CN112720392A - Auxiliary supporting device for dismounting and mounting small aircraft - Google Patents
Auxiliary supporting device for dismounting and mounting small aircraft Download PDFInfo
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- CN112720392A CN112720392A CN202011553380.3A CN202011553380A CN112720392A CN 112720392 A CN112720392 A CN 112720392A CN 202011553380 A CN202011553380 A CN 202011553380A CN 112720392 A CN112720392 A CN 112720392A
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- dismounting
- supporting device
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25H—WORKSHOP EQUIPMENT, e.g. FOR MARKING-OUT WORK; STORAGE MEANS FOR WORKSHOPS
- B25H1/00—Work benches; Portable stands or supports for positioning portable tools or work to be operated on thereby
- B25H1/14—Work benches; Portable stands or supports for positioning portable tools or work to be operated on thereby with provision for adjusting the bench top
- B25H1/16—Work benches; Portable stands or supports for positioning portable tools or work to be operated on thereby with provision for adjusting the bench top in height
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Abstract
The invention relates to the field of airplane equipment, in particular to an auxiliary supporting device for dismounting and mounting a small airplane, which comprises a moving base, a transverse supporting beam and two longitudinal beams, wherein two ends of the moving base are provided with two hollow pipe columns respectively used for inserting the two longitudinal beams, one side of each longitudinal beam is fixedly embedded with a vertical rack, and the upper half part of each hollow pipe column is fixedly provided with a driving mechanism, the longitudinal beam is put down quickly, the whole device is ingenious in structure, flexible and convenient to use, and the adjusting range is more accurate and flexible.
Description
Technical Field
The invention relates to the field of airplane equipment, in particular to an auxiliary supporting device for dismounting and mounting a small airplane.
Background
Light aircraft generally refers to aircraft having a maximum takeoff weight of less than 5700 kilograms. The airplane has the characteristics of portability, safety, low use requirement, capability of taking off and landing on the grassland, easiness in operation, low price and the like. Light aircraft are small, relatively simple in construction, and well suited for leisure and commercial travel. Although some light aircraft are equipped with jet engines, piston engines are typically used to drive propellers. Large high-speed aircraft are equipped with landing gear, and the wheels can be retracted after taking off. Light aircraft are often equipped with fixed foot rests in order to reduce weight and save costs. As new synthetic materials are developed, light aircraft will become stronger, lighter, and can fly farther.
Present light aircraft is when the dismouting is maintained, supports organism, wing and fin through simple and easy bracket to cooperation maintainer carries out the dismouting to organism, wing and tail and maintains, and this type of simple and easy bracket application range is extensive, if: the detachable wing, the supporting tail fin, the placing wing, the supporting fuselage and the like.
As shown in fig. 1 and 2, the existing bracket structure includes a movable supporting base 2, a supporting beam 3 and longitudinal beams 4 fixedly disposed at the bottoms of the two ends of the supporting beam 3, wherein the two longitudinal beams 4 are movably inserted into the movable supporting base 2 downward, each of the longitudinal beams 4 and the movable supporting base 2 is provided with a pin hole, and the longitudinal beams 4 and the movable supporting base 2 can transversely pass through the pin holes through a pin 5, so as to complete the locking of the current height position.
Such a bracket has the following problems in use:
1. when the wing 1 is disassembled and assembled, because the heights of the two ends of the supporting beam 3 are moderate and consistent, and the shape of the wing 1 is mostly of a curved surface structure, in the process of supporting, lifting and installing the wing 1, the wing 1 needs to keep the upward posture of one side and be installed with the fuselage, so that additional personnel need to be added to carry out auxiliary support on the wing 1, and the purpose of enabling one side of the wing 1 to be upward is achieved (as shown in fig. 2).
2. The traditional bracket is simple in construction, the height of the bracket is adjusted in a mode that the bolt 5 is matched with the pin hole, so that the height adjustable range of the bracket is rough and not fine enough, when the longer part of the wing 1 is installed with a fuselage, a plurality of brackets are used for supporting the wing 1 together, the supporting height of the brackets at different positions is required to be adjusted flexibly, and the traditional bolt 5 mode cannot be used for more precise height adjustment.
3. The traditional bracket needs to be matched with two persons at least for use, and because the heights of the two ends of the traditional bracket are adjusted by adopting the mode of the bolt 5, when the heights are adjusted, the two persons need to lift the supporting beam 3 upwards together and then insert the bolt 5 for locking, so that the practical use is very troublesome.
Disclosure of Invention
In order to solve the technical problem, an auxiliary supporting device for dismounting and mounting a small airplane is provided.
In order to achieve the above purposes, the technical scheme adopted by the invention is as follows:
an auxiliary supporting device for dismounting and mounting a small airplane comprises a moving base, a transverse supporting beam and two longitudinal beams which are respectively arranged at the bottoms of the two ends of the transverse supporting beam, wherein two hollow pipe columns which are respectively used for inserting the two longitudinal beams are arranged at the two ends of the moving base, a rack which is in a vertical state is fixedly embedded in one side of each longitudinal beam, and a driving mechanism which is used for driving the corresponding rack to longitudinally move is fixedly arranged at the upper half part of each hollow pipe column;
each driving mechanism comprises a shell, a gear meshed with the rack, a locking mechanism positioned at the center of the gear and a hand-operated rod connected with the gear;
the gear is positioned in the shell, the rack meshed with the gear is lifted in the hollow pipe column through rotation, and a rectangular avoiding hole for avoiding the gear is formed in the pipe wall of the hollow pipe column;
the locking mechanism is positioned on the inner side of the gear, a circle of ratchets are arranged on the inner edge of the gear, and the ratchets are matched with the locking mechanism to prevent the gear from reversely rotating to cause the rack to fall down after the gear drives the rack to rise through rotation;
the hand-operated lever is coaxially and fixedly connected with the gear and is used for driving the gear to rotate;
and the locking mechanism is also provided with an unlocking deflector rod for releasing the reverse rotation locking state of the gear.
Preferably, the tops of the two longitudinal beams are hinged with the bottoms of the two ends of the transverse supporting beam respectively, and the bottom of one end of the transverse supporting beam is provided with a sliding groove structure for providing transverse displacement offset for the lower longitudinal beam.
Preferably, locking mechanism includes runner, rigidity jack catch and torsional spring, the runner is coaxial and fixed to be set up in the inboard of gear, and the outer fringe of runner is equipped with one along self periphery to radial sunken holding tank, be equipped with the axially uniform fixed axle of a length direction and runner in the holding tank, the one end of rigidity jack catch all overlaps with the torsional spring and is located on the fixed axle, and the torsional spring has the trend of popping out the free end of rigidity jack catch to the holding tank outward all the time.
Preferably, the top ends of the two longitudinal beams are respectively provided with an upper hinged support and a lower hinged support which are connected with each other through a shaft, each lower hinged support is fixedly arranged at the top end of the corresponding longitudinal beam, one upper hinged support and one lower hinged support are fixedly arranged at the bottom of one end of the transverse supporting beam, and the other upper hinged support is embedded in the sliding groove structure in a sliding manner.
Preferably, the both sides of gear all are equipped with along the sunken circular caulking groove of self axial, every all be provided with circular end cover plate in the circular caulking groove, the runner is along two axial terminal surfaces of self laminating respectively in two circular end cover plates, the inner wall fixed connection of one of them circular end cover plate and shell, the outside center department of another circular end cover plate is fixed to be equipped with one and is used for supplying the first square shaft that the hand lever cup jointed.
Preferably, the axis direction of the unlocking deflector rod is parallel to the axis direction of the rotating wheel, one end of the unlocking deflector rod is fixedly connected with one side of the free end of the rigid clamping jaw, arc avoiding through grooves used for unlocking the deflector rod arc motion path are formed in the groove wall of the containing groove, the circular end cover plate and the shell, and the other end of the unlocking deflector rod sequentially penetrates through all the arc avoiding through grooves.
Preferably, a first square hole is formed in the center of the rotating wheel, a second square shaft is fixedly inserted into the first square hole, and a second square hole for the second square shaft to be fixedly inserted is formed in the center of the circular end cover plate fixedly connected with the shell.
Preferably, a longitudinal through groove for enabling the gear to contact the rack is formed in the side wall of the longitudinal beam, one side of the tooth end of the rack is flush with the outer wall of the longitudinal beam, and the upper end and the lower end of the longitudinal beam are fixedly embedded with cover sleeves for fixedly connecting the end portions of the rack.
Preferably, the fixed cover in the upper end outside of longeron is equipped with a tenesmus buffer board, the bottom of tenesmus buffer board is fixed and is provided with the one deck shock attenuation glue.
Preferably, the top of the transverse supporting and supporting beam is provided with an anti-skid protective sponge.
The invention has the beneficial effects that: according to the invention, two groups of independent driving mechanisms are arranged for independently driving the longitudinal beams on the two sides to lift, so that the two ends of the transverse supporting beam can be independently adjusted in height, the machine body component can be supported upwards more comfortably, the lifting is realized in a gear-rack matching mode, the height adjusting range of the longitudinal beams is more accurate and flexible, and finally, an unlocking deflector rod is additionally arranged for quickly putting down the longitudinal beams after the dismounting process is finished.
Drawings
Fig. 1 is a schematic perspective view of a conventional bracket.
Fig. 2 is a schematic plan view illustrating an operation state of a conventional cradle.
Fig. 3 is a schematic perspective view of the first embodiment of the present invention.
Fig. 4 is a schematic front view of the present invention.
Fig. 5 is a schematic perspective view of the present invention.
Fig. 6 is an enlarged view of a structure at a in fig. 5.
Fig. 7 is a partial perspective view of the present invention.
Fig. 8 is a schematic view of the working principle of the driving mechanism of the present invention in cooperation with the rack.
Fig. 9 is a perspective view of the upper end structure of the longitudinal beam of the present invention.
Fig. 10 is an exploded perspective view of a stringer of the present invention.
Fig. 11 is a schematic perspective view of the driving mechanism of the present invention.
Fig. 12 is an exploded perspective view of the drive mechanism of the present invention.
Fig. 13 is a partially exploded perspective view of the driving mechanism of the present invention.
Fig. 14 is a partial perspective exploded view of the driving mechanism of the present invention.
The reference numbers in the figures are: 1-moving the base; 2-a transverse support beam; 3-longitudinal beams; 4-hollow pipe column; 5-a rack; 6-a drive mechanism; 7-a housing; 8-gear; 9-a hand-operated lever; 10-rectangular avoidance holes; 11-a ratchet; 12-unlocking deflector rod; 13-a chute configuration; 14-a rotating wheel; 15-rigid jaws; 16-torsion spring; 17-accommodating grooves; 18-a stationary shaft; 19-upper hinge base; 20-lower free bearing; 21-circular caulking groove; 22-circular end cover plate; 23-a first square axis; 24-arc avoidance through grooves; 25-a first square hole; 26-a second square shaft; 27-a second square hole; 28-longitudinal through grooves; 29-cover sleeve; 30-rectangular caulking grooves; 31-a fastening plate; 32-a drop-down buffer plate; 33-cushion gum; 34-antiskid protection sponge.
Detailed Description
The following description is presented to disclose the invention so as to enable any person skilled in the art to practice the invention. The preferred embodiments in the following description are given by way of example only, and other obvious variations will occur to those skilled in the art.
Referring to fig. 3 to 14, the auxiliary supporting device for dismounting and mounting a small aircraft comprises a moving base 1, a transverse supporting beam 2 and two longitudinal beams 3 respectively arranged at the bottoms of the two ends of the transverse supporting beam 2, wherein two ends of the moving base 1 are provided with two hollow tubular columns 4 respectively used for inserting the two longitudinal beams 3, one side of each longitudinal beam 3 is fixedly embedded with a vertical rack 5, and the upper half part of each hollow tubular column 4 is fixedly provided with a driving mechanism 6 used for driving the corresponding rack 5 to move longitudinally; the driving mechanism 6 drives the rack 5 to lift, so as to drive the longitudinal beam 3 fixedly connected with the rack 5 to lift, and further drive the transverse supporting beam 2 to lift through the two longitudinal beams 3.
Each driving mechanism 6 comprises a shell 7, a gear 8 meshed with the rack 5, a locking mechanism positioned at the center of the gear 8 and a hand lever 9 connected with the gear 8; the driving mechanism 6 works in a mode that the hand-operated rod 9 drives the gear 8 to rotate, so that the rack 5 meshed with the gear 8 moves upwards, and finally the transverse supporting beam 2 is lifted and adjusted.
The gear 8 is positioned in the shell 7, the rack 5 meshed with the gear is lifted in the hollow pipe column 4 through rotation, and a rectangular avoidance hole 10 for avoiding the gear 8 is formed in the pipe wall of the hollow pipe column 4; the rectangular avoiding hole 10 is formed in the joint of the hollow pipe column 4 and the shell 7 and used for avoiding the outer edge of the tooth end of the gear 8, so that the gear can be in meshed contact with the rack 5 in the hollow pipe column 4 through the rectangular avoiding hole 10.
The locking mechanism is positioned on the inner side of the gear 8, a circle of ratchets 11 are arranged on the inner edge of the gear 8, and the ratchets 11 are matched with the locking mechanism to prevent the rack 5 from falling due to reverse rotation of the gear 8 after the gear 8 rotates to drive the rack 5 to rise; make gear 8 have the unidirectionality in the rotation process in the locking mechanism outside through ratchet 11, do not receive locking mechanism's resistance effect when gear 8 corotation promptly, thereby can drive longeron 3 be connected with rack 5 and realize rising, otherwise loosen hand lever 9 back, rack 5 can just have the trend of tenesmus under the action of gravity, thereby make the gear 8 with it meshing have the trend of reversal, because locking mechanism's effect makes gear 8 can't take place the reversal in the locking mechanism outside this moment, and then has avoided rack 5 tenesmus.
The hand rocker 9 is coaxially and fixedly connected with the gear 8 and is used for driving the gear 8 to rotate; the gear 8 is driven to rotate in one direction by holding and rotating the hand rocker 9, so that the operation is convenient and labor-saving.
The locking mechanism is also provided with an unlocking shift lever 12 for releasing the reverse rotation locking state of the gear 8. When the device is not needed, the current reverse locking effect of the counter gear 8 is relieved by stirring the unlocking deflector rod 12, so that the longitudinal beam 3 can directly and quickly fall back to the lowest position, and the trouble that the reverse hand rocker 9 drives the rack 5 to descend is avoided.
The tops of the two longitudinal beams 3 are respectively hinged with the bottoms of the two ends of the transverse supporting beam 2, and the bottom of one end of the transverse supporting beam 2 is provided with a sliding groove structure 13 for providing transverse displacement offset for the lower longitudinal beam 3. When the supported wing needs to be installed in a one-side-up state, as shown in fig. 2, the heights of the two ends of the transverse supporting beam 2 need to be different, that is, the transverse supporting beam 2 needs to be inclined to support the wing, when the transverse supporting beam 2 is inclined, the position where the top end of one longitudinal beam 3 is connected with the transverse supporting beam 2 inevitably slides according to the triangle pythagorean theorem, so that after the position where one longitudinal beam 3 is connected with the transverse supporting beam 2 is fixed, when the other longitudinal beam 3 is connected with the other end of the transverse supporting beam 2, the sliding chute structure 13 arranged at the connecting point in sliding fit is used for overcoming the transverse sliding deviation generated when the transverse supporting beam 2 is inclined.
Locking mechanism includes runner 14, rigidity jack catch 15 and torsional spring 16, 14 coaxial and fixed settings in the inboard of gear 8 of runner, 14's outer fringe is equipped with one and follows self periphery to radial sunken holding tank 17, be equipped with the axially uniform fixed axle 18 of a length direction and runner 14 in the holding tank 17, rigidity jack catch 15's one end and torsional spring 16 all overlap and locate on the fixed axle 18, and torsional spring 16 has the trend of popping out the free end of rigidity jack catch 15 to holding tank 17 outward all the time. By rotating the gear 8 outside the runner 14, as shown in fig. 8, when the gear 8 rotates counterclockwise, the ratchet 11 at the inner edge rotates against the rigid clamping jaw, so as to lift the rack 5 engaged with the gear 8 upwards along with the rotation of the gear 8, thereby realizing the lifting process of the longitudinal beam 3. When the longitudinal beam 3 drives one end of the transverse supporting beam 2 to ascend to a proper position to support the wing, the hand-operated rod 9 is loosened, at the moment, due to gravity factors, the rack 5 tends to descend, so that the gear 8 also tends to rotate in the reverse direction, namely, in the direction of the pointer, and the rigid claw 15 which is pushed out by the torsion spring 16 at the moment can be inserted into the ratchet 11 on the inner edge of the gear 8, so that the effect of preventing the gear 8 from rotating in the reverse direction is achieved, and further, the rack 5 and the longitudinal beam 3 are prevented from descending.
The top ends of the two longitudinal beams 3 are respectively provided with an upper hinged support 19 and a lower hinged support 20 which are mutually coupled, each lower hinged support 20 is fixedly arranged at the top end of the corresponding longitudinal beam 3, one upper hinged support 19 is fixedly arranged at the bottom of one end of the transverse supporting beam 2, and the other upper hinged support 19 is slidably embedded in the sliding groove structure 13. The fuselage section of the aircraft is finally supported by the individual raising of the two stringers 3, if the transverse support beam 2 is now in an inclined position, the end of the transverse support beam 2, which is brought with freedom of rotation by the cooperation of the upper hinge mount 19 and the lower hinge mount 20, is adapted to the change between horizontal and inclined positions of the transverse support beam 2. The runner structure 13 at the bottom of one end thereof is used to provide a sliding movement of the upper hinge base 19 connected thereto during the transition of the lateral support beam 2 from the horizontal position to the inclined position, thereby overcoming the lateral offset generated at the time of the transition between the inclined position and the horizontal position.
The axial direction of the unlocking deflector rod 12 is parallel to the axial direction of the rotating wheel 14, one end of the unlocking deflector rod 12 is fixedly connected with one side of the free end of the rigid claw 15, arc avoiding through grooves 24 used for enabling the unlocking deflector rod 12 to move in an arc shape are formed in the groove wall of the accommodating groove 17, the circular end cover plate 22 and the shell 7, and the other end of the unlocking deflector rod 12 penetrates through all the arc avoiding through grooves 24 outwards in sequence. The movement path of the release lever 12 is an arc track that is centered on the fixed shaft 18, and therefore, the corresponding arc-shaped escape through groove 24 is provided to escape the movement thereof. When the disassembly, assembly and maintenance of the aircraft components are finished, the longitudinal beam 3 needs to descend and retract, the unlocking deflector rod 12 is pulled at the moment, the rigid claw 15 is driven to rotate around the fixed shaft 18 and retract into the accommodating groove 17, the rigid claw 15 and the ratchet 11 are separated at the moment, so that the rotating wheel 14 loses the effect of preventing the reverse rotation of the gear 8, the longitudinal beam 3 vertically descends to the bottom under the action of self gravity, and the rack 5 still engages with the gear 8 and drives the gear to overturn in the process.
A first square hole 25 is formed in the center of the rotating wheel 14, a second square shaft 26 is fixedly inserted in the first square hole 25, and a second square hole 27 for the second square shaft 26 to be fixedly inserted is formed in the center of the circular end cover plate 22 fixedly connected with the housing 7. The second square shaft 26 passes through the first square hole 25 and the second square hole 27 simultaneously and is used for achieving the axial limiting effect on the rotating wheel 14 and the circular end cover plate 22, and the circular end cover plate 22 is fixedly connected with the shell 7, so that the rotating wheel 14 cannot rotate all the time under the limiting effect of the second square shaft 26, and the rigid clamping jaws 15 are matched to achieve the reverse rotation locking effect on the gear 8.
Offer a vertical logical groove 28 that is used for supplying gear 8 contact rack 5 on the lateral wall of longeron 3, tooth end one side of rack 5 flushes with the outer wall of longeron 3, and the last lower extreme of longeron 3 is all fixed to be inlayed and is equipped with a lid cover 29 that is used for fixed connection rack 5 tip, and one side of lid cover 29 is provided with the rectangle caulking groove 30 that is used for supplying rack 5 tip embedding, and the middle part of rectangle caulking groove 30 is fixed and is provided with a mounting plate 31 that is used for supporting tight rack 5 terminal surface, and bolt and mounting plate 31 fixed connection are passed through to the tip of rack 5. The upper cover sleeve 29 and the lower cover sleeve 29 are matched with bolts to fasten the rack 5 at the current position, so that one side of the tooth end of the rack 5 can extend out of the longitudinal through groove 28 and is flush with the outer side wall of the longitudinal beam 3, and the longitudinal beam 3 can smoothly and unimpededly move longitudinally in the hollow tubular column 4.
The outer side of the upper end of the longitudinal beam 3 is fixedly sleeved with a falling buffer plate 32, and the bottom of the falling buffer plate 32 is fixedly provided with a layer of damping rubber 33. In the process that the longitudinal beam 3 rapidly falls to the bottom through the unlocking deflector rod 12, the process is stopped until the falling buffer plate 32 abuts against the top end of the hollow pipe column 4 downwards, and the shock absorption rubber 33 is used for buffering the falling impact force.
The top of the transverse supporting beam is provided with an anti-skid protective sponge 34. The anti-slip protective sponge 34 is used for achieving an anti-slip effect on the supported component and can prevent the surface of the component from being scratched.
The foregoing shows and describes the general principles, essential features, and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are merely illustrative of the principles of the invention, but that various changes and modifications may be made without departing from the spirit and scope of the invention, which fall within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (10)
1. An auxiliary supporting device for dismounting a small airplane comprises a moving base (1), a transverse supporting beam (2) and two longitudinal beams (3) which are respectively arranged at the bottoms of the two ends of the transverse supporting beam (2), wherein two hollow pipe columns (4) which are respectively used for inserting the two longitudinal beams (3) are arranged at the two ends of the moving base (1), the auxiliary supporting device is characterized in that a rack (5) in a vertical state is fixedly embedded at one side of each longitudinal beam (3), and a driving mechanism (6) which is used for driving the corresponding rack (5) to longitudinally move is fixedly arranged at the upper half part of each hollow pipe column (4);
each driving mechanism (6) comprises a shell (7), a gear (8) meshed with the rack (5), a locking mechanism positioned at the center of the gear (8) and a hand lever (9) connected with the gear (8);
the gear (8) is positioned in the shell (7), the rack (5) meshed with the gear is lifted in the hollow pipe column (4) through rotation, and a rectangular avoiding hole (10) for avoiding the gear (8) is formed in the pipe wall of the hollow pipe column (4);
the locking mechanism is positioned on the inner side of the gear (8), a circle of ratchets (11) are arranged on the inner edge of the gear (8), and the ratchets (11) are matched with the locking mechanism to prevent the gear (8) from reversely rotating to cause the rack (5) to fall down after the gear (8) is rotated to drive the rack (5) to rise;
the hand-operated lever (9) is coaxially and fixedly connected with the gear (8) and is used for driving the gear (8) to rotate;
the locking mechanism is also provided with an unlocking shift lever (12) for releasing the reverse rotation locking state of the gear (8).
2. An auxiliary supporting device for dismounting a small airplane according to claim 1, wherein the top of each of said longitudinal beams (3) is hinged with the bottom of each of the two ends of a transverse supporting beam (2), and the bottom of one of the ends of said transverse supporting beam (2) is provided with a sliding groove structure (13) for providing a transverse displacement offset for the lower longitudinal beam (3).
3. The auxiliary supporting device for dismounting and mounting a small airplane as claimed in claim 1, wherein the locking mechanism comprises a rotating wheel (14), a rigid claw (15) and a torsion spring (16), the rotating wheel (14) is coaxially and fixedly arranged at the inner side of the gear (8), an accommodating groove (17) which is radially recessed along the outer peripheral surface of the rotating wheel (14) is arranged at the outer edge of the rotating wheel (14), a fixed shaft (18) which is consistent with the axial direction of the rotating wheel (14) in the length direction is arranged in the accommodating groove (17), one end of the rigid claw (15) and the torsion spring (16) are both sleeved on the fixed shaft (18), and the torsion spring (16) always has a tendency of ejecting the free end of the rigid claw (15) out of the accommodating groove (17).
4. The auxiliary supporting device for dismounting a small airplane as claimed in claim 2, wherein the top ends of two longitudinal beams (3) are respectively provided with an upper hinge base (19) and a lower hinge base (20) which are coupled with each other, each lower hinge base (20) is fixedly arranged at the top end of the corresponding longitudinal beam (3), one upper hinge base (19) is fixedly arranged at the bottom of one end of the transverse supporting beam (2), and the other upper hinge base (19) is slidably embedded in the chute structure (13).
5. The auxiliary supporting device for dismounting and mounting of the small airplane as claimed in claim 3, wherein two sides of the gear (8) are respectively provided with a circular caulking groove (21) which is recessed along the self axial direction, each circular caulking groove (21) is internally provided with a circular end cover plate (22), the rotating wheel (14) is respectively attached to the two circular end cover plates (22) along two axial end faces of the rotating wheel, one of the circular end cover plates (22) is fixedly connected with the inner wall of the shell (7), and the center of the outer side of the other circular end cover plate (22) is fixedly provided with a first square shaft (23) which is used for sleeving the hand-operated rod (9).
6. The auxiliary supporting device for disassembling and assembling the small airplane as claimed in claim 5, wherein an axial direction of the unlocking deflector rod (12) is parallel to an axial direction of the rotating wheel (14), one end of the unlocking deflector rod (12) is fixedly connected with one side of a free end of the rigid claw (15), arc-shaped avoiding through grooves (24) for arc-shaped movement paths of the unlocking deflector rod (12) are formed in the groove wall of the accommodating groove (17), the circular end cover plate (22) and the shell (7), and the other end of the unlocking deflector rod (12) sequentially penetrates through all the arc-shaped avoiding through grooves (24) outwards.
7. The auxiliary supporting device for dismounting a small airplane as claimed in claim 5, wherein a first square hole (25) is formed at the center of the rotating wheel (14), a second square shaft (26) is fixedly inserted in the first square hole (25), and a second square hole (27) for fixedly inserting the second square shaft (26) is formed at the center of the circular end cover plate (22) fixedly connected with the outer shell (7).
8. The auxiliary supporting device for dismounting and mounting the small airplane as claimed in claim 1, wherein a longitudinal through groove (28) for the gear (8) to contact the rack (5) is formed in the side wall of the longitudinal beam (3), one side of the tooth end of the rack (5) is flush with the outer wall of the longitudinal beam (3), and a cover sleeve (29) for fixedly connecting the end part of the rack (5) is fixedly embedded in the upper end and the lower end of the longitudinal beam (3).
9. The auxiliary supporting device for dismounting and mounting a small airplane as claimed in claim 1, wherein a falling buffer plate (32) is fixedly sleeved outside the upper end of the longitudinal beam (3), and a layer of shock absorption glue (33) is fixedly arranged at the bottom of the falling buffer plate (32).
10. The auxiliary supporting device for dismounting a small airplane as claimed in claim 1, wherein a skidproof protective sponge (34) is arranged on the top of the transverse supporting beam.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011553380.3A CN112720392A (en) | 2020-12-24 | 2020-12-24 | Auxiliary supporting device for dismounting and mounting small aircraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011553380.3A CN112720392A (en) | 2020-12-24 | 2020-12-24 | Auxiliary supporting device for dismounting and mounting small aircraft |
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| CN112720392A true CN112720392A (en) | 2021-04-30 |
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| CN202011553380.3A Pending CN112720392A (en) | 2020-12-24 | 2020-12-24 | Auxiliary supporting device for dismounting and mounting small aircraft |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113654542A (en) * | 2021-07-21 | 2021-11-16 | 浙江吴浙建设有限公司 | Building engineering straightness detection device that hangs down convenient to remove |
| CN114967587A (en) * | 2022-06-05 | 2022-08-30 | 广州汉光电气股份有限公司 | Enterprise energy management terminal device |
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| JPH0529681U (en) * | 1991-03-30 | 1993-04-20 | 九州電気建設工事株式会社 | Hydraulic torque wrench |
| US20050268448A1 (en) * | 2004-06-03 | 2005-12-08 | Grant Jones | Semi-automated door hinge pin removal tool |
| CN203471305U (en) * | 2013-09-04 | 2014-03-12 | 奇瑞汽车股份有限公司 | Supporting tool |
| CN209444892U (en) * | 2019-01-23 | 2019-09-27 | 刘振伟 | Support frame is used in a kind of maintenance of municipal pipeline |
| CN212123180U (en) * | 2020-03-30 | 2020-12-11 | 上海登杰机器设备有限公司 | General bracket of machining |
| CN111576813A (en) * | 2020-06-08 | 2020-08-25 | 汪方堂 | Interior wall whitewashing device of automatic spacing support based on construction |
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