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At a glance
DF-21larger 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 source10.7 metres (35 ft)[source]
Length
Single sourceConfiguration
| Specification | DF-21 | R-36 (missile) |
|---|---|---|
| Speed | Mach 10 (estimated maximum before re-entry)[source] | — |
| Type | MRBM / IRBM[source] | Intercontinental ballistic missile[source] |
| Place of origin | China[source] | Soviet Union[source] |
| In service | 1991[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]
Operational; DF-21C
Single sourceOperational; DF-21D ASBM
Single sourceOperational; DF-21/DF-21A
Single source1,770 km (1,100 mi) (DF-21/DF-21A) 1,700 km (1,100 mi) (DF-21C) 1,500 km (930 mi; 810 nmi) (DF-21D ASBM )[source]
Operational; Operational range
Single source10,200–16,000 km[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 Royal Saudi Strategic Missile Force[source] |
Russian Strategic Rocket Forces[source] |
| Warhead | conventional 600kg: 1, or 5-6 (improved variant) nuclear 200-300-500 kt nuclear[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 fueled[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] |
|---|
| Guidance system | Inertial + terminal active radar guidance[source] | Inertial, autonomous[source] |
|---|
| Accuracy | DF-21 700m, DF-21A 50m, DF-21B 10m CEP (with BeiDou Navigation Satellite System and active radar)[source] | 220–1,300 m CEP[source] |
|---|
| Launch platform | Mobile launcher[source] | Silo[source] |
|---|
| Manufacturer | ( Capital Astronautics Co. )[source] | Factory: Yuzhny Machine-Building Plant Developer: Yuzhnoye Design Office[source] |
|---|
| Designed | — | From 1962[source] |
|---|
| Unit cost | — | $7,000,000[source] |
|---|
| Propellant | — | N 2 O 4 / UDMH[source] |
|---|