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Ion thrusters require a lot of energy because of their high exhaust velocities. But why can't they just pump a mixture of hydrogen and xenon into the chamber, mix it with oxygen and burn it? Doesn't this ionize the gas and also provide enough thermal heat to push the plasma through the grids?

Maybe not hydrogen and oxygen, but some other exothermic reaction. Not to completely avoid electricity input but reduce it. Maybe reducing the size of the solar panels. I am talking about deep space missions.

This would also be much more efficient than energy production through turbines, wouldn't it?

Is there any drawback of using exothermic reactions?

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  • $\begingroup$ Maybe you would be interested by this: en.wikipedia.org/wiki/Nuclear_thermal_rocket $\endgroup$
    – Antzi
    Feb 8, 2017 at 5:06
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    $\begingroup$ In fact, you have simultaneously asked the same question in Physics stackexchange, only 40 minutes before you posted it here. This is not considered good stackexchange behavior. $\endgroup$
    – uhoh
    Feb 8, 2017 at 6:02

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Ion engines need the ions to stay ionized

To be usefully efficient, an ion engine needs to ionize a substantial fraction of the propellant, and keep it ionized until it passes through most of the positive electrostatic potential gradient to whatever potential the local free space is assigned. I won't say "ground" here, but the assignment of zero is arbitrary.

It's the electrostatic acceleration of the ions that is the "push" of the engine.

That means the plasma needs to be low enough pressure so that the ions and electrons don't recombine too much. In some designs using electron cyclotron resonance, the vacuum must be so low that the electrons can accelerate to high energy before a useful, ionizing collision. That low pressure is way too low to allow a sustained chemical reaction.

Stuff doesn't burn in a near-vacuum

An ion engine's biggest job is to keep generating high energy electrons to continue to ionize the neutral gas constantly introduced into the chamber. There are then so few collisions that the reaction of one oxygen/hydrogen atom pair wouldn't trigger any nearby atoms to undergo a similar reaction. It wouldn't be self-sustaining, and in fact almost all the hydrogen and oxygen would pass out of the engine unreacted.

enter image description here

above: from this YouTube Video Introduction to Ion Thrusters. Right-click and open in a new view for full size readability and detail. Image is placed here to avoid link rot if the YouTube video is ever moved or deleted.

Here is a link to the actual video:

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  • $\begingroup$ Is there any way to overcome this? $\endgroup$
    – Chandrahas
    Feb 8, 2017 at 5:41
  • $\begingroup$ @Chandrahas I can't think of one. There is a question here somewhere about using electrostatic air purifiers for thrust, doesn't seem likely to be useful. $\endgroup$
    – uhoh
    Feb 8, 2017 at 5:45
  • $\begingroup$ @Chandrahas this answer links to this video: youtu.be/PvnF2bMnJtU $\endgroup$
    – uhoh
    Feb 8, 2017 at 5:50
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The ion thruster should be as simple as possible and it should use the propellant mass effectively. Why use three gases if using xenon only works? The propellant mass should be accelerated totally, not only the xenon part. If you use the full heat of a reaction of hydrogen with oxygen, the combustion chamber must be cooled to prevent melting. An ion thruster is used for long missions due to the low thrust, but liquid hydrogen and oxygen can't be stored that long. High pressure tanks for gaseous hydrogen and oxygen are heavy. Xenon is a very heavy gas, a tank for the same mass of gas could be much smaller and lighter for xenon than for hydrogen or oxygen. The amount of electrical energy used for the heating and ionization of xenon is much smaller than that used for the acceleration of xenon. You don't need additional consumables to heat the xenon, just a part of the solar panels is enough.

Chemical energy could only deliver about 2 % of the energy that an electric accelerated ion gets.

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Because what you are just describing is regular liquid fueled rocket.

The efficiency of a rocket fuel is dictated by its exhaust velocity. This velocity has a maximum value for each kind of fuel.

If you are going to burn hydrogen, you can achieve about $4\ 400 \frac{\text{m}}{\text{s}}$. Ion thrusters reach about $29\ 000 \frac{\text{m}}{\text{s}}$

Moreover, we cannot store liquid hydrogen/oxygen for a long time. For a deep space mission, this is an issue.

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  • $\begingroup$ But we are using hydrogen just to ionize and heat up xenon. Later we pull the electrons off the plasma. After this it would function just like a regular ion thruster, since the grids would still accelerate the ions. Hence, we still get high exhaust velocities, don't we? $\endgroup$
    – Chandrahas
    Feb 8, 2017 at 5:22
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    $\begingroup$ The thing is that you added liquid fuel to the equation. This is more mass you will need to carry around, lowering your efficiency. Since efficiency is the whole point of ion thrusters, I don't think this is something you would realistically want. I'm not even sure this is even possible, someone else would have to answer for that $\endgroup$
    – Antzi
    Feb 8, 2017 at 5:27
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    $\begingroup$ @Chandrahas Using hydrogen and oxygen to ionize and heat up xenon would be just less efficient than to use only electric energy from solar cells alone to ionize and accelerate xenon. It would add additional mass to the spacecraft and increase complexity of the engine. So the reliability of the spacecraft would be lower. $\endgroup$
    – Uwe
    Jun 1, 2022 at 12:33

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