Editing Dual mode propulsion rocket

'''Dual mode [[Spacecraft propulsion|propulsion]] systems''' combine the high efficiency of [[bipropellant rocket]]s with the reliability and simplicity of [[monopropellant rocket]]s.<ref name="Napolitano2013">{{cite book|author=L. G. Napolitano|title=Applications of Space Developments: Selected Papers from the XXXI International Astronautical Congress, Tokyo, 21 — 28 September 1980|url=https://books.google.com/books?id=qdogBQAAQBAJ&pg=PA134|date=22 October 2013|publisher=Elsevier Science|isbn=978-1-4831-5976-8|pages=134–}}</ref>

Dual mode systems are either [[hydrazine]]/[[nitrogen tetroxide]], or [[monomethylhydrazine]]/[[hydrogen peroxide]] (the former is much more common). Typically, this system works as follows: During the initial high-[[Impulse (physics)|impulse]] [[orbit]]-[[orbit raising|raising]] maneuvers, the system operates in a bipropellant fashion, providing high [[thrust]] at higher [[specific impulse]]; when it arrives on orbit, it closes off either the [[fuel]] or [[oxidizer]], and conducts the remainder of its mission in a simple, predictable monopropellant fashion.

==See also==
* [[Propulsion system]]
* [[Spacecraft propulsion]]

== References ==
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[[Category:Rocket propulsion]]
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