A more conventional bipropellant could more than double the specific impulse.

Pentaborane was also investigated to be used as a bipropellant with nitrogen tetroxide.

All current spacecraft use chemical rocket engines (bipropellant or solid-fuel) for launch.

The body is built around the main propulsion system, which consists of a bipropellant 400 N main engine.

Boeing asserts that this is "a fraction of what bipropellant or arcjet systems consume".

The fuel will be a methane-oxygen bipropellant.

It combines the simplified plumbing of a monopropellant with the performance of a bipropellant.

Propulsion for the rocket will be a mix of solid rocket and liquid rocket bipropellant technology.

Most Spacebus satellites use bipropellant, liquid-fuelled chemical engines to achieve their orbits, and subsequently perform station-keeping.

Propulsion was furnished by a bipropellant (monomethylhydrazine and nitrogen tetroxide) liquid-fueled rocket engine which could be gimballed up to 9 degrees.

Attitude was controlled by a Sun-star sensor with attitude correction performed by a dimethylhydrazine/nitric acid bipropellant rocket engine.

The engines are high pressure, regeneratively cooled staged combustion cycle bipropellant rocket engines, and use oxygen-rich preburners to drive the turbopumps.

When used with a suitable catalyst, HTP can be used as a monopropellant, or with a separate fuel as a bipropellant.

Both use bipropellant, namely monomethylhydrazine (MMH) as fuel and mixed oxides of nitrogen (MON3) as oxidizer.

The R-36 (SS-9) is a two-stage rocket powered by a liquid bipropellant, with UDMH as fuel and nitrogen tetroxide as an oxidizer.

All current spacecraft use chemical rockets (bipropellant or solid-fuel) for launch, though some (such as the Pegasus rocket and SpaceShipOne) have used air-breathing engines on their first stage.

This vehicle lands and fuels itself using a Sabatier process, creating methane/oxygen rocket fuel (bipropellant) out of carbon dioxide obtained from the Martian atmosphere and a relatively small amount of hydrogen imported from Earth.

UDMH is often used in hypergolic rocket fuels as a bipropellant in combination with the oxidizer nitrogen tetroxide and less frequently with IRFNA (red fuming nitric acid) or liquid oxygen.

In a vacuum thruster, this can provide a monopropellant specific impulse (I) of as much as 180 s. While noticeably less than the I available from hydrazine thrusters (monopropellant or bipropellant with nitrogen tetroxide), the decreased toxicity makes nitrous oxide an option worth investigating.

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.