UGM-133 Trident II

"Trident II" redirects here. For the French fighter plane, see SNCASO Trident.

UGM-133A Trident II
A Trident II launch from a submerged Royal Navy submarine.
Type	SLBM
Place of origin	United States
Service history
In service	1990-present
Used by	United States Navy Royal Navy
Production history
Manufacturer	Lockheed Martin Space Systems
Unit cost	$30.9 million (2019)
Produced	1983
Specifications
Mass	130,000 lb (59,000 kg)
Length	44 ft 6.6 in (13.579 m)
Diameter	6 ft 11 in (2.11 m) (1st stage)
Warhead	1-8 Mk-5 RV/W88 (455 kt) or 1-14 Mk-4 RV/W76-0 (100 kt) or 1-14 Mk-4A RV/W-76-1 (90 kt) Single or multiple W76-2 (5-7 kt)
Engine	Three solid-fuel rocket motors; first & second stage – Thiokol/Hercules solid-fueled rocket; third stage – United Technologies Corp. solid-fueled rocket
Propellant	Nitrate ester, plasticized polyethylene glycol
Operational range	More than 7,500 mi (12,000 km) (exact is classified)
Maximum speed	Approximately 18,030 mph (29,020 km/h) (Mach 24; 8,060 m/s) (terminal phase)
Guidance system	MK 6 astro-inertial guidance which is able to receive GPS (Global Positioning System) updates
Steering system	Single movable nozzle actuated by a gas generator
Accuracy	90 m with Mk-5 RV using GPS guidance 120-183 m with Mk-5 RV using astro-inertial guidance 381 m with Mk-4 RV(in the process of retirement with the W76-0 warhead)
Launch platform	Ballistic missile submarine

The UGM-133A Trident II, or Trident D5 is a submarine-launched ballistic missile (SLBM), built by Lockheed Martin Space Systems in Sunnyvale, California, and deployed with the American and British navies. It was first deployed in March 1990, and remains in service. The Trident II Strategic Weapons System is an improved SLBM with greater accuracy, payload, and range than the earlier Trident C-4. It is a key element of the U.S. strategic nuclear triad and strengthens 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, and its high accuracy – approaching that of land-based missiles – enables it to be used as a first strike weapon.

Trident II missiles are carried by 14 US Ohio and four British Vanguard-class submarines, with 24 missiles on each Ohio class and 16 missiles on each Vanguard class (the number of missiles on Ohio-class submarines will be reduced to 20 each in coming years, in compliance with the New Strategic Arms Limitation Treaty). There have been 176 successful test flights of the D5 missile since design completion in 1989, the most recent being from USS Nebraska in September 2019. There have been fewer than 10 test flights that were failures, the most recent being from HMS Vengeance off the coast of Florida in June 2016. The D5 is the sixth in a series of missile generations deployed since the sea-based deterrent program began 60 years ago. The Trident D5LE (life-extension) version will remain in service until 2042.

History

USS Kentucky firing a Trident II SLBM in 2015 as part of the DASO 26 test launch

The Trident II was designed with greater range and payload capacity than its predecessor (Trident C-4). In 1972, the US Navy projected an initial operating capability (IOC) date of 1984. The US Navy shifted the IOC date to 1982. On 18 October 1973, a Trident program review was administered. On 14 March 1974, the US Deputy Secretary of Defense disseminated two requirements for the Trident program. The first was an accuracy improvement for the Trident C-4. The second requirement asked for an alternative to the C-4, or a new Trident II missile with a larger first-stage motor than the C-4.

The U.S. Navy conducted studies to determine whether the more expensive Trident II could be constructed similarly to the US Air Force's MX ICBM, primarily to decrease budget costs. It was established that the Trident II would be 83 inches in diameter and 44 feet in length in order to match the performance of the existing MX ICBM. Modifications to the guidance system, electronics hardening, and external protective coatings were incorporated into the design. While this satisfied the Navy's study requirements, it did not accommodate the US Air Force payload requirements.

Propulsion stages were proposed to be used between the first stage and second stage motors, effectively making the Trident II a longer three-stage missile than the C-4. Studies were delayed in 1978 when Congress only approved $5 million of the suggested $15 million for the Navy and Air Force program studies. By December 1978, the Navy's and the Air Force's own studies agreed with each other that a similar missile structure would not achieve desired savings. It was determined that the Navy and Air Force would maintain and be responsible for their own unique weapon systems. The US Navy continued with its own design of the Trident II.

In March 1980, US Secretary of Defense Harold Brown proposed an increased level of funding for the submarine-launched ballistic missile modernization, emphasizing increased accuracy. The House Armed Services Committee (HASC) recommended no funding, while the Senate Armed Services Committee (SASC) recommended full funding of $97 million. The SASC asked for a plan incorporating "the fullest possible competition . . . [and] should consider competing among contractors for each major component, including the integrated missile." $65 million was awarded for the submarine-launched ballistic missile modernization.

On 2 October 1981, President Reagan called for the modernization of the strategic forces. The Defense Department directed the Navy to fund all development of the Trident II D5 missile with a December 1989 IOC. All research and development efforts would be directed toward "a new development, advanced technology, high accuracy Trident II D5 system." In December 1982, Deputy SECDEF Frank Carlucci advised Secretary of the Navy Caspar Weinberger to include funding for a new reentry vehicle–warhead combination for Trident II. The reentry vehicle was to be designated as the Mk 5, which was to have a greater yield than the Mk 4. The development contract for Trident II was issued in October 1983. On 28 December 1983, the deputy SECDEF authorized the Navy to proceed with full-scale engineering development of the Trident II D5. The first Trident II launch occurred on 15 January 1987, and the first submarine launch was attempted by USS Tennessee, the first D-5 ship of the Ohio class, on 21 March 1989 off the coast of Cape Canaveral, Florida. The launch attempt failed four seconds into the flight because the plume of water following the missile rose to greater height than expected, and water was in the nozzle when the motor ignited. Once the problem was understood, relatively simple changes were quickly made, but the problem delayed the IOC of Trident II until March 1990. IOC for SWFPAC^{[Clarification needed]} completed on schedule in 2001, allowing Trident II SSBN to be deployed in the Pacific theater.

In 1980, the United Kingdom adopted the missile as part of its Trident nuclear program.

Design

The Trident II is a three-stage rocket, each stage containing a solid-fuel rocket 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. This fuel is more commonly known as NEPE-75. (NEPE stands for nitrate ester plasticized polyether.)

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.

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. 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 and third-stage motor. Mounted within the nose cap (above the nose fairing) is an extendable aerospike. This aerospike effectively decreases drag by 50%. The third-stage hull is also reinforced by carbon fiber and kevlar.

The Trident II is the first missile of the US Navy's Fleet Ballistic Missile program to incorporate a 3D printed component.

Sequence of operation

US Navy test firing two Trident II D-5 UGM-133A missiles in the Atlantic Missile Range, June 2014 (DASO 25 SSBN 736) during a Demonstration and Shakedown Operation.

Before the launch sequence is initiated, the on-board MARK 6 navigation system is activated. The specified mission trajectory is loaded onto the flight computer.

Once the launch command is given, a steam generator system is activated, igniting a fixed solid-grain small rocket motor. The exhaust is fed into cooling water, causing expanding gas within the launch tube to force 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 enables hydraulic actuators attached to the first-stage nozzle. Soon after, the first-stage motor ignites and burns for approximately 65 seconds until the fuel is expended; in addition, an aerospike atop the missile deploys shortly after first-stage ignition to shape airflow. 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.

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 astro-inertial guidance uses star positioning to fine-tune the accuracy of the inertial guidance system after launch. As the accuracy of a missile is dependent upon the guidance system knowing the exact position of the missile at any given moment during its flight, the fact that stars are a fixed reference point from which to calculate that position makes this a potentially very effective means of improving accuracy. In the Trident system this was achieved by a single camera that was trained to spot just one star in its expected position. If it was not quite aligned to where it should be, it would indicate that the inertial system was not precisely on target and a correction would be made.

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.

Additional specifications

• Range (exact is classified):
  Full load: ~7600 km
  Reduced load: >12000 km
• Guidance system: The MK 6 Astro-inertial guidance navigation system which is able to receive GPS (Global Positioning System) updates.
• CEP: Requirement: 90 metres (300 ft). (Information from flight tests is classified.)^{[citation needed]}
• Warhead (in US usage only): Up to 8 Mk-5 RVs with W88 (455 kt) warheads, up to 14 Mk-4 RVs with W76-0 (100 kt) warheads (in the process of retirement in favor of Mk-4A/W76-1) or up to 14 Mk-4A RVs with W76-1 (90 kt) warheads. The smaller (5-7 kt) W76-2 warhead is planned to be deployed in limited numbers with the Mk-4A reentry vehicle, employing the "super fuze" able to adjust the height of burst to compensate reentry inaccuracy and enhancing the missile's effectiveness against hardened targets. START I reduced the number of warheads per missile 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, therefore on average a missile will carry only 4 warheads.
• Warhead (in UK usage): Under a 1958 agreement, the U.S. supplies the UK with blueprints of its own warhead designs but the design, manufacture and maintenance of UK warheads are purely a UK responsibility. The Atomic Weapons Establishment (AWE) at Aldermaston constantly manufactures (and along with the maintenance and remanufacturing plant at Burghfield) a range of warheads of varying yield for fitting to Trident II missiles while pursuing ongoing research into new and improved warheads. Between 2005 and 2008 a £1.1bn program was undertaken to simulate and validate the safety and operation of the entire stockpile in to the mid 2020s without underground testing. The AWE has contributed scientists and £85m to the development of the Mk4A arming, fusing, and firing system at Sandia with the intention UK production at Aldermaston and fitting to existing warheads would commence in the latter half of the 2010s. The AWE is currently researching a fundamentally new warhead design to replace the existing design from the mid 2020s.^{[citation needed]}

Mk-5 RV (175 kg each) offloading effects on D-5 range

Mk-5 RVs	Throw-weight (kg)	D-5 Range (km)	Increase in range (%)
8	2700	7593	nominal
7	2525	8278	9
6	2350	9111	20
5	2175	10,148	34
4	2000	11,519	52
3	1825	13,482	78

Operators

Map with UGM-133 operators in blue

USS Kentucky, an Ohio-class submarine of the US Navy

HMS Vigilant, a Vanguard-class submarine of the Royal Navy

The Royal Navy operates its missiles from a shared pool, together with the Atlantic squadron of the U.S. Navy Ohio-class SSBNs at King's Bay, Georgia. The pool is co-mingled and missiles are selected at random for loading on to either nation's submarines.

Trident II missile submarines

United States Navy Ohio-class submarine Henry M. Jackson Alabama Alaska Nevada Tennessee Pennsylvania West Virginia Kentucky Maryland Nebraska Rhode Island Maine Wyoming Louisiana Columbia-class submarine (planned) Columbia

Royal Navy Vanguard-class submarine Vanguard Victorious Vigilant Vengeance Dreadnought-class submarine (planned) Dreadnought Valiant Warspite King George VI

See also

• JL-1
• JL-2
• K Missile family
• Pukkuksong-1
• M45 (missile)
• M51 (missile)
• R-29RMU Sineva
• R-29RMU2 Layner
• R-39 Rif
• RSM-56 Bulava