| MAJ_MainRING _PhaseCurve | Observations of the main rings at various phase angles (N angles), one ansae (always the same), 20 vertical lines
Pointing: S/C pointing ring plane at 1.8 R_J (extremity of main rings)
Satellite orientation: OFF-NADIR, Ring plane while maintaining horizontal orientation of MAJIS slit, MAJIS scan mode activated for vertical sampling centered on the rings (20 lines)
Duration: 200 sec for one observations at a given phase angle | MAJIS |
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| MAJ_Ring_Occultation | Observation of a star occulted by the rings
Scan windowing of 9 lines centered on the star (1 scan step = 1/3 MAJIS IFOV) possible
Pointing: Inertial. For each occultation, transit of TBD min
Satellite orientation: Inertial pointing of the S/C towards the position of the star to maintain MAJIS slit fixed on it. These occultation observations need to be consolidated in the future (star atlas, signal, Tint, S/C inertial capabilities). Scan mirror can be used to mitigate APE drift | MAJIS |
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| MAJ_SAFE | Initiated after ASW loading
All channels are off and no PE HK are generated. Only ME HK are generated (only DPU ON)
From SAFE it is possible 1) to switch OFF MAJIS, 2) to change the status of MAJIS to DIAG1 or SERVICE mode
Duration: less than 5min | MAJIS |
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| MAJ_SAT_DISK_SCAN | Observation of a distant satellite dayside or nightside surface. Satellite offset required for pointing then disk coverage is achieved using the internal pointing mirror scanning in the Y (N-S) direction.
Pointing: NADIR-P with possible offset around Y, YS, MAJIS scan (‘Nadir scan’).
Satellite orientation: MAJIS slit perpendicular to the ground-track
Duration: 30min | MAJIS |
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| MAJ_SAT_DISK_SLEW | Flyby observations of the satellite surface with vertical (N-S) slews across track, during yaw-steering phase. One or two slews (pole to pole) necessary to complete dayside coverage. Satellite offset around Y-axis (E-W) before each observation, then satellite offsets around X axis (N-S) between each slit acquisition.
Pointing: NADIR Pointing, YS, S/C scan (slew) with offset around Y (‘mosaic mode’ tbc). MAJIS slit perpendicular to the ground-track.
Satellite orientation: MAJIS slit perpendicular to the ground-track
Duration: 30 min | MAJIS |
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| MAJ_SAT_LIMB_SCAN | Flyby observations of the satellite dayside or nightside limbs with vertical (N-S) slews across track, during yaw-steering phase. Satellite offsets to limb around Y-axis (E-W) before each observation, then satellite offsets around X axis (N-S) between each slit acquisition or continuous slew pointing.
Pointing: S/C slew scan centred a limb ( ‘Limb slew scan mode’).
Satelliteo orientation: Slit tangent to the limb
Duration: 60min | MAJIS |
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| MAJ_SAT_LIMB_TRACK | Continuous stare observation of a satellite limb during flyby using inertial pointing from satellite, dayside or nightside. Additional offsets within limb by means of internal pointing mirror. Scanning with MAJIS internal mirror. (--> ‘track limb’).
Pointing: S/C limb tracking (‘track limb’)
satellite otientation: SLIT tangent to the limb (slit not aligned with S/C motion)
Duration: 60min | MAJIS |
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| MAJ_SERVICE | MAJIS in service MODE (1 or 2 channels with FPE/FPA off + AUX w/o loads)
SERVICE Mode as soon as one or two channels are switched ON (PE and AUX)
From SERVICE, it is possible to return to SAFE mode or to change the status of MAJIS to DIAG2, DIAG3 or SCIENCE
Duration: less than 10min | MAJIS |
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| MAJ_STANDBY | After switch-on of MAJIS, the Boot SW automatically starts, and performs the primary boot from the PROM (Init fugitive BSW mode).
After processor modules initialization, the Boot software goes to STANDBY mode. By default, the ASW Image0 (stored in MRAM0 = ASM0) is autonomously loaded after a timeout of 30 seconds. MAJIS then enters into ASW init Mode and then into SAFE mode.
In STANDBY Mode, all channels are off, and only DPU HK SID1 are received.
MAJIS needs to be maintained in STANDBY mode using the TC(17,1) in the following cases :
- upload (using service 6) of new ASW images (or CUSW, or firmware) into MRAM: FCP-MAJ-070 describes the maintenance process.
- upload a new BROWSE Table FCP-MAJ-060 into MRAM
- select ASW Image1 and then start ASW Image 1 instead of teh default ASW Image0. FCP-MAJ-062
- any other update of MRAM using service 6 | MAJIS |
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| JAN_CONFIG_ALLOFF | No observations, but instrument ON for thermal stabilization of the complete electronics (PEU and detector are OFF) and for setting the observation sequences and between two observation sequences that are too close to switch the detector OFF. | JANUS |
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| JAN_CONFIG_ALLON | No observations, but instrument ON for thermal stabilization of the complete electronics (PEU and detector are ON) and for setting the observation sequences and between two observation sequences that are too close to switch the detector OFF. | JANUS |
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| JAN_IDLE | No observations, but instrument ON for thermal stabilization before observations or between two observation phases that are too close to switch the instrument OFF. | JANUS |
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| JAN_OFF | No observations, instrument OFF. | JANUS |
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| JAN_SCI_INERTIAL | TBW | JANUS |
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| JAN_SCI_LIMB | Children observations defined during scenarios
│ ├── JAN_SCI_LIMB_HAZES
│ ├── JAN_SCI_LIMB_HIGHPHASE
│ ├── JAN_SCI_LIMB_POLAR_SOUTH | JANUS |
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| JAN_SCI_PB | Observations of single or multiple frames with a pointing offset wrt to nominal S/C pointing (e.g., wrt nadir-looking while in G orbit, during FB or while in Jupiter orbit) | JANUS |
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| JAN_SCI_RASTER | Observations of multiple frames in (m x n) positions targeted with a raster pointing of the S/C. The raster is done with a stop-and-go approach: the S/C maintain an inertial pointing allowing images acquisitions, then perform a slew to the new position and repeat the cycle till the (m x n) raster is completed. To be used while in J orbit or during FBs (out from CA phase).
Children observation defined during scenarios:
│ ├── JAN_SCI_RASTER_AMALTHEA_HIGH_RES
│ ├── JAN_SCI_RASTER_AURORAS
│ ├── JAN_SCI_RASTER_FEATURES
│ ├── JAN_SCI_RASTER_GLOBAL_MAP
│ ├── JAN_SCI_RASTER_HIGH_RES_MAP_JOINED_SET_003_S007_01_S00P01.def
│ ├── JAN_SCI_RASTER_HIGH_RES_MAP
│ ├── JAN_SCI_RASTER_IO_TRANSIT_001_PART_1_S007_01_S00P01.def (name non compliant)
│ ├── JAN_SCI_RASTER_IO_TRANSIT_001_PART_2_S007_01_S00P01.def (name non compliant)
│ ├── JAN_SCI_RASTER_IO_TRANSIT_001_S007_01_S00P01.def
│ ├── JAN_SCI_RASTER_LIGHTING_MAP
│ ├── JAN_SCI_RASTER_POLAR_SOUTH | JANUS |
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| JAN_SCI_SLEW | Observations of multiple frames in (m x n) positions targeted with a raster pointing of the S/C made with a continuous slew. The raster is done with continuous slew approach: images are acquired while the S/C is slewing; slew rate shall be adapted with the instrument angular sampling and the integration time. To be used while in J orbit or during FBs (out from CA phase) | JANUS |
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| GAL_FULLSCIENCE_FLYBY | Primary full science for flyby operations during closest approach. | GALA |
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| GAL_GAN_OFF_POINTING | science mode for Ganymede off-nadir operations. | GALA |
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| GAL_HR_TARGET_GAN | Additional science mode for Ganymede operations | GALA |
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| GAL_IDLE | Idle operations. | GALA |
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| GAL_LR_FB_ALBEDO | Passive albedo operations for flybys – before or after closest approach | GALA |
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| GAL_MONITORING_GAN | Primary science mode for Ganymede operations | GALA |
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| GAL_WARMUP_GAN | Active operation for laser warmup. This observation shall be used before real science measurements, e.g. before closest approach. | GALA |
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| 3GM_BISTATIC_RADAR | Characterization of the surface by determination of roughness, dielectric constant of surface material and material density. The chosen antenna points towards surface, radio signal reflects from surface and received on ground. USO unmuted. The HAA shall be in SCIENCE to calibrate the sloshing potentially excited by pointing the HGA toward a moon’s Surface. | 3GM |
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| 3GM_GRAVITY_FLYBYS | Gravity measurement during flyby requires the use of the MGA.
KaT and HAA should be operating during gravity measurements
USO assumed to be ON during the full tour: this should be defined in the scenario set-up and not at 3GM observation approach.
HAA should be in CONFIGURATION mode at least 48 hours before the gravity measurement.
The observation should start with 1 hour of HAA in SELF_CALIBRATION mode. KaT starts with 10min of warm-up.
Additional X/X and X/Ka (DST) link may be required whenever the Sun-
Earth-Spacecraft angle is < 60 deg to cancel noise due to the solar wind plasma. | 3GM |
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| 3GM_GRAVITY_GCO500_200 | Gravity measurement during GCO500 and GCO200 will use the HGA during downlink sessions. If not possible, it will use the MGA. KaT and HAA should be operating during gravity measurement. USO is OFF during this phase (except in case of BSR opportunity). HAA should be in STANDBY mode at least 48 hours before the gravity measurement. The observation should start with 1 hour of HAA in SELF_CALIBRATION mode. KaT starts with 10min of warm-up. | 3GM |
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| 3GM_GRAVITY_TOUR | Gravity measurement during flyby requires the use of the HGA.
KaT and HAA should be operating during gravity measurement
USO assumed to be ON during the full tour: this should be defined in the scenario set-up and not at 3GM observation approach.
HAA should be in CONFIGURATION mode at least 48 hours before the gravity measurement.
The observation should start with 1 hour of HAA in SELF_CALIBRATION mode. KaT starts with 10min of warm-up.
Additional X/X and X/Ka (DST) link may be required whenever the Sun-
Earth-Spacecraft angle is < 60 deg to cancel noise due to the solar wind plasma | 3GM |
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| 3GM_IO_PLASMA_TORUS_OCCULTATION | The radio science experiment 3GM will use navigation data in X/X and X/Ka band to characterize the Io plasma torus. The data generated by the DST in 2-way dual-frequency radio links will be the primary observable to perform this investigation. Occultations occur throughout the jovian tour, but their phasing is not always synchronized with the timing of dedicated Jupiter observations by the other orbiter experiments. USO will stay MUTED and HAA in nominal SCIENCE.
Note that other observation strategy would be possible (2-way triple link, 1-way X and Ka link with USO UNMUTED). | 3GM |
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| 3GM_JUPITER_OCCULTATION | The radio science experiment 3GM, with its 1-way dual-frequency radio links (X and Ka-band) referenced to an ultrastable oscillator (USO), is performed as JUICE spacecraft moves in and out of occultation. Occultations occur throughout the jovian tour, but their phasing is not always synchronized with the timing of dedicated Jupiter observations by the other orbiter experiments. USO unmuted, HAA in nominal SCIENCE. | 3GM |
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