Search

CN-224211253-U - Damping mechanism for main landing gear of light aircraft

CN224211253UCN 224211253 UCN224211253 UCN 224211253UCN-224211253-U

Abstract

The utility model relates to the technical field of aircraft landing gears, in particular to a damping mechanism for a main landing gear of a light aircraft, which comprises a landing gear, wheels, a connecting rod, vertical dampers and the like, wherein the landing gear consists of two support frames which are bilaterally symmetrical, the left support frame and the right support are transversely connected in a sliding manner through a middle sliding rail, the vertical dampers are symmetrically arranged in the rear side of the landing gear, and the vertical dampers consist of a fixed end, a movable end and springs. After the aircraft wheel contacts with the ground, pressure can be applied to the vertical shock absorber through the connecting rod, the spring of the vertical shock absorber deforms, and meanwhile, the connecting rod rotates, so that the movement of the oblique shock absorber is driven to slide downwards through the kidney slot, the spring of the oblique shock absorber deforms, and therefore, the vertical force and the oblique force generated when the aircraft slides can be effectively decomposed and absorbed through the cooperation of the oblique shock absorber of the vertical shock absorber, the shock absorption effect is optimized, the stability of the undercarriage is improved, and the stable attitude of the aircraft on the ground is ensured.

Inventors

  • PENG JINYE
  • XUE GUOHANG
  • GONG FUJIN

Assignees

  • 珠海市海卫科技有限公司

Dates

Publication Date
20260508
Application Date
20250515

Claims (6)

  1. 1. A damping mechanism for a main landing gear of a light aircraft is characterized by comprising a landing gear (1), a wheel (2), a connecting rod (201), a vertical shock absorber (3), an oblique shock absorber (4), a waist-shaped groove (5), an adjusting mechanism and a rotating mechanism, wherein the landing gear (1) is composed of two support frames which are bilaterally symmetrical, the left support frame and the right support realize transverse sliding connection through a middle sliding rail, the vertical shock absorber (3) is symmetrically arranged inside the rear side of the landing gear (1), the vertical shock absorber (3) is composed of a fixed end, a movable end and a spring, the movable end is in sliding connection with the fixed end and is provided with damping, the fixed end of the vertical shock absorber (3) is provided with a rotating mechanism, a spring is arranged between the rotating mechanism and the movable end, the rotating mechanism is used for adjusting the damping force of the vertical shock absorber (3), the fixed end top end of the vertical shock absorber (3) is fixedly connected to the landing gear (1), the bottom of the connecting rod (201) is provided with the wheel (2), the front side of the landing gear (1) is internally and symmetrically provided with the oblique shock absorber (4), the fixed end (4) is also provided with the spring and the movable end which is connected with the fixed end and the movable end, the damping end is arranged between the fixed end and the movable end, the damping end is fixedly connected with the damping end, the waist-shaped groove (5) has been seted up at the top of connecting rod (201), and the expansion end of slant bumper shock absorber (4) passes undercarriage (1) and waist-shaped groove (5) sliding fit on connecting rod (201), is equipped with adjustment mechanism on undercarriage (1), and adjustment mechanism is used for adjusting the width of undercarriage (1).
  2. 2. The damping mechanism for the main landing gear of the light aircraft according to claim 1, wherein the adjusting mechanism comprises a rotating ring (6) and a screw (7), the screw (7) is arranged in the middle of the landing gear (1), the left support frame is rotationally connected with the screw (7), the right support frame is connected with a thread (8) of the screw (7), and the rotating ring (6) is fixedly connected to the left side of the screw (7).
  3. 3. A damping mechanism for a main landing gear of a light aircraft according to claim 2, characterized in that the rotation mechanism comprises a screw thread (8) and a screw cap (9), the screw thread (8) being provided on the fixed end of the vertical shock absorber (3), the screw cap (9) being provided on the fixed end of the vertical shock absorber (3) by means of the screw thread (8).
  4. 4. A shock absorbing mechanism for a light aircraft main landing gear according to claim 3, The novel nut is characterized by further comprising a handle (10), and the handle (10) is arranged on the nut (9).
  5. 5. A shock absorbing mechanism for a light aircraft main landing gear according to claim 4, The landing gear also comprises gaskets (11), and two gaskets (11) are symmetrically and fixedly connected to the left side and the right side of the top of the landing gear (1).
  6. 6. A shock absorbing mechanism for a light aircraft main landing gear according to claim 5, The machine wheel (2) is fixedly connected with the resistance blocks (12) in a circular uniform distribution mode.

Description

Damping mechanism for main landing gear of light aircraft Technical Field The utility model relates to the technical field of aircraft landing gears, in particular to a damping mechanism for a main landing gear of a light aircraft. Background The landing gear is a key system for the aircraft to operate on the ground, and is used for supporting the weight of the aircraft, absorbing landing impact, assisting in sliding and steering, ensuring the safe operation of the aircraft during take-off, landing and ground sliding, supporting the body, maintaining the attitude and effectively absorbing shock during landing, and supporting the body and maintaining the attitude during parking and sliding, and being used as a main bearing component, the landing gear bears various loads during the gravity of the aircraft, take-off, landing and sliding, transmits the force to a fuselage structure, and ensures the stable take-off, landing and sliding of the aircraft. When an aircraft drops, the landing gear is difficult to realize complete vertical drop due to the influence of various factors, the landing gear is often subjected to oblique force, however, most of existing landing gears are of unidirectional shock absorption design, the absorption capacity of the existing landing gear is extremely limited for such oblique shock, the aircraft structure can bear additional stress to influence the flight safety and the service life of the aircraft, in addition, the existing landing gear can not be well adapted when dealing with the uneven runway condition, the bumping feeling is stronger when the aircraft slides, the sliding stability is influenced, and even extra abrasion and damage to landing gear components can be caused. Disclosure of utility model In order to overcome the technical problems in the prior art, the utility model provides a multifunctional damping mechanism for a main landing gear of a light aircraft. The damping mechanism for the light aircraft main landing gear comprises a landing gear, wheels, connecting rods, vertical shock absorbers, oblique shock absorbers, waist-shaped grooves, an adjusting mechanism and a rotating mechanism, wherein the landing gear is composed of two supporting frames which are bilaterally symmetrical, the left supporting frame and the right supporting frame are in transverse sliding connection through middle sliding rails, the vertical shock absorbers are symmetrically arranged inside the rear sides of the landing gear, each vertical shock absorber is composed of a fixed end, a movable end and a spring, the movable ends are in sliding connection on the fixed ends and are provided with damping, the fixed ends of the vertical shock absorbers are provided with the rotating mechanism, the spring is arranged between the rotating mechanism and the movable ends, the rotating mechanism is used for adjusting the damping force of the vertical shock absorbers, the top ends of the fixed ends of the vertical shock absorbers are fixedly connected to the landing gear, the movable ends of the vertical shock absorbers penetrate through the landing gear and are connected with the connecting rods in a rotating mode, the bottom of the connecting rods is provided with the wheels, the front sides of the landing gear are symmetrically provided with the oblique shock absorbers, the oblique shock absorbers are also composed of the fixed ends, damping ends are arranged between the fixed ends and the movable ends, the top ends of the fixed ends are fixedly connected to the landing gear, the waist-shaped grooves are formed between the fixed ends, the movable ends are fixedly connected to the top of the landing gear, the movable ends of the connecting rods are provided with waist-shaped grooves, the waist-shaped shock absorbers, the movable ends are used for adjusting the damping force, and the landing gear is matched with the landing gear, and the damping mechanism. Further, adjustment mechanism includes swivel becket and screw rod, and the undercarriage middle part is equipped with the screw rod, and left side support frame and screw rod rotate to be connected, right side support frame and screw rod threaded connection, screw rod left side fixedly connected with swivel becket. Further, the rotating mechanism comprises threads and nuts, the fixed end of the vertical shock absorber is provided with the threads, and the fixed end of the vertical shock absorber is provided with the nuts through the threads. Further, the novel nut comprises a handle, and the handle is arranged on the nut. Further, the landing gear further comprises gaskets, and two gaskets are symmetrically and fixedly connected to the left side and the right side of the top of the landing gear. Further, the machine wheel also comprises resistance blocks, and the resistance blocks are fixedly connected to the machine wheel in a circular uniform distribution mode. The vertical shock absorber has the beneficial effects that after the wheel is contacted