Tail-sitter type three-rotor canard aircraft capable of vertically taking off and landing

Abstract

The invention discloses a tail-sitter type three-rotor canard aircraft capable of vertically taking off and landing. The tail-sitter type three-rotor canard aircraft capable of vertically taking off and landing comprises an aircraft body, wings, a canard wing, a vertical tail and power devices; the canard wing is mounted at the head part of the aircraft body; the wings are positioned on two sides of the tail part of the aircraft body; the vertical tail is arranged under the tail part of the aircraft body; the power devices are respectively arranged at the wing tip parts of the wings and the wing tip part of the vertical tail; and the power devices are variable pitch propellers. Elevons are mounted at the rear edges of the wings; a rudder is mounted at the rear edge of the vertical tail; and an elevating rudder is mounted at the rear edge of the canard wing. The wing tips of the wings, the wing tip of the vertical tail and the tail end of the aircraft body of the tail-sitter type three-rotor canard aircraft capable of vertically taking off and landing mutually form four supporting points; in a stopping state, the four supporting points enable the aircraft to vertically land on the ground upwards; the vertical takeoff and landing response speed of the aircraft is high and the aircraft has good stability during vertically taking off and landing. Through adoption of canard configuraiton, the tail-sitter type three-rotor canard aircraft capable of vertically taking off and landing can horizontally fly at a high speed in the form of a fixed wing and has the advantages of long flying time, good controllability and good motility.

Description

technical field [0001] The invention relates to a vertical take-off and landing aircraft, in particular to a tail-sitting three-rotor canard layout aircraft capable of vertical take-off and landing. Background technique [0002] Air vehicle design experts and researchers have been trying to design a vehicle that can take off and land short distances or vertically. To solve the problems that fixed-wing aircraft are limited by the take-off and landing site and the tilt-rotor aircraft has the defects of slow flight speed and short endurance time, as well as the problems of low control efficiency and poor wind resistance of the existing tail-sitting vertical take-off and landing fixed-wing unmanned aircraft . [0003] At present, in practical applications, unmanned aerial vehicles are generally divided into two types: fixed-wing aircraft and rotary-wing aircraft. Although conventional fixed-wing unmanned aerial vehicles have the characteristics of fast speed, long range and lon...

AI Technical Summary

Problems solved by technology

Its shortcoming is that during the vertical take-off and landing and hovering stages, under the action of the propeller slipstream, the control moment is generated by the deflection of the aerodynamic rudder surface, the control efficiency is low, and the wind resistance is poor.

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