The AIM-54 Phoenix (Airborne Interception Missile) is a radar guided air to air missile that was used alongside its more popular compatriots, the AIM-9 Sidewinder and AIM-7 Sparrow, and used operationally with the AWG-9 radar system mounted on the F-14A and F-14B Tomcat. This missile is the grandfather of all Fox-3 active radar homing missiles used in today’s modern air to air battlefield.
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Here’s a brief explanation of how the AIM-54 Phoenix works utilizing the super small amount of information that is available to the public:
Guidance Modes:
The AIM-54’s operates in 4 distinct modes, 3 of which will be important to gameplay in WT. Those 3 modes are sample data semi-active (datalink mid-course guidance), continuous semi active (Fox-1 mode basically), and active (Fox-3 fire and forget). For a pretty good explanation of the AIM-54 guidance, I’ll direct you to a thesis written about the AIM-54 and AWG-9 system written by Naval Undergraduate Stephen Thornton Long[1].
The sample data semi-active, like stated in the document above, is used during the mid-course guidance phase of a TWS missile shot prior to the missile going “pitbull” or fully radar active. Once the missile is active, the firing aircraft no longer has to support the missile and can turn away. The AIM-54 will be fired in a Fox-1 mode (continuous semi-active) when the AIM-54 is fired in a PD-STT (Pulse Doppler Single Target Track) at a target. This mode doesn’t not allow for the AIM-54 to go active in any way (unless fired within 10nms) and will basically be a super long range AIM-7. The AIM-54 can be fired in an active mode off the rail when ether in P-STT (Pulse Single Target Track), PH ACT switch is selected in the RIO seat, a TCS track is used, the missile is fired within 10nms of the target, or ACM cover is lifted upwards (which disregards any prior radar modes i.e. disregards if you’re in PD-STT or TWS, that missile is going active off the rail). An exception is used for P-STT and PH-ACT when used outside of a the seeker’s own detection range: the AIM-54 will fall back to the AWG-9’s datalink guidance and guide on that course using that guidance until it detects the target with its own seeker.
This datalink guidance (not to be confused with military tactical data links like Link-16 or Link-4) uses the AWG-9’s pulse signals, datalink transmitter at the tail of the AIM-54, and the antenna of the AIM-54 itself in order to give mid-course guidance to the missile.
Lofting:
The AIM-54 does not loft when:
- Using P-STT to fire a missile
- PH ACT switch is engaged
- ACM cover is up
- If fired within 10nms of the target
Active Distance :
The AIM-54 can have varying active distances depending on the target size switch in the RIO’s pit as this switch changes when the AWG-9’s WCS sends the active command to the missile.
- Target size small sends the active signal at 6 nms
- Target size normal sends the active signal at 10 nms
- Target size large sends the active signal at 13 nms
The Phoenix Evolution and Performance
Major Variants:
AIM-54A
Without going into the history of the precursor systems that eventually led to the development of the AIM-54, the development of the AIM-54 Phoenix (AAM-N-11 Phoenix at the time) began in 1960 by Hughes with it being redesignated the AIM-54A in 1962. The Phoenix was developed initially to face the ever growing threat of Soviet bombers carrying anti-ship missiles against US carriers. The missile was then optimized to face that threat along with fighter aircraft. Initially intended to be mounted on the F-111B, it was later mounted on the F-14 platform after the F-111B was cancelled. The first production AIM-54A missiles were delivered in 1973 and were ready for deployment with the first F-14A squadron (VF-1 Wolfpack on the USS Enterprise) in 1974 during the first F-14 deployment. AIM-54As during airborne testing had achieved a success rate of 88% during its test program. Most famously in 1973, an F-14A was able to fire 6 AIM-54As at various target drones within 37 seconds at ranges up to 43.19 nms (80 kms) with 4 scoring direct hits, 1 missing due to the target drone veering off course due to a malfunction, and 1 missing due to a hardware failure. These were determined that if there were no hardware malfunctions, the missiles would have hit the targets. Initial AIM-54A production would eventually end in 1981.
Sidenote: AIM-54As can be distinctly differentiated from AIM-54Cs because they’re all painted white compared to AIM-54Cs (which initially came in white but were later phased out with grey as their standard color).
There were several subvariants/improvements of the AIM-54A that are known specifically about what the exact improvements did in terms of performance.
- Reject Image Device (RID) offered improved capabilities against low altitude targets over water, and was incorporated during production of later missiles.
- Extended Active Gate (EAG) improved the missile’s resistance to certain ECM threats, and was also a production feature of later missiles.
- High Altitude Performance (HAP) modification improved performance against very high-altitude and high-speed targets.
There were also 2 distinct variants of motors used by the AIM-54A. There was one made by Rocketdyne utilizing their Mk47 Mod 0 motor. This was initially found to be substandard construction and reliability when initially delivered so a secondary company, Aerojet, utilizing their Mk60 motor. There were several differences with these motors even though they were all designated the MXU-637/B. Aerojet production of the Mk60 motor would eventually end by 1978.
- Burn Time
- The Aerojet Mk60 burned for
3020.6 seconds while the Rocketdyne Mk47 Mod 0 burned for 27 seconds
- The Aerojet Mk60 burned for
IspAerojet Mk60 had an estimated Isp of 250 while the Rocketdyne Mk47 Mod 0 had an Isp of 252
- Thrust
- The Aerojet Mk60 produced around 17000Ns of thrust compared to the roughly 15000Ns of the Rocketdyne Mk47 Mod 0
WeightThe Mk60 motor weighed approx. 256 kgs while the Mk47 motor weight 201 kgs. Their respective fuel weights were 208 kgs and 163 kgs.
- Propellant
- The Mk47 Mod 0 used Flexadyne (tradename for CTPB but formulation might be different) while the Mk60 used CTPB.
Even with these differences, the missile was still rated to the same top speed, range, and altitude.
AIM-54A Performance
- Length: 13.15 ft (401 cm)
- Finspan: 36.41 in (92.5 cm)
- Diameter: 14.96 in (38 cm)
- Weight: 978.85 lbs (444 kgs) | Up to 1000 lbs by 1999
With Aerojet Mk60 Motor: 987.01 lbs (447.7 kgs)With Rocketdyne (later Hercules) Mk47 Mod 0 Motor: 1039.92 lbs (471.7 kgs)
- Speed: Mach 4.3
- Propulsion:
- Aerojet Mk60
- Thrust: 17,020.4N for
3020.6 seconds
- Thrust: 17,020.4N for
- Rocketdyne (later Hercules) Mk47 Mod 0
- Thrust: 13,595N for 27 seconds
- 1970s Document (one of the only definitive data sources we have regarding the AIM-54’s motor performance for any variant)
- Thrust: 4000 lbf (17793 N) for 24+ seconds (dependent on altitude)
- Total Impulse: 97000 lbs
- Aerojet Mk60
- Guidance duration: 160 seconds minimum
- Warhead: 133.77 lbs (60.68 kg) Mk82 Mod 0 blast fragmentation and impact fuse
- Detection Device: DSU-28/A
- Safety Fuse: FSU-10/A
- Detonation distance: 50 feet (15 meters)
- Guidance type: Sample data semi-active, continuous semi-active, active, home-on jam
- Maneuvering capability: At least 18Gs
- Max Launch Altitude: 48,800 ft (14,878 m)
- Max Missile Altitude : 81,400 ft (24,817 m)
- Min Range: 2.1 nm (203.25 m)
- Max Range: 107.92nm (200 km)
AIM-54C
Development of an improved AIM-54 variant began in 1976. The 1979 Iranian Revolution had accelerated the development of an improved AIM-54 due to the AIM-54As that were sent to Iran to equip their air force’s F-14A Tomcats being potentially compromised. In August of the same year, the first development models were completed. By 1981, the first AIM-54Cs were delivered. By the next year, production of the AIM-54A had switched over to production of the AIM-54C. Initial Operational Capability of the AIM-54C was reached in 1984. The AIM-54C features a completely new digital WGU-11/B guidance and WCU-7/B control sections. With the progression of computer technology, they were able to integrate a programmable digital signal processor and an autopilot that uses a strap-down inertial navigation system. All while improving the ECCM capability of the missile. This INS system was later used as the bases for the AIM-120 AMRAAM. It was touted that the missile had improved range and speed thanks to an improved motor. However I was unable to find any statistics to substantiate this claim outside of a new Mk47 Mod 1 motor that incorporated a reduced smoke signature. There was a new DSU-28/B target detection device which improved the fusing accuracy in high-clutter environments and for small and low-altitude targets.
Sidenote: Rocketdyne’s McGregor, Texas factory, which produced the Mk47 motor, was sold to Hercules Inc. in 1978 so the motor might also be called the Hercules Mk47 motor.
AIM-54C Performance
- Length: 13.15 ft (401 cm)
- Finspan: 36.41 in (92.5 cm)
- Diameter: 14.96 in (38 cm)
- Weight:
1026.47 lbs (465.6 kgs)1000.9 lbs (454 kgs) | 1020-1040 lbs depending on configuration - Speed: Mach 5+
- Propulsion:
- Rocketdyne (later Hercules) Mk47 Mod 1
- Propellant type: HTPB
- Thrust: 13,595N for 27 seconds
- Aerojet Mk60 (some squadrons equipped their AIM-54Cs with their remaining Mk60 motors)
- Propellant type: CTPB
- Thrust: 17,793N for 20.6 seconds
- Rocketdyne (later Hercules) Mk47 Mod 1
- Guidance duration: 160 seconds minimum
- Warhead:
- 133.77 lbs (60.68 kg) Mk82 Mod 0 warhead blast fragmentation and impact fuse (serial number 83001 through 83054)
- Detection Device: DSU-28
- Safety Fuse: FSU-10/A
- Detonation distance: 50 feet (15 meters)
- 133.77 lbs (60.68 kg) WDU-29/B blast fragmentation and impact fuse warhead in a WAU-16/B or WAU-20/B (serial number 83055 to end of production)
- Detection Device: DSU-28/B
- Safety Fuse: FSU-10/A
- Detonation distance: 50 feet (15 meters)
- 133.77 lbs (60.68 kg) Mk82 Mod 0 warhead blast fragmentation and impact fuse (serial number 83001 through 83054)
- Guidance type: Sample data semi-active, continuous semi-active, active, home-on jam
- Maneuvering capability: At least 18Gs but more maneuverable than the AIM-54A
- Max Launch Altitude: 60,000 ft (18,292.68 m)
- Max Missile Altitude : 100,000 ft (30,487.81 m)
- Min Range: 2.1 nm (203.25 m)
- Max Range: 107.92nm+ (200 km+)
AIM-54C+ (AIM-54C ECCM/Sealed)
First delivered in 1985 as a configuration Engineering Change Proposal (ECP) to the AIM-54C, the AIM-54C+ or AIM-54C ECCM/Sealed was the final known major operational improvement variant of the AIM-54. This variant featured improved ECCM performance along with finally removing the need for externally bottled coolant to be used as the missile was now cooled with its own internally provided coolant supply. With the LAU-132A pylons on the F-14D, they no longer carried coolant bottles and reduced the weight and complexity. By the year 2000, all the AIM-54s left in the US Navy’s inventory was AIM-54Cs, with all AIM-54As being expended. The AIM-54 was later retired in 2004, 2 years before the F-14 Tomcat itself was retired from service.
Sidenote: The AIM-54A and the earlier AIM-54C both had the requirement for external coolant that brought more external weight along with extra complexity. The coolant bottle was stored in the LAU-93 pylon itself and therefore necessitated that the front 2 AIM-54 fuselage pylons in order for early AIM-54s to be fired (as the rear and glove pylons didn’t carry a coolant bottle). It is said that these cooled AIM-54s could be fired from the LAU-132A pylons of the F-14D even though they didn’t have cooling. The aircraft would have to be confined to stricter launch parameters. The name coolant used is a bit of a misnomer since it is intended to keep the internals of the AIM-54 from getting too cold at the harsher environments of high altitude flight.
AIM-54C+ (AIM-54C ECCM/Sealed) Performance
- Length: 13.15 ft (401 cm)
- Finspan: 36.41 in (92.5 cm)
- Diameter: 14.96 in (38 cm)
- Weight: 1023 lbs (464.025 kg)
- Speed: Mach 5+
- Propulsion:
- Hercules Mk47 Mod 1
- Propellant type: HTPB
- Thrust: 13,595N for 27 seconds
- Hercules Mk47 Mod 1
- Guidance duration: 160 seconds minimum
- Warhead:
- 133.77 lbs ( 60.68 kg) WDU-29/B blast fragmentation and impact fuse warhead in a WAU-16/B or WAU-20/B
- Detection Device: DSU-28/B
- Safety Fuse: FSU-10/A
- Detonation distance: 50 feet (15 meters)
- 133.77 lbs ( 60.68 kg) WDU-29/B blast fragmentation and impact fuse warhead in a WAU-16/B or WAU-20/B
- Guidance type: Sample data semi-active, continuous semi-active, active, home-on jam
- Maneuvering capability: At least 18Gs but more maneuverable than the AIM-54A
- Max Launch Altitude: 60,000 ft (18,292.68 m)
- Max Missile Altitude : 100,000 ft (30,487.81 m)
- Min Range: 2.1 nm (203.25 m)
- Max Range: 107.92nm+ (200 km+)
Sources:
- See the post on the old forum.
Obviously, not all the data will be 100% accurate so I would love you guy’s support if you guys are able to pitch in and help aggregate sources in improving the understanding of this missile.
