Helirota plane

Abstract

A rotor craft able to vertically take off and land is composed of main body, mainshaft, rotor fixed to mainshaft and with the adjustable torsional blades, horizontally driving clutch, power system, rear fin and propeller for horizontally driving. Its advantages are flexibly taking-off and landing, high safety and low noise.

Description

technical field [0001] The invention belongs to an aeronautical vehicle, which is an improved rotorcraft with a new structure, in particular a helicopter rotorcraft. Background technique [0002] The traditional rotorcraft is driven forward by the horizontal drive of the front or rear propeller of the fuselage, see figure 1 , figure 2 , (the arc arrow in the plane of rotor rotation in the figure indicates the direction of rotor rotation, figure 1 Briefly shows the cross-sectional view of a blade and its three cross-sectional positions, the following image 3 , Figure 5 also the same). The gyroplane flies forward at speed V; figure 1 Pull-in propeller shown, figure 2 Pusher propeller shown. The airflow horizontally passes through the rotor rotation plane at a certain speed to drive the rotor to rotate at high speed, so that the rotor can gain lift and fly, and the blades are in negative pitch and positive torsion working state. After the airflow passes through the ...

AI Technical Summary

Problems solved by technology

This aircraft has combined traditional helicopter and traditional rotorcraft, and it partially solves the respective deficiencies of traditional helicopter and traditional rotorcraft, but it also has disadvantages: 1. This aircraft will use two different engines, making it The power system is relatively complicated; 2. Its two engines use different fuels, which are not compatible with each other, which increases the restrictions on its own flight; 3. When cruising, it uses negative twist propellers and negative pitch blades for positive Working in the range of torsion and negative pitch reduces the aerodynamic efficiency of the rotor during cruising flight; 4. The aircraft can only use the maneuvering method of a helicopter for maneuvering flight

[0007] The pitch control blade of the above-mentioned helicopter is formed by changing the fixed paddle shaft of the ordinary fixed pitch blade to the pitch adjustment shaft. The disadvantage of this pitch control blade is that the efficient working range of the pitch is small, and the entire The blades all rotate at the same angle, and it can work efficiently only when the pitch is set; when it is adjusted to deviate from the optimum value, only a certain section of the blade has high efficiency, and the installation angle error of other parts increases, and the efficiency is significantly reduced

Due to the deficiency of existing pitch control blades, the development of various aircrafts utilizing pitch control blades is limited

[0008] A kind of existing rotor with servo flap 16 (see Figure 8 ), its torsion is fixed to the traditional blade, and its torsion cannot be adjusted; the servo flap 16 is used to adjust the lift of the rotor, which cannot change the basic characteristics of its blade as negative torsion, and its high-efficiency pitch adjustment range is small

[0009] State-of-the-art non-twisting propellers, which are only used for scientific research, it has never been used in any practical aircraft

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