An aircraft nose landing gear assembly test vehicle

Abstract

This application provides a test vehicle for assembling aircraft nose landing gear, relating to the field of aircraft assembly. It includes: a base plate with casters mounted on its bottom; a support plate for placing the nose landing gear on its top; a receiving groove formed in the top of the base plate; a fixing rod disposed within the receiving groove; a bushing fitted onto the fixing rod; and a guide plate fixedly disposed on the bushing. Before the nose landing gear is placed on the support plate, the guide plate is located below the support plate. An adjustment mechanism is provided within the receiving groove for adjusting the guide plate, thereby facilitating the placement of the nose landing gear on the support plate. This application provides the advantage of relatively easy placement of the nose landing gear on the support plate.

Description

Technical Field

[0001] This application relates to the field of aircraft assembly, and in particular to an aircraft nose landing gear assembly test vehicle. Background Technology

[0002] The nose landing gear is a component of the landing gear system, located below the nose of the aircraft and serving as a ground support. It consists of the nose wheel, struts, shock absorbers, steering mechanism, yaw dampers, brakes, retraction mechanism, and skid plates. When the aircraft is moving on the ground, the nose landing gear, besides supporting a small portion of the weight load, primarily serves a guiding function. The pilot operates the steering mechanism of the nose wheel to steer the aircraft. Swaying or deflection caused by uneven ground or other external forces is eliminated by the yaw dampers to maintain stable gliding along the intended direction.

[0003] With the continuous development of my country's large transport aircraft, higher requirements have been placed on the automation level, assembly cost, and assembly reliability and safety of the nose landing gear assembly. Therefore, in this process, it is necessary to use an assembly test vehicle so that it can be assembled and moved repeatedly.

[0004] Currently, in the relevant technology, Chinese patent with authorization publication number CN103434655A discloses an aircraft nose landing gear assembly test vehicle, which includes an installation platform, casters, push rods, as well as a control cabinet, V-shaped plate, vertical plate, extended fixing plate, rotating plate, servo electric cylinder, slider mechanism, and safety limit switch. The control cabinet is located on the outside of the vertical plate on the installation platform, the push rod is fixed on the upper part of the outside of the vertical plate, and casters are installed at the four corners of the bottom surface of the installation platform.

[0005] The V-shaped plate is fixed in the middle of the installation platform. There is a rectangular hole in the middle of the two plates of the V-shaped plate. The four corners of the V-shaped plate are fixed to the ends of four vertical servo electric cylinders fixed on the installation platform through the middle connecting plate. The rotating plate and the side baffle are fixed to the side of the V-shaped plate. The slider mechanism is connected to the horizontal servo electric cylinder and installed between the extended fixed plate and the rotating plate. The safety limit switch is fixed between the vertical servo electric cylinders at both ends of the V-shaped plate. The side of the extended fixed plate is fixed to the V-shaped plate. The horizontal servo electric cylinder is connected to the vertical plate of the extended fixed plate. The rod of the horizontal servo electric cylinder is engaged with the threaded hole at the bottom of the clamping block.

[0006] The rotating plate is L-shaped and fixed to the side baffle. The vertical section of the rotating plate has a through hole in the middle and a dovetail groove at the bottom. The slider mechanism includes a locking block and a dovetail groove slider. The rectangular plate at the bottom of the slider is inserted into the concave groove of the locking block. The small rotating shaft passes through the through hole of the rectangular block and the through hole on the side of the locking block. The dovetail groove slider rotates around the small rotating shaft and is inserted into the dovetail groove of the rotating plate. The servo electric cylinder includes four vertical servo electric cylinders and one horizontal servo electric cylinder.

[0007] Four vertical servo electric cylinders are fixed on the mounting platform. Ball nuts are installed at the ends of the rods of the four vertical servo electric cylinders and are fixed by large and small locking nuts. The threaded balls of the four ball nuts are respectively installed in the round holes of the first ball nut connecting plate, the round slots of the second ball nut connecting plate, the round slots of the third ball nut connecting plate, and the square slots of the fourth ball nut connecting plate. The four ball nut connecting plates are respectively fixed to the four corners of the V-shaped plate.

[0008] Utilizing four omnidirectional wheels and five servo electric cylinders, the nose landing gear achieves six degrees of freedom motion, as well as the rotation of the nose landing gear strut along the axle. The movement of the nose landing gear along the X and Y axes and its rotation around the Z axis can be manually and quickly adjusted. The movement of the nose landing gear along the Z axis and its rotation around the X and Y axes, as well as the rotation of the nose landing gear strut along the axle, can be quantitatively adjusted via the servo electric cylinders. Real-time quantitative control enables six degrees of freedom motion. The nose landing gear assembly test vehicle boasts high degrees of freedom, accurate and easy positioning during assembly, and allows for quantitative control and flexible manual and rapid adjustment, significantly improving the assembly accuracy of the nose landing gear and saving assembly time.

[0009] However, before assembling the nose landing gear, it needs to be placed on a V-shaped plate. Since the nose landing gear is generally large in size and weight, lifting and moving it onto the V-shaped plate requires a lot of effort, especially since multiple nose landing gears need to be moved repeatedly. Furthermore, due to the large size and weight of the nose landing gear, if it is not properly controlled during the handling process, it is easy to accidentally injure the staff. Summary of the Invention

[0010] To address the issues of excessive effort required to lift and move the nose landing gear onto the V-shaped plate, and the potential for injury to personnel if the nose landing gear is not properly controlled during transport due to its large size and weight, this application provides an aircraft nose landing gear assembly test vehicle.

[0011] This application provides an aircraft nose landing gear assembly test vehicle, which adopts the following technical solution:

[0012] An aircraft nose landing gear assembly test vehicle includes: a base plate with casters mounted on its bottom; a support plate for placing the nose landing gear on the top of the base plate; a receiving groove formed on the top of the base plate; a fixing rod disposed in the receiving groove; a bushing sleeve fitted on the fixing rod; a guide plate fixedly disposed on the bushing; and before the nose landing gear is placed on the support plate, the guide plate is located below the support plate. An adjustment mechanism is provided in the receiving groove for adjusting the guide plate, thereby facilitating the placement of the nose landing gear on the support plate.

[0013] By adopting the above technical solution, the guide plate is moved to one end of the receiving plate using the adjustment mechanism, and the guide plate will automatically tilt until the end of the guide plate close to the receiving plate abuts against the receiving plate; then the guide plate is used to push the nose landing gear onto the receiving plate, so that the nose landing gear does not need to be lifted and carried onto the receiving plate with effort, and it is less likely to cause accidental injury due to poor control of the nose landing gear during the carrying process.

[0014] Optionally, the adjustment mechanism includes a pushing assembly, which includes a slider, a lead screw, a transmission belt, and a drive motor. The inner sidewall of the receiving groove is provided with a sliding groove. The slider is slidably connected to the sliding groove and slides horizontally. The fixing rod is fixed to the slider. The lead screw is rotatably installed in the sliding groove and passes through the slider and is threadedly connected to the slider. The drive motor is installed in the receiving groove, and the output end of the drive motor is driven to the lead screw through the transmission belt.

[0015] By adopting the above technical solution, the drive motor is started, and the lead screw is driven to rotate through the transmission belt. The rotation of the lead screw can drive the slider to slide in the slide groove, thereby driving the guide plate to move towards the end of the receiving plate away from the side plate, until the slider slides to the top of the slide groove, that is, the guide plate moves to the end of the receiving plate away from the side plate.

[0016] Optionally, the adjustment mechanism further includes a flipping assembly, which includes a lifting part, comprising a sliding plate, a sleeve, a screw, and a connecting block. The sliding plate is fixed to the slider, the sleeve is rotatably mounted on the sliding plate, a connecting groove is provided at the bottom of the guide plate, the connecting block is slidably connected to the connecting groove, one end of the screw is threaded to the sleeve, and the other end is hinged to the connecting block.

[0017] By adopting the above technical solution, the sleeve is rotated to drive the screw to extend out of the sleeve, thereby lifting the end of the guide plate close to the drive motor so that the guide plate can slowly tilt.

[0018] Optionally, the flipping assembly further includes a driving unit, which includes a driving rod, a gear, and a rack. The bottom of the receiving groove has a placement groove, and the rack is installed in the placement groove. One end of the driving rod is rotatably mounted on the slide plate and fixed to the sleeve, while the other end extends into the placement groove. The gear is coaxially sleeved on the driving rod, and the gear meshes with the rack.

[0019] By adopting the above technical solution, since the gear and rack mesh, the gear will rotate, and the rotation of the gear will drive the drive rod and the sleeve to rotate in sequence; the rotation of the sleeve will cause the drive screw to extend out of the sleeve, thereby lifting the end of the guide plate close to the drive motor, so that the guide plate will slowly tilt until the guide plate abuts against the receiving plate, thereby facilitating the push of the front landing gear onto the receiving plate.

[0020] Optionally, a connecting plate is provided on the end wall of one end of the receiving plate, and the top of the connecting plate is provided with an arc-shaped surface. When the front landing gear needs to be placed on the receiving plate, the guide plate abuts against the connecting plate.

[0021] By adopting the above technical solution, when the nose landing gear is pushed onto the receiving plate through the guide plate, the curved surface on the connecting plate can easily push the nose landing gear onto the connecting plate, and then the connecting plate can easily push the nose landing gear onto the receiving plate, so that jamming is less likely to occur during the process of pushing the nose landing gear.

[0022] Optionally, a floor plate is fixedly provided at the end of the guide plate away from the drive motor. When the front landing gear needs to be placed on the receiving plate, the floor plate is attached to the ground, and the end of the floor plate away from the guide plate is provided with an inclined surface.

[0023] By adopting the above technical solution, the nose landing gear can be easily pushed onto the ground, and then the ground can easily push the nose landing gear onto the guide plate.

[0024] Optionally, the top of the receiving plate is provided with a limiting groove, and when the front landing gear is placed on the receiving plate, the tires of the front landing gear are inserted into the limiting groove.

[0025] By adopting the above technical solution, the limiting groove can limit the front landing gear, so that the front landing gear is not easy to shift on the bearing plate.

[0026] Optionally, a lifting assembly is provided in the limiting groove. The lifting assembly includes a lifting plate and a lifting cylinder. The lifting plate is slidably connected in the limiting groove and can slide in the vertical direction. The lifting cylinder is fixed to the bottom of the limiting groove, and the push shaft of the lifting cylinder is fixed to the lifting plate. When the front landing gear is placed on the receiving plate, the tires of the front landing gear are inserted into the limiting groove and abut against the lifting plate.

[0027] By adopting the above technical solution, if it is necessary to separate the front landing gear from the bearing plate, the lifting cylinder is activated to push the lifting plate to slide upward in the vertical direction until the top of the lifting plate is flush with the top of the horizontal plate, thereby facilitating the separation of the front landing gear from the bearing plate.

[0028] Optionally, a stabilizing component is provided between the guide plate and the connecting plate.

[0029] By adopting the above technical solution, the stabilizing component can improve the stability of the guide plate in maintaining its tilted state.

[0030] Optionally, the stabilizing component includes: an iron plate and a plurality of electromagnets. The connecting plate has a plurality of receiving holes, and the electromagnets are fixed in the receiving holes. The iron plate is fixed to one end of the guide plate near the drive motor, and when the front landing gear needs to be placed on the receiving plate, the electromagnets are attracted to the iron plate.

[0031] By adopting the above technical solution, when the front landing gear needs to be placed on the receiving plate, the iron plate abuts against the connecting plate, and the electromagnet attracts the iron plate. Thus, during the rolling of the front landing gear on the guide plate, the electromagnet attracts the iron plate, which not only improves the stability of the guide plate in maintaining its tilted state, but also makes it less likely to put excessive pressure on the screw.

[0032] In summary, this application includes at least one of the following beneficial effects:

[0033] 1. Using the adjustment mechanism, the guide plate is moved to one end of the receiving plate, and the guide plate will automatically tilt until the end of the guide plate close to the receiving plate abuts against the receiving plate; then, the guide plate is used to push the nose landing gear onto the receiving plate, so that the nose landing gear does not need to be lifted and carried onto the receiving plate with effort, and it is less likely to cause accidental injury due to poor control of the nose landing gear during the carrying process.

[0034] 2. The limiting groove can limit the front landing gear to prevent it from shifting on the bearing plate.

[0035] 3. If it is necessary to separate the front landing gear from the bearing plate, activate the lifting cylinder to push the lifting plate to slide vertically upward until the top of the lifting plate is flush with the top of the horizontal plate, thus facilitating the separation of the front landing gear from the bearing plate. Attached Figure Description

[0036] Figure 1 This is a schematic perspective view of an aircraft nose landing gear assembly test vehicle according to an embodiment of this application;

[0037] Figure 2 yes Figure 1 A schematic front view;

[0038] Figure 3 It is along Figure 2 A schematic cross-sectional view taken by the cutting line AA in the diagram;

[0039] Figure 4 yes Figure 3 A schematic enlarged view of part B.

[0040] In the diagram: 1. Base plate; 11. Caster wheel; 12. Receiving groove; 13. Slide groove; 14. Placement groove; 15. Fixing rod; 151. Bushing; 2. Receiving plate; 21. Horizontal plate; 22. Inclined plate; 23. Limiting groove; 24. Connecting plate; 241. Receiving hole; 242. Arc surface; 3. Guide plate; 31. Floor plate; 311. Inclined surface; 32. Connecting groove; 4. Pushing assembly; 41. Slider; 42. Lead screw; 4 3. Transmission belt; 44. Drive motor; 5. Tilting assembly; 51. Lifting section; 511. Slide plate; 512. Sleeve; 513. Screw; 514. Connecting block; 52. Drive section; 521. Drive rod; 522. Gear; 523. Rack; 6. Lifting assembly; 61. Lifting plate; 62. Lifting cylinder; 7. Stabilizing assembly; 71. Iron plate; 72. Electromagnet; 8. Side plate; 81. Support rod; 9. Front landing gear. Detailed Implementation

[0041] This application provides a test vehicle for assembling aircraft nose landing gear.

[0042] See Figure 1 A typical aircraft nose landing gear assembly test vehicle may include: a base plate 1 with casters 11 mounted on its bottom, the casters 11 being located at the four corners of the bottom of the base plate 1. A pusher is fixedly provided at the top of the base plate 1 along its length, and a receiving plate 2 for placing the nose landing gear 9 is provided at the top of the base plate 1. In this embodiment, the receiving plate 2 is integrally formed from a horizontal plate 21 and two inclined plates 22, and the two inclined plates 22 are symmetrically arranged about the horizontal plate 21 as the central axis. Since the casters 11 are mounted on the four corners of the bottom of the base plate 1, pushing the pusher can drive the casters 11 to move and rotate, making it easy for the base plate 1 to move along the X-axis, Y-axis and rotate around the Z-axis. The nose landing gear 9 moves along the X-axis and Y-axis and rotates around the Z-axis with the base plate 1. Operators can easily move and turn within the factory by operating the pusher, transporting the nose landing gear 9 from the assembly station to the jig installation position, thus realizing the transportation function.

[0043] In this application embodiment, to achieve the purpose of moving the front landing gear 9 along the Z-axis and rotating the front landing gear 9 around the X-axis and Y-axis, the prior art in the patent with publication number CN103434655A can be used to achieve the purpose of moving the front landing gear 9 along the Z-axis and rotating the front landing gear 9 around the X-axis and Y-axis.

[0044] See Figure 2A side plate 8 is fixedly mounted on the top of the base plate 1, located at one end of the receiving plate 2 along its length. A support rod 81 is rotatably mounted on the side plate 8. The support rod 81 is L-shaped and can be used to support the strut of the front landing gear 9. A block is slidably mounted on the support rod 81. A servo electric cylinder is fixedly mounted on the base plate 1, and the push shaft of the servo electric cylinder is hinged to the block. By pushing the block with the servo electric cylinder, the support rod 81 can be rotated, so that the strut of the front landing gear 9 rotates around the wheel axle.

[0045] See Figure 3 and Figure 4 The top of the base plate 1 has a receiving groove 12, which is located directly below the receiving plate 2. A fixing rod 15 is provided in the receiving groove 12 and is horizontally arranged. The length of the fixing rod 15 is equal to the width of the receiving groove 12. A bushing 151 is fitted on the fixing rod 15 and can rotate on the fixing rod 15. A guide plate 3 is fixedly installed on the bushing 151. Before the front landing gear 9 is placed on the receiving plate 2, the guide plate 3 is located directly below the receiving plate 2.

[0046] An adjustment mechanism is provided in the receiving slot 12. When it is necessary to place the front landing gear 9 on the receiving plate 2, the guide plate 3 is moved to the end of the receiving plate 2 away from the side plate 8 using the adjustment mechanism. The guide plate 3 will automatically tilt and the end of the guide plate 3 close to the receiving plate 2 will abut against the receiving plate 2. Then, the guide plate 3 and the tires of the front landing gear 9 are used to push the front landing gear 9 onto the receiving plate 2. This eliminates the need to lift and transport the front landing gear 9 onto the receiving plate 2, and makes it less likely that the front landing gear 9 will be accidentally injured due to poor control during transport.

[0047] See Figure 3 The top of the horizontal plate 21 has a limiting groove 23, and there is a pair of limiting grooves 23, with each limiting groove 23 corresponding to one of the two tires of the front landing gear 9. After the front landing gear 9 is placed on the receiving plate 2, the bottom of the tires of the front landing gear 9 is inserted into the limiting groove 23. The limiting groove 23 can limit the front landing gear 9 so that the front landing gear 9 is not easy to deviate on the receiving plate 2.

[0048] See Figure 3Specifically, a lifting assembly 6 is provided within the limiting groove 23. The lifting assembly 6 includes a lifting plate 61 and a lifting cylinder 62. The lifting plate 61 is slidably connected within the limiting groove 23 and can slide vertically. When the front landing gear 9 is placed on the receiving plate 2, the bottom of the tires of the front landing gear 9 is inserted into the limiting groove 23 and abuts against the top wall of the lifting plate 61. The lifting cylinder 62 is fixed to the bottom of the limiting groove 23, and the push shaft of the lifting cylinder 62 is fixedly connected to the bottom wall of the lifting plate 61. If it is necessary to separate the front landing gear 9 from the receiving plate 2, the lifting cylinder 62 is activated to push the lifting plate 61 to slide vertically upward until the top of the lifting plate 61 is flush with the top of the horizontal plate 21, thereby facilitating the separation of the front landing gear 9 from the receiving plate 2.

[0049] See Figure 3 and Figure 4 The adjustment mechanism includes: a pushing component 4 and a flipping component 5.

[0050] See Figure 3 and Figure 4 The pushing component 4 includes: a slider 41, a lead screw 42, a transmission belt 43, and a drive motor 44. In this embodiment, except for the drive motor 44, the slider 41, lead screw 42, and transmission belt 43 are all configured as a pair. The receiving groove 12 has a sliding groove 13 on the inner sidewalls of both ends in the width direction and in the length direction of the receiving groove 12. The slider 41 is slidably connected in the sliding groove 13 and can slide in the horizontal direction; the fixing rod 15 is fixedly installed between the two sliders 41.

[0051] See Figure 3 and Figure 4 The lead screw 42 is rotatably mounted in the slide groove 13 and is horizontally positioned. The lead screw 42 passes through the slider 41 and is threadedly connected to the slider 41. The drive motor 44 is mounted at one end of the receiving groove 12 along its length, and the output end of the drive motor 44 is connected to the lead screw 42 by a transmission belt 43 (a single transmission belt 43 includes two pulleys for fixing on the output end of the drive motor 44 and the lead screw 42). When it is necessary to place the front landing gear 9 on the support plate 2, the drive motor 44 is started, and the lead screw 42 is driven to rotate through the transmission belt 43. The rotation of the lead screw 42 can drive the slider 41 to slide in the slide groove 13, thereby driving the guide plate 3 to move towards the end of the support plate 2 away from the side plate 8, until the slider 41 slides to the top of the slide groove 13, that is, the guide plate 3 moves to the end of the support plate 2 away from the side plate 8. During the movement, the flipping component 5 can be used to slowly flip the guide plate 3 to an inclined state until the guide plate 3 moves to the end of the support plate 2 away from the side plate 8. The end of the guide plate 3 close to the support plate 2 abuts against the support plate 2, thereby facilitating the push of the front landing gear 9 onto the support plate 2.

[0052] See Figure 4The flipping component 5 includes a lifting part 51 and a driving part 52.

[0053] See Figure 4 The lifting part 51 includes a sliding plate 511, a sleeve 512, a screw 513, and a connecting block 514. The sliding plate 511 is fixed between two sliders 41. The sleeve 512 is rotatably mounted on the sliding plate 511. In this embodiment, a pair of sleeves 512, screws 513, and connecting blocks 514 are provided to improve the strength of the support for the guide plate 3. A connecting groove 32 is provided on the bottom wall of the guide plate 3. The connecting block 514 is slidably connected to the connecting groove 32 and can slide along the length direction of the connecting groove 32. One end of the screw 513 is threaded into the sleeve 512, and the other end is hinged to the bottom wall of the connecting block 514.

[0054] See Figure 4 The drive unit 52 includes a drive rod 521, a gear 522, and a rack 523. A placement groove 14 is formed at the bottom of the receiving groove 12 along its length, and the rack 523 is fixed to the inner wall of the placement groove 14. One end of the drive rod 521 is rotatably mounted on the slide plate 511 and fixedly connected to the sleeve 512; the other end extends into the placement groove 14 and is coaxially fixed to the gear 522. The gear 522 meshes with the rack 523. During the process of pushing the guide plate 3 towards the end of the receiving plate 2 away from the side plate 8, the gear 522 will rotate due to the meshing of the gear 522 and the rack 523. The rotation of the gear 522 will sequentially drive the drive rod 521 and the sleeve 512 to rotate. Since the screw 513 cannot follow the rotation of the sleeve 512, the rotation of the sleeve 512 will drive the screw 513 to extend outward from the sleeve 512, thereby lifting the end of the guide plate 3 near the drive motor 44, so that the guide plate 3 slowly tilts until the guide plate 3 abuts against the receiving plate 2, thus facilitating the push of the front landing gear 9 onto the receiving plate 2. Moreover, the tilting of the guide plate 3 does not require the guide plate 3 to move to the end of the receiving plate 2 before tilting, but can be slowly tilted during the movement of the guide plate 3, thus achieving synchronization and saving time.

[0055] See Figure 3Furthermore, a connecting plate 24 is fixedly installed on the end wall of the receiving plate 2 away from the side plate 8. The connecting plate 24 is inclined, and the end of the connecting plate 24 away from the receiving plate 2 tilts downward. The tilt angle of the connecting plate 24 is consistent with the tilt angle of the guide plate 3 when it is flipped to abut against the connecting plate 24. The top of the connecting plate 24 is provided with an arc-shaped surface 242, and the end of the arc-shaped surface 242 away from the receiving plate 2 tilts downward. When the front landing gear 9 is pushed onto the receiving plate 2 via the guide plate 3, the arc-shaped surface 242 on the connecting plate 24 can easily push the front landing gear 9 onto the connecting plate 24, and then the connecting plate 24 can easily push the front landing gear 9 onto the receiving plate 2, thus preventing jamming during the pushing of the front landing gear 9.

[0056] See Figure 3 A ground contact plate 31 is fixedly provided on the end wall of the guide plate 3 away from the drive motor 44, and the ground contact plate 31 can be in contact with the ground when the front landing gear 9 needs to be placed on the receiving plate 2. The end of the ground contact plate 31 away from the guide plate 3 is provided with an inclined surface 311, and the inclined surface 311 is inclined downward at the end away from the guide plate 3. The front landing gear 9 can be easily pushed onto the ground contact plate 31 through the inclined surface 311, and then the ground contact plate 31 can easily push the front landing gear 9 onto the guide plate 3.

[0057] See Figure 3 A stabilizing component 7 is provided between the guide plate 3 and the connecting plate 24. The stabilizing component 7 includes an iron plate 71 and multiple electromagnets 72. The bottom wall of the connecting plate 24 has multiple receiving holes 241, and each receiving hole 241 corresponds to one of the multiple electromagnets 72. The electromagnets 72 are fixedly installed in the receiving holes 241. The iron plate 71 is fixed on the end wall of the guide plate 3 near the drive motor 44. When the front landing gear 9 needs to be placed on the receiving plate 2, the iron plate 71 abuts against the connecting plate 24, and the electromagnets 72 attract the iron plate 71. Thus, during the rolling of the front landing gear 9 on the guide plate 3, the electromagnets 72 attract the iron plate 71, which not only improves the stability of the guide plate 3 in maintaining its tilted state, but also prevents excessive pressure on the screw 513.

[0058] In this embodiment, a control cabinet is also provided on the substrate 1 for connection to electronic equipment for easy operation, especially for the adjustment mechanism which can be programmed for operation. Power can be supplied by a storage battery.

[0059] The working principle of the aircraft nose landing gear assembly test vehicle of this application is as follows: During the process of pushing the guide plate 3 towards the end of the receiving plate 2 away from the side plate 8, the gear 522 will rotate due to the meshing of the gear 522 and the rack 523. The rotation of the gear 522 will drive the drive rod 521 and the sleeve 512 to rotate in sequence. Since the screw 513 cannot follow the rotation of the sleeve 512, the rotation of the sleeve 512 will drive the screw 513 to extend outward from the sleeve 512, thereby lifting the end of the guide plate 3 near the drive motor 44, so that the guide plate 3 slowly tilts until the guide plate 3 abuts against the receiving plate 2, thereby facilitating the pushing of the nose landing gear 9 onto the receiving plate 2. Moreover, the tilting of the guide plate 3 does not require the guide plate 3 to move to the end of the receiving plate 2 before tilting, but can be slowly tilted during the movement of the guide plate 3, thereby achieving synchronization and saving time.

[0060] The above are all preferred embodiments of this application, and are not intended to limit the scope of protection of this application. Therefore, all equivalent changes made in accordance with the structure, shape and principle of this application should be covered within the scope of protection of this application.

Claims

1. An aircraft nose landing gear assembly test vehicle characterized by, Include: The base plate (1) is provided with universal wheel (11) on the bottom, the top of the base plate (1) is provided with the receiving plate (2) for placing the front landing gear (9), the top of the base plate (1) is provided with the accommodating groove (12), the accommodating groove (12) is provided with the fixed rod (15), the fixed rod (15) is provided with the shaft sleeve (151), the shaft sleeve (151) is fixedly provided with the guide plate (3), and the guide plate (3) is below the receiving plate (2) before the front landing gear (9) is not placed on the receiving plate (2), the accommodating groove (12) is provided with adjusting mechanism, for adjusting the guide plate (3), so as to facilitate the front landing gear (9) to be placed on the receiving plate (2); The adjusting mechanism comprises: a pushing assembly (4), the pushing assembly (4) comprises: a sliding block (41), a lead screw (42), a transmission belt (43) and a drive motor (44), the inner side wall of the accommodating groove (12) is provided with a sliding groove (13), the sliding block (41) is slidably connected in the sliding groove (13) and slides in the horizontal direction, the fixed rod (15) is fixed on the sliding block (41), the lead screw (42) is rotatably installed in the sliding groove (13), and the lead screw (42) penetrates the sliding block (41) and is threadedly connected with the sliding block (41), the drive motor (44) is installed in the accommodating groove (12), and the output end of the drive motor (44) is driven by the transmission belt (43) and the lead screw (42); The adjusting mechanism further comprises: a turnover assembly (5), the turnover assembly (5) comprises: a jacking part (51), the jacking part (51) comprises: a sliding plate (511), a sleeve (512), a screw rod (513) and a connecting block (514), the sliding plate (511) is fixed with the sliding block (41), the sleeve (512) is rotatably installed on the sliding plate (511), the bottom of the guide plate (3) is provided with a connecting groove (32), the connecting block (514) is slidably connected in the connecting groove (32), one end of the screw rod (513) is threadedly connected in the sleeve (512), and the other end is hingedly connected with the connecting block (514); The turnover assembly (5) further comprises: a driving part (52), the driving part (52) comprises: a driving rod (521), a gear (522) and a rack (523), the groove bottom of the accommodating groove (12) is provided with a placing groove (14), and the rack (523) is installed in the placing groove (14), one end of the driving rod (521) is rotatably installed on the sliding plate (511) and fixed with the sleeve (512), the other end extends into the placing groove (14), and the gear (522) is coaxially provided on the driving rod (521), and the gear (522) is engaged with the rack (523).

2. The aircraft nose landing gear assembly test vehicle of Claim 1, wherein, The end wall of one end of the receiving plate (2) is provided with a connecting plate (24), and the top of the connecting plate (24) is provided with an arc surface (242). When the front landing gear (9) needs to be placed on the receiving plate (2), the guide plate (3) abuts against the connecting plate (24).

3. The aircraft nose landing gear assembly test vehicle of Claim 1, wherein, The end of the guide plate (3) away from the driving motor (44) is fixedly provided with a ground plate (31). When the front landing gear (9) needs to be placed on the receiving plate (2), the ground plate (31) is attached to the ground, and the end of the ground plate (31) away from the guide plate (3) is provided with an inclined surface (311).

4. The aircraft nose landing gear assembly test vehicle of Claim 1, wherein, The top of the receiving plate (2) is provided with a limiting groove (23), and when the front landing gear (9) is placed on the receiving plate (2), the tire of the front landing gear (9) is inserted into the limiting groove (23).

5. An aircraft nose landing gear assembly test vehicle as claimed in claim 4, wherein, The limiting groove (23) is provided with a jacking assembly (6), which comprises a jacking plate (61) and a jacking cylinder (62). The jacking plate (61) is slidably connected in the limiting groove (23) and can slide in the vertical direction. The jacking cylinder (62) is fixed to the groove bottom of the limiting groove (23), and the pushing shaft of the jacking cylinder (62) is fixed with the jacking plate (61). When the front landing gear (9) is placed on the receiving plate (2), the tire of the front landing gear (9) is inserted into the limiting groove (23) and abuts against the jacking plate (61).

6. The aircraft nose landing gear assembly test vehicle of Claim 2, wherein, The guide plate (3) and the connecting plate (24) are provided with a stabilizing assembly (7).

7. An aircraft nose landing gear assembly test vehicle as claimed in claim 6, characterised in that, The stabilizing assembly (7) comprises an iron plate (71) and a plurality of electromagnets (72). The connecting plate (24) is provided with a plurality of accommodating holes (241), and the electromagnets (72) are fixed in the accommodating holes (241). The iron plate (71) is fixed to the end of the guide plate (3) close to the driving motor (44), and when the front landing gear (9) needs to be placed on the receiving plate (2), the electromagnets (72) are attracted to the iron plate (71).

Images