This response addresses the generic degradation of solar arrays passing through Van Allen belts, rather than those specifically bound for the moon.

Its a topic that has stirred up a lot of interest in the last few years as Boeing, a manufacturer of commercial communications satellites, announced a launch of two satellites designed to be deployed in GTO and transferred to GEO with electric propulsion. They (Eutelsat 115 West B and ABS 3A) were launched in 2015 and are now on station.

Prior to this I am only aware of two other satellites having made such a transfer with thrusters that were not intended for that part of the mission. One was Artemis and the other was AEHF-1, and this was in both cases because of earlier failures that would otherwise have prevented deployment in GEO. I believe that all other satellites to date employing ion thrusters or hall effect thrusters have done so with their primary use being for station-keeping once delivered to GEO and they have not spent a long time in transit. [EDIT Much has changed in the last 8 years, as of 2024 the "electric" GTO-GEO transfer is more common these days]

I think this recent paper is relevant: Space Weather Concerns for All-Electric Propulsion Satellites from Ref 1.

I have extracted the following figure from it:

[NB "EOR" refers to "Electric Orbit Raising"]

Satellites are designed with shielding against specifications which in turn depend upon a good picture of the environment. Solar arrays can, to degree, be protected by thicker cover-glasses, hence the 6.7 year part of the caption does not apply to solar arrays other than to show the concept. I believe the Van Allen probes, mentioned in PearsonArtPhoto's response will have featured allowances for uncertainties in the very phenomenon they are there to measure. In the case of geostationary communications satellites which are usually relatively power-hungry compared to science satellites, the effect of mis-judging the uncertainties would be felt later in the mission as the available power dropped.

Lastly, referring to a part of the Dr. Geoffrey Landis article referred to in the question:

He noted the slow speed used by this form of propulsion to transit the Van Allen radiation belts saying that for HSF, one must go through the belts much faster. He said nuclear propulsion was needed, mentioned the fear factor that several have but that we should develop and implement it.

His solution may be consistent with some lunar mission scenarios though there isn't enough context given to conclude that it is "needed".

Ref 1. Horne, R. B., and D. Pitchford (2015), Space Weather Concerns for All-Electric Propulsion Satellites, Space Weather , 13 , 430 – 433, doi:10.1002/2015SW001198

This response addresses the generic degradation of solar arrays passing through Van Allen belts, rather than those specifically bound for the moon.

Its a topic that has stirred up a lot of interest in the last few years as Boeing, a manufacturer of commercial communications satellites, announced a launch of two satellites designed to be deployed in GTO and transferred to GEO with electric propulsion. They (Eutelsat 115 West B and ABS 3A) were launched in 2015 and are now on station.

Prior to this I am only aware of two other satellites having made such a transfer with thrusters that were not intended for that part of the mission. One was Artemis and the other was AEHF-1, and this was in both cases because of earlier failures that would otherwise have prevented deployment in GEO. I believe that all other satellites to date employing ion thrusters or hall effect thrusters have done so with their primary use being for station-keeping once delivered to GEO and they have not spent a long time in transit. 

[EDIT Much has changed in the last 8 years, as of 2024 the "electric" GTO-GEO transfer is more common these days. Also note that some of the damage comes from particles originating from the sun rather than considered to be trapped in the belts]

I think this recent paper is relevant: Space Weather Concerns for All-Electric Propulsion Satellites from Ref 1.

I have extracted the following figure from it:

[NB "EOR" refers to "Electric Orbit Raising"]

Satellites are designed with shielding against specifications which in turn depend upon a good picture of the environment. Solar arrays can, to degree, be protected by thicker cover-glasses, hence the 6.7 year part of the caption does not apply to solar arrays other than to show the concept. I believe the Van Allen probes, mentioned in PearsonArtPhoto's response will have featured allowances for uncertainties in the very phenomenon they are there to measure. In the case of geostationary communications satellites which are usually relatively power-hungry compared to science satellites, the effect of mis-judging the uncertainties would be felt later in the mission as the available power dropped.

Lastly, referring to a part of the Dr. Geoffrey Landis article referred to in the question:

He noted the slow speed used by this form of propulsion to transit the Van Allen radiation belts saying that for HSF, one must go through the belts much faster. He said nuclear propulsion was needed, mentioned the fear factor that several have but that we should develop and implement it.

His solution may be consistent with some lunar mission scenarios though there isn't enough context given to conclude that it is "needed".

Ref 1. Horne, R. B., and D. Pitchford (2015), Space Weather Concerns for All-Electric Propulsion Satellites, Space Weather , 13 , 430 – 433, doi:10.1002/2015SW001198

This response addresses the generic degradation of solar arrays passing through Van Allen belts, rather than those specifically bound for the moon.

Its a topic that has stirred up a lot of interest in the last few years as Boeing, a manufacturer of commercial communications satellites, announced a launch of two satellites designed to be deployed in GTO and transferred to GEO with electric propulsion. They (Eutelsat 115 West B and ABS 3A) were launched in 2015 and are now on station.

Prior to this I am only aware of two other satellites having made such a transfer with thrusters that were not intended for that part of the mission. One was Artemis and the other was AEHF-1, and this was in both cases because of earlier failures that would otherwise have prevented deployment in GEO. I believe that all other satellites to date employing ion thrusters or hall effect thrusters have done so with their primary use being for station-keeping once delivered to GEO and they have not spent a long time in transit.

I think this recent paper is relevant: Space Weather Concerns for All-Electric Propulsion Satellites from Ref 1.

I have extracted the following figure from it:

[NB "EOR" refers to "Electric Orbit Raising"]

Satellites are designed with shielding against specifications which in turn depend upon a good picture of the environment. Solar arrays can, to degree, be protected by thicker cover-glasses, hence the 6.7 year part of the caption does not apply to solar arrays other than to show the concept. I believe the Van Allen probes, mentioned in PearsonArtPhoto's response will have featured allowances for uncertainties in the very phenomenon they are there to measure. In the case of geostationary communications satellites which are usually relatively power-hungry compared to science satellites, the effect of mis-judging the uncertainties would be felt later in the mission as the available power dropped.

Lastly, referring to a part of the Dr. Geoffrey Landis article referred to in the question:

He noted the slow speed used by this form of propulsion to transit the Van Allen radiation belts saying that for HSF, one must go through the belts much faster. He said nuclear propulsion was needed, mentioned the fear factor that several have but that we should develop and implement it.

His solution may be consistent with some lunar mission scenarios though there isn't enough context given to conclude that it is "needed".

Ref 1. Horne, R. B., and D. Pitchford (2015), Space Weather Concerns for All-Electric Propulsion Satellites, Space Weather , 13 , 430 – 433, doi:10.1002/2015SW001198

This response addresses the generic degradation of solar arrays passing through Van Allen belts, rather than those specifically bound for the moon.

Its a topic that has stirred up a lot of interest in the last few years as Boeing, a manufacturer of commercial communications satellites, announced a launch of two satellites designed to be deployed in GTO and transferred to GEO with electric propulsion. They (Eutelsat 115 West B and ABS 3A) were launched in 2015 and are now on station.

Prior to this I am only aware of two other satellites having made such a transfer with thrusters that were not intended for that part of the mission. One was Artemis and the other was AEHF-1, and this was in both cases because of earlier failures that would otherwise have prevented deployment in GEO. I believe that all other satellites to date employing ion thrusters or hall effect thrusters have done so with their primary use being for station-keeping once delivered to GEO and they have not spent a long time in transit. [EDIT Much has changed in the last 8 years, as of 2024 the "electric" GTO-GEO transfer is more common these days]

I think this recent paper is relevant: Space Weather Concerns for All-Electric Propulsion Satellites from Ref 1.

I have extracted the following figure from it:

[NB "EOR" refers to "Electric Orbit Raising"]

Satellites are designed with shielding against specifications which in turn depend upon a good picture of the environment. Solar arrays can, to degree, be protected by thicker cover-glasses, hence the 6.7 year part of the caption does not apply to solar arrays other than to show the concept. I believe the Van Allen probes, mentioned in PearsonArtPhoto's response will have featured allowances for uncertainties in the very phenomenon they are there to measure. In the case of geostationary communications satellites which are usually relatively power-hungry compared to science satellites, the effect of mis-judging the uncertainties would be felt later in the mission as the available power dropped.

Lastly, referring to a part of the Dr. Geoffrey Landis article referred to in the question:

He noted the slow speed used by this form of propulsion to transit the Van Allen radiation belts saying that for HSF, one must go through the belts much faster. He said nuclear propulsion was needed, mentioned the fear factor that several have but that we should develop and implement it.

His solution may be consistent with some lunar mission scenarios though there isn't enough context given to conclude that it is "needed".

Ref 1. Horne, R. B., and D. Pitchford (2015), Space Weather Concerns for All-Electric Propulsion Satellites, Space Weather , 13 , 430 – 433, doi:10.1002/2015SW001198