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At a glance
R-36 (missile)larger figure on 2 of 2
UGM-133 Trident IIlarger figure on 0 of 2
Counts only measures both sources give with the same scope. A larger figure is not a better system.
Measured figures
Length
Single sourceR-36-O
Single sourceConfiguration
| Specification | R-36 (missile) | UGM-133 Trident II |
|---|---|---|
| Type | Intercontinental ballistic missile[source] | SLBM[source] |
| Place of origin | Soviet Union[source] | United States[source] |
| In service | 1966–1979 (original variant) 1988–present (R-36M2 Voevoda variant)[source] | 1990–present[source] |
| Used by | Russian Strategic Rocket Forces[source] | United States Navy Royal Navy |
18,900 mm (740 in) - (R-36-O) 32,200 mm (1,270 in)[source]
Length
Single source44 ft 6.6 in (13.579 m)[source]
Maximum; Approximately Mach 24
Single sourceMaximum; ) (terminal phase
Single sourceApproximately 18,030 mph (29,020 km/h) (Mach 24; 8,060 m/s) (terminal phase)[source]
Operational; Operational range
Single source10,200–16,000 km[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.
| Designed | From 1962[source] | — |
|---|
| Manufacturer | Factory: Yuzhny Machine-Building Plant Developer: Yuzhnoye Design Office[source] | Lockheed Martin Space[source] |
|---|
| Unit cost | $7,000,000[source] | $30.9 million (1987 USD) ($87.6 million in 2025 dollars)[source] |
|---|
| Warhead | Depending on variant (see variants). Newest (R-36M2), 10 × 550–750 kiloton MIRV warheads with a large amount of decoys and other penetration aids . Originally (R-36), 1 × 8–20 megaton warhead.[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 | Two or three (R-36MUTTKH and R-36M2) liquid fueled rocket stages First Stage: 1x RD-251 (R-36) 1x RD-251P (R-36P) 1x RD-251M (R-36-O) 1x RD-264 (R-36M) 1x RD-264 (R-36MUTTKh and R-36M2) Second Stage: 1x RD-252 (R-36) 1x RD-252 (R-36P) 1x RD-0228 (R-36M) 1x RD-0255 (R-36MUTTKh) 1x RD-0255 (R-36M2) Third Stage: 1x RD-864 (R-36MUTTKh) 1x RD-869 (R-36M2)[source] | Three solid-fuel rocket motors; first & second stage – Thiokol / Hercules solid-fueled rocket; third stage – United Technologies Corp. solid-fueled rocket[source] |
|---|
| Propellant | N 2 O 4 / UDMH[source] | NEPE-75 : Nitrate ester , plasticized polyethylene glycol -bound HMX , aluminum , ammonium perchlorate[source] |
|---|
| Guidance system | Inertial, autonomous[source] | MK 6 astro-inertial guidance[source] |
|---|
| Accuracy | 220–1,300 m CEP[source] | 100 m[source] |
|---|
| Launch platform | Silo[source] | Ballistic missile submarine[source] |
|---|
| Produced | — | 1983[source] |
|---|
| Steering system | — | Single movable nozzle actuated by a gas generator[source] |
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