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BBallistic missiles
Surface-to-surface ballistic missile Surface-to-surface cruise missile Submarine-launched ballistic missile
Measured figures
Configuration
| Specification | Ghauri (missile) | Hyunmoo |
|---|---|---|
| Type | MRBM[source] | Surface-to-surface ballistic missile Surface-to-surface cruise missile Submarine-launched ballistic missile[source] |
| Place of origin | Pakistan[source] | South Korea[source] |
| In service | 2003 –present[source] | 1987–present[source] |
| Used by | Pakistan Army ( Army Strategic Forces Command )[source] |
Diameter
Single source1.35 m (4.4 ft)[source]
Maximum; > Mach 4 (
Single sourceMaximum; Maximum speed
Single source> Mach 4 (3,045 mph ; 4,900 km/h )[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.
Republic of Korea Armed Forces[source]
| Designer | Khan Research Laboratories (KRL)[source] | Agency for Defense Development[source] |
|---|
| Designed | 1994–2001[source] | — |
|---|
| Manufacturer | Khan Research Laboratories[source] | Hanwha (Hyunmoo-2/4/5) LIG Defense & Aerospace (Hyunmoo-3)[source] |
|---|
| No. built | 30 (estimated 2021)[source] | — |
|---|
| Variants | Ghauri-II , Ghauri-III[source] | Hyunmoo-1 Hyunmoo-2A Hyunmoo-2B Hyunmoo-2c Hyunmoo-3A Hyunmoo-3B Hyunmoo-3C Hyunmoo-3D Hyunmoo-4 Hyunmoo-4.4 ( submarine version ) Hyunmoo-5 ( bunker buster )[source] |
|---|
| Warhead | HE / NE[source] | Conventional[source] |
|---|
| Blast yield | 12 kilotons of TNT (50 TJ)—35 kilotons of TNT (150 TJ)[source] | — |
|---|
| Engine | Single Stage[source] | — |
|---|
| Payload capacity | 760 kg (1,680 lb)–1,158 kg (2,553 lb)[source] | 500 to 8,000 kg (1,100 to 17,600 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] | solid fuel[source] |
|---|
| Fuel capacity | 12,912 kg (28,466 lb)[source] | — |
|---|
| Flight altitude | 350 km (220 mi) reached in first test flight[source] | — |
|---|
| Guidance system | Inertial , Terminal[source] | command guidance[source] |
|---|
| Accuracy | 190 m (620 ft) CEP[source] | — |
|---|
| Launch platform | Launch pad[source] | mobile launchers[source] |
|---|
| Alternative designation | Ghauri–I[source] | — |
|---|
| Produced | — | 1980s–present[source] |
|---|
| Transport | — | KM1500[source] |
|---|