| Description |
Overview: ========= The Electron Spectrometer (ELS) provides in situ electron measurements in the energy range 0.05 eV to 20 keV to help satisfy the following scientific objectives: 1. Determine the instantaneous global distributions of plasma and neutral gas near Mars by providing undisturbed solar wind parameters 2. Define the local characteristics of the main plasma regions 3. Complement the ENA images Parameters: =========== All ELS data products have the same format and parameters, and each row (data file record) in the ELS SPREADSHEET data products has eight (8) COLUMN objects (parameters): 1. Start Time - Begin Date/Time in UTC of data samples 2. Stop Time - Ending Date/Time in UTC of data samples 3. Data Type Name - SENSOR, SCAN, or MODE. The SENSOR rows are the ELS science data for each sector (16 sectors). The SCAN rows are the deflection voltages (volts) that correspond to the SENSOR rows. There is one SCAN row per 16 SENSOR rows. The 16 SENSOR rows are followed by one corresponding SCAN row. The SCAN row indicates the deflection voltage per step that corresponds to the previous 16 SENSOR rows for each step. To convert the deflection voltages to center energies (eV), use the K_FACTOR per anode in the calibration tables: eV = volt * K_FACTOR. There are 16 SENSOR rows + 1 SCAN row (17 in all) followed by 23 rows of MODE data for the same time period. The MODE rows contain informational data such as Time/Step Summations and Sector Enable Flags. 4. Data Type Id - Numeric ID indicating SENSOR, SCAN, or MODE. 5. Data Name - Short description for data on that row. For example ELS Sector 0 LR for ELS sector 0 Low Range science data (SENSOR rows for ELSSCIL data products), ELS Sector 0 HR for ELS sector 0 High Range science data (SENSOR rows for ELSSCIH data products), Deflection Potential for SCAN rows, or Time Summation for informational data (MODE row). 6. Data Unit - Indicates the data unit: cnts/(cm**2-sr-sec-eV) for SENSOR data volt for SCAN data Unitless for MODE data 7. Values - These are the actual data values. For this column there are multiple values as indicated by the ITEMS keyword in the label files. This value will vary from file to file, but remains consistent within a data (.CSV) file. For the SENSOR rows, these are the science data sampled at the corresponding deflection volts indicated in the corresponding SCAN row that follows the 16 ELS sector (SENSOR rows) data. The MODE data rows contain only one value each and remaining ITEMS are indicated missing with commas (value,,...,,). Please note that the data values are formatted for a high level of accuracy, and that this does not indicate the accuracy of the ELS instrumentation. 8. Data Quality Value - Quality indicator for the data on that row. The data quality value is only applicable for the SENSOR data. See CONFIDENCE_LEVEL_NOTE under Data Coverage/Quality for valid values and descriptions. Data Products: ============== The Standard Data Products for ELS PSA Level 2 (RDR) products are: 1. ELSSCIL_DNF - ELectron Spectrometer SCIence Low range data in Differential Number Flux units. 2. ELSSCIH_DNF - ELectron Spectrometer SCIence High range data in Differential Number Flux units. NOTE: There is not a one-to-one correspondence between the ELSSCIL and ELSSCIH data products. Most of the time, both products are produced for the same time period. However, there are times when only ELSSCIL products are produced or only ELSSCIH products are produced, not both. Ancillary Data: =============== It is important for ASPERA-3 science studies to know where in space and time the Mars Express spacecraft and ASPERA-3 instruments are located and what objects (Sun, Mars, Earth, Phobos, Deimos) are in the fields of views. The ASPERA-3 view directions for each sensor can be derived using the SPICE kernels and software. The ASPERA-3 Sensor Frames and Geometry Information document (in DOCUMENT directory) provides a code example (in C and FORTRAN) for determining the view directions for the ASPERA-3 sensors. Coordinate System: ================== The ASPERA-3 data are always in the instrument reference frame since data are sampled in situ. The GEOMETRY table contains spacecraft related parameters expressed in the J2000 reference frame, and the ASPERA-3 Sensor Frames and Geometry Information document (in DOCUMENT directory) provides information for determining the ASPERA-3 sensors view directions and transforming to the J2000 reference frame. References: =========== Refer to the ASPERA-3 Experiment to Archive Interface Control Document (EAICD) found in the DOCUMENT directory (MEX_ASPERA3_PSA_ICD_V01_03) for more information and detail concerning data set formulation and contents. |
| Mission Description |
Mission Overview ================ Mars Express was the first flexible mission of the revised long-term ESA Science Programme Horizons 2000 and was launched to the planet Mars from Baikonur (Kazakhstan) on June 2nd 2003. A Soyuz-Fregat launcher injected the Mars Express total mass of about 1200 kg into Mars transfer orbit. Details about the mission launch sequence and profile can be obtained from the Mission Plan (MEX-MMT-RP-0221) and from the Consolidated Report on Mission Analysis (CREMA)(MEX-ESC-RP- 5500). The mission consisted of (i) a 3-axis stabilized orbiter with a fixed high-gain antenna and body-mounted instruments, and (ii) a lander named BEAGLE-2, and was dedicated to the orbital and in-situ study of the interior, subsurface, surface and atmosphere of the planet. After ejection of a small lander on 18 December 2003 and Mars orbit insertion (MOI) on 25 December 2003, the orbiter experiments began the acquisition of scientific data from Mars and its environment in a polar elliptical orbit. The nominal mission lifetime for the orbiter was 687 days following Mars orbit insertion, starting after a 5 months cruise. The nominal science phase was extended (tbc) for another Martian year in order to complement earlier observations and allow data relay communications for various potential Mars landers up to 2008, provided that the spacecraft resources permit it. The Mars Express spacecraft represented the core of the mission, being scientifically justified on its own by investigations such as high- resolution imaging and mineralogical mapping of the surface, radar sounding of the subsurface structure down to the permafrost, precise determination of the atmospheric circulation and composition, and study of the interaction of the atmosphere with the interplanetary medium. The broad scientific objectives of the orbiter payload are briefly listed thereafter and are given more extensively in the experiment publications contained in ESAs Special Publication Series. See NEUKUM&JAUMANN2004, BIBRINGETAL2004, PICARDIETAL2004, FORMISANOETAL2004, BERTAUXETAL2004, PAETZOLDETAL2004 and PULLANETAL2004. The Mars Express lander Beagle-2 was ejected towards the Mars surface on 19 December 2003, six days before the orbiters capture manoeuvre. The probe mass was limited to about 70 kg by the mission constraints, which led to a landed mass of 32 kg. The complete experimental package was weighed in approximately at 9kg. The landers highly integrated scientific payload was supposed to focus on finding whether there is convincing evidence for past life on Mars or assessing if the conditions were ever suitable. Following safe landing on Mars, this lander mission would have conducted dedicated studies of the geology, mineralogy, geochemistry, meteorology and exobiology of the immediate landing site located in Isidis Planitia (90.74deg E, 11.6deg N), as well as studies of the chemistry of the Martian atmosphere. Surface operations were planned to last about 180 sols or Martian days (about 6 months on Earth), see SIMSETAL1999. As no communication could be established to the BEAGLE-2 lander, it was considered lost in February 2004 after an extensive search. A nominal launch of Mars Express allowed the modify the orbit to a G3-ubeq100 orbit. The G3-ubeq100 orbit is an elliptical orbit, starting with the sub-spacecraft point at pericentre at the equator and a sun ^ation of 60 degrees. At the beginning of the mission, the pericentre moves southward with a shift of 0.54 degree per day. At the same time the pericentre steps towards the terminator which will be reached after about 4 months, giving the optical instruments optimal observing conditions during this initial period. Throughout this initial phase lasting until mid- May 2004, the downlink rate will decrease from 114 kbit/s to 38 kbit/s. After an orbit change manoeuvre on 06 May 2004 the pericentre latitude motion is increased to guarantee a 50/50 balance between dayside and nightside operations. With this manoeuvre, the apocentre altitude is lowered from 14887 km to 13448 km, the orbital period lowered from ~7.6 hours to 6.645 hours, and the pericentre latitude drift slightly increased to 0.64 degree per day. After 150 days, at the beginning of June 2004, the South pole region was reached with the pericentre already behind the terminator. Following, the pericentre moves northward with the Sun ^ation increasing. Thus, the optical instruments covered the Northern Mars hemisphere under good illumination conditions from mid-September 2004 to March 2005. During the next mission phase, lasting until July 2005, the pericentre was again in the dark. It covered the North polar region and moves southward. Finally, throughout the last 4 months of the nominal mission, the pericentre was back to daylight and moves from the equator to the South pole, and the downlink rate reached its highest rate of 228 kbit/s. The osculating orbit elements for the eq100 orbit are listed below: Epoch 2004:1:13 - 15:56:0.096 Pericentre (rel. sphere of 3397.2 km) 279.29 km Apocentre (rel. sphere) 11634.48 km Semimajor axis 9354.09 km Eccentricity 0.60696 Inclination 86.583 Right ascension of ascending node 228.774 Argument of pericentre 357.981 True anomaly -0.001 Mission Phases ============== The mission phases are defined as: (i) Pre-launch, Launch and Early Operations activities, including (1) science observation planning; (2) payload assembly, integration and testing; (3) payload data processing software design, development and testing; (4) payload calibration; (5) data archive definition and planning; (6) launch campaign. (ii) Near-Earth verification (EV) phase, including (1) commissioning of the orbiter spacecraft; (2) verification of the payload status; (3) early commissioning of payload. (iii) Interplanetary cruise (IC) phase (1) payload checkouts (2) trajectory corrections (iv) Mars arrival and orbit insertion (MOI) (1) Mars arrival preparation; (2) lander ejection; (3) orbit insertion; (4) operational orbit reached and declared; (5) no payload activities. (v) Mars commissioning phase (1) final instrument commissioning, (2) first science results, (3) change of orbital plane. (vi) Routine phase; Opportunities for dawn/dusk observations, mostly spectroscopy and photometry. This phase continued into a low data rate phase (night time; favorable for radar and spectrometers). Then daylight time, and went into a higher data rate period (medium illumination, zenith, then decreasing illumination conditions). Observational conditions were most favorable for the optical imaging instruments at the end of the routine phase, when both data downlink rate and Sun ^ation are high. (vii) MARSIS Deployment The dates of the MARSIS antenna deployment is not known as of writing this catalogue file. (viii) Extended operations phase A mission extension will be proposed in early 2005 to the Science Programme Committee (SPC). (ix) Post-mission phase (final data archival). Science Subphases ================= For the purpose of structuring further the payload operations planning, the mission phases are further divided into science subphases. The science subphases are defined according to operational restrictions, the main operational restrictions being the downlink rate and the Sun ^ation. The Mars Commissioning Phase and the Mars Routine Phase are therefore divided into a number of science subphases using various combinations of Sun ^ations and available downlink bit rates. The discrete downlink rates available throughout the nominal mission are: - 28 kbits/seconds - 38 kbits/seconds - 45 kbits/seconds - 57 kbits/seconds - 76 kbits/seconds - 91 kbits/seconds - 114 kbits/seconds - 152 kbits/seconds - 182 kbits/seconds - 228 kbits/seconds The adopted Sun ^ation coding convention is as follows: - HSE for High Sun Elevation (> 60 degrees) - MSE for Medium Sun Elevation (between 20 and 60 degrees) - LSE for Low Sun Elevation (between -15 and 20 degrees) - NSE for Negative Sun Elevation (< -15 degrees) The science subphase naming convention is as follows: - Science Phase - Sun Elevation Code - Downlink Rate - Science Subphase Repetition Number The following tables gives the available Science Subphases: NAME START END ORBITS BIT SUN RATE ELE ---------------------------------------------------------- MC Phase 0 2003-12-30 - 2004-01-13 1 - 16 MC Phase 1 2004-01-13 - 2004-01-28 17 - 58 114 59 MC Phase 2 2004-01-28 - 2004-02-12 59 - 105 91 69 MC Phase 3 2004-02-12 - 2004-03-15 106 - 208 76 71 MC Phase 4 2004-03-15 - 2004-04-06 209 - 278 57 51 MC Phase 5 2004-04-06 - 2004-04-20 279 - 320 45 33 MC Phase 6 2004-04-20 - 2004-06-04 321 - 475 38 22 MR Phase 1 2004-06-05 - 2004-08-16 476 - 733 28 -13 MR Phase 2 2004-08-16 - 2004-10-16 734 - 951 28 -26 MR Phase 3 2004-10-16 - 2005-01-07 952 - 1250 28 16 MR Phase 4 2004-01-08 - 2005-03-05 1251 - 1454 45 63 MR Phase 5 2004-03-05 - 2005-03-24 1455 - 1522 76 16 MR Phase 6 2004-03-25 - 2005-07-15 1523 - 1915 91 0 The data rate is given in kbit per seconds and represents the minimal data rate during the subphase. The sun ^ation is given in degrees and represents the rate at the beginning of the subphase. Detailed information on the science subphases can be found in MEX-EST-PL-13128. |
