MONITORING MARS' ATMOSPHERIC DYNAMICS: FROM AN AREOSTATIONARY SMALLSAT CONCEPT TO A "MULTISAT" CONCEPT - ICUBESAT
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Monitoring Mars’ Atmospheric Dynamics:
From an Areostationary SmallSat Concept to a “MultiSat” Concept
L. Montabone 1
B. Cantor 2, M. Capderou 3, L. Feruglio 4, F. Forget 3,
N. G. Heavens 1, R. J. Lillis 5, M. D. Smith 6, F. Topputo 7,
M. VanWoerkom 8, M. J. Wolff 1
1 Space Science Institute (USA)
2 Malin Space Science Systems (USA)
3 Laboratoire Météorologie Dynamique (France)
4 AIKO S.r.l. (Italy)
5 University of California, Berkeley (USA)
6 NASA Goddard Space Flight Center (USA)
7 Polytechnic University of Milan (Italy)
8 ExoTerra Resource LLC (USA) Mars Aerosol Tracker (MAT): A concept study funded by NASA
Planetary Science Deep Space SmallSat Studies (PSDS3)
1
Ma rs G l o b a l S u r ve yo r Ma rs O r b i te r C a m e ra C re d i t : N A SA /J P L /2 MS S S
Dust events
Dust devils MRO / H I R I S E
Local and regional MG S / MO C
and Viking
dust storms
May 2 0 1 8 July 2018
MRO / MA RC I
Global dust events
3
C re d i t : N A SA /J P L / MS S S
Water ice clouds
MG S / MO C Hubble
Credit:
NASA/JPL/MSSS Aphelion cloud belt Polar hood 4
A regional dust storm from areostationary vs polar orbit
View from about 17,000 km above the equator
Polar orbiter Areostationary orbiter
Mars Global Surveyor
Data from:
Thermal Emission Spectrometer 5
Montabone et al., Icarus, 2015
Gridded Infrared Column Dust Optical Depth
Mars Aerosol Tracker (MAT): Mission goal and objectives
GOAL
Understand the regional Martian weather and its effects
OBJECTIVE 1 OBJECTIVE 2
Understand the processes controlling the dynamics Study the impact of the regional aerosol variability on
of dust and water ice aerosols at the regional scale. the derivation of surface physical properties.
We plan to place and operate MAT in areostationary orbit in order to:
➢ Monitor at high sampling rate a large, fixed portion of the planet where dust storms and
water ice clouds are likely to occur, using visible and infrared wavelengths;
➢ Observe the temporal evolution of dust storms and water ice clouds in the monitored area
throughout the diurnal cycle;
➢ Derive surface properties accounting for the aerosol contribution (e.g. thermal inertia and
albedo when large dust storms occur). 6
Mission Architecture
We analyzed 3 mission scenarios
Case 1 Case 2
Rideshare on an orbiter mission to Rideshare on any mission to Mars,
Mars, release after Mars capture, autonomous Mars capture,
descent into areostationary orbit. descent into areostationary orbit.
35 kg spacecraft wet mass 45 kg spacecraft wet mass
Case 3 (current baseline)
Being released in GTO,
autonomous navigation to Mars,
autonomous Mars capture,
descent into areostationary orbit.
100 kg spacecraft wet mass 7
Mission Architecture
We analyzed 3 mission scenarios
Case 2
Rideshare on any mission to Mars,
autonomous Mars capture,
descent into areostationary orbit.
Case 3 (current baseline)
Being released in GTO,
autonomous navigation to Mars,
autonomous Mars capture,
descent into areostationary orbit.
100 kg spacecraft wet mass 8
The 100 kg SmallSat with Solar Electric Propulsion
ESPA ring
“Halo” 5th Generation Thruster Prototype (Xenon gas) 1100 W Solar Array IRIS transponder + KaPDA 9antenna
Payload
➢ One visible camera: Off-the-shelf camera
( ECAM-C50 from MSSS):
→ Fixed-focus, narrow-angle lens;
→ 2592 x 1944 pixels;
→ 29° x 22° FOV (full disk and limb);
→ 4 km resolution.
➢ Two thermal infrared camera developed by MSSS:
→ Fixed-focus, narrow-angle lens;
→ 640 x 480 pixels;
→ Same field of view as visible camera; 16 km resolution;
→ Filter wheel for selecting 6 spectral ranges;
→ Detectors responsive in the range 7.9 - 16 μm.
➢ Digital Video Recorder: Off-the-shelf from MSSS (ECAM-DVR4) Malin Space Science Systems, Inc
Proprietary Information
→ Buffer Size: 32 GB Non-Volatile / 128 MB Volatile 10Products
Weighting functions for the center of
three spectral ranges on one side of
the CO2 15 μm absorption band. 11From one to three Areostationary SmallSats…
Vertical perspectives
(equivalent to
areostationary views
from about 17,000 km
above the equator)
From monitoring
regional weather
to monitoring
planetary-scale
weather
Equirectangular
projection
12…to a “MultiSat” concept
Areostationary SmallSats Polar-orbit CubeSats
Weather monitoring, ground telecom Atmospheric profiling
Mothership
Sub-surface/surface ice, aerosols,
winds, telecom relay
Elliptical-orbit SmallSats Spacecraft images are only
Long-orbit SmallSat
Plasma monitoring Solar wind and EUV monitoring
for illustrative purpose 13Thanks for your attention !
lmontabone@spacescience.org
14Back up slide
15First optimal launch opportunity
2019 2020 2021 2022 2023 2024 2025 2026 2027 2028 2029
Start End Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4
Phase A (Concept
7/1/2019and Technology
9/30/2019Development)
1
Phase B (Preliminary
10/1/2019 Design
6/30/2020
and Technology Completion)
2
Phase C (Final
7/1/2020
Design and12/31/2021
Fabrication) 3 4
Phase D (System
1/1/2022
Assembly,
8/31/2023
Integration & Test, Launch) 5 6 7
Phase E (Operations)
9/1/2023 12/31/2027 Cruise 8 9
Phase F (Closeout)
1/1/2028 6/30/2028 10 11
Notes on milestones
System Requirements Review (SRR) 1
Launch window:
Start of science ops:
Preliminary Design Review (PDR) 2 July/August 2023
Critical Design Review (CDR) 3 February 2026
System Integration Review (SIR) 4
Operational Readiness Review (ORR) 5 (MY 38 LS~230°)
Mission Readiness Review (MRR) 6 End of science ops:
Launch and Early Orbit Phase (LEOP)
Initial Science Operations (ISO)
7
8
January 2028
Decomissioning Review (DR) 9 (MY 39 LS~230°)
Disposal Readiness Review (DRR) 10
End of Mission (EOM) 11
Mars-Earth Distance
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