Lockheed CL-475

CL-475

CL-475 flight testing at Edwards AFB
Role	Experimental helicopter
National origin	United States
Manufacturer	Lockheed
Designer	Irven Culver
First flight	2 November 1959
Status	On display
Number built	1

The Lockheed CL-475 (registration N6940C)^[1] is a two-seat, single-engine, light helicopter developed by Lockheed to explore rigid rotor technology. The CL-475 has a three-bladed main rotor and a two-bladed tail rotor. Only one was built.^[2]

Design and development

In 1958 Irv Culver presented to the Lockheed management an idea for how to rigidly attach the rotor blades of a helicopter to the hub. In 1920, Juan de la Cierva had tried the same concept, but had trouble controlling the rotor, because of excessive gyroscopic moments. Culver's research led him to believe that there was a way to control the excessive pitch and roll moments by incorporating a feedback system into the rotor. Culver's solution to high control moments was a device known as the "compliance factor". It kept the blades forward less than a degree, which would apply a corrective feathering input to the opposite blade. This essentially was the moment feedback system. Before presenting his ideas, he had built a radio-controlled model that demonstrated the feasibility of the concept. Lockheed gave him use of part of a flight test hangar, a flight test engineer and two mechanics.^[3]

The CL-475 is a two-seat helicopter with a fabric-covered steel and aluminum structure. The glazed cockpit provides side-by-side seating for two occupants. The landing gear is designed in a tricycle configuration, with two large wheels mounted alongside the bottom of the fuselage, and a nosewheel mounted underneath the cockpit. The helicopter is powered by a 140 hp (104 kW), four-cylinder, air-cooled Lycoming O-360-A1A piston engine. Designed to test a rigid-rotor concept, it originally utilized a two-bladed wooden rotor.^[2]

After completion at Burbank, the CL-475 was taken to Rosamond Lake on Edwards Air Force Base in the Mojave Desert for testing. It was first flown on 2 November 1959, but the pilot reported severe vibrations. For six months, Lockheed experimented with three and four-bladed wooden rotors, but stability was finally achieved by using metal blades in a three-blade configuration and the addition of a gyroscopic control ring connected directly to the swashplate.^[1] In the mid-1960s, the helicopter was test flown by a number of government and military agencies and the military. The stability offered by the rigid rotor control system made the helicopter easy to fly,^[2] and the lessons learned from the CL-475 rigid rotor were later used to develop the XH-51 and AH-56A Cheyenne.

In 1975, Lockheed donated the CL-475 to the National Air and Space Museum. The helicopter was loaned to the United States Army Aviation Museum at Fort Rucker, Alabama,^[1] but is currently in the museum's storage.^[4]

Specifications

Data from ^[2]

General characteristics

Crew: 2
Main rotor diameter: 32 ft 0 in (9.75 m)
Height: 9 ft 3 in (2.82 m)
Empty weight: 1625 lb (737 kg)
Gross weight: 2000 lb (907 kg)
Powerplant: 1 × Lycoming VO-360-A1A four-cylinder air-cooled piston engine, 140 hp (104 kW)

Performance

Maximum speed: 90 mph (145 km/h)
Range: 75 miles (120 km)
Service ceiling: 2,000 ft (610 m)

References

Notes

↑ 1.0 1.1 1.2 Francillon 1987
↑ 2.0 2.1 2.2 2.3 Francillon 1982, pp. 414-415
↑ Cefaratt, Gil, "Lockheed: The People Behind the Story", Turner Publishing Company, 2002, ISBN 978-1-56311-847-0.
↑ United States Army Aviation Museum. Rotary Wing Collection. United States Army Aviation Museum Association. 2 January 2003. Accessed on 13 July 2009

Bibliography

Wikimedia Commons has media related to Lockheed CL-475.

Francillon, René J. (1982). :Lockheed Aircraft since 1913. London: Putnam & Company. ISBN 0-370-30329-6.
Francillon, René J. Lockheed Aircraft Since 1913. Annapolis, Md: Naval Institute Press, 1987. ISBN 978-0-85177-805-1

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Lockheed-California Temporary Design Numbers	CL-282 CL-288 CL-295 CL-320 CL-325 CL-329 CL-346 CL-379 CL-400 CL-407 CL-475 CL-595 CL-704 CL-760 CL-823 CL-901 CL-915 CL-934 CL-981 CL-984 CL-985 CL-1026 CL-1195 CL-1200 CL-1400 CL-1600 CL-1700 CL-1800 CL-1980

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Lockheed CL-475

Design and development

Specifications

See also

References