Unmanned aerial vehicle

Abstract

An unmanned aerial vehicle comprises: a fuselage (1) containing a nose fairing (2) and a load compartment (6), a front and a rear wings (3, 7) attached to the fuselage (1), a front camera (15) and a sighting camera (16) mounted to the fuselage (1), an engine with a propeller (14) mounted on the rear of the fuselage (1), a communication module with an antenna (17) mounted on the fuselage (1). The front wing (3) contains two height rudders (4) and two vertical fins (5) at its ends, the rear wing (7) contains ailerons (8). The unmanned aerial vehicle additionally contains a keel (11) with a directional rudder (12) and an altimeter (18). Said rear wing (7) additionally contains two consoles (9) at its ends, made with the possibility of attaching to it in the process of assembling the UAV. The said fuselage (1) containing the nose fairing (2) and a load compartment (6) is made of flat plywood sheets.

Description

[0001] UNMANNED AERIAL VEHICLE

[0002] The utility model relates to unmanned aerial vehicles (UAVs). More specifically, the utility model relates to biplane-type drones that are designed to perform combat missions, namely, delivering and dropping load over specified distances and military targets.

[0003] BACKGROUND

[0004] Unmanned aerial vehicles (UAVs) are gradually becoming a part of our everyday life: they deliver goods, perform various research, analyse the environment, monitor territories, control objects, take photos and videos, are used in rescue operations, during military operations and find many other applications.

[0005] The patent of Ukraine for utility model No. 142716 discloses an unmanned aerial vehicle containing a fuselage with a propeller, a V-shaped tailplane, a straight wing with an increased extension, characterised in that it comprises a brightness meter for the sky background, the output of which is connected to the input of a brightness control device, which output is connected to the input of a light-emitting device made in the form of spotlight sources, located along the entire length of the landing skids installed under the fuselage, which length is commensurate with the length of the fuselage and is sufficient to illuminate the entire lower surface of the fuselage with the light-emitting device, wherein the light-emitting device is located in such a way that the spotlight is directed to the lower and side surfaces of the unmanned aerial vehicle. Its disadvantages are the relative complexity of the design and insufficient stability of the UAV in flight, which makes it impossible to increase the payload weight to deliver it to the target.

[0006] Iranian-made UAV Shahed 136 (https: / / ru.wikipedia.org / wiki / Shahed 136) is known in the prior art. Shahed 136 is a monoplane according to its aerodynamic design with a triangular wing and is built according to the “tailless” configuration. Containers with such drones can be easily accommodated not only on trucks, but also on train cars, various ships and other vehicles. According to some reports, the effective range of the drone is over 1,000 kilometres with the ability to deliver a 50 kg warhead.

[0007] The maximum flight range is claimed to be 2,000 km, but many experts believe that its actual range is several hundred kilometres. It flies at an altitude of 60 to 4,000 metres with a cruising speed of about 150 to 170 km / h. The drone has a total length of about three metres and a wingspan of just over two metres, weighing about 200 kg. The weight of the warhead is 40 to 50 kg. These UAVs are manufactured for mass use separately or as a group of targets. Disadvantages of the UAVs: It has a 2-stroke engine with a capacity of 50 hp (37 kW), so the “moped-like” sound of the drone can be heard for many kilometres. Therefore, when approaching a target, it is easy to spot it visually and, therefore, try to hit it with all types of available weapons, including small arms. Furthermore, it has a rather inefficient ratio between take-off weight and payload weight.

[0008] Russian UAV ZALA Lancet https: / / ru.wikipedia.org / wiki / ZALA_%D0%9B%D0%B0%D0%BD%D1%86%D0%B5%D1%82) is known in the prior art. Lancet can be used for both combat and reconnaissance missions, with a maximum range of 40 to 50 km, depending on the sub-version, and a maximum take-off weight (MTOW) of about 12 kg. It uses an electric motor to reduce visibility in the audio and thermal ranges, with a maximum flight time of 40 minutes. In combat mode, it can be armed with both high- explosive fragmentation and shaped charge warheads. It has optoelectronic guidance, and even a television guidance unit, which allows the munition to be guided at the final stage of flight. This design was chosen as a prototype. This UAV design has significant drawbacks. In particular, it is a loitering munition and consists of a fuselage and four wings arranged crosswise. This ensures the required overall range and flight duration, and to ensure the large payload weight that the UAV can deliver, it requires a very powerful electric motor and, therefore, a large-capacity battery. Furthermore, the drone is made mainly of composite materials, which increases the cost of its production and makes it difficult to launch mass production at general-purpose industrial enterprises.

[0009] Thus, there is a technical challenge of providing a design of an unmanned aerial vehicle that would have a sufficiently simple design that would allow it to stay stable in the air and deliver a larger payload over longer distances, as well as ensure its relatively small weight and overall dimensions and the possibility of its mass production at general-purpose industrial enterprises.

[0010] STATEMENT OF THE UTILITY MODEL

[0011] The stated technical problem is solved by means of an unmanned aerial vehicle consisting of: a fuselage I containing a nose fairing 2 and a load compartment 6; the front 3 and rear 7 wings attached to the fuselage 1 ; a front camera 15 and sighting camera 16 mounted on the fuselage 1 ; an engine 13 with propeller 14 mounted on the rear of the fuselage 1; a communication module with antenna 17 mounted on the fuselage 1 ; characterised in that the front wing 3 contains two rudders 4 and two vertical fins 5 at its ends; the rear wing 7 contains ailerons 8; additionally contains a keel 11 with a directional rudder 12 mounted thereon, which is made to rotate in a vertical plane, mounted in the fuselage 1 behind said rear wing 7; and an altimeter 18 mounted on the fuselage 1 behind said nose fairing 2; wherein said rear wing 7 additionally contains two consoles 9 at its ends, made with the possibility of attaching to it during the assembly of the UAV in such a way as to provide a ratio of the span of the front wing 3 to the rear wing 7 from 1:1.5 to 1 :2; whereas said fuselage 1, containing the nose fairing 2 and the cargo compartment 6, is made of flat sheets of plywood.

[0012] The technical result of the unmanned aerial vehicle according to the utility model is a UAV having a simple design that allows it to be manufactured quickly and inexpensively, low weight and overall dimensions, increased overall range and duration of flight, and also provides the possibility of its mass production at general-purpose industrial enterprises.

[0013] DETAILED DESCRIPTION OF THE UTILITY MODEL

[0014] Brief description of the figures

[0015] The following figures describe in more detail the design of various embodiments of the unmanned aerial vehicle according to the utility model.

[0016] Figure 1 illustrates a general view of an embodiment of an unmanned aerial vehicle according to the utility model, wherein:

[0017] 1 — fuselage

[0018] 2 — nose fairing;

[0019] 3 — front wing;

[0020] 4 — elevator;

[0021] 5 — vertical fin;

[0022] 6 — load compartment;

[0023] 7 — rear wing;

[0024] 8 — aileron;

[0025] 9 — console;

[0026] 11 — keel;

[0027] 12 — rudder;

[0028] 13 — electric motor;

[0029] 14 — propeller;

[0030] 15 — front camera;

[0031] 16 — sighting camera;

[0032] 17 — communication module with antenna;

[0033] 18 — altimeter.

[0034] Figure 2 illustrates a general view of an embodiment of an unmanned aerial vehicle according to the utility model, wherein: 1 — fuselage

[0035] 2 — nose fairing;

[0036] 3 — front wing;

[0037] 4 — elevator;

[0038] 5 — vertical fin;

[0039] 7 — rear wing;

[0040] 8 — aileron;

[0041] 9 — console;

[0042] 10 — upper keel;

[0043] Ila — lower keel;

[0044] 12 — rudder;

[0045] 14 — propeller;

[0046] 18 — altimeter;

[0047] 19 — cargo compartment with fuel tank;

[0048] 20 — reciprocating engine.

[0049] The claimed UAV is part of a complex that also includes a set of ground equipment sufficient for its operation (means for controlling and configuring the UAV, providing communication with the UAV via secure communication channels, receiving, recording and reproducing the type of information obtained during flights).

[0050] The general features of the claimed UAV : high payload capacity with relatively small dimensions and weight; high speed and manoeuvrability; it can operate in difficult meteorological conditions; relatively short deployment time;

[0051] The aerodynamic design of the UAV according to the utility model is a longitudinal biplane, i.e. it includes two wings (the front wing 3 and the rear wing 7) (see Figures 1 and 2).

[0052] The front 3 and the rear wing 7 of the UAV according to the utility model are unified. The addition of the consoles 9 to the rear wing 7 provides the required ratio of the front to rear wingspan from 1 :1.5 to 1 :2. It provides the UAV with the necessary stability in the air and allows it to deliver the payload to the required distance.

[0053] The fuselage 1 of the UAV according to the utility model is formed from flat sheets of plywood cut using automated equipment and assembled using carpentry tools. The fuselage 1 is then coated with paint or varnish to increase the resistance of the UAV to adverse weather conditions.

[0054] The wings of the UAV according to the utility model are made using the technology of cutting foam with a hot string or forming a profile using a die. The foam is painted or coated with glass fibre cloth impregnated with epoxy resin to provide strength and resistance to weather conditions. To add strength, a spar made of aluminium or carbon fibre composite is installed inside the wing, and ribs made of plywood, composite materials or aluminium are mounted.

[0055] This method can be used to build UAVs with a take-off weight of 1 kg to 3,000 kg.

[0056] In general, the UAV according to the utility model is different from other solutions in terms of ease of assembly, low requirements for personnel qualifications, high flight characteristics, and small dimensions during transportation.

[0057] The UAV’s propulsion system is an engine that provides thrust and orientation of the UAV in the air. The propulsion system does not perform any other functions.

[0058] In one embodiment of the utility model, the engine 13 is an electric motor, and the front camera 15 and the sighting camera 16 are located on the nose fairing 2 of the fuselage 1 (see Figure 1). In this case, the engine is powered by a rechargeable battery located inside the fuselage 1 in the load compartment 6. This UAV modification is also equipped with the altimeter 18, which allows it to fly at an altitude of up to 30 m, avoiding the effects of electromagnetic interference from ground sources. When used, this UAV is usually launched from a launching arrangement. It is also possible to launch a group of drones from an airborne carrier (aircraft), as well as with the help of a tail booster or launch from a moving ground carrier. Tandem warheads consisting of two parts, a break- in and a main charge, are used as payloads. Upon contact with the target, the break-in charge explodes and penetrates the target’s external defences (e.g., its dynamic protection), while the main charge penetrates the main armour and destroys the target. In addition to tandem warheads, high- explosive, thermobaric, fragmentation, incendiary, and combined-action munitions can also be used. The small overall dimensions of the UAV allow it to be transported and carried even by one person.

[0059] In another embodiment of the utility model, the engine is a reciprocating engine, the keel 11 consists of the upper keel 10 and the lower keel I la, and the front camera 15 and the sighting camera 16 are located in the lower part of the fuselage 1 (the latter are not shown in Figure 2). In this case, the engine is powered by a fuel tank located in the load compartment 19 of the fuselage 1. This UAV can be launched from a launching arrangement or using a tail booster, as well as from a runway of 100 m or more. This modification of the UAV according to the utility model is also a loitering munition. Two 122 -mm rounds can be used as payloads, as well as specialised ammunition of various types, and the fuel reserve allows them to be delivered over a very long distance of up to 750 km. This modification of the UAV is equipped with a CRPA GNSS receiver, which allows the drone to be controlled even in dense electronic warfare (EW) conditions. It can also be equipped with a positioning system using optical landmarks, optical odometry, and a flight to radiation source system. This modification of the UAV is also equipped with the altimeter 18, which allows the drone to fly at an altitude of up to 30 m, avoiding electromagnetic interference from ground sources. The UAVs according to the utility model also use other methods of guidance, in particular, flight with guidance using satellite navigation, optical odometry, navigation by visual landmarks, and flight to radiation source.

[0060] Both UAV modifications according to the utility model are inexpensive to manufacture and allow hitting targets with the help of warheads attached to them in conditions when GPS control is not possible due to enemy actions. The UAVs according to the utility model can also easily carry out reconnaissance and combat missions that do not require high operator qualifications and are able to avoid expensive enemy anti-aircraft systems.

[0061] Comparative characteristics of the unmanned aerial vehicles based on existing analogues and the utility model are shown in Table 1.

[0062] Table 1

[0063] As can be seen from Table 1, the UAVs according to the utility model provide a much better ratio between the payload and take-off weight of the UAV than their analogues (maximum 0.43 and 0.25, respectively); as well as a much better ratio between the payload and maximum flight range (maximum 0.057 and 0.042, respectively). Moreover, their cruising and maximum speeds remain comparable.

[0064] Thus, the use of the UAV according to the utility model achieves the desired technical result, namely: the UAV has a simple design compared to its analogues, which, together with the inexpensive materials used in their manufacture, allows them to be put into mass production at general-purpose industrial enterprises. The UAV has an increased overall range and duration of flight, as well as a relatively low weight and overall dimensions.

Claims

UTILITY MODEL CLAIMS1.An unmanned aerial vehicle comprising: a fuselage containing a nose fairing and a load compartment; front and rear wings attached to the fuselage; front camera and a sighting camera mounted to the fuselage; an engine with a propeller mounted on the rear of the fuselage; a communication module with an antenna mounted on the fuselage; characterised in that the front wing 3 contains two height rudders 4 and two vertical fins 5 at its ends; the rear wing contains ailerons; additionally contains a keel with a directional rudder fixed to it, which is made with the ability to rotate in the vertical plane, installed in the the fuselage behind said rear wing; and an altimeter mounted on the fuselage behind said nose fairing; wherein said rear wing additionally contains two consoles at its ends, made with the possibility of attaching to it in the process of assembling the UAV in such a way as to provide the ratio of the wingspan of the front wing to the rear wing from 1 :1.5 to 1:2; wherein the said fuselage containing the nose fairing and cargo compartment is made of flat plywood sheets.

2. An unmanned aerial vehicle according to claim 1, characterised in that the engine is an electric motor and the front camera and the sighting camera are located on the nose fairing of the fuselage.

3. An unmanned aerial vehicle according to claim 1, characterised in that the engine is a reciprocating engine, the keel comprises an upper keel and a lower keel, and the front camera and the sighting camera are located in the lower part of the fuselage.

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