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CN-122009476-A - Landing buffer gear and flight device

CN122009476ACN 122009476 ACN122009476 ACN 122009476ACN-122009476-A

Abstract

The application discloses a landing buffer mechanism and a flying device, and relates to the field of aircrafts. The landing buffer mechanism comprises at least one group of buffer components which are arranged below the wing. The buffer assembly comprises a shell, a plurality of buffer rods, a linkage unit and an elastic piece. The plurality of buffer rods are slidably assembled on the housing, and at least part of the rod body extends to the outer side of the housing. The linkage unit is arranged between two adjacent buffer rods and used for enabling the buffer rods to move in opposite directions or in opposite directions when the buffer rods slide relatively. The elastic piece is sleeved on the outer wall of the linkage unit and is used for driving the buffer rod to reset. When the landing surface is uneven, each buffer rod independently slides according to the terrain difference, relative movement is generated through a linkage unit to adaptively match the terrain fluctuation, the elastic piece and damping force generated by the relative movement cooperate to provide a buffering effect, so that the change of the body posture is effectively inhibited, and the landing stability and safety are improved.

Inventors

  • SONG WEICHAO
  • LIU YE

Assignees

  • 西安羚控电子科技有限公司

Dates

Publication Date
20260512
Application Date
20260409

Claims (10)

  1. 1. A landing cushioning mechanism, comprising: At least one group of buffer components (1) arranged below the wing (2); the cushioning assembly (1) comprises: a housing (11); a plurality of buffer rods (12) slidably mounted on the housing (11), and at least a portion of the rod body of each buffer rod (12) extends to the outside of the housing (11) for contacting a landing surface; A linkage unit (13) arranged between two adjacent buffer rods (12) and used for enabling the two adjacent buffer rods (12) to move towards or away from each other when the buffer rods (12) slide relatively; The elastic piece (14) is arranged in the shell (11) and sleeved on the outer wall of the linkage unit (13) and is used for driving the buffer rod (12) to reset after buffering and/or buffering are finished.
  2. 2. The landing cushioning mechanism according to claim 1, characterized in that the linkage unit (13) comprises: A sliding rod (131) slidably disposed in the housing (11) in a direction perpendicular to the sliding direction of the buffer rod (12); The elastic piece (14) is sleeved on the outer wall of the sliding rod (131), and two ends of the elastic piece are respectively abutted to the inner top wall of the shell (11) and the sliding rod (131).
  3. 3. The landing cushioning mechanism of claim 2, further comprising a transmission assembly (15); The transmission assembly (15) is respectively connected with the sliding rod (131) and the buffer rod (12) in a transmission way and is used for converting sliding of the buffer rod (12) into linear displacement of the sliding rod (131).
  4. 4. A landing cushioning mechanism according to claim 3, characterized in that the transmission assembly (15) comprises: A linkage gear (151) arranged at one end of the sliding rod (131); a plurality of rack portions (152) which are provided on the corresponding buffer rods (12) and which are engaged with the linking gear (151); Wherein, the opposite or opposite movement of the two buffer rods (12) is converted into the linear displacement of the sliding rod (131) through the engagement of the linkage gear (151) and the rack part (152).
  5. 5. The landing cushioning mechanism of claim 2, further comprising a cushioning unit (16); The buffer unit (16) is in transmission connection with the sliding rod (131) and is used for converting the linear motion of the sliding rod (131) into rotary motion and providing buffer force through the shearing resistance of viscous damping medium so as to absorb impact energy.
  6. 6. The landing cushioning mechanism of claim 5, wherein the cushioning unit (16) comprises: a buffer tube (161) fixedly arranged in the shell (11), and filled with viscous damping medium; a transmission rod (162) rotatably arranged in the buffer cylinder (161); The toggle piece (163) is fixedly arranged on the transmission rod (162) and immersed in the viscous damping medium; the linear displacement of the sliding rod (131) drives the transmission rod (162) to rotate through the transmission pair (164) to drive the stirring piece (163) to stir the viscous damping medium so as to generate buffering damping.
  7. 7. The landing cushioning mechanism of claim 6, wherein the drive pair (164) comprises: a buffer rack (1641) provided on the slide bar (131); and a buffer gear (1642) coaxially fixed on the transmission rod (162) and meshed with the buffer rack (1641).
  8. 8. The landing cushioning mechanism according to claim 1, characterized in that an end of the cushioning rod (12) outside the housing (11) is provided with an abutment foot (17); The abutting pins (17) are of a spherical structure or a roller structure; and/or further comprising a plurality of horn arms (3); The buffer assemblies (1) are respectively arranged on the corresponding horn (3) and correspond to the front, back, left and right directions of the flying device.
  9. 9. Landing cushioning mechanism according to claim 1, characterized in that the cushioning rod (12) is provided with a limit structure (18) for limiting the sliding travel of the cushioning rod (12) relative to the housing (11); the limit structure (18) comprises: a positioning groove (181) penetrating through the buffer rod (12); the positioning rod (182) is fixedly arranged in the shell (11) and is in sliding clamping connection with the positioning groove (181).
  10. 10. A flying device comprising the landing cushioning mechanism of any one of claims 1-9.

Description

Landing buffer gear and flight device Technical Field The application relates to the technical field of aircrafts, in particular to a landing buffer mechanism and an flying device. Background The fixed wing aircraft has been widely used in various fields such as mapping, exploration, agricultural plant protection, etc. by virtue of the advantages of long endurance time, high flight efficiency, etc. During the take-off and landing of an aircraft, the landing cushioning mechanism is a key component for ensuring the safety of the machine body structure and the stability of equipment. Currently, the landing gear or buffer mechanism of the existing fixed wing aircraft mostly adopts a structure that a rigid supporting rod is matched with a single spring or a telescopic sleeve. However, such conventional designs have drawbacks in practical applications, and when an aircraft lands on uneven or sloped ground, since each supporting point cannot be independently and adaptively adjusted according to the concave-convex change of the terrain, the aircraft body is easily inclined or even turned on one's side, and landing stability and safety are seriously affected. Disclosure of Invention The landing buffer mechanism and the flight device solve the problems in the background technology. The embodiment of the application provides a landing buffer mechanism, which comprises at least one group of buffer components arranged below a wing, wherein the buffer components comprise a shell, a plurality of buffer rods, a linkage unit and an elastic piece, wherein the buffer rods are assembled on the shell in a sliding mode, at least part of rod bodies of each buffer rod extend to the outer side of the shell and are used for contacting a landing surface, the linkage unit is arranged between two adjacent buffer rods and is used for enabling the two adjacent buffer rods to move oppositely or reversely when the buffer rods slide relatively, and the elastic piece is arranged in the shell and sleeved on the outer wall of the linkage unit and is used for driving the buffer rods to reset after buffering and/or buffering are finished. In combination with the first aspect, in one possible implementation manner, the linkage unit comprises a sliding rod which is slidably arranged in the shell along a direction perpendicular to the sliding direction of the buffer rod, wherein the elastic piece is sleeved on the outer wall of the sliding rod, and two ends of the elastic piece are respectively abutted to the inner top wall of the shell and the sliding rod. With reference to the first aspect, in a possible implementation manner, the landing buffer mechanism further comprises a transmission assembly, and the transmission assembly is respectively in transmission connection with the sliding rod and the buffer rod and is used for converting sliding of the buffer rod into linear displacement of the sliding rod. With reference to the first aspect, in one possible implementation manner, the transmission assembly includes a linkage gear disposed at one end of the sliding rod, and a plurality of rack portions respectively disposed on the corresponding buffer rods and meshed with the linkage gear, wherein opposite or opposite movements of the two buffer rods are converted into linear displacement of the sliding rod through meshing of the linkage gear and the rack portions. With reference to the first aspect, in a possible implementation manner, the landing buffer mechanism further comprises a buffer unit, wherein the buffer unit is in transmission connection with the sliding rod and is used for converting the linear motion of the sliding rod into rotary motion and providing buffer force through the shearing resistance of the viscous damping medium so as to absorb impact energy. With reference to the first aspect, in a possible implementation manner, the buffer unit comprises a buffer cylinder fixedly arranged in the shell and filled with viscous damping medium, a transmission rod rotatably arranged in the buffer cylinder, a stirring piece fixedly arranged on the transmission rod and immersed in the viscous damping medium, wherein linear displacement of the sliding rod drives the transmission rod to rotate through a transmission pair to drive the stirring piece to stir the viscous damping medium so as to generate buffer damping. With reference to the first aspect, in a possible implementation manner, the transmission pair includes a buffer rack disposed on the sliding rod, and a buffer gear coaxially fixed on the transmission rod and meshed with the buffer rack. In combination with the first aspect, in one possible implementation manner, an abutting foot is arranged at one end of the buffer rod, which is located outside the shell, the abutting foot is in a spherical structure or a roller structure, and/or the buffer rod further comprises a plurality of machine arms, and a plurality of groups of buffer assemblies are respectively arranged on the corresponding