RU71960U1 - UNMANNED AIRCRAFT WITH FOUR TURNING ENGINES - Google Patents

Abstract

An unmanned aerial vehicle with four rotary engines, consisting of a free-flying wing, a control system, a propulsion system and a payload, characterized in that the propulsion system consists of four rotary engines located symmetrically about the axis of the aircraft and outside it, rigidly connected by axes to the glider and independently operating from a single control system, and the engines are located in such a way that the center of mass of the apparatus is symmetrically between the axes of the engines, and the control system The phenomena and elements of power and drive of the propulsion system uniformly occupy the entire free volume of the free-carrying wing, and the payload is placed on the surface of the wing.

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 many tasks that are not practical for manned aircraft for various reasons.

The main areas of use of UAVs include:

• Remote environmental monitoring with automatic sampling of environmental elements from hard-to-reach 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 (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 ponds (identifying poaching on them), environmental monitoring and control of facilities and routes for the production, extraction and transportation of electric energy, natural gas, crude oil and its refined 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 with the use of weapons of mass destruction), as well as the identification and prevention of attempts to steal natural gas, crude oil, and petroleum 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.) using non-lethal means of deterrence (by designation or directly from the UAV).

• 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, and 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 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 V64C29 / 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.

Partially, these shortcomings were eliminated in an unmanned aerial vehicle according to patent No. 2288140 dated November 27, 2006, IPC ВСС 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. Unmanned aerial vehicle is made on the fuselage-free

aerodynamic design "flying wing".

However, one of the disadvantages of this engine is the low margin of static stability, which leads to its unstable position during take-off, when the stabilizer is still ineffective. In addition, not all UAVs can be used.

The closest in principle of operation and technical nature of the claimed device is “Unmanned aerial vehicle with two rotary engines” according to application No. 2007136130/22 (039514), which decided to issue a patent of the Russian Federation of November 15, 2007 for a utility model. However, this UAV does not completely eliminate the unstable situation during take-off, landing and in the event of disturbing factors.

The objective of the utility model is to increase the stability margin and expand the technical characteristics.

The technical result that can be obtained using the utility model is to expand the range of UAV application by placing special equipment or a person on the outer surface of the carrier wing.

The task is achieved in that the unmanned aerial vehicle is a freestanding wing with four rotary engines, a control system, a propulsion system and a payload. In this case, the propulsion system consists of four rotary engines located symmetrically with respect to the axis of the apparatus and outside it, rigidly connected by axes to the glider and independently controlled from a single control system, and the engines are located so that the center of mass of the apparatus is located symmetrically between

engine axles, and the control system and power components of the propulsion system uniformly occupy the entire free volume of the free-standing wing, and the payload is placed on the wing surface.

Figure 1 shows a top view of the UAV, and figure 2 shows a side view of the UAV, where: 1 - free-standing wing;

2-rotary engines;

3 - a nose fairing;

4 - lifting screw;

5 - skeg;

6 - sleeve;

7- engine mount rods;

8 - wheels;

9 - control system.

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

Freestanding wing 1 is designed to accommodate and fasten all components of the apparatus. A nose fairing 3 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 free-flying wing 1 has a shape that provides minimal aerodynamic drag. Inside the free-carrying wing 1, only special equipment is fixed. Special equipment depending on the purpose of the UAV can

be different and mounted on the outer surface. For example, for environmental purposes, equipment can be represented by samplers, gas analyzers, etc.

The propulsion system consists of four lifting motors 2 located symmetrically about the axis of the apparatus and outside it. The lifting engines 2 are rigidly fixed to the UAV free wing 1, and the axis of the shafts of these engines pass through the center of mass of the apparatus, while the entire payload completely occupies the entire free volume of the free supporting wing 1. Each engine 2 consists of a lifting screw 4, fixed with a skeg 5 to the sleeve 6, which with the help of rods 7 connects the rotary engines 2 to the UAV case.

Rotary engines 2 are designed to create the thrust necessary to move the UAV in the horizontal plane, as well as for vertical take-off and landing of the device.

The UAV in the initial state can be installed or progressively move on a solid surface with the help of wheels 8. At the initial position, a ground-based remote control point for an unmanned aerial vehicle is deployed. 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 addition, it can be carried out both by the commands of the operator located in the area of the control point, and can be stored in the memory of control system 9, as well as from the UAV. In the first case, the launch is carried out from the launcher, and in the second - from the place of the tragedy, disaster,

infection, etc.

The start of the propulsion system at startup is carried out automatically or at the command of the operator. When starting the UAV, rotary engines 2 begin their work. As soon as the total thrust created by 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 lifting motors 2 pass through the center of mass of the UAV, the apparatus is statically stable during its lifting. 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. For this, engines 2 operate in such a way that the UAV is located above a given point on the surface. Then, on command, they are put into hover mode. In this case, the total thrust created by engines 2 should be equal to the starting weight of the UAV.

The mode is “Flight”. At the command of the control system, engines 2 are put into horizontal flight mode.

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.

The developed UAV is economical. This is achieved by its shape, which reduces its aerodynamic drag. Freestanding wing 1 allows the UAV to plan. To rotate the UAV, a command is sent from the control system to the engines 2, which directly carry out the rotation. The change in flight speed is carried out by changing the number of revolutions of the shaft of engines 2. In the case of a decrease in the flight speed of the UAV or the reverse of the thrust, it is necessary either to reduce the number of revolutions of the shaft of the engines or to rotate it in the opposite direction with a given angular velocity. If you need to set a given height, the lifting motors 2 change the angle of inclination.

The mode is “Landing”. UAVs are landing when engines 2 are in take-off and landing mode. 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 a combined unmanned aerial vehicle with four rotary engines are:

- the ability to place any special equipment on the outer surface of the wing of the UAV;

- the possibility of implementing four UAV operation modes;

- 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.);

-reliability due to the presence of four engines at once, which can hold the device in the air in case of failure up to two.

Claims (1)

An unmanned aerial vehicle with four rotary engines, consisting of a free-flying wing, a control system, a propulsion system and a payload, characterized in that the propulsion system consists of four rotary engines located symmetrically with respect to the aircraft axis and outside it, rigidly connected by axes to the glider and independently operating from a single control system, and the engines are located in such a way that the center of mass of the apparatus is symmetrically between the axes of the engines, and the control system The phenomena and elements of power and drive of the propulsion system uniformly occupy the entire free volume of the free-carrying wing, and the payload is placed on the surface of the wing.