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ForceTally · AI-generated illustration · Not a photograph · AI-generated · OpenAI output terms · Source ↗ · Modified
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At a glance
Pralay (missile)larger 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
>
Single source> 7.5 - 11 m[source]
Length
Single sourceConfiguration
| Specification | Pralay (missile) | R-36 (missile) |
|---|---|---|
| Type | Tactical ballistic missile[source] | Intercontinental ballistic missile[source] |
| Place of origin | India[source] | Soviet Union[source] |
| Used by | Indian Army Indian Air Force[source] | Russian Strategic Rocket Forces[source] |
| Designer | Research Centre Imarat[source] | — |
R-36-O
Single source18,900 mm (740 in) - (R-36-O) 32,200 mm (1,270 in)[source]
Maximum; 2.08 km/s
Single sourceMaximum; Mach 6.1 (
Single sourceMach 6.1 (7,470 km/h; 4,640 mph; 2.08 km/s)[source]
Warhead weight · source measurement 1
Single sourceWarhead weight · source measurement 2
Single source350–700 kg (770–1,540 lb) 500–1,000 kg (1,100–2,200 lb)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| Manufacturer | Bharat Electronics Bharat Dynamics Limited[source] | Factory: Yuzhny Machine-Building Plant Developer: Yuzhnoye Design Office[source] |
|---|
| Warhead | HE PF , PCB , RDPS[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 rocket + MaRV[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] |
|---|
| Propellant | Solid[source] | N 2 O 4 / UDMH[source] |
|---|
| Guidance system | Mid-course: INS Terminal: MMW DSMAC + Radar Imaging[source] | Inertial, autonomous[source] |
|---|
| Accuracy | <10 metres (33 ft) CEP[source] | 220–1,300 m CEP[source] |
|---|
| Launch platform | 12 x 12 Ashok Leyland HMV TEL[source] | Silo[source] |
|---|
| In service | — | 1966–1979 (original variant) 1988–present (R-36M2 Voevoda variant)[source] |
|---|
| Designed | — | From 1962[source] |
|---|
| Unit cost | — | $7,000,000[source] |
|---|
| Reported operators |
| — |
|---|