Aircraft model retrieval device

Abstract

The application discloses an aircraft model taking device, which comprises a first AGV, a bearing frame connected to the first AGV through a first lifting structure, two bearing seats oppositely arranged on the bearing frame, and a moving holding assembly arranged below the two bearing seats. The aircraft model taking device can take aircraft models, thereby greatly reducing the work amount of operators, shortening the test preparation period, and greatly improving the safety and convenience of the work process.

Description

Technical Field

[0001] This invention relates to the field of aircraft model testing, and in particular to an aircraft model receiving device. Background Technology

[0002] Aircraft models are used for wind tunnel testing to collect flight data. The testing process mainly involves assembly, pick-up, lifting, and position adjustment in the test area. The pick-up process, in particular, requires a large amount of auxiliary equipment, resulting in low overall efficiency and impacting the testing cycle. Summary of the Invention

[0003] The purpose of this invention is to provide an aircraft model receiving device that can receive aircraft models, thereby greatly reducing the workload of operators, shortening the test preparation cycle, and significantly improving the safety and convenience of the operation process.

[0004] The present invention provides an aircraft model receiving device, comprising a first AGV, a support frame connected to the first AGV via a first lifting structure, two oppositely arranged support seats on the support frame, and a movable clamping assembly located below the two support seats.

[0005] The present invention relates to an aircraft model receiving device, wherein the first lifting structure is a first spiral elevator.

[0006] This invention relates to an aircraft model receiving device, wherein the movable clamping assembly includes a chassis, a second slider fixedly mounted on the bottom of the chassis, a second slide rail fixedly mounted on a support frame arranged horizontally, the second slide rail being parallel to the line connecting the centers of two support seats, the second slider being slidably connected to the second slide rail, a clamping cylinder rotatably mounted on the top of the chassis, the axis of the clamping cylinder being parallel to the second slide rail, the two ends of the clamping cylinder being a first end and a second end, respectively, a support plate fixedly mounted on the chassis at the first end of the clamping cylinder, the support plate and... The first ends of the clamping cylinder are connected by a second rotary drive. A support roller is rotatably mounted on the chassis of the second end of the clamping cylinder. The second end of the clamping cylinder is supported on the support roller. An opening extending toward the first end of the clamping cylinder is provided on the cylinder wall of the second end of the clamping cylinder. An arc-shaped locking plate is provided on the opening. One end of the arc-shaped locking plate is hinged to the clamping cylinder wall on one side of the opening. The other end of the arc-shaped locking plate is fixed to the clamping cylinder wall on the other side of the opening by a first locking member. The arc-shaped locking plate and the clamping cylinder wall at the opening together form a circular structure.

[0007] The present invention relates to an aircraft model receiving device, wherein the support frame includes an upper frame and a lower frame, both of which are rectangular, and both the upper frame and the lower frame are arranged horizontally. The lower frame is connected to a first spiral lift. The upper frame is located above the lower frame, and the long side and the wide side of the upper frame are respectively arranged to correspond to the long side and the wide side of the lower frame. A fixing rod is fixedly connected between the corresponding long sides of the upper frame and the lower frame. The support seat is provided at each of the two wide sides of the upper frame. The second slide rail is fixedly provided on the lower frame along the length direction of the lower frame. The movable clamping assembly is located in the space enclosed by the upper frame, the lower frame, and the fixing rod. An inlet and outlet are provided on the wide side of the upper frame near the second end of the clamping cylinder. The support seat of the upper frame near the second end of the clamping cylinder is rotatably mounted on the upper frame.

[0008] The present invention relates to an aircraft model receiving device, wherein the support base includes an upper support platform, a middle support platform, and a lower support platform arranged sequentially from top to bottom. The top surface of the upper support platform is provided with a support groove, and the bottom surface of the upper support platform is a downwardly protruding arc-shaped surface. The top surface of the middle support platform is provided with an arc-shaped groove that matches the shape of the bottom surface of the upper support platform. A support roller is provided on the arc-shaped groove, and the bottom surface of the upper support platform is supported on the support roller. A third driving structure is provided between the middle support platform and the upper support platform. The third driving structure can drive the upper support platform to rotate along the support roller on the middle support platform. A second lifting structure is provided on the lower support platform, and the second lifting structure is connected to the middle support platform.

[0009] The present invention relates to an aircraft model receiving device, wherein the top surface of the upper support platform is provided with a strap, and the two ends of the strap are respectively connected to the opposite sides of the support groove.

[0010] The present invention relates to an aircraft model receiving device, wherein the upper support platform is provided with an arc-shaped limiting through hole, the arc-shaped limiting through hole is coaxially arranged with the bottom surface of the upper support platform, and a limiting shaft is fixedly provided on the middle support platform, the limiting shaft being inserted into the arc-shaped limiting through hole.

[0011] The present invention relates to an aircraft model receiving device, wherein the third drive structure includes a handwheel, a gearbox, a gear, and an arc-shaped rack. The arc-shaped rack is fixedly mounted on an upper support platform and is coaxially arranged with the bottom surface of the upper support platform. The gearbox is fixedly mounted on a middle support platform. The input shaft of the gearbox is fixedly connected to the handwheel, which is located outside the middle support platform. The output shaft of the gearbox is fixedly connected to the gear, and the gear meshes with the arc-shaped rack.

[0012] The present invention relates to an aircraft model receiving device, wherein the second lifting structure is a second spiral elevator.

[0013] The present invention relates to an aircraft model receiving device, wherein the two carrier seats are a first carrier seat and a second carrier seat. The lower carrier platform of the first carrier seat is fixedly disposed on the wide side of the upper frame near the first end of the clamping cylinder. One end of the lower carrier platform of the second carrier seat is mounted on the wide side of the upper frame near the second end of the clamping cylinder via a slewing bearing. The other end of the lower carrier platform of the second carrier seat is fixed to the other wide side of the upper frame near the second end of the clamping cylinder via a second locking member. The inlet and outlet are located directly below the lower carrier platform of the second carrier seat.

[0014] The aircraft model receiving device of this invention differs from existing technologies in that, during use, the receiving device is first placed on a lifting device, and then the assembled aircraft model (fixed to a support rod) is secured to a carrier frame. Specifically, the aircraft model can be fixed to two carrier seats, or the support rod fixed to the aircraft model can be fixed to a movable clamping assembly, depending on actual needs. The lifting device then moves to below the test area, specifically below the test equipment. The lifting device then lifts the receiving device and aircraft model through an opening in the test equipment to above it. Next, the receiving device and aircraft model are moved from the lifting device to the test area, i.e., the test equipment. The position of the aircraft model in the test area can be adjusted using the receiving device, facilitating its fixation to the fixed components in the test equipment for testing. Therefore, this invention enables aircraft model receiving, significantly reducing operator workload, shortening the test preparation cycle, and greatly improving the safety and convenience of the operation.

[0015] The invention will now be further described with reference to the accompanying drawings. Attached Figure Description

[0016] Figure 1 This is a three-dimensional schematic diagram of the aircraft model receiving and lifting device using the present invention; Figure 2 A three-dimensional schematic diagram of the auxiliary assembly device in the aircraft model receiving and lifting equipment of the present invention. Figure 1 ; Figure 3 A three-dimensional schematic diagram of the auxiliary assembly device in the aircraft model receiving and lifting equipment of the present invention. Figure 2 ; Figure 4 A three-dimensional schematic diagram of the support frame, support base, first rotary drive, and second drive structure in the aircraft model receiving and lifting device of the present invention; Figure 5 for Figure 4 A schematic diagram showing the connection relationship between the second drive structure and the support base, hidden behind the support frame. Figure 6 This is a three-dimensional schematic diagram of the aircraft model receiving device of the present invention; Figure 7 This is a three-dimensional schematic diagram of the first AGV in this invention; Figure 8 This is a top view of the interior of the first AGV in this invention; Figure 9 This is a schematic diagram of the structure of the first screw jack in this invention; Figure 10 This is a three-dimensional schematic diagram of the support frame and the movable clamping assembly in this invention; Figure 11 This is a three-dimensional schematic diagram of the movable clamping component in this invention. Figure 1 ; Figure 12 This is a three-dimensional schematic diagram of the movable clamping component in this invention. Figure 2 ; Figure 13 This is a three-dimensional schematic diagram of the support base in this invention. Figure 1 ; Figure 14 This is a three-dimensional schematic diagram of the support base in this invention. Figure 2 ; Figure 15 This is a three-dimensional schematic diagram of the upper support platform in this invention. Figure 1 ; Figure 16 This is a three-dimensional schematic diagram of the upper support platform in this invention. Figure 2 ; Figure 17 This is a three-dimensional schematic diagram of the support platform in this invention. Figure 1 ; Figure 18 This is a three-dimensional schematic diagram of the support platform in this invention. Figure 2 ; Figure 19 This is a three-dimensional schematic diagram of the support platform in this invention. Figure 3 ; Figure 20 This is a three-dimensional schematic diagram of the lower support platform in this invention. Figure 1 ; Figure 21 This is a three-dimensional schematic diagram of the lower support platform in this invention. Figure 2 ; Figure 22 This is a three-dimensional schematic diagram of the lifting device in the aircraft model receiving and lifting equipment of the present invention (the scissor platform is in a retracted state). Figure 23 for Figure 22 A 3D diagram showing the hidden accordion cover; Figure 24 A three-dimensional schematic diagram of the limiting component in the aircraft model receiving and lifting device of the present invention. Figure 1 ; Figure 25A three-dimensional schematic diagram of the limiting component in the aircraft model receiving and lifting device of the present invention. Figure 2 ; Figure 26 A three-dimensional schematic diagram of the support components in the aircraft model receiving and lifting device of the present invention. Figure 1 ; Figure 27 A three-dimensional schematic diagram of the support components in the aircraft model receiving and lifting device of the present invention. Figure 2 ; Figure 28 This is a three-dimensional schematic diagram of the lifting device in the aircraft model receiving and lifting equipment of the present invention (the scissor platform is in the extended state). Figure 29 for Figure 28 A three-dimensional schematic diagram of the lifting device behind the concealed bellows cover; Figure 30 This is a three-dimensional schematic diagram of the support rod after it is connected to the auxiliary assembly device. Figure 31 A three-dimensional diagram showing an airplane model connected to a support rod. Figure 32 A three-dimensional diagram illustrating how the second support seat is rotated to allow the aircraft model to enter the support frame; Figure 33 A three-dimensional diagram showing the aircraft model entering the support frame and then rotating the second support seat to install the second support seat on the support frame; Figure 34 A three-dimensional schematic diagram of an airplane model being fixed to a movable clamping assembly; Figure 35 A three-dimensional schematic diagram of an airplane model fixed on a support. Figure 36 A three-dimensional schematic diagram of the transfer of an aircraft model from an auxiliary assembly device to the aircraft model receiving device of the present invention. Figure 37 A three-dimensional schematic diagram of the transfer of an aircraft model from the auxiliary assembly device to the aircraft model receiving device of the present invention (the support rod is not separated from the auxiliary assembly device). Figure 38 A three-dimensional schematic diagram of the transfer of an aircraft model from the auxiliary assembly device to the aircraft model receiving device of the present invention (the support rod has been separated from the auxiliary assembly device). Figure 39 This is a three-dimensional schematic diagram showing the lifting device lifting the aircraft model receiving device and the aircraft model of the present invention.

[0017] Figure reference numerals: 01. Auxiliary assembly device; 02. Lifting device; 03. Aircraft model receiving device; 04. Support column; 05. Third AGV; 06. Control box; 07. First motor; 08. First reducer; 09. Support frame; 10. Support base; 11. First rotary drive; 12. Ladder; 13. First slide rail; 14. First lead screw; 15. Telescopic cylinder; 16. Extension rod; 17. First slider; 18. First rotating shaft; 19. Third rotating shaft; 20. Second rotating shaft; 21. 21. First AGV; 22. First screw jack; 23. Receiving slot; 24. Receiving opening; 25. Bearing frame; 26. Moving clamping assembly; 27. Bearing seat; 28. Third motor; 29. ​​Second reducer; 30. Lower frame; 31. Upper frame; 32. Fixed rod; 33. Second slide rail; 34. Second slider; 35. Inlet / outlet; 36. Chassis of moving clamping assembly; 37. Bearing plate; 38. Support roller; 39. Second rotary drive; 40. Clamping cylinder; 41. Clamping... 42. First end of the clamping cylinder; 43. Second end of the clamping cylinder; 44. Opening on the clamping cylinder; 45. Arc-shaped locking plate; 46. Upper bearing platform; 47. Middle bearing platform; 48. Lower bearing platform; 49. Bearing groove; 50. Binding strap; 51. Arc-shaped rack; 52. Handwheel; 53. Gear; 54. Arc-shaped limiting through hole; 55. Limiting shaft; 56. First handwheel; 57. Bearing rod; 58. Slewing bearing; 59. Baffle; 60. Bottom surface of the upper bearing platform; 61. Arc-shaped groove; 62. Bearing roller. 62. Gearbox; 63. Second screw jack; 64. Second AGV; 65. Scissor lift platform; 66. Scissor lift platform surface; 67. Limiting assembly; 68. Support assembly; 69. Limiting bracket; 70. Limiting arm; 71. Third locking component; 72. Support arm; 73. Second lead screw; 74. Second nut; 75. Second motor; 76. Reducer; 77. Third slide rail; 78. Third slider; 79. Testing equipment; 80. Support rod; 81. Airplane model. Detailed Implementation

[0018] To further illustrate the technical means and effects of the present invention in achieving its intended purpose, the following detailed description of the specific implementation methods, structures, features, and effects of the present invention, in conjunction with the accompanying drawings and preferred embodiments, is provided below.

[0019] like Figure 1 As shown, and in combination Figure 2-39 As shown, the aircraft model 81 receiving and lifting device of the present invention includes an auxiliary assembly device 01, an aircraft model receiving device 03 of the present invention, and a lifting device 02.

[0020] The auxiliary assembly device 01 includes a vertically arranged support column 04. A support frame 09 and a first drive structure for driving the support frame 09 to slide vertically are slidably connected on the support column 04. A support seat 10 is rotatably mounted on the support frame 09 via a horizontally arranged first rotating shaft 18. A first rotary drive 11 is provided on the support seat 10. The axis of the first rotary drive 11 is perpendicular to the first rotating shaft 18. A second drive structure for driving the support seat 10 to rotate is provided on the support frame 09. That is, the second drive structure can drive the support seat 10 to rotate relative to the support frame 09 around the first rotating shaft 18.

[0021] The aircraft model receiving device 03 includes a first AGV 21, on which a carrier frame 25 is connected via a first lifting structure, meaning that the first lifting structure can lift and lower the carrier frame 25.

[0022] The lifting device 02 includes a second AGV 64, on which a scissor platform 65 is provided. The scissor platform 65 is used to support the aircraft model receiving device 03. The scissor platform 65 is capable of lifting and lowering the aircraft model receiving device 03.

[0023] like Figure 1 As shown, and in combination Figure 2-5 As shown, the auxiliary assembly device 01 also includes a third AGV 05. The support column 04 is fixedly mounted on the third AGV 05. A vertically arranged first slide rail 13 is fixedly mounted on the support column 04. A first slider 17 is fixedly mounted on the support frame 09. The first slider 17 is slidably connected to the first slide rail 13. The first drive structure includes a first lead screw 14, a first nut, and a first motor 07. The first lead screw 14 is rotatably mounted on the support column 04. One end of the first lead screw 14 is connected to the first motor 07. A first nut is threaded onto the first lead screw 14. The first nut is fixedly mounted on the support frame 09.

[0024] The first motor 07 is fixed to the top of the support column 04. The output shaft of the first motor 07 is fixedly connected to the input shaft of the first reducer 08. The output shaft of the first reducer 08 is fixedly connected to the top of the first lead screw 14. The bottom end of the first lead screw 14 is rotatably mounted on the support column 04 via a bearing. Specifically, the bottom end of the first lead screw 14 is rotatably mounted on a support plate via a bearing, and the support plate is fixed on the support column 04. Thus, when the first motor 07 drives the first lead screw 14 to rotate, since the support frame 09 is slidably connected to the support column 04 via the first slider 17 and the first slide rail 13, and since both the first lead screw 14 and the first slide rail 13 are arranged vertically, the support frame 09 can slide up and down along the first slide rail 13 via the first slider 17 under the action of the first nut.

[0025] like Figure 2-5 As shown, the second drive structure is a telescopic cylinder 15 arranged vertically. The upper end of the telescopic cylinder 15 is rotatably mounted on the support frame 09 via a horizontally arranged second rotating shaft 20. The lower end of the telescopic cylinder 15 is rotatably mounted on the support base 10 via a horizontally arranged third rotating shaft 19. The first rotary drive 11 and the third rotating shaft 19 are located on opposite sides of the first rotating shaft 18, and the first rotating shaft 18, the second rotating shaft 20, and the third rotating shaft 19 are parallel to each other.

[0026] The telescopic cylinder 15 can be an electric cylinder. The cylinder body of the telescopic cylinder 15 is arranged with the telescopic rod facing downwards. That is, the cylinder body of the telescopic cylinder 15 is rotatably mounted on the support frame 09 via the second rotating shaft 20, and the telescopic rod is rotatably mounted on the support seat 10 via the third rotating shaft 19. Since the first rotary drive 11 and the third rotating shaft 19 are located on opposite sides of the first rotating shaft 18, the telescopic cylinder 15 can drive the support seat 10 to rotate relative to the support frame 09 around the first rotating shaft 18 when it performs telescopic movement, that is, it can make the first rotary drive 11 swing up or down.

[0027] When the piston rod of the telescopic cylinder 15 is connected to the support base 10, an extension rod 16 is fixedly provided on the side of the support base 10 away from the first rotary drive 11. The piston rod of the telescopic cylinder 15 is rotatably mounted on the extension rod 16 through the third rotating shaft 19. The number of telescopic cylinders 15 and extension rods 16 can be determined according to the actual situation. In this embodiment, there are two telescopic cylinders 15 and two extension rods 16, arranged in a one-to-one correspondence.

[0028] It should be noted that the first rotary drive 11 is existing technology, and only a schematic diagram is shown in the accompanying drawings of this invention.

[0029] like Figure 3 As shown, the chassis of the third AGV 05 is equipped with an air cushion. When it needs to be moved, air can be supplied to the air cushion, which will then push the entire auxiliary assembly device 01 to move. Using an air cushion to move the AGV is existing technology, and its structure and principle will not be described in detail here. Figure 1 As shown, the auxiliary assembly device 01 also includes a control box 06, which is used to control the movement of each component in the auxiliary assembly device 01.

[0030] like Figure 6-12As shown, the first lifting structure is a first spiral lift 22. Two opposing support seats 27 are provided on the support frame 25. A movable clamping assembly 26 is provided on the support frame 25, located below the two support seats 27. The movable clamping assembly 26 includes a chassis 36. A second slider 34 is fixedly provided at the bottom of the chassis 36. A second slide rail 33, arranged horizontally, is fixedly provided on the support frame 25. The second slide rail 33 is parallel to the line connecting the centers of the two support seats 27. The second slider 34 is slidably connected to the second slide rail 33. A clamping cylinder 40 is rotatably provided on the top of the chassis 36. The axis of the clamping cylinder 40 is parallel to the second slide rail 33. The two ends of the clamping cylinder 40 are a first end 41 and a second end 42, respectively. A support plate 37 is fixedly provided on the base 36 of the first end 41 of the clamping cylinder 40. The support plate 37 and the first end 41 of the clamping cylinder 40 are connected by a second rotary drive 39. A support roller 38 is rotatably mounted on the base 36 of the second end 42 of the clamping cylinder 40. The second end 42 of the clamping cylinder 40 is supported on the support roller 38. An opening 43 extending towards the first end 41 of the clamping cylinder 40 is provided on the cylinder wall of the second end 42 of the clamping cylinder 40. An arc-shaped locking plate 44 is provided on the opening 43. One end of the arc-shaped locking plate 44 is hinged to the cylinder wall of the clamping cylinder 40 on one side of the opening 43. The other end of the arc-shaped locking plate 44 is fixed to the cylinder wall of the clamping cylinder 40 on the other side of the opening 43 by a first locking member. The arc-shaped locking plate 44 and the cylinder wall of the clamping cylinder 40 at the opening 43 together form a circular structure.

[0031] The support frame 25 includes an upper frame 31 and a lower frame 30, both of which are rectangular. The upper frame 31 and the lower frame 30 are arranged horizontally. The lower frame 30 is connected to the first spiral lift 22. The upper frame 31 is located above the lower frame 30, and the long side and the wide side of the upper frame 31 correspond to the long side and the wide side of the lower frame 30, respectively. A fixing rod 32 is fixedly connected between the corresponding long sides of the upper frame 31 and the lower frame 30. The support seat 27 is provided at the two wide sides of the upper frame 31. The second slide rail 33 is fixedly installed on the lower frame 30 along the length direction of the lower frame 30. The movable clamping assembly 26 is located in the space enclosed by the upper frame 31, the lower frame 30 and the fixing rod 32. An inlet and outlet 35 is provided on the wide side of the upper frame 31 near the second end 42 of the clamping cylinder 40. The support seat 27 of the upper frame 31 near the second end 42 of the clamping cylinder 40 is rotatably installed on the upper frame 31.

[0032] The first screw jack 22 is existing technology, and four of them are configured. These four first screw jacks 22 are mounted in a directional structure on the first AGV 21 (i.e., the housing of each first screw jack 22 is fixed to the first AGV 21). The four first screw jacks 22 are divided into two groups, and the lead screws of the two groups of first screw jacks 22 are respectively connected to the two long sides of the bottom frame 30. Two first screw jacks 22 in each group are simultaneously driven by a third motor 28. Figure 9 As shown, the output shaft of the third motor 28 is fixedly connected to the input shaft of the second reducer 29, and the two output shafts of the second reducer 29 are respectively fixedly connected to the worm gears of the two first screw jacks 22 (in the specific connection, the output shaft of the second reducer 29 can be connected to the worm gear of the first screw jack 22 through the transmission shaft according to the actual situation). In this way, the third motor 28 can drive the lead screws of the two first screw jacks 22 to extend and retract through the second reducer 29, that is, to perform lifting and lowering operations on the support frame 25.

[0033] In this embodiment, the upper border 31 and the lower border 30 are of equal size and the long and wide sides of the two borders are arranged accordingly. That is to say, the projections of the upper border 31 and the lower border 30 on the horizontal plane can coincide.

[0034] The two support seats 27 are respectively located on the two wide sides of the upper frame 31. The line connecting the centers of the two support seats 27 is the length direction of the upper frame 31 and the lower frame 30. The second slide rail 33 is located on the lower frame 30 along the length direction of the lower frame 30, so the second slide rail 33 is parallel to the line connecting the centers of the two support seats 27.

[0035] Since the axis of the clamping cylinder 40 is parallel to the second slide rail 33, and the second slide rail 33 is arranged along the length of the upper frame 31 and the lower frame 30, the axis of the clamping cylinder 40 is parallel to the length of the upper frame 31 and the lower frame 30. Since the two bearing seats 27 are respectively located at the two wide sides of the long frame, and the movable clamping assembly 26 is located in the space enclosed by the upper frame 31, the lower frame 30 and the fixed rod 32, the two bearing seats 27 are respectively arranged close to the first end 41 and the second end 42 of the clamping cylinder 40.

[0036] Due to the design of the opening 43 on the clamping cylinder 40, the cylinder wall at the second end 42 of the clamping cylinder 40 forms a long U-shaped groove structure. The two ends of the arc-shaped locking plate 44 are located at the two ends of the groove opening of the long U-shaped groove. The first locking component can be a bolt or other locking component. The arc-shaped locking plate 44 and the long U-shaped groove form a circular structure, which facilitates the fixing of the support rod 80 below. The number of arc-shaped locking plates 44 can be set according to actual requirements.

[0037] The first end 41 of the clamping cylinder 40 is connected to the support plate 37 via a second rotary drive 39. The second rotary drive 39 is a manual rotary drive, which is existing technology, and its specific structure and working principle will not be described in detail here. Two support rollers 38 are provided, respectively located on opposite sides of the second end 42 of the clamping cylinder 40. Since the first end 41 of the clamping cylinder 40 is connected to the support plate 37 via the second rotary drive 39 (the second rotary drive 39 is coaxially arranged with the clamping cylinder 40), and the second end 42 is supported on the support rollers 38, the clamping cylinder 40 can be driven to rotate around its own axis via the second rotary drive 39.

[0038] When specifically setting the inlet and outlet 35, the wide side of the upper frame 31 near the second end 42 of the clamping cylinder 40 can be completely removed, so that the inlet and outlet 35 is formed between the two long sides of the upper frame 31 near the second end 42 of the clamping cylinder 40.

[0039] like Figure 13-21 As shown, the two support seats 27 have the same structure. Each support seat 27 includes an upper support platform 45, a middle support platform 46, and a lower support platform 47 arranged sequentially from top to bottom. The top surface of the upper support platform 45 is provided with a support groove 48, which is used to support the aircraft model 81. The bottom surface 59 of the upper support platform 45 is a downwardly protruding arc-shaped surface. The top surface of the middle support platform 46 is provided with an arc-shaped groove 60 that matches the shape of the bottom surface 59 of the upper support platform 45. The arc-shaped groove 60 is provided with a support roller 61. The bottom surface 59 of the upper support platform 45 is supported on the support roller 61. A third driving structure is provided between the middle support platform 46 and the upper support platform 45. The third driving structure can drive the upper support platform 45 to rotate along the support roller 61 on the middle support platform 46. The lower support platform 47 is provided with a second lifting structure, which is connected to the middle support platform 46.

[0040] The upper support platform 45 has a strap 49 on its top surface, with both ends of the strap 49 connected to opposite sides of the support groove 48. The upper support platform 45 has an arc-shaped limiting through hole 53, which is coaxially arranged with the bottom surface 59 of the upper support platform 45. A limiting shaft 54 ​​is fixedly mounted on the middle support platform 46, and the limiting shaft 54 ​​passes through the arc-shaped limiting through hole 53. The third drive structure includes a handwheel 51, a gearbox 62, a gear 52, and an arc-shaped rack 5. 0. The arc-shaped rack 50 is fixedly mounted on the upper support platform 45. The arc-shaped rack 50 is coaxially arranged with the bottom surface 59 of the upper support platform 45. The gearbox 62 is fixedly mounted on the middle support platform 46. The input shaft of the gearbox 62 is fixedly connected to the handwheel 51. The handwheel 51 is located outside the middle support platform 46. The output shaft of the gearbox 62 is fixedly connected to the gear 52. The gear 52 meshes with the arc-shaped rack 50. The second lifting structure is a second screw lift 63.

[0041] Multiple bearing rollers 61 are provided, and the multiple bearing rollers 61 are arranged circumferentially along the arc-shaped groove 60 of the middle bearing platform 46. The bottom surface 59 of the upper bearing platform 45 is fixedly provided with downwardly extending baffles 58 on opposite sides. The two baffles 58 are respectively located on opposite sides of the top of the middle bearing platform 46. Each baffle 58 is provided with an arc-shaped limiting through hole 53. On opposite sides of the top of the middle bearing platform 46, limiting shafts 54 corresponding to the arc-shaped limiting through holes 53 on the two baffles 58 are fixedly provided. The limiting shafts 54 are inserted into the corresponding arc-shaped limiting through holes 53.

[0042] The arc-shaped rack 50 is fixedly mounted on the lower outer side of the upper support platform 45, the gearbox 62 is located inside the middle support platform 46, and the handwheel 51 and gear 52 are both located on the outer side of the middle support platform 46. Rotating the handwheel 51 causes the gear 52 to rotate via the gearbox 62. Since the gear 52 meshes with the arc-shaped rack 50, and the arc-shaped rack 50 is coaxially arranged with the bottom surface 59 of the upper support platform 45, the upper support platform 45 rotates around its own axis along the support roller 61. Because the arc-shaped limiting through hole 53 is coaxially arranged with the bottom surface 59 of the upper support platform 45, the limiting shaft 54 ​​is always located in the arc-shaped limiting through hole 53 when the upper support platform 45 rotates, and the two ends of the arc-shaped limiting through hole 53 alternately move towards the limiting shaft 54. In other words, if we consider the movement of the limiting shaft 54 ​​relative to the arc-shaped limiting through hole 53, then the limiting shaft 54 ​​moves back and forth between the two ends of the arc-shaped limiting through hole 53. Thanks to the setting of the limiting shaft 54 ​​and the arc-shaped limiting through hole 53, the upper support platform 45 can rotate more smoothly and will not fall off the middle support platform 46.

[0043] Two second screw jacks 63 are provided, and the housings of both second screw jacks 63 are fixed on the lower support platform 47. The lead screws of both second screw jacks 63 are connected to the bottom end of the middle support platform 46 (in this embodiment, they are plugged in). The worm gears of the two second screw jacks 63 are fixedly connected by a drive shaft. At least one second screw jack 63 has a first handwheel 55 fixedly installed on the end of its worm gear that is not connected to the drive shaft. The first handwheel 55 is located outside the lower support platform 47. Rotating the first handwheel 55 can simultaneously drive the lead screws of both second screw jacks 63 to extend and retract, thus driving the middle support platform 46 and the upper support platform 45 mounted on it to move up and down together.

[0044] like Figure 20As shown, a vertically arranged support rod 56 is fixedly installed inside the lower support platform 47. The support rod 56 is located below the middle support platform 46. When the screw of the second screw jack 63 retracts and does not lift the middle support platform 46 and the upper support platform 45, the middle support platform 46 can be supported on the support rod 56. Conversely, when the second screw jack 63 lifts the middle support platform 46 and the upper support platform 45, the middle support platform 46 is not supported on the support rod 56.

[0045] The two bearing seats 27 are a first bearing seat and a second bearing seat. The lower bearing platform 47 of the first bearing seat is fixedly mounted on the wide side of the upper frame 31 near the first end 41 of the clamping cylinder 40. One end of the lower bearing platform 47 of the second bearing seat is mounted on the wide side of the upper frame 31 near the second end 42 of the clamping cylinder 40 via a slewing bearing 57. The other end of the lower bearing platform 47 of the second bearing seat is fixed to the other end of the wide side of the upper frame 31 near the second end 42 of the clamping cylinder 40 via a second locking member. The inlet and outlet 35 is located directly below the lower bearing platform 47 of the second bearing seat.

[0046] The second locking element can be a bolt or other locking element. After the second locking element is released, the second bearing seat can be rotated around the slewing bearing 57 to the outside of the bearing frame 25, thereby exposing the inlet and outlet 35. This makes it convenient to transfer the support rod 80 and the aircraft model 81 mounted on it from the auxiliary assembly device 01 to the bearing frame 25 of the aircraft model receiving device 03.

[0047] like Figure 22-25 As shown in Figures 28 and 29, a limiting component 67 for limiting the first AGV21 of the aircraft model receiving device 03 is fixedly provided on the platform 66 of the scissor platform 65. The limiting component 67 includes a limiting bracket 69, on which a limiting arm 70 is rotatably mounted. When the limiting arm 70 rotates to a horizontal position, it can lock its relative position with the limiting bracket 69 by a third locking member 71, that is, fix the limiting arm 70 in a horizontal position.

[0048] When it is necessary to remove the model aircraft receiving device 03 from the lifting device 02 or to transfer the model aircraft receiving device 03 to the lifting device 02, the third locking member 71 needs to be unlocked and the limiting arm 70 needs to be rotated from the horizontal position to the vertical position. Only in this way can the model aircraft receiving device 03 be removed from the lifting device 02 or transferred to the lifting device 02. The number of limiting components 67 can be determined according to the actual situation. In this embodiment, the limiting components 67 are set to four sets. After the aircraft model receiving device 03 is transferred to the lifting device 02, the four sets of limiting components 67 are respectively located at the four corners of the first AGV 21. Then, the limiting arms 70 of the four sets of limiting components 67 are rotated from the vertical position to the horizontal position. At this time, two limiting arms 70 are respectively abutted on the opposite sides of the first AGV 21. Then, the limiting arms 70 are fixed in the horizontal position by the third locking member 71 (such as bolts, pins, etc.). In this way, when the lifting device 02 transfers the aircraft model receiving device 03, the aircraft model receiving device 03 will not fall off the lifting device 02.

[0049] like Figure 22 , 23 As shown in Figures 26-29, a support assembly 68 is provided on the platform 66 of the scissor lift platform 65. The support assembly 68 includes two opposing support arms 72, which are slidably connected to the platform 66 of the scissor lift platform 65 along their respective length directions. Under the drive of a fourth drive structure, the two support arms 72 can slide closer to or further away from each other. The fourth drive structure includes a second motor 75, a reducer 76, two second lead screws 73, and two second nuts 74. The two second lead screws 73 are rotatably mounted on the platform 66 of the scissor lift platform 65 and are parallel to the two support arms 72. Two second lead screws 73 are coaxial and spaced apart. The reducer 76 is fixedly mounted on the scissor platform 65 platform 66 between the two second lead screws 73. The output shaft of the second motor 75 is fixedly connected to the input shaft of the reducer 76. The two output shafts of the reducer 76 are respectively fixedly connected to the two second lead screws 73. Two second nuts 74 are respectively threaded onto the two second lead screws 73. The two second nuts 74 are respectively fixedly connected to the two support arms 72. When the two support arms 72 slide away from each other under the drive of the fourth drive structure, the two support arms 72 can extend to the outside of the scissor platform 65 platform 66.

[0050] The ends of the two second lead screws 73 closest to the reducer 76 are fixedly connected to the two output shafts of the reducer 76, and the ends of the two second lead screws 73 furthest from the reducer 76 are rotatably mounted on the platform 66 of the scissor lift platform 65 through bearing seats.

[0051] Each support arm 72 has a third slide rail 77 fixedly arranged along the length of the support arm 72 on its bottom surface. The scissor platform 65 has a third slider 78 arranged corresponding to the two third slide rails 77 on its platform 66. Each support arm 72 is slidably connected to the corresponding third slider 78 through its own third slide rail 77.

[0052] When the second motor 75 drives the two second lead screws 73 to rotate simultaneously through the reducer 76, since the two second nuts 74 are respectively threaded onto the two second lead screws 73 and respectively fixedly connected to the two support arms 72, and the two support arms 72 are respectively slidably connected to the platform 66 of the scissor lift platform 65 along their respective length directions, and the two second lead screws 73 are respectively parallel to the two support arms 72, the two second nuts 74 can move closer or further away from each other along their respective second lead screws 73, that is, they can drive the two support arms 72 to slide closer or further away from each other.

[0053] The number of support components 68 can be determined according to the actual situation. In this embodiment, the support components 68 are set in two groups, and the two groups of support components 68 are respectively set on opposite sides of the scissor lift platform 65 platform 66.

[0054] The scissor lift platform 65 is covered with a bellows-shaped protective cover. It should be noted that the scissor lift platform 65 is existing technology, and its specific structure and working principle will not be described in detail.

[0055] The difference between the aircraft model receiving device of the present invention and the prior art is that, in use, the receiving device 03 is first placed on the lifting device 02, and then the assembled aircraft model 81 (which is fixedly connected to a support rod 80) is fixed on the carrier frame 25. Specifically, the aircraft model 81 can be fixed on two carrier seats 27 according to actual needs, or the support rod 80 fixedly connected to the aircraft model 81 can be fixed on the movable clamping assembly 26. Then, the lifting device 02 moves to below the test area, specifically below the test equipment 79. The lifting device 02 then lifts the receiving device 03 and the aircraft model 81 through the opening of the test equipment 79 to above the test equipment 79. Then, the receiving device 03 and the aircraft model 81 are moved from the lifting device 02 to the test area, i.e., the test equipment 79. The position of the aircraft model 81 in the test area can be adjusted by the receiving device 03 to facilitate the fixing of the aircraft model 81 to the fixed parts in the test equipment 79 for testing. Therefore, it can be seen that the present invention can receive aircraft model 81, thereby greatly reducing the workload of operators, shortening the test preparation cycle, and greatly improving the safety and convenience of the operation process.

[0056] When using the aircraft model 81 of the present invention to receive the lifting device, such as Figure 30 ,31 As shown, the auxiliary assembly device 01 is moved to the assembly area of ​​the aircraft model 81 by the third AGV 05, and the aircraft model 81 is assembled on the auxiliary assembly device 01, specifically on the first rotary drive 11. That is, one end of the L-shaped support rod 80 is first fixedly installed on the first rotary drive 11, and then the aircraft model 81 is fixedly installed on the other end of the support rod 80. Figure 36 , 37 As shown in Figure 38, the aircraft model receiving device 03 is placed on the lifting device 02, specifically on the platform 66 of the scissor platform 65, and the aircraft model receiving device 03 is limited by the limiting component 67. Then, the lifting device 02 is moved by the second AGV 64 to the vicinity of the auxiliary assembly device 01. The lifting device 02 then adjusts its own position by the second AGV 64, and at the same time, the height of the support frame 09 is adjusted by the first drive structure, thereby adjusting the height of the aircraft model 81. The support base 10 is rotated relative to the support frame 09 around the first rotating shaft 18 by the second drive structure, that is, the pitch angle of the aircraft model 81 is adjusted. The roll angle of the aircraft model 81 is adjusted by the first rotation drive 11 so that the aircraft model 81 can be aligned with the aircraft model receiving device 03, specifically aligned with the side of the support frame 25 near the second end 42 of the clamping cylinder 40. Figure 32 , 33 As shown in Figures 36 and 37, the second locking element is then unlocked, allowing the second carrier to rotate to the outside of the carrier frame 25, exposing the inlet / outlet 35. The lifting device 02 is then moved closer to the auxiliary assembly device 01, causing the support rod 80, carrying the aircraft model 81, to enter the carrier frame 25 through the inlet / outlet 35. The second carrier is then rotated in the opposite direction, and the second locking element locks the second carrier onto the carrier frame 25. Afterward, the support rod 80 is separated from the first rotary drive 11, as shown in Figures 36 and 37. Figure 38 As shown. Then, the aircraft model 81 is transferred to the aircraft model receiving device 03, specifically the support frame 25, where the aircraft model 81 can be fixed to the two support seats 27 of the support frame 25 (e.g., Figure 35 (As shown), the airplane model 81 can also be fixed to the movable clamping assembly 26 (as shown). Figure 34 As shown), to correspond to the fixed components (not shown) at different heights in the test device 79 (only a partial structure of the test device 79 is shown in the figure).

[0057] The support rod 80 is L-shaped and includes a horizontal rod and a vertical rod that are fixedly connected. The end of the horizontal rod is fixedly connected to the first rotary drive 11, and the horizontal rod is coaxially arranged with the first rotary drive 11. The end of the vertical rod faces upward and is fixedly connected to the aircraft model 81. When the second drive structure drives the support base 10 to rotate around the first rotating shaft 18 relative to the support frame 09, since the axis of the first rotary drive 11 is perpendicular to the first rotating shaft 18, the first rotary drive 11 can drive the aircraft model 81 and the support rod 80 to swing up and down together to adjust the pitch angle of the aircraft model 81 and the support rod 80. Since the horizontal rod of the support rod 80 is coaxially arranged with the first rotary drive 11, the first rotary drive 11 can drive the horizontal rod to rotate around its own axis, and the aircraft model 81 also rotates with the support rod 80 to adjust the roll angle of the aircraft model 81 and the support rod 80.

[0058] like Figure 35 As shown, before fixing the aircraft model 81 onto the carrier 27, the chassis 36 of the movable clamping assembly 26 is slid away from the auxiliary assembly device 01 via the second slider 34 and the second slide rail 33 (i.e., towards the first end 41 of the clamping cylinder 40). The height, pitch angle, and roll angle of the aircraft model 81 are adjusted by the auxiliary assembly device 01. Then, the aircraft model 81 is placed in the bearing grooves 48 of the two carriers 27 and fixed to the two carriers 27 by the two straps 49. Of course, if the height of the carrier frame 25 is too low to fully accommodate the support rod 80, a receiving opening 24 is provided on the wide side of the lower frame 30 near the second end 42 of the clamping cylinder 40, and a receiving groove 23 is provided on the first AGV 21 at the location corresponding to the receiving opening 24, so that when the support rod 80 enters the carrier frame 25, it passes through the inlet / outlet 35, the receiving opening 24, and the receiving groove 23 from top to bottom.

[0059] like Figure 34 As shown, before fixing the aircraft model 81 to the movable clamping assembly 26, the chassis 36 of the movable clamping assembly 26 is first slid towards the auxiliary assembly device 01 via the second slider 34 and the second slide rail 33 (i.e., slid towards the second end 42 of the clamping cylinder 40). Then, the first locking member is unlocked, the arc-shaped locking plate 44 is opened, and the height, pitch angle and roll angle of the aircraft model 81 and the support rod 80 are adjusted by the auxiliary assembly device 01. Then, the support rod 80 is placed in the cylinder wall at the opening 43 of the clamping cylinder 40, i.e., in the long U-shaped groove mentioned above. Then, the arc-shaped locking plate 44 is rotated in the opposite direction, and the arc-shaped locking plate 44 is fixed to the clamping cylinder 40 by the first locking member, i.e., the support rod 80 is fixed to the clamping cylinder 40, thereby fixing the aircraft model 81 to the movable clamping assembly 26.

[0060] After securing the aircraft model 81 to the support frame 25, the lifting device 02 is moved below the test area, specifically below the test equipment 79. Then, the lifting device 02 uses the scissor platform 65 to lift the aircraft model receiving device 03 and the aircraft model 81 through the opening of the test equipment 79 to above the test equipment 79. Figure 28 , 39 As shown, the two support arms 72 in the support assembly 68 are then driven by the fourth drive structure, causing them to slide away from each other until they extend beyond the platform 66 of the scissor lift platform 65 and then attach to the test equipment 79. This establishes a fixed connection between the platform 66 of the scissor lift platform 65 and the test equipment 79. Then, the limiting assembly 67 releases the restriction on the aircraft model receiving device 03, and the first AGV 21 moves the aircraft model receiving device 03 and the aircraft model 81 from the lifting device 02 to the test area, i.e., the test equipment 79. The position of the aircraft model 81 in the test area can be adjusted via the aircraft model receiving device 03 to facilitate its fixation for testing. Specifically: (1) When the aircraft model 81 is fixed on the carrier 27: the aircraft model 81 can be moved to the fixed part close to the test equipment 79 by the aircraft model receiving device 03 (which is part of the test equipment 79 and is used to fix the aircraft model 81 so that the test equipment 79 can test the aircraft model 81). Then, the carrier frame 25 and the aircraft model 81 and support rod 80 installed on it are raised and lowered by the first spiral lift 22 to make a coarse adjustment of the height of the aircraft model 81 and support rod 80. The middle carrier platform 46, the upper carrier platform 45 and the aircraft model 81 and support rod 80 fixed on the upper carrier platform 45 are raised and lowered by the second spiral lift 63 to make a fine adjustment of the height of the aircraft model 81 and support rod 80. At the same time, the handwheel 51 can be turned to make the upper carrier platform 45 and the aircraft model 81 and support rod 80 on it rotate together along the carrier roller 61 to adjust the rolling angle of the aircraft model 81 and support rod 80 so that the support rod 80 is aligned with the fixed part. Then the support rod 80 is fixedly connected to the fixed part. Next, release the restraints on the aircraft model 81 by the straps 49, then unlock the second locking piece, allowing the second carrier to rotate to the outside of the carrier frame 25, exposing the inlet and outlet 35. Then, allow the aircraft model receiving device 03 to move away from the fixed part until the aircraft model 81 separates from the carrier frame 25. At this point, the aircraft model 81 is fixed to the fixed part.

[0061] (2) When the aircraft model 81 is fixed on the movable clamping assembly 26: the difference between this and the above-mentioned aircraft model 81 fixed on the carrier 27 is that the height adjustment of the aircraft model 81 and the support rod 80 is only carried out by the first spiral lift 22, the roll angle adjustment of the aircraft model 81 and the support rod 80 is carried out by the second rotary drive 39 driving the clamping cylinder 40 to rotate, and when separating the aircraft model 81 and the carrier 25, the arc-shaped locking plate 44 is unlocked instead of the strap 49. The rest of the operation process is the same as the operation process when the aircraft model 81 is fixed on the carrier 27.

[0062] After fixing the aircraft model 81 to the fixed component and separating the carrier frame 25 from the aircraft model 81, the second carrier seat is rotated in the opposite direction and locked onto the carrier frame 25 by the second locking member. Then, the aircraft model receiving device 03 is moved back onto the lifting device 02, and the aircraft model receiving device 03 is limited by the limiting component 67. Next, the two support arms 72 of the support component 68 are allowed to slide closer to each other, separating the two support arms 72 from the test equipment. Finally, the scissor platform 65 is lowered, and the lifting device 02 is driven away from the test area.

[0063] After the aircraft model 81 has been tested, it can be removed from the test equipment 79 using the aircraft model lifting device. The process is the reverse of the process of installing the aircraft model 81 on the test equipment 79, and will not be described in detail here.

[0064] like Figure 1 As shown, when transferring the aircraft model 81 from the auxiliary assembly device 01 to the aircraft model receiving device 03, a ladder 12 can be placed next to the lifting device 02 to facilitate the staff to climb onto the lifting device 02 and complete the transfer operation of the aircraft model 81.

[0065] Therefore, it can be seen that the aircraft model receiving and lifting equipment of the present invention can assist in the assembly, receiving, lifting and testing of the aircraft model 81 and the adjustment of the test area position. The whole process can greatly reduce the workload of operators, shorten the test preparation cycle, and greatly improve the safety and convenience of the operation.

[0066] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention in any way. Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make some modifications or alterations to the above-disclosed technical content to create equivalent embodiments without departing from the scope of the present invention. Any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the scope of the present invention shall still fall within the scope of the present invention.

Claims

1. An aircraft model receiving device, characterized in that: The system includes a first AGV, on which a support frame is connected via a first lifting structure. The support frame has two oppositely arranged support seats and a movable clamping assembly located below the two support seats.

2. The aircraft model receiving device according to claim 1, characterized in that: The first lifting structure is a first screw jack.

3. The aircraft model receiving device according to claim 2, characterized in that: The movable clamping assembly includes a chassis, a second slider fixedly mounted on the bottom of the chassis, a second slide rail fixedly mounted on the support frame and arranged horizontally, the second slide rail being parallel to the line connecting the centers of the two support seats, the second slider being slidably connected to the second slide rail, a clamping cylinder rotatably mounted on the top of the chassis, the axis of the clamping cylinder being parallel to the second slide rail, the two ends of the clamping cylinder being a first end and a second end, respectively, a support plate fixedly mounted on the chassis at the first end of the clamping cylinder, the support plate and the first end of the clamping cylinder being connected by a second rotary drive, a support roller rotatably mounted on the chassis at the second end of the clamping cylinder, the second end of the clamping cylinder being supported on the support roller, an opening extending toward the first end of the clamping cylinder being provided on the cylinder wall at the second end of the clamping cylinder, an arc-shaped locking plate being provided on the opening, one end of the arc-shaped locking plate being hinged to the clamping cylinder wall on one side of the opening, the other end of the arc-shaped locking plate being fixed to the clamping cylinder wall on the other side of the opening by a first locking member, the arc-shaped locking plate and the clamping cylinder wall at the opening together forming a circular structure.

4. The aircraft model receiving device according to claim 3, characterized in that: The support frame includes a rectangular upper frame and a rectangular lower frame, both arranged horizontally. The lower frame is connected to a first spiral lift. The upper frame is located above the lower frame, and its long and wide sides correspond to the long and wide sides of the lower frame, respectively. A fixing rod is fixedly connected between the corresponding long sides of the upper and lower frames. The support seats are respectively provided at the two wide sides of the upper frame. The second slide rail is fixedly installed on the lower frame along its length. The movable clamping assembly is located within the space enclosed by the upper frame, the lower frame, and the fixing rod. An inlet and outlet are provided on the wide side of the upper frame near the second end of the clamping cylinder. The support seats of the upper frame near the second end of the clamping cylinder are rotatably mounted on the upper frame.

5. The aircraft model receiving device according to claim 4, characterized in that: The support base includes an upper support platform, a middle support platform, and a lower support platform arranged sequentially from top to bottom. The top surface of the upper support platform is provided with a support groove, and the bottom surface of the upper support platform is a downwardly protruding arc-shaped surface. The top surface of the middle support platform is provided with an arc-shaped groove that matches the shape of the bottom surface of the upper support platform. A support roller is provided on the arc-shaped groove, and the bottom surface of the upper support platform is supported on the support roller. A third driving structure is provided between the middle support platform and the upper support platform. The third driving structure can drive the upper support platform to rotate along the support roller on the middle support platform. A second lifting structure is provided on the lower support platform, and the second lifting structure is connected to the middle support platform.

6. The aircraft model receiving device according to claim 5, characterized in that: The top surface of the upper support platform is provided with a strap, and the two ends of the strap are respectively connected to the opposite sides of the support groove.

7. The aircraft model receiving device according to claim 6, characterized in that: The upper support platform is provided with an arc-shaped limiting through hole, which is coaxially arranged with the bottom surface of the upper support platform. A limiting shaft is fixedly provided on the middle support platform, and the limiting shaft is inserted into the arc-shaped limiting through hole.

8. The aircraft model receiving device according to claim 7, characterized in that: The third drive structure includes a handwheel, a gearbox, a gear, and an arc-shaped rack. The arc-shaped rack is fixedly mounted on the upper support platform and is coaxially arranged with the bottom surface of the upper support platform. The gearbox is fixedly mounted on the middle support platform. The input shaft of the gearbox is fixedly connected to the handwheel, which is located outside the middle support platform. The output shaft of the gearbox is fixedly connected to the gear, and the gear meshes with the arc-shaped rack.

9. The aircraft model receiving device according to claim 8, characterized in that: The second lifting structure is a second screw jack.

10. The aircraft model receiving device according to claim 9, characterized in that: The two bearing seats are a first bearing seat and a second bearing seat. The lower bearing platform of the first bearing seat is fixedly installed on the wide side of the upper frame near the first end of the clamping cylinder. One end of the lower bearing platform of the second bearing seat is installed on the wide side of the upper frame near the second end of the clamping cylinder through a slewing bearing. The other end of the lower bearing platform of the second bearing seat is fixed to the other end of the wide side of the upper frame near the second end of the clamping cylinder through a second locking member. The inlet and outlet are located directly below the lower bearing platform of the second bearing seat.

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