.

Ballistic Missile Redstone

BACK NEXT
    Basing

    :

    Surface PU

    management system:

    management software

    Warhead:

    spetsboepripasov, high-explosive

    Application:

    Land-Plot

    Country:

    U.S.

    Range:

    800 km.

    year development:

    1958

    ballistic missile redstone In 1950, Wernher von Braun and his team of 130 engineers in Seattle have begun work to improve the design of a rocket A-4 . Rocket Center settled in Fort Bliss at Arsenal "Redstone". In 1951, the U.S. Army Command ordered missile suitable for use in military units. The rocket was supposed to be mobile, to carry nuclear warheads and have a range of 200 miles. After two years of hard work was presented at the missile tests.

    First launch, dubbed "Redstone", held on 20 August 1953 with a sense Canaveral. After a series of missile launches was transferred to military trials. For this purpose, formed a special military unit (40th Field Artillery Missile Group). In May 1958 it was decided to take a rocket to the U.S. Army.

    Rockets "Redstone" were installed on the launch pad in Germany in 1958. Reliability missiles characterized the 35th successive starts of 38 and performed for five and a half years. This number includes three combat and run conducted troops. High reliability missiles allowed to use it as a booster in the early stages of space exploration. In the summer of 1958, two missiles "Redstone" abandoned nuclear warhead, which were blown up at an altitude of 80 km above the Pacific Ocean near Johnston Island.

    B Rocket currently removed from service and not used.

    Composition

    ballistic missile redstone Launch "Redstone" consists of:

    brain compartment comprising a warhead, and a control system;

    engine compartment consisting of a tank of fuel, oxidizer tank and liquid rocket engine.

    head compartment

    head section of the missile separated from the propulsion system consists of two main parts: a combat unit and control system.

    Warhead: In rocket "Redstone" may be used as a regular and nuclear warhead. Warhead includes: an annular plug stringers conical part of the body, reverse nose cone, nose cone mount ring, hatches for access to the warhead and the control system, as well as the hatch hinge and attaching lifting hoists. Warhead together with the control system is attached to the missile unit using mnogoshpilechnogo connection. The spacer ring on the border compartments has eight bolts. The head part is separated from the body in flight after engine stops running hydraulic separator. Upon entering the Earth's atmosphere its flight operated wedge crosswise arranged rudders placed on the back of the head of the body skirt.

    management system:

    In

    rocket used completely autonomous inertial control system. Once the missile is launched from a platform, it should be the goal along a predetermined path, regardless of external influences. Target data fed into the device software which then provides the necessary information of the various elements. The control system is equipped with an air suspension gyroscopes, which provide a constant orientation in space instrumentation platform. Executive bodies of the control system are the gas-jet and aerodynamic control surfaces.

    ballistic missile redstone

    Engine compartment

    This bay is a large part of the rocket. Otsek comprises the oxidizer tank, the fuel tank and liquid fuel rocket motor.

    tank unit: Consists of oxidizer and fuel tanks. Tank unit is mounted in such a way that the oxidizer tank is located directly over the engine. Tanks are cylindrical in shape. Fuel compartment housing made of aluminum, consists of eight cylindrical shell length from 610 to 1530mm, backed frames and one stringer, located at the longitudinal seam of the shell. Trimming and beveling shells weld made with an accuracy of 0.37 mm on a special machine. The fuel cell is divided into three subassemblies: the first consists of an upper bottom of the tank and an alcohol of two shells, the average - promezhutochnogo of bottoms and four shells and the third - the lower bottom of the liquid oxygen tanks and two shells. Shell forming subassemblies, butt welded together by argon arc welding machine running at an average speed 645mm/min. Used for welding of aluminum wire 4043. All seams are fluoroscopy. Welding circumferential weld shell whose length is 5588mm, takes 10-12 minutes to prepare and check the seam spent about three hours. Leak tests fuel compartment is carried out using ultraviolet irradiation. To do this, the water that fills the tank of fuel or okislstelya added flourestsiruyuschaya fluid and flow is detected by irradiation with ultraviolet lamp seams. Final check size compartments are held in camera optical control where straightness is checked shells and mounting holes. After that tanks are washed with trichlorethylene and painted outside with white enamel. Compartments are joined by bolts and after sealing up all the holes with paper rocket body goes to the factory where the equipment is installed.

    ballistic missile redstone

    Engine

    In

    rakete "Redstone" is used a single-chamber liquid-propellant rocket engine "Rokitdayn A-7." This engine was developed by the department "Rokitdayn" firm "North American" and has been in production since 1952. This engine operates on a two-component fuel rod 34 and produces that consists of a combustion chamber, a jet nozzle, of the turbopump unit and the gas generator. B is used as a fuel ethanol, and as oxidizer - lox.

    combustion chamber - is fixedly mounted and has an igniter for the initial ignition of the fuel. At end of the chamber is located injector head. The temperature in the combustion chamber 2670 degrees Centigrade. Main amount of heat entering the wall from the hot gases, fuel removed. Luggage performed for this double-walled and cooling components of the nozzle enters the manifold from the nozzles is directed in countercurrent, removing the necessary amount of heat from the inner chamber wall.

    Jet nozzle - cooled fuel. Diameter of the outlet nozzle exit 840 mm. Around the nozzle there are four actuating mechanism for rotating the control surfaces of the graphite, which is produced using a gas jet deflection.

    turbopump unit - consists of impulse turbine capacity of 780 liters. sec. running on hydrogen peroxide decomposition products, and the two centrifugal pumps. The turbine and pump are mounted on a common shaft and mounted in a single housing: two input flange for fuel components, two - for exit of the same components under high pressure, the entrance of the hot gas entering the turbine blades, and a flange for connecting the exhaust gas pipe. For power supply turbine provided hydrogen peroxide, the decomposition of which is allocated sufficient heat. Turbine pumps reports required number of revolutions.

    gasifier - is lightweight and works on concentrated hydrogen peroxide. Hydrogen peroxide - an unstable compound and is easily decomposed in the presence of certain substances (do not enter in this reaction) to water vapor and oxygen gas. This mixture is called vapor gas. Perico hydrogen and a catalyst under pressure fed to the gasifier, where the decay reaction. The thus obtained gas-vapor enters the turbine blades, spinning them. Giving them some of the energy, he is thrown out. The exhaust is made through a special tube and exhaust gases create a little extra traction.

    Service and prelaunch rocket: For compressed air required when preparing to launch rockets, used compressor 350atm. The compressor is mounted on a truck and driven by a light engine with air cooling. Compressor is designed for charging air battery, from which clean and dry air flows through the gears and valve box launch pad in ball balloons rocket. This air is used to test rocket-launch for its pneumatic system and tank pressurization. As the ground source power during prelaunch testing and launch rockets used diesel generator providing AC 60 Hz. The resulting electricity is used to power the control system of air valves, as well as to charge onboard batteries. Missile system "Redstone" settings are applied to the production of liquid oxygen in place in the field. In 1954 he initiated the development of plants with capacity 20-25t liquid oxygen per day. Such a device can operate at a temperature of from -32 to 52 degrees. The design capacity of the plant - 20t pure (99.5%) of liquid oxygen per day at normal atmospheric pressure. The resulting clear liquid oxygen is pumped and discharged into the reserve tanks or refueling servers with a capacity of 9 t refill tank missiles manufactured directly from the bowser. For storing oxygen exists 35-ton container Vacuum insulation.

    rocket transported in nine trucks. Most truck-lift. With its help, initially to the launch pad. Fire calculation using jacks, aligns the table in the horizontal plane with the required accuracy. At the same time, unloaded and transported separately joined two sections, and the software used to configure the device management system. Towards the bottom edge of the cruciform stabilizers projectile attached square frame. After installing missiles in vertical position closes the electrical and pneumatic connections between the launch pad and the projectile. Refuel rockets alcohol, liquid oxygen and concentrated hydrogen peroxide. After refueling, the launch pad is leveled. Top ring launch pad rotates in azimuth so that stabilized platform control system precisely oriented in the direction of the target. 5 minutes before the start of the oxygen line is disconnected.

    rocket launch: The launch carried the commander of the platoon firing, which closes the starting circuit. Air from balonov ball begins to flow in a rocket system. Ignites the initial powder charge. Air enters the oxidizer and fuel tanks, creating boost pressure. Due to the displacement distance of the hydrogen peroxide vessel in which it resides. Perique fed to the gasifier, where its expansion takes place. Steam and gas turbine and drives the fuel injection starts in a combustion chamber.

    PERFORMANCE

    Length, m

    19.3

    Diameter, m

    1.83

    head cover length, m

    8.84

    The diameter of the head cover

    m

    1.77

    step length, m

    10.4

    engine length, m

    1.78

    motor diameter, m

    1.83

    up weight

    24000

    Mass consumption, kg

    18000

    Weight, kg

    660

    Warhead weight, kg

    1360

    weight control devices, kg

    80

    Maximum range

    c light warhead km

    800

    Maximum range

    c heavy warhead km

    320

    flight speed, m / c

    2020

    engine run time, with

    140

    Fuel consumption, kg / c

    136

    specific impulse, m / s

    2360





BACK NEXT TOP

Site is a private collection of materials and is an amateur informational and educational resource. All information is obtained from public sources. The administration does not apply for authorship of the materials used. All rights belong to their owners