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Delta II Aquarius/SAC-DMission OverviewVandenberg Air Force Base, CA

United Launch Alliance (ULA) is proud to launch the Aquarius/SAC-D mission.Aquarius/SAC-D will be launched aboard a Delta II 7320-10C launch vehiclefrom Vandenberg Air Force Base (VAFB), California. The Delta II will deliver theAquarius/SAC-D spacecraft into Sun-synchronous orbit, where it will begin itsmission to improve our understanding of Earth’s climate system by mapping theconcentration of dissolved salt at the ocean’s surface.ULA provides Delta II launch services under the NASA Launch Services (NLS)contract with the NASA Kennedy Space Center Launch Services Program. Weare delighted that NASA has chosen the Delta II for this mission developed bythe Comision Nacional de Actividades Espaciales (CONAE), Argentina and theJet Propulsion Laboratory (JPL) and built by Investigciones Aplicades (INVAP),Argentina.I congratulate the entire team for their significant efforts. ULA looks forward tocontinued launches of scientific space missions.Vernon L. ThorpNASA Program ManagerUnited Launch AllianceAtlas V AEHF-11

Aquarius/sac-d observatory OverviewThe Aquarius/SAC-D Observatory is a joint U.S./Argentinian mission to map the salinity—theconcentration of dissolved salt—at the ocean surface. This information is critical to improvingour understanding of two major components of Earth’s climate system: the water cycle andocean circulation. By measuring ocean salinity from space, the Aquarius/SAC-D mission willprovide new insights into how the massive natural exchange of freshwater between the ocean,atmosphere and sea ice influences ocean circulation, weather and climate.NASA’s Aquarius is the primary instrument on the SAC-D spacecraft. It consists of threepassive microwave radiometers to detect the surface emission that is used to obtain salinityand an active scatterometer to measure the ocean waves that affect the precision of the salinitymeasurement.The Aquarius instrument was jointly built by NASA’s Jet Propulsion Laboratory and NASA’sGoddard Space Flight Center. Complementing data from Aquarius, the SAC-D platform has several CONAE-sponsoredinstruments and sensors from the French Space Agency (Centre National D-Etudes Spatiales)and the Italian Space Agency (Agenzia Spaziale Italiana) as noted below:MWR—Microwave Radiometer (CONAE): Measures precipitation, wind speed, sea iceconcentration and water vapor.NIRST—New Infrared Sensor (CONAE): Senses hot spots on the Earth’s surface (fires) andsea surface temperature.HSC—High Sensitivity Camera (CONAE): Captures urban lights, fires and the auroras.DCS—Data Collection System (CONAE): Performs environmental data collection.ROSA—Radio Occultation Sounder for Atmosphere (ASI): Gathers atmospherictemperature and humidity profiles.ICARE (CNES): Measures the effects of cosmic radiation on electronics.SODAD (CNES): Measures the distribution of micro-particles and space debris.2Delta II Aquarius/SAC-D

Image Courtesy of NASA3

Delta ii 7320-10C launch vehicle OverviewThe Delta II 7320-10C consists of the Delta II booster stage, the Delta II hypergolic secondstage, three solid rocket motors (SRMs), and a 10-foot diameter payload fairing (PLF).The Delta II booster is 8 ft in diameter and approximately 87 ft in length. The booster’s fuel andoxidizer tanks are structurally rigid and constructed of stiffened isogrid aluminum barrels andspun-formed aluminum domes. The booster structure is completed by the centerbody; whichjoins the fuel and oxidizer tanks and the LO2 Skirt; which joins the tank structure to the enginesection. Delta booster propulsion is provided by the RS-27A engine. The RS-27A burns RP-1(Rocket Propellant-1 or highly purified kerosene) and liquid oxygen, and delivers 200,000 lbof thrust at sea level. The Delta II booster is controlled by the second-stage avionics system,which provides guidance, flight control, and vehicle-sequencing functions during the booster andsecond-stage phases of flight.The SRMs, approximately 40 in. in diameter and 42 ft 6.7 in. in length, are constructed of agraphite epoxy composite with the throttle profile designed into the propellant grain. The SRMsare jettisoned by structural thrusters following a 64-second burn.The second stage is 8 ft in diameter and approximately 20 ft in length. Its propellant tanks areconstructed of corrosion resistant stainless steel. The Delta II second stage is a hypergolic(Aerozine 50 and Nitrogen Tetroxide) fueled vehicle. It uses a single AJ10-118K engineproducing 9,850 lb of thrust. The propellant tanks are insulated with Dacron/Mylar blankets.The second stage’s miniskirt/guidance section provides payload’s load path to the booster, thestructural support for the second-stage propellant tanks and the PLF, mountings for vehicleelectronics, and the structural and electronic interfaces with the spacecraft. The second-stage,other than the miniskirt, is nested inside the interstage adapter.The Aquarius/SAC-D observatory is encapsulated in the 10-ft diameter PLF. The 10-ft PLFis a sandwich composite structure made with a structural foam core and graphite-epoxy facesheets. The bisector (two-piece shell) PLF encapsulates the second stage’s miniskirt/guidancesection and the spacecraft; and separates using a debris-free pyrotechnic actuating system. Thevehicle’s height with the 10-ft PLF is approximately 128 ft.4Delta II Aquarius/SAC-D

Delta ii 7320-10C launch vehicle Expanded ViewAquarius/SAC-D10 ft dia.CompositePayload FairingGuidanceElectronicsGuidance SectionSecond StageMiniskirtAJ10 EngineInterstageOxidizer Tank (LOX)Fuel Tank (RP-1)CenterbodySolid RocketMotorsRS-27A EngineFirst Stage45

SLC-2 Overview1 Mobile Service Tower (MST)2 Launch Vehicle3 Fixed Umbilical Tower (FUT)216Delta II Aquarius/SAC-D33

Delta II AQUARIUS/SAC-D Mission OverviewThe Delta II vehicle will launch the Aquarius/SAC-D Observatory from Space Launch Complex 2West (SLC-2W) at Vandenberg Air Force Base down an initial flight azimuth of 196 degrees fromtrue north.The three solid rocket motors burn for approximately 64.0 seconds before they are jettisoned at99.0 seconds in order to satisfy range safety trajectory shaping constraints.Main engine cutoff (MECO) occurs at 264.2 seconds after liftoff when booster propellants aredepleted. First stage separation follows 8 seconds later with second stage ignition occurring at277.7 seconds. Payload fairing jettison occurs at 290 seconds when the free molecular heatingrate has dropped below 0.1 BTU/ft2-sec (1135 W/m2).After the first cutoff of the second-stage engine (SECO-1) at 676.1 seconds after liftoff, thesecond stage then performs two sets of attitude reorientation maneuvers and one thermalconditioning maneuver during the coast phase between SECO-1 and the first restart.Following SECO-2, the second stage is re-oriented to the desired attitude for separation of theAquarius/SAC-D spacecraft, which occurs at 3,402 seconds in view of the TDRS satellites fortelemetry coverage and Hartebeesthoek (HBK) for video coverage of separation and postseparation events.Spacecraft separation ends the primary portion of this Delta II mission at just over 56 minutesafter liftoff.7

Flight profile Liftoff to Spacecraft Separation57936482Launch:Flight Azimuth:196 Orbit at SC Separation:Semi Major AxesEccentricityInclination:7038.099 km.001298.008 (3800.269 nmi)Approximate Values18Delta II Aquarius/SAC-D

sequence of events Liftoff to Spacecraft SeparationEvent1 LiftoffTime(seconds)Time(hr:min:sec)0.000.00.0Mach 136.100.36.12 SRM Burnout64.001.04.0SRM Jettison99.001.39.03 Main Engine Cutoff (MECO)264.204.24.2First-Stage Separation272.204.32.2Second-Stage Ignition277.704.37.7Payload Fairing Jettison290.004.50.0456789676.111.16.1First Restart—Second Stage3139.752.19.7Second Cutoff—Second Stage (SECO-2)3251.052.32.0Spacecraft Separation3402.056.42.0First Cutoff—Second Stage (SECO-1)9

Delta II Production & Launch OverviewBrigham City, UTBrig SoliSolidRocket Motor FabricationDecatur, AL Payload Fairing/Adapter Fabricationn Booster Fabrication Second Stage FabricationVandenberg Air Force Base, CA Payload Processing & Encapsulation Launch Vehicle Processing Encapsulated Payload Mate Launch10Denver, CO ULA Headquarters &Design Center EngineeringDelta II Aquarius/SAC-D

Delta II processing VandenbergSolid MotorBuilding 1670Receiving & InspectionStagingFinal ProcessingMaterial Stores3-m FairingHalves InterstageAdapterSolid Rocket Motor (SRM)Second StageBoosterBuilding 936Receiving & InspectionTransfer Booster to Erector azardousProcessing FacilityReceiving & InspectionDestruct InstallationStage 2 Nozzle InstallationLC-2WTest & LaunchMobile Service TowerStage Erection and MateLaunch Vehicle TestingSpacecraft MateSpacecraft EncapsulationIntegrated System TestingSpacecraftSpacecraft Processing FacilityReceiving & InspectionSpacecraft Processing,Testing, Mate to PAFTransport Encapsulation11

Ground trace Liftoff to Spacecraft SeparationEnd TDRS 275Begin TDRS 0465End TDRS 046Begin TDRS 168TTSWRHTS162TDRS 168 AOSTDRS 168TDRS 046Ascent CoverageOrbital CoverageMandatory Coverage PeriodDropouts Expected1 MECO (00:04:24.2) 2 SECO-1 (00:11:16.1) 3 SII Burn5 SII Evasive Burn (01:26:40.0 – 1:26:45.0) 12Delta II Aquarius/SAC-D

STATION IDENTIFICATION (Acquisition Elevation 2 Degrees)WR Western Range Telemetry Receiving Stations ( TRS VTS SNI)TDRS 046 NASA Tracking and Data Relay Satellite - EastTDRS 168 NASA Tracking and Data Relay Satellite -WestTDRS 275 NASA Tracking and Data Relay Satellite - ZenithHBK Hartebeesthoek , South AfricaTTS POGO, AFSCN at Thule, GreenlandHTS HULA, AFSCN at HawaiiTDRS 2754HBK3End TDRS 046Begin TDRS 275End TDRS 168Begin TDRS 0462 (00:52:19.7 – 00:52:32.0) 4 Spacecraft Separation (00:56:42.0)6 SII Depletion Burn (01:43:20.0 – 01:43:42.2)13

Countdown Timeline Launch Day14Delta II Aquarius/SAC-D

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NOTES16Delta II Aquarius/SAC-D

United Launch Alliance P.O. Box 277005 Littleton, CO 80127-7005 www.ulalaunch.comCopyright 2009 United Launch Alliance, LLC. All Rights Reserved.Copyright 2011 United Launch Alliance, LLC. All Rights Reserved.

Delta II Aquarius/SAC-D 4 DeLTA II 7320-10C LAunCh VehICLe Overview The Delta II 7320-10C consists of the Delta II booster stage, the Delta II hypergolic second stage, three solid rocket motors (SRMs), and a 10-foot diameter payload fairing (PLF). The Delta II booster is 8 ft in diameter and approximately 87 ft in length. The booster's fuel and