RU69838U1 - COMBINED UNMANNED AIRCRAFT - Google Patents

Abstract

Combined unmanned aerial vehicle refers 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, which consist in the efficient use of the internal volume of the UAV wing and in increasing the statistical stability margin. The technical result that can be obtained using the utility model is to expand the range of UAV application by placing any special equipment in the internal volume of its wing 1. The task is achieved in that the combined unmanned aerial vehicle contains a free-flying wing, aerodynamic controls, and engine installation and payload. In this case, the propulsion system consists of two hoisting engines located symmetrically with respect to the axis of the apparatus and outside it, and a marching engine located in its rear part, while the hoisting motors are rigidly fixed to the wing of the apparatus, and the axis of the shafts of these engines pass through the center of mass of the apparatus, moreover, the payload evenly occupies the entire free volume of the free-carrying wing. Using the proposed combined unmanned aerial vehicle allows you to place any special equipment in the internal volume of the UAV wing, realize four UAV operation modes, as well as provide the modes of takeoff, UAV landing on any hard surface and hovering conditions over any hard-to-reach 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 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 points, 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 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.) 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, 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 of operation and technical nature of the claimed device is "Unmanned aerial vehicle" according to patent No. 2288140 from 11/27/2006, IPC V64C 39/00. It contains a free-wing wing equipped with aerodynamic

controls, vertical tail, 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 disadvantages of this engine is the inefficient use of the internal volume of the UAV wing due to the placement of a lifting engine in it, as well as its placement outside the center of mass of the device, which leads to its unstable position during take-off, when the stabilizer is still ineffective. In addition, not all special equipment can be placed in the area of the lifting engine. For example, placement of devices for air sampling, etc., is problematic.

The objective of the utility model is to improve the technical characteristics, which consist in the efficient use of the internal volume of the UAV wing and in increasing the statistical stability margin.

The technical result that can be obtained using the utility model is to expand the range of UAV application by placing any special equipment in the internal volume of its wing 1.

The task is achieved in that the combined unmanned aerial vehicle contains a free-flying wing, aerodynamic controls, a propulsion system and a payload. In this case, the propulsion system consists of two hoisting engines located symmetrically with respect to the axis of the apparatus and outside it, and a marching engine located in its rear part, while the hoisting motors are rigidly fixed to the wing of the apparatus, and the axis of the shafts of these engines pass through the center of mass of the apparatus, moreover, the payload evenly occupies the entire free volume of the free-carrying wing.

Figure 1 shows a top view of the UAV, and figure 2 shows a side view of the UAV,

Where: 1 - freestanding wing;

2 - a lifting engine;

3 - marching engine;

4 - stabilizer;

5 - a nose fairing;

6 - aerodynamic controls;

7 - lifting screw;

8 - skeg;

9 - a cylindrical housing of the lifting engine;

10 - rods mounting the lifting engine;

11 - stabilizer mounting rods;

12 - 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, lift engine 2, traction engine 3 and stabilizer 4.

Freestanding wing 1 is designed to accommodate and fasten all components of the apparatus. A nose fairing 5 is installed in front of the apparatus, inside of which are placed elements of functionally interconnected electronic surveillance equipment, a transceiver unit, a transceiver antenna, a flight-navigation system, etc.

The front part of the wing 1 has a shape that provides minimal aerodynamic drag, and controls are installed on its rear part 6. 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 lifting motors 2 located symmetrically with respect to the axis of the apparatus and outside it, and a mid-flight engine 3 located in its rear part. Lifting engines 2 are rigidly fixed to the UAV wing 1, and the axis of the shafts of these engines pass through the center of mass of the apparatus, while the entire payload fully occupies the entire free volume of the free-carrying wing 1. Each lifting engine 2 consists of a screw 7, fixed with a skeg 8 to a cylindrical body 9, which with the help of rods 10 for mounting the lifting engine is rigidly connected to the body of the UAV.

Marching engine 3 is designed to create traction necessary to move the UAV in the horizontal plane. It is attached to the rear of the wing 1.

The stabilizer 4 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 aerodynamic focus of the wing, 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 4 is made in the form of a plate, fastened with the help of connecting rods 11 to the wing 1 at a small angle, which is necessary to create a lifting force, which ensures the planning flight of the UAV.

UAV in the initial state can be installed or progressively move

on a hard surface using wheels 12. At the starting 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. Starting the engine at startup is carried out automatically or at the command of the operator. When starting the UAV, the lifting engines 2 begin their work (the main engine is in the off state). As soon as the total thrust created by the lifting engines 2 exceeds the starting weight of the UAV, it breaks off 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. At the command of the control system, the lifting motors 2 are turned off and the traction motor is turned on.

The mode is “Hanging”. If necessary, the UAV hangs in the air above a given point. For this, the main engine 3 operates in such a way that the UAV is located above a given point on the surface. Then it turns off, and the lifting motors 2 turn on. In this case, the total thrust created by the lifting motors 2 should be equal to the starting weight of the UAV.

The mode is “Flight”. 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. The stabilizer 4 together with the free-flying wing 1 allows the UAV to plan. To rotate the UAV, a command is sent from the control system to the aerodynamic controls 6. The flight speed is changed by changing the number of revolutions of the main engine shaft 3. If the UAV speed decreases or thrust is reversed, it is necessary either to reduce the number of revolutions of the engine shaft or rotate it in the opposite direction with a given angular velocity. If necessary, the set height is turned on

lifting motor 2.

The mode is “Landing”. UAVs are landing when the mid-flight engine 3 is stopped and the lifting engines 2 are turned on. At the same time, the UAVs land 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 ability to place any special equipment in the internal volume of the UAV wing;

- 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.).

Claims (1)

Combined unmanned aerial vehicle, consisting of a free-flying wing, aerodynamic controls, propulsion system and payload, characterized in that the propulsion system consists of two lift engines located symmetrically about the axis of the device and outside it, and the main engine located in its rear part while the lifting motors are rigidly fixed to the wing of the apparatus, and the axis of the shafts of these engines pass through the center of mass of the apparatus, and the payload is uniformly behind It takes all the free volume of the free-carrying wing.