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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 .
Minimizing the mass of propellant required to achieve a given change in velocity is crucial to building effective rockets. The Tsiolkovsky rocket equation shows that for a rocket with a given empty mass and a given amount of propellant, the total change in velocity it can accomplish is proportional to the effective exhaust velocity.
It became the propellant for most of the early American rockets and ballistic missiles such as the Atlas, Titan I, and Thor. The Soviets quickly adopted RP-1 for their R-7 missile, but the majority of Soviet launch vehicles ultimately used storable hypergolic propellants. As of 2017, it is used in the first stages of many orbital launchers.
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 ...
Rocket engines using hydrogen peroxide propellant (3 C, 1 P) Pages in category "Rocket engines using hypergolic propellant" The following 87 pages are in this category, out of 87 total.
It is powered by a hypergolic mixture of unsymmetrical dimethylhydrazine (UDMH) fuel with dinitrogen tetroxide (N 2 O 4) oxidizer. [2] This combination is hypergolic, meaning the two substances ignite on contact, eliminating the need for an external ignition source. The RD-855 can orient its chambers within a range of ±42° using hydraulic ...
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]
Nitrous oxide fuel blend propellants are a class of liquid rocket propellants that were intended in the early 2010s to be able to replace hydrazine as the standard storable rocket propellent in some applications. In nitrous-oxide fuel blends, the fuel and oxidizer are blended and stored; this is sometimes referred to as a mixed monopropellant.