RU98394U1 - COMBINED UNMANNED AIRCRAFT - Google Patents

Abstract

 Combined unmanned aerial vehicle, consisting of a free-flying wing, equipped with aerodynamic controls, marching and lifting engines and payload, characterized in that the lifting engine is installed in the center of mass of the device, and the marching engine is on the trailing edge of the wing, which is connected through the tail beams to the stabilizer made in the form of a plate installed between them, and having the ability to rotate relative to the horizontal axis, while the aerodynamic controls represent they are keels that can be rotated about their vertical axes, interconnected and installed on both sides of the stabilizer, and at the inlet and at the outlet of the lifting engine aerodynamic covers with rotary shutters made in the form of blinds are installed, and the payload occupies the entire free volume of the free-bearing wings.

Description

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

Recently, there has been growing interest in the use of unmanned aerial vehicles to solve many problems, the implementation of which 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 hard-to-reach places with visual control of measurements and sampling points, 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, man-made disasters and identifying victims in them);

- monitoring of sea and river highways and reservoirs (identifying poaching on them), environmental monitoring and control of facilities and routes for the production, production 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 dangerous 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 PCs at the end of the flight path;

- geological studies, remote monitoring of volcanic or seismic activity;

- notification of the occurrence and development of accidents, natural disasters or dangerous situations in controlled areas, the 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.

Similar developments are carried out abroad: FR No. 2581614, A1, GALLAS YVES IEAN, 1986; US No. 4,194,707, A1, SHARPE THOMAS H, 1980; US No. 3645474, A1, ARBUSE SAMUEL, 1972; EP 0798207, A2, GEVERS DAVID E, 1997; DE No. 19540272, A1, SCHIER IOHANNES, 1997.

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-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 disadvantages of this engine is the placement of the engine outside the center of mass, which leads to an unstable position of the UAV at startup. In addition, the aerodynamic drag increases due to the violation of the continuity of the flow of air flowing along the body of the flying wing, caused by air flowing through the cylinder of the lifting engine.

The objective of the utility model is to improve the technical characteristics of increasing the margin of statistical stability and increasing the flight range of the UAV by reducing aerodynamic drag, provided that the remaining parameters are constant.

The technical result that can be obtained using the utility model is to expand the range of its technical characteristics.

The task is achieved in that the combined unmanned aerial vehicle contains a free-carrying wing equipped with aerodynamic controls, marching and lifting engines, as well as the payload. At the same time, the lifting engine is installed in the center of mass of the apparatus, and the marching engine is located on the trailing edge of the wing, which is connected through the tail beams to a stabilizer made in the form of a plate mounted between them and capable of rotation relative to the horizontal axis, while the aerodynamic controls are keels having the ability to rotate relative to its vertical axes, interconnected and installed on both sides of the stabilizer, and at the input and output of the lifting motor Credited aerodynamic cover with adjustable dampers, made in the form of blinds and payload occupies the entire free volume of the cantilever wing.

Figure 1 shows a top view of a UAV with open covers of the lifting engine, and figure 2 shows a view of a UAV with closed covers, where:

1 - free-carrying wing;

2 - a lifting engine;

3 - traction engine;

4 - stabilizer;

5 - a nose fairing;

6 - aerodynamic controls;

7 - lifting screw;

8 - a cylindrical sleeve;

9 - rotary shutters;

10 - tail beams;

11 - connecting rod.

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, lifting engine 2, traction motor 3 and stabilizer 4 (figure 1).

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 free-carrying wing 1 has a shape that provides minimal aerodynamic drag, the controls 6 are installed at the rear. Inside the wing 1, 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 lifting engine 2 is installed in the center of mass of the free-flying wing 1. It is designed to create the vertical thrust necessary for the implementation of launch, hovering and landing modes. It consists of a screw 7, the axis of which is fixed inside the cylindrical sleeve 8, located in the center of mass of the UAV. Inoperative, the lifting motor 2 is closed by the rotary shutters 9 (Fig.2).

Traction motor 3 is designed to create a horizontal component of traction. It is mounted at the rear of the free-standing wing 1.

The stabilizer 4 is designed to shift the center of pressure away from the center of mass, which provides an increase in the margin of static stability of the UAV. 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 the tail beams 10 to the free-carrying wing 1 at a small angle, which is necessary to create the initial lifting force, which ensures the planning flight of the UAV. In this case, the stabilizer 4 is installed between the tail beams 10 with the possibility of rotation relative to its horizontal axis, providing UAV control by pitch angle.

In the initial state, the UAV can be installed or progressively move on a solid surface with the help of wheels attached to the lower part of the free-flying wing 1 using the chassis. At the starting position, a ground-based remote control point for unmanned aerial vehicle is being 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”. Developed 3 types of UAV launch:

- by giving the initial impulse of force due to bailout;

- by giving the initial impulse to the force created by the hand of the calculation number;

- Autonomously using a UAV lifting engine.

UAV launch in the first two cases can be carried out both from a mobile and stationary launcher.

In the third case, before the autonomous launch and vertical take-off of the UAV, it is necessary to open the input and output rotary valves 9. The start-up of the lifting engine 2 with the vertical take-off of the UAV is carried out automatically according to a pre-programmed program or by the operator’s command from the ground control panel

When the UAV starts autonomously, the lifting engine 2 starts its operation (the traction engine 3 is in the off state). As soon as the thrust created by the lifting engine 2 exceeds the starting mass of the UAV, it breaks away from the surface and rises vertically up to gain the desired height. At the command of the UAV control system, the lifting engine 2 is turned off and the traction engine 3 is turned on.

The mode is “Hanging”. If necessary, the UAV hangs in the air above a given point. For this, the traction engine 3 in conjunction with the UAV control system operates in such a way that the UAV is located above a given point on the surface. Then it turns off, and the lifting engine 2 turns on. In this case, the rotary shutter 9 must be open.

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. In this case, the pitch angle control is carried out by turning the stabilizer 4 around its axis, and the yaw angle control is performed by rotating the aerodynamic controls 6, which are keels, interconnected by a connecting rod 11 and installed on both sides of the stabilizer 4. When This rotary flap 9 aerodynamic covers must be closed to give the best aerodynamic characteristics of the UAV.

UAV flight control is carried out using the flight-navigation system. At the same time, the results of a remote survey of the terrain, as well as video and telemetry information, are transmitted to the ground-based remote control point via a UAV transceiver antenna.

The developed UAV is economical. This is achieved by its shape, which helps to reduce aerodynamic drag. The stabilizer 4 together with the free-flying wing 1 allows the UAV to plan. The change in flight speed is carried out by changing the number of revolutions of the shaft of the traction engine 3. 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 engine or to rotate it in the opposite direction with a given angular velocity. If you need to set a predetermined height, the lifting motor 2 is turned on.

The mode is “Landing”. Landing of the UAV can be carried out vertically when the traction motor 3 is stopped and the lifting engine 2 is turned on. At the same time, the rotary shutters 9 must be open (Fig. 1). The UAV can land smoothly on an airplane. When this rotary shutter 9 must be closed (figure 2).

The main advantages of the combined unmanned aerial vehicle are:

- increased margin of statistical stability caused by the displacement of the center of pressure from the center of mass of the unmanned aerial vehicle;

- high efficiency, achieved due to the configuration of the free-standing wing and the presence of a stabilizer;

- an increase in the flight range of the UAV by reducing aerodynamic drag, provided that the remaining parameters are constant;

- the possibility of implementing four UAV operation modes;

- the ability to land UAVs on any hard surface, as well as providing a hover mode over any hard-to-reach terrain.

Claims (1)

Combined unmanned aerial vehicle, consisting of a free-flying wing, equipped with aerodynamic controls, marching and lifting engines and payload, characterized in that the lifting engine is installed in the center of mass of the device, and the marching engine is on the trailing edge of the wing, which is connected through the tail beams to the stabilizer made in the form of a plate installed between them, and having the ability to rotate relative to the horizontal axis, while the aerodynamic controls represent they are keels that can be rotated about their vertical axes, interconnected and installed on both sides of the stabilizer, and at the inlet and at the outlet of the lifting engine aerodynamic covers with rotary shutters made in the form of blinds are installed, and the payload occupies the entire free volume of the free-bearing wings.