RU2350893C2 - Supersonic jet shell - Google Patents

Abstract

FIELD: weaponry.

SUBSTANCE: invention relates to combat jet equipment and can be used in conducting battle and to fight against terrorists. The proposed jet shell has axially-symmetric casing housing explosive, shell trajectory control system, onboard computer connected to engine controller and fuel tank. Note that the shell incorporates four liquid-fuel gas turbine jet engines. Each of the aforesaid engines comprises, air intake, compressor, combustion chamber and turbine. Note that the compressor rotor and turbine wheel rotor make the engine rotor, while the engine stator is formed by air intake, compressor stator, combustion chamber and supersonic nozzle.

EFFECT: higher shell velocity, range and accuracy along with expanded performances.

4 cl, 7 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 machine for shooting weapons according to US Pat. RF №2082932, IPC 6 F41A 31/00, publ. 06/27/97, the Machine contains a massive base, a fixture for fixing and a back emphasis. The device is not intended for military operations and does not contain a remote control system.

A known installation for mounting weapons on a vehicle according to US Pat. RF №2026527, IPC 6 F41A 23/34, a prototype that contains a barrel, horizontal and vertical displacement drives and limiters of the angles of rotation of the barrel in horizontal and vertical planes. Shooting is carried out from the vehicle, aiming is carried out by the shooter by horizontal and vertical rotation of the barrel manually. The movement of the vehicle and its turn provide an additional expansion of the shelling sector.

The disadvantages of the device are that it is not intended for remote control of shooting, and the shooter is exposed to significant danger during the fighting. A remote control (security) system is not provided at all.

A known method and device for radio wave detection of an intruder according to the patent of the Russian Federation for invention No. 2145441. This alarm method is designed to enhance border protection in addition to other well-known activities. To achieve this goal, the invention poses the following technical tasks: to introduce features that make it possible to synchronize and power the device and receiver spaced apart in the space of the sensor, to introduce features that specify the procedure for adjusting the phase of the spatial wave.

The technical result is achieved by the fact that in the method and device with the transmitter and receiver of the RF oscillations spaced apart, the lines of the surface radio waves perform several functions: the sensitive element of the guard detector, the LF line, time synchronization, and the power line of the transmitter.

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

Disadvantages: limited flight range, low accuracy, high aerodynamic drag of the aerodynamic rudders and 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 of this problem was achieved in a supersonic rocket containing an axisymmetric body inside which an explosive device, control system devices, a fuel tank, a jet engine are installed, characterized in that four supersonic gas turbine engines running on liquid fuel are used as a jet engine, containing a supersonic air intake, a compressor, a combustion chamber and a turbine forming an engine rotor and a housing separated by bearings, fuel the tank is connected by a fuel line, in which a fuel pump is installed, with pump drives, with combustion chambers, a supersonic jet nozzle is made as a non-rotating part of the projectile, control system devices are installed in the housing, containing an on-board computer connected to the engine controller, which, in turn, is connected with the on-board computer. A receiver and transmitter with an antenna and a receiver of the global positioning system, also connected to the antenna, are connected to the on-board computer. The fuse controller is connected to the on-board computer, which, in turn, is connected to the explosive device.

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

The invention is illustrated by drawings, where:

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

figure 2 shows a view of the projectile from below,

figure 3 ... 5 shows a diagram of a control system,

figure 6 shows the control circuit for the pitch angle,

Fig.7 shows a control diagram for the yaw angle.

The projectile (FIG. 1) comprises an axisymmetric housing 1. An explosive device 2 and a fuel tank 3 are installed inside the housing 1. Preferably, the fuel tank 3 is toroidal in shape for dynamically balancing the projectile during rotation during flight and as fuel is consumed.

Also inside the housing 1 there are four supersonic gas turbine engines 4 operating on liquid fuel. The projectile has a control system installed inside the housing 1.

The supersonic gas turbine engine 4 consists of a supersonic air intake 5 with a central cone shaped fairing 6, a compressor 7, which, in turn, consists of a compressor stator 8 and compressor rotor 9, a combustion chamber 10 with nozzles 11, to which a fuel pipe 12 with a fuel pump 13 is connected having a pump drive 14. A turbine 15 is installed behind the combustion chamber 10, containing a nozzle apparatus 16 and an impeller of the turbine 17. A supersonic jet nozzle 18 with a conical fairing 19 is installed at the output of the turbine 15. all the rotor assemblies, namely the compressor rotor 9 and the turbine impeller 17, are installed. All other components of the gas turbine engine 4 form a stator 21, which includes a supersonic air intake 5, a compressor stator 8, a combustion chamber 10 and a supersonic jet nozzle 18. The control system contains an onboard a computer 22 connected to a motor controller 23, which is connected to a pump drive 14.

The control system includes an accelerometer 24 and a magnetometer 25 for measuring the orientation angle of the projectile in flight, which are connected to the on-board computer 22. All communications between electronic devices and sensors are made by wired communication channels 26.

To the on-board computer 22 can be connected to the transmitting and receiving device 27 (figure 2), to which the antenna 28 is connected. The antenna 28 has an annular shape, and a portion of the housing 1 in the region of the location of the antenna 28 is made transparent.

Inside the housing 1 (Fig. 3), a receiver of the global positioning system 29 (Fig. 4) can be installed, which is also connected to the on-board computer 22 and to the antenna 28. All connections are made by wire connections 26. To the global positioning system (GLONAS or GPS ) includes satellites connected to antenna 28 via radio channels 30.

Perhaps the use of the scheme (figure 4) undermining with a demolition controller 31 connected to the on-board computer 22 and to the explosive device 2.

The projectile can be equipped with stabilizers 32, mounted on the outside of the housing 1 in its lower part (figure 1).

In Fig.6 shows a control circuit for the pitch angle α, and Fig.7 - control for the yaw angle - β. The control over the roll angles (rotation) γ is not shown in FIGS. 1 ... 7.

When using a projectile in the operational memory of the on-board computer 22 enter the initial flight data. The projectile starts from the launcher, for this start the supersonic gas turbine engines 4, while the on-board computer 22 gives a command to drive the pump 14 and to the fuel pump 13. Fuel is supplied from the fuel tank 3 to the combustion chamber 10, where it is ignited using an electric igniter (not shown ) The combustion products drive the impeller of the turbine 17, which spins the rotor of the compressor 9 through the shaft 20.

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.

When flying, the receiver of the global positioning system 29 (GLONAS or GPS) receives a signal from three satellites of the system via radio channels 30 and determines its own coordinates. Using the established program, through the influence of the on-board computer n 22 on the drives of the pumps 14 and further on the fuel pumps 13, it is possible to reduce or increase the thrust of each gas turbine engine 4 and thereby change the flight path of the projectile from launch point “A” to target “B” in range and all angles: pitch, yaw and roll.

On command from the on-board computer 22 transmitted to the blast controller 31 (FIG. 1), the explosive device 2 may be detonated, for example, in flight.

The control of the projectile at the corners of pitch, yaw and roll is carried out according to Fig.6 and 7 by mismatching the thrust of supersonic jet engines. The initial data on the angular orientation of the projectile are constantly monitored by the accelerometer 24 and magnetometer 25. The magnetometer 25 determines the projection azimuth, and the accelerometer 24 determines its deviation from the direction of the gravity vector. The placement of these sensors in a non-rotating housing 1 eliminates the influence of centrifugal forces on the readings of the sensors.

The application of the invention allowed:

- increase the speed of the projectile to supersonic through the use of four supersonic gas turbine engines,

- increase the relative speed of the rotors in 2 times, because the relative speed of rotation of the rotors is equal to the sum of the speeds of their rotation,

- reduce the dimensions of the device by 2 times compared with the usual scheme,

- reduce centrifugal loads on components and parts by 4 times,

- to increase the power and efficiency of a 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,

- to improve and simplify the controllability of the projectile in flight due to a mismatch in engine thrust.

Claims (4)

1. A supersonic missile containing an axisymmetric body inside which an explosive device is installed, a projectile control system for pitch, yaw and roll angles, including an on-board computer connected to the engine controller, a fuel tank and four supersonic gas turbine jet engines operating on liquid fuel, and each of which contains an air intake, a compressor, a combustion chamber and a turbine, the compressor rotor and the turbine impeller forming the engine rotor A, separated by bearing bearings with an engine stator formed by an air intake, compressor stator, a combustion chamber and a supersonic nozzle, and the fuel tank is connected by fuel lines, in which fuel pumps with drives are installed, with combustion chambers. 2. The projectile of claim 1, wherein the pump drive is connected to an engine controller, which, in turn, is connected to the on-board computer. 3. The projectile according to claim 2, in which a transmitting and receiving device with an antenna and a global positioning system receiver connected to the antenna are connected to the on-board computer. 4. The projectile according to claim 2 or 3, in which the fuse controller is connected to the on-board computer, which, in turn, is connected to the explosive device.

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