RU2348895C2 - Combined missile - Google Patents

Abstract

FIELD: weapons.

SUBSTANCE: present invention pertains to weapons and is meant for use in combat with terrorists. The combined missile has a case with axially symmetrical shape with four stabilisers. Inside the case there is an explosive device, a fuel tank, solid fuel jet engines, fitted in the rear part of the missile on its periphery. Along the axis of the missile there is a gas-turbine engine, working on liquid fuel and with an air intake, compressor, combustion chamber and a turbine. The fuel tank is anchor ring shaped and is joined by a fuel line, fitted with a fuel pump, to the combustion chamber.

EFFECT: increase in missile velocity, range and target accuracy and widening of functional capabilities of the missile.

6 cl, 4 dwg

Description

The invention relates to military equipment, in particular to means of warfare, border protection and defense, and the fight against terrorists.

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 rudders mounted on the body from the outside, see the Internet at 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 to this problem was achieved by the fact that in a combined rocket projectile containing an axisymmetric body with four stabilizers, inside which an explosive device, a fuel tank, solid propellant rocket engines were installed, four solid propellant rocket engines installed in the rear part of the projectile around the periphery were used, and along the axis of the projectile is a gas turbine engine running on liquid fuel containing an air intake, a compressor, a combustion chamber and turbines Forming the inner and outer rotors separated bearing supports, wherein the outer rotor is fixedly connected to the housing, the fuel tank is connected to the fuel line, in which a fuel pump with a pump drive, with a combustion chamber, and the control system comprising actuators stabilizers and the onboard computer. A control controller is installed in the control system, connected on one side to the control drive, and on the other, to the on-board computer. The pump drive is connected to the engine controller, which, in turn, is connected to the on-board computer. A transmitting and receiving device with an antenna is connected to the on-board computer. The projectile may comprise a global positioning system receiver connected to the antenna and to the on-board computer. A fuse controller may be connected to the on-board computer, which, in turn, is connected to an explosive device.

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

The invention is illustrated in figures 1-4, 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 shows a radio-controlled projectile,

figure 4 shows the projectile with control using a global positioning system,

The projectile (Fig. 1) contains an axisymmetric body 1. An explosive device 2 and a fuel tank 3 are installed inside the housing 1. It is preferable that the fuel tank 3 be of a torroid shape for dynamically balancing the projectile during rotation during flight and as fuel is consumed.

Also inside the housing 1 is installed a gas turbine engine 4 operating on liquid fuel. The projectile has a control system installed inside the housing 1.

The gas turbine engine 4 consists of an 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 connected to a pump drive is connected 14. Behind the combustion chamber 10, a turbine 15 is installed, comprising a nozzle apparatus 16 and an impeller of the turbine 17. At the turbine outlet 15, a supersonic jet nozzle 18 and four solid propellant jet engines 19 are installed. A shaft 20 is installed all nodes of the rotor 20, namely the rotor of the compressor 9 and the impeller of the turbine 17. All other nodes of the gas turbine engine 4 form a stator 21, which includes a supersonic air intake 5, a stator of the compressor 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 the pump drive 14. The projectile is equipped with stabilizers 24 mounted on the outside of the housing 1 in its lower part. The control system includes a controller 25 solid propellant jet engines 19, connected to the on-board computer 22.

The control system includes an accelerometer 26 and a magnetometer 27 for measuring the orientation angles of the projectile in flight, which are connected to the on-board computer 22.

To the on-board computer 22 can be connected to the transmitting and receiving device 28 (figure 2), to which the antenna 29 is connected. The antenna 29 has an annular shape, and a portion of the housing 1 in the region of the location of the antenna 29 is made transparent. All communications between the electronic components of the control system are wired 30.

Inside the housing 1 (Fig. 3), a receiver of the global positioning system 31 (Fig. 4) can be installed, which is also connected to the on-board computer 22 and to the antenna 29.

The global positioning system (Glonas or GPS) includes 32 satellites 33 connected to the antenna 29 via radio channels.

Perhaps the use of the scheme (figure 4) undermining with a demolition controller 34 connected to the on-board computer 22 and to the explosive device 2.

When using a projectile in the operational memory of the on-board computer 22 enter the initial flight data. The projectile 1 starts from the launcher, to do this, start the gas turbine engine 4, while the on-board computer 22 gives the 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 (in FIG. .1-4 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.

During the flight, the receiver of the global positioning system 31 (GLONAS or GPS) receives a signal from three satellites 33 of the system via radio channels 32 and determines its own coordinates. Using the program in place, the on-board computer 22 influences the pump drives 14, and further on the fuel pumps 13, it is possible to reduce or increase the thrust of the gas turbine engine 4 and thereby change the flight path of the projectile from the starting point to the target in range.

On command from the on-board computer 22 transmitted to the blast controller 34 (Fig. 1), the explosive device 2 may be detonated, for example, in flight.

The projectile is controlled by pitch, yaw and roll angles according to FIGS. 5 and 6 by the mismatch of the thrust of the solid-propellant jet engines 19. The initial data on the angular orientation of the projectile are constantly monitored by the accelerometer 26 and magnetometer 27. The magnetometer 27 determines the projection azimuth and the accelerometer 26 deviates it 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:

- 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 the mismatch of the thrust of solid propellant jet engines.

Claims (6)

1. Combined missile containing an axisymmetric housing with four stabilizers, inside which an explosive device, a fuel tank, solid propellant jet engines are installed, characterized in that it is equipped with a stabilizer drive control system, an on-board computer and four solid propellant jet engines mounted in the rear parts of the projectile on the periphery, and a gas turbine engine running on liquid fuel and containing an air intake is installed along the axis of the projectile a pressor, a combustion chamber and a turbine, while the fuel tank is made in the form of a torus and is connected by a fuel pipe in which the fuel pump is installed to the combustion chamber. 2. The projectile according to claim 1, characterized in that the control system is equipped with a control controller connected to the control drive and to the on-board computer. 3. A missile according to claim 1 or 2, characterized in that the fuel pump drive is connected to a controller connected to the on-board computer. 4. The missile according to claim 1 or 2, characterized in that the on-board computer is connected to the receiving-transmitting device with an antenna. 5. The missile according to claim 4, characterized in that it comprises a global positioning system receiver connected to the antenna and the on-board computer. 6. The missile according to claim 1 or 2, characterized in that it is equipped with a fuse controller connected to the on-board computer and to the explosive device.

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