RT-15 / RT-2P / SS-14
SCAPEGOAT 8K96 Missile
The total length of the rocket (with tray) was 11.93 m, maximum diameter - 1.9 meters. The launch weight was 16 tons. The missile had a two-stage boosters. Each stage of the rocket consists of a one-piece solid propellant and the tail section. The interstage had a coupling section truss, allowing free exit gases from the working engine of the second stage at the "firing" separation. In the second stage of the rocket and warhead was the instrument compartment and an adapter for fixing the head portion. The SRM of the two stages wre executed in different diameters.
The nozzle block rocket engines had four split control nozzles used as actuators for missile flight controls. The nozzles consist of fixed and mobile (supersonic) parts and fittings. The nozzle design widely employed heat resistant material based on graphite, metal-ceramic, as well as molybdenum and titanium alloys. Deviation movable nozzle parts during operation of the propulsion system was by a special steering transmission, which allowed obtaining sufficient control moment at low deflection angles. The control efforts do not occur due to changes in gas flow direction, and due to occurrence of the shock wave in the supersonic stream. The nozzle blocks, and control actuators of the control system units are placed in the compartment of the tail stages having a truncated cone shape.
Missile guidance to the target is by means of an autonomous inertial gyro platform control system. Control system is based on a gyro-stabilized platform with float gyro unit and pendulum accelerometers. This manages the flight from launch to the uncontrolled flight of the warhead. The control system used electronic-mechanical computing devices range of machine control and management for flexible trajectory, consisting in the fact that the program is given by the pitch angle is not a function of time, as a function of the apparent velocity of the rocket. Most of the control system is located in the instrument compartment.
The range of the missile is controlled by a device cut-off thrust of the second stage. Opening the shut-off units made to undermine the elongated detonating charges in advance and the main team of missile control system. At the same time the new engine operating mode, there is a negative resultant thrust, which provides a braking body of a stage. To reduce the spread of the effects of switching off the engine pulse stage is carried out in two stages: first opened two nodes cutoff of four, after which the engine switches to a reduced craving, and then, with a certain time delay, - the two remaining node cutoff finally zeroed cravings. After that there is a separation of the head from spetszaryadom and continues solo flight to the target on a ballistic trajectory. The missile is equipped with the 15F1 monobloc nuclear warhead (weight 535 kg), with a yield of 600 kilotons.
The first stage of the rocket includes a one-piece solid-propellant motor and tail section with the pallet. Solid rocket engine 15D27 consists of a cylindrical steel shell diameter of 1.49 meters with a "charge" [grain] firmly fastened to the body and elliptic rear and front bottoms. Body and heads are welded, made of high-strength alloy steel. The solid fuel charge is firmly attached to the motor housing by means of adhesive applied in a protective layer. It is designed as a monoblock with a central circular channel, four long and four short slots, equally spaced on the rear side of the bottom of the circle, and an annular groove at the front end of the charge.
To remove thermal stresses during operation of the SRM charge, the front end of the body used a special cuff. The body of the propulsion system together with the bottoms constituted the combustion chamber, the inner surface of which is applied to a thermal barrier coating which protects the body against the heat of the solid propellant gases formed during the combustion of the charge. The bottoms assembly is joined with the housing by means of wedge joints.
The assembled motor is sealed. The body is welded from individual sections. Each section consists of several shells, welded in series with each other and arranged so that their longitudinal welds are offset from each other. Shells for the housing sections are made by drawing from billets produced by rolling a sheet. The ends of the shell frames conduct power to the junction of the bottoms. The front bottom has a central neck and lid fastening device and igniter assembly emergency engine shutdown. In the background there are four bottom nozzle for attaching the nozzle blocks.
Control bodies are the four split nozzles. The gap between the moving and stationary parts of the nozzle is sealed with rubber-elastic cuff. Oscillation of each nozzle is carried out in the same plane self-contained electro-hydraulic steering gears. Missile flight control in the corners of the pitch, yaw and roll provided deflection nozzles (pairs) in two mutually perpendicular planes. The power of the design of the nozzle is made of titanium alloys. The nozzle path applied parts made of erosion-resistant plastics, high-density graphite and tungsten alloy.
The engine is started by applying an electric pulse to the squib of the safety type, which triggers a pyrotechnic igniter and its products of combustion ignites the solid fuel charge. Motor runs until complete combustion of fuel - 60 seconds. Its design provides a device for emergency stop, consisting of an elongated detonating charge and an electric safety type, installed on the bottom of the front cover SRM. When deviation of the missile trajectory by a command from the control system EB activated that triggers the detonating charge mounted on the outer surface of the cover. Cumulative jet elongated detonating charge cuts the cover charge and ceases to burn due to a sharp collapse.
Tail section is a power element of the first stage. It has the shape of a truncated cone (as the diameter of the nozzle block than the diameter of the motor housing) and riveted construction, backed by a mating end frames and stringers. The tail compartment designed to accommodate the split control nozzles, and parts of the steering gear control system devices and also protects these units against heat engine operating speed and pressure when the rocket flight. The connection between the tail section with the housing SRM covered fairing. To increase the stability of the missile in the initial stage of the flight, in-flight drop four lattice stabilizer placed at the tail section of the first stage. Tail section ends attached thereto a support ring tray.
The second stage of the rocket on the assembly scheme similar to the first, and also consists of a solid rocket motor and tail section. The engine 15D28 monoblock with a charge firmly bonded to the body. The charge of solid propellant is a slotted piece with front and rear-slots and the center channel. The slots are in planes stabilization and allow assembly of traction cut-off operation after a few seconds of the main engine.
The case is of welded construction made of high alloy steel and consists of a front and bottom shell. Teh front bottom is a welded construction consisting of punched bottom elliptical shape, front bulkhead, the central neck nodes and connections thrust cutoff. The cylindrical part of the housing has a diameter of 1.1 m with a combined, two-layer. It is made of high-strength steel jacket reinforced with fiberglass filaments are wound outside. By the motor housing by means of a wedge connection docks back plate. Back plate welded structure made of stamped blanks, frames and four spherical nozzles. When assembled, the engine is sealed.
On the inside of the casing and back plate are protected from exposure to combustion products of fuel and thermal barrier coatings. The outer surface of the housing, back plate and nozzle pipes to protect against aerodynamic heating and the thermal impact of gas jets are sublimated coating.
At the bottom of the front of the engine are arranged components made of titanium alloy for thrust cutoff. These end bells are of special fiberglass to reset the combustion products into the environment. In the central neck of the bottom set igniting the engine unit.
In the back, the bottom four split control nozzles are mounted to the connector in the supersonic part. They are the thrust of the engine controls the direction. Oscillation of each nozzle is carried out in the same plane and mutually perpendicular arrangement of the swing axis is provided in the control stage rocket flight in the corners of the pitch, yaw and roll. As controls actuators applied standalone electro-hydraulic steering gears. The connector between the movable and stationary parts of the nozzle is sealed by a rubber cuff tissue. The power of the design of the nozzle is made of a titanium alloy. The nozzle gas duct erosion-resistant plastics used, and high-strength graphite pirovolfram.
Launch ["Start"] is performed by applying an electric pulse to the squib of the safety type, mounted on the front of the engine bottom. From the cutter operates pyrotechnic igniter and then ignited solid fuel charge. The engine run time - 45 seconds. The engine is switched off in two stages by successive actuation of two pairs of rods cutoffs after the preliminary and the main commands on electrodetonators that initiate detonating charges, providing separation cutoff covers. At the expiration of gases through a nozzle to create the necessary cutoff. Units for cutoff traction can be used for emergency engine shutdown.
The stage tail section has a conical shape and consists of two segments. It serves to protect the nozzle block and the steering gear. The compartment is a power element of the design stage, and takes the load from the axial compressive forces, bending moments and aerodynamic pressure. Fixing the tail section to the motor housing made explosive bolts. The connection between the tail section with SRM covered fairing. To reduce the weight of the construction of the third stage, the tail section is reset after the separation of the steps that has a positive impact on increasing the range of the missile.
Intersection compartment is designed as a lattice truss. It is made of steel. Transitional compartment still attached to the first stage. In the second stage of the connection effected by means of explosive bolts triggered at the time of the second stage engine output at full thrust. Instrument compartment cylindrical shape accommodates the main part of the control system devices. The compartment is riveted construction, power unit which consists of frames and stringers. Casing cover made of duralumin sheet, on the outer surface of which is coated with a thermal barrier coating.
The adapter serves to connect the head part with the instrument compartment. It has the shape of a truncated cone and represented riveted construction having power set (the frames and the stringers) and the covering. On the front end surface of the frame set spring pushers to ensure reliable separation of the head portion and the frangible connection bolt head portion with an adapter.
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