RU2477446C1 - Antiaircraft missile - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: antiaircraft design comprises warhead, axially symmetric body, four steering jet nozzles at lower fins, body head and tail fins. Said body accommodates explosive assembly, compressed air bottle, oxidiser and fuel tanks, liquid-propellant rocket engine, and control system. Control system is connected with onboard computer and comprises video camera, controller, GPS receiver, and antenna. Liquid-propellant rocket engine is arranged along body axis and comprises combustion chamber, turbo pump unit with turbine and oxidiser and fuel pumps communicated via pipelines with turbo pump unit. Steering jet nozzles are aligned with said engine and communicated with turbine via lines provided with flow controllers and drives.

EFFECT: higher speed, increased range and accuracy.

7 cl, 13 dwg

Description

The invention relates to military equipment, in particular to means for hitting air targets.

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. 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.

Known anti-aircraft missile with a solid propellant rocket engine according to the patent of the Russian Federation for the invention №2327949, IPC F42B 15/00, publ. 06/27/2008

The disadvantage is the low speed of the anti-aircraft missile and its poor controllability. In the case of the use of a solid fuel rocket engine, it is impossible to regulate its traction and it is very difficult to control the course of the rocket.

Known anti-aircraft missile with LRE (liquid rocket engine) according to St. RF for utility model No. 93962, IPC F42B 15/00, publ. 06/27/2008 g, prototype.

An anti-aircraft missile contains an axisymmetric case, inside of which there is an explosive device, a cylinder of compressed air, oxidizer and fuel tanks, a liquid rocket engine and a control system.

Disadvantages - relatively low speed and range, and limitations in the management and guidance of the rocket and, as a result, low accuracy.

Objectives of the invention: the speed of the anti-aircraft missile, range and accuracy, and the expansion of the functionality of the application.

The solution of these problems was achieved in an anti-aircraft missile containing a warhead, stabilizers and an axisymmetric body, inside which an explosive device, a compressed air cylinder, oxidizer and fuel tanks, a liquid rocket engine and control system, characterized in that the liquid rocket engine is installed along the axis of the housing and contains a combustion chamber and a turbopump unit with a turbine and oxidizer and fuel pumps, oxidizer and fuel tanks, which are connected by missile pipelines to the turbine the pump unit, the rear end of the body coaxially installed with liquid rocket engine four steering jet nozzles which tubes containing flow control with actuators connected to the turbine. Stabilizers can be mounted on the back of the chassis and on the head. The control system may include an on-board computer connected to the 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 control system may include a global positioning system receiver connected to the antenna and to the on-board computer. The control system may include 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 ... 13, where:

figure 1 shows a schematic diagram of a simple version of an anti-aircraft missile,

figure 2 shows a diagram of the rocket engine for anti-aircraft missiles,

figure 3 ... 5 shows a view of a universal anti-aircraft missile rear,

6 ... 8 shows a view of the lower stabilizers,

figure 9 shows a diagram of an anti-aircraft missile with autonomous control,

figure 10 shows a radio-controlled anti-aircraft missile,

11 shows an anti-aircraft missile with control using a global positioning system,

in Fig.12 shows a universal anti-aircraft missile with a video camera,

in Fig.13 shows a complete diagram of the rocket engine.

The anti-aircraft missile (FIGS. 1 ... 13) contains a housing 1, of an axisymmetric shape, containing a conical head part 2, lower stabilizers 3 and upper stabilizers 4. Inside the housing 1, oxidizer and fuel tanks 5 and 6 are installed. It is preferable that tanks 5 and 6 have 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.

Anti-aircraft missile is equipped with four control nozzles 30 (Fig.1, 2 and 13). 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. To this end, gas sampling pipelines 31 containing flow controllers 32 are connected to the main turbine 15 (to the inlet or outlet). The control nozzles 30 can be installed inside the lower stabilizers 3 (Fig. 6) or in streamlined nacelles 33 (Figs. 7 and 8) )

This arrangement of control nozzles allows you to transfer them to a greater distance from the longitudinal axis of the anti-aircraft missile and increase control efficiency with a lower thrust force of these nozzles.

The output of the oxidizer pump 14 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. 2).

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 14, 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 anti-aircraft missile has a control system comprising an on-board computer 56 connected by electrical communication 57 to the control controller 58. The control system includes a transmitting and receiving device 59 to which an antenna 60 and a receiver of a remote positioning system 61 are connected, to which an electric communication 57 antenna 62 is connected. 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). The accelerometer 65 and magnetometer 66, for measuring the angles of orientation of the anti-aircraft missiles in motion (flight), which are connected to the control controller 58 (Fig.1, 2 and 13).

Inside the combustion chamber 8 (Fig. 13), 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 oxidizing and fuel nozzles, respectively, 77 and 78. Ignition devices 46 are installed on the head of the combustion chamber 8, and ignition devices 47 are installed on the gas generator 19 (Fig. 2 and 13).

TNA 9 (Fig. 13) 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 are connected to the on-board computer 56 by electrical connections 57, preferably pyrozapal devices, a fuel valve 26, an oxidizer valve 45, a flow regulator 37, and a high pressure valve 38.

An explosive device 87 is installed in the conical head part 2.

For remote control (figures 1, 2 and 13), a control panel 88 is used, which is electrically connected 57 to a receiving-transmitting device 89, to which an antenna 90 is connected.

The anti-aircraft missile can be equipped with a video camera 91 connected via electrical connection 57 to the on-board computer 56.

BATTLE APPLICATION OF AN anti-aircraft missile

When launching an anti-aircraft missile launch rocket engine 7.

To do this, 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 compressed air enters the start-up 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 a high pressure valve 35 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 combustion chamber 8. When the components of rocket fuel are burned in the gas generator 19 with excess oxidizer, the “acid gas” has a temperature of 500 ... 700 ° C, and burns in the combustion chamber 8 at high temperatures up to 3500 ° C. The motion control of the anti-aircraft missile is carried out by the on-board computer 56 using the flow controllers 33 and 37 (Fig.2 and 8)

1st control option (autonomous guidance)

When using anti-aircraft missiles in standalone mode (figure 10) in the operational memory of the on-board computer 56 enter the initial flight data. An anti-aircraft missile is launched from the ground or from a ship, for this they launch a rocket engine 7, while the on-board computer 56 sends a command to the control controller 58, then to the controllers 32 and 37. The components of the rocket fuel are fed from the fuel tanks 5 and 6 into the gas generator 19 and into the chamber combustion 8, where they are ignited using ignition devices 46 and 47. The combustion products drive the rotor of the main turbine 13, which spins through the shaft 79.

The use of liquid fuel allows you to get an advantage in flight range compared to solid-fuel anti-aircraft missiles, 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 65 and magnetometer 66. After approaching the target at a distance of 300 ... 500 m on an anti-aircraft missile, the on-board computer 56 puts the liquid-propellant rocket engine 7 into maximum thrust mode.

2nd option of management. Radio control.

The control signal is supplied from a computer from the land (Fig. 11), from a ship or aircraft from the control device 88. The signal from the control device 88 is transmitted by electrical communication 57 to the receiving and transmitting device 89, then to the antenna 90 and via radio channel 64 to the antenna 60 and further to the receiving and transmitting device 59 and to the on-board computer 56 of the anti-aircraft missile.

3rd option of management. Global Positioning Management

When flying an anti-aircraft missile, 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 (Fig. 12). Using the inherent program through the influence of the on-board computer 56 on the flow control 44, it is possible to reduce or increase the thrust of a liquid-propellant rocket engine 7 and thereby change the speed and direction of flight of the anti-aircraft missile.

The control of the anti-aircraft missile at the pitch and yaw angles in motion is carried out according to figure 1 by turning on the control nozzles 30 by opening the corresponding gas flow controller 32. The initial data on the angular orientation of the anti-aircraft missile are constantly monitored by the accelerometer 65 and magnetometer 66. The magnetometer 66 determines the azimuth of the anti-aircraft missile movement, and the accelerometer 65 is its deviation from the direction of the gravity vector. Stabilizers 3 and 4 prevent the rotation of anti-aircraft missiles in flight. The roll angle control is not provided.

The application of the invention allowed:

- increase the speed of approach of the anti-aircraft missile target to supersonic, through the use of a liquid rocket engine,

- increase the accuracy of the hit to 2 ... 5 m,

- to ensure good stabilization of anti-aircraft missiles in motion in flight through the use of two groups of stabilizers: upper and lower,

- reduce the load on the instruments and sensors of the anti-aircraft missile control system, due to their placement in the shell of the shell,

- stabilize the position of the anti-aircraft missile in flight,

- to improve and simplify the controllability of an anti-aircraft missile in flight, especially at the final stage of flight.

Claims (7)

1. An anti-aircraft missile containing a warhead, stabilizers and an axisymmetric-shaped body inside which an explosive device, a compressed air cylinder, oxidizer and fuel tanks, a liquid rocket engine and control system are installed, characterized in that the liquid rocket engine is installed along the axis of the body and contains a combustion chamber and a turbopump unit with a turbine and oxidizer and fuel pumps, the oxidizer and fuel tanks of which are connected by missile pipelines to the turbopump unit, at lower izatorah mounted coaxially with liquid rocket engine four steering jet nozzles which tubes containing flow control with actuators connected to the turbine. 2. Anti-aircraft missile according to claim 1, characterized in that the upper stabilizers are mounted on the head part. 3. Anti-aircraft missile according to claim 1 or 2, characterized in that the control system comprises an on-board computer connected to the control controller. 4. Anti-aircraft missile according to claim 2, characterized in that the control controller is connected by means of communication with flow controllers. 5. Anti-aircraft missile 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. Anti-aircraft missile according to claim 1 or 2, characterized in that the control system comprises a global positioning system receiver connected to an antenna and to an on-board computer. 7. Anti-aircraft missile 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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