ACE Weekly 11/07/2012 - 11/13/2012

All ACE spacecraft subsystems are performing as expected.

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Orbit/Attitude:

	Type        Attitude
	Date        11/13/2012
	DOY         318 2012
	Thrusters   2R 4R+ 4R-
	Duration    19:22 min
	Start       20:41:42z
	Stop        21:01:04z
	HGAStart    -7.72deg
	HGAStop     +8.45deg
	SunStart     6.37deg
	SunStop     11.81deg
	SpinStart   5.0807rpm
	SpinStop    5.0856rpm
	Nutation     0.15deg
	Firing      99 pulses
	FuelUsed      0.2944lbs
	FuelRemain  118.2604lbs
	FinalSCMass 1352.520lbs

The next attitude maneuver and station keeping #63 are scheduled for
Monday 11/19/2012.


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OCRs:

None

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Activities:

Data Capture:  100%  DOY 309-316 2012

The next WS1 certification test is scheduled for 11/20/2012, which
coincides with a day we are unable to get a DSN pass.

NOAA SWPC scheduled Air Force support for tracking ACE while NICT
(Japan) was down on DOY 314 & 315 and KSWC (Korea) remains down for the
past month.  This data is routed through the MMOC since the NISN SCD has
not yet been upgraded to perform Reed-Solomon decoding.


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Anomalies:

None

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Average Sun Angles With Weekly Attitude Maneuvers

Dates        Avg SEV  Avg Sun  Comments
-----------  -------  -------  --------------------------------------
10/18-10/23  5.1deg   11.0deg
10/23-10/28  3.3deg    9.3deg
10/28-11/06  2.0deg    7.3deg  sun-sev=5.3 due to 9days between mnvrs
11/06-11/13  3.8deg    8.4deg

ACE is moving away from the sun-earth line (larger sun-earth-vehicle
angle, SEV) which allows for larger sun angles over the next 5 weeks.
After mid-December, the L1 orbit will bring ACE back towards the
sun-earth line (smaller SEV angles).

The following is background information that will be included in each
weekly report.
The project has accepted the SWEPAM team proposal to keep the spacecraft
at larger sun angles with weekly attitude maneuvers.  The SWEPAM-Ion
instrument has a series of channel electron multipliers (CEMs) and
larger sun angles allows more responsive CEMs to measure the solar wind.
The maximum sun angle follows the Sun-Earth-Vehicle angle (SEV).  The
SEV angle is determined by the size/shape of the orbit around L1.  When
the spacecraft antenna is pointed directly towards earth, the
spacecraft's sun angle will be equal to the Sun-Earth-Vehicle angle.
With weekly maneuvers, the sun angle can be kept ~6deg more than the SEV
angle.  This results in the spacecraft antenna aspect angle being kept
between 5 and 9 degrees and never pointing directly back at earth.  For
reference, the SWEPAM team prefers sun angles above 13 degrees.  With
the current size of the L1 orbit, the sun angle will be above 13 degrees
for ~45% of the time.