Difference between revisions of "Propellant"
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In a [[chemical rocket]], the propellant is the reaction product of the [[oxidizer]] and the [[fuel]]. In a [[nuclear thermal rocket]], it is normally [[hydrogen]], since the [[specific impulse]] is dependant on the [[exhaust velocity]] of the rocket, which is higher for propellants with low [[molar mass]]. A [[laser ablation rocket]] will tend to use a combination of [[metal]] and [[plastic]] (due to their optical properties). | In a [[chemical rocket]], the propellant is the reaction product of the [[oxidizer]] and the [[fuel]]. In a [[nuclear thermal rocket]], it is normally [[hydrogen]], since the [[specific impulse]] is dependant on the [[exhaust velocity]] of the rocket, which is higher for propellants with low [[molar mass]]. A [[laser ablation rocket]] will tend to use a combination of [[metal]] and [[plastic]] (due to their optical properties). | ||
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| + | On Mars, propellant can be produced [[In-situ resource utilization|in-situ]] from water and CO2. Argon from the atmosphere could be used for electrical engines either solar or nuclear powered. | ||
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[[Category:Propulsion]] | [[Category:Propulsion]] | ||
Revision as of 08:05, 28 April 2019
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Propellant is mass which is ejected from a jet engine (of which a rocket is one possible type) to produce thrust through Newton's third law of motion.
In a chemical rocket, the propellant is the reaction product of the oxidizer and the fuel. In a nuclear thermal rocket, it is normally hydrogen, since the specific impulse is dependant on the exhaust velocity of the rocket, which is higher for propellants with low molar mass. A laser ablation rocket will tend to use a combination of metal and plastic (due to their optical properties).
On Mars, propellant can be produced in-situ from water and CO2. Argon from the atmosphere could be used for electrical engines either solar or nuclear powered.
