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At a glance
Agni-IIlarger figure on 0 of 4
R-36 (missile)larger figure on 4 of 4
Counts only measures both sources give with the same scope. A larger figure is not a better system.
Measured figures
Length
Single source21 m[source]
Length
Single sourceConfiguration
| Specification | Agni-II | R-36 (missile) |
|---|---|---|
| Type | Medium Range Ballistic Missile[source] | Intercontinental ballistic missile[source] |
| Place of origin | India[source] | Soviet Union[source] |
| In service | Active[source] | 1966–1979 (original variant) 1988–present (R-36M2 Voevoda variant)[source] |
| Used by | Strategic Forces Command[source] | Russian Strategic Rocket Forces |
R-36-O
Single source18,900 mm (740 in) - (R-36-O) 32,200 mm (1,270 in)[source]
Maximum; 3.5 km/s (
Single source3.5 km/s (14,040 km/h)[source]
Warhead weight
Single source1,000 kg (2,200 lb)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| Designer | Defence Research and Development Organisation[source] | — |
|---|
| Manufacturer | Bharat Dynamics Limited[source] | Factory: Yuzhny Machine-Building Plant Developer: Yuzhnoye Design Office[source] |
|---|
| Unit cost | ₹ 25 crore (US$2.6 million) to ₹ 35 crore (US$3.6 million)[source] | $7,000,000[source] |
|---|
| No. built | 12 (2017 est.)[source] | — |
|---|
| Warhead | Conventional high explosive -unitary, penetration, sub-munitions , incendiary , thermobaric , strategic nuclear weapon[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 | Multi-stage solid 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] |
|---|
| Propellant | Solid fuel[source] | N 2 O 4 / UDMH[source] |
|---|
| Flight ceiling | 405 km[source] | — |
|---|
| Flight altitude | 230 km[source] | — |
|---|
| Guidance system | Mid-course: RLG - INS + multi- GNSS Terminal: Radar scene matching. Upgraded to ARH[source] | Inertial, autonomous[source] |
|---|
| Accuracy | 30–40 m CEP[source] | 220–1,300 m CEP[source] |
|---|
| Launch platform | Ashok Leyland /Tata transporter erector launcher[source] | Silo[source] |
|---|
| Designed | — | From 1962[source] |
|---|