RU2535958C1 - Method to hit underwater targets - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: invention relates to methods for hitting of underwater targets. The method to hit underwater targets consists in delivery of a detachable warhead of underwater action to a target location area, separation of a warhead in the end section of flight trajectory and its actuation after landing on water. The detachable warhead is delivered by the first missile. Prior to delivery of the warhead to the target location area, they deliver one radio hydroacoustic buoy. The buoy is delivered by the second missile. After buoy landing on water, as the first missile gets closer to the area of target location, by means of equipment placed on it, they provide for reception of information from the buoy on location of the target, and the point of warhead landing on water is corrected. Cruise missiles are used for delivery of the warhead and buoy to the area of target location. The cruise missile is equipped with a sustainer power plant with an air jet engine. The speed of acceleration of each missile by a speeding device in the initial section of the trajectory is limited by the value sufficient for development of an aerodynamic lifting force that sustains the flight and to start the sustainer engine, afterwards they provide for its separation from the speeding device, start of the sustainer engine and further flight to the area of target location in the atmosphere. Correction of the point of warhead landing on water is carried out due to correction of the trajectory of the first missile flight by confirmed coordinates of the target and separation of the warhead closer to the target.

EFFECT: invention provides for reduced mass of a missile complex.

4 cl, 2 dwg

Description

The invention relates to methods for hitting an underwater target using an underwater warhead delivered by a rocket.

There is a known method for hitting underwater targets at long ranges, patent RU No. 2371667, which consists in delivering a detachable underwater warhead to the target area using the first ballistic missile using an accelerating engine (booster device), in which the warhead is located under the nose nose fairing being discharged, discharge fairing and separation of the warhead at the final section of the flight path and its activation after splashdown, while before the delivery of the warhead underwater to paradise at least one radio sonar buoy is delivered to the target location by means of a second missile flight using an acceleration device. The sonar buoy is delivered as part of a detachable cruise missile located under the second nose rocket being dropped off, the fairing is dropped and the cruise rocket is separated at the end of the flight path, a horizontal flight of the cruise missile is carried out over the target area, in which at least one radiohydroacoustic discharge buoy; the underwater warhead is delivered to the target location area together with a detachable block of deflectable aerodynamic surfaces with drives docked with it after a sufficient time interval to float the buoy, while approaching the target location area, information receiving equipment is received via the first ballistic missile control system on the location of the target from the sonar buoy via the radio channel, and before the separation of the underwater warhead is entered s target coordinates in its management system; in the air section of the movement of the underwater warhead, its trajectory is corrected by means of the aerodynamic surface block for splashdown in the region of the specified location of the underwater target and the block of aerodynamic surfaces is separated before splashdown.

The essential features of the proposed method, which coincide with the features of the prototype, are as follows: a method for hitting underwater targets, which consists in delivering a detachable underwater warhead to the target area by flying the first rocket using the booster device, separating the warhead at the end of the flight path and activating it after splashdown, at the same time at least one radio hydro is delivered to the target area before delivery of the underwater warhead an acoustic buoy, by flying a second rocket using an accelerating device, the sonar buoy is separated and, after being brought in, when approaching the target rocket’s target area, using the equipment placed on it, receive information from the radio sonar buoy about the target’s location via radio channel, and according to the information received, the point of splashdown of the warhead of the underwater action is adjusted.

In the known method for the flight of each BR along a ballistic trajectory, the thrust of the booster must exceed the weight of the BR, which determines a large consumption and fuel supply, including a large consumption of oxidizing agent, which is technically impossible to take from the atmosphere, and therefore, in the volume of BR, in addition to fuel, oxidizer reserve required for the flight. These factors increase the mass of BR. In addition, in the known method during the flight of the BR, aerodynamic lift is not used, which further increases the required fuel consumption, its supply in the composition of the BR and their mass. The large mass of BR complicates their manufacture, maintenance during operation, transportation and increases their cost, as well as facilitates opposition to enemy forces, which reduces the likelihood of hitting an underwater target.

The technical problem to which the proposed method is directed is to reduce the mass of the device for hitting underwater targets.

To solve the problem in a method of destroying underwater targets, which consists in delivering a detachable underwater warhead to the target area by flying the first rocket using an accelerating device, separating the warhead at the end of the flight path and activating it after splashdown, while before delivery at least one sonar buoy delivers the underwater action to the target area by means of a second missile flight using of the racing device, the sonar buoy is separated and, after being brought in, when approaching the target rocket’s target area, using the equipment located on it, receive information from the radio sonar buoy on the target’s location via the radio channel and correct the splashdown point of the warhead of the underwater actions to deliver a detachable underwater warhead and at least one sonar buoy to the target area cruise missiles are used, each of which is equipped with a marching propulsion system with an air-jet engine, while the acceleration speed of each rocket by an accelerating device in the initial portion of the trajectory is limited to a value sufficient to create an aerodynamic lift supporting flight and launch the sustainer engine, after which it is separated from the booster device, the launch of the main engine and further flight to the area of the target in the atmosphere, and the correction of the point of splashdown of the warhead under one action is carried out by correcting the trajectory of the first rocket on the specified target coordinates and separating warhead submarine action closer to the goal. For an economical flight on a marching section with subsonic speed, the air-jet engine of the marching power plant of each rocket is chosen turbojet, while their flight on the marching section of the trajectory is carried out at altitudes of 0.05-15 km. For an economical flight on a marching section with supersonic speed, the air-jet engine of the marching power plant of each rocket is selected as direct-flow, while their flight on the marching section of the trajectory is carried out at altitudes of 10-40 km. To increase the reliability and range of destruction by the target complex, after the sonar buoy is splashed, using electronic equipment installed on the second missile, the information from the buoy is received, amplified and transmitted over the air.

Distinctive features of the proposed method for hitting underwater targets are as follows: cruise missiles are used to deliver a detachable underwater warhead and at least one sonar buoy to the target area, each of which is equipped with a marching propulsion system with an air-jet engine, while the acceleration of each rocket by an accelerating device in the initial portion of the trajectory is limited to a value sufficient to create an aerodynamic support flight lift force and launch the sustainer engine, after which it is separated from the booster device, launch the sustainer engine and then fly to the target area in the atmosphere, and the correction of the splashdown point of the underwater warhead is carried out by correcting the flight path of the first rocket according to the specified target coordinates and separation of the underwater warhead closer to the target; for the flight of the first and second missiles, a turbojet engine is used, while their flight on the marching section of the trajectory is carried out at altitudes of 0.05-15 km; For the flight of the first and second missiles, a ramjet engine is used, while their flight on the marching section of the trajectory is carried out at altitudes of 10-40 km; after splashing the sonar buoy by means of the electronic equipment installed on the second rocket, information is received from the buoy, its amplification and transmission via radio channel.

Due to the presence of these distinctive features, together with the known ones, the following technical result is achieved - the masses of the first and second missiles are reduced, the time and money spent on their manufacture, maintenance during operation and transportation are expanded, the range of the possible range of destruction of the underwater target is expanded, and the likelihood of destruction of the underwater target is increased.

The proposed technical solution can find application in the development of anti-submarine weapons of reduced mass and an extended range range, increased probability of hitting submarine targets.

The method is illustrated by the anti-submarine weapons device shown in the drawings (figure 1 and figure 2).

Figure 1 presents the first KP device equipped with a marching power plant based on a ramjet engine.

Figure 2 presents the second KR device equipped with a marching propulsion system based on ramjet.

Presented on the drawings, the anti-submarine weapon system comprises a first control gear 1, including a control system 2, steering surfaces 3 with actuators 4 in communication with the control system 2. KR 1 is equipped with a marching power plant based on a jet engine, including ramjet 5, fuel tank 6, fuel supply line 7 to ramjet 5, containing a fuel metering device 8 in communication with the control system 2. KR 1 also contains a warhead 9 underwater with a device 10 for its separation, connected with the control system 2, which includes equipment 11 for receiving radio waves, calculating the specified coordinates of the target and determining the separation point of the warhead 9 underwater action. KR 1 is also equipped with an accelerating device made in the form of a solid fuel rocket engine (solid propellant engine) 12 located in the ramjet cavity 13 5. CR 1 is docked with the solid propellant rocket engine 12 by means of the separation device 14. As an acceleration device, a carrier aircraft can also be used as the main acceleration device or additional. The ramjet 5 contains a multi-leaf adjustable jet nozzle 15. The cavity 16 above the nozzle 15 is connected to the atmosphere by a line 17 containing a shutoff valve 18 in communication with the control system 2. The complex includes a second KP 19, including a control system 20, steering surfaces 21 with actuators 22 in communication with the control system 20. KP 19 is equipped with a power plant based on an air-jet engine containing ramjet 23, fuel tank 24, fuel supply line 25 to ramjet 23, containing a fuel metering device 26, in communication with control system 20 of the KR 19, which is also equipped with three sonar buoys 27 and devices 28 of their separation, in communication with the control system 20. KP 19 contains apparatus 29 for receiving, amplifying and transmitting information on the target location via radio channel and is equipped with an acceleration device made in the form of a solid propellant rocket engine 30 located in the cavity 31 of the ramjet 23. KR 19 is connected to the solid rocket motor 30 by means of a separation device 32. As an acceleration device, a carrier aircraft can also be used as the main acceleration device or additional. The ramjet 23 contains a multi-leaf adjustable jet nozzle 33. The cavity 34 above the nozzle 33 is connected to the atmosphere by a line 35 containing a shutoff valve 36 in communication with the control system 20.

Device anti-submarine weapons works as follows. Flight KP 19 is carried out ahead of flight KP 1, sufficient to bring the sonar buoys 27 after separation by sequentially turning on the control system 20 of the separation devices 28 at various points in the area where the underwater target is located. To ensure the flight of KP 1 and KP 19, the solid propellant rocket engines 12 and 30 provide their acceleration only to a flight speed sufficient to create the aerodynamic lifting force supporting their flight and launch mid-flight ramjet engines, respectively 5 and 23, therefore, the mass of solid propellant rocket engines 12 and 30, in comparison with prototype, small. After acceleration of KP 1 and KP 19, control systems 2 and 20 use devices 14 and 32, respectively, providing separation of solid propellant rocket engines 12 and 30, which further reduces the mass of KP 1 and KP 19 required for their cruise flight, and launch marching ramjet engines, respectively 5 and 23. The marching section of the flight of КР 1 and КР 19 in the atmosphere, using ramjet 5 and 23 of air oxygen contained in it, eliminates the presence of an oxidizing agent in the composition of КР 1 and КР 19 for flight, which reduces, compared with the prototype , volume and mass of KR 1 and KR 19, necessary for execution their flight march. In addition, the controlled flight of KP 1 and KP 19 in the atmosphere, with an unpredictable enemy end point of flight, in contrast to the prototype with a ballistic trajectory, complicates the task of counteraction forces and, thereby, increases the likelihood of hitting underwater targets. KR 1 allows, due to the possibility of its maneuverable flight at low altitude, more accurately, with a smaller deviation, compared with the prototype, to deliver the underwater warhead 9 according to the specified coordinates of the underwater target, determined by the equipment 11 after receiving from the sonar buoys 27 via the radio channel information about the location of the target, and use the device 10 separation of the warhead 9 closer to the target, which increases the likelihood of hitting an underwater target. In addition, the maneuverable flight of the KR 1 and KR 19 at low altitude allows the delivery of sonar buoys 27 and underwater warhead 9 to the target located at a short range, which expands the range of the possible range of destruction of underwater targets by the complex. Equipping ramjet engines 5 and 23 with multi-leaf adjustable jet nozzles 15 and 33 provides for their open positioning of solid propellant rocket engines 12 and 30, respectively, in cavities 13 and 31 of ramjet engines 5 and 23. In addition, after separation of solid propellant rocket engines 12 and 30, with ramjet engines 5 and 23, by shutting off the valves 18 and 36 with control systems 2 and 20, respectively, an increase in the pressure of the products of fuel combustion in the cavities 16 and 34 is ensured and, as a result, the multi-leaf adjustable jet nozzles 15 and 33 are moved to the position of the minimum critical section, which leads to an increase pressure in the cavities 13 and 31, respectively, ramjet 5 and 23 and their rods, which provide an increase in speed and altitude, respectively, KP 1 and 19, after which their control system, respectively, 2 and 20, acting on the device 8 and 26 dosing of fuel, reduce its consumption to the value necessary to maintain the accumulated RR 1 and 19 cruising speed and altitude. The cruise flight of КР 1 and КР 19 to the area of location of a sea target with low fuel consumption in ramjet, respectively, 5 and 23, is performed at altitudes of 10-40 km with high supersonic speed, which reduces the flight time of КР 1 and КР 19 to the area of target location . When a turbojet engine (not shown) is used in the marching power plant КР 1 and КР 19, their economical march flight to the area of sea target location, with low fuel consumption, is performed at altitudes of 0.05-15 km, while flying at low altitude reduces their visibility against the background of the Earth's surface, which reduces the likelihood of their detection and counteraction, respectively, increases the likelihood of hitting an underwater target. The defeat of the underwater target can be realized if there is at least one detachable radio-acoustic buoy 27 in the composition of the CR 19. An increase in their number leads to an increase in the reliability of detection and the likelihood of hitting the underwater target, due to the location of the radio-acoustic buoys 27, after splashing, at a distance from a friend, with different angles of direction to the target, with known proper coordinates, it is possible to increase the accuracy of determining the coordinates of the target, which increases oyatnost its defeat. The equipment 29 on KP 19, after the flooding of buoys 27, provides reception, amplification and transmission by radio channel of information about the location of the target, which ensures its reception by the equipment 11 at a greater distance of KP 1 from the target, while this is possible through the control system 2, after receiving the greater the distance KP 1 from the target information about the specified position of the target, optimize the trajectory of KP 1 for faster delivery of the warhead 9 to the specified target location on a shortened route. In addition, the flight of the KR 1 along a shortened trajectory ensures, with the same fuel supply, the delivery of the warhead 9 to a target far from the KR 1 at a greater distance, which extends the range of the range of destruction of the underwater target by the complex, and the equipment 29 receives information from radio-acoustic buoy 27, its amplification and transmission over the air increases the reliability of its reception by the apparatus 11 KR 1 and, due to this, increases the likelihood of hitting an underwater target.

Claims (4)

1. The method of destroying underwater targets, which consists in delivering a detachable underwater warhead to the target area through the flight of the first rocket using an accelerating device, separating the warhead at the final section of the flight path and activating it after splashdown, while before delivering the underwater warhead at least one radio sonar buoy is delivered to the target area by means of a second missile flight using an accelerating device, the separation of the sonar buoy and after it is brought in when approaching the target missile target region by means of the equipment located on it, they receive information on the radio channel from the sonar buoy about the target’s location and, according to the received information, correct the splashdown point of the underwater warhead, characterized in that for delivery of the detachable use a winged underwater warhead and at least one sonar buoy to the target area missiles, each of which is equipped with a marching propulsion system with an air-jet engine, while the acceleration speed of each rocket by an accelerating device in the initial portion of the trajectory is limited to a value sufficient to create an aerodynamic lift supporting flight and launch the sustainer engine, after which it is separated from accelerating device, starting the main engine and further flying to the area where the target is located in the atmosphere, and correcting the splashdown point of the underwater warhead Ia is carried out by correcting the flight path of the first missile according to the specified coordinates of the target and separating the warhead of the underwater action closer to the target. 2. The method according to claim 1, characterized in that the air-rocket engine of the marching propulsion system of each rocket is chosen turbojet, while their flight on the marching section of the trajectory is carried out at altitudes of 0.05-15 km. 3. The method according to claim 1, characterized in that the air-rocket engine of the marching propulsion system of each rocket is selected direct-flow, while their flight on the marching section of the trajectory is carried out at altitudes of 10-40 km. 4. The method according to any one of claims 1 to 3, characterized in that after the radio-acoustic buoy is brought in by means of radio-electronic equipment installed on the second rocket, information is received from the radio-hydro-acoustic buoy, its amplification and transmission via radio channel.

Images