3.5-Inch Forward Firing Aircraft Rocket

Design and development

Following trials by the Royal Air Force of rocket-propelled, air-launched weapons for anti-submarine warfare during 1942 (which resulted in the adoption of the RP-3 by RAF Coastal Command), the United States Navy launched a high-priority project during the summer of 1943 for the development of an anti-submarine rocket of its own.

The resulting rocket was a simple design with four tail fins for stabilization at the rear, powered by a rocket motor that had been under development by Caltech since 1943. The warhead contained no explosive. The rocket's nose was a solid steel mass, weighing 20 lb, that punctured the pressure hull of a target submarine through the kinetic energy and momentum from its high velocity and mass. The nose of the 3.5" FFAR was given a relatively blunt conical shape that had been shown experimentally to give a maximum pitch-up as the rocket entered the water. This caused the rocket to shoot forward at a shallow depth deadly to submarines that were surfaced or traveling at snorkel or periscope depth. The rockets were launched in a shallow dive, since entry into the water at too steep an angle would defeat their ability to shoot forward at the required shallow depth. The rocket remained lethal even after passing through up to 130 ft of water, giving the pilot a target several times the actual size of the submarine. The sweet spot for targeting was considered to be 60 ft in front of the near side of the submarine. Typical firing range was about 1500 yd.

Operational history

Following expedited development, the weapon, officially designated the "3.5-inch forward firing aircraft rocket", entered operational service with the U.S. Navy late in 1943; production of 10,000 rockets per month had been ordered that August. The FFAR's first "kill" of an enemy submarine took place 11 January 1944. The rocket was originally carried by the Grumman TBF Avenger torpedo bombers. Excessive drag caused by the original 92 in channel-slide launchers was largely eliminated with the introduction of zero-length launchers in May 1945. Zero-length launchers quickly became standard on most fighters and many light bombers for firing a variety of rockets with 3.25" or 5" diameter rocket motors.

Although the rocket's accuracy was more than sufficient to allow usage against surface targets, the narrow body diameter restricted the size of any explosive warhead that could be fitted. Therefore, for use against ships and land targets, the rocket was given a warhead consisting of a 45 lb re-fused 5" (127 mm) Mark 35 artillery shell, producing the 5-inch forward firing aircraft rocket, usually shortened to 5" AR.

References

;Citations ;Bibliography

References

1. Parsch 2004
2. von Braun and Ordway 1975, p.98.
3. Campbell 1985, p.170.
4. C. W. Snyder, Caltech's ''Other'' Rocket Project: Personal Recollections, pp. 7-10, Engineering & Science, Spring 1991
5. E.W. Price, C.L. Horine, and C.W. Snyder (July 1998). "EATON CANYON, A History of Rocket Motor Research and Development in the Caltech-NDRC-Navy Rocket Program, 1941-1946,". 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Cleveland, Ohio. AIAA.
6. Friedman 1982, p.198.
7. Parsch 2006