STS-51 Orbiting Retrievable Far and Extreme Ultraviolet Spectrometer - Shuttle Pallet Satellite Spas) Prelaunch Mission Operation Report

8/7/2019 STS-51 Orbiting Retrievable Far and Extreme Ultraviolet Spectrometer - Shuttle Pallet Satellite Spas) Prelaunch Miss

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re LaunchMission Operation ReportOffice of Life and Microgravity Sciences and ApplicationsReport No.

Orbiting Retrievable Far and Extreme Ultraviolet Spectrometer- Shuttle Pallet SatelliteORFEUS-SPAS


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Orbiting and Retrievable Far and Extreme Ultraviolet Spectrometer -Shuttle Pallet SatelliteORFEUS-SPAS 1

Prelaunch Mission Operation Reportle of Cm

List of Figures ......................................................................................................2List of Acronyms ..................................................................................................3Forward ................................................................................................................41.0 General ..... .. .... ................................ ...... ...... .... ...................... ......*.........................52.0 Mission Objectives ..... .. .... .............. ............................ .................. ......*.................63.0 Mission Description ....... ...... .. .. .... ......................*.....*.*.........................................73.1 Payload Description ....... .............. ...... ................................ .. ...........................~....84.0 Mission Sequence... .................................................... ........ .............. .......... ...... .. 145.0 Mission Support ....... ...... .... ...................... ........................ .. ............ ................ .. .. 166.0 Mission Management ............................. .............. .... ...................... .... ................ 19


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List of Figures3.1-1 ORFEUS-SPAS Configuration3.1.2-1 ORFEUS-Telescope3.1.7-1 SESAM5.0-l ORFEUS-SPASMission Support5.0-2 ORFEUS-SPAS Command and Data Links


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List of AcronymsACTSE4FSCCTVZTADARADASADCUDLRDPUDTREMUTVERPCLEUVEVAGPSGSFCICBCIMAPSJIPJSCJSWTkmKSCL-LCCLSWLVLHMCCML1MMMOUbrnmusPIPIPPOCCPODRIGSRMSSESAMSPASSPEESPOCSTSTAGSTDRSTOSUCB

Advanced Communications Technology SatelliteAstronomical Institute, TiibingenCape Canaveral Air Force StationClosed Circuit TelevisionCarbon Fiber EpoxyCryogenic Infrared Spectrometerand Telescopefor AtmosphereDeutsche Agentur fti Rahmfahrtangelegenheiten(German SpaceAgentDeutsche AerospaceDirect Command Unit(German Institute for Researchand Technology)Data ProcessingUnitData Tape RecorderEVA Maneuvering Unit TelevisionExtended Range Payload Communications LinkExtreme UltravioletExtravehicular ActivityFar UltravioletGlobal Positioning SatelliteGoddard SpaceFlight CenterIMAX Cargo Bay CameraInterstellar Medium Absorption Profile SpectrographJoint Implementation PlanJohnsonSpace CenterJoint ScienceWorking GroupKilometerKennedy Space CenterLaunch MinusLaunch Commit CriteriaLandesstemwarte,HeidelbergLocal Vertical/Local HorizontalMission Control CenterMultilayer InsulationMillimeterMemorandum of UnderstandingNanometerOrbiting, Retrievable, Far and Extreme Ultraviolet SpectrometerPayload Interrogator, also Principle InvestigatorPayload Integration PlanPayload Operations Control CenterPayload OperationsDirectorRemote IMAX CameraSystemRemote Manipulator SystemSurface Effects Sample MonitorShuttle Pallet SatelliteSpecial Purpose End EffectorSPAS Payload OperationsCenterSpaceTransportation SystemText and Graphics SystemTracking and Data Relay SatelliteTransfer Orbital StageUniversity of California, Berkeley

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ForewordMISSION OPERATION REPORTS are published expresslyfor the use of NASA senior management,as required by the Administrator in NASA ManagementInstruction (NMI) 861O.lC, dated November26,199l. The purpose of thesereports is to provide NASA seniormanagementwith timely, complete,and definitive information on flight mission plans, and to establish official mission objectives thatprovide the basis for assessmentof mission accomplishment.Reports are prepared and issuedfor eachtight project just prior to launch. Following launch, updatedreports for eachmission areissuedto keep managementcurrently informed of definitive mission resultsas provided in NASA Management Instruction HQMI 861O.lC.Thesereports are sometimeshighly technical andarefor personnelhaving program/project managementresponsibilities. The Public Affairs Division publishesa comprehensiveseriesof reportson NASA flightmissions, which are available for dissemination to the news media.

PreparedbyFLIGHT SYSTEMS DMSIONNASA Headquarters

Published and Distributed byHEADQUARTERS OPERATIONSNASA Headquarters


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1.0 GeneralThe Orbiting, Retrievable,FarandExtremeUltraviolet Spectrometer-Shuttle Pallet Satellite (ORFEUS-SPAS) mission is the first of a seriesof at least4 joint sciencecooperativemissions between NASA andDARA which will utilize the ASTRO-SPAS carrier platform. ORFEUS-SPASconsistsof 3 ultravioletspectrographswhich will obtain spectral data on a number of celestial targets; an optical materialsexperiment; and the RemoteJMAX CameraSystem (RICS) which will obtain footage of the ORFEUS-SPAS deployment operations.After shuttle launch and ORFEUS-SPAScheck-out, the spacecraftis deployed by the RMS while RIGSrecords the deployment on special large format film. During scienceoperations, ORFEUS-SPAS iscontrolled from the SPAS Payload Control center (SPOC) located at KSC, and only one of the threespectrographsare in data collection mode at any one time.Spectral data are recordedon the SPAS tape recorder systemfor postflight analysis. However, a smallamount of science data is downlinked with engineering data for quick-look analysis and systemsperformance evaluation.At the end of the sciencephaseof the ORFEUS-SPASmission, the spacecraftis recoveredandreberthedinto the orbiter for return to earth and refurbishment for the next ASTRO-SPAS mission.ORFEUS-SPAS is manifested on STS-51 on board Discovery, which will also launch the ACTS/TOSpayload, currently targetedfor launch in mid-July, 1993. The STS-51 mission is planned to be 9 daysin duration, with the possibility of extending one day, if resourcesallow.

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2.0 Mission ObjectivesProgram 0 bjective:

The objective of the ORFEUS mission is to launch a deployable/retrievableastronomical platformand obtain ultraviolet spectra for both astrophysically interesting sources and the interveninginterstellar medium.Also, the IMAX cameraswill obtain footage of both the Shuttle and the ORFEUS-SPAS satelliteduring the deployment/retrieval operations phaseof the ORFEUS-SPASmission.

Science Objectives:Obtain scientifically useful spectra in the Far Ultraviolet (FUV) or Extreme Ultraviolet (EUV)region, from at least one of the two ORFEUS spectrometers,for the purposeof learning about stellarsourcesand the interstellar medium, and/or perform high resolution spectroscopyon bright FUVsourcesfor the purpose of characterizing the intervening interstellar medium using the InterstellarMedium Absorption Profile Spectrometer(IMAPS).Objects of prime interest for the ORFEUS spectrographsare white dwarfs, cataclysmic variables,young OB sequencestars,coronal sources,supernovaeremnants,extragalactic sourcesand both hotand cool phasesof the interstellar medium.Objectives of prime interest for IMAPS are bright 0 and B type stars whose spectra containinformation on the intervening interstellar gas.Obtain data on the degradationof optical materials when exposedto spaceflight conditions using theSurface Effects Sample Monitor (SESAM).

R.W. RichieORFBUS-SPAS Program Manager

E. M. ReevesDirector, Flight SystemsDivision

H. C. HollowayAssociate Administrator for Lifeand Microgravity SciencesandApplications

R.V. StachnikORFEUS-SPASProgram Scientist

G.P. NewtonActing Director, Astrophysics Division

W. HuntressAssociate Adminstrator forAstrophysicsand SpaceSciences6


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3.0 Mission DescriptionThe STSJ 1 mission is composedof two primary payloads;the AdvancedCommunications TechnologySatellite/Transfer Orbit Stage(ACTS/TOS) and ORFEUS-SPAS. Launch will be a direct insertion intoa 296 km orbit where ACTS/TOS is planned to be deployed on flight day 1. After the ACTSEOSdeployment, the orbiter then circularizes its orbit and deploys ORFEUS-SPAS on flight day 2.ORFEUS-SPAS scienceis then conducteduntil flight day 7 when ORFEUS-SPAS is retrieved (unlessa one day mission extension is granted). The primary landing site is KSC..STS-51 Cwo Configuration

LAUNCH:STS FLIGHT NUMBER:ORBITAL VEHICLE:ORBITAL ALTITUDE/INCLINATION:DURATION:LANDING:CREW:

-ORFEUS-SPAS ACTS/TOSJuly 15, 1993, (launch window is 9:18 am to lo:28 am EDT)STS-51Discovery (OV 103)290 kmj28.59+( 1)+2 DaysKSCCommander: F. CulbertsonPilot: W. ReaddyMission Specialist: D. BurschMission Specialist: J. NewmanMission Specialist: C. Walz


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3.1 Payload DescriptionThe ORFEUS-SPAS spacecraftconsists of the ASTRO-SPAS caxrier and subsystems;the OFGEUStelescopewith both the FUV and EUV spectrometers;the MAPS spectrograph,SESAM; and FUCS/EMU TV.

ORFEUS 1 METER TELESCOPEORFEUS 1 METER TELESCOPE\

STAR TRACKERSTAR TRACKER ,&FUV SPECTFiOMET=FUV SPECTROMETER

u

UV SPECTROMETER (INSIDE)RAPPLE FIXTURE

S-BAND ANTENNA

TRUNIONTRUNIONFllTlNGFllTlNG

S-SAND ANTENNAS-SAND ANTENNA(1 OF 2)(1 OF 2)Tl LD GAS THRUSTERS (KEEL)LD GAS THRUSTERS (KEEL)

\ \ KEEL FITIINGKEEL FITIING

Figure 3. l-l ORFEUS-SPAS ConfigurationFigure 3. l-l ORFEUS-SPAS Configuration

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3.1.1 SPAS CarrierThe ASTRO-SPAS spacecraftcantraceits heritageback to the SPAS-01satellite (June1983),the SPAS-OlA (February 1984) and Infrared Background Signature Survey (April 1991). ASTRO-SPAS wasdesigned to be a reusable, low cost satellite that is launched,deployed, retrieved and returned to Earthusing the SpaceShuttle. It is designedto accommodateprimarily large telescopesand spectrometers,but also may carry various supplementalexperiments.The ASTRO-SPAS structure subsystemis a primary truss framework made of carbon fiber tubes withtitanium nodes. The secondarystructureis provided by interchangeableequipment supportpanelswhichalso serve as mounting plates for subsystemand payload components. The end result is a very rigid,stable, light weight, optical platform. Thermal regulation is passive,accomplished through the use ofmultilayer insulation (MLI) blankets.Power for all ASTRO-SPAS and payload systemsis provided by a modular battery pack comprised ofstate of the art lithium sulfite @SO,) battery cells and its associatedpower distribution system. Dataare recorded through an on-board processorand data tape recorder and stored for post-flight analysis.Some quick look and systemsdata are transmitted to the ground for performance analysis.For position determination and 3-axis stabilized attitude control, rate integrating gyroscopesalong witha high precision star tracker and a cold gas (N2)thruster systemare used. For ORFEUS-SPASa GlobalPositioning Satellite (GPS) receiver will also be flown as a systemsdemonstrationtest for the upcomingCRISTA-SPAS mission. Interactive command and control are provided via an S-band link via theExtended Range Payload Communications Link (ERPCL) on-board the Shuttle which then communi-cateswith the ground via the Ku system. ASTRO-SPAS hasa grapplefixture for deploy andreberth withpower and data interfaces for spacecraftcheck-out while attachedto the Remote Manipulator System(I-w.3.1.2 ORFEUS TelescopeORFEUS is an astronomical telescopefor observationsat very short wavelengthsin two spectralranges,the Far Ultraviolet (FIN) in the range 90 to 125 nm and the Extreme Ultraviolet (EUV) from 40 to 90nm. (See Figure 3.1.2-1).

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ORFEUS Telescope Door,EUV Spectrometer

ORFEUSStructure

/UV Spectrometer

Main Mirror (1 m)

Figure 3.1.2-1 ORFEUS TelescopeThe overall design and construction of the ORFEUS Telescopeand of the FUV(Echelle) spectrometerhasbeendevelopedby Astronomical Institute, Tiibingen (AIT) togetherwith Landesstemwarte(LSW).The detailed design and construction was performed by Kayser Threde Inc., Munich. The main mirror(Schott Zerodur) has been polished and mounted by the REOSC company in France. Design andmanufacturing of the telescopetube was done at MAN, Munich. The main mirror is a paraboloid witha diameter of 1000mm and a focal length of 2426 mm with an iridium coating to improve its reflectivity.The telescope tube is made of a carbon fiber epoxy compound (CFK).

This tube is highly stable against mechanical and thermal load deformations, which is very essentialtokeep the instruments final adjustment during launch and at deep spacetemperaturesin orbit.The primary mirror bundles the beam in the primary focus where a mechanical aperturelimits the fieldof view, With the collimator mirror in off position the undeflected beam will enter into the EW-Spectrograph (a design which incorporates a set of four novel spherically figured, varied line-spacegratings used in a geometry which is similar to that of the classicRowland mount). Alternatively, whenthe collimator mirror is moved into the beam, the light is deflected into the FUV-Spectrograph.10


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3.1.3.1 Far Ultraviolet Spectrometer(FUV)All information which we receive from a star is comprised in its light, or more precisely in its spectralintensity distribution. It is therefore important to resolve the light spectrally as far as possible with theconstraint that the amount of light limits, i.e. the size of the telescope,the useful observing time and thestrength of the sources.In order to achievethe highest possible resolution with the ORFEUS telescopean Echelle spectrometerwas conceived.Its main characteristicis that two diffraction gratings dispersethe light very effectively with the result of an especially wide spread spectrum. Spectral featuresseperatedby 0.01 nm, (l/10,000 of the wavelength), can be resolved.This spectrum is projected onto atwo-dimensional microchannel plate detectorwhich is extremely sensitivewith a very low backgroundnoise. Thus even rather faint sourcescan be investigated with full spectralresolution.3.1.3.2 Extreme Ultraviolet SpectrometerAfter striking the telescopemirror, incoming rays of light are directed to one of four novel diffractiongratings. Due to unique characteristicsof the gratings, the sharpnessof the images formed by the highquality telescopemirror is retained in the dispersedlight, allowing a much higher spectralresolution tobe achieved than would be possible with conventional diffraction gratings. The detectorswhich recordthe arrival position of eachray of light do so with an accuracybetterthan 40 micrometers, less than halfthe thickness of a typical human hair, and encodethis arrival position electronically.The EW Spectrometeris being built by the SpaceAstrophysics Group at the University of California,Berkeley (UCB) under the direction of the Principal Investigator, Prof. Stuart Bowyer, and InstrumentScientist, Dr. Mark Hurwitz. NASA provides funding for the fabrication of this instrument, whichmounts to the spider structure in the upper half of the ORFEUS telescopetube. The EUV spectrometeracceptslight from the ORFEUS telescopeprimary mirror, as does the Far Ultraviolet (FUV) Echellespectrometer built by Tiibingen and LSW, although the two spectrometersdo not operate simulta-neously. The EW instrument covers the wavelength region from 40 to 120 nanometers.Its resolvingpower is about 1 part in 5000. To achievehigh spectralresolution acrosssuch a large wavelengthrange,a new spectrometerdesign,neverbefore flown in space,was developed.It utilizes four unique diffractiongratings fabricated by the Central ResearchLaboratory of Hitachi Instruments near Tokyo, Japan.Thediffraction gratings have as many as 6000 parallel groovesper mm on their surfaceto dispersethe lightinto its component EW colors. The spacingof the groovesvaries acrossthe surfaceof each gratingto reduce spectral aberrations.The instrument employs a radically new type of detector, developedbySpace Astrophysics Group personnel. These detectorscan electronically record the position of eachphoton of light with a precision better than 30 micrometersand are about twice aslong asany previouslyflown detector, representing an unprecedentedlevel of performance.

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3.1.4 IMAPSInterstellar Medium Absorption Profile Spectrometer (IMAPS) is an instrument which is speciallydesigned to study the large contrastsin the chemical and physical propertiesof the interstellar mediumand help us to understand the interactions between different types of gas. While ASTRO-SPAS isoperating in orbit, IMAPS will observeultraviolet radiation from hot, bright starsand will record howthe light is altered by different atoms,ions and molecules which createunique patternsof absorption atdifferent wavelengths. The design of IMAPS has two special features: first, it works in a wavelengthregion which is very important for studying principal constituents of the medium (95 -115 nm), andsecond,it has a very high spectralresolving power which permits it to disentanglethe Doppler shifts ofparcelsof gaswhich are moving very slowly with respectto eachother (at relative speedsof order 1 km/9.The construction of IMAPS is very simple. Housed within a cylindrical enclosureare 4 elements:1. a mechanical collimator with aligned aperturesto block the light from starsother than the desiredtarget,2.3.

an Echelle grating which dispersesthe light so that it is separatedinto different wavelengths,another, low-power grating on a curved surfacewhich eliminates someoverlapping of differentwavelengths from the Echelle grating and also focuses the light beam, and

4. a specially developed ultraviolet image sensorthat has very high sensitivity.IMAPS is planned to operatefor a total 1 day on the ORFEUS-SPASmission and record the spectraofabout 15 stars.3.1.5 Remote IMAX Camera System (RIGS)The RICS camerais a modified IMAX cargobay camera(ICBC) mountedto ORFEXJS-SPASfor filmingorbiter scenesduring RMS and freeflight operations. The RICS is an IMAX camera enclosed in acontainer to protect it from contamination andprovide a controlled environmentfor the cameraand film.The container has a door assemblywhich opensfor filming operations.The RICS has both a power anda signal harnessto interface the camera electronics on the top cover with the ORFBUS-SPAS powerdistribution system. All RICS command, data, and power interfaces are through the ORPEUS-SPAS.RICS filming operation are commandedby both the SPOC and the crew. Crew control of the cameraisvia the RICS-ORFEUS onboard display.3.1.6 EVA Maneuvering Unit (EMU) Television (TV)The RICS does not give the SPOC or the crew the capability to view scenesbeing filmed in real-time.Therefore, aiding in the RICS filming operationsis an EMU TV also mounted to the ORFEUS-SPAS.

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The EMU TV is a video camerawith a transmitterand associatedelectronics.The EMU TV camerafieldof view is co-aligned with the RICS camerafield of view. Therefore, an eqivalent sceneto that seenbythe RICS camera is transmitted to the orbiter and downlinked in real-time.The EMU TV transmits its video signal to the orbiter ClosedCircuit Television (CCTV) systemthroughthe orbiter EMU receiver. The CCIV systemcan be usedto display the sceneon the TV monitors or todownlink the video s ignal to the ground during times of Tracking and Data Relay Satellite (TDRS) Ku-band signal coverage.3.1.7 SESAMThe Surface Effects Sample Monitor (SESAM) experiment is designed to study the effects ofcontaminants and atomic oxygen on optical materials during spaceflight. A number of different opticalcoatings are exposed for various lengths of time during the mission, and then analyzed post-flight fordegradation in reflectivity. Data from this experiment will assistin the planning and use of opticalcoatings for future flights. (See Figure 3.1.7-1).

Sample Windows

SESAM

Figure 3.1.7-l SESAM13


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4.0 Mission SequenceThe ORPEUS-SPAS mission is divided into six distinct phases:1. Launch and ascent2. Deployment operations3. Post release operations4. ORFEUS-SPAS free flight5. Rendezvousand retrieval6. Berthing and landing4.1 Launch and AscentIMAPS telescopeservicing occursup to L-72 hours. This servicing consistsof providing a dry nitrogen(NJ or dry air purge. There are no prelaunch activities after L-72 hours and no payload launch commitcriteria (LCC) for ORPEUS-SPAS. The other payload on STS-51, ACTS, however, does have launchwindow constraints due to orbit insertion requirements. These constraintsdictate a launch window ofapproximately 1 hour and 10 minutes in duration. There are no scrub turn around constraints forORFEUS-SPAS through a 48 hour launch delay. If the launch is delayedbeyond 48 hours, IMAPS willrequire reconnection of the purge to ensurethe humidity in the interior of the instrument remains belowspecified levels.

The ORFEUS-SPAS is completely unpowered throughout this mission phase. Although no payloadactivities occur until the deployment phase,ORFEUS attitude constraints begin at payload bay dooropening. Theseconstraintsrequire the Sun bekept at least8 off from the startrackerboresightto preventdamage to the star tracker.4.2 Deployment OperationsIf ACTS/TOS is deployed as planned on flight day 1, on flight day 2, the ORPEUS-SPASis grappledby the RemoteManipulator System(RMS) and poweredon throughan interfaceestablishedby theSpecial Purpose End Effector (SPEE) attached to the end of the RMS. The Remote IMAX CameraSystem (RICS) is powered on via the sameinterface at this time to allow a 1 to 5 hour warm-up periodprior to filming. The ORPEUS-SPAS transmitter is enabled, and the command and data links areestablished.The SPOC then commands the ORPEUS-SPASthrough an extensivepredeploy checkoutto ensure all systems are operating nominally. The checkout includes a verification of the DataProcessingUnit (DPU) and the Direct Command Unit (DCU) command capabilities and a power downand repower of the SPAS.14


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Following the repower of the SPAS, the communications link is reestablishedand the SPAS predeploycheckout continues. The SPAS gyros are then calibrated while the ORFEUS-SPAS is still berthed. Atthe conclusion of the gyro calibration and predeploy checkout, the SPAS data tape recorder (DTR) isreset, and the SPAS is unberthedand maneuveredto deploy position. The RICS standby is powered on,and adjustmentsof aperturerange andfocusesareperformedto setupfor filming the SPAS release.Upona go call from the SPOC, the ORFEUS-SPAS is releasedby the RMS.4.3 Post-releaseOperationsUpon releaseof ORFEUS-SPAS from the RMS, the orbiter separatesfrom ORFEUS-SPAS with RICSfilming the sequence. Simultaneous with RICS filming, immediately after release, ORFFUS-SPASperforms an inertial attitude hold while the SPOC acquiresthe ORFEUS-SPAS inertial reference. Asecondgyro calibration is then performed. The ORFEUS-SPASis then commanded to maneuverto anew RICS filming attitude. ORFEUS-SPAS then performs an inertial attitude hold while the SPOCdefines the ORFEUS-SPAS inertial reference and gyro calibration. When the gyro calibration iscomplete, ORFEUS-SPAS continues to maneuverto new attitudesto support RICS fdming objectives.Approximately 45 minutes after release,the orbiter may station keep with the ORFEUS-SPAS until theSun is at a proper angle to support RICS filming of the next orbiter separationburn. After the orbiterseparation from ORFEUS-SPAS is complete, the orbiter then maneuversto a predetermined stationkeeping attitude for ORFEUS-SPAS free-flight operations. A minimum of 7.5 hours of continuousorbiter-to-ORFEUS-SPAS communication is require-dpost releaseto achievethe aboveobjectives andto configure the SPAS experiments for autonomousoperations.4.4 ORFEUS-SPAS Free FlightThe ORFEUS-SPAS free-flight mission phaseis plannedto last at least96 hours with a maximumof 200hours, during which time the ORFEUS-SPASmaneuversbetweeninertial attitudes approximately every25 minutes depending upon available sciencetargets. The ORFEUSandIMAPS telescopesareoperatedalternatively, and only one of the two ORFEUS spectrometersis active at any time. A communicationslink between the SPOC and the ORFEUS-SPASvia the orbiter is establishedfor 90 minutes every thirdorbit as a minimum to load new targetsfor sciencedata takesand to support experiment health checks.This link is establishedusing either the orbiter Payload Interrogator (PI) or the Extended RangePayloadCommunications Link (ERPCL). The ERPCL is the prime system,and the PI is a backup to the ERPCL.If the PI is used, the orbiter is required to perform extensivemaneuversto establish and maintain thenecessaryrange to support the ORFEUS-SPAS communicationsrequirements. The ERPCL does notrequire extensive orbiter maneuversdue to its capability of maintaining a communications link for anextended range.

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4.5 Rendezvousand RetrievalAt the completion of the ORFEUS-SPAS sciencemission and five hours prior to grapple, a continuousPI lock is established with ORFEUS-SPAS to configure the spacecraftfor retrieval. This includespowering down the science and commanding the ORFEUS and IMAPS telescopedoors closed andlatched. Nominally, the ORFEUS-SPAS will be oriented in a stable local vertical/local horizontal(LVLH) attitude compatible with retrieval prior to the orbiter closing for rendevous. The orbiterperforms a standardrendezvoussequenceto approachthe ORFEUS-SPASfor grapple. After verifyingthat ORFEUS-SPAS is in the proper attitude, the crew grapplesthe spacecraftand establishesthe SPEEelectrical interface with the SPAS.4.6 BerthingIf required, the crew visually verifies that the ORFEUS and IMAPS doors are closed prior to berthing.The ORFEUS door and at leastone of the two IMAPS doors are closedfor the payload to be consideredsafe for return. An extra vehicular activity (EVA) is possible to close a telescopedoor in a contingencysituation. The ORFEUS-SPAS attitude measurementsand control systemand transmitter are poweredoff, and final RICS filming is supported if conditions allow. ORFEUS-SPAS is then berthed andcompletely powered down. The SPEE interface is disconnected electrically and ungrappled. TheORFEUS-SPAS mission is complete at this point.

5.0 Mission SupportThe mission support organization is shown in Figure 5.0-l. The SPAS Mission Manager directs theSPOC activities and is responsible for the operational successof the ORFEUS-SPAS mission. SPASREP coordinatesthe various functions within the SPOCand communicateswith the JSCPayloadOfficerfor and inflight changesto the deploy/retrieval timeline.

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Figure 5.0-l ORFEUS--SPAS Mission SupportNominal operations during ORFJXJS-SPASfree-flight, as shown in Figure 5.0-2, are accomplishedviaa command link from the SPOCthrough the JSCMCC, up through TDRS to the Shuttle which thenrelayscommands to the ORFEUS-SPAS spacecraft.Downlink data are transmitted from the Shuttle to TDRSback to the SPOC in real-time where spacecraftand instrument performance is analyzed. Real timemission support is provided at JSC by the Payload Officer in the MCC. Coordination between the KSCSPOC and the JSC MCC is accomplishedby dedicatedvoice communications links.KSC will be used as the ORFEUS-SPAS payload operations control center, or remote PayloadOperations Control Center (POCC). The sameKSC facility, Hangar AM, that is used to integrate andtest the ORFXUS-SPAS for flight will also housethe SPAS Payload OperationsControl center (SPOC).From the SPOC, all SPAS commands will be initiated and the scienceareaof the SPOC will receiveORFEUS, JMAPS and SPAS systems data for quick look analyses and telescope performanceevaluation.The local operational responsibility for the execution of the mission lies with the SPAS REP. Thisfunction is similar to that of the Payload OperationsDirector (POD) function in the Spacelabprogram.This function coordinates all of the SPOC flight control team through the JSC Payload Officer. Allrequests for action on the part of the STS aswell asthe ORFEUS-SPAScommandsare focusedthroughthis interface. 17


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TDRS GROUND TERMINALFigure 5.0-2 ORFEUS-SPASCommand and Data Links

All scientific decisions are made by an agreementof the membersof the Joint ScienceWorking Team(JSWT.),chaired by the Mission Scientist, who areassistedby the ScienceSupport Team. Decisions arecommunicated to the SPAS REP through the Mission Scientist. The JSWT team hasinput a desired listof targetsto the SPAS program prior to launch. This targetlist was loadedinto the SPAS systemsoftwareand a pre-mission timeline was generated,which optimizes SPAS movementsand resourcesrequired toachieve the prioritized targets. This file is maintained by the SPAS target file generator and is theresponsibility of the SPAS Targets Manager (SPAS TM).The SPAS Data Manager ensuresthat all data being downlinked from ORFEUS-SPAS are formattedcorrectly, distributed to the appropriate display console and archived for post-mission analysis.The SPAS SystemsManager is responsiblefor the configuration andoperationof all SPAS SPOCgroundsystems. He is supportedby the System SupportTeam, which also supportsthe SPAS TargetsManagerand the SPAS Data Manager.Requestsfor mission timeline or procedural changesare made by the SPAS REP to the JSC PayloadOfficer in the Mission Control Center @KC). Approved changerequestsarethen forwarded to the flightcontrol team for implementation. Thesechangerequestsare communicatedto the flight crew either viavoice link or the Text and Graphics System (TAGS) which is similar to a fax machine. The Payload18


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Officer is supported at JSC by the Payload Data and Payload Systemsfunctions who have direct voicelinks to their counterparts at the KSC SPOC.Decisions that may impact mission resourceswill be made jointly by the DARA/NASA MissionManagement Team. The MMT is composed of the NASA Program Manager, the NASA ProgramScientist, the DARA Mission Manager, and the DASA SPAS Project Manager. Decisions of this typeinclude reduction or extension of mission duration, or significant changesto the pre-flight mission plan.6.0 Mission ManagementAgreementsbetween NASA and DARA aredocumentedin the Memorandum of Understanding(MOLT)for the ASTRO-SPAS series,signedin 1993,and the Joint Implementation Plan (JIP) for the ORPFXJS-SPAS- 1 mission. Deutsche Aerospace@AS A) has beendesignatedasDAR45 agentto negotiate andimplement the lower level agreements such as the Payload Integration Plan (PIP) and the safetydocumentation process.DASA is alsoresponsiblefor the configuration and operation of the SPOC. TheORFBUS-SPAS-1 mission teamreportsto the Mission Manager,with consultation from NASA HQs andDARA management.The Joint ScienceWorking Team (JSWT) is chairedandrepresentedto the missionteam by the Mission Scientist and consistsof representativesfrom ATT, Princeton, UCB, and represen-tatives from RICS and SESAM as observers. The NASA Program Scientist servesas an ex-officiomember of the JSWT.The majority of integration and testing for ORPEUS-SPAS-1 occurred in Germany. Therefore, theNASA Wallops Transportation Office wasinstrumentalin providing shipping andimport/export supportto the successfulexecution of the ORFEXJS-SPAS-1mission.

NASA HQsProgram Manager R W. RichieProgram Scientist Dr. R V. StachnikDeputy Program Scientist Dr. R. Miller

DARAIDASADARA Program ManagerDARA Project ManagerDARA System ScientistDASA Project Manager

Dr. R. WattenbachK. SteinbergDr. R. DensingDr. K. Moritz

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The following scientific institutions participate in the developmentof the instrumentation, thescientific preparation of the observationsand the final evaluationof the results:University of Tiibingen,Astronomical Institute (AIT); LandesstemwarteHeidelberg (LSW); University of California, Berkeley,SpaceSciencesLaboratory (SSL); PrincetonUniversity Observatory,the GermanInstitute for Researchand Technology (DLR) and the IMAX Corporation.Mission Scientist, IS WUCB Principle InvestigatorUCB Instrument ScientistPrinceton Principle Investigator

AIT Principle InvestigatorAIT Project ScientistDLR Principle InvestigatorIMAX Producer

Prof. I. AppenzellerProf. S. Bowyer

Dr. M. Hun&zDr. E. JenkinsFrof. M. GrewingDr. G. IWmerDr. D-R. SchmittGraeme Fergeson

STS-51 Orbiting Retrievable Far and Extreme Ultraviolet Spectrometer - Shuttle Pallet Satellite Spas) Prelaunch Mission Operation Report

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