<figure><img src="image_41.png" /><figcaption>**Figure 28.** The Elliptical platform is based on the THEMIS spacecraft (Harvey et al. 2008), shown above. This platform carries the Magnetosphere and Ion Escape instruments. The spacecraft spins at 16 RPM to stabilize the radial EFI booms and sweep out the fields of view of the particle instruments (ESA and SST). The steady spin also helps to calibrate the magnetometers.</figcaption></figure>

ion-electron instrument is expected to have a mass of ~5 kg and consume ~6 W. The electron instrument is TRL 9. The components of the ion instrument (electrostatic analyzer and time-of-flight mass spectrometer) are flight-proven through successful mission operations—e.g., THEMIS-ESA (McFadden et al. 2008), shown in Figure 28, and MAVEN-STATIC (McFadden et al. 2015)—although this particular configuration has not been flown. Thus, the ion instrument is TRL 6.

### Electric field instrument (Elliptical platform)

The Electric Field Instrument measures the three components of the ambient electric field over a range of ±300 mV m⁻¹ (DC) and ±100 mV m⁻¹ (AC). Waveform measurements cover DC up to 4 kHz, with AC-coupled differential measurements from ~10 Hz to 8 kHz. Onboard spectral measurements cover the same ranges, in addition to providing an estimate of integrated power in the 100–400 kHz band. The instrument also measures the spacecraft floating potential. The instrument operates continuously, producing spin-averaged vectors, waveform data, and spectral data, which can be configured to fit within the available telemetry bandwidth. The instrument, which is based on THEMIS EFI (Bonnell et al. 2008), is composed of six sensors (high-input-impedance, low-noise, broadband digital voltmeters) with preamps at the ends of six booms: four spin-stabilized 22 m wire booms orthogonal to the spin axis, and two 2.5 m stacer booms along the spin axis, as shown in Figure 28. The mass including booms is 12 kg, and the instrument consumes 0.24 W. This instrument is TRL 9.

### Search coil magnetometer (Elliptical platform)

The tri-axial Search Coil Magnetometer is designed to measure the magnetic components of plasma waves in the Mars environment. Three search coil antennas cover the bandwidth from 0.1 Hz to 4 kHz, which provides overlap with the fluxgate magnetometer. Each antenna consists of a high magnetic permeability core (which amplifies the ambient field) surrounded

by two wire windings. The main winding, with ~50,000 turns, passively detects voltage induced by the changing external field. The secondary winding is used to induce feedback to flatten the temperature-dependent frequency response. The sensor is mounted at the end of a rigid one-meter boom. The instrument operates continuously, producing waveforms, FFT processed data, and filter-bank data. The instrument has a mass of 1.8 kg and consumes 0.075 W. The instrument has flown on eight Earth-orbiting and interplanetary missions, most recently THEMIS (Roux et al. 2008). It is TRL 9.

### Ion spectrometer (Areo Carrier and Areo SmallSat A/B platforms)

The ion spectrometer for the non-spinning areostationary platform is a toroidal electrostatic analyzer with electrostatic deflectors to provide a 360 × 90° field of view, with a mechanical attenuator to provide a high dynamic range. The instrument measures ions from 5 eV to 25 keV, with an energy resolution of 14.5% (dE/E, FWHM) and an angular resolution of 3.75° × 4.5° in the sunward direction and 22.5° × 22.5° elsewhere. The instrument operates continuously, generating energy-angle distributions, energy spectra, and bulk moments. These data products are packaged into telemetry with different (adjustable) cadences to fit within the available telemetry bandwidth. This instrument would be based closely on MAVEN-SWIA (shown in Figure 28 left) (Halekas et al. 2015), which has a mass of 2.6 kg and consumes 2.1 W. It is TRL 9.

### Electron spectrometer (Areo Carrier and Areo SmallSat A/B platforms)

The electron spectrometer is a hemispherical electrostatic analyzer with electrostatic deflectors to provide a 360 × 120° field of view. The instrument measures the energy and angle distributions of electrons from 3 eV to 4.6 keV with an energy resolution of 17% (dE/E, FWHM) and an angular resolution of 22.5 × 20°. The instrument has two concentric toroidal entrance grids across which a sweepable potential can be placed to decelerate electrons as they enter the analyzer. This can be used to provide finer energy resolution for measuring ionospheric photoelectrons, for lowering the sensitivity to high magnetosheath fluxes, and to calibrate the low-energy response in flight. The instrument operates continuously, generating energy-angle distributions, PADs, and energy spectra with different cadences to fit within the available telemetry bandwidth. PADs are calculated on board in real time using data from the fluxgate magnetometer. This allows high-cadence PADs with modest telemetry usage. This instrument would be based closely on MAVEN-SWEA (shown in Figure 29 right) (Mitchell et al. 2016), which has a mass of 1.8 kg and consumes 1.6 W. It is TRL 9.

### Solid-state telescope (Energetic Particle Detector) (Areo Carrier and Areo SmallSat A platforms)

The solid-state telescope measures the energy spectrum and angular distribution of energetic electrons (20–1000 keV) and ions (20–6000 keV). It consists of two identical sensors located on the spacecraft body. Each sensor consists of a dual, double-ended telescope that collimates ions and electrons onto a stack of three passivated ion-implanted silicon detectors. One end of the telescope is covered by a foil that stops ions below 400 keV, while the opposite end has a broom magnet that sweeps away electrons below 400 keV, so ions and electrons below this energy are cleanly separated. Higher-energy electrons and ions are identified by the energy loss in an
<figure><img src="image_42.png" /><figcaption>**Figure 29.** The ion and electron spectrometers on the Areo platforms are based on the MAVEN Solar Wind Ion Analyzer (Halekas et al. 2015), left, and Solar Wind Electron Analyzer (Mitchell et al. 2016), right. Both instruments use electrostatic deflectors to increase their fields of view on a three-axis stabilized spacecraft.</figcaption></figure>

<figure><img src="image_43.png" /><figcaption>**Figure 30.** The solid-state telescope on the Aero platforms is based on MAVEN SEP (Larson et al. 2015), above. Top: Cross section showing the locations of the solid-state detector stack and the positions of sweep magnets and foils to separate energetic ions and electrons. Bottom: MAVEN SEP flight model. Red aperture covers are for protection on the ground and are removed for flight.</figcaption></figure>

outside detector ($dE/dx$) coincident with the energy (E) deposited in the center detector. Two telescopes are packaged with oppositely directed sweep magnets sharing a yoke to save mass and minimize stray fields (see Figure 30). Each telescope has a rectangular 42 × 31° field of view. The instrument operates continuously, measuring events once per second, which are collected, accumulated, and packetized to fit within the available telemetry bandwidth. A total of 128 energy/angle bins are available for accumulations, allowing 16 energy steps × 4 angles × 2 species per time step. The instrument has

a mass of 0.9 kg and consumes an average power of 5.5 W. This instrument has been flown on MAVEN (shown in Figure 30) (Larson et al. 2015), THEMIS, and STEREO (Lin et al. 2008). It is TRL 9.

*EUV monitor (Areo Carrier and Areo SmallSat A platforms)*

The EUV monitor is a set of four photometers that consist of very stable Si photodiodes covered by thin metal film or interference filters and a pre-amplifier circuit. Different filters provide sensitivity in three wavelength ranges: C/Al/Nb/C thin foil (17–22 nm), C/Al/Ti/C thin foil (0.1–7 nm), and an
<figure><img src="image_44.png" /><figcaption>**Figure 31.** The MAVEN EUV monitor (Eparvier et al. 2015) shown on a lab bench. Photo credit: University of Colorado LASP.</figcaption></figure>

interference filter for Lyα (121–122 nm). A fourth diode is permanently covered to monitor variations in dark signal due to

temperature and radiation background changes. The three science channels monitor emissions from the highly variable corona and transition region of the solar atmosphere. The instrument operates continuously with a measurement cadence of 1 s. The broadband sensors monitor the most rapid changes in solar irradiance due to flares. These measurements can be used in a spectral irradiance model (M-FISM) to generate the full EUV spectrum at Mars from 0.1 to 190 nm in 1 nm bins (Thiemann et al. 2017). The instrument has a mass of 1.1 kg and consumes 0.73 W. The instrument is based on MAVEN-EUVM (Eparvier et al. 2015) (see Figure 31), with three modifications: (1) a smaller, lower-power electronics box, (2) a smaller, lower-mass photometer system, and (3) a modified optical path that includes a reflection to reject soft X-rays for improved sensitivity in the 17–22 nm channel. It is currently TRL 4, but could be brought to TRL 6 within ~6 months.

### A.8. Measurement Requirements

Figure 32 provides detailed requirements for all of MOSAIC’s required measurements, separately for each of the eight scientific investigations.
<table><caption>Figure 32. Detailed Requirements for Each of the Measurements Required to Complete the Eight MOSAIC Science Investigations</caption><thead><tr><th rowspan="2">ID</th><th rowspan="2">Instrument Type(s)</th><th rowspan="2">Physical Parameter (PP) Description</th><th rowspan="2">Link to Objectives</th><th rowspan="2">Units</th><th rowspan="2">PP Range</th><th rowspan="2">PP Resolution</th><th rowspan="2">PP Altitude Range</th><th rowspan="2">PP Altitude Resolution</th><th rowspan="2">PP Coordinate System</th><th rowspan="2">PP Local Time (LT) Range</th><th rowspan="2">PP LT Resolution</th><th rowspan="2">PP Longitudinal Range</th><th rowspan="2">PP Longitudinal Resolution</th><th rowspan="2">PP Latitude Range</th><th rowspan="2">PP Latitude Resolution</th><th rowspan="2">PP Cadence</th><th rowspan="2">PP Seasonal Range</th><th rowspan="2">PP Seasonal Resolution</th><th rowspan="2">OQ Description</th><th colspan="5">Observable Quantity (OQ), Separate from physical parameter for remote data</th><th rowspan="2">Angular FOV Azimuth (X) range Resolution</th><th rowspan="2">Azimuth (X) range Resolution</th><th rowspan="2">Polar (Y) Range</th><th rowspan="2">Energy/ Wavelength/ Frequency Range</th><th rowspan="2">Resolution</th><th rowspan="2">Mass (where applicable) Mass Range Resolution</th></tr><tr><th>OQ Description</th><th>OQ Units</th><th>OQ Dynamic Range</th><th>OQ Precision</th><th>OQ SNR</th><th>OQ Time Resolution</th></tr></thead><tbody><tr><td>ICE-1</td><td>Radar (P-band) Polarimetric SAR)</td><td>Surface ice distribution over time</td><td>Objectives I.A. - II.A. Essential for monitoring of surface changes due to volatile exchange with the atmosphere and for the characterization of potentially extractable water ice resources</td><td>Percent ice coverage per unit area over time</td><td>0-100% 10%</td><td></td><td>0 m</td><td>N/A</td><td>IAU Mars</td><td>0-24 h</td><td>N/A</td><td>180°W - 180°E</td><td>30 m</td><td>80°S - 80°N</td><td>30 m</td><td>N/A - Cadence determined by orbital speed and longitudinal/ altitude resolution</td><td>0-360° Ls</td><td>90°</td><td>Returned radar power dimension as a ratio of less a standard power</td><td>Watts or dimension (saturation level of instrument)</td><td>30 dB to infinity (noise limit)</td><td>9</td><td>N/A - Cadence determined by orbital speed and longitudinal/ altitude resolution.</td><td>N/A - no imaging. Each integration is one "pixel"</td><td>0.15°</td><td>N/A - no imaging. Each integration is one "pixel"</td><td>3°</td><td>350-450 MHz</td><td>N/A each pulse is a multi-frequency "chirp"</td><td>N/A</td><td>N/A</td></tr><tr><td>ICE-2</td><td>Radar (P-band) Polarimetric SAR)</td><td>Near-surface moisture content</td><td>Objectives I.A. - II.A. Essential for monitoring of surface changes due to volatile exchange with the atmosphere and for the characterization of potentially extractable water ice resources</td><td>Percentage (%)</td><td>0-100% Moisture content: (0-1 cm²/cm³)</td><td>0-3 m subsurface ice</td><td></td><td>Bulk measurement (no resolution, sensitive to entire column)</td><td>IAU Mars</td><td>0-24 h</td><td>N/A</td><td>180°W - 180°E</td><td>30 m</td><td>80°S - 80°N</td><td>30 m</td><td>N/A - Cadence determined by orbital speed and longitudinal/ altitude resolution</td><td>0-360° Ls</td><td>90°</td><td>Circular polarization ratio</td><td>Dimensionless</td><td>0-2</td><td>0.1</td><td>N/A</td><td>N/A - Cadence determined by orbital speed and longitudinal/ altitude resolution.</td><td>N/A - no imaging. Each integration is one "pixel"</td><td>0.15°</td><td>N/A - no imaging. Each integration is one "pixel"</td><td>3°</td><td>350-450 MHz</td><td>N/A each pulse is a multi-frequency "chirp"</td><td>N/A</td><td>N/A</td></tr><tr><td>ICE-2</td><td>Radar (P-band) Sounder)</td><td>Near-surface moisture content</td><td>Objectives I.A. - II.A. Essential for monitoring of surface changes due to volatile exchange with the atmosphere and for the characterization of potentially extractable water ice resources</td><td>Percentage (%)</td><td>0-100% Moisture content: (0-1 cm²/cm³)</td><td>1-15 m subsurface ice</td><td></td><td>0.8 m in water ice</td><td>IAU Mars</td><td>0-24 h</td><td>N/A</td><td>180°W - 180°E</td><td>1 km</td><td>80°S - 80°N</td><td>1 km</td><td>N/A - Cadence determined by orbital speed and longitudinal/ altitude resolution</td><td>0-360° Ls</td><td>90°</td><td>Dielectric permittivity</td><td>Dimensionless</td><td>0-15</td><td>0.1</td><td>maximum 9 (decreases with depth)</td><td>N/A - Cadence determined by orbital speed and longitudinal/ altitude resolution.</td><td>N/A - no imaging. Each integration is one "pixel"</td><td>0.15°</td><td>N/A - no imaging. Each integration is one "pixel"</td><td>3°</td><td>350-450 MHz</td><td>N/A each pulse is a multi-frequency "chirp"</td><td>N/A</td><td>N/A</td></tr><tr><td>ICE-3</td><td>Wide angle imager (VIS) distribution over time</td><td>Surface ice distribution over time</td><td>Objectives I.A. - II.A. Essential for monitoring of surface changes due to volatile exchange with the atmosphere and for the characterization of potentially extractable water ice resources</td><td>Percent ice coverage per unit area over time</td><td>0-100% 10%</td><td>N/A</td><td></td><td>N/A</td><td>IAU Mars</td><td>Daytime</td><td>N/A</td><td>180°W - 180°E</td><td>1 km</td><td>80°S - 80°N</td><td>1 km</td><td>Daily global coverage (as downlink rate allows)</td><td>0-360° Ls</td><td>90°</td><td>RGB values</td><td>Data number (DN)</td><td>0-2047 (11 bit)</td><td>&lt; 10% (VIS), &lt; 20% (UV)</td><td>&gt; 100 (VIS)</td><td>10-100 s msec (VIS), 1-10 s sec (UV)</td><td>22°</td><td>0.01°</td><td>22°</td><td>0.01°</td><td>0.34-0.75 µm, 1.1-1.6 µm</td><td>6 channels between 0.34-0.75 µm, 6 channels between 1.1-1.6 µm</td><td>N/A</td><td>N/A</td></tr><tr><td>ATM-1</td><td>Radio occultation</td><td>Vertical profile of temperature</td><td>Objectives I.B. - I.C.1. - I.B. Essential for monitoring of atmospheric state and collection of long-term climatologies.</td><td>Kelvin</td><td>150-300 K</td><td>1 K near the surface (10 K at 40 km)</td><td>0-40 km</td><td>2 km or less</td><td>PC</td><td>0-24 h</td><td>depends</td><td>180°W - 180°E</td><td>~ 1°</td><td>90°S - 90°N possible (depends on orbits)</td><td>~ 1 deg</td><td>up to ~30 soundings/daily per pair of spacecrafts</td><td>0-360° Ls</td><td>90°</td><td>depends on number of satellites and orbits</td><td>Doppler shift</td><td>Hz</td><td>10 Hz at X-band</td><td>10 mHz</td><td>50 dB-Hz 0.1 sec</td><td>60°</td><td>N/A</td><td>10°</td><td>N/A</td><td>1-10 GHz</td><td>N/A</td><td>N/A</td><td>N/A</td></tr><tr><td>ATM-2</td><td>Radio occultation (Added Sub-mm here as note that it's derived along with other variables)</td><td>Vertical profile of pressure</td><td>Objectives I.B. - I.C.1. - I.B. Essential for monitoring of atmospheric state and collection of long-term climatologies.</td><td>Pascals</td><td>10°-10° Pa</td><td>2 Pa near 0-40 km</td><td>2 km or less</td><td>PC</td><td>0-24 h</td><td>depends</td><td>180°W - 180°E</td><td>~ 1°</td><td>90°S - 90°N possible (depends on orbits)</td><td>~ 1 deg</td><td>up to ~30 soundings/daily per pair of spacecrafts</td><td>0-360° Ls</td><td>90°</td><td>depends on number of satellites and orbits</td><td>Doppler shift</td><td>Hz</td><td>10 Hz at X-band</td><td>10 mHz</td><td>50 dB-Hz 0.1 sec</td><td>60°</td><td>N/A</td><td>10°</td><td>N/A</td><td>1-10 GHz</td><td>N/A</td><td>N/A</td><td>N/A</td></tr></tbody></table>
## A.9. Instrument Requirements

Figure 33 provides detailed requirements for all of the scientific instruments necessary to make MOSAIC's required measurements.

<table><caption>Figure 33. Details of Measurement, Accommodation, and Development Requirements for the MOSAIC Instruments. Each row corresponds to a single instrument</caption><thead><tr><th>Investigation<br>ICE</th><th>Description<br>Radar (P-<br>band SAR)</th><th>Name<br>(polarimetric<br>orbital p-band<br>SAR)</th><th>Platform<br>Mothership</th><th>Measurements<br>(Up to 4; please link to physical parameters)</th><th>Supplier</th><th>TRL</th><th>Time to<br>TRL5</th><th>$ to<br>TRL5</th><th>Time<br>TRL 5 to 6</th><th>$ TRL<br>5 to 6</th><th>FOV</th><th>Mass</th><th>Power</th><th>Volume</th><th>Accommodation/<br>Operational<br>Requirement</th><th>Wavelength/<br>Frequency/<br>Energy/<br>Field Range<br>400 MHz</th><th>Resolution/<br>Number of<br>channels<br>30 m<br>(HDR)/100<br>m (LDR)</th><th>Bits Per<br>Sample</th><th>Sample<br>Rate</th><th>Threshold<br>Data Rate<br>(bps)<br>800,000</th><th>Baseline<br>Data Rate<br>(orbital<br>average bps)<br>1.50E+06</th><th>Phase A-D<br>Cost ($FY20)<br>$170M<br>(estimate<br>based on<br>ESA<br>Biomass)</th><th>Contributable?<br>Yes - Canada<br>(already<br>offered as<br>part of<br>COMPASS)</th><th>Notes</th></tr></thead><tbody><tr><td>ICE</td><td>UV-VIS-NIR<br>Imager</td><td>Mars<br>Atmosphere,<br>Volatile, and<br>Resource<br>Investigation<br>Camera<br>(MAVIC)</td><td>Mothership</td><td>Duration of<br>(dust/water<br>ice) aerosol<br>clouds</td><td>Water ice<br>column<br>opacity</td><td></td><td>N/A</td><td>N/A</td><td>N/A</td><td>N/A</td><td>35-39°<br>(based on<br>Eagle)</td><td>125 kg<br>(based on<br>ESA<br>Biomass)</td><td>200 W<br>operational,<br>500 W peak</td><td>1.94 m³<br>(Eagle)</td><td></td><td>0.34-0.75<br>um, 1.1-1.6<br>um</td><td>6 channels<br>between<br>0.34-0.75<br>um, 6<br>channels<br>between<br>1.1-1.6 um</td><td></td><td>8.8 Gb/sol<br>downlinked<br>~102 Kbps<br>collected<br>orbit<br>average</td><td>11 Gb/sol<br>downlinked<br>~127 Kbps<br>collected<br>orbit<br>average</td><td>$13M<br>(without<br>reserves)</td><td>Yes</td><td></td></tr><tr><td>ATM</td><td>Lidar</td><td>MARLI</td><td>Mothership</td><td>Vertical<br>profile of<br>horizontal<br>wind in its<br>zonal and<br>meridional<br>components<br>(U, V)</td><td>Vertical<br>profile of<br>dust<br>opacity</td><td></td><td></td><td>6 by 6/2020</td><td></td><td></td><td></td><td>38 kg</td><td>81 W</td><td>760 x 760<br>x 640 mm</td><td></td><td>1064 nm</td><td></td><td>50<br>kbps/<br>data rate<br>50 kbps<br>baseline</td><td>25 kbps<br>threshold,<br>50 kbps<br>baseline</td><td>50000</td><td>$-40M</td><td>No</td><td></td></tr><tr><td>ATM</td><td>Lidar</td><td>OPAL</td><td>Mothership</td><td>0-50 km or<br>greater<br>temperature</td><td>Pressure,<br>density,<br>(down to<br>surface<br>possible</td><td>Aerosol<br>Opacity</td><td>Wind<br>velocity<br>(u.v.w)</td><td>NASA<br>Langley</td><td>3<br>(Developed<br>under the<br>IRAD<br>program)</td><td>3 years</td><td>$3M</td><td>2 years</td><td>$5M</td><td>-0.1<br>mrad</td><td>40 kg</td><td>45-55 W</td><td>0.15 m²<br>(MOLA)</td><td>N/A</td><td>1600 nm</td><td>25 MHz<br>over 1 GHz<br>wide<br>spectral<br>interval</td><td>5188-<br>15564<br>3 s</td><td>5000</td><td>1730-5190;<br>raw data of<br>1 sample<br>per orbit<br>would<br>require<br>139000</td><td>$-70M</td><td>No</td></tr><tr><td>ATM</td><td>Sub-mm<br>sounder</td><td>Sub-mm<br>sounder</td><td>Mothership</td><td>0-100 km<br>temperature<br>(ind.<br>surface)</td><td>Horizontal<br>wind<br>velocity</td><td>Water<br>vapor<br>concentration</td><td></td><td>JPL</td><td>5<br>(Developed<br>under the<br>IRAD<br>program);<br>There is<br>only one<br>item<br>needing<br>testing;<br>could be<br>done with<br>$50K</td><td>N/A</td><td>N/A</td><td>3-6<br>months</td><td>$50K</td><td>2-antenna:<br>35 kg;<br>1-fixed-<br>antenna:<br>11.5 kg</td><td>2-antenna:<br>50 W (+20<br>for USO, if<br>needed);<br>1-fixed-<br>antenna:<br>15.6 W</td><td>2-antenna:<br>20x20x10<br>cm<br>2.30 cm<br>diam<br>antennas;<br>1-fixed-<br>antenna:<br>20x10x10<br>cm, 1.30<br>cm diam<br>antenna</td><td></td><td></td><td>-450 GHz</td><td>3 GHz<br>spectrometer<br>zoom to<br>300 MHz<br>channels;<br>tunable</td><td>10 kbps<br>compressed<br>(40<br>kbps raw)</td><td>Variable</td><td></td><td></td><td>2-antenna:<br>~$35M<br>(Discovery<br>mission<br>proposal);<br>1-antenna:<br>~$25M<br>(Delta from<br>Discovery<br>mission<br>proposal)</td><td>No</td></tr><tr><td>ATM</td><td>Thermal<br>IR<br>radiometer</td><td>Limb-nadir<br>radiometer</td><td>Mothership</td><td>Vertical<br>profile of<br>temperature</td><td>Vertical<br>profile of<br>dust<br>opacity</td><td>Vertical<br>profile of<br>water ice<br>opacity</td><td>Vertical<br>profile of<br>water<br>vapor<br>volume<br>mixing<br>ratio</td><td>JPL</td><td>9<br>(Equivalent<br>to MRO/MCS)</td><td>N/A</td><td>N/A</td><td>N/A</td><td>N/A</td><td>FOV 70<br>mrad,<br>IFOV<br>1.8 mrad</td><td>9 kg</td><td>18 W</td><td>Swept<br>volume:<br>420 mm<br>(cylindrical<br>diameter)<br>x 400 mm<br>(height)</td><td>12-42<br>micron<br>0.3-3<br>microns</td><td>9 channels</td><td>8<br>kbps/sample</td><td>2 s</td><td>4000</td><td>$-25M</td><td></td></tr><tr><td>ATM/DIU</td><td>Thermal<br>IR<br>radiometer</td><td>Mini-MCS<br>(limb-nadir)</td><td>SmallSats</td><td>Vertical<br>profile of<br>temperature</td><td>Vertical<br>profile of<br>dust<br>opacity</td><td>Vertical<br>profile of<br>water ice<br>opacity</td><td>Vertical<br>profile of<br>water<br>vapor<br>volume<br>mixing<br>ratio</td><td>JPL</td><td>6<br>(Heritage from MCS<br>subsystems,<br>PREFIRE)</td><td>N/A</td><td>N/A</td><td>N/A</td><td>N/A</td><td>FOV 70<br>mrad,<br>IFOV<br>1.8 mrad</td><td>3.5 kg</td><td>8 W</td><td>2U</td><td>12-42<br>micron, 0.3-<br>3 micron</td><td>9 channels</td><td>8<br>kbps/sample</td><td>2 s</td><td>4000</td><td>$-10M for<br>first unit,<br>~$5M for<br>follow-on<br>units</td><td></td></tr></tbody></table>
<table><caption>Figure 33. (Continued.)</caption><thead><tr><th>Investigation (VIS-NIR)</th><th>Name</th><th>Platform</th><th>Measurements (Up to 4; please link to physical parameters)</th><th>Supplier</th><th>TRL</th><th>Time to TRL5</th><th>$ to TRL5</th><th>Time TRL 5 to 6</th><th>$ TRL 5 to 6</th><th>FOV</th><th>Mass</th><th>Power</th><th>Volume</th><th>Accommodation/ Requirement</th><th>Wavelength/ Frequency/ Energy/ Field Range</th><th>Resolution/ Number of channels</th><th>Bit per Sample</th><th>Sample Rate</th><th>Threshold Data Rate (kbps)</th><th>Baseline Data Rate (kbps) average (bps)</th><th>Phase-A Average Cost ($FY20) Contributable?</th><th>Notes</th></tr></thead><tbody><tr><td rowspan="2">DIU</td><td>RGB or multispectral imager</td><td>GEOCI Imager/SmallSats</td><td>Weather context/Imagery-RGB (PAN-MIS)</td><td>S/C/S &amp; Space Advisory Earth Observation satellite</td><td>9 (Feas. on n-Sight-1)</td><td>N/A</td><td>N/A</td><td>N/A</td><td>N/A</td><td>500 g</td><td>&lt;3.5 W</td><td>58 mm x 97 mm x 96 mm (1U)</td><td>if at areostationary, it requires some scanning to cover full Mariner disk</td><td>Visible</td><td>Visible</td><td>450 KB-3 MB</td><td>5 frames/s (5x450 kb -5 frames/s per hour)</td><td>30 kbps</td><td>$100K</td><td></td><td></td><td></td></tr><tr><td>Radio/occultation with directional antenna</td><td>TX/RX radio and SmallSats</td><td>Mothership and Vertical profile of temperature pressure</td><td>Geopotential (geostroph (evars))</td><td>JPL</td><td>&gt;6 (based on the IRS ratio with modification s for SmallSats and USST for large orDiter)</td><td>N/A</td><td>N/A</td><td>N/A</td><td>N/A</td><td>10 cm x10 cm x 5 cm (IRIS)</td><td>10 cm x10 cm x 5 cm (IRIS)</td><td>Objective/ SX dual-bands, thresholded: X-band</td><td>Objective/ SX dual-bands, thresholded: X-band</td><td>16 (1 and Q, 8 bits each)</td><td>5 kHz</td><td>5 minutes 1 kHz</td><td>5000 images (5x450 kb -5 frames/s per hour)</td><td></td><td></td><td></td></tr><tr><td rowspan="2">DIU</td><td>UV/VIS-NIR</td><td>Mars Atmosphere, and Resource Investigation Camera (MAVIC)</td><td>Mothership/ SmallSats</td><td>Dustwater (ice) aerosol clouds</td><td>Water ice column opacity</td><td>Carbon ice column opacity</td><td>JHU APL</td><td>7 (accept for detector array (TRL 5))</td><td>N/A</td><td>N/A</td><td>TBD</td><td>10 cm x 75.5 x 14.4 x 12.2 x 10 x 3.5 in elevato n</td><td>0.97+2.42 2.1 W kg electronics/8.2W electronics</td><td>0.34-0.75 um, 1.1-1.6 um</td><td>6 channels between 0.34-0.75 um, 6 channels between 1.1-1.6 um</td><td>8.8 Gelsic/1.1 Gelsic/ downlink: d ~102 Kbps collected orbit average</td><td>8.8 Gelsic/1.1 Gelsic/ downlink: d ~127Kbps collected orbit average</td><td>8 kbps</td><td>$30M ROM</td><td></td><td></td><td></td></tr><tr><td>FUV/FUV spectrograph</td><td>IUVS</td><td>Mothership</td><td>Thermosp profiles of O heric thermosphere/temperature profiles</td><td>Composi/ on (CO2, O as primary target, NO as secondary gas)</td><td>LASP/S9 SLSWRI</td><td>N/A</td><td>N/A</td><td>N/A</td><td>N/A</td><td>28 W</td><td>27 kg</td><td>Limb (needs accurate imd tracking)</td><td>Limb viewing: 50-FUV:134-165km tangent 250 km tangent altitude</td><td>FUV: 1.5 nm, MUV: 2 nm</td><td>FUV: 10 Kb, MUV: 20 Kb</td><td>40 integrals for FUV + MUV + MUV every 3 minutes</td><td>5 kbps</td><td>8 kbps</td><td>10 kbps</td><td>$40M (without reserves)</td><td></td></tr><tr><td rowspan="2">THER</td><td>EUV/FUV EMUS spectrograph</td><td>ICON MIGHT/Mothership</td><td>Mothership or Areostationary/thermosphere/temperature profiles</td><td>Thermosp profiles of O heric thermosphere/temperature profiles</td><td>LASP/S9 SLSWRI</td><td>N/A</td><td>N/A</td><td>N/A</td><td>N/A</td><td>15 kg</td><td>15 W</td><td>Limb (needs accurate imd tracking)</td><td>Limb view: 45 and 557.7 nm and 1.27 unreach with 2 wavelengths, and 50 altitude elements</td><td>2 channels, 2 wavelengths, and 50 altitude elements</td><td>$1.28M</td><td>2 exposures per channel every 3 minutes</td><td>10 kbps</td><td>14 kbps</td><td>Orbit av</td><td></td><td></td><td></td></tr><tr><td>Interferometer</td><td></td><td>Horizontal Wind</td><td></td><td></td><td>NRL</td><td>9</td><td>N/A</td><td>N/A</td><td>9 months $3M</td><td>40 kg</td><td>13 W</td><td>Limb view: 15° to reach, 15° to exclude, 15° to exclude planet, pointing control to keep FUV away from lower atmosphere, sun etc.</td><td></td><td></td><td></td><td></td><td></td><td></td><td></td><td></td></tr></tbody></table>
<table><caption>Figure 33. (Continued.)</caption><thead><tr><th>Investigation</th><th>Description</th><th>Name</th><th>Platform</th><th>(Up to 4: please link to physical parameters)</th><th>Measurements</th><th>Supplier</th><th>TRL</th><th>Time to TRL5</th><th>$ to TRL5</th><th>Time TRL 5 to 6</th><th>$ TRL 5 to 6</th><th>FOV</th><th>Mass</th><th>Power</th><th>Volume</th><th>Accommodation/ Operational Requirement</th><th>Wavelength/ Frequency/ Energy/ Field Range</th><th>Resolution/ Number of channels</th><th>Bits Per Sample</th><th>Sample Rate</th><th>Threshold Data Rate (bps)</th><th>Baseline Data Rate (orbit-average bps)</th><th>Phase A-D Cost ($FY20)</th><th>Contributable?</th><th>Notes</th></tr></thead><tbody><tr><td>MAGN</td><td>Electric field and waves</td><td>Electric field antennas</td><td>Elliptical</td><td>Vector electric field power</td><td>Electric field wave power</td><td>SSL</td><td>9</td><td>N/A</td><td>N/A</td><td>N/A</td><td>N/A</td><td>N/A (must be spinner)</td><td>12 kg (6)</td><td>0.24 W</td><td>8-cm-diameter spheres</td><td>Spinning, electrostatically clean spacecraft</td><td>DC to 300 kHz</td><td>up to 8192</td><td>16</td><td>4 samples per second</td><td>500</td><td>1000</td><td>~$2M</td><td></td><td>Reflight of THEMIS EFI</td></tr><tr><td>MAGN</td><td>Magnetic waves</td><td>Search coil magnetometer</td><td>Elliptical</td><td>Magnetic field wave power</td><td></td><td>CETP, France Univ. Iowa</td><td>9</td><td>N/A</td><td>N/A</td><td>N/A</td><td>N/A</td><td>omnidirectional</td><td>1.8 kg (1 boom)</td><td>0.08 W</td><td>3 orthogonal 18-cm-long rods on a 1-m boom</td><td>Magnetic cleanliness (dynamic)</td><td>0.1 Hz to 4 kHz</td><td>up to 8192</td><td>16</td><td>4 samples per second</td><td>200</td><td>800</td><td>~$3M (incl. boom)</td><td></td><td>Reflight of THEMIS SCM</td></tr><tr><td>SPA</td><td>Extreme ultraviolet monitor</td><td>EUVM</td><td>Long</td><td>Solar EUV flux in three band passes</td><td></td><td>LASP</td><td>9</td><td>N/A</td><td>N/A</td><td>N/A</td><td>N/A</td><td>Sun pointed to within 3°</td><td>1.4 kg</td><td>0.09 W (operational)</td><td>16 x 13 x 9 cm</td><td>Sun pointing</td><td>10-20 nm, 17-22 nm, 121.6 nm</td><td>3 bands</td><td>48</td><td>1 sample per second</td><td>20</td><td>200</td><td>$1.39M</td><td></td><td>Reflight of MAVEN EUVM requires external A/D signal processing electronics</td></tr><tr><td>SPA</td><td>Extreme ultraviolet monitor</td><td>EUVM v2</td><td>Long</td><td>Solar EUV flux in three band passes</td><td></td><td>LASP</td><td>4</td><td>1 month</td><td>$10K</td><td>3 months</td><td>$40K</td><td>Sun pointed to within 3°</td><td>0.75 kg</td><td>0.73 W (operational)</td><td>10 x 10 x 7 cm</td><td>Sun pointing</td><td>10-20 nm, 17-22 nm, 121.6 nm</td><td>3 bands</td><td>48</td><td>1 sample per second</td><td>20</td><td>200</td><td>$1.66M</td><td></td><td>Updated MAVEN EUVM design with internal A/D signal processing electronics</td></tr><tr><td>SPA</td><td>Extreme ultraviolet monitor</td><td>EUVM v3</td><td>Long</td><td>Solar EUV flux in three band passes</td><td></td><td>LASP</td><td>4</td><td>3 months</td><td>$60K</td><td>3 months</td><td>$40K</td><td>Sun pointed to within 3°</td><td>1.1 kg</td><td>0.73 W (operational)</td><td>15 x 10 x 7 cm</td><td>Sun pointing</td><td>10-20 nm, 17-22 nm, 121.6 nm</td><td>3 bands</td><td>48</td><td>1 sample per second</td><td>20</td><td>200</td><td>$1.85M</td><td></td><td>Updated MAVEN EUVM design that mitigates soft x-ray contamination to signal resulting in a factor of two improvement in accuracy</td></tr><tr><td>SPA</td><td>Ion electroscanning Analyzer</td><td>Solar Wind</td><td>L1, high elliptical</td><td>Ion moments (density, temperature, velocity) of functions solar wind and magnetosphere H, with some discrimination of He using energy</td><td>Ion velocity distribution</td><td>SSL, SwRI</td><td>9</td><td>N/A</td><td>N/A</td><td>N/A</td><td>N/A</td><td>360 x 90° (3-axis stabilization)</td><td>1.8 kg</td><td>1 W</td><td>20 x 16 x 16 cm</td><td>N/A</td><td></td><td></td><td></td><td>500</td><td>1000</td><td>~$3M</td><td></td><td></td></tr><tr><td>SPA</td><td>Solid state solid state telescope</td><td>Solid state solid state telescope</td><td>L1, high elliptical</td><td>Energetic ion flux in 4 look directions</td><td>Energetic electron flux in 4 look directions</td><td>SSL</td><td>9</td><td>N/A</td><td>N/A</td><td>N/A</td><td>N/A</td><td></td><td>1.1 kg</td><td>3.2 W</td><td></td><td></td><td></td><td></td><td></td><td>20</td><td>100</td><td>~$0.8M</td><td></td><td></td></tr></tbody></table>

A.10. MOSAIC Concept Study Report Cover Art

Figure 34 shows the original cover and cover art from the MOSAIC Final Report submitted to NASA and the National Academies of Science, Engineering, and Medicine in 2020 August.
<figure><img src="image_45.png" /><figcaption>**Figure 34.** Cover page from the MOSAIC Planetary Mission Concept Study Report (437 pages) submitted to NASA and the National Academy of Sciences, Engineering, and Medicine on 2020 August 7.</figcaption></figure>
ORCID iDs

Robert J. Lillis https://orcid.org/0000-0003-0578-517X

David Mitchell https://orcid.org/0000-0001-9154-7236

Luca Montabone https://orcid.org/0000-0003-4998-914X

Nicholas Heavens https://orcid.org/0000-0001-7654-503X

Scott Guzewich https://orcid.org/0000-0003-1149-7385

Scott England https://orcid.org/0000-0001-5336-0040

Paul Withers https://orcid.org/0000-0003-3084-4581

Mike Chaffin https://orcid.org/0000-0002-1939-4797

Shannon Curry https://orcid.org/0000-0002-7463-9419

Chi Ao https://orcid.org/0000-0001-6171-0872

Steven Matousek https://orcid.org/0000-0001-9712-0380

Ryan Woolley https://orcid.org/0000-0002-5179-5953

Isaac Smith https://orcid.org/0000-0002-4331-913X

Gordon R. Osinski https://orcid.org/0000-0002-1832-5925

Leslie Tamppari https://orcid.org/0000-0001-5124-6375

Michael Mischna https://orcid.org/0000-0002-8022-5319

David Kass https://orcid.org/0000-0002-7154-2566

Michael Wolff https://orcid.org/0000-0002-1127-8329

Aymeric Spiga https://orcid.org/0000-0002-6776-6268

François Forget https://orcid.org/0000-0002-3262-4366

Justin Deighan https://orcid.org/0000-0003-3667-902X

Amanda Brecht https://orcid.org/0000-0002-9018-6528

Stephen Bougher https://orcid.org/0000-0002-4178-2729

Christopher M. Fowler https://orcid.org/0000-0003-3431-0739

David Andrews https://orcid.org/0000-0002-7933-0322

Kerstin Peter https://orcid.org/0000-0001-1353-0110

Mark Lester https://orcid.org/0000-0001-7353-559

Beatriz Sánchez-Cano https://orcid.org/0000-0003-0277-3253

Janet Luhmann https://orcid.org/0000-0003-0626-9353

François Leblanc https://orcid.org/0000-0002-5548-3519

Jasper Halekas https://orcid.org/0000-0001-5258-6128

David Brain https://orcid.org/0000-0001-8932-368X

Xiaohua Fang https://orcid.org/0000-0002-6584-2837

Jared Espley https://orcid.org/0000-0002-6371-9683

Hermann Opgenooth https://orcid.org/0000-0001-7573-5165

Oleg Vaisberg https://orcid.org/0000-0002-6590-644X

David Hinson https://orcid.org/0000-0002-1620-4011

Sami Asmar https://orcid.org/0000-0002-9912-645X

Joshua Vander Hook https://orcid.org/0000-0002-0493-237X

Ozgur Karatekin https://orcid.org/0000-0003-0153-7291

Aroh Barjatya https://orcid.org/0000-0002-1939-6143

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