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At a glance
Astra (missile)larger figure on 2 of 2
PL-2larger figure on 0 of 2
Counts only measures both sources give with the same scope. A larger figure is not a better system.
Measured figures
Length
Single source3.84 m (12.6 ft)[source]
Length · source measurement 1
Single sourceConfiguration
| Specification | Astra (missile) | PL-2 |
|---|---|---|
| Speed | Mk-1: Mach 4.5[source] | Mach 1.6 to 2.5[source] |
| Type | Beyond-visual-range air-to-air missile[source] | Short-range air-to-air missile[source] |
| Place of origin | India[source] | China[source] |
| In service | 2019 ( 2019 ) –present[source] | 1970s to present |
Length · source measurement 2
Single sourceLength · source measurement 3
Single source2.15–2.99 m (7 ft 1 in – 9 ft 10 in)[source]
Wingspan · source measurement 1
Single sourceWingspan · source measurement 2
Single sourceWingspan · source measurement 3
Single source528–609 mm (1 ft 9 in – 2 ft 0 in)[source]
Warhead weight
Single source15 kg (33 lb)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| Used by | Indian Air Force Indian Navy[source] | China[source] |
|---|
| Wars | 2025 India–Pakistan conflict[source] | — |
|---|
| Designer | Defence Research and Development Laboratory ( DRDO )[source] | — |
|---|
| Manufacturer | Bharat Dynamics Limited[source] | Luoyang Electro-Optics Technology Development Centre (EOTDC)[source] |
|---|
| Unit cost | Mk-1: ₹ 7−8 crore (US$−830,000)[source] | — |
|---|
| Produced | 2017 − Present[source] | 1970s to 1980s[source] |
|---|
| Variants | Mk-1 (Operational) Mk-2 (LSP) Mk-3 (Trial-phase) VL-SRSAM (Trial-phase)[source] | — |
|---|
| Warhead | High-explosive pre- fragmented HMX / PU[source] | 11.3 kg (25 lb) high explosive[source] |
|---|
| Detonation mechanism | Mk-1: Radio proximity fuze Mk-2: Optical proximity fuze[source] | Impact / Proximity[source] |
|---|
| Engine | Mk-1: Solid-propellant rocket Mk-2: Dual-thrust pulsed rocket motor Mk-3: Solid Fuel Ducted Ramjet[source] | rocket 2668dN[source] |
|---|
| Propellant | Solid fuel[source] | solid fuel[source] |
|---|
| Flight ceiling | 20 km (66,000 ft)[source] | 15–21.5 km (9–13 mi)[source] |
|---|
| Guidance system | Mid-course: FOG - INS + Mid-course update via datalink Terminal: ARH[source] | Nitrogen cooled passive InPb infrared seeker[source] |
|---|
| Launch platform | Su-30MKI MiG-29K Tejas Mk.1/1A MiG-29UPG (Trial-phase) HAL Tejas Mk2 (Planned) AMCA (Planned) TEDBF (Planned) Rafale Marine (Planned)[source] | aerial[source] |
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