PDS_VERSION_ID = PDS3
LABEL_REVISION_NOTE = "
2002-10-21 JV: INITIAL DRAFT
2002-10-22 JJZ: MISSION_PHASE_INFORMATION OBJECT ADDED
2004-09-23 KW: Partly updated. MISSION_PHASE_INFORMATION
removed.
2005-09-19 KW: Added INSTRUMENT_HOST_ID RL.
2005-12-09 AC: two MISSION_HOST, one for each inst_host
updated MISSION_DESC,
added MISSION_TARGET objects,
changed MISSION_STOP_DATE to NULL
added References
2006-01-12 AC: removed special characters
2006-01-23 AC: removed double quotes within description
2007-01-26 MB: update to 70 char line length
2008-02-05 MB: TBD updates
2008-05-27 MB: TBD updates
2009-11-24 MB: REF (GLASSMEIER), STEINS
2010-01-18 MB: Non ascii characters
2010-01-20 MB: GULKIS ref
2010-02-10 IR: GLASSMEIER REF 2007B + added
2010-02-24 MB: EAR3 updated
2010-03-25 MB: PC12 addition
2010-08-25 MB: REF updates.
2011-02-18 MB: REF updates (KISSSEL)
2011-03-31 MB: REF RO-EST-RP-3226 removed
2011-06-06 MB: editorial after RPC MIP delta review
"
RECORD_TYPE = STREAM
OBJECT = MISSION
MISSION_NAME = "INTERNATIONAL ROSETTA MISSION"
OBJECT = MISSION_INFORMATION
MISSION_ALIAS_NAME = ROSETTA
MISSION_START_DATE = 1995-03-01
/* THIS IS THE ANNOUNCEMENT OF OPPORTUNITY DATE [RO-EST-AO-0001] */
MISSION_STOP_DATE = "NULL"
MISSION_OBJECTIVES_SUMMARY = "
The prime scientific objective of the Rosetta mission
is to study the origin of comets, the relationship
between cometary and interstellar material and its
implications with regard to the origin of the Solar
System. "
MISSION_DESC = "
TABLE OF CONTENTS
----------------------------------
= ROSETTA Mission Overview
= ROSETTA Mission Objectives
- Science Objectives
= Mission Profile
= Mission Phases Overview
- Mission Phase Schedule
- Solar Conjunctions/Oppositions
- Payload Checkouts
= Mission Phases Description
- Launch phase (LEOP)
- Commissioning phase
- Cruise phase 1
- Earth swing-by 1
- Cruise phase 2 (and Deep Impact)
- Mars swing-by
- Cruise phase 3
- Earth swing-by 2
- Cruise phase 4 (splitted in 4-1 and 4-2)
- Steins flyby
- Earth swing-by 3
- Cruise phase 5
- Lutetia flyby
- Rendez-Vous Manouver 1
- Cruise phase 6
- Rendez-Vous Manouver 2
- Near comet drift (NCD) phase
- Approach phase
- Lander delivery and relay phase
- Escort phase
- Near perihelion phase
- Extended mission
= Orbiter Experiments
- ALICE
- CONSERT
- COSIMA
- GIADA
- MIDAS
- MIRO
- OSIRIS
- ROSINA
- RPC
- RSI
- VIRTIS
- SREM
= LANDER (PHILAE)
- Science Objectives
- Lander Experiments
= Ground Segment
- Rosetta Ground Segment
- Rosetta Science Operations Center
- Rosetta Mission Operations Center
- Rosetta Lander Ground Segment
- Lander Control Center
- Science Operations and Navigation Center
- Rosetta Scientific Data Archive
= Acronyms
ROSETTA Mission Overview
=====================================================================
The ROSETTA mission is an interplanetary mission whose main
objectives are the rendezvous and in-situ measurements of the comet
67P/Churyumov-Gerasimenko, scheduled for 2014/2015. The spacecraft
carries a Rosetta Lander, named Philae, to the nucleus and deploys it
onto its surface.
A brief description of the mission and its objectives can be found in
the Rosetta Science Management Plan [RO-EST-PL-0001] and in papers
[GLASSMEIERETAL2007A]. A detailed description of the
mission analysis can be found in the Consolidated Report on Mission
Analysis [RO-ESC-RP-5500], the ROSETTA User Manual [RO-DSS-MA-1001],
and the flight Operations Plan [RO-ESC-PL-5000].
On its long way to the comet nucleus after a Launch by Ariane 5 P1+
in March 2004, the ROSETTA spacecraft orbits the Sun for one year
until it returns to Earth for the first swing-by. The planet Mars is
reached in February 2007, about 3 years after launch. In November
2007 a second Earth swing-by takes place and a third one in November
2009. Two asteroid flybys (2867 Steins and 21 Lutetia) are performed
on the way to the comet. These two asteroids were selected at the
Science Working Team meeting on 11th March 2004 among all the
available candidate asteroids, depending on the scientific interest
and the propellant required for the correction manoeuvre. Around the
aphelion of its orbit, which is 5.3 AU from the Sun, the spacecraft
is in a spinning hibernation mode for about 2.5 years.
The comet 67P/Churyumov-Gerasimenko is reached about 10.5 years after
launch, in May 2014. After a comet mapping phase the Surface Science
Package, carried piggyback on the spacecraft are released for landing
on the comet's surface for in situ measurements. The ROSETTA mission
then makes a detailed study of the comet and its environment until a
Sun distance of 2 AU is reached again after comet perihelion, at the
end of the year 2015.
Please note:
------------
The ROSETTA spacecraft was originally designed for a mission to the
comet 46 P/Wirtanen to be launched in January 2003. Due to a delay of
the launch a new comet (67P/Churyumow-Gerasimenko) had been selected
by the Science Working Team on 3rd-4th April 2003 [RO-SWT-2004APR04].
The compliance of the design was checked and where necessary adapted
for this new mission. Therefore in the following all the details and
characteristics for this new mission are used.
ROSETTA Mission Objectives
=====================================================================
The scientific objectives of the ROSETTA mission can be considered
from three main viewpoints:
First of all, comets and asteroids are fully-fledged members of our
solar system, which means, that they are objects of intrinsic
interest to planetary scientists. The level of investigations
conducted on these bodies is therefore far below that achieved for
the other objects of the solar system.
The study of the small solar-system bodies arguably represents the
last major gap in the tremendous worldwide effort that has been made
to reveal our planetary neighbours to us.
The most important scientific rationale for studying small solar-
system bodies is the key role-play in helping us to understand the
formation of the solar system. Comets and asteroids have a close
genetic relationship with the planetesimals, which formed from the
solar nebula 4.57 billion years ago. Most of our present
understanding of these processes has been obtained by studying
meteorites, which constitute a biased sample of asteroidal material,
and micrometeoroids, which may represent cometary grains processed by
solar radiation and atmospheric entry. There is therefore a strong
scientific case of studying cometary material in situ, as it is
surely more primitive than extraterrestrial samples.
A third scientific aspect is the study of the physio-chemical
processes, which are specific to comets and asteroids. In this
respect, asteroids can provide information on impact phenomena,
particularly on very large scale. However, the increase in cometary
activity as these bodies approach the Sun undoubtedly represents one
of the most complex and fascinating processes to be observed in the
solar system.
Science Objectives
---------------------
The prime scientific objectives as defined in the Announcement of
Opportunity [RO-EST-AO-0001] by the Rosetta Science Team can be
summarized as:
- Global characterisation of the nucleus, determination of dynamic
properties, surface morphology and composition
- Chemical, mineralogical and isotropic compositions of volatiles and
refractories in a cometary nucleus
- Physical properties and interrelation of volatiles and refractories
in a cometary nucleus
- Study of the development of cometary activity and the processes in
the surface layer of the nucleus and in the inner coma (dust-gas
interaction)
- Origin of comets, relationship between cometary and interstellar
material.
- Implications for the origin of the solar system
- Global characterisation of the asteroid, determination of dynamic
properties, surface morphology and composition.
Mission Profile
=====================================================================
The ROSETTA mission profile results from the orbit of the target
comet 67P/Churyumov-Gerasimenko, which has a perihelion close to 1.2
AU and an aphelion of about 5.7 AU, resulting in a period of about
6.5 years. A detailed description of the Mission Profile can be found
in the Consolidated Report on Mission Analysis [RO-ESC-RP-5500], in
the Rosetta Mission Calendar [RO-ESC-PL-5026] and in the RSOC Design
Specification [RO-EST-PL-2010].
The injection of the spacecraft by a single Ariane 5 Launch with the
so-called 'delayed ignition' of the upper stage, is not directly into
the trajectory to the comet, because of the high spacecraft wet mass.
Therefore the spacecraft has to be accelerated by a sequence of
gravity assist manoeuvres at Mars and the Earth, in order to catch up
with the comet's velocity at perihelion. However, this increases the
mission duration to a total of nearly 12 years.
The initially large distance to the comet at the perihelion of its
trajectory is slowly decreasing after the third Earth swing-by. At
the intersection of both orbits, the difference in orbit inclination
and the residual relative velocity are diminished by the comet orbit
matching manoeuvre at around 4.0 AU Sun distance. The range of the
spacecraft-to-Sun distance is between 0.88 and 5.33 AU, defined by
the minimum Sun distance during the first five years of the mission
with the swing-bys at Earth, and the maximum Sun distance close to
the aphelion of the comet's orbit. The evolution of the spacecraft
distance to Earth over the mission time follows the profile of the
Sun distance superimposed by an oscillation with an amplitude of 2 AU
(+1,-1) and a period of about one year due to the Earth's motion
around the Sun. This results in a range from 0 AU (Earth Departure
and Swing-by) to 6.3 AU during the superior solar conjunction close
to the spacecraft's aphelion (see Solar Conjunctions section below).
After the second and third Earth swing-by ROSETTA crosses the
asteroid main belt, which gives the opportunity of two asteroid
flybys. The asteroids 2867 Steins and 21 Lutetia, are encountered on
5 September 2008 and 10 July 2010 respectively. These two asteroids
were selected at the Science Working Team meeting on 11th March 2004
among all the available candidate asteroids, depending on the
scientific interests and the propellant required for the correction
manoeuvre.
Between the major mission events, up to the comet rendezvous
manoeuvre, the spacecraft performs long interplanetary cruise phases
(up to 2.5 years) with several solar conjunctions (see Solar
Conjunctions section below) and the power critical aphelion passage
(last cruise phase). In order to reduce the ground segment costs and
the wear and tear of spacecraft equipment during these phases, the
spacecraft is put in 'Hibernation Mode'.
Two types of hibernation modes are planned to be used:
* 'Deep Space Hibernation Mode' above 4.5 AU: Inertial spin mode with
a spin rate of 4 deg/sec. The spacecraft is almost entirely passive,
except of receivers/ decoders, power supply, heaters and two
Processor Modules with one RTU.
* 'Near Sun Hibernation Mode' below 4.5 AU: 3-axes stabilised mode
with the solar arrays Sun-pointing and the +X-axis Earth-pointing.
Attitude control is performed with thrusters and star trackers, based
on ephemerides; occasional solar array adjustments and ground
contacts via the medium gain antenna (MGA).
The final approach to the comet into its sphere of influence is
prepared by the rendezvous manoeuvre (RVM-2), that matches the
spacecraft orbit with the comet orbit.
A subsequent sequence of approach manoeuvres, supported by optical
navigation, takes the spacecraft closer and closer to the comet.
After determination of the physical model of the comet by Doppler and
optical measurements, the spacecraft is inserted into a global
mapping orbit around the comet.
The global mapping starts from orbital heights of 5 to 25 comet
radii, depending on the actual size, shape and mass of the comet.
Close observation of specific landmarks from altitudes down to one
comet radius is planned. At least 80% of the illuminated surface
shall be mapped. The very low velocity of the spacecraft in the comet
orbit (few cm/s) requires a high performance accuracy of the
propulsion system.
The delivery of the Lander or Surface Science Package (SSP) is
achieved from an eccentric orbit, which takes the spacecraft to a low
altitude above the selected landing site. The Lander release is fully
automatic according to a predefined schedule, and shall lead to touch
down with minimum vertical and horizontal velocities relative to the
local rotating surface. Upon the landing of the Lander, the
spacecraft provides uplink and downlink data relay between the Lander
and the Earth.
After the Lander delivery the ROSETTA spacecraft escorts the comet
until the perihelion passage and outwards again, until a Sun distance
of 2 AU is reached end of the year 2015. The main scientific
objective during this phase is the monitoring of the features of the
active comet.
Mission Phases Overview
======================================================================
This section gives an overview of the major mission phases and main
events in scheduled tables. A description of the individual phases is
given in the following section. More detailed information can be
found in the Rosetta Mission Calendar [RO-ESC-PL-5026], the
Consolidated Report on Mission Analysis [RO-ESC-RP-5500] and the RSOC
Design Specification [RO-EST-PL-2010]
Mission Phase Schedule
-----------------------
The following table shows a schedule of the mission phases, with
start-end times (dd/mm/yyyy), duration (days) and distance to the sun
(Astronomical Units). Some of the most important events within the
mission phases are marked with an arrow (->). Further description of
each mission phase is given below.
.====================================================================
| Phase |Start Date|Main Event| End Date |Dur |SunDist(AU)|
|=================|==========|==========|==========|====|===========|
|LEOP |02/03/2004| |04/03/2004| 3 | |
|-----------------|----------|----------|----------|----|-----------|
|Commissioning1 |05/03/2004| |06/06/2004| 94 | 0.89-0.99 |
| ->DSM1 | |11/05/2004| | | |
| ->DSM1 Touch-up| |16/05/2004| | | |
|-----------------|----------|----------|----------|----|-----------|
|Cruise 1 |07/06/2004| |05/09/2004| 91 | 0.89-1.04 |
|-----------------|----------|----------|----------|----|-----------|
|Commissioning2 |06/09/2004| |16/10/2004| 41 | 1.04-1.09 |
|-----------------|----------|----------|----------|----|-----------|
|Earth Swing-by1 |17/10/2004| |04/04/2005| 170| 0.99-1.11 |
| ->Earth | |04/03/2005| | | |
|-----------------|----------|----------|----------|----|-----------|
|Cruise 2 |05/04/2005| |28/07/2006| 480| 1.04-1.76 |
| ->Deep Impact | |04/07/2005| | | |
|-----------------|----------|----------|----------|----|-----------|
|Mars Swing-by |29/07/2006| |28/05/2007| 304| 0.99-1.59 |
| ->DSM2 | |29/09/2006| | | |
| ->Mars | |25/02/2007| | | |
| ->DSM3 | |29/04/2007| | | |
|-----------------|----------|----------|----------|----|-----------|
|Cruise 3 |29/05/2007| |12/09/2007| 107| 1.32-1.58 |
|-----------------|----------|----------|----------|----|-----------|
|Earth Swing-by2 |13/09/2007| |27/01/2008| 137| 0.91-1.32 |
| ->Earth | |13/11/2007| | | |
|-----------------|----------|----------|----------|----|-----------|
|Cruise 4-1 |28/01/2008| |03/08/2008| 189| 1.02-2.03 |
|-----------------|----------|----------|----------|----|-----------|
|Steins Flyby |04/08/2008| |05/10/2008| 63 | 2.03-2.19 |
| ->Steins | |05/09/2008| | | |
|-----------------|----------|----------|----------|----|-----------|
|Cruise 4-2 |06/10/2008| |13/09/2009| 343| 1.35-2.26 |
| ->DSM4 | |19/03/2009| | | |
|-----------------|----------|----------|----------|----|-----------|
|Earth Swing-by3 |14/09/2009| |13/12/2009| 92 | 0.98-1.35 |
| ->Earth | |13/11/2009| | | |
|-----------------|----------|----------|----------|----|-----------|
|Cruise 5 |14/12/2009| |16/05/2010| 154| 1.03-2.45 |
|-----------------|----------|----------|----------|----|-----------|
|Lutetia Flyby |17/05/2010| |03/09/2010| 111| 2.45-3.14 |
| ->Lutetia | |10/07/2010| | | |
|-----------------|----------|----------|----------|----|-----------|
|Rendez-vousMan1 |04/09/2010| |13/07/2011| 313| 3.15-4.58 |
| ->RVM1 | |23/01/2011| | | |
|-----------------|----------|----------|----------|----|-----------|
|Cruise 6 (DSHM) |14/07/2011| |22/01/2014| 917| 4.49-5.29 |
|-----------------|----------|----------|----------|----|-----------|
|Rendez-vousMan2 |23/01/2014| |17/08/2014| 206| 3.53-4.49 |
| ->RVM2 | |23/05/2014| | | |
|-----------------|----------|----------|----------|----|-----------|
|Global Mapping |18/08/2014| |19/10/2014| 63 | 3.15-3.53 |
|and Close | | | | | |
|Observation | | | | | |
|-----------------|----------|----------|----------|----|-----------|
|Lander Delivery |20/10/2014| |16/11/2014| 28 | 2.97-3.15 |
|->Lander Delivery| |11/11/2014| | | |
|-----------------|----------|----------|----------|----|-----------|
|Comet Escort |17/11/2014| |31/12/2015| 410| 1.24-2.97 |
'-------------------------------------------------------------------'
Payload Checkouts
-----------------
Payload checkouts are scenarios designed to allow Rosetta payload to
make regular health checks, to activate mechanisms and to monitor
trends through calibration tests. They are allocated in the mission
calendar at regular 6-month periods during the first 10 years of the
mission cruise phase. They are split into passive and active payload
checkouts. Passive payload checkouts are entirely non-interactive.
Conditions for the passive checkout are that it will:
a) not require any real time monitoring, b) run entirely off of MTL,
c) not require s/c specific pointing other than to maintain listed
constraints, d) produce minimal science data. Active payload checkout
operations are executed both interactively and non-interactively .
Conditions for the active checkout are that it will: a) limit the
requirement for real time monitoring, b) run mostly from MTL, c) limit
the requirement for s/c specific pointing beyond maintaining listed
constraints, d) produce minimal science data. There is more
flexibility during active checkouts and in addition payloads use
interactive passes to make any necessary memory patches and tests.
.-------------------------------------------------------------------.
| Name | Type | Begin | End | Mission Phase |
|-----------------|--------|----------|-----------|-----------------|
| P/L Checkout 0 |Passive |27/03/2005| 31/03/2005| Earth Swing-by 1|
| P/L Checkout 1 |Passive |30/09/2005| 05/10/2005| Cruise 2 |
| P/L Checkout 2 |Passive |03/03/2006| 08/03/2006| Cruise 2 |
| P/L Checkout 3 |Passive |25/08/2006| 30/08/2006| Mars Swing-by |
| P/L Checkout 4 | Active |27/11/2006| 21/12/2006| Mars Swing-by |
| P/L Checkout 5 |Passive |18/05/2007| 23/05/2007| Mars Swing-by |
| P/L Checkout 6 | Active |13/09/2007| 30/09/2007| Earth Swing-by 2|
| P/L Checkout 7 |Passive |04/01/2008| 09/01/2008| Earth Swing-by 2|
| P/L Checkout 8 | Active |19/07/2008| 24/07/2008| Cruise 4-1 |
| P/L Checkout 9 |Passive |28/01/2009| 02/02/2009| Cruise 4-2 |
| P/L Checkout 10 | Active |18/09/2009| 08/10/2009| Earth Swing-by 3|
| P/L Checkout 12 |Passive |22/04/2010| 15/05/2010| Cruise 5 |
'-------------------------------------------------------------------'
Solar Conjunctions/Oppositions
-------------------------------
Other mission phases, which result from the orbit geometry and
interfere with the above operational phases, are the solar
conjunctions. Two types of conjunctions occur throughout the mission:
* Solar Oppositions: The Earth is between spacecraft and Sun,
resulting in a degradation of the command link to the spacecraft.
* Superior Solar Conjunctions: Sun is between spacecraft and Earth,
resulting in a degradation of the command and telemetry link to/from
the spacecraft.
Table below shows the solar conjunction phases throughout the mission
with type, begin and duration of the conjunction and correspondant
mission phase. The phases are defined as the periods, during which
the Sun-SpaceCraft-Earth (SSCE) angle is below 5 degrees.
.-------------------------------------------------------------------.
| Type |Duration| Begin | End | Mission Phase |
|---------------|--------|------------|------------|----------------|
| Conjunction 1 | 48d | 21/03/2006 | 07/05/2006 | Cruise 2 |
| Conjunction 2 | 39d | 08/12/2008 | 15/01/2009 | Cruise 4-2 |
| Conjunction 3 | 50d | 22/09/2010 | 10/11/2010 | RV Manouver 1 |
| Opposition 1 | 37d | 13/04/2011 | 19/05/2011 | RV Manouver 1 |
| Conjunction 4 | 64d | 15/10/2011 | 17/12/2011 | Cruise 6 |
| Opposition 2 | 47d | 30/04/2012 | 15/06/2012 | Cruise 6 |
| Conjunction 5 | 67d | 31/10/2012 | 05/01/2013 | Cruise 6 |
| Opposition 3 | 46d | 20/05/2013 | 04/07/2013 | Cruise 6 |
| Conjunction 6 | 60d | 24/11/2013 | 22/01/2014 | Cruise 6 |
| Opposition 4 | 28d | 25/06/2014 | 22/07/2014 | RV Manouver 2 |
| Conjunction 7 | 41d | 21/01/2015 | 02/03/2015 | Comet Escort |
'--------------------------------------------------------------------
Mission Phases Description
=====================================================================
Launch and Early Orbit Phase (LEOP)
-----------------------------
Rosetta was launched by an Ariane 5/G+ in a dedicated flight (single
launch configuration) from Kourou at 07:17:51 UTC 2 March 2004. After
burnout of the lower composite, the upper stage together with the
spacecraft remained in an eccentric coast arc for nearly 2 hours.
Then the upper stage performed delayed ignition and injected the
Rosetta spacecraft into the required escape hyperbola.
After spacecraft separation from the upper stage, Rosetta acquires
its three axes stabilised Sun pointing attitude and deploys the solar
arrays autonomously. Ground operations acquire the down-link in
S-band using the ESA network and control the spacecraft to a fine-
pointing attitude with the HGA pointing towards Earth using X-band
telemetry. Tracking and orbit determination are performed, the
departure trajectory is verified and corrected by the on-board
propulsion system of the spacecraft.
The launch locks of the Lander Philae are released at the end of the
first ground station pass. Philae remains firmly attached to the
spacecraft by the cruise latches until its release at the comet.
Commissioning phase (1 and 2)
-------------------
Commissioning starts three days after launch following the first
trajectory correction manoeuvre. A Deep Space Manouver (DSM1) of 173
m/s is executed at perihelion. All spacecraft functions needed during
the cruise to the comet, in particular for hibernation, are checked
and the scientific payload is commissioned.
Commissioning is done in two parts, as the New Norcia ground station
must be shared with Mars Express and cannot be used by Rosetta from
June to mid-September 2004.
For more information refer to the following reports:
[RO-EST-RP-3293] Consolidated Rosetta Payload Report of the Mission
Commissioning Results Review
[RO-EST-RP-3307] RSOC_Commissioning_Results_Report_2005Dec19.pdf
[RO-EST-RP-3343] Interference Scenario Report
Cruise phase 1
--------------
Almost all the scientific instruments, except ALICE are switched off
while ground contact is practically not available. No payload
operations are done during this phase.
Earth swing-by 1
----------------
The actual Earth swing-by takes place on 4-Mar-05. The phase ends one
month after the swing-by and the spacecraft is prepared for the next
cruise phase to Mars.
One passive Payload Checkout is scheduled end of March 2005.
Immediately after this flyby an Asteroid Flyby Mode Simulation is
performed using the Moon as a target. Some limited payload operations
are permitted shortly before during and shortly after this Earth
Flyby. Rosetta payload teams are given the opportunity to conduct
scientific investigation that includes close approach of both the
Earth and the Moon and the AFM simulation. Any activities that do not
require the Earth-Moon system i.e. continued instrument commissioning,
are considered for later in the Mission, such as during the next
active checkout.
The instrument objectives are listed below.
ORBITER
ALICE objectives are:
- Flat field calibration
- Extended object scattered light calibration (Moon as the target)
- Absolute solar calibration
- Absolute flux and wavelength calibration (wide part of the slit
to take in the Moon)
- Door performance test due to anomalies raised during
commissioning
MIRO
- Asteroid Flyby Simulation test
- H2O lines in Earth (high quality data obtained but analysis not
complete)
- Radiometric calibration of the Moon
RPC
- Sensor calibration
- Magnetospheric physics
- Verification of the science operations modes for the Mars flyby
RSI
- HGA to Earth around closest approach to Moon
OSIRIS
- Because of technical issues OSIRIS was
not operated during the Earth Swing-By itself so only periodic
exists in this node.
VIRTIS
- Co-alignment M/H
- Aldebaran target in IR (failed, boresight did not detect the
target)
- Absolute calibration using the Moon
- Full disc Earth imaging including exosphere over one rotation
LANDER
CIVA
- Earth Picture with Camera #2 or 4
ROMAP with RPC MAG
- magnetic axes alignment of sensors with Earth magnetic field
- Checking of scaled values with known Earth values
- Solar wind values comparison with other s/c
Problems:
RPC
- Loss of LAP science data for 41.5 hours (2005-03-01 19:00 --
2005-04-03 12:30).
For more information refer to the following reports:
[RO-EST-RP-3318] Payload Passive Checkout 0 Report
[RO-EST-RP-3321] Rosetta Earth-Swingby #1 Payload Operations Report
Cruise phase 2 (and Deep Impact)
--------------------------------
After leaving the Earth, the spacecraft makes one revolution around
the Sun, and in the second arc from perihelion to aphelion makes a
swing-by of Mars.
There is a solar conjunction for more than one month in April 2006
(see Solar Conjunctions section above). Two passive check-outs with
non-interactive instrument operations for about 5 days are scheduled
during the cruise to Mars. PC1 occurs from 5/09/2005 to 5/10/2005. PC2
takes place from 3/03/2006 to 8/03/2006.
The NASA Deep Impact mission encounters comet 9P/Tempel 1 on 4 July
2005, which falls into the Cruise 2 mission phase. At around 06:00
UTC, the mother probe sends a 362 kg impactor into the nucleus with a
relative speed of 10.2 km/s. Rosetta is in a privileged position for
its remote sensing instruments to observe the event (80 million km
distance, 90 degrees angle respect to the sun). Rosetta monitors
Tempel 1 continuously (i.e. 24 hrs per day) over an extended period
from 7 days before the deep impact to 11 days afterwards (27Jun-15Jul
2005). The first 2 days ALICE observe the stars for calibration. From
the 28th June to the 15th July, OSIRIS, ALICE, and MIRO operate
observing comet 9P/Tempel 1 continuously. VIRTIS was on only several
hours around the impact. Maintenance activities were carried out for
COSIMA, ROSINA, ALICE.
During the Deep Impact subphase, the instruments have the following
objectives:
ORBITER
ALICE
- Baseline pre-impact spectrum. Comparison with near and long
term post impact spectra. The comet is detected in all spectra.
- Strong atomic lines of neutral H and O were detected throughout
the observation period.
- Two weak lines of neutral C detected on some dates. No change
detected by ALICE in comet's UV spectrum as a result of impact
- except for possible enhancement in C emission.
- No evidence of Ar, S, N, CO.
- Water production rates. Results TBC.
- Dark histograms.
- Calibration star before the encounter. Spectra of calibration
star is used for calibration of the Deep Impact spectra and
instrument sensitivity. The data is also used to look for any
flux variations due to pointing/jitter (initial results do not
show any evidence of significant fluctuations in the stellar
count rate).
- Memory patch (time synchronisation issue).
MIRO
- Changes in the coma composition induced by the impact.
- Upper limit on the water production rate in the pre-impact
phase of the experiment. Water production rate and albeit
with low signal-to-noise measured in the post impact phase. The
water production rate is less than has been anticipated based
on models.
- Detection of carbon monoxide: the analysis is not complete but
so far no CO was detected.
- Estimate of Doppler velocity.
OSIRIS
- Accurate photometry of the unresolved nucleus (no atmosphere in
between) with complete time coverage. The time resolution is
better than a minute around the impact and can draw conclusion
about the evolution of the impact cloud during the first hour.
The long term monitoring allowed determination of the composition
and evolution of the impact cloud (water production and dust/ice
ratio)
- UV coverage that allowed imaging of the OH emission at 308nm
(estimate of the water production by the impact)
- Imaging of the coma out to at least 150000km from the nucleus.
The effect of the impact can be seen in the images for
appromximately a week (stereo reconstruction of coma,
impact cloud).
VIRTIS
- Coma and ejecta composition and temporal evolution. But the
outburst due to the impact was not energetic enough to reach the
minimum sensitivity required.
Conclusions of the Deep Impact Observations:
The science objectives of the Deep Impact Observations scenario are
met. The brightness increase of Tempel 1 produced by the impact is
lower than we had hoped for, and as a result the comet was too weak to
be detected by VIRTIS. For ALICE and MIRO the signal was just above
the sensitivity limit, but nevertheless important measurements could
be achieved. The results of OSIRIS even exceeded the expectations, and
the first scientific publications are widely cited. The data collected
by the experiments on board Rosetta are unique because Tempel 1 was
monitored continuously over an extended period of time (no day-and-
night cycle in contrast to ground-based telescopes) and in the absence
of an absorbing atmosphere.
The following operations have been done during the Passive checkout 1:
ORBITER
ALICE
- Electronic and software
- Test pattern and stim test
- Memory check
- dark exposures
There is no instrument anomalies. The door performance test showed
nominal behavior.
CONSERT
- Consert Orbiter verification
- Consert Lander verification
- Consert Orbiter/Lander time synchronisation
COSIMA
- Self check
- Target manipulator unit maintenance
- Ion emitter maintenance
GIADA
- Run mechanisms - cover operations
- Health check (all subsystems, electronics, noise and
contamination monitoring, performances estimation)
MIDAS
- Exercising of all mechanisms (shutter, approach mechanism,
linear stage, wheel, scanner)
The test is successful and MIDAS is fully operable.
MIRO
- Regular exercise and health check of all commands in all modes
- Regular dump of EEPROM memory to check for radiation damage.
All objectives are met. There is no radiation damage of the
EEPROM.
RPC
- MAG: instrument calibration. Undisturbed solar wind is measured
to calibrate the offsets of the MAG instrument in quiet conditions
(Hedgecock method).
- LAP: instrument calibration.
- MIP: Instrument checkout
- IES: measurement in the undisturbed solar wind for calibration
of its sensors and cross calibration with LAP.
The PC operations are completed successfully with no change in
instrument performance for MAG and IES.
RSI
Two frequency downlink drven by the USO and a ground station
that can receive the X and S band signals.
- Investigate the stability of the USO
- Verify interaction with the ground
Investigations of the USO data from PC#0 revealed that the
behaviour of the USO is obviously not as good as it was during
the last USO test in October.
OSIRIS
- Exercise the instrument mechanisms
- Verify the sanity of the CCD
- Verify the focus
No anomaly occurs.
LANDER
Test of the Lander Platform overall performance
Secondary battery monitoring
Lander extended AFT
CDMS EEPROM dump
functional test for
PTOLEMY
CONSERT
The following operations have been done during the Passive checkout 2:
ORBITER
ALICE
- same health tests as PC1. Tests successful.
CONSERT
- same as PC1. Tests generally successful (see report)
COSIMA
- self check of all hardware sub-systems on operational voltage
levels
- target manipulator unit checkout
- maintenance COSISCOPE checkout
- emitter maintenance
Tests generally successful.
GIADA
- Same as PC1 plus monitoring of MBS coating evolution.
The cover operations went fine. There is no further contamination
of the microbalances. GDS is not fully tested for light
conditions. IS seems nominal. All HK values are as expected.
MIDAS
- same as PC1. Tests are successful.
MIRO
- Same as PC1. Overall success.
RPC
- Same as PC1. All performances checked are nominal.
RSI
- Same as PC1. The USO behaves very good, USO drift satisfactory.
OSIRIS
- Same as PC1. Generally successful. For solar elongation
angles < 90 degrees OSIRIS gets substantial scattered light
through the nominally closed doors. The scattered light observed
during PC2 was unfortunately enough that parts of the CCD surface
was saturated. This happened in spite of the large exposure time
reduction that was made after PC1.
VIRTIS
- The check done were performed properly.
LANDER
Same as PC1 plus functional tests for
MUPUS
CONSERT
For more information refer to the following reports:
[RO-EST-RP-3341] Deep Impact Observations, Payload Operations Report
[RO-EST-RP-3342] Passive Payload Checkout 1 Report
[RO-EST-RP-3418] Passive Payload Checkout 2 Report
Mars swing-by
-------------
The mission phase begins two months before DSM2 of 65 m/s, which is
performed near perihelion. The actual Mars swing-by takes place on
25-Feb-07. The minimum altitude with respect to the Martian surface
is 200 km. The relative approach and departure velocity is 8.8 km/s.
During the swing-by a communications black-out of approximately 14
min is expected due to occultation of the spacecraft by Mars.
Furthermore the spacecraft is expected to be in eclipse for about 24
min. The phase ends one month after DSM3. DSM3 of 129 m/s is scheduled
near the aphelion of this arc in order to obtain the proper arrival
conditions at the Earth. Two passive payload check-outs of about 5
days and an active longer one of 25 days are scheduled during the
phase.
PC3 starts on 25th August 2006 and ends 30th August 2006.
The following operations were planed during PC3. GIADA and ROSINA did
not take part in this PC.
ORBITER
ALICE
- Electronics & software verification, test pattern and stim test,
Memory Check, Aperture Door, Performance Test.
All operations are executed as expected.
CONSERT
- Consert Orbiter verification, Consert Lander verification,
Consert Orbiter/Lander time Synchronisation.
COSIMA
- self check of all hardware sub-systems on operational voltage
levels, target manipulator unit checkout and maintenance emitter
maintenance
MIDAS
- Regular health check and exercising of all mechanisms (shutter,
approach mechanism, linear stage, wheel, scanner)
MIRO
- Regular exercise and health check of all commands in all modes.
Regular dump of EEPROM memory to check for radiation damage.
All operations are successful.
RPC
- MAG: Instrument calibration. Undisturbed solar wind measurement.
Such data will be used to calibrate the offsets of the MAG
instrument in quiet conditions (Hedgecock method).
- LAP: Instrument calibration.
- MIP: Instrument checkout.
- IES: measurements in the undisturbed solar wind for calibration
of its sensors and crosscalibration with LAP.
RSI
- Investigate the stability of the USO and verify interaction
with the ground.
The PC3 results are very promising and the behavior of the USO
is as good as expected. The stability of the USO is still one
order of magnitude better than anticipated before launch.
OSIRIS
- Instrument mechanisms, verify the sanity of the CCD, verify the
focus of the instrument.
VIRTIS
- Both VIRTIS M and H are working as expected.
- PC3 has been used to verify the upload of a new pixel map for
VIRTIS-H to be used during the forthcoming PC4 (pixel map allows
to drastically reduce the data volume).
LANDER
- Test of the Lander platform to check the overall performance and
Secondary Battery Status
- Lander Extended AFT with short function
- tests of some units and
EEPROM
- checks for all ComDPU units
- Secondary Battery Monitoring
- CDMS EEPROM dump
- Separate short functional tests for MUPUS and CONSERT
The report has not yet been written. Payload checkout reports:
RO-SGS-RP-0001_1_-
_Rosetta_Passive_Payload_Checkout_3_Report_2007Jun27.pdf
RO-EST-RP-3464_1_-
_Rosetta_Report_Active_Payload_Checkout_4_2006Apr13.pdf
RO-SGS-RP-0002_1_-
_Rosetta_Passive_Payload_Checkout_5_Report_2007June27.pdf
Cruise phase 3
--------------
No check-outs are scheduled during the short cruise to Earth.
Earth swing-by 2
----------------
Daily operations start again around two months before Rosetta reaches
Earth with tracking and navigation manoeuvres. The actual Earth swing
-by takes place on 13-Nov-07. The perigee altitude is 13890 km. The
relative approach and departure velocity is 9.3 km/s. The phase ends
one month after the LGA strobing phase. In this phase the spacecraft
gets very close to the sun (min distance 0.91AU). One 15 day payload
checkout and one 5 day payload checkout are also scheduled in this
phase.
The report has npt been written yet. The Payload checkout reports are:
RO-SGS-RP-0004_1_-
_Rosetta_Report_Active_Payload_Checkout_6_2007Oct30.doc
RO-SGS-RP-0005_1_a
_Rosetta_Passive_Payload_Checkout_7_Report_2008Jun24.pdf.
Cruise phase 4 (split into 4-1 and 4-2)
--------------
In this phase the spacecraft makes one revolution around the Sun.
. A solar
conjunction takes place in January 2009 (see Solar Conjunctions
section above), together with another two conjunctions of the Earth-
spacecraft- Sun angle (Sun-Earth conjunction as seen from the
spacecraft). In this phase the spacecraft gets very close to the sun
(min distance 0.91AU). This Cruise phase has been splitted in two
parts after the selection of the first Asteroid flyby which falls
in the middle of this phase. Cruise 4-1 is before the flyby phase,
and 4-2 is right after. Two passive check-outs are scheduled, one
during Cruise 4-1 and the second one during Cruise 4-2.
The report will be provided later.
Steins flyby
-------------
Asteroid Steins was the first dedicated scientific target of the
Rosetta mission. Closest approach was on 5 September 2008 at 18:38:22
UTC. Rosetta flew at 800 km from asteroid Steins. For the first time a
European spacecraft flew next to an asteroid, performed an optical
navigation campaign, and autonomously tracked the asteroid by means of
its on board camera.
The 2867 Steins E-type asteroid had been discovered on 4 November 1969
by N. Chernykh. Its dimensions have been estimated by [KELLERETAL2010]
to 6.67 x 5.81 x 4.47 km3, corresponding to a spherical equivalent
radius of 2.65 km. Its sideral rotation period has been estimated to
6.04681 +/- 0.00002h, its pole direction in ecliptic coordinates to
approximately Lambda = 250 deg and Beta = -89 deg with an error of
about 5 degrees [LAMYETAL2008]. Its albedo has been estimated to 0.3
in the visible and 0.4 in the infrared, both by [KELLERETAL2010] and
[LAMYETAL2008].
The two asteroids Rosetta flew by are secondary science targets of the
Rosetta mission, with comet 67P/Churyumov-Gerasimenko being the
primary science target. Therefore, scientific measurements of Asteroid
(2867) Steins had highest priority during the Steins flyby.
Calibrations was performed during the flyby phase only if a
calibration close in time to the actual scientific measurement was
needed.
The flyby geometry necessitated a flip in the spacecraft attitude
before closest approach. As a compromise between the incompatible
requirements to minimize the illumination of the -X and +-Y panels of
the spacecraft (flip as late as possible) and to minimize the impact
on the science observations (flip as early as possible), the
spacecraft flip was performed between 40 and 20 minutes before closest
approach. The flyby of Steins is a very fast flyby in the sense that
the distance between Rosetta and the Asteroid changes by an order of
magnitude within 15 minutes before and after the flyby.
The heliocentric and geocentric distances of Rosetta during the Steins
flyby was 2.14 AU and 2.41 AU, respectively. The one way light travel
time were 20 minutes.
The estimated accuracy of the determination of the position of Steins
in the plane perpendicular to the flight direction during the naviga-
-tion campaign was +/-2 kms for navigation with OSIRIS and +/-16 kms
for navigation with the NAVCAMs (from navigation slot on Sept. 4). For
the targeted passage through phase angle 0 at a distance of 1280 kms
from Steins, a positional offset of 2 kms would correspond to a
minimum phase angle of 0.1 degree.
The following table shows an overview of the Steins Flyby scenario:
------------------------------------------------------------------
| Start Date | End Date | Operation |
------------------------------------------------------------------
| 04/08/2008 | 04/09/2008 | Navigation campaign (astrometry) using|
| | | NAVCAM and OSIRIS NAC |
------------------------------------------------------------------
| 01/09/2008 | 10/09/2008 | Scientific operations targeting the |
| | | asteroid |
------------------------------------------------------------------
| 07/09/2008 | 04/10/2008 | Observation of gravitational |
| | | microlensing events in the galactic |
| | | bulge by OSIRIS |
-------------------------------------------------------------------
The following table shows the observation results per instrument:
----------------------------------------------------------------------
| Instrument| Title |Success| Comments |
----------------------------------------------------------------------
| ALICE 01 | Alice optics | Yes | at the beginning and |
| | decontamination | | end of all scenarios |
|--------------------------------------------------------------------|
| ALICE 02 | Standard stellar flux | Yes | During major |
| | calibration using the AL| | scenarios |
| | narrow center boresight | | |
|--------------------------------------------------------------------|
| ALICE 03 | Standard stellar flux | Yes | During major |
| | calibration using the AL| | scenarios |
| | +X wide bottom boresight| | |
|--------------------------------------------------------------------|
| ALICE 04 | Dark exposures | Yes | Regular calibration |
|--------------------------------------------------------------------|
| ALICE 05 | Search for evidence of | Yes | No exosphere or coma |
| | exosphere/coma around | | found |
| | Steins | | |
|--------------------------------------------------------------------|
| ALICE 06 | Point at Steins to | Yes | First Spectrum of an |
| | obtain an FUV spectrum | | asteroid below 200nm |
|--------------------------------------------------------------------|
| ALICE 07 | Point to the Steins RA | Yes | |
| | and Dec at the mid point| | |
| | of AL 06 observation | | |
|--------------------------------------------------------------------|
| ALICE 08 | Point to the Steins RA | Yes | |
| | and Dec at the mid point| | |
| | of AL 05 observation | | |
|--------------------------------------------------------------------|
| ALICE 09 | Standard stellar flux | Yes | During major |
| | calibration using the AL| | scenarios |
| | -X wide top boresight | | |
|--------------------------------------------------------------------|
| COSIMA 01 | Image and expose D8 | No | TMU error |
| | substrate | | |
|--------------------------------------------------------------------|
| COSIMA 02 | Image all D8 substrates | No | Cancelled after |
| | and store it | | failure of CS 01 |
|--------------------------------------------------------------------|
| GIADA 01 | non nominal operational | Yes | |
| | configuration, i.e. only| | |
| | impact sensor on and | | |
| | cover closed | | |
|--------------------------------------------------------------------|
| LANDER 01 | Run MUPUS TEM mode | Yes | |
| | during periods with | | |
| | pronounced temperature | | |
| | changes | | |
|--------------------------------------------------------------------|
| LANDER 02 | Operate ROMAP in slow | Yes | Interference from |
| | mode and fast mode | | MUPUS deteceted |
| | during CA +/-30min | | |
|--------------------------------------------------------------------|
| LANDER 03 | CASSE measurements | Yes | |
| | during WOL with SW FM-2 | | |
|--------------------------------------------------------------------|
| LANDER 04 | Thermal test of SESAME | Yes | |
| | soles | | |
|--------------------------------------------------------------------|
| LANDER 05 | Operation of CASSE and | Yes | |
| | DIM in a dusty environ-| | |
| | -ment | | |
|--------------------------------------------------------------------|
| MIRO 01 | Observation of Steins | Yes | |
| | during approach | | |
|--------------------------------------------------------------------|
| MIRO 02 | Run Asteroid Mode | Yes | Poiting inaccuracy |
| | sequence at closest | | during Asteroid Flyby|
| | approach to Steins | | mode affects scienti-|
| | | | -fic output |
|--------------------------------------------------------------------|
| MIRO 03 | Observation of Steins | Yes | |
| | during Recession | | |
|--------------------------------------------------------------------|
| ROSINA 01 | Outgassing | Yes | |
|--------------------------------------------------------------------|
| ROSINA 02 | Single mass measurement | Yes | Contamination issue |
| | sequence | | due to s/c flip. |
| | | | Sw instability caused|
| | | | temporary switch-off |
| | | | of detector |
|--------------------------------------------------------------------|
| ROSINA 03 | Pressure monitoring | Yes | Contamination issue |
| | | | due to s/c flip |
|--------------------------------------------------------------------|
| RPC 01 | Steins Fly by | Mostly| ICA did not produce |
| | | | scientifically useful|
| | | | data due to a comman-|
| | | | -ding error. |
| | | | Interference from |
| | | | MUPUS detected |
|--------------------------------------------------------------------|
| RSI 01 | Coherent measurement | TBD | TBD |
| | with Xup/Xdown or Xup/ | | |
| | Sdown received by a | | |
| | groundstation capable of| | |
| | receiving X- and S- band| | |
| | Doppler and Ranging | | |
| | Signals | | |
|--------------------------------------------------------------------|
| SREM 01 | SREM standard | YES | No Steins specific |
| | accumulation | | operations, general |
| | | | particle flux |
| | | | monitoring |
|--------------------------------------------------------------------|
| OSIRIS 01 | Vega Stare | Yes | Stellar calibrations |
| | | | repeated during major|
| | | | scenarios |
|--------------------------------------------------------------------|
| OSIRIS 02 | 16 Cyg Stare | Yes | Stellar calibrations |
| | | | repeated during major|
| | | | scenarios |
|--------------------------------------------------------------------|
| OSIRIS 03 | Steins Lightcurve at | Yes | TBD |
| | CA-2 weeks | | |
|--------------------------------------------------------------------|
| OSIRIS 04 | Steins Lightcurve at | Mostly| WAC data compromised |
| | CA-24 hours | | by overexposure |
|--------------------------------------------------------------------|
| OSIRIS 05 | Steins observation at CA| Mostly| NAC went into Safe |
| | | | mode due to shutter |
| | | | issues about 10 min |
| | | | before CA |
|--------------------------------------------------------------------|
| OSIRIS 06 | Fast imaging sequence | Yes | observation merged |
| | around the time of phase| | with OSIRIS 05 |
| | angle 0 | | |
|--------------------------------------------------------------------|
| OSIRIS 07 | Characterization of | Yes | TBD |
| | solar straylight for | | |
| | same orientation as the | | |
| | one the s/c had when | | |
| | the OSIRIS hill sphere | | |
| | dust search was | | |
| | performed | | |
|--------------------------------------------------------------------|
| VIRTIS 01 | VIRTIS-M lightcurve of | Yes | TBD |
| | Steins | | |
|--------------------------------------------------------------------|
| VIRTIS 02 | V-M and V-H operating; | Yes | Operations were |
| |s/c stare at target Nadir| |affected by inaccuracy|
| | looking; continuous | | of s/c pointing |
| | acquisition in pushbroom| | |
| | mode | | |
|--------------------------------------------------------------------|
| VIRTIS 03 | V-M and V-H continuous | Yes | TBD |
| |observation of Steins for| | |
| | 1 hour after VR02; V-M | | |
| | in image mode (10 lines | | |
| | scan) | | |
|--------------------------------------------------------------------|
Summary results per instrument during closest approach:
ALICE: Beginning 7 minutes before CA, ALICE made a 10 minute
histogram observation of the asteroid. The spectrum extracted
from this histogram observation is the first of an asteroid
below 200nm and has an excellent signal to noise ratio. The
observed count rate from Steins was about a factor of two larger
than predicted. The spectrum of Steins is similar both to the
spectrum of the Earth's moon obtained during ESB2, and the solar
spectrum. During CA, Alice recorded the total count rate of the
detector at a rate of once per second. This data will be used to
derive a FUV phase curve for the asteroid; this analysis is
currently under way. There are two spikes in the observed count
rate, one slightly before passing through zero phase and the
other centered at the time Rosetta passed through zero phase. It
was initially thought that this second spike might represent an
opposition surge. However, subsequent analysis using the
reconstructed attitude information revealed that the two spikes
are actually due to the apparent motion of the multiple star
Rho Oph as Rosetta was tracking the asteroid: the initial spike
is caused by the star gazing the wide top part of the Alice slit,
the second spike is caused by the star grazing the wide bottom
part of the slit, and the gap between the spikes is caused by the
star lying outside of field of view of the narrow center segment
of the slit.
MIRO: the instrument was on during approximately 10 hours around
CA. The instrument was operated in three modes: a)spectroscopic-
dual continuum mode, b) dual continuum mode, and c)asteroid mode.
High signal-to-noise responses to Steins were seen in both
continuum channels, however the responses were of short duration
(minutes), because of the s/c pointing. Near closest approach,
the submillimeter beam boresight was located approximately on the
limb of Steins, rather than near the center of Steins. As a
result of the mis-pointing, phase coverage was severely limited.
No spectral features were visible in the individual spectrum
data. A preliminary study to search for water by integrating
multiple spectra was carried out, but no spectral line of water
was detected. The immediate plans are to compare the (dual
frequency) continuum data with thermal models of Steins. For this
purpose, both the reconstructed pointing data, and a (projected
area) shape model for Steins are needed. Using the IR surface
temperature maps provided by VIRTIS, the goal is to derive a
subsurface temperature gradient, and the loss tangent of the
regolith material. It is planned to continue the effort to detect
or set an upper limit on the water abundance around Steins. The
full spectrum will also be examined to search for other molecules.
LANDER/ROMAP: ROMAP worked perfectly and all HK values are in the
expected range. Magnetic field measurements were disturbed by
MUPUS supply current. All the measured signatures were spacecraft
generated. The magnetic field measurement showed that Steins does
not interact significantly (>nT) with the solar wind. The global
magnetization of Steins has to be therefore less than 1mAm2/kg.
For the first time both magnetometers (ROMAP-MAG and RPC-MAG)
worked in parallel doing a true interference test.
LANDER/SESAME: The flyby at asteroid (2867) Steins and its
observation on 5 September 2008 required an attitude change that
moved Philae out of the orbiter shadow for about half an hour.
This circumstance was used to obtain calibration measurements for
the new CASSE temperature measuring method. CASSE listenings were
used to investigate the vibration background caused by the orbiter
reacion wheels (RW). It was found that part of the backgound
vibration is not caused by the RW but other orbiter units or
experiment. In addition, new possible harmonics of the RW have
been identified.
LANDER/MUPUS: MUPUS was continuously operated for 17h around CA,
starting 7h before CA. During the heating period, a current of
about 100 mA was drawn from the +12V line which disturbed the
ROMAP measurements during the flyby. There were differences in
temperature measurements between ANC-T and TCU sensors. It seems
that a loss of sensitivity by about 28% compared to the ground
calibration occurred in the MUPUS TM sensors (TBC during descent
to comet).
ROSINA: COPS was switched on to the highest sensitivity with both
gauges. The COPS pressure is normally transmitted in the
housekeeping, one value every minute. One hour before to one houre
after CA COPS transmitted science data with a pressure value every
2 s. There is clearly a peak at closest approach.
DFMS was switch on in an outgassing mode. The sensor gave error
during CA due to the cold temperatude of the LEDA. Nevertheless,
DFMS produced excellent scientific data. The oxygen peak measured
by DFMS was much more pronounced during the closest approach than
during normal background measurements. However, the S/C flip also
produced a high oxygen peak and it remains to be seen what amount
of oxygen can be attributed to the S/C water and what to the
Steins exosphere. This needs modelling with the Rosetta S/C model.
An interesting feature has been seen during the S/C flip: the COPS
pressure rises much more rapidly than the DFMS oxygen signal. This
means that the first gas sublimating from the S/C is probably not
water but a molecule which does not contain oxygen. This is also
compatible with the fact that COPS measured a much higher pressure
peak during the flip than during CA whereas for the oxygen of DFMS
both peaks have similar amplitudes.
The table below summarizes the ROSINA switch on/off:
------------------------------------------------------------------
Date | Time |
2/09/08| 06:00 | On: Outgassing mode
4/09/08| 18:00 | Calib and asteroid mode
5/09/08| 06:00 | Stand by and OFF
5/09/08| 15:45 | On
6/09/08| 05:00 | Stand by
6/09/08| 18:00 | OFF
------------------------------------------------------------------
The general conclusion is that COPS and DFMS delivered good
scientific data despite the DFMS issue. Outgassing of the s/c is a
problem and has to be taken into account for all operations near
the comet.
RPC/ICA: ICA was not turned on in the appropriate mode (human
error) so no data was taken.
RPC/IES: IES operation during the flyby was nominal although no
indication of material from the asteroid was seen. RPC IES was
able to estimate solar wind velocity.
RPC/LAP: LAP operations were nominal in the entire period of
operations. The photoemission level was as small as expected (15
nA) due to the large heliocentric distance (around 2 AU). The
results (variations in the time series) are still under
investigation.
RPC/MAG: RPC MAG was switch on between 2008-09-01T00:10:00 and
2008-09-10T06:01:00. The spectra of the magnetic field data
measured by the OB sensor show, as usual, an influence of ROSETTAs
reaction wheels when in Burstmode. The data of the flyby are
disturbed by pulsed MUPUS heater currents. The currents generate
magnetic disturbances in the order of 2nT (100nT at the location
of the ROMAP sensors). The comparision between IB and OB data
showed that the measurements are very sensitive to specific
temperature changes at the single sensors. All flyby data are very
disturbed. Disturbances occur in various time scales. The origin
of the disturbance cannot clearly be identified (MUPUS?). Rotation
of the solar array and movement of the HGA cannot be seen in the
magnetic field data. Any signature of Steins cannot be seen in the
magnetic field data.
RPC/MIP: Very low values of MIP sensor temperatures are observed,
affecting the electronics and MIP response. Interferences are
observed in the whole frequency range when the temperature is
particularly low (around -150 degrees). The apparition of these
interferences is clearly correlated with the satellite manoeuvres.
Nominal temperatures and spectra are obtained in favorable
attitude configuration. LDL mode in Normal rate is affected due to
the lack of emission in this period (to be
confirmed/investigated). No plasma signature has been observed
during the STEINS flyby.
VIRTIS: TBW
RSI: The Earth was tracked by the High-gain antenna for most of
the time around the Steins flyby. However, it was known beforehand
that a mass determination of the small asteroid Steins would not
be possible.
SREM: SREM was on during the Steins flyby in its usual
accumulation mode, but did not perform any Steins specific
operations.
OSIRIS:
Slot Name Start Time End Time Purpose
----------------------------------------------------------------------
| Steins | 2008-08-07 | 2008-09-04 | Campaign for determining the |
|Navigation | | | position of 2867 Steins |
| | | | before the flyby |
----------------------------------------------------------------------
|2867 Steins| 2008-08-20 | 2008-09-06 | Observations of 2867 Steins |
| flyby | | | |
----------------------------------------------------------------------
| Micro- | 2008-09-06 | 2008-10-06 | |
| -lensing | | | Detection of microlensing |
| | | | events in the galactic center|
---------------------------------------------------------------------
GIADA: TBW (the report has not been provided by the team)
COSIMA: After the instrument power on 20080901, the highlevel task
to image one of the D8 substrates was started. The TMU started
from its initial position to grasp the D8 target holder from its
exposed location in the COSIMA dust funnel. The TMU generated an
error event during the grasping action and stopped any further
COSIMA command execution. After the operator reported of the error
to the COSIMA team, all the remaining operations were cancelled
and COSIMA was left switched on. On the following day, 20080902,
the COSIMA instrument was shutdown.
The Rosetta first asteroid flyby was a success. The navigation
campaign produced highly accurate predictions of the Steins position,
and during the flyby most instruments worked without serious problems.
Asteroid flyby mode worked well, although with somewhat lower tracking
accuracy than expected.
Earth swing-by 3
----------------
Operations are essentially the same as for the Earth swing-by 2. The
actual Earth swing-by takes place in Nov-09. The perigee altitude is
300 km. The relative approach and departure velocity is 9.9 km/s.
Phase starts 3 months before the swing-by and ends 1 month later. Two
short payload checkouts of about 5 days each are scheduled during
this phase.
The phase contains the Active Payload Checkout 10 (PC10). This section
will first describe PC 10 and then the Earth Flyby.
PC10
----
The Active PC10 ran for 18 consecutive days from 18th September 2009
to 4th October 2009. It represented a target independent opportunity
to perform interactive operations and to request spacecraft
pointing. All payloads took part in this scenario, as interactive
or non-interactive operations. There were approximately 425 hours of
non-interactive and 68 hours of interactive operations. Four
instruments required active s/c pointing with 15 targets observed
(111 hours of dedicated s/c pointing). These were mostly for
calibration purposes.
ALICE
-----
- EEPROM refresh
- Instrument Checkout
- Optics decontamination
- Standard stellar flux calibration (narrow center boresight and
wide top and bottom boresight)
- Analyze performance at 5 different voltages and 8 detector
discriminator thresholds to find the optimal operation parameter
values
- Determine the location of the center of narrow center boresight,
of wide bottom boresight and of wide top boresight in OSIRIS WAC
pixel coordinates (this was not achived).
- Scan alog slit (psuedo flat field, slit corners location,
pinhole aperture location)
- Stray light observations (anomalous spike at 30 deg real?)
- Point and stare at a star (flight software and instrument
safety test)
- Interference test
CONSERT
------
- Interference test
representative of comet observation with no Lander/Orbiter comm.
- Orbiter electronics and noise level measurement
- Turn on test
- Investigation of the 2 second delays between switch on of the
lander and of the orbiter (Switch on by ATTC or by RF Link
commanding).
COSIMA
------
- Passive Checkout
- Emitter A and C test
- s/w update (partial success)
GIADA
-----
- Standard procedures and full functional verification
- GIADA/VIRTIS interference test
- New parameters upload (emergency procedure)
LANDER
------
- Philae Lander interactive and non interactive operations
(report TBW)
MIDAS
-----
- Checkout and mechanism activation
- High resolution image of a dust collector facet
- Calibration of a scanner head
- Magnetic Mode Test
- S/w upload and functional checkout
MIRO
----
- Payload Checkout partially achieved
OSIRIS
------
- Pasive Checkout (insturment mechanisms, CCD sanity, instrument
focus)
- Calibration at different CCD temperatures
ROSINA
------
- test of GIADA effect because of higher pressure than normal
detected by COPS
- test of Lander effect because of pressure peaks registered
by DFMS and COPS.
- PTOLEMY and COPS measurement comparison
- Optimisation of DFMS settings because of possible outgasing
from the s/c
- Main and Redundant DPU s/w upload (partially achieved)
- COPS microtips test
- DFMS and RTOF covers test
RPC
---
- Passive Checkout: status check and instrument calibration
MAG, IES: undisturbed solar wind measurement
- IES/ROMAP Cross Calibration
- Test MIP levels during LDL
- test of MAG/LAP possible interference
- ICA perform test
- IES flight s/w upgrade and checkout
RSI
---
- USO behaviour under use of Transporter 2
results are TBD
SREM
----
- SREM standard accumulation: monitor the radiation environment in
the solar system during the cruise to the target comet.
results are TBD
VIRTIS
------
- S/w upload
- verfication of full scientific operative modes
- GIADA interference test
Earth flyby 3 (EAR3)
--------------
The EAR3 is the last of the three gravity assists from the Earth.
The swing-by spacecraft operations were of highest priority. Rosetta
had the opportunity to perform specific scientific observation of
the Earth-Moon system, instrument calibrations using Earth and/or
Moon and public relation observations.
ALICE
-----
- Instrument Checkout
- Optic decontamination
- Stellar calibration for cross comparision to Earth and Moon cals
- Spectra of illuminated Earth to obtain measurements of Earth's
airglow for relative calibration at wavelengths below 912A. Earth
will overfill the slit to be able to get flat field information at
the various airglow wavelengths.
- Observation of Moon limb
* to see if there is any change in instrument sensitivity
since EAR2
* for absolute calibration below 912 A
* to measure scattered solar light when observing an extended
object
- Spectra of illuminated moon limb to obtain a flat field
- Observation of the Moon as a point source
* for absolute calibration
- Dark count rate monitoring
- Ride along with MIRO raster scan of the moon for flux
calibration and possible boresight co-alignment information
- Ride along with OSIRIS to get Earth cal spectra
- Ride along with OSIRIS and VIRTIS to get Earth Aurora data
- Ride along with VIRTIS to observe the Moon
- Measurement of high energy electrons (HEET) while passing
through Earth magnetosphere
- Obtain baseline spectra of star for comparison to occultation
spectra
- Lunar atmosphere absorption spectra
MIRO
----
- Observation of Earth (H2O line for CTS calibration) around
closest approach
- Moon observation around closest approach (H2O detection)
- slew scan of Moon with OSIRIS (boresight alignment campaign)
RPC
---
- Sensors calibration and magnetospheric physics studies
- MAG LAP interferences: confirm whether LAP is or isn't the
source of the interference
SREM
----
- Spatial distribution of radiation belts along trajectory of
Rosetta around the Earth
OSIRIS
------
- Stellar calibration
- Flat field images and instrument calibration by pointing at
illuminated ocean surface on Earth crescent.
- Aurorae search by Earth night side targeted pointing during
approach phase
- Test of comet observations, monitoring of Moon motion by
post-encounter Moon tracking
- Lunar stray light calibration
- Characterization of ghosts of bright objects in WAC and NAC
optics
- Slew scan of Moon with MIRO
- Pre-encounter monitoring of Earth rotation
- Observation of the Earth-Moon system when both are in the field
of view of the WAC.
VIRTIS
------
- Earth night side pointing
- Earth limb scan, day and night side (non-LTE emission and Oxygen
airglow studies)
- Earth day side full-disk simultaneous acquisition by H and M
- Moon side observation by H and M for temperature calibration
- 4 cycles of scan across Earth day side to check the compression
algorithm and binning algorithm performance
- Limb to limb scan of Earth by H for calibration
- Moon staring for performance verification of M visible channel
- M-visible and H scan of Moon with MIRO (boresignt alignment)
According to the available reports, the EAR3 can be considered as
fully successful.
Cruise phase 5
--------------
Two passive check-outs are scheduled during this cruise phase.
The phase has not yet occurred. The report will be provided later.
Lutetia Flyby
--------------
The second of the flybys takes place on 10 July 2010 to the asteroid
21 Lutetia, discovered on 15 November 1852 by H. Goldsmith. It is
roughly 100 km in diameter, as determined by IRAS measurements.
This is the second of the two asteroids selected at the Science
Working Team meeting on 11th March 2004 among all the available
candidate asteroids, depending on the scientific interests and the
propellant required for the correction manoeuvre.
The flyby phase starts 2 months before the flyby and ends 2 months
later. In parallel with the daily tracking with orbit determination
and corrections, the scientific payload is checked out. The relative
asteroid ephemeris is determined by spacecraft optical navigation.
The aim is to pass the asteroid on the sunward side. The cameras and
scientific payload point in the direction of the asteroid until after
the flyby. Science data are recorded in the mass memory.
After the actual flyby, when the Earth link via the HGA is
recovered, the data recorded in the mass memory are transmitted to
Earth. Orbit correction manoeuvres required to put the spacecraft on
course are performed. Also one long payload checkout of 25 days is
scheduled during this phase.
The phase has not yet occurred. The report will be provided later.
Rendez-Vous Manouver 1
----------------------
The deep space manoeuvre is carried out when the spacecraft has
reached a distance from the Sun around 4.5 AU on 23-Jan-11. One
passive check-out is scheduled during this phase. One solar
conjunction of 50 days and one solar opposition of 37 days happen
during this phase.(see Solar Conjunctions section above).
The phase has not yet occurred. The report will be provided later.
Cruise phase 6
--------------
The whole period is spent in Deep-Space Hibernation Mode (DSHM).
Maximum distances to Sun and Earth are encountered during this
period, i.e. 5.3 AU (aphelion) and 6.3 AU, respectively. During this
phase, 3 superior solar conjuctions and 2 solar oppositions occur
(see table above).
The phase has not yet occurred. The report will be provided later.
Rendez-Vous Manouver 2
----------------------
This phase starts 4 months before the rendez-vous manouver 2
The phase has not yet occurred. The report will be provided later.
Near comet drift (NCD) phase
----------------------------
The spacecraft reaches the comet on 22-May-14 at a distance of 4.0 AU
from the Sun. A sequence of four rendezvous manoeuvres within 30 days
reduce the relative velocity with respect to the comet from 780 m/s
to 50 m/s. The spacecraft is in active cruise mode. During this phase
Rosetta approaches the comet without observing the comet with the
navigation camera (NAVCAM). The comet orbit is determined by a
dedicated ground-based astrometric observation campaign. The errors
in the estimated position of the comet can still be several tens of
thousand km. The final point of the NCD phase is the Comet
acquisition point (CAP) at 100000 km distance from the comet. The
selection of this position depends on two factors: avoiding cometary
debris (assuming there is any), and achieving good comet illumination
conditions.
The phase has not yet occurred. The report will be provided later.
Approach phase
--------------
-> Far Approach Trajectory (FAT)
Far-approach trajectory operations start at CAP. During this phase
the first images of the comet are obtained with the optical
measurement system (NAVCAM, OSIRIS). After detection, knowledge of
the comet ephemeris is drastically improved by processing the on-
board observations. Image processing on the ground derives a coarse
estimation of comet size, shape and rotation. The first landmarks are
identified.
The approach manoeuvre sequence reduces the relative velocity in
stages down to 3.1 m/s after 30 days. The manoeuvre strategy is
designed to:
* retain an apparent motion of the comet with respect to the star
background,
* retain the illumination angle (Sun-comet-spacecraft) below 70
degrees,
* avoid the danger of impact with the cometary nucleus in case of
manoeuvre failure.
The FAT ends at the Approach Transition Point (ATP), which is located
in the Sun direction at about 1000 comet nucleus radii from the
nucleus. During this phase the spacecraft is in active cruise mode
with the navigation camera and some orbiter payloads switched on.
-> Close Approach Trajectory (CAT)
Close approach trajectory operations start at ATP and take 17 days.
The spacecraft distance to the comet is decreased to 40 nucleus radii
and the relative velocity falls below 1 m/s. The final point of this
phase is called the Orbit Insertion Point (OIP) and is the point
where the spacecraft starts orbiting the comet. The injection is
performed by means of a hyperbolic orbit. Lines of sight to landmarks
are processed together with on-ground radiometric measurements in
order to estimate the spacecraft's relative position and velocity,
the comet absolute position, attitude, nucleus angular velocity,
gravitational constant and location of landmarks.
-> Transition to Global Mapping (TGM)
The transition to global mapping starts at OIP. A hyperbolic arc is
used down to a distance to the comet of about 10-25 comet radii where
a capture manoeuvre closes the orbit. The plane of motion is defined
by the comet spin axis and the Sun direction. This plane is rotated
slightly in order to avoid solar eclipses and Earth occultations.
-> Global Mapping Phase (GMP)
Mission scenarios have the objective of completing a science goal and
require a trajectory and attitude profile which is driven by
experiments selected to have priority in achieving this goal. The
first scenario is the mapping scenario, during which at least 80 % of
the comet surface is observed from a circular orbit with a radius in
the range of 10-25 comet radii and the comet model increases in
accuracy by evaluating the scientific results.
-> Close Observation Phase (COP)
In this second scenario detailed observations are made of up to five
potential landing sites for the Rosetta lander from a distance of
less than 1 nucleus radius.
The phase has not yet occurred. The report will be provided later.
Lander delivery and relay phase
-------------------------------
The priority of this phase is the successful delivery of the lander
to the surface of the comet. After the landing, the Rosetta orbiter
is brought into a trajectory which is optimised such that the orbiter
can act as a relay for the lander-ground communications. Note that
the other experiments are also operating during this phase, regular
science planning is performed. However, the operations of other
experiments cannot interfere with the lander operations.
The phase has not yet occurred. The report will be provided later.
Escort phase
------------
-> Comet activity: low activity (LOW)
Starting from 3.5 to 3.3 AU the comet develops a measurable coma. At
this point spacecraft resources limit the on-board orbiter
experiments to be fully operational and time-sharing by choosing
priorities determines the operations. Over the interval of 3.3 to 2.6
AU the activity is low and more or less constant, but occurrences of
outburst are possible. The nominal start of the scientific mission is
3.25 AU and spacecraft resources are capable of supporting full
experiments operations. It is a mission preference that the lander is
separated preferably before 3 AU while the comet is still relatively
in-active. Therefore the lander separation and relay has to be
executed as soon as a landing site has been selected. (Note that the
lander team baselines a delivery at 3 AU and not before.)
-> Comet activity: moderate increase (MINC)
The overall activity is expected to show a steady and moderate
increase. The completion of the science objectives drive the
selection of the mission scenarios for this phase.
-> Comet activity: sharp increase (SINC)
A sudden and steep increase in activity together with a change in
outgassing conditions are expected for this phase from previous
observations. Special orbit requirements, like dust/gas jet
crossings, are possible for mission scenario selection.
-> Comet activity: high activity (HIGH)
The production rate of gas and dust is expected to have a steep
increase indicating a distinct change in outgassing conditions. The
thermal conditions of the spacecraft for distances smaller then 1.4
AU may influence the science operations capabilities and time-sharing
of the payload operations may be necessary.
The phase has not yet occurred. The report will be provided later.
Near perihelion phase
---------------------
This phase is likely to show a steady increase of overall activity.
The phase has not yet occurred. The report will be provided later.
Extended mission
----------------
Nominally, unless a mission extension is agreed and if the spacecraft
survives in the cometary environment, the mission ends at the
perihelion pass after 11.5 years. If possible, however, the mission
is continued. More risky or more time consuming scenarios may be
executed.
The phase has not yet occurred. The report will be provided later.
Orbiter Experiments
=====================================================================
ALICE
-----
ALICE, an Ultraviolet Imaging Spectrometer, will characterize the
composition of the nucleus and coma, and the nucleus/coma coupling of
comet 67 P/Churyumov-Gerasimenko. This will be accomplished through
the observation of spectral features in the extreme and far
ultraviolet (EUV/FUV) spectral regions from 70 to 205 nm.
ALICE will make measurements of noble gas abundances in the coma, the
atomic budget in the coma, and major ion abundances in the tail and
in the region where solar wind particles interact with the ionosphere
of the comet. ALICE will determine the production rates, variability,
and structure of H2O and CO, and CO2 gas surrounding the nucleus and
the far-UV properties of solid grains in the coma.
ALICE will also map the cometary nucleus in the FUV, and study Mars
and the Rosetta asteroid flyby targets while en route to Churyumov-
Gerasimenko.
Instrument References: [STERNETAL2007]
CONSERT
-------
CONSERT (Comet Nucleus Sounding Experiment by Radio wave
Transmission) is an experiment that will perform tomography of the
comet nucleus revealing its internal structure. CONSERT operates as a
time domain transponder between the Lander which will be on the comet
surface and the Orbiter will orbit the comet. A radio signal passes
from the orbiting component of the instrument to the component on the
comet surface and is then immediately transmitted back to its source,
the idea being to establish a radio link that passes through the
comet nucleus. The varying propagation delay as the radio waves pass
through different parts of the cometary nucleus will be used to
determine the dielectric properties of the nuclear material. Many
properties of the comet nucleus will be examined as its overall
structural homogeneity, the average size of the sub-structures
(Cometesimals) and the number and thickness of the various layers
beneath the surface.
Instrument References: [KOFMANETAL2007]
COSIMA
------
The Cometary Secondary Ion Mass Analyser is a secondary ion mass
spectrometer equipped with a dust collector, a primary ion gun, and
an optical microscope for target characterization. Dust from the near
comet environment is collected on a target. The target is then moved
under a microscope where the positions of any dust particles are
determined. The cometary dust particles are then bombarded with pulses
of indium ions from the primary ion gun. The resulting secondary ions
are extracted into the time-of-flight mass spectrometer.
Instrument References: [KISSELETAL2007]
GIADA
-----
The Grain Impact Analyser and Dust Accumulator will measure the
scalar velocity, size and momentum of dust particles in the coma of
the comet using an optical grain detection system and a mechanical
grain impact sensor. Five microbalances will measure the amount of
dust collected as the spacecraft orbits the comet.
Instrument References: [COLANGELIETAL2007]
MIDAS
-----
The Micro-Imaging Dust Analysis System is intended for the
microtextural and statistical analysis of cometary dust particles.
The instrument is based on the technique of atomic force microscopy.
This technique, under the conditions prevailing at the Rosetta
Orbiter permits textural and other analysis of dust particles to be
performed down to a spatial resolution of 4nm.
Instrument References: [RIEDLERETAL2007]
MIRO
----
MIRO (Microwave Instrument for the Rosetta Orbiter) is composed of a
millimetre wave mixer receiver and a submillimetre heterodyne
receiver. The submillimetre wave receiver provides both broad band
continuum and high resolution spectroscopic data, whereas the
millimetre wave receiver provides continuum data only.
MIRO will measure the near surface temperature of the comet, allowing
estimation of the thermal and electrical properties of the surface.
In addition, the spectrometer portion of MIRO will allow measurements
of water, carbon monoxide, ammonia, and methanol in the comet coma.
Instrument References: [GULKISETAL2007]
OSIRIS
------
OSIRIS (Optical, Spectroscopic, and Infrared Remote Imaging System)
is a dual camera imaging system operating in the visible, near
infrared and near ultraviolet wavelength ranges. OSIRIS consists of
two independent camera systems sharing common electronics. The narrow
angle camera is designed to produce high spatial resolution images of
the nucleus of the target comet. The wide angle camera has a wide
field of view and high straylight rejection to image the dust and gas
directly above the surface of the nucleus of the target comet. Each
camera is equipped with filter wheels to allow selection of imaging
wavelengths for various purposes. The spectroscopic and wider band
infrared imaging capabilities originally proposed and incorporated in
the instrument name were descoped during development.
Instrument References: [KELLERETAL2006]
ROSINA
------
ROSINA (Rosetta Orbiter Spectrometer for Ion and Neutral Analysis)
consists of two mass spectrometers, since no one technique is able to
achieve the resolution and accuracy required to fulfil the ROSETTA
mission goals over the range of molecular masses under analysis. In
addition, two pressure gauges provide density and velocity data for
the cometary gas.
The two mass analysers are:
* A double focusing magnetic mass spectrometer with a mass range of 1
- 100 amu and a mass resolution of 3000 at 1 % peak height, optimised
for very high mass resolution and large dynamic range
* A reflectron type time-of-flight mass spectrometer with a mass
range of 1 -300 amu and a mass resolution better than 500 at 1 % peak
height, optimised for high sensitivity over a very broad mass range
Instrument References: [BALSIGERETAL2007]
RPC
---
RPC (Rosetta Plasma Consortium) is a set of five sensors sharing a
common electrical and data interface with the Rosetta orbiter. The
RPC sensors are designed to make complementary measurements of the
plasma environment around the comet 67P/Churyumov-Gerasimenko.
The RPC sensors are:
* ICA: an Ion Composition Analyser, which measures the three-
dimensional velocity distribution and mass distribution of positive
ions;
* IES: an Ion and Electron Sensor, which will simultaneously measure
the flux of electrons and ions in the plasma surrounding the comet;
* LAP: a Langmuir Probe, which will measure the density, temperature
and flow velocity of the cometary plasma;
* MAG: a Fluxgate Magnetometer, which will measure the magnetic field
in the region where the solar wind plasma interacts with the comet;
Instrument References: [GLASSMEIERETAL2007B]
* MIP: a Mutual Impedance Probe, which will derive the electron gas
density, temperature, and drift velocity in the inner coma of the
comet.
Instrument References: [CARRETAL2007]
RSI
---
RSI (Radio Science Investigation) makes use of the communication
system that the Rosetta spacecraft uses to communicate with the
ground stations on Earth. Either one-way or two-way radio links can
be used for the investigations. In the one-way case, a signal
generated by an ultra-stable oscillator on the spacecraft is received
on earth for analysis. In the two way case, a signal transmitted from
the ground station is transmitted back to Earth by the spacecraft. In
either case, the downlink may be performed in either X-band or both X
-band and S-band.
RSI will investigate the nondispersive frequency shifts (classical
Doppler) and dispersive frequency shifts (due to the ionised
propagation medium), the signal power and the polarization of the
radio carrier waves. Variations in these parameters will yield
information on the motion of the spacecraft, the perturbing forces
acting on the spacecraft and the propagation medium.
Instrument References: [PAETZOLDETAL2007]
VIRTIS
------
VIRTIS (Visible and Infrared Thermal Imaging Spectrometer) is an
imaging spectrometer that combines three data channels in one
instrument. Two of the data channels are committed to spectral
mapping and are housed in the Mapper optical subsystem. The third
channel is devoted solely to spectroscopy and is housed in the High
resolution optical subsystem.
The mapping channel optical system is a Shafer telescope consisting
of five aluminium mirrors mounted on an aluminium optical bench. The
mapping channel uses a silicon charge coupled device (CCD) to detect
wavelengths from 0.25 micron to 1 micron and a mercury cadmium
telluride (HgCdTe) infrared focal plane array (IRFPA) to detect from
0.95 micron to 5 microns.
The high resolution channel is an echelle spectrometer. The incident
light is collected by an off-axis parabolic mirror and then
collimated by another off-axis parabola before entering a cross-
dispersion prism. After exiting the prism, the light is diffracted by
a flat reflection grating, which disperses the light in a direction
perpendicular to the prism dispersion. The high-resolution channel
employs a HgCdTe IRFPA to perform detection from 2 to 5 microns.
Instrument References: [CORADINIETAL2007]
SREM
----
The Standard Radiation Environment Monitor (SREM) is a monitor-class
instrument intended for space radiation environment characterisation
and radiation housekeeping purposes. SREM will provide continuous
directional, temporal, and spectral data of high-energy electron,
proton, and cosmic ray fluxes encountered along the orbit of the
spacecraft, as well as measurements of the total accumulated
radiation dose absorbed by SREM itself.
This instrument is a facility monitor flown on several ESA
spacecrafts. It is not considered as a PI (Principal Investigator)
instrument.
Instrument References: [MOHAMMADZADEETAL2003]
LANDER (PHILAE)
=====================================================================
The 100 kg Rosetta Lander, named Philae, will be the first spacecraft
ever to make a soft landing on the surface of a comet nucleus. The
Lander is provided by a European consortium under the leadership of
the German Aerospace Research Institute (DLR) and the French Space
Research Center (CNES). Other members of the consortium are ESA and
institutes from Austria, Finland, France, Hungary, Ireland, Italy and
the UK. A descripion of the Lander can be found in [RO-EST-RS-3020].
The box-shaped Lander is carried in piggyback fashion on the side of
the Orbiter until it arrives at Comet 67P/Churyumov-Gerasimenko. Once
the Orbiter is aligned correctly, the ground station commands the
Lander to self-eject from the main spacecraft and unfold its three
legs, ready for a gentle touch down at the end of the ballistic
descent. On landing, the legs damp out most of the kinetic energy to
reduce the chance of bouncing, and they can rotate, lift or tilt to
return the Lander to an upright position.
Immediately after touchdown, a harpoon is fired to anchor the Lander
to the ground and prevent it escaping from the comet's extremely weak
gravity. The minimum mission target for scientific observations is
one week, but surface operations may continue for many months.
Science Objectives
------------------
It is the general aim of the scientific experiments carried and
operated by the Rosetta Lander to obtain a first in situ composition
analysis of primitive material from the early solar system, to study
the composition and structure of a cometary nucleus, reflecting
growth processes in the early solar system, to provide ground truth
data for the Rosetta Orbiter experiments and to investigate dynamic
processes leading to changes in cometary activity.
The primary objective of the Rosetta Lander mission is the in situ
investigation of the elemental, isotopic, molecular and mineralogic
composition and the morphology of early solar system material as it
is preserved in the cometary nucleus. Measurement of the absorption
and phase shift of electromagnetic waves penetrating the comet
nucleus will help to determine its internal structure. Seismometry
and magnetometry will also be used to investigate the interior of the
comet.
The scientific objectives of the Rosetta Lander can be listed
according to their priority as follows:
1. Determination of the composition of cometary surface and
subsurface matter: bulk elemental abundances, isotopic ratios,
minerals, ices, carbonaceous compounds, organics, volatiles - also
in dependence on time and insolation.
2. Investigation of the structure and physical properties of the
cometary surface: topography, texture, roughness, regolith scales,
mechanical, electrical, optical, and thermal properties,
temperatures. Characterization of the near surface plasma
environment.
3. Investigation of the global internal structure.
4. Investigation of the comet/plasma interaction.
The in situ measurements performed by the Rosetta Lander instruments
will also provide local ground truth to calibrate Orbiter
instruments.
Lander Experiments
------------------
The Rosetta-Lander is equipped with a Sample Drill & Distribution
(SD2) subsystem which is in charge to collect cometary surface
samples at given depth and distribute them to the following
instruments: CIVA-M (microscope (MS) & Infrared Spectrometer (IS)),
the ovens, serving COSAC and PTOLEMY.
Comet sample from pre-determinated and/or known (measured) depth are
collected and transported by SD2 to well defined locations:
* MS & IS viewing place
* ovens for high temperature (800 deg C) heating
* ovens for medium temperature (130 deg C) heating.
* ovens with a window, where samples can be investigated by CIVA-M
Here a description of all the instruments of the Lander:
APXS: Alpha-p-X-ray spectrometer
- - - - - - - - - - - - - - - -
The goal of the Rosetta APXS experiment is the determination of the
chemical composition of the landing site and its potential alteration
during the comet's approach to the Sun. The data obtained will be
used to characterize the surface of the comet, to determine the
chemical composition of the dust component, and to compare the dust
with known meteorite types.
Instrument References: [KLINGELHOFERETAL2007]
CIVA: Panoramic and microscopic imaging system
- - - - - - - - - - - - - - - - - - - - - - - -
The Cometary Infrared and Visible Analiser (CIVA) is an integrated
set of imaging instruments, designed to characterize the landing and
sampling site, the 360 deg panorama as seen from the Rosetta Lander,
all samples collected and delivered by the Drill Sample and
Distribution System, and the stratigraphy within the boreholes. It is
constituted by a panoramic stereo camera (CIVA-P), and a microscope
coupled to an IR spectrometer (CIVA-M). CIVA is sharing a common
Imaging Main Electronics (CIVA/ROLIS/IME) with ROLIS. CIVA-P will
characterize the landing site, from the landing legs to the local
horizon. The camera is composed of 6 identical micro-cameras, mounted
of the Lander sides, with their optical axes separated by 60 deg. In
addition, stereoscopic capability is provided by one additional micro-
camera, identical to and co-aligned with one of the panoramic micro-
camera, with its optical axis 10 cm apart.
CIVA-M combines in separated boxes, two ultra-compact and
miniaturized channels, one visible microscope CIVA-M/V and one IR
spectrometer CIVA-M/I, to characterize, by non-destructive analyses,
the texture, albedo, mineralogical and molecular composition of each
of the samples collected and distributed by the Drill Sample and
Distribution System.
Instrument References: [BIBRINGETAL2007A]
CONSERT: Radio sounding, nucleus tomography
- - - - - - - - - - - - - - - - - - - - - -
The Comet Nucleus Sounding Experiment by Radio wave Transmission
(CONSERT) is a complex experiment that will perform tomography of the
comet nucleus revealing its internal structure. CONSERT operates as a
time domain transponder between the Lander which will be on the comet
surface and the Orbiter will orbit the comet. A radio signal passes
from the orbiting component of the instrument to the component on the
comet surface and is then immediately transmitted back to its source,
the idea being to establish a radio link that passes through the
comet nucleus. The varying propagation delay as the radio waves pass
through different parts of the cometary nucleus will be used to
determine the dielectric properties of the nuclear material. Many
properties of the comet nucleus will be examined as its overall
structural homogeneity, the average size of the sub-structures
(Cometesimals) and the number and thickness of the various layers
beneath the surface.
Instrument References: [KOFMANETAL2007]
COSAC: Evolved gas analyser - elemental and molecular composition
- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -
The COmetary SAmpling and Composition experiment COSAC is one of the
two 'evolved gas analysers' (EGAs) on board the Rosetta-Lander.
Whereas the other EGA, Ptolemy, aims mainly at accurately measuring
isotopic ratios of light elements, the COSAC is specialised on
detection and identification of complex organic molecules. The
instrument can be described as an effort to analyse in situ, mainly
with respect to the composition of the volatile fraction, cometary
matter nearly as well and accurately as could be done in a laboratory
on Earth. Due to the Rosetta Lander rotatability, the instrument can
conduct analyses and investigations at different spots of the landing
site and, aided by the drill, take samples for analysis from a depth
up to at least 0.2 m.
Instrument References: [GOESMANNETAL2007]
PTOLEMY: Evolved gas analyser - isotopic composition
- - - - - - - - - - - - - - - - - - - - - - - - - - -
The size of a small shoe box and weighing less than 5 kg, Ptolemy
will use gas chromatography / mass spectrometry (GCMS) techniques to
investigate the comet surface & subsurface. The instrument concept is
termed 'MODULUS' which is taken to mean Methods Of Determining and
Understanding Light elements from Unequivocal Stable isotope
compositions. The scientific goal of the PTOLEMY is to understand the
geochemistry of light elements, such as hydrogen, carbon, nitrogen
and oxygen, by determining their nature, distribution and stable
isotopic compositions.
Instrument References: [WRIGHTETAL2007]
MUPUS: Measurements of surface and subsurface properties
- - - - - - - - - - - - - - - - - - - - - - - - - - - - -
The Multi-Purpose Sensor Experiment actually consists of four parts:
1. A penetrator, approximately 40 cm long, will be hammered into the
ground about 1m apart from the Lander for measuring during the
penetration process the mechanical strength of the material by means
of a depth sensor and a densitometer. The penetrator is equipped with
a series of temperature sensors and heaters for determining the
temperature as a function of depth and insolation.
2. An accelerometer and a temperature sensor accommodated in the
harpoon(s)
3. A four-channel infrared radiometer measures surface temperatures
in the vicinity of the Lander. Density of the nearsurface (down to
20cm) material will be determined by measuring the absorption of
gamma-rays emitted from a radioactive isotope mounted at the tip of
the penetrator.
Instrument References: [SPOHNETAL2007]
ROLIS: Descent & Down-Looking Imaging
- - - - - - - - - - - - - - - - - - -
The ROLIS Camera (Rosetta Lander Imaging System) will deliver first
close-ups of the environment of the landing place of comet
67P/Churyumov-Gerasimenko during the descent.
After landing ROLIS will make high-resolved investigations to study
the structure (morphology) and mineralogy of the surface.
Instrument References: [MOTTOLAETAL2007]
ROMAP: Magnetometer and plasma monitor
- - - - - - - - - - - - - - - - - - - -
The Rosetta Lander Magnetometer and Plasma Monitor ROMAP is a multi-
sensor experiment. The magnetic field is measured with a fluxgate
magnetometer. An electrostatic analyzer with integrated Faraday cup
measures ions and electrons. The local pressure is measured with
Pirani and Penning sensors. The sensors are situated on a short boom.
The deployment on the surface of a cometary nucleus demanded the
development of a special digital magnetometer of little weight and
small power requirements. For the first time a magnetic sensor will
be operated from within a plasma sensor. A prototype of the
magnetometer, named SPRUTMAG, was flown on space station MIR.
Instrument References: [AUSTERETAL2007]
SD2: Sampling, Drilling and Distribution Subsystem
- - - - - - - - - - - - - - - - - - - - - - - - - -
The sampling, drilling and distribution (SD2) subsystem will provide
microscopes and advanced gas analysers with samples collected at
different depths below the surface of the comet. Specifically SD2 can
bore up to 250 mm into the surface of the comet and collect samples
of material at predetermined and/or known depths. It then transports
each sample to a carousel which feeds samples to different instrument
stations: a spectrometer, a volume check plug, ovens for high and
medium temperatures and a cleaning station. SD2 will be accommodated
on the flat ground-plate of the Rosetta, where it will be exposed to
the cometary environment.
Instrument References: [ERCOLIFINZIETAL2007]
SESAME: Surface electrical, acoustic and dust impact monitoring
- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -
The SESAME (Surface Electrical, Seismic and Acoustic Monitoring
Experiments) electronics board and the integration of the components
are managed by the German Aerospace Center (DLR), Institute of Space
Simulation, Cologne.
The results of SESAME will help in understanding how comets, have
formed and thus, how the solar system, including the Earth, was born.
Instrument References: [SEIDENSTICKERETA2007]
GROUND SEGMENT
=====================================================================
This section summarizes the roles and responsabilities for the
Rosetta Ground Segment, which are defined in the Rosetta Science
Management Plan [RO-EST-PL-0001] and the Lander Project Plan
[RL-PL-DLR-97002].
The primary responsibility for developing the payload operations
strategy for the Rosetta Scientific Mission is the Rosetta Science
Working Team. The Rosetta Science Working Team (SWT) monitors and
advises on all aspects of Rosetta which affect its scientific
performance.
Rosetta Ground Segment
-----------------------
The Rosetta ground segment will consist of two major elements: the
Rosetta Mission Operations Centre (RMOC) and the Rosetta Science
Operations Centre
(RSOC).
Rosetta Science Operations Center
- - - - - - - - - - - - - - - - - -
The Rosetta Science Operations Center (RSOC) is located at the
European Space Research and Technology Center (ESTEC) in The
Netherlands. The main task is to support the Rosetta Project
Scientist in the planning of the science operations schedule and in
the generation of coordinated operational sequences, the payload
command sequences for all Rosetta instruments and their onward
transmission to the Rosetta Mission Operations Centre (RMOC). In
addition, the RSOC will prepare comet nucleus and comet coma models
in collaboration with the Interdisciplinary Scientists, specialists
from the Principal Investigator teams and the Lander teams.
Rosetta Mission Operations Center
- - - - - - - - - - - - - - - - - -
The Rosetta Mission Operations Center (RMOC) is located at the
European Space Operations Center (ESOC) in Darmstadt, Germany. The
RMOC is responsible for the Spacecraft operations and all real time
contacts with the spacecraft and payload, the overall mission
planing, flight dynamics and spacecraft and payload data
distribution.
Rosetta Lander Ground Segment
------------------------------
The Rosetta Lander Ground Segment (RLGS) is made up of two
operational teams. Due to the discussions when CNES joined the DLR
consortium for developing the Lander, it was decided to divide the
RLGS into 2 centers (see Lander Project Plan [RL-PL-DLR-97002]).
These teams are responsible for the success of the Lander operations,
to ensure that the Lander performs the science with regards to its
status, and to give the data to the PI's and suppliers.
Lander Control Center
- - - - - - - - - - - -
The Lander Control Center (LCC), located at DLR/MUSC in Koeln
(Germany), in charge of Rosetta Lander operations during the flight
segment definition, design, realization, assembly and tests.
Science Operations and Navigation Center
- - - - - - - - - - - - - - - - - - - - -
The Science Operations and Navigation Center is under CNES
responsibility, located in Toulouse (France). It is responsible for
the navigation and mission analysis aspects, including separation,
landing and descent strategies and generation of the scientific
sequences.
Rosetta Scientific Data Archive
--------------------------------
All scientific data obtained during the full mission duration will
remain proprietary of the PI teams and the Lander teams for a maximum
period of one year after they have been received from ESOC. After
this period, the scientific data products from the mission have to be
submitted to RSOC in a reduced and calibrated form such that they can
be used by the scientific community. RSOC will prepare the Rosetta
Scientific Data Archive within one year of the receipt of the
complete data sets from the individual Rosetta science
investigations.
Acronyms
--------
For more acronyms refer to Rosetta Project Glossary [RO-EST-LI-5012]
ATTC Absolute Time Telecommand
AU Astronomical Unit
CAP Comet Acquisition Point
CAT Close Approach Trajectory
CNES Centre National d'Etudes Spatiales
COP Close Observation Phase
DLR German Aerospace Center
DSM Deep Space Manouver
ESA European Space Agency
ESOC European Space Operations Center
ESTEC European Space Research and Technology Center
EUV Extreme UltraViolet
FAT Far approach trajectory
FUV Far UltraViolet
GCMS Gas Chromatography / Mass Spectrometry
GMP Global Mapping Phase
HGA High Gain Antenna
HgCdTe Mercury Cadmium Telluride
HIGH High Activity Phase (Escort Phase)
HK HouseKeeping
IRAS InfraRed Astronomical Satellite
IRFPA Infrared Focal Plane Array
IS Infrared Spectrometer
LCC Lander Control Center
LDL Long Debye Length
LEOP Launch and Early Orbit Phase
LOW Low Activity Phase (Escort Phase)
LTE Local Thermodynamic Equilibrium
MINC Moderate Increase Phase (Escort Phase)
MGA Medium Gain Antenna
MLI Multi Layer Insulation
MS Microscope
NNO New Norcia ground station
OIP Orbit Insertion Point
PI Principal Investigator
P/L PayLoad
PC Payload Chackout
RF Radio Frequency
RMOC Rosetta Mission Operations Center
RLGS Rosetta Lander Ground Segment
RL Rosetta Lander
RO Rosetta Orbiter
RSOC Rosetta Science Operations Center
RVM Rendez-vous Manouver
S/C SpaceCraft
SINC Sharp Increase Phase (Escort Phase)
SONC Science Operations and Navigation Center
SSP Surface Science Package
STR Star TRacker
SWT Science Working Team
TGM Transition to global mapping
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