Forwarded from Neal Ausman, Galileo Mission Director

                                 GALILEO
                     MISSION DIRECTOR STATUS REPORT
                               POST-LAUNCH
                           April 23 - 29, 1993

SPACECRAFT

1.  On April 22 and 23, delta Differenced One-way Range (DOR) passes were
performed over DSS-14/63 (Goldstone/Madrid 70 meter antennas) and DSS-14/43
(Goldstone/Canberra 70 meter antennas), respectively.  Initial results 
indicate the delta DOR pass on April 22 was unsuccessful due to ground
station hardware problems but the one on April 23 was successfully performed.

2.  On April 23, a cruise science Memory Readout (MRO) was performed for the
Magnetometer (MAG) instrument.  Analysis indicates the data was received
properly.

3.  On April 23, the spare power relay contacts were commanded closed via the
spacecraft stored sequence.  These relays were commanded closed by the CDS
(Command Data Subsystem) prior to launch and were again commanded closed to
preclude the possibility at Jupiter of the PPS relays/wiring being a
source of internal electrostatic charge (IESD).

4.  On April 26, cruise science Memory Readouts (MRO) were performed for the
Extreme Ultraviolet Spectrometer (EUV), Dust Detector (DDS), and Magnetometer
(MAG) instruments.  Preliminary analysis indicates the data was received
properly.

5.  During the period from April 26 to April 27, a navigation cycle was
performed.  This navigation cycle provided near-continuous acquisition of
two-way doppler and ranging data during three consecutive passes of the
spacecraft over DSS-63, DSS-14, and DSS-43.

6.  On April 26, real-time commands were sent to test slew the Radio Relay
Antenna (RRA) in preparation for the mini-sequence slew test on April 28.
The RRA was slewed from approximately 3.5 degrees from stow to approximately
20.3 degrees.  Preliminary analysis indicated the antenna slewed to about 18
degrees which was well within the predicted range.  The RRA was commanded back
to approximately 15.2 degrees from stow.  Preliminary analysis indicated the
antenna reached about 15.8 degrees also well within the predicted range.  The
RRA motor temperature was at 1 degree C at the start of the activity and had
increased to 1.6 degrees C at its completion.

     After verifying proper RRA slewing, the RRA slew test mini-sequence was
uplinked to the spacecraft for execution on April 28.  Upon successful uplink,
a Delayed Action Command (DAC) was sent which will reposition the stator on
May 4 to its initial pre-test position.  Also, a DAC was sent to turn the
Two-Way Noncoherent (TWNC) on April 28 prior to the start of the RRA slew test
mini-sequence.

7.  On April 27, a NO-OP command was sent to reset the command loss timer to
264 hours, its planned value during this mission phase.

8.  On April 28, the RRA slew test executed nominally.  The spacecraft under
stored sequence control performed six RRA slews starting at about 16 degrees
from stow and going to 53 degrees, back to 25 degrees, then to 51 degrees,
back to 22 degrees, then to 48 degrees and then back to 21 degrees.  All of
the slews were well within the predicted range.  The RRA motor temperature was
at 2.3 degrees C at the start of the activity and had increased to 4.4
degrees C at its completion.  After completion of the RRA slews, real-time
commands were sent to reconfigure back to the pre-test configuration.

9.  The AC/DC bus imbalance measurements have not exhibited significant change
(greater than 25 DN) throughout this period.  The AC measurement reads 17 DN
(3.9 volts).  The DC measurement reads 134 DN (15.7 volts).  These
measurements are consistent with the model developed by the AC/DC special
anomaly team.

10. The Spacecraft status as of April 29, 1993, is as follows:

       a)  System Power Margin -  75 watts
       b)  Spin Configuration - Dual-Spin
       c)  Spin Rate/Sensor - 3.15rpm/Star Scanner
       d)  Spacecraft Attitude is approximately 23 degrees
           off-sun (lagging) and 4 degrees off-earth (leading)
       e)  Downlink telemetry rate/antenna- 40bps(coded)/LGA-1
       f)  General Thermal Control - all temperatures within
           acceptable range
       g)  RPM Tank Pressures - all within acceptable range
       h)  Orbiter Science- Instruments powered on are the PWS,
           EUV, UVS, EPD, MAG, HIC, and DDS
       i)  Probe/RRH - powered off, temperatures within
           acceptable range
       j)  CMD Loss Timer Setting - 264 hours
           Time To Initiation - 203 hours


GDS (Ground Data Systems):

1.  The first Galileo-GDS test of the MGDS V18.0 Command System (CMD) took
place April 27, 1993 with DSS-61 (Madrid 34 meter antenna).  The test went
well and demonstrated that the new command system interfaced with the new DSN
(Deep Space Network) Group 5 Command Processor Assembly (CPA).  The test was
successful and the next test for V18.0 CMD is scheduled for May 1, 1993 with
DSS-15 (Goldstone 34 meter antenna).

2.  The April System Engineers Monthly Report(SEMR)/Ground System Development
Office (GSDO) MMR was conducted Thursday, April 29.   A review of current
Project and Institutional (DSN and MOSO) system status was conducted.  On-going
cruise development plus the GSDO Phase 1 and 2 delivery schedules, past months
accomplishments  and potential problem areas were discussed.  No significant
schedule changes or significant problems were reported.


TRAJECTORY

     As of noon Thursday, April 29, 1993, the Galileo Spacecraft trajectory
status was as follows:

	Distance from Earth         187,745,300 km (1.26 AU)
	Distance from Sun           296,335,800 km (1.98 AU)
	Heliocentric Speed          89,100 km per hour
	Distance from Jupiter       522,015,800 km
	Round Trip Light Time       20 minutes, 58 seconds

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