RU2338150C1 - Birotating jet shell - Google Patents

Abstract

FIELD: weapons.

SUBSTANCE: invention concerns combat equipment and is intended for conducting fight and struggle against terrorists. The birotating jet shell contains controls of a course of movement of a shell on pitch angles, hunting and heeling, the case of axisymmetric form made of rotating and unrotative parts. The explosive device, control system devices, drives of course of movement controls, hunting and heeling, a fuel tank, a birotating gas turbine engine with the jet nozzle, working on liquid fuel and containing air inlet, compressor, combustion chamber and a turbine, forming an internal and external rotors divided by bearing support, are established in the case. Thus the rotor of the compressor and the turbine driving wheel form an internal rotor, and an air inlet, the compressor stator and the combustion chamber form an external rotor which is rigidly connected to a rotating part of the case. The tank with fuel is connected via engine feed line with the fuel pump with a pump drive established, to the combustion chamber, and the jet nozzle is executed as an unrotative part of a shell and established on a bearing support between the internal and external rotors. Controls are executed in the form of four rotary aerodynamic wheels.

EFFECT: increase of firing accuracy and expansion of shell functionality.

4 cl, 11 dwg

Description

The invention relates to military equipment, in particular to means of warfare, border protection and defense, and the fight against terrorists. A weapon design has been developed for installation on a mobile installation for the purpose of remote control of fire during the assault on concrete or armored structures.

Known rockets according to the patent of Russian Federation No. 2272984, containing a housing, an explosive device and a solid fuel engine.

The disadvantage of the projectile is the low efficiency of solid propellant engines.

Missiles are known that contain an axisymmetric body, an explosive device, a solid fuel tank and a solid fuel rocket engine, a control system and aerodynamic control wheels mounted on the body from the outside, see the Internet site http: //rbase.new-factoria. ru. Appendix 1, prototype.

Disadvantages: limited flight range, low hit accuracy, high aerodynamic drag of the aerodynamic rudders and the large dimensions and weight of the projectile with a relatively small explosive device, low projectile speed due to the use of solid fuel having lower energy properties compared to liquid fuel.

The objective of the invention is to increase the projectile flight speed, accuracy and firing range, reducing the weight and dimensions of the projectile with a certain explosive device power and projectile range.

The solution to this problem was achieved in a biotational missile, including controls for the course of the projectile along the pitch, yaw and roll angles, an axisymmetric body made of rotating and non-rotating parts, inside of which an explosive device, control system devices, and actuators of the projectile’s course are installed in the angles of pitch, yaw and roll, fuel tank, a bi-jet gas turbine engine with a jet nozzle running on liquid fuel and containing an air intake, A compressor, a combustion chamber and a turbine forming internal and external rotors separated by bearing bearings, while the compressor rotor and the turbine impeller form an internal rotor, and the air intake, compressor stator and combustion chamber form an external rotor that is rigidly connected to the rotating part of the housing, the tank connected to the fuel with a fuel line in which a fuel pump with a pump drive is installed, with a combustion chamber, and the jet nozzle is made as a non-rotating part of the projectile and is mounted on bearing bearings ah between the inner and outer rotors, the rate controls are made in the form of four rotary aerodynamic control surfaces mounted on the outer surface of the non-rotating housing part, and the control system devices are installed in the instrument container connected to a nonrotating part of the projectile. The projectile can be equipped with an engine controller and an on-board computer, while the pump drive is connected to an engine controller, which is connected to the on-board computer. The projectile can be equipped with a transmitter and receiver connected to the on-board computer with an antenna and a receiver of the global positioning system, while the receiver of the global positioning system is connected to the antenna. The projectile can be equipped with a fuse controller connected to the on-board computer, while the explosive device is also connected to the on-board computer.

Patent studies have shown that the proposed technical solution has novelty, inventive step and industrial applicability.

The invention is illustrated in figure 1 ... 11, where:

figure 1 shows a schematic diagram of the simplest version of the projectile,

figure 2 shows a section along aa

figure 3 shows a section bB,

figure 4 ... 6 shows a diagram of a control system,

Fig.7 shows a diagram of a projectile with a global positioning system,

on Fig shows a diagram with a controlled detonation of an explosive device,

figure 9 shows a diagram of a projectile with a global positioning system,

figure 10 shows the control circuit for the pitch angle,

figure 11 shows the control circuit for the yaw angle.

The projectile (Fig. 1) contains an axisymmetric body consisting of two parts: a rotating part of the body 1 and a non-rotating part of the body 2. An explosive device 3 and a fuel tank 4 are installed inside the rotating part of the body 1. Preferably, the explosive device 3 and the fuel tank 4 are toroidal for dynamic balancing of the projectile during rotation during flight and as fuel is consumed.

Also inside the rotating part of the housing 1 is installed a gas turbine engine 5 operating on liquid fuel. The projectile has a control system 6 installed inside the non-rotating part of the housing 2, which avoids the large loads of centrifugal forces on the instruments and sensors.

The gas turbine engine 5 consists of an air intake 7, a compressor 8, which in turn consists of a compressor stator 9 and an internal rotor 10, a combustion chamber 11 to which a fuel line 12 is connected with a fuel pump 13 having a pump drive 14. A turbine 15 is installed behind the combustion chamber 11 comprising a nozzle apparatus 16 and an impeller of a turbine 17. A jet nozzle 18 is installed at the output of the turbine 15. The jet nozzle 18 comprises an inner part of the jet nozzle 19 and an outer part of the jet nozzle 20. The jet nozzle 18 is separate from gas turbine engine 5 and is installed relative to the rotating part of the engine 5 on the bearings of the nozzle 21, for example, rolling or sliding bearings, with the possibility of rotation relative to them. However, in flight, the jet nozzle 18 does not rotate, and all other nodes of the gas turbine engine 5 and the rotating part of the housing 1 rotate.

On the shaft 22 are installed all the nodes of the internal rotor 23, namely the compressor rotor 10 and the impeller of the turbine 17. All other nodes of the gas turbine engine 5 form an external rotor, which includes a supersonic air intake 7, the compressor stator 9 and the combustion chamber 11.

The control system 6 is located in a container fixed in the jet nozzle 18, i.e. does not rotate in flight, which reduces the load on the sensors and control system devices.

The shaft of the engine 22 with the compressor rotor 10 and the turbine rotor 17 mounted on it forms the internal rotor of the gas turbine engine 23, and the compressor stator 9, the combustion chamber 11 and the nozzle apparatus of the turbine 6 form the external rotor of the gas turbine engine rotating in the other direction, i.e. . the gas turbine engine 5 is made according to the birotative scheme. Between these rotors mounted engine mount 24 (figure 1).

Four aerodynamic rudders 25 with rudder drives 26 are installed on the outer surface of the non-rotating part of the body 2 (FIGS. 1, 2, and 3). The rudder drives 26 are connected to the control system 6 and allow controlling the projectile movement along pitch — α, yaw — β and roll - γ.

The external rotor is rigidly connected to the housing 2 and rotates in flight on the engine mounts 24 in the direction opposite to the rotation of the internal rotor 23, i.e. the gas turbine engine and the entire projectile are made according to the birotative scheme, which gives significant advantages, described below.

To the fuel pump 13 is docked the drive of the pump 14, which is connected to the control system 6 (figure 2). The control system 6 (Figs. 4 ... 6) contains an on-board computer 27, to which an accelerometer 28 and a magnetometer 29 are connected, for measuring the angles of orientation of the projectile in flight. All communications between electronic devices and sensors are made by wired communication channels 30.

To the on-board computer 27 can be connected to the transmitting and receiving device 31 (Fig. 5), to which the antenna 32 is connected. The antenna 32 has an annular shape, and the portion of the fixed housing 2 in the region where the antenna 32 is located is made transparent. Inside the fixed part of the housing 2, a receiver of the global positioning system 33 (FIG. 4) can be installed, which is also connected to the on-board computer 27 and to the antenna 32. All connections are made by wire communications 30. The system includes satellites 33 connected to the antenna 32 radio channels.

Perhaps the use of the circuit (Fig.9) undermining with the controller of the fuse 34 connected to the on-board computer 27 and to the explosive device 3.

Figure 10 and 11 shows a diagram of the flight of the projectile along trajectory 35, while figure 10 shows the control diagram for pitch angle α, and in figure 11 for yaw angle β. The control over the roll angles (rotation) γ is not shown in FIGS. 1 ... 11.

When using a projectile in the operational memory of the on-board computer 27 enter the initial flight data. The projectile starts from the launcher, to do this, start the gas turbine engine 5, while the on-board computer 27 sends a command to the pump drive 14 and to the fuel pump 13. Fuel is supplied from the fuel tank 4 to the combustion chamber 11, where it is ignited using an electric igniter (in FIG. 1 ... 11 not shown). The combustion products drive the impeller of the turbine 17, which spins the inner rotor 23 through the shaft 22. The outer rotor begins to rotate in the opposite direction, i.e. the rotating part of the housing 1 rotates in flight, which ensures stabilization of the projectile and improves firing accuracy. During rotation, centrifugal forces press the fuel against the outer walls of the fuel tank and create pressure at the inlet to the fuel pump without a boost system. In addition, as the fuel is consumed, the balance of the projectile is not disturbed. The use of liquid fuel, as well as atmospheric oxygen, makes it possible to obtain an advantage in flight range in comparison with solid propellant rockets, since the calorific value of liquid fuel is 3 ... 4 times greater than that of solid fuel, and an oxidizing agent in the form of atmospheric oxygen is taken from the atmosphere.

During the flight, the receiver of the global positioning system 33 (GLONAS or GPS systems) receives a signal from three satellites of the system via radio channels and determines its own coordinates. Using the program in place by means of the on-board computer 27 affecting the drive of the pump 14 and then on the fuel pump 13, it is possible to reduce or increase the thrust of the gas turbine engine 5 and thereby change the flight path of the projectile from launch point “A” to target “B” in range.

On command from the on-board computer 27 transmitted to the blast controller 34 (Fig. 9), the explosive device 3 can be detonated, for example, in flight.

The pitch, yaw and roll angles are controlled according to FIGS. 10 and 11 by rotating the conical fairing of the jet nozzle 25. The initial data on the angular orientation of the projectile are constantly monitored by the accelerometer 28 and magnetometer 29. The magnetometer 29 determines the projection azimuth, and the accelerometer 28 determines its deviation from directions of the gravity vector. The placement of these sensors in the non-rotating part of the housing 2 eliminates the influence of centrifugal forces on the readings of the sensors.

The application of the invention allowed:

- increase the speed of the projectile by 2 times, because the relative speed of rotation of the rotors is equal to the sum of the speeds of their rotation, to reduce the dimensions of the device by 2 times compared with the usual scheme, to reduce centrifugal loads on the nodes and parts by 4 times;

- to increase the power and efficiency of the gas turbine engine with smaller dimensions, to ensure good stabilization of the projectile in flight due to its rotation with a huge angular velocity;

- reduce the load on the instruments and sensors of the projectile control system, stabilize the position of the projectile in flight;

- improve the handling of the projectile in flight.

Claims (4)

1. A rotational missile, including controls for the course of the projectile movement along the pitch, yaw and roll angles, an axisymmetric case made of rotating and non-rotating parts, an explosive device, control system devices, actuators for controlling the course of the projectile movement along the pitch angles are installed inside the case , yaw and roll, fuel tank, a biotational gas turbine engine with a jet nozzle running on liquid fuel and containing an air intake, a compressor, a combustion chamber and a turbine, o the internal and external rotors that are separated by bearings, the compressor rotor and the turbine impeller form the internal rotor, and the air intake, compressor stator and combustion chamber form the external rotor, which is rigidly connected to the rotating part of the housing, and the fuel tank is connected by a fuel line, in which a fuel pump with a pump drive and a combustion chamber is installed, and the jet nozzle is designed as a non-rotating part of the projectile and is mounted on bearing bearings between the inner and outer rotors while the heading controls are made in the form of four rotary aerodynamic rudders mounted on the outer surface of the non-rotating part of the body, and the control system devices are installed in the instrument container connected to the non-rotating part of the shell. 2. The rotational missile according to claim 1, characterized in that it is equipped with an engine controller and an on-board computer, while the pump drive is connected to an engine controller, which is connected to the on-board computer. 3. The rotational missile according to claim 2, characterized in that it is equipped with a transmitter and receiver connected to the on-board computer with an antenna and a receiver of the global positioning system, while the receiver of the global positioning system is connected to the antenna. 4. The rotational missile according to claim 2 or 3, characterized in that it is equipped with a fuse controller connected to the on-board computer, while the explosive device is also connected to the on-board computer.

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