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BMW 109-558

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109-558
Type

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This page is a soft redirect. Liquid-propellant rocket (sustainer) #REDIRECTmw:Help:Magic words#Other
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National origin

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This page is a soft redirect. Germany #REDIRECTmw:Help:Magic words#Other
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Manufacturer

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This page is a soft redirect. BMW #REDIRECTmw:Help:Magic words#Other
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Major applications

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This page is a soft redirect. Henschel Hs 117 Schmetterling missile #REDIRECTmw:Help:Magic words#Other
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Number built

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This page is a soft redirect. 120 #REDIRECTmw:Help:Magic words#Other
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Unit cost

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This page is a soft redirect. 400-500 RM[1] #REDIRECTmw:Help:Magic words#Other
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The BMW 109-558 is a liquid fuelled sustainer rocket motor developed by BMW at their Bruckmühl facility,[2] in Germany during the Second World War.

The 109-558 (with the "109-" prefix being the Reichsluftfahrtministerium, or RLM, designation for reaction-propulsion aircraft power projects, encompassing all jet & rocket engine designs)[3] was designed as a sustainer rocket for the Henschel Hs 117 surface-to-air missile.[4] It was tubular, measuring Script error: No such module "convert". diameter and about Script error: No such module "convert". long overall.[5] The engine had a compressed air tank to pressurise tanks for the R-Stoff fuel (50% triethylamine and 50% xylidine) and SV-Stoff oxidiser (94% nitric acid with 6% dinitrogen tetroxide).[6] SV-Stoff was used to cool the combustion chamber.[7]

The 109-558 was capable of propelling an Hs 117 at Script error: No such module "convert"., with throttle control by sliding valves in the exhaust nozzle, operated by a servomotor controlled by a Mach sensor. Production of the 109-558 took forty to sixty hours using a very high proportion of slave labour.

Applications

Specifications

General characteristics

  • Type: liquid-fuelled rocket engine
  • Length: Script error: No such module "convert".
  • Diameter: Script error: No such module "convert".
  • Dry weight: Script error: No such module "convert"..[8]

Components

Performance

  • Maximum thrust: Script error: No such module "convert". for 33 sec, followed by Script error: No such module "convert". for 24 sec
  • Thrust-to-weight ratio: 0.023125 kN/kg (2.36 lbf/lb)

Notes

  1. Christopher, p.127.
  2. Christopher, John. The Race for Hitler's X-Planes (The Mill, Gloucestershire: History Press, 2013), p.127.
  3. Christopher, p.124.
  4. Christopher, p.127.
  5. Christopher, p.127.
  6. Christopher, p.127.
  7. Christopher, p.127.
  8. Christopher, p.127.

Sources

  • Christopher, John. The Race for Hitler's X-Planes. The Mill, Gloucestershire: History Press, 2013.