NOAA Office of Satellite and Product Operations

NOAA 16 ADACS Subsystem Summary

Component Status:

Component
Description
Status
ESAEarth Sensor AssemblyGreen
GYRO 1Gyroscopic Rate Measuring Device #1 (YA, ZA)Red
GYRO 2Gyroscopic Rate Measuring Device #2 (XA, ZB)Green
GYRO 3Gyroscopic Rate Measuring Device #3 (XB, YB)Yellow
IMUInertial Measurement UnitGreen
PTC 1APitch Torque Coil 1AGreen
PTC 1BPitch Torque Coil 1BGreen
PTC 2APitch Torque Coil 2AGreen
PTC 2BPitch Torque Coil 2BGreen
RWA SSkew Reaction Wheel AssemblyGreen
RWA XX-axis Reaction Wheel AssemblyGreen
RWA YY-axis Reaction Wheel AssemblyGreen
RWA ZZ-axis Reaction Wheel AssemblyGreen
RYTC 1ARoll-Yaw Torque Coil 1AGreen
RYTC 1BRoll-Yaw Torque Coil 1bGreen
RYTC 2ARoll-Yaw Torque Coil 2AGreen
RYTC 2BRoll-Yaw Torque Coil 2BGreen
SSASun Sensor AssemblyGreen

Subsystem History:

Date Time Component Description
11/15/201214:54:35 Restored CPUTLM1 after GYE complete.
11/15/201214:53:03 Ended GYROLESS test.
11/14/201213:27:02 Started GYROLESS test.
11/14/201213:25:06 Upload to get YRP rates and ADAYAW in CPUTLM1, replacing EPHTIME and CMDTIME.
03/25/200619:36:00GYRO 2N16 Gyro-2 spin motor current surged 7 mAmps but returned to its nominal 64 mAmps within 8 minutes. TCA voltage increased with spin motor current. IMU block temp and all other ADACS components not affected.
03/16/200620:14:00 IMU logic backup function inhibit
03/16/200620:13:00 IMU logic backup function inhibit
03/16/200620:10:00GYRO 2To proactively prevent gyro-2 from stalling, uploaded and activated safing macro to monitor gyro-2 spin motor current and turn off power to gyro-2 if that current exceeds 160 mAmps. Also inhibited IMU autonomous switching.
03/13/200617:17:00GYRO 2N16 Gyro-2 spin motor current surged 10 mAmps (from 63 to 73) then retreated to a new equilibrium of 64 mAmps at 17:29z. TCA voltage increased in conjunction with spin motor current. IMU block temp and all other ADACS components apparently not affected.
03/09/200621:43:00 Change N2 gas unloading trigger on pitch axis momentum to 145 in/lb/sec (from 40) absolute.CONTROL side
03/09/200621:41:00 Change N2 gas unloading trigger on pitch axis momentum to 145 in/lb/sec (from 40) absolute.Non-control side
01/17/200614:55:00 Increase pitch RWA bias from 1500 RPM to 2400 RPM
12/15/200519:15:00RWA ZSet pitch RWA bias to 1500 RPM to provide stiffness to attitude control in case final gyro becomes non-functional.
12/08/200515:53:00 Enable IMU logic switching, control CPU
12/08/200515:52:00 Enable IMU logic switching, non-control CPU
11/17/200516:35:00GYRO 2Flight software updated to reduce gyro filter gains and clean up roll attitude signal implemented. Operation successful, objective achieved.
11/08/200521:40:00 Update to MODE software module to change Gyro 1 on command pulse to a Gyro 2 on command pulse
10/25/200500:30:00 Command non control side to Reduced Gyro attitude control mode.
10/24/200522:55:00 N16 attitude control now running in reduced gyro (RGYRO) mode (estimated Y-axis/roll) and is expected to remain that way for the remainder of the mission. IMU switch capability remains disabled pending FSW alterations.
10/24/200522:50:00GYRO 1Gyro-1 "slipped a pole" at 15:00z causing an IMU logic switch which then masked RED HIGH spin motor currents on both gyro-1 and 2. Gyro-1 complete failure considered imminent. IMU-AC power supplies toggled and gyro-1 was powered off. Gyro-1 downgraded to RED status. ADACS downgraded to YELLOW status.
10/24/200522:50:00GYRO 1Permanently power off Gyro-1 after placing spacecraft ADACS in Reduced Gyro Mode, and toggling IMU AC power supplies.
10/24/200515:00:01IMUIMU switched to Primary (from Backup which it had always been since launch) after gyro spin motor current surge.
10/24/200515:00:00GYRO 1Gyro-1 spin motor current surged 100% above normal then quickly fell to 20% below normal (yellow low value) causing IMU switch.
08/30/200500:31:00 N16 donwgraded to secondary PM spacecraft after N18 declared operational.
10/03/200412:00:00ESAESA has momentary limit violations in the ORS+I1 and ORS+I2 channels on every orbit, direct sunlight on detector suspected. Should continue for several months. No health impact.
06/10/200413:12:00GYRO 3Turnoff Gyro-3 power permanently. Place Rgyro to MONITOR mode.
06/09/200412:00:00GYRO 3Downgrade color status to YELLOW because of continued degradation of Gyro-3.
07/29/200314:25:00GYRO 2Change gyro channel assignments to XA, YA, ZA from XB, YB, ZB in both OBP. Gyro #3 deselected from control loop.
07/29/200314:25:00GYRO 1Change gyro channel assignments to XA, YA, ZA from XB, YB, ZB in both OBP. Gyro #3 deselected from control loop.
07/29/200314:25:00GYRO 3Change gyro channel assignments to XA, YA, ZA from XB, YB, ZB in both OBP. Gyro #3 deselected from control loop.
05/30/200317:00:00GYRO 2change in counts and spin motor current characterstics
05/30/200317:00:00GYRO 3change in counts and spin motor current characteristics
10/10/200117:20:00RWA XCommanded back to XYZ wheel set from SYZ
10/09/200121:03:00 Commanded ADACS back to nominal mode from YGC
10/09/200115:12:51RWA XSpacecraft swapped from X to S reaction wheel due to 24 hour pointing test
10/09/200112:44:00 Forced YGC mode for 24 hour pointing test
09/21/200010:56:00PTC 2BOn Orbit
09/21/200010:56:00PTC 1BOn Orbit
09/21/200010:56:00PTC 1AOn Orbit
09/21/200010:56:00IMUOn Orbit
09/21/200010:56:00PTC 2AOn Orbit
09/21/200010:56:00GYRO 2On Orbit
09/21/200010:56:00RYTC 1BOn Orbit
09/21/200010:56:00GYRO 1On Orbit
09/21/200010:56:00GYRO 3On Orbit
09/21/200010:56:00RWA SOn Orbit
09/21/200010:56:00RWA XOn Orbit
09/21/200010:56:00RWA YOn Orbit
09/21/200010:56:00RYTC 1AOn Orbit
09/21/200010:56:00RYTC 2AOn Orbit
09/21/200010:56:00RYTC 2BOn Orbit
09/21/200010:56:00SSAOn Orbit
09/21/200010:56:00ESAOn Orbit
09/21/200010:56:00RWA ZOn Orbit