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The most common use of monopropellants [3] is in low-impulse monopropellant rocket motors, [4] such as reaction control thrusters, the usual propellant being hydrazine [5] [6] which is generally decomposed by exposure to an iridium [7] [8] catalyst bed (the hydrazine is pre-heated to keep the reactant liquid).
The power for the thruster comes from the high pressure gas created during the decomposition reaction that allows a rocket nozzle to speed up the gas to create thrust. The most commonly used monopropellant is hydrazine (N 2 H 4, or H 2 N−NH 2), a compound unstable in the presence of a catalyst and which is also a strong reducing agent.
Aerozine 50 is a mixture of 50% UDMH and 50% straight hydrazine (N 2 H 4). [5]: 45 Monomethylhydrazine (MMH) + nitrogen tetroxide (NTO) – smaller engines and reaction control thrusters: Apollo command and service module RCS, [20] Space Shuttle OMS and RCS; [21] Ariane 5 EPS; [22] Draco thrusters used by the SpaceX Dragon spacecraft. [23]
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 ...
Hydrazine is used as a low-power monopropellant for the maneuvering (RCS/Reaction control system) thrusters of spacecraft, and was used to power the Space Shuttle's auxiliary power units (APUs). In addition, mono-propellant hydrazine-fueled rocket engines are often used in terminal descent of spacecraft.
R-4D (MMH/NTO) – 100 lbf (exact thrust depends on variant) hypergolic thruster, originally developed by Marquardt as RCS thrusters for the Apollo SM and LM. Currently used as secondary engines on the Orion European Service Module, and as apogee motors on various satellite buses. MR103G — 0.2 lb hydrazine monopropellant thruster