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At a glance
Ghauri (missile)larger figure on 0 of 4
RS-24 Yarslarger figure on 4 of 4
Measured figures
Length
Single source15.90 m (52.2 ft)[source]
Length
Single sourceConfiguration
| Specification | Ghauri (missile) | RS-24 Yars |
|---|---|---|
| Type | MRBM[source] | Intercontinental Ballistic Missile[source] |
| Place of origin | Pakistan[source] | Russia[source] |
| In service | 2003 –present[source] | 2010–present[source] |
| Used by | Pakistan Army ( Army Strategic Forces Command )[source] | Russian Strategic Missile Troops |
Counts only measures both sources give with the same scope. A larger figure is not a better system.
22,500 mm[source]
Maximum; Mach 25 (
Single sourceMaximum; Maximum speed · source measurement 2
Single sourceMaximum; Maximum speed · source measurement 3
Single sourceMach 25 (30,600 km/h; 19,000 mph; 8,510 m/s)[source]
Warhead weight
Single source750 kg (1,650 lb)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| Designer | Khan Research Laboratories (KRL)[source] | Moscow Institute of Thermal Technology[source] |
|---|
| Designed | 1994–2001[source] | — |
|---|
| Manufacturer | Khan Research Laboratories[source] | Votkinsk Machine Building Plant[source] |
|---|
| No. built | 30 (estimated 2021)[source] | — |
|---|
| Variants | Ghauri-II , Ghauri-III[source] | — |
|---|
| Warhead | HE / NE[source] | 3 x 200 kiloton MIRV warheads[source] |
|---|
| Blast yield | 12 kilotons of TNT (50 TJ)—35 kilotons of TNT (150 TJ)[source] | — |
|---|
| Engine | Single Stage[source] | Three-stage Solid-fuel rocket[source] |
|---|
| Payload capacity | 760 kg (1,680 lb)–1,158 kg (2,553 lb)[source] | — |
|---|
| Transmission | Manual[source] | — |
|---|
| Suspension | Atego x 8WD semi-trailer (with Pakistani military markings)[source] | — |
|---|
| Propellant | Liquid-propellant Fuel: TM-185 (20% Gasoline 80% Kerosene ) Oxidizer: AK-27I (73% HNO 3 , 27% N 2 O 4 )[source] | — |
|---|
| Fuel capacity | 12,912 kg (28,466 lb)[source] | — |
|---|
| Flight altitude | 350 km (220 mi) reached in first test flight[source] | — |
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| Guidance system | Inertial , Terminal[source] | Inertial with Glonass[source] |
|---|
| Accuracy | 190 m (620 ft) CEP[source] | — |
|---|
| Launch platform | Launch pad[source] | Silo , road-mobile TEL MZKT-79221[source] |
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| Alternative designation | Ghauri–I[source] | — |
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| Produced | — | 2009[source] |
|---|