UNMANNED AERIAL VEHICLE Russian patent published in 2021 - IPC B64C39/00 

FIELD: aircraft engineering.

SUBSTANCE: invention relates to the field of development and application of mobile unmanned aerial systems with unmanned aerial vehicles of the aircraft type, designed for aerial surveillance, reconnaissance, detection, target designation and laser illumination of targets for the guidance of guided munitions. An unmanned aerial vehicle of the aircraft type, made according to a combined aerodynamic scheme of a flying wing and a tailless one, contains a swept wing, including a left console and a right console, is equipped with vertical tips and control surfaces made in the form of elevons, and a longitudinal fuselage with a profile in the longitudinal section, creating an additional lifting force in relation to the swept wing. The unmanned aerial vehicle also contains a propulsion system located in the rear part of the fuselage, a fuel system with fuel tanks located in the fuselage, a parachute landing system, a navigation system, a flight control system, two-way radio communication facilities with a ground control station, a payload in the form of active and passive sensors located in the fuselage, an anti-icing system. In this case, the ratio of the length of the fuselage to the width of the fuselage is less than 6. In the front part of the fuselage, a smooth transition to the wing from the right and left sides is made, starting in the interval from 0.4 to 0.6 of the length of the front part of the fuselage and ending at the beginning of the rectilinear section of the leading edge of the left and right wing consoles. In the rear part of the fuselage, a smooth transition to the wing from the right and left sides is made, starting in the interval from 0.4 to 0.6 of the length of the rear part of the fuselage and ending at the beginning of the rectilinear section of the rear edge of the left and right wing consoles. The ratio of the length of the entire fuselage to the length of the front part of the fuselage is within the range from 2.8 to 3.6. The ratio of the length of the entire fuselage to the length of the rear part of the fuselage is within the range from 2.8 to 3.6. In the upper part of the fuselage and in the lower part of the fuselage, a smooth transition to the wing is made from the upper and lower sides, from the right and left sides with the formation of a uniform aerodynamic profile in the longitudinal section, creating lifting power.

EFFECT: increased duration and range of flight.

9 cl, 3 dwg