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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 .
A hypergolic derivative of the RS-88, fueled by monomethylhydrazine (MMH) and nitrogen tetroxide, was chosen as the launch escape motor for the Boeing Starliner capsule. [3] This variant, called the Launch Abort Engine (LAE), provides 176.6 kN (39,700 lb f ) of thrust. [ 4 ]
Specific impulse (usually abbreviated I sp) is a measure of how efficiently a reaction mass engine, such as a rocket using propellant or a jet engine using fuel, generates thrust.
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 ...
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 ...
This is a short table intended for use in rocket, rocket engine, etc. of the performance of common propellant mixes. It's intended to have only about 10 entries at most; it is NOT a complete list. Table has been edited to include actual vacuum performance of rocket engines instead of theoretical maximum Isp.
The Vikas (a portmanteau from initials of VIKram Ambalal Sarabhai [5] [6]) is a family of hypergolic liquid fuelled rocket engines conceptualized and designed by the Liquid Propulsion Systems Centre in the 1970s. [7] [8] The design was based on the licensed version of the Viking engine with the chemical pressurisation system. [9]
Embodying a pressure-fed fuel system using hypergolic (self-igniting) propellants, the ascent engine was fixed-thrust and nongimbaled, capable of lifting the ascent stage off the Moon or aborting a landing if necessary.