Canard high-speed tilting rotor aircraft and control method thereof

Abstract

The invention belongs to the technical field of aircrafts, and discloses a canard high-speed tilting rotor aircraft and a control method thereof.The canard high-speed tilting rotor aircraft comprisesan aircraft body, a front canard, a rear wing, a front rotor, a rear tilting rotor and a tilting mechanism; wherein the front canard and the front rotor are mounted at the front part of the aircraft body,, the front rotor is mounted in a through hole of the front canard, and the rear wing is mounted at the rear part of the aircraft body; and the rear tilting rotor wing is arranged at the rear partof the gravity center of the aircraft body through the tilting mechanism and is positioned in front of the rear wing. Compared with helicopters, autorotorcrafts and multi-rotor aircrafts, the tilt angle of a tilting thrust rotor is adjusted, so that the attitude of the aircraft body does not need to be additionally tilted in flight, and the front rotor on the front canard is closed in a flat flight mode to form a canard type fixed-wing aircraft, so that the forward flight resistance is small, and the speed is remarkably increased; in a flat flight mode, the thrust comes from the backward tilting rotor, the diameter of the rotor is smaller than that of a tilting rotor aircraft, the resistance is small during forward flight, and the speed is higher.

Description

technical field [0001] The invention belongs to the technical field of aircraft, and in particular relates to a canard high-speed tilt-rotor aircraft and a control method thereof. Background technique [0002] In helicopter aircraft, conventional helicopters and coaxial helicopters obtain forward flight thrust by tilting the angle of the main rotor. When the main rotor is tilted, the forward flight resistance will be increased, and when the forward flight speed is high, the fuselage needs to be tilted downward. To further increase the forward tilt angle of the main rotor to obtain more thrust, if the fuselage bows too much, it will further increase the flight resistance, so the forward flight speed of the helicopter is low, and the fuselage is in a bowed state when flying forward, and the ride comfort is also low. It has a shortpart. [0003] The compound helicopter is to increase the thrust by adding propellers on the basis of conventional helicopters or coaxial helicopter...

AI Technical Summary

Problems solved by technology

[0003]Composite helicopters increase the thrust by installing propellers on the basis of conventional helicopters or coaxial helicopters, and reduce the tilt angle of the main rotor, so the speed increase is relatively small. Large, and the forward tilt angle of the fuselage is also eased, but because the compound helicopter uses two main rotors, the resistance cannot be further reduced, the high-speed potential is limited, and the size of the main rotor of the helicopter is large, and the requirements for the size of the take-off and landing site are high. At the same time, the exposed blades also affect the safety of take-off and landing

[0004] Since the rotor is in the state of autorotation, the speed of the autogyro is low and the noise is low; and the large-sized rotor has high resistance, the flight speed is lower than that of conventional helicopters, and the timeliness is poor

[0005] Multi-rotor aircrafts can not provide greater thrust due to the inclination of the fuselage during forward flight, which increases the windward area and increases the windward area, and the inclination angle of the aircraft is too large, which will affect the flight balance and cannot provide greater thrust. The forward flight thrust is limited. The forward flight resistance is high and the forward flight thrust is insufficient, and the forward flight speed is low. The compound multi-rotor aircraft reduces the resistance by adding propellers. UAV or manned aircraft, the speed is about 100km / h

[0006] Since the propulsion device of the tilt-rotor unmanned aerial vehicle needs to take into account both the takeoff and landing and the forward flight state, the diameter of the rotor of the propulsion device is relatively large. In flight mode, the resistance is relatively large, which affects the further improvement of forward flight speed; since the propulsion device is installed on the wing, the point of action of the total lift is only at the wing position, and the adjustable range of the center of gravity of the whole machine along the axis of the fuselage is small. High requirements on the position of the center of gravity of mission equipment loading

[0007] Conventional fixed-wing configuration tilt-rotor aircraft realizes the combination of fixed-wing aircraft and quad-rotor aircraft by adding four-rotor mechanisms on both sides of the fixed-wing wing, and the implementation is simple , but there is a problem of large structural resistance, so the high-speed performance is poor, and it is currently only used on small UAVs

[0008] In addition, the organic support under the rotor of the multi-rotor UAV and the above two tilt-rotor UAVs is connected to the body, which will hinder the downward airflow of the rotor , which reduces the take-off, landing and hovering efficiency of the propulsion device

[0009]The lift body configuration tilt-rotor aircraft achieves the conversion of vertical take-off and landing and horizontal forward flight by tilting the tail duct, and further closes the lift when flying forward at high speed Duct, so the resistance of the whole machine is small, but there is also a tail tilting duct arranged behind the wing, which is far away from the center of gravity, so the tilting thrust accounts for a small proportion of the overall lift, which has an impact on further increasing the flight speed; at the same time , because the tail duct is installed at the rear of the wing, the structure of the installation is weak, and the force transmission characteristics need to be improved. If the structure is strengthened alone, the weight of the airframe will increase, which will affect the weight efficiency of the whole machine

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