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At a glance
AAM-5 (missile)larger figure on 0 of 3
AIM-54 Phoenixlarger figure on 3 of 3
Counts only measures both sources give with the same scope. A larger figure is not a better system.
Measured figures
Configuration
| Specification | AAM-5 (missile) | AIM-54 Phoenix |
|---|---|---|
| Type | Short-range air-to-air missile[source] | Long range BVR air-to-air missile[source] |
| Place of origin | Japan[source] | United States[source] |
| In service | 2004–present[source] | 1974–present[source] |
| Used by | Japan Air Self-Defense Force[source] | United States Navy (former) Iranian Air Force |
Length
Single source12 ft 9 + 1 ⁄ 2 in (3.9 m)[source]
Maximum; AIM-54A/B - Mach 4.3 (
Single sourceMaximum; ) AIM-54C – Mach 5 (
Single sourceMaximum; Maximum speed · source measurement 3
Single sourceMaximum; Maximum speed · source measurement 4
Single sourceAIM-54A/B - Mach 4.3 (1,460 m/s; 4,800 ft/s) AIM-54C – Mach 5 (1,700 m/s; 5,600 ft/s)[source]
Warhead weight
Single source133 lb (60.33 kg)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| Manufacturer | Mitsubishi Heavy Industries[source] | Hughes Aircraft Company Raytheon Corporation[source] |
|---|
| Unit cost | 55–60 million yen[source] | US$ 477,131 (1974 FY)[source] |
|---|
| Warhead | blast-frag[source] | AIM-54A/B - HE continuous rod AIM-54C – HE Mk 82; WDU‐29/B continuous rod[source] |
|---|
| Detonation mechanism | laser proximity fuze and impact[source] | Proximity fuze[source] |
|---|
| Propellant | solid fuel rocket[source] | — |
|---|
| Guidance system | Infrared homing AAM-5: (IIR + INS) AAM-5B: ((Dual Wavelength) IIR + INS)[source] | Semi-active radar homing and terminal phase active radar homing[source] |
|---|
| Guidance | AAM-5A: Terminal IIR, INS)[source] | — |
|---|
| Role | short-range air-to-air missile[source] | — |
|---|
| Source measurement | Enhanced background discrimination capability and IRCCM by changing to a dual wavelength seeker and a 3-axis gimbal. Seeker cooling time is extended by the adoption of a Stirling engine , up to a maximum cooling time of 1 hours.[source]AAM-5 (missile) · Variants; only the objects and conditions stated in this passage Length: 3,105 mm[source]AAM-5 (missile) · Specifications; only the objects and conditions stated in this passage Diameter: 130 mm[source]AAM-5 (missile) · Specifications; only the objects and conditions stated in this passage Wing span: 440 mm[source]AAM-5 (missile) · Specifications; only the objects and conditions stated in this passage Weight: 95 kg[source]AAM-5 (missile) · Specifications; only the objects and conditions stated in this passage Range: 35 km[source]AAM-5 (missile) · Specifications; only the objects and conditions stated in this passage | — |
|---|
| Designer | — | Hughes Aircraft Company[source] |
|---|
| Designed | — | 1960–1966[source] |
|---|
| Produced | — | 1966-1993[source] |
|---|
| Engine | — | Solid propellant rocket motor[source] |
|---|
| Flight ceiling | — | 103,500 ft (31.5 km)[source] |
|---|
| Launch platform | — | Grumman F-14 Tomcat[source] |
|---|
| References | — | Janes[source] |
|---|
| Reported operators | — |
|
|---|
AIM-54A/B - 72.9 nmi (135.0 km; 83.9 mi) AIM-54C – 99.4 nmi (184.1 km; 114.4 mi)[source]