CN114408829A

CN114408829A - Airplane model turning-over system

Info

Publication number: CN114408829A
Application number: CN202111514488.6A
Authority: CN
Inventors: 刘雪松; 王志华; 邵天双; 李凯亮
Original assignee: Beijing Institute of Specialized Machinery
Current assignee: Beijing Institute of Specialized Machinery
Priority date: 2021-12-10
Filing date: 2021-12-10
Publication date: 2022-04-29

Abstract

The invention discloses an aircraft model turnover system which comprises a first AGV and a second AGV, wherein a first lifting platform and a second lifting platform are respectively arranged on the bodies of the first AGV and the second AGV, turnover frames are arranged on the first lifting platform and the second lifting platform, each turnover frame comprises a driving rolling device and a driven rolling device, each driving rolling device and each driven rolling device comprises a supporting frame and a hoop, two rollers which are oppositely arranged are arranged on the supporting frame, the hoops are clamped between the two rollers, clamping mechanisms are arranged in the hoops, the supporting frames of the driving rolling device and the driven rolling device are respectively arranged on the first lifting platform and the second lifting platform, the two hoops are fixedly connected through connecting rods, racks which are circumferentially arranged are fixedly arranged on the hoops of the driving rolling device, gears which are meshed with the racks are arranged on the supporting frames of the driving rolling device, and the gears are driven by a motor. The turning system for the airplane model in the wind tunnel is compact in structure size, good in operation adaptability and capable of greatly shortening working hours.

Description

Airplane model turning-over system

Technical Field

The invention relates to the field of tools related to airplane models in wind tunnels, in particular to a turning system for airplane models in wind tunnels.

Background

Before different types of airplane products are put into use, the blowing test is carried out in the wind tunnel by using the scaled model, and in the blowing test process, the airplane model is placed on a balance support rod in the wind tunnel to carry out the blowing test at different positions and angles. In the blowing test, the airplane model needs to be turned over and the position of the airplane model needs to be adjusted, the existing method is that the whole wind tunnel test step is dismantled, and the airplane model is turned over and the position of the airplane model is adjusted through a crane, so that the method is difficult to operate and low in efficiency, and the time of the airplane model test can be greatly prolonged.

Disclosure of Invention

The invention aims to provide a turning system of an airplane model in a wind tunnel, which has compact structure size and good operation adaptability and can greatly shorten the labor hour consumption.

The invention relates to an aircraft model turning system, which comprises a first AGV and a second AGV, wherein a first lifting platform is arranged on the body of the first AGV, a second lifting platform is arranged on the body of the second AGV, turning frames are arranged on the first lifting platform and the second lifting platform, each turning frame comprises a driving rolling device and a driven rolling device, each driving rolling device and each driven rolling device comprises a support frame and a hoop, two rollers which are oppositely arranged are arranged on the support frames, the hoops are clamped between the two rollers, each hoop comprises two semicircular rings, one ends of the two semicircular rings are hinged with each other, the other ends of the two semicircular rings are fixedly connected through fasteners, clamping mechanisms which are radially arranged are arranged in the hoops, the support frames of the driving rolling devices are arranged on the first lifting platform, and the support frames of the driven rolling devices are arranged on the second lifting platform, the active rolling device is characterized in that the hoop of the active rolling device and the hoop of the driven rolling device are fixedly connected through a connecting rod, a rack which is circumferentially arranged is fixedly arranged on the hoop of the active rolling device, a support frame of the active rolling device is provided with a gear which is meshed with the rack, and the gear is driven by a motor.

The invention relates to an airplane model turning system, wherein a support frame comprises two support plates which are oppositely arranged, two rollers are respectively and rotatably arranged between the two support plates, the two rollers are respectively positioned at two ends of the support plates, a spiral lead screw lifter is arranged below the support frame, a lead screw of the spiral lead screw lifter is fixedly connected with the support frame, the spiral lead screw lifter is fixedly arranged on a steel wire rope shock absorber, a bottom plate is arranged below the steel wire rope shock absorber, a sliding block is arranged at the bottom of the steel wire rope shock absorber, a guide rail is arranged on the bottom plate, the sliding block is slidably arranged on the guide rail, a screw rod is further rotatably arranged on the bottom plate and is parallel to the guide rail, a screw block is in threaded connection with the screw rod and is fixedly arranged at the bottom of the steel wire rope shock absorber, a bottom plate below the support frame of an active rolling device is fixedly arranged on a first lifting platform, and a bottom plate below the support frame of the driven rolling device is fixedly arranged on the second lifting platform.

The invention relates to an airplane model turning system, wherein two spiral lead screw elevators are arranged below a supporting frame, worms of the two spiral lead screw elevators are fixedly connected through a coupler, two fixing plates are respectively and fixedly connected between the bottoms of two supporting plates of the supporting frame, and lead screws of the two spiral lead screw elevators are respectively and fixedly connected with the two fixing plates.

The invention relates to an aircraft model turning system, wherein baffles are arranged on the peripheries of a spiral lead screw lifter and a steel wire rope shock absorber below a support frame, the baffles are fixedly connected to the support frame, a worm of the spiral lead screw lifter below the support frame penetrates through the baffles and then is fixedly connected with a first crank, a strip-shaped through hole for the worm to penetrate through is formed in each baffle, and the strip-shaped through holes are arranged along the vertical direction.

The invention relates to an aircraft model turning system, wherein a motor drives a gear through a speed reducer, an output shaft of the motor is fixedly connected with an input shaft of the speed reducer, an output shaft of the speed reducer is fixedly connected with the gear, and the motor and the speed reducer are fixedly arranged on a supporting plate of an active rolling device, which is arranged opposite to a rack.

The invention relates to an airplane model turning system, wherein more than two clamping mechanisms are arranged in a hoop, the more than two clamping mechanisms are uniformly arranged at intervals along the circumferential direction of the hoop, each clamping mechanism is an air cylinder, an electric cylinder or a hydraulic cylinder, the air cylinders, the electric cylinders or the hydraulic cylinders are arranged along the radial direction of the hoop, the cylinder bodies of the air cylinders, the electric cylinders or the hydraulic cylinders are fixedly arranged on the hoop, the piston rods of the air cylinders, the electric cylinders or the hydraulic cylinders are arranged towards the center of the hoop, and the piston rods of the air cylinders, the electric cylinders or the hydraulic cylinders are connected with clamping plates through spherical hinges.

The invention relates to an aircraft model turning system, wherein more than two clamping mechanisms are arranged in a hoop, the more than two clamping mechanisms are uniformly arranged at intervals along the circumferential direction of the hoop, each clamping mechanism comprises a support, the supports are fixedly arranged on the inner ring wall of the hoop, outer sleeves arranged along the radial direction of the hoop are fixedly arranged on the supports, threaded shafts are rotatably arranged in the outer sleeves, one ends of the outer sleeves, close to the circle center of the hoop, are sleeved with inner sleeves, the inner sleeves are sleeved on the threaded shafts, the inner sleeves and the threaded shafts are in threaded connection, sliding grooves arranged axially are formed in the outer cylinder walls of the inner sleeves, inserting pins are arranged on the cylinder walls of the outer sleeves, the inserting pins are inserted into the sliding grooves, and clamping plates are connected to the inner sleeves through spherical hinges.

The invention relates to an aircraft model turning system, wherein a first lifting platform and a second lifting platform respectively comprise a base, a rigid chain lifter is fixedly arranged on the base, a rigid chain of the rigid chain lifter is fixedly connected with a supporting table, a scissor structure is connected between the supporting table and the base, a triangular support is fixedly arranged on the supporting table, a bottom plate below a supporting frame of a driving rolling device is fixedly arranged on the supporting table of the first lifting platform, a bottom plate below a supporting frame of a driven rolling device is fixedly arranged on the supporting table of the second lifting platform, the base of the first lifting platform is fixedly arranged on a vehicle body of a first AGV, and the base of the second lifting platform is fixedly arranged on a vehicle body of a second AGV.

According to the aircraft model turning system, the four support legs are arranged on the bodies of the first AGV and the second AGV, the two ends of the head and the tail of the body of the first AGV are respectively provided with a telescopic rigid connecting piece, the two ends of the head and the tail of the body of the second AGV are also respectively provided with a telescopic rigid connecting piece, the telescopic rigid connecting pieces at the head ends of the bodies of the first AGV and the second AGV are mutually connected after extending out, and the telescopic rigid connecting pieces at the tail ends of the bodies of the first AGV and the second AGV are mutually connected after extending out.

The aircraft model turning system comprises two base plates, wherein guide rails on the two base plates are arranged in a mutually perpendicular mode, the guide rail on one base plate is arranged in parallel to a connecting rod, the guide rail on the other base plate is arranged in a perpendicular mode to the connecting rod, and a second crank is fixedly connected to a screw.

The aircraft model turning system is different from the prior art in that when the aircraft model turning system is used, the connecting rod between the two hooping rings is firstly detached, then the first lifting platform and the active rolling device are transported to a destination (namely the proper position in the wind tunnel) through the first AGV, simultaneously also transport second lift platform and driven roll-over device to the destination through second AGV, later adjust the position between two AGV, with connecting rod fixed connection between two armful rings, later pull down the fastener on two armful rings, open two armful rings, arrange the aircraft model in two armful rings and close two armful rings, the closed condition locking of two armful rings is do not used again to the fastener, next clip the aircraft model through fixture (the head of aircraft is located one armful intra-annular and is cliied by the fixture of this armful ring, the afterbody of aircraft is located another armful intra-annular and is cliied by the fixture of this armful ring). According to the actual test demand, adjust the height of first lift platform and second lift platform simultaneously, treat that the aircraft model reachs the requirement height after, rotate through motor drive gear, because gear and rack meshing, consequently the armful of initiative roll-over device encircles and takes place to rotate (because the armful is connected in between two rollers, so the armful can take place to rotate under the drive of gear), under the transmission of connecting rod, the armful of driven roll-over device also follows the armful of initiative roll-over device and takes place synchronous rotation, so the aircraft model also takes place to rotate (stands up promptly), when rotating suitable position, close the motor, can carry out the test of blowing afterwards. After the blowing test is completed, the first AGV and the second AGV are controlled to move synchronously, and the airplane model can be transferred to the next test site. Therefore, the turning system of the airplane model has compact structure size and good operation adaptability, and can greatly reduce the labor hour consumption. The invention can realize the moving, the conversion and the turning of the abdominal support and the back support of different types of airplane models in the wind tunnel.

The invention will be further explained with reference to the drawings.

Drawings

FIG. 1 is a schematic structural diagram I of an aircraft model turning system according to the present invention (the lifting platform is in a lowered state);

FIG. 2 is a schematic structural view of the turning system of the airplane model of the present invention (the lifting platform is in a raised state);

FIG. 3 is a first structural schematic view (the hoop is in a closed state) of the turnover frame of the present invention;

FIG. 4 is a second structural schematic view of the turnover frame (with the hoop in an open state) of the present invention;

FIG. 5 is a first schematic structural view (with the hoop in a closed state) of the active roll device of the present invention;

FIG. 6 is a schematic structural diagram of the active rolling device of the present invention (with the hoop in an open state);

FIG. 7 is a view showing an installation state of the motor and the decelerator (hiding a shielding plate at the periphery of the motor and the decelerator) in the present invention;

FIG. 8 is a diagram showing the engagement state of the gear and the rack in the present invention (hiding the motor, the shielding plate around the reducer, and the supporting plate for fixing the reducer);

FIG. 9 is a schematic structural view of the active rolling device according to the present invention (hiding the motor, the reducer and the shielding plate around the reducer, and hiding a portion of the shielding plate);

FIG. 10 is a schematic structural view of the active rolling device of the present invention (hiding the motor, the reducer and the shielding plate around the motor, and hiding part of the shielding plate);

FIG. 11 is a schematic structural view of a base plate of the active roll device of the present invention;

FIG. 12 is a first schematic view of a driven tumbling device according to the present invention;

FIG. 13 is a second schematic view (with a portion of the blind) of the driven cascading device of the present invention;

FIG. 14 is a third schematic view (with the partial baffles hidden) of the driven cascading device of the present invention;

FIG. 15 is a schematic structural view of a base plate of the slave rollover unit of the present invention;

FIG. 16 is a first schematic structural view of a clamping mechanism according to the present invention;

FIG. 17 is a second schematic structural view of the clamping mechanism of the present invention (hidden outer sleeve);

FIG. 18 is a third schematic structural view of the clamping mechanism of the present invention (hiding the outer sleeve and the inner sleeve);

fig. 19 is a state diagram of the clamping mechanism of the present invention clamping the airplane model.

Detailed Description

As shown in fig. 1 and fig. 2-19, the aircraft model turning system of the present invention comprises a first AGV and a second AGV, a first lifting platform 8 is disposed on a car body 7 of the first AGV, a second lifting platform 2 is disposed on a car body 4 of the second AGV, a turning frame 1 is disposed on the first lifting platform 8 and the second lifting platform 2, the turning frame 1 comprises a driving rolling device 21 and a driven rolling device 42, the driving rolling device 21 and the driven rolling device 42 both comprise a support frame 9 and a hoop 12, two rollers 14 disposed oppositely are disposed on the support frame 9, the hoop 12 is clamped between the two rollers 14, the hoop 12 comprises two semicircular rings, one ends of the two semicircular rings are hinged to each other, the other ends of the two semicircular rings are fixedly connected through a fastening member 11 (such as a bolt), a clamping mechanism 10 disposed radially is disposed in the hoop 12, the utility model discloses a roll over the drive roll device 21, including first lift platform 8, second lift platform 2, connecting rod 13 fixed connection between the armful ring 12 of initiative roll-over device 21 and the armful ring 12 of driven roll-over device 42, the fixed rack 22 that is equipped with circumference and arranges on the armful ring 12 of initiative roll-over device 21, be equipped with on the support frame 9 of initiative roll-over device 21 with the gear 35 of rack 22 meshing, gear 35 passes through the drive of motor 33.

The driving rolling device 21 is provided with a motor 33, a gear 35 and a rack 22, the motor 33 drives the gear 35 to rotate, and since the rack 22 is meshed with the gear 35 and the rack 22 is arranged along the circumferential direction of the hoop 12 of the driving rolling device 21, when the gear 35 rotates, the hoop 12 of the driving rolling device 21 also rotates under the support of the two rollers 14, and under the transmission action of the connecting rod 13, the hoop 12 of the driven rolling device 42 also rotates under the support of the two rollers 14.

As shown in fig. 3 and 4, when the fastening member 11 between the two semicircular rings of the hoop 12 is detached, the hoop 12 can be opened, that is, the upper semicircular ring is rotated around the hinge end (the hinge end is the end where the two semicircular rings are hinged to each other), so that the upper semicircular ring is gradually away from the lower semicircular ring until the hoop 12 is rotated to the position shown in fig. 4, at which time the hoop is in an opened state; when the clasping rings 12 are closed, the upper semicircular ring is rotated reversely to be gradually close to the lower semicircular ring until the clasping rings 12 are rotated to the position shown in fig. 3, and at this time, the clasping rings 12 are in a closed state, and then the closed states of the two clasping rings 12 are locked by using the fasteners 11 respectively.

As shown in fig. 1 and in combination with fig. 2 to 4, the connecting rod 13 is formed by splicing two sections of rigid structural members, and is used for connecting the two hoops 12 in the overturning process of the airplane model 51, specifically, the connecting rod is connected with the hoops 12 in a bolt connection manner, so as to complete the improvement of the structural rigidity of the equipment in the overturning process of the airplane model 51.

As shown in fig. 1, and in conjunction with fig. 2-10 and 12-14, the airplane model turning system of the present invention, wherein the supporting frame 9 comprises two supporting plates arranged oppositely, two rollers 14 are rotatably mounted between the two supporting plates through bearings, and the two rollers 14 are respectively located at two ends of the supporting plates. The height of the two ends of the supporting plate is higher than that of the middle part. A screw lifting machine 36 is arranged below the supporting frame 9, a screw 39 of the screw lifting machine 36 is fixedly connected with the supporting frame 9, the screw elevator 36 is fixed on a wire rope damper 38, the bottom plate 24 is arranged below the wire rope damper 38, the bottom of the steel wire rope shock absorber 38 is provided with a slide block 29, the bottom plate 24 is provided with a guide rail 28, the sliding block 29 is slidably mounted on the guide rail 28, the bottom plate 24 is also rotatably mounted with a screw 27, two ends of the screw 27 are respectively mounted on the bottom plate 24 through bearing blocks 25, the screw 27 is arranged in parallel with the guide rail 28, a screw block 41 is connected to the screw 27 in a threaded manner, the screw block 41 is fixed at the bottom of the steel wire rope shock absorber 38, the bottom plate 24 below the support frame 9 of the active rolling device 21 is fixed on the first lifting platform 8, the bottom plate 24 below the support frame 9 of the driven rolling device 42 is fixedly arranged on the second lifting platform 2.

The wire rope damper 38 is conventional and its specific structure will not be described in detail. The steel wire rope shock absorber 38 is used for providing flexible support for the airplane model 51 during overturning, and preventing the airplane model 51 from being damaged due to overlarge rigidity of the overturning frame 1 during overturning.

When the screw 27 rotates, the screw block 41 can move back and forth along the axial direction of the screw 27 (because the screw block 41 is fixed at the bottom of the wire rope damper 38, it cannot rotate along with the screw 27, but can only move back and forth along the axial direction of the screw 27), and under the driving of the screw block 41, the wire rope damper 38, the screw elevator 36, the support frame 9 and the hoop 12 can slide back and forth along the guide rail 28 through the slider 29.

The invention relates to an airplane model turning system, wherein two spiral lead screw elevators 36 are arranged below a support frame 9, worms 37 of the two spiral lead screw elevators 36 are fixedly connected through a coupler, two fixing plates 40 are respectively and fixedly connected between the bottoms of two support plates of the support frame 9, and lead screws 39 of the two spiral lead screw elevators 36 are respectively and fixedly connected with the two fixing plates 40.

The spiral lead screw lifter 36 is a prior art, and comprises a worm 37, a worm wheel and a lead screw 39, wherein the worm 37, the worm wheel and the lead screw 39 are arranged in a box body, the worm 37 and the lead screw 39 both penetrate out of the box body, when the worm 37 rotates, the worm wheel meshed with the worm 37 also rotates, and as the lead screw 39 is in threaded connection with the worm wheel and the lead screw 39 is fixedly connected with a fixing plate 40 at the bottom of a supporting plate, when the worm wheel rotates, the lead screw 39 can do lifting movement. The relative position in the vertical direction between the two hoops 12 and the airplane model 51 can be adjusted by the screw elevator 36 so that the two hoops 12 are coaxially arranged.

As shown in fig. 5, and as shown in fig. 6-10 and 12-14, in the aircraft model turning system according to the present invention, a baffle 30 is disposed at the periphery of a screw elevator 36 and a wire rope damper 38 below the supporting frame 9, the baffle 30 is fixedly connected to a supporting plate of the supporting frame 9, a worm 37 of the screw elevator 36 below the supporting frame 9 penetrates through the baffle 30 and is fixedly connected to a first crank 31, a strip through hole 32 through which the worm 37 penetrates is formed in the baffle 30, and the strip through hole 32 is arranged in the up-down direction.

As shown in fig. 7, and as shown in fig. 8-10 and 12-14, since the worms 37 of the two screw lifters 36 below the supporting frame 9 are fixedly connected by the coupling, when the first crank 31 is rotated, the worms 37 of the two screw lifters 36 are simultaneously rotated, that is, the screws 39 of the two screw lifters 36 perform synchronous lifting movement, so that the supporting frame 9 and the clasps 12 on the supporting frame 9 perform lifting movement. When the supporting frame 9 and the embracing ring 12 perform lifting movement together, the baffle 30 fixedly connected with the supporting frame 9 also performs lifting movement along with the supporting frame 9, so that the strip-shaped through hole 32 formed in the baffle 30 also performs lifting movement relative to the worm 37 penetrating through the through hole, namely, under the action of the strip-shaped through hole 32, the worm 37 penetrating through the baffle 30 cannot block the baffle 30 to perform lifting movement along with the supporting frame 9.

As shown in fig. 7 and 8, the aircraft model turning system according to the present invention, wherein the motor 33 drives the gear 35 through the reducer 34, the output shaft of the motor 33 is fixedly connected to the input shaft of the reducer 34, the output shaft of the reducer 34 is fixedly connected to the gear 35, the motor 33 and the reducer 34 are fixedly disposed on the support plate of the active roll device 21 disposed opposite to the rack 22 (specifically, the reducer 34 is fixedly disposed on the support plate, and since the motor 33 is fixedly connected to the reducer 34, the motor 33 is also fixedly disposed on the support plate through the reducer 34), the output shaft of the reducer 34 passes through the support plate and extends to between the two support plates, and is fixedly connected to the gear 35, and the gear 35 is disposed between the two support plates. As shown in fig. 5 and 6, a shielding plate 23 is disposed around the motor 33 and the reducer 34, and the shielding plate 23 is fixedly connected to the supporting frame 9 of the active rolling device 21, specifically, the supporting plate of the supporting frame 9.

As shown in fig. 11 and 15, the airplane model turning system of the present invention has two guide rails 28 on the bottom plates 24 arranged perpendicular to each other, wherein the guide rail 28 on one of the bottom plates 24 is arranged parallel to the connecting rod 13, the guide rail 28 on the other bottom plate 24 is arranged perpendicular to the connecting rod 13, and the second crank 26 is fixedly connected to the screw 27. In the present embodiment, the guide rail 28 on the bottom plate 24 of the active rolling device 21 is arranged parallel to the connecting rod 13, and the guide rail 28 on the bottom plate 24 of the passive rolling device 42 is arranged perpendicular to the connecting rod 13.

When the second crank 26 of the active rolling device 21 is rotated to rotate the screw 27, the wire rope damper 38, the screw elevator 36, the support frame 9 and the clasps 12 in the active rolling device 21 all slide along the guide rail 28 parallel to the connecting rod 13, that is, when the connecting rod 13 is fixedly connected between the two clasps 12, the distance between the two clasps 12 can be adjusted by rotating the second crank 26 of the active rolling device 21, so that the distance is matched with the length of the connecting rod 13, thereby facilitating the installation of the connecting rod 13.

Similarly, when the second crank 26 of the driven rolling device 42 is rotated to rotate the screw 27, the wire rope shock absorber 38, the screw elevator 36, the support frame 9 and the clasping rings 12 in the driven rolling device 42 all slide along the guide rail 28 perpendicular to the connecting rod 13, that is, the coaxiality between the two clasping rings 12 can be adjusted by rotating the second crank 26 of the driven rolling device 42, and finally the two clasping rings 12 are coaxially arranged, so that the installation of the connecting rod 13 can be facilitated, and the installation and later overturning of the airplane model 51 can be facilitated.

As shown in fig. 3, in conjunction with fig. 4-15, the active and passive tumbling

devices

21, 42 may differ in structure in two ways: (1) the driving rolling device 21 is provided with a motor 33, a speed reducer 34, a gear 35 and a rack 22, and under the driving of the motor 33, through the transmission of the speed reducer 34, the gear 35 and the rack 22, the hoop 12 of the driving rolling device 21 can rotate, so as to drive the hoop 12 of the driven rolling device 42 to rotate; (2) the arrangement directions of the guide rails 28 on the bottom plates 24 of the active rolling device 21 and the driven rolling device 42 are different, namely the guide rails 28 on the bottom plate 24 of the active rolling device 21 are arranged in parallel to the connecting rod 13, so that the distance between the two embracing rings 12 can be conveniently adjusted; the guide rail 28 on the bottom plate 24 of the driven rolling device 42 is arranged perpendicular to the connecting rod 13, so that the coaxiality between the two hoops 12 can be conveniently adjusted. Except for the two differences, the active and

passive rolling devices

21 and 42 have the same structure.

As shown in fig. 1, and as shown in fig. 2-10, 12-14, and 16-18, the aircraft model turning system of the present invention includes more than two clamping mechanisms 10 in the hoop 12, wherein the more than two clamping mechanisms 10 are uniformly spaced along the circumference of the hoop 12. In the present embodiment, six clamping mechanisms 10 are provided in each hoop 12, that is, three clamping mechanisms 10 are respectively provided in two semicircular rings of the hoop 12. The clamping mechanism 10 comprises a support 48, the support 48 is fixedly arranged on an inner annular wall of the embracing ring 12, an outer sleeve 45 radially arranged along the embracing ring 12 is fixedly arranged on the support 48, a threaded shaft 46 (the threaded shaft 46 and the outer sleeve 45 are coaxially arranged) is rotatably arranged in the outer sleeve 45 through a bearing 50, an inner sleeve 44 is sleeved at one end, close to the circle center of the embracing ring 12, of the outer sleeve 45, the inner sleeve 44 is sleeved on the threaded shaft 46, the inner sleeve 44 is in threaded connection with the threaded shaft 46, the inner sleeve 44 and the threaded shaft 46 are also coaxially arranged, a sliding groove 49 axially arranged is formed in the outer sleeve wall of the inner sleeve 44, a bolt 47 is formed in the sleeve wall of the outer sleeve 45, the bolt 47 is inserted into the sliding groove 49, and a clamping plate 43 is connected to the inner sleeve 44 through a ball hinge. Because the inner sleeve 44 and the clamping plate 43 are connected through the spherical hinge, the position of the clamping plate 43 relative to the inner sleeve 44 can be adjusted, the flexibility of the clamping plate 43 in clamping is enhanced, and different types of airplane models 51 can be clamped.

Referring to fig. 19, when the clamping mechanism 10 is used, the threaded shaft 46 is rotated, since the inner sleeve 44 is screwed on the threaded shaft 46, and the inner sleeve 44 is limited in circumferential rotation by the latch 47 and the slide groove 49, when the threaded shaft 46 is rotated, the inner sleeve 44 moves back and forth along the axial direction of the threaded shaft 46, that is, the inner sleeve 44 can extend out of or retract into the outer sleeve 45. When the airplane model 51 needs to be clamped, the airplane model 51 is placed in the embracing ring 12, then the threaded shaft 46 is rotated forward, the inner sleeve 44 extends out of the outer sleeve 45 until the clamping plate 43 on the inner sleeve 44 abuts against the airplane model 51, and the airplane model 51 can be clamped; when the model airplane 51 needs to be released, the threaded shaft 46 is rotated reversely, so that the inner sleeve 44 retracts into the outer sleeve 45, and the clamping plate 43 on the inner sleeve 44 is separated from the model airplane 51, so that the model airplane 51 can be taken out of the hoop 12.

Of course, in addition to the above-described structure of the chucking mechanism 10, the chucking mechanism 10 may also adopt the following structure: fixture 10 is cylinder, electronic jar or pneumatic cylinder, electronic jar or pneumatic cylinder are along embracing the radial arrangement of ring 12, the cylinder body of cylinder, electronic jar or pneumatic cylinder is fixed to be located on embracing ring 12, the piston rod of cylinder, electronic jar or pneumatic cylinder is arranged towards the centre of a circle of embracing ring 12, be connected with grip block 43 through the ball pivot on the piston rod of cylinder, electronic jar or pneumatic cylinder. Six air cylinders, electric cylinders or hydraulic cylinders are arranged in each embracing ring 12, and the six air cylinders, electric cylinders or hydraulic cylinders are uniformly arranged at intervals along the circumferential direction of the embracing ring 12, namely, three air cylinders, electric cylinders or hydraulic cylinders are respectively arranged in two semicircular rings of the embracing ring 12. When the airplane model 51 needs to be clamped, the piston rod of the air cylinder, the electric cylinder or the hydraulic cylinder is controlled to extend out until the clamping plate 43 on the piston rod abuts against the airplane model 51; conversely, when the airplane model 51 needs to be released, the piston rod of the control cylinder, the electric cylinder or the hydraulic cylinder retracts, and the clamping plate 43 on the piston rod is separated from the airplane model 51. Because the piston rod of the air cylinder, the electric cylinder or the hydraulic cylinder is connected with the clamping plate 43 through the spherical hinge, the position of the clamping plate 43 relative to the piston rod can be adjusted, the flexibility of the clamping plate 43 in clamping is enhanced, and airplane models 51 of different types can be clamped.

As shown in fig. 1 and 2, the airplane model turning system of the present invention has the same structure of the first lifting platform 8 and the second lifting platform 2, wherein the first lifting platform 8 and the second lifting platform 2 both comprise a base 20, a rigid chain lifter 19 is fixedly arranged on the base 20, a rigid chain 18 of the rigid chain lifter 19 is fixedly connected with the supporting platform 16, a scissor structure 17 is connected between the supporting platform 16 and the base 20, a triangular bracket 15 is fixedly arranged on the supporting platform 16, a bottom plate 24 below the support frame 9 of the active rolling device 21 is fixedly arranged on the support platform 16 of the first lifting platform 8, the bottom plate 24 below the supporting frame 9 of the driven rolling device 42 is fixedly arranged on the supporting platform 16 of the second lifting platform 2, the base 20 of the first lifting platform 8 is fixed on the vehicle body 7 of the first AGV, and the base 20 of the second lifting platform 2 is fixed on the vehicle body 4 of the second AGV.

As shown in fig. 1, a control box 6 is mounted on the support platform 16 of each lifting platform, and a control mechanism is mounted in the control box 6 and used for controlling the action of the whole turning system.

In the use process of the invention, the lifting height of the airplane model 51 and the embracing ring 12 is adjusted by the lifting platform, the lifting platform is arranged at a bearing position on the AGV body, and the turning frame 1 is arranged at the top. The first 8 and second 2 lifting platforms each employ two rigid chain hoists 19, each rigid chain hoist 19 being driven by a servo motor and using a scissor structure 17 to assist in structural shape retention of the platform. It should be noted that the rigid chain elevator 19 is a conventional art, and mainly includes a servo motor, a base, a sprocket and a rigid chain 18, the sprocket and the rigid chain 18 are installed in the base, the sprocket and the rigid chain 18 are engaged with each other, the servo motor drives the sprocket to rotate, so that the rigid chain 18 is raised or lowered, and the rigid chain 18 drives the support platform 16 to be raised or lowered.

The fixed triangular support 15 that sets up on the brace table 16 is used for: when the embracing ring 12 is opened, the fastening piece 11 between the two semicircular rings of the embracing ring 12 is detached, then the semicircular ring above the embracing ring is rotated around the hinged end until the semicircular ring rotates to the position shown in figure 4, the semicircular ring above the semicircular ring falls on the triangular support 15, and the triangular support 15 supports the semicircular ring above the semicircular ring at the moment by combining figures 1 and 2, so that the deformation of the embracing ring 12 is prevented, and the use is influenced.

As shown in fig. 1 and 2, the aircraft model turning system of the invention is characterized in that four support legs 3 are arranged on the vehicle bodies 7 and 4 of the first AGV and the second AGV, two ends of the vehicle body 7 of the first AGV are respectively provided with a telescopic rigid connecting piece 5, two ends of the vehicle body 4 of the second AGV are respectively provided with a telescopic rigid connecting piece 5, the telescopic rigid connecting pieces 5 at the head ends of the vehicle bodies 7 and 4 of the first AGV and the second AGV are connected with each other after extending, and the telescopic rigid connecting pieces 5 at the tail ends of the vehicle bodies 7 and 4 of the first AGV and the second AGV are connected with each other after extending.

For each AGV, four legs 3 are hinged at four corners of the AGV body. After the AGVs reach the destination, in order to improve the stability of the whole system when the airplane model 51 is turned over, the supporting legs 3 are turned over to the outer side of the automobile body and fixed on the ground, and meanwhile, the telescopic rigid connecting pieces 5 of the two AGVs are pulled out to be fixedly connected with each other, namely, the two AGVs are fixed together through the rigid connecting pieces 5, so that the stability of the whole turning-over system is enhanced.

As shown in fig. 19, when the present invention is used, the connecting rod 13 between the two clasps 12 is firstly removed, the rigid connecting member 5 between the two AGVs is separated, then the rigid connecting member 5 and the supporting leg 3 of each AGV are both in a retracted state, then the first lifting platform 8 and the active rolling device 21 are transported to a destination (i.e. a proper position in the wind tunnel) by the first AGV, the second lifting platform 2 and the driven rolling device 42 are also transported to the destination by the second AGV, then the position between the two AGVs is adjusted, after the position is adjusted, the supporting leg 3 of the two AGVs is turned out of the vehicle body and fixed on the ground, the rigid connecting members 5 of the two AGVs are pulled out for fixed connection, then the connecting rod 13 is fixedly connected between the two clasps 12, then the fastening members 11 on the two clasps 12 are removed, the two clasps 12 are opened, the airplane model 51 is placed in the two embracing rings 12 and the two embracing rings 12 are closed, then the closed states of the two embracing rings 12 are locked by using the fasteners 11 respectively, and then the airplane model 51 is clamped by the clamping mechanisms 10 (the head of the airplane is positioned in one embracing ring 12 and clamped by the clamping mechanism 10 of the embracing ring 12, and the tail of the airplane is positioned in the other embracing ring 12 and clamped by the clamping mechanism 10 of the embracing ring 12). According to actual test requirements, the heights of the first lifting platform 8 and the second lifting platform 2 are adjusted simultaneously, after the aircraft model 51 reaches a required height, the gear 35 is driven to rotate by the motor 33, and the gear 35 is meshed with the rack 22, so that the hoop 12 of the driving rolling device 21 rotates (the hoop 12 can rotate under the drive of the gear 35 because the hoop 12 is clamped between the two rollers 14), under the transmission action of the connecting rod 13, the hoop 12 of the driven rolling device 42 also synchronously rotates along with the hoop 12 of the driving rolling device 21, so that the aircraft model 51 also rotates (namely turns over), when the aircraft model rotates to a proper position, the motor 33 is turned off, and then the blowing test can be performed. After the blowing test is completed, the supporting legs 3 are retracted, and the first AGV and the second AGV are controlled to move synchronously, so that the airplane model 51 can be transferred to the next test site. Therefore, the turning system of the airplane model has compact structure size and good operation adaptability, and can greatly reduce the labor hour consumption. The invention can realize the moving and the conversion and turning of the abdominal bracing and the back bracing of different types of airplane models 51 in the wind tunnel, namely realize the 180-degree turning of the airplane models 51.

The AGV of the invention adopts four sets of Mecanum wheel units for driving, and can realize the omnidirectional running of the turning system and the airplane model 51 in the wind tunnel. In order to ensure the stability of the turnover system when the aircraft model is turned over for 180 degrees, two groups of telescopic rigid connecting mechanisms and four supporting legs 3 are further arranged at the head end and the tail end of the AGV body. When carrying out aircraft model 180 upset operations, with the telescopic rigid connection spare 5 of automobile body 7, 4 head ends of first AGV and second AGV pulling out back interconnect, with telescopic rigid connection spare 5 of automobile body 7, 4 tail ends of first AGV and second AGV pulling out back interconnect, overturn 3 upset to automobile body both sides and fix subaerial with landing leg simultaneously.

The invention can be split into two movable components (each component comprises an AGV, a lifting platform and a rolling device) before entering the wind tunnel, and the components enter the wind tunnel through a maintenance entrance of the wind tunnel, in order to adapt to the height and the width of the maintenance entrance of the wind tunnel, the hoop 12 structure of the components is in an open state, and simultaneously, the rigid connecting piece 5 and the supporting legs 3 on the AGV body retract.

The AGV has the advantages that the AGV chassis is adopted, the overall structure is compact, the integration is high, the clamping mechanism 10 can be adjusted to clamp airplane models 51 with different sizes, and therefore stable movement and turnover of the airplane models 51 with different sizes are achieved, and the AGV has good adaptability; the invention has good operability, and can realize the quick assembly and disassembly of the airplane model 51 in the using process; the turning-over device has compact integral structure and size, occupies smaller space and saves more operation cost compared with the turning-over device of the existing airplane model 51.

The invention has the following beneficial effects:

(1) the invention has compact structure and high integration degree;

(2) the invention has simpler and more convenient operation, can improve the convenience of the turning-over work of the airplane model 51 in the wind tunnel and further improves the working efficiency;

(3) when the turning-over operation of the airplane model 51 is carried out, the operation of the transportation and the turning-over operation of the airplane model 51 in the wind tunnel can be realized only through the self function of the turning-over operation device without operating the wind tunnel step, so that the manpower consumption is reduced, and the operation cost is saved.

It should be noted that the terms "center", "upper", "lower", "front", "rear", "left", "right", "middle", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience in describing the present invention and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention.

In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "connected" and "connected" are to be interpreted broadly, e.g., as being fixed or detachable or integrally connected; can be mechanically or electrically connected; may be directly connected or indirectly connected through an intermediate. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

The above-mentioned embodiments are merely illustrative of the preferred embodiments of the present invention, and do not limit the scope of the present invention, and various modifications and improvements of the technical solution of the present invention by those skilled in the art should fall within the protection scope defined by the claims of the present invention without departing from the spirit of the present invention.

Claims

1. An aircraft model turning system is characterized in that: including first AGV and second AGV, be equipped with first lift platform on first AGV's the automobile body, be equipped with second lift platform on second AGV's the automobile body, be equipped with the frame of turning over on first lift platform and the second lift platform, it includes initiative rolling device and driven rolling device to turn over the frame, initiative rolling device and driven rolling device all include support frame and embrace the ring, be equipped with two rollers of mutual disposition on the support frame, the embrace the ring joint between two rollers, the embrace the ring including two semicircle rings, two one end of semicircle ring is articulated each other, two the other end of semicircle ring passes through fastener fixed connection, embrace the intra-annular and be equipped with radial clamping mechanism who arranges, the support frame of initiative rolling device is located on first lift platform, the support frame of driven rolling device is located on second lift platform, through fixed connection between the embrace of ring and the ring of driven rolling device of initiative rolling device, the active rolling device is characterized in that a circumferential rack is fixedly arranged on an embracing ring of the active rolling device, a support frame of the active rolling device is provided with a gear meshed with the rack, and the gear is driven by a motor.

2. The aircraft model turning system of claim 1, wherein: the support frame comprises two support plates which are oppositely arranged, the two rollers are respectively and rotatably arranged between the two support plates, the two rollers are respectively positioned at two ends of the support plates, a spiral lead screw lifter is arranged below the support frame, a lead screw of the spiral lead screw lifter is fixedly connected with the support frame, the spiral lead screw lifter is fixedly arranged on a steel wire rope shock absorber, a bottom plate is arranged below the steel wire rope shock absorber, a sliding block is arranged at the bottom of the steel wire rope shock absorber, a guide rail is arranged on the bottom plate, the sliding block is slidably arranged on the guide rail, a screw rod is also rotatably arranged on the bottom plate and is parallel to the guide rail, a screw block is in threaded connection with the screw rod and is fixedly arranged at the bottom of the steel wire rope shock absorber, and the bottom plate below the support frame of the active rolling device is fixedly arranged on a first lifting platform, and a bottom plate below the support frame of the driven rolling device is fixedly arranged on the second lifting platform.

3. The aircraft model turning system of claim 2, wherein: the support frame is characterized in that two spiral lead screw lifters are arranged below the support frame, worms of the two spiral lead screw lifters are fixedly connected through a coupler, two fixing plates are fixedly connected between the bottoms of two supporting plates of the support frame respectively, and lead screws of the two spiral lead screw lifters are fixedly connected with the two fixing plates respectively.

4. The aircraft model turning system of claim 3, wherein: the spiral lead screw lifter comprises a support frame, a spiral lead screw lifter and a steel wire rope shock absorber, and is characterized in that baffle plates are arranged on the peripheries of the spiral lead screw lifter and the steel wire rope shock absorber below the support frame, the baffle plates are fixedly connected to the support frame, a worm of the spiral lead screw lifter below the support frame penetrates through the baffle plates and then is fixedly connected with a first crank, a strip-shaped through hole for the worm to penetrate through is formed in each baffle plate, and the strip-shaped through holes are arranged in the vertical direction.

5. The aircraft model turning system of claim 4, wherein: the motor drives the gear through the speed reducer, an output shaft of the motor is fixedly connected with an input shaft of the speed reducer, an output shaft of the speed reducer is fixedly connected with the gear, and the motor and the speed reducer are fixedly arranged on a supporting plate of the active rolling device, wherein the supporting plate is opposite to the rack.

6. The aircraft model turning system of claim 5, wherein: the clamping mechanism in the embracing ring is set to be more than two, and the clamping mechanism more than two is arranged along the even interval of circumference of embracing the ring, clamping mechanism is cylinder, electronic jar or pneumatic cylinder, electronic jar or pneumatic cylinder are arranged along the radial of embracing the ring, the cylinder body of cylinder, electronic jar or pneumatic cylinder is fixed to be located on the embracing the ring, the piston rod of cylinder, electronic jar or pneumatic cylinder is arranged towards the centre of a circle of embracing the ring, be connected with the grip block through the ball pivot on the piston rod of cylinder, electronic jar or pneumatic cylinder.

7. The aircraft model turning system of claim 5, wherein: the clamping mechanism in the embracing ring is set to be more than two, the clamping mechanism more than two is arranged along the even interval of circumference of embracing the ring, clamping mechanism includes the support, the support is fixed to be located on the interior rampart of embracing the ring, the fixed outer sleeve that is equipped with along embracing the radial arrangement of ring on the support, the threaded shaft is installed to the outer sleeve internal rotation, the outer sleeve be close to embrace ring centre of a circle one end cover and be equipped with the inner skleeve, the inner skleeve suit in the threaded shaft, be threaded connection between inner skleeve and the threaded shaft, be equipped with the spout that the axial was arranged on the outer tube wall of inner skleeve, be equipped with the bolt on the section of thick bamboo wall of outer sleeve, the bolt inserts in the spout, be connected with the grip block through the ball pivot on the inner skleeve.

8. An aircraft model turning system according to claim 6 or 7, wherein: first lift platform and second lift platform all include the base, the fixed rigid chain lift that is equipped with on the base, the rigid chain and the brace table fixed connection of rigid chain lift, be connected with between brace table and the base and cut the fork structure, the fixed triangle-shaped support that is equipped with on the brace table, the bottom plate of the support frame below of initiative roll-over device is fixed on locating the brace table of first lift platform, the bottom plate of the support frame below of driven roll-over device is fixed on locating the brace table of second lift platform, the base of first lift platform is fixed on locating the automobile body of first AGV, the base of second lift platform is fixed on locating the automobile body of second AGV.

9. The aircraft model turning system of claim 8, wherein: all be equipped with four landing legs on first AGV and second AGV's the automobile body, first AGV's automobile body end to end both ends respectively are equipped with a scalable rigid connection spare, second AGV's automobile body end to end both ends also respectively are equipped with a scalable rigid connection spare, the scalable rigid connection spare of first AGV and second AGV's automobile body head end is stretching out back interconnect, the scalable rigid connection spare of first AGV and second AGV's automobile body tail end is stretching out back interconnect.

10. The aircraft model turning system of claim 9, wherein: the guide rails on the two bottom plates are arranged in a mutually perpendicular mode, the guide rail on one bottom plate is arranged in parallel to the connecting rod, the guide rail on the other bottom plate is arranged in a perpendicular mode to the connecting rod, and the screw rod is fixedly connected with a second crank.