
As shown in fig. 1 and 11, the second truss 4 includes a second beam 401 and a third beam 402 that are arranged oppositely, and a second longitudinal beam 403 fixedly connected to the second beam 401 and the third beam 402, at least one second longitudinal beam 403 is provided, one second beam 401 and one third beam 402 are provided, the second beam 401 is arranged obliquely, the third beam 402 is arranged horizontally, the second longitudinal beam 403 is arranged vertically, the second longitudinal beam 403 is located between the second beam 401 and the third beam 402, and all second longitudinal beams 403 are arranged in sequence along the length direction of the second beam 401. The second crossbeam 401 is located the top of third crossbeam 402, have the contained angle and this contained angle is the acute angle between the length direction of second crossbeam 401 and the length direction of third crossbeam 402, the length of second crossbeam 401 is less than the length of third crossbeam 402, the length direction's of second crossbeam 401 one end and third crossbeam 402 fixed connection, the length direction's of second crossbeam 401 other end is equipped with a connecting plate 405, this connecting plate 405 is through the second fastener with the second end rotation of first truss 3 be connected, the length direction's of third crossbeam 402 one end also is equipped with a connecting plate 405, this connecting plate 405 is through the second fastener with the second end rotation of first truss 3 be connected, two connecting plates 405 are in same vertical line, two connecting plates 405 all have a through-hole that lets second bolt 22 pass and the through-hole on two connecting plates 405 is coaxial setting. In this embodiment, two second stringers 403 are provided, and the second cross member 401, the third cross member 402 and the second stringers 403 are made of square steel, so that the formed second truss 4 has high structural strength.
As shown in fig. 1, 11 and 12, the second truss 4 further includes a tab 404 fixedly connected to the third beam 402, one end of the third beam 402 in the length direction is fixedly connected to a connecting plate 405, the other end of the third beam 402 in the length direction is fixedly connected to the tab 404, the tab 404 is horizontally disposed, the tab 404 has a certain length, and the tab 404 extends toward the outer side of the third beam 402 along the length direction of the third beam 402. The adjusting piece 404 has a through groove 406 through which the first bolt 21 passes, the through groove 406 is a through groove formed in the adjusting piece 404 so as to extend in the thickness direction of the adjusting piece 404, the first nut 20 is located above the through groove 406, and the first center leg 6 has a through hole through which the first bolt 21 passes, the through hole is located below the through groove 406 and the through hole is aligned with the through groove 406. As the preference, dodge the groove 406 and be L shape, dodge the groove 406 and form the opening that lets first bolt 21 pass through on the side that the axis of adjustment piece 404 and first bolt 21's axis and the length direction of adjustment piece 404 are parallel, dodge the groove 406 that sets up on the adjustment piece 404 and be the open slot, like this when second truss 4 need dismantle and be connected with the aircraft nose jacking device, first bolt 21 moves out and dodges the groove 406 and moves into dodge the groove 406 through the opening on the side of adjustment piece 404, and then be convenient for need dismantle and connect second truss 4 and aircraft nose jacking device, and first fastener still can remain on the aircraft nose jacking device, need not to dismantle first fastener also from the aircraft nose jacking device, convenient operation, help improving efficiency. The avoidance groove 406 extends along the length direction of the adjustment sheet 404, the length of the avoidance groove 406 (the length direction of the avoidance groove 406 is parallel to the length direction of the adjustment sheet 404) is larger than the diameter of the first bolt 21, and the width of the avoidance groove 406 (the width direction of the avoidance groove 406 is horizontal and perpendicular to the length direction of the adjustment sheet 404) is smaller than the outer diameter of the first nut 20.
As shown in fig. 1, 11 and 12, the first central leg 6 is located between two first trusses 3, the first central leg 6 includes a first connecting rod 601, a second connecting rod 602 and a third connecting rod 603 which are sequentially connected, the first connecting rod 601, the second connecting rod 602 and the third connecting rod 603 are horizontally arranged, one end of the first connecting rod 601 is fixedly connected with the central guide post 8, the other end of the first connecting rod 601 is fixedly connected with one end of the second connecting rod 602, the other end of the second connecting rod 602 is fixedly connected with the third connecting rod 603, the length direction of the third connecting rod 603 is parallel to the length direction of the second connecting rod 602, the length direction of the third connecting rod 603 is perpendicular to the length direction of the third connecting rod 603, the third connecting rod 603 is fixedly connected with the two second trusses 4, correspondingly, two through holes allowing the first bolts 21 to pass through are respectively located at one side of the second connecting rod 602, and the two second connecting rods 4 are respectively connected with the third trusses 603 at one side of the second connecting rod 602 through the first connecting rod 603. After the two second trusses 4 are fixedly connected with the first central supporting leg 6, the included angle between the two second trusses 4 in the length direction is 180 degrees, and the whole supporting tool is of a triangular structure.
The invention is described above by way of example with reference to the accompanying drawings. It will be clear that the invention is not limited to the embodiments described above. As long as various insubstantial improvements are made using the method concepts and technical solutions of the present invention; or the invention is not improved, and the conception and the technical scheme are directly applied to other occasions and are all within the protection scope of the invention.
Claims (6)
1. Flexible general aircraft supports frock, its characterized in that: the aircraft nose jacking device is used for supporting the general aircraft at the aircraft nose of the general aircraft, the wing jacking device is used for supporting the general aircraft at the wing of the general aircraft, the relative position and/or distance between the wing jacking device and the aircraft nose jacking device are adjustable, and one aircraft nose jacking device is arranged;
the flexible general aircraft support tool also comprises a first truss connected with the aircraft nose jacking device and the wing jacking device and a second truss connected with the first truss and the aircraft nose jacking device and used for keeping the aircraft nose jacking device and the wing jacking device relatively fixed;
the machine head jacking device comprises a central base, a central supporting column movably arranged on the central base, a machine body bracket arranged on the central supporting column and used for supporting the general aircraft, and a binding belt connected with the machine body bracket and used for binding the machine head of the general aircraft, wherein the central supporting column can move along the vertical direction relative to the central base, and the central base provides a guiding function for the central supporting column;
the wing jacking device comprises a side base, a side support column movably arranged on the side base, a wing bracket arranged on the side support column and used for providing support for the general aircraft, and a side hydraulic cylinder arranged on the side base and used for controlling the side support column to move along the vertical direction;
the first end of the first truss is rotationally connected with the central base, the second end of the first truss is fixedly connected with the side base, and the second end of the first truss is rotationally connected with the second truss;
the first end of the second truss is detachably connected with the central base, and the second end of the second truss is rotatably connected with the second end of the first truss;
the two wing jacking devices are arranged, each wing jacking device is connected with the aircraft nose jacking device through one first truss, each first truss is connected with one second truss, and the second trusses are detachably connected with the aircraft nose jacking device;
the central base comprises a central guide column, a first central supporting leg, a second central supporting leg and casters, wherein the central guide column is vertically arranged, the first central supporting leg and the second central supporting leg are connected with the central guide column, the casters are arranged on the first central supporting leg and the second central supporting leg, and the central supporting column and the central hydraulic cylinder are arranged in the central guide column;
the first central supporting leg and the second central supporting leg are fixedly connected with the central guide post, the first central supporting leg and the second central supporting leg are horizontally arranged, the first central supporting leg and the second central supporting leg are positioned at the same height, the length direction of the first central supporting leg and the length direction of the second central supporting leg are vertical, the length direction of the machine body bracket is parallel to the length direction of the second central supporting leg, and the second central supporting leg is positioned below the machine body bracket;
the central guide post is fixedly connected with the second central support leg at the middle position in the length direction of the second central support leg, one end of the first central support leg is fixedly connected with the central guide post, and the other end of the first central support leg is connected with the second truss and detachably connected with the second truss.
2. The flexible general aircraft support tooling of claim 1, wherein: the machine head jacking device further comprises a central hydraulic cylinder which is arranged on the central base and used for controlling the central support column to move along the vertical direction.
3. The flexible general aircraft support tooling of claim 2, wherein: the central base is provided with a manual hydraulic pump for controlling the central hydraulic cylinder to stretch out and draw back, the manual hydraulic pump is connected with the central hydraulic cylinder through a hydraulic pipeline and is used for converting manual mechanical energy into hydraulic energy, and an operator manually operates the manual hydraulic pump to realize lifting control of the general aircraft.
4. A flexible general aircraft support tooling according to any one of claims 1 to 3, wherein: the fuselage bracket is provided with a cushion block for contacting with the general aircraft, and the cushion block is made of soft materials.
5. A flexible general aircraft support tooling according to any one of claims 1 to 3, wherein: the side base comprises a side guide column, a first side support leg, a second side support leg and a castor, wherein the side guide column is vertically arranged, the first side support leg and the second side support leg are connected with the side guide column, the castor is arranged on the first side support leg and the second side support leg, and the side support column and the side hydraulic cylinder are arranged in the side guide column.
6. The flexible general aircraft support tooling of claim 5, wherein: the first side landing leg with the second side landing leg with side guide post fixed connection, first side landing leg and second side landing leg are the level setting and first side landing leg, second side landing leg, first central landing leg and second central landing leg all are in same height, and the second side landing leg is located the below of first truss and second truss, and the length direction of first side landing leg and the length direction of second side landing leg are mutually perpendicular, side guide post is in the ascending intermediate position department of length direction of second side landing leg and second side landing leg fixed connection, and the one end and the side guide post fixed connection of first side landing leg, and the one end of first central landing leg is provided with a truckle, sets up two truckles on the second side landing leg, and two truckles on the second side landing leg are fixed respectively and are set up the both ends on the length direction of second side landing leg, and the side base has three truckle, and three truckle are three point and distribute.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810400770.3A CN108516102B (en) | 2018-04-28 | 2018-04-28 | Flexible general aircraft support tool |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810400770.3A CN108516102B (en) | 2018-04-28 | 2018-04-28 | Flexible general aircraft support tool |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108516102A CN108516102A (en) | 2018-09-11 |
| CN108516102B true CN108516102B (en) | 2023-09-26 |
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| CN201810400770.3A Active CN108516102B (en) | 2018-04-28 | 2018-04-28 | Flexible general aircraft support tool |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112660413B (en) * | 2021-03-02 | 2023-11-10 | 北京清航紫荆装备科技有限公司 | Movable U-shaped opening tool table of crossed double-rotor unmanned helicopter |
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