CN216546687U

CN216546687U - Aircraft rotor shockproof structure

Info

Publication number: CN216546687U
Application number: CN202123429160.2U
Authority: CN
Inventors: 解保刚
Original assignee: Hebei Baogang Rotorcraft Technology Co ltd
Current assignee: Hebei Baogang Rotorcraft Technology Co ltd
Priority date: 2021-12-31
Filing date: 2021-12-31
Publication date: 2022-05-17
Anticipated expiration: 2031-12-31

Abstract

The utility model discloses a shockproof structure of a rotor wing of an airplane, wherein a rotor wing upright post is arranged at the top of a frame body, a rotor wing assembly at the top is fixed through the rotor wing upright post, the rotor wing assembly is driven through an engine, in order to realize the stability of the operation of the rotor wing during the operation and the steering of the rotor wing assembly, a swing seat is arranged on the rotor wing upright post to realize the transition of the drive of the rotor wing assembly, and meanwhile, an elastic element is arranged on the swing seat, and the elastic element absorbs the trembling energy to prevent the trembling during the operation of the rotor wing assembly.

Description

Aircraft rotor shockproof structure

Technical Field

The utility model relates to the technical field of rotorcraft, in particular to a rotor shockproof structure of an airplane.

Background

In the existing rotorcraft, the engine drives the propeller to provide forward power, and the rotor drives airflow to rotate to generate lift force when moving by the aircraft, so that the aircraft cannot drop when stalling. When the rotor wing of the rotorcraft is connected with the engine transmission system, the engine provides rotary power for the rotor wing, but in the process of the rotorcraft flying, the rotor wing is blown by front airflow and is matched with the engine to drive the rotor wing to rotate to generate lift force, like a windmill, so that the problem of stall cannot be generated. Because of the lower part of rotor is provided with direction control device, its angular adjustment when realizing turning to the rotor, but when the rotor rotated, the rotor often can appear and rotates reverse application of force, made rotor angle adjusting device tremble, the stability of direct influence flight.

In view of the above description of the prior art, it is necessary for those skilled in the art to design a stable structure capable of preventing the vibration caused by the rotation of the rotor wing through technical improvement, so as to improve the flight stability of the aircraft.

Disclosure of Invention

In view of the above-mentioned drawbacks of the prior art, it is an object of the present invention to provide an anti-vibration structure for an aircraft rotor, which is structurally improved in a rotor angle adjustment device and effectively absorbs vibration.

According to the anti-vibration structure of the aircraft rotor wing, the oscillating seats are symmetrically arranged on the left side and the right side of the rotor wing upright post, the oscillating seats are hinged and fixed on the rotor wing upright post, the oscillating seats are provided with the upper oscillating point and the lower oscillating point, the oscillating seats are connected with the bottom oscillating rod through the lower oscillating point, the oscillating seats are connected with the upper oscillating rod through the upper oscillating point, and the upper oscillating rod is connected with the rotor wing assembly to realize the left-right oscillation adjustment; the middle part of swing seat articulated be provided with an elastic element, elastic element fix on the rotor upright post through bottom fixing base, it is used for preventing its tremble to swing seat application of force.

The bottom swing rod and the upper swing rod are arranged in a left-right mode and respectively correspond to the swing seats.

The utility model has the following beneficial effects: according to the device, through the structural arrangement, the rotor wing upright column is arranged at the top of the frame body, the top rotor wing assembly is fixed through the rotor wing upright column, the rotor wing assembly is driven through the engine, in order to realize the stability of the rotor wing assembly in operation and steering, the swing seat is arranged on the rotor wing upright column to realize the transition of the drive of the rotor wing assembly, and meanwhile, the elastic element is arranged on the swing seat, and the elastic element absorbs the vibration energy to prevent the vibration of the rotor wing assembly in operation.

Drawings

The utility model is further illustrated with reference to the following figures and examples.

FIG. 1 is a schematic perspective view of the present invention;

FIG. 2 is an enlarged view of the structure of area A in FIG. 1;

in the figure, 1, a rotor upright post, 2, a swinging seat, 21, an upper swinging point, 22, a lower swinging point, 23, a base, 24, a hinged swinging point, 3, a rotor component, 31, a driven fluted disc, 32, a driving gear, 4, a swinging part, 41, a swinging connecting rod, 42, an upper swinging rod, 43, a bottom swinging rod, 5, a damper, 51, a damping seat, 52 and a damping seat hinged platform.

Detailed Description

The present invention is described in detail below, and other advantages and effects of the present invention will be easily understood by those skilled in the art from the disclosure of the present specification.

As shown in the accompanying drawings, the anti-vibration structure of the aircraft rotor disclosed by the utility model is the same as the existing structure, the rotor assembly 31 is arranged at the top of the rotor upright post 1, the rotor assembly 31 is provided with fan blades, the bottom of the rotor assembly 31 is provided with a driven fluted disc 31, the rotor assembly 31 is fixed at the top of the swinging part 4, and the swinging part 4 is internally provided with a driving gear 32 which is meshed with the driven fluted disc to drive the fan blades; the swing part 4 is transversely provided with a swing connecting rod 41, the upper swing rod 42 is connected and fixed through the left end and the right end of the swing connecting rod 41, the upper swing rod 42 is connected into a whole through a swing seat 2 and a bottom swing rod 43, and the technical key points of the utility model are as follows: swing seat 2 pass through the base 23 articulated to be fixed on rotor upright 1, be provided with upper portion swing point 21 and lower part swing point 22 on swing seat 2, be connected with bottom swinging arms 43 through lower part swing point 22, be connected through upper portion swing point 21 and upper portion swinging arms 42, be connected through upper portion swinging arms 42 and rotor subassembly 3 and realize its swing adjustment about it. Therefore, the swing angle of the rotor wing assembly can be adjusted when the airplane turns.

Swing seat 3's middle part articulate through damping seat hinge table 52 and be provided with an elastic element, elastic element can be the extension spring, also can be attenuator 5, this embodiment explains with attenuator 25 as an example, fix damping seat hinge table 52 on rotor upright 16 through damping seat 51, attenuator 25 is fixed and is connected through articulated pendulum point 24 and swing seat 2 in damping seat hinge table 52, it is used for when preventing rotor subassembly 3 high-speed rotation to swing seat 2 application of force, with rotatory power reverse transmission messenger swing seat 2 or upper portion swinging arms 42, bottom swinging arms 43 tremble, technical problem more than the solution that can be fine through setting up of attenuator 5.

To summarize: through the structural arrangement, the swing seat 2 is arranged on the rotor wing upright post 1 to realize the transition of the driving of the rotor wing assembly, and meanwhile, the elastic element is arranged on the swing seat to prevent the vibration of the rotor wing assembly during the operation, so that the utility model is an ideal solution for the reverse vibration of the aircraft rotor wing.

Claims

1. The utility model provides an aircraft rotor shockproof structure which characterized in that: swing seats are symmetrically arranged on the left and right of a rotor wing upright post, the swing seats are hinged and fixed on the rotor wing upright post, upper swing points and lower swing points are arranged on the swing seats, the swing seats are connected with a bottom swing rod through the lower swing points, the swing seats are connected with an upper swing rod through the upper swing points, and the swing seats are connected with a rotor wing assembly through the upper swing rods to realize left-right swing adjustment; the middle part of swing seat articulated be provided with an elastic element, elastic element fix on the rotor upright post through bottom fixing base, it is used for preventing its tremble to swing seat application of force.

2. An aircraft rotor anti-vibration structure according to claim 1, wherein: the bottom swing rod and the upper swing rod are arranged in a left-right mode and respectively correspond to the swing seats.