FORCETALLY
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At a glance
Ghauri-IIlarger 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 source26 m (85 ft)[source]
Length
Single sourceConfiguration
| Specification | Ghauri-II | R-36 (missile) |
|---|---|---|
| Type | MRBM[source] | Intercontinental ballistic missile[source] |
| Place of origin | Pakistan[source] | Soviet Union[source] |
| In service | 2004–present (Not currently deployed)[source] | 1966–1979 (original variant) 1988–present (R-36M2 Voevoda variant)[source] |
| Used by | Pakistan Army ( Army Strategic Forces Command )[source] |
R-36-O
Single source18,900 mm (740 in) - (R-36-O) 32,200 mm (1,270 in)[source]
Warhead weight
Single source1,500 kg (3,300 lb)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
Russian Strategic Rocket Forces[source]
| Designer | Khan Research Laboratories (KRL)[source] | — |
|---|
| Designed | 1993–2003[source] | From 1962[source] |
|---|
| Manufacturer | Khan Research Laboratories[source] | Factory: Yuzhny Machine-Building Plant Developer: Yuzhnoye Design Office[source] |
|---|
| Variants | Ghauri-III[source] | — |
|---|
| Warhead | HE / NE[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 | Two-stage[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] |
|---|
| Transmission | Manual[source] | — |
|---|
| Suspension | Atego x 8WD semi-trailer[source] | — |
|---|
| Propellant | Liquid-propellant[source] | N 2 O 4 / UDMH[source] |
|---|
| Flight altitude | 612 mi (985 km), reached in first test flight[source] | — |
|---|
| Guidance system | Inertial , Terminal[source] | Inertial, autonomous[source] |
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| Launch platform | Launch pad[source] | Silo[source] |
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| Unit cost | — | $7,000,000[source] |
|---|
| Accuracy | — | 220–1,300 m CEP[source] |
|---|