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Piasecki PV-15 / H-16 / H-27

piask-pv-15

 

A USAF requirement for a wide-ranging helicopter capable of rescuing downed strategic bomber crews had given rise to the new helicopter. The hefty fuel capacity required to meet its specified 2250km range in part dictated its size. Without the extra fuel, the capacious aircraft also had possible military application as a large troop and cargo transport. In 1946 the Army Air Forces awarded Piasecki Aircraft a contract for the development of a tandem rotor helicopter intended for use in the long-range search and rescue (SAR) role. The resultant Piasecki Model PV-15 was originally given the military designation XR-16 (R denoting rotorcraft under the World War II system), though this was changed to XH-16 in June 1948. The Air Force placed an order for two service test and evaluation aircraft in June 1949, and subsequently allocated the serial numbers 50-1269 and -1270 for these machines.

 

Piask-Yh-16-2

 

At the time of its inception the H-16 was the largest helicopter in the world. Though originally intended for the SAR role the Transporter, as the H-16 was ultimately named, evolved during the design process into a heavy-lift craft equipped with a tail loading ramp and optimized for troop and cargo transport. In this role the aircraft could carry up to forty troops or three light trucks within its fuselage, the interior of which was kept clear of obstructions by mounting the engines and all dynamic components in the upper fuselage. The H-16 was also capable of transporting large exterior cargo pods, and was equipped with variable-height landing gear legs in order to accommodate pods of varying sizes.

It had tandem three-blade rotors, and two engines, one at the front and the other in the rear of the fuselage. The rear engine drove the rotor at the top of a tail pylon nearly 4m high. The helicopter had a horizontal stabilizer, to which vertical control surfaces were later added in order to overcome problems of directional stability during fast flight. It weighed 14 tonnes on take-off with two pilots and 40 equipped infantry on board.

It was 23.8m long and topped by two overlapping rotors each 25m in diameter. In-flight vibration was low and of a loping nature. Bonded and tapered all-metal rotor blades (built using a new company process) combined milled-aluminum skins, aluminum honeycomb filler, and a leading-edge balance weight that also served as a mechanical fastener for the skins.

These capabilities appealed to the U.S. Army, which saw in the H-16 an answer to several helicopter mission requirements of its own. It therefore joined the USAF in sponsoring further development of the YH-16.

The first Transporter (serial 50-1269) was powered by two 1650hp Pratt & Whitney piston engines and made its first flight on 23 October 1953 at Philadelphia International Airport, designated YH-16. Company personnel and military officials watched the helicopter take off, hover, and fly forward and sideways during a successful twelve-minute maiden hop flown by Harold Peterson and Phil Camerano.

The Air Force ultimately decided against procuring the H-16 for operational use, and in 1955 the YH-16 was turned over to the Army for evaluation. The Army found the piston-driven Transporter to be underpowered and therefore awarded the reorganized Vertol company a contract for the machine's conversion to turbine power.

During construction the second prototype (50-1270) was modified to Model PV-45 (first designated H-27 and then H-16A) standard through the replacement of its piston engines with two 1800shp Allison T38-A-6 turboshafts, and modified to carry up to fifty troops, and redesignated YH-16B. The change in powerplants and inclusion of various structural modifications prompted a redesignation to XH-27 in October 1952, though this was changed to YH-16A prior to the aircraft's first flight in July 1955 with Harold Peterson and George Callaghan at the controls. This aircraft set an unofficial world record of 270km/h in 1956. Both H-16 variants were at times fitted with varying types of experimental horizontal tail surfaces, one of which incorporated large end-plate rudders, but none of these designs were adopted for permanent use.

Despite timprovements the type was ultimately judged to be unsuited to sustained operations under field conditions, and the Army terminated the H-16 test programme in mid-1956.

 

Piask-YH16-4
YH-16

 

In December, the YH-16A broke apart in the air and crashed near the Delaware River, killing Peterson and Callaghan as they returned from a test flight in New Jersey. Investigators determined that the rear rotor shaft had failed, allowing the blades to desynchronize and wobble into the plane of those of the forward rotor. In fact, a frozen bearing in the test instrumentation had precipitated this failure by allowing a steel-tube standpipe, placed within the aluminum rotor shaft to guide wires from the instrumented blades, to undetectably inscribe a deepening groove within the shaft.

This accident caused the H-16 program to be scrapped, preempting the sixty-nine-passenger YH-16B Turbotransporter (a conversion of the YH-16 then in progress), which would have flown with two 3700shp Allison T56 engines. It also preempted Frank Piasecki's vision of interchangeable under-body pods for the rapid transport of differing loads such as field operating rooms, communications centers, and mobile repair centers. A tall stilt landing gear had already been designed to let the YH-16B accommodate such pods.

 

  Piask-YH-16

 

YH-16
Engines: two 1,650 h.p. Pratt & Whitney R2180-11
Rotors: 2 x 3-blade main rotors in tandem.
Rotor diameter: 25m / 85 ft
Fuselage length: 23.8m / 78 ft
Loaded weight: Over 30,000 lb
Max speed: Over 130 mph
Capacity: 32 stretchers, 3 jeeps or 40 troops.

 

YH-16A
Engine: 2 x Allison YT-38A-10 turboshaft, 1800 / 1340kW
Rotor diameter: 24.99m
Length: 23.65m
Height: 7.62m
Max take-off weight: 15244kg
Empty weight: 10218kg
Max speed: 235km/h
Hovering ceiling, IGE: 4800m
Service ceiling: 6980m
Range: 2300km

 

Piask-YH-16-ld

 

 

 

 

 

 

 

 


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