Credit
Vitaly V. Kuzmin · CC BY-SA 4.0 · Resized · CC BY-SA 4.0 · Source ↗ · Modified
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At a glance
RS-24 Yarslarger figure on 1 of 2
UGM-133 Trident IIlarger figure on 1 of 2
Counts only measures both sources give with the same scope. A larger figure is not a better system.
Measured figures
Length
Single source22,500 mm[source]
Length
Single sourceConfiguration
| Specification | RS-24 Yars | UGM-133 Trident II |
|---|---|---|
| Type | Intercontinental Ballistic Missile[source] | SLBM[source] |
| Place of origin | Russia[source] | United States[source] |
| In service | 2010–present[source] | 1990–present[source] |
| Used by | Russian Strategic Missile Troops[source] | United States Navy Royal Navy |
44 ft 6.6 in (13.579 m)[source]
Maximum; Mach 25 (
Single sourceMaximum; Maximum speed · source measurement 2
Single sourceMaximum; Maximum speed · source measurement 3
Single sourceMach 25 (30,600 km/h; 19,000 mph; 8,510 m/s)[source]
Maximum; Approximately Mach 24
Single sourceMaximum; ) (terminal phase
Single sourceOperational; Operational range
Single source11,000 km (6,800 mi) - 12,000 km (7,500 mi)[source]
Operational; Full load (8x Mk5/W88)
Single sourceOperational; Full load (8x Mk5/W88) Reduced load (4x Mk5/W88)
Single sourceFull load (8x Mk5/W88): 4,100 nmi (4,700 mi; 7,600 km) Reduced load (4x Mk5/W88): 6,220 nmi (7,160 mi; 11,520 km)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| Designer | Moscow Institute of Thermal Technology[source] | — |
|---|
| Manufacturer | Votkinsk Machine Building Plant[source] | Lockheed Martin Space[source] |
|---|
| Produced | 2009[source] | 1983[source] |
|---|
| Warhead | 3 x 200 kiloton MIRV warheads[source] | United States 1–8 Mk-5 RV / W88 (475 kt) or 1–12 Mk-4 RV/ W76-0 (100 kt) or 1–12 Mk-4A RV/ W-76-1 (90 kt) or Mk-7 RV/ W93 (planned) Single or multiple W76-2 (5–7 kt) United Kingdom Mk-4A RV/Holbrook (100 kt) Mk-7 RV/ A21 Astraea (planned)[source] |
|---|
| Engine | Three-stage Solid-fuel rocket[source] | Three solid-fuel rocket motors; first & second stage – Thiokol / Hercules solid-fueled rocket; third stage – United Technologies Corp. solid-fueled rocket[source] |
|---|
| Guidance system | Inertial with Glonass[source] | MK 6 astro-inertial guidance[source] |
|---|
| Launch platform | Silo , road-mobile TEL MZKT-79221[source] | Ballistic missile submarine[source] |
|---|
| Unit cost | — | $30.9 million (1987 USD) ($87.6 million in 2025 dollars)[source] |
|---|
| Propellant | — | NEPE-75 : Nitrate ester , plasticized polyethylene glycol -bound HMX , aluminum , ammonium perchlorate[source] |
|---|
| Steering system | — | Single movable nozzle actuated by a gas generator[source] |
|---|
| Accuracy | — | 100 m[source] |
|---|
Approximately 18,030 mph (29,020 km/h) (Mach 24; 8,060 m/s) (terminal phase)[source]