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>>UGM-96 Trident I



Overview

UGM-96 Trident I

UGM-96 Trident I test launch in 1977.
Source: US Navy - © Public domain

Origin
United States
Type
Service life
1979 - 2005
Status
Out of service
Development
1971 - late 1970's
Developer
United States - Lockheed Martin Space Systems
Production
Late 1970's - 1980's
Producer
United States
Number produced
Over 100
Designations
Trident C4
ULMS II (early project name)
Notable users
United States - Navy

Description

Introduction

The UGM-96 Trident I is a late Cold War era submarine launched ballistic missile of US origin. It was developed to provide a longer range than the its predecessor, the UGM-73 Poseidon, while retaining the same firepower. During development it was decided that the Trident I was to be fitted to new ballistic missile submarines and also be retrofitted to existing ones. The Trident I became operational in 1979 and served until 2005. It was replaced by the more capable UGM-133 Trident II.

Design

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Firepower

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Users

The UGM-96 Trident I was used only by the United States. The United Kingdom requested acquisition of the Trident I in the early 1980's. This request was later stage changed this to the newer Trident II. The Trident I was fitted to the first eight newly built Ohio class ballistic missile submarines. A total of 12 of the James Madison and Benjamin Franklin class ballistic missile submarines were retrofitted with the Trident I, replacing the UGM-73 Poseidon. A total of 20 ballistic submarines were equipped with the Trident I, with the last Trident I removed from service in 2005.

Details

Facts UGM-96 Trident I
General
Origin
United States
Type
Submarine launched ballistic missile
Dimensions
Weight
84 t combined rocket weight
90 t with gas booster and gas generator in launch tube
Length
16.1 m overall
9.5 m first stage
4.1 second stage
Diameter
2.41 m
Warhead
Throw weight
2.550 kg
Layout
10 MIRV
Type
Single thermonuclear warhead per reentry vehicle
Yield
100 - 200 kT each
Guidance
First phase
Gyro-stabilized inertial navigation
Warhead release phase
Astro-inertial guidance
Accuracy
350 - 500 m CEP per MIRV
Engine
Missile design
Three stage missile
Booster
Solid fuel rocket for two booster sections
Post-boost
Liquid fuel engine for warhead section
Maximum range
8.250 - 8.400 km
Trajectory height
About 3.000 km
Launch system
Ejection
Cold launch gas booster
Gas generator for cavity creation
Launch depth
Up to 40 - 50 m
Submarine speed
Up to 5 kt

Media