RU2763896C1 - Multipurpose unmanned aerial vehicle - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: invention relates to the field of aviation, in particular to unmanned aerial vehicles (UAVs), and can be used in the development of UAV designs using the "flying wing" aerodynamic scheme. The nose of the UAV is raised above the surface of the hull, on it there is a horizontal wing with a tail, at the tips of which two engines are located in the swivel nacelles. In the bow there is a satellite navigation system, a communication and control system, optical observation devices in the visible and infrared ranges, in the lower and upper hemispheres, a small-sized radar (SSR), and a laser rangefinder. In the tail section there are two inclined keels with vertical tail. The upper surface of the body is a solar battery connected to a battery in the body, there is also a closed cargo compartment. At the bottom, the hull is equipped with multi-wheeled non-retractable chassis.

EFFECT: lift force, maneuverability and controllability in flight are increased. The possibility of using the ground effect in flight, prolonged stay in the air and replenishment of energy reserves in flight is provided.

1 cl, 2 dwg

Description

The invention relates to the field of aviation, in particular to unmanned aerial vehicles (UAVs), and can be used in the development of UAV designs using the "flying wing" aerodynamic scheme, which can be widely used, in particular, in monitoring the earth and water surface, cargo transportation , reconnaissance, search, in emergency situations to ensure effective management and obtaining operational information.

Known unmanned aerial vehicle (patent RU No. 107126 of 2011), including a fuselage, a wing with controls, an engine and a propeller, the wing is made from the condition of using the aerodynamic scheme "flying wing", while the fuselage is located in the bow of the UAV in contact with leading edge of the wing, and the engine - in the tail section of the UAV in contact with the trailing edge of the wing.

The disadvantage of this device is the presence of the fuselage, as an element that is not involved in the creation of lift, while the fuselage creates additional friction losses - it increases the drag of the aircraft, which worsens the takeoff and landing characteristics of the UAV (increases the takeoff run). The use of a pushing screw necessitates high-precision balancing of the apparatus.

The closest in technical essence to the claimed invention is a short takeoff and landing unmanned aerial vehicle (RU patent No. screw, and controls, the wing in the bow is equipped with a power plant and controls made in the form of front horizontal tail and front vertical tail, while the power plant, front horizontal tail and front vertical tail are placed above the upper surface of the wing on a support with the possibility of blowing propeller of the upper surface of the wing and controls.

The disadvantage of this device is that when performing a short takeoff and landing, carried out at high angles of attack, the speed of the aircraft decreases and the characteristics of its maneuverability - stability and controllability - deteriorate. To keep the aircraft at the lowest speed, the highest value of lift is required. However, an increase in the lift coefficient by increasing the angle of attack is possible only up to the critical value of the angle of attack. An increase in the angle of attack above the critical one leads to a stall on the upper surface of the wing and to a sharp decrease in the lift coefficient, which is unacceptable.

The objective of the invention is to create a design of an unmanned aerial vehicle, which will provide the possibility of increasing the lifting force, increasing the maneuverability and controllability of the aircraft in flight, the possibility of using the screen effect in flight, the possibility of a long stay in the air and making long flights using electric motors and replenishing electricity reserves in flight , the ability to deliver various types of payload to a given point on the route.

The required technical result is achieved by the fact that the multi-purpose unmanned aerial vehicle contains a forward-swept wing made according to the "flying wing" scheme (3), a power plant with a propeller (9), the nose of the unmanned aerial vehicle is raised above the surface of the hull, on it is located a horizontal wing (2) with a horizontal tail, on the tips of which in the rotary nacelles (1) there are two electric motors with a propeller, in the bow there is a satellite communication and navigation system GPS / GLONASS (7), a control system, optical observation devices (8 ) in the visible and infrared ranges, in the lower and upper hemisphere, a small-sized radar (9), a laser rangefinder, in the tail part of the body there are two inclined keels (6) with vertical tail, the upper surface of the body is a solar battery (5) connected to battery located in the body of the unmanned aerial vehicle, there is also closed cargo compartment (4), at the bottom of the body is equipped with multi-wheel non-retractable landing gear (11) with protected fairings (10).

The essence of the invention is illustrated by the drawing, where in Fig. 1 shows a multi-purpose unmanned aerial vehicle, which includes:

1 - rotary nacelles with engines;

2 - horizontal wing;

3 - wing body;

4 - cargo compartment;

5 - solar battery;

6 - inclined keel;

7 - satellite communication and navigation system GPS/GLONASS;

8 - optical observation devices.

On FIG. 2 is a right side view of a multipurpose unmanned aerial vehicle, where:

1 - rotary nacelles with engines;

2 - horizontal wing;

3 - wing body;

6 - inclined keel;

7 - satellite communication and navigation system GPS/GLONASS;

8 - optical observation devices;

9 - small-sized radar;

10 - chassis fairings;

11 - multi-wheel non-retractable landing gear.

The invention works as follows: takeoff of a multi-purpose unmanned aerial vehicle is carried out by turning the rotary nacelles with engines (1) into a vertical position in the takeoff engine mode. When the engines gain enough power to take off, the aircraft takes off in a vertical position. Further, due to the rotation of the nacelles with engines (1) and the mechanization of the wing, a horizontal movement is given, an additional lift force is created from the pressure difference on the upper and lower surfaces of the wing due to the blowing of the upper surface of the wing with a propeller.

Such a takeoff is carried out in the absence of runways of sufficient length. In the presence of runways, takeoff is carried out with a takeoff run with a horizontal arrangement of rotary nacelles with engines (1) to save battery power. In the cruising flight mode, blowing the upper surface of the wing and controls can significantly improve the maneuverability of the aircraft by increasing the efficiency of the controls in pitch, roll and yaw in a wide range of angles of attack.

During the flight, it is possible to give a multi-purpose unmanned aerial vehicle, depending on the tasks being solved, various motion parameters. Altitude and speed of flight for the effective use of means of observation, destruction and flight until the mission is completed or energy resources are exhausted. To increase the range and duration of the flight, an aircraft made according to the “flying wing” scheme can use the screen effect - the effect of a sharp increase in the wing lift and other aerodynamic characteristics of the aircraft when flying near a screening surface (water, earth, etc.)

Landing with a short run is carried out by turning the rotary nacelles with engines (1) into a vertical position and reducing engine speed. The presence of multi-wheeled non-retractable landing gear (11) protected by fairings (10) makes it possible to land on both ordinary and snow-covered sites and water. When landing on snow, multi-wheel non-retractable landing gear (11) work like skis, and are protected from mechanical damage by fairings (10). When landing on water, the multi-wheel non-retractable landing gear (11) act as additional floats.

During the flight of a multi-purpose unmanned aerial vehicle, it is possible to carry out visual observation along the flight route using optical observation devices (8) in the visible and infrared ranges, in the lower and upper hemisphere, radar surveillance of a small-sized radar station (9), determining the range to detected objects using laser rangefinder. The image of the detected objects and their coordinates are transmitted via the GPS/GLONASS satellite communication and navigation system (7) to the control point, which controls the flight parameters and the use of the payload placed in the closed cargo compartment (4) through the control system. The payload can be means of destruction, various types of small-sized ammunition, detection means, drop sensors, sonar buoys, etc., means of setting passive and drop stations of active jamming, and other known means.

The flight of the aircraft is carried out using two electric motors with a propeller. The electric motors are powered by a solar battery (5) on the upper surface of the body and a battery located in the body of the unmanned aerial vehicle. During the flight, it is possible to charge the battery.

Claims (1)

A multi-purpose unmanned aerial vehicle containing a forward-swept wing made according to the "flying wing" scheme, a power plant with a propeller, characterized in that the nose of the unmanned aerial vehicle is raised above the surface of the hull, a horizontal wing is located on it, having an empennage, on the tips of which two engines are located in the rotary nacelles, in the bow there is a GPS / GLONASS satellite navigation system, a communication and control system, optical observation devices in the visible and infrared ranges, in the lower and upper hemispheres, a small-sized radar, a laser rangefinder, in the tail part of the hull there are two inclined keel with vertical tail, the upper surface of the hull is a solar battery connected to a battery located in the hull of an unmanned aerial vehicle, there is also a closed cargo compartment, at the bottom of the hull is equipped with multi-wheel fixed landing gear.

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