GOES-M STATUS last update 9 July 2013

Spacecraft

In late 2000, GOES-M spacecraft completed construction and testing at Space Systems/Loral in Palo Alto, California. The GOES-M spacecraft has a number of technical upgrades to improve orbit-and-attitude control for image stability. The GOES-M launch date was planned for Sunday, 15 July 2001, but delayed until 22 July to replace and retest a rocket controller.

In December 2007, while acting as GOES-EAST, the GOES-12 (GOES-M) spacecraft could not maintain earth-pointing control after the annual firing of thrusters that keep the orbit inclination within 0.5 degree of the equator. One of the valves to a thruster was leaking, pushing the satellite. An emergency cut-off valve was closed to stop the leak. A redundant fuel line and thruster were used to bring the satellite back on station after one week. By design, each of the the small thrusters have a backup, so that one thruster failure does not kill the mission. Eventually, it was discovered that the main and alternate thrusters were cross-wired, so that commanding one set actually activated the other. This did not cause the leak, but confused ground control.

On 14 December 2008, GOES-12 (as GOES-EAST at 75W) developed a thruster leak from the inactive set that prevented stable imaging. So, GOES-13 (a spare satellite at 105W) was turned on and operated to provide weather images of the US east coast from its mid-USA viewpoint. The leak on GOES-12 subsided after a few weeks. At 1500 UTC on 5 January 2009, GOES-12 resumed operational imaging from its eastern viewpoint. In the GSFC server movie for 5 January, the underlying map does not catch up to the change in viewpoint until 0015 UTC on the following day.

On 15 May 2009, another minor yaw thruster leak occurred, causing noticeable navigation errors in the GOES-EAST imagery, but not stopping operations.

On 14 May 2010, GOES-13 replaced GOES-12 as GOES-EAST, since station-keeping fuel was low and the satellite was not trusted to make it through the 2010 hurricane season. GOES-12 was put on "standby" status.

In June 2010, GOES-12 was moved to orbit at 60W, routinely scanning the full disk and South America. Imagery can be found on-line at SSEC at the University of Wisconsin.

In July 2013, GOES-12 was scheduled to be decommissioned on August 16, 2013. GOES-12 was launched on July 23, 2001, and it supported South America at 60W starting May 2010.

Imager

Imager SN07 was constructed and tested at ITT in Fort Wayne, Indiana in the late 1990's. It was delivered to SS/Loral and integrated onto GOES-M in 2000. There are no significant issues with the Imager. The GOES-M Imager will have some changes in the wavelength and spatial resolution of two channels:

Sounder

Sounder SN07 was constructed and tested at ITT in Fort Wayne, Indiana in the late 1990's. It was delivered to SS/Loral and integrated onto GOES-M in 2000. There were no significant pre-launch issues with the Sounder.

In November 2009, one of the shortwave detectors became noisy, and in December the filter wheel became 'sticky', intermittantly delivering an all-black strobe. Both problems made the standard sounding products nearly worthless.

SXI

A Solar X-ray Imager (SXI) prototype has been built by NASA-MSFC. The SXI flys on GOES-M's solar panel to provide soft x-ray images of the Sun minute-by-minute to warn of solar flare activity.

Launch & Storage

GOES-M was assembled and tested by Space Systems/Loral during 1997-2000. After one week's delay to replace a faulty controller in the second stage rocket, and one day's delay to double check the systems after lighning struck an adjacent launch pad, GOES-M was launched on 23 July 2001. There was 3 months of on-orbit testing, and then on-orbit cold storage as GOES-12. GOES-M was nominally planned as the replacement for GOES-10 (GOES-WEST) circa 2004, but it was called up earlier to replace GOES-8 as GOES-EAST at 75W, in order to get solar data from the unique SXI instrument during the waning years of the solar cycle.

If GOES-M were stored on the earth, it would have to be to be called out of storage to replace an on-orbit failure. There would be 9 to 12 months of preparation between call-up and launch, followed by 3 months of post-launch deployment and testing before it could become operational. On-orbit storage reduces this delay to less than a week, and avoids the chance of a launch failure when you can least afford it.

GOES-12 was activated as GOES-EAST in the spring of 2003. There was an elaborate plan to swap-in-place with GOES-8 to provide as much data continuity as possible.

By December 2009, NOAA/NESDIS decided to semi-retire GOES-12 to a slot at 60W to deliver additional imaging to South America in mid-2010, after replacing it with GOES-13 at the operational EAST slot at 75W. Remarkably, GOES-12 was still serving remapped South American imagery in June 2013.

Images

GOES-12 Science Tests (at Colorado State)

NASA-GSFC Press Releases


Orbit Raising History

GOES-M suffered overheating of the built-in third-stage rocket designed to circularize the orbit by three successive burns totalling 90 minutes of 100-lb thrust at apogee near geosynchronous altitude. Instead, the satellite was raised by nine 11-minute burns at apogee. Here is the day-by-day history of those manuevers, as they happened (most recent first).

SUMMARY OF ACTIVITIES (21 August):

Orbit raising activities were officially completed tonight  (August 20)
with the successful execution of TMF #3.  This final TMF parked GOES-12
at a 90 degree west station longitude.  The total burn duration was 65.2
seconds and was executed with no problems.  Following the maneuver, the
spacecraft was then returned back to a stationkeeping control mode and
then transitioned back to normal on-orbit V1 mode at 0230z.  DIRA 2
(gyros) which have been on since launch, were turned off following V1
mode transition and will remain off until the next maneuver. The XRP was
then slewed back to Sun.   This was also the final night for scan mirror
contamination avoidance. Communications subsystem PLTs continue to be
performed at CDA during evening shifts.  All activities were
successfully completed without incident.

Activities for GOES-12 for August 19 were highlighted with a successful
TMF#2.    The execution of TMF#2 contained two separate Thruster Fire
burns. The maneuver was conducted in two separate firings due to east
face thruster firing constraints using the on-board propellent
management device which constrains total contiguous thruster on times to
37 seconds.  The first Thruster Fire Command procedure was initiated at
13:49:40Z with a duration of approximately 26 seconds.  This burn was
successful and all parameters remained within limits. The second
Thruster Fire of TMF#2 occurred approximately 15 minutes later at
14:05:40Z.  This burn lasted approximately 25.5  seconds with all
parameters again remaining within limits. Following the completion of
TMF#2, GOES-11 was transitioned back to Normal On-Orbit V mode at
14:34:00Z.  The XRP was then slewed back to Sun (18.8 degrees).
All events performed nominally. 

Activities for August 17 were highlighted with the GOES-12 First
Full-disk Image.  This image can be found at 
.    TMF #1 and normal V mode configuration were also successfully
performed today. Trim Maneuver #1 was the first translation maneuver on
GOES-12 to be performed using the attitude thrusters.   The execution of
TMF#1 occurred at 01:57:57z and lasted approximately 20 seconds. 
Following the completion of the burn GOES-12 was transitioned to Pitch
Earth Acq Mode.  The  Reaction Wheel was turned off with Momentum Wheel
#1 then being spun-up to the V mode configuration at approximately
02:00z.  MW#1 stabilized nominally at 2900 RPM.  Transition to Normal
On-Orbit V-mode (with both momentum wheel #1 and #2 at 2900 RPM) from
Stationkeeping mode occurred at 02:45Z.  The XRP was then slewed back to
the operational position.   All events performed nominally.

All other telemetry parameters remained within limits throughout the events.

Other Significant Activities

None.

SPACECRAFT CONFIGURATION 
(items underlined indicate S/C config changes from previous report):

Sensors 
AOCE 1 on 
DIRA 2 (gyros) off
Coarse Analog Sun Sensor (CASS) 1 on 
Digital Sun Sensor (DSS) 1 on 
Earth Sensor (ES) 1 on 
Magnetometer 1 on 
EPS/HEPAD on 
X-Ray Sensor on

Deployments 
Magnetometer boom-released-locked 
Solar Array fully deployed 
Solar Array Drive Electronics side 1 on 
Solar Array Run Mode 
Trim Tab at  degrees 
Solar Sail fully deployed
        
Control mode & Actuators 
Momentum Wheels 1 & 2 @2900 RPM and Reaction Wheel off
Magnetic Torquers 1 & 2 on
Attitude thrusters disabled
Main Spacecraft Thruster Isolated

Telemetry & Command Subsystem 
CDA A transmitter on 
DSN A transmitter on 
DSN B transmitter off 
Command Units 1&2 in secure mode

Communications

Power AMPs A&C on 

Sensor data transmitter on 

Thermal

Imager/Sounder Outgas heaters on High

Payload

Imager & Sounder on and scan functional


ANOMALIES/CONCERNS:

None.

MISCELLANEOUS:


SIGNIFICANT EVENTS TIMELINE (events will be dropped as they're completed):

SXI VB Door August 25
Cooler Cover deployment September 10 

Imager/Sounder Outgassing August 14 September 9 

Instrument Contamination Avoidance August 14 20

Battery Reconditioning August 21 August 30

Communications Testing August 15-August 30
Solar Array Drive stepping tests August 30-September 3
Earth Sensor Characterization November 14-November 23

First SXI Image September 4

NOAA Science Testing September-October 27

Station Maneuvers
North/South Stationkeeping Maneuver December 19
East/West Stationkeeping Maneuver December 21

NOAA Science Testing July 24 August 13

Enter Z-Axis Precession (ZAP) storage mode December 23

Spacecraft Hand-over to NOAA December 24

SUMMARY OF ACTIVITIES (14 August)

GOES-12 activities for Imager/Sounder initialization, L2 Wheels spin-up
and Solar Sail deployment executed extremely smoothly.  Command Units #1
and #2 were configured to secure mode and the sensor data transmitter
was turned on in preparation for Imager/Sounder initialization.   The
sounder was successfully initialized at 5:08pm EDT.   The reaction wheel
(RW) was commanded on at 5:50pm EDT and Momentum wheel (MW) #2 commanded
on at 6:00pm EDT and spun up to 5350 RPM in preparation for the Solar
Sail Deployment.  The Imager was successfully initialized at 6:25pm EDT.
 CDA Sensor Processing System (SPS) successfully processed and recorded
wide-band data throughout both imager and sounder initializations.

The Solar Sail was successfully deployed at 7:-13pm EDT.  The deployment
took approximately 14.5 minutes to complete.  Just prior to the
deployment, the CDA transmitter was configured to transmit dwell
telemetry for indication of Solar Sail 3-inch status.  All solar sail
release and deployment switches indicated a successful deployment.

Shortly after the deployment, operations engineers enthusiastically
executed command sequences to isolate the MST.  Normal on-orbit L-2 mode
(MW #2 and RW used for control) was successfully commanded at 8:30pm EDT
and the Solar Array put into run mode.  The XRS was deployed and was
aligned to the sun-line within .1 degree in the east/west direction as
measured by the SAS.  The spacecraft will stay in L-2 configuration with
MW #2 at 4500 rpm until TMF#1 on August 17, at which time the spacecraft
will be configured to V1 mode (both MW#1 and #2 on and at 2900 RPM, RW
off).   Imager/Sounder scan mirror contamination avoidance activities
will continue for the next 7 nights.

During this evening’s activities, the SAS cooled enough to toggle the
yellow low limit at 30 degrees C (still considerably higher than the 36
degrees C red low limit).  This was consistent with what was observed
for GOES-9, 10, and 11.   SAS temperatures quickly returned to normal
following XRS turn-on and slew.  All other telemetry parameters remained
within limits throughout the event.

The SXI UV lamp continues to be cycled on/off every hour for
approximately 5 minute on-time durations.  After tonight this will be
made part of the daily ops schedule.

GOES-12 will now start Post-Launch Testing!

MISCELLANEOUS:

None

Spacecraft Orbit Parameters:
Inclination = .302 degrees
Apogee = 42269 km
Perigee = 42040 km
Orbital Period = 23.93 hours
Drift Rate = .147 degrees/day East
Station Location = 91.02 degrees


SPACECRAFT CONFIGURATION 
(items underline indicate S/C config changes from previous report):

AOCE 1 on
DIRA 2 (gyros) on
Coarse Analog Sun Sensor (CASS) 1 on
Digital Sun Sensor (DSS) 1 on
Earth Sensor (ES) 1 on
Magnetometer 1 on
Magnetometer boom-released-locked
Solar Array fully deployed
Solar Array Drive Electronics on
Trim Tab at
Imager/Sounder Outgas heaters on High
EPS/HEPAD on
Side-A thrusters selected
Normal Sun Acquisition Mode (and off-axis during night time hours)
Outer panel Solar Array Deployed
Trim Tab at 23.5 degrees
CDA A transmitter on
DSN A transmitter on
DSN B transmitter off
SXI on
Notch Filters and Rate gain/2
Solar Sail Deployed
X-Ray Sensor  on
Solar Array Run Mode
Normal on-orbit L1Mode (earth pointing)
Momentum Wheels 1 @4500 RPM and Reaction Wheel on
Main Spacecraft Thruster  Isolated
Command Units 1&2  in secure mode
Sensor data transmitter on
Imager & Sounder on and scan functional



UPCOMING ACTIVITIES :

TMF #1:  Friday, August 17, at 9:15pm EDT, burn duration of .99 minutes

ANOMALIES/CONCERNS:

None at present

SIGNIFICANT EVENTS TIMELINE (events will be dropped as they’re completed):

Circularize Orbit
TMF #1:  Friday, August 17, at 9:15pm EDT, burn duration of .99 minutes
TMF #2:  Sunday, August 19, at 9:31am EDT, burn duration of .54 minutes
TMF #3:  Monday, August 20, at 8:59pm EDT, burn duration of .1 minutes

Deployments  August 25 September 10
	SXI VB Door  August 25
	Cooler Cover deployment  September 10

Imager/Sounder Outgassing  August 14 September 9

Instrument Contamination Avoidance  August 14 20

Battery Reconditioning August 19 August 30

Start-ups and functional tests  August 16 November 23
	X-Ray Sensor (XRS) Turn on  August 16
	Safehold Mode Characterization  August 21
	Communications Testing  August 15-August 30
	Solar Array Drive stepping tests  August 30-September 3
	Earth Sensor Characterization  November 14-November 23
	
First VIS Image  August 17 1800z

First SXI Image  September 4

NOAA Science Testing  September-October 27

Station Maneuvers
	North/South Stationkeeping Maneuver  December 19
	East/West Stationkeeping Maneuver  December 21

NOAA Science Testing  July 24  August 13

Enter Z-Axis Precession (ZAP) storage mode  December 23

Spacecraft Hand-over to NOAA  December 24

SUMMARY OF ACTIVITIES (13 August)

GOES-M was officially renamed to GOES-12 today.

Dipole estimation maneuvers were successfully performed today.   The
Dipole maneuvers were performed for final determination of the
spacecraft’s magnetic field for future correction of magnetometer data. 
The maneuver was conducted in roll, pitch, and yaw axes, and was
entirely uneventful.  Worst case DOD during the pitch maneuver was
approximately 24%  (as predicted).  As part of the Dipole maneuver the
solar array was successfully slewed 90 degrees in the reverse direction
(2 X 45 degree slews) and slewed 90 degrees back in the forward
direction to the original 270 index position.  At completion of the
Dipole estimation activities the spacecraft was commanded back to Normal
Sun Acq mode.

All telemetry parameters remained within limits.

The SXI UV lamp continues to be cycled on/off every hour for
approximately 5 minute on-time durations.

MISCELLANEOUS:

None

Spacecraft Orbit Parameters:
Inclination = .302 degrees
Apogee = 42269 km
Perigee = 42040 km
Orbital Period = 23.93 hours
Drift Rate = .147 degrees/day East
Station Location = 91.17 degrees


SPACECRAFT CONFIGURATION 
(items underline indicate S/C config changes from previous report):

AOCE 1 on
DIRA 2 (gyros) on
Coarse Analog Sun Sensor (CASS) 1 on
Digital Sun Sensor (DSS) 1 on
Earth Sensor (ES) 1 on
Magnetometer 1 on
Magnetometer boom-released-locked
Solar Array fully deployed
Solar Array Drive Electronics on
Trim Tab at
Imager/Sounder Outgas heaters on High
EPS/HEPAD on
Side-A thrusters selected
Normal Sun Acquisition Mode (and off-axis during night time hours)
Outer panel Solar Array Deployed
Trim Tab at -9 degrees
CDA A transmitter on
DSN A transmitter on
DSN B transmitter off
SXI on
Notch Filters and Rate gain/2

UPCOMING ACTIVITIES :

Dipole:  Monday, August 13, at 6:34am EDT

WH+SL:  Sounder Initialization- Tuesday, August 14, at 5:06pm EDT
                L2 Wheel Spin-Up- Tuesday, August 14, at 5:20pm EDT
                Imager Initialization- Tuesday, August 14, at 6:22pm EDT
                Solar Sail Deploy- Tuesday, August 14, at 8:07pm EDT

ANOMALIES/CONCERNS:

None at present

SIGNIFICANT EVENTS TIMELINE (events will be dropped as they’re completed):

Circularize Orbit
TMF #1:  Friday, August 17, at 9:15pm EDT, burn duration of .99 minutes
TMF #2:  Sunday, August 19, at 9:31am EDT, burn duration of .54 minutes
TMF #3:  Monday, August 20, at 8:59pm EDT, burn duration of .1 minutes

Deployments  August 25 September 10
	SXI VB Door  August 25
	Cooler Cover deployment  September 10

Imager/Sounder Outgassing  August 14 September 9

Instrument Contamination Avoidance  August 14 20

Battery Reconditioning August 19 August 30

Start-ups and functional tests  August 16 November 23
	X-Ray Sensor (XRS) Turn on  August 16
	Safehold Mode Characterization  August 21
	Communications Testing  August 15-August 30
	Solar Array Drive stepping tests  August 30-September 3
	Earth Sensor Characterization  November 14-November 23
	
First VIS Image  August 17 1800z

First SXI Image  September 4

NOAA Science Testing  September-October 27

Station Maneuvers
	North/South Stationkeeping Maneuver  December 19
	East/West Stationkeeping Maneuver  December 21

NOAA Science Testing  July 24  August 13

Enter Z-Axis Precession (ZAP) storage mode  December 23

Spacecraft Hand-over to NOAA  December 24

SUMMARY OF ACTIVITIES (12 August):

On August 12, 2001, GOES-M successfully achieved a series of milestones
with the AAM part 2, final deployment of the magnetometer boom and solar
array, and SXI turn on.

AAM part 2 was executed at 9:47am EDT.  This maneuver was performed at
perigee 28.  The burn lasted exactly 45.5 seconds.  The Main Spacecraft
Thruster (MST) flange temperature reached 104 degrees C.  The JPL/DSN
Goldstone 34 meter antenna (D27) was used as the primary commanding site
for this maneuver.  This maneuver reduced the apogee by 950 km.  Current
station location is 91 degrees West longitude and drifting approximately
.4 degrees per day.  The orbital period is a near nominal 24 hours.  All
telemetry parameters remained well within limits throughout this
maneuver.

The spacecraft was then configured to DIRA Attitude Reference (DREF)
mode in preparation for Magnetometer Boom deployment.  Magnetometer 1
turn-on occurred at 10:00am EDT.  In-flight magnetometer calibration was
then performed and valid data receipt verified.  DIRA rates observed
during the deployment (10:06am EDT) were nominal and consistent with the
GOES-11 magnetometer deployment signature.

The spacecraft was then slewed to S/A deployment attitude.  Notch
filters #1&2 were enabled prior to the SA deployment.  SA phase 1
outboard panel deployment was executed at 10:45am EDT in DREF mode. 
Attitude transients experienced were nominal.  A series of yaw
reorientations were performed to warm the solar array hinges while
keeping adequate T&C coverage.   Solar Array Phase 2 deployment sequence
was successfully executed at 11:33am EDT.  Battery DOD reached 24.1%,
which was slightly lower than GOES-L.  The Trim Tab was slewed back to
120 degrees.  SXI was successfully commanded on at 11:51am EDT following
solar array phase 2 deployment.  The SXI was powered on to maintain
thermal constraints on the instrument.  In addition, the SXI UV lamp
will be cycled on every hour (for a 5 minute duration) then turned-off
to ensure the UV lamp stays within thermal limits.  Spacecraft bus and
payload heaters were then configured for transfer orbit.  Power amps A &
C were also turned on to provide heating as well.

After returning to Normal Sun Acq mode the SA was briefly placed in run
mode to verify solar array drive motor (10 minutes forward and 10
minutes reverse motion) for a total of 2.5 degrees each direction.   In
addition, the solar array was slewed 30 degrees in a reverse direction
and slewed back to the original 270 degree position.  The slew test was
performed in preparation for tonight's Off-axis Sun Acq. mode entrance
which will require a 30 degree solar array slew to sun-line normal to
prevent excessive SAS cooling.  Magnetometer  #2 was powered on and
calibrated to verify proper operation then reconfigured back to
Magnetometer #1.


Again, the MST will not be permanently isolated until Tuesday evening
following the Solar Sail deployment.  The orbit will be circularized
into the final orbit over the next week through a series of 3 trim
maneuvers using the 5 lb attitude thrusters.

All other telemetry parameters remained within limits.

Spacecraft Orbit Parameters:
Inclination = .314 degrees
Apogee = 42248 km
Perigee = 42026 km
Orbital Period = 23.91 hours
Drift Rate = .4 degrees/day East
Station Location = 92 degrees


SPACECRAFT CONFIGURATION (items underline indicate S/C config changes from previous report):

AOCE 1 on
DIRA 2 (gyros) on
Coarse Analog Sun Sensor (CASS) 1 on
Digital Sun Sensor (DSS) 1 on
Earth Sensor (ES) 1 on
 Magnetometer 1 on
 Magnetometer boom-released-locked
 Solar Array fully deployed
 Solar Array Drive Electronics  on
 Trim Tab at
 Imager/Sounder Outgas heaters on High
EPS/HEPAD on
Side-A thrusters selected
Normal Sun Acquisition Mode (and off-axis during night time hours)
Outer panel Solar Array Deployed
Trim Tab at -120 degrees
CDA  A transmitter on
DSN A transmitter on
DSN B transmitter off

UPCOMING ACTIVITIES :

Dipole:  Monday, August 13, at 6:34am EDT

WH+SL:  Sounder Initialization- Tuesday, August 14, at 5:06pm EDT
                L2 Wheel Spin-Up- Tuesday, August 14, at 5:20pm EDT
                Imager Initialization- Tuesday, August 14, at 6:22pm EDT
                Solar Sail Deploy- Tuesday, August 14, at 8:07pm EDT

ANOMALIES/CONCERNS:

Prior to SA deployment part 1 the JPL D27 subnet loaded a new set of FDF
predicts and subsequently lost lock.  D27 was instructed to reload their
old set of predicts and subsequently locked back up to the satellite.

MISCELLANEOUS:

None.

SIGNIFICANT EVENTS TIMELINE (events will be dropped as they are completed):

Circularize Orbit
TMF #1:  Friday, August 17, at 9:15pm EDT, burn duration of .99 minutes
TMF #2:  Sunday, August 19, at 9:31am EDT, burn duration of .84 minutes
TMF #3:  Monday, August 20, at 8:59pm EDT, burn duration of .11 minutes

Deployments  August 25 September 10
	SXI VB Door  August 25
	Cooler Cover deployment  September 10

Imager/Sounder Outgassing  August 14 September 9

Instrument Contamination Avoidance  August 14 20

Battery Reconditioning August 19 August 30

Start-ups and functional tests  August 16 November 23
	X-Ray Sensor (XRS) Turn on  August 16
	Safehold Mode Characterization  August 21
	Communications Testing  August 15-August 30
	Solar Array Drive stepping tests  August 30-September 3
	Earth Sensor Characterization  November 14-November 23
	
First VIS Image  August 17 1800z

First SXI Image  September 4

NOAA Science Testing  September-October 27

Station Maneuvers
	North/South Stationkeeping Maneuver  December 19
	East/West Stationkeeping Maneuver  December 21

NOAA Science Testing  July 24  August 13

Enter Z-Axis Precession (ZAP) storage mode  December 23

Spacecraft Hand-over to NOAA  December 24

SUMMARY OF ACTIVITIES (11 August):

Part 1 of the GOES-M Apogee Adjust Maneuver (AAM) was successfully
executed today, Saturday, August 11, at 9:29am EDT.  This maneuver was
performed at perigee 27.  The burn lasted 4 minutes and 25 seconds.  The
Main Spacecraft Thruster (MST) flange temperature reached 182 degrees C.
The Goldstone 26 meter antenna was used as the primary commanding site
for this maneuver.  This maneuver reduced the apogee by 6024 km and the
orbital period decreased to a near nominal 24 hours.  All telemetry
parameters remained well within limits throughout the entire maneuver.
The spacecraft was configured back into normal sun acquisition mode. Off
Axis Sun Acquisition will be commanded in the back orbits in order to
reduce telemetry and command nulls.  The MST will be permanently
isolated on Tuesday evening following the Solar Sail deployment.  The
orbit will be circularized into the final orbit over the next week
through a series of 3 trim maneuvers using the 5 lb attitude thrusters.

The next maneuver, AAM, Part 2 is scheduled for Sunday, August 12, at
9:49am EDT, and will have a burn duration of .75 minutes.  Following AAM
Part 2, the MB and SA deployments will occur as scheduled below.

Other Significant Activities

None.

Spacecraft Orbit Parameters
Inclination = .289 degrees
Apogee = 43184 km
Perigee = 42039 km
Orbital Period = 24.32 hours
Drift Rate = 5.5 degrees/day West

SPACECRAFT CONFIGURATION:

AOCE 1 on
DIRA 2(gyros) on
Coarse Analog Sun Sensor (CASS) 1 on
Digital Sun Sensor (DSS) 1 on
Earth Sensor (ES) 1 on
EPS/HEPAD on
Side-A thrusters selected
Normal Sun Acquisition Mode
Outer panel Solar Array Deployed
Trim Tab at 0 degrees

SIGNIFICANT EVENTS TIMELINE:

AAM:
Part 2- Sunday, August 12, at 9:49am EDT, burn duration of .75 minutes

MBSA: (MB and SA Deploy/Phases 1 & 2 are approximate times post AAM Part 2)
MB Deploy- Sunday, August 12, at 10:19am EDT
SA Deploy/Phase 1- Sunday, August 12, at 10:45am EDT
SA Deploy/Phase 2- Sunday, August 12, at 11:30am EDT

Dipole:  Monday, August 13, at 6:34am EDT

WH+SL:
L2 Wheel Spin-Up- Tuesday, August 14, at 5:20pm EDT
Solar Sail Deploy- Tuesday, August 14, at 8:07pm EDT

TMF #1:  Saturday, August 18, at 9:15pm EDT, burn duration of .82 minutes
TMF #2:  Sunday, August 19, at 9:31am EDT, burn duration of .54 minutes
TMF #3:  Tuesday, August 21, at 8:59pm EDT, burn duration of .1 minutes

SUMMARY OF ACTIVITIES (August 9):

Our ninth, and final, Apogee Maneuver Firing (AMF #9) was successfully
executed today, Thursday, August 9, at 1:47pm EDT.  The burn lasted 6
minutes and 15 seconds- 375 seconds in total.  The Main Spacecraft
Thruster (MST) flange temperature reached 201 degrees C, well below the
abort criteria limit.  The flange temperature profile tracked that of
the previous burns.  Following this maneuver the spacecraft was
configured back to a normal sun acquisition mode.  All subsystems are
safe and remain well within limits.  Off Axis Sun Acquisition will be
commanded during back orbits in order to reduce telemetry and command
nulls.  This maneuver raised perigee approximately 6168 km and increased
the orbital period to approximately 27 hours.  The orbit after AMF#9
will actually be slightly super-synchronous, and won't be GEO until
after the AAMs.  The last MST firings will occur at perigee during the
upcoming AAMs which will be performed this weekend.

The next maneuver, AAM, part 1 is scheduled for Saturday, August 11, at
9:29am EDT, with a burn duration of 4.67 minutes

Other Significant Activities

None.

Spacecraft Orbit Parameters
Inclination = .301 degrees
Apogee = 49207 km
Perigee = 42055 km
Orbital Period = 26.95 hours

SPACECRAFT CONFIGURATION:

AOCE 1 on
DIRA 2(gyros) on
Coarse Analog Sun Sensor (CASS) 1 on
Digital Sun Sensor (DSS) 1 on
Earth Sensor (ES) 1 on
EPS/HEPAD on
Side-A thrusters selected
Normal Sun Acquisition Mode
Outer panel Solar Array Deployed
Trim Tab at 0 degrees

SIGNIFICANT EVENTS TIMELINE:

AAM:
Part 1- Saturday, August 11, at 9:29am EDT, burn duration of 4.67 minutes
Part 2- Sunday, August 12, at 9:53am EDT, burn duration of .49 minutes

MBSA: (MB and SA Deploy/Phases 1 & 2 are approximate times post AAM Part 1)
MB Deploy- Sunday, August 12, at 7:22am EDT
SA Deploy/Phase 1- Sunday, August 12, at 10:45am EDT
SA Deploy/Phase 2- Sunday, August 12, at 11:30am EDT

Dipole:  Monday, August 13, at 6:34am EDT

WH+SL:
L2 Wheel Spin-Up- Tuesday, August 14, at 5:20pm EDT
Solar Sail Deploy- Tuesday, August 14, at 8:07pm EDT

TMF #1:  Saturday, August 18, at 9:16pm EDT, burn duration of .82 minutes
TMF #2:  Sunday, August 19, at 9:20am EDT, burn duration of .84 minutes
TMF #3:  Tuesday, August 21, at 9:12am EDT, burn duration of .11 minutes


SUMMARY OF ACTIVITIES (August 7):

Our eighth Apogee Maneuver Firing (AMF #8) was successfully executed
today, Tuesday,  August 7, 2001 at 1:37pm EDT.  The burn lasted 8
minutes and 35 seconds- 515 seconds in total.  The Main Spacecraft
Thruster (MST) flange temperature reached 231 degrees C, well below the
abort criteria limit.  The flange temperature profile tracked that of
AMF#7.  Following this maneuver the spacecraft was configured back to a
normal sun acquisition mode and will remain in this mode until the next
maneuver.  All subsystems are safe and remain well within limits.  The
maneuver raised perigee approximately 6724 km and increased the orbital
period to approximately 24 hours.

1 AMF remains in order to achieve geosynchronous orbit.

The next maneuver, AMF #9, is planed for Thursday, August 9, at 1:46pm
EDT, with a burn duration of 6.25 minutes

Other Significant Activities

None.

Spacecraft Orbit Parameters
Inclination = 1.09 degrees
Apogee = 48753 km
Perigee = 35899 km
Orbital Period = 24.07 hours

SPACECRAFT CONFIGURATION:

AOCE 1 on
DIRA 2(gyros) on
Coarse Analog Sun Sensor (CASS) 1 on
Digital Sun Sensor (DSS) 1 on
Earth Sensor (ES) 1 on
EPS/HEPAD on
Side-A thrusters selected
Normal Sun Acquisition Mode
Outer panel Solar Array Deployed
Trim Tab at 0 degrees

SIGNIFICANT EVENTS TIMELINE:

AMF #9:  Thursday, August 9, at 1:46pm EDT, burn duration of 6.25 minutes

AAM:
Part 1- Saturday, August 11, at 9:27am EDT, burn duration of 4.67 minutes
Part 2- Sunday, August 12, at 9:41am EDT, burn duration of .49 minutes

MBSA: (MB and SA Deploy/Phases 1 & 2 are approximate times post AAM Part 1)
MB Deploy- Sunday, August 12, at 7:22am EDT
SA Deploy/Phase 1- Sunday, August 12, at 10:45am EDT
SA Deploy/Phase 2- Sunday, August 12, at 11:30am EDT

Dipole:  Monday, August 13, at 6:34am EDT

WH+SL:
L2 Wheel Spin-Up- Tuesday, August 14, at 5:20pm EDT
Solar Sail Deploy- Tuesday, August 14, at 8:07pm EDT

TMF #1:  Saturday, August 18, at 9:16pm EDT, burn duration of .82 minutes
TMF #2:  Sunday, August 19, at 9:20am EDT, burn duration of .84 minutes
TMF #3:  Tuesday, August 21, at 9:12am EDT, burn duration of .11 minutes

SUMMARY OF ACTIVITIES (4 August):

Our seventh Apogee Maneuver Firing (AMF) #7 was successfully executed
today, Saturday,  August 4, 2001 at 10:05pm EDT.  The burn lasted 9
minutes and 10 seconds- 550 seconds in total.  The Main Spacecraft
Thruster (MST) flange temperature reached 236 degrees C, well below the
abort criteria limit.  The flange temperature profile tracked that of
AMF#6.  Following this maneuver the spacecraft was configured back to a
normal sun acquisition mode and will remain in this mode until the next
maneuver.  All subsystems are safe and remain well within limits.  The
maneuver raised perigee approximately 5446 km and increased the orbital
period to approximately 21 hours.

2 AMFs remain in order to achieve geosynchronous orbit.

The next maneuver, AMF#8, is planned for Tuesday, August 7, at 1:48pm
EDT with a burn duration of 8.67 minutes.

Other Significant Activities

Prior to the actual burn the JPL/DSN 26-Meter Subnet, D16, experienced a
CPA (Command Processor Assembly) failure.  Commanding was immediately
switched over to NASA Wallops where burn execution was successfully
performed.  A fail-over to the backup CPA at D16 was performed post
AMF#7.  Handover back to D16 ensued and successful commanding was
performed.  A trouble report has been initiated by the DSN regarding
this D16 CPA issue.

Spacecraft Orbit Parameters
Inclination = 2.41 degrees
Apogee = 48606 km
Perigee = 29191 km
Orbital Period = 21.21 hours


SPACECRAFT CONFIGURATION:

AOCE 1 on
DIRA 2(gyros) on
Coarse Analog Sun Sensor (CASS) 1 on
Digital Sun Sensor (DSS) 1 on
Earth Sensor (ES) 1 on
EPS/HEPAD on
Side-A thrusters selected
Normal Sun Acquisition Mode
Outer panel Solar Array Deployed
Trim Tab at 0 degrees

SIGNIFICANT EVENTS TIMELINE:

AMF #8:  Tuesday, August 7, at 1:48pm EDT, burn duration of 8.67 minutes
AMF #9:  Thursday, August 9, at 2:02pm EDT, burn duration of 6.17 minutes

AAM:
Part 1- Saturday, August 11, at 9:43am EDT, burn duration of 5.25 minutes
Part 2- Sunday, August 12, at 9:45am EDT, burn duration of .22 minutes

MBSA: (MB and SA Deploy/Phases 1 & 2 are approximate times post AAM Part 1)
MB Deploy- Sunday, August 12, at 7:22am EDT
SA Deploy/Phase 1- Sunday, August 12, at 10:45am EDT
SA Deploy/Phase 2- Sunday, August 12, at 11:30am EDT

Dipole:  Monday, August 13, at 6:34am EDT

WH+SL:
L2 Wheel Spin-Up- Tuesday, August 14, at 5:20pm EDT
Solar Sail Deploy- Tuesday, August 14, at 8:07pm EDT

TMF #1:  Saturday, August 18, at 9:18pm EDT, burn duration of .42 minutes
TMF #2:  Sunday, August 19, at 9:29am EDT, burn duration of .52 minutes
TMF #3:  Tuesday, August 21, at 9:08pm EDT, burn minutes of .17 minutes


SUMMARY OF ACTIVITIES (3 August):

Our sixth Apogee Maneuver Firing (AMF) #6 was successfully executed
today, Friday, August 3, 2001 at 8:04am EDT.  The burn lasted exactly 10
minutes and 45 seconds (645 seconds total).  The Main Spacecraft
Thruster (MST) flange temperature reached 247.33 degrees C, well below
the abort criteria limit.  The flange temperature profile tracked that
of AMF#5.  Following this maneuver the spacecraft was configured back to
a normal sun acquisition mode and will remain in this mode until the
next maneuver.  All subsystems are safe and remain well within limits. 
The maneuver raised perigee approximately 4759 km and increased the
orbital period to approximately 19 hours.

A total of 3 AMFs remain in order to achieve geosynchronous orbit.

The next maneuver (AMF#7) is planned for Saturday, August 4, at 10:00pm
EDT (DOY 217 @ 0200z) with a burn duration of 9.25 minutes.

Spacecraft Orbit Parameters
Inclination = 3.92 degrees
Apogee = 48553 km
Perigee = 23713 km
Orbital Period = 18.99 hours


SPACECRAFT CONFIGURATION:

AOCE 1 on
DIRA 2(gyros) on
Coarse Analog Sun Sensor (CASS) 1 on
Digital Sun Sensor (DSS) 1 on
Earth Sensor (ES) 1 on
EPS/HEPAD on
Side-A thrusters selected
Normal Sun Acquisition Mode
Outer panel Solar Array Deployed
Trim Tab at 0 degrees

SIGNIFICANT EVENTS TIMELINE:

AMF #7:  Saturday, August 4, at 10:00pm EDT,  9.25 minutes burn duration
AMF #8:  Tuesday, August 7, at 1:39pm EDT,  8.67 minutes burn duration
AMF #9:  Thursday, August 9, at 1:56pm EDT,  6.17 minutes burn duration

AAM:
Part 1- Saturday, August 11, at 9:43am EDT,  5.25 minutes burn duration
Part 2- Sunday, August 12, at 9:49am EDT,  .22 minutes burn duration

MBSA: (MB and SA Deploy/Phases 1 & 2 are approximate times post AAM Part 1)
MB Deploy- Sunday, August 12, at 7:22am EDT
SA Deploy/Phase 1- Sunday, August 12, at 10:45am EDT
SA Deploy/Phase 2- Sunday, August 12, at 11:30am EDT

Dipole:  Monday, August 13, at 6:34am EDT

WH+SL:
L2 Wheel Spin-Up- Tuesday, August 14, at 5:20pm EDT
Solar Sail Deploy- Tuesday, August 14, at 8:07pm EDT

TMF #1:  Saturday, August 18, at 9:18pm EDT,  .42 minutes burn duration
TMF #2:  Sunday, August 19, at 9:29am EDT,  .57 minutes burn duration
TMF #3:  Tuesday, August 21, at 9:08pm EDT,  .17 minutes burn duration

SUMMARY OF ACTIVITIES (July 31):

Our fifth Apogee Maneuver Firing (AMF) #5 was successfully executed
today, Tuesday, July 31, at 11:01am EDT.  The burn lasted exactly 11
minutes.  The Main Spacecraft Thruster (MST) flange temperature reached
252.77 degrees, a little over 5 degrees below the abort criteria limit. 
The flange temperature profile during this burn was nearly identical to
AMF#4.  Following this maneuver the spacecraft was configured back to a
normal sun acquisition mode and will remain in this mode until the next
maneuver.  All subsystems are safe and remain well within limits.  The
maneuver raised perigee approximately 3657 km and increased the orbital
period to approximately 17 hours.

A total of 4 AMFs remain in order to achieve geosynchronous orbit.

The next maneuver (AMF#6) is planned for Friday, August 3, at 8:01am EDT
(DOY 215 @ 1201z).


Spacecraft Orbit Parameters
Inclination = 5.82 degrees
Apogee = 48544 km
Perigee = 18944 km
Orbital Period = 17.14 hours


SPACECRAFT CONFIGURATION:

AOCE 1 on
DIRA 2(gyros) on
Coarse Analog Sun Sensor (CASS) 1 on
Digital Sun Sensor (DSS) 1 on
Earth Sensor (ES) 1 on
EPS/HEPAD on
Side-A thrusters selected
Normal Sun Acquisition Mode
Outer panel Solar Array Deployed
Trim Tab at 0 degrees

SIGNIFICANT EVENTS TIMELINE:

AMF #6:  Friday, August 3, at 8:01am EDT (DOY 215 @ 1201z)
AMF #7:  Saturday August 4, at 10:00pm EDT (DOY 218 @ 0200z)
AMF #8:  Tuesday, August 7, at 1:39pm EDT (DOY 220 @ 1739z)
AMF #9:  Thursday, August 9, at 1:56pm EDT (DOY 222 @ 1756z)

AAM:
Part 1- Saturday, August 11, at 9:43am EDT (DOY 223 @ 1343z)
Part 2- Sunday, August 12, at 9:49am EDT (DOY 224 @ 1345z)

MBSA: (Phase 1 & 2 are approximate times post AAM Part 2)
Phase 1- Sunday, August 12, at 10:30am EDT (DOY 224 @ 1430z)
Phase 2- Sunday, August 12, at 11:25am EDT (DOY 224 @ 1525z)

Dipole:  Monday, August 13, at 6:34am EDT (DOY 225 @ 1034z)

WH+SL:
L2 Wheel Spin-Up- Tuesday, August 14, at 5:20pm EDT (DOY 226 @ 2150z)
Solar Sail Deploy- Tuesday, August 14, at 8:07pm EDT (DOY 227 @ 0007z)

TMF #1:  Saturday, August 18, at 9:18pm EDT (DOY 231 @ 0118z)
TMF #2:  Sunday, August 19, at 9:29am EDT (DOY 231 @ 1329z)
TMF #3:  Tuesday, August 21, at 9:08pm EDT (DOY 234 @ 0108z)

SUMMARY OF ACTIVITIES (July 29):

Our third Apogee Maneuver Firing (AMF) #4 was successfully early this
morning at 4:00am EDT.  The burn lasted 11 minutes and 10 seconds.  The
Main Spacecraft Thruster (MST) flange temperature reached 253 degrees, 5
degrees below the abort criteria limit.  The flange temperature profile
during this burn was nearly identical to the first three AMFs. 
Following this maneuver the spacecraft was configured back to a normal
sun acquisition mode and will remain in this mode until the next
maneuver.  All subsystems are safe and remain well within limits.  The
maneuver raised perigee approximately 2861 km and increased the orbital
period to approximately 16 hours.

A total of 5 AMFs remain in order to achieve geosynchronous orbit.

The next maneuver (AMF#5) is planned for Tuesday, July 31, at 11:00am
EDT (DOY 212 @ 1500z), with a burn duration of 670 seconds.


Spacecraft Orbit Parameters
Inclination = 7.99 degrees
Apogee = 48479 km
Perigee = 15261 km
Orbital Period = 15.72 hours


SPACECRAFT CONFIGURATION:

AOCE 1 on
DIRA 2(gyros) on
Coarse Analog Sun Sensor (CASS) 1 on
Digital Sun Sensor (DSS) 1 on
Earth Sensor (ES) 1 on
EPS/HEPAD on
Side-A thrusters selected
Normal Sun Acquisition Mode
Outer panel Solar Array Deployed
Trim Tab at 0 degrees

SIGNIFICANT EVENTS TIMELINE:

AMF #5:  Tuesday, July 31, at 11:00am EDT (DOY 212 @ 1500z)
AMF #6:  Friday, August 3, at 8:13am EDT (DOY 215 @ 1213z)
AMF #7:  Sunday, August 5, at 10:31pm EDT (DOY 217 @ 0231z)
AMF #8:  Tuesday, August 7, at 1:51pm EDT (DOY 219 @ 1751z)
AMF #9:  Thursday, August 9, at 2:14pm EDT (DOY 221 @ 1814z)

AAM:  Saturday, August 11, at 9:26am EDT (DOY 223 @ 1326z)

MBSA:  Phase 1- Sunday, August 12, at 9:05am EDT (DOY 224 @ 1305z)
              Phase 2- Sunday, August 12, at 10:00am EDT (DOY 224 @ 1400z)

Dipole:  Monday, August 13, at 6:34am EDT (DOY 225 @ 1034z)

WH+SL:  L2 Wheel Spin-Up-  Tuesday, August 14, at 5:20pm EDT (DOY 226 @ 2150z)
                Solar Sail Deploy-   Tuesday, August 14, at 8:07pm EDT (DOY 226 @ 0007z)

TMF #1:  Saturday, August 18, at 9:00pm EDT (DOY 230 @ 0100z)
TMF #2:  Sunday, August 19, at 8:58am EDT (DOY 231 @ 1258z)
TMF #3:  Saturday, August 21, at 8:52pm EDT (DOY 233 @ 0052z)

SUMMARY OF ACTIVITIES (July 28):

Our third Apogee Maneuver Firing (AMF) #3 was successfully executed
today.  The burn lasted 11 minutes and 10 seconds.  The Main Spacecraft
Thruster (MST) flange temperature reached 253 degrees, 5 degrees below
the abort criteria limit.  The flange temperature profile during this
burn was nearly identical to the first two AMFs.  Following this
maneuver the spacecraft was configured back to a normal sun acquisition
mode and will remain in this mode until the next maneuver.  All
subsystems are safe and remain well within limits.  The maneuver raised
perigee approximately 1500 km and increased the orbital period to
approximately 15 hours.

The plan is still to continue to perform shorter and more frequent AMFs
on the order of 11 to 12 minutes in duration.  A total of 6 AMFs will
now be required to achieve geosynchronous orbit.

The next maneuver is planned for Monday, July 30, at 04:01am EDT (DOY
211 @ 0801z), with a burn duration of 670 seconds.


Spacecraft Orbit Parameters
Inclination = 10.4 degrees
Apogee = 48478 km
Perigee = 12415 km
Orbital Period = 14.7 hours


SPACECRAFT CONFIGURATION:

AOCE 1 on
DIRA 2(gyros) on
Coarse Analog Sun Sensor (CASS) 1 on
Digital Sun Sensor (DSS) 1 on
Earth Sensor (ES) 1 on
EPS/HEPAD on
Side-A thrusters selected
Normal Sun Acquisition Mode
Outer panel Solar Array Deployed
Trim Tab at 0 degrees

SIGNIFICANT EVENTS TIMELINE:

AMF #4:  Monday, July 30, at 04:07am EDT (DOY 211 @ 0807z).

A detailed timeline based on AMF replan will be provided post AMF#4,
Monday morning July 30, 2001.

SUMMARY OF ACTIVITIES (July 26):

Our second Apogee Maneuver Firing (AMF) #2 was executed today.  The burn lasting 11 minutes, 55 seconds was terminated approximately 4.5 seconds early due to the Main Spacecraft Thruster (MST) flange temperature exceeding its 260 degree abort criteria limit.  The flange temperature profile during this burn was nearly identical to the first AMF.  Following this maneuver the spacecraft was configured back to a normal sun acquisition mode and will remain in this mode until the next maneuver.  All subsystems are safe and remain well within limits.  The maneuver raised perigee approximately 1500 km and increased the orbital period to approximately 14 hours.

A meeting was conducted following the maneuver with spacecraft manufacturer, NASA and NOAA project management, and operations personnel to analyze AMF data and to finalize future AMF sequence plans.  As a result, the plan is to continue to perform shorter and more frequent AMFs on the order of 11 to 12 minutes in duration.  A total of 9 or 10 AMFs will now be required to achieve geosynchronous orbit.

The next maneuver is planned for Saturday, July 28, at 10:47pm EDT (DOY 210 @ 0247z).


Spacecraft Orbit Parameters
Inclination = 13.2 degrees
Apogee = 48476 km
Perigee = 10165 km
Orbital Period = 13.9 hours


SPACECRAFT CONFIGURATION:

AOCE 1 on
DIRA 2(gyros) on
Coarse Analog Sun Sensor (CASS) 1 on
Digital Sun Sensor (DSS) 1 on
Earth Sensor (ES) 1 on
EPS/HEPAD on
Side-A thrusters selected
Normal Sun Acquisition Mode
Outer panel Solar Array Deployed
Trim Tab at 0 degrees

SIGNIFICANT EVENTS TIMELINE:

AMF #3:  Saturday, July 28, at 10:47pm EDT (DOY 210 @ 0247z).

A detailed timeline based on AMF replan will be provided over the next couple of days.


SUMMARY OF ACTIVITIES (July 25):

Apogee Maneuver Firing (AMF) #1 was terminated early today by ground
command when the Main Spacecraft Thruster (MST) flange temperature
exceeded its 260 degree abort criteria limit.  The burn was terminated
approximately 13 minutes into a scheduled 53 minute burn.  The flange
temperature is used to give an indication of the thruster valve
temperature trends that will be experienced as a result of soakback
following maneuver completion.  The spacecraft was configured back to a
normal sun acquisition mode following the abort command with no
problems.  All subsystems are safe and remain well within limits.

Shortly after achieving Sun Acquisition, engineers and flight dynamics
personnel convened a meeting to start discussing AMF re-plans that will
be implemented over the next several days.   Preliminary analysis and
results from the meeting indicate that the only impact to the mission
timeline will be to conduct shorter more frequent AMFs over the next
several days to raise the orbit to a geostationary altitude.   Mission
planners are in the process of scheduling ground station and network
resources to accommodate the additional maneuvers.    Additional
meetings will be conducted on a Thursday to finalize AMF plans.


Other Significant Activities

The EPS/HEPAD was turned on at 1504z July 24.


Spacecraft Orbit Parameters
Inclination = 16.4 degrees
Apogee = 48420 km
Perigee = 8276 km
Orbital Period = 13.2 hours


SPACECRAFT CONFIGURATION:

AOCE 1 on
DIRA 2(gyros) on
Coarse Analog Sun Sensor (CASS) 1 on
Digital Sun Sensor (DSS) 1 on
Earth Sensor (ES) 1 on
EPS/HEPAD on
Side-A thrusters selected
Normal Sun Acquisition Mode
Outer panel Solar Array Deployed
Trim Tab at 0 degrees

SIGNIFICANT EVENTS TIMELINE:

A meeting was held earlier today to discuss AMF re-planning efforts
resulting from this morning's AMF#1 Abort.  With both NASA ad NOAA
management on hand it was determined that a 12 minute AMF#2 burn will be
executed tomorrow, July 26th, at 3:24pm EDT.  Data from this AMF#2 burn
will then be analyzed against not only the aborted GOES-M AMF#1 burn,
but also the AMF burn data observed during the previous GOES missions. 
Upon completion of their analyses, the engineering staff from NASA,
NOAA, and SS/L will then recommend to NASA and NOAA management the
subsequent AMF burn scenario/timeline to safely raise the GOES-M
satellite orbit to a geostationary altitude.

Mission planners are actively in the process of re-scheduling the ground
station and network resources to accommodate this maneuver.  Additional
meetings will be conducted on an as needed basis in order to optimize
the overall AMF plan.


SUMMARY OF ACTIVITIES (July 23):

GOES-M was successfully launched at 204/072301z.  Apogee was approximately 25 km 
low- overall an excellent ride from the Atlas/Centaur.   Following separation 
the sequence of command activities leading up to solar array deployment were 
successfully executed with a maximum DOD of 22% on the batteries well below the 
60% maximum allowable DOD and consistent with GOES-9, GOES-10, and GOES-11 
launches.   Initial acquisitions at Diego Garcia, Perth, and Canberra occurred 
close to predicts.   Three-way doppler between Diego Garcia and Canberra was 
successfully processed by Flight Dynamics to aid in quickly determining a 
post-separation orbit.

Initial commanding was performed through Diego to initialize the Attitude and 
Orbit Control Electronics (AOCE #1), vent the propellant lines, perform 300 msec 
thruster firings using the primary thrusters, command an off-axis sun 
acquisition, and deploy the solar array outer panel.  All command sequences were 
performed flawlessly and the spacecraft responded as expected.  Following solar 
array deployment, a command hand-over to Canberra was performed and two-way 
ranging was initiated to provide Flight Dynamics range data to accurately 
determine a post-launch orbit.  Following command handover, the trim tab was 
slewed 180 degrees away from the solar array panel.    As the spacecraft 
approached first apogee, intermediate attitude thruster control modes required 
from AMFs were all successfully exercised.   Following first apogee the side-B 
thrusters were exercised by performing 200 msec individual thruster firings with 
the spacecraft in a sun acquisition mode.  The launch script was completed two 
hours ahead of schedule.   The spacecraft will remain in a normal sun 
acquisition mode until preparation for  a 4th apogee maneuver firing scheduled 
for Tuesday evening.

SPACECRAFT CONFIGURATION:

AOCE 1 on
DIRA 2 on
CASS 1 on
DSS 1 on
ES 1 on
Side-B thrusters selected
Normal Sun Acquisition Mode
Outer panel Solar Array Deployed
Trim Tab slewed to 0 degrees


UPCOMING ACTIVITIES:

1)  EPS/HEPAD Turn on July 24 1443z
2)  AMF #1  July 24 0301z

ANOMALIES/CONCERNS:

NONE

MISCELLANEOUS:

SIGNIFICANT EVENTS TIMELINE (events will be dropped as theyâre completed):

Circularize Orbit July 23 thru August 9
	AMF 1     July 24
	AMF 2     July 27
	AMF 3     July 29
	AAM        July 31
	Trim 1     August 7
	Trim 2     August 8
	Trim 3     August 10

Deployments
	Mag boom and final SA deployment  August 1
	Dipole Estimation  August 2
	Momentum Wheel turn-on and Solar Sail Deployment  August 3	

GOES-M becomes GOES-12  July 31

SXI Turn-on  August 2

IMG/SND Outgas  August 1 to August 29

IMG/SND Contamination Avoidance   August 3 to August 9

First VIS Image  August 7

First SXI Image  August 21

GOES Project Science and Images