Engineering:Gyrodyne RON Rotorcycle

Short description: Experimental US Navy & Marine Corps helicopter

XRON-I Rotorcycle
Rotorcycle conducting a test flight
Role	Helicopter
National origin	United States
Manufacturer	Gyrodyne Company of America
First flight	23 November 1955
Primary user	United States Navy
Number built	10
Developed from	Bendix Model 2C
Developed into	Gyrodyne QH-50 DASH

The Gyrodyne RON Rotorcycle (originally designated HOG) was a tiny, single-seat helicopter designed under contract for the United States Navy. in the mid-1950s. It later was redesigned for a U.S. 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.

Development

Gyrodyne purchased the assets of Bendix Helicopters in 1949, including the Model 2C coaxial helicopter which provided the technology for the XRON-1. 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-1 used a manually started 40 hp 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 torque between the rotors. Gyrodyne patented the control on 24 October 1954 Patent No. 2,835,331. 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.

Operational history

Gyrodyne RON Rotorcycle making a water landing

The first flight was in 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-1, and three YRON-1 prototypes.

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 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 two-place enclosed "gyrocycle" commercial variant was proposed after initial tests.

Variants

XRON-1

Prototype

YRON-1

• Powered by a 55 hp (41 kW) 4-stroke Porsche YO-95-2 model Model GP-702/1 600cc variant with 17 ft (5 m) diameter rotors.
• Powered by a 55 hp (41 kW) Solar YT62 turbine model with 17 ft (5 m) diameter rotors.
• Powered by a 72 hp (54 kW) 4-stroke Porsche YO-95-6 engine variant - Rotor diameter increased to 20 ft (6 m), 5 units built and tested at NAS Patuxent River and Camp Pendleton.
• Powered by a 62 hp (46 kW) Solar T62 gas turbine engine and 15 ft (5 m) diameter rotors.
• Powered by a 72 hp (54 kW) 4-stroke Porsche YO-95-8 DSN-1/QH-50A engine.
• Powered by a 125 hp (93 kW) Electric Engine with 50 Min endurance.

On display

The Cradle of Aviation Museum in New York has a XRON-1 on display

The New England Air Museum, Windsor Locks, CT.

Specifications

Data from Jane's All The World's Aircraft 1961–62

General characteristics

• Crew: 1
• Length: 11 ft 6 in (3.51 m)
• Empty weight: 550 lb (249 kg)
• Gross weight: 832 lb (377 kg)
• Max takeoff weight: 906 lb (411 kg)
• Powerplant: 1 × Porsche YO-95-6 4-cylinder air-cooled horizontally-opposed piston engine, 72 hp (54 kW)
• Main rotor diameter: 2× 20 ft (6.1 m)
• Main rotor area: 314 sq ft (29.2 m²)

Performance

• Maximum speed: 78 mph (126 km/h, 68 kn)
• Cruise speed: 60 mph (97 km/h, 52 kn)
• Range: 55 mi (89 km, 48 nmi)
• Ferry range: 112 mi (180 km, 97 nmi) (overload weight, auxiliary fuel)
• Service ceiling: 12,400 ft (3,800 m)
• Rate of climb: 1,140 ft/min (5.8 m/s)

See also

Related development

• Gyrodyne QH-50 DASH

Aircraft of comparable role, configuration and era

• Hiller YROE
• Hoppi-Copter

References

Bibliography

• The Rotorcycle. Gyrodyne Company of America. 
• Rawlins, Eugene W. (1976). Marines and Helicopters 1946–1962. Washington, D.C.: History and Museums Division Headquarters, United States Marine Corps. pp. 89. 
• Simpson, Rod (1998). Airlife's Helicopters and Rotorcraft. Shrewsbury, UK: Airlife Publishing. pp. 220. ISBN 9781853109683. OCLC 438025217. 
• Taylor, John W. R. (1961). Jane's All the World's Aircraft 1961–62. London: Sampson Low, Marston & Company, Ltd.. 
• Taylor, Michael J. H. (1989). Jane's Encyclopedia of Aviation. London: Studio Editions. pp. 455. 

Further reading

• Bridgman, Leonard, ed (1958). Jane's All the World's Aircraft 1958-59. London: Jane's All the World's Aircraft Publishing Co. Ltd.. p. 312.