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At a glance
Astra (missile)larger figure on 1 of 1
PF-89larger figure on 0 of 1
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
Single sourceConfiguration
| Specification | Astra (missile) | PF-89 |
|---|---|---|
| Speed | Mk-1: Mach 4.5[source] | — |
| Type | Beyond-visual-range air-to-air missile[source] | Anti-tank, anti-bunker[source] |
| Place of origin | India[source] | China[source] |
| In service | 2019 ( 2019 ) –present[source] | 1993–present[source] |
| Used by | Indian Air Force Indian Navy |
900 mm (2 ft 11 in)[source]
single-use, disposable
Single source1 (single-use, disposable)[source]
Operational; Mk-1
Single sourceOperational; Mk-2
Single sourceOperational; Mk-3
Single sourceMk-1: 110 km (68 mi) Mk-2: 240 km (150 mi) Mk-3: 350 km (220 mi)[source]
Effective; Effective firing range
Single sourceMaximum; Maximum firing range
Single sourceWarhead weight
Single source15 kg (33 lb)[source]
Muzzle velocity
Single source147 m/s (480 ft/s)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
See Users[source] |
| Wars | 2025 India–Pakistan conflict[source] | — |
|---|
| Designer | Defence Research and Development Laboratory ( DRDO )[source] | China North Industries Group Corporation[source] |
|---|
| Manufacturer | Bharat Dynamics Limited[source] | Norinco[source] |
|---|
| Unit cost | Mk-1: ₹ 7−8 crore (US$−830,000)[source] | — |
|---|
| Produced | 2017 − Present[source] | 1989[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] | — |
|---|
| Detonation mechanism | Mk-1: Radio proximity fuze Mk-2: Optical proximity fuze[source] | — |
|---|
| Engine | Mk-1: Solid-propellant rocket Mk-2: Dual-thrust pulsed rocket motor Mk-3: Solid Fuel Ducted Ramjet[source] | — |
|---|
| Propellant | Solid fuel[source] | — |
|---|
| Flight ceiling | 20 km (66,000 ft)[source] | — |
|---|
| Guidance system | Mid-course: FOG - INS + Mid-course update via datalink Terminal: ARH[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] | — |
|---|
| Designed | — | 1980s[source] |
|---|
| Cartridge | — | 80×900 mm rocket-assist grenade[source] |
|---|
| Cartridge weight | — | 1.84 kg (4.1 lb)[source] |
|---|
| Action | — | Single-shot[source] |
|---|
| Sights | — | Optical 2.5x (day sight)[source] |
|---|
| Reported operators | — |
|
|---|