                     THIS IS NOT AN OFFICIAL DOCUMENT!
                       This is a scanned copy of the
                          original document, and
             it MUST not be used as a source for flight data 
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                               STS-50

                          FLIGHT PLAN NOTES
                    (CONSTRAINTS AND GUIDELINES)




A.  FLIGHT DESCRIPTION

    The STS-50 (OV102) launch from KSC on June 9, 1992, will be into a
    162 by 160 nm orbit at an inclination of 29.45 degrees.  The mission
    duration will be 13 days with the capability of 2 addltional days
    for contingency operations and weather avoidance.  Nominal landing
    occurs at EDW on June 22, 1992.

    Landing opportunities are:
                                Landing
                                  orbit No.        Site      Local Time
   Nominal       Primary             206
                 One Rev. Late                     EDW        05:29 PDT
                                                   EDW        07:04 PDT
                 Alternate           205           KSC        07:02 EDT
                 Weather Att.        206
                                                   KSC        08:37 EDT
                 Weather Att.        206           NOR        06:31 MDT
   1 Day Late    Primary             222           EDW        05:31 PDT
                 One Rev Late        223
                 Alternate           221           EDW        07:06 PDT
                 Weather Alt.        222           KSC        07:04 EDT
                 Weather Alt.        222                      08:39 EDT
                                                   NOR        06:33 MDT
   2 Days Late   Primary             238           EDW        05:32 POT
                 Alternate           237           KSC        07:06 EDT
                 Weather Alt.        238           NOR        06:35 MDT

   MAJOR EVENTS
          LAUNCH (KSC)               July  9, 1992
          MET (DD/HH:MM:SS)          0/00:00:00
          Day of Year                161
          CDT/GMT                    11:00/16:00


          OMS-2
          MET (DD/HH:MM)             0/00:42
          DV (fps)                   221
          ORBIT ha/hp (nm)           162/160

          DEORBIT BURN
          MET (DD/HH:MM)             12/19:27
          DV (fps)                   274

          LANDING (EDW)
          MET (DD/HH:MM)             12/20:29
          Day of year                174
          CDT/GMT                    07:29/l2:29









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B.  CREW

    1.  There will be seven crewmembers flying this mission with each
        specialist assigned to the following tasks:

        COR - Richard N. Richards
        PLT - Kenneth D. Bowersox
        MSi - Bonnie J. Dunbar
        MS2 - Ellen S. Baker
        MS3 - Carl J. Heade
        PSl - Lawrence DeLucas
        PS2 - Eugene Trinh

    2.  The crewmembers responsible for performing an EVA, should one
        become necessary, are:  MS2 as EV1, MS3 as EV2, and PLT as IV.

C.  ORBITER SYSTEMS

    1.  Communications and Instrumentation

        a.  The Operational Instrumentation (01) system will nominally be
            managed from the ground through uplink real-time commands
            (RTCs) coordinated with the crew.

        b.  TDRS coverage is assumed to be supported by TDRS-E (41
            degrees W) and TDRS-W (174 degrees W) and is the prime mode
            of communication coverage.  TDRS-W is shared with many other
            users and may have to be given up for periods of time.

        c.  There are five Ground Network (GM) sites available for on-
            orbit contingency support:  MEL (MLX), BDA (BDX), BKR, DFR,
            and GDX.  (Note:  DFR is not shown in this Flight Plan.)
            MAD (MAX) and CAN are available for emergency support
            (2-hour lead time is required).

        d.  TDRS Ku-band is the prime mode of real-time TV; however,
            there are also two GM sites available as backup:  GDX and MEL
            (MLX) (90-minute lead time required).

        e.  RTS sites are available for contingency support or when
            scheduled in advance (4-hour lead time required):  HTS, GTS,
            VTS, 105, CTS, NHS, TCS, and DGS.

        f.  TQRS-E and TDRS-W are available to support Ku-band uplink
            (e.g., TAGS).

        g.  5-band NOR uplink (e.g., Teleprinter) is available through
            TDRS-E and TDR5-W.

        h.  TDRS-E and TDR5-W are available for ascent and entry support.
            105 (RTS site) is available for UHF voice in an emergency
            (2-hour lead time required).

        i.  Early TDRS handovers are planned throughout the mission for
            all TORS passes except on orbits 1 through 4 and orbit 200
            through landing.





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    2.  Television/Photography

        a.  Two camcorders are available for in-cabin coverage.  There
            will also be four PLB TV cameras.  There are three different
            lens assemblies for the PLB cameras (color, monochrome, and
            wide-angle lens assembly).  The type of lens assembly for
            each PLB camera is documented in the Flight Requirements
            Document.

        b.  The Orbiter has one video tape recorder available which uses
            30-minute cassettes.

        c.  Three camera systems are available:  35mm, 16mm, and 70mm.

D.  PAYLOADS

    1.  United States Microgravity Laboratory - 1 (USML-1)

        USML-1 is a mission of various experiments which focus on micro-
        gravity materials processing technology and other science and
        research requiring the low gravity environment of Earth orbit.
        It will include a long Spacelab Transfer Tunnel (SST) and a long
        module made up of a core segment and an experiment segment to be
        located in the cargo bay.  Some experiments will also be
        installed in the Orbiter middeck locker spaces.

        a.  USML-1 Module Experiments

            (1)  Crystal Growth Furnace (CGF)

                 The CGF experiment consists of a large structure that
                 has three furnaces (high temp, low temp, adiabatic) and
                 a carousel mechanism that places material samples into
                 the processing mechanism.  The CGF dictates the Orbiter
                 attitude since it requires that the long axis of the
                 furnace be pointed along the velocity vector.  Four
                 different CGF samples will be processed with run
                 durations of 1, 2, 4, and 6 days.

            (2)  Surface Tension Driven Convection Experiment (STDCE)

                 The purpose of STDCE is to study how thermocapillary
                 flow affects containerless materials processing.  In the
                 experiment, a 4-inch diameter by 2-inch deep container
                 of silicone oil is heated and data is collected on the
                 velocity profile of the cross section of the oil.  Two
                 different methods of heating are used:  surface heating
                 by a C02 laser and internal heating by a heater
                 cartridge.  The effects of both are studied.

            (3)  Drop Physics Module (DPM)

                 DPM studies containerless materials processing.  With
                 the use of acoustic waves, a drop of a particular
                 material will be held in the middle of a container.





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(4) Glovebox (GBX)

    The glovebox will house many experiments to be conducted
    in a closed environment.  These will include combustion
    experiments using wire insulation, candles, etc.

(5) Space Acceleration Measurement System (5AM5)

    5AM5 will measure the accelerations of the module
    experiments with the use of three triaxal sensor heads
    and an optical drive.

     (6)  Solid Surface Combustion Experiment (SSCE)

    SSCE will burn pieces of paper and other materials to
    study flame propagation in space.

        (7)  Generic Bioprocessing Apparatus (GBA)

    GBA is a self-contained mixing and heating module used
    to process biological fluid samples.  The experiment
    hardware is located in the SMIDEX rack in the module,
    and refrigerated samples (4~C) will be kept in the GBA
    Refrigerator/lncubator Module (R/IM) located in the
    middeck.

(8) Extended Duration Orbiter Medical Project (ED0MP)

    (a) In-Flight Lower Body Negative Pressure (LBNP)

          Fluid loading via ingestion of salt tablets and
          water in association with lower body negative
          pressure (LBNP) treatment will protect tolerance to
          orthostatis (simulated in-flight by LBNP).  The
          objective of this study is to evaluate the
          effectiveness of fluid loading during LBNP in
          improving tolerance of a LBNP stress protocol.

    (b) Blood Pressure Variability During Spaceflight

          The objective of this experiment is to determine
          whether arterial blood pressure and heart rate
          exhibi+ less varibility in a microgravity
          environment than on Earth.  The data will be used
          to investigate whether reduced blood pressure
          variability in-flight, if any, is correlated with
          the extent of baroreflex attenuation that has been
          measured postflight.  Integrity of the baroreceptor
          function is required for the appropriate blood
          pressure responses to the orthostatic stresses
          imposed by entry, landing, and egress.  The
          crewmember will wear blood pressure and
          electrocardiograph equipment for two flight days on
          orbit.

    (c)   Air Monitoring Instrument Evaluation and Atmosphere
          Characterization

          This experiment will evaluate and verify the
          microbial air sampler (MAS) to ensure proper

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                  function and operations in-flight.  In addition,
                  data will be collected on contaminant levels to
                  establish baseline levels and to evaluate potential
                  risks to crew health and safety.

    b.  USML-1 Middeck Experiments

                 (1)  Protein Crystal Growth (PCG)

             The primary objective of PCG is to produce large high-
             quality crystals of selected proteins while under
             controlled conditions of microgravity.  There will be
             two R/IMs on the Orbiter middeck, one at 22~C and one at
             4~C.

                 (2)  Zeolite Crystal Growth (ZCG)

             ZCG will try to synthesize large zeolite crystals made
             up of a complex arrangement of silica and alumina.
             Because of its molecular sieve characteristics, zeolite
             is used for highly selective catalysts, absorbents, and
             ion exchange materials.

        (3) Astroculture (ASC)

             ASC is essentially a hydroponic experiment that will be
             conducted in a microgravity environment.  Its fluid
             system will spray a nutrient solution on the roots of
             several plants.

        (4)  Generic Bioprocessing Apparatus (GBA)

             Refer to a. (7).

2.  Investigations Into Polymer Membrane Processing (IPMP)

    The research objective of the IPMP payload is to flash evaporate
    mixed solvent systems in the absence of convection to control the
    porosity of the polymer membrane.  The crewmember will activate
    the system during a period of low 'G' and deactivate the test
    after the appropriate amount cf time.

3.  Shuttle Amateur Radio Experiment   II (SAREX-II)

    The SAREX-II payload provide voice communications between the
    Orbiter and amateur radio operators on the Earth.  The SAREX
    will be operated at the direction of the licensed crewmember.
    Crewmembers are licensed radio operators for STS-50.  SAREX will
    fly a modified configuration D on STS-50.

4.  Ultraviolet Plume Instrument (UVPI)

    The UVPI is an instrument on the Low-power Atmospheric
    Compensation Experiment (LACE) satellite in orbit at 43 degrees
    inclination and approximately 290 nm altitude.  It is desired to
    use the Orbiter during cooperative encounters of the LACE
    satellite to obtain imagery and/or signature data to support the
    calibration of the UVPI space-based sensors and to observe
    Orblter events.

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E.  ON-ORBIT DTOs

1.  Cabin Air Monitoring (DTO 623)

    This DTO will use the solid sorbent sampler to continuously
    sample the Orbiter atmosphere throughout the flight.  The solid
    sorbent sampler is to be flown on all Spacelab manned module
    flights.  For STS-50, the solid sorbent sampler will alternate
    readings between the middeck and the Spacelab module.

2.  Foot Restraint Evaluation (DTO 655)

    The purpose of this DTO is to evaluate a new conceptual design
    for foot restraints.  The crew will comment on ease of
    ingress/egress, if pitch is required in design, foot loop size
    and spacing, fit and comfort, as well as base plate size.  The
    foot restraints will be used in the Spacelab module during
    Spacelab experiment operations.

3.  Evaluation of the Ergometer Vibration Isolation System (EVIS)
    (DTO 658)

    The purpose of this DTO is to measure the magnitude and frequency
    of the vibration generated in the Spacelab and Orbiter middeck by
    the cycle ergometer with EVIS on specific areas of the Spacelab
    and the middeck.  The crew will also comment on ease of setup and
    stowage, impact on exercise activities, as well as activities in
    the middeck.

4.  Acoustical Noise Dosimeter Data (DTO 663)

    The primary purpose of this DTO is to obtain baseline data of
    time-averaged acoustical noise levels for the middeck (crew sleep
    station, airlock) and the module (location OH7) during daytime
    and nighttime operations using an audio dosimeter.

5.  Acoustical Noise Sound Level Data (DTO 665)

    The purpose of this DTO is to obtain baseline data of octave-band
    acoustical noise levels for the middeck and flight deck using a
    Spacelab analog sound level meter.  The Spacelab sound level
    meter will also be used to record eight sound level readings for
    the USML-1 payload.

6.  Orbiter Experiment (OEX) Orbital Acceleration Research Experiment
    (OARE) (DTO 910)

    OARE will acquire accurate measurement data on low-level
    aerodynamic acceleration on the Orbiter principal axes during
    orbit and reentry.  Its instruments have 'nano-g' measurement
    capability, and are therefore more sensitive than SAMS.









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F.  ON-ORBIT DSOs

1.  OV1O2 Acceleration Data Collection to Support Microgravity
    Disturbances (DSO 314)

    The purpose of this DSO is to measure Orbiter accelerations
    during thruster firings, crew exercise, and other disturbances
    using the High Resolution Acceleration Package (HIRAP).  This
    data will be used to define the acceleration environment of the
    Orbiter during microgravity experiments.

2.  Intraocular Pressure (DSO 472)

    The purpose of this DSO is to establish a database of changes in
    intraocular pressures that can be used to evaluate crew health.
    The handheld tonometer will be validated as a tool for diagnostic
    and scientific data collection on-orbit.

3.  Retinal Photography (DSO 474)

    The purpose of this DSO is to analyze retinal photography taken
    on-orbit and determine if microgravity-induced cephalad fluid
    shifts elevate intracranial pressure.  It will also certify
    equipment to provide retinal images for diagnostic and
    investigative purposes.

4.  Orthostatic Function During Entry, Landing, and Egress (DSO 603B)

    The objective of this DSO is to measure the changes in
    orthostatic function of crewmembers during the actual stresses of
    entry, landing, and egress from the Orbiter.  Crewmembers will
    don equipment prior to donning the LES during deorbit
    preparation.  Equipment consists of a blood pressure monitor,
    accelerometers, an Impedance Cardiograph, and Transcranial
    Doppler hardware.  The crewmember wears the equipment and records
    verbal comments throughout entry.

5.  Changes in the Endocrine Regulation of Orthostatic Tolerance
    Following Spaceflight (DSO 613)

    DSO 613 will characterize the extent and pattern of changes in
    plasma volume during spaceflight of up to 16 days duration.  It
    will also determine whether resting levels of catecholamines are
    elevated immediately after flight, and whether catecholamine
    release in response to varying degrees of orthostatic and
    cardiovascular stresses is impaired after spaceflight.  There are
    no in-flight requirements for this DSO.

6.  The Effect of Prolonged Spaceflight on Head and Gaze Stability
    During Locomotion (DSO 614)

    The objective of this DSO is to characterize head and body
    movement along with gaze stability during exercise.  Changes in
    these parameters due to the microgravlty environment could impair
    a crewmember's ability to perform an emergency egrees from the
    vehicle.  There are no in-flight requirements for this DSO.




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7.  Evaluation of Functional Skeletal Muscle Performance Following
    Spaceflight (DSO 617)

    The purpose of this DSO is to determine the physiological effect
    of long duration spaceflight on skeletal muscle strength,
    endurance, and power.  On-orbit activities consist of maintaining
    an exercise log.

8.  Effects of Intense Exercise During Spaceflight on Aerobic
    Capacity and Orthostatic Function (DSO 618)

    The purpose of this DSO is to evaluate the effects of cycle
    erogometer exercise prior to landing with similar exercise
    performed immediately postflight, to quantify deconditioning that
    occurs over the duration of the flight, and to compare pre-
    flight, in-flight, and postflight heart rate responses to cycle
    ergometry.

9.  Physiological Evaluation of Astronaut Seat Egress Ability at
    Wheel Stop (DSO 620)

    The purpose of this DSO is to determine the nature and magnitude
    of equilibrum control, effect of head position on postural
    stability, and vision as it affects stability immediately
    postflight.  This DSO will enable the design of appropriate
    countermeasures to ensure the crew can perform an emergency
    egress.

10. In-Flight Use of Mineralocorticoid to Improve Orthostatic
    Intolerance Postflight (DSO 621)

    The purpose of this DSO is to evaluate mineralocorticoid's,
    commonly known as Florlnef, effects on postflight orthostatic
    tolerance using heart rate, blood pressure, and stroke volume, as
    well as other cardiovascular responses to orthostatic stresses.

11. Educational Activities (DSO 802)

    The purpose of this DSO is to use spaceflight to motivate
    students toward careers In engineering, science, and mathematics.
    This will be accomplished by live downlink of educational
    activities performed by the crew and production of video lessons
    with scenes recorded both on-orbit and on the ground.

12. Documentary Television (DSO 901)

    The DSO requires live television transmission or VTR dumps of
    crew activities and spacecraft functions which include:  Payload
    Bay Views, STS and Payload Crew Activities, VTR Downllnk of Crew
    Activities, In-Flight Crew Conference, and unscheduled TV
    Activities.

13. Documentary Motion Picture Photography (DSO 902)

    The DSO 902 requires documentary and public affair motion picture
    photography of significant activities which best depicts the
    basic capabilities of the space shuttle and key objectives.  This
    DSO includes motion picture photography of spacelab module
    activities, flight deck activities, middeck activities, and any
    unscheduled motion picture photography.

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14. Documentary Still Photography (DSO 903)

    The DSO 903 requires still photography of crew activities in the
    Orbiter and Spacelab and mission-related scenes of general public
    and historical interest.  Still photography with 70mm format for
    exterior photography and 35mm format for interior photography is
    required.

15. Assessment of Human Factors (DSO 904)

    This DSO will analyze data from the digital sound level meter
    recording device in the middeck, flight deck, and module,
    relative to crew comments and crew performance.  In addition, it
    will evaluate human-machine interactions during routine Spacelab
    operations (e.g., stowage, hand and foot restraints, wire and
    cable interface, etc.)










































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