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At a glance
DF-31larger figure on 0 of 3
R-36 (missile)larger figure on 3 of 3
Counts only measures both sources give with the same scope. A larger figure is not a better system.
Measured figures
Length
Single source21.6 m (70 ft 10 in)[source]
Length
Single sourceConfiguration
| Specification | DF-31 | R-36 (missile) |
|---|---|---|
| Speed | Up to 8.16 km/s (Mach 25)[source] | — |
| Type | Intercontinental ballistic missile[source] | Intercontinental ballistic missile[source] |
| Place of origin | People's Republic of China[source] | Soviet Union[source] |
| In service | 2006 (DF-31), 2007 (DF-31A), 2017 (DF-31B)[source] | 1966–1979 (original variant) 1988–present (R-36M2 Voevoda variant)[source] |
R-36-O
Single source18,900 mm (740 in) - (R-36-O) 32,200 mm (1,270 in)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| Used by | People's Liberation Army Rocket Force[source] | Russian Strategic Rocket Forces[source] |
|---|
| Manufacturer | Academy of Rocket Motors Technology (ARMT)[source] | Factory: Yuzhny Machine-Building Plant Developer: Yuzhnoye Design Office[source] |
|---|
| Unit cost | $7,000,000[source] |
|---|
| Warhead | 425 kilotonnes of TNT (1,780 TJ)[source] | 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] |
|---|
| Engine | Solid-fuel rocket[source] | 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] |
|---|
| Flight altitude | Up to 1,200 km (750 mi)[source] | — |
|---|
| Guidance system | Astro-inertial guidance with BeiDou Navigation Satellite System[source] | Inertial, autonomous[source] |
|---|
| Accuracy | 100 m CEP for silo launched and 150–300 m for TEL-launched.[source] | 220–1,300 m CEP[source] |
|---|
| Launch platform | Silo, 8 axle TEL[source] | Silo[source] |
|---|
| Designed | — | From 1962[source] |
|---|
| Propellant | — | N 2 O 4 / UDMH[source] |
|---|