Unmanned aerial vehicle

Abstract

The utility model relates to vertical takeoff and landing (VTOL) aircraft. The unmanned aerial vehicle comprises a fuselage housing an onboard electronics unit, a tail-mounted propeller, and side-mounted left and right consoles, each of which supports a left and right boom, each of which in turn supports two lifting propellers. Additionally, left and right tail stabilizers are mounted on the rear of each boom, interconnected at the top. The forward fuselage contains an air pressure receiver in the form of a combined pneumometric tube, secured to a bracket and connected via static, dynamic, and total air pressure lines to an integrated multifunctional avionics unit.A digital magnetic compass and a two-way half-duplex data exchange radio modem are mounted within the aluminum housing at the bottom of the left wing, while a radio altimeter is mounted on the bottom of the fuselage, under the battery. The tail section of the fuselage houses a processing bay housing an integrated multifunctional avionics unit and a brushless electric motor to generate the thrust required for horizontal flight. Additionally, ailerons, navigation lights, and speed controllers are symmetrically located on the trailing edges of each wing. The technical result of using the claimed unmanned aerial vehicle is increased accuracy in automatic flight mode. 1 fig.

Description

[0001] The utility model relates to vertical takeoff and landing aircraft.

[0002] A vertical takeoff and landing aircraft is known (RU PM 189830), comprising a fuselage, a twin-fin tail unit, chassis, a center section, on-board electrical equipment, as well as control and stabilization systems, the power plant contains four independent electric fan-propulsors, located two symmetrically relative to the plane of symmetry of the aircraft and mounted on profiled pylons, a battery.

[0003] The disadvantage of this solution is that takeoff and landing occurs due to a mechanical change in the direction of the propeller thrust, which requires the use of a special drive to change the tilt of the engines.

[0004] The closest to the claimed technical solution is an unmanned aerial vehicle (RU PM 236 959), consisting of a glider, four propeller-motor units based on electric motors, rigidly attached to the glider, a battery, an on-board control controller, navigation and radio communication equipment, characterized in that the glider does not have controlled aerodynamic surfaces, and the change in the direction of flight in the vertical and horizontal planes occurs due to a change in the thrust of the corresponding propeller-motor units under the control of the on-board controller.

[0005] The disadvantage of this solution is low control accuracy.

[0006] The technical result of using the claimed unmanned aerial device is to increase the accuracy in automatic flight mode.

[0007] The utility model is illustrated by drawings: Fig. 1 - general view of the device.

[0008] The unmanned aerial vehicle comprises a fuselage with an on-board electronics unit located inside it, a propeller for horizontal flight installed in the tail section, left and right consoles installed on the sides, on each of which the left and right beams are fixed, respectively, on which in turn two lifting propellers are installed, in addition, left and right tail stabilizers are installed on the rear part of each beam, connected to each other at the top.

[0009] The fuselage is an aerodynamic shape designed to accommodate the device's on-board and target equipment, housed in compartments. It consists of a nose cone, a central section, and a rear section. The nose cone contains a hatch providing access to the payload. A hatch in the central section provides access to the battery. The main electric motor (MED) is mounted in the rear of the fuselage. The landing gear is mounted in the lower section of the fuselage.

[0010] The nose section of the fuselage houses the air pressure receiver (APR), a combined pneumometric tube designed to sense dynamic air pressure during the aircraft's movement. The APR tube is secured to a bracket and connected via static, dynamic, and total air pressure lines to the integrated multifunctional avionics unit. A quick-release module for mounting and dismounting the payload is located under the payload bay hatch. The payload bay contains a three-axis gimbal system with a video camera, ensuring precise control of the aircraft.

[0011] The battery compartment is located in the central part of the fuselage. The batteries are designed to provide power to the device's onboard equipment.

[0012] The tail section of the fuselage houses a technological compartment that houses an integrated multifunctional avionics unit and a brushless electric motor.

[0013] The integrated multifunctional avionics unit combines the main systems that ensure the operation of the device and contains:

[0014] - autopilot (AP) - performs the functions of controlling all systems of the device, monitoring parameters and exchanging data;

[0015] - on-board power supply controller (OPC) - provides power to all device systems, charges and monitors the state of the instrument battery;

[0016] - module of the angle-measuring global navigation satellite system (UGNSS) - is designed to determine the coordinates and angles of the device's position using (GNSS);

[0017] - inertial navigation system (INS) - allows you to calculate coordinates, position angles, direction and speed of the device in autonomous mode, without the use of external navigation systems;

[0018] - manual control receiver (MCR) - ensures reception of device control signals in manual mode.

[0019] Each wing console contains ailerons, on-board navigation lights (ONL), and speed controllers, which enhance the device's precision. The ailerons are located symmetrically on the trailing edges of the wing consoles and are used to control the device's roll (lateral control channel). The ailerons are controlled by two servos, receiving signals from the automated control system (ACS). The ONL are external lighting equipment and are used to illuminate the device during flight and on the ground. The red ONL is located on the left console, and the green ONL is located on the right console. The speed controllers, designed as brushless motor controllers, are used to control the rotation speed of the lifting propellers. Their primary function is to control the electric motor's operation, including starting, changing speed, direction of rotation, and stopping.

[0020] The digital magnetic compass is designed to determine magnetic azimuth and is mounted inside an aluminum housing on the lower left wing console. The radio modem is located in the left console housing and is designed for two-way half-duplex data exchange over a range of up to 100 km.

[0021] The radio altimeter is located under the battery, attached to the bottom of the fuselage and is designed to determine the flight altitude during takeoff and landing.

[0022] Lifting propellers are designed to generate the thrust necessary for vertical takeoff and landing. The lifting propellers are mounted on electric motors.

[0023] The elevators, which are part of the left and right stabilizers located in the tail section of the aircraft, are designed for longitudinal pitch control. The elevators are controlled by two servos mounted in the left and right stabilizers and connected to the rudder via a pushrod. These servos receive signals from the automatic control system (ACS), providing increased precision in aircraft control.

[0024] Automatic flight control is carried out by an integrated multifunctional avionics unit in accordance with the flight program (flight assignment), signals from the ground control station (GCS) and the navigation system.

[0025] The automatic flight mode is divided into standard navigation algorithm and autonomous.

[0026] Practical implementation example.

[0027] The mini SIGMA UAS was developed. Power is supplied by a battery with a nominal voltage of 44.4 V, consisting of two 30 Ah lithium-ion batteries connected in series. The onboard electronics unit contains a payload module located on the nose of the miniSIGMA UAS, which is replaceable. The onboard electronics unit also contains a command and telemetry radio modem (CTR), which receives and transmits command and telemetry data.

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