The 9M112M2 and 9M124 anti-tank guided missiles are designed to engage stationary and moving armoured targets when fired from the ground and while moving in direct optical visibility, and also allow combating small targets (DOT, DZOT, etc.). The missiles are used as part of the 9KP7 and 9KP2-1 guided weapon systems mounted on the T-80B, T-80BV, T-64BV and T-64BM tanks. The missiles are fired from the 2A46 smoothbore tank gun or its modifications 2A46M1 and 2A46-2. The 9M112M2 and 9M124 missiles are similar in design, but are equipped with different combat units. The 9M112M2 is equipped with the 9H138 combat unit and the 9M124 with the 9H144 combat unit.
The transfer of control commands from the equipment of the tank to the missile is carried out via a radio communication line. The missile's feedback from the control equipment mounted on the tank is automatically transmitted via a light line from a modulated light source mounted on board the missile.
Along with the 9M112M2 and 9M124 missiles, their prototypes are in service - 9M112 (production from 1975 to 1979) and 9M112M (production from 1979 to 1984). Modernization of the missiles was carried out to increase the power of combat units, improve the design and reliability of missiles without changing their dimensions (caliber, length) and operating conditions. The control system of guided weapon complexes remained unchanged and allows launching missiles of all modifications (9M112, 9M112M, 9M112M2, 9M124).
Missiles 9M112M2 (9M124) is made according to the "normal" aerodynamic scheme The missile body is a cylindrical body with the ogival part in front and a flat bottom at the back. Carrying aerodynamic surfaces of the rocket are sickle wings 1 rectangular shape in terms of creating lifting force and stabilizing the rocket. Due to the adjusting angle of mismatch of the wings, the missile in flight rotates relative to its longitudinal axis. The control organs of the missile are the rudders of 2 trapezoidal shape in the plan. The wings and rudders in the folded state fit into the mid-range of the rocket. The wings and rudders are opened after the missile leaves the channel of the cannon barrel.
1-piezo generator of an explosive device; 2-battle part; 3-PIM; 4-engine; 5-inertial ignition;
6-node of mechanical docking of compartments; 7-front lid; 8-switching device; 9-gyroscopic layout of commands; 10-vowel;
11-board radio equipment for receiving control commands; 12-electronics unit; 13- drive amplifier; 14-battery;
15-rudder; 16-obbing belt; 17-barreled charging of throwing device;
18-node of mechanical and electrical connection of the equipment compartment and the throwing device;
19-galvanic sleeve; 20 sleeves; 21-throwing device; 22-plug of the socket of the throwing device;
23-ignition device; 24-cap; 25-emitter; 26-pallet; 27-drive; 28-tail compartment
29-wing; 30-apparatus compartment; 31-PAD; 32-spring spacer ring; 33-lock; 34-head compartment
The missile consists of two parts that are separately transported in the capping box and the tank gun mount: the head compartment 34 and the tail compartment 28, which are connected to each other in the trays of the tank charging mechanism while the missile is being sent to the gun chamber.
The main compartment 34 of the missile consists of a warhead 2 (see description ) and an engine 4 (see description ). The combat unit is connected to the threaded engine. The main compartment 9H46 of the 9M112M2 missile is equipped with the 9H138 combat unit and the main compartment 9H145 of the 9M124 missile is equipped with the 9H144 combat unit. Engine ignition is carried out behind the muzzle cut of the cannon from the inertial ignition 5. In the rear cover of the engine has a ring flow under the spring spacer ring 32 knots 6 mechanical docking compartments and stops 33 to stop the rocket in the chamber of the gun at sending.
The tail compartment 28 consists of a hardware compartment 80 and a throwing device 21. The equipment compartment contains all the missile's onboard equipment, its rudders, wings and the reciprocal part of the docking mechanism with the head compartment. Carrying elements of the equipment compartment are cowling 10 with a front cover 7 and a pallet 26. The front cover 7 has a spring spacer ring 32 of the docking mechanism. In the front part of the cowling 10 are installed in special sockets four wings 29 with latches, fixing the wings in the open position, and two units of pyrotechnic opening of the wings.
The tail end of the cowling has a pallet 26, which protects the equipment of the compartment from direct exposure to high-pressure gases at gunshot. Pallet 26 is attached to the actuator by 27 collet device. In the cylindrical part of the pallet there are samples for placing the rudders 15 in a folded state. The rudders open when the pallet is discharged; the rudders open by springs. Resetting the pallet is carried out by a pyrotechnic pusher.
On the outer surface of the pallet there is an obturizing belt 16, which eliminates the penetration of gunpowder gases as the missile moves along the channel of the gun barrel. On the bottom of the pallet there is a node 18 of mechanical and electrical connection of the equipment compartment and the throwing device. Through the electrical connection node is the transit electrical connection of the onboard connector of the equipment compartment with the plug 22 of the throwing device plug.
The onboard missile control equipment installed in the equipment compartment includes the onboard radio equipment 11 receiving control commands, switching device 8, gyroscopic layout 9 commands, amplifier 13 drive, drive 27, emitter 25, 12 electronics unit, battery 14, powder battery 31 pressure. Onboard radio equipment 11 receiving control commands is designed to receive, detect, amplify and decrypt control command signals. To increase noise immunity of the radio channel and to expand the tactical capabilities of the complex, the on-board radio equipment can operate on two codes and five litre frequencies. The codes are switched automatically at the moment of missile launch. Literary frequencies are switched with a mechanical switch.
The 9 command gyroscopic spreader is designed to coordinate the missile's coordinate systems and command control. Amplifier 13 of the drive is designed to amplify and correct command signals. Drive 27 is designed to convert electrical signals of commands in the angles of rotation of the rocket rudder. As a working body for the steering machine is used hot gas gunpowder battery 31 pressure. The ignition of the PAD powder charge is performed by an electric ignition device.
Emitter 25 is designed to create, form and transmit from the board of light modulated signal to ground (tank) equipment. Block 12 of electronics is designed to create a modulated light flux of the transmitter 25. Battery 14 is a source of power supply to the on-board equipment of the missile. The battery enters the operating mode at the moment of firing.
Switching device 8 is designed for interblock mounting and layout of signals coming from BAU and GRK through the channels of course and pitch. Throwing device 21 is designed to give the missile an initial speed and transfer electrical impulses from the tank equipment to the missile. It consists of the cartridge case 20 with the lid 24, the bouncing charge 17, the ignition device 23 and the galvanic bushing 19. The galvanic bushing has contact pins under the sockets of the telecommunications plug of the equipment compartment.
When fired, the missile moves along the barrel channel due to the pressure of the gunpowder gases of the bouncing charge of the throwing device. The obtained muzzle velocity of the rocket is maintained in flight by the engine 4. When meeting the target piezo generator 1 explosive device generates an electrical impulse that triggers a detonating device VU, which causes a detonation of the charge of the warhead of the missile.
FUSION OF ROCKET ELEMENTS DURING LOADING, LAUNCHING AND FLIGHT
Charging a rocket
The guided missiles in the tank ammo are placed in its mechanised bowl. The choice of the type of firing (by missile or by the standard projectile) is made by the ballistic switch, and the charging - by pressing the MZ button located on the front panel of the 1G42-1 sight.
1-head compartment; 2-lower half-track; 3-tail compartment; 4-throwing device; 5-upper half-track; 6-klotz
When the guided missile is fired after the MZ button has been pressed, the conveyor of the tank's charging mechanism is rotated and the tray with the guided missile compartments located outside the charging line is set. The tray is fed to the charging line, opens and releases the missile compartments. The flip-flop mechanism signals progressive motion to the tail compartment of the missile. After the tail compartment is moved forward, the compartments are docked with a spacing spring ring, a stop located on the head compartment, falls out and releases the docked missile, which continues the translational motion in the gun barrel. In the process of sending the missile throwing device 4 is resting on the shell shoulder in the breech and stops.
The missile continues to move in the barrel by inertia until the obturizing belt is crimped on the entry cone of the cannon chamber. The afterburner in all cases guarantees the delivery of the missile and the crimping of the obturizing belt on the entry cone of the cannon chamber.
The electrical connection between the missile and the contacts on the cartridge case is made by wires that are unwound as the missile is removed from the cartridge case. When the cartridge case comes to the breech cut, it squeezes the legs of the extractor with its burt and the bolt closes. The contact on the bolt is combined with the contact on the cartridge case, which provides electrical connection between the missile and the tank's launcher.
The missile is ready to be launched.
The rocket is launched by pressing the gun button of the ground equipment sighting panel. At pressing the Gun button electric impulses are fed to pyrozaparnye circuits of the rocket through the contact of the wedge gate of the gun and the communication unit of the throwing device with the equipment compartment. Positive impulses of 27V voltage during 1.1 s are fed through the breakaway connector contacts to the electromagnet of the command gyroscopic layout (GRK), to the ignitors of the battery, GRK rotor, afterburner and heater to ensure their output to the operating mode at the moment of firing.
If necessary, the codes are switched over the radio channel by burning the jumper installed in the onboard radio equipment receiving control commands. For this purpose, a -27 V voltage pulse with a duration of 0.6 s is supplied to the UAS immediately after positive impulses through the same contacts of the breakaway connector.
In 1.8 s after the impulse is applied to the rotor ignition of the hydraulic system, the impulse is applied to trigger the galvanic bushing of the throwing device. A shot is fired.
At movement of the rocket on the channel of a trunk under the action of axial overloads the inertial moderator operates and delivers voltage -28,5 V from the battery 9B145M on ignition of pyrotechnic devices: the pusher for reset of the pallet 9X242, mechanisms of opening of wings EVP-28 and PAD-9X241. Circuit of the transmitter at this time is disconnected from -28.5 V battery by the switch button, which is pressed by the steering wheel folded under the pallet. Under the action of inertial forces in the channel of the barrel is triggered inertial igniter engine 9X516 and begins to ignite the VU combat unit.
After the missile departs from the barrel and the muzzle gas period is over, the starting overloads are no longer effective. The wings are opened and the pallet is reset, opening the feedback channel emitter, the on-board radio antenna and releasing the folded rudders, the opening of which is carried out by springs. When the rudders are opened, the switch button is released and the switch provides -28.5 V voltage to the transmitter circuit. With the wing mismatch angle set, the rocket starts rotating around its longitudinal axis and within 0.5 seconds picks up the calculated speed.
The battery gives out operating voltages to power the rocket equipment, and the powder pressure accumulator gives out gas for the drive.
At a distance of 4-100 m from the muzzle cut of the barrel provides ignition of the fuse device (FU).
In the control area before the meeting with the target coordinator on the tank perceives the modulated radiation of the transmitter and gives signals proportional to the deviation of the missile from the line of sight of the target to the ground command equipment. The ground equipment generates signals necessary to return the missile to the line of sight. These signals are transmitted in encrypted form to the missile via a radio line and received by the missile's antenna.
In the on-board radio equipment, the commands are decoded and come in the form of DC voltages to the switchgear controlled by the GRK, which spreads commands through the control channels for each specific time point. The commands through UP-2 are received by the steering machines. Helmsmen turn the rocket rudders to angles proportional to the control commands. The missile is moving on the line of sight of the target.
Mark (vizier) of the sight held at the target by the operator during the flight of the rocket to the target.
When the missile meets the target in the piezo generator VU combat unit generates an electrical pulse, which is transmitted to the bottom of the VU. It triggers a detonator at the bottom of the VU and causes a detonation of the warhead's VU charge. Under the influence of the explosive products of the explosive charge, the warhead's funnel is crimped and a cumulative jet is formed, which hits the target.