Aerozine 50: Difference between revisions
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'''Aerozine 50''' is a 50/50 mix by weight of [[hydrazine]] and [[unsymmetrical dimethylhydrazine]] (UDMH),<ref>{{cite web | url = http://propellants.ksc.nasa.gov/commodities/Aerzone50.pdf | title = Aerozine50 Specifications & DOT Shipping Information | publisher = [[NASA]] |date=October 5, 2006|archiveurl = https://web.archive.org/web/20140326180521/http://propellants.ksc.nasa.gov/commodities/Aerzone50.pdf|archivedate = March 26, 2014}}</ref><ref>{{Cite book | last = Clark | first = John D. | authorlink = John Drury Clark | title = Ignition! An Informal History of Liquid Rocket Propellants | publisher = [[Rutgers University Press]] | year = 1972 | page = 45 | isbn = 0-8135-0725-1 }}</ref> originally developed in the late 1950s by [[Aerojet General]] Corporation as a storable, high-energy, hypergolic fuel for the [[LGM-25C Titan II|Titan II]] [[Intercontinental ballistic missile|ICBM]] rocket engines. '''Aerozine''' continues in wide use as a [[rocket fuel]], typically with [[dinitrogen tetroxide]] as the [[oxidizer]], with which it is [[hypergolic]]. Aerozine 50 is more stable than hydrazine alone, and has a higher density and boiling point than UDMH alone. |
'''Aerozine 50''' is a 50/50 mix by weight of [[hydrazine]] and [[unsymmetrical dimethylhydrazine]] (UDMH),<ref>{{cite web | url = http://propellants.ksc.nasa.gov/commodities/Aerzone50.pdf | title = Aerozine50 Specifications & DOT Shipping Information | publisher = [[NASA]] |date=October 5, 2006|archiveurl = https://web.archive.org/web/20140326180521/http://propellants.ksc.nasa.gov/commodities/Aerzone50.pdf|archivedate = March 26, 2014}}</ref><ref>{{Cite book | last = Clark | first = John D. | authorlink = John Drury Clark | title = Ignition! An Informal History of Liquid Rocket Propellants | publisher = [[Rutgers University Press]] | year = 1972 | page = 45 | isbn = 0-8135-0725-1 }}</ref> originally developed in the late 1950s by [[Aerojet General]] Corporation as a storable, high-energy, hypergolic fuel for the [[LGM-25C Titan II|Titan II]] [[Intercontinental ballistic missile|ICBM]] rocket engines. '''Aerozine''' continues in wide use as a [[rocket fuel]], typically with [[dinitrogen tetroxide]] as the [[oxidizer]], with which it is [[hypergolic]]. Aerozine 50 is more stable than hydrazine alone, and has a higher density and boiling point than UDMH alone. |
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By cutting straight hydrazine, hydrazine's inconveniently high freezing point of 2 °C is lowered through [[freezing point depression]]. In addition, UDMH is a more stable molecule; this reduces the chances of straight hydrazine decomposing unexpectedly, increasing safety and allowing the blend to be used as a coolant in [[Regenerative cooling (rocket)|regeneratively cooled]] engines. |
By cutting straight hydrazine with UDMH, hydrazine's inconveniently high freezing point of 2 °C is lowered through [[freezing point depression]]. In addition, UDMH is a more stable molecule; this reduces the chances of straight hydrazine decomposing unexpectedly, increasing safety and allowing the blend to be used as a coolant in [[Regenerative cooling (rocket)|regeneratively cooled]] engines. |
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Hydrazine may also be mixed with [[monomethyl hydrazine]] (MMH). Because MMH is slightly denser, net performance is increased slightly. |
Hydrazine may also be mixed with [[monomethyl hydrazine]] (MMH). Because MMH is slightly denser, net performance is increased slightly. |
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Revision as of 14:08, 7 April 2018
Aerozine 50 is a 50/50 mix by weight of hydrazine and unsymmetrical dimethylhydrazine (UDMH),[1][2] originally developed in the late 1950s by Aerojet General Corporation as a storable, high-energy, hypergolic fuel for the Titan II ICBM rocket engines. Aerozine continues in wide use as a rocket fuel, typically with dinitrogen tetroxide as the oxidizer, with which it is hypergolic. Aerozine 50 is more stable than hydrazine alone, and has a higher density and boiling point than UDMH alone.
By cutting straight hydrazine with UDMH, hydrazine's inconveniently high freezing point of 2 °C is lowered through freezing point depression. In addition, UDMH is a more stable molecule; this reduces the chances of straight hydrazine decomposing unexpectedly, increasing safety and allowing the blend to be used as a coolant in regeneratively cooled engines.
Hydrazine may also be mixed with monomethyl hydrazine (MMH). Because MMH is slightly denser, net performance is increased slightly.
This type of fuel is mainly used for interplanetary probes and spacecraft propulsion because unlike other more common propellants like liquid oxygen or liquid hydrogen Aerozine 50 is liquid at room temperature and can be stored in liquid state without significant boil off, thus making it a storable propellant better suited for long term interplanetary missions. Aerozine 50 was largely used in ICBMs and in their derivative launchers such as the core stages of the Titan-II/III/IV rocket because an ICBM requires long term storage and launch on short notice; the rocket must be stored already fueled. This fuel was also used in ICBM heritage upper stages, such as the Delta II rocket. It was also used by the Apollo Lunar Module and the Service Propulsion System engine in the Apollo CSM. The Ariane 1 through Ariane 4 family used a related fuel, a mixture of 75% UDMH and 25% hydrazine hydrate called UH 25.
Aerozine is not used as a monopropellant. The extra stability conferred by the methyl groups affects reactivity and thrust.
Alternatives
A potentially novel hypergolic alternative has been developed based on tertiary amine azides – called CINCH (Competitive Impulse Non-Carcinogenic Hypergol) and the name of the compound is 2-Dimethylaminoethylazide.[3][4]
See also
- UH 25 – a mixture of 75% UDMH and 25% hydrazine.
References
- ^ "Aerozine50 Specifications & DOT Shipping Information" (PDF). NASA. October 5, 2006. Archived from the original (PDF) on March 26, 2014.
- ^ Clark, John D. (1972). Ignition! An Informal History of Liquid Rocket Propellants. Rutgers University Press. p. 45. ISBN 0-8135-0725-1.
- ^ "Army Develops New Fuel". Spacedaily.com. February 23, 2000. Retrieved July 12, 2014.
- ^ McQuaid, Michael J. (April 2004). The Structure of Secondary 2-Azidoethanamines: A Hypergolic Fuel vs. a Nonhypergolic Fuel (PDF) (Technical report). Army Research Laboratory. ARL-TR-3176.