* RS-27A – RP-1 engine currently used in the US Delta II launcher ; Saturn 1B H-1 heritage.

The RS-27A is a liquid-fuel rocket engine developed by Rocketdyne for use on the first stage of the Delta II and Delta III launch vehicles.

The typical formula included maraging steel ( HY-140 ) for structure, pressure-fed engines using N2O4 / UDMH, later LOX / RP-1, with pintle injectors scaled up from TRW's Lunar Module Descent Engine ( LMDE ).

* H-1 ( RP-1 / LOX ) Used by the Saturn I, Ib, Jupiter, and some Delta rockets

* F-1 ( RP-1 / LOX ) Used by the Saturn V.

Also the RP-1 / LOX combination has become a popular choice for reliable and cost-sensitive commercial spaceflight applications.

The Merlin LOX / RP-1 turbopump was developed and is manufactured by Barber-Nichols.

The Kestrel engine is an LOX / RP-1 pressure-fed rocket engine.

The single B-1 design replaced the intermediate with an all-new 220 " LOX / RP-1 design using four of the H-1 engines that the lower stage also used, along with a new four-engine third stage derived from Centaur but in a 220 " diameter.

The H-1 engine is a thrust LOX / RP-1 engine, used alone in the first stages of some Delta rockets and the Jupiter rocket.

The Titan I and Atlas ICBMs using RP-1 / LOX fuel did not have a quick launch sequence.

* RD-58 upper stage RP-1 / LOX engine used in the N-1 rocket, derivatives used in the Proton and Zenit rockets

It was the first in a series of Titan rockets, but was unique among them in that it used LOX and RP-1 as its propellants, while the later Titan versions all used storeable fuels instead.

The fact that Titan I, like Atlas, burned RP-1 and LOX meant that the oxidizer had to be loaded onto the missile just before launch from the underground storage tank, and the missile raised above ground on the enormous elevator system, exposing the missile for some time before launch.

In total there were 89 trailer-truck loads of LOX ( liquid oxygen ), 28 trailer loads of LH2 ( liquid hydrogen ), and 27 rail cars of RP-1 ( refined kerosene ).

* liquid oxygen ( LOX ) and kerosene or RP-1 – Saturn V, Zenit rocket, R-7 Semyorka family of Soviet boosters which includes Soyuz, Delta, Saturn I, and Saturn IB first stages, Titan I and Atlas rockets

The F-1 was a liquid-fueled rocket motor, burning RP-1 ( kerosene ) as fuel, and using liquid oxygen ( LOX ) as the oxidizer.

This equated to a flow rate of of LOX and RP-1 per second.

Rocketdyne's H-1 is a thrust liquid-propellant rocket engine burning LOX and RP-1.

* LOX and kerosene ( RP-1 ).

The propellant containers consisted of eight Redstone tanks ( four holding LOX and four holding RP-1 ) clustered around a Jupiter rocket tank containing LOX.

It was a two-stage rocket powered by RP-1 and LOX.

The fuels were pushed into the engine by liquid nitrogen, which provided a pressure of 32 atm for the RP-1 and 17 atm for the LOX, providing a total pressure in the engine of 20 atm (~ 300 psi ) at takeoff.

This bipropellant engine burns the Russian equivalent of RP-1 fuel and LOX oxidizer in four combustion chambers supplied by a single turbo pump according to a staged combustion cycle and is rated at 170 MW.

It provides 1. 05 meganewtons of thrust burning RP-1 and LOX in a gas-generator cycle.

In the initial phase of liftoff, the Saturn V launch vehicle was powered by the reaction of liquid oxygen with RP-1.

For instance the Saturn Vs used a lower stage powered by RP-1 ( kerosene ) and upper stages powered by LH2.

The first stage of Falcon 5 was to be powered by five Merlin engines and the upper stage by one Merlin engine, both burning RP-1 with a liquid oxygen oxidizer.

* NK-33 – RP-1 engine used on Soviet N1, currently slated for use by Orbital Sciences in Antares launcher.

It will be powered by high-test peroxide ( HTP ) and RP-1 kerosene.

The first stage was to be powered by a single enormous thrust engine burning RP-1 and liquid oxygen.

The CCB is 12. 5 ft ( 3. 8 m ) in diameter by 106. 6 ft ( 32. 5 m ) long and uses 627, 105 lb ( 284, 450 kg ) of liquid oxygen and RP-1 rocket fuel propellants.

Heavy variants of Angara will be simpler and cheaper than Proton ( and like the new Atlas V rocket, will not use hypergolics ; instead, it will use the same RP-1 fuel as that used on the Soyuz rocket ).

* RD-180 – RP-1 engine currently used in the first-stage of the US Atlas V launcher.

* Licofelone acts by inhibiting LOX ( lipooxygenase ) & COX and hence known as 5-LOX / COX inhibitor

The A-4 used a 75 % ethanol / water mixture for fuel and liquid oxygen ( LOX ) for oxidizer.

At that point the engine is largely a straight LH2 / LOX engine, with an extra fuel pump hanging onto it.

* Raptor ( rocket stage ), a LOX / LH2 powered rocket upper stage being developed by SpaceX

CSULB students had developed their Prospector 2 ( P-2 ) rocket using a 1, 000 lb < sub > f </ sub > ( 4. 4 kN ) LOX / ethanol aerospike engine.

In a LOX / LH2 bipropellant rocket the liquid oxygen needed for combustion is the majority of the weight of the spacecraft on lift-off, so if some of this can be collected from the air on the way, it might dramatically lower the take-off weight of the spacecraft.

LOX is dense ( 1. 141 kg / L ), whereas LH2 has a very low density ( 0. 0678 kg / L ) and is therefore very bulky.

The main advantage of hydrogen rocket fuel is the high effective exhaust velocity compared to kerosene / LOX or UDMH / NTO engines.

The disadvantages of LH2 / LOX engines are the low density and low temperature of liquid hydrogen, which means bigger and insulated and thus heavier fuel tanks are needed.

The third stage had one LOX / LH2 bipropellant engine capable of a thrust of 7, 000 kgf ( 69 kN ).

* J-2 ( LH2 / LOX ) Used by both the Saturn V and Saturn IB.

* Space Shuttle Main Engine ( SSME ) ( LH2 / LOX ) The main engine for the Space Shuttle

* RS-68 ( LH2 / LOX ) Used by the Delta IV first stage

The Space Shuttle system requires extensive refurbishing between flights, primarily dealing with the silica tile TPS and the high performance LH2 / LOX burning main engines.

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** Propellants: LOX / Kerosene ( Thor kerosene propellant was referred to as ' RP1 ' by RAF users )

The Roton engine had a projected vacuum I < sub > SP </ sub > ( specific impulse ) of ~ 355 seconds ( 3. 5 kN · s / kg ), which is very high for a LOX / kerosene engine – and a thrust to weight ratio of 150, which is extremely light.