An aircraft landing gear installation vehicle

Abstract

This invention provides an aircraft landing gear installation vehicle, which includes a chassis assembly, a mobile platform, and a landing gear support component. The mobile platform is mounted on the chassis assembly and can rotate or translate relative to the chassis assembly. The landing gear support component is mounted on the mobile platform. The mobile platform includes a load-bearing component and at least three translation components located in the same plane. The translation components are fixed to the chassis assembly and movably connected to the load-bearing component in two mutually perpendicular directions. The multiple translation components can push the load-bearing component to move or rotate in its plane. The landing gear support component includes a landing gear bracket for supporting the landing gear and several lifting components. The lifting components are fixed to the load-bearing component, and the lifting ends of the lifting components are connected to different parts of the landing gear bracket, which can drive the landing gear bracket to rise or fall in the vertical direction or rotate relative to the horizontal axis.

Description

Technical Field

[0001] This invention relates to the field of aircraft manufacturing equipment technology, and in particular to an aircraft landing gear installation vehicle. Background Technology

[0002] Landing gear is an accessory device on the lower part of an aircraft used to support the aircraft during takeoff, landing, or taxiing and for ground movement. It is the only component that supports the entire aircraft, making it an indispensable part; without it, the aircraft cannot move on the ground. After takeoff, the landing gear can be retracted depending on flight performance. Special equipment is required for the disassembly and replacement of aircraft landing gear during maintenance.

[0003] For example, patent CN111348217B provides a landing gear disassembly and assembly device for aircraft. This device uses four cylinders driven simultaneously to create a support block that supports the aircraft body via rubber pads. As the support block moves upward, a first connecting rod causes a V-shaped rod to rotate counter-clockwise. Simultaneously, the counter-clockwise rotation of the V-shaped rod, through a second connecting rod, moves the positioning plates closer to the center of the hydraulic lifting platform. These two positioning plates guide and position the sides of the aircraft landing gear wheels. As the two positioning plates move towards the center, they also move two clamping plates, clamping and positioning the landing gear wheels at both ends. This ensures the landing gear wheels are directly below the installation area, facilitating more precise installation and preventing the landing gear from becoming too heavy and difficult to move, thus guaranteeing smooth installation and disassembly.

[0004] The aforementioned aircraft landing gear disassembly and assembly equipment has the following problems: the entire equipment can only move up and down relative to the landing gear, and it does not have the function of fine-tuning the relative position of the entire equipment and the landing gear. As a result, when fixing the landing gear, the entire equipment and the landing gear need to be carefully aligned. If the entire equipment and the landing gear are not aligned, it may lead to the failure of fixing the landing gear. Summary of the Invention

[0005] In view of this, it is necessary to provide an aircraft landing gear installation vehicle to solve the problem that existing aircraft landing gear installation vehicles cannot fine-tune the relative position relationship with the landing gear.

[0006] This invention provides an aircraft landing gear installation vehicle, comprising:

[0007] The chassis assembly, the mobile platform, and the landing gear support components are provided. The mobile platform is mounted on the chassis assembly and is capable of rotating or translating relative to the chassis assembly. The landing gear support components are mounted on the mobile platform.

[0008] The mobile platform includes a load-bearing component and at least three translation components located in the same plane. The translation components are fixed to the chassis assembly and are movably connected to the load-bearing component in two mutually perpendicular directions. The multiple translation components can push the load-bearing component to move or rotate in its plane.

[0009] The landing gear support component includes a landing gear bracket for supporting the landing gear and several lifting components. The lifting components are fixed on the support component, and the lifting ends of the lifting components are connected to different parts of the landing gear bracket, which can drive the landing gear bracket to move up and down in the vertical direction or rotate relative to the horizontal axis.

[0010] Optionally, at least two of the translation components are connected to the bearing assembly in the same direction and can work synchronously to drive the bearing assembly to translate along the first direction or work asynchronously to drive the bearing assembly to rotate in the plane. The remaining translation components are connected to the bearing assembly and can drive the bearing assembly to translate along a second direction perpendicular to the first direction.

[0011] Optionally, the chassis assembly includes a chassis frame and a caster assembly. The caster assembly is connected to the chassis frame, enabling the chassis frame to move. The moving platform is mounted on the chassis frame.

[0012] Optionally, the load-bearing component includes a base frame and a cover plate, the cover plate being disposed on the base frame, the landing gear support component being fixed on the cover plate, and the translation component being movably connected to the base frame in two mutually perpendicular directions.

[0013] Optionally, the translation component includes a motor, a lead screw, and a lead screw nut assembly. The motor is fixed on the chassis assembly, the lead screw is shaft-connected to the output end of the motor, the lead screw nut assembly is movably embedded in the bottom frame and can move in a direction perpendicular to the lead screw, and the lead screw passes through the bottom frame and is threadedly connected to the lead screw nut assembly.

[0014] Optionally, the bottom frame has a hollowed-out interior forming multiple moving spaces, and a limiting hole communicating with the moving space is provided on the outer surface of the bottom frame. The nut assembly is movably disposed within the moving space, and the moving space restricts the nut assembly to move only in the direction perpendicular to the lead screw. The lead screw passes through the limiting hole, and the limiting hole has space that allows the lead screw to translate in the direction perpendicular to the lead screw.

[0015] Optionally, the wire nut assembly includes a wire nut, a pair of lugs, rollers, and roller shafts. The middle portions of the pair of lugs are respectively hinged to the two sides of the wire nut, and each end of the lugs is respectively hinged to a roller via the roller shaft.

[0016] Optionally, one end of the roller shaft protrudes relative to the roller, and the protruding end of the roller shaft relative to the roller has an arc-shaped surface that contacts the inner wall.

[0017] Optionally, the landing gear support component includes at least three lifting components, two of which are connected to one side of the landing gear bracket, and the other lifting component is connected to the other side of the landing gear bracket. The three lifting components can simultaneously lift the same height or can lift different heights.

[0018] Optionally, the lifting assembly includes a lifting cylinder and a universal joint. The lifting cylinder is fixed on the bearing assembly, and the universal joint is hinged to the output end of the lifting cylinder and the landing gear bracket, respectively. The universal joint enables the lifting cylinder and the landing gear bracket to be universally connected.

[0019] The beneficial effects of this invention are as follows:

[0020] This invention provides an aircraft landing gear installation vehicle, which is equipped with several translation components and lifting components. It can drive the landing gear bracket to translate in the horizontal plane, rotate in the horizontal plane, lift in the vertical direction, and rotate relative to the horizontal axis. This enables the landing gear bracket to be adjusted relative to the landing gear in various directions, and can achieve precise fixing of the landing gear at different angles, thereby improving the efficiency of disassembly and assembly. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0022] Figure 1 This is a schematic diagram of the structure of the aircraft landing gear installation vehicle in this invention;

[0023] Figure 2 for Figure 1 Schematic diagram of the mid-chassis assembly;

[0024] Figure 3 for Figure 2 Enlarged schematic diagram of the central channel steel section;

[0025] Figure 4 for Figure 1 Schematic diagram of the middle traction rod;

[0026] Figure 5 for Figure 1 Schematic diagram of the mid-chassis assembly and mobile platform;

[0027] Figure 6 for Figure 5 A schematic diagram of the China Mobile platform;

[0028] Figure 7 for Figure 6 Schematic diagram of the structure of the central wire mother assembly;

[0029] Figure 8 for Figure 1 Structural diagram of the landing gear support components and the moving platform;

[0030] Figure 9 for Figure 1 A schematic diagram of the structure of the lifting assembly in one embodiment;

[0031] Figure 10 for Figure 1 A schematic diagram of the structure of the lifting assembly in another embodiment;

[0032] Figure 11 for Figure 8 Schematic diagram of the adjustable support component;

[0033] Figure 12 for Figure 11 Enlarged structural diagram of the locking claw plate;

[0034] Wherein: 1-Chassis assembly, 11-Chassis frame, 111-Outer frame, 112-Channel steel, 113-Universal ball joint component, 113a-Ball seat, 113b-Universal ball, 12-Cast wheel assembly, 121-Cast wheel mounting base, 122-Cast wheel, 13-Traction rod, 131-Outer sleeve, 132-Inner rod, 133-Pin, 2-Moving platform, 21-Bearing assembly, 211-Base frame, 211a-Moving space, 211b-Limiting hole, 212-Cover plate, 22-Transfer component, 221-Motor, 222-Lead screw, 223-Lead screw nut assembly, 223 a-Nut, 223b-Ear, 223c-Roller, 223d-Roller Shaft, 3-Landing Gear Support Component, 31-Landing Gear Bracket, 32-Lifting Assembly, 321-Lifting Cylinder, 322-Universal Connector, 322a-Ball Head, 322b-Ball Recess, 322c-Compensating Moving Cover, 33-Adjustable Support Assembly, 331-Support Seat, 331a-Clamping Block, 332-Lifting Mechanism, 332a-Lifting Screw, 332b-Sleeve, 332c-Lifting Nut, 332d-Locking Claw, 332e-Ratchet Tooth, 333-Fixed Bracket. Detailed Implementation

[0035] Preferred embodiments of the present invention will now be described in detail with reference to the accompanying drawings, which form part of this application and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not intended to limit the scope of the present invention.

[0036] like Figure 1 , Figure 2 , Figure 3 , Figure 4 As shown, an embodiment of the present invention provides an aircraft landing gear installation vehicle, which includes a chassis assembly 1, a mobile platform 2, and a landing gear support component 3. The mobile platform 2 is disposed on the chassis assembly 1 and is capable of rotating or translating relative to the chassis assembly 1. The landing gear support component 3 is disposed on the mobile platform 2.

[0037] The mobile platform 2 includes a load-bearing component 21 and a plurality of translation components 22. The plurality of translation components 22 are fixed on the chassis assembly 1 and connected to the load-bearing component 21. The plurality of translation components 22 can push the load-bearing component 21 to move or rotate within its plane.

[0038] The landing gear support component 3 includes a landing gear bracket 31 for supporting the landing gear and a plurality of lifting components 32. The plurality of lifting components 32 are fixed on the bearing component 21. The lifting ends of the plurality of lifting components 32 are connected to different parts of the landing gear bracket 31, and can drive the landing gear bracket 31 to rise or fall in the vertical direction or rotate relative to the horizontal axis.

[0039] In this invention, a plurality of translation components 22 and lifting components 32 are provided, which can drive the landing gear bracket 31 to translate in the horizontal plane, rotate in the horizontal plane, lift in the vertical direction, and rotate relative to the horizontal axis, so that the landing gear bracket 31 can be adjusted relative to the landing gear in various directions, and can achieve precise fixation of the landing gear at different angles, thereby improving the efficiency of disassembly and assembly.

[0040] Specifically, the chassis assembly 1 includes a chassis frame 11 and a caster assembly 12. The caster assembly 12 is connected to the chassis frame 11, enabling the chassis frame 11 to move. The mobile platform 2 is mounted on the chassis frame 11.

[0041] Furthermore, the chassis frame 11 includes an outer frame 111 and several channel steels 112 arranged in a crisscross pattern within the outer frame 111. Several universal ball joint components 113 are fixed on the channel steels 112, and the moving platform 2 abuts against the universal ball joint components 113. The universal ball joint components 113 facilitate the movement of the moving platform 2.

[0042] Furthermore, the omnidirectional ball component 113 includes a ball seat 113a and an omnidirectional ball 113b. The ball seat 113a is fixed to the channel steel 112, and the omnidirectional ball 113b is movably embedded in the top of the ball seat 113a, abutting against the moving platform 2. When the moving platform 2 moves, the omnidirectional ball 113b rolls relative to the moving platform 2, providing rolling support for the moving platform 2.

[0043] Furthermore, the caster assembly 12 includes a caster mounting base 121 and a caster 122. The caster mounting base 121 is L-shaped, having a higher end and a lower end. The lower end of the caster mounting base is fixed to the outer frame 111, and the caster 122 is connected to the higher end of the caster mounting base 121. The purpose of this design is to allow the chassis frame 11 to sink relative to the caster assembly 12, getting closer to the ground; thus, sufficient installation space is provided above during aircraft landing gear installation.

[0044] In addition, the chassis assembly 1 also includes a tow bar 13, one end of which is hinged to the chassis frame 11, and the other end of which forms a tow end that cooperates with other equipment.

[0045] The traction rod 13 includes an outer sleeve 131, an inner rod 132, and a pin 133. One end of the outer sleeve 131 is hinged to the chassis frame 11. One end of the inner rod 132 extends into the outer sleeve 131. The outer sleeve 131 has a pin fixing hole, and the inner rod 132 has several locking holes corresponding to the pin fixing hole. The pin 133 can pass through both the pin fixing hole and any of the locking holes simultaneously. The other end of the inner rod 132 forms the traction end. This design allows for multi-level adjustment of the length of the traction rod 13 to meet various usage scenarios.

[0046] Specifically, the mobile platform 2 includes a support component 21 and a plurality of translation components 22. The plurality of translation components 22 are fixed on the chassis assembly 1 and connected to the support component 21. The plurality of translation components 22 can push the support component 21 to move or rotate within its plane.

[0047] In this embodiment, one part of the translation component 22 and another part of the translation component 22 are connected to the bearing component 21 in two mutually perpendicular directions, and can respectively push the bearing component 21 to move in two mutually perpendicular directions.

[0048] Furthermore, the supporting component 21 includes a base frame 211 and a cover plate 212. The cover plate 212 is placed on the base frame 211, and the landing gear support component 3 is fixed on the cover plate 212. The base frame 211 is connected to the translation component 22. The interior of the base frame 211 is hollowed out to form multiple moving spaces 211a, and the outer surface of the base frame 211 has limiting holes 211b communicating with the moving spaces 211a.

[0049] The translation component 22 includes a motor 221, a lead screw 222, and a lead screw nut assembly 223. The motor 221 is fixed to the chassis assembly 1. The lead screw 222 is shaft-connected to the output end of the motor 221. The lead screw nut assembly 223 is embedded in the moving space 211a, which restricts the lead screw nut assembly 223 to move only in the direction perpendicular to the lead screw 222. The lead screw 222 passes through the limiting hole 211b and is threadedly connected to the lead screw nut assembly 223. The limiting hole 211b provides space for the lead screw 222 to translate in the direction perpendicular to the lead screw 222. The motor 221 drives the lead screw 222 to rotate, thereby pushing the bearing component 21 to move along the lead screw 222. Because the limiting hole 211b provides space for the lead screw 222 to translate in the direction perpendicular to the lead screw 222, the lead screw 222 in the other direction does not restrict the movement of the bearing component 21.

[0050] Furthermore, the nut assembly 223 includes a nut 223a, a pair of lugs 223b, rollers 223c, and roller shafts 223d. The middle portions of the pair of lugs 223b are respectively hinged to the two sides of the nut 223a, and the two ends of each lug 223b are respectively hinged to a roller 223c via the roller shafts 223d. When the nut assembly 223 is disposed within the moving space 211a, the rollers 223c can roll against the inner wall of the moving space 211a, facilitating the movement of the nut assembly 223 within the moving space 211a.

[0051] Additionally, one end of the roller shaft 223d protrudes relative to the roller 223c, and the protruding end of the roller shaft 223d relative to the roller 223c has an arc-shaped surface that contacts the inner wall of the 211a. The arc-shaped surface can reduce the friction between the nut assembly 223 and the inner wall of the moving space 211a.

[0052] In this embodiment, three translation components 22 are included. Two of the translation components 22 are arranged in the same direction and connected to the support assembly 21. The two translation components 22 can drive the support assembly 21 to move along a first direction when they work simultaneously. When only one translation component 22 is used, since the nut 223a is hinged to the lug 223b, the nut 223a has a partial rotation space within the movement space 211a, which will drive the support assembly 21 to rotate in the plane, thus achieving the rotation effect of the support assembly 21. The other translation component 22 is connected to the support assembly 21 and can drive the support assembly 21 to move along a second direction perpendicular to the first direction. Thus, by setting three translation components 22, the translation and rotation of the support assembly 21 in the plane are realized.

[0053] Specifically, the landing gear support component 3 includes a landing gear bracket 31 for supporting the landing gear and a plurality of lifting components 32. The plurality of lifting components 32 are fixed on the bearing component 21, and the lifting ends of the plurality of lifting components 32 are connected to different parts of the landing gear bracket 31, which can drive the landing gear bracket 31 to rise or fall in the vertical direction or rotate relative to the horizontal axis.

[0054] Furthermore, the landing gear bracket 31 is made of Q235 steel and is U-shaped, having a U-shaped bearing surface for receiving the wheel. The two sides of the landing gear bracket 31 are connected to the lifting assembly 32.

[0055] Furthermore, the landing gear support component 3 includes at least three lifting assemblies 32. Two of the lifting assemblies 32 are connected to one side of the landing gear bracket 31, and the other lifting assembly 32 is connected to the other side of the landing gear bracket 31. The three lifting assemblies 32 cooperate to drive the landing gear bracket 31 to move up and down in the vertical direction or rotate relative to the horizontal axis: when the three lifting assemblies 32 move up and down to the same height simultaneously, the landing gear bracket 31 is driven to move up and down in the vertical direction; when the three lifting assemblies 32 move up and down to different heights, the landing gear bracket 31 is driven to rotate relative to the horizontal axis.

[0056] In this embodiment, the lifting height of each lifting component 32 is 300mm. When each lifting component 32 lifts to a different height, the landing gear bracket 31 can rotate in different directions with a rotation angle of ±2°.

[0057] Furthermore, the lifting assembly 32 includes a lifting cylinder 321 and a universal joint 322. The lifting cylinder 321 is fixed on the bearing assembly 21, and the universal joint 322 is hinged to the output end of the lifting cylinder 321 and the landing gear bracket 31, respectively. The universal joint 322 realizes the universal connection between the lifting cylinder 321 and the landing gear bracket 31.

[0058] In some feasible embodiments, the universal joint 322 includes a ball head 322a and a ball socket 322b. The ball socket 322b is fixed to the landing gear bracket 31. The bottom of the ball socket 322b has a spherical groove for accommodating the ball head 322a. The ball head 322a is spherical and rotatably embedded in the ball socket 322b and fixedly connected to the movable end of the lifting cylinder 321. This universal joint structure allows the ball head 322a to deflect concentrically within the ball socket 322b.

[0059] In other embodiments, the universal joint 322 includes a ball head 322a, a ball socket 322b, and a compensating movable cover 322c. The compensating movable cover 322c is fixed to the landing gear bracket 31. The bottom of the compensating movable cover 322c has a movable groove. The top of the ball socket 322b is movably embedded in the movable groove, and the diameter of the portion of the ball socket 322b located in the movable groove is larger than the opening diameter of the movable groove. The bottom of the ball socket 322b has a spherical groove for accommodating the ball head 322a. The ball head 322a is spherical and is rotatably embedded in the ball socket 322b and fixedly connected to the movable end of the lifting electric cylinder 321. When the ball joint 322b deflects, the landing gear bracket 31 can translate relative to the ball joint 322b via the compensating movable cover 322c, to compensate for the change in nodal distance caused by the change in angle during the rotation of the landing gear bracket 31. This improves the accuracy of attitude adjustment.

[0060] In addition, in order to provide stable support for the landing gear, the landing gear support component 3 also includes an adjustable support assembly 33. The adjustable support assembly 33 is fixed on the landing gear bracket 31. The adjustable support assembly 33 has a support surface for supporting the landing gear. In use, the adjustable support assembly 33 supports the landing gear arm portion, and the landing gear bracket 31 supports the wheel portion on the landing gear, thereby achieving stable support for the entire landing gear.

[0061] Furthermore, the adjustable support assembly 33 includes a support base 331, a lifting mechanism 332, and a fixed bracket 333. The fixed bracket 333 is fixed to the landing gear bracket 31. The lifting mechanism 332 is fixed to the fixed bracket 333 and the landing gear bracket 31. The lifting mechanism 332 has a lifting section that can be raised and lowered and can stably stop at any position within its lifting stroke. The support base 331 is hinged to the lifting section and has a support surface that supports the landing gear. In use, when the lifting section of the lifting mechanism 332 is raised and lowered to a suitable position, the support base 331 contacts the support arm portion of the landing gear, achieving stable support for the landing gear.

[0062] Furthermore, the central recess of the support base 331 accommodates the area of ​​the landing gear arm portion. A pair of clamping blocks 331a that can move relative to or away from each other are provided at both ends of the support base 331. When the landing gear arm portion is placed on the support base 331, the clamping blocks 331a move relative to each other and contact the two sides of the landing gear arm portion to clamp the landing gear arm portion.

[0063] To prevent damage to the surface of the landing gear arm when clamping it, the clamping block 331a is fitted with a rubber pad, which can act as a buffer to prevent damage to the landing gear arm.

[0064] Furthermore, the lifting mechanism 332 includes a lifting screw 332a, a sleeve 332b, a lifting nut 332c, and a locking claw 332d. The sleeve 332b is fixed to the support base 331 and the landing gear bracket 31. One end of the lifting screw 332a extends into the sleeve 332b. The lifting nut 332c is rotatably disposed on the top of the sleeve 332b and threadedly connected to the lifting screw 332a. The outer circumferential surface of the lifting nut 332c extends radially to form a plurality of ratchet teeth 332e. The locking claw 332d is rotatably connected to the sleeve 332b and partially cuts into the ratchet teeth 332e. The locking claw 332d only allows the lifting nut 332c to rotate in one direction.

[0065] In this embodiment, the locking claw 332d has an inclined surface and a vertical surface. When the lifting nut 332c rotates in the direction permitted by the locking claw 332d, the contact surface between the locking claw 332d and the lifting nut 332c is the inclined surface. The lifting nut 332c can push the locking claw 332d to rotate relative to the sleeve 332b, thereby disengaging from the lifting nut 332c. This process is repeated to achieve the rotation of the lifting nut 332c. When the lifting nut 332c rotates in a direction away from the direction permitted by the locking claw 332d, the contact surface between the locking claw 332d and the lifting nut 332c is the vertical surface. The vertical surface abuts tightly against the lifting nut 332c to achieve locking and prevent the lifting nut 332c from rotating in a direction away from the direction permitted by the locking claw 332d.

[0066] In this embodiment, the locking claw 332d only allows the lifting nut 332c to rotate in the direction of raising the lifting screw 332a, thus raising the lifting screw 332a. When it is necessary to lower the lifting screw 332a, the locking claw 332d needs to be manually raised. This design is intended to prevent accidental lowering of the lifting screw 332a during landing gear installation, thus ensuring personnel safety.

[0067] The beneficial effects of the present invention are:

[0068] This invention provides an aircraft landing gear installation vehicle, which is equipped with several translation components and lifting components. It can drive the landing gear bracket to translate in the horizontal plane, rotate in the horizontal plane, lift in the vertical direction, and rotate relative to the horizontal axis. This enables the landing gear bracket to be adjusted relative to the landing gear in various directions, and can achieve precise fixing of the landing gear at different angles, thereby improving the efficiency of disassembly and assembly.

[0069] The above are merely preferred embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention.

Claims

1. An aircraft landing gear installation vehicle, characterized in that, include: The chassis assembly, the mobile platform, and the landing gear support components are provided. The mobile platform is mounted on the chassis assembly and is capable of rotating or translating relative to the chassis assembly. The landing gear support components are mounted on the mobile platform. The mobile platform includes a load-bearing component and at least three translational components located in the same plane. The translational components are fixed to the chassis assembly and movably connected to the load-bearing component in two mutually perpendicular directions. The multiple translational components can push the load-bearing component to move or rotate in its plane. The load-bearing component includes a base frame and a cover plate. The cover plate is placed on the base frame. The landing gear support component is fixed to the cover plate. The translational components are movably connected to the base frame in two mutually perpendicular directions. The translational component includes a motor, a lead screw, and a lead screw nut assembly. The motor is fixed to the chassis assembly. The lead screw is shaft-connected to the output end of the motor. The lead screw nut assembly is movably embedded in the base frame and can move in a direction perpendicular to the lead screw. The lead screw passes through the base frame and is threadedly connected to the lead screw nut assembly. The lead screw nut assembly includes a lead screw nut, a pair of lugs, rollers, and roller shafts. The middle parts of the pair of lugs are respectively hinged to the two sides of the lead screw nut. The two ends of the lugs are respectively hinged to a roller through the roller shaft. The landing gear support component includes a landing gear bracket for supporting the landing gear and several lifting components. The lifting components are fixed on the support component, and the lifting ends of the lifting components are connected to different parts of the landing gear bracket, which can drive the landing gear bracket to move up and down in the vertical direction or rotate relative to the horizontal axis.

2. The aircraft landing gear installation vehicle as described in claim 1, characterized in that, At least two of the translation components are connected to the bearing assembly in the same direction and can work synchronously to drive the bearing assembly to translate along the first direction or work asynchronously to drive the bearing assembly to rotate in the plane. The remaining translation components are connected to the bearing assembly and can drive the bearing assembly to translate along a second direction perpendicular to the first direction.

3. The aircraft landing gear installation vehicle as described in claim 1, characterized in that, The chassis assembly includes a chassis frame and a caster assembly. The caster assembly is connected to the chassis frame, enabling the chassis frame to move. The moving platform is mounted on the chassis frame.

4. The aircraft landing gear installation vehicle as described in claim 2, characterized in that, The bottom frame has a hollowed-out interior forming multiple moving spaces. A limiting hole communicating with the moving space is provided on the outer surface of the bottom frame. The nut assembly is movably disposed within the moving space. The moving space restricts the nut assembly to move only in the direction perpendicular to the lead screw. The lead screw passes through the limiting hole, which has space to allow the lead screw to translate in the direction perpendicular to the lead screw.

5. The aircraft landing gear installation vehicle as described in claim 4, characterized in that, One end of the roller shaft protrudes relative to the roller, and the protruding end of the roller shaft relative to the roller has an arc-shaped surface that contacts the inner wall of the moving space.

6. The aircraft landing gear installation vehicle as described in claim 1, characterized in that, The landing gear support component includes at least three lifting components, two of which are connected to one side of the landing gear bracket, and the other lifting component is connected to the other side of the landing gear bracket. The three lifting components can lift the same height simultaneously or can lift different heights.

7. The aircraft landing gear installation vehicle as described in claim 6, characterized in that, The lifting assembly includes a lifting cylinder and a universal joint. The lifting cylinder is fixed on the bearing assembly, and the universal joint is hinged to the output end of the lifting cylinder and the landing gear bracket, respectively. The universal joint enables the lifting cylinder and the landing gear bracket to be universally connected.

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