oxidiser

This is the only part of the craft, other than the fuel and oxidiser themselves, that must be replaced.

Several different fuel/oxidiser combinations have been used in heavy lift launch vehicles.

Fuel and oxidiser are stored in two tanks of 390 litres each.

Because the oxidiser is stored under pressure, no pump is required.

It has an oxidiser tank and associated fittings identical to the one used in flight.

It is a yellowish solid that is a strong oxidiser.

Big spherical propellant and oxidiser tanks are fixed to the floor.

It is highly corrosive and an extremely powerful oxidiser.

In rockets, the most common combinations are bipropellants, which use two chemicals, a fuel and an oxidiser.

The launch failed due to a leak in the second stage oxidiser pressurisation system, which caused it to cut out early.

The oxidiser is either kept separate and mixed in the combustion chamber, or comes premixed, as with solid rockets.

Firstly, as the pressure in the oxidiser tank decreases, the flow rate reduces, reducing thrust.

Due to the optimum mixture ratio being about 7, a larger oxidiser tank was required compared to many contemporary launch systems.

At elevated temperatures, nitrous oxide is a powerful oxidiser similar to molecular oxygen.

During the launch, the first stage sustainer engine failed to shut down on time, and instead burned until all of its oxidiser had been depleted.

An oxidiser supports the burning of fuel much like oxygen supports burning.

Four seconds after liftoff, the engine overheated and burned through its gas generator, severing an oxidiser line.

Both the fuel and oxidiser can be stored without special precautions, and they do not burn when brought together without a significant source of heat.

As a result, the scope of the chemistry of O is quite limited, acting mainly as a 1-electron oxidiser.

Less frequently are reverse-hybrid propellant systems with a liquid fuel (injectant) and a solid oxidiser.

(The oxidiser side of the engine and tankage is of course unaffected.)

The dry weight of a spacecraft is the mass of the spacecraft without oxidiser, fuel or other consumables.

This is achieved by combusting a solid, liquid or gaseous fuel with an oxidiser within a combustion chamber.

The oxidiser fill, vent, and dump system is supplied by Environmental Aeroscience Corporation.

Due to the limited types of missile that could be carried and the lack of precautions for oxidiser leaks this version was not pursued further.