RU2477448C1 - Universal torpedo - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: torpedo comprises axially symmetric body to house explosive device, compressed air bottle, oxidiser and fuel tanks, liquid-propellant rocket engine, control system, onboard computer connected with video camera, controller, transceiver with antenna, and GPS receiver. Said liquid-propellant rocket engine is arranged along body axis and comprises combustion chamber, turbo pump unit with turbine and oxidiser and fuel pumps, oxidiser and fuel tanks communicated via appropriate pipelines with said turbo pump unit. Fast-release tight plug is fitted at the body rear end as well as four steering jet nozzles aligned with liquid-propellant rocket engine and connected with turbine via tubes provided with flow meters and drives.

EFFECT: higher speed, increased range and accuracy.

7 cl, 8 dwg

Description

The invention relates to military equipment, in particular to means for the bombardment of surface, underwater and ground coastal 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 lack of control efficiency.

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

The aircraft torpedo is known from the Internet site http://www.airwar.ru, the prototype (Appendix 1), which contains an axisymmetric case, an explosive device installed inside it, a screw hydraulic engine driven by an air turbine and a cylinder with compressed air, as well as a system steering wheel controls. The control system only works underwater.

The disadvantages of such a torpedo: 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 torpedo and the impossibility of bombing from lower and even with indicated heights. When bombing from heights of 20 ... 30 km, the bomber remains virtually invulnerable, but the probability of a torpedo entering a circle with a diameter of 1 km is practically zero.

It is known to use global navigation systems to determine the coordinates of an object using special purpose satellites.

If the distance to one satellite is known, then the coordinates of the receiver cannot be determined (it can be located anywhere in the sphere with a radius described around the satellite). Let the receiver distance from the second satellite be known. In this case, the determination of coordinates is also not possible - the object is on a circle, which is the intersection of two spheres. The distance to the third satellite reduces the uncertainty in coordinates to two points. This is already enough to uniquely determine the coordinates - the fact is that of the two possible points of location of the receiver, only one is on the surface of the Earth (or in the immediate vicinity of it), and the second, false, is either deep inside the Earth or very high above surface. Thus, for three-dimensional navigation it is theoretically sufficient to know the distance from the receiver to 3 satellites.

Global Navigation Satellite System (GLONASS) - Soviet and Russian satellite navigation system, developed by order of the USSR Ministry of Defense. This is one of two currently functioning global satellite navigation systems. The basis of the system should be 24 satellites moving above the Earth's surface in three orbital planes with an inclination of orbital planes of 64.8 ° and a height of 19100 km. The measurement principle is similar to the American NAVSTAR GPS navigation system. Currently, the GLONASS project is being developed by the Federal Space Agency (Roscosmos) and Russian Space Systems OJSC.

The Russian Global Navigation Satellite System (GLONASS) is designed for operational navigation and temporal support for an unlimited number of land, sea, air and space-based users. Access to civilian GLONASS signals anywhere in the world on the basis of a decree of the President of the Russian Federation is provided to Russian and foreign consumers free of charge and without restrictions.

In order to ensure the commercialization and mass introduction of GLONASS technologies in Russia and abroad, in July 2009, by the Decree of the Government of the Russian Federation, a “Federal Network Operator in the Field of Navigation Activities” was created, the functions of which were assigned to OJSC Navigation and Information Systems.

The main difference from the GPS system is that the GLONASS satellites in their orbital motion have no resonance (synchronization) with the rotation of the Earth, which provides them with greater stability. Thus, the GLONASS spacecraft grouping does not require additional adjustments during the entire period of active existence. Nevertheless, the service life of GLONASS satellites is noticeably shorter.

Aircraft torpedo is known according to US Pat. RF for invention No. 2348003, IPC F42D 17/00, publ. 02/27/2008

The torpedo has a gas turbine engine, which allows to increase its speed to M = 0.3 ... 0.5.

Disadvantages - relatively low speed and the inability to launch torpedoes from ships and submarines.

Known torpedo for US Pat. RF invention No. 2289091, IPC F42B 19/18, publ. 12/10/2008. This torpedo contains a powder charge, an axial piston engine and a hydraulic screw.

The disadvantage is the low speed of the torpedo.

Known torpedo with LRE (liquid rocket engine) according to St. RF for utility model No. 26603, IPC A02K9 / 48, publ. 12/10/2002, the prototype.

The torpedo contains an axisymmetric case, inside the case of which an explosive device is installed, a cylinder with compressed air, oxidizer and fuel tanks, a liquid rocket engine and a control system.

Disadvantages - relatively low speed and the inability to launch torpedoes from ships and submarines.

The objective of the invention is to increase the flight speed of an aircraft torpedo and the accuracy of hitting a large distance from the target.

The solution of these problems was achieved in a dashboard containing an axisymmetric case, inside of which there is an explosive device, a cylinder with compressed air, oxidizer and fuel tanks, a liquid rocket engine and a control system, according to the invention, a liquid rocket engine is installed inside the body along its axis containing a combustion chamber and a turbopump unit with a turbine and oxidizer and fuel pumps, oxidizer and fuel tanks are connected by fuel lines to a turbopump, at the rear four steering jet nozzles are installed coaxially with a liquid rocket engine at the end of the housing, and the gas ducts containing flow controllers with drives are connected to the turbine. At the rear end, a quick-release sealed plug can be installed.

A universal torpedo may contain an on-board computer connected by electrical communication to a control controller. The control controller can be connected by means of communication with flow controllers. A transmitting and receiving device with an antenna can be connected to the on-board computer by means of communication. The torpedo may include a global positioning system receiver connected to the antenna and to the on-board computer. The torpedo may contain a video camera connected by means of communication 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 ... 8, where:

figure 1 shows a schematic diagram of a simple version of a torpedo,

figure 2 shows a diagram of the rocket engine,

figure 3 shows a view of the torpedo universal rear

figure 4 shows a diagram of a torpedo with autonomous control,

figure 5 shows the radio-controlled torpedo,

Fig.6 shows a torpedo with control using a global positioning system,

Fig.7 shows a universal torpedo with a video camera,

Fig.8 shows a complete diagram of the rocket engine.

The torpedo (FIGS. 1 ... 8) contains an axisymmetric body 1 containing a conical part 2, stabilizer wings 3. An explosive device 4 and oxidizer and fuel tanks 5 and 6 are installed inside the body 1. Preferably, the tanks 5 and 6 are made of a torroid shape.

Also inside the housing 1, along its axis in the central part, a liquid propellant rocket engine is installed 7. The liquid propellant rocket engine 7 consists of a combustion chamber 8 and TNA 9. The combustion chamber 8 has a head 10, a cylindrical part 11 and a nozzle 12.

The turbopump unit 9 (FIGS. 1 and 2) comprises a main turbine 13, an oxidizer pump 14, a fuel pump 15, an additional fuel pump 16 and a start turbine 17 to which an exhaust pipe 18 is connected. A gas generator 19 is installed above the TNA 9. The main turbine 13 and the head 10 of the combustion chamber 8 is connected by a gas duct 20. The combustion chamber 8 is made with the possibility of regenerative cooling and contains an outer wall 21, an inner wall 22 with a gap 23 between them. From the lower part of the nozzle 12, a lower manifold 24 is made, the cavity of which is connected to the gap 23, and a fuel pipe 25 containing a fuel valve 26 is connected to it. The other end of the fuel pipe 25 is connected to the outlet of the fuel pump 15 (Fig. 2). The liquid propellant rocket engine 7 is equipped with a purge system that contains an inert gas cylinder 27, a purge pipe 28 with a purge valve 29. The purge pipe 28 is connected to the lower manifold 24.

The universal torpedo is equipped with four control nozzles 30 (figures 1, 2 and 3). The control nozzles 30 operate on sour gas, i.e. combustion products in the gas generator 19 with an excess of oxidizing agent, but having a relatively high temperature from 500 to 700 ° C. For this, a gas withdrawal pipe 31 is attached to the main turbine 15 (to the inlet or outlet), to which 4 pipelines 32 are connected, containing flow controllers 33.

The output of the oxidizer pump 15 by the oxidizer pipe 34 containing the oxidizer valve 35 is connected to the inlet of the gas generator 19. The output of the additional fuel pump 16 by a pipe 36 containing the flow regulator 37 and the high pressure valve 38 is connected to the inlet of the gas generator 19.

The liquid propellant rocket engine 7 is also equipped with a launch system, which contains a compressed air cylinder 39, a high pressure pipe 40 with a start valve 41. The pipe 40 is connected to the inlet of the start turbine 17 (Fig. 3).

The oxidizer tank 5 with a rocket pipe 42 containing a rocket valve 43 is connected to the TNA 9, specifically with the entrance to the oxidizer pump 15, similarly the fuel tank 6 with the rocket pipe 44 containing the rocket valve 45 is connected with the TNA 9, specifically with the entrance to the fuel pump 15 .

Ignition devices 46 are installed on the combustion chamber 8, and ignition devices 47 are installed on the TNA 9. The TNA 9 is mounted on the combustion chamber 8 using two brackets 48 and hinges 49 and 50.

The oxidizer and fuel tanks 5 and 6 (Fig. 1) are equipped with pressurization systems that contain a cylinder of compressed air 51. The oxidizer tank 5 with a boost pipe 52 containing a boost valve 53 is connected to the compressed air cylinder 51, similarly to the fuel tank 6 with a boost pipe 54, comprising a boost valve 55, connected to a cylinder of compressed air 51.

In addition, the universal torpedo has a control system containing an on-board computer 56 connected by electrical connection 57 to the control controller 58. The control system includes a transmitting and receiving device 59, to which an antenna 60 is connected, and a receiver of a remote positioning system 61, to which an electric Antenna 62 is connected by communication 57. The system includes satellites 63, which are connected via radio channel 64.

Sensors are connected to the control controller 58, including an accelerometer 65 and a magnetometer 66. A fuse 67 is connected to the control controller (Figs. 1 and 2). Accelerometer 65 and magnetometer 66 - for measuring the angles of orientation of the torpedo in motion (flight) are connected to the control controller 58 (Fig.1, 2 and 7).

Inside the combustion chamber 8 (Fig. 8), an outer plate 68 and an inner plate 69 with a gap (cavity) between them 70 are formed. Inside the head 10 of the combustion chamber 8, a cavity 71 is made and oxidizer nozzles 72 and fuel nozzles 73 are installed. The oxidizer nozzles 72 communicate with the cavity 71 with an internal cavity 73 of the combustion chamber 8.

The gas generator 19 has an external and an internal plate 74 and 75, respectively, with a cavity between them 76 and the oxidizer and fuel nozzles 77 and 78, respectively. Ignition devices 46 are installed on the head 10 of the combustion chamber 8, and ignition devices 47 are installed on the gas generator 19 (Fig. 2 and 8).

TNA 9 (Fig. 8) has a speed sensor 80 mounted on the shaft 79. An electric connection 57 is connected to the speed sensor 80, which is connected to the on-board computer 56. The impeller of the turbine 81, the centrifugal impeller 82 of the oxidizer pump 14 are installed on the shaft 79 , the centrifugal impeller 83 of the fuel pump 15 and the impeller 84 of the starting turbine 13. The centrifugal impeller 85 of the additional fuel pump 16 is connected to the shaft 79 through the multiplier 86.

Ignition devices 46 and 47, preferably pyrozap valves, a fuel valve 26, an oxidizer valve 45, a flow regulator 37, and a high pressure valve 38 are connected to the on-board computer 56 by electrical connections 57.

The universal torpedo is equipped with a plug 87 at the rear end, which is sealed relative to the housing 1 by a seal 88. At the rear end of the housing 1 there are installed mechanisms for its discharge 89, for example a squib. The universal torpedo is intended for movement mainly on the surface of the water 90 and in some cases for a short time - under water, in the air, on ice and on snow. For remote control (figures 1, 2 and 8), a control panel 91 is used, which is electrically connected 57 to a transmitter-receiver unit 92 to which an antenna 93 is connected.

The torpedo can be equipped with a video camera 94 connected via electrical connection 57 to a computer 94.

COMBAT APPLICATION OF A TORPEDA UNIVERSAL

When launching a universal torpedo, it is first dumped onto the water surface 84, then the sealed plug 81 is dropped, for example, using the reset mechanisms 83. Then the rocket engine 7 is launched.

To this end, on a command from the on-board computer transmitted via electrical connections 57, first the start valve 41 is opened to the control controller 58 and the compressed air enters the starting turbine 17 through the high pressure pipe 40. Then the boost rocket valves 53 and 55 are opened, rocket valves 43, 45, and valves 26, 35, and high pressure valve 37 and include ignition devices 46 and 47 (FIGS. 2 and 8). The fuel components (oxidizing agent and fuel) are simultaneously ignited in the gas generator 19 and in the combustion chamber 8. When the components of rocket fuel are burned in the gas generator 19 with an excess of oxidizer, the “acid gas” has a temperature of 500 ... 700 ° C, and burns in the combustion chamber 8 at high temperature up to 3500 ° C. The control of the universal torpedo movement is carried out by the on-board computer 56 using the flow controllers 33 and 37 (figure 2 and 8).

1st control option (autonomous guidance)

When using a torpedo in standalone mode, the source data of the flight is entered into the RAM of the on-board computer 56. A universal torpedo is released from the torpedo tube of a ship or a submarine or dropped from the side of a topopedo-carrying aircraft, then the rocket engine 7 is launched, and the on-board computer 56 sends a command to the control controller 58, then to the controllers 33 and 37. The components of rocket fuel are fed from the fuel tanks 5 and 6 to the gas generator 19 and to the combustion chamber 8, where they are ignited using ignition devices 46 and 47. The combustion products drive the rotor of the main turbine 13, which spins it through the shaft 79.

The use of liquid fuel allows you to get an advantage in flight range compared to solid propellant rockets, because the calorific value of liquid fuel is 3 ... 4 times greater than that of solid fuel. The position control is carried out by the accelerometer 34 and magnetometer 25. After approaching the target at a distance of 300 ... 500 m on a dashboard, the universal on-board computer 33 puts the liquid-propellant rocket engine 7 into maximum thrust mode. Then an aviation torpedo either submerses to destroy a sea target below the waterline, or takes off to hit coastal targets.

2nd option of management. Radio control

The control signal is supplied from the computer of the ship, submarine or torpedo bomber aircraft (not shown in FIGS. 1 ... 6) via radio channel 64 to antenna 60 and further to the transmitting and receiving device 36 and to the on-board computer 56.

3rd option of management. Global Positioning Management

When flying, the receiver of the global positioning system 61 (GLONAS or GPS) receives a signal from three satellites 63 of the system via radio channels 64 and determines its own coordinates. Using the embedded program through the influence of the on-board computer 56, the flow controller 44 can reduce or increase the thrust of the liquid-propellant rocket engine 7, and thereby change the speed and direction of movement (flight) of the universal torpedo.

The control of the projectile by the pitch and yaw angles (according to rocket terminology) in motion is carried out according to FIG. 1 by turning on the control nozzles 30 by opening the corresponding gas flow regulator 32. The initial data on the angular orientation of the aviation torpedo are constantly monitored by the accelerometer 63 and magnetometer 64. The magnetometer 64 determines the azimuth torpedo movement, and accelerometer 63 - its deviation from the direction of the gravity vector.

The application of the invention allowed:

- increase the speed of approach of the universal torpedo to the target to supersonic due to the use of a liquid rocket engine,

- increase the speed of the torpedo under water due to the operation of a liquid rocket engine,

- increase the accuracy of hitting to 2 ... 5 m when dropping a torpedo at a distance of 100 km from the target and from a height of more than 20 km, to ensure good stabilization of the projectile in motion on the surface of the water, in flight and under water,

- reduce the load on the instruments and sensors of the control system of the universal torpedo by placing them in the shell of the shell,

- stabilize the position of the universal torpedo in flight,

- to improve and simplify the control of a torpedo in flight, especially at the final stage of flight and movement under water,

- to ensure torpedo firing from ships, submarines and aircraft of all types, including bombers and fighters, to ensure the defeat of ground coastal targets,

- provide targeted destruction of ground targets in the winter.

Claims (7)

1. A torpedo containing an axisymmetric housing, inside of the housing of which an explosive device is installed, a cylinder of compressed air, oxidizer and fuel tanks, a liquid rocket engine and a control system, characterized in that a liquid rocket engine containing a combustion chamber is installed along the axis of the body along the axis of the housing and a turbopump assembly with a turbine and oxidizer and fuel pumps, oxidizer and fuel tanks are connected by fuel pipelines to a turbopump, at the rear end of the casing they are installed coaxially with the fluid ostnym four steering rocket engine jet nozzles which tubes containing flow control with actuators connected to the turbine. 2. The torpedo according to claim 1, characterized in that a quick-release sealed plug is installed on the rear end. 3. The torpedo according to claim 1 or 2, characterized in that it contains an on-board computer connected to the control controller. 4. The torpedo according to claim 2, characterized in that the control controller is connected by means of communication with flow controllers. 5. The torpedo according to claim 1 or 2, characterized in that a transmitting and receiving device with an antenna is connected to the on-board computer by means of communication. 6. Torpedo according to claim 1 or 2, characterized in that it contains a global positioning system receiver connected to the antenna and to the on-board computer. 7. Torpedo according to claim 1 or 2, characterized in that it contains a video camera connected by means of communication to the on-board computer.

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