Radioplane RP-77D target drone
|Place of origin||United States|
|Used by||United States Army|
|Weight||1,050 pounds (480 kg)|
|Length||14.9 feet (4.53 m)|
|Engine||Boeing 502 turboprop
285 shaft horsepower (213 kW)
|Wingspan||15.3 feet (4.66 m)|
|Flight ceiling||47,000 feet (14,000 m)|
|Speed||425 miles per hour (684 km/h)|
The Radioplane RP-77 was a small target drone missile, constructed largely of plastic materials, produced by the Radioplane division of the Northrop Corporation. Although the RP-77D was successfully tested by the United States Army, the decision was made not to procure the aircraft.
Design and development
The development of the RP-77 began in 1955. Similar in outline to Radioplane's earlier OQ-19, four prototypes of the RP-77 were constructed, two each of the RP-77, powered by a four-cylinder McCulloch piston engine, and of the RP-77A, powered by a six-cylinder Lycoming engine. Results of flight-testing were insufficient to interest the U.S. Army, however in 1957 a proposal for an improved RP-77D, powered by a Boeing 502 turboprop, resulted in a contract for the construction of 20 aircraft.
The design of the RP-77D made extensive use of glass-polyester plastic materials. The drone was launched using a rocket-assisted take-off system consisting of four Loki rockets, and was fitted with a radio control apparatus that, with the assistance of radar tracking, allowed the drone to be operated at a considerable distance from its launching point. In addition to equipment typically carried by target drones, the RP-77D could be equipped with reconnaissance or meteorological sensors, or with air sampling equipment. The RP-77D utilised the RPTA tracking system, developed by Radioplane, using audio frequency tones for control. Tip tanks allowed for carriage of additional fuel to extend the aircraft's range, and recovery at the end of the flight was by parachute.
Following its maiden flight in March 1958, evaluation of the RP-77D by the U.S. Army took place throughout the remainder of that year, nearly 40 test flights being conducted. Although the test results were generally satisfactory, it was determined that the performance of the aircraft was an insufficient improvement over existing types in service to have the aircraft ordered into production, and the project was cancelled, along with the improved RP-86, a dedicated reconnaissance variant.
Following the termination of the Army's evaluation, Radioplane, as a private venture, conducted an improvement program for the RP-77D, fitting the aircraft with a larger wing, along with other modifications that improved the performance of the drone. However these improvements were insufficient to produce a renewed interest from the Army.
- Proposed version of RP-77A with turbo-supercharged Lycoming SO-360M engine, none built.
- Proposed reconnaissance version of RP-77D; none built.
- Crew: None
- Length: 14 ft 10 in (4.53 m)
- Wingspan: 15 ft 3 in (4.66 m)
- Height: 5 ft 2 in (1.58 m)
- Gross weight: 1,050 lb (476 kg)
- Powerplant: 1 × Boeing 502-10F turboprop, 285 shp (213 kW)
- Propellers: 2-bladed
- Maximum speed: 425 mph (684 km/h; 369 kn)
- Endurance: One hour at 40,000 feet
- Service ceiling: 47,000 ft (14,326 m)
- Aircraft of comparable role, configuration and era
- Duffin, Daniel J. (1958). Laminated Plastics. Reinhold Plastics Applications Series. New York: Reinhold Publishing Corporation. ASIN B0000CK84G.
- Erickson, Jack (2009). "Lycoming, Avco Lycoming, Textron Lycoming (US) Part 1: Introduction and O-145 through O-365". Horizontally-Opposed Piston Aero Engines. Retrieved 2010-12-21.
- International Aeronautic Federation, 1961. Interavia. Jane's Information Group.
- Jane, Fred T., et al. (1958) Jane's All The World's Aircraft. London: S. Low, Marston & Company.
- Merrill, Arthur M, 1956. Plastics Technology, Volume 2.
- Parsch, Andreas (2004). "RP-77D". Directory of U.S. Military Rockets and Missiles, Appendix 4: Undesignated Vehicles. designation-systems.net. Retrieved 2010-11-25.
- Royal Aeronautical Society, 1959. The Aeronautical Journal, Volume 63.