Difference between revisions of "Propellant"
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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. | 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]] | + | == Chemical propulsion == |
| + | In a [[chemical rocket]], the propellant is the reaction product of the [[oxidizer]] and the [[fuel]]. | ||
| − | On Mars, propellant can be produced [[In-situ resource utilization|in-situ]] from water and CO2. Argon from the atmosphere could be used for | + | == Nuclear thermal propulsion == |
| + | In a [[nuclear thermal rocket]], it is normally [[hydrogen]], since the [[specific impulse]] is dependent on the [[exhaust velocity]] of the rocket, which is higher for propellants with low [[molar mass|molar m]] | ||
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| + | == Nuclear or Solar Electric propulsion == | ||
| + | For [[Ion thruster|Ion thrusters]], an easily ionized gas is preferred. Vaporized liquid metals are good candidates. As for nuclear rockets, the lower the molar mass the higher the exhaust velocity. However, as electric engines work on ionized gases, the ionization energy of the propellant adds complexity to the engine and favors elements that are easy to ionize. The nobles gases, such as [[Argon]], [[Neon]] [[Krypton]] and [[Xenon]] are all usable, with Krypton achieving the best propulsion properties for many missions. | ||
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| + | == Laser ablation propulsion == | ||
| + | A [[laser ablation rocket]] will tend to use a combination of [[metal]] and [[plastic]] (due to their optical properties). | ||
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| + | == Propellant production on Mars == | ||
| + | On Mars, propellant can be produced [[In-situ resource utilization|in-situ]] from water and CO2. Argon from the atmosphere could be used for NEP or SEP. | ||
[[Category:Propulsion]] | [[Category:Propulsion]] | ||
Revision as of 12:31, 30 August 2021
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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.
Contents
Chemical propulsion
In a chemical rocket, the propellant is the reaction product of the oxidizer and the fuel.
Nuclear thermal propulsion
In a nuclear thermal rocket, it is normally hydrogen, since the specific impulse is dependent on the exhaust velocity of the rocket, which is higher for propellants with low molar m
Nuclear or Solar Electric propulsion
For Ion thrusters, an easily ionized gas is preferred. Vaporized liquid metals are good candidates. As for nuclear rockets, the lower the molar mass the higher the exhaust velocity. However, as electric engines work on ionized gases, the ionization energy of the propellant adds complexity to the engine and favors elements that are easy to ionize. The nobles gases, such as Argon, Neon Krypton and Xenon are all usable, with Krypton achieving the best propulsion properties for many missions.
Laser ablation propulsion
A laser ablation rocket will tend to use a combination of metal and plastic (due to their optical properties).
Propellant production on Mars
On Mars, propellant can be produced in-situ from water and CO2. Argon from the atmosphere could be used for NEP or SEP.
