World Library  
Flag as Inappropriate
Email this Article

Fairey Ultra-light Helicopter

Article Id: WHEBN0022010363
Reproduction Date:

Title: Fairey Ultra-light Helicopter  
Author: World Heritage Encyclopedia
Language: English
Subject: Sud-Ouest Djinn, Turbomeca Palouste, Fairey Delta 1, Folland Midge, Fairey Delta 2
Collection:
Publisher: World Heritage Encyclopedia
Publication
Date:
 

Fairey Ultra-light Helicopter

Ultra-light Helicopter
The fourth Ultra-light Helicopter exhibited on a lorry at the 1957 Paris Air Salon
Role Light Army helicopter
National origin United Kingdom
Manufacturer Fairey Aviation Company
First flight 14 August 1955
Number built 6

The Fairey Ultra-light Helicopter was a small British military helicopter for reconnaissance and casualty evacuation, designed by the Fairey Aviation Company to be low cost and easily transportable. The project was a casualty of the UK defence economies of the later 1950s.

Development

In 1953, there was a UK government call for a low-cost two-seat helicopter suitable for reconnaissance, casualty evacuation and training duties. The specification was demanding, calling for high speeds and climb rates in tropical conditions. The aircraft also had to be transportable on the back of a standard Army three-ton truck. Fairey's detailed proposal won a contract for four development aircraft and the company decided to build two more as a private venture.[1]

Gas turbines were beginning to appeal to helicopter designers and there was also an interest in producing machines with tip driven rotors, in order to avoid the torque produced by shaft drive and the consequent complicated and vulnerable torque-compensating tail rotor. Some contemporary designs, such as the Sud-Ouest Djinn bled high pressure air from the engine directly to the tips, but Fairey had been developing a drive where this air was mixed with fuel at the tips and burned. Such methods had already been tested on the Fairey Jet Gyrodyne. For the Ultra-light Helicopter, Fairey adopted the French Turbomeca Palouste turbojet, produced under licence by Blackburn, and fitted with an oversized compressor to provide air to the tip-burners at 40 psi (275 kPa).

The Ultra-light Helicopter[1] emerged as a compact side-by-side two-seater with the engine mounted semi-externally at floor level behind the seats. The aircraft was built around a light alloy box with the rotor pylon in the centre and carrying a box girder boom which carried the engine, a horizontal tailplane and vertical stabilizer and rudder surfaces. The rudder projected below the boom into the jet efflux and provided yaw control even when the aircraft was stationary. The undercarriage was a simple pair of skids attached to the box structure. The rotor was a tip-driven two-blade teetering unit mounted atop a pylon.[1]

The aircraft first flew in August 1955 and appeared at the September Society of British Aircraft Constructors (SBAC) show at Farnborough that year. Though the first four military machines were built, defence economies left the Ultra-light without Ministry support by mid-1956 and Fairey had to develop it at their own expense. Several modifications were made to the first prototype. This machine originally had only the rudder at the end of the boom, but a horizontal tailplane bearing end-plate fins was added. A less obvious change was the addition of hydraulically assisted cyclic pitch control. The second prototype had a modified cabin which allowed stretcher-borne casualties to be carried. Two Ultra-lights had slightly larger diameter rotors (32 ft/9.75 m rather than 28 ft/8.6 m) to improve performance in situations where compactness was not at a premium. There were many demonstrations of the Ultra-light's capabilities at airshows, in nuclear war exercises and aboard ship (HMS Grenville). Civil airworthiness certification was achieved in 1958. Despite interest from abroad, particularly the USA and Canada, no orders were received and only the six aircraft were built before the programme was abandoned in 1959.[1]

Specifications

Data from Taylor 1974, p. 404

General characteristics
  • Crew: 2
  • Length: 15 ft 0 in (4.57 m)
  • Height: 8 ft 2 in (2.49 m)
  • Empty weight: 959 lb (435 kg)
  • Gross weight: 1,800 lb (817 kg)

Performance

  • Cruise speed: 95 mph (153 km/h)
  • Range: (under tropical conditions) 180 miles (290 km)
  • Endurance: max, tropical 2.5 hours
  • Service ceiling: hovering, out of ground effect 4,800 ft (1,463 m)
  • Rate of climb: sea level 950 ft/min (4.83 m/s)

See also

Aircraft of comparable role, configuration and era
Related lists

References

Notes

  1. ^ a b c d Taylor 1974, pp. 398–404

Bibliography

  • Taylor, H.O. (1974). Fairey Aircraft since 1915. London: Putnam Publishing.  
This article was sourced from Creative Commons Attribution-ShareAlike License; additional terms may apply. World Heritage Encyclopedia content is assembled from numerous content providers, Open Access Publishing, and in compliance with The Fair Access to Science and Technology Research Act (FASTR), Wikimedia Foundation, Inc., Public Library of Science, The Encyclopedia of Life, Open Book Publishers (OBP), PubMed, U.S. National Library of Medicine, National Center for Biotechnology Information, U.S. National Library of Medicine, National Institutes of Health (NIH), U.S. Department of Health & Human Services, and USA.gov, which sources content from all federal, state, local, tribal, and territorial government publication portals (.gov, .mil, .edu). Funding for USA.gov and content contributors is made possible from the U.S. Congress, E-Government Act of 2002.
 
Crowd sourced content that is contributed to World Heritage Encyclopedia is peer reviewed and edited by our editorial staff to ensure quality scholarly research articles.
 
By using this site, you agree to the Terms of Use and Privacy Policy. World Heritage Encyclopedia™ is a registered trademark of the World Public Library Association, a non-profit organization.
 


Copyright © World Library Foundation. All rights reserved. eBooks from Project Gutenberg are sponsored by the World Library Foundation,
a 501c(4) Member's Support Non-Profit Organization, and is NOT affiliated with any governmental agency or department.