RU181026U1 - Multipurpose Unmanned Aerial Vehicle - Google Patents

Abstract

The utility model relates to small aircraft. The unmanned aerial vehicle is a single-body monoplane. The device is made with a high wing, which is presented in the form of two half-wings. The tail stabilizer spaced two-winged, removable. A parachute and an inflatable buffer are located at the top and bottom of the fuselage, respectively. On-board equipment includes: automatic control system; radio modem; air receiver receiver tube; payload equipment (removable and placed in the inner space of the fuselage); aeronautical lights and solar panels (located on the wings); 12 liter tank (made of composite materials); a power plant located in the front of the fuselage, and an engine steering gear installed there, as well as a generator mounted on the engine shaft. The technical result of the utility model is the possibility of a long, trouble-free environmental monitoring, patrolling forests, power lines, oil and gas pipelines.

Description

The utility model relates to the field of small-sized aviation equipment, namely to unmanned aerial vehicles (UAVs), designed for environmental monitoring, patrolling forests, power lines, oil and gas pipelines.

Known reconnaissance unmanned aerial vehicle (patent for a utility model of the Russian Federation No. 41295, IPC ВСС 39/02, publication date 10/20/2004), made according to the aerodynamic airplane scheme of a monoplane, including the fuselage, wing and tail, while the wing has a flyeron, the fuselage is connected to the tail unit by a beam fixed along the longitudinal axis of the aircraft on the center section. The tail unit is made V-shaped and consists of two keels symmetrically located relative to the plane of symmetry of the aircraft, mounted on a beam, each of which is equipped with a rotary rudder, the rudders are installed with the possibility of their differential deflection, the power plant is located in the head of the fuselage and consists of an electric battery , an electric motor and a pulling propeller kinematically connected to the electric motor, and the on-board electronic equipment includes a functional about interconnected television monitoring equipment, a transmitting and receiving unit, a transmitting and receiving antenna, and is located in the inner cavity of the wing.

However, it has narrow functional capabilities, in particular, it can not fly long duration, because has a limit on the capacity of the onboard power source for the traction electric motor.

The closest known technical solutions to the claimed device is an unmanned aerial vehicle (patent for a utility model of the Russian Federation No. 132421, IPC B64D 43/00, B64D 47/02, B64D 27/08, B64D 17/80, B64C 13/38, date publication September 20, 2013 g), made according to the aerodynamic scheme of a single-fuselage monoplane and containing a fuselage, having the ability to undock on the front and tail with a tail unit, consisting of a removable stabilizer with elevator and keel with rudder, removable high wing, power at SETTING internal combustion engine with a pulling propeller and the stationary fuel tank, avionics, which includes automatic control system, the command unit with radio-telemetry transceiver antenna and receiver pipe air pressure, payload, servos and accumulator. Additionally, the unmanned aerial vehicle contains an inflatable buffer and a parachute, stacked one above the other in the parachute compartment. However, it has a number of limitations in operation:

- has a limit on the capacity of the on-board power source to ensure the continuous operation of on-board electronic systems;

- in the event of a malfunction of the inflatable buffer and parachute, it is impossible to make a safe landing;

- cannot make flights of long duration, because has a limit on the capacity of the fuel tank.

The objective of the utility model is to create such an unmanned aerial vehicle that, due to its design features, would solve problems, providing a long, trouble-free flight.

The technical result of the claimed utility model is to increase flight reliability, thus providing the possibility of a long, trouble-free environmental monitoring, patrolling forests, power lines, oil and gas pipelines.

The technical result is achieved by the fact that a multi-purpose unmanned aerial vehicle, made according to the aerodynamic scheme of a single-body monoplane with a power plant, presented in the form of an internal combustion engine with a fuel tank, a high wing, avionics, payload, steering machines, a radio modem, an air pressure receiver, parachute and inflatable buffer, characterized in that it contains a spaced two-tail tail, solar panels and a generator moreover, the parachute is located in the lower part of the fuselage, and the inflatable buffer in the upper part, while the wing is presented in the form of two removable half-wings, and the lower part of the fuselage is made with higher stiffness characteristics compared to the upper part.

The spaced twin-tail plumage provides directional stability both at small and at large angles of attack, which is very important for an unmanned aerial vehicle in bad weather conditions.

Solar panels and a generator allow providing the device with additional electricity, which significantly affects the duration of the flight.

The location of the parachute in the lower part of the fuselage, and the inflatable buffer in the upper part, ensures the greatest security of these devices, preventing them from interfering with each other when carrying out their work.

The manufacture of the lower part of the fuselage with higher stiffness characteristics allows the device to land most painlessly without the help of a parachute and an inflatable buffer. The automatic control system allows you to smoothly put the device on the "belly".

Making a wing in the form of two removable half-wings allows you to make the device more compact when transporting to the desired area.

The set of essential features of the invention ensures the achievement of the technical result obtained by implementing the utility model, in the form of the possibility of a long, trouble-free environmental monitoring, patrolling forests, power lines, oil and gas pipelines.

An analysis of the state of the art by the applicant has established that analogues that are characterized by sets of features identical to all the features of the claimed unmanned aerial vehicle to enable long-term, trouble-free environmental monitoring, patrolling forests, power lines, oil and gas pipelines are missing, therefore, the claimed utility model meets the condition "novelty".

The essence of the utility model is illustrated by drawings, where in FIG. 1 shows a side view of a UAV, in FIG. 2 is an exploded view of an UAV in isometry.

The following notation is introduced:

1 - fuselage;

2 - the upper part of the fuselage;

3 - the lower part of the fuselage;

4 - stabilizer console;

5 - spaced twin-winged plumage;

6 - floor wings;

7 - ailerons;

8 - metal fixing pins on the floor of the wings;

9 - parachute;

10 - inflatable buffer;

11 - cover closing the inflatable buffer;

12 - cover closing parachute;

13 - automatic control system (ACS);

14 - radio modem;

15 - tube receiver air pressure;

16 - payload;

17 - aeronautical lights;

18 - solar panels;

19 - internal combustion engine;

20 - air propeller;

21 - steering engine "gas" ICE;

22 - fuel tank;

23 - generator;

The unmanned aerial vehicle contains the fuselage 1, consisting of the upper 2 and lower 3 parts. The tail unit is installed on the fuselage 1 in the form of a removable stabilizer console 4 and a spaced twin-tail unit 5. The half wings 6, with ailerons 7, are fixed with fixing pins 8. The parachute 9 and the inflatable buffer 10 are closed respectively by covers 11 and 12, which are mechanically connected to the steering machines. The covers are not sealed. The automatic control system 13 is installed in the front of the fuselage, the radio modem 14 is installed in the rear of the fuselage, and the receiver tube of the air pressure 15 is installed on the left wing console. The payload 16 is located in the middle of the fuselage, and the navigation lights 17 and the solar panels 18 are mounted on the wing consoles. The power plant consists of an internal combustion engine 19, an air propeller 20, a gas engine 21 engine 21 and a fuel tank 22, and a generator 23 mounted on the engine shaft.

UAV works as follows.

The unmanned aerial vehicle is delivered to the launch site in an unassembled transport container - half wings 6 and the stabilizer console 4 are undocked from the fuselage 1.

After removing the UAV from the transport container, it is assembled in the following sequence:

- dock to the fuselage 1 console 4 stabilizer;

- at the same time the docking of the connectors of the payload 16 and the docking of the wings 6, which are fixed there with metal pins 8.

Then the UAV is installed on the catapult (launching device) and the following operations are performed to prepare for launch:

- On-board electronic equipment is switched on;

- the flight program is being loaded into the self-propelled guns 13 via a radio channel through a radio modem 14;

- self-propelled guns using its GPS-Glonass channel determines the location of the UAV;

- barometric pressure sensor SAU 13 is automatically reset;

- self-propelled guns 13 automatically checks the serviceability of on-board systems and, if ready for flight, gives a signal about the possibility of the UAV launching at the ground control station (NSU);

- a signal is supplied from the NSU to the self-propelled guns 13 via a radio channel, and the voltage from the on-board battery to the spark plug of the internal combustion engine 19.

After that, the ICE 19 is started by an electric starter, the engine operation stability is checked at different revolutions - the revolutions are regulated by the “gas” engine 21 engine. CAU 13 disconnects the ICE spark plug from the on-board battery and signals the UAV's readiness for launch.

The UAV start signal is received from the NSU via the radio channel via radio modem 14 to the self-propelled guns 13, which, in turn, provides a signal to the catapult trigger and the UAV takes off using the acceleration created by the catapult.

Next, the UAV flight is carried out in automatic mode according to the program laid down in the self-propelled guns 13, moreover, the airspeed data is received from the receiver tube of the air pressure 15. Aerodynamic surfaces (ailerons 7) are controlled by steering cars.

An important stage of the UAV flight is landing (regular or emergency). Both full-time and emergency landing are carried out either by plane on the "belly" of the device or with the help of a parachute 9 and an inflatable buffer 10.

During a standard or emergency landing in an airplane (without the release of a parachute 9 and an inflatable buffer 10), the UAV operates as follows:

- after completing the flight mission and returning the UAV to the start point, the NSU operator turns off the internal combustion engine 19 by means of the “gas” steering gear 21 or in case of an accidental stop of the internal combustion engine 19, the device automatically performs a smooth decrease until it comes into contact with the ground;

When performing a standard or emergency landing by parachute, the UAV operates as follows:

- when approaching the UAV landing site or in the event of an emergency, self-propelled guns 13 issues a command to turn off the internal combustion engine 19;

- with a slight delay in time according to the signal from the self-propelled guns 13 steering machines are triggered, opening the covers 12, 11 and releasing the parachute 9 and the inflatable buffer 10; the parachute is pulled out, filled with air and the aircraft hangs on parachute slings, the buffer is inflated;

- the inflatable buffer 10 touches the ground first, and the UAV makes a soft landing on it;

If the continuation of work with UAVs is not expected, then the device is disassembled and placed in a transport container.

The proposed unmanned aerial vehicle allows due to its design to obtain long-term trouble-free operation during environmental monitoring, patrolling forests, power lines, oil and gas pipelines, namely:

- the possibility of landing in an airplane on the earth's surface, replete with various kinds of obstacles (mounds, stones, etc.);

- the ability to land on a parachute using an inflatable buffer that softens the first contact with the earth's surface;

- ease of transportation due to the possibility of undocking the wings and stabilizer consoles from the fuselage;

- the presence of a generator that provides continuous charging of the battery during engine operation;

- the use of a fuel tank of 12 liters, made of composite materials, contributing to weight reduction;

- the availability of a renewable energy source (solar panels), ensuring the autonomy of electronic equipment;

Thus, the above information proves that when implementing the claimed device, the following conditions are met:

- the tool that performs the proposed device in its implementation, is intended for use in the field of operation of unmanned aerial vehicles, namely for environmental monitoring, patrolling forests, power lines, oil and gas pipelines;

- the tool that performs the device when it is implemented, is able to provide the specified technical result.

Claims (1)

A multi-purpose unmanned aerial vehicle, made according to the aerodynamic scheme of a single-body monoplane with a power unit, presented in the form of an internal combustion engine with a fuel tank, a highly located wing, electronic avionics, payload, steering machines, a radio modem, an air pressure receiver, a parachute and an inflatable buffer the fact that it contains a spaced two-tail tail, solar panels and a generator, and the parachute is located in the lower part of the inflatable buffer in the upper part, while the wing is presented in the form of two removable half-wings, and the lower part of the fuselage is made with higher stiffness characteristics compared to the upper part.

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