RU2812634C1 - Small unmanned aerial vehicle - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: small-sized unmanned aerial vehicle designed to transport a small payload at high subsonic speeds over a distance. In this case, the small-sized unmanned aerial vehicle contains a “tailless” aircraft-type airframe made of composite material, containing a fuselage and a swept-shaped wing. In this case, the wing is made either in the form of easily removable detachable parts with elevons and a vertical tail with rudders mounted on the wingtips, or in the form of parts that are permanently attached to the fuselage and have rotating parts with rudders located on the wingtips. In this case, the aircraft also contains an engine located behind the fuselage on an air intake spacer. The flight control device in the form of a flight navigation complex (FNC) includes an automatic control system that ensures flight according to programmed coordinates, carried out according to inertial system data and global navigation satellite system (GNSS) data, and also ensures autonomous flight, including in the absence of data from GNSS or data substitution (GNSS snuffing). In this case, an electrical control system is used to influence the control elements. The aircraft is also equipped with a parachute for landing.

EFFECT: high flight reliability and high loading factor.

6 cl, 4 dwg

Description

The invention relates to aviation technology, and more precisely to unmanned aerial vehicles (UAVs).

A number of unmanned aerial vehicles of various capabilities are known.

An unmanned aerial vehicle (UAV) is known, containing a fuselage, a power plant, including one or more air-breathing engines (WRE) with thrust vector deviation, tail surfaces, load-bearing planes, landing gear, a control system that simultaneously implements aerodynamic and traction-torque control of the movement of the vehicle and the angular position of its construction axis in space, and on-board equipment. The device has a short trapezoidal wing. The invention is aimed at expanding functionality by increasing maneuverability (Pat. RU 2181333 C2, (51) IPC B64D 27/20, B64D 33/02). Due to the large amount of mechanization and oversized vertical tail, the UAV has a low weight return and, therefore, a high operating cost. The control system does not exclude the negative impact of radio communication interference and the possibility of unauthorized flight control.

There is a well-known complex of small-sized air targets E95 developed and manufactured by JSC Enics, Kazan (http://www.enics.ru). This complex includes a small-sized radio-controlled aerial target E95M, made in the form of a UAV, with a pulsating air-jet engine. The UAV of this complex has an aerodynamic design with a straight, high aspect ratio wing, which does not provide the aircraft with sufficient speed and maneuverability. In addition, the flight of this UAV is carried out with GNSS correction, but the command radio line of the device does not have protection against GNSS snooping, which reduces reliability and increases the risk of an abnormal flight.

There is a known multi-mode unmanned aerial vehicle with an aerodynamic design, low-wing, with an overhead engine, having traction and geometric characteristics that allow the device to fly in a wide range of speeds (values not specified). The main feature of this device is a support in the form of an elastic landing ski located in the lower part of its body. (Pat. RU 2327604 C1, MPK V64S]. The low-wing design has a higher aerodynamic drag of the aircraft compared to other designs due to unfavorable mutual influence (interference). In addition, this design has disadvantages in the form of a diving moment arising due to the large distance between the center the mass of the device and the thrust axis of the engine, which must be compensated.In addition, the use of a ski chassis in this configuration eliminates the possibility of landing the device on most surfaces.

A small-sized unmanned aerial system is known, including a modular aircraft-type UAV. (Pat. RU 2473455 C2, (51) IPC, V64S 39/02). The system is designed for aerial surveillance and reconnaissance with the ability to transmit information received by on-board sensors of an unmanned aerial vehicle to a ground control station in real time. The UAV has a power plant located in the fuselage and equipped with an engine with a propeller. The horizontal flight speed of an unmanned aerial vehicle is low and amounts to 60-110 km/h, the maximum flight altitude above sea level is up to 3000 meters, flight duration is up to 1.5 hours, range of action is up to 70 kilometers.

There is a wide variety of UAVs of various types. Almost all aircraft layouts and types of fuselages that are found in manned aircraft are also applicable in unmanned aircraft, but the designs, power plants, and control systems are designed to solve the specifics of a specific task.

The present invention is based on the task of creating a small-sized unmanned aerial vehicle intended for use at a considerable distance (150-180 km) at high subsonic speed (650-750 km/h) with a small payload (10-12 kg) with high control reliability flight while eliminating the possibility of unauthorized control and reducing flight operating costs.

The technical result is high flight reliability and high weight return.

The problem is solved and the technical result is achieved by the fact that the small-sized unmanned aerial vehicle UAV contains: a “tailless” aircraft-type airframe made of composite material, containing a fuselage and a swept-shaped wing with contours formed by NASAM airfoils, while the wing can have easily removable detachable parts with elevons, vertical tail with rudders mounted on the wingtips, or be permanently attached to the fuselage, and have rotating parts of a symmetrical profile; engine located behind the fuselage on an air intake spacer; a flight control device in the form of a flight navigation complex that provides autonomous flight according to programmed coordinates, using data from on-board inertial sensors and GNSS data, excluding the possibility of unauthorized flight control, while an electrical control system is used to influence the control elements.

The wing, which has detachable parts with elevons, vertical tail with rudders, can be made with an aerodynamic twist around the longitudinal axis of the wing up to - 2°

It is advisable for the detachable part of the wing to be easily removable; its fastening is carried out by means of a moment unit formed by fixing the tubular spar of the detachable part of the wing in the fuselage bushing with a pin element and additionally, by means of a unit that receives a shearing load, made in the form of a short pin extending from the detachable part of the wing inserted into bushing fixed in the fuselage.

This invention is further explained by a description of its implementation and is accompanied by drawings, in which:

in fig. Figure 1 shows a version of the UAV with a detachable part of the wing (isometric view)

in fig. 2 view of the UAV Fig. 1 in projections: in Fig. 2a shows the UAV (side view) in FIG. Fig. 2b shows the UAV (front view); Fig. 2c shows the UAV (plan view)

Fig.3 shows a fragment of the UAV Fig.1 illustrating the connection of the fuselage and the detachable part of the wing

fig. Figure 4 shows a version of the UAV with a folding wing part:

in fig. 4a shows a UAV (plan view);

in fig. Figure 4b shows the UAV (front view), illustrating the wing folding.

A small unmanned aerial vehicle (UAV), according to the invention, is designed as follows.

The aerodynamic design of the unmanned aerial vehicle is a tailless aircraft-type glider (monoplane) with a swept wing with a span of about 2 meters made of composite material, containing a fuselage 1 and a swept wing with contours formed by NASAM airfoils.

The wing, in one embodiment, may have easily removable detachable parts with elevons, vertical tail surfaces with rudders mounted on the wing tips, which is further described and illustrated in Fig. 1-3, or, in another embodiment, be permanently attached to the fuselage, and have rotating parts of a symmetrical profile, which is further described and illustrated in Fig. 4. Both options provide stability and controllability of the device in flight.

Fuselage 1 contains an instrument compartment, a payload compartment, fuel system lines and control systems. In the detachable part of the wing 2 there is a fuel tank (not shown in the drawings).

T-10-14 material with ED-20 binder can be used as a composite material.

The UAV will have an engine 7 located behind the fuselage 1 on the spacer-air intake 6.

The engine 7 is a turbojet or piston engine.

A piston engine has a fuel consumption lower than a turbojet, this allows it to achieve a maximum flight range (up to 200 km), relative to a turbojet (up to 170 km). The air intake spacer 6 is adapted to the specific type of engine 7 mounted on it.

The flight control device is made in the form of a flight navigation complex (FNC), including an automatic control system that ensures flight according to programmed coordinates using data from onboard inertial sensors and GNSS data. In this case, an electrical control system is used to influence the control elements. The control device operates autonomously and eliminates the possibility of unauthorized flight control.

The UAV has its own launch device in the form of a launcher. The launcher can be made in the form of a pneumatic pulley system, providing an initial flight speed of 20 m/s.

In fig. 1 and fig. Figure 2 shows an unmanned aerial vehicle with a wing version with a detachable part. Easily removable detachable parts 2 of the wing with elevons 3 are attached to the sides of the fuselage 1. At the tips of the detachable parts 2, a vertical tail 4 is installed at a transverse angle, containing a rudder 5.

In fig. Figure 3 shows the fastening of the detachable part of the wing 2 with the fuselage 1 by means of a moment unit, which is formed by fixing with a pin element 10 the tubular spar 8 of the detachable part of the wing in the fuselage sleeve 9 and the second unit formed by fixing a short pin (not shown) extending from the detachable part of the wing in

Examples of UAV embodiments are discussed in more detail below.

The small-sized unmanned aerial vehicle has the following parameters:

In one version, the wing is swept-shaped, with an aerodynamic twist around the longitudinal axis of the wing up to -2°, contours formed by NASAM-6 mod airfoils. С=9.7% and NASAM-6 С=12% with large sweep along the leading edge. This makes it possible to optimize flow stall, as well as to realize small values of relative wing thicknesses at large values of absolute wing heights, especially in the root part, which reduces the increase in drag force.

This design produces the best aerodynamic lift, allowing for maximum aerodynamic efficiency and high maneuverability.

The detachable part of the wing is made easily removable by means of a moment unit formed by fixing the tubular spar 9 of the detachable part of the wing in the fuselage sleeve 10 with a cotter pin element 8 and additionally, by means of a unit that receives a cutting load, made in the form of a short pin 11, coming out of the detachable part of the wing inserted into the sleeve fixed in the fuselage (Fig. 3).

A vertical tail 4 is fixed to the wing tips at an angle of 99 degrees, which has rudders 5 with the following parameters:

The UAV's roll and pitch control is implemented by elevons 7 with the following parameters:

Fuselage 1 contains an instrument compartment, a payload compartment, fuel system lines and control systems.

The UAV airframe is made of composite material. T-10-14 on ED-20 binder.

The payload compartment is located in the forward part of the fuselage 1 and has dimensions: diameter 122 mm, length 600 mm. The maximum payload weight in the form of cargo or monitoring equipment is no more than 12 kg.

Engine 7 is a turbojet with a thrust of 20 to 40 kgf and is located behind the fuselage. This arrangement minimizes aerodynamic drag and contributes to achieving cruising speeds of up to 700 km/h, maneuverability and 8G overload.

The flight control device is made in the form of a flight navigation complex (FNC), located in the middle part of the fuselage 1, and includes an autonomous flight program according to pre-programmed coordinates for a certain number of intermediate flight points, according to data received from GNSS and according to inertial sensors.

Protection against interference and exclusion of the possibility of unauthorized flight control (GNSS-snoofing) is implemented as follows: in the absence of data from GNSS or substitution of this data (sharp change in one’s own coordinates or coordinates of specified points), the flight is carried out using inertial sensors of the PNK. Thus, during the further flight, the data received from the GNSS are compared with the calculated coordinate values, taking into account the movement of the UAV. If the calculated coordinate values coincide with those newly received from the GNSS, within the error limits of the automatic control system, the flight continues with GNSS correction. At the same time, an electrical control system is used to influence the control elements.

In fig. 4 shows a UAV with a different wing design. The UAV has a wing that is permanently attached to the fuselage 1 and has rotating parts 12 of a symmetrical profile that can be folded and detached. Increasing weight transfer and minimizing aerodynamic drag in this embodiment is possible due to the fact that instead of the vertical tail 4, the stability and controllability of the vehicle after launch is ensured by the rotating part 12 of the wing, which has a symmetrical profile. As speed increases, the required wing area decreases quadratically.

The wing design makes it possible to optimize flow stall, as well as to realize small values of relative wing thicknesses at large values of absolute wing heights, especially in the root part, which reduces the increase in drag force.

The design also generates aerodynamic lift in the best possible way, which maximizes aerodynamic efficiency and ensures high maneuverability.

The aerodynamic design of the wing and the aerodynamic layout of all mechanisms together make it possible to achieve the required flight characteristics with a minimum number of mechanization elements and the weight of the UAV, harmonize the stability, aerodynamic control and maneuverability of the UAV while increasing weight efficiency, and, consequently, reducing the cost of operation. The above can help achieve high weight yield (about 25%).

The launcher is made in the form of a pneumatic pulley system, providing an initial flight speed of 20 m/s. To ensure the mobility of the UAV, the launcher is transported and used for its intended purpose mounted on a chassis (trailer or KAMAZ vehicle). In this case, the UAV is transported in a container with detachable part 2, vertical tail 4, detachable rotating parts 12 and connectors of the fuel system and control system lines. This allows the UAV to be launched from almost any location, ensuring high mobility rates.

The invention makes it possible to achieve high flight reliability by excluding the possibility of unauthorized flight control by protection from interference and GNSS snuffing, while simultaneously achieving high weight output, and, consequently, reducing operating costs.

The invention can be used to transport cargo weighing up to 12 kg over a distance of up to 200 km, at a speed of up to 750 km/h. The invention can also be used to solve other problems, for example, to monitor various objects, in a wide range of speeds, at a considerable distance.

Claims (6)

1. A small-sized unmanned aerial vehicle designed to transport a small payload at high subsonic speed over a distance, characterized in that it contains: a “tailless” aircraft-type glider made of composite material, containing a fuselage and a swept-shaped wing, wherein the wing is made either in the form easily removable detachable parts with elevons and vertical tail surfaces with rudders mounted on the wingtips, or in the form of parts that are permanently attached to the fuselage and have rotating parts with rudders located on the wingtips, wherein the aircraft also contains an engine located behind fuselage on an air intake spacer; flight control device in the form of a flight navigation complex (FNC), including an automatic control system that ensures flight according to programmed coordinates, carried out according to inertial system data and global navigation satellite system (GNSS) data, and also ensures autonomous flight, including in the absence data from GNSS or data substitution (GNSS snuffing), while an electrical control system is used to influence the control bodies; The aircraft is also equipped with a parachute for landing. 2. A small-sized unmanned aerial vehicle according to claim 1, characterized in that the wing has detachable parts with elevons, a vertical tail with rudders, and is made with an aerodynamic twist around the longitudinal axis of the wing up to - 2°. 3. A small-sized unmanned aerial vehicle according to claim 1, characterized in that it contains an instrument compartment, a payload compartment, fuel system lines and control systems located in the fuselage, and a fuel tank located in a detachable part of the wing. 4. A small-sized unmanned aerial vehicle according to claim 1, characterized in that the detachable part of the wing has an easily removable fastening by means of a moment unit formed by fixing the tubular spar of the detachable part of the wing in the fuselage bushing with a cotter pin element and additionally, by means of a unit that perceives shearing load, made in the form a short pin extending from a detachable part of the wing, inserted into a bushing fixed to the fuselage. 5. A small-sized unmanned aerial vehicle according to claim 1, characterized in that the T-10-14 material with an ED-20 binder is used as a composite material. 6. A small-sized unmanned aerial vehicle according to claim 1, characterized in that it uses a turbojet or piston engine.

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