RU44811U1 - MULTI-TARGET CONTROLLED ROCKET IN A STARTING CONTAINER - Google Patents

Abstract

The proposal relates to rocketry and is intended to hit targets of various types. The missile is operated in a launch container and contains an accelerating engine, a radio equipment unit, a mid-flight engine, a steering compartment and a replaceable warhead. As a combat unit of your choice, depending on the type of target, you can set: cumulative tandem warhead, high-explosive fragmentation or high-explosive warhead. To coordinate the procedure for launching rocket launch chains, depending on the type of warhead, a matching board containing an electronic delay driver is installed on the container. On the container there are two power trunnions for suspension to the helicopter, as well as yokes for mounting in the drum of the launcher on a ground carrier (BMP type combat vehicle). In the front axle there is a pyro-stop for holding the rocket in the container, and in the rear axle there is a switching board, through which the starting circuits are switched from the control panel on the carrier with the rocket starting circuits. The number of dependent claims of the utility model formula is 3, 12 - illustrations.

Description

The proposal relates to rocket science and is intended to hit targets of various types.

Known fragmentation-beam projectile containing an explosive charge and a bottom fuse mounted in a housing with a front bottom, on which a unit with densely laid ready-made striking elements (GGE) and an easily removable head cap are mounted. The block is made with the possibility of its replacement, including immediately before the shot. Replaceable blocks are equipped with ready-made striking elements of various weights, see the description of the patent of the Russian Federation 2208759, IPC 7 F 42 V 12/32.

A multi-purpose projectile is known, consisting of a head and a bottom unit fastened with a detachable connection and electrically connected to each other, the bottom unit having a body, explosive charge, fuse, and the head unit also contains inset elements and is interchangeable. After determining the goal and choosing the desired type of head unit (high-explosive, cumulative, etc.), both blocks are fed to an assembly manipulator that connects the blocks in the projectile and feeds it to the gun’s loading system, see description of RF patent 2080548, IPC 6 F 42 V 12/02.

The effectiveness of hitting remote (at 5 or more kilometers) targets with small dimensions (tank, armored car) with shells of this kind is relatively low due to their significant dispersion relative to the aiming line inherent in an unguided projectile.

The closest analogue is the Sturm rocket in the launch tube, see "Guided Projectile 9M114." Technical description and instruction manual, Moscow, Military Publishing, 1982

The combat use of missiles is provided as part of the Sturm-S and Sturm-V self-propelled and helicopter systems deployed on the BM 9P149 combat vehicle and on the Mi-24 helicopter.

The projectile structurally consists of three parts: a guided missile, an accelerating engine and a container tube.

Guided missile is made according to the aerodynamic scheme "duck" and contains a warhead, steering compartment, main engine and radio unit. Four arched feathers are used to create the necessary lifting force, and the aerodynamic control force is created when the aerodynamic rudders are deflected. To ensure launch from the container pipe, the rocket does not have protruding parts, the rudders and feathers are folded and open after the launch of the rocket from the container pipe. The warhead is located in front of the rocket and is an autonomous unit that allows multiple docking with the steering compartment. In the body of the warhead is a cumulative charge with a safety-executive mechanism of electromechanical action.

The rocket is electrically connected to the container tube with a block that is disconnected at the moment of the shot.

For mechanical and electrical docking with the carrier, there are two trunnions in the form of power flanges spaced along the length of the container pipe. In the front axle there is a pyrostopor for holding the rocket, and in the rear axle there is a switching board with contacts for switching the launch circuits of the rocket with the launch circuits of the carrier (combat vehicle, helicopter, etc.).

In the steering compartment, located behind the warhead, there are blocks for the formation and execution of control commands and for supplying power to the on-board equipment - the steering gear, gyroscopic sensor and their gas and electric power, i.e. sources of electric and gas

energy (powder pressure accumulator, powder engine, turbogenerator power supply).

Marching engine is a single-chamber dual-mode engine with two side inclined sockets.

In the main engine there is a solid propellant sustainer charge and an igniter, the starting circuit of which is connected to the on-board power source through an inertial contactor located in the steering compartment.

Behind the marching engine is a radio unit with a transponder unit.

Behind the radio equipment unit, a solid-fuel single-mode accelerating engine with an electric igniter is detached from the rocket after it leaves the container pipe, the starting circuit of which is connected to the power source on the carrier through a switching board in the rear axle on the container pipe.

The missile has a relatively low effectiveness of the destructive action, since it is structurally provided for equipping it only with a single-block cumulative warhead with limited armor penetration.

The technical result of the proposal is to expand the combat capabilities of the rocket, its damaging effects on targets of various types.

This is achieved by the fact that in a guided missile containing an accelerating engine, a radio equipment unit, with folding wings fixed to its body, a main engine, a steering compartment with gas and electric power supply for the steering drive, a gyroscopic sensor, and a radio equipment unit; with a side connector for electrical connection of the launch chains of the rocket with the container through a block on the container that is detachable during firing, as well as a removable warhead, the container has two power pivots spaced along its length for attachment to the carrier, in front of which there is a pyro-support for holding the rocket, and in rear axle mounted switching board with two groups of contacts for

serial connection to the power source on the carrier, the first group of which is connected through the disconnectable block to the start-up circuits of gas and electric power means, and the second group of contacts to the start-up circuits of the pyrostop and accelerating engine, a matching board is installed on the starting container, mounted in a common housing with a disconnectable block and electrically connected by the input to the second group of contacts of the switching board on the rear axle, and the output - with the contacts of the starting circuit of the pyrostop on the disconnect my block, while in the front axle under the pyrostop there is mounted a starting switching terminal, which is switched on when it is triggered, of current from the carrier to the starting circuit of the accelerating engine.

The guided missile can be equipped as a warhead with a cumulative tandem warhead, including the main cumulative charge with a bottom fuse, a leader charge put forward at launch using a powder gas generator, the launch circuit of which is connected to the second group via an intermediate block mounted on the launch container contacts of the switching board, while the starting circuit of the pyrostop is connected to the same contacts through the electronic delay driver installed in the matching board.

A high-explosive fragmentation warhead can be installed on the rocket, including a explosive explosive charge placed in the framework, a safety-actuating mechanism, a non-contact target sensor for laser scanning of the surrounding space connected to it, and a charged current source battery, the electric igniter of which is connected through an intermediate block the launch container to the second group of contacts of the switching board, while the launch circuit of the pyrostop is connected to the same contacts through the Atel electronic delay set in the agreed fee.

A high-explosive warhead with volume-detonating and dispersing-initiating charges can be used as a warhead on a rocket, while the pyrostop launch circuit is connected to the second group of contacts of the switching board together with the starting circuit of the accelerating engine through a short-circuit jumper installed in the matching circuit board.

The essence of the proposal is presented in the drawings, where in FIG. 1 is a general view of a rocket with an accelerating engine in a launch container (PC), in FIG. 2 is a steering compartment and its connection with a container, in FIG. 3 are elements of a steering compartment, in FIG. 4 - high-voltage rocket connector, in Fig. 5 - pirostop with contacts, in Fig. 6 - instrument compartment and PC, in Fig. 7 - missile locking unit in the PC, in Fig. 8 - missile with a cumulative tandem warhead, in Fig. .9 - mounting of the warhead with the steering compartment, figure 10 - rocket with high-explosive fragmentation warhead, figure 11 - rocket with high-explosive warhead part, in Fig. 12 is a diagram of the location of electrical connections and their functioning when launching a rocket.

Multipurpose guided missile in a launch container is presented in figure 1. In the launch container 1 are located: warhead (warhead) 2, steering compartment 3, mid-flight propulsion system (MDU) 4, instrument compartment 5, accelerating engine 6. On the outer surface of container 1 there is a rear block 7, rear axle 8, front axle 9 , intermediate block 10. The ends of the container are closed by the front cover 11 and the back cover 12.

Figure 2 presents the elements of the steering compartment 3 and its docking with the launch container 1. Figure 2 shows the housing 13, in which there is a separable block 14 of the connector of the launch container, which is mated with the block 15 of the rocket connector, matching board 16, electronic delay driver 17. In the steering compartment (RO) is a gyroscope 18, inertial closure 19, stabilizer-rectifier 20, on the outside

the surface of the PO there is a cover 21 of the control connector, which is fixed by a screw 22.

The steering compartment is connected to the bottom 23 of the marching propulsion system 4, in front of which there is a delayed-action electric igniter 24, an ignitor 25 of the charge 26 of the MRL. During operation, the rocket is locked inside the launch container with the aid of a pyrostop lock 27.

Figure 3 shows the elements of the steering compartment: a starting engine 28 for accelerating the rotor of the gyroscope 18, a powder pressure accumulator (LAD) 29, a PAD filter 30, a turbogenerator power supply 31, a gas steering machine 32, a socket 33.

Figure 4 shows the elements of the high-voltage connector: high-voltage block 34, contacts 35, connector 36, cover 37, pin 38, axis 39.

Figure 5 shows the circuit elements of the accelerating engine 6 using a pyrostop 27: knife contact 40, insulator 41, inrush current switching terminal 42.

Figure 6 shows the elements of the instrument compartment (ON) 5, the rear axle 8 and the launch container. In the rear axle there is a switching board 43.

The instrument compartment contains: a unit of equipment 44 with a receiving antenna 45, a transponder unit 46 with a lamp 47. There is a cover 48 on the housing of the launch container 1 that closes access to the cover 49 of the control waveguide of the radio block and the cover 50 of the radio code switch.

The rear cover 12 of the launch container 1 is locked using a spring 51. To secure the rockets in the drum on a self-propelled carrier, 2 yokes 52 (with seats) are used, located in the plane of the front 9 and rear 8 trunnions of the launch container and offset 90 ° relative to the trunnions.

On an air carrier (helicopter), pins 8 and 9 are used to mount the rocket.

Figure 7 shows the elements of locking the rocket in the PC using the ring 53, nut 54 and locking screws 55.

On Fig shows a missile with a tandem cumulative warhead 56, consisting of a leader 57 and a main stage 58. Folding aerodynamic rudders 59 are installed on the body of the steering compartment 3, and on the body 5 are fixed: lower wing 60, upper wing 61. Using contacts 62, which are connected to the intermediate block 10, power is supplied to the warhead 56.

Figure 9 shows the fastening elements of the warhead 2 with the steering compartment 3 using countersunk screws 63 and split sleeves 64.

Figure 10 shows a rocket 65 with a high-explosive fragmentation warhead 66. On the body of the warhead 66 there are output windows 67 of the laser radiation sensor and input windows 68 of the laser receiver of the reflected signal from the target. Using the contacts 69, which are connected to the intermediate block 10, power is supplied to the warhead 66.

11 shows a rocket 70 with a high-explosive warhead 71.

On Fig shows the location of the rocket elements in the launch container with electrical connections, explaining the sequence of interaction (functioning) of the rocket elements at startup, the connection of the rocket with the carrier (air, ground), a power source and a control panel.

Figure 12 presents: an electric igniter 72 of the pyrotechnic leader extension mechanism 57 warheads, an electric ignitor 73 of a power supply 74 of a non-contact sensor of a high-explosive fragmentation warhead 66, an electric igniter of a gyroscope starting engine, an electric igniter of a pressure powder accumulator 76, an electric igniter of a pyro igniter 77, an electric igniter 78, power source 79,

operator panel 80, board slot 81 of the carrier, first group of contacts 82, second group of contacts 83.

The electric connection between the rocket and the carrier (air :, terrestrial :), its power source 79, and the operator panel 80 is carried out using the onboard connector 81 through the switching board 43 of the rear axle of the launch container. Voltage is supplied to the 1st and 2nd group of contacts 82 and 83, respectively.

Multipurpose guided missile in the launch container is operated in the form of a shot. The missile is supported by the centering belts of the marching remote control on the inner walls of the launch container made of fiberglass.

The rocket is electrically connected to the launch container by a disconnect block 14 of the connector of the launch container 1. The launch container with the carrier is connected by a switching board 43 of the rear axle of the PC with the carrier connector 81 of the carrier.

After detection, aiming the mark of the sight on the target, the operator presses the "Start" button.

The voltage from the power source 79 of the carrier is supplied to the first group of contacts 82 of the board 81 and is supplied to the switching board 43 of the rear axle of the PC. Further, the voltage through the disconnecting block 14 of the PC connector is supplied to the block 15 of the rocket’s onboard connector and through it, power is supplied to the electric igniter 75 of the gyroscope starting engine, the electric igniter 76 of the powder pressure accumulator, they are launched and the turbo-generator power supply is launched, and the onboard equipment of the rocket is powered up.

After a delay time, from the operator’s console, from the power supply source 79 of the carrier, power is supplied to the 2nd group of contacts 83 of the connector 81 and supplied to the contacts of the switching board 43 of the rear axle of the PC. Then the voltage is supplied to the intermediate block 10 and through it to the electric igniter

72 of the pyrotechnic leader extension mechanism, matching board 16, electronic delay driver 17, the leader extends forward, destroying the cover 11 and stops.

After 0.095 s, the electronic delay driver applies voltage to the pyrostop igniter 77.

The pyrostopor fires, the rocket detaches from the launch container.

In a rocket with a high-explosive fragmentation warhead, the voltage is supplied to an electric igniter 73 of the power source of a non-contact target sensor (NCC) and to an electronic delay shaper 17.

The battery goes into mode and power is supplied to the fuse. After 0.095 s, the electronic delay driver applies voltage to the pyrostop igniter 77. The pyrostopor fires, the rocket detaches from the launch container.

In a rocket with a high-explosive warhead, instead of an electronic delay driver, the matching board has a short-circuit jumper and the voltage immediately goes to the pyrostop ignitor 77.

Further, the launch process for all missiles is the same.

The release mechanism is triggered. The missile is released from the transport lock.

When the opening mechanism located in the front axle is triggered, with the help of a pirostop 27, the knife contact 40 breaks through the insulator 41 and closes the switching terminal of the starting current 42 and the voltage is supplied to the rear block 7 and through it to the electric igniter 78 of the accelerating engine 6.

Under the influence of the RD thrust, the rocket advances to the PC, pins are pushed, the rocket connector pads 15 are disconnected from the rocket 14 disconnect pad, and the MDU start circuit is connected to the contacts of the inertial contactor 19.

Under the influence of the RD thrust, the rocket flies out of the PC, having received an initial speed and an angular twist of up to 12-18 r / s, while under the influence of overloads, an inertial contactor 19 is activated and the voltage from the stabilizer-rectifier 20 is supplied to a delayed-action electric igniter 24 MDU.

After the launch of the rocket from the PC under the action of centrifugal forces, the rudders 59 and the arched wings 60, 61 are opened, which lock in the open position.

At a distance of 3-5 m from the launcher, the MDU turns on, which accelerates the rocket to supersonic speed.

Due to the difference in speed between the rocket and the rocket, the taxiway is separated from the rocket and it falls to the ground.

The missile is controlled by carrier control equipment with the transmission of commands over the radio line, during which the operator holds the sight mark on the target, and the control system automatically keeps the missile on the aiming line.

The deviation of the rocket from the line of sight is measured by the direction finder of the control device, which receives pulsed infrared (IR) radiation from a lamp 47 mounted on the rocket.

Structurally, the sight and the direction finder are combined into a control device and have a common optical axis.

Direction finder signals, in the form of voltages proportional to the angular deviations of the rocket from the aiming line in the horizontal plane (course) and in the vertical plane (pitch), are sent to the command generation unit, where they, taking into account the change in the dynamic characteristics of the rocket in flight time, are converted into control commands in the form of stresses proportional to the linear deviations of the rocket from the line of sight at the heading and pitch. In addition, signals to compensate for the weight of the rocket and dynamic

pointing errors in the presence of the angular velocity of the line of sight.

The direction and pitch control commands from the command generation unit are sent to the command transmission radio equipment located on the medium and are transmitted in encrypted form over the radio link to the rocket.

The control commands for the onboard equipment of the rocket received by the antenna 45 of the radio block 44 are decrypted and converted into a single-channel control signal supplied to the electromagnets of the steering machine 32, which drives the aerodynamic wheels 59.

When meeting with the target (tank) of the tandem warhead missile, the leader is undermined, dynamic defense is triggered, after a delay time, the subsequent warhead of the main warhead is broken, the main armor breaks through and the target (tank) is defeated.

A target is hit by a rocket with a high-explosive fragmentation warhead when a rocket approaches a target. At a given distance from the underlying surface of the terrain or target, a non-contact target sensor is triggered, which gives an electric pulse to the PIM, causing it to trigger and undermine the warhead warhead.

In case of failure of the NCC, the PIM operation occurs from contact sensors. When a combat charge is undermined, the resulting damaging elements provide for the destruction of the target.

The defeat of a missile target with a high explosive warhead occurs when it hits the target.

Comparison of the claimed technical solution with the prototype made it possible to establish compliance with its criterion of "novelty."

Using the proposed technical solution allows to increase the combat effectiveness of guided weapons systems by equipping the missile with warheads of various functional purposes while maintaining a unified missile unit and launch container,

which significantly reduces the cost of the sample and the costs of its production and operation in the army.

The tests carried out confirmed the high efficiency of guided weapon systems using a multi-purpose missile equipped with military units for various purposes.

Claims (4)

1. A multipurpose guided missile in a launch container, comprising an accelerating engine, a radio equipment unit with folding wings fixed to its body, a main engine, a steering compartment with gas and electric power for the steering drive, a gyroscopic sensor and a radio equipment unit, with an airborne connector for electrical connection of the starting circuits missiles with a container through a block on the container that is detachable during firing, as well as a replaceable warhead, while the container has two spaced apart along its length power trunnions for mounting on a carrier, the first of which has a pyrostop to hold the rocket, and in the rear trunnion there is a commutation board with two groups of contacts for sequential connection to a power source on the carrier, the first group of which is connected through the disconnect block to the starting circuits of gas and electric power supply, and the second group of contacts - to the starting circuits of the pyrostopor and the accelerating engine, characterized in that a matching board is mounted on the starting container, mounted I am in a common housing with a disconnectable block and electrically connected by an input to the second group of contacts of the switching board on the rear axle, and the output - with the contacts of the start circuit of the pyrostopor, while in the front axle under the pyrostopor is mounted the terminal for switching the starting current from the carrier to the starting booster circuit. 2. The multi-purpose guided missile according to claim 1, characterized in that a cumulative tandem warhead is used as the warhead, including the main cumulative charge with a bottom fuse, a leader charge advanced at launch by means of a powder gas generator, the starting circuit of which is connected through an intermediate a block mounted on the starting container to the second group of contacts of the switching board, while the starting circuit of the pyrostop is connected to the same contacts through the electronic delay driver, nny in the matching board. 3. The multi-purpose guided missile according to claim 1, characterized in that a high-explosive fragmentation warhead is used as a warhead, including an explosive explosive charge placed in the frame, a safety-actuating mechanism, a non-contact contact target sensor for laser scanning connected to it the surrounding space and a charged battery of the current source, the electric igniter of which is connected through the intermediate block of the starting container to the second group of contacts of the switching board, while starting pirostopora-hand circuit is connected to the same contacts via electronic delay generator mounted in the matching board. 4. The multipurpose guided missile according to claim 1, characterized in that a high-explosive warhead with volume-detonating and dispersing-initiating charges is used as the warhead, while the pyrostop launch circuit is connected via a short-circuit jumper in the matching board to the second group of contacts of the switching board together with the starting circuit of the booster engine.