Steerable aircraft undercarriage folding and unfolding structure

Abstract

The utility model provides a steerable aircraft undercarriage folding and unfolding structure, which relates to the technical field of aircraft undercarriages, and comprises a steering undercarriage assembly, the steering undercarriage assembly comprises a folding and unfolding rack, a hydraulic push rod, a connecting arm and a steering wheel, the hydraulic push rod is rotatably connected in the folding and unfolding rack, the steering wheel is rotatably connected on the connecting arm, and the connecting arm is connected with the hydraulic push rod; in the mounting assembly, a mounting plate is matched with four rotatable buffering mounting pieces which are distributed in a rectangular shape, vibration generated during operation of the aircraft can be effectively buffered, loss of parts is reduced, the service life of the aircraft is prolonged, the weight of the mounting plate is reduced through load reducing holes, and the structural strength of the mounting plate is ensured through reinforcing rods; and in the deformation assembly, arc-shaped elastic steel and auxiliary elastic steel cooperate with each other, flexible deformation and energy absorption can be achieved when the aircraft is subjected to external force or steers, and the landing stability and impact resistance of the aircraft are enhanced.

Description

TECHNICAL FIELD

[0001] The utility model relates to an aircraft landing gear technical field especially relates to a kind of steerable aircraft landing gear retraction structure. BACKGROUND

[0002] With the continuous development of aircraft technology, the performance requirements of aircraft landing gear are also increasingly high;

[0003] Traditional aircraft landing gear mostly only has simple retraction function, and steering flexibility is poor when aircraft ground taxi, and it needs large turning radius, which is inconvenient when used in some space-limited airports or landing sites;

[0004] In addition, the existing landing gear retraction structure also has certain improvement space in reliability, occupied space and weight;

[0005] Therefore, the utility model provides a kind of steerable aircraft landing gear retraction structure. INVENTION CONTENTS

[0006] The utility model aims at solving the shortcomings in the prior art, and provides a kind of steerable aircraft landing gear retraction structure.

[0007] In order to achieve the above-mentioned purpose, the utility model adopts the following technical scheme: a kind of steerable aircraft landing gear retraction structure, comprising:

[0008] Steering landing gear assembly, steering landing gear assembly is by retraction frame, hydraulic push rod, connecting arm and steering wheel, the hydraulic push rod is rotationally connected in the inside of retraction frame, the steering wheel is rotationally connected on connecting arm, the top of connecting arm is connected with the bottom of hydraulic push rod;

[0009] Mounting assembly, mounting assembly is by the mounting plate being arranged between two retraction frames and four buffer mounting components, four buffer mounting components are rotationally connected on mounting plate respectively, and four buffer mounting components are distributed in rectangle, mounting plate is equipped with the negative hole, the reinforcing rod is arranged in mounting plate and penetrates the negative hole, the limit stand is arranged on mounting plate, and the side of limit stand close to negative hole is provided with limit clamping seat;

[0010] Deformation assembly, deformation assembly is by the arc spring steel being arranged between two limit clamping seats and auxiliary spring steel, and auxiliary spring steel is arranged between arc spring steel and mounting plate.

[0011] Further, the side of limit stand away from limit clamping seat is provided with buffer spring, and one end of buffer spring away from limit stand is connected with retraction frame.

[0012] The beneficial effect of adopting the further scheme is that the limiting vertical plate is provided with a buffer spring away from the limiting clamping base, one end of the buffer spring is connected with the folding frame, the effect is remarkable, the buffer spring can effectively absorb the impact force generated during the operation of the equipment, reduce the wear and tear of parts, prolong the service life of the equipment, and also reduce the displacement deviation caused by vibration, improve the operation stability of the equipment, and ensure efficient and accurate work.

[0013] Further, the load reduction holes are provided in plurality, and the spacing between adjacent two load reduction holes is equal.

[0014] The beneficial effect of adopting the further scheme is that the plurality of load reduction holes are uniformly distributed, and the adjacent spacing is equal, which brings many benefits.

[0015] Further, the folding frame and the hydraulic push rod are rotationally connected with a bogie, and the bottom of the bogie and the top of the hydraulic push rod are mutually clamped.

[0016] The beneficial effect of adopting the further scheme is that the folding frame and the hydraulic push rod are rotationally connected through the bogie, and the bottom is also mutually clamped, so that the bogie can flexibly steer the folding frame to adapt to complex working conditions, and the clamping design enhances the connection stability to ensure operation safety.

[0017] Further, the folding frame is rotationally connected with a gas pump on one side, and the other end of the gas pump is connected with the hydraulic push rod.

[0018] The beneficial effect of adopting the further scheme is that the folding frame is rotationally connected with the gas pump on one side, and the other end of the gas pump is connected with the hydraulic push rod, which has obvious advantages, and the rotational connection enables the gas pump to flexibly adjust the position of the folding frame, so that the folding operation of the folding frame is more stable and efficient, and the overall operation efficiency is greatly improved.

[0019] Further, the end of the gas pump connected with the folding frame is provided with a folding frame, and the other end of the folding frame is rotationally connected with the bottom of the hydraulic push rod.

[0020] The beneficial effect of adopting the further scheme is that the end of the gas pump connected with the folding frame is provided with a folding frame, and the other end of the folding frame is rotationally connected with the bottom of the hydraulic push rod, so that the folding frame can flexibly adjust the distance and angle between the gas pump and the hydraulic push rod, adapt to different working conditions, effectively relieve the stress between the parts during the operation of the equipment, reduce the wear and tear, ensure stable gas supply of the gas pump, assist the stable operation of the hydraulic push rod, and improve the overall reliability of the equipment.

[0021] Compared with the prior art, the advantages and positive effects of the utility model are that:

[0022] In this invention, the mounting assembly includes a mounting plate with four rectangularly distributed and rotatable buffer mounting parts, which can effectively buffer vibrations during aircraft operation, reduce component wear, and extend the service life of the aircraft. The load-reducing holes reduce the weight of the mounting plate, while the reinforcing rods ensure its structural strength. The limiting upright plate and limiting bracket can accurately position the aircraft. In the deformation assembly, the arc-shaped elastic steel and the auxiliary elastic steel work together to flexibly deform when the aircraft is subjected to external forces or turns, absorb energy, and enhance the stability and impact resistance of the aircraft during landing. Attached Figure Description

[0023] Figure 1 This is a front view of a steerable aircraft landing gear retraction structure according to the present invention.

[0024] Figure 2 This is an exploded view of a steerable aircraft landing gear retraction structure according to the present invention.

[0025] Figure 3 This is an exploded view of the steerable landing gear assembly in the steerable aircraft landing gear retraction structure of this utility model.

[0026] Figure 4 This is an exploded view of the mounting components in a steerable aircraft landing gear retraction structure according to the present invention.

[0027] Figure Labels

[0028] 1. Bogie landing gear assembly; 11. Retraction and extension frame; 12. Hydraulic push rod; 13. Air pump; 131. Folding frame; 14. Connecting arm; 15. Steering wheel; 16. Bogie;

[0029] 2. Mounting components; 21. Mounting plate; 22. Buffer mounting component; 23. Limiting upright plate; 231. Limiting bracket; 24. Buffer spring; 25. Load-reducing hole; 251. Reinforcing rod;

[0030] 3. Deformation component; 31. Arc-shaped elastic steel; 32. Auxiliary elastic steel. Detailed Implementation

[0031] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0032] like Figures 1-4 As shown, this utility model provides a technical solution: a steerable aircraft landing gear retraction structure, comprising:

[0033] Turning to the landing gear assembly 1, the landing gear assembly 1 is composed of a retractable frame 11, a hydraulic push rod 12, a connecting arm 14 and a steering wheel 15, the hydraulic push rod 12 is rotatably connected inside the retractable frame 11, the steering wheel 15 is rotatably connected on the connecting arm 14, the top of the connecting arm 14 is connected with the bottom of the hydraulic push rod 12;

[0034] The mounting assembly 2 is composed of a mounting plate 21 arranged between the two retractable frames 11 and four buffer mounting members 22, the four buffer mounting members 22 are rotatably connected on the mounting plate 21, and the four buffer mounting members 22 are distributed in a rectangular shape, the mounting plate 21 is provided with a weight reduction hole 25, the mounting plate 21 is provided with a reinforcing rod 251 penetrating through the weight reduction hole 25, the mounting plate 21 is provided with a limiting stand 23, and the side of the limiting stand 23 close to the weight reduction hole 25 is provided with a limiting clamp 231;

[0035] The deformation assembly 3 is composed of an arc-shaped elastic steel 31 arranged between the two limiting clamps 231 and an auxiliary elastic steel 32, and the auxiliary elastic steel 32 is arranged between the arc-shaped elastic steel 31 and the mounting plate 21. In the mounting assembly 2, the mounting plate 21 is matched with the four buffer mounting members 22 which are rotatable and distributed in a rectangular shape, so that the vibration of the aircraft during operation can be effectively buffered, the part wear is reduced, the service life of the aircraft is prolonged, the weight reduction hole 25 reduces the weight of the mounting plate 21, the reinforcing rod 251 ensures the structural strength, the limiting stand 23 and the limiting clamp 231 can be accurately positioned, and in the deformation assembly 3, the arc-shaped elastic steel 31 and the auxiliary elastic steel 32 cooperate to flexibly deform, absorb energy and enhance the stability and impact resistance of the aircraft during landing when the aircraft is subjected to external force or steering.

[0036] The side of the limiting stand 23 away from the limiting clamp 231 is provided with a buffer spring 24, and one end of the buffer spring 24 away from the limiting stand 23 is connected with the retractable frame 11. The limiting stand 23 is provided with the buffer spring 24 on the side away from the limiting clamp 231, and one end of the buffer spring 24 is connected with the retractable frame 11. The effect is remarkable. The buffer spring 24 can effectively absorb the impact force generated during equipment operation, reduce the wear of parts, prolong the service life of the equipment, reduce the displacement deviation caused by vibration, improve the stability of equipment operation, and ensure efficient and accurate work.

[0037] The weight reduction hole 25 is provided with a plurality of weight reduction holes 25, and the distance between the adjacent two weight reduction holes 25 is equal. The plurality of weight reduction holes 25 are evenly distributed, and the adjacent distance is equal, which brings many benefits. On the one hand, it can effectively reduce the overall weight of the equipment. On the other hand, the uniform layout makes the equipment force more balanced, avoids local stress concentration, enhances the structural stability of the equipment, and improves the durability while ensuring the performance of the equipment.

[0038] The rotary connection between the storage and release frame 11 and the hydraulic push rod 12 is provided with a steering frame 16, the bottom of the steering frame 16 is clamped with the top of the hydraulic push rod 12, the storage and release frame 11 and the hydraulic push rod 12 are rotatably connected through the steering frame 16, and the bottom is also clamped with each other, the steering frame 16 enables the storage and release frame 11 to be flexibly steered, adapts to complex working conditions, the clamping design enhances the connection stability, and ensures the operation safety, when the hydraulic push rod 12 is retracted, the steering frame 16 assists the storage and release frame 11 to accurately adjust the angle and position.

[0039] The storage and release frame 11 is rotatably connected with a gas pump 13 on one side, the other end of the gas pump 13 is connected with the hydraulic push rod 12, the storage and release frame 11 is rotatably connected with the gas pump 13 on one side, and the other end of the gas pump 13 is connected with the hydraulic push rod 12, which has obvious advantages, the rotary connection enables the gas pump 13 to be flexibly adjusted in position with the storage and release frame 11, so that the storage and release operation of the storage and release frame 11 is more stable and efficient, and the overall operation efficiency is greatly improved.

[0040] The end, connected with the storage and release frame 11, of the gas pump 13 is provided with a folding frame 131, the other end of the folding frame 131 is rotatably connected with the bottom of the hydraulic push rod 12, the end, connected with the storage and release frame 11, of the gas pump 13 is provided with the folding frame 131, and the other end of the folding frame 131 is rotatably connected with the bottom of the hydraulic push rod 12, the folding frame 131 can flexibly adjust the distance and angle between the gas pump 13 and the hydraulic push rod 12, adapt to different working conditions, effectively relieve the stress between components during equipment operation, reduce wear and tear, ensure stable gas supply of the gas pump 13, assist the hydraulic push rod 12 to stably run, and improve the overall reliability of the equipment.

[0041] The above is only a preferred embodiment of the present application, and is not intended to limit the present application in other forms, and any skilled person in the art can modify or change the above disclosed technical content into equivalent embodiments applied to other fields, but any simple modification, equivalent change and modification made on the basis of the technical essence of the present application to the above embodiments still belongs to the protection scope of the technical scheme of the present application.

Claims

1. A steerable aircraft landing gear retraction structure, characterised in that, Include: The steering landing gear assembly (1) is composed of a stowable rack (11), a hydraulic push rod (12), a connecting arm (14) and a steering wheel (15), the hydraulic push rod (12) is rotatably connected inside the stowable rack (11), the steering wheel (15) is rotatably connected on the connecting arm (14), the top of the connecting arm (14) is connected with the bottom of the hydraulic push rod (12); The mounting assembly (2) is composed of a mounting plate (21) arranged between the two stowable racks (11) and four buffer mounting pieces (22), the four buffer mounting pieces (22) are rotatably connected on the mounting plate (21), and the four buffer mounting pieces (22) are distributed in a rectangular shape, the mounting plate (21) is provided with a negative hole (25), the mounting plate (21) is provided with a reinforcing rod (251) penetrating through the negative hole (25), the mounting plate (21) is provided with a limiting stand plate (23), and the side of the limiting stand plate (23) close to the negative hole (25) is provided with a limiting clamp (231); The deformation assembly (3) is composed of an arc-shaped elastic steel (31) arranged between the two limiting clamps (231) and an auxiliary elastic steel (32), and the auxiliary elastic steel (32) is arranged between the arc-shaped elastic steel (31) and the mounting plate (21).

2. A steerable aircraft landing gear retraction structure according to claim 1, characterised in that: The side of the limiting stand plate (23) away from the limiting clamp (231) is provided with a buffer spring (24), and the end of the buffer spring (24) away from the limiting stand plate (23) is connected with the stowable rack (11).

3. A steerable aircraft landing gear retraction structure according to claim 1, characterised in that: The negative hole (25) is provided with a plurality of negative holes (25), and the distance between the two adjacent negative holes (25) is equal.

4. A steerable aircraft landing gear retraction structure according to claim 1, characterised in that: The stowable rack (11) and the hydraulic push rod (12) are rotatably connected with a steering truck (16), and the bottom of the steering truck (16) and the top of the hydraulic push rod (12) are connected with each other.

5. A steerable aircraft landing gear retraction structure as claimed in claim 1, characterised in that: The side of the stowable rack (11) is rotatably connected with an air pump (13), and the other end of the air pump (13) is connected with the hydraulic push rod (12).

6. A steerable aircraft landing gear retraction structure according to claim 5, characterised in that: The end of the air pump (13) connected with the stowable rack (11) is provided with a folding rack (131), and the other end of the folding rack (131) is rotatably connected with the bottom of the hydraulic push rod (12).

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