Pegasus Booster

From Wikipedia, the free encyclopedia
Jump to: navigation, search
Booster
Role Powered hang glider
National origin United Kingdom
Manufacturer Pegasus Aviation
Status Production completed
Unit cost
US$5000 (circa 2000, without wing)

The Pegasus Booster is a British powered hang glider that was designed and produced by Pegasus Aviation.[1]

Design and development[edit]

The booster was sold either as an engine package or as a powered hang gliding harness, to which the pilot could add any standard hang glider wing. When ready to fly the aircraft features a cable-braced hang glider-style high-wing, weight-shift controls, single-place accommodation, foot-launching and landing and a single engine in pusher configuration.[1]

The aircraft uses a standard hang glider wing, made from bolted-together aluminium tubing, with its single surface wing covered in Dacron sailcloth. The wing is supported by a single tube-type kingpost and uses an "A" frame control bar. The engine is a lightweight, two-stroke, single cylinder Radne Raket 120 of 14 hp (10 kW), which is mounted at the rear of the pilot's prone position harness pod, with the propeller at the very rear.[1]

Variants[edit]

Pegasus Booster
Version produced by Pegasus Aviation in the late 1990s period.[1]
Solar Wings Booster Mk I
Version produced by Solar Wings in the early-2000s period. Was noted as being compatible with the Woody Valley harness that was popular in Europe in that time period.[2]
Solar Wings Booster Mk II
Version produced by Solar Wings in the mid-2000s period. Was noted as being not compatible with the Woody Valley harness that was popular in Europe in that time period.[2]

Specifications (Booster)[edit]

Data from Cliche[1]

General characteristics

  • Crew: one
  • Empty weight: 42 lb (19 kg) powered harness only, plus wing weight
  • Fuel capacity: 1.3 U.S. gallons (4.9 L; 1.1 imp gal)
  • Powerplant: 1 × Radne Raket 120 single cylinder, two-stroke, air-cooled, aircraft engine, 14 hp (10 kW)

Performance

  • Cruise speed: 25 mph (22 kn; 40 km/h)
  • Stall speed: 14 mph (12 kn; 23 km/h) depending on the wing selected
  • Rate of climb: 400 ft/min (2.0 m/s)

References[edit]

  1. ^ a b c d e Cliche, Andre: Ultralight Aircraft Shopper's Guide 8th Edition, page C-32. Cybair Limited Publishing, 2001. ISBN 0-9680628-1-4
  2. ^ a b Bertrand, Noel; Rene Coulon; et al: World Directory of Leisure Aviation 2003-04, page 75. Pagefast Ltd, Lancaster UK, 2003. ISSN 1368-485X