Armstrong Siddeley Beta: Difference between revisions
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'''Armstrong Siddeley Beta''' was an early rocket engine, intended for use in supersonic aircraft. |
'''Armstrong Siddeley Beta''' was an early rocket engine, intended for use in supersonic aircraft. |
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The [[Miles M.52]], the intended British contender for supersonic flight, had been cancelled in 1946 due to uncertainty concerning its [[turbojet]] engine's thrust potential and the risks of manned supersonic flight. A scale model was then built by [[Vickers Armstrong|Vickers]] with a 362 kg (800 lbf) thrust [[hydrogen peroxide]] 'hot' motor evolved at [[Rocket Propulsion Establishment|Westcott]] derived from the [[Walter HWK 109-509]] engine. This initiated the Beta and the subsequent [[Armstrong Siddeley Delta|Delta]] engines. In October 1948 the Vickers ''Transonic'' model flew at 930 mph (Mach 1.5) in level flight at 35,000 ft.<ref>{{cite journal|title=Rockets and Assisted Take-Off|last=Cleaver|first=V.|journal=J. Royal Aeronautical Society|date=Feb 1951|url=http://www.cue-dih.co.uk/aerospace/aeropdfs/htp_for_prop.pdf}}</ref> |
The [[Miles M.52]], the intended British contender for supersonic flight, had been cancelled in 1946 due to uncertainty concerning its [[turbojet]] engine's thrust potential and the risks of manned supersonic flight. A scale model was then built by [[Vickers Armstrong|Vickers]] with a 362 kg (800 lbf) thrust [[hydrogen peroxide]] 'hot' motor evolved at [[Rocket Propulsion Establishment|Westcott]] derived from the [[Walter HWK 109-509]] engine. This initiated the Beta and the subsequent [[Armstrong Siddeley Delta|Delta]] engines. In October 1948 the Vickers ''Transonic'' model flew at 930 mph (Mach 1.5) in level flight at 35,000 ft.<ref>{{cite journal|title=Rockets and Assisted Take-Off |last=Cleaver |first=V. |journal=J. Royal Aeronautical Society |date=Feb 1951 |url=http://www.cue-dih.co.uk/aerospace/aeropdfs/htp_for_prop.pdf |deadurl=yes |archiveurl=https://web.archive.org/web/20060215104117/http://www.cue-dih.co.uk:80/aerospace/aeropdfs/htp_for_prop.pdf |archivedate=2006-02-15 |df= }}</ref> |
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To reduce the risks of single-sourced engines, other makers were given experience of work with [[hydrogen peroxide]]. In 1952 [[Napier & Son|Napier]] were providing their [[Napier NRE.17|NRE.17]] engines for missile trials, as a line of development from Beta.<ref>{{cite journal|title=Napier Rocket Engines|journal=The [[English Electric]] Journal|date=June 1957|url=http://www.cue-dih.co.uk/aerospace/aeropdfs/htp_for_prop.pdf}}</ref> |
To reduce the risks of single-sourced engines, other makers were given experience of work with [[hydrogen peroxide]]. In 1952 [[Napier & Son|Napier]] were providing their [[Napier NRE.17|NRE.17]] engines for missile trials, as a line of development from Beta.<ref>{{cite journal|title=Napier Rocket Engines |journal=The [[English Electric]] Journal |date=June 1957 |url=http://www.cue-dih.co.uk/aerospace/aeropdfs/htp_for_prop.pdf |deadurl=yes |archiveurl=https://web.archive.org/web/20060215104117/http://www.cue-dih.co.uk:80/aerospace/aeropdfs/htp_for_prop.pdf |archivedate=2006-02-15 |df= }}</ref> |
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== Variants == |
== Variants == |
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Revision as of 07:57, 18 October 2016
| Country of origin | Britain |
|---|---|
| Manufacturer | Armstrong Siddeley |
| Liquid-fuel engine | |
| Propellant | hydrogen peroxide HTP / C-fuel (57% methanol, 30% hydrazine hydrate and 13% water) [1] |
| Pumps | First British rocket with gas-generator powered turbo-pump.[1] |
| Configuration | |
| Chamber | Double |
Armstrong Siddeley Beta was an early rocket engine, intended for use in supersonic aircraft.
The Miles M.52, the intended British contender for supersonic flight, had been cancelled in 1946 due to uncertainty concerning its turbojet engine's thrust potential and the risks of manned supersonic flight. A scale model was then built by Vickers with a 362 kg (800 lbf) thrust hydrogen peroxide 'hot' motor evolved at Westcott derived from the Walter HWK 109-509 engine. This initiated the Beta and the subsequent Delta engines. In October 1948 the Vickers Transonic model flew at 930 mph (Mach 1.5) in level flight at 35,000 ft.[2]
To reduce the risks of single-sourced engines, other makers were given experience of work with hydrogen peroxide. In 1952 Napier were providing their NRE.17 engines for missile trials, as a line of development from Beta.[3]
Variants
- Beta II
- Larger version of Beta I [1]
References
- ^ a b c "United Kingdom Aerospace and Weapons Projects: Rocket Engines". Skomer.
- ^ Cleaver, V. (Feb 1951). "Rockets and Assisted Take-Off" (PDF). J. Royal Aeronautical Society. Archived from the original (PDF) on 2006-02-15.
{{cite journal}}: Unknown parameter|deadurl=ignored (|url-status=suggested) (help) - ^ "Napier Rocket Engines" (PDF). The English Electric Journal. June 1957. Archived from the original (PDF) on 2006-02-15.
{{cite journal}}: Unknown parameter|deadurl=ignored (|url-status=suggested) (help)