Rolls-Royce Soar

{{Use dmy dates|date=October 2019}}

{{Use British English|date=August 2017}}

{{Infobox Aircraft Begin

|name=Soar

|image=Rolls-Royce Soar RRHT Derby.jpg

|caption=Rolls-Royce Soar on display at the Rolls-Royce Heritage Trust, Derby

}}{{Infobox Aircraft Engine

|type=Turbojet

|manufacturer=Rolls-Royce Limited

|first run=January 1953

|major applications=

|number built =

|program cost =

|unit cost =

|developed from =

|developed into = Rolls-Royce RB108

|variants with their own articles =

}}

The Rolls-Royce RB.93 Soar, also given the Ministry of Supply designation RSr., was a small, expendable British axial-flow turbojet intended for the UB.109T cruise missile use and built by Rolls-Royce Limited in the 1950s and 1960s. Like all the company's gas turbine engines it was named after a British river, in this case, the River Soar. It was also produced under license in the US as the Westinghouse J81.

Design and development

The Soar was developed as part of the Short Range Expendable Bomber cruise missile program of 1950. This called for a surface-to-surface missile similar to the V-1 flying bomb but jet-powered to provide much longer range, and using a new radio navigation system to give it the required accuracy at these extended ranges. Two designs were proposed, Bristol Aircraft's Blue Rapier and Vickers-Armstrongs' Red Rapier.

Red Rapier was selected as the winner after Winston Churchill returned to power in late 1951. The Vickers concept was similar to the original V-1, with a mostly cylindrical fuselage, straight wings, and conventional tail surfaces. Power was provided by three small engines located at the tips of the tail surfaces. Rolls-Royce was selected to build the engines, whilst the Telecommunications Research Establishment (TRE) began development of the guidance system. Designed to be expendable, the powerplant had a design life of 10 hours for a Red Rapier flight time of about 1 hour (range 400 nautical miles at 475 knots).The Secret World of Vickers Guided Weapons, John Forbat, 2006, Tempus Publishing Limited, {{ISBN|0 7524 3769 0}}, p.29

Red Rapier had been conceived as an emergency program as it was believed the Soviets were planning to start a war in 1953, before the Royal Air Force's new jet-powered bombers would be in service. As the date approached and it became clear no such attack was looming, combined with the good progress on the V-bomber designs, the program, now known as UB.109T, was cancelled. By this time the engine was running and was demonstrated at the Farnborough Airshow in 1953 on each wingtip of a Gloster Meteor flying testbed.Gunston (RRAE) 1989 pp.152-155

Applications

Development of the Soar continued for a time despite the cancellation of the UB.109T program. 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.Gunston (RRAE) 1989 pp.152-155

Looking to power a target drone design, Lockheed contracted Westinghouse to provide a similar engine. They licensed the Soar from Rolls, as the Westinghouse J81. This powered the AQM-35 missile.[http://www.designation-systems.net/usmilav/engines.html US designation systems]

It was also 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.{{cite journal

|journal=Flight

|title=Cancelled projects: the list up-dated

|url=http://www.flightglobal.com/pdfarchive/view/1967/1967%20-%201672.html

|date=17 August 1967

|pages=262

|ref=Flight, Flight, 17 August 1967, Cancelled projects list

}}

Specifications (RB.93 Soar)

{{jetspecs

|

|ref=Rolls-Royce Aero Engines Gunston (RRAE) 1989, p. 152/Appendix 3

|type=Single-spool turbojet

|length=

|diameter={{convert|15.8|in|mm|0|abbr=on}}

|weight={{convert|267|lb|kg|0|abbr=on}}

|compressor= 7-stage axial

|combustion=Annular

|turbine=Single stage

|fueltype=

|oilsystem=

|power=

|thrust={{convert|8.05|kN|lbf|0|abbr=on}}

|compression=4.9

|aircon=13.47 kg/s (30 lb/s)

|turbinetemp=

|fuelcon=

|specfuelcon=

|power/weight=

|thrust/weight=6.97

}}

See also

{{aircontent

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|related=

|similar aircraft=

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References

=Notes=

{{reflist}}

=Bibliography=

{{refbegin}}

  • Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. {{ISBN|1-85260-163-9}}
  • Gunston, Bill. Rolls-Royce Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. {{ISBN|1-85260-037-3}}

{{refend}}