RU2534476C1 - Underwater target hitting method - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: underwater target hitting method consists in supply to a target location area of an underwater action separated warhead and one hydroacoustic buoy by means of a missile using an acceleration device, separation of the warhead in the final section of the flight trajectory and its involvement after splashdown. Before the underwater action warhead is separated, one hydroacoustic buoy is separated, and after its splashdown, by means of equipment arranged on the missile there provided is a reception via a radio channel of information from the hydroacoustic buoy on a target location. A point of splashdown of the underwater action warhead is corrected as per the received information. In order to deliver the separated underwater action warhead and one hydroacoustic buoy to the target location area, a cruise missile is used. The missile is provided with a propulsion power plant with an air-jet engine. The missile acceleration velocity in the initial section of the trajectory is restricted by a value sufficient for the creation of an aerodynamic lift supporting the flight and for the start of a cruise engine, after which there provided is its separation from the acceleration device, the start of the cruise engine and further flight to the location area of the target in the atmosphere.

EFFECT: reduction of the weight of an underwater target hitting device.

3 cl, 1 dwg

Description

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

There is a known method of hitting underwater targets at long ranges, patent RU No. 2371668, which consists in delivering a detachable underwater warhead to the target area by means of a ballistic missile (BR), in which the warhead is located under a releasable nose fairing as part of a detachable cruise missile, and the discharge of the fairing and the separation of a cruise missile (RC) in the area of the target, controlled by horizontal flight of the cruise missile above the area of the target, in which at least one radiog a buoyancy buoy placed in a cruise missile, after which it is received radio information from the buoy about the target’s location by means of radio wave receiving equipment placed on the cruise missile, the coordinates of the separation point of the underwater warhead are determined, the approach to the separation point is carried out, the underwater action warhead is separated and used after splashdown. Acceleration of the BR is carried out by an accelerating engine (accelerating device).

The essential features of the proposed method that match the features of the prototype are the following: a method for hitting underwater targets, which consists in delivering to the target area a detachable underwater warhead and at least one radio-acoustic buoy by means of a rocket using an accelerating device, separation of the warhead on the final section of the flight path and its activation after splashdown, while before the separation of the underwater warhead’s separation, Raina least one sonobuoy and after splashdown by hardware located on the rocket provide reception over the air from a sonobuoy information about target location, and the received information is corrected branch point warhead submarine actions.

In the known method for flying BR along a ballistic trajectory, the thrust of the booster device must exceed the weight of the BR, which determines a large consumption and fuel supply, including a large consumption of oxidizer, which is technically impossible to take from the atmosphere, and therefore, in the volume of BR, besides the fuel, the required for flight oxidizer reserve. 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 reserve in the composition of the BR and its mass. The large mass of BR complicates its 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 to the target area a detachable underwater warhead and at least one radio-acoustic buoy by means of a rocket using an accelerating device, separating the warhead at the end of the flight path and using it after splashdown, while before separation of the underwater warhead, at least one radio-acoustic buoy is separated and, after it, splashed I, through the equipment placed on the rocket, provide information on the radio channel from the radio-acoustic buoy about the location of the target, and according to the information received, correct the separation point of the underwater warhead to deliver a detachable underwater warhead and at least one sonar buoy to the area the target’s location uses a cruise missile equipped with a marching propulsion system with an air-jet engine, while its acceleration speed in the initial section of the trajectory The arrays are limited by a value sufficient to create an aerodynamic lift supporting the flight and start the mid-flight engine, after which it is separated from the booster device, the mid-flight engine is launched and then further flying to the target location in the atmosphere. To save fuel during the flight of the Kyrgyz Republic to the target area, the rocket marching propulsion engine is chosen turbojet, while the flight on the marching portion of the trajectory is carried out at altitudes of 0.05-15 km. To reduce the flight time of the cruise missile to the target area, the air-rocket engine of the marching propulsion system of the rocket is selected as direct-flow, while the flight on the marching section of the trajectory is carried out at altitudes of 10-40 km.

Distinctive features of the proposed device: to deliver a detachable underwater warhead and at least one sonar buoy to the target area, a cruise missile equipped with a marching propulsion system with an air-jet engine is used, and its acceleration speed at the initial portion of the trajectory is limited by sufficient to create aerodynamic lift supporting the flight and start the main engine, after which it is separated from the accelerating one construction, launch of the main engine and further flight to the area where the target is located in the atmosphere; an air-jet engine of a marching propulsion system of a rocket is chosen turbojet, while the flight on the marching section of the trajectory is carried out at altitudes of 0.05-15 km; the air-rocket engine of the marching propulsion system of the rocket is selected direct-flow, while the flight on the marching section of the trajectory is carried out at altitudes of 10-40 km.

Due to the presence of these distinctive features in conjunction with the known, the following technical result is achieved - the mass of the device, the time and money spent on its manufacture, maintenance during operation and transportation are reduced, the range of the possible range of destruction of the underwater target is expanded, and the likelihood of damage to 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 device shown in the drawing, on which the ramjet is used in the power plant, as an option of an air-jet engine.

The anti-submarine weapons device is made in the form of KR 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 containing ramjet 5, a fuel tank 6, a 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, in communication with the control system 2, at least one radio-acoustic buoy 11 with a device 12 for its separation, in communication with the control system 2, including apparatus 13 for receiving radio waves, calculating the adjusted coordinates goals and definitions of the separation point of the underwater warhead 9, an accelerator made in the form of a solid propellant rocket engine (RDTT) 14 located in the ramjet cavity 15 5 and docked with the KR 1 by means of the device 16 about divisions. 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 17. The orifice cavity 18 of the jet nozzle 17 of the ramjet 5 is connected to the atmosphere by a line 19 containing a shutoff valve 20 in communication with the control system 2.

The device operates as follows. The fuel reserve of the solid propellant rocket engine 14 is selected based on ensuring the acceleration of the rocket engine 1 to a speed sufficient to create aerodynamic lift supporting the flight of the rocket engine 1 and launch ramjet 5. Once the solid rocket rocket fuel burns out 14, the control system 2 activates the separation device 16, ensuring separation of the rocket engine 1 and rocket engine 14 , which is ejected under the influence of excess air pressure in the cavity 15 ramjet 5. The control system 2 provides the launch ramjet 5 and mid-flight KR 1 from the start to the target area. Moreover, due to the fact that the marching propulsion system based on ramjet engine 5 uses atmospheric oxygen to burn fuel coming from the fuel tank 6 through the line 7 through the dispenser 8, the starting mass of the KR 1 decreases several times due to a decrease in the required fuel supply for it board and, accordingly, reducing the mass of the power plant structure. The cruise flight of the Kyrgyz Republic 1 to the area of the marine target is carried out using aerodynamic lift, therefore, with low fuel consumption in the ramjet 5, and is performed at altitudes of 10-40 km. The use of ramjet 5 in a power plant provides an increase in the cruising speed of the KR 1 and reduces the flight time of the KR 1 to the target area. When a turbojet engine (turbojet engine, not shown) is used in the marching power plant instead of the ramjet 5, the low-cost march flight of rocket 1 to the sea target area, with low fuel consumption, is performed at altitudes of 0.05-15 km. The marching flight of CR 1 with a turbojet engine at low altitude reduces the visibility of CR 1 against the background of the Earth's surface, which reduces the likelihood of its detection and counteraction and thereby increases the likelihood of hitting an underwater target. The presence of a marching power plant based on an air-jet engine (ramjet 5 or turbojet engine) in combination with the possibility of maneuverable flight of the KR 1 in the atmosphere provides a variety of flight paths of the KR 1 and delivery of the sonar buoy 11 and the underwater warhead 9 to both large and short ranges, which extends the possible range of range of application of the device. The presence of a multi-leaf adjustable jet nozzle 17 allows, after the KR 1 has been set to altitude and flight speed, at the command of control system 2, the valve 20 is activated to shut off line 19. at the same time, the gas discharge from the suprastatic cavity 18 to the atmosphere ceases, and the gases flowing through the gaps between the wings the jet nozzle 17 into the cavity 18, increase the pressure in it, under the action of which the jet nozzle 17 is translated into position with a minimum critical section. The decrease in the critical cross section of the jet nozzle 17 leads to an increase in pressure in the combustion chamber and the thrust of the ramjet 5, which allows the control system 2 by acting on the dispenser 8 to reduce fuel consumption from the tank 6 along the line 7 in the ramjet 5 and thereby further reduce the required fuel supply in the fuel tank 6, the mass of the tank 6 and the mass of the CR 1 as a whole. In the area of the location of the underwater target, KR 1 separates at least one sonar buoy 11 by activating the device 12 of its separation. The presence in the KR 1 of several sonar buoys 11 allows, thanks to their location after splashdown at a distance from each other, with different angles of direction to the target, with known proper coordinates, to determine the coordinates of the underwater target with greater accuracy, and to ensure the involvement of the device 10 for splashing combat part 9 of underwater action closer to the location of the target, which further increases the likelihood of its destruction.

Claims (3)

1. A method of destroying submarine targets, which consists in delivering to the target location area a detachable underwater warhead and at least one sonar buoy by means of a rocket using an accelerating device, separating the warhead at the end of the flight path and activating it after splashing, at the same time, before separation of the underwater warhead, they carry out the separation of at least one sonar buoy and, after its splashdown, by means of the cancer equipment, provide reception on the radio channel of information from the radio-acoustic buoy about the location of the target, and according to the information received, correct the point of splashdown of the underwater warhead, characterized in that for the delivery of a detachable warhead underwater action and at least one radio-acoustic buoy to the area of location targets use a cruise missile equipped with a marching propulsion system with an air-jet engine, while its acceleration speed in the initial part of the facet path Chiva quantity sufficient to create a supporting flight aerodynamic lift and main engine start, and then ensure its separation from the accelerating device, start the main engine and the further flight to the target location area in the atmosphere. 2. The method according to claim 1, characterized in that the rocket propulsion engine is chosen turbojet, while the flight on the marching portion 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 the rocket is selected direct-flow, while the flight on the marching section of the trajectory is carried out at altitudes of 10-40 km.