WO2022231478A1

WO2022231478A1 - Device and method for launching and accelerating a uav with a turbojet engine

Info

Publication number: WO2022231478A1
Application number: PCT/RU2022/050134
Authority: WO
Inventors: Глеб Владимирович ПОНОМОРЕНКО
Original assignee: Глеб Владимирович ПОНОМОРЕНКО
Priority date: 2021-04-30
Filing date: 2022-04-21
Publication date: 2022-11-03
Also published as: RU2770510C1

Abstract

The invention relates to takeoff and acceleration systems for unmanned aerial vehicles. A method comprises the launching and acceleration of aircraft up to take-off speed using the mortar method, characterized by opening the aircraft nozzle, starting the engine, inflating a receiver with exhaust gases of the aircraft turbojet engine, adjusting the pressure required for launching using a pressure-reducing valve of the receiver, releasing a wad with the aircraft fixed thereto by means of a lock starter mechanism, separating the wad and bringing the nozzle of the turbojet engine to its normal state after the latter exits the mortar barrel. The device for implementing the method includes a mortar barrel rigidly mounted on a storage receiver equipped with a pressure-reducing valve, tightly inserted and fixed, by a lock starter mechanism arranged on the mortar barrel, into the wad barrel, on which the tail section of the aircraft is installed and secured by means of a fixation device. The aircraft is launched according to the mortar principle, wherein the energy source is the turbojet engine of the aircraft itself.

Description

DEVICE AND METHOD FOR STARTING, ACCELERATING UAV WITH TURBOJET ENGINE

Technical field

SUBSTANCE: invention relates to rocket technology, namely to take-off and acceleration systems for unmanned aerial vehicles.

State of the art

One of the main stages of the flight of any aircraft from the earth's surface is its acceleration to a speed at which the lift and stability required for the flight are provided (the so-called evolutionary speed).

From the prior art, various solutions are known aimed at implementing methods for accelerating aircraft to an evolutionary speed, such as:

- Takeoff on the airplane principle;

- Takeoff due to the creation of excess thrust in excess of the weight of the BILA;

-Acceleration of the aircraft with the help of a catapult.

The invention relates to an ejection method for accelerating unmanned aerial vehicles.

The launch method in existing catapults is to create and accumulate energy, with its subsequent transformation into force, which makes it possible to accelerate the aircraft along the guide devices.

Specific examples are:

- catapults on elastic elements;

- pneumatic catapults;

- steam catapults (on aircraft carriers);

- electromagnetic catapults (railguns). All examples of catapults cited above have external sources of energy and rail guides along which the accelerated vehicle moves.

Catapults on elastic elements most often use rubber cords as an energy storage device. Having a fairly simple design, these catapults are used only for accelerating very light BILs and having a low evolutionary speed. This is due to the low energy consumption of the elastic elements of the catapult.

Pneumatic catapults use compressed gas energy stored in high-pressure cylinders (receiver) to accelerate.

The catapult includes:

- rail guides;

- high pressure receivers; high pressure compressors; pneumatic cylinders;

- transmissions that transmit energy to the carriage moving along the guides to which the aircraft is attached;

- deceleration devices for moving mechanisms to dampen the residual energy of the piston and transmission after the launch of the aircraft.

Pneumatic catapults are quite effective for accelerating UAVs and are widely used in various unmanned systems. However, they have a bulky design, are complex and unsafe in operation, and have a short service life of the units.

Steam catapults are used on aircraft carriers. In fact, these are pneumatic catapults that use the energy available on board, generated by running steam boilers. To launch UAVs in land conditions, their use is impractical.

Electromagnetic catapults, which are currently gaining popularity, have advantages in speed controllability and acceleration acceleration, which is very important for smooth and uniform acceleration of aircraft. But the use of railguns in unmanned aerial vehicles is currently not justified. Known mortar launch method, which is widely used in the practice of launching missiles for various purposes.

Wikipedia gives the following definition of a mortar launch:

“Mortar launch (“cold” start) is a method of launching a rocket, in which it is ejected from the launcher (transport and launch container) due to pressure created in a closed volume by some source located outside the rocket. Such a source can be, for example, a powder _ pressure accumulator _ (PAL) or a steam and gas generator. At the same time, the rocket engine starts after the rocket leaves the launcher.

There are a large number of patents and real samples, but all of them are only methods for quickly ejecting an item from a transport-launch container, but not for accelerating the aircraft to an evolutionary speed. The method of acceleration in all cases of using a mortar launch is the use of excess thrust of the engine itself or powder boosters. In addition, they all have external energy sources. These are either high-pressure cylinders, or the so-called expelling powder charges. In the RF patent N°2240489, such an expelling charge is a low-thrust engine, while acceleration is performed, again, by a high-thrust powder engine.

That is, all the solutions given in the patents and the known ejection launch devices are not devices for accelerating the aircraft.

Disclosure of invention

The technical problem to be solved by the claimed invention is the acceleration of unmanned aerial vehicles. devices to the evolutionary speed at ground launch at minimal cost.

The technical result of the claimed invention lies in the fact that the start and acceleration of an unmanned aerial vehicle is carried out "according to the mortar" principle, and the power source is the turbojet engine of the device itself, which can provide a ground launch of a group of unmanned aerial vehicles without external energy supply at minimal cost.

To achieve this technical result, a method is proposed for launching and accelerating at least one unmanned aerial vehicle with a turbojet engine, which consists in launching and accelerating the aircraft to takeoff speed using a mortar method characterized by opening the nozzle of the aircraft, starting the aircraft engine, inflating the receiver with exhaust gases of the aircraft turbojet engine. apparatus, by adjusting the pressure reducing valve of the receiver necessary to start the pressure, releasing the wad with the unmanned aerial vehicle fixed on it by means of a locking-starting mechanism, separating the wad from the unmanned aerial vehicle and bringing the nozzle of the turbojet engine to the normal state after the latter exits the mortar barrel.

It is also proposed a device for launching and accelerating unmanned aerial vehicles with a turbojet engine, including at least one mortar barrel, rigidly mounted on a receiver tank equipped with a pressure reducing valve, tightly inserted and fixed by a locking-starting mechanism located on the mortar barrel into the wad barrel, on in which the aircraft with a turbojet engine is installed and fixed with a latch, while the nozzle of the turbojet engine of the aircraft is made dual-mode with the possibilities of both full opening and standard and is installed in the wad gas pipeline channel connected to the receiver tank. In preferred cases, in cases where multiple mortar barrels are used:

- the container-receiver is equipped with a ventilation valve;

- between the wad and the receiver there are stem atmospheric and receiver valves;

- before starting the engines, the atmospheric valves of the trunks are opened, after starting, the receiver valve of one of the trunks is opened and the atmospheric valve of this trunk is closed, after the aircraft exits the trunk, the receiver is ventilated by means of the ventilation valve.

The combination of the above essential features leads to the fact that:

- Provides quick start and acceleration to evolutive speed without the use of powder accelerators and external energy sources;

- The launch cost is negligible compared to analogues;

- There is an opportunity to ensure the mass launch of unmanned aerial vehicles from a ground launcher to create a "swarm".

Thus, the proposed solution makes it possible to reduce the cost of ground launch of vehicles by more than 40 times.

Brief description of the drawings

In FIG. 1-3 shows diagrams of a single-barreled mortar, as shown in FIG. 1 in the initial state, the view of figure 2 in the boost mode of the receiver, the view of fig. 3, 4 in the UAV acceleration mode, the positions indicate:

1- Barrel;

2- Unmanned aerial vehicle (UAV)

3- UAV turbojet engine;

4- Lock-trigger mechanism;

5- wad;

6- Receiver; 7- Receiver pressure reducing valve.

In FIG. 5-7 shows diagrams of a multi-barreled mortar, as shown in FIG. 5 in its original state, as shown in FIG. 6 at the moment of readiness for launch, as shown in FIG. 7 in the mode of readiness for launch and pressurization of the receiver, positions are indicated:

1- First trunk;

2- Unmanned aerial vehicle in the first barrel (UAV-1)

3-Turbojet engine UAV-1

4- Locking and trigger mechanism of the first barrel;

5- Wad of the first trunk;

6- Receiver;

7- Reducing valve of the receiver;

8- Stem atmospheric valve of the first stem (SAK-1);

9- Stem receiver valve of the first stem (SRK-1)

10- Ventilation valve of the receiver;

11- Second trunk;

12- Unmanned aerial vehicle in the second barrel (UAV-2);

13- UAV-2 turbojet engine

14- Locking and trigger mechanism of the second barrel;

15- Wad of the second trunk;

16- Barrel atmospheric valve of the second barrel (SAK-2);

17- Stem receiver valve of the second stem (SRK-2)

In FIG. 8.9 shows diagrams of a multi-barreled mortar, view from Fig. 8 in the receiver ventilation mode, as shown in FIG. 9 in the mode of boosting the receiver with the second UAV, positions are indicated:

4- Locking and trigger mechanism of the first barrel;

7- Reducing valve of the receiver;

8- Stem atmospheric valve of the first stem (SAK-1);

9- Stem receiver valve of the first stem (SRK-1); 10- Ventilation valve of the receiver;

17- Stem receiver valve of the second stem (SRK-2)

Implementation and examples of the invention

The claimed invention according to FIG. 1-9 is a method and device operating on the principle of a mortar, where acceleration occurs along the barrel 1 by creating pressure behind the aircraft 2, and the source of energy converted into pressure and force is the gas generator of the turbojet engine 3.

In fact, the claimed device is a pneumatic catapult that uses the energy of compressed gas.

From the classic pneumatic catapult, the proposed method and device has the following differences:

- the barrel of 1 mortar is used as a guide system;

- accelerated UAV 2 is induced inside the barrel 1;

- barrel 1 with wad 5 is used as an expansion cylinder that converts the accumulated energy of compressed gases; in the mortar there is no transmission that transmits energy from the expansion cylinder to the aircraft 2 - the energy is transmitted directly to the accelerated vehicle 2 through the wad 5; no braking of the pneumatic cylinder rod and transmission is required - a one-time cheap wad 5 simply flies out of the barrel;

- no external compressor is required to accumulate the energy of the compressed gas; the energy source is the gas generator of the turbojet engine 3 accelerated by the UAV 2;

- the pressure in the receiver 6 is extremely low - 1.7-2 atm., in contrast to 20-60 atm. on existing catapults and in this sense the catapult is absolutely safe.

- the energy accumulation time is extremely short - 4-5 seconds and is incommensurable with the receiver pumping 6 bOatm. compressor; one receiver 6 can operate several barrels 1.11 of Fig. 2, which ensures the launch of the UAV group 2.12.

The simplest implementation of the proposed method in the form of a single-barreled mortar is shown in Fig.1-4

The simplest "mortar" consists of a barrel 1, rigidly connected to the receiver 6. The barrel is a smooth tube of circular cross section. The receiver connected to the barrel is a container that can withstand an overpressure of 200 kPa.

An unmanned aerial vehicle (UAV) 2 with a turbojet engine 3, placed on a wad 5, is installed in the barrel.

The wad 4 is inserted into the barrel with a seal that maintains pressure in the receiver 6. The UAV 2 is installed on the wad 5 with the tail part and fixed on it with a latch (not shown in the drawings), which provides a rigid connection between the UAV 2 and the wad 5, when they are in the barrel 1 and their undocking at the exit from the barrel 1.

The nozzle of the turbojet engine 3 is installed in a through gas channel located on the wad 5. The gas channel of the wad 5, on one side, is tightly connected to the adjustable nozzle of the turbojet engine 3, and on the other side it discharges gases into the receiver 6.

The turbojet engine 3 of the UAV 2 has an adjustable nozzle apparatus having two modes - with a fully opened nozzle and with a regular section nozzle. The control of the modes of the nozzle apparatus of the engine 3 is carried out either by changing the position of the central body of the nozzle, or by opening the flaps.

In the open nozzle mode, the thrust of the TRD 3 disappears, while the gas generator of the engine 3 is able to operate at a back pressure equal to the normal pressure behind the turbine.

On the wad 5, a device is mounted that controls the modes of the nozzle. When connecting the UAV with the wad 5 in the barrel 1 of the mortar, the nozzle is mechanically opens, and the thrust of the engine 3 is exchanged for the pressure in the receiver 6. When exiting the barrel 1, the nozzle apparatus is brought to its normal state and the thrust necessary for the flight of the UAV 2 appears.

The barrel 1 is equipped with a lock-trigger mechanism 4, which ensures the fixation of the wad from the UAV in the barrel before launch and release them upon launch.

The receiver 6 has a pressure reducing valve 7, which maintains the set pressure in the receiver 6.

The proposed method, according to Fig. 1-9 is to give speed to the unmanned aerial vehicle 2, when moving along the barrel of the mortar 1. Acceleration is carried out due to the gas pressure behind the wad 5, on which the UAV 2 is installed. up to a pressure corresponding to the pressure behind the turbojet 3 turbine.

In FIG. 2 shows the pressurization mode of the receiver 6 of the mortar. TRD 3 is started and delivers exhaust gases through the air duct to the receiver 6. To maintain the set pressure in the receiver 6, a pressure reducing valve 7 is installed, which discharges excess gas, acting as a jet engine nozzle apparatus. Valve 7 maintains the pressure in the receiver at about 170=200 kPa. This pressure creates a force on wad 5.

On FIG. 3. shows the process of acceleration of the UAV 2. The lock-trigger mechanism 4 releases the wad 5, which begins to move along the trunk

one.

On FIG. 4. the exit of the UAV 2 from the trunk 1 is shown. The wad 5 is separated from the aircraft 2 and falls. The nozzle of the engine 3 assumes a normal position, providing the thrust necessary for flight. The wad retainer to the engine nozzle is separated at the moment the UAV 2 exits the barrel 1. Implementation example

A feature of the invention is the possibility of implementing a multi-barreled mortar of FIG. 5-9, using one receiver 6 to accelerate UAVs 2 and 12 along several barrels in example 1 and 11.

Double-barreled mortar according to Fig. 5-7 includes the following elements: Receiver designed to store compressed gas energy 7 Mortar barrels 1 and 11;

The valve system that controls the flow of gases in each barrel located between the wad and the receiver:

• stem atmospheric valve of the first stem (SAK-1) 8;

• stem receiver valve of the first stem (SRK-1) 9;

• stem atmospheric valve of the second stem (SAK-2) 16;

• stem receiver valve of the second stem (SRK-2) 17; Locking and triggering mechanisms of trunks 4 and 14;

Valves that control pressure and gas flows in the receiver 6:

• pressure reducing valve of the receiver 7 ;

• vent valve of the receiver 10;

- Wads 5, 15, which are accelerating unmanned aerial vehicles 2 and 12.

The launch of two UAVs 2 and 12 occurs in the following order:

The atmospheric valves of the SAK-1 and SAK-2 barrels open. The engines of both UAVs are sequentially started. The gases from the engines through the SAK are discharged outside into the atmosphere and the mortar goes into ready-to-launch mode Fig.6

To accelerate the first aircraft, the stem receiver valve 9 of the first stem of the SRK-1 is opened, and the SAK-1 is closed. The gases from the engine 3 enter the receiver 6 and pressurize, increasing the pressure in it. After reaching the critical value, the reduction valve 7 opens, discharging excess gases into the atmosphere and maintaining the operating pressure in the receiver 6. Due to this pressure, a force is created on the wad 5, which ensures mortar acceleration. Start and acceleration occurs after the wad 5 is removed from the stopper 4. The force acting on the wad 5 accelerates the UAV 2 until the wad 5 leaves the barrel 1. In the free space, the wad 5 is separated from the UAV 2 and the wing opens (not shown in the drawings).

After the UAV 2 leaves the barrel 1, the receiver is ventilated

Fig. eight

Through the freed barrel 1, the gases exit and the pressure is released, after which the vent valve 10 opens on the receiver 6, through which the heated air is replaced by atmospheric air.

To ensure the launch of the second UAV 12 SRK-1 is closed, isolating the first barrel 1 from the receiver 6. The ventilation valve 10 is also closed, sealing the receiver 6.

The firing operation is repeated for the second barrel 12 in the same order as shown in Fig. 9 for the first barrel.

The SRK-2 is opened and the SAK-2 is closed, after which the receiver 6 is pressurized from the second barrel 12, followed by the launch of the second UAV 12 and the ventilation of the receiver 6. The pressure relief valve 7 of the receiver 6 serves to quickly relieve pressure, if necessary, stop the pressurization of the receiver 6, for example, when the engine suddenly stops 13.

Claims

Claim

1. A method for launching and accelerating at least one unmanned aerial vehicle with a turbojet engine, which consists in launching and accelerating the aircraft to takeoff speed using a mortar method, characterized by opening the nozzle of the aircraft, starting the aircraft engine, inflating the receiver with exhaust gases of the turbojet engine of the aircraft, adjusting the required to start the pressure by the pressure reducing valve of the receiver, release the wad with the unmanned aerial vehicle fixed on it by means of a locking-start mechanism, separate the wad from the unmanned aerial vehicle and bring the nozzle of the turbojet engine to the normal state after the latter exits the mortar barrel.

2. A device for launching and accelerating unmanned aerial vehicles with a turbojet engine, including at least one mortar barrel, rigidly mounted on a receiver tank equipped with a pressure reducing valve, tightly inserted and fixed by a locking-starting mechanism located on the mortar barrel into the wad barrel, on which an aircraft with a turbojet engine is installed and secured with a latch by the tail section, while the nozzle of the turbojet engine of the aircraft is made dual-mode with the possibilities of both full opening and standard and is installed in the wad gas pipeline channel connected to the receiver tank.

3. A device for launching and accelerating unmanned aerial vehicles with a turbojet engine according to claim 2, characterized in that the receiver is equipped with a ventilation valve.

4. A device for launching and accelerating unmanned aerial vehicles with a turbojet engine according to item 2, characterized in that atmospheric and receiver valves are located between the wad and the receiver. A method for launching and accelerating unmanned aerial vehicles with a turbojet engine according to claim 1, characterized in that before starting the engines, the atmospheric valves of the trunks are opened, after launch, the receiver valve of one of the trunks is opened and the atmospheric valve of this trunk is closed, after the aircraft exits the trunk through the ventilation valve ventilate the receiver.