Ion Engine - Revision history

Lwcamp: /* Example Engine Performance */

2026-02-20T05:58:51Z

Example Engine Performance

← Older revision		Revision as of 22:58, 19 February 2026
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	\|Drive Power		\|Drive Power
	\|<14.09 W (Calculated)<ref group="C">Drive Power = 1.25 mN thrust ~~<math alt=>\cdot</math>~~ 22,555 m/s exhaust velocity ~~<math alt=>/<~~/~~math>~~ 2</ref>		\|<14.09 W (Calculated)<ref group="C">Drive Power = 1.25 mN thrust · 22,555 m/s exhaust velocity / 2</ref>
	\|-		\|-
	\|Power Consumption		\|Power Consumption

Lwcamp at 05:56, 20 February 2026

2026-02-20T05:56:47Z

← Older revision		Revision as of 22:56, 19 February 2026
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	Most ion engines’ mechanisms involve knocking electrons out from a neutral gas, ionizing it, and using electromagnetic repulsion to accelerate it out of the engine. It is a scalable technology, with no upper limit as to how big they can get and the smallest ion engines are the size of your fingertip.		Most ion engines’ mechanisms involve knocking electrons out from a neutral gas, ionizing it, and using electromagnetic repulsion to accelerate it out of the engine. It is a scalable technology, with no upper limit as to how big they can get and the smallest ion engines are the size of your fingertip.

	Ionizing neutral gas requires significant power - a typical ratio requires kilowatts of power for a few hundred millinewtons of thrust. 100 millinewtons of thrust is comparable to the force exerted by about three grapes (10 grams) sitting on a table <ref> <~~math alt=~~>F=MA</~~math~~> where <~~math alt=~~>F</~~math~~> is force, <~~math alt=~~>M</~~math~~> is mass, and <~~math alt=~~>A</~~math~~> is acceleration. 10.2 grams times 9.8 m/s<sup>2</sup>, or the gravitational acceleration on Earth, is equal to 100 Millinewtons.</ref>. Even small chemical rockets, such as the 30 kg wet-mass [[Super Loki\|Super Loki]] sounding rocket’s motor produces a force of 9,550 Newtons, huge in comparison.		Ionizing neutral gas requires significant power - a typical ratio requires kilowatts of power for a few hundred millinewtons of thrust. 100 millinewtons of thrust is comparable to the force exerted by about three grapes (10 grams) sitting on a table <ref> <i>F</i> = <i>M</i> <i>a</i> where <i>F</i> is force, <i>M</i> is mass, and <i>a</i> is acceleration. 10.2 grams times 9.8 m/s<sup>2</sup>, or the gravitational acceleration on Earth, is equal to 100 Millinewtons.</ref>. Even small chemical rockets, such as the 30 kg wet-mass [[Super Loki\|Super Loki]] sounding rocket’s motor produces a force of 9,550 Newtons, huge in comparison.

	Ion drives have an advantage in exhaust velocity (20,000 to 50,000 meters per second is a useful range), which translates into specific impulse of 2039-5099 seconds. By way of comparison, the [[Raptor Engine\|Raptor]] engine used by SpaceX’s Starship has an exhaust velocity of 3,200 m/sec, and an Isp of 330 seconds. Since ion drives provide higher exhaust velocities, this allows for higher delta-v from the same mass-ratio, or the same delta-v for a smaller mass-ratio.		Ion drives have an advantage in exhaust velocity (20,000 to 50,000 meters per second is a useful range), which translates into specific impulse of 2039-5099 seconds. By way of comparison, the [[Raptor Engine\|Raptor]] engine used by SpaceX’s Starship has an exhaust velocity of 3,200 m/sec, and an Isp of 330 seconds. Since ion drives provide higher exhaust velocities, this allows for higher delta-v from the same mass-ratio, or the same delta-v for a smaller mass-ratio.
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	These figures are derived from the equation for kinetic energy:		These figures are derived from the equation for kinetic energy:

	<i>E</i> = <i>m</i> <i>v</i><sup>2</sup>/2~~</math>~~		<i>E</i> = <i>m</i> <i>v</i><sup>2</sup>/2
	* Where <i>E</i> is the particle's energy, <i>m</i> is the particle's mass, and <i>v</i> is the particle's velocity.		* Where <i>E</i> is the particle's energy, <i>m</i> is the particle's mass, and <i>v</i> is the particle's velocity.
	Which is rearranged to give velocity:		Which is rearranged to give velocity:

Lwcamp: /* Basic Electrostatic Ion Thruster Mathematics */

2026-02-20T05:54:11Z

Basic Electrostatic Ion Thruster Mathematics

← Older revision		Revision as of 22:54, 19 February 2026
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	The drive power of the electrostatic ion thruster can be calculated two ways, most simply with 1:		The drive power of the electrostatic ion thruster can be calculated two ways, most simply with 1:

	# <~~math alt=~~>P=vN/2</~~math~~>		# <i>P</i> = <i>v</i> <i>N</i>/2
	# <~~math alt=~~>P=AV</~~math~~>		# <i>P</i> = <i>A</i> <i>V</i>
	* Where <~~math alt=~~>A</~~math~~> is the amperage		* Where <i>A</i> is the amperage

	The equation for the amperage needed is:		The equation for the amperage needed is:

	<~~math alt=~~>A=~~\dot{m}~~/nq</~~math~~>		<i>A</i> = <i>ṁ</i> / (<i>n</i> <i>q</i>)
	* Where <~~math alt=~~>n</~~math~~> is the molar mass of the propellant.		* Where <i>n</i> is the molar mass of the propellant.

	==History & Development==		==History & Development==

Lwcamp: /* Basic Electrostatic Ion Thruster Mathematics */

2026-02-20T05:51:59Z

Basic Electrostatic Ion Thruster Mathematics

← Older revision		Revision as of 22:51, 19 February 2026
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	The thrust of the electrostatic ion thruster is given by:		The thrust of the electrostatic ion thruster is given by:

	<~~math alt=~~> N=v~~\dot{m}~~</~~math~~>		<i>N</i> = <i>v</i> <i>ṁ</i>
	* Where <~~math alt=~~>N</~~math~~> is the thrust of the thruster and <~~math alt=~~>~~\dot{m}~~</~~math~~> is the propellant mass flow rate.		* Where <i>N</i> is the thrust of the thruster and <i>ṁ</i> is the propellant mass flow rate.
	That can be rearranged to give mass flow rate instead:		That can be rearranged to give mass flow rate instead:
	<br/><~~math alt~~=>~~\dot{m}=~~N/v</~~math~~>		<br/><i>ṁ</i> = <i>N</i> / <i>v</i>

	The drive power of the electrostatic ion thruster can be calculated two ways, most simply with 1:		The drive power of the electrostatic ion thruster can be calculated two ways, most simply with 1:

Lwcamp: /* Basic Electrostatic Ion Thruster Mathematics */

2026-02-20T05:49:32Z

Basic Electrostatic Ion Thruster Mathematics

← Older revision		Revision as of 22:49, 19 February 2026
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	An electron or negatively charged ion with a charge of -1 leaving a hot cathode to an anode with a 100 V voltage difference between them will acquire an energy of 100 electron-Volts (or eV). A nanogram sized speck of dust with a million positive charges moving up a 10 V gradient will acquire an energy of 10 million electron-Volts (or MeV).		An electron or negatively charged ion with a charge of -1 leaving a hot cathode to an anode with a 100 V voltage difference between them will acquire an energy of 100 electron-Volts (or eV). A nanogram sized speck of dust with a million positive charges moving up a 10 V gradient will acquire an energy of 10 million electron-Volts (or MeV).

	The equation for how much energy <~~math alt=~~>E</~~math~~> a charged particle gains is:		The equation for how much energy <i>E</i> a charged particle gains is:

	<~~math alt=~~> E=qV </~~math~~>		<i>E</i> = <i>q</i> <i>V</i>
	* Where <~~math alt=~~>E</~~math~~> is the particle's energy, <~~math alt=~~>q</~~math~~> is the particle’s charge, and <~~math alt=~~>V</~~math~~> is the voltage.		* Where <i>E</i> is the particle's energy, <i>q</i> is the particle’s charge, and <i>V</i> is the voltage.

	The electron is a lightweight subatomic particle. 100 eV is enough to get it moving at 5929 km/s. The dust particle is relatively heavy. 10 MeV will just push it to 1.79 m/s. The velocity of the propellant is the exhaust velocity of the ion engine.		The electron is a lightweight subatomic particle. 100 eV is enough to get it moving at 5929 km/s. The dust particle is relatively heavy. 10 MeV will just push it to 1.79 m/s. The velocity of the propellant is the exhaust velocity of the ion engine.
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	These figures are derived from the equation for kinetic energy:		These figures are derived from the equation for kinetic energy:

	<~~math alt=~~> E=~~mv^~~2/2</math>		<i>E</i> = <i>m</i> <i>v</i><sup>2</sup>/2</math>
	* Where <~~math alt=~~>E</~~math~~> is the particle's energy, <~~math alt=~~>m</~~math~~> is the particle's mass, and <~~math alt=~~>v</~~math~~> is the particle's velocity.		* Where <i>E</i> is the particle's energy, <i>m</i> is the particle's mass, and <i>v</i> is the particle's velocity.
	Which is rearranged to give velocity:		Which is rearranged to give velocity:

	<~~math alt=~~>v=~~\sqrt{2E~~/m}</~~math~~>		<i>v</i> = √(2 <i>E</i> / <i>m</i>)

	The thrust of the electrostatic ion thruster is given by:		The thrust of the electrostatic ion thruster is given by:

Lwcamp: /* Propellant Considerations */

2026-02-20T05:46:11Z

Propellant Considerations

← Older revision		Revision as of 22:46, 19 February 2026
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	! Propellant Type !! 1st State Ionization energy !! Availability !! Toxicity !! Molar Mass <ref> https://www.webqc.org/mmcalc.php <br/> Reference for molar mass. </ref> !! Ionization Specific Energy <br/> (Calculated)<ref group="C2"> The formula to find the amount of energy needed to ionize some amount of mass of any material (ionization specific energy) is given by:		! Propellant Type !! 1st State Ionization energy !! Availability !! Toxicity !! Molar Mass <ref> https://www.webqc.org/mmcalc.php <br/> Reference for molar mass. </ref> !! Ionization Specific Energy <br/> (Calculated)<ref group="C2"> The formula to find the amount of energy needed to ionize some amount of mass of any material (ionization specific energy) is given by:
	:: <~~math alt=~~>i=I/M</~~math~~>		:: <i>i</i> = <i>I</i>/<i>M</i>
	<div style="padding-left: 50px;"> • where <~~math alt=~~>I</~~math~~> is the ionization energy of the material, <~~math alt=~~>M</~~math~~> is the molar mass of the material and <~~math alt=~~>i</~~math~~> is the ionization specific energy of the material. </div> </ref>		<div style="padding-left: 50px;"> • where <i>I</i> is the ionization energy of the material, <i>M</i> is the molar mass of the material and <i>i</i> is the ionization specific energy of the material. </div> </ref>
	\|-		\|-
	\| Xenon \|\| 1170.4 kJ/mol \|\| Uncommon \|\| Nontoxic \|\| 131.293 g/mol \|\| 8.914 MJ/kg		\| Xenon \|\| 1170.4 kJ/mol \|\| Uncommon \|\| Nontoxic \|\| 131.293 g/mol \|\| 8.914 MJ/kg

Tshhmon at 21:38, 23 April 2024

2024-04-23T21:38:29Z

← Older revision		Revision as of 14:38, 23 April 2024
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	* To MatterbeamToughSF for checking sources, technical details and contributing useful information		* To MatterbeamToughSF for checking sources, technical details and contributing useful information

	[[Category:Spacecraft Systems]]		[[Category:Spacecraft Systems]][[Category:Transportation & Infrastructure‏‎]][[Category:Transportation]][[Category:Propulsion]][[Category:Engines]][[Category:Rocket Science]]

Tshhmon at 16:20, 7 April 2024

2024-04-07T16:20:46Z

← Older revision		Revision as of 09:20, 7 April 2024
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	* To MatterbeamToughSF for checking sources, technical details and contributing useful information		* To MatterbeamToughSF for checking sources, technical details and contributing useful information

	[[Category:Spacecraft ~~& Infrastructure‏‎~~]]		[[Category:Spacecraft Systems]]

Tshhmon at 21:21, 15 March 2024

2024-03-15T21:21:59Z

← Older revision		Revision as of 14:21, 15 March 2024
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	[[Image:next.jpg\|thumb\|Image of NASA's Evolutionary Xenon Thruster (NEXT) operation in vacuum chamber. (Source: Wikipedia)]]		[[Image:next.jpg\|thumb\|400px\|Image of NASA's Evolutionary Xenon Thruster (NEXT) operation in vacuum chamber. (Source: Wikipedia)]]

	Ion engines are a form of electromagnetic propulsion using ions and other charged particles as propellant. They produce low, but constant, thrust for kilowatts of electrical power. The low particular mass of their propellant results in high exhaust velocities, or high specific impulse, giving them impressive amounts of delta-V for a given mass of propellant. Some more speculative designs can achieve higher thrust.		Ion engines are a form of electromagnetic propulsion using ions and other charged particles as propellant. They produce low, but constant, thrust for kilowatts of electrical power. The low particular mass of their propellant results in high exhaust velocities, or high specific impulse, giving them impressive amounts of delta-V for a given mass of propellant. Some more speculative designs can achieve higher thrust.
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	===Example Engine Performance===		===Example Engine Performance===
	[[Image:Busekbit-3.png\|thumb\|Image of Busek BIT-3 thruster in operation in vacuum chamber. (Source: Busek) Left: iodine. Right: xenon.]]		[[Image:Busekbit-3.png\|thumb\|600px\|Image of Busek BIT-3 thruster in operation in vacuum chamber. (Source: Busek) Left: iodine. Right: xenon.]]

	Example table for Engine Performance for Busek RF Gridded Electrostatic Ion Thrusters <ref> https://satsearch.co/products/busek-bit-3		Example table for Engine Performance for Busek RF Gridded Electrostatic Ion Thrusters <ref> https://satsearch.co/products/busek-bit-3

Tshhmon at 09:05, 24 September 2023

2023-09-24T09:05:22Z

← Older revision		Revision as of 02:05, 24 September 2023
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	<references group="C2"/>		<references group="C2"/>

			An important consideration is that the specific ionization energy refers primarily to the first ionization energy (i.e. the energy needed to strip the first electron off the atom.) Second, third, and other ionization energies are not given.

	==Engine Designs==		==Engine Designs==