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At a glance
2K12 Kublarger figure on 1 of 2
Akash-NGlarger figure on 1 of 2
Counts only measures both sources give with the same scope. A larger figure is not a better system.
Measured figures
Warhead weight
Single source59 kg[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
Configuration
| Specification | 2K12 Kub | Akash-NG |
|---|---|---|
| Speed | Mach 2.8[source] | Mach 3[source] |
| Type | Tracked medium-range surface-to-air missile system[source] | Medium-range surface-to-air missile system[source] |
| Place of origin | Soviet Union[source] | India[source] |
| In service | 1967–present[source] | — |
| Used by | See list of operators[source] | Indian Army Indian Air Force[source] |
| Wars | List Yom Kippur War Angolan Civil War Chadian Civil War Western Sahara War Iran–Iraq War 1982 Lebanon War Gulf War Yugoslav wars Kosovo War Syrian Civil War Russo-Ukrainian War Russian invasion of Ukraine Yemeni Civil War (2014–present) 2020 Nagorno-Karabakh war[source] | — |
| Designer | NIIP / Vympel MMZ ( GM chassis )[source] | Defence Research and Development Organisation[source] |
| Designed | 1958–1967[source] | 2021[source] |
| Manufacturer | Ulyanovsk Mechanical Plant (SURNs) ZiK (TELs)[source] | Bharat Dynamics Limited Bharat Electronics Electropneumatics and Hydraulics India[source] |
| Produced | 1968–1985[source] | — |
| No. built | 500 launchers, 10,000 missiles[source] | — |
| Variants | 2K12 Kub, 2K12E Kvadrat (export version), 2K12M3, 2K12M4[source] | — |
| Main armament | 3 3M9M4(or variants) guided missiles[source] | — |
| Engine | Integral rocket motor/ ramjet booster and sustainer motor[source] | Dual-pulse solid rocket motor[source] |
| Guidance system | Command guidance with terminal semi-active radar homing (SARH)[source] | Mid-course: INS + two-way datalink Terminal: ARH[source] |
| Warhead | Frag-HE[source] | Fragmentation[source] |
| Detonation mechanism | Contact and proximity[source] | Optical proximity fuze[source] |
| Propellant | integral rocket motor/ramjet booster and sustainer motor[source] | Solid fuel[source] |
| Flight altitude | Max. 14,000 metres (46,000 ft) Min. 100 metres (330 ft)[source] | 0.030–14 km (98–45,932 ft)[source] |
| Launch platform | 2P25 TEL[source] | — |
| Developed from | — | Akash missile system[source] |
| Rate of fire | — | Normal: 1 missile in 10 seconds Salvo: 3 missiles in 20 seconds[source] |
| Flight ceiling | — | 18 km (59,000 ft)[source] |
| Reported operators |
| — |