Planetary Instrumentation - Remote · Head, ESA Solar System Missions Division and Coordinator, ESA Solar System Missions ESA-ESTEC/SRE-SM, Postbus 299 2200 AG Noordwijk (The Netherlands)

PLANETARY INSTRUMENTATION

REMOTE SENSING

Luigi Colangeli Head, ESA Solar System Missions Division

and Coordinator, ESA Solar System Missions

ESA-ESTEC/SRE-SM, Postbus 299 2200 AG Noordwijk (The Netherlands) Tel: +31 - 71 565 3573 Fax: +31 - 71 565 4697 [email protected]

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Outline

1. WHAT => Targets to observe

a. Terrestrial planets

b. Small bodies

2. WHY => Scientific objectives

a. Atmospheres => Composition, physical status

b. Surface => Geo-chemistry/geology

c. Sub-surface => Geology

3. HOW => Methodologies

a. Imaging

b. Spectroscopy

c. Radar sounding

d. Others...

4. (Some) results from flying missions

a. Mars

b. Venus

c. Mercury

5. (Some) expectations from future missions

a. Mars

b. Mercury

c. Comets – asteroids

6. Conclusions? 2

Outline


a. Terrestrial planets

b. Small bodies


a. Atmospheres => Composition, physical status

b. Surface => Geo-chemistry/geology

c. Sub-surface => Geology


a. Imaging

b. Spectroscopy

c. Radar sounding

d. Others...

4. (Some) results from flying missions

5. (Some) expectations from future missions

6. Conclusions?

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WHAT

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1. WHAT => Targets to observe The ESA fleet in the Solar System

Proba-2 Carries solar observation and space weather experiments

The ESA Science Programme has consistently allowed European scientists to score key “firsts”

Europe today has leadership in a number of fields in Space Science

ESA aims at maintaining this leadership

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1. WHAT OBJECTIVES for 2013-2015

-2013: Launch of GAIA To create the largest and most precise three dimensional chart of our Galaxy by providing unprecedented positional and radial velocity measurements for about one billion stars in our Galaxy and throughout the Local Group

-2014: Launch of LISA Pathfinder LISA Pathfinder is to demonstrate the key technologies to be used in future missions for gravitational wave detection

-2015: Launch of BepiColombo

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1. WHAT COSMIC VISION (2015-2025) Step 1

Proposal selection for assessment phase in October 2007 3 M missions concepts: Euclid, PLATO, Solar Orbiter 3 L mission concepts: X-ray astronomy, Jupiter system science,

gravitational wave observatory 1 MoO being considered: European participation to SPICA

Selection of Solar Orbiter as M1 and Euclid as M2 in 2011. Selection of Juice as L1 in 2012.

Euclid Solar Orbiter

JUICE

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1. WHAT COSMIC VISION (2015-2025) Step 2

Second “Call for Missions” issued in 2010 Only M mission proposals solicited ECHO, MarcoPolo-R, LOFT, STE-QUEST selected for assessment

with PLATO (possibly) retained from previous round. Selection planned for 2013.

LOFT EChO

MarcoPolo-R

STE-QUEST

PLATO

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1. Terrestrial planets

a. Mars and Mars Express

http://sci.esa.int/science-e/www/area/index.cfm?fareaid=9

b. Mercury and BepiColombo


c. Venus and Venus Express


2. Small bodies

• Comets, Giotto and Rosetta



• Asteroids and MarcoPolo-R


MarcoPolo-Science Requirements Document

http://sci.esa.int/science-e/www/object/index.cfm?fobjectid=49579

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Mercury (not true-color), Venus (stripped of its atmosphere), Earth (true-color), and Mars (stripped of its atmosphere), and dwarf planet Ceres (true-color). Sizes to scale






















1. WHAT => Targets to observe Terrestrial planets Mars and Mars Express


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1. WHAT => Targets to observe Terrestrial planets Venus and Venus Express


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1. WHAT => Targets to observe Terrestrial planets Venus and Venus Express

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1. WHAT => Targets to observe Terrestrial planets Mercury and BepiColombo

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1. WHAT => Targets to observe Small Bodies Comets and Giotto

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1. WHAT => Targets to observe Small Bodies Comets and Giotto

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1. WHAT => Targets to observe Small Bodies Comets and Rosetta

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1. WHAT => Targets to observe Small Bodies Comets and Rosetta

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1. WHAT => Targets to observe Small Bodies Comets and Rosetta... and Asteroids

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1. WHAT => Targets to observe Small Bodies Asteroids... and MarcoPolo-R (study)

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WHY

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2. WHY COSMIC VISION “Grand Themes”

1. What are the conditions for planetary formation and the emergence of life ?

2. How does the Solar System work?

3. What are the physical fundamental laws of the Universe?

4. How did the Universe originate and what is it made of?

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2. WHY => Targets to observe

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2. WHY => Targets to observe

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http://fr.wikipedia.org/wiki/Fichier:Solar_sys.jpg


1. Mars and Mars Express

• Background Science


• ESA SP-1291: Mars Express - The Scientific Investigations


• ESA SP-1240: Mars Express - The Scientific Payload


• Workshop Mars III, Les Houches, 2010


2. Mercury and BepiColombo



• BepiColombo-Comprehensive exploration of Mercury: Mission overview and science goals

Benkhoff, J., et al. (2010) - Planetary and Space Science Vol. 58

3. Venus and Venus Express



4. Giant Planets

• see other dedicated Lectures

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2. WHY => Scientific objectives Geology

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Nicolas MANGOLD - Workshop Mars III, Les Houches, 2010 http://sci.esa.int/science-e/www/object/index.cfm?fobjectid=46845




2. WHY => Scientific objectives Mars and Earth

• Mars is geologically inactive, but meteorologically very active because of winds and dust.

• Mars surface is characterized by impact craters, extinct volcanoes, valleys, deserts and two polar caps made of carbon dioxide (CO2) and water ice (H2O) and dust, whose extension depends on seasonal condensation/sublimation processes.

• The Martian seasonal and daily climatic conditions depend on the planet orbit and rotation.

• Because of the orbital eccentricity, summer lasts more in the northern hemisphere than in the southern hemisphere.

MARS EARTH

Mean Day 24.66 h = 1 sol 24.00 h

Orbit Semimajor Axis 228106 km 150106 km

Orbit Eccentricity 0.0934 0.0167

Inclination to Ecliptic 1.85° 0°

Longitude of the Ascending

Node 49.6° 348.7°

Argument of the Perihelion 286.5° 114.2°

Orbital Period 687 days 365.2 days

Distance Mars-Earth 55.7106-401.3106 km

Average Gravity 3.73 m/s2 9.81 m/s2

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2 WHY => Scientific objectives Geology and water

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2 WHY => Scientific objectives Geology, water and chronology

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2 WHY => Scientific objectives Geology, water and chronology

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2 WHY => Scientific objectives Cratering

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Stephanie C. Werner - Workshop Mars III, Les Houches, 2010 http://sci.esa.int/science-e/www/object/index.cfm?fobjectid=46845

Neukum et al. 1975




2. WHY => Scientific objectives Martian Atmosphere

• Thin, dry, cold, dominated by carbon dioxide (CO2)

• Dependence on season, time location and altitude

• Dust influence on planetary climate

• Environmental conditions close to the water triple point (T = 273 K, p = 610 Pa)

Atmospheric Parameters

Composition (volume fraction)

95.32% CO2, 2.70% N2, 1.60% Ar40,

0.13% O2, 0.07% CO, 0.03% H2O, 0.013%

NO, 5.3 ppm Ar36+38, 2.5 ppm Ne, 0.3 ppm

Kr, 0.13 ppm CH2O, 0.08 ppm Xe, 0.04-

0.02 ppm O3, 10.5 ppb CH4

Mean Molecular Mass 43.49 g/mole

Gas Constant 192 J/kg/K

Ratio between Heat Capacities 1.33

Specific heat capacity at constant pressure 860 J/kg/K

Mean Free Molecular Path 4.74·10-6 m

Pressure 6.1 mbar (average) - 0.2-12 mbar (range)

Temperature 215 K (average) - 140-310 K (range)

Density 0.010-0.020 kg/m3

Viscosity (T = 293.15 K) 1.4673·10-5 Pa·s

Wind Speed 0-30 m/s

Atmospheric visible optical depth 0.1-10

Atmospheric dust mass density 1-100·103 kg/m3

Atmospheric dust particle number density 1-100 cm-3

Atmospheric dust grain size 0.010-10 μm

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2. WHY => Scientific objectives Martian Atmosphere

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Michael A. Mischna - Workshop Mars III, Les Houches, 2010 http://sci.esa.int/science-e/www/object/index.cfm?fobjectid=46845




2. WHY => Scientific objectives Martian Climate

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François Forget - Workshop Mars III, Les Houches, 2010 http://sci.esa.int/science-e/www/object/index.cfm?fobjectid=46845




2. WHY => Scientific objectives Martian Climate

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François Forget - Workshop Mars III, Les Houches, 2010 http://sci.esa.int/science-e/www/object/index.cfm?fobjectid=46845




2. WHY => Scientific objectives Climate

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2. WHY => Scientific objectives Venus atmosphere

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• Venus is totally covered by thick clouds, which are practically featureless in visible spectral range. • The main cloud deck is in the range 48-70 km altitude. • Three layers with different properties: upper (roughly 60-70 km), middle (50-60 km) and low (48-50 km). • The total optical depth of the clouds changes in the range 20 – 40. • The main compounds of the clouds is sulfuric acid with concentration 75 - 85 % at all latitudes • The abundance of the H2SO4 vapor is in saturation at 50 km at low and high latitudes indicating to sulfuric

acid condensation in low clouds. • Other compounds: S, Cl, P and Fe • The sulfuric acid is produced by photochemical way from H2O and SO2 near the cloud top. • Particle sizes: submicron, 1-2 μm, 3.5 μm. • One of the mysteries of Venus is ‘unknown’ UV absorber in the upper clouds (in the 0.32 – 0.45 μm

spectral range, at λ< 0.32 μm the UV absorption are explained by SO2 and SO).

2. WHY => Scientific objectives Mercury interior… and exosphere

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2. WHY => Scientific objectives Small bodies and Solar system formation

1. Mars and Mars Express

2. Mercury and BepiColombo

3. Venus and Venus Express

4. Small bodies

• Comets and Rosetta

ROSETTA - ESA's Mission to the Origin of the Solar System

Schulz, R.; Alexander, C.; Boehnhardt, H.; Glaßmeier, K.H. (Eds.) 1st Edition., 2009, - ISBN 978-0-387-77517-3 – Springer

• Asteroids and MarcoPolo-R

MarcoPolo-R: proposal to ESA in response to call for medium-size missions

http://sci.esa.int/science-e/www/object/index.cfm?fobjectid=49380#

• Asteroids and Rosetta

Rosetta Fly-by at Asteroid (2867) Steins

PSS – Volume 58, Issue 9 (2010)

Rosetta Fly-by at Asteroid (21) Lutetia

Edited by Rita Schulz and Claudia Alexander

PSS - Volume 66, Issue 1, Pages 1-212 (June 2012)

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2. WHY => Scientific objectives Small bodies and Solar system formation

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HOW

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• Imaging (examples)

HRSC-MEX / VMC-VEX / OSIRIS-ROS

• Spectroscopy (examples)

OMEGA-MEX / VIRTIS-VEX / PFS-VEX / MERTIS-BC / SIMBIO-SYS-BC / VIRTIS-ROS

• Radar sounding

MARSIS-MEX / CONSERT-ROS / RSI-ROS

• Others...

SPICAM-ASPERA-MEX / SPICAV-VEX / BELA-BC (Laser Altimeter) / MIXS-BC (X-ray) / PHEBUS-BC (UV) /

ALICE-ROS (UV)

Ref.s:

MEX


ESA SP-1291: Mars Express - The Scientific Investigations


ESA SP-1240: Mars Express - The Scientific Payload


VEX

http://sci.esa.int/science-e/www/object/index.cfm?fobjectid=33964&fbodylongid=1441

BC


BepiColombo-Comprehensive exploration of Mercury: Mission overview and science goals


Rosetta


ROSETTA - ESA's Mission to the Origin of the Solar System

Schulz, R.; Alexander, C.; Boehnhardt, H.; Glaßmeier, K.H. (Eds.) - 2009, - ISBN 978-0-387-77517-3 – Springer

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3. HOW => Methodologies Imaging – HRSC MEX


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G. Neukum et al. ESA SP-1240 (2004) ESA SP-1291 (2009)


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3. HOW => Methodologies Imaging – OSIRIS Rosetta

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H.U. Keller et al. In “ROSETTA” p. 315 (2009)

3. HOW => Methodologies Mapping Spectrometer – Omega - MEX

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J.-P. Bibring et al. ESA SP-1240 (2004)

OMEGA is a mapping spectrometer, with coaligned channels working in the 0.38-1.05 μm visible and near-IR range (VNIR channel) and in the 0.93-5.1 μm short wavelength IR range (SWIR channel).

3. HOW => Methodologies Mapping Spectrometer – Omega - MEX

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J.-P. Bibring et al. ESA SP-1240 (2004)

Telescope and its fore-optics, a beam splitter and two spectrometers, each with its detector array actively cooled. The telescope is a Cassegrain of 200 mm focal length, an f/4 aperture, leading to a 1.2 mrad (4.1 arcmin) IFOV and a 15 arcmin free FOV (including the positioning tolerances). The distance between the primary and secondary mirrors is 51 mm; between the secondary mirror and the image plane is 82 mm. In front of the telescope, a fore-optics system has the primary goal of providing a cross-track scanning of the IFOV. It includes two mirrors, moving and fixed. The total scanning angle is ±4.4° (FOV = 128

IFOV), and is adjusted to the OMEGA viewing direction. The control of the scanning mechanism is performed by a dedicated FPGA-based electronic sub-system. Focused by the telescope on an entrance slit, through a shutter, the beam is first collimated, then separated, by a dichroic filter with its cut-off wavelength at 2.7 μm towards two spectrometers, operating at 0.93-2.73 μm and 2.55-5.1 μm.

3. HOW => Methodologies Imaging + Spectrometry SIMBIO-SYS BepiC

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E. Flamini et al. PSS 58, 125 (2010)


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3. HOW => Methodologies Spectroscopy – PFS - MEX

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V. Formisano et al. ESA SP-1240 (2004)

3. HOW => Methodologies Spectroscopy – MERTIS - BepiC

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H. Hiesinger et al. PSS 58, 144 (2010)

3. HOW => Methodologies Spectroscopy – SPICAM - MEX

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J—L. Bertaux et al. ESA SP-1240 (2004) ESA SP-1291 (2009)

3. HOW => Methodologies Spectroscopy – SPICAM - MEX

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J—L. Bertaux et al. ESA SP-1240 (2004) ESA SP-1291 (2009)

3. HOW => Methodologies Spectroscopy – ALICE - Rosetta

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J. Parker et al. In “ROSETTA” p. 167 (2009)

3. HOW => Methodologies Spectroscopy – PHEBUS - BepiC

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E. Chassefière et al. PSS 58, 201 (2010)

3. HOW => Methodologies Spectroscopy – MIRO - Rosetta

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S. Gulkis et al. In “ROSETTA” p. 291 (2009)

3. HOW => Methodologies Spectroscopy – MIXS – BepiC

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G.W. Fraser et al. PSS 58, 79 (2010)

3. HOW => Methodologies Laser Altimetry – BELA – BepiColombo

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A laser altimeter is an instrument that measures the distance from an orbiting spacecraft to the surface of the planet/asteroid that the spacecraft is orbiting. The distance is determined by measuring the complete round trip time of a laser pulse from the instrument to the planet's/asteroid's surface and back to the instrument. The distance to the object can be determined by multiplying the round-trip pulse time by the speed of light and dividing by two. With a well-known attitude and position of the instrument/spacecraft the location on the surface illuminated by the laser pulse can be determined. The series of the laser spot, or footprint, locations provides a profile of the surface.

K. Gunderson et al. PSS 58, 309 (2010)

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Laser Altimetry MGS - MOLA

When this voltage exceeds a noise threshold, counts are latched by the time interval unit (TIU). Four separate channels filter the voltage output in parallel to detect pulses spread out by the roughness of terrain or clouds, increasing the likelihood of detection, and providing some information about surface or cloud characteristics. The noise threshold is set by software and, based on statistics from the past 14 seconds worth of returns, minimizes the probability of false hits while maximizing the probability of detection. While the MOLA-2 instrument is functionally the same as that carried on Mars Observer, we updated the electronics to improve reliability and in the course of doing so improved overall instrument performance. Time-delay lines enable the measurement of return pulses with two extra bits of precision, that will allow measurement of changes in surface elevation due to polar ice over the course of a Martian year. The received pulse energy will measure the infrared reflectivity of the surface. In addition, measurements of the returned laser pulse width are providing fascinating information about the 100-meter-scale roughness of the Martian surface.

By firing short (~8-ns) pulses of infrared light at the surface and measuring the time for the reflected laser energy to return, dT=Tr-To, MOLA measures the range from the Mars Global Surveyor spacecraft to the tops of Mars' mountains and the depths of its valleys. A telescope focuses the light scattered by terrain or clouds onto a silicon avalanche photodiode detector. A portion of the output laser energy that is diverted to the detector, starts a precision clock counter. The detector outputs a voltage proportional to the rate of returning photons that have been backscattered from Mars' surface or atmosphere.

3. HOW => Methodologies Radar sounding – MARSIS - MEX

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G.Picardi et al. ESA SP-1240 (2004)

3. HOW => Methodologies Radar sounding – MARSIS - MEX

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G.Picardi et al. ESA SP-1240 (2004)

3. HOW => Methodologies Radar sounding – SHARAD - MRO

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• The Shallow Subsurface Radar (SHARAD) seeks liquid or frozen water in the first few hundreds of feet (up to 1 kilometer) of Mars' crust.

• SHARAD probes the subsurface using radar waves using a 15-25 MHz frequency band in order to get the desired high depth resolution.

• The radar wave return, which is captured by the SHARAD antenna, is sensitive to changes in the electrical reflection characteristics of the rock, sand, and any water present in the surface and subsurface. Water, like high-density rock, is very conducting, and will have a very strong radar return. Changes in the reflection characteristics of the subsurface, such as layers deposited by geological processes in the ancient history of Mars, will also be visible

• The instrument has a horizontal resolution of between 0.3 and 3 kilometers (between 2/10 of a mile and almost 2 miles) horizontally and 15 meters (about 50 feet) vertically. Subsurface features will have to be of the order of these dimensions for them to be observable.

R. Croci, et al. Proceedings of IEEE Vol. 99, Issue 5, 794 (2011)

4. (Some) results

• Mars

• ESA SP-1291: Mars Express - The Scientific Investigations


• Workshop Mars III, Les Houches, 2010


• Venus

• Advances in Venus Science

Gierasch, P., et al., Icarus 217 (2012)

This issue of Icarus presents papers on the planet Venus based principally on presentations at two

international conferences during the summer of 2010

• Mercury

Messenger http://www.nasa.gov/mission_pages/messenger/spacecraft/index.html

Barnouin, O.S. et al.; The morphology of craters on Mercury: Results from MESSENGER flybys,

Icarus 219, 414-427 (2012)

• Asteroids

3 Papers - Science 334 (2011)

The Surface Composition and Temperature of Asteroid 21 Lutetia As Observed by Rosetta/VIRTIS - Science, Volume 334, 492- (2011).

Asteroid 21 Lutetia: Low Mass, High Density - Science, Volume 334, Issue 6055, pp. 491- (2011).

Images of Asteroid 21 Lutetia: A Remnant Planetesimal from the Early Solar System - Science, Volume 334, Issue 6055, pp. 487- (2011).

Rosetta Fly-by at Asteroid (21) Lutetia

Edited by Rita Schulz and Claudia Alexander

PSS - Volume 66, Issue 1, Pages 1-212 (June 2012)

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http://www.nasa.gov/mission_pages/messenger/spacecraft/index.html

4. Results – Mars Express Images

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ESA’s Report to the 39th COSPAR Meeting ESA SP-1223 June 2012 http://sci.esa.int/cospar_report

http://sci.esa.int/cospar_report

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Global topographic map of Mars with major surface features labeled. (Credit: MOLA Science Team) http://mola.gsfc.nasa.gov/ The Mars Orbiter Laser Altimeter, or MOLA, is an instrument on the Mars Global Surveyor (MGS), a spacecraft that was launched on November 7, 1996. The mission of MGS was to orbit Mars, and map it over the course of approximately 3 years, which it did sucessfully, completing 4 1/2 years of mapping. Determining the height of surface features on Mars is important to mapping it. To this end, MGS carried a laser altimeter on board. This instrument, MOLA, collected altimetry data until June 30, 2001. MOLA has been operating, and continues to operate, as a radiometer since June 2001

4. Results – MGS – MOLA Laser Altimetry

http://mola.gsfc.nasa.gov/

4. Results – Mars Express North Pole MARSIS investigation

• MARSIS has conducted a successful north polar night-side campaign.

• This new MARSIS campaign provided many examples of deep detections that were not possible before, and many others that are inaccessible to SHARAD.

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200 km


• Base of basal unit is visible across entire polar plateau. Allows better constraints on thickness and volume.

• Preliminary estimate of real dielectric constant of basal unit at Rupes Tenuis is ~4. Implies lithic component up to ~50%.

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200 km

Olympia Undae Rupes Tenuis plateau

Basal unit

NP Layered Deposit


• Base of basal unit is visible across entire polar plateau. Allows better constraints on thickness and volume.

• Preliminary estimate of real dielectric constant of basal unit at Rupes Tenuis is ~4. Implies lithic component up to ~50%.

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4. Results – Mars Express Atmosphere and water cycle


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4. Results – Venus Express A complex atmosphere


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Data from Venus Express + ground based mm-wave and IR observations Extended photochemical model of the middle atmosphere: it uses more than 150 chemical reactions and produces vertical profiles of 44 atmospheric gases. Profiles of a few key species are shown at the left. The drop in SO2 concentration at around 64 km altitude is due to the formation of H2SO4 droplets in the upper cloud layer at this level. Krasnopolsky, Icarus, doi: 10.1016/j.icarus.2011.11.012., 2011

Altitude

[km

] 4. Venus Express Photochemical model of the middle atmosphere

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VIRTIS data @5μm, sampling altitude ~65km

4. Results – Venus Express A complex atmosphere - Polar vortex dynamics

4. Results – Venus Express A planet geologically still active?

Recent Hot-Spot Volcanism on Venus from VIRTIS Emissivity Data S.E. Smrekar, et al., Science 10.1126/science.1186785 2010

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4. Results – NASA Messenger Crater counting

The morphology of craters on Mercury: Results from MESSENGER flybys O.S. Barnouin, Icarus 219 (2012) 414–427

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5. Expectations from future missions

• Jupiter System

The JUpiter ICy moons Explorer (JUICE)


JUICE assessment study report (Yellow Book)


Announcement of Opportunity for the JUICE Payload (PIP)


• Mars

• The ExoMars Program and the Trace Gas Orbiter

http://exploration.esa.int/science-e/www/object/index.cfm?fobjectid=46048


• Mercury

• BepiColombo-Comprehensive exploration of Mercury: Mission overview and science goals


• Comets

• ROSETTA - ESA's Mission to the Origin of the Solar System

Schulz, R.; Alexander, C.; Boehnhardt, H.; Glaßmeier, K.H. (Eds.)

2009, - ISBN 978-0-387-77517-3 – Springer

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5. The JUICE Scientific Objectives and Model Payload

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JUICE assessment study report (Yellow Book) http://sci.esa.int/science-e/www/object/index.cfm?fobjectid=49837













5. The JUICE Scientific Objectives and Model Payload

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5. The (optional) European Robotic Exploration Program

1. Focused on the robotic exploration

2. Optional program

a. Not all Member States participate

b. Individual missions are specifically

funded by Member States

a. Based on international cooperation

with Russia

3. Two missions currently approved (“ExoMars”)

a. Trace gas orbiter (TGO) and Entry,

Descent, and Landing Demonstrator

Module (EDM) (2016)

b. Exo-biology rover with Pasteur P/L

(2018)

4. Long-term goal is Mars Sample Return

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5. ExoMars - The EDL Demonstrator Module

A technology demonstrator for landing payloads on Mars

A platform to conduct environmental measurements, particularly during the dust storm season

EDM PAYLOAD

Integrated payload mass: 5 kg;

Lifetime: 4–8 sols;

Measurements:

• Descent science;

• P, T, wind speed and

direction;

• Optical depth;

• Atmospheric charging;

• Descent camera.

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5. ExoMars – The Trace Gas Orbiter

Instrument Science

ACS-NIR Echelle-AOTF spectrometer

(nadir + limb + occultation)

Water, photochemistry

ACS-MIR Echelle spectrometer

(occultation)

Methane and minor constituents

ACS-TIR Fourier spectrometer (nadir +

occultation)

Aerosols; Minor constituents;

Atmospheric structure

NOMAD Echelle spectrometer

(nadir + occultation)

Trace gas inventory;

Mapping of sources/sinks

FREND Collimated neutron detector Mapping of subsurface water

CASSIS High-resolution, stereo camera Mapping of sources;

Landing site selection

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5. ExoMars – The 2018 Mission

TECHNOLOGY OBJECTIVES

Surface mobility with a rover (having several kilometres range);

Access to the subsurface to acquire samples (with a drill, down to 2-m depth);

Sample acquisition, preparation, distribution, and analysis. SCIENTIFIC OBJECTIVES

To search for signs of past and present life on Mars;

To characterise the water/subsurface environment as a

function of depth in the shallow subsurface.

To characterise the surface and subsurface environment.

Nominal mission: 220 sols

Nominal science: 6 Experiment

Cycles +

2 Vertical Surveys

EC length: 16–20 sols

Rover mass: 300-kg class

Mobility range: Several km

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5. The EREP perspectives PHOOTPRINT & INSPIRE

Missions with a strong scientific and technology content:

• Phobos sample return;

• Mars network.

INSPIRE

PHOOTPRINT

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5. The MarcoPolo-R study

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Conclusions

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Documents

Planetary Instrumentation - Remote · Head, ESA Solar System Missions Division and Coordinator, ESA Solar System Missions ESA-ESTEC/SRE-SM, Postbus 299 2200 AG Noordwijk (The Netherlands)