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Variable pitch device and installation method thereof

A pitch-variable and pitch-variable mechanism technology, applied in the field of aircraft, can solve problems such as easy vibration, wear control accuracy of the pitch-variable mechanism, and reduce control accuracy, and achieve higher reliability and service life, high reliability and service life, and structural form. compact effect

Active Publication Date: 2019-01-29
西安君晖航空科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The existing propeller pitch change mechanism is the most typical pitch change rod of the helicopter. The pitch change rod adjusts the angular displacement of the curved rod and the angle of the swash plate through the linear displacement to change the pitch of the propeller blade. This external pitch change rod is exposed In the propeller airflow, the pitch change rod will interact with the propeller airflow, and the connection form is prone to gaps, wear and vibration, which poses hidden dangers to the control and safety of the aircraft; in addition, the propeller blades and related mechanisms of the traditional pitch change mechanism The connection form is complicated, and it is impossible to realize quick installation, disassembly and replacement
[0004] In CN108372927A, a six-degree-of-freedom full-control eight-rotor aircraft based on variable-pitch propellers discloses a pitch-variable device, which realizes adjusting the angle connected to the fixed curved rod by adjusting the angle between the moving rod and the fixed curved rod. The pitch of the propeller blades; this device is similar to the traditional variable pitch structure, located in the airflow of the propeller blades, which will affect the aerodynamic efficiency of the propeller blades, and will also be affected by the airflow of the propeller blades to reduce the control accuracy, and the crank and the moving rod The connection is prone to vibration, resulting in the wear of the pitch change mechanism and the reduction of control accuracy, and it is not easy to install and disassemble

Method used

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  • Variable pitch device and installation method thereof
  • Variable pitch device and installation method thereof

Examples

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Embodiment 1

[0033] Such as Figure 1 to Figure 6 Shown, a kind of pitch control device that is applied in the aircraft shown in this embodiment includes propeller hub 3, four propeller blades 4 that are movable around the propeller hub 3 at equidistant intervals and movable on the propeller hub 3. The crank arm mechanism in the propeller hub 3 and the variable pitch mechanism 5, the pitch variable mechanism 5 can move back and forth along the axial direction of the propeller hub 3, and rotate together with the propeller hub 3 during work; The mechanism 5 is connected, and the crank arm mechanism rotates with the movement of the pitch variable mechanism 5. The other end of the crank arm mechanism protrudes from the propeller hub 3 and is connected with the propeller blade, and the arc displacement axis of the crank arm mechanism is aligned with the propeller blade. The rotation axis of the propeller pitch is the same, and the linear displacement of the pitch variable mechanism along the ax...

Embodiment 2

[0043] The present invention also provides a method for installing the pitch control device described in Embodiment 1, comprising the following steps:

[0044] S1. First connect the movable ejector rod in the pitch variable mechanism with the connecting rod in the propeller rotating shaft, and then insert the anti-twist strut on the upper splint and the lower splint;

[0045] S2. Set the propeller hub outside the pitch changing mechanism and fix it on the fixed base plate, and then install the top cover;

[0046] S3. Assemble the tapered thread jacket and the cylindrical crank arm boss through pins, and sequentially set washers and clamps on the outer circumference of the tapered thread jacket (the clamps include two semicircular clamps and a circular clamp), forming Crank arm mechanism;

[0047] S4. Install the crank arm mechanism into the propeller hub through the through hole of the installation part and fix it with the blade cover, and the boss inside the cylindrical cran...

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Abstract

The invention discloses a variable pitch device and an installation method thereof. The variable pitch device comprises a propeller hub and at least two propeller blades movably arranged on the wholebody of the propeller hub, wherein a variable pitch mechanism which moves in the axial direction of the propeller hub is movably arranged in the propeller hub; the inner side ends of the propeller blades are arranged in the propeller hub and are connected with the variable pitch mechanism; and the variable pitch mechanism drives the propeller blades to rotate when moving in the axial direction ofthe propeller hub. The variable pitch device has the characteristics of compact structure, convenient installation, higher reliability and longer service life.

Description

technical field [0001] The invention relates to the technical field of aircraft, in particular to a pitch variable device used in an aircraft and an installation method thereof. Background technique [0002] Using propeller rotation to generate power is one of the most important forms of power for current aircraft. In order to make full use of the capabilities of the engine and propeller blades at different speeds and different flight modes, using non-fixed pitch is a good solution. [0003] The existing propeller pitch change mechanism is the most typical pitch change rod of the helicopter. The pitch change rod adjusts the angular displacement of the curved rod and the angle of the swash plate through the linear displacement to change the pitch of the propeller blade. This external pitch change rod is exposed In the propeller airflow, the pitch change rod will interact with the propeller airflow, and the connection form is prone to gaps, wear and vibration, which poses hidd...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C11/32
CPCB64C11/32
Inventor 张冰融张甲奇杨先锋陈希平
Owner 西安君晖航空科技有限公司
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