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Ion engines are an electric thruster type that uses charged particles as propellant. Particle sizes range from subatomic particles to small grains of dust. Propellant is ejected from a nozzle using electrostatic or electromagnetic forces. Generally, they have very high exhaust velocities and little thrust.
[[Image:next.jpg|thumb|400px|Image of NASA's Evolutionary Xenon Thruster (NEXT) operation in vacuum chamber. (Source: Wikipedia)]]


Thrust power has to be handled by components such as wires, electrostatic tubes or magnetic coils. These are usually heavy and limited to a low operating temperature, so the specific power of an ion engine is much lower than a thermal rocket. After including the power generating system and the radiators to remove waste heat, we get a propulsion system that accelerates slowly.  
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.


The low acceleration of ion engines means spacecraft generally have to use less efficient spiral trajectories near planets with a strong gravitational field, and have to forgo the benefits of Oberth burns. Trying to take off from a planet will usually require an entirely different propulsion system with better thrust. The ion drive’s high exhaust velocity means that an impressive amount of deltaV is possible with a small propellant load. A spaceship with ion engines can accelerate to huge velocities given enough time; the greater the distance required, the likelier it is that an ion drive can get you there in less time.  
The low acceleration of ion engines means spacecraft generally have to use less efficient [[Spiral Trajectories|spiral trajectories]] near planets with a strong gravitational field, and have to forgo the benefits of [[Gravity Assists and Oberth Effect|Oberth burns]]. They are a common propulsion choice for satellites and as interplanetary transit engines for spacecraft. They are a poor choice for any use that requires high thrust and short impulsive burns, and cannot make [[Hohmann Transfer|Hohmann orbit transfers]] efficiently.  


==Introduction==
==Introduction==
Ion engines are not a modern technology, but have only recently been embraced by aerospace companies. Satellite manufacturers are relying on ion engines to perform station-keeping over the course of decades. Interplanetary probes use them for deep space maneuvers, or to cut down on the size of the spacecraft needed to reach planets like Mercury or Jupiter.  
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.  


This is all thanks to it being a highly scalable solution with a high specific impulse, leading to kilometers per second of deltaV with low mass ratios. The smallest ion engines are the size of your fingertip, and they have no upper limit to how large and powerful they can get.  
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.


Most development of ion engines happens at small scales, aimed at CubeSat-sized missions. These engines consume a few watts to a few hundred watts of power, with their thrust being measured in milliNewtons. Their main challenge is efficiency. Converting electrical current from the voltage that is produced by solar panels to the voltage used by the engine, ionizing the propellant flow, energizing the nozzle coils and even resistance in the wires become disproportionately large losses. Less watts come out of the engine as exhaust than is spent doing all these other tasks.
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.


There is also research into making larger ion engines. Existing record-holding designs climb into the hundreds of kilowatts. Their efficiency improves, as does their specific power. However, some designs run into endurance limits. Solid electrodes are eroded after being held at high temperatures, ceramic chambers suffer from sputtering and electric grids wither away when bombarded by ions. Solutions like electrodeless thrusters are necessary to run these engines for long durations.
The tradeoff of high exhaust velocity and low thrust makes ion engines ideally suited to orbit-to-orbit missions; for anything that requires higher thrust, like getting things out of even a modest gravity well, you’ll need a second rocket with higher thrust. Ion engines are well-suited for satellite orbital maneuvering, and long duration spacecraft missions between planets. Ion drives work best for Ward-spiral style interplanetary transits as lowest delta-V Hohmann transfers require a short burn of high thrust to work; Ion drives will get your payload or passengers to their destination with a smaller fuel fraction and/or less time. Ion engines do not provide enough thrust for [[Brachistochrone Transfer|brachistochrone transfers]].


Ion engines naturally have low thrust due to their high exhaust velocity. The electrical generation system and radiator requirements quickly add mass that reduces the overall specific power of the propulsion system. Low specific power and low thrust means much lower acceleration than a thermal engine of the same power level. Prolonged burns are needed to get anywhere.  
Where ion engines shine are missions where long-duration accelerations are key to mission success. Delta-V in the tens of kilometers per second are possible even with today’s technology. They can drastically reduce the travel time between planets and if given enough time, cover great distances. Their low acceleration is not a major hindrance in accelerating in interplanetary space, overcoming solar gravity, or around the reduced surface gravities of the numerous small bodies in our solar system.  


Low acceleration limits ion engines are only suited for transfers from one orbit in space to another. Strong gravity bends the trajectories they can take into a series of tight spirals that cost a lot more deltaV than the simple Hohmann transfers a high-thrust engine could use. A spaceship equipped with an ion engine that tries to climb from Low Earth Orbit to reach the Moon could take months and require more than twice the deltaV of a chemical rocket. The low thrust of ion engines prevents them from overcoming the gravity of a planet for a surface takeoff, exploiting the Oberth effect or making use of powered gravitational assists.  
===Example Engine Performance===
[[Image:Busekbit-3.png|thumb|600px|Image of Busek BIT-3 thruster in operation in vacuum chamber. (Source: Busek) Left: iodine. Right: xenon.]]


Where ion engines shine are missions where long-duration accelerations are key to mission success. DeltaVs in the tens of kilometers per second are possible even with today’s technology. They can drastically reduce the travel time between planets and if given enough time, cover great distances. Their low acceleration is not a major hindrance in accelerating in interplanetary space, overcoming solar gravity,.or around the reduced surface gravities of the numerous small bodies in our solar system.
Example table for Engine Performance for Busek RF Gridded Electrostatic Ion Thrusters <ref> https://satsearch.co/products/busek-bit-3
 
<br/> The example table thruster </ref>
===Engine Performance===
Example table for Engine Performance for Busek RF Gridded Electrostatic Ion Thrusters
{| class="wikitable"
{| class="wikitable"
|+
|+
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|-
|-
|Efficiency
|Efficiency
|17.6% (Calculated)*
|17.6% (Calculated)<ref group="C">Drive Power / Power Consumption (80 W) = 0.176 </ref>
|-
|-
|Drive Power
|Drive Power
|<14.09 W (Calculated)**
|<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>
|-
|-
|Power Consumption
|Power Consumption
Line 57: Line 56:
|Grids
|Grids
|-
|-
|Specific Density
|Specific Power
|10.9 W/kg (Calculated)
|10.9 W/kg (Calculated)
|}
|}
Calculated Figures:
<references group="C"/>


==Design and Function==
==Design and Function==
There are three main steps in an ion engine’s operation.
There are two usual steps in an ion engine’s operation:
-Delivering propellant
* Creating charged propellant
-Creating charged particles
* Accelerating the charged propellant
-Accelerating charged particles
 
Creating charged propellant is usually done by ionizing it, through a variety of methods like electron guns or heating the propellant to plasma temperatures. It must be accelerated through electromagnetic means such as a voltage difference between grids, or oscillating electric and magnetic fields. This is the primary working principle of ion engines.


Ion engines conduct these steps in a variety of ways, depending on their exact model. The NSTAR ion engine used on the Dawn space probe used xenon gas as propellant. The gas was piped into a chamber where an electron gun knocked off charges from the xenon atoms, giving them a positive charge and making them xenon ions. Once inside the chamber, the ions were held by a magnetic field to improve ionization efficiency. Eventually, the ions would diffuse out of the chamber and into the gap between a pair of charged grids. The voltage difference between the grids accelerated the ions out of the engine, producing thrust, and shunting free electrons back into the chamber. A second electron gun fired electrons into the exhaust to neutralize it.
There are multiple factors in ion engine design as well, such as reliability, cost and/or simplicity and lifetime. In particular, when long lifetimes are needed - electrode-less ion thruster designs can be used, sidestepping the problem of propellant induced erosion on the electrodes.


While NSTAR’s xenon engine is efficient, there are several other ways to achieve the three steps listed above. For example, a liquid propellant could be sprayed in the form of droplets, charged particles could be created by the action of radiofrequency waves and the propellant could be accelerated by powerful magnetic pulses. Each method has its own advantages and disadvantages, but in general, designers of ion engines strive to minimize the portion of electrical energy spent ionizing the propellant and maximizing how much is spent sending it out the nozzle. This has an impact on the choice of propellant. Ion engines that use mercury need 5.02 MJ/kg, while xenon requires  8.91 MJ/kg. A thruster that aims for a higher exhaust velocity at the expense of thrust has a lower propellant flow; this allows mission planners to spend more of their launch payload on useful hardware, rather than propellant.
===Propellant Considerations===


Here is a list of elements by their ionization energy in MJ/kg:
Ion engines can suffer significant inefficiency as ionizing the propellant may take significant amounts of energy input, thus designers focus on minimizing the amount of electricity spent in ionizing the propellant, influencing things like what propellant to use. A thruster that aims for a higher exhaust velocity at the expense of thrust has a lower propellant flow and allows mission planners to spend more of their launch payload on useful hardware, rather than propellant.


Note that ion engines can be designed to use a huge number of propellants, including molecules, dust particles, liquid metals and more. Ionization energy is an important parameter but many other factors come into play.
The ideal propellant choice is easy to ionize and has a high mass to ionization energy ratio <ref> https://en.wikipedia.org/wiki/Ionization_energy <br/> Reference for ionization energy ratio. </ref>. Another consideration is erosion, which limits the life-time of thrusters with electrodes<ref>https://en.wikipedia.org/wiki/Ion_thruster#Lifetime<br/> Reference for erosion. </ref>. Some otherwise excellent propellants are toxic (mercury) or toxic and carcinogenic (cadmium). Additionally, being able to source propellants without significant processing overhead may be a desirable advantage; the colloid thrusters can use finely ground regolith as a propellant.  


For example, many of the elements with the lowest ionization energy per kilogram are highly radioactive and solid up to extreme temperatures. They would be a pain to handle! Other options may be toxic (mercury) or carcinogenic (cadmium). Erosion from reactive species like potassium must be considered. As is the availability and ease of production of a propellant if ISRU is something you want. Xenon may be a great choice for most electric thrusters, but it is much harder to find in our solar system than nitrogen.
Balancing these considerations (except the processing and availability concerns) have led to xenon and krypton being common choices for electrostatic ion thrusters. They are high Z (Z is the proton number, therefore having more mass per atom), inert and require less energy to ionize. For gridless ion thrusters, like the Hall effect ion thrusters, bismuth and iodine are also available.


Some ion engine designs are flexible enough to use multiple propellants, or mixes that meet certain specifications. For example, airbreathing electric ramjets use different nitrogen, oxygen and hydrogen ratios depending on which orbital altitude they operate at.  
Some ion engine designs are flexible enough to use multiple propellants, or mixes that meet certain specifications. For example, airbreathing electric ramjets use different nitrogen, oxygen and hydrogen ratios depending on which orbital altitude they operate at.  


With all these options and possibilities in mind, we can reduce ion engines into two main categories:
{| class="wikitable sortable"
|-
! 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>
<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>
|-
| Xenon || 1170.4 kJ/mol || Uncommon || Nontoxic || 131.293 g/mol || 8.914 MJ/kg
|-
| Krypton || 1350.8 kJ/mol || Uncommon || Nontoxic || 83.798 g/mol || 16.12 MJ/kg
|-
| Argon || 1520.6 kJ/mol || Uncommon || Nontoxic || 39.948 g/mol || 38.064 MJ/kg
|-
| Mercury || 1007.1 kJ/mol || Rare || Toxic || 200.59 g/mol || 5.021 MJ/kg
|-
| Bismuth || 703 kJ/mol || Rare || Nontoxic || 208.98 g/mol || 3.364 MJ/kg
|-
| Iodine || 1008.4 kJ/mol || Rare || Nontoxic || 126.904 g/mol || 7.946 MJ/kg
|-
| Caesium || 375.7 kJ/mol || Rare || Toxic || 132.905 g/mol || 2.827 MJ/kg
|-
| Indium || 558.3 kJ/mol || Rare || Nontoxic || 114.818 g/mol || 4.862 MJ/kg
|-
| Sodium || 495.8 kJ/mol || Common || Debated || 22.989 g/mol || 21.567 MJ/kg
|-
| Potassium || 418.8 kJ/mol || Common || Debated || 39.098 g/mol || 10.712 MJ/kg
|-
| Magnesium || 737.7 kJ/mol || Common || Nontoxic || 24.305 g/mol || 30.352 MJ/kg
|-
| Cadmium || 867.8 kJ/mol || Uncommon || Toxic || 112.411 g/mol || 7.72 MJ/kg
|-
| Iridium ||  880 kJ/mol  || Rare || Nontoxic || 192.217 g/mol || 4.578 MJ/kg
|-
| Nitrogen || 1402.3 kJ/mol || Common || Nontoxic || 14.006 g/mol || 100.121 MJ/kg
|-
| Hydrogen || 1312 kJ/mol || Very common || Nontoxic || 1.007 g/mol || 1302.88 MJ/kg
|-
| Ammonia || 1208 kJ/mol || Common || Toxic || 17.03 g/mol || 70.934 MJ/kg
|-
| Water || 1217.61 kJ/mol || Common || Nontoxic || 18.015 g/mol || 67.589 MJ/kg
|-
| Helium || 2372.3 kJ/mol || Very common || Nontoxic || 4.002 g/mol || 592.779 MJ/kg
|}
 
<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==
<ref> http://www.projectrho.com/public_html/rocket/enginelist.php
<br/> Atomic Rockets Engine List </ref>With all these options and possibilities in mind, we can reduce ion engines into two main categories:
* Electrostatic thrusters
* Electrostatic thrusters
* Electromagnetic thruster / plasma propulsion engines
* Electromagnetic thruster / plasma propulsion engines
==Engine Design==
The categories differ in how the ions are accelerated.


===Electrostatic Ion Thruster:===
===Electrostatic Ion Thruster:===
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There are four types of electrostatic thruster that use this principle:
There are four types of electrostatic thruster that use this principle:


*The gridded electrostatic ion thruster [link], which uses electrostatic grids to accelerate the propellant. Charged particles are subject to an electric force when travelling between the grids but not outside the grids.
*The [[Gridded Electrostatic Ion Thruster|gridded electrostatic ion thruster]], which uses electrostatic grids to accelerate the propellant. Charged particles are subject to an electric force when travelling between the grids but not outside the grids. <ref> https://en.wikipedia.org/wiki/Gridded_ion_thruster <br/> Reference for the gridded electrostatic ion thruster. </ref>


*The electrostatic colloid thruster [link], which uses droplets of ionic liquid produced by an electrospray ionization process. An electrode provides the electric field to extract the droplets and accelerate them.
*The [[Electrostatic Colloid Thruster|electrostatic colloid thruster]], which uses droplets of ionic liquid produced by an electrospray ionization process. An electrode provides the electric field to extract the droplets and accelerate them.
** The [[Radioisotope Electrostatic Colloid Thruster|radioisotope electrostatic colloid thruster]], which uses a beta emitter to generate huge voltages for the electrostatic colloid thruster without power conversion. <div class="toccolours mw-collapsible mw-collapsed" style="width:500px; overflow:auto;"> (when the radioisotope ion thruster article is made, make sure this is still conformant with it, and use it as context for the link to encourage someone to go read that article.) Further reading on radioisotope ion thrusters: Bookmark </div>


*The Hall effect ion thruster [link], which uses a voltage between a cylindrical anode and a negatively charged plasma cathode. Propellant is introduced and ionized at the anode, and accelerates after reaching the cathode, picking up electrons and becoming a neutral gas so that it is not pulled back into the engine.
*The [[Hall Effect Electrostatic Ion Thruster|Hall effect electrostatic ion thruster]], which uses a voltage between a cylindrical anode and a negatively charged plasma cathode. Propellant is introduced and ionized at the anode, and accelerates after reaching the cathode, picking up electrons and becoming a neutral gas so that it is not pulled back into the engine. <ref> https://en.wikipedia.org/wiki/Hall-effect_thruster <br/> Reference for the Hall effect thruster. </ref>


*The field emission electric propulsion thruster [link], which extracts ions from liquid metal using very high electric fields. Liquid metals like caesium or iridium flow into the tip of a fountain-pen-like structure to make this process easier.
*The [[Field Emission Electric Propulsion Thruster|field emission electric propulsion thruster]], which extracts ions from liquid metal using very high electric fields. Liquid metals like caesium or iridium flow into the tip of a fountain-pen-like structure to make this process easier. <ref> <br/>https://en.wikipedia.org/wiki/Field-emission_electric_propulsion <br/> Reference for the FEEP thruster. </ref>
 
There is a form of electrostatic colloid thruster that uses the beta emissions of a radioactive substance to generate the voltages necessary to eject droplets of ionic liquid.


===Electromagnetic Ion Thruster / Plasma Propulsion Engine:===
===Electromagnetic Ion Thruster / Plasma Propulsion Engine:===
Line 108: Line 156:
There are 8 main types of electromagnetic ion thrusters in summary:
There are 8 main types of electromagnetic ion thrusters in summary:


*The [[Pulsed Plasma Thruster|pulsed plasma thruster]], which uses an electric arc to vaporize propellant (usually a block of teflon or PTFE) into plasma. Due to the force of the vaporization, the propellant plasma is ejected into the gap between an electrode and anode, where an electrical current runs through it and causes it to be further accelerated by the Lorentz force.


*The pulsed plasma thruster [link], which uses an electric arc to vaporize propellant (usually a block of teflon or PTFE) into plasma. Due to the force of the vaporization, the propellant plasma is ejected into the gap between an electrode and anode, where an electrical current runs through it and causes it to be further accelerated by the Lorentz force.
*The [[ELF Pulsed Plasmoid Thruster|ELF pulsed plasmoid thruster]], which generates a plasmoid (a smoke torus of plasma) from propellant and expands it down an electrically conducting nozzle, with directed kinetic energy (KE) generated from image currents in the nozzle due to interactions with the plasmoid. It is also electrodeless.
**The [[Alfvenic Pulsed Plasmoid Thruster|alfvenic pulsed plasmoid thruster]], which uses magnetic reconnection (the same kind that causes solar flares) to spontaneously generate low-temperature plasmoids. The outgoing plasmoid is an alfvenic outflow from the reconnection site, and so depends on the magnetic field strength rather than the propellant ion species mass for thrust.


*The [[Pulsed Inductive Thruster|pulsed inductive thruster]], which uses pulses instead of continuous thrust and can run on high power levels (on the order of megawatts). Using a coil and conical propellant emitter, large built up charges are released behind the coil. This creates an electric current, and induces a magnetic field in the propellant. Together, the electric and magnetic fields accelerate the propellant through the Lorentz force. <ref> https://en.wikipedia.org/wiki/Pulsed_inductive_thruster <br/> Reference for the PIT thruster. </ref>


*The ELF pulsed plasmoid thruster [link], which generates a plasmoid (a smoke torus of plasma) from propellant and expands it down an electrically conducting nozzle, with directed kinetic energy (KE) generated from image currents in the nozzle due to interactions with the plasmoid. It is also electrodeless.
*The [[Magnetoplasmadynamic Thruster|magnetoplasmadynamic thruster]], which ionizes the propellant via the electric field between an anode and a cathode. The plasma conducts electricity between the anode and cathode, closing the circuit, and creating a new magnetic field, which with the electric field, accelerates the propellant through the Lorentz force. <ref> https://en.wikipedia.org/wiki/Magnetoplasmadynamic_thruster <br/> Reference for the MPD thruster. </ref>


**The alfvenic pulsed plasmoid thruster [link], which uses magnetic reconnection (the same kind that causes solar flares) to spontaneously generate low-temperature plasmoids. The outgoing plasmoid is an alfvenic outflow from the reconnection site, and so depends on the magnetic field strength rather than the propellant ion species mass for thrust.
*The [[Electrodeless Plasma Thruster|electrodeless plasma thruster]], which does not use anode or cathode electrodes. Propellant is ionized through electromagnetic waves, and oscillating electric and magnetic fields in another chamber accelerate the propellant due to the ponderomotive force. The separation of ionization and acceleration steps allows for throttling. <ref> https://en.wikipedia.org/wiki/Electrodeless_plasma_thruster <br/> Reference for the EPT thruster. </ref>


*The [[Arcjet Thruster|arcjet thruster]], which uses an electrical arc between two electrodes to heat flowing propellant into plasma. The expansion of the plasma into the nozzle generates thrust. <ref> https://en.wikipedia.org/wiki/Arcjet_rocket <br/> Reference for the arcjet thruster. </ref>
**The [[Microwave Electrothermal Thruster|microwave electrothermal thruster]], which is similar to the arcjet but utilizes a microwave antenna to heat the flowing propellant instead. <ref> https://en.wikipedia.org/wiki/Microwave_electrothermal_thruster <br/> Reference for the MET thruster. </ref>


*The pulsed inductive thruster [link], which uses pulses instead of continuous thrust and can run on high power levels (on the order of megawatts). Using a coil and conical propellant emitter, large built up charges are released behind the coil. This creates an electric current, and induces a magnetic field in the propellant. Together, the electric and magnetic fields accelerate the propellant through the Lorentz force.
*The [[Helicon Double Layer Thruster|helicon double-layer thruster]], which uses radio waves emitted from an antenna to ionize the propellant into a plasma and excite a helicon wave (a low frequency EM wave bounded inside the plasma), further heating it. A special kind of magnetic nozzle accelerates the propellant. <ref> https://en.wikipedia.org/wiki/Helicon_double-layer_thruster <br/> Reference for the HDL thruster. </ref>


*The [[Variable Specific Impulse Magnetoplasma Rocket|VASIMR]], which functions similarly to the helicon double-layer thruster but uses an additional second step to heat the plasma to 1 million K through ion cyclotron resonance heating. It uses superconductors to magnetically confine the plasma, and thrust is generated when the plasma escapes confinement as the exhaust. The VASIMR has mechanisms that allow it to trade lower exhaust velocity and Isp for higher thrust. <ref> https://en.wikipedia.org/wiki/Variable_Specific_Impulse_Magnetoplasma_Rocket <br/> Reference for the VASIMR. </ref>


*The magnetoplasmadynamic thruster [link], which ionizes the propellant via the electric field between an anode and a cathode. The plasma conducts electricity between the anode and cathode, closing the circuit, and creating a new magnetic field, which with the electric field, accelerates the propellant through the Lorentz force.
==Basic Electrostatic Ion Thruster Mathematics==
<ref> https://spacemath.gsfc.nasa.gov/weekly/5Page64.pdf
<br/>Electrostatic Ion Engine Math </ref>
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 electrodeless plasma thruster [link], which does not use anode or cathode electrodes. Propellant is ionized through electromagnetic waves, and oscillating electric and magnetic fields in another chamber accelerate the propellant due to the ponderomotive force. The separation of ionization and acceleration steps allows for throttling.
<math alt=> E=qV </math>
* 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.


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 helicon double-layer thruster [link], which uses radio waves emitted from an antenna to ionize the propellant into a plasma and excite a helicon wave (a low frequency EM wave bounded inside the plasma), further heating it. A special kind of magnetic nozzle accelerates the propellant.
These figures are derived from the equation for kinetic energy:


<math alt=> E=mv^2/2</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.
Which is rearranged to give velocity:


*The VASIMR [link], which functions similarly to the helicon double-layer thruster but uses an additional second step to heat the plasma to 1 million K through ion cyclotron resonance heating. It uses superconductors to magnetically confine the plasma, and thrust is generated when the plasma escapes confinement as the exhaust. VASIMR has mechanisms that allow it to trade lower exhaust velocity and Isp for higher thrust.
<math alt=>v=\sqrt{2E/m}</math>


==Electrostatic Ion Thruster Mathematics==
The thrust of the electrostatic ion thruster is given by:
An electron 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> in eV a charged particle gains is:
<math alt=> N=v\dot{m}</math>
* Where <math alt=>N</math> is the thrust of the thruster and <math alt=>\dot{m}</math> is the propellant mass flow rate.
That can be rearranged to give mass flow rate instead:
<br/><math alt=>\dot{m}=N/v</math>


<math alt=> E=qV </math>
The drive power of the electrostatic ion thruster can be calculated two ways, most simply with 1:
* With <math alt=>E</math> the energy in joules, <math alt=>q</math> the particle’s charge in coulombs, and <math alt=>V</math> the voltage in volts.


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.
# <math alt=>P=vN/2</math>
# <math alt=>P=AV</math>
* Where <math alt=>A</math> is the amperage


These figures are derived from the equation for kinetic energy:
The equation for the amperage needed is:


<math alt=> E=\frac{1}{2}mv^2</math>
<math alt=>A=\dot{m}/nq</math>
* With <math alt=>E</math> the particle’s energy in joules, <math alt=>m</math> the particle’s mass in kg, and <math alt=>v</math> the velocity in m/s.
* Where <math alt=>n</math> is the molar mass of the propellant.
Which is rearranged to give velocity:


<math alt=>v=(2E/m)^\frac{1}{2}</math>
==History & Development==
 
<ref> https://en.wikipedia.org/wiki/Ion_thruster#Origins <br/> Reference for the history and development of ion engines. </ref>
==History / Development==
'''[This section should be in its own specific history article, so a link would be provided here instead of the text]'''
'''[This section should be in its own specific history article, so a link would be provided here instead of the text]'''


The conceptual history of ion engines dates back to 1911, by Konstantin Tsiolkovsky, the first person to publish a paper on the subject. He recommended it for near-vacuum conditions at altitude, however thrust was also seen with ionized air streams at atmospheric pressure.
The conceptual history of ion engines dates back to 1911, by Konstantin Tsiolkovsky, the first person to publish a paper on the subject. He recommended it for near-vacuum conditions at altitude, however thrust was also seen with ionized air streams at atmospheric pressure.
[[Image:sert.jpg|thumb|Image of the SERT-1 spacecraft. (Source: Wikipedia)]]


Hermann Oberth later reignited conversation with his “Ways to Spaceflight” book in 1923, talking about its advantages in mass ratios and mass savings for payloads. He predicted its usage in spacecraft propulsion and attitude control, as well advocated for the electrostatic kind of ion thruster.
Hermann Oberth later reignited conversation with his “Ways to Spaceflight” book in 1923, talking about its advantages in mass ratios and mass savings for payloads. He predicted its usage in spacecraft propulsion and attitude control, as well advocated for the electrostatic kind of ion thruster.


By 1959, a gridded electrostatic ion thruster had been built by Harold R. Kaufman at NASA Glenn Research Facilities, using mercury as its propellant. Suborbital tests were conducted throughout the 1960s, and an orbital test was done in 1970, the SERT-1 and SERT-2 demonstration missions.
By 1959, a gridded electrostatic ion thruster had been built by Harold R. Kaufman at NASA Glenn Research Facilities, using mercury as its propellant. Suborbital tests were conducted throughout the 1960s, and an orbital test was done in 1970, the SERT-1 and SERT-2 demonstration missions. <ref> https://en.wikipedia.org/wiki/SERT-1 <br/> Reference for the SERT missions. </ref>


The Hall effect thruster design, studied by both the United States and the Soviet Union, had been used by the Soviets from 1972 to late 1990s for attitude control. It is estimated that 100-200 engines were used on Soviet and Russian missions. By 1992, the designs had been brought to the West, thanks to a team of electric propulsion specialists from the Ballistic Missile Defense Organization (BMDO) visiting Soviet labs.
The Hall effect thruster design, studied by both the United States and the Soviet Union, had been used by the Soviets from 1972 to late 1990s for attitude control. It is estimated that 100-200 engines were used on Soviet and Russian missions. By 1992, the designs had been brought to the West, thanks to a team of electric propulsion specialists from the Ballistic Missile Defense Organization (BMDO) visiting Soviet labs.
Line 188: Line 254:


==Additional Reading==
==Additional Reading==
Links from ion engine design section
[[Spiral Trajectories]]
Links from history section
<br/>[[Gravity Assists and Oberth Effect]]
<br/>[[Hohmann Transfer]]
<br/>[[Super Loki]]
<br/>[[Raptor Engine]]
<br/>[[Brachistochrone Transfer]]
<br/>[[Gridded Electrostatic Ion Thruster]]
<br/>[[Electrostatic Colloid Thruster]]
<br/>[[Radoisotope Electrostatic Colloid Thruster]]
<br/>[[Hall Effect Electrostatic Ion Thruster]]
<br/>[[Field Emission Electric Propulsion Thruster]]
<br/>[[Pulsed Plasma Thruster]]
<br/>[[ELF Pulsed Plasmoid Thruster]]
<br/>[[Alfvenic Pulsed Plasmoid Thruster]]
<br/>[[Pulsed Inductive Thruster]]
<br/>[[Magnetoplasmadynamic Thruster]]
<br/>[[Electrodeless Plasma Thruster]]
<br/>[[Arcjet Thruster|arcjet thruster]]
<br/>[[Microwave Electrothermal Thruster|microwave electrothermal thruster]]
<br/>[[Helicon Double Layer Thruster]]
<br/>[[Variable Specific Impulse Magnetoplasma Rocket]]


https://cdn.discordapp.com/attachments/886253956777533450/887757110501318757/POTENTIALITIES_OF_THE_RADIOISQTOPE_ELECTROSTATIC_PROPULSION_SYSTEM.pdf
https://cdn.discordapp.com/attachments/886253956777533450/887757110501318757/POTENTIALITIES_OF_THE_RADIOISQTOPE_ELECTROSTATIC_PROPULSION_SYSTEM.pdf
Further reading for the radioisotope ion thruster.
<br/>https://www.osti.gov/biblio/4875645
<br/>Further reading for the radioisotope ion thruster.


==Additional References==
==Additional References==
https://satsearch.co/products/busek-bit-3
<ref> https://www.busek.com/bet-300p <br/> Reference for colloid thrusters</ref> <ref> https://en.wikipedia.org/wiki/Ion_thruster </ref> <ref> https://en.wikipedia.org/wiki/NASA_Solar_Technology_Application_Readiness
<br/>http://www.projectrho.com/public_html/rocket/enginelist.php
<br/> NSTAR Ion Thruster </ref> <ref> https://www1.grc.nasa.gov/space/sep/gridded-ion-thrusters-next-c/ </ref>
<br/>https://www.busek.com/bet-300p
<references/>
 
https://en.wikipedia.org/wiki/Ion_thruster
<br/>https://en.wikipedia.org/wiki/NASA_Solar_Technology_Application_Readiness
<br/>https://www1.grc.nasa.gov/space/sep/gridded-ion-thrusters-next-c/
 
https://en.wikipedia.org/wiki/Gridded_ion_thruster
<br/>https://en.wikipedia.org/wiki/Hall-effect_thruster
<br/>https://en.wikipedia.org/wiki/Field-emission_electric_propulsion
 
https://en.wikipedia.org/wiki/Pulsed_inductive_thruster
<br/>https://en.wikipedia.org/wiki/Magnetoplasmadynamic_thruster
<br/>https://en.wikipedia.org/wiki/Electrodeless_plasma_thruster
<br/>https://en.wikipedia.org/wiki/Helicon_double-layer_thruster
<br/>https://en.wikipedia.org/wiki/Variable_Specific_Impulse_Magnetoplasma_Rocket
<br/>https://en.wikipedia.org/wiki/Microwave_electrothermal_thruster
 
https://en.wikipedia.org/wiki/SERT-1
<br/>https://spacemath.gsfc.nasa.gov/weekly/5Page64.pdf
<br/>Electrostatic Ion Engine Math


==Credit:==
==Credit:==
Line 223: Line 290:
* To KRKIIIIII for test-reading
* To KRKIIIIII for test-reading
* To AdAstraGames for test-reading and some editing
* To AdAstraGames for test-reading and some editing
* To MatterbeamToughSF for checking sources and technical details
* To MatterbeamToughSF for checking sources, technical details and contributing useful information
 
[[Category:Spacecraft Systems]][[Category:Transportation & Infrastructure‏‎]][[Category:Transportation]][[Category:Propulsion]][[Category:Engines]][[Category:Rocket Science]]

Latest revision as of 13:38, 23 April 2024

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.

The low acceleration of ion engines means spacecraft generally have to use less efficient spiral trajectories near planets with a strong gravitational field, and have to forgo the benefits of Oberth burns. They are a common propulsion choice for satellites and as interplanetary transit engines for spacecraft. They are a poor choice for any use that requires high thrust and short impulsive burns, and cannot make Hohmann orbit transfers efficiently.

Introduction

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 [1]. Even small chemical rockets, such as the 30 kg wet-mass 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 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.

The tradeoff of high exhaust velocity and low thrust makes ion engines ideally suited to orbit-to-orbit missions; for anything that requires higher thrust, like getting things out of even a modest gravity well, you’ll need a second rocket with higher thrust. Ion engines are well-suited for satellite orbital maneuvering, and long duration spacecraft missions between planets. Ion drives work best for Ward-spiral style interplanetary transits as lowest delta-V Hohmann transfers require a short burn of high thrust to work; Ion drives will get your payload or passengers to their destination with a smaller fuel fraction and/or less time. Ion engines do not provide enough thrust for brachistochrone transfers.

Where ion engines shine are missions where long-duration accelerations are key to mission success. Delta-V in the tens of kilometers per second are possible even with today’s technology. They can drastically reduce the travel time between planets and if given enough time, cover great distances. Their low acceleration is not a major hindrance in accelerating in interplanetary space, overcoming solar gravity, or around the reduced surface gravities of the numerous small bodies in our solar system.

Example Engine Performance

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 [2]

Name Busek BIT-3
ISP or Exhaust Velocity <22,555 m/s
<2300 s
Thrust <1.25 mN
Mass 1.28 kg
Efficiency 17.6% (Calculated)[C 1]
Drive Power <14.09 W (Calculated)[C 2]
Power Consumption 56-80 W
T/W 0.0000996 (Calculated)
Energy Source (Fuel) Electricity
Propellant Iodine
Reactor Grids
Specific Power 10.9 W/kg (Calculated)

Calculated Figures:

  1. Drive Power / Power Consumption (80 W) = 0.176
  2. Drive Power = 1.25 mN thrust 22,555 m/s exhaust velocity 2

Design and Function

There are two usual steps in an ion engine’s operation:

  • Creating charged propellant
  • Accelerating the charged propellant

Creating charged propellant is usually done by ionizing it, through a variety of methods like electron guns or heating the propellant to plasma temperatures. It must be accelerated through electromagnetic means such as a voltage difference between grids, or oscillating electric and magnetic fields. This is the primary working principle of ion engines.

There are multiple factors in ion engine design as well, such as reliability, cost and/or simplicity and lifetime. In particular, when long lifetimes are needed - electrode-less ion thruster designs can be used, sidestepping the problem of propellant induced erosion on the electrodes.

Propellant Considerations

Ion engines can suffer significant inefficiency as ionizing the propellant may take significant amounts of energy input, thus designers focus on minimizing the amount of electricity spent in ionizing the propellant, influencing things like what propellant to use. A thruster that aims for a higher exhaust velocity at the expense of thrust has a lower propellant flow and allows mission planners to spend more of their launch payload on useful hardware, rather than propellant.

The ideal propellant choice is easy to ionize and has a high mass to ionization energy ratio [3]. Another consideration is erosion, which limits the life-time of thrusters with electrodes[4]. Some otherwise excellent propellants are toxic (mercury) or toxic and carcinogenic (cadmium). Additionally, being able to source propellants without significant processing overhead may be a desirable advantage; the colloid thrusters can use finely ground regolith as a propellant.

Balancing these considerations (except the processing and availability concerns) have led to xenon and krypton being common choices for electrostatic ion thrusters. They are high Z (Z is the proton number, therefore having more mass per atom), inert and require less energy to ionize. For gridless ion thrusters, like the Hall effect ion thrusters, bismuth and iodine are also available.

Some ion engine designs are flexible enough to use multiple propellants, or mixes that meet certain specifications. For example, airbreathing electric ramjets use different nitrogen, oxygen and hydrogen ratios depending on which orbital altitude they operate at.

Propellant Type 1st State Ionization energy Availability Toxicity Molar Mass [5] Ionization Specific Energy
(Calculated)[C2 1]
Xenon 1170.4 kJ/mol Uncommon Nontoxic 131.293 g/mol 8.914 MJ/kg
Krypton 1350.8 kJ/mol Uncommon Nontoxic 83.798 g/mol 16.12 MJ/kg
Argon 1520.6 kJ/mol Uncommon Nontoxic 39.948 g/mol 38.064 MJ/kg
Mercury 1007.1 kJ/mol Rare Toxic 200.59 g/mol 5.021 MJ/kg
Bismuth 703 kJ/mol Rare Nontoxic 208.98 g/mol 3.364 MJ/kg
Iodine 1008.4 kJ/mol Rare Nontoxic 126.904 g/mol 7.946 MJ/kg
Caesium 375.7 kJ/mol Rare Toxic 132.905 g/mol 2.827 MJ/kg
Indium 558.3 kJ/mol Rare Nontoxic 114.818 g/mol 4.862 MJ/kg
Sodium 495.8 kJ/mol Common Debated 22.989 g/mol 21.567 MJ/kg
Potassium 418.8 kJ/mol Common Debated 39.098 g/mol 10.712 MJ/kg
Magnesium 737.7 kJ/mol Common Nontoxic 24.305 g/mol 30.352 MJ/kg
Cadmium 867.8 kJ/mol Uncommon Toxic 112.411 g/mol 7.72 MJ/kg
Iridium 880 kJ/mol Rare Nontoxic 192.217 g/mol 4.578 MJ/kg
Nitrogen 1402.3 kJ/mol Common Nontoxic 14.006 g/mol 100.121 MJ/kg
Hydrogen 1312 kJ/mol Very common Nontoxic 1.007 g/mol 1302.88 MJ/kg
Ammonia 1208 kJ/mol Common Toxic 17.03 g/mol 70.934 MJ/kg
Water 1217.61 kJ/mol Common Nontoxic 18.015 g/mol 67.589 MJ/kg
Helium 2372.3 kJ/mol Very common Nontoxic 4.002 g/mol 592.779 MJ/kg
  1. The formula to find the amount of energy needed to ionize some amount of mass of any material (ionization specific energy) is given by:
    • where is the ionization energy of the material, is the molar mass of the material and is the ionization specific energy of the material.

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

[6]With all these options and possibilities in mind, we can reduce ion engines into two main categories:

  • Electrostatic thrusters
  • Electromagnetic thruster / plasma propulsion engines

Electrostatic Ion Thruster:

Electrostatic thrusters accelerate ions via large voltage differences. Charged particles feel an attraction to a charge of the opposite sign and a repulsion to a charge of the same sign, resulting in a force called the Coulomb force.

There are four types of electrostatic thruster that use this principle:

  • The gridded electrostatic ion thruster, which uses electrostatic grids to accelerate the propellant. Charged particles are subject to an electric force when travelling between the grids but not outside the grids. [7]
  • The electrostatic colloid thruster, which uses droplets of ionic liquid produced by an electrospray ionization process. An electrode provides the electric field to extract the droplets and accelerate them.
    • The radioisotope electrostatic colloid thruster, which uses a beta emitter to generate huge voltages for the electrostatic colloid thruster without power conversion.
      (when the radioisotope ion thruster article is made, make sure this is still conformant with it, and use it as context for the link to encourage someone to go read that article.) Further reading on radioisotope ion thrusters: Bookmark
  • The Hall effect electrostatic ion thruster, which uses a voltage between a cylindrical anode and a negatively charged plasma cathode. Propellant is introduced and ionized at the anode, and accelerates after reaching the cathode, picking up electrons and becoming a neutral gas so that it is not pulled back into the engine. [8]
  • The field emission electric propulsion thruster, which extracts ions from liquid metal using very high electric fields. Liquid metals like caesium or iridium flow into the tip of a fountain-pen-like structure to make this process easier. [9]

Electromagnetic Ion Thruster / Plasma Propulsion Engine:

There are even more ways to accelerate ions using magnetic fields instead of electric fields. Charged particles are sensitive to the Lorentz force, the same force that ejects projectiles out of a railgun. Other electromagnetic ion thrusters use the ponderomotive force, the result of oscillating magnetic fields, or have found some other clever way to use magnetic fields.

Magnetic fields push on negatively and positively charged particles equally. This means they put on both ions and electrons, which together form a plasma, and is the reason this type of electric thruster is also called a plasma propulsion engine.

There are 8 main types of electromagnetic ion thrusters in summary:

  • The pulsed plasma thruster, which uses an electric arc to vaporize propellant (usually a block of teflon or PTFE) into plasma. Due to the force of the vaporization, the propellant plasma is ejected into the gap between an electrode and anode, where an electrical current runs through it and causes it to be further accelerated by the Lorentz force.
  • The ELF pulsed plasmoid thruster, which generates a plasmoid (a smoke torus of plasma) from propellant and expands it down an electrically conducting nozzle, with directed kinetic energy (KE) generated from image currents in the nozzle due to interactions with the plasmoid. It is also electrodeless.
    • The alfvenic pulsed plasmoid thruster, which uses magnetic reconnection (the same kind that causes solar flares) to spontaneously generate low-temperature plasmoids. The outgoing plasmoid is an alfvenic outflow from the reconnection site, and so depends on the magnetic field strength rather than the propellant ion species mass for thrust.
  • The pulsed inductive thruster, which uses pulses instead of continuous thrust and can run on high power levels (on the order of megawatts). Using a coil and conical propellant emitter, large built up charges are released behind the coil. This creates an electric current, and induces a magnetic field in the propellant. Together, the electric and magnetic fields accelerate the propellant through the Lorentz force. [10]
  • The magnetoplasmadynamic thruster, which ionizes the propellant via the electric field between an anode and a cathode. The plasma conducts electricity between the anode and cathode, closing the circuit, and creating a new magnetic field, which with the electric field, accelerates the propellant through the Lorentz force. [11]
  • The electrodeless plasma thruster, which does not use anode or cathode electrodes. Propellant is ionized through electromagnetic waves, and oscillating electric and magnetic fields in another chamber accelerate the propellant due to the ponderomotive force. The separation of ionization and acceleration steps allows for throttling. [12]
  • The arcjet thruster, which uses an electrical arc between two electrodes to heat flowing propellant into plasma. The expansion of the plasma into the nozzle generates thrust. [13]
  • The helicon double-layer thruster, which uses radio waves emitted from an antenna to ionize the propellant into a plasma and excite a helicon wave (a low frequency EM wave bounded inside the plasma), further heating it. A special kind of magnetic nozzle accelerates the propellant. [15]
  • The VASIMR, which functions similarly to the helicon double-layer thruster but uses an additional second step to heat the plasma to 1 million K through ion cyclotron resonance heating. It uses superconductors to magnetically confine the plasma, and thrust is generated when the plasma escapes confinement as the exhaust. The VASIMR has mechanisms that allow it to trade lower exhaust velocity and Isp for higher thrust. [16]

Basic Electrostatic Ion Thruster Mathematics

[17] 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 a charged particle gains is:

  • Where is the particle's energy, is the particle’s charge, and 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.

These figures are derived from the equation for kinetic energy:

  • Where is the particle's energy, is the particle's mass, and is the particle's velocity.

Which is rearranged to give velocity:

The thrust of the electrostatic ion thruster is given by:

  • Where is the thrust of the thruster and is the propellant mass flow rate.

That can be rearranged to give mass flow rate instead:

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

  • Where is the amperage

The equation for the amperage needed is:

Failed to parse (SVG (MathML can be enabled via browser plugin): Invalid response ("Math extension cannot connect to Restbase.") from server "https://wikimedia.org/api/rest_v1/":): {\displaystyle A=\dot{m}/nq}

  • Where Failed to parse (SVG (MathML can be enabled via browser plugin): Invalid response ("Math extension cannot connect to Restbase.") from server "https://wikimedia.org/api/rest_v1/":): {\displaystyle n} is the molar mass of the propellant.

History & Development

[18] [This section should be in its own specific history article, so a link would be provided here instead of the text]

The conceptual history of ion engines dates back to 1911, by Konstantin Tsiolkovsky, the first person to publish a paper on the subject. He recommended it for near-vacuum conditions at altitude, however thrust was also seen with ionized air streams at atmospheric pressure.

Image of the SERT-1 spacecraft. (Source: Wikipedia)

Hermann Oberth later reignited conversation with his “Ways to Spaceflight” book in 1923, talking about its advantages in mass ratios and mass savings for payloads. He predicted its usage in spacecraft propulsion and attitude control, as well advocated for the electrostatic kind of ion thruster.

By 1959, a gridded electrostatic ion thruster had been built by Harold R. Kaufman at NASA Glenn Research Facilities, using mercury as its propellant. Suborbital tests were conducted throughout the 1960s, and an orbital test was done in 1970, the SERT-1 and SERT-2 demonstration missions. [19]

The Hall effect thruster design, studied by both the United States and the Soviet Union, had been used by the Soviets from 1972 to late 1990s for attitude control. It is estimated that 100-200 engines were used on Soviet and Russian missions. By 1992, the designs had been brought to the West, thanks to a team of electric propulsion specialists from the Ballistic Missile Defense Organization (BMDO) visiting Soviet labs.

Worked Examples

Electrostatic Ion Thruster:

Gridded Electrostatic Ion Thruster - NSTAR, NeXT

Colloid Thruster - Busek Electrospray Thruster Bookmark

Hall Effect Ion Thruster - PPS-1350, on the SMART-1 mission. AEPS

Field Emission Electric Propulsion Thruster - IFM Nano

Electromagnetic Ion Thruster / Plasma Propulsion Engine:

Pulsed Inductive Thruster - Several laboratory examples built by NGST.

Magnetoplasmadynamic Thruster - MPD thrusters flown on EPEX (Japan) mission

Helicon Double-Layer Thruster - Prototype built by Dr Christine Charles

VASIMR - VX-10, VX-50, VX-100, VX-200. Built by Ad Astra. (not flown)

Additional Reading

Spiral Trajectories
Gravity Assists and Oberth Effect
Hohmann Transfer
Super Loki
Raptor Engine
Brachistochrone Transfer
Gridded Electrostatic Ion Thruster
Electrostatic Colloid Thruster
Radoisotope Electrostatic Colloid Thruster
Hall Effect Electrostatic Ion Thruster
Field Emission Electric Propulsion Thruster
Pulsed Plasma Thruster
ELF Pulsed Plasmoid Thruster
Alfvenic Pulsed Plasmoid Thruster
Pulsed Inductive Thruster
Magnetoplasmadynamic Thruster
Electrodeless Plasma Thruster
arcjet thruster
microwave electrothermal thruster
Helicon Double Layer Thruster
Variable Specific Impulse Magnetoplasma Rocket

https://cdn.discordapp.com/attachments/886253956777533450/887757110501318757/POTENTIALITIES_OF_THE_RADIOISQTOPE_ELECTROSTATIC_PROPULSION_SYSTEM.pdf
https://www.osti.gov/biblio/4875645
Further reading for the radioisotope ion thruster.

Additional References

[20] [21] [22] [23]

  1. Failed to parse (SVG (MathML can be enabled via browser plugin): Invalid response ("Math extension cannot connect to Restbase.") from server "https://wikimedia.org/api/rest_v1/":): {\displaystyle F=MA} where Failed to parse (SVG (MathML can be enabled via browser plugin): Invalid response ("Math extension cannot connect to Restbase.") from server "https://wikimedia.org/api/rest_v1/":): {\displaystyle F} is force, Failed to parse (SVG (MathML can be enabled via browser plugin): Invalid response ("Math extension cannot connect to Restbase.") from server "https://wikimedia.org/api/rest_v1/":): {\displaystyle M} is mass, and Failed to parse (SVG (MathML can be enabled via browser plugin): Invalid response ("Math extension cannot connect to Restbase.") from server "https://wikimedia.org/api/rest_v1/":): {\displaystyle A} is acceleration. 10.2 grams times 9.8 m/s2, or the gravitational acceleration on Earth, is equal to 100 Millinewtons.
  2. https://satsearch.co/products/busek-bit-3
    The example table thruster
  3. https://en.wikipedia.org/wiki/Ionization_energy
    Reference for ionization energy ratio.
  4. https://en.wikipedia.org/wiki/Ion_thruster#Lifetime
    Reference for erosion.
  5. https://www.webqc.org/mmcalc.php
    Reference for molar mass.
  6. http://www.projectrho.com/public_html/rocket/enginelist.php
    Atomic Rockets Engine List
  7. https://en.wikipedia.org/wiki/Gridded_ion_thruster
    Reference for the gridded electrostatic ion thruster.
  8. https://en.wikipedia.org/wiki/Hall-effect_thruster
    Reference for the Hall effect thruster.

  9. https://en.wikipedia.org/wiki/Field-emission_electric_propulsion
    Reference for the FEEP thruster.
  10. https://en.wikipedia.org/wiki/Pulsed_inductive_thruster
    Reference for the PIT thruster.
  11. https://en.wikipedia.org/wiki/Magnetoplasmadynamic_thruster
    Reference for the MPD thruster.
  12. https://en.wikipedia.org/wiki/Electrodeless_plasma_thruster
    Reference for the EPT thruster.
  13. https://en.wikipedia.org/wiki/Arcjet_rocket
    Reference for the arcjet thruster.
  14. https://en.wikipedia.org/wiki/Microwave_electrothermal_thruster
    Reference for the MET thruster.
  15. https://en.wikipedia.org/wiki/Helicon_double-layer_thruster
    Reference for the HDL thruster.
  16. https://en.wikipedia.org/wiki/Variable_Specific_Impulse_Magnetoplasma_Rocket
    Reference for the VASIMR.
  17. https://spacemath.gsfc.nasa.gov/weekly/5Page64.pdf
    Electrostatic Ion Engine Math
  18. https://en.wikipedia.org/wiki/Ion_thruster#Origins
    Reference for the history and development of ion engines.
  19. https://en.wikipedia.org/wiki/SERT-1
    Reference for the SERT missions.
  20. https://www.busek.com/bet-300p
    Reference for colloid thrusters
  21. https://en.wikipedia.org/wiki/Ion_thruster
  22. https://en.wikipedia.org/wiki/NASA_Solar_Technology_Application_Readiness
    NSTAR Ion Thruster
  23. https://www1.grc.nasa.gov/space/sep/gridded-ion-thrusters-next-c/

Credit:

To Tshhmon for writing the article

  • To SOPHONT SIMP for test-reading
  • To KRKIIIIII for test-reading
  • To AdAstraGames for test-reading and some editing
  • To MatterbeamToughSF for checking sources, technical details and contributing useful information