Tailstock type vertical take-off and landing unmanned aerial vehicle and control method thereof

A tailstock type vertical take-off and landing unmanned aerial vehicle, wherein the unmanned aerial vehicle comprises:

• a fuselage, wings, ailerons, empennages, an elevator, a rudder, an engine, an attitude adjustment nozzle, and a landing gear;
• the wings are symmetrically fixed on both sides of the middle of the fuselage, and the ailerons are hinged to trailing edges of the wings on the both sides;
• the empennages are located at the tail of the fuselage, and the elevator and the rudder are hinged to the trailing edges of the empennages;
• the engine is arranged at the tail of the fuselage for producing forward thrust;
• and the landing gear is arranged at the tail of the fuselage, capable of being automatically folded and unfolded, and configured to support the unmanned aerial vehicle;
• the attitude adjustment nozzle is composed of a plurality of nozzles, which are distributed on an outer surface of the front of the fuselage, and capable of spraying gas outward to generate thrust and a rotation torque, so as to assist in adjusting an attitude of the unmanned aerial vehicle;
• the plurality of nozzles are distributed on the outer surface of the front of the fuselage, and are away from the center of gravity of the unmanned aerial vehicle by a set distance, the plurality of nozzles point to the outside of the fuselage for generating thrust and the rotation torque, so as to assist in adjusting the attitude of the unmanned aerial vehicle;
• the center lines of some or all of the plurality of nozzles do not pass through the center axis of the fuselage of the unmanned aerial vehicle;
• and thrust of each nozzle of the plurality of nozzles is capable of being independently controlled;
• and
• the wings are straight wing, arranged above or below the fuselage, and capable of being folded, unfolded and locked, and a sweepback of the wings is adjustable;
• the ailerons are composed of two or more ailerons hinged to the trailing edges of the left and right wings through rotating shafts, the left and right ailerons are symmetrically distributed, and the ailerons are capable of being deflected.