solar mesosphere explorer press kit

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NASA NewsNational Aeronautics andSpace AdministrationWashington D C 20546AC 202 755-8370

For Release INMEDMATE

Solar IM-esospherePress Kit Project ExplorerRELEASE NO: 81-10b

ContentsGENERAL RELLASE .......................................... 5SC I ENCE BACKGROUND .......................................MISSION OBJECTIVES.......................8SPACECRAFT DESCRI PTION....................................... 8

OBSERVATORY MODULE...............................SPACECRAFT BU.S .............................................. 1114GROUND SEGMENT .................................................... ..... 16LAUNCH OPERATIONS................................SVIE TEAM ........................................................... 17

August 27, 1981


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Five scientific instruments will simultaneously monitor

ozone and minor atmospheric-constituent quantities, water-vapor

abundance and temperature, and the amount of incoming solar radi-ation to determine the role each plays in ozone production anddistribution throughout the mesosphere. Scientific data from themission will help to develop models for ozone production and de-pletion on a global scale.

(The mesosphere is the region of the atmosphere between 30

km 19 mi. and 80 km 50 mi. altitude -- above the stratosphereand below the ionosphere. Radiation of short wavelength in thatregion causes a variety of photochemical reaction; the most not-

able is creation of a layer of ozone that effectively absorbssolar ultraviolet radiation and causes a warm layer at about 30km 18 mi. altitude.)

The experiments are:* An Ultraviolet Ozone Spectrometer, to measure ozone (03)between 40 km (25 mi.) and 70 km (43 mi.) altitude;* A 1.27-micron spectrometer, to measure ozone between 50km (31 mi.) and 90 km (56 mi.) altitude, and hydroxyl (011)

between 60 km (37 mi.) and 90 km (56 mi.) altitude;* A Nitrogen Dioxide Spectrometer, to measure NO2 between 20

km (12 mi.) and 40 km (25 mi.) altitude;* A tour-channel Infrared Radiometer, to measure temperatureand pressure between 20 km (12 mi.) and 70 km (43 mi.)altitude; and water vapor and ozone between 30 kin (19 mi.)and 65 km. (40 nii.) altitude;* A Solar Ultraviolet Monitor, to measure incoming radiationfrom the Sun.

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The Solar Mesosphere Explorer satellite will be launchedinto a Sun-synchronous (3 a.m.-3 p.m.) circular orbit, 540 km

(336 mi.) above the Earth's surface, aboard a two-stage Delta2310 launch vehicle. (A Sun-synchronous orbit allows the space-craft to observe any spot on Earth at the same relative localtime of day.)

The satellite consists of two major moaules: the Observa-tory Module and the Spacecraft Bus. The satellite body is a cyl-

inder 1.7 meters (69 inches) tall by 1.25 in (50 in.) in diameter.The spacecraft is powered by a disk-shaped solar array 2.2 m (88in.) in diameter. The solar array is lixed to thc lower end of

the main cylinder, and charges nickel-cadmium batteries.

The satellite is spin-stabilized. A 5-rpin controlled spinrate stores angular momentum.

Magnetic Torquing precesses the spin axis to control rollerror. The spin axis is mraintained at right angles to the orbitplane. Yaw errors are sensed and corrected as roll error one-quarter of an orbit later. Horizon sensors measure roll errorand spin rate, and a three-axis magnetometer provides Earth mag-

netic-field data to a closed-loop, control-law electronics set(attitude computer) for automatic roll ano spin-rate control.

The instruments are gated (open and closed) once each revo-lution to gather aata as their field of view sweep toward theEarth's limb in the general altitude range of 80 km (50 mi.) to20 ki n (12 mi.) above the limb.

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The Jet Propulsion Laboratory, Pasaaena, Calif., manages theSolar M1esosphere Explorer project for NASA's Office of SpaceScience. Ball Aerospace Systems Division provided the spacecraftbus, satellite integration and system test. The University ofColorado's Laboratory for Atmospheric and Space Physics is re-sponsible for the science instruments, mission operations, theProject Operations Control Center and science data evaluation anddissemination, under contract to Jet Propulsion Laboratory.

(END OF GENERAL RELEASE; BACKGROUND INFORMATION FOLLOWS.)

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SCIENCE BACKGROUNDOzone is present in the Earth's atmosphere as a consequence

of the photodissociation (breakdown by solar cadiation) of mole-cular oxygen (02) by solar ultraviolet radiation.Oxygen atoms (0) that result from the dissociation processjoin with oxygen molecules (02) more up to form ozone (03). Solarradiation also acts to destroy ozone by photodissociation, parti-cularly in middle ultraviolet. Oxygen atoms also break down ozoneinto molecular oxygen.Other atmospheric constituents react with ozone, sometimesin cyclic reactions that consume ozone while they themselves areregenerated. Atomic hydrogen (H) and the hydroxyl (Ol) radical,the photodissociation products of water vapor, catalytically de-stroy ozone. Another atmospheric species that reacts catalytic-ally to destroy ozone is nitrogen dioxide.Water vapor occurs naturally in the atmosphere, but itsabundance may vary, and this variation will affect the density ofozone.Nitric oxide and nitrogen cioxiae also occur naturally by

the oxidation of nitrous oxide, bv solar proton events, and byionospheric reactions, but tne y may be injected in the atmosphereartificially as well.Other atmospheric constituents have also been identified ascatalytic destroyers of ozone. halogens and oxides of halogensbelong to this class, ano their origins lie at least partly in

human activities. Chlorofluoromethane, a propellant fourd inspray cans and refLigerants, conrains chlorine, a halogcr thatcan be transported into the stratosphere before ultraviolet radi-ation can plotodissociate it.The v . tiLcal uist ibution of ozone in the LartLh's atnospherebetween 40 and 80 km _-) an, o0 rni. ) is uetermiined by photochemki-cal processes. 'ITranF or t processLS (vertical ana hotr izontal mix-ing) are primarily resronsiole fo r the distribution of oZOn1e bC -low 2)0 km (19 mi. ) and auove 80 km (50 imi.). AoovC 80 km (50 mi.)transport controls atomic oxygen, atomic hydrogen, and therebyozone.In tne altitude range of 40 to 80 kIn, (25 to 50 mi.) the

amount and distribution of ozone is determined by th e intensityand spectral distribution. of solaL ultraviolet radiation, by theabundance and distribution of minor atmospheric Constituents, andby the temperature structure of t1he atmotosplere.

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MISSION OBJECTIVESThe objectives of the Solar licsosphere Explorer project are:* To provide a comprehensive study of atniospheric ozne and

the processes that form and destroy it above 30 km (19mi

* To determine what changes occur in ozone aistribution as aresult of changes in incoming solar radiation;* To measure changes in ozone density distribution in thealtituce range of 30 to 90 kii. (19 to 56 ini.) and determinethe causes of those changes;

* To measure simultaneosly temperature, pressure, watervapor, nitrogen aioxiue, near-infrared airgIow and theamount of incoming solar radiation;

* To aetermin e what solaI- teort stri l correlation exists andthe paths that 1cad to changhs in ozo.nc d-rsity;* To UeteriLtine othei changes in ozone ahunnance and distinguish thein ruioa changes caused by the Sun.

SPACECRAFT DESCRI PTIONTne SoLar Mesosphere Explorer spacecraft consists of twomajor modules: the Observatory Module and the Spacecraft Bus.The satellite body is a cylinoer 1.7 m (69 in.) tall by 1.25m (50 in.) ir n aiameter. The solar array is a disk located on the

booster end of the cylinder. The array is 2.2 Im (88 in.) indiameter.Tne satellite is spin-stabilized. A 5-rpm controlled spinrate stores angular momentum. Magnetic torquing precesses thespin axis to control Loll error. The spin axis is maintained atright angles to the orbit plane. Yaw errors are sensed and cor-rected as roll eiror one-quarter of an orbit later. Horizon sen-sors measure roll error and spin rate, and a three-axis magneto-

meter ptovides fiela direction and magnitude data to a closed-loop, control-law electronic set (attitude computer) for auto-matic roll and spin-rate control.

Data from the rotating science instruments are gated (cycled"on") once each revolution as the instruments' fields of viewsweep toward the Earth's limb in the altitude range of 80 kin (50mi.) to 20 km (12 mi.) above the limb.

The satellite is powered by a solar array that chargesnickel-cadimuim batteries. Voltage/temperature control is used,and an undervoltage switch guards against inadvertently depletingiischarae of the batteries.

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Uplink command capability from the Project Operations Con-trol Center in Boulder, Colo., to the satellite, and downlinkdata communications from the satellite to the center are handledvia the NASA Communications Network and Ground-Station Trackingand Data Relay Satellite System and, when it is operational, theTracking and Data Relay Satellite System on its S-band multiple-access channel. Ground Station Tracking Data Network will beprime communications source until TDRSS is operational and veri-fied as comoatible with the Solar Mesosphere Explorer multiple-access mode.

A command and data processor will format instrument andengineering data and will decode, store and issue commands. Com-mancs may be stored for four days and issued at any time witheight-second resolution. Data are returned in real-time and fromredundant tape recorder playback via Ground Station Tracking DataNetwork or Tracking Data Relay System Network. The satellite hasa near-omniuirectional command antenna pattern and a near-omni-directional real time data downlink antenna pattern.

One high-gain antenna, on the sunlit end of the satellite,provides coverage for tape-recorded data playback via TDRSS twiceeach 24 hours as the two TDRSS satellites transit the Solar Meso-sphere Explorer spin-axis direction.

A NASA standard transponder is used for receiving commands,downlinking data, and tracking.

The satellite has passive thermal control, using painted sur-faces, tape surfaces, multilayer insulation blankets and heaters.The orbit plane stays at 45 degrees to the Sun direction (3 a.m.-3 p.m. Sun-synchronous orbit) so that the spinning satellite-Sun-Earth geometry is nearly fixed.

The satellite does not have a propulsion system or pyrotech-nic devices. The radiator for the infrared radiometer instrumenthas a cover that is jettisoned in oLbit. The radiometer also hasan aperture cover that may be closed by command for occasionalcalibration on-orbit.

OBSERVATORY MODULEThe Solar M'esosphere Explorer payload consists of five ex-

periment packages. Two sets of engineering sensors provide auxil-iary information. Four of the instruments -- ultraviolet ozone,1.27-micron airglow, visible nitrogen dioxide and infrared radi-ometer -- will view at right angles to the spacecraft spin axis.Those four instruments scan through the limb twice each space-craft rotation.

The four limb-scanning instruments will measure all para-meters required fo r analysis of the ozone photochemistry.

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The ultraviolet ozone spectrometer measures ozone between 40Kir1 (25 mi.) ani 70 km (43 mi. ) altitude; the I .27-micLon spectro-meter measuies ozone between 50 km (31 mi.) and 90 km (55 mi.)alt i tude, and Lydroxyl between A0 kii (37 mi. ) and 90 ksii (57 mi.)altitude: the Nitrogen Dioxicie Spectrometer measures NO-) betweenn0 ki i (12 mi ) and *'0 kmi (2 i i. ) altitude; thle four-channelInfrared Radiometer measures temperature and pressure between 20km (12 mi. ) and 70 km (43 iri. ) alt i tude; and water vapor arn'ozone between 30 km (19 mi.) and 'U5 km (40 mi.) alt i tude.The fifth instrument, the ultraviolet solar anonitor looks 45uegrees from the spacecraft rotation axis, so that, in the 3 a.m.-3 p.m. Sur.-synchronous orbit, the instrument will scan throughtihe Sun once each Levolution of the spacecraft. TLe instrumrrentwill measure the amount of incoming solar radiation from 1,700Angstroms to 3,100 angstroms, and at 1,216 Angsturnlis.Tw o engineering devices SUppOLt operation of the five sci-unce instrumients. A proton alarm sensor ,nonitors the amounlt otintegrated solar protons in the range from 30 to 500 mil lionelect.on volts (11ev). I. corrmcind-selectable protcr level triggerputs the exper iment conmplekent in a preselected active Sun obser-ving mode when proton flux exceeds the triggcr level. The protonalarm moce sea.uencing regime is storea in onboard memory as ablock of timed comaianus.A spatial reference unit, actuated by limb-crossing pulsesfrom the satellite horizon-crossing indicators, control the tim-ing fo r uata gating from tihe instrurlents. rhe reference systeri,is command-admii tted to select the alti tude range of viewing foreac h inst iumen. and contains a c1ock for alLi tude incLcarents for

which data are gated.SPACECRAFT BUS

The mechanical subsystem provides structural mounting plat-forms for the satellite engineering components and harness, theObservatory M;odLule instrument complernent, and Lhe Soldr at r y.The suosystem also provides the Del ta Launch vehicle attachfitting.The Spacecraft Bus combines a .93-m (37-in.) Delta vehicleadapter ring, three vertical spars on a .33-m (37-in.) diameterthat carry loads to the booster adapter from the interface plate

that mounts the Observatory Module, three vertical equipment-mounting pltes that span the spars, and a horizontal lowerequipment mounting plate Just above the attach fitting that, fo-gether with the interface plate, closes out the three-sided boxformed by the basic structure.The Observatory Mlodule interface plate and the lower plateare circular and carry The outer thiermal-control surtaces so thatthe Bus outer shell is a cylinder. The fixed annular solar arrayhonoeycomb suostrate is made trom two symmetrical pieces.

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The array honeycoillb subsLrate is made from two syliinetricalpieces. Thc array is LtaheL1d al t the lower plate arid bracket-surpported LoRn tLhe vox sLtucture.The Observatory veuule basic st uctturu is a box madte Liomheavv aluminulll plate. The box acComiiliouoites Lhe inLiated tadzio-me te r on tie i[IS zJ 1and pt oVi CS 1oun t ng for tLhe othrer instL uI-ients on the outside.1 he Ubservato. y Module mouIInts to tile inter Lace plate pads,andI t he ilnterfaCe PIlat Q noL0s to tle bus spat hatid poinits w ththi ce puds. Mounting pads on thc- uus are insulated so tLhe busandl Obset vatoty Module i n Let face-pl ate combinaLion are nearlythermally i ndependeri .

ElectLic Power Subsystem'P e ( 1 c4r'iie powe suebf ,Lv; is a convent ionai, L[U1-shUL,'diL-eret gy Li nsL Or system suplyinl; unt(lI(ulateed DC power at2 tLo 31 .5 volts . 'Thi- S(O- at arrAy consislts of -,156 cells in 28strings of 10-ohm/cm, each 2 by 4 centilcLtL-rs ( .78 to 1 in. ),oul ,teLd on an annul t hloney coib,, subs t late of 4,000 s uuaI e i rches(88 in. ) outer 0iIametet and 44 in. inner diameter ). The arrayproducLes i .88 aii-ps at Ihe non, i na i 4V)-dcj ree anlg e of incidenceTwo batter i cs, wiLh 1 , si x-amnp- hour nickel cav ill, iln ccel seaCih, store enerk3y ot op.tationl diurin tLhe Occul Leo pot Lion ofeach orbit anoC at I i(l-pw0er-LIsaCe Pet iods.rLatLery charge is oflLr(, Iled by voitaye/temnportilje-Cori-troiled si uLIt tegul tot using fLour voi tage/temperature ratesi nld i v.; dual Y se i(Ic ta)L iy culil t. nior3attotiy dc-ptLh-ot-aischarge is nominally less than 20 per-cent . An undetvol tage :-witcl, pt etects tlhe system ayainst illad-ver tent high curient o0 luw voltage condi tions.A 1oau bank dissipates the solar ataray curt ent when thebiatteLies reachI full chaige.

AtLitIUdC ConLittol SUbsysteii,The at tituoc-cecntrol subsystLem keeps the spin axis at "0cley r eei to thie otbit plane, lim its nirLtation to less than 0. 1de C,e maintainis spin tate at 5 rpmil, and generates a stablenlmb-Let ('ICnce pulse 0 Ob!ser vatot y Module instrument dataat i ng.Tihe systerM uSeS a fixed-horizon sensor V pair totating withtle satellite to rnoasur. spin-axis position ano spin rate. Atht.e-axis inaynetometet is otiented so that its sensiLive axesare alignea with the velocity vector, 90 u'grV-ees to i.he orbit,and nah'it at t[o titie th!e I.-izon sensur cnc~uuLtet, tihe horizon.

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The magnetometer is sampled at that instant arnd thie magneticfield values, together with roll- arnd spin-rate eLror values, arefed to control-law electronic.A magnet aii 3neu with the spin axis is swi tched by the con-trol-law electronics to torque (prccess) the satellite Lo reduceany roll error when the field direction is proper. Anothei inag-net, at right angles to the spin axis, is switched by the control-law electronics to reduce any spin-rate error when the ielodirection is proper. A fluia-filled-ring nutation damper absorbsenergy to tecuce nutation.A processec limh pulse from the horizon sensois is sent tothe instruments so tlhat giting occurs when the instruments areviewing tLh alti tucie tihat is Of interest.The control systemL is atonomrous anu reuuitres no groundcontrol. Ground-contto] aujubtment of the instrument uata yatetimes relative to the 'horizon reference pulse allows full ausjt-menLt of the a' t uuc o the ( xper iment oata acqiui s ti o-.

Commana ana Data-iHandlinqSubsjsteimThe command anid Jata-handling subsystem rlecioeves, decodesana distrioutes commanas, formats aigital and; nalog (iata, stUrescemnmanus fo r later time- tagged execution, and storcs data on tapefor loter uownl ink trarsinissioti.The systen, consists of a commai.d decooer, a aigiti11 tele-metry unit, two redunoant tape recoruers, and a telemetry uistri-bution unit that serves to interface the contiol -and-aata-hanci-ling units ano the transponder that is part of tLh( communicationssubsys tenis.ThI e) telemetry sys tenI as four owtmiats, eachi of whi chIa. 128eight-bit wors as a rrinor LIarne. The rcal-time oit rate is 12bi ts pet seconu so t hat ( ;1ch innI frame is t9. J secnrds 1rc gThcre are 14 subcommutattrs. Four subcoms, four weids deep, pro-vioe an eight-second sample-rate capability. One subcom, eigitwords Jeeup, provides a 16-secoru sample-rate capa)ility; ari(d nineSUbcoiS, It, ' ors ecp, puvil ie 32-seconu sample-ratc capability.The four fotmats arc conmmand selcctable anU CvlnslSt kf )primary operating forn~at for normal operatL(rts, a Sto(red-cvmz'.aLjm moriy-Jump format to cunLtmr, the storca coinmaurd loac:, a secnr.-ualy scm- ': Lormat, ana a iyh rate 'r ir erung to!r:at Lor ur bltInitialization, testing an' truuoies ootinyiach tape tecoraer stures 16 milloio its A uaita. i'le play-back rate is 8, 1C-, bits ptDr secou. T' e comr-rand-storoe capa-

b iI it ts 51 - Six teen-Dlt C onoi tI comamanusran rnade steVto(,ufu r up to 96 hours and executed i th cight-sccord rAsciutlen. ACoX!rlr i, ck ir C{..--: ' Vi CC '.; Q; g 'L7u LiL- aLscojUcnce s5 t he I rs L ui c-nt Can-ciLfC cally, UDs Ie Sz'ara fla tLffCcts On tile &).'ot, .l ,et-r W >


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CDrnmunica_ s ons SubsystemThe communicarions subsystem uses the NASA standard Groundystem Tracking Data Network/Tracking Data Relay System trans-onder for uplink command reception, downlink telemetry transmis-ion and tracking by coherent transpornding of ranging signals.The transponder has a 5-watt transmitter. The Tracking Dataelay System multiple-access downlink is used.An omni-direcional tnterna pattern is produced by two hemi-pherical pattern antennas, one on each end of the satellite, forommand reception.Hiemispherical antenna patterns produced by command-select-ble antennas are used fo r real-time (512-bps) data downlink viaracking Data Relay System and fo r simultaneous real-time andape-recorded playback (8,192 bps) data dcwnlink via Ground Sys-em Tracking Data Network.One ligh-gain antenna locateu un the Sun si.ie of the satel-ite is used to transmit the tar)p- recorded uata whenever a Track-g Data Relay System is near the spin axis of the Solar Meso-phcre Exploter. Data are transinited either in the real time orLom thE tape recorder in sinul t aneous t eal-time and tape-ecorder playback. Comnands are uplirnk at 125 bits per second.The satellite is operated fron, a Project Operations ConLLolenter located at thic Laboratoty for Atmospheric and Space Phy-ics at Bouler, Colorado, that tics to NASCOM usirga links fromeuldet to Goddard Space Fiioht Centci Greenbelt, Md.

GROUND SEGMENTThe Mission Operations System is !


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The Command .:eanory Maragemnent and Sequencing System receivesinputs and prepares a tiaie-o:dezed, error-free, bit-structuredcommand memory load synchroni.-u with scheduled Ground-StationIracking and Data relay Satellit. Network contacts.Experiment obiserving sequences are planned by the scientificinvestigators baseo on the major scientific mission objectivesand priorities, the current condition of the Sun as monitored andreported by tihe Space Environmental Services Center in Boulder,and results of current Solar Mesosphere Explorer observations.The task reauests to support the observations are then scheduledby the science and mission planners according to the predictedtineline of orbital events.R'ai-time and tape-recorded playback data are downlinked viaGround Station Tracking Data Network/Tracking Data Relay Satel-lite System anu transmittd in real-time to the Project Opei.ationControl Center via NASCOM-i System. The real-time data ate usedfor command verification, quick evaluation of scientific opera-tion, and spacecraft ana instrument performance checks. The taperecorder playback uata are used for detailed spacecraft and in-strument performance checks, quick-look scientific evaluation,ana in-depth scientific analysis.Both real-time and tape-recorded playback data, received atthe Project Operation Cor.ttol Center, are processed and availablewithin hours to the Mission and Science Analysis Subsystems fotinteractive data analysis.Initial processing is done by Mission Data Processing toconvert the data into science format, the check for errors in thetape playback data, to correct experiment times, to determinesatellite attitude, and to process the orbit parameters. Pro-cessed oata are includeu inr he Mission Data-Base ManagementSys teal.scientists anu s,:i ion analysts access formatted data fromthe .lission Data-Base System using an Interactive Data Languagethat allows them to edit, manipulate, display and plot the oata.Results of the quick evaluation serve as inputs for the nextday's experiment plan.The interactive system is als- used for in-depth analysiswhere the Interactive Data Language, along with system and user-written procedures, enables the scientist and mission analysts toprocess and correlate large amounts of Solar Mesosphere Expledata.Tracking uata are transmitted from Ground Station TrackingData Network to the Orbit Determination Division at Goddard forcomputation of definitive orbit parameters.

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Preparation for tihe Solar Mesosphere Explorer launch beganAug. 4 with the erection of the Delta 156 booster at SLC-2W. Theinterstage was erection Aug. 5.

Three Castor II solid rocket motors were mounted around thebase of the booster stage on Aug. 6 and the second stage wasmounted with the booster on Aug. 7.

The spacecraft arrived Aug. 16 arnd was tested and checkedoat in the Spacecraft Checkout Laboiatory. It is scheduled formovement to the launch pad on September 1 fo r mating with theDelta second stage. The payload fairing, which will protect thespacecraft on its flight through the atmosphere, is scheduled forinstallation on September 8.

SME TEAMNASPI "-iquartersADn Ha Stofan Associate Administrator fo rSpace Science (Acting)Dr. juffrey D. Rosendahl Assistant Associate Adminis-trator Space Science (Acting)DL. Franklin D. Martin Director, Solar Terrestrialand Astrophysics Division3. Ivarien Keller Dcputy Director, Solar' rerrestrial and Astrophysics

Division

Richard E. Halpern Manager, Research FlightPrograms DevelopmentMarius lWeinrab Program Manager, SolarMesophere ExplorerK\vnnedy Spac e CenterRichlai J G. Smith Di ectuiLThomlas S. Walton Director, Cargo OperationsCharles D. Gay Ditector, Expendable Vehicles

Operations DirectorateGuYne L. McCaLl Chief, Delta OperationsDivisionRay Kinmlirgcr Chief, Delta Western OperationBranchE. J. Langenfeld Spacecraft Coordinator

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Jet Propulsion LaboratoryDr. Bruce C. Murray DirectorGen. Charles A. Terhune Jr. Deputy DirectorRobert J. Parks Assistant Director for Flight

ProjectsJohn Paulson Project ManagerDr. James Stuart Deputy Project ManagerKathleen Lee Resources Documentation Control

tManager

University of Colorado (Boulder)Ldboratory for Atmospheric and Space PhysicsDr. Charles Earth Principal InvestigatorLowell Dorman Observatory Moaule ManagerElainec Hansen Mfission Operations [Manager

Ball Aerospace Systems Division (Boulder)John Simpson Programr lanagciRon Brown Deputy Program iiaznageL

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solar mesosphere explorer press kit

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