| MISSION_DESCRIPTION |
Mission Overview
================
The Mars Exploration Rover (MER) mission consisted of two
spacecraft, MER-2 hardware which included the Spirit rover,
and MER-1 hardware, which included the Opportunity rover
[CRISPETAL2003, GARVINETAL2003]. Spirit was launched June 10,
2003, on a Delta II 7925 launch vehicle. Opportunity followed
3 weeks later, launching July 7, 2003 on a Delta II 7925 Heavy
vehicle. Each spacecraft followed a Type I trajectory from
Earth to Mars, with Spirit landing in Gusev Crater on January 4,
2004 UTC and Opportunity landing in Meridiani Planum on January
25, 2004 UTC. The Earth-Mars range was 170.2 million km at the
time of Spirit's landing and 198.7 million km at the time of
Opportunity's landing.
The spacecraft design was based on the Mars Pathfinder configuration
for cruise and entry, descent, and landing. Each MER spacecraft
contained a rover which was carried to Mars inside a lander. The
lander was packed inside a heatshield and backshell attached to a
cruise stage. At Mars arrival, the cruise stage was jettisoned from
the entry capsule. The entry capsule entered the Martian atmosphere
directly from the Earth-Mars transfer trajectory at a velocity of
5.4 km/s. The lander velocity was reduced from this high entry
speed by the application of aerodynamic braking by a parachute and
aeroshell, propulsive deceleration using small solid rocket motors,
and inflated airbags to reduce the remaining vertical and horizontal
velocity components at surface impact (involving significant
bouncing). Key engineering status information was collected and
returned in near real time to the extent possible during entry and
descent. In addition, all engineering data obtained during the
critical entry, descent, and landing phase were recorded for later
playback during the first week of landed operations.
The two landing sites were selected because of their science
potential and safety characteristics [GOLOMBEKETAL2003]. The two
sites exhibited different types of evidence suggesting past
liquid-water activity. For Gusev, the evidence was primarily
geomorphologic (possible crater lake) and for Meridiani, it was
primarily mineralogic (gray coarse-grained hematite). The
navigation team determined the location of the landing sites in
inertial space, by fitting direct-to-Earth (DTE) two-way X-band
Doppler and two passes of UHF two-way Doppler between each rover
and Mars Odyssey. Translated to the MOLA IAU 2000 frame
[SEIDELMANNETAL2002] these inertial positions are 14.571892
degrees S latitude and 175.47848 degrees E longitude for Spirit,
and 1.948282 degrees S latitude, 354.47417 degrees E longitude for
Opportunity. The location of the landing sites, with respect to
surface features in maps produced in the MOLA IAU 2000 cartographic
reference frame, are 14.5692 degrees S latitude, 175.4729 degrees
E longitude for Spirit and 1.9462 degrees S latitude, 354.4734
degrees E longitude for Opportunity.
Each of the identical rovers was equipped with a science payload
consisting of two remote sensing instruments (Pancam and the
Miniature Thermal Emission Spectrometer) at the top of a rotatable
mast to survey the surrounding terrain, a robotic arm capable of
placing three instruments (Alpha Particle X-Ray Spectrometer,
Moessbauer Spectrometer, and Microscopic Imager) and a rock
abrasion tool (RAT) on selected rock and soil samples, and
several on-board magnets and calibration targets. Engineering
sensors and other components on the rovers useful for science
investigations included stereo navigation cameras (Navcam) on the
top of the mast, stereo hazard cameras in front and rear under the
solar panels (Hazcams), wheel motors, the wheels themselves
for digging, gyros, accelerometers, and reference solar cells.
Mission operations allowed commanding of the rover each martian day,
or sol, on the basis of the previous sol's data. Over the 90-sol
prime mission lifetime and several mission extensions, the
rovers carried out field geology investigations, exploration,
and atmospheric characterization.
Many extended missions followed the 90-sol primary mission.
Brief summaries of the activities in each mission phase are
described below. The mission has been described in many papers,
including a pre-landing set of papers in the December 2003 special
section of Journal of Geophysical Research - Planets, and post-
landing special issues of Science in 2004 for Spirit rover (volume
305, number 5685) and Opportunity rover (volume 306, number 5702).
Additional special issues were published in 2005 for Earth and
Planetary Science Letters (volume 240, number 1) and Nature (volume
436, number 7047). In 2006, the science team published several
papers on the Spirit rover in Journal of Geophysical Research -
Planets (volume 111, number E02). Another JGR special issue was
published in 2008 (volume 113, number E06), and a 2010 update is
in press as of this writing.
Mission Phases
==============
DEVELOPMENT
-----------
The development phase began with the start of mission funding in
May, 2000. During this phase, the science and technology
requirements were developed and analyzed, and the spacecraft and
mission were designed. The instruments and spacecraft were
fabricated and tested before delivery to Kennedy Space Center.
The design of the spacecraft trajectory and mission operations
were also determined during this period.
Spacecraft Id : MER2
Target Name : MARS
Mission Phase Start Time : 2000-05-08
Mission Phase Stop Time : 2003-06-10
Spacecraft Operations Type : LANDER
Spacecraft Id : MER1
Target Name : MARS
Mission Phase Start Time : 2000-05-08
Mission Phase Stop Time : 2003-07-07
Spacecraft Operations Type : LANDER
LAUNCH
------
The launch phase for each vehicle began at the final countdown
through spacecraft separation from the upper stage. Spirit
(MER-2 hardware) was launched June 10, 2003, at 1759 UTC
(1359 EDT) from launch complex 17A at Cape Canaveral Air Force
Station, Florida. The launch azimuth was 93 degrees. The boost
portion of the launch vehicle trajectory took approximately 10
minutes, and was followed by a short coast phase in a parking
orbit for approximately 15 minutes. After third stage burnout,
the upper stage despun the stack using a yo-yo despin system.
Separation of the third stage occurred approximately 36 minutes
after launch.
Opportunity (MER-1 hardware) was launched July 8, 2003, at
0318 UTC (July 7, 2003, 2318 EDT) from launch complex 17B at
Cape Canaveral Air Force Station, Florida. The launch azimuth
was 99 degrees. The boost portion of the launch vehicle
trajectory took approximately 9 minutes, and was followed by
a long coast phase of approximately 60 minutes in a parking
orbit. After third stage burnout, the upper stage despun the
stack using a yo-yo despin system. Separation of the third
stage occurred approximately 83 minutes after launch.
Spacecraft Id : MER2
Target Name : MARS
Mission Phase Start Time : 2003-06-10
Mission Phase Stop Time : 2003-06-10
Spacecraft Operations Type : LANDER
Spacecraft Id : MER1
Target Name : MARS
Mission Phase Start Time : 2003-07-07
Mission Phase Stop Time : 2003-07-07
Spacecraft Operations Type : LANDER
CRUISE
------
The cruise phase for each spacecraft began soon after separation
from the third stage and ended 45 days before entry into the Mars
atmosphere. The duration of cruise phase was 162 days for Spirit
and 156 days for Opportunity. The major activities during this
phase included: checkout and maintenance of the spacecraft in its
flight configuration, monitoring, characterization and calibration
of the spacecraft and payload systems, software parameter updates,
attitude correction turns, navigation activities for determining
and correcting the vehicle's flight path, and preparation for EDL
and surface operations, including EDL X-band communication tests.
No science investigations were conducted during cruise, except for
instrument health checkouts.
Spacecraft Id : MER2
Target Name : MARS
Mission Phase Start Time : 2003-06-10
Mission Phase Stop Time : 2003-11-19
Spacecraft Operations Type : LANDER
Spacecraft Id : MER1
Target Name : MARS
Mission Phase Start Time : 2003-07-07
Mission Phase Stop Time : 2003-12-10
Spacecraft Operations Type : LANDER
APPROACH
--------
The approach phase was dedicated to the activities necessary to
ensure a successful Entry, Descent, and Landing for each
spacecraft, beginning 45 days before entry into the Martian
atmosphere and ending at the atmospheric entry interface point
3522.2 km from the center of Mars. The main activities during
this phase were: acquisition and processing of navigation data to
support development of the final trajectory correction maneuvers
and activities leading up to the final turn to the entry attitude
70 minutes before entry and separation from the cruise stage 15
minutes before entry.
Spacecraft Id : MER2
Target Name : MARS
Mission Phase Start Time : 2003-11-19
Mission Phase Stop Time : 2004-01-03
Spacecraft Operations Type : LANDER
Spacecraft Id : MER1
Target Name : MARS
Mission Phase Start Time : 2003-12-10
Mission Phase Stop Time : 2004-01-24
Spacecraft Operations Type : LANDER
ENTRY, DESCENT, AND LANDING
---------------------------
The entry, descent, and landing (EDL) phase for each spacecraft
started six minutes prior to landing. Approximately 20 seconds
after parachute deploy, the heatshield separated from each
spacecraft, followed approximately 10 seconds later by lander
separation on a bridle. This was followed by radar acquisition
of the ground, acquisition of three images by the DIMES (Descent
Image Motion Estimation System), airbag inflation, RAD/TIRS
rocket firing, bridle cut (6.5 m above the surface for Spirit,
8.5 m for Opportunity), and landing. The landing (first impact)
occurred at 04:26 UTC on January 4, 2004 for Spirit (1425 Mars
local solar time, solar longitude Ls = 327.66) and 04:55 UTC on
January 25, 2004 for Opportunity (1323 Mars local solar time,
solar longitude Ls = 339.10). Spirit bounced 28 times
before coming to rest on the base petal of the lander.
After retraction of the airbags and opening of the petals, the
base petal was oriented at a tilt of 2 degrees. Opportunity
bounced 26 times before coming to rest on a side petal (+Y petal)
of the lander. After retraction of the airbags and opening of
the petals, the base petal was oriented at a tilt of 5 degrees,
with the base petal down on the surface. The entry, descent,
and landing phase for each spacecraft was completed once the
rover solar panels were opened and the lander was on the
surface of Mars in a thermally stable, positive energy balance,
in a commandable configuration.
Spacecraft Id : MER2
Target Name : MARS
Mission Phase Start Time : 2004-01-04
Mission Phase Stop Time : 2004-01-04
Spacecraft Operations Type : LANDER
Spacecraft Id : MER1
Target Name : MARS
Mission Phase Start Time : 2004-01-25
Mission Phase Stop Time : 2004-01-25
Spacecraft Operations Type : LANDER
POST-LANDING THROUGH EGRESS
---------------------------
The post-landing through egress phase of each mission began after
the lander petals and rover solar panels had been opened. This
phase ended 12 Martian sols (each sol being 24.66 hours) after
landing for Spirit, and 7 Martian sols for Opportunity, when
each rover drove off of the lander directly onto the surface of
Mars. Data confirming the egress event for Spirit were received
at 01:53 PST January 15, 2004 (09:53, January 15, UTC). Engineers
received confirmation that Opportunity's six wheels successfully
rolled off the lander and onto martian soil at 03:01 PST,
January 31, 2004 (11:01 January 31, UTC).
Spacecraft Id : MER2
Target Name : MARS
Mission Phase Start Time : 2004-01-04
Mission Phase Stop Time : 2004-01-15
Spacecraft Operations Type : LANDER
Spacecraft Id : MER1
Target Name : MARS
Mission Phase Start Time : 2004-01-25
Mission Phase Stop Time : 2004-01-31
Spacecraft Operations Type : LANDER
PRIMARY MISSION
---------------
Spirit and Opportunity's primary missions each lasted for 90
Martian sols from time of landing. During this phase and the
extended mission phase, a wealth of science and engineering
information was collected from the rover and instrument payload.
During Spirit's mission, the rover traveled in a primarily
northeast direction from its landing site to the 210-meter
diameter crater informally called 'Bonneville,' and then headed
southeast towards the hills nicknamed 'Columbia Hills,' covering
a distance travelled of 635 meters. During that time, Spirit
acquired 23810 Pancam images, 2886 Navcam images, 3980 Hazcam
images, and 1872 Microscopic Imager images (these image counts
include full frames, subsampled frames, downsampled frames, and
thumbnails). During Opportunity's prime mission, the rover
spent the first two months investigating the surrounding area
where it landed, which was a 20-meter diameter crater nicknamed
'Eagle.' After the study of 'Eagle,' it headed east towards the
130-meter diameter crater nicknamed 'Endurance,' covering a
distance travelled of 772 meters. During the prime mission,
Opportunity acquired 22503 Pancam images, 2343 Navcam images,
4421 Hazcam images, and 1395 Microscopic Imager images.
Spacecraft Id : MER2
Target Name : MARS
Mission Phase Start Time : 2004-01-11
Mission Phase Stop Time : 2004-04-06
Spacecraft Operations Type : LANDER
Spacecraft Id : MER1
Target Name : MARS
Mission Phase Start Time : 2004-02-01
Mission Phase Stop Time : 2004-04-27
Spacecraft Operations Type : LANDER
EXTENDED MISSION 1
------------------
The rovers' extended missions have not yet ended. Objectives
for each of the extended missions are described in the next
section.
Spacecraft Id : MER2
Target Name : MARS
Mission Phase Start Time : 2004-04-06
Sol Start Time: 91
Mission Phase Stop Time : 2004-09-30
Sol Stop Time: 264
Spacecraft Operations Type : LANDER
Spacecraft Id : MER1
Target Name : MARS
Mission Phase Start Time : 2004-04-27
Sol Start Time: 91
Mission Phase Stop Time : 2004-09-30
Sol Stop Time: 243
Spacecraft Operations Type : LANDER
EXTENDED MISSION 2
------------------
Spacecraft Id : MER2
Target Name : MARS
Mission Phase Start Time : 2004-10-01
Sol Start Time: 265
Mission Phase Stop Time : 2005-03-31
Sol Stop Time: 441
Spacecraft Operations Type : LANDER
Spacecraft Id : MER1
Target Name : MARS
Mission Phase Start Time : 2004-10-01
Sol Start Time: 244
Mission Phase Stop Time : 2005-03-31
Sol Stop Time: 420
Spacecraft Operations Type : LANDER
EXTENDED MISSION 3
------------------
Spacecraft Id : MER2
Target Name : MARS
Mission Phase Start Time : 2005-04-01
Sol Start Time: 442
Mission Phase Stop Time : 2006-09-30
Sol Stop Time: 974
Spacecraft Operations Type : LANDER
Spacecraft Id : MER1
Target Name : MARS
Mission Phase Start Time : 2005-04-01
Sol Start Time: 421
Mission Phase Stop Time : 2006-09-30
Sol Stop Time: 954
Spacecraft Operations Type : LANDER
EXTENDED MISSION 4
------------------
Spacecraft Id : MER2
Target Name : MARS
Mission Phase Start Time : 2006-10-01
Sol Start Time: 975
Mission Phase Stop Time : 2007-09-28
Sol Stop Time: 1328
Spacecraft Operations Type : LANDER
Spacecraft Id : MER1
Target Name : MARS
Mission Phase Start Time : 2006-10-01
Sol Start Time: 955
Mission Phase Stop Time : 2007-09-28
Sol Stop Time: 1307
Spacecraft Operations Type : LANDER
EXTENDED MISSION 5
------------------
Spacecraft Id : MER2
Target Name : MARS
Mission Phase Start Time : 2007-09-29
Sol Start Time: 1329
Mission Phase Stop Time : 2008-09-28
Sol Stop Time: 1684
Spacecraft Operations Type : LANDER
Spacecraft Id : MER1
Target Name : MARS
Mission Phase Start Time : 2007-09-29
Sol Start Time: 1308
Mission Phase Stop Time : 2008-09-28
Sol Stop Time: 1663
Spacecraft Operations Type : LANDER
EXTENDED MISSION 6
------------------
Spacecraft Id : MER2
Target Name : MARS
Mission Phase Start Time : 2008-09-29
Sol Start Time: 1685
Mission Phase Stop Time : 2010-09-26
Sol Stop Time: 2393
Spacecraft Operations Type : LANDER
Spacecraft Id : MER1
Target Name : MARS
Mission Phase Start Time : 2008-09-29
Sol Start Time: 1664
Mission Phase Stop Time : 2010-09-26
Sol Stop Time: 2372
Spacecraft Operations Type : LANDER
EXTENDED MISSION 7
------------------
Spacecraft Id : MER2
Target Name : MARS
Mission Phase Start Time : 2010-09-27
Sol Start Time: 2394
Mission Phase Stop Time : 2012-09-30
Sol Stop Time: 3108
Spacecraft Operations Type : LANDER
Spacecraft Id : MER1
Target Name : MARS
Mission Phase Start Time : 2010-09-27
Sol Start Time: 2373
Mission Phase Stop Time : 2012-09-30
Sol Stop Time: 3087
Spacecraft Operations Type : LANDER
|
| MISSION_OBJECTIVES_SUMMARY |
Mission Objectives Overview
===========================
The MER mission had a set of science and technology objectives.
The science was closely aligned with the Mars Exploration Program
objective of determining the degree to which Mars provided
conditions necessary for formation and preservation of prebiotic
compounds and whether life started and evolved. This objective can
be broadly stated as defining habitability of Mars and providing
an understanding of roles of tectonic and climatic processes in
possibly providing the conditions that led to life. The presence of
water and its interaction with crustal materials is of fundamental
importance. Thus, three of the MER objectives focused on searching
for evidence of water in the past: (1) to investigate landing sites
which have a high probability of containing evidence of the action
of liquid water, (2) to search for and characterize a diversity of
rocks and soils that hold clues to past water activity, and (3) to
extract clues related to the environmental conditions when liquid
water was present and assess whether those environments were
conducive to life.
The other MER science objectives were related to the Mars
Exploration Program objective of determining the nature and sequence
of the various geologic processes that have created and modified the
Martian crust and surface: (4) to determine the spatial distribution
and composition of minerals, rocks and soils surrounding the landing
sites, (5) to determine the nature of local surface geologic
processes from surface morphology and chemistry, (6) to calibrate
and validate orbital remote sensing data and assess the amount and
scale of heterogeneity at each landing site, (7) for iron-containing
minerals, to identify and quantify relative amounts of specific
mineral types that contain H2O or OH, or are indicators of formation
by an aqueous process, and (8) to characterize the mineral
assemblages and textures of different types of rocks and soils and
put them in geologic context. These are basic field geology
objectives that can be carried out at any landing site, but will
provide the basis for addressing the first three objectives related
to past water and thus habitability.
Three additional objectives for MER were technology related: (9) to
demonstrate long-range traverse capabilities by mobile science
platforms to validate long-lived, long-distance rover technologies,
(10) to demonstrate complex science operations through the
simultaneous use of multiple science-focused mobile laboratories,
and (11) to validate the standards, protocols and capabilities of
NASA-provided and internationally-provided orbiter-based Mars
communications infrastructure. These objectives provided experience,
lessons-learned, and technology feed-forward to enable improved Mars
science missions in the future. While not part of the formal
mission objectives, the rovers' remote sensing instruments were also
used to make scientific observations of the martian atmosphere.
The objectives of the First Extended Mission were as follows:
1) Extend investigation of the water history in Gusev Crater by
traversing to the Columbia Hills
2) Investigate the geologic context of the Opportunity outcrop by
traversing to other targets (Endurance crater and the etched
region south of the landing site) and conducting in-situ
investigations of exposed outcrops
3) Continue atmospheric measurements at both sites to encompass a
longer portion of the Martian seasonal cycle
4) Calibrate and validate orbital remote sensing data for additional
types of soil and rock deposits
5) Conduct long range traverses (>1 km) to extend Mars surface
exploration and demonstrate relevant mobility technologies
6) Demonstrate long term, sustainable operations of two mobile
science platforms on remote planetary surfaces
7) Characterize solar array performance over long durations of dust
depositions at two different landing sites
The objectives of the Second Extended Mission were as follows:
1) Continue search for evidence of the role of water in the
geological history of Gusev Crater
2) Extend the geological exploration of the water-lain sedimentary
and other outcrops in Meridian Plains into the regions south of
Endurance Crater
3) Continue atmospheric measurements at both sites
4) Calibrate and validate orbital remote sensing data for additional
types of soil and rock deposits
5) Characterize solar array performance over long durations of dust
depositions at two different landing sites
6) Demonstrate long term, sustainable operations of two mobile
science platforms on remote planetary surfaces, with much of the
science team participating from their remote home institutions
The objectives of the Third Extended Mission were as follows:
1) Continue to search for evidence of the role of water in the
geological history of Gusev Crater by exploring a large variety
of outcrops found within the Columbia Hills
2) Extend the geological exploration of water-lain sedimentary and
other outcrops in Meridian Planum into the regions south of
Endurance Crater, including the expansive Etched Terrain and,
if the Etched Terrain can be crossed, Victoria Crater
3) Continue atmospheric measurements at both sites to encompass a
full martian year
4) Calibrate and validate orbital remote sensing data for
additional types of soil and rock deposits
5) Characterize solar array performance over long durations of
dust depositions at two different landing sites
6) Demonstrate continued long term, sustainable operations of
two mobile science platforms on remote planetary surfaces,
with most of the science team participating from their remote
home institutions
7) Demonstrate specific improvements in rover capability
The objectives of the Fourth Extended Mission were as follows:
1) Continue to search for evidence of the role of water in the
geological history of Gusev Crater by exploring a large
variety of outcrops and soils found within the Columbia Hills,
including unexplored regions south of the Inner Basin.
2) Extend the geological exploration of water-lain sedimentary
and other rock outcrops in Meridiani Planum to Victoria Crater.
Search for lake-bed sedimentary deposits that have not been
transported by wind or water, which would provide key geologic
insight into the processes involved in the formation of the
evaporate-rich rocks at Eagle, Endurance, and Erebus Craters.
3) Determine the nature of local surface geologic processes at
new locations in Gusev Crater and Meridiani Planum.
4) Continue atmospheric measurements at both sites to characterize
interannual variations across a second martian year.
5) Calibrate and validate orbital remote sensing data for
additional types of soil and rock deposits.
6) Characterize solar array performance over long durations of
dust depositions at two different landing sites.
7) Continue to demonstrate long term, sustainable operations of
two mobile science platforms on remote planetary surfaces,
with most of the science team participating from their remote
home institutions.
The objectives of the Fifth Extended Mission were as follows:
1) Continue to search for evidence of the role of water in the
geological history of Gusev Crater by exploring a large
variety of outcrops and soils found within the Columbia Hills,
including the target-rich Inner Basin.
2) Extend the geological exploration of water-lain sedimentary
and other rock outcrops in Cape Victory to Victoria Crater.
Search for lake-bed sedimentary deposits that have not been
transported by wind or water, which would provide key geologic
insight into the processes involved in the formation of the
evaporate-rich rocks at Eagle, Endurance, and Erebus Craters.
3) Determine the nature of local surface geologic processes at
new locations in Gusev Crater and Victoria Crater.
4) Continue atmospheric measurements at both sites to characterize
interannual variations across a second martian year.
5) Calibrate and validate orbital remote sensing data for
additional types of soil and rock deposits.
6) Characterize solar array performance over long durations of
dust depositions at two different landing sites.
7) Continue to demonstrate long term, sustainable operations of
two mobile science platforms on remote planetary surfaces,
with most of the science team participating from their remote
home institutions
The objectives of the Sixth Extended Mission were as follows:
1) Continue to search for evidence of the role of water in the
geological history of Gusev Crater by exploring a large
variety of outcrops and soils found within the Columbia Hills,
including the target-rich Inner Basin.
2) Extend the geological exploration of water-lain sedimentary
and other rock outcrops in Victoria Crater to Endeavor Crater.
Search for lake-bed sedimentary deposits that have not been
transported by wind or water, which would provide key geologic
insight into the processes involved in the formation of the
evaporate-rich rocks at Eagle, Endurance, and Erebus Craters.
3) Determine the nature of local surface geologic processes at
new locations in Gusev Crater and en route to Endeavor Crater.
4) Continue atmospheric measurements at both sites to characterize
interannual variations across a second martian year.
5) Calibrate and validate orbital remote sensing data for
additional types of soil and rock deposits.
6) Characterize solar array performance over long durations of
dust depositions at two different landing sites.
7) Continue to demonstrate long term, sustainable operations of
two mobile science platforms on remote planetary surfaces,
with most of the science team participating from their remote
home institutions
The objectives of the Seventh Extended Mission were as follows:
1) Use Spirit to measure two-way X-band Doppler shift over a period
of months to years to constrain the moment of inertia of Mars.
2) Use Spirit to monitor surface-atmospheric interactions within the
Inner Basin with regular Pancam albedo panoramas to track eolian
dynamics on a terrain-level scale and repeated Microscopic Imager
imaging of specific soil sites to track eolian dynamics on a soil
grain scale.
3) Use Spirit to continue the geologic and geochemical investigations
of sulfate deposits in Scamander crater.
4) Use Opportunity to advance toward Endeavor crater with the objective
of investigating the phyllosilicate-bearing materials present in
Endeavor's rim.
5) Use Opportunity to continue sampling cobbles along the route to
Endeavor, with particular emphasis on finding and characterizing
rocks that may be representative of the ones that were altered to
form the Meridiani sediments.
6) Use Opportunity to continue a comprehensive search for 'wet'
sedimentary facies preserved in the bedrock at Meridiani.
7) Continue atmospheric measurements at both sites to extend the
characterization of interannual variations for a fourth martian year
8) Calibrate and validate orbital remote sensing data for both sites
for additional types of soil and rock deposits.
9) Characterize solar array performance over long durations of dust
deposition at two different landing sites.
10) Continue to demonstrate long-term, sustainable operations of scienc
platforms on remote planetary surfaces with a distributed team
participating from their remote locations, and dynamically model ro
mobility both post drive and, in a predictive sense, predrive.
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