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A total of 100 bench tests of liquid-propellant rockets were conducted using various types of fuel, both low and high-boiling and thrust up to 300 kg was achieved. [19] [18] During this period in Moscow, Fredrich Tsander – a scientist and inventor – was designing and building liquid rocket engines which ran on compressed air and gasoline ...
Konstantin Tsiolkovsky proposed the use of liquid propellants in 1903, in his article Exploration of Outer Space by Means of Rocket Devices. [3] [4] On March 16, 1926, Robert H. Goddard used liquid oxygen (LOX) and gasoline as propellants for his first partially successful liquid-propellant rocket launch. Both propellants are readily available ...
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.
The XLR11, company designation RMI 6000C4, was the first liquid-propellant rocket engine developed in the United States for use in aircraft. It was designed and built by Reaction Motors Inc. , and used ethyl alcohol and liquid oxygen as propellants to generate a maximum thrust of 6,000 lbf (27 kN).
The Reaction Motors LR99 engine was the first large, throttleable, restartable liquid-propellant rocket engine. Development began in the 1950s by the Reaction Motors Division of Thiokol Chemical Company to power the North American X-15 hypersonic research aircraft.
The XLR50 was a pump-fed liquid-propellant rocket engine burning RP-1 and LOX in a gas generator cycle developed by General Electric. [3] It was used to power the first stage of the Vanguard rockets on the Vanguard project.
The rocket is launched using liquid hydrogen and liquid oxygen cryogenic propellants. Rocket propellant is used as reaction mass ejected from a rocket engine to produce thrust . The energy required can either come from the propellants themselves, as with a chemical rocket , or from an external source, as with ion engines .
The RD801 (Ukrainian: РД801) is a Ukrainian liquid propellant rocket engine burning LOX and Kerosene in a staged combustion cycle. [4] It has a single combustion chamber that provides thrust vector control by gimbaling of the nozzle in two axis by +/- 6°.