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A hypergolic propellant is a rocket propellant combination used in a rocket engine, whose components spontaneously ignite when they come into contact with each other. The two propellant components usually consist of a fuel and an oxidizer .
Aerozine is not used as a monopropellant (a propellant that is not mixed with anything). The extra stability conferred by the methyl groups affects reactivity and thrust. In 1980, an accidental leakage of Aerozine 50 resulted in the 1980 Damascus Titan missile explosion. The leak occurred due to puncture of the first-stage Titan fuel tank by a ...
Apogee engines typically use one fuel and one oxidizer. This propellant is usually, but not restricted to, [7] a hypergolic combination such as: N 2 H 4 / N 2 O 4, MMH/ N 2 O 4, UDMH/ N 2 O 4. Hypergolic propellant combinations ignite upon contact within the engine combustion chamber and offer very high ignition reliability, as well as the ...
The ascent propulsion system (APS) or lunar module ascent engine (LMAE) is a fixed-thrust hypergolic rocket engine developed by Bell Aerosystems for use in the Apollo Lunar Module ascent stage. It used Aerozine 50 fuel, and N 2 O 4 oxidizer.
Download as PDF; Printable version; ... Rocket engines using hydrogen peroxide propellant (3 C, 1 P) Pages in category "Rocket engines using hypergolic propellant"
On February 1, 2012 SpaceX announced that it had completed the development of a new, more powerful storable-propellant rocket engine, this one called SuperDraco. This high-thrust hypergolic engine—about 200 times larger than the Draco RCS thruster hypergolic engine—offers deep throttling ability and just like the Draco thruster, has multiple restart capability and uses the same shared ...
Both propellants are extremely dangerous individually: nitric acid is highly corrosive and releases toxic nitrogen dioxide during reactions, or even simply while exposed to air in its highly concentrated "red fuming" form, typically used as rocket propellant. UDMH is both toxic and corrosive.
Aestus is a hypergolic liquid rocket engine used on an upper stage of Ariane 5 family rockets for the orbital insertion. It features unique design of 132 coaxial injection elements causing swirl mixing of the MMH propellants with nitrogen tetroxide oxidizer. The pressure-fed engine allows for multiple re-ignitions.