| 词条 | Rolls-Royce Soar | |||||||||||||
| 释义 |
The Rolls-Royce RB.82 Soar, also given the Ministry of Supply designation RSr., was a small, expendable British axial-flow turbojet intended for cruise missile use and built by Rolls-Royce Limited in the 1950s. Design and developmentThe Soar was developed in the early 1950s, and was demonstrated at the Farnborough Airshow in 1953 on each wingtip of a Gloster Meteor flying testbed. It was the smallest aero-engine ever made by Rolls-Royce and was an extremely simple engine with very few parts. Its starting and control systems were almost non-existent. Lessons learned in producing the Soar at low weight and cost would be applied to the next light-weight engine, the RB108 lift engine.[1] As a cruise-missile expendable powerplant the Soar engine had a design life of 10 hours for a Red Rapier flight time of about 1 hour (range 400 nautical miles at 475 knots).[2] ApplicationsIt was to be the intended powerplant for the "Red Rapier" missile project[3] one of the projects coming from the UB.109T operational requirement. Red Rapier was to be built by Vickers-Armstrong Ltd, Weybridge, Surrey as the Vickers 825. Development was cancelled in 1953. Three Soar engines were used on this design, two on the tips of the tailplane, and one on the tip of the fin. One-third scale models without engines were built and air launched from a Washington bomber (the Boeing B-29 Superfortress in RAF service) on the Woomera missile range to test the aerodynamics and autopilot operation.[4] As the Westinghouse J81 it was a powerplant for the US AQM-35 missile [5] It was employed as an auxiliary powerplant for the Italian Aerfer Ariete fighter design and also considered as a JATO powerplant for other aircraft. The Soar project was cancelled in March 1965, at a reported total cost of £1.2 million.[6] Specifications (RB.93 Soar){{jetspecs| |ref=Gunston[7] |type=Single spool turbojet |length= |diameter= |weight=267 lb (121.1 kg) |compressor= |combustion=Annular |turbine= |fueltype= |oilsystem= |power= |thrust=1,810 lb (8.04 kN) |compression= |aircon= |turbinetemp= |fuelcon= |specfuelcon= |power/weight= |thrust/weight=6.78 lbf/lb (0.066 kN/kg) }} See also{{aircontent|see also= |related=
|similar aircraft= |lists=
|similar engines= }} ReferencesNotes1. ^Rolls-Royce Aero Engines, Bill Gunston 1989, Patrick Stephens Limited, {{ISBN|1-85260-037-3}}, P. 152/155 2. ^The Secret World Of Vickers Guided Weapons, John Forbat2006, Tempus Publishing Limited, {{ISBN|0 7524 3769 0}}, p.29 3. ^Skomer.net {{webarchive|url=https://web.archive.org/web/20060714171945/http://www.skomer.u-net.com/projects/turbines.htm |date=14 July 2006 }}, 4. ^Ozz files - Drury affair 5. ^US designation systems 6. ^{{cite journal |journal=Flight |title=Cancelled projects: the list up-dated |chapter= |url=http://www.flightglobal.com/pdfarchive/view/1967/1967%20-%201672.html |format=PDF |date=17 August 1967 |pages=262 |ref=Flight, Flight, 17 August 1967, Cancelled projects list}} 7. ^Gunston 1989, p.150. Bibliography{{refbegin}}
External links
2 : Turbojet engines 1950–1959|Rolls-Royce aircraft gas turbine engines |
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