MISSION AA United United Launch Launch AllianceAlliance (ULA)(ULA) AtlasAtlas VV rocketrocket willwill MISSION deliverdeliver Boeing’s Boeing’s CST-100CST-100 StarlinerStarliner spacecraftspacecraft toto aa 98-nautical 98-nautical mile mile (nmi)(nmi) sub-orbitalsub-orbital trajectorytrajectory onon itsits second second Orbital Orbital FlightFlight TestTest (OFT-2).(OFT-2). FollowingFollowing separationseparation from from AtlasAtlas V,V, StarlinerStarliner enginesengines willwill MISSION burnburn taking taking it it the the restrest ofof thethe wayway toto orbitorbit andand onon MISSION toto the the International International SpaceSpace StationStation (ISS).(ISS). LiftoffLiftoff willwill occuroccur from from Space Space LaunchLaunch Complex-41Complex-41 atat CapeCape ATLAS V CanaveralCanaveral Space Space ForceForce Station,Station, Florida.Florida. OVERVIEWOVERVIEW PartPart of of NASA’s NASA’s CommercialCommercial CrewCrew ProgramProgram (CCP),(CCP), thethe uncr uncrewedewed OFTOFT isis thethe secondsecond launchlaunch ofof thethe CST-100 Starliner. The second uncrewed CST-100 Starliner. The second uncrewed ImageImage CourtesyCourtesy TheThe BoeingBoeing CompanyCompany testtest flight flight will will demonstrate demonstrate end-to-endend-to-end perfor-perfor- mancemance of of the the Atlas Atlas VV rocketrocket andand StarlinerStarliner space-space- AllAll humanhuman launchlaunch systems,systems, going back to the craft,craft, including including performanceperformance ofof thethe guidance,guidance, MercuryMercury Atlas,Atlas, traditionallytraditionally conduct uncrewed nanavigationvigation and and controlcontrol systems,systems, groundground systemssystems testtest flightsflights priorprior toto crewedcrewed flights.flights. TheThe uncreweduncrewed andand operations operations teams,teams, asas wellwell asas on-orbit,on-orbit, dockdock-- flightflight willwill alloalloww thethe teamteam toto thoroughly evaluate ing,ing, re-entry re-entry and and landinglanding operations.operations. StarlinerStarliner willwill allall flightflight datadata againstagainst pre-flightpre-flight predictions The Atlas V Starliner configuration land at one of five designated sites in the western land at one of five designated sites in the western andand makemake anyany necessarynecessary adjustmentsadjustments prior will launch The Boeing Company’s UnitedUnited States. States. to flying astronauts. to flying astronauts. CST-100 Starliner spacecraft as part of NASA’s Commercial Crew Program. This is the second flight of this configuration. Spacecraft LAUNCHLAUNCH Spacecraft ModifiedModified specifically specifically forfor thethe BoeingBoeing CST-100CST-100 StarlinerStarliner space-space- VEHICLEVEHICLE craft,craft, the the Atlas Atlas VV StarlinerStarliner configurationconfiguration doesdoes notnot includeinclude aa pay-pay- First flown in 2002, the Atlas V loadload fairing. fairing. Instead, Instead, thethe Starliner’sStarliner’s insulatedinsulated surfacessurfaces taketake thethe launch vehicle has a record of placeplace of of the the fairing fairing toto protectprotect thethe uncreweduncrewed spacecraftspacecraft duringduring 100 percent mission success over ascent.ascent. The The vehicle’s vehicle’s heightheight withwith thethe BoeingBoeing CST-100CST-100 StarlinerStarliner isis Starliner more than 85 launches. approximatelyapproximately 172 172 ftft (52.4(52.4 meters).meters). Spacecraft
TheThe CST-100 CST-100 Starliner Starliner isis attachedattached toto thethe AtlasAtlas VV usingusing aa launchlaunch vehiclevehicle adapter adapter (LVA),(LVA), whichwhich alsoalso includesincludes anan aeroskirtaeroskirt toto reducereduce Launch thethe aerodynamic aerodynamic loadsloads onon thethe vehicle.vehicle. TheThe aeroskirtaeroskirt isis jettisonedjettisoned Vehicle forfor improved improved performance performance followingfollowing boosterbooster stagestage separation.separation. Adapter & CentaurCentaur Aeroskirt TheThe Centaur Centaur second second stagestage isis 1010 ftft (3(3 meters)meters) inin diameterdiameter andand 41.541.5 ft ft (12.6 (12.6 meters) meters) inin length.length. ItsIts propellantpropellant tankstanks areare pres-pres- Centaur sure-stabilizedsure-stabilized andand constructedconstructed ofof corrosion-resistantcorrosion-resistant stainlessstainless steel.steel. Centaur Centaur is is aa cryogeniccryogenic vehicle,vehicle, fueledfueled withwith liquidliquid hydro-hydro- RL10A-4-2 gengen and and liquid liquid oxygen. oxygen. TheThe AtlasAtlas VV configurationconfiguration forfor thisthis missionmission Engines isis powered powered by by dual dual RL10A-4-2RL10A-4-2 engines,engines, eacheach producingproducing 22,60022,600 lbs lbs (100.5 (100.5 kilo-Newtons)kilo-Newtons) ofof thrust.thrust. TheThe cryogeniccryogenic tankstanks Aft Stub areare insulated insulated with with aa combinationcombination ofof helium-purgedhelium-purged blankets,blankets, Adapter radiationradiation shields shields andand spray-onspray-on foamfoam insulationinsulation (SOFI).(SOFI). TheThe Cen-Cen- taur forward adapter (CFA) provides structural mountings for the taur forward adapter (CFA) provides structural mountings for the InterstageInterstage fault-tolerantfault-tolerant avionics avionics systemsystem andand electricalelectrical interfacesinterfaces withwith thethe Adapter MISSION With more than a century of com- spacecraft.spacecraft. The The CentaurCentaur alsoalso includesincludes anan EmergencyEmergency DetectionDetection bined heritage, ULA is the nation’s System (EDS) that monitors for critical hazards to detect an System (EDS) that monitors for critical hazards to detect an most experienced and reliable launch imminentimminent or or occurring occurring failure.failure. TheThe EDSEDS alsoalso providesprovides criticalcritical SUCCESS most experienced and reliable launch in-flightin-flight data data which which supportssupports jettisonjettison ofof thethe ascentascent covercover andand service provider. ULA has successful- initiatesinitiates CST-100 CST-100 StarlinerStarliner spacecraftspacecraft separation.separation. Booster ly delivered more than 140140 missionsmissions to orbit that aid meteorologists inin BoosterBooster tracking severe weather, unlock thethe TheThe booster booster is is 12.5 12.5 ftft (3.81(3.81 meters)meters) inin diameterdiameter andand 106.5106.5 ftft (32.4(32.4 mysteries of our solar system, provide meters) in length. The booster’s tanks are structurally rigid and mysteries of our solar system, provide meters) in length. The booster’s tanks are structurally rigid and critical capabilities for troops in the constructedconstructed of of isogridisogrid aluminumaluminum barrels,barrels, spun-formedspun-formed alumi-alumi- critical capabilities for troops in the numnum domes domes and and intertankintertank skirts.skirts. BoosterBooster propulsionpropulsion isis providedprovided field, deliver cutting-edge commercial byby the the RD-180 RD-180 engine engine systemsystem (a(a singlesingle engineengine withwith twotwo thrustthrust Solid services and enable GPS navigation. chambers).chambers). The The RD-180RD-180 burnsburns RP-1RP-1 (Rocket(Rocket Propellant-1Propellant-1 oror highlyhighly Rocket purifiedpurified kerosene) kerosene) andand liquidliquid oxygenoxygen andand deliversdelivers 860,200860,200 lbslbs Boosters (3.83(3.83 mega-Newtons) mega-Newtons) ofof thrustthrust atat seasea level.level. TwoTwo solidsolid rocketrocket boostersboosters (SRBs) (SRBs) generategenerate thethe additionaladditional powerpower requiredrequired atat liftoff,liftoff, withwith each each SRB SRB providing providing 348,500348,500 lbslbs (1.55(1.55 mega-Newtons)mega-Newtons) ofof thrust.thrust. The The Centaur Centaur avionicsavionics systemsystem providesprovides guidance,guidance, flightflight RD-180 controlcontrol and and vehicle vehicle sequencingsequencing functionsfunctions duringduring thethe boosterbooster Engine andand Centaur Centaur phases phases ofof flight.flight.
ulalaunch.com Copyright © 2021 United Launch Alliance, LLC. All Rights Reserved. ATLAS V STARLINER PRODUCTION DELTAFLIGHT IV HEAVY PROFILE 8 9 10 1 Sacramento, CA 7 Solid Rocket Booster Fabrica- tion at Aerojet Rocketdyne 11 2 Denver, CO 6 ULA Headquarters & Design Center Engineering 3 Harlingen, TX 1 Canoga Park, CA Booster Adapter & Centaur OFT 5 RS 68A Engine Fabrication at 1 2 Adapter Fabrication Aerojet Rocketdyne 4 Decatur, AL 2 Time 2 Denver, CO Booster Fabrication & Final MISSIONEvent 6 (hr:min:sec)7 8 ULA Headquarters9 & Design 1 5 Center Engineering10 Assembly, Centaur Tank 1 RD-180 Engine Ignition -0:00:02.7 4 Fabrication & Centaur Final PROFILE 3 Decatur, AL Liftoff (Thrust to Weight> 1) 0:00:01.1 11 Assembly, Aeroskirt 4 3 Booster, Payload Fairing and Fabrication Begin Pitch/Yaw Maneuver 0:00:06.1 Second Stage Fabrication 5 West Palm Beach, FL 4 Maximum Dynamic Pressure 0:00:41.8 4 West Palm Beach, FL 12 RL10 Engine Fabrication at Aerojet 5 RL10A 4 2 Engine Fabrication Mach 1 0:01:05.8 6 at Aerojet Rocketdyne 4 Rocketdyne 3 2 SRB Jettison 0:02:22.0 6 Khimki, Russia 3 RD 180 Engine Fabrication at 3 Atlas Booster Engine Cutoff (BECO) 0:04:29.0 NPO Energomash 4 Time Cape Canaveral Air Force Station, Florida Atlas CentaurEvent Separation (hr:min:sec)0:04:35.0 5 Ascent Cover1 Jettison -0:00:02.70:04:41.0 0:00:01.1 9 6 Centaur First Main Engine Start (MES-1) 0:04:45.0 MECO-1 Begin Pitch/Yaw Maneuver 0:00:06.1 8 7 SPACE 7 Aeroskirt JettisonMach 1 0:00:0:05:0544.3 .0 6 LAUNCH 8 Centaur FirstMaximum Main Engine Dynamic PressureCutoff (MECO-1)0:01:05.9 0:11:5 4.5 CAPE ATLAS V Starliner 2 2 SRB Jettison 0:02:20.6 9 Starliner Separation 0:14:54.5 COMPLEX-41 3 3 0:04:29.0 10 Start Blowdown4 Atlas Centaur Separation 0:04:35.00:26:07.5 PROCESSING 5 Ascent Cover Jettison 0:04:41.0 11 End of Atlas V Mission 0:38:03.5 6 0:04:45.0 1 Orbit Solid Rocket Starliner Orbit7 Aeroskirtat Separation Jettison 0:05:05.0 Ascent Boosters Perigee: 39.308 nmi | Apogee: 98.00 nmi 0:11:54.3 Booster Inclination: 51.619 Starlinerdeg | Azimuth: Separation 50.40 deg 0:14:54.3 Boattail 10 Start Blowdown 0:26:07.3 Starliner Orbit at Separation ISA 11 End of Mission 0:38:03.3 Centaur 1 Perigee: 39.30 nmi | Apogee: 98.00 deg 12 Ocean Impact 0:57:46.0 Inclination: 51.62 deg | Azimuth: 50.40 deg Aeroskirt Longitude (deg) 2 80 2 60
BOSS 9 Starliner 40 8 TEL-4 10 7 20 6
1 Atlas Spaceflight 0 11 Operations Center (ASOC) Launch Control Center & Mission Director’s Center -20 Geodetic Latitude (deg)
2 Delta Operations Center -40 ISA, Centaur, Boattail & 1 Mobile Aeroskirt Vertical Integration Launch Platform Crew -60 Access 3 Vertical Integration Facility 3 Launch Vehicle Integration & Tower Launch Vehicle /Spacecraft Groundtrack Testing, Starliner Mate & -80 Integrated Operations -135 -90 -45 0 45 90 135 All Values Approximate