Gyroplane

Abstract

A novel rotary-wing aircraft is composed of main body, mainshaft, rotary wings, horizontal drive clutch, power system, rear wings and horizontal drive propeller. The rotary wings fixed to top end of mainshaft are adjustable-pitch torsional blades and used for vertical taking off or landing. Said horizontal drive propeller is used for horizontal flying. Its advantages are high safety and efficiency, and low cost and noise.

Description

Technical field [0001] The invention belongs to an aerospace vehicle, particularly a new type of rotorcraft. Background technique [0002] The traditional rotorcraft relies on the horizontal drive of the front or rear propellers of the fuselage, see figure 1 , figure 2 , (The arc-shaped arrow on the plane of rotation of the rotor in the figure indicates the direction of rotation of the rotor, figure 1 Briefly show a cross-sectional view of a blade and its three cross-sectional positions. image 3 , Figure 5 The same is true). The rotorcraft flies forward at speed V; figure 1 Shown is a pull-in propeller, figure 2 Shown is a propeller. The airflow horizontally passes through the rotation plane of the rotor at a certain speed to drive the rotor to rotate at high speed, so that the rotor gains lift and flies, and the blades are in a negative pitch and positive torsion working state. After the airflow passes through the rotor, the wake of the air is basically parallel to the he...

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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