RU2347179C1 - Air bomb with birotary gas turbine engine - Google Patents

Abstract

FIELD: weaponry.

SUBSTANCE: invention relates to ammunition used for bombing the ground, water surface and underwater targets. The proposed bomb comprises an axisymmetric body made up of two parts, i.e. a rotary one and a fixed one housing explosive and control system. The body houses also a fuel tank, birotary gas turbine engine running on fluid fuel and incorporating an air intake, compressor, combustion chamber and turbine. Note that the fuel tank is connected, via a fuel line accommodating fuel pump, with the pump drive connected to the control system controller and with the combustion chamber. Note also that the control system comprises built-in computer connected with the control system controller, which is connected in its turn with the adjusting devices. The pump drive is connected to the control system controller connected to the built-in computer. The transceiver with aerial is connected to the built-in computer. The bomb incorporates also the GPRS system receiver connected to both computer and aerial. The fuse controller connected to the explosive can also be connected to the said computer.

EFFECT: higher speed and range, improved accuracy of bombing and expanded performances.

6 cl, 6 dwg

Description

The invention relates to military equipment, in particular to means for bombing ground surface and underwater targets.

Known aircraft bomb containing a control system according to the patent of the Russian Federation for invention No. 2232973.

The disadvantage is the low flight speed in the final section of the trajectory and the insufficient control efficiency.

Known guided aerial bomb PX 1400, Germany, Internet site http: //base13/glasnet.ru. This bomb contains a housing, inside of which an explosive device, a control system, stabilizers, stabilizer drives are installed.

Disadvantages - low speed in the last section of the trajectory and very low accuracy. The probability of hitting a battleship when bombing from a height of 7 km is 0.13, and when bombing from a height of 4 ... 5 km it is approximately 0.2 ... 0.3, which is practically unacceptable due to the high cost of the bomb and the impossibility of bombing from lower and even from the indicated heights. When bombarded from heights of 20 km ... 30 km, the bomber remains virtually invulnerable, but the probability of even a guided aircraft bomb falling into a circle with a diameter of 1 km is practically zero.

The objective of the invention is to increase the flight speed of an aircraft bomb, and the accuracy of impact during bombing from very high altitudes.

The solution of these problems was achieved in an aircraft bomb with a turbotropic gas turbine engine containing an axisymmetric case made with rotating and non-rotating parts, inside of which an explosive device, a control system, a fuel tank, a rotational gas turbine engine with external and internal rotors running on liquid fuel are installed, with an air intake, a compressor, a combustion chamber and a turbine, while the fuel tank is connected by a fuel pipe in which a fuel pump with a pump drive is installed CA connected to the control controller and the combustion chamber, and the control system comprises an on-board computer connected to the control controller. The aerial bomb is equipped with regulators connected to a control controller. The pump drive is connected to a control controller. Aircraft bomb is equipped with a transmitting and receiving device with an antenna connected to the on-board computer. The aerial bomb is equipped with a global positioning system receiver connected to an antenna and an on-board computer. The aircraft bomb is equipped with a fuse controller connected to the on-board computer and the explosive device.

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

The invention is illustrated in figure 1 ... 6, where

figure 1 shows a schematic diagram of the simplest version of an aircraft bomb,

figure 2 shows a diagram of an aviation bomb with autonomous control,

figure 3 shows the radio-controlled aircraft bomb,

figure 4 shows an aerial bomb controlled by a global positioning system,

figure 5 shows an aircraft bomb with a video camera,

figure 6 shows a diagram of a controlled (non-contact) detonation of an explosive device of an aircraft bomb.

Aircraft bomb (figure 1) contains an axisymmetric body 1 containing a cylindrical and conical part. Four stabilizers 2 are mounted on the cylindrical part, which are rotatable to control the flight of an aircraft bomb. An explosive device 3 and a fuel tank 4 are installed inside the housing 1. Preferably, the fuel tank 3 is made in a toroidal shape.

Also inside the housing 1, along its axis in the central part, a gas turbine engine 5 is installed, operating on liquid fuel, it is possible to use a supersonic gas turbine engine). The aircraft bomb has a control system installed inside the housing 1.

The bi-turbine gas turbine engine 5 consists of an air intake 6 with a central cone-shaped fairing, 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 having a drive is connected pump 14. A turbine 15 is installed behind the combustion chamber 10, comprising a nozzle apparatus 16 and an impeller of the turbine 17. A jet nozzle 18 is installed at the turbine outlet 15. Four control nozzles 19 are installed on the periphery. All the rotor assemblies, namely the compressor rotor 9 and the turbine impeller 17, are provided. All other components of the gas turbine engine 4 form a stator 21, which includes a supersonic air intake 6, a compressor stator 8, a combustion chamber 10, and a supersonic jet nozzle 18. The stator of the engine 21 is external rotor and rotates in the opposite direction. The control system contains controllers 23, to which a control controller 24 is connected, which is connected to the on-board computer 25. The control controller 24 is also connected to the pump drive 14 (Fig. 3).

The control system includes an accelerometer 26 and a magnetometer 27 for measuring the orientation angle of the projectile in flight, which are connected to the on-board computer 22. To the on-board computer 25 can be connected to the transmitting and receiving device 28 (figure 4), to which the antenna 29 is connected. The antenna 29 has an annular shape, and a section of the housing 1 in the region of the location of the antenna 29 is made transparent. All connections are made by wire ties 30.

Inside the housing 1 (Fig. 5), a receiver of the global positioning system 31 can be installed, which is also connected to the on-board computer 25 and to the antenna 29. The global positioning system (Glonas or OP8) includes satellites 33 connected to the antenna 29 via radio channels 32 .

For control, a video signal from a video camera 34 can be used. For this, it is possible to install a video camera 34 in the rotating part of the housing 1, which is connected to the on-board computer 25 (Fig. 6).

It is possible to use the scheme (Fig. 1) of a blasting with a blasting controller 35 connected to the on-board computer 25 and to the explosive device 4.

The bomb can be equipped with stabilizers 36, mounted on the outside of the housing 1 in its lower part (figure 1).

When using a bomb in the operational memory of the on-board computer 25 enter the initial flight data. A biotic aviation bomb is dropped from the bomber, then the gas turbine engine 5 is started, and the on-board computer 25 gives a command to drive the pump 14 and to the fuel pump 13. The fuel is supplied from the fuel tank 4 to the combustion chamber 10, where it is ignited using an electric igniter (in FIG. 1 ... 6 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 31 (Glonas or OP8 system) receives a signal from three satellites 33 of the system via radio channels 32 and determines its own coordinates. Using the inherent program through the influence of the on-board computer 25 drive the pump 14, and then on the fuel pump 13, you can reduce or increase the thrust of the gas turbine engine 5, and thereby change the flight path of the bomb.

On command from the on-board computer 25 transmitted to the blasting controller 35 (FIG. 1), the explosive device 2 may be detonated, for example, in flight.

The projectile control in pitch, yaw and roll angles is carried out according to figure 1 by turning on the control nozzles 19. The initial data on the angular orientation of the bomb is constantly monitored by the accelerometer 26 and magnetometer 27. The magnetometer 27 determines the azimuth of the bomb’s movement, and the accelerometer 26 determines its deviation from the vector direction gravity. 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 aircraft bomb to supersonic through the use of a gas turbine engine,

- increase the accuracy of hitting to 2 ... 5 m when bombing from a height of more than 20 km,

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

- reduce the load on the instruments and sensors of the bomb control system, due to their placement in the non-rotating part of the body, to stabilize the position of the bomb in flight,

- to reduce the dimensions of the birotational gas turbine engine and centrifugal loads on the external and internal rotors due to their rotation in different directions and the creation of such conditions that from the point of view of aerodynamics and gas dynamics it is considered that the relative speed of rotation of the rotors is equal to the sum of their peripheral speeds, at the same time real speeds are 2 times less, and centrifugal loads are almost 4 times lower

- Improve and simplify the handling of the bomb in flight.

Claims (6)

1. Aircraft bomb with a turbocharged gas turbine engine, comprising an axisymmetric housing made with rotating and non-rotating parts, inside which an explosive device, a control system, a fuel tank, a rotational gas turbine engine with external and internal rotors operating on liquid fuel, with an air intake, are installed, a compressor, a combustion chamber and a turbine, while the fuel tank is connected by a fuel pipe in which a fuel pump is installed with a pump drive connected to the control controller eniya and the combustion chamber, and the control system comprises an onboard computer connected to the management controller. 2. Aircraft bomb according to claim 1, characterized in that it is equipped with regulators connected to the control controller. 3. Aircraft bomb according to claim 1 or 2, characterized in that the pump drive is connected to a control controller. 4. Aircraft bomb according to claim 1 or 2, characterized in that it is equipped with a receiving and transmitting device with an antenna connected to the on-board computer. 5. Aircraft bomb according to claim 1 or 2, characterized in that it is equipped with a global positioning system receiver connected to the antenna and the on-board computer. 6. Aircraft bomb according to claim 1 or 2, characterized in that it is equipped with a fuse controller connected to the on-board computer and the explosive device.

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