Nord CT41

Starting development in 1957, the CT.41 used a canard configuration, with a short, straight wing located at mid-fuselage with wingtip-mounted ramjet engines.^[1] Launched using an elevating ramp,^[2] two solid rocket boosters provided initial thrust upon launch, with the ramjets igniting at a speed of Mach 1.7.^[3] Command guidance was used for control; the aircraft could be fitted with electronic enhancers and flares to boost its target signature.^[3] Two types were produced, the CT.41A for high-altitude use, and the CT.41B for low-altitude training. If the drone was not shot down, recovery was via parachute.^[3]

The CT.41 began test flights during 1959,^[2] with production starting later that year; 62 aircraft were constructed for use by the French Air Force. They had only a brief service life before being retired due to being too fast to provide practical training for interceptor pilots. Hawker Siddeley acquired a manufacturing license for the type in November 1960.^[2] Six were acquired by Bell Aircraft for evaluation by the United States Navy; Bell also acquired a production license for the type, which in 1962 received the U.S. designation PQM-56A. The PQM-56A was out of service by the early 1970s.^[3]

Data from Directory of U.S. Military Rockets and Missiles (2003)^[1][3]

General characteristics

• Crew: None
• Length: 9.80 m (32 ft 2 in)
• Wingspan: 3.73 m (12 ft 3 in)
• Height: 2.18 m (7 ft 2 in)
• Gross weight: 1,297 kg (2,860 lb)
• Max takeoff weight: 2,550 kg (5,622 lb) with boosters
• Powerplant: 2 × Type 625 ramjet

Performance

• Maximum speed: Mach 3.1
• Endurance: 14 minutes
• Service ceiling: 20,000 m (65,000 ft)

 

Wikimedia Commons has media related to CT.41.

• Parsch, Andreas (2003). "Nord/Bell CT.41/PQM-56". Directory of U.S. Military Rockets and Missiles. designation-systems.net. Retrieved 2014-05-09.