MPCS and the MARCO POLO Mission - H. Boehnhardt, G. Cremonese, L.M. Lara and the MPCS Study Team - CDTI
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MPCS and the MARCO POLO Mission
H. Boehnhardt, G. Cremonese, L.M. Lara
and the MPCS Study Team
Science Mission Goal of MarcoPolo
:
:
To return a sample from a near-Earth asteroid belonging
to a primitive class to Earth
sample ~ several 10 grams of surface material
Key questions of the mission to be addressed by laboratory
analysis of the sample and supported by orbiter and in-situ
experiments
Do NEAs of primitive classes contain
pre-solar material yet unknown in
meteoritic samples?
What are the physical properties and
evolution of the building blocks of
terrestrial planets?
What are the nature and
the origin of the organics
in primitive asteroids
and how can they shed
light on the origin of
molecules necessary for
life?
What were the processes occurring in
the primitive Solar System and
accompanying planet formation?
Scientific Objectives of the MarcoPolo Mission
:
A. Characterize the chemical and physical environments in the early solar nebula
B. Define the processes affecting the gas and the dust in the solar nebula
C. Determine the timescales of solar nebula processes
D. Determine the interstellar grain inventory
E. Determine the stellar environment in which the grains formed
F. Define the interstellar processes that created and formed the grains
G. Determine the diversity and complexity of organic species in a primitive asteroid
H. Understand the origin of organic species
I. Provide insight into the role of organics in life formation
J. Determine the global physical properties of a NEA
K. Determine the physical processes and theirchronology that shaped the surface structure
L. Characterize the chemical processes that shaped the NEA composition (e.g. volatiles, water)
M. Link the obtained characterization to meteorites and Interstellar Dust Particles (IDPs) and
provide ground truth to the astronomical database
MarcoPolo Overview
• Landing and surface sampling by orbiter is the prime goal
• Sample return and lab experiments on Earth are key for
science success
• Orbit and in-situ science before and after landing
– to enable identification and selection of scientifically most rewarding
landing sites
– to put sampling site into scientific context
– to perform science that is not possible to be performed with the sample
alone
Object ID Prelim. Designation Taxonomic spectral Estimated diameter Rotation period
class (km) (h)
162173 1999 JU3 Cg 0.92 7.7
162998 2001 SK162 T 1.52 68
65679 1989 UQ C 0.76 7.73
2001 SG286 D 0.35 Tbd
ESA Defined Mission Scenario
Target: 1999 JU3 Backup DSM 2 & 3
( launch )
Launch from Kourou, direct escape: Dec.
2020 Arrival:
Vinf ~ 3.15-3.3 km/s, Dec = 0o Dec. 2019 Feb. 2022
DSM 1
6 year mission, 17 months at asteroid
X-band
Single spacecraft + return capsule
Launch:
ROM budgets: Dec. 2018
• ~ 1440 kg launch mass capability
• Power ~ 500 W Re-entry:
• Instrument total mass: ~ 25 kg Dec. 2024
∆V (incl. margins):
Departure:
• Total in/out transfer < ~ 1500 m/s Jul. 2023
DSM 4
• Near-asteroid phase < ~ 50-100 m/s
Re-entry velocity ~ 11.9 km.s-1
European Industry System Studies
Astrium Ltd - Astrium GmbH/SAS/ST, Deimos, DLR, Selex Galileo
OHB - Aerosekur, GMV, Qinetiq, SENER
TAS-I - NGC, Selex Galileo, TAS-F
Design iterations and consolidation were performed
Mass margins comfortably sit within ESA requirements at this stage
Courtesy of Astrium Ltd Courtesy of OHB Courtesy of Thales Alenia Space
MarcoPolo Baseline Payload
• Baseline payload is capable of fulfilling the science requirements of the mission
Apart from the sampling equipment:
• Orbiter:
• Considerable scientific interest to fly:
• a lander & touch-down instruments
MPCS Instrument Concept
• MPCS = visible imaging system covering all needs of the
science mission to this respect
• 4 instrument units: NAC, WAC, CUC, CSU
WAC NAC
+ CSU
CUC electronic boxMPCS Instrument Concept
• 3 independent cameras
– WAC in orbit: shape, surrounding of asteroid, context for NAC
(f/6.5 dioptric system, 16mm aperture, 19.5”/px, fixed focus: ~2km –
∞, 1filter)
– NAC in orbit: shape, terrain, composition (3/8 filters), landing site
(f/8 3 mirror axis optics, 82mm aperture, 3.1”/px, variable focus:
150m – 2.5km – ∞, 3mm/px @ 200m, ≥8 filters)
– CUC@surface: sampling area constitution, grains & layering,
composition
(f/16 dioptric system, 12mm aperture, 10.3”/px, variable focus:
~10cm surface depth from 1m distance, 50µm/px @ 1m; filters TBD,
study contract with Kayser-Threde company)
• 1 common support unit CSU = PCU + CDPU
– PCU = power control unit
– CDPU = command and data processing unit
– both units (PCU, CDPU) as main and redundant
– operational interface between MPCS units and to S/CMPCS Study
• Study performed by European science & engineering
institute consortium between Jan. to Aug. 2009
– Submitted to ESA and part of MarcoPolo Mission documents
(Yellow Book released on Dec. 1, 2009)
• Study responsibilities
– WAC+NAC optomechanics: Univ. Padova (G. Cremonese, S.
Debei)
– CUC optomechanics: DLR Berlin-Adlershof (H. Michaelis)
– CDPU: IDA Braunschweig (H. Michalik)
– PCU: IAA Granada (L. M. Lara, J.M. Castro)
– Thermal aspects: UPM (I. Perez-Grande)
– Detector system, system engineering, calibration, study lead: MPS
Katlenburg-Lindau (H. Boehnhardt, H. Perplies, G. Tomasch)
• Performed without DLR funding
– but now DLR funded industry study contract for CUCMarcoPolo – Next Steps (hopefully) • 1 Dec. 2009: Mission Yellow Book presentation (followed by review) • mid Feb. 2010: Down-selection of CV mission (3-4 out of 6) • spring 2010: 2nd mission study phase (industry) • spring 2010: AO for scientific instruments • summer 2010: instrument selection • early 2012: final selection of CV missions for implementation • mid 2012: start mission/instrument implementation phase • mid/end 2013: PDR • mid/end 2015: CDR • mid 2018: flight acceptance (for launch in 2019)
MPS Tasks for MPCS - A Possible Scenario
• MPS responsibilities
– PIship & science lead
– detector system for all three cameras
– system engineering (TBD)
– system integration
– calibration
– data pipeline (TBD)
• MPS manpower (TBD)
Function Total work MPS work DLR funded work
power power power
PIship + science + pipeline 4 1 S + 1PD 1 E + 1PD
Management 1 0 1E
Detector system 4 1E + 1T 1E + 1T
System eng. + calibration 2(3) 1E (+ 1T) 1E
Total work power 11(11) 5(6) 6You can also read
