UGM-133 Trident II

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UGM-133A Trident II
Trident II missile image.jpg
A Trident II launch from a submerged submarine.
Type SLBM
Place of origin  United States
Service history
In service March 1990
Used by  United States Navy
 Royal Navy
Production history
Manufacturer Lockheed Martin Space Systems
Unit cost $37,320,070 (2014)[1]
Produced 1983
Specifications
Weight 130,000 lb (59,000 kg)[1]
Length 44 ft 6.6 in (13.579 m)
Diameter 6 ft 11 in (2.11 m) (1st stage)[1]
Warhead Multiple W88 or W76 thermonuclear warheads[2][3]

Engine Three solid-propellant rocket motors; first & second stage - Thiokol/Hercules solid-fueled rocket; third stage - United Technologies Corp. solid-fueled rocket[4]
Propellant Nitrate ester, Plasticized Polyethylene Glycol[5]
Operational
range
With full load 7,840 kilometres (4,230 nmi);
with reduced load approx. 7,000 mi (11,300 km) (exact is classified)[6]
Speed Approximately 18,030 mph (29,020 km/h) (Mach 24)[1](terminal phase)
Guidance
system
MK 6 stellar/inertial navigation system[1]
Steering
system
Single Movable Nozzle Actuated by a Gas Generator[5]
Accuracy 90–120 m (300–390 ft) CEP
Launch
platform
Ballistic Missile Submarine
US Navy test firing two Trident II D-5 UGM-133A missiles in the Atlantic Missile Range, on June 02 2014 (DASO 25 SSBN 736).

UGM-133A Trident II, or Trident D5 is a submarine-launched ballistic missile, built by Lockheed Martin Space Systems in Sunnyvale, California, and deployed with the US and Royal Navies. It was first deployed in March 1990,[4] and is still in service. The Trident II Strategic Weapons System is an improved Submarine Launched Ballistic Missile with greater accuracy, payload, and range than the Trident C-4, strengthening U.S. strategic deterrence. The Trident II is considered to be a durable sea-based system capable of engaging many targets. It enhances the U.S. position in strategic arms negotiation with performance and payload flexibility that can accommodate active treaty initiatives (See New START). The TRIDENT II's increased payload allows nuclear deterrence to be accomplished with fewer submarines.[7]

Trident II was designed to be more advanced than Trident I (retired in 2005[8]), and have a greater range and payload capacity. It is accurate enough to be used as a first strike weapon. Trident II missiles are carried by US Ohio and British Vanguard-class submarines. USS Tennessee (SSBN-734) was the first submarine to be armed with Trident IIs. Trident II missiles are currently carried by fourteen Ohio class and four Vanguard class SSBNs, with 24 missiles on each Ohio class and 16 missiles on each Vanguard class. There have been 150 successful test flights [9] of the D5 missile since 1989, the most recent being from the USS West Virginia (SSBN-736) in June 2014.

The development contract for Trident II was issued in October 1983. The first Trident II launch occurred in January 1987, and the first submarine launch was attempted by Tennessee,[1] the first D-5 ship of the Ohio class, in March 1989. The launch attempt failed because the plume of water following the missile rose to greater height than expected, resulting in water being in the nozzle when the motor ignited. Once the problem was understood relatively simple changes were quickly made, but the problem delayed the Initial Operational Capability (IOC) of Trident II until March 1990.[4]

It is estimated that 540 missiles will be built by 2013. The Trident D5LE (life-extension) version will remain in service until 2042.[10]

Design[edit]

The Trident II is a three-stage rocket, each stage containing a solid propellant motor. The first motor is made by Thiokol and Hercules Inc.. This first stage incorporates a solid propellant motor, parts to ensure first-stage ignition, and a thrust vector control (TVC) system. The first-stage section, compared to the Trident C-4, is slightly larger, allowing increased range and a larger payload. In addition to a larger motor, the D-5 uses an advanced and lighter fuel binder (Polyethylene glycol) than the C-4.[11] This fuel is more commonly known as NEPE-75.[12]

Both the first- and second-stage motors are connected by an interstage casing, which contains electronic equipment and ordnance for separation during flight. The second stage also contains a motor made by Thiokol and Hercules Inc., parts to ensure the second-stage ignition, and a TVC system. The first and second stages are both important to the structural integrity of the missile. To ensure that the stages maintain a maximal strength-to-weight ratio, both stages are reinforced by a Carbon-fiber-reinforced polymer hull.[12]

The second- and third-stage sections are connected by an integrated equipment/adapter section (ES). The equipment/adapter section is modified to be shorter and more compact than the C-4's adapter section.[11] The D-5's equipment section contains critical guidance and flight control avionics, such as the MK 6 navigation system. The equipment section also contains the third-stage TVC system, ordnance for ejecting from the second-stage motor, and the MIRV platform. The Nose Fairing shields the payload of the missile and third-stage motor. Mounted within the nose cap (above the nose fairing) is an extendable aerodynamic spike.[13] This aerodynamic spike effectively decreases drag by 50% on the missile. The third-stage hull is also reinforced by Carbon-fiber and Kevlar, but was not originally designed to be.[12]

Sequence of Operation[edit]

Once the launch command is given, expanding gas within the launch tube forces the missile upward, and out of the submarine. Within seconds, the missile breaches the surface of the water and the first-stage Thrust Vectoring Control (TVC) subsystem ignites. This allows the missile to correct its position prior to first-stage motor ignition. Once the position is corrected, the first-stage motor ignites and burns for approximately 65 seconds until the fuel is expended. When the first-stage motor ceases operation, the second-stage TVC subsystem ignites. The first-stage motor is then ejected by ordnance within the interstage casing.[14][15]

Once the first stage is cleared, the second-stage motor ignites and burns for approximately 65 seconds. The nose fairing is then jettisoned, separating from the missile. When the nose fairing is cleared of the missile, the third-stage TVC subsystem ignites, and ordnance separates the second-stage motor. The third-stage motor then ignites, pushing the equipment section the remaining distance (approx. 40 seconds) of the flight. When the third-stage motor reaches the targeted area, the Post Boost Control System (PBCS) ignites, and the third-stage motor is ejected. The navigation system uses the PBCS to orient and maneuver for stellar sighting, allowing the navigation system to update and revise the inertial guidance flight plan.[16] The equipment section, with the MIRV, then aims the reentry vehicles (RV) towards earth. The payload is then released from the MIRV platform. To prevent the PBCS correctional thrust from interfering with the RV when released, the equipment section initiates the Plume Avoidance Maneuver (PAM). If the RV will be disrupted by the PBCS nozzle's thrust, the nearest nozzle will shut off until the RV is away from the MIRV. The PAM is used only when a nozzle's plume will disrupt the area near an RV. The PAM is a specialized design feature added to the Trident II to increase accuracy.[14]

Specifications[edit]

  • Purpose: Seaborne Nuclear Deterrence[1]
  • Unit Cost: US$ 37.3 million
  • Range: With full load 7,840 kilometres (4,230 nmi);
    with reduced load approx. 7,000 mi (11,300 km) (exact is classified)[6]
  • Maximum speed: Approximately 18,030 mph (29,020 km/h) (Mach 24)[1](terminal phase)
  • Guidance system: Inertial, with Star-sighting.
  • CEP: Requirement: 90–120 metres (300–390 ft).[4] (Information from flight tests is classified.)
  • Warhead (in USA usage only): The Mark 5 MIRV can carry up to 14 W88 (475 kt) warheads, while the Mark 4 MIRV can also carry 14 W76 (100 kt) warheads.[17][18] START I reduced this to eight. New START provides for further reductions in deployed launch vehicles, limiting the number of Submarine-launched ballistic missiles (SLBM) to 288, and the number of deployed SLBM warheads to a total of 1,152. In 2014, another START Treaty will reduce the number of deployed SLBMs to 240.[19]

Submarines currently armed with Trident II missiles[edit]

 United States Navy
 Royal Navy

See also[edit]

References[edit]

  1. ^ a b c d e f g h Parsch, Andreas. "Trident D-5". Encyclopedia Astronautica. Retrieved 11 June 2014. 
  2. ^ "The W88 Warhead, Intermediate yield strategic SLBM MIRV warhead". Retrieved 12 June 2014. 
  3. ^ "The W76 Warhead, Intermediate Yield Strategic SLBM MIRV Warhead". Retrieved 12 June 2014. 
  4. ^ a b c d Parsch, Andreas. "UGM-133". Directory of U.S. Military Rockets and Missiles. Retrieved 2014-06-11. 
  5. ^ a b "History Facts 2". Retrieved June 21, 2014. 
  6. ^ a b "DEPARTMENT OF DEFENSE APPROPRIATIONS ACT, 1996 (Senate - August 11, 1995)". Retrieved 13 June 2014. 
  7. ^ "Trident II (D-5) Sea-Launched Ballistic Missile UGM 133A (Trident II Missile)". Retrieved June 21, 2014. 
  8. ^ Popejoy, Mary. "USS Alabama Offloads Last of C4 Trident Missiles". Retrieved 21 November 2013. 
  9. ^ Fisher, Lynn (13 June 2014). "Trident II D5 Missile Reaches 150 Successful Test Flights" (Press release). Lockheed Martin. PR Newswire. 
  10. ^ "UGM-133 TRIDENT D-5". Missiles of the World. missilethreat.com. Retrieved 2012-11-23. 
  11. ^ a b "Trident I C-4 FBM / SLBM". Retrieved June 13, 2014. 
  12. ^ a b c "Trident II D-5 Fleet Ballistic Missile". Retrieved June 13, 2014. 
  13. ^ "TRIDENT II (D5) DIMENSIONS AND JOINTS". Retrieved June 13, 2014. 
  14. ^ a b "Santa Cruz Facility Brochure". Retrieved June 23, 2014. 
  15. ^ "Trident II D-5 Fleet Ballistic Missile". Retrieved June 23, 2014. 
  16. ^ "Trident II D-5 Fleet Ballistic Missile". Retrieved June 23, 2014. 
  17. ^ "Lockheed Martin UGM-133 Trident II". Retrieved December 12, 2013. 
  18. ^ "Lockheed UGM-96A Trident I C4/UGM-113A Trident II D5". Retrieved December 12, 2013. 
  19. ^ "Fact Sheet on U.S. Nuclear Force Structure under the New START Treaty" (pdf). United States Department of Defense. Retrieved 2014-06-12.