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=--=--=START=--=--= NASA Spacelink File Name:930604.REL

6/4/93: STATION REDESIGN TEAM TO SUBMIT FINAL REPORT

Mark Hess
Headquarters, Washington, D.C.                         June 4, 1993

RELEASE:  93-104


        The Space Station Redesign Team, comprised of representatives from NASA
and the international partners, will submit its final report on three space
station options to the White House Advisory Committee on the Redesign of the
Space Station on Monday, June 7, at the Stouffer Hotel in Crystal City, Va.

        The three options, the results of nearly 3 months of intensive research
and analysis, include a modular concept that would use existing flight-proven
hardware, a derivative of the current Space Station Freedom design and a space
station that could be placed into orbit with a single launch of a
Shuttle-derived vehicle.

        "The Team has done a tremendous job," said NASA Administrator Daniel
Goldin. "They have developed 3 technically viable space stations.  Each
provides for international cooperation, establishes a fully-capable space
research center in orbit that will enable high priority science, technology and
engineering research and in every case, do it for significantly less money than
the current Space Station Freedom baseline."

        "The cost estimates provided by the Redesign Team reflect complete and
accurate costs of each option and the current Space Station Freedom design,"
Goldin said.

        The baseline Freedom cost numbers were subjected to rigorous review by
an expert NASA team working apart from the Freedom program.  Those results,
plus the costs of the three space station options, are being reviewed by an
experienced, independent cost analysis team created by the White House advisory
committee.

        "The estimates are honest and defensible.  They provide a solid basis
for decision because they are comprehensive and compare all options on an
apples- to-apples basis," Goldin said.  "Our books are open and will withstand
the closest scrutiny."

President Directs Redesign

        An assessment early in 1993 by the incoming Administration determined
the increases in the Space Station Freedom budget in the outyears would not fit
within the expected NASA budget, which the Administration planned to cut by
about 15 percent over the next 5 years in the interest of federal deficit
reduction.  The White House also wanted to place increased emphasis on other
NASA programs such as aeronautics and science.

        Rather than cancel the program, President Clinton directed NASA to
redesign the space station and produce a configuration that would significantly
reduce development, operations and utilization costs, while at the same time
honor the United StatesU commitments to the international partners and provide
the essential resources to advance the nationUs scientific and technology
development capabilities in space.

        The Station Redesign Team also was charged with recommending new and
streamlined management structures and acquisition strategies and to develop
operational concepts that would cut operations costs in half.

        Monday's meeting will be the third and final public meeting with the
Advisory Committee. Chaired by MIT President Dr. Charles Vest, the 16- member
Advisory Committee will provide an independent assessment of the designs, cost,
proposed management structure and the operations plan, and forward that
assessment to the President on or about June 10.

        "The objective of the redesign team was to develop options for a
redesigned space station," said Goldin. "The team was not asked to recommend
one option over the others but rather to characterize each design's strengths
and weaknesses in an unbiased manner."

        Directed by Deputy Associate Administrator for Space Flight and former
astronaut Bryan O'Connor, the NASA team was led by a core group of about 36
people.  The diversified team had at least one representative from each NASA
center, several scientists and engineers with backgrounds that ranged from
program managers to spacecraft designers.

        Ten representatives from the international partners - the European
Space Agency, Japan and Canada - and from Italy formed the remainder of the
core team.  Consultants from other government agencies and from industry served
as advisors to the group.  The core team, working in Crystal City, Va.,
received technical support on each of the options by people from across NASA.


Station Objectives Outlined

        Goldin provided specific objectives and constraints, reflecting
guidance from the Administration, to the team in an implementation letter of
March 9, 1993.  In the letter, Goldin stressed that the redesigned space
station must:

% Provide a cost effective solution to basic and applied research challenges
whose merit is clearly indicated by scientific peer review, significant
industrial cost sharing or other widely accepted method;

% Provide the capability for significant long-duration space research in
materials and life sciences during this decade;

% Bring both near-term and long-term annual funding requirements within the
constraints of the budget;

% Continue to accommodate and encourage international participation; and

% Reduce technical and programmatic risk to acceptable levels.

        Other directions to the team from Goldin included constraints or
objectives of greatly reducing on-orbit assembly and checkout; planning for a
shorter on-orbit lifetime (e.g., 10 years extendible to 15 years); greatly
reducing the number of Shuttle launches and extravehicular requirements for
deployment; advancing the permanently manned capability date; and
reestablishing national leadership in space.

        In addition, the team was directed to give consideration to greater use
of Shuttle and Spacelab capabilities (which may be modified to allow longer
stays in orbit) and the Russian Mir space station.

Budget Guidelines Set

        In addition, Dr. John Gibbons, the PresidentUs Science Advisor,
provided budget guidance for the Advisory Committee to use in their
deliberations.  For the 5-year period from Fiscal Years 1994 to 1998, NASA was
to assume a low option of $5 billion, a mid-range option of $7 billion and a
high option of $9 billion.

        Activities which were to be paid for within the $5 billion, $7 billion
and $9 billion accounts included: space station development, operations,
utilization (including building science experiments and other payloads for the
station and for Spacelab as well as the ground infrastructure to manage and
deliver data to the users), Shuttle integration, facilities, research
operations support, termination costs, transition costs and an appropriate
level of reserves.

Three Main Options Evolve

        Option A is a modular build-up configuration which uses a combination
of Space Station Freedom hardware and flight-qualified space systems from other
sources, including the potential use of a self-contained DoD spacecraft called
"Bus-1" to provide propulsion, guidance, navigation and control.  Option A
includes a "Bus-1" configuration and a configuration without "Bus-1." Option A
has four distinct phases of buildup including: Power Station (1
photovoltaic(PV) array on-orbit for increased power to a docked
orbiter/Spacelab); Human Tended Capability (adds U.S. laboratory);
International Human Tended (adds an additional PV array and international
elements); and Permanent Human Capability (adds third PV array, the U.S.
habitat module and two Russian Soyuz ACRVs).

        Option B is derived from mature Space Station Freedom designs.  It
makes maximum use of current systems and hardware to provide an incrementally
increasing capability, emphasizing accommodations for users, adherence to
international partner commitments, flexibility and growth potential, and
recommends some system changes to save money.  Like Option A, the
Freedom-derived option is built up over 4 stages.  From an assembly sequence
standpoint, the primary difference between the Option A and B is that the
Freedom-derived configuration adds the third PV array before the international
partner elements are added.

        Option C is a single-launch space station.  This configuration features
a 92- foot-long, 23-foot-diameter core module launched as part of a Space
Shuttle vehicle and uses an existing external tank, solid rocket boosters and
Shuttle main engines.  The module would provide 26,000 cubic feet of
pressurized volume, separated into 7 "decks" connected by a centralized
passageway.  Seven berthing ports would be located on the circumference of the
module to place the international modules and other elements.

        "Each option is capable of accomplishing the mission of the space
station," said Goldin. "All of them offer significant scientific and
engineering research capabilities, especially in their permanently human
presence stages."

        Goldin said all the options also would:

% make maximum use of Space Station Freedom systems and components, which have
completed a rigorous critical design review, where it is both cost effective
and schedule enhancing, thus benefiting from the nationUs investment to date in
the Freedom program;

% incorporate changes that would reduce complexity and increase the probability
for meeting cost and schedule;

% achieve substantial savings through a streamlined management structure that
provides clear lines of authority, reduces overlap and gives accountability and
authority to the lowest level to get the job done; and

% benefit from a new operations approach that would significantly reduce
operational costs.

        Goldin said Russian hardware alternatives, where it could benefit the
redesigned space station program, also were investigated.  In all three
options, the Soyuz crew return vehicle has been baselined as the assured crew
return vehicle.  Launch capability and other systems developed and in operation
in the Russian space program are described in the report and will be considered
for use in the redesigned space station or in future improvements.

-end-
     Source:NASA Spacelink    Modem:205-895-0028  Internet:192.149.89.61
=--=--=-END-=--=--=

=--=--=START=--=--= NASA Spacelink File Name:930604.SHU

KSC SHUTTLE STATUS REPORT 6/4/93


        KENNEDY SPACE CENTER SPACE SHUTTLE STATUS REPORT
                      Friday, June 4, 1993

KSC Contact: Bruce Buckingham       407-867-2468 (fax [phone])
-----------------------------------------------------------------

Mission: STS-57/Spacehab/EURECA-Retrieval  Orbital Alt. 287 miles
Vehicle: Endeavour/OV-105                 Inclination: 28 degrees
Location: Pad 39-B                        Crew Size: 6
Target Launch Date/Window: Around the third weekend of June
Target KSC Landing Date/Time: TBD
Expected Mission Duration: 7 days/23 hours (if cryogenics allow)

IN WORK TODAY:
*  Secure new high pressure oxidizer turbopump (HPOTP) to main
   engine 2
*  Pressurization checks and trickle purge of Reaction Control
   System and Orbital Maneuvering System

WORK SCHEDULED:
*  Engine and HPOTP leak checks
*  Helium Signature test

WORK COMPLETED:
*  Bolted HPOTP to main engine 2
*  Re-position body flap and main engines 1 and 3
*  HPOTP powerhead checks

-----------------------------------------------------------------
Mission: STS-51/ACTS-TOS/ORFEUS-SPAS      Orbital Alt.: 184 miles
Vehicle: Discovery/OV-103                 Inclination: 28 degrees
Location: OPF bay 3                       Crew Size: 5
Mission Duration: 9 days/22 hours  Target Launch Period: mid-July

IN WORK TODAY:
*  Orbiter aft compartment closeouts
*  Orbiter mid-body closeouts
*  External tank/solid rocket booster electrical checks in VAB
   high bay 1
*  Microwave landing system tests

WORK SCHEDULED:
*  Orbiter/Forward Reaction Control System (FRCS) interface
   verification checks
*  Crew equipment interface tests
*  Main landing gear functional checks

WORK COMPLETED:
*  Freon coolant loop sampling
*  External tank/solid rocket booster hard mate
*  Orbiter/payload pre-installation and interface verification
   tests

-----------------------------------------------------------------
Mission: STS-58/SLS-2              Orbital Altitude: 176 miles
Vehicle: Columbia/OV-102           Inclination: 39 degrees
Location: OPF bay 2                Crew Size: 7
Mission Duration: 14 days
Target launch period: Early September

IN WORK TODAY:
*  Operations to remove fifth cryogenic tank set
*  Orbital maneuvering system hypergolic deservice preparations
*  Auxiliary power unit catch bottle drain
*  Configure payload bay for SLS-2
*  Preparations to remove main engines

WORK SCHEDULED:
*  Close OPF bay this weekend for hypergolic deservice operations
*  Remove main engines

WORK COMPLETED:
*  Remove and replace thruster from left OMS pod

     Source:NASA Spacelink    Modem:205-895-0028  Internet:192.149.89.61
=--=--=-END-=--=--=

=--=--=START=--=--= NASA Spacelink File Name:930604.SKD

Daily News/TV Sked 6-4-93

Daily News
Friday, June 4, 1993                  Two Independence Square, Washington, D.C.

Audio Service: 202/358-3014


 % STS-57 mission update;
 % Spacecraft Technology Briefing at Lewis;
 % NASA exhibits at the Paris Air Show.


Technicians at the Kennedy Space Center, in
preparation for the upcoming STS-57 mission,
plan to secure the new high pressure oxidizer
turbopump to main engine #2.  They will also
conduct pressurization checks and trickle purge
of the reaction control system and the orbital
maneuvering system.  Scheduled work on the
Space Shuttle Endeavour includes engine and
turbopump leak checks as well as conducting the
helium signature test.

At present, the targeted launch date is around the
third week in June.  Expected duration of the
mission is 7 days and 23 hours.

* * * * * * * * * * * * * * * *

NASA'S Lewis Research Center plans to host more
than 100 "decision makers" from industry and
government on June 8-9, 1993.

The purpose of this Spacecraft Technology
Industry Briefing is to give a base for reshaping
technology development programs at the Lewis
Research Center and NASA to better serve the
customer's needs.  The participants will discuss
viewpoints in an open forum on topics including
communications, power propulsion and materials
and structures.

* * * * * * * * * * * * * * * *

With emphasis on environmental compatibility,
the NASA exhibit at this year's Paris Air Show will
focus on high speed research for a new
generation of airliners.  NASA will also exhibit a
50-monitor videowall.  The video presentation
has participants discussing space station, space
technology, space science, space exploration and
aeronautics.


This year's exhibit theme, "A New Age of
Exploration--Expanding the Frontiers of Air and
Space for the Benefit of All" acknowledges the
many contribution of NASA's international
partners in human and robotic spaceflight and
the importance of the international cooperation
to help meet the challenges of the 1990's and
beyond.  The show dates for this years event are
June 10 - 20.

* * * * * * * * * * * * * * * *




Here's the broadcast schedule for Public Affairs events on NASA TV.
Note that all events and times may change without notice and that all
times listed are Eastern.


Friday, June 4, 1993

        Noon    NASA Today news program.
        12:15 pm        Aeronautics & Space Report.
        12:30 pm        The Aeronauts.
          1:00 pm       Shuttle Flow at KSC.
          1:30 pm       Map the Martian World.
          2:00 pm       NSTA Convention.
          2:30 pm       Life on the Moon.
          3:00 pm       Al Sherman on Quality.



NASA TV is carried on GE Satcom F2R, transponder 13, C-Band, 72
degrees West Longitude, transponder frequency is 3960 MHz, audio
subcarrier is 6.8 MHz, polarization is vertical.
     Source:NASA Spacelink    Modem:205-895-0028  Internet:192.149.89.61
=--=--=-END-=--=--=

=--=--=START=--=--= NASA Spacelink File Name:6_10_9.TXT

6/4/93: STATION REDESIGN TEAM TO SUBMIT FINAL REPORT

Mark Hess
Headquarters, Washington, D.C.                         June 4, 1993

RELEASE:  93-104


        The Space Station Redesign Team, comprised of representatives from NASA
and the international partners, will submit its final report on three space
station options to the White House Advisory Committee on the Redesign of the
Space Station on Monday, June 7, at the Stouffer Hotel in Crystal City, Va.

        The three options, the results of nearly 3 months of intensive research
and analysis, include a modular concept that would use existing flight-proven
hardware, a derivative of the current Space Station Freedom design and a space
station that could be placed into orbit with a single launch of a
Shuttle-derived vehicle.

        "The Team has done a tremendous job," said NASA Administrator Daniel
Goldin. "They have developed 3 technically viable space stations.  Each
provides for international cooperation, establishes a fully-capable space
research center in orbit that will enable high priority science, technology and
engineering research and in every case, do it for significantly less money than
the current Space Station Freedom baseline."

        "The cost estimates provided by the Redesign Team reflect complete and
accurate costs of each option and the current Space Station Freedom design,"
Goldin said.

        The baseline Freedom cost numbers were subjected to rigorous review by
an expert NASA team working apart from the Freedom program.  Those results,
plus the costs of the three space station options, are being reviewed by an
experienced, independent cost analysis team created by the White House advisory
committee.

        "The estimates are honest and defensible.  They provide a solid basis
for decision because they are comprehensive and compare all options on an
apples- to-apples basis," Goldin said.  "Our books are open and will withstand
the closest scrutiny."

President Directs Redesign

        An assessment early in 1993 by the incoming Administration determined
the increases in the Space Station Freedom budget in the outyears would not fit
within the expected NASA budget, which the Administration planned to cut by
about 15 percent over the next 5 years in the interest of federal deficit
reduction.  The White House also wanted to place increased emphasis on other
NASA programs such as aeronautics and science.

        Rather than cancel the program, President Clinton directed NASA to
redesign the space station and produce a configuration that would significantly
reduce development, operations and utilization costs, while at the same time
honor the United StatesU commitments to the international partners and provide
the essential resources to advance the nationUs scientific and technology
development capabilities in space.

        The Station Redesign Team also was charged with recommending new and
streamlined management structures and acquisition strategies and to develop
operational concepts that would cut operations costs in half.

        Monday's meeting will be the third and final public meeting with the
Advisory Committee. Chaired by MIT President Dr. Charles Vest, the 16- member
Advisory Committee will provide an independent assessment of the designs, cost,
proposed management structure and the operations plan, and forward that
assessment to the President on or about June 10.

        "The objective of the redesign team was to develop options for a
redesigned space station," said Goldin. "The team was not asked to recommend
one option over the others but rather to characterize each design's strengths
and weaknesses in an unbiased manner."

        Directed by Deputy Associate Administrator for Space Flight and former
astronaut Bryan O'Connor, the NASA team was led by a core group of about 36
people.  The diversified team had at least one representative from each NASA
center, several scientists and engineers with backgrounds that ranged from
program managers to spacecraft designers.

        Ten representatives from the international partners - the European
Space Agency, Japan and Canada - and from Italy formed the remainder of the
core team.  Consultants from other government agencies and from industry served
as advisors to the group.  The core team, working in Crystal City, Va.,
received technical support on each of the options by people from across NASA.


Station Objectives Outlined

        Goldin provided specific objectives and constraints, reflecting
guidance from the Administration, to the team in an implementation letter of
March 9, 1993.  In the letter, Goldin stressed that the redesigned space
station must:

% Provide a cost effective solution to basic and applied research challenges
whose merit is clearly indicated by scientific peer review, significant
industrial cost sharing or other widely accepted method;

% Provide the capability for significant long-duration space research in
materials and life sciences during this decade;

% Bring both near-term and long-term annual funding requirements within the
constraints of the budget;

% Continue to accommodate and encourage international participation; and

% Reduce technical and programmatic risk to acceptable levels.

        Other directions to the team from Goldin included constraints or
objectives of greatly reducing on-orbit assembly and checkout; planning for a
shorter on-orbit lifetime (e.g., 10 years extendible to 15 years); greatly
reducing the number of Shuttle launches and extravehicular requirements for
deployment; advancing the permanently manned capability date; and
reestablishing national leadership in space.

        In addition, the team was directed to give consideration to greater use
of Shuttle and Spacelab capabilities (which may be modified to allow longer
stays in orbit) and the Russian Mir space station.

Budget Guidelines Set

        In addition, Dr. John Gibbons, the PresidentUs Science Advisor,
provided budget guidance for the Advisory Committee to use in their
deliberations.  For the 5-year period from Fiscal Years 1994 to 1998, NASA was
to assume a low option of $5 billion, a mid-range option of $7 billion and a
high option of $9 billion.

        Activities which were to be paid for within the $5 billion, $7 billion
and $9 billion accounts included: space station development, operations,
utilization (including building science experiments and other payloads for the
station and for Spacelab as well as the ground infrastructure to manage and
deliver data to the users), Shuttle integration, facilities, research
operations support, termination costs, transition costs and an appropriate
level of reserves.

Three Main Options Evolve

        Option A is a modular build-up configuration which uses a combination
of Space Station Freedom hardware and flight-qualified space systems from other
sources, including the potential use of a self-contained DoD spacecraft called
"Bus-1" to provide propulsion, guidance, navigation and control.  Option A
includes a "Bus-1" configuration and a configuration without "Bus-1." Option A
has four distinct phases of buildup including: Power Station (1
photovoltaic(PV) array on-orbit for increased power to a docked
orbiter/Spacelab); Human Tended Capability (adds U.S. laboratory);
International Human Tended (adds an additional PV array and international
elements); and Permanent Human Capability (adds third PV array, the U.S.
habitat module and two Russian Soyuz ACRVs).

        Option B is derived from mature Space Station Freedom designs.  It
makes maximum use of current systems and hardware to provide an incrementally
increasing capability, emphasizing accommodations for users, adherence to
international partner commitments, flexibility and growth potential, and
recommends some system changes to save money.  Like Option A, the
Freedom-derived option is built up over 4 stages.  From an assembly sequence
standpoint, the primary difference between the Option A and B is that the
Freedom-derived configuration adds the third PV array before the international
partner elements are added.

        Option C is a single-launch space station.  This configuration features
a 92- foot-long, 23-foot-diameter core module launched as part of a Space
Shuttle vehicle and uses an existing external tank, solid rocket boosters and
Shuttle main engines.  The module would provide 26,000 cubic feet of
pressurized volume, separated into 7 "decks" connected by a centralized
passageway.  Seven berthing ports would be located on the circumference of the
module to place the international modules and other elements.

        "Each option is capable of accomplishing the mission of the space
station," said Goldin. "All of them offer significant scientific and
engineering research capabilities, especially in their permanently human
presence stages."

        Goldin said all the options also would:

% make maximum use of Space Station Freedom systems and components, which have
completed a rigorous critical design review, where it is both cost effective
and schedule enhancing, thus benefiting from the nationUs investment to date in
the Freedom program;

% incorporate changes that would reduce complexity and increase the probability
for meeting cost and schedule;

% achieve substantial savings through a streamlined management structure that
provides clear lines of authority, reduces overlap and gives accountability and
authority to the lowest level to get the job done; and

% benefit from a new operations approach that would significantly reduce
operational costs.

        Goldin said Russian hardware alternatives, where it could benefit the
redesigned space station program, also were investigated.  In all three
options, the Soyuz crew return vehicle has been baselined as the assured crew
return vehicle.  Launch capability and other systems developed and in operation
in the Russian space program are described in the report and will be considered
for use in the redesigned space station or in future improvements.

-end-
     Source:NASA Spacelink    Modem:205-895-0028  Internet:192.149.89.61
=--=--=-END-=--=--=

=--=--=START=--=--= NASA Spacelink File Name:6_2_18_5.TXT

 NOTE: This file is too large {27855 bytes} for inclusion in this collection.
    The first line of the file:

- Current Two-Line Element Sets #203 -

     Source:NASA Spacelink    Modem:205-895-0028  Internet:192.149.89.61
=--=--=-END-=--=--=

=--=--=START=--=--= NASA Spacelink File Name:6_7_2_14_2.TXT

 NOTE: This file is too large {18375 bytes} for inclusion in this collection.
    The first line of the file:

HUBBLE SPACE TELESCOPE: A NEW VIEW OF THE UNIVERSE

     Source:NASA Spacelink    Modem:205-895-0028  Internet:192.149.89.61
=--=--=-END-=--=--=

=--=--=START=--=--= NASA Spacelink File Name:6_7_2_14_3.TXT

 NOTE: This file is too large {17951 bytes} for inclusion in this collection.
    The first line of the file:

HST OBSERVER SPRING 1991

     Source:NASA Spacelink    Modem:205-895-0028  Internet:192.149.89.61
=--=--=-END-=--=--=

=--=--=START=--=--= NASA Spacelink File Name:6_8_3_4_26.TXT

MGN STATUS 6/3/93

Magellan Status Report for 6-3-93


1.  The Magellan Transition Experiment continues to go extremely well.
The spacecraft has completed its "walk-in" phase to the desired
aerobraking corridor. The spacecraft has made 70 atmospheric drag
passes and the periapsis is now under 140.4 km and the apoapsis has
been reduced below 7800 km.   All subsystems are reported to be
nominal.

2.  The solar panels continue to increase by 40-45 degrees C during
the drag pass, reaching a peak of 64 degrees C.

3.  Spacecraft controllers are considering performing the desat
shortly before the drag pass in order to reduce the residual momentum
and the resulting thruster activity.  This may reduce the propellant
usage during the drag pass, even though the present usage is under the
allocated amount.

4.  The periapsis altitude will be raised about 800 meters by the
first "1/2 up" COTM is now planned for orbit #7702  at 10:20 AM
tomorrow.  However, it will continue its downward drift and require a
series of 1/2 up COTMs at intervals of 4 to 9 days as the general
downward drift continues.

COTM = Corridor Orbit Trim Maneuver
     Source:NASA Spacelink    Modem:205-895-0028  Internet:192.149.89.61
=--=--=-END-=--=--=

=--=--=START=--=--= NASA Spacelink File Name:6_8_5_3_12.TXT

ULYSSES STATUS REPORT 139 & 140  APRIL 20-26, 1993


ULYSSES STATUS REPORT 139

JET PROPULSION LABORATORY

27 April 1993

SUBJECT:  ULYSSES MISSION OPERATIONS REPORT No. 139

PERIOD:   20th April to 26th April 1993


1.   MISSION OPERATIONS

     Experiment reconfigurations have been carried out as required.

     On 20th April a routine KEP GAS monthly health check was performed.

     On 21st April a HED calibration was performed.

     On 26th April a KEP EPAC in-flight calibration was carried out.

     An Earth pointing manoeuvre was performed on 23rd April.

     An average of 96.2% data recovery was achieved during the reporting
     period.

     The percentage of data acquired as a function of bit rate is as follows:

     1024 bps 44.3 %
      512 bps 51.9 %

2.   SPACECRAFT STATUS

     POWER

     Nominal.

     Estimated S/C power consumption 255 watts.

     AOCS

     Nominal.

     TTC

     The  spacecraft is currently configured with receiver  2  as
     the  prime  unit  fed  via the high gain  antenna  and  with
     receiver 1 as backup fed through the low gain antenna  (LGA-
     F). The downlink is provided through EPC2/TWTA2.

     The  34  meter  ground stations are in use  to  support  TTC
     operations.   Ranging from 34 meter or 70 meter antennas  is
     once again routinely performed.

     Received downlink level -140 dBm.(34 meter) X-band.

     (Variations of up to 10 db. can be expected as a  result  of
     station  antenna  in  use,  local  weather  conditions,  and
     spacecraft antenna off-pointing).

     Received uplink level -122 dBm.

     DATA HANDLING

     Nominal.

     THERMAL

     Nominal.

3.   FLIGHT DYNAMICS

     Solar  Aspect    The  angle increased from  10.76  on  Angle
     (deg.)   20th April to 11.30 on 26th April.

     Sun-Probe-Earth   The angle increased from  10.62  on  Angle
     (deg.)     20th April to 11.21 on 26th April.

     Spin Rate               4.978 rpm.

4.   ORBITAL DATA

     Correction to last week's data which were in error:

     Data taken at 13:00 PDT on 19th April.
     Distance from Earth                635,083,459 km.
     Velocity relative to the Earth          86,639 km/hr.
     Velocity relative to the Sun            37,221 km/hr.
     Ecliptic latitude                         22.0 deg/south

     This week's data:

     Data taken at 13:00 PDT on 26th April.
     Distance from Earth                646,502,166 km.
     Velocity relative to the Earth          84,016 km/hr.
     Velocity relative to the Sun            37,485 km/hr.
     Ecliptic latitude                         22.5 deg/south

5.   PLANNED OPERATIONS

     Routine  data  gathering operations will  continue  together
     with experiment reconfigurations as required.

     On 27th April a SIM HET calibration will be carried out.

     A GRU program reload will be performed on 30th April.

     On  3rd May a KEP EPAC in-flight calibration will be carried
     out.

     An  Earth  pointing manoeuvre will be carried  out  on  28th
     April.

6.   GROUND SEGMENT

     The  ground segment performed nominally during the reporting
     period, with the exception of a period of bad data caused by
     heavy rain in Madrid on 24th April.





ULYSSES MISSION STATUS REPORT  4/27/93

ULYSSES: The spacecraft is in a highly inclined solar orbit, now
almost 30 degrees south (relative to the Sun's equator), in
transit from its Jupiter gravity assist in February 1992 toward
its solar polar passages (about 80 degrees south and north) in
1994 and 1995.  Ulysses spacecraft condition and performance are
excellent, and cruise science data-gathering continues.  The
Ulysses spacecraft was built by the European Space Agency and
launched October 6, 1990 aboard Space Shuttle Discovery, with IUS
and PAM-S stages.






ULYSSES STATUS REPORT 140   APRIL 27 - MAY 3, 1993

JET PROPULSION LABORATORY

May 10, 1993

ULYSSES MISSION OPERATIONS REPORT No. 140

PERIOD:   27th April to 3rd May 1993

1.   MISSION OPERATIONS

     Experiment reconfigurations have been carried out as
     required.

     On 27th April a SIM HET calibration was carried out.

     A GRU program reload was performed on 30th April.

     On 3rd May a KEP EPAC in-flight calibration was carried out.

     An Earth pointing manoeuvre was performed on 28th April and
     3rd May.

     An average of 96.9% data recovery was achieved during the
     reporting period.

     The percentage of data acquired as a function of bit rate is
     as follows:

     1024 bps 56.08 %
      512 bps 38.82 %

2.   SPACECRAFT STATUS

     POWER

     Nominal.

     Estimated S/C power consumption 255 watts.

     AOCS

     Nominal.

     TTC

     The spacecraft is currently configured with receiver 2 as
     the prime unit fed via the high gain antenna and with
     receiver 1 as backup fed through the low gain antenna (LGA-
     F). The downlink is provided through EPC2/TWTA2.

     The 34 meter ground stations are in use to support TTC
     operations.  Ranging from 34 meter or 70 meter antennas is
     once again routinely performed.

     Received downlink level -140 dBm.(34 meter) X-band.

     (Variations of up to 10 db. can be expected as a result of
     station antenna in use, local weather conditions, and
     spacecraft antenna off-pointing).

     Received uplink level -123 dBm.

     DATA HANDLING

     Nominal.

     THERMAL

     Nominal.

3.   FLIGHT DYNAMICS

     Solar Aspect   The angle increased from 11.29 on Angle
     (deg.)   27th April to 12.07 on 3rd May.

     Sun-Probe-Earth  The angle increased from 11.30 on Angle
     (deg.)     27th April to 11.75 on 3rd May.

     Spin Rate               4.978 rpm.

4.   ORBITAL DATA


     Data taken at 13:00 PDT on 3rd May

     Distance from Earth                657,694,184 km.
     Velocity relative to the Earth          81,556 km/hr.
     Velocity relative to the Sun            37,692 km/hr.
     Ecliptic latitude                         22.9 deg/south

5.   PLANNED OPERATIONS

     Routine data gathering operations will continue togetherwith
     experiment reconfigurations as required.

     On 5th May a HED calibration will be carried out.

     On 10th May a KEP in-flight calibration will be carried out.

     An Earth pointing manoeuvre will be carried out on 12th May.

6.   GROUND SEGMENT

     The ground segment performed nominally during the reporting
     period.


ULYSSES MISSION OPERATIONS REPORT No. 141

PERIOD:   4th May to 10th May 1993

1.   MISSION OPERATIONS

     Experiment reconfigurations have been carried out as
     required.

     On 5th May a HED calibration was carried out.

     On 6th May a GRU reconfiguration took place.

     On 10th May a KEP in-flight calibration was carried out.

     No Earth pointing manoeuvre was performed during this
     reporting period.

     An average of 95.5% data recovery was achieved during the
     reporting period.

     The percentage of data acquired as a function of bit rate is
     as follows:

     1024 bps 37.94 %
      512 bps 57.26 %

     On 9th May a 14 minute loss of realtime data occurred due to
     acquisition problems at Goldstone.

2.   SPACECRAFT STATUS

     POWER

     Nominal.

     Estimated S/C power consumption 255 watts.

     AOCS

     Nominal.

     TTC

     The spacecraft is currently configured with receiver 2 as
     the prime unit fed via the high gain antenna and with
     receiver 1 as backup fed through the low gain antenna (LGA-
     F). The downlink is provided through EPC2/TWTA2.

     The 34 meter ground stations are in use to support TTC
     operations.  Ranging from 34 meter or 70 meter antennas is
     once again routinely performed.

     Received downlink level -141 dBm.(34 meter) X-band.

     (Variations of up to 10 db. can be expected as a result of
     station antenna in use, local weather conditions, and
     spacecraft antenna off-pointing).

     Received uplink level -123 dBm.

     DATA HANDLING

     Nominal.

     THERMAL

     Nominal.

3.   FLIGHT DYNAMICS

     Solar Aspect   The angle increased from 12.07 on Angle
     (deg.)   4th May to 12.08 on 10th May.

     Sun-Probe-Earth  The angle increased from 11.81 on Angle
     (deg.)     4th May to 12.13 on 10th May.

     Spin Rate               4.978 rpm.

4.   ORBITAL DATA

     Data taken at 00:00:00 UTC on 10th May

     Distance from Earth                669,167,650 km.
     Velocity relative to the Earth          79,728 km/hr.
     Velocity relative to the Sun            37,930 km/hr.
     Ecliptic latitude                         23.2 deg/south

5.   PLANNED OPERATIONS

     Routine data gathering operations will continue together
     with experiment reconfigurations as required.

     On 11th May a KEP RAM dump will be carried out.

     On 17th May A KEP in-flight calibration will be carried out.

     An Earth pointing manoeuvre will be carried out on 12thMay.

6.   GROUND SEGMENT

     The ground segment performed nominally during the reporting
     period with the exception of the problem at Goldstone
     reported above .


ULYSSES MISSION OPERATIONS REPORT No. 142

PERIOD:   11th May to 17th May 1993

1.   MISSION OPERATIONS

     Experiment reconfigurations have been carried out as
     required.

     On 11th May a KEP RAM dump was carried out.

     On 17th May A KEP in-flight calibration was carried
     out.

     An Earth pointing manoeuvre was performed on 12th May.

     An average of 94.5% data recovery was achieved during
     the reporting period.

     The percentage of data acquired as a function of bit
     rate is as follows:

     1024 bps 47.28 %
      512 bps 47.21 %

     On 12th May a 2 hour 50 minute loss of realtime and
     playback data occurred due to antenna problems at the
     34 meter site at Goldstone.

2.   SPACECRAFT STATUS

     POWER

     Nominal.

     Estimated S/C power consumption 255 watts.

     AOCS

     Nominal.

     TTC

     The spacecraft is currently configured with receiver 2
     as the prime unit fed via the high gain antenna and
     with receiver 1 as backup fed through the low gain
     antenna (LGA-F). The downlink is provided through
     EPC2/TWTA2.

     The 34 meter ground stations are in use to support TTC
     operations.  Ranging from 34 meter or 70 meter antennas
     is once again routinely performed.

     Received downlink level -142 dBm.(34 meter) X-band.

     (Variations of up to 10 db. can be expected as a result
     of station antenna in use, local weather conditions,
     and spacecraft antenna off-pointing).

     Received uplink level -122 dBm.

     DATA HANDLING

     Nominal.

     THERMAL

     Nominal.

3.   FLIGHT DYNAMICS

     Solar Aspect   The angle increased from 12.08 on Angle
     (deg.)   11th May to 12.46 on 17th May.

     Sun-Probe-Earth  The angle increased from 12.17 onAngle
     (deg.)     11th May to 12.35 on 17th May.

     Spin Rate      4.978 rpm.

4.   ORBITAL DATA

     Data taken at 00:00:00 UTC on 17th May

     Distance from Earth                682,091,226 km.
     Velocity relative to the Earth          78,408 km/hr.
     Velocity relative to the Sun            38,202 km/hr.
     Ecliptic latitude                         23.6
     deg/south

5.   PLANNED OPERATIONS

     Routine data gathering operations will continue
     together with experiment reconfigurations as required.

     On 18th May a KEP GAS monthly health check will be
     carried out.

     On 19th May a HED calibration will be carried out.

     On 24th May A KEP in-flight calibration will be carried
     out.

     An Earth pointing manoeuvre will be carried out on 30th
     May.

6.   GROUND SEGMENT

     The ground segment performed nominally during the
     reporting period with the exception of the problem at
     Goldstone reported above .



ULYSSES MISSION STATUS 5/17/93

PUBLIC INFORMATION OFFICE
JET PROPULSION LABORATORY
CALIFORNIA INSTITUTE OF TECHNOLOGY
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
PASADENA, CALIF. 91109


                     ULYSSES MISSION STATUS
                          May 17, 1993


     All spacecraft and science operations are performing well.
Ground-controllers are carrying out routine data-gathering
activities and experiment reconfigurations as required.  The 34-
meter (112-foot) and 70-meter (230-foot) ground antennas are
tracking the spacecraft as it continues to move farther south of
the ecliptic plane -- the plane in which the planets orbit.


     Earth-pointing maneuvers continue to be carried out about
every five days.  The last maneuver was performed on May 12,
1993.


     Today Ulysses is about 683 million kilometers (424 million
miles) from Earth, traveling at a heliocentric velocity of about
36,000 kilometers per hour (24,000 miles per hour).  The
spacecraft is now more than 30 degrees south of the sun's
equator.


                              #####
     Source:NASA Spacelink    Modem:205-895-0028  Internet:192.149.89.61
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