Fixed-wing helicopter with independently-driven rotor propellers

A technology for helicopters and propellers, applied in the directions of rotorcraft, aircraft control, and aircraft stability, can solve problems such as accidents, high requirements on wing spar strength, and fast horizontal flight speed, and achieve the effect of reducing height

Inactive Publication Date: 2020-04-10
江富余
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0002] At present, there are known successful methods that can realize helicopters that can use the airport to slide forward, or can not rely on the airport to adopt multi-rotor vertical lift, hover, front, back, left, and right. The successful method is the tilt rotor, which has the advantage of large load capacity and horizontal flight. The speed is fast, but its disadvantage is that the rotor is set at both ends of the fixed wing, a

Method used

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  • Fixed-wing helicopter with independently-driven rotor propellers

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Embodiment Construction

[0061] figure 1 In the shown embodiment, the two rotors adopt a tandem layout, and the fuselage (20) head is provided with the first small tower (9) of the airfoil, and the first small tower (9) of the airfoil acts as a vertical tail. The first rotor (1) is set on the type first small tower (9), and the airfoil second small tower (10) is set at the rear of the fuselage (20). The small tower plays the role of a vertical empennage. Set the second rotor (2) on (10).

[0062] The second small tower (10) is set higher than the first small tower (9), and the distance between the two small towers is greater than the radius of the rotor, which can reduce the influence of the front rotor downwash on the rear rotor.

[0063] The center of the line connecting the centers of rotation of the first rotor (1) and the second rotor (2) is on the center of gravity (P), and the line overlaps with the longitudinal line of the fuselage (33).

[0064] The vertical tail of the second small tower (...

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Abstract

The invention discloses a fixed-wing helicopter with independently-driven rotor propellers. Two rotor wings are arranged on wing-shaped small towers at the head and the tail of a fuselage. The bladesof the rotor wings are connected with a rotor wing shaft through a paddle shell which is provided with a flapping hinge, a shimmy hinge and a variable pitch hinge. A total pitch controller and a periodic variable pitch controller are arranged to control the pitch change of the rotor blades. An upper single-wing fixed wing with high aspect ratio is arranged in the middle of the fuselage, and variable-pitch propellers are arranged on the left and right of the fixed wing. One engine is arranged to drive a rotor wing synchronous reverser through a gearbox and a clutch, and a universal shaft drivesthe two rotor wings. The other engine is arranged to drive a propeller synchronous reverser through a gearbox and a clutch, and a universal shaft drives the left and right variable-pitch propellers.A wheel type undercarriage is arranged. The power of one engine is distributed to the rotor wings and the power of the other engine is distributed to the variable-pitch propellers, and various flightmodes of helicopters, fixed wings and autorotation rotors can be freely switched. The helicopter has the advantages of being high in speed, low in energy consumption and suitable for take-off and landing occasions with electric or oil-electricity hybrid power and requiring no airports.

Description

technical field [0001] The invention relates to an independently driven rotor-propeller fixed-wing helicopter that can be pulled by a propeller and fly forward by taxiing at an airport, and can also adopt multi-rotor vertical lift, hover, and fly forward, backward, left, and right without relying on the airport. Background technique [0002] At present, there are known successful methods that can realize helicopters that can use the airport to slide forward, or can not rely on the airport to adopt multi-rotor vertical lift, hover, front, back, left, and right. The successful method is the tilt rotor, which has the advantage of large load capacity and horizontal flight. The speed is fast, but its disadvantage is that the rotor is set at both ends of the fixed wing, and the two ends support the weight of the whole aircraft. The huge moment requires high strength of the spar, and the rapid tilting of the huge rotor produces a large gyro force, which affects the tilting mechanism...

Claims

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Application Information

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IPC IPC(8): B64C27/08B64C27/32B64C27/12B64C9/20B64C5/06
CPCB64C5/06B64C9/20B64C27/08B64C27/12B64C27/32Y02T50/40
Inventor 江富余
Owner 江富余
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