Uplinked the daily Master Command Loads and Ephemeris.
Loaded and dumped the SCSs in preparation for the GNC Sensor Calibrations (Pitch maneuver). A positive 25 degree Pitch maneuver was performed first (maneuver start 1445z), followed by a negative 25 degree Yaw maneuver (maneuver start 1945z). The maneuvers are being performed as part of the IRU calibration.
Loaded and dumped the SCSs in preparation for the GNC Sensor Calibrations (Roll maneuver). A positive 25 degree Roll maneuver was performed first (maneuver start 0219z), followed by a negative 25 degree Roll maneuver (maneuver start 0534z). The negative Roll maneuver was aborted after reaching the dwell attitude (see Anomaly description #3).
Science data processing status: HSB Level 0 science data has been received by the JPL DAAC. Processing of the HSB data to Level 1A has been delayed until after the initial AMSU data processing is complete.
The following activities are scheduled for the next 24 hours:
The AMSR-E sensor has been rotating at 4 rpm since launch + 6 hours. Over the next 3 days the speed will be gradually increased to the operational rate of 40 rpm. Over the next 24 hours the rate will be increased in two phases: from 4 to 12 rpm, then from 12 to 18 rpm.
Aqua Spacecraft Status:
Spacecraft State is currently Standby.
GNC Mode is Fine Point Mode, HiFi Ephemeris.
Aqua Instrument Status:
AIRS is in Decontaminate state, Quiet bus is ON, Noisy bus is ON, Cryocooler is OFF, Scan mirror rotating is OFF and earth shield is CLOSED.
AMSR-E is in Modified Sleep mode, rotating at 4 RPM.
AMSU A1 is in Full Scan mode.
AMSU A2 is in Full Scan mode.
CERES Aft is in Safe mode and the covers are CLOSED.
CERES Fore is in Safe mode and the covers are CLOSED.
HSB is in Scan Normal mode and the antenna is in the TARGET position.
MODIS is in Standby mode, Nadir Door is Unlatched and CLOSED, Solar Diffuser Door is Unlatched and CLOSED, and the Space View Door is Unlatched and CLOSED.
Continuing to evaluate the apparent misalignment of approximately 0.2 degrees between Star Tracker Assembly (STA) 1 and STA2. A review of the mechanics associated with translating alignment measurement data into rotation matrices has been completed. No consequential discrepancies were found, working with Ball this week, to review the Star Tracker alignment data and conventions. The actions stated in the May 10 daily continue.
A patch has been developed to address the timing issue between the CTC and the USO. The patch was successfully loaded and demonstrated 5/16/02 @ 0200Z. All indications show the frequency is close to expected value. Final adjustments will be made to achieve the proper clock configuration.
The GNC Sensor Calibration Negative Roll maneuver was aborted after reaching the dwell attitude, due to operator error. Flight Dynamics was only able to gather 5.46 minutes of dwell data instead of the scheduled 10 minutes. The spacecraft was commanded to fine point mode gains and returned to nadir. At no time was spacecraft health and safety at risk. Flight Dynamics has determined that they received enough data to achieve their analysis and no further GNC Sensor Calibrations are required.