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Sikorsky R-4
The Sikorsky R-4 was a two-seat helicopter designed by Igor Sikorsky with a single, three-bladed main rotor and powered by a radial engine. The R-4 was the world's first large-scale mass-produced helicopter and the first helicopter used by the United States Army Air Forces,〔("Fact Sheet: Sikorsky R-4" ). ''National Museum of the United States Air Force''. Retrieved: 26 September 2010.〕 Navy, Coast Guard, and the United Kingdom's Royal Air Force and Royal Navy.
==Development==
The VS-316 was developed from the famous experimental VS-300 helicopter, invented by Igor Sikorsky and publicly demonstrated in 1940. The VS-316 was designated the XR-4, under the United States Army Air Forces' series for "Rotorcraft". The XR-4 made its initial flight on 13 January 1942 and was accepted by the Army on 30 May 1942. The XR-4 exceeded all the previous helicopter endurance, altitude and airspeed records that had been set before it. The XR-4 completed a 761-mile (1,225 km) cross country flight from Connecticut to Wright Field, Ohio, set a service ceiling of 12,000 feet (3,700 m), 100 flight hours without a major incident, and an airspeed approaching 90 mph (140 km/h).〔McGowen 2005, p. 29.〕
The British Admiralty, having learned of the VS-300, made a ship available that had been intended to show the USN their work with autogyros and ship operations. The ''Empire Mersey'' was fitted with a landing platform. After her loss in 1942 to a U-boat, she was replaced by the SS ''Daghestan''.〔Cocker 2008, p. 114.〕 The first deck landing trials on ''Daghestan'' were carried out in 1944〔 The British would receive two of the first eight helicopters built.
On 5 January 1943, the United States Army Air Forces ordered 29 prototypes.〔 The first three prototypes were designated as the YR-4A and used for evaluation testing. The YR-4A benefited from a larger, 180 hp (130 kW) Warner Super Scarab (R-550-1) engine, compared to the 165 hp (123 kW) R-500-3 engine in the prototype, and a rotor diameter increased by one foot (30 cm). Evaluation of the YR-4A demonstrated a need for further improvements, including moving the tailwheel further towards the rear of the tailboom, venting the exhaust to the side instead of downward, and increasing the fuel capacity by five gallons (19 liters). These and other design changes led to the designation of later prototypes as YR-4B, which were used for service testing and flight training.
抄文引用元・出典: フリー百科事典『 ウィキペディア（Wikipedia）』
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