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Gyrodyne RON Rotorcycle

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Title: Gyrodyne RON Rotorcycle  
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Subject: New England Air Museum, Gyrodyne QH-50 DASH, Backpack helicopter, Ron, 1922 United States Navy aircraft designation system
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Gyrodyne RON Rotorcycle

Gyrodyne Company of America XRON-I Rotorcycle
Rotorcycle on display at the Cradle of Aviation Museum
Role Helicopter
National origin United States of America
Manufacturer Gyrodyne Company of America
First flight 23 November 1955
Number built 10
Developed from Gyrodyne Model 2C
Developed into Gyrodyne QH-50 DASH

The The XRON-I Rotorcycle or YRON-I Rotorcycle (originally designated HOG) was a tiny, single-seat helicopter designed under contract for the U.S. Navy.[1] in the mid-1950s. It later was designed for a United States Marine Corps requirement for a small personal helicopter that would fulfill a number of roles, including observation, liaison, small unit tactical maneuvers, and which could be dropped to downed airmen behind enemy lines to facilitate their escape.[2]

Development

Gyrodyne purchased the assets of Bendix Helicopters in 1949, including the model 2C coaxial heicopter which provided the technology for the XRON-I. In 1951 the model 2C was demonstrated to the Navy with shortcomings noted in autorotation control. The XRON-I was demonstrated under a new Navy contract NOas 55-388-c for a lightweight single man helicopter.

Design

Gyrodyne's design was an open-framework helicopter with coaxial rotors, which was evaluated with three different power plants (two reciprocating, one turbine).

The XRON-I uses a manually started 40hp two-cycle engine with a gross weight capability of 500 lb. The fuselage is a simple box-beam construction. The rotor uses co-axial blades which alleviate the need for an anti-torque tail rotor. Yaw control is provided by rotor tip mounted "tip brakes" providing differential speeds between the rotors. Gyrodyne patented the control on 24 October 1954 Patent No. 2,835,331.[3] There is a small inverted V-tail for control at forward speeds. The rotors are laminated wood construction. The mast is pressure lubricated and becomes a cooling surface for oil inflight. The landing gear consists of three small wheels.[4]

Operational history

The first flight was on November 1955. The two-cycle engine was prone to overheating and other engines were added to the program for testing. The Marine Corps also tested one XRON-I, and three YRON-1 protoypes.[5]

The Marine Corps eventually concluded that both the RON, and the competing Hiller ROE were too heavy and too difficult to fly and abandoned the project. The United States Navy, however, had noticed the compact size and high load-carrying capacity of the RON, and in 1960 awarded a contract to Gyrodyne to produce a radio-controlled drone version of the Rotorcycle, to be used as an Anti-Submarine Warfare (ASW) platform. Using the dynamic components of the RON, this was eventually developed as the Gyrodyne QH-50.

The Rotorcycle went on to win the prize for most maneuverable helicopter at the Paris Air Show in 1961, and was selected for a 1964 trade fair in Morocco by the United States Department of Commerce.

A 2 place enclosed "gyrocycle" commercial variant was proposed after initial tests.[6]

Variants

  • 55 HP 4-Cycle Porsche YO-95-2 model Model GP-702/1 600cc variant with 17 ft rotors.
  • 55 HP Solar YT62 turbine model with 17 ft rotors.
  • 72 HP 4-Cycle Porsche YO-95-6 engine variant - Rotor increased to 20 ft, 5 units built and tested at Pax River and Camp Pendleton.
  • 62 hp Solar T62 gas turbine engine and 15 ft rotor.[7]
  • The DSN-1 modified as a drone.

On display

The Cradle of Aviation Museum in New York has a XRON-I on display [8]

On display at The New England Air Museum, Windsor Locks, CT.[9]

Specifications

General characteristics

  • Crew: One pilot
  • Length: 11 ft 6 in (3.51 m)
  • Main rotor diameter: × 20 ft 0 in (6.10 m)
  • Main rotor area: 314 ft2 (29.2 m2)
  • Empty weight: 550 lb (250 kg)
  • Gross weight: 832 lb (378 kg)
  • Powerplant: 1 × Porsche YO-95-6, 72 hp (54 kW)

Performance

  • Maximum speed: 78 mph (125 km/h)
  • Range: 55 miles (88 km)
  • Service ceiling: 12,400 ft (3,780 m)
  • Rate of climb: 1,140 ft/min (5.8 m/s)

See also

Hiller YROE

References

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