Basing :
Armoured, Mine PU
management system:
management software
Warhead:
spetsboepripasov
Application:
Strategic
Country:
Russia
Range:
11000 km.
year development:
1967
Developing mobile missile system equipped with intercontinental ballistic missile (ICBM), began in the" Southern "(Dnepropetrovsk) in 1964. The first variant of RS-20 (8K99) represented the three-stage solid-fuel missile. During the next stage of design work to reduce the weight of the rocket launch was decided to develop a two-step RT-20P with the first stage, equipped with a solid-propellant rocket motor, and a second stage with LRE. This decision was taken due to the fact that the rocket was placed on a movable track propelled installation based on the T-10M (object 821), which could not be transported rocket weighing more than 30t.
Officially development of the complex was given the USSR CM Resolution of 24 August 1965. In 1966 he was made preliminary design rolling complex 15P699.
Developer propelled launcher - LACA (chief designer BG drums) solid first-stage engine was developed in KBM (chief designer Barber M. Yu), a developer of charge - SRI-130 (chief designer A . N. Kozlov). Parallel to the main embodiment of the missiles in LACA worked out several options based ICBM silo RT-20P.
flight tests began in October 1967 in Plesetsk (Technical Lead Test VS Budnik). Was carried out 12 test launches, followed in October 1969 issued a decree for the winding up of the USSR. Cause cessation of work was operational complexity rolling complex with liquid rocket engine in the second stage as well as the absence of the state program for its placement in the country.
complex was demonstrated for the first time during a military parade in Moscow on November 7 19665 years.
complex was designated NATO SS-X-15 "Scrooge" .
Composition
The complex 15P699 included:
six self-propelled PU CM-SP21 missile RT-20P (8K99);
Machine combat control 15N809;
two car preparation position 15N1034;
two diesel power 15P694;
communication node "Relief".
8K99 rocket intended to be used in two ways: with a light (see Figure 1) and heavy (see Figure 2) warheads. Warheads - monobloc, fusion. "Light" warhead had a body made in the form of a set of three truncated cones with spherical blunting. To reduce the drag on the "easy" the head of the conical fairing installed resettable while the engine of the second stage, when the rocket reaches the rarefied atmosphere. The head part was attached to the upper docking frames instrument compartment with three explosive bolts. To separate the head from the second stage of the rocket used three engine reverse thrust.
Instrument compartment in the case of "light" parts of the head has a frustoconical shape, the "heavy" head part - cylindrical shape. In the instrument compartment placed the bulk of the missile control system devices. Missile control system 8K99 - inertial, autonomous gyro with air suspension (SU weight - 250 kg) and high-speed digital computer. Communication with the onboard equipment launcher via the two blocks connectors, one of which is located on the side surface of the housing of the instrument compartment other - on the container. Before leaving missile from the container using a discontinuous bolts and springs are separated repelling block connectors container. After the rocket from the container similarly split terminal block missiles. The remaining part of the block on the missile lid is closed. Instrument compartment bolted to the upper end of the fuel compartment bulkhead.
Fuel tank compartment is separated by an intermediate bottom into two cavities: the upper and lower oxidant for fuel. As the oxidizing agent used nitrogen tetroxide in a fuel - unsymmetrical dimethylhydrazine (UDMH) to the lower end of the fuel compartment frames using the frame rod attached 15D12 liquid rocket engine of the second stage. Management of the second stage for pitch and yaw done blowing turbine gas in the supercritical part of the engine nozzle. For roll control are two pairs tangentsilno established control nozzles that are also turbogas.
separation steps "hot", ie, triggering explosive bolts occurs after launching the second stage propulsion system. The shell of the transfer compartment are windows providing gas output at the initial stage of the separation process. Collision of transitional housing to the engine compartment in the separation of the second stage, specifically excluded by constructive measures.
Transitional compartment with bolts connected to the first stage solid engine. On the front bottom of the engine of the first stage propellant rocket engine is the final stage, triggered after burning fuel in the engine of the first stage and terminates after breaking the bonds between the stages of the rocket. Final stage engine nozzle goes into the cavity of the main engine.
to the lower end of the frames first-stage engine is mounted tail section that protects the engine nozzle and the steering gear from the effects of air flow and gas jets. Executive bodies of the control system of the first stage are four rotary nozzle of the solid propellant. Buildings along both rocket stages outside paved and secured by brackets onboard cable network, on the opposite side along the body of the second stage pipelines laid fluid system.
Fastening pyatyam missile to the support container made discontinuous by the eight bolts mounted on the lower end of the frames of the first stage engine. Radial movement of the container and prevent the rocket four support rings.
The launch is made from a vertical container. Launch canister - with thermostat. Carried out before the start azimuth aiming missiles, which consists in combining the X-axis gyro-stabilized platform with the plane of fire. Rough alignment of the X-axis and the plane of fire (± 10 °) is performed by rotating the starting unit in the current - turning the gyro-stabilized platform. Enter the flight mission in SU - remote.
on the command "Start" begin operations prior to the launch of a rocket: check onboard systems, switching missiles on board meals, etc. After about 3 min, after the command "Start" is undermined by an elongated hollow charge covers the WPK, the engine runs powder slip cover and separates the latter from the container. After separation of the terminal box of the container and rupture of bolts rocket propellant starts to TPK pressure accumulator is disposed in the container and when the pressure in the volume podraketnom 6h105N/m2 rocket starts moving. Shape of powder charge pressure accumulator is chosen so that said pressure podraketnom volume during movement of a rocket container is maintained constant. At the time of release of the WPK rocket reaches a speed of 30m / s. At a height of 10-20m above the cut container will start up the first stage solid propellant. Simultaneously, the separation of the support rings and the separation of the terminal box of the rocket. First-stage engine runs about 58c. When the pressure in the chamber to 5h105N/m2 gunpowder engine starts the final stage, which runs until complete combustion of fuel. Through 11c after starting the final stage the engine is started the second stage, when the output mode is 90% of rated thrust rocket stage separation occurs. In the case of "light" on the head portion 56c of the second-stage resets fairing. When the desired combination of parameters of the rocket (speed, coordinates, etc.) providing a predetermined range, the control system commands the engine shutdown. Simultaneously the head of the department.
Before leaving missiles from WPK. if necessary, be produced moyaet start abort. It is also possible accidental detonation missile in flight.
In the first stage rocket as the government uses four rotary nozzle of the solid propellant. Rotating nozzles provided with hydraulic steering machines. Gas is used to generate a powder pressure accumulator. Management of the second stage of the launch on pitch and yaw is performed by injection of gas in the supercritical part of the nozzle engines. The second stage was designed and produced in ampulizirovannom performance. Management of the second stage is carried out at an angle of heel two pairs of nozzles tangentially mounted control. To operate and control nozzles blowing gas is used, the bleed after the turbine turbopump unit propulsion second stage (turbogas). The gas supply for intake and control nozzle carried gas distributors, which are powered by electric motors.
Management missile carried by six control channels:
channel stabilization angle of heel;
stabilization side channel;
normal rate control channel;
longitudinal velocity control channel;
a range of control channel (control channel off the engine of the second stage and the head of the department);
control channel separation steps.
Each of the first four channels of control is a closed loop automatic control system that operates on the principle of eliminating the mismatch between the current value of the controlled parameter and its value programmatically. The fifth and sixth channels are open to the scheme, ie, when the necessary conditions are served on the team division steps off the engine of the second stage and the separation of the head portion.
In rocket implemented so-called "hot" separation steps, in which the first stage separation occurs after the engine of the second stage. At the end of the first stage engine rocket climbs about 27km. Produce separation stages at such a low altitude is unprofitable, as due to the large aerodynamic forces acting on the rocket, would require considerable efforts for breeding steps to a safe distance. In connection with this step are separated after the missile altitude ~ 40 km. During recovery up to this altitude handling provided by the auxiliary rocket engine - powder rocket engine thrust the final stage, which starts after burning fuel in the engine of the first stage.
Branch head part is made at the end of the active portion of the trajectory during the aftereffect of engine thrust second stage. First triggered three discontinuous bolt with which the head portion is attached to the instrument compartment, and then braked rocket of the second stage due to the gas flow through the oxidizer tank pressurization protivosopla two located on the front bottom of the tank. Protivosopla communicate with the atmosphere through two hatches in the body of the instrument compartment. Opening occurs as a result of nozzle actuation elongated detonating charges actuated electric detonators. Manhole covers instrument compartment bouncer plugs emitted from the nozzles. After opening of the nozzles is triggered pyro valve through which the gas pressurization ends in a direction perpendicular to the longitudinal axis of the missile. As a result of this second stage, performing the role of decoy, led away from the trajectory of the head portion.
PERFORMANCE
|
General characteristics BR
|
|
Parameter
|
With severe MS
|
With easy MS
|
|
firing range, km
|
7000-8000
|
11000
|
|
Weapon Accuracy (CWE), m
|
2000-4000
|
|
Power charge warhead, Mt
|
1.5
|
0.55
|
|
MS Weight, kg
|
1410
|
545
|
|
Missile length
|
17.8
|
17.48
|
|
length without rocket warhead, m
|
16.2
|
|
Diameter, m
|
1.6
|
|
starting weight, t
|
30-30.2
|
|
first stage
|
|
Length, m
|
6.12
|
|
length with the transfer compartment, m
|
9.8
|
|
Diameter, m
|
1.8
|
|
solid propellant engine RD-15D15
|
|
Link on earth, n
|
60
|
|
fuel weight, t
|
16.7
|
|
WEIGHT, t
|
2.45
|
|
second stage 8K94
|
|
Length, m
|
8.4
|
|
Diameter, m
|
1.8
|
|
Engine LRE 15D12
|
|
Vacuum thrust, n
|
14-15
|
|
fuel weight, t
|
8.9
|
|
head part
|
|
Length (with fairing), m
|
2.435
|
|
diameter at the bottom, m
|
1.06
|
|
launcher SM-SP21
|
|
Length (with TPC), m
|
20
|
|
Height, m
|
3.15
|
|
Width, m
|
4.4
|
|
Weight, t
|
62.2
|
BACK NEXT 
TOP 
