RU2347178C1 - Air bomb - Google Patents

Abstract

FIELD: weaponry.

SUBSTANCE: invention relates to ammunition used for bombing the ground, water surface and underwater targets. The proposed air bomb comprises four solid-propellant jet engines and a gas turbine engine. Note that the former are arranged at the bomb rear all along its edges while the latter is fitted along the bomb shell. The said gas turbine runs on fluid propellant and comprises fluid fuel tank, air intake, compressor, combustion chamber and turbine. The bomb is furnished also with the control system, funs drives and built-in computer.

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

6 cl 5 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.

Disadvantages - low flight speed in the final section of the trajectory and insufficient control efficiency.

Known controlled aircraft bomb FX 1400, Germany, Internet site http: //base13/glasnet.ru, prototype, application 1. This bomb contains a housing inside which an explosive device, 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 - 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 practically invulnerable, but the probability of even a guided aircraft bomb falling into a circle with a diameter of 1 km is almost zero.

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

The solution of these problems was achieved in an aircraft bomb containing an axisymmetric casing with four stabilizers, inside which an explosive device was installed, and a control system, characterized in that it was equipped with four solid propellant jet engines located at the rear of the casing along the periphery, and a gas turbine engine on liquid fuel installed along the axis of the housing and containing a container for liquid fuel, an air intake, a compressor, a combustion chamber and a turbine, the container A fuel line is connected to the liquid fuel in which a fuel pump to the combustion chamber, and the control system comprising actuators stabilizers and the onboard computer.

The control system is equipped with a control controller connected to the control drive and to the on-board computer. The bomb is equipped with an engine controller connected to the fuel pump and to the on-board computer. The bomb is equipped with a transmitter and receiver with an antenna connected to the on-board computer. The bomb contains a global positioning system receiver connected to the antenna and to the on-board computer. The 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 ... 5, 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 and a controller for detonating 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 container for liquid fuel 4 are installed inside the housing 1. Preferably, the container for liquid fuel 4 is of a toroidal shape.

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

The gas turbine engine 5 consists of an air intake 6 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 is connected with a fuel pump 13 having pump drive 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 jet nozzle 18 is installed. Four solid propellant jet (rocket) engines 19 are installed on the periphery. All rotor assemblies are installed on the shaft 20, namely, the compressor rotor 9 and the turbine impeller 17. 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. System The control includes an on-board computer 22 connected to an engine controller 23, which is connected to a pump drive 14. Each solid-fuel jet engine 19 is equipped with an engine start controller 25, which is connected to an on-board computer 22 m.

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 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 section of the housing 1 in the region of the antenna 20 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 29. All connections are made by wire connections 30. To the global positioning system (Glonas or GPS ) includes satellites 33 connected to antenna 29 via radio channels 32.

Installation is possible in front of the camera body 34, which is connected to the on-board computer 22 (Fig. 5).

It is possible to use the scheme (Fig. 5) of an explosion with an explosion controller 35 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.1 ... 5 shows the control circuit by the pitch angle α, by the yaw angle β and the control by the roll angles (rotation) γ.

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, 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 action of the on-board computer 22 on the pump drive 14 and then on the fuel pump 13, it is possible to reduce or increase the thrust of each gas turbine engine 5 and thereby change the projectile flight path from the bombing point to the target in range and all angles: pitch, yaw and roll.

Solid propellant rocket engines 19 are turned on immediately after dropping an aircraft bomb from a bomber in order to overcome a high altitude from the place of bombing as soon as possible. At the same time, bombing is possible from altitudes of more than 20 km. Air at such altitudes is not enough for the operation of a gas turbine engine, and solid fuel reactive (rocket) carry an oxidizer and fuel reserve in the combustion chamber of these engines and do not need air oxygen. At an altitude of 4 ... 5 km, the reserve of solid fuel is exhausted, and the gas turbine engine is turned on, the thrust of which can be regulated depending on the command from the on-board computer 22, which is supplied to the engine controller 23, which speeds up or slows down the operation of the drive 14 of the fuel pump 13. Upon receipt of a signal from the on-board computer 22 that the aerial bomb goes exactly on target, the regulatory system sets the maximum thrust of the gas turbine engine, and the aerial bomb goes to defeat. In this case, the flight of an aircraft bomb at the final site may not be carried out vertically, but at an angle to the target, by analogy with a missile.

On command from the on-board computer 22 transmitted to the blasting controller 36 (FIG. 5), the explosive device 3 may be detonated, for example, in flight.

The projectile is controlled by pitch, yaw and roll angles by turning the stabilizers 2 using the drives 24. 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 determines its deviation from the direction of the gravity vector. You must use either three one-component accelerometers, or one three-component. The magnetometer must be installed near the magnetically permeable portion of the housing. The influence of centrifugal forces on the readings of sensors 26 and 27 is excluded, because the projectile does not rotate.

The application of the invention allowed:

- increase the speed of the aircraft bomb to supersonic through the use of four solid propellant jet engines and one 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 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 handling of the projectile in flight.

Claims (6)

1. Aircraft bomb containing an axisymmetric casing with four stabilizers, inside which an explosive device and control system are installed, characterized in that it is equipped with four solid propellant rocket engines located at the rear of the casing on the periphery, and a gas turbine engine running on liquid fuel, installed along the axis of the housing and containing a tank for liquid fuel, an air intake, a compressor, a combustion chamber and a turbine, while the tank for liquid fuel is connected to the fuel the wire in which the fuel pump is installed, with a combustion chamber, and the control system contains stabilizer drives and an on-board computer. 2. The bomb 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. The bomb according to claim 1 or 2, characterized in that it is equipped with a controller
engine connected to the fuel pump and to the on-board computer. 4. The 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. The bomb according to claim 4, characterized in that it contains a global positioning system receiver connected to the antenna and to the on-board computer. 6. The 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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