RU226216U1 - MULTI-FUNCTIONAL UNMANNED AIRCRAFT LAUNCHED FROM A TRANSPORT AND LAUNCH CONTAINER - Google Patents

Abstract

The utility model relates to the field of aviation technology, namely unmanned aerial vehicles designed for long-term monitoring of the earth's surface using surveillance equipment. A multifunctional unmanned aerial vehicle launched from a transport and launch container contains a fuselage consisting of two articulated parts; inside the front part of the fuselage there are navigation, control and radio communication units for controlling the flight and ensuring the use of a payload module and a fixed optical camera located in the nose and infrared range. There are also batteries located there to provide power to the propulsion motor and accumulate electricity from solar panels located on the upper surface of the wing. On top of the front part of the fuselage there is a folded wing, which when opened forms a circular wing, on which a solar battery is applied on top. The opening of the circular wing is ensured by an electric motor located inside the fuselage. Also on top of the front part of the fuselage, in front of the circular wing, is a closed compartment with a parachute system. In the hinged rear part of the fuselage there is a main electric motor with a folding main rotor. The articulated joint allows the rear part of the fuselage, that is, the main electric motor with the propeller, to deflect in all directions, which allows you to control the direction of movement and flight altitude of a multifunctional unmanned aerial vehicle. Also, a launch-acceleration stage is attached to the rear part of the fuselage using clamps for launching from a transport-launch container and pre-climbing the flight altitude.

Description

The utility model relates to the field of aviation technology, namely to atmospheric unmanned aerial vehicles designed for long-term monitoring of the earth's surface using a wide range of surveillance equipment, installation of seismoacoustic detection sensors, communications and target designation, active and passive radio interference, and fire damage.

Currently, unmanned aerial vehicles have gained enormous popularity, especially in the most developed countries of the world. The scope of application of drones is quite wide. They are actively developing, there are a large number of varieties of these devices, and the creation of new ones and the improvement of existing ones continue. Unmanned aerial vehicles are actively used in various fields of activity.

In the interests of border authorities, unmanned aerial vehicles are used to control hard-to-reach sections of the border, reconnaissance in the area of violation of the state border, identifying enemy activities on the engineering equipment of the area, monitoring the quality of camouflage of strongholds of their outposts, and monitoring the zone of economic interests of the Russian Federation.

In military affairs, they are used for reconnaissance, adjusting fire and striking, shooting the coordinates of enemy objects, measuring distances and areas; they have proven themselves well in combat operations. In this regard, increasing attention is being paid to the characteristics of unmanned aerial vehicles, their versatility, and the ability to perform a wide range of tasks for a long time.

There are dozens of developments of unmanned aerial vehicles in the world based on the use of new wing shapes. The challenges facing modern drone developers are increasing the time in the air and the payload weight. You should pay attention to the use of a round wing in the developed models of unmanned aerial vehicles. Tests of such aircraft models have proven their advantages; such a wing provides a smooth flow of air around it, which does not stop even at very high angles of attack reaching about 45 degrees, which is three times higher than that of conventional aircraft. Even at such angles of attack, the aircraft does not fall into a tailspin, but can parachute steadily and safely, and the lifting force of the wing continuously increases. The aircraft lands smoothly due to the appearance of a screen effect underneath it. You cannot force the landing to speed up until the flight speed naturally decays and the screen effect disappears. This is also an advantage, since piloting errors at the time of landing will not lead to unpleasant consequences.

There is another positive quality of aircraft with a round wing - under no flight conditions does it go into a tailspin. When reaching maximum angles of attack, only steep, extremely stable parachute is possible. It is noteworthy that this mode is the safest. Whereas for vehicles with conventional wings, parachuting is especially risky from the point of view of a possible tailspin.

The use of new technical solutions improves the operational characteristics of aircraft, increases the flight time and, accordingly, the flight range, and makes it possible to solve assigned tasks more efficiently.

The creation of new models of unmanned aerial vehicles using modern advances in aerodynamics and electrical engineering contributes to the acquisition of new opportunities for application and expansion of the range of tasks to be solved.

The "Lanner" aircraft is known (patent RU No. 139040 of 2014), made according to the "flying wing" design and having a round wing in plan with a cabin, power units, tricycle landing gear, standard aircraft systems, mechanisms, components and units that ensure the functioning of the aircraft, flaperons are located on the trailing edge of the round wing in plan, and in the said wing there are three profiled cutouts in which the “propeller in a ring” systems are located, equipped with four-bladed coaxial propellers with the ability to reverse thrust.

The disadvantages of this device are the need to pilot the aircraft, use from runways, limited flight time associated with limited fuel reserves on board.

There is also known a reusable unmanned aerial vehicle in a transport and launch container and a method for launching a reusable unmanned aerial vehicle from a transport and launch container (RU patent No. 2714616 of 2020), containing a fuselage, a propulsion system, a launch-acceleration stage, a folding wing and tail, each of the wing consoles is made of two or more telescopically connected parts, installed with the possibility of opening using one or more spars, each of which is made of telescopically connected parts, while the root part of the spar is rigidly fixed in the root part of the wing console, and in the end part of the wing console is made of a rigidly fixed power frame, into which the spar rests after extension, the outer ends of the root and end parts of the spar are made blind, while the unmanned aerial vehicle, hereinafter referred to as the UAV, is equipped with folding takeoff and landing landing gear.

The disadvantages of this device are the complexity of the design, the need for a landing strip and the flight time limited by fuel reserves on board.

The closest in technical essence to the claimed invention is a multifunctional small-sized transformable reusable unmanned aerial vehicle in a transport and launch container (TPC) and launch methods (RU patent No. 2778177 of 2022), containing an axisymmetric fuselage, replaceable target load modules, navigation units, control and two-way radio communications, a sustainer propulsion unit, an adapter frame, a launch-acceleration stage (STS) coaxially connected to the fuselage, a folding wing and rudders, each of which is made of two kinematically connected parts folding around the rear fuselage of the UAV, additionally containing SRS stabilizers , folding around the tail part of the SRS, and the diameter of the tail part of the UAV fuselage and the diameter of the tail part of the SRS is less than the outer diameter of the largest (midship) section of the fuselage; in the area of the upper arch of the fuselage there is a parachute rescue system for the UAV for its next use, and a propulsion power plant based on a gas turbine engine.

The disadvantage of this device is the complexity of the design and the limited flight time by fuel reserves on board.

The technical task of the utility model is to create a UAV design, the implementation of which will ensure the placement of a UAV with a folded wing in a small-sized TPK, the possibility of launching from a TPK, the opening of the wing after the UAV exits the small-sized TPK, the possibility of replenishing energy reserves in flight and the repeated use of the UAV.

The technical results of the proposed solution are to ensure longer flight duration through the use of a round wing and the possibility of replenishing electricity in flight.

The required technical result is achieved by the fact that the multifunctional unmanned aerial vehicle launched from the TPK contains a fuselage consisting of two articulated parts. Inside the front part of the fuselage there are navigation, control and radio communication units for flight control and a non-removable surveillance camera located in the nose in the optical and infrared ranges. There are also batteries located there to provide power to the propulsion motor and accumulate electricity from solar panels located on the upper surface of the wing. On top of the front part of the fuselage there is a folded wing, which when opened forms a circular wing, on which a solar battery is applied on top. The opening of the circular wing is ensured by an electric motor located inside the fuselage. Also on top of the front part of the fuselage in front of the circular wing is a closed compartment with a parachute system. In the hinged rear part of the fuselage there is a main electric motor with a folding main rotor. The articulated joint allows the rear part of the fuselage, that is, the main electric motor with the propeller, to deflect in all directions, which allows you to control the direction of movement and flight altitude of a multifunctional unmanned aerial vehicle. Also, a launch-acceleration stage is attached to the rear part of the fuselage using clamps for launching from the TPK and pre-climbing the flight altitude.

The essence of the utility model is illustrated by the drawing, where

in fig. 1 - diagram of a multifunctional unmanned aerial vehicle launched from a transport and launch container, where:

1 - folding wing;

2 - front part of the fuselage;

3 - transport and launch container;

4 - start-acceleration stage;

5 - folding main rotor;

6 - rear part of the fuselage;

7 - non-removable optical and infrared camera.

In fig. Figure 2 shows a top view of a multifunctional unmanned aerial vehicle launched from a transport and launch container, with the wing unfolded, where:

8 - solar battery;

9 - parachute landing system.

In fig. Figure 3 shows a diagram of functional blocks and devices located in the fuselage of a multifunctional unmanned aerial vehicle launched from a transport and launch container, where:

10 - main electric motor;

11 - block of electromagnets;

12 - control unit;

13 - electric motor;

14 - navigation block;

15 - battery;

16 - communication unit.

The utility model works as follows: in preparation for performing tasks, the multifunctional unmanned aerial vehicle is equipped with a charged battery (15). The launch-acceleration stage (4) is attached and the entire structure is placed in a transport-launch container (3), which allows the aircraft to be kept ready for launch, carried by personnel and transported on various vehicles.

A multifunctional unmanned aerial vehicle is launched from the TPK due to the activation of the start-acceleration stage (4) and makes a preliminary climb to flight altitude. After testing, the launch-acceleration stage (4) is reset at the command of the control unit (12), the folding main rotor (5) is released, the electric motor (13) is started, which, through a gear transmission, unfolds the folding wing (1) folded like a fan, which, after deployment is fixed to form a continuous surface. Consumers receive power. The main electric motor (10) is started and the multifunctional unmanned aerial vehicle, launched from the TPK, carries out a flight under control from the command post via a radio channel, performing tasks depending on the target load on board.

Control in flight is carried out by changing the thrust vector of the main electric motor (10), which is formed by the deflection of the hinged rear part of the fuselage (6) by four electromagnets of the electromagnet block (11), the cores of which are connected to the front part of the fuselage (2).

During the flight, the battery (15) is replenished with electricity from the solar battery (8), which increases the time the UAV is used and increases the functionality of the payload used.

The route of movement is regulated by the control unit (12) according to pre-entered data, coordinates obtained during the flight, using the navigation unit (14) through the GLONASS/GPS satellite global navigation system or visually according to the image obtained by a fixed optical and infrared camera (7). The information collected during operation is transmitted to the command post through the communication unit (15).

The multifunctional unmanned aerial vehicle lands smoothly due to the appearance of a screen effect underneath it and the use of a parachute landing system (9). After landing, the devices used are serviced, the battery is charged (15), the folding wing (1) and the folding main rotor (5) are brought into the transport position, replacement of replaceable payload modules (if necessary), and attachment of the launch-acceleration stage (4) and installation in a transport and launch container (3) for the next application.

A multifunctional unmanned aerial vehicle launched from a transport and launch container is capable of quickly deploying and for a long time ensuring the effective use of various modules of interchangeable payload (control, surveillance, relay, destruction, etc.) due to the ability to replenish and accumulate energy reserves in flight.

Claims (1)

A multifunctional unmanned aerial vehicle launched from a transport and launch container, containing a fuselage, navigation, control and radio communication units, batteries, a propulsion system, a launch-acceleration stage connected to the fuselage, a folding wing, a parachute landing system, and a non-removable camera in the nose. optical and infrared range, characterized in that there is a folded wing on top, which, when opened, forms a circular wing with a solar battery applied on top; in the rear part of the fuselage there is a sustainer electric motor with a folding main rotor.