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

Abstract

The invention discloses a tail-sitter four-rotor canard aircraft capable of vertically taking off and landing. The tail-sitter four-rotor canard aircraft capable of vertically taking off and landing comprises an aircraft body, wings, canards, vertical tails and power devices; a pair of canards is mounted at the head part of the aircraft body; the wings are on two sides of the tail part of the aircraft body; the vertical tails are respectively arranged above and under the tail part of the aircraft body; the power devices are respectively arranged at the tip parts of the wings and the tip parts of the vertical tails; the power devices are variable pitch propellers; and rotating shafts of the power devices are parallel to the axis of the aircraft body. The tips of the wings, the tips of the vertical tails and the tail end of the aircraft body of the four-rotor canard aircraft mutually form five supporting points; and in a stopping state, the five supporting points enable the aircraft to vertically land on the ground upward. The tail-sitter four-rotor canard aircraft capable of vertically taking off and landing has the advantages of rapid vertical takeoff and landing response speed as well as good controllabitity, stability and wind-resistant performance during vertical takeoff and landing. By using canard configuration, the tail-sitter four-rotor canard aircraft capable of vertically taking off and landing can horizontally fly for a long time at a high speed in the form of a fixed wing and can realize good controllabitity and maneuverability.

Description

technical field [0001] The invention relates to a vertical take-off and landing aircraft, in particular to a tail seat type four-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 slow flight speed and short endurance time, as well as the problems of low control efficiency and poor wind resistance of the existing tailseat 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 long cruise time, the...

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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