RU69839U1 - UNMANNED AIRCRAFT WITH TWO TURNING ENGINES - Google Patents

Abstract

An unmanned aerial vehicle with two rotary engines relates to aircraft, in particular to unmanned aerial vehicles of vertical take-off and landing. The objective of the utility model is to improve the technical characteristics of effective UAV control while increasing its flight speed. The technical result that can be obtained using the utility model is to expand the range of UAV application by increasing speed and reducing traction loss during UAV control. The task is achieved in that the combined unmanned aerial vehicle contains a free-flying wing, a propulsion system and a payload. In this case, the apparatus has two rotary engines located symmetrically with respect to the axis of the apparatus and outside it, each rotary engine consisting of a screw, connecting brackets and a cylindrical body, which is connected to an engine drive, with each engine having an independent controllable drive. The main advantages of a combined unmanned aerial vehicle are the absence of thrust loss during UAV flight control, which increases the efficiency of UAV control; UAV flight control performance is determined only by the characteristics of the engine drive; higher UAV flight speed, determined only by the characteristics of the engines; the ability to place any special equipment in the internal volume of the UAV wing; the ability to take off and land UAVs on any hard surface, as well as providing a hover mode over any inaccessible terrain (water, swamp, sand, mountains, forest, ravine, etc.). 1 ill.

Description

The utility model relates to aircraft, in particular to unmanned aerial vehicles of vertical take-off and landing.

Recently, there has been growing interest in the use of unmanned aerial vehicles (UAVs) for solving a variety of tasks, the fulfillment of which by manned aircraft, for various reasons, is impractical.

The main areas of use of UAVs include:

- Remote environmental monitoring with automatic sampling of environmental elements from inaccessible places with visual monitoring of measurements and sampling sites, as well as their delivery to the place of analysis.

- High efficiency and effectiveness of search and rescue operations (the state of facilities and the extent of destruction, hazardous areas and fires, accidents, natural disasters, technological disasters and identifying victims in them).

- Monitoring of sea and river highways and water bodies (poaching), environmental monitoring and control of facilities and routes for the production, production and transportation of electric energy, natural gas, crude oil and its processed products, hazardous chemicals and other substances.

- Continuous and covert intelligence (military, radiation, chemical, biological) in real time and visual data transmission to the operator’s monitor.

- Prevention of attempts to carry out terrorist acts at nuclear power plants, hydroelectric power stations, thermal power plants, radiation, chemical and biological and other hazardous facilities (the consequences of which can be comparable to the use of weapons of mass destruction), as well as the identification and prevention of attempts to steal natural gas, crude oil, oil products.

- Patrolling (land and water) borders, military, administrative, economic facilities, large industrial enterprises with dangerous production, monitoring strategic (rail and road) highways, monitoring mobile facilities and population groups, monitoring and ensuring security during mass events (at stadiums, squares, summits, olympiads, etc.) with the use of (non-target designation or directly from the UAV) non-lethal

deterrents.

- Direct participation in the fight against terrorists, as well as participation in hostilities and military conflicts.

- Covert patrolling and guarding the territory of important military installations, capturing targets and / or target designation, collecting data, organizing communications and transmitting data, launching false targets, escorting military and dangerous goods, as well as guiding missiles guided by warheads and rockets at the end of the flight path .

- Geological exploration, remote monitoring of volcanic or seismic activity

- Notification of the occurrence and development of accidents, natural disasters or dangerous situations in controlled areas, identification of the operational situation and the presence of victims in criminogenic places (areas closed to access, places where crimes are committed), as well as from places of chemical infection, etc.

The most widespread are the designs of UAV aircraft and helicopter circuits. Also promising is the screw-in-ring design.

The disadvantages of most UAV aircraft schemes (for example, patent No. 2181333 dated 04/20/2002 "Unmanned multi-mode highly maneuverable aircraft", IPC B64D 27/20, B64D 33/02) are:

- the need for a runway;

- lack of hanging mode.

These shortcomings are eliminated in the helicopter scheme, for example, patent No. 2021165 from 10/15/1994. “A control method for a remotely piloted vehicle and a control system for its implementation”, IPC V64C 29/00, V64C 15/00. However, most of them are characterized by the following disadvantages:

- with a large specific load, the flow from the rotor will be so strong that it will not allow operation under the rotor;

- high fuel consumption;

- low speed in the horizontal direction.

Partially, these disadvantages are eliminated in the screw-in-ring design. However, for this type of UAV, a characteristic drawback is the high aerodynamic drag due to the placement of a large number of special equipment, which leads to a decrease in the flight speed of the UAV. For example, “Aircraft of vertical take-off and landing” according to patent No. 2089458 of 09/10/1997, IPC В64С 29/00.

The closest in principle and technical essence of the claimed device is "Unmanned aerial vehicle" according to patent No. 2288140 from

11/27/2006, IPC В64С 39/00. It contains a free-carrying wing equipped with aerodynamic controls, vertical tail, a nacelle and one engine with a propeller. The engine is installed in the engine nacelle. The unmanned aerial vehicle is made according to the fuselage-free aerodynamic scheme "flying wing".

One of the drawbacks of this engine is the presence of traction loss when using the aerodynamic controls of UAV flight, because they are solid shields, representing a large aerodynamic drag. The use of gas-dynamic controls are effective only at high flight speeds.

The objective of the utility model is to improve the technical characteristics of effective UAV control while increasing its flight speed

The technical result that can be obtained using the utility model is to expand the range of UAV application by increasing speed and reducing traction loss during UAV control.

The task is achieved in that the combined unmanned aerial vehicle contains a free-flying wing, a propulsion system and a payload. In this case, the apparatus has two rotary engines located symmetrically with respect to the axis of the apparatus and outside it, each rotary engine consisting of a screw, connecting brackets and a cylindrical body, which, through a shaft mounted in a cylindrical bushing, is rigidly fixed to the free-carrying wing of the apparatus and connected to an engine drive, with each engine having an independent controllable drive.

Figure 1 shows a top view of the UAV, and figure 2 shows a side view of the UAV with the plane of the rotary engine screws parallel to the axis of the UAV, figure 3 shows a top view of the UAV, and figure 4 shows the side view of the UAV with the plane of the screws rotary engine perpendicular to the UAV axis,

where: 1 - free-standing wing;

2 - engines;

3 - stabilizer;

4 - a nose fairing;

5 - screw;

6 - connecting brackets;

7 - a cylindrical engine housing;

8 - shaft;

9 - a cylindrical sleeve;

10 - stabilizer mounting rods;

11 - wheels.

The combined unmanned aerial vehicle is made according to the fuselage-free aerodynamic scheme "flying wing". It consists of the following main elements: wing 1, engines 2 and stabilizer 3.

Freestanding wing 1 is designed to accommodate and fasten all components of the apparatus. A nose fairing 4 is installed in front of the apparatus, inside of which are placed elements of functionally interconnected electronic monitoring equipment, a transceiver unit, a transceiver antenna, a flight-navigation system, etc.

The front part of the wing 1 has a shape providing minimal aerodynamic drag. Inside the wing, only special equipment is fixed, which, depending on the purpose of the UAV, can be different. For example, for environmental purposes, equipment can be represented by samplers, gas analyzers, etc.

The propulsion system consists of two rotary engines 2 located symmetrically with respect to the axis of the apparatus and outside it. Each rotary engine consists of a screw 5, connecting brackets 6 and a cylindrical body 7, which, through a shaft 8 installed in a cylindrical sleeve 9, rigidly fixed to the free-carrying wing of the apparatus, is connected to the motor drive. Moreover, each engine 2 has an independent controllable drive. Each rotary engine 2 performs the functions of both marching and lifting engines.

The stabilizer 3 is designed to shift the center of pressure away from the center of mass, which provides a margin of static stability. Since the center of mass of the aircraft is located in front of the center of pressure of the wing 1, an increase in the angle of attack, for example, due to a gust of wind, will cause an increase in lift. In this case, an additional moment will arise on the aircraft relative to the center of mass, causing a dive. As a result of the dive, the angle of attack decreases and the given flight direction is restored. The stabilizer 3 is made in the form of a plate, fastened with the help of connecting rods 10 to the wing 1 at a small angle, which is necessary to create a lifting force that ensures the planning flight of the UAV.

The UAV in the initial state can be installed or progressively move on a solid surface using wheels 11. At the initial position,

deployment of a ground-based remote control center for an unmanned aerial vehicle. In addition, pre-flight UAV preparation is carried out.

The UAV can operate in the following modes: launch, flight, hover and landing.

The mode is “Launch”. UAV launch can be carried out both from a mobile and stationary launcher. In this case, the plane of the screws 5 are parallel to the axis of the UAV (Fig.1-2). The start of rotary engines 2 at start is carried out automatically or at the command of the operator. When starting the UAV, rotary engines 2 begin their work at the same time. As soon as the total thrust created by rotary engines 2 exceeds the starting weight of the UAV, it breaks away from the surface and begins to climb to gain the desired height. Since the axis of the shafts of the rotary engines 2 pass through the center of mass of the UAV, the apparatus is statically stable during its rise. In this mode, rotary motors 2 act as a lifting motor. It should be noted that the launch of the UAV does not require a runway.

The mode is “Hanging”. If necessary, the UAV hangs in the air above a given point (Fig.1-2). For this, rotary engines 2 operate in such a way that the UAV is located above a given point on the surface. In this case, the total thrust created by the rotary engines 2 should be equal to the starting weight of the UAV.

The mode is “Flight”. To implement this regime, it is necessary to give a command from the control system to rotate the engines 2 by 90 °. The plane of the screws 5 are perpendicular to the axis of the UAV (Fig.3-4). This position of the engines 2 allows to achieve high flight speed of the UAV,

UAV flight can take place in accordance with the flight task both according to a given program, and according to radio commands transmitted by the operator from a ground-based remote control point. The ground-based remote control station generates commands transmitted over the air to the on-board electronic equipment installed on the UAV. These commands control the flight of the aircraft using the flight-navigation system, as well as remote viewing of the terrain and the transmission of video and telemetry information via a transmit-receive antenna and a transmit-receive unit to the ground control station.

UAV flight control both in direction (pitch, yaw and rotation angles), and modulo (change in flight speed) is carried out by synchronous rotation of engines 2, rotation of only one of them or a corresponding change in the number of revolutions of these engines (one of the engines).

The developed UAV is economical. This is achieved by its shape, which reduces

its aerodynamic drag. The stabilizer 3 together with the free-flying wing 1 allows the UAV to plan.

The mode is “Landing”. UAV landing is carried out with decreasing speed of both rotary engines 2 (Fig.1-2). At the same time, the UAV lands smoothly. It should be noted that the UAV does not require a runway to land.

The main advantages of the combined unmanned aerial vehicle are:

- the absence of traction loss in the process of UAV flight control, which increases the efficiency of UAV control;

- the speed of UAV flight control is determined only by the characteristics of the engine drive;

- higher UAV flight speed, determined only by the characteristics of the engines;

- the ability to place any special equipment in the internal volume of the UAV wing;

- the ability to take off and land UAVs on any hard surface, as well as providing a hover mode over any inaccessible terrain (water, swamp, sand, mountains, forest, ravine, etc.).

Claims (1)

An unmanned aerial vehicle with two rotary engines, including a free-flying wing and an engine, characterized in that the device has two rotary engines located symmetrically about the axis of the device and outside it, each rotary engine consists of a screw, connecting brackets and a cylindrical body, which a shaft mounted in a cylindrical bushing, rigidly fixed to the free-carrying wing of the apparatus, is connected to the engine drive, with each engine being independently controlled the first drive.