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Monomethylhydrazine (MMH) is a highly toxic, volatile hydrazine derivative with the chemical formula CH 6 N 2. It is used as a rocket propellant in bipropellant rocket engines because it is hypergolic with various oxidizers such as nitrogen tetroxide (N 2 O 4) and nitric acid (HNO 3). As a propellant, it is described in specification MIL-PRF ...
The most common hypergolic fuels, hydrazine, monomethylhydrazine and unsymmetrical dimethylhydrazine, and oxidizer, nitrogen tetroxide, are all liquid at ordinary temperatures and pressures. They are therefore sometimes called storable liquid propellants. They are suitable for use in spacecraft missions lasting many years.
Draco are hypergolic liquid-propellant rocket engines that utilize a mixture of monomethyl hydrazine fuel and nitrogen tetroxide oxidizer. Each Draco thruster generates 400 newtons (90 lbf) of thrust. [26] They are used as Reaction Control System (RCS) thrusters on both the Dragon spacecraft, and on the Falcon 9 launch vehicle second-stage. [27]
Draco thrusters generate 400 newtons (90 pounds-force) of thrust using a storable propellant mixture of monomethyl hydrazine fuel and nitrogen tetroxide oxidizer.The Draco thrust is comparable to the Marquardt R-4D engine developed for the Apollo Service and Lunar Modules in the 1960s and used for apogee/perigee maneuvers, orbit adjustment, and attitude control.
Dual mode propulsion systems combine the high efficiency of bipropellant rockets with the reliability and simplicity of monopropellant rockets. [1]Dual mode systems are either hydrazine/nitrogen tetroxide, or monomethylhydrazine/hydrogen peroxide (the former is much more common).
The Launch Abort Engine fires during a pad abort test of Starliner. 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]
The highest-specific-impulse chemistry ever test-fired in a rocket engine was lithium and fluorine, with hydrogen added to improve the exhaust thermodynamics (all propellants had to be kept in their own tanks, making this a tripropellant). The combination delivered 542 s specific impulse in vacuum, equivalent to an exhaust velocity of 5320 m/s.
Aerozine continues in wide use as a rocket fuel, typically with dinitrogen tetroxide (N 2 O 4) as the oxidizer, with which it is hypergolic. Aerozine 50 is more stable than hydrazine alone, and has a higher density and boiling point than UDMH alone. Pure hydrazine has a higher performance than Aerozine 50, but an inconvenient freezing point of ...