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At a glance
Aspidelarger figure on 0 of 1
Astra (missile)larger figure on 1 of 1
Counts only measures both sources give with the same scope. A larger figure is not a better system.
Measured figures
Air to air
Single sourceSurface to air
Single sourceSurface to air: 80 cm (31 in) Air to air: 100 cm (39 in)[source]
Effective; Aspide Mk. 1 for air to air Aspide 2000: >
Single sourceEffective; Aspide Mk. 1 for surface to air · source measurement 1
Single sourceEffective; Aspide Mk. 1 for surface to air · source measurement 3
Single sourceAspide Mk. 1: 15 km (9.3 mi) for surface to air 40 km (25 mi) for air to air Aspide 2000: > 25 km (16 mi) for surface to air[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]
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.
Configuration
| Specification | Aspide | Astra (missile) |
|---|---|---|
| Speed | Mach 5[source] | Mk-1: Mach 4.5[source] |
| Type | Medium range Surface to air missile / Air to air missile[source] | Beyond-visual-range air-to-air missile[source] |
| Place of origin | Italy[source] | India[source] |
| In service | 1977-present[source] | 2019 ( 2019 ) –present[source] |
| Wars | Russo-Ukrainian War[source] | 2025 India–Pakistan conflict[source] |
| Manufacturer | Selenia (former), MBDA Italy[source] | Bharat Dynamics Limited[source] |
| Produced | 1973-present[source] | 2017 − Present[source] |
| Warhead | 35 kg (77 lb)[source] | High-explosive pre- fragmented HMX / PU[source] |
| Guidance system | semi-active radar homing[source] | Mid-course: FOG - INS + Mid-course update via datalink Terminal: ARH[source] |
| Used by | — | Indian Air Force Indian Navy[source] |
| Designer | — | Defence Research and Development Laboratory ( DRDO )[source] |
| Unit cost | — | Mk-1: ₹ 7−8 crore (US$−830,000)[source] |
| Variants | — | Mk-1 (Operational) Mk-2 (LSP) Mk-3 (Trial-phase) VL-SRSAM (Trial-phase)[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] |
| 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] |