RU2839069C1 - Method of launching unmanned aerial vehicle and device for implementing said method - Google Patents

Abstract

FIELD: unmanned aerial vehicles.

SUBSTANCE: method of launching unmanned aerial vehicle (1) consists in the fact that orientation of tubular launcher (2) is performed in azimuthal and elevation planes. In onboard equipment of UAV there performed is input of flight task, including time of UAV reaching the top of ballistic flight trajectory. Wherein a cased propellant charge is installed in the channel of the tubular launcher behind the UAV, obturation, acceleration and removal of UAV (1) from tubular launcher (2) under the influence of the total thrust of the propellant charge gases. At the moment of time corresponding to the top of the ballistic flight trajectory, the UAV cruise engines are launched.

EFFECT: high efficiency and accuracy of guidance.

4 cl, 6 dwg, 2 tbl

Description

The invention relates to aviation technology, in particular to unmanned aerial vehicles (UAVs).

The main layout schemes of unmanned aerial vehicles [6] and the main tactical and technical characteristics of UAVs carrying a shock load are known. The main layout schemes of UAVs include single-rotor, multi-rotor, aircraft and hybrid layout schemes of the UAV airframe.

In a single-rotor airframe configuration (also known as a helicopter airframe configuration), the UAV has one main rotor and one tail rotor.

In a multi-rotor airframe design, the UAV has several supporting rotors that also function as tail rotors. Depending on the number of rotors, the airframe design of the UAV in this design is conventionally divided into tricopters (has 3 rotors), quadcopters (has 4 rotors), hexacopter (has 6 rotors), and octocopter (has 8 rotors).

In the aircraft layout scheme of the UAV airframe, the main principle of constructing the layout scheme is the use of a rigid wing with a special aerodynamic profile.

In a hybrid UAV airframe design, a rigid wing with a special aerodynamic profile is used simultaneously with several rotors.

The main tactical and technical characteristics of UAVs carrying shock loads are given in Table 1.

A method for launching an unmanned aerial vehicle is known [1], which consists of placing the UAV on the guides of the launcher at an angle to the horizon in a position rotated around its longitudinal axis by 180 degrees relative to the normal flight position, attaching it to the launcher, starting its engine to the maximum thrust mode, unfastening the fastening and subsequent acceleration under the influence of the engine thrust, wherein the aerodynamic surfaces of the UAV before acceleration are set in a position that ensures the creation of a torque along the roll when the speed of the UAV increases, and in autonomous flight, returning the aerodynamic surfaces of the UAV to the normal flight position for controlling the aerodynamic surfaces of the UAV.

The disadvantage of this method is that it does not provide for the launch of UAVs with a multi-rotor glider configuration.

A variant of the method for launching the Progress UAV (P-35) of the Redut complex [4] is known, used when launching a large-mass UAV, which consists of placing the UAV on the launcher guides at an angle to the horizon, attaching it to the launcher, starting its cruise jet engine to maximum thrust mode and starting the solid-fuel booster jet engine, unfastening the fastening, subsequent acceleration under the influence of the total thrust and separating the booster jet engine after the solid fuel burns out.

The disadvantage of this method is that its implementation requires a special launcher with a complex design.

A method for launching and controlling the flight of a UAV from a carrier aircraft is known [2], which consists of the following:

- the operator's workplace, flight and payload control equipment, as well as the UAV are placed inside the carrier aircraft;

- transmitting and receiving antennas are placed on the external structural elements of the carrier aircraft, ensuring interaction between the flight control equipment and the UAV’s target load after the UAV is launched into flight;

- the preparation of the UAV for launch into flight is carried out on board the carrier aircraft on approach to the area where the UAV’s flight mission is to be carried out;

- the launch of the UAV into flight, namely entry into the air flow, is carried out through the open hatch of the carrier aircraft;

- the operator controls the further flight of the UAV from his workplace on the carrier aircraft;

- provide the best conditions for interaction between flying UAVs along the line “control equipment - UAV” by maneuvering the carrier aircraft relative to the UAV;

- transfer control of the UAV flight from remote ground control stations to the equipment of the carrier aircraft and back.

The disadvantage of this method is the limited possibility of its implementation in the event of damage to the carrier aircraft or failure of the on-board equipment responsible for preparing the UAV for launch due to interference.

The closest to the claimed method, i.e. the prototype, is the method of pneumatic launch of the UAV from the launcher [3], which consists of placing the UAV with fully folded aerodynamic surfaces (wings and propeller) in a tubular launcher, holding it in the tubular launcher, filling the container under pressure with starting gas, unfastening the UAV mount, filling the launch tube with starting gas from the container under pressure, applying the force of the starting gas to accelerate the UAV and separate the UAV from the tubular launcher and deploying the aerodynamic surfaces of the UAV to the working (cruise) position.

The disadvantage of this method is that, firstly, the method used to load the UAV into the tubular launcher is not efficient, and secondly, there is no guidance of the tubular launcher to the point of the solid angle or sector of the encounter with the target.

Fig. 1 shows a diagram of a device implementing the prototype method.

The device for implementing the prototype method consists of an aircraft (1) and a launcher (2). The aircraft (1) has a pressure pipe (3) which forms part of the fuselage of the aircraft (1). The aircraft (1) has two wings (4) folded when the aircraft (1) is in the launcher (2), a tail unit (5) and one folded propeller (6).

The pressure tube (3) enters the launcher (2) and is the interface for transmitting energy between the launcher (2) and the aircraft (1). The launcher (2) has a tube (7) that provides a shell for the components of the launcher and the aircraft (1). The launcher (2) also has a starting gas reservoir (8) that stores the gas used to launch the aircraft (1). The starting gases can be air, nitrogen and helium. A starting tube (9) is attached to the starting gas reservoir (8) and enters the pressure tube (3) of the aircraft (1). A valve (10) allows the operator to control the moment of gas admission from the starting gas reservoir (8) into the starting tube (9).

The holding mechanism (11) is used to hold the aircraft (1) in the launch tube (9). A trigger mechanism (12) is provided to release the holding mechanism (11).

Work according to this method is carried out as follows.

The aircraft (1) is placed in the launcher (2). To launch the aircraft (1), the trigger (12) is pressed. In this case, the holding mechanism (11) releases the starting gas from the starting gas reservoir (8) through the valve (10) and the launch tube (9) into the pressure tube (3). The aircraft (1) moves relative to the launch tube (9) under the action of the force acting on the pressure tube (3) passing through the space between the pressure tube (3) and the inner wall of the launch tube (9). After the aircraft (1) leaves the launcher (2), the two wings (4) of the aircraft (1), its tail unit (5) and the propeller (6) are unfolded. After they are deployed to the working position, the engine of the aircraft (1) is started.

The disadvantage of the device is that, firstly, to re-launch the UAV, it is necessary to charge the launcher from an external pressure source, which may be impossible in a special period or wartime during the solution of specialized tasks (combat tasks); secondly, the launch is possible only for UAVs whose design has a pressure tube, which sharply limits the versatility of the launcher; thirdly, if any element of the pneumatic system is damaged, the launch of the UAV becomes impossible.

The invention is based on the task of creating a method for launching UAVs carrying a shock load with an aviation or multi-plane airframe configuration that provides improved characteristics of its use.

In order to achieve the specified goal, the method for launching an unmanned aerial vehicle additionally includes the orientation of the tubular launcher in the azimuth and elevation planes, the input of a flight task into the on-board apparatus of the UAV, including, in particular, the time for the UAV to reach the apex of the ballistic flight trajectory, the installation of a cased propellant charge in the channel of the tubular launcher behind the UAV, obturation, acceleration and removal of the UAV from the tubular launcher under the influence of the total thrust of the propellant charge gases, and the launch of the UAV cruise engines at a time corresponding to the apex of the ballistic flight trajectory.

The proposed method for launching an unmanned aerial vehicle was carried out as follows:

To orient the tubular launcher in the azimuth and elevation planes, the tubular launcher is turned by the inner longitudinal axis of the tubular launcher channel to a specified azimuth angle toward the UAV flight position toward the potential target and the elevation angle of the tubular launcher is set. For this purpose, the longitudinal axis of the tubular launcher channel is given a horizontal position according to the control level in the longitudinal and transverse positions, zero settings are set on the sight, at which the bubbles of the longitudinal and transverse levels should be in the middle and the required angle between the horizon and the longitudinal axis of the tubular launcher channel is given according to the sight.

To achieve the maximum range of UAV reconciliation, a set of necessary data and commands is entered into its control unit to deploy its aerodynamic surfaces to the working (cruise) position, start the cruise engine and perform specialized tasks. In particular, a time delay is entered from the moment the UAV leaves the channel of the tubular launcher to the moment of reaching the apex of the ballistic flight trajectory, calculated according to the formula [5]:

where V ₀ is the initial throwing speed, m/s;

- the elevation angle of the tubular trifle mount (barrel) during firing, degrees;

G is the acceleration of gravity (9.81 m/sec ² ).

A UAV is installed in the channel of a tubular launcher, the aerodynamic surfaces of which are in a position that ensures the creation of a torque along the roll, i.e. folded.

The installation of a cased propellant charge in the channel of the tubular launcher behind the UAV is performed, which allows for the creation of pressure of gases formed during the combustion of the propellant charge made of gunpowder. The installation of a cased propellant charge is performed from the breech side of the channel of the tubular launcher.

A cased propellant charge is attached to the channel of the tubular launcher.

To ensure the UAV is removed from the tubular launcher channel, obturation is performed, during which the propellant charge made of ballistic powder of the RSI-12K, RSI-60, RSAM brands or pyroxylin powder of the 12/1Tr+12/7+VTX-10, 4/1+9/7+VTX-10 brands is ignited from the igniter through the firing connection. Due to the pressure of the gases on the propellant charge body (sleeve) and the channel of the tubular launcher, obtained during the combustion of the powder, the propellant charge body and the channel of the tubular launcher are stretched (elastically deformed), during which the propellant charge body, tightly pressing against a part of the channel of the tubular launcher (chamber), prevents the breakthrough of powder gases in the opposite direction from the UAV, thereby creating conditions under which the gases obtained from the combustion of the powder will expand behind the UAV.

The acceleration and removal of the UAV from the tubular launcher under the influence of the total thrust of the propellant charge gases is carried out by the pressure of the gases formed as a result of the combustion of the propellant charge powder and exerted on the UAV, which causes the UAV to move from its place in the channel of the tubular launcher and its movement along the channel of the tubular launcher toward its open end with continuously increasing speed and the ejection of the UAV outward in the direction of the axis of the channel of the tubular launcher.

At the moment of time advising the top of the UAV ballistic flight trajectory, under the action of the spring mechanism, the UAV aerodynamic surfaces are deployed from the position that ensures the creation of a roll torque to the working position that prevents the creation of a roll torque, and the UAV cruise engine is started. Depending on the glider design, there may be either one in the aircraft glider design of the UAV, or several in the multirotor glider design of the UAV.

The UAV, using its own cruise engine, begins moving to perform the flight mission tasks.

The device implementing the proposed method is shown in Fig. 2 and consists of a newly introduced cased propellant charge (15), a positioning device (16) (not shown in the graphic part), as well as the previously known tubular launcher (13) with a channel in the direction of its longitudinal axis, a UAV (14), a holding mechanism (11) and a trigger mechanism (12) (not shown in the graphic part).

The design of the UAV (14) includes, at a minimum, a newly introduced control unit (17), as well as the previously known cruise engine (18), aerodynamic surfaces (19), and a spring mechanism (20) (Fig. 3).

In a multi-rotor glider design, the UAV (14) contains several cruise engines (18) (Fig. 4).

The cased propellant charge (15) consists of a case (21), an igniter (22), a fire link (23) and a propellant charge (24). It may also include a nozzle (25), stabilizer blades (26) and a spring mechanism (20) for deploying them (Fig. 5).

The tubular launcher (13) contains grooves (27) (Fig. 6) made in the form of strip-shaped recesses winding along the walls of the channel of the tubular launcher (13).

In the first variant, the device implementing the proposed method operates as follows:

The tubular launcher (13) is oriented towards the normal flight position of the UAV (14) towards the potential target. The positioning device (16) sets the elevation angle of the tubular launcher (13). A time delay is entered into the control unit (17) of the UAV (14), from the moment the UAV (14) leaves the channel of the tubular launcher (13) until the moment of the UAV (14) reaching the apex of the ballistic flight trajectory, a set of necessary data and commands for deploying its aerodynamic surfaces to the normal position, starting the cruise engine and performing specialized tasks (flight mission).

A UAV (14) is installed in the channel of the tubular launcher (13), the aerodynamic surfaces (19) of which are in a position that ensures the creation of a torque along the roll, i.e. folded, and a cased propellant charge (15) is installed behind the UAV (14) in front of the holding mechanism (11).

In the channel of the tubular launcher (13), the holding mechanism (11) prevents radial displacements of the cased propellant charge (15) in the channel of the tubular launcher (13).

The action on the trigger mechanism (12) results in the operation of the igniter (22), which, through the fire connection (23) of the cased propellant charge (15), ignites the propellant charge (24).

The outflow of burning propellant gases of the propellant charge (24) begins. Under the action of the pressure of burning propellant gases of the propellant charge (24) in the channel of the tubular launcher (13), high pressure is created on the UAV (14) and the body (21) of the cased propellant charge (15), as well as on the walls of the tubular launcher (13).

As a result of the pressure of the burning propellant gases of the propellant charge (24) on the UAV (14), it moves from its place and cuts into the grooves (27) of the tubular launcher (13), rotating along them, moves along the channel of the tubular launcher (13) with a continuously increasing speed and is thrown out of the channel of the tubular launcher (13) in the direction of the axis of its channel.

The pressure of the burning propellant gases of the propellant charge (24) on the body (21) of the cased propellant charge (15) and the walls of the tubular launcher (13) causes them to stretch (elastic deformation), and the body (21) of the cased propellant charge (15), tightly pressing against the channel of the tubular launcher (13), prevents the breakthrough of the propellant gases towards the breech by the holding mechanism (11) and its destruction.

The pressure of the burning propellant gases of the propellant charge (24) on the bottom of the body (21) of the cased propellant charge (15) through a mechanical connection acts on the retaining mechanism (11) and allows it to be opened for repeated use of the tubular launcher (13).

After the UAV (14) leaves the channel of the tubular launcher (13), it begins to move along a ballistic trajectory while maintaining the roll torque specified by the movement along the grooves (27) of the tubular launcher (13).

At the moment of time corresponding to the apex of the ballistic trajectory of the UAV (14), on command from its control unit (17), the spring mechanism (20) deploys the aerodynamic surfaces (19) from the position that ensures the creation of a torque along the roll to the working position that prevents the creation of a torque along the roll, and the cruise engine (18) is started.

The UAV (14) begins to move using its own cruise engine (18) to perform the tasks of the flight mission entered into the control unit (17).

In the second variant, the device implementing the proposed method operates as follows:

The tubular launcher (13) is oriented towards the normal flight position of the UAV (14) in the direction of the potential target.

The positioning device (16) sets the elevation angle of the tubular launcher (13). The following are entered into the control unit (17) of the UAV (14): a time delay from the moment the UAV (14) leaves the channel of the tubular launcher (13) until the moment corresponding to the apex of the ballistic trajectory of the UAV (14), a set of necessary data and commands for deploying its aerodynamic surfaces to a normal position, starting the cruise engine and performing specialized tasks (flight mission).

A UAV (14) is installed in the channel of the tubular launcher (13), the aerodynamic surfaces (19) of which are in a position that ensures the creation of a torque along the roll, i.e. folded.

A cased propellant charge (15) is installed in the channel of the tubular launcher (13) behind the UAV (14), which is attached to the UAV (14), and a cased propellant charge (15) is installed behind the UAV (14), in front of the holding mechanism (11), which is attached to the UAV (14).

In the channel of the tubular launcher (13), the holding mechanism (11) prevents radial displacements of the cased propellant charge (15), secured to the UAV (14), in the channel of the tubular launcher (13).

The action on the trigger mechanism (12) results in the operation of the igniter (22), which, through the fire connection (23) of the cased propellant charge (15), ignites the propellant charge (24).

The combustion of propellant gases of the propellant charge (24) begins to flow out through the nozzle (25) of the cased propellant charge (15). Under the action of the pressure of the combustion of propellant gases of the propellant charge (24) in the channel of the tubular launcher (13), the holding mechanism (11) and the igniter (22) are destroyed, which are ejected from the channel of the tubular launcher (13) in the direction opposite to the direction of movement of the UAV (14), a shift from its place and a movement with rotation along the grooves (27) of the channel of the tubular launcher (13) with an increasing speed of the UAV (14) with a cased propellant charge (15) occurs, leading to their further ejection outward from the channel of the tubular launcher (13).

When a UAV (14) with a cased propellant charge (15) is ejected out of the channel of the tubular launcher (13) in the direction of the axis of its channel, under the action of the spring mechanism (20), the stabilizer blades (26) of the cased propellant charge (15) open and the movement of the UAV (14) with the cased propellant charge (15) begins along a ballistic trajectory while maintaining the torque along the roll.

At the moment of time corresponding to the apex of the ballistic trajectory of the UAV (14) with the encapsulated propellant charge (15), on command from the control unit (19), the UAV (14) by its spring mechanism (20) deploys the aerodynamic surfaces (19) from the position ensuring the creation of a roll torque to the working position preventing the creation of a roll torque, the cruise engine (18) is started, and the UAV (14) is separated from the encapsulated propellant charge (15).

The UAV (14) begins moving on its own cruise engine (18) to perform the tasks of the flight mission entered into the control unit (17).

The proposed method for launching an unmanned aerial vehicle, in contrast to the prototype method, by ensuring the movement of the UAV along a ballistic trajectory and the deployment of its aerodynamic surfaces to the working (cruise) position, as well as the launch of its cruise engine at the moment corresponding to the top of the ballistic trajectory with long-range movement of the UAV bearing an impact load over known ranges of the flight mission, provides improved characteristics for the use of UAVs bearing an impact load with an aviation or multi-rotor airframe configuration.

The proposed device, in contrast to the device implementing the prototype method according to the calculated data given in Table 2, makes it possible to deliver UAVs with an aviation or multirotor glider configuration to distances exceeding their currently known autonomous flight ranges in a minimum amount of time, which makes it possible to perform specialized tasks at points significantly more remote from the current autonomous flight ranges of UAVs of various types.

For the purposes of practical implementation of the proposed device, the cased propellant charge (15) with all its components can be made from the mass-produced G-35 cartridge case for the 152 mm howitzer type 2A65 or the 9D160 missile part for the 9K57 multiple launch rocket system projectiles.

Sources of information:

1. Patent for invention of the Russian Federation No. 2507468 “Method for launching an unmanned aerial vehicle and a jet complex for its implementation (variants)”, application 2012110331/11 dated 20.03.2012, published 20.02.2014 Bulletin No. 5

2. Patent for invention of the Russian Federation No. 2784099 "Method for launching and controlling the flight of an unmanned aerial vehicle (UAV) from a carrier aircraft", application 2022112533 dated 05.05.2022, published: 23.11.2022 Bulletin No. 33

3. US Patent No. US7410124B2 "Light Aircraft and Pneumatic Launcher", application US10/509,659 from 2004-02-19, published 2008-08-12

4. Weapons and Technologies of Russia: Encyclopedia of the 21st Century, Volume III, “Armament of the Navy” - Moscow: Publishing House “Weapons and Technologies”, 2001, pp. 97-102

5. External ballistics: a tutorial / A.V. Guskov, K.E. Milevsky, A.V. Sotenko. - Novosibirsk: Publishing house of NSTU, 2010. - 188 p.

6. 55th Anniversary Scientific Conference of Postgraduate, Master's and Undergraduate Students of the Belarusian State University of Informatics and Radioelectronics // Layout diagrams of unmanned aerial vehicles, 2019. URL: https://libeldoc.bsuir.by/bitstream/123456789/36951/1/Nguyen_Kompnovochnyye.pdf (Accessed: 14.01.2024).

Claims (4)

1. A method for launching an unmanned aerial vehicle, which consists in placing the unmanned aerial vehicle with fully folded aerodynamic surfaces in a tubular launcher, holding it in the tubular launcher, unfastening the unmanned aerial vehicle’s fasteners, filling the tubular launcher with starting gas, applying the starting gas force to accelerate the unmanned aerial vehicle, separating the unmanned aerial vehicle from the tubular launcher and deploying the aerodynamic surfaces of the unmanned aerial vehicle into a working position, characterized in that before placing the unmanned aerial vehicle with fully folded aerodynamic surfaces in the tubular launcher, the tubular launcher is oriented in the azimuth and elevation planes, and a flight mission is entered into the on-board equipment of the unmanned aerial vehicle, including, in particular, the time to reach the unmanned aerial vehicle of the apex of the ballistic flight trajectory, and after placing the unmanned aerial vehicle with fully folded aerodynamic surfaces in the tubular launcher, a cased propellant charge is installed in the channel of the tubular launcher behind the unmanned aerial vehicle, after which the unmanned aerial vehicle is obturation, accelerated and removed from the tubular launcher under the influence of the total thrust of the propellant charge gases, the deployment of the aerodynamic surfaces into the working position of the unmanned aerial vehicle is performed at a time corresponding to the apex of the ballistic flight trajectory, the launch of the cruise engine of the unmanned aerial vehicle is performed at a time corresponding to the apex of the ballistic flight trajectory. 2. A device for launching an unmanned aerial vehicle, consisting of a tubular launcher connected to each other with a channel in the direction of its longitudinal axis, a holding mechanism and a trigger mechanism, characterized in that a cased propellant charge is additionally introduced, containing the propellant charge itself, a case, an igniter and a fire connection, and a positioning device for positioning in the azimuth and elevation planes of the tubular launcher. 3. The device according to item 2, characterized in that the cased propellant charge contains a nozzle, stabilizer blades and a spring mechanism, while the cased propellant charge is designed with the possibility of connection to an unmanned aerial vehicle. 4. The device according to item 3, characterized in that the propellant charge is made of gunpowder, and the tubular launcher contains grooves on the inner surface.