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Unmanned aerial vehicle nose landing gear shock absorption and steering mechanism

A technology of front landing gear and steering mechanism, applied in landing gear, weight reduction, aircraft parts, etc., can solve the problems of left and right sway of the fuselage, large weight and size, short matching size, etc., to reduce the number of parts and structural weight, The effect of low number of parts and high reliability

Active Publication Date: 2017-05-10
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Description
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  • Application Information

AI Technical Summary

Problems solved by technology

The front landing gear of a general UAV has an independent steering mechanism and a shock absorbing mechanism. Poor performance, large weight dimensions, low lateral stiffness
It is easy to bend and deform under the action of side load when landing, or cause the fuselage to shake from side to side when sliding

Method used

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  • Unmanned aerial vehicle nose landing gear shock absorption and steering mechanism
  • Unmanned aerial vehicle nose landing gear shock absorption and steering mechanism

Examples

Experimental program
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Embodiment Construction

[0013] The present invention will be described in detail below.

[0014] Landing gear among the present invention is assembled together by landing gear steering rocker arm (1), mounting base (3), landing gear buffer strut (4) (containing machine wheel), bearing pin (2), compression spring (5). The pin shaft (2) passes through the round hole on the steering rocker arm (1) of the landing gear, the circumferential groove on the mounting seat (3) and the axial groove on the landing gear buffer strut (4) successively from outside to inside. Bearing pin (2) can prevent prolapse by installing shaft retaining ring at both ends. A compression spring (5) is arranged between the mounting base (3) and the landing gear buffer strut (4), which provides buffering when the landing gear is impacted.

[0015] When the landing gear is stressed and compressed, the landing gear buffer strut (4) moves upward, and the pin shaft (2) relatively moves downward in the axial groove in the landing gear b...

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Abstract

The invention belongs to the field of unmanned aerial vehicle nose landing gear structure / mechanism design, and relates to a nose landing gear suitable for small and medium-sized unmanned aerial vehicles. A landing gear steering rocker arm (1), a pin shaft (2), an installation base (3), a landing gear bumper post (4) and a compression spring (5) are included. The purposes are to improve steering of existing unmanned aerial vehicle nose landing gears and the force transmission characteristic of shock absorption mechanisms and decrease the number and the weight of structural parts. According to the nose landing gear, steering and buffering by two degrees of freedom are simultaneously achieved through an annular groove, an axial groove and the pin shaft, the number of parts is greatly decreased, the structure complexity and the manufacturing cost of the landing gear are reduced, and the reliability is improved; and as the landing gear post and an installation sleeve always have the maximum length of fit at any moment, the lateral rigidity is good, and the force bearing capacity of the parts is good.

Description

technical field [0001] The invention belongs to the field of UAV front landing gear structure / mechanism design, and relates to a front landing gear suitable for small and medium-sized UAVs. Background technique [0002] The front landing gear of the UAV requires light weight, good structural rigidity, steering function and good shock absorption performance. The front landing gear of a general UAV has an independent steering mechanism and a shock absorbing mechanism. Poor performance, heavy dimensions, low lateral stiffness. It is easy to bend and deform under the action of side load when landing, or cause the fuselage to shake from side to side when sliding. Contents of the invention [0003] The purpose of the present invention is to provide a shock-absorbing steering mechanism for the front landing gear of an unmanned aerial vehicle, so as to meet the needs of the development of various types of unmanned aerial vehicles. [0004] Technical scheme of the present invent...

Claims

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Application Information

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IPC IPC(8): B64C25/50B64C25/62
CPCB64C25/50B64C25/62Y02T50/40
Inventor 付强孙辽黎欣
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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