Editing Liquid-propellant rocket (section)

=== Non-cryogenic/storable/hypergolic ===
[[File:Messerschmitt Me 163B USAF.jpg|thumb|left| The [[NMUSAF]]'s Me 163B ''Komet'' rocket plane]]

Many non-cryogenic bipropellants are [[hypergolic propellant|hypergolic]] (self igniting).
* [[T-Stoff]] (80% hydrogen peroxide, H<sub>2</sub>O<sub>2</sub> as the oxidizer) and [[C-Stoff]] (methanol, {{chem2|CH3OH}}, and hydrazine hydrate, {{chem2|N2H4*''n''(H2O)}} as the fuel) – used for the Hellmuth-Walter-Werke [[HWK 109-509]]A, -B and -C engine family used on the [[Messerschmitt Me 163]]B Komet, an operational rocket fighter plane of [[World War II]], and [[Bachem Ba 349|Ba 349 ''Natter'']] crewed [[Takeoff#Vertical takeoff|VTO]] interceptor prototypes.
* [[Nitric acid]] (HNO<sub>3</sub>) and kerosene – [[Soviet Union|Soviet]] [[Bereznyak-Isayev BI-1|BI-1]] and [[Mikoyan-Gurevich I-270|MiG I-270]] rocket fighter prototypes, [[Scud]]-A, aka [[SS-1]] [[SRBM]]
* Inhibited red fuming nitric acid (I[[RFNA]], HNO<sub>3</sub> + N<sub>2</sub>O<sub>4</sub>) and unsymmetric dimethyl hydrazine ([[UDMH]], (CH<sub>3</sub>)<sub>2</sub>N<sub>2</sub>H<sub>2</sub>) – Soviet [[Scud]]-C, aka [[SS-1]]-c,-d,-e
* Nitric acid 73% with [[dinitrogen tetroxide]] 27% (AK27) and kerosene/gasoline mixture (TM-185) – various Russian (USSR) cold-war ballistic missiles ([[R-12 Dvina|R-12]], [[Scud]]-B,-D), [[Iran]]: [[Shahab-5]], [[North Korea]]: [[Taepodong-2]]
* [[High-test peroxide]] (H<sub>2</sub>O<sub>2</sub>) and kerosene – [[United Kingdom|UK]] (1970s) [[Black Arrow]], [[United States|USA]] Development (or study): BA-3200
* [[Hydrazine]] (N<sub>2</sub>H<sub>4</sub>) and [[red fuming nitric acid]] – [[MIM-3 Nike Ajax]] Anti-aircraft missile
* Unsymmetric dimethylhydrazine ([[UDMH]]) and [[dinitrogen tetroxide]] (N<sub>2</sub>O<sub>4</sub>) – [[Proton rocket|Proton]], [[Rokot]], [[Long March 2 (rocket family)|Long March 2]] (used to launch [[Shenzhou (spacecraft)|Shenzhou]] crew vehicles.)
* [[File:LGM-25C Titan II Test Launch.jpg|thumb|Titan II]][[Aerozine 50]] (50% UDMH, 50% hydrazine) and [[dinitrogen tetroxide]] (N<sub>2</sub>O<sub>4</sub>) – [[Titan (rocket family)|Titans 2–4]], Apollo [[lunar module]], Apollo [[service module]], interplanetary probes (Such as [[Voyager 1]] and [[Voyager 2]])
* [[Monomethylhydrazine]] (MMH, (CH<sub>3</sub>)HN<sub>2</sub>H<sub>2</sub>) and dinitrogen tetroxide (N<sub>2</sub>O<sub>4</sub>) – [[Space Shuttle orbiter]]'s [[orbital maneuvering system]] (OMS) engines and [[Reaction control system]] (RCS) thrusters. [[SpaceX]]'s [[Draco (rocket engine)|Draco]] and SuperDraco engines for the [[Dragon spacecraft]].

For [[storable propellant|storable]] [[ICBM]]s and most spacecraft, including crewed vehicles, planetary probes, and satellites, storing cryogenic propellants over extended periods is unfeasible. Because of this, mixtures of [[hydrazine]] or its derivatives in combination with nitrogen oxides are generally used for such applications, but are toxic and [[carcinogenic]]. Consequently, to improve handling, some crew vehicles such as [[Dream Chaser]] and [[Space Ship Two]] plan to use [[hybrid rocket]]s with non-toxic fuel and oxidizer combinations.