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At a glance
AAM-4larger figure on 3 of 4
Astra (missile)larger figure on 1 of 4
Counts only measures both sources give with the same scope. A larger figure is not a better system.
Measured figures
Length
Single source12 ft (3,667 mm)[source]
Length
Single sourceConfiguration
| Specification | AAM-4 | Astra (missile) |
|---|---|---|
| Type | Beyond-visual-range air-to-air missile / surface-to-air missile[source] | Beyond-visual-range air-to-air missile[source] |
| Place of origin | Japan[source] | India[source] |
| In service | September 1999 ( 1999-09 ) –present[source] | 2019 ( 2019 ) –present[source] |
| Used by | See Operators[source] Japan Air Self-Defense Force |
3.84 m (12.6 ft)[source]
AAM-4
Single sourceAAM-4B
Single sourceOperational; AAM-4
Single sourceOperational; AAM-4B
Single sourceOperational; AAM-4TDR
Single sourceAAM-4: 46 nmi (85 km) AAM-4B: 65 nmi (120 km) AAM-4TDR: 92 nmi (170 km)[source]
70 km (AAM-4), 120 km (AAM-4B )[source]
Operational; Mk-1
Single sourceOperational; Mk-2
Single sourceBars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
Indian Air Force Indian Navy[source] |
| Manufacturer | 1999–present – Mitsubishi Heavy Industries[source] | Bharat Dynamics Limited[source] |
|---|
| Unit cost | US$450,000[source] | Mk-1: ₹ 7−8 crore (US$−830,000)[source] |
|---|
| Variants | AAM-4, XRIM-4, AAM-4B, AAM-4TDR[source] | Mk-1 (Operational) Mk-2 (LSP) Mk-3 (Trial-phase) VL-SRSAM (Trial-phase)[source] |
|---|
| Warhead | High explosive Directional blast-fragmentation[source] | High-explosive pre- fragmented HMX / PU[source] |
|---|
| Detonation mechanism | 4-Quadrant Radar Proximity fuse , impact fuse[source] | Mk-1: Radio proximity fuze Mk-2: Optical proximity fuze[source] |
|---|
| Blast yield | 16.2kg TNT Equivalent[source] | — |
|---|
| Engine | Two-stage Solid-fuel rocket motor[source] | Mk-1: Solid-propellant rocket Mk-2: Dual-thrust pulsed rocket motor Mk-3: Solid Fuel Ducted Ramjet[source] |
|---|
| Guidance system | Fuzzy guidance logic Mid-Course: Inertial guidance , datalink , SARH Terminal: Active radar homing , inertial guidance , datalink[source] | Mid-course: FOG - INS + Mid-course update via datalink Terminal: ARH[source] |
|---|
| Steering system | AAM-4/4B: 25G maximum overload[source] | — |
|---|
| Launch platform | F-15J , F-2[source] | Su-30MKI MiG-29K Tejas Mk.1/1A MiG-29UPG (Trial-phase) HAL Tejas Mk2 (Planned) AMCA (Planned) TEDBF (Planned) Rafale Marine (Planned)[source] |
|---|
| References | Japanese Ministry of Defense , MHI[source] | — |
|---|
| Guidance | inertial guidance , datalink , semi-active radar homing , active radar homing[source] | — |
|---|
| Wars | — | 2025 India–Pakistan conflict[source] |
|---|
| Designer | — | Defence Research and Development Laboratory ( DRDO )[source] |
|---|
| Produced | — | 2017 − Present[source] |
|---|
| Propellant | — | Solid fuel[source] |
|---|
| Flight ceiling | — | 20 km (66,000 ft)[source] |
|---|
Operational; Mk-3
Single sourceMk-1: 110 km (68 mi) Mk-2: 240 km (150 mi) Mk-3: 350 km (220 mi)[source]