FORCETALLY
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Measured figures
I/B
Single sourceMinuteman I/A Minuteman
Single sourceConfiguration
| Specification | K-5 (ballistic missile) | LGM-30 Minuteman |
|---|---|---|
| Type | SLBM[source] | Intercontinental ballistic missile[source] |
| Place of origin | India[source] | United States[source] |
| In service | Under development[source] | Minuteman I: 1962–1969 Minuteman II: 1965–1994 Minuteman III: 1970–present[source] |
| Designer | Defence Research and Development Organisation[source] |
Minuteman II
Single sourceMinuteman III
Single sourceMinuteman I/A: 53 ft 8 in (16.36 m) Minuteman I/B: 55 ft 11 in (17.04 m) Minuteman II: 57 ft 7 in (17.55 m) Minuteman III: 59.9 ft (18.3 m)[source]
weighing two tonnes[source]K-5 (ballistic missile) · Description · The missile will be able to carry a payload weighing two tonnes.
Mass
Single sourceMinuteman I: About Minuteman II: About
Single sourceMinuteman III
Single sourceMinuteman I: About 65,000 lb (29,000 kg) Minuteman II: About 73,000 lb (33,000 kg) Minuteman III: 79,432 lb (36,030 kg)[source]
Maximum; 2.55 km/s
Single sourceMaximum; Mach 7.5 (
Single sourceMach 7.5 (9,190 km/h; 5,710 mph; 2.55 km/s)[source]
Maximum; 7.83 km/s ) (terminal phase
Single sourceMaximum; Mach 23 (
Single sourceOperational; Operational range
Single sourcerange of around
Single source5,000–8,000 km (3,100–5,000 mi)[source]
range of around 5,000–6,000 km (3,100–3,700 mi)[source]K-5 (ballistic missile) · Description · It is planned to have a range of around 5,000–6,000 km (3,100–3,700 mi).
Operational; Minuteman I
Single sourceOperational; Minuteman II
Single sourceEngine · source measurement 3
Single sourceEngine · source measurement 5
Single source) First stage 202,600 lb (91,900 kg) (Minuteman III
Single source) Second stage : Aerojet-General SR-19-AJ-1 (
Single source) Third stage : Aerojet / Thiokol SR73-AJ/TC-1 (
Single sourceThree-stage solid-fuel rocket engines First stage : Thiokol TU-122 (M-55) (
Single sourceThree-stage solid-fuel rocket engines First stage : Thiokol TU-122 (M-55) (178,000 lbf, 790 kN) Second stage : Aerojet-General SR-19-AJ-1 (60,181 lbf, 267.70 kN) Third stage : Aerojet / Thiokol SR73-AJ/TC-1 (34,170 lbf, 152.0 kN) First stage 202,600 lb (91,900 kg) (Minuteman III)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| — |
| Warhead | 2,000 kg (4,400 lb ) nuclear war-head[source] | Minuteman I: W59 (retired) Minuteman I and II: W56 (retired) Minuteman III: 2–3 × W62 (retired), 2–3 × W78 (retired), 1 × W78 (active), or 1 × W87 (active)[source] |
|---|
| Engine | Solid-fuelled[source] | — |
|---|
| Launch platform | Arihant-class submarines , S5-class submarines[source] | Missile silo[source] Missile silo[source] |
|---|
| Role | submarine-launched ballistic missile[source] | — |
|---|
| Source measurement | The K-5 is a submarine-launched ballistic missile. The missile consists of three separate stages and uses solid rocket propellant . It is planned to have a range of around 5,000–6,000 km (3,100–3,700 mi). The missile will be able to carry a payload weighing two tonnes. It is being developed to match the range of the Agni-V missile. It will be equipped on the Arihant-class submarines code named S4 .[source]K-5 (ballistic missile) · Description; only the objects and conditions stated in this passage On 12 September 2025, the Advanced Centre for Energetic Materials (ACEM) in Nashik conducted a static firing test of the second-stage motor developed under Project K5. The motor is a 10-tonne-class solid-propellant design measuring approximately 2.68 metres in length and 2.4 metres in diameter. Its composite motor case uses T700 carbon-fibre reinforcement with Epofine resin, while the propellant grain employs a nine-fin finocyl configuration of HD 1.3 composite propellant. The motor incorporates a pyrogen ignition system and a submerged, thrust-vectoring nozzle actuated by two electromechanical actuators.[source]K-5 (ballistic missile) · Development / Static testing of the second stage motor; only the objects and conditions stated in this passage The test was intended to characterise the motor's ballistic performance and verify the operation and safety margins of its major subsystems. Instrumentation comprising more than 250 measurement channels was used to acquire test data. The nozzle was commanded through approximately ±2° of movement, with actuator operation beginning 10 seconds after ignition. The recorded pressure and thrust profiles were reported to be consistent with pre-test predictions, indicating the expected motor performance during the static firing.[source]K-5 (ballistic missile) · Development / Static testing of the second stage motor; only the objects and conditions stated in this passage The motor was manufactured using a newly established 50-tonne-capacity cast-cure installation at ACEM, which employs hopper-based continuous casting for large propellant grains. The successful processing and subsequent firing provided a demonstration of the facility's capability for larger-class solid motors and was also the first reported test of this motor type at ACEM's refurbished static-test facility.[source]K-5 (ballistic missile) · Development / Static testing of the second stage motor; only the objects and conditions stated in this passage | — |
|---|
| Country of origin | India[source]Inventory Origin column; table 1, row 5, cell 2; revision 1373427941; retrieved 2026-10-02 | — |
|---|
| Used by | — | United States Air Force[source] |
|---|
| Manufacturer | — | Boeing[source] |
|---|
| Unit cost | — | US$ 7,000,000 (equivalent to $34,600,000 in 2025)[source] |
|---|
| No. built | — | 550[source] |
|---|
| Detonation mechanism | — | Air-burst or contact (surface)[source] |
|---|
| Propellant | — | Ammonium perchlorate composite propellant[source] |
|---|
| Flight ceiling | — | 1,120 km (3,670,000 ft; 700 mi)[source] |
|---|
| Guidance system | — | Inertial NS-50[source] Inertial NS-50[source] |
|---|
| Accuracy | — | Minuteman I: 1.1 nmi (2.0 km) CEP initially, then 0.6 nmi (1.1 km) CEP Minuteman II: 0.26 nmi (0.48 km) CEP Minuteman III: 200 m (660 ft) CEP[source] |
|---|
Mach 23 (17,500 mph ; 28,200 km/h ; 7.83 km/s ) (terminal phase)[source]
Operational; Minuteman III
Single sourceMinuteman I: 5,500 nmi (6,300 mi; 10,200 km) Minuteman II: 6,300 nmi (7,200 mi; 11,700 km) Minuteman III: 7,600 nmi (8,700 mi; 14,000 km)[source]