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Tilt rotary-wing aircraft and control method thereof

A technology of tilting rotorcraft and tilting mechanism, applied in the direction of rotorcraft, motor vehicles, aircraft, etc., can solve the problems of long range, fast horizontal flight speed, need for take-off and landing runway, etc., to increase the flight envelope, speed wide range of effects

Active Publication Date: 2015-11-25
IANGSU COLLEGE OF ENG & TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The former has a long range and fast horizontal flight speed, but it needs a takeoff and landing runway
The latter does not require a take-off and landing runway, but because its thrust is realized by the horizontal component of the rotor lift, the horizontal speed is not as fast as that of the fixed-wing aircraft, and because its lift is generated by the engine driving the main rotor instead of the airflow passing through Produced by fixed-wing aircraft, so the fuel consumption rate or power consumption for the same flight distance is higher than that of fixed-wing aircraft

Method used

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  • Tilt rotary-wing aircraft and control method thereof
  • Tilt rotary-wing aircraft and control method thereof
  • Tilt rotary-wing aircraft and control method thereof

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Embodiment Construction

[0020] Such as figure 1 with figure 2 A tiltable rotorcraft shown includes four sets of tiltable rotors, namely front rotor 1, rear rotor 3, left rotor 2 and right rotor 4, two deflectable wings 5,6, vertical Tail 7, engine, tilting mechanism and pitch-changing mechanism and flight control system, described vertical tail 7, wing 5,6 are connected with described rotor respectively, and described rotor is connected with engine, tilting mechanism and pitch-changing mechanism respectively ;Such as figure 2 As shown, each set of tiltable rotors includes three blades 11, 12, 13, a hub 16 (including a pitch-variable hinge 14, a shimmy hinge 17, and a flapping hinge 18), a pitch-variable tie rod 19 and a tilting The nacelle 20, each blade is connected to the tilting nacelle 20 through the hub 16 and the variable pitch rod 19, the tilting nacelle 20 is provided with a wing tilting mechanism 21, and the wing tilting mechanism 21 is connected with wing by tilt hinge 22, and describe...

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Abstract

The invention discloses a tilt rotary-wing aircraft and a control method thereof. The tilt rotary-wing aircraft comprises four tilt rotor wing sets, two deflectable wings, a vertical fin, engines, a tilting mechanism, distance-variable mechanisms and a flight control system. The vertical fin and the wings are arranged on a aircraft body and controlled by a control system. The four rotor wing sets are connected with the engines, the tilting mechanism and the distance-variable mechanisms. Each rotor wing set comprises a plurality of blades, a blade hub, a distance-variable pull rod and a short tilting cabin. All the blades are connected with the short tilting cabins through the blade hubs and the distance-variable pull rods. The tilting mechanism is arranged in the short tilting cabins. The tilting mechanism is connected to girders of the wings through tilt hinges. Another independent deflection mechanism of the wings can drive the wings to deflect up and down. The tilt rotary-wing aircraft has the advantages that the advantages of a tilt rotary-wing aircraft and the advantages of a fixed-wing aircraft are combined, the tilt rotary-wing aircraft can lift vertically and achieve horizontal long-voyage flight at a high speed, the flight envelope is increased, and the defects of the two kinds of traditional aircrafts are overcome.

Description

technical field [0001] The invention belongs to the technical field of unmanned aerial vehicle and its control, and in particular relates to a tiltable rotorcraft and its control method. Background technique [0002] The existing UAVs on the market are mainly divided into two categories: fixed-wing UAVs and rotary-wing UAVs. The former has a long range and fast horizontal flight speed, but it needs a takeoff and landing runway. The latter does not require a take-off and landing runway, but because its thrust is realized by the horizontal component of the rotor lift, the horizontal speed is not as fast as that of the fixed-wing aircraft, and because its lift is generated by the engine driving the main rotor instead of the airflow passing through Fixed-wing generation, so the fuel consumption rate or power consumption for the same flight distance is higher than that of fixed-wing aircraft. Contents of the invention [0003] Purpose of the invention: the purpose of the pres...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/28B64C27/08
Inventor 连亮
Owner IANGSU COLLEGE OF ENG & TECH
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