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Ballistic missile submarines UGM-96A Trident-1 C-4

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    Basing

    :

    Submarine

    management system:

    management software

    Warhead:

    spetsboepripasov

    Application:

    Strategic

    Country:

    U.S.

    Range:

    7400 km.

    year development:

    1979

    ballistic missile submarines ugm-96a trident-1 c-4 The second half of the 70s begins the transformation of the American political leadership views on the prospects of nuclear war. Given the opinion of the majority of scholars, even disastrous for U.S. retaliatory Soviet nuclear attack, it has decided to accept the theory of a limited nuclear war for one theater, specifically European. For its implementation were needed new nuclear weapons. The administration of President Jimmy Carter has allocated funds for the development and production of high strategic sea-based systems "Trident".

    The project is being provided in two stages. At first it was planned to re-12 class SSBNs "J. Madison "missiles" Trident C4 ", as well as to build and put into operation 8 SSBN new generation of" Ohio "with the same 24 missiles. In the second stage was supposed to build another 14 SSBNs and equip all boats of this project new SLBM "Trident-D5" with higher performance characteristics.

    Generalnyypodryadchik - company "Lockheed Missiles and Space Company". The U.S. Navy adopted in 1979.

    Composition

    ballistic missile submarines ugm-96a trident-1 c-4 Launch UGM-96A" Trident-1 "is based on a three-stage scheme. In this third stage is located in the central opening of the instrument compartment and the head. Solid rocket motor (SRM) of all three stages "Trident-1" are made of materials with improved characteristics (an aramid fiber, Kevlar-49, as a binder epoxy resin used), and swinging the nozzle have a lightweight construction. Kevlar 49 has a higher specific strength and modulus of elasticity as compared with glass fiber. Selection aramid fiber gave weight gains, and also an increase of the firing range. Engines are loaded with high-energy solid fuel - nitrolan having a density of 1.84 g/cm3 and a specific impulse of 271 kg-s/kg. As the plasticizer used polyurethane rubber.

    The rocket

    "Trident-1" at each stage there is one rocking nozzle ensures pitch control and yaw. The nozzle is made of composite materials (based on graphite) having a lower weight and greater resistance to erosion. Thrust vector control (UHT) at the boost phase in pitch and yaw deviation carried out by the nozzles, and the management of roll on the job site of the main engines are not made. Accumulating during the work RDTT deflection compensated roll during operation propulsion head. Rotation angles UHT nozzles are small and do not exceed 6 - 7 °. Maximum angle of rotation of the nozzle is determined based on the magnitude of the possible random deviations caused by underwater launch and steer the rocket. The angle of rotation of the nozzle in the separation stages (correction of the trajectory) is typically 2-3 °, and during the rest of the flight - 0,5 °. The first and second stage of the rocket has the same structure UHT system, and the third stage is much smaller. They consist of three main elements: a powder pressure accumulator, which provides gas (1200 ° C) hydraulic unit, a turbine, which drives a centrifugal pump and a hydraulic actuator with pipelines. The operating speed of the turbine and rigidly associated centrifugal pump 100-130 thousand rev / min. UHT missile system "Trident-1" as opposed to "Poseidon-NW" has no reduction gear connecting the turbine to the pump and reducing the rotational speed nacoca (up to 6000 rev / min). This resulted in a decrease of their mass and increase reliability. In addition, the system UHT steel hydraulic lines that were used on the rocket "Poseidon-NW", replaced by Teflon. Hydraulic fluid in the centrifugal pump has a working temperature of 200-260 ° C. SRBs all levels SLBM "Trident-1" work to complete fuel burn.

    Application lighter materials in buildings SRBs, nozzles and UHT device elements, and the use of rocket fuel with high specific impulse, modernization thrust vector control device and the introduction of the third stage allowed to increase the firing range missiles "Trident-1" in comparison with "Poseidon-NW" for about 2,300 km.

    guidance system SLBM "Trident-1" missile flight controls both at the stage of its main engines, and at the stage of breeding warheads. The main elements of the system are navedeniya gyrostabilized platform that hosts the gyro and astrodatchik and onboard computer that generates control signals. To ensure normal operation of the guidance system it uses subsystem thermostatic control, which includes temperature sensors and heaters inertial devices, as well as water cooling. In SLBM "Trident-1" instrument compartment is located on the third stage of the rocket. It housed equipment and devices inertial guidance system with celestial. Inertial navigation devices missiles have errors accumulate in the firing range of 1480 meters per hour of flight. To reduce it in SLBM "Trident-1" along with the improvement of the mechanical components of inertial devices, in particular the use of air bearings for gyros (thus avoiding errors due to heat, wear, thermal effect of the rotating bearing contact with the surface), introduced celestial. It is produced by refining space rocket in space under the supervision of one or two stars that are close to the zenith in the target area. Correction for distance measurements are used elevation of the star relative to the local vertical at the start, for azimuth correction - the results of measurements of the horizontal component. To implement astronavigatsionnyh measurements missiles "Trident-1" are equipped with an optical telescope and the star sensor on the vidicon, which are integral with the complex inertial devices.

    Application for SLBM "Trident-1" new achievements in the field of microelectronics has reduced the weight of the unit of electronic equipment in the system of guidance and control sing by 50% compared to the same block on the rocket "Poseidon-NW." In particular, the rate of integration of electronic equipment for rockets "Polaris-AZ" conditional elements was 0.25 per 1 cm3 for "Poseidon-NW" - 1 for "Trident-1" - 30 (by the use of thin-film hybrid circuits).

    warhead missiles "Trident-1" consists of boevogo compartment system (stage) breeding warheads and guidance subsystem obtekagelya head with needle nose wind. Fighting compartment carries eight warheads W-76 , arranged in a circle. Power of each of about 100 kt. Breeding system compensates for errors warheads launch warhead to the target and produces a correction maneuver when targeting warheads. It includes a propulsion system consisting of two solid-propellant gas generators and small nozzles subsystem control valves, through which at a dilution of warheads carried the head of the speed control, as well as its orientation and stabilization. Performs the role of the gas generator propellant pressure accumulator (operating temperature to 1650 ° C, the specific impulse of 236 kg-s/kg, high pressure 33 kg-s/sm2 low pressure kg-s/sm2 12). Earlier breeding system SLBM warheads "Poseidon-NW" working gas temperature was 450 ° C below, and specific impulse - 15% less.

    Gas flows through the inlet duct into four control nozzles supply a total of 16 nozzles (chetype front, four rear eight and stabilization in roll). Weight system rdzvedeniya warheads 295 kg, 193 kg of mass consumption, the maximum time after the separation of the third stage of 7 min.

    nose fairing SLBM "Trident -1" made of special spruce veneer, and his bow - phenolic fiberglass. In the foreign press noted that a special spruce veneer resulted in significantly better characteristics at the head of the output from the atmosphere than the other tested materials. At the same time with the release of the dense layers of the atmosphere, charring only the outer layer of the fairing, and the remaining layers provide good protection instrument compartment and elements warhead. Reset (and away from the trajectory of the missile) fairing made at the work site of the second stage engine using solid fuel engines.

    bow aerodynamic needle used in rockets "Trident" in order to reduce drag and increase the firing range with the existing form of their nose cones. On SLBM "Trident-1" Wind needle recessed into the fairing, and its six parts telescopically nominated under the influence of powder pressure accumulator for 100 ms at a height of 600 m needle reduces the maximum force frontal drag on the boost phase with 18 thousand 9 thousand kgs. Application of this scheme leads to increase in the firing range for SLBM "Trident-1" 550 km "Poseidon-NW" 325 km compared with the rocket "Polaris-AZ", which has a similar shape fairing.

    SLBM launchers are the most important part of the launch complex and are designed for storage, maintenance and launch. The main elements of each PU are mine launcher glass hydropnevmosystems, diaphragm valves, plug, steam supply subsystem, the subsystem control and verification of all nodes launcher.

    ballistic missile submarines ugm-96a trident-1 c-4

    Mine is a steel structure, a cylindrical shape. She fixedly housing SSBN. Mine the top lid is closed with a hydraulic drive (ravnoprochnoj with rugged SSBN), which is located under the membrane to prevent ingress of seawater into the mine when the lid is opened. Installed inside the mine launcher steel glass. The annular gap between the cup walls and the shaft is filled elastomeric polymer. In the gap between the inner surface of the beaker and placed missile obtyuriruyuschie cushioning and belt. In SLBM launch glass mounted on a support ring, which ensures its azimuthal exhibition. In the lower part of the rocket has four depreciation and device four centering cylinder in the gap between the walls of the shaft and is part of the starting glass units (shock absorbers), intended for damping shock loads on the rocket.

    Starting

    glass "Trident-1" is mounted to a robust housing SSBN 20-30 shoes, based on hydraulic shock absorbers, it is covered on top membrane. Rigid shell membrane thickness of 6.3 mm has a dome shape (of diameter 2.02 m and height 0.71 m). It is made from a phenolic resin reinforced asbestos. To the inner surface of the membrane is attached a low density polyurethane foam with open cells and cellular material, made in shape of a rocket nose. This provides protection from SLBMs power and thermal load at the opening of the membrane using explosive shaped charges are installed on the inner surface of the shell. When opening the shell breaks into several parts: the central and side.

    For access to systems and missile sites for the purpose of inspection and maintenance of each mine has a cap and hatches located on different levels. Silos SLBM "Trident-1" is equipped with a new type of plug connector for connection of devices with missile fire control system onboard. It automatically disconnects when the missile launch.

    for firing rockets "Trident-1" of mine used gunpowder pressure accumulator. It generates gases pass through the chamber with water and partially cooled. The resultant low-temperature steam is supplied into the lower cup portion of the trigger and pushes the missile. Daylight steam and gas, according to American specialists, allowed to increase mass shoots missiles without an increase in the emission system. In silo SLBM "Trident-1" embedded system overpressure before missile launch, cooling chamber and mine closure device of this type. Sizes start at glass class SSBNs "Ohio" by 15 percent. in diameter and 30 percent. height greater than that of the type of boat "Lafayette". This is done by taking into account the possibilities for accommodation in the future for the first eight ships of the "Ohio" SLBM "Trident-2".

    missile fire control system is designed for the data input and firing them in a rocket-launch of the test and control equipment ready for launch. On class SSBNs "Lafayette" installed control missile firing Mk88 Mod. 2, for "Ohio" has developed a new system Mk98 Mod. A. Unlike similar systems missile complex "Polaris" they allow retargeting missiles in mines patrolling SSBN, the newly designated purpose.

    missile fire control system includes positions Launch Control, navigation and control subsystem ejection missiles from the mine. It is based on a computer. Missile firing control post is located in the central post SSBN. Necessary data characterizing all the missiles and the training of auxiliary subsystems for shooting are displayed on its special remote. Such control on class SSBNs "Lafayette" series includes 16 indicator lights green, showing the stages of preparation and readiness for flight. In the center of the bottom of the console there is a hole for the trigger key. Navigation Station provides data describing the location of the media and elements of its motion, as well as the magnetic and gravitational fields of the Earth to area SSBN. They, as well as information from the subsystem control and ejection missiles, introduced in ship's computers.

    ballistic missile submarines ugm-96a trident-1 c-4

    functioning missile system.

    On receipt of the signal-order on missile launching boats commander announces combat anxiety. After authentication, the orders of the commander gives the command to bring the submarine technical readiness ISy, which is the highest degree of readiness. At this command specifies the coordinates of the ship, the speed is reduced to values, ensuring the missile launch, boat podvsplyvaet to a depth of about 30 m On readiness navigation fasting and fasting control subsystem and release missile SSBN commander of mines starting key inserts into the hole remote control shooting , and switches. By this action, he gives the command to the missile bay boats for immediate prelaunch preparation missile system. Before starting the missile silo pressure equalized with outboard, then opens a durable cover mine. Access outboard water only after blocks located beneath a comparatively thin membrane.

    Direct launch next commander warhead weapons (rocket torpedo) with the help of a trigger mechanism with a handle of red color (for training launches - black) that connects to the computer using a special cable. Then turned powder pressure accumulator. It generates gases pass through the chamber with water and partially cooled. The resultant low-temperature steam is supplied into the lower cup portion of the trigger and pushes the shaft of the missile. When driving up the rocket breaks membrane and seawater flows freely into the mine. After the rocket cover mine closes automatically, and located in a mine outside water drained into a special tank replacement inside the pressure hull. SSBN missile motion in the starting glass is exposed to significant reactive force, and after its exit from the mine pressure incoming seawater. Tie with special machines that control the gyroscopic stabilizing devices and pumping ballast water, keeps the boat from a depth of failure.

    After

    uncontrolled movement in the water rocket reaches the surface. First-stage engine SLBM included a height of 10-30 m above sea level acceleration sensor signal. Together with the missile to the surface pieces are ejected starting glass seal.

    Then

    rocket rises vertically and reaches a certain speed begins to work a given flight program. At the end of the first stage engine at an altitude of about 20 km takes her department and the inclusion of the second-stage, and the body of the first stage is shot. Similarly is switched third-stage engine SLBM "Trident-1." When moving missiles at the boost phase of its flight control at the expense of engine nozzle deflection stages. After separation of the third stage begins breeding stage warheads. Head section with instrument compartment continues to fly on a ballistic trajectory. Trajectory correction made the head of the engine, targeting and shooting warheads.

    At the head of

    MIRV type used so-called "principle of the bus": MS, the correction of its location, is aimed at the first target and detonates the warhead, which flies along a ballistic trajectory to the target, then MS ("bus") the correction of its location propulsion system breeding warheads aimed at the second goal and shoots following warhead. Such a procedure is repeated for each warhead. If you want to hit a single target, the warhead zakladyvaetsya program that allows you to strike spacing in time (MS-type MRI after the second stage engine targeting performed simultaneous shooting of all warheads).

    After 15-40 minutes after the missile launch warheads reach of targets. The flight time depends on the removal area SSBN fire position on the purpose and trajectory of a missile.

    PERFORMANCE

    Maximum range, km

    7400

    Weapon Accuracy (CWE), m

    300

    amount of stages, pcs

    3

    The line speed

    Tandem

    guidance system

    Inertial

    with celestial

    starting weight, t

    32

    Diameter, m

    1,88

    Length, m

    10,36

    length of the first stage, m

    4,16

    length of the second stage, m

    3,37

    length of the third stage, m

    2,83

    separation process steps

    Hot

    The geometry of the head part

    alive with the spherical blunt needle aerodynamic +

    blunting the head of the radius, m

    0,266

    A method of separating

    warhead

    repulsion

    payload weight, kg

    1280

    full weight of the first stage, t

    32

    full weight of the second stage, t

    11,85

    full weight of the third stage, t

    3,2

    Charge weight with bookings first stage, kg

    18820

    Charge weight with Reservations second stage, kg

    7260

    Charge weight with bookings third stage, kg

    1810

    ratio recessed nozzle first stage

    0,5

    ratio recessed second stage nozzle

    0,3

    ratio drowning third stage nozzle

    0,3

    Home thrust first stage

    2,313

    Home thrust second stage

    3,06

    Home thrust

    third stage

    3,38

    Nominal thrust solid propellant second stage, tf

    54,4

    Fuel weight RDTT second stage, t

    7,26

    Nominal thrust solid propellant third stage, tf

    18,1

    Weight

    fuel third stage solid propellant, t

    1,81

    Brand Fuel

    Nitrolan

    fuel density, kg/m3

    1770

    Specific impulse

    Earth

    2880





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