# SP4GATEWAY: a Space Plasma Physics Payload Package conceptual design for the Deep Space Gateway Lunar Orbital Platform

Iannis Dandouras, Pierre Devoto, Johan de Keyser, Yoshifumi Futaana, Ruth Bamford, Graziella Branduardi-Raymont, Dragos Constantinescu, Jean-Yves Chaufray, Jonathan Eastwood, Marius Echim, et al.

<figure><img src="image_1.png" /></figure>

To cite this version:

Iannis Dandouras, Pierre Devoto, Johan de Keyser, Yoshifumi Futaana, Ruth Bamford, et al. SP4GATEWAY: a Space Plasma Physics Payload Package conceptual design for the Deep Space Gateway Lunar Orbital Platform. 22nd EGU General Assembly, May 2020, Online, Unknown Region. pp.id.10565, 10.5194/egusphere-egu2020-10565. insu-04419058

HAL Id: insu-04419058

https://insu.hal.science/insu-04419058

Submitted on 30 May 2024

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# SP4GATEWAY:
A Space Plasma Physics Payload Package conceptual design
for the Deep Space Gateway Lunar Orbital Platform

Iannis Dandouras, Pierre Devoto, Johan De Keyser, Yoshifumi Futaana, André Laurens, Julien Forest, Arnaud Trouche, Sébastien Hess, Jean-Charles Mateo-Vélez, Ruth Bamford, Graziella Branduardi-Raymont, Dragos Constantinescu, Jean-Yves Chaufray, Jonathan Eastwood, Marius Echim, Benjamin Grison, David Hercik, Anna Milillo, Rumi Nakamura, Lubomír Přech, Elias Roussos, Štěpán Štverák, Josef Winter, Matt G. G. T. Taylor, and the SP4GATEWAY team
# SP4GATEWAY:
A Space Plasma Physics Payload Package conceptual design
for the Deep Space Gateway Lunar Orbital Platform

Iannis Dandouras, Pierre Devoto, Johan De Keyser, Yoshifumi Futaana, André Laurens, Julien Forest, Arnaud Trouche, Sébastien Hess, Jean-Charles Mateo-Vélez, Ruth Bamford, Graziella Branduardi-Raymont, Dragos Constantinescu, Jean-Yves Chaufray, Jonathan Eastwood, Marius Echim, Benjamin Grison, David Hercik, Anna Milillo, Rumi Nakamura, Lubomír Přech, Elias Roussos, Štěpán Štverák, Josef Winter, Matt G. G. T. Taylor, and the SP4GATEWAY team
ABSTRACT

The Deep Space Gateway is a crewed platform that will be assembled and operated in the vicinity of the Moon by ESA and its international partners in the early 2020s and will offer new opportunities for fundamental and applied scientific research.

The Moon is a unique location to study the deep space plasma environment, due to the absence of a substantial intrinsic magnetic field and the direct exposure to the solar wind, galactic cosmic rays (GCRs) and solar energetic particles (SEPs). However, 5-6 days each orbit, the Moon crosses the tail of the terrestrial magnetosphere facilitating the in-situ study of the terrestrial magnetotail plasma environment as well as atmospheric escape from the ionosphere. When back outside of the magnetosphere, a variety of these and other phenomena, e.g. those driving solar-terrestrial relationships, can be investigated through remote sensing using a variety of imaging techniques. Most importantly, the lunar environment offers a unique opportunity to study the interaction of the solar wind and the magnetosphere with the lunar surface and the lunar surface-bounded exosphere.

In preparation of the scientific payload of the Deep Space Gateway, we have undertaken a conceptual design study for a Space Plasma Physics Payload Package onboard the Gateway (SP4GATEWAY). The main goal is first to provide a science rationale for hosting space plasma physics instrumentation on the Gateway and to translate that into a set of technical requirements. A conceptual payload design, that identifies a strawman payload and is compatible with the technical requirements, is then put forward. The final outcome of this project, which is undertaken following an ESA AO, is an implementation plan for this space plasma physics payload package.
# ABSTRACT

The Deep Space Gateway is a crewed platform that will be assembled and operated in the vicinity of the Moon by ESA and its international partners in the early 2020s and will offer new opportunities for fundamental and applied scientific research.

The Moon is a unique location to study the deep space plasma environment, due to the absence of a substantial intrinsic magnetic field and the direct exposure to the solar wind, galactic cosmic rays (GCRs) and solar energetic particles (SEPs). However, 5-6 days each orbit, the Moon crosses the tail of the terrestrial magnetosphere facilitating the in-situ study of the terrestrial magnetotail plasma environment as well as atmospheric escape from the ionosphere. When back outside of the magnetosphere, a variety of these and other phenomena, e.g. those driving solar-terrestrial relationships, can be investigated through remote sensing using a variety of imaging techniques. Most importantly, the lunar environment offers a unique opportunity to study the interaction of the solar wind and the magnetosphere with the lunar surface and the lunar surface-bounded exosphere.

In preparation of the scientific payload of the Deep Space Gateway, we have undertaken a conceptual design study for a Space Plasma Physics Payload Package onboard the Gateway (SP4GATEWAY). The main goal is first to provide a science rationale for hosting space plasma physics instrumentation on the Gateway and to translate that into a set of technical requirements. A conceptual payload design, that identifies a strawman payload and is compatible with the technical requirements, is then put forward. The final outcome of this project, which is undertaken following an ESA AO, is an implementation plan for this space plasma physics payload package.
# Moon space plasma environment

During 21 – 22 days every Lunar orbit the Moon is directly exposed to the Solar wind

<figure><img src="image_1.png" /></figure>

Due to the absence of a substantial magnetic field, it is then exposed to:

* Solar Wind : ~keV

* Solar Energetic Particles (SEPs): ~MeV

* Jovian Energetic Electrons : ~MeV

* Galactic Cosmic Rays (GCRs) : ~GeV

The Moon's vicinity, during these periods, is typical of deep space

During the remaining 5 – 6 days of each Lunar orbit the Moon gets within the terrestrial magnetotail

Moon exposed then to the terrestrial magnetotail plasma environment:

* **Plasmoids** released from the near-Earth magnetotail

* **Bursty bulk flows** (BBFs)

* Magnetic reconnection

* Plasma sheet dynamics

* Ion outflow from the terrestrial ionosphere

## Lunar exosphere

<figure><img src="image_2.png" /></figure>

Regolith – exosphere - space environment: a complex multi-scale system
# Moon space plasma environment

During 21 – 22 days every Lunar orbit the Moon is directly exposed to the Solar wind

<figure><img src="image_2.png" /></figure>

Due to the absence of a substantial magnetic field, it is then exposed to:

* Solar Wind : ~keV

* Solar Energetic Particles (SEPs): ~MeV

* Jovian Energetic Electrons : ~MeV

* Galactic Cosmic Rays (GCRs) : ~GeV

The Moon's vicinity, during these periods, is typical of deep space

## Lunar exosphere

<figure><img src="image_3.png" /></figure>

During the remaining 5 – 6 days of each Lunar orbit the Moon gets within the terrestrial magnetotail

Moon exposed then to the terrestrial magnetotail plasma environment:

* **Plasmoids** released from the near-Earth magnetotail

* **Bursty bulk flows (BBFs)**

* Magnetic reconnection

* Plasma sheet dynamics

* Ion outflow from the terrestrial ionosphere

## Regolith – exosphere - space environment: a complex multi-scale system
Deep Space (or Lunar Orbital Platform) Gateway

☐ Crewed platform that will be assembled (2022 – 2028) and operated in the vicinity of the Moon by NASA, ESA, Roscosmos, JAXA and CSA.

☐ Will offer new opportunities for fundamental and applied scientific research.

<figure><img src="image_3.png" /></figure>

In preparation of its scientific payload, ESA set up international science teams to prepare and to support the definition of payload studies, including a topical team in the field of space plasma physics.
Deep Space (or Lunar Orbital Platform) Gateway

☐ Crewed platform that will be assembled (2022 – 2028) and operated in the vicinity of the Moon by NASA, ESA, Roscosmos, JAXA and CSA.

☐ Will offer new opportunities for fundamental and applied scientific research.

<figure><img src="image_4.png" /></figure>

In preparation of its scientific payload, ESA set up international science teams to prepare and to support the definition of payload studies, including a topical team in the field of space plasma physics.
<table><thead><tr><th>Science Objective</th><th>Measurement Requirement<br>Short Term</th><th>In-situ Meas.<br>Instrument</th><th>Remote Sensing<br>Instrument</th></tr></thead><tbody><tr><td>Monitor solar wind as a driver for the dynamics of terrestrial magnetosphere, terrestrial & lunar exospheres, lunar surface sputtering & charging</td><td>Solar wind density & transport velocity<br>1 – 10<sup>2</sup> cm<sup>-3</sup>, 200 – 1000 km/s<br>IMF: 10 000 nT instrument range<br>1 nT / 0.1 nT absolute/relative resol.</td><td>Faraday Cup<br>Electrostatic Analyser</td><td>-</td></tr><tr><td>Monitor & characterise SEPs & GCRs for rad. environment & as lunar surface sputtering sources</td><td>40 keV – 100 MeV ions (SEPs)<br>up to ~5 GeV (GCRs)<br>500 MeV / nucleon for composition</td><td>Energetic particle detectors</td><td>MeV ENA Imager</td></tr><tr><td>Monitor and characterise the response of the terrestrial magnetosphere to the solar wind with a wide coverage of geospace</td><td>Detect and image solar wind charge exchange X-rays (0.2 – 2.0 keV),<br>FOV 10° x 10°, angular resolution: 0.3 R<sub>E</sub> from the Moon</td><td></td><td>Soft X-ray Imager<br>ENA Imager</td></tr><tr><td>Monitor solar wind interaction with lunar exosphere, regolith & magnetic anomalies</td><td>Detect and image low-energy ENAs, 0.1 – 10 keV,<br>30% ΔE/E, ~5° resol.<br>Strong UV suppression: 10<sup>-8</sup></td><td></td><td>LENA imager</td></tr><tr><td>Reveal the solar wind ion dynamics in the vicinity of the lunar magnetic anomalies</td><td>Detect and image low-energy ENAs,<br>0.01 – 3 keV, 30% ΔE/E,<br>~5° resol., FOV ~ 5° x 120°</td><td></td><td>LENA imager</td></tr><tr><td>Monitor the terrestrial & lunar exospheres, plasmasphere</td><td>Detect and image EUV emissions<br>30.4, 83.6, 121.6 & 130.4 nm<br>~5 arcmin resol.</td><td></td><td>UV / EUV<br>spectro-imager</td></tr><tr><td>Monitor ambient plasma in different environments (solar wind/magnetosheath/terrestrial magnetotail/lunar wake)</td><td>Plasma density & temperature<br>10<sup>-4</sup> – 10<sup>2</sup> cm<sup>-3</sup><br>Magnetic field: 10 000 nT range<br>1 nT / 0.1 nT absolute/relative resol.</td><td>Langmuir probe<br>Magnetometer</td><td></td></tr></tbody></table>
<table><thead><tr><th>Science Objective</th><th>Measurement Requirement<br>Short Term</th><th>In-situ Meas.<br>Instrument</th><th>Remote Sensing<br>Instrument</th></tr></thead><tbody><tr><td>Monitor solar wind as a driver for the dynamics of terrestrial magnetosphere, terrestrial & lunar exospheres, lunar surface sputtering & charging</td><td>Solar wind density & transport velocity<br>1 – 10<sup>2</sup> cm<sup>-3</sup>, 200 – 1000 km/s<br>IMF: 10 000 nT instrument range<br>1 nT / 0.1 nT absolute/relative resol.</td><td>Faraday Cup<br>Electrostatic Analyser</td><td>-</td></tr><tr><td>Monitor & characterise SEPs & GCRs for rad. environment & as lunar surface sputtering sources</td><td>40 keV – 100 MeV ions (SEPs)<br>up to ~5 GeV (GCRs)<br>500 MeV / nucleon for composition</td><td>Energetic particle detectors</td><td>MeV ENA Imager</td></tr><tr><td>Monitor and characterise the response of the terrestrial magnetosphere to the solar wind with a wide coverage of geospace</td><td>Detect and image solar wind charge exchange X-rays (0.2 – 2.0 keV),<br>FOV 10° x 10°, angular resolution: 0.3 R<sub>E</sub> from the Moon</td><td></td><td>Soft X-ray Imager<br>ENA Imager</td></tr><tr><td>Monitor solar wind interaction with lunar exosphere, regolith & magnetic anomalies</td><td>Detect and image low-energy ENAs, 0.1 – 10 keV,<br>30% ΔE/E, ~5° resol.<br>Strong UV suppression: 10<sup>-8</sup></td><td></td><td>LENA imager</td></tr><tr><td>Reveal the solar wind ion dynamics in the vicinity of the lunar magnetic anomalies</td><td>Detect and image low-energy ENAs,<br>0.01 – 3 keV, 30% ΔE/E,<br>~5° resol., FOV ~ 5° x 120°</td><td></td><td>LENA imager</td></tr><tr><td>Monitor the terrestrial & lunar exospheres, plasmasphere</td><td>Detect and image EUV emissions<br>30.4, 83.6, 121.6 & 130.4 nm<br>~5 arcmin resol.</td><td></td><td>UV / EUV<br>spectro-imager</td></tr><tr><td>Monitor ambient plasma in different environments (solar wind/magnetosheath/terrestrial magnetotail/lunar wake)</td><td>Plasma density & temperature<br>10<sup>-4</sup> – 10<sup>2</sup> cm<sup>-3</sup><br>Magnetic field: 10 000 nT range<br>1 nT / 0.1 nT absolute/relative resol.</td><td>Langmuir probe<br>Magnetometer</td><td></td></tr></tbody></table>
SP4GATEWAY:
Space Plasma Physics
Payload Package Conceptual Design for the Gateway

☐ Translate the **science rationale** for space plasma physics instrumentation into a set of **technical requirements**.

☐ Simulate the Gateway – plasma environment interaction.

☐ Conceptual payload design, that identifies a strawman payload and is compatible with the technical requirements.

☐ Instruments grouped in terms of **accommodation & pointing requirements**
(Sun / Earth / Lunar pointing, fixed mounting or on a pointable 1-axis rotation platform).

☐ The final outcome of this project, which is undertaken following an ESA AO, will be an
implementation plan for this space plasma physics payload package.
SP4GATEWAY:
Space Plasma Physics
Payload Package Conceptual Design for the Gateway

☐ Translate the **science rationale** for space plasma physics instrumentation into a set of **technical requirements**.

☐ Simulate the Gateway – plasma environment interaction.

☐ Conceptual payload design, that identifies a strawman payload and is compatible with the technical requirements.

☐ Instruments grouped in terms of **accommodation & pointing requirements**
(Sun / Earth / Lunar pointing, fixed mounting or on a pointable 1-axis rotation platform).

☐ The final outcome of this project, which is undertaken following an ESA AO, will be an **implementation plan for this space plasma physics payload package.**
Gateway Phase 2:
2024 - 2028

**US-Hab:** *US Habitat*

**International-Hab:** *International Habitat*

**HALO:** *Habitation and Logistics Outpost*

**PPE:** *Power & Propulsion Element*

**LM:** *Logistics Module*

**HLS:** *Human Landing System*

<figure><img src="image_4.png" /></figure>
Gateway Phase 2:
2024 - 2028

**US-Hab:** *US Habitat*

**International-Hab:** *International Habitat*

**HALO:** *Habitation and Logistics Outpost*

**PPE:** *Power & Propulsion Element*

**LM:** *Logistics Module*

**HLS:** *Human Landing System*

<figure><img src="image_5.png" /></figure>
# Deep Space Gateway: Orbit

<figure><img src="image_5.png" /></figure>

<figure><img src="image_6.png" /></figure>

<table><thead><tr><th>Orbit</th><th>Property</th><th>Value</th></tr></thead><tbody><tr><td rowspan="5">Near Rectilinear Halo Orbit (NRHO)</td><td>Period</td><td>≈6.5 (Earth) days</td></tr><tr><td>Orbit around</td><td>Moon</td></tr><tr><td>Periapsis × Apoapsis</td><td>≈3 200 × 70 000 km</td></tr><tr><td>Inclination</td><td>≈90°</td></tr><tr><td>Earth visibility</td><td>Constant</td></tr><tr><td></td><td colspan="2">9:2 resonance with the lunar synodic period</td></tr></tbody></table>

<figure><img src="image_7.png" /></figure>

<figure><img src="image_8.png" /></figure>

## Deep Space Gateway: Attitude

<figure><img src="image_9.png" /></figure>

<figure><img src="image_10.png" /></figure>
# Deep Space Gateway: Orbit

<figure><img src="image_6.png" /></figure>

<figure><img src="image_7.png" /></figure>

<table><thead><tr><th>Orbit</th><th>Property</th><th>Value</th></tr></thead><tbody><tr><td rowspan="5">Near Rectilinear Halo Orbit (NRHO)</td><td>Period</td><td>≈6.5 (Earth) days</td></tr><tr><td>Orbit around</td><td>Moon</td></tr><tr><td>Periapsis × Apoapsis</td><td>≈3 200 × 70 000 km</td></tr><tr><td>Inclination</td><td>≈90°</td></tr><tr><td>Earth visibility</td><td>Constant</td></tr><tr><td></td><td colspan="2">9:2 resonance with the lunar synodic period</td></tr></tbody></table>

<figure><img src="image_8.png" /></figure>

<figure><img src="image_9.png" /></figure>

## Deep Space Gateway: Attitude

<figure><img src="image_10.png" /></figure>

<figure><img src="image_11.png" /></figure>
# Simulation of the Gateway – plasma environment interaction

<figure><img src="image_11.png" /><figcaption>Electrostatic potential simulation
in the solar wind</figcaption></figure>

<figure><img src="image_12.png" /><figcaption>Ambient proton density (m⁻³)
in the solar wind</figcaption></figure>

<figure><img src="image_13.png" /><figcaption>Electrostatic potential simulation
in the magnetotail</figcaption></figure>

## Identification of the most favourable positions for the plasma instruments

Remaining positions can then be used for energetic particle & magnetospheric imaging instruments
Simulation of the Gateway – plasma environment interaction

<figure><img src="image_12.png" /><figcaption>Electrostatic potential simulation
in the solar wind</figcaption></figure>

<figure><img src="image_13.png" /><figcaption>Ambient proton density (m⁻³)
in the solar wind</figcaption></figure>

<figure><img src="image_14.png" /><figcaption>Electrostatic potential simulation
in the magnetotail</figcaption></figure>

Identification of the most favourable positions for the plasma instruments

Remaining positions can then be used for energetic particle & magnetospheric imaging instruments
# Preliminary space plasma physics instrumentation conceptual design

<figure><img src="image_14.png" /></figure>

Work in progress...
# Preliminary space plasma physics instrumentation conceptual design

<figure><img src="image_15.png" /></figure>

Work in progress...
<figure><img src="image_15.png" /></figure>

cMAGF

MAGF Sensor (1)

cMENA

MENA Body (1)

cMISP

MISP
<figure><img src="image_16.png" /></figure>

cMAGF

MAGF Sensor (1)

cMENA

MENA Body (1)

cMISP

MISP
Instrument Fields-of-View (FOV) / Fields-of-Regard (FOR) along the Gateway Orbit

<figure><img src="image_16.png" /></figure>

cENPD FOVs near periapsis:

* Pristine energetic particles flux (purple FOV)

* Moon albedo energetic particles flux (yellow FOV)

<figure><img src="image_17.png" /></figure>

cLENA instantaneous FOV (in magenta) near periapsis. Yellow line: track of the centre of the FOV, for the portion of the orbit close to periapsis, as projected on the sky.

<figure><img src="image_18.png" /></figure>

cMENA instantaneous FOR (total accessible FOV, using the 1-axis rotation platform), in magenta, as projected on the sky.
# Instrument Fields-of-View (FOV) / Fields-of-Regard (FOR) along the Gateway Orbit

<figure><img src="image_17.png" /></figure>

## cENPD FOVs near periapsis:

* Pristine energetic particles flux (purple FOV)

* Moon albedo energetic particles flux (yellow FOV)

<figure><img src="image_18.png" /></figure>

## cLENA instantaneous FOV (in magenta)

near periapsis. Yellow line: track of the centre of the FOV, for the portion of the orbit close to periapsis, as projected on the sky.

<figure><img src="image_19.png" /></figure>

## cMENA instantaneous FOR

(total accessible FOV, using the 1-axis rotation platform), in magenta, as projected on the sky.
* The Deep Space Gateway Lunar Orbital Platform is well-suited for space plasma physics research

* Conceptual design for a Space Plasma Physics Payload Package, under an ESA study

<figure><img src="image_19.png" /></figure>
* The Deep Space Gateway Lunar Orbital Platform is well-suited for space plasma physics research

* Conceptual design for a Space Plasma Physics Payload Package, under an ESA study

<figure><img src="image_20.png" /></figure>