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    Hatfield skip Hatfield skip Presentation Transcript

    • From Alpha to OrionSkip HatfieldOrion CEV Project Manager
    • Orion - Crew Exploration Vehicle• Orion is the next generation crew piloted spacecraft – Human access to Low Earth Orbit … – … and to the Moon and Mars• Development will be managed by a diverse government - industry team – Project Manager located at Johnson – Project Management Office elements at Johnson, Langley and Glenn – Technical involvement by 9 NASA Centers – Lockheed Martin Team formally selected to be the industry partnerJanuary 11, 2007 2
    • Components of Program Constellation Earth Departure Stage Orion - Crew Exploration Vehicle Heavy Lift Launch Vehicle Lunar Lander Crew Launch VehicleJanuary 11, 2007 3
    • Orion Project Philosophy• Expect to fly Orion for a generation• Mission adaptability as exploration evolves• Invest in safety – “Liftoff to Landing”• Design for low operations cost – Invest in life cycle efficiency and lowest total ownership cost• Leverage experienced workforce and industrial capabilityJanuary 11, 2007 4
    • Approach for Achieving System Adaptability and Flexibility• “Build-in” flexibility in areas where technologies are mature – Outer Mold Line, vehicle size, primary structure – Propulsion system components – size for margin SM OME and RCS – Power system – Launch Abort System performance – size for margin Power Supply A Power Supply B Design for state-of-the-art where Interconnect Arbiter• Prox Ops / Arbiter Network Gateway Flash memory technology is rapidly advancing Video Card Isolated interconnect Audio Card between Serial I/O Comm Flt-critical and Discrete & Analog I/O Non-Flt-critical Low power equipment processing 1394B card – partitions 1553 card (2-ch) SDC Processor Graphics card – Small size electronic packaging Interconnect Flight Critical Processor Arbiter Discrete & Analog I/O 1553 card (2-Ch) – Commercial software Backplane I/O Connector area – Software reuse – Open source software – Flexible, state-of-the-art avionicsJanuary 11, 2007 5
    • Orion Leverages Flight Certified Technologies & Innovations• Architecture – Spacecraft Survivability Methodology – Open Architecture Systems – Block Upgrade Approach for Lunar System Development – Passive & Active Launch Abort System 787 Avionics – Modularity Approach – P3I, Continuous Process Improvements – ICE/IDE & Tools• Avionics Systems Phoenix Solar Array & TPS – State-of-the-Art Fifth-Generation Fault-Tolerant Commercial Aircraft Avionics (787 heritage) – Star Tracker, Rendezvous & Proximity Operation Systems – 6-DOF Sensors – Solar Panels, Electrical Systems & Batteries Friction Stir• Structures Welded – TPS & Analytical Tools Orthogrid Al-Li – Friction Stir Welding, Al-Li – Composites in SoA Applications (JSF Experience) JSF Composite• Propulsion Materials & – Non-toxic (CM) Propellants Manufacturing – SMME ApproachJanuary 11, 2007 6
    • Project Orion is Leveraging Unique Skills Throughout NASA Ames Glenn • Lead Thermal Protection System ADP • Lead Service Module and • Aero-Aerothermal database Spacecraft Adapter integration • Software and GN&C support • Flight Test Article “Pathfinder” fabrication • SE&I Support Dryden Goddard • Lead Abort Flight • Communications Test Integ/Ops Support • Abort Test Booster procurement Orion Project • Flight Test Article Devt/Integ Management Langley JPL • Lead Launch Abort • Thermal Protection System integration System support • Lead landing system ADP • SE&I Support Johnson Kennedy • Lead Crew Module integration • Ground processing • Orion Spacecraft Integration • Launch operations • GFE projects management Marshall • Recovery operations • Flight Test Program • LAS and SM SE&I SupportJanuary 11, 2007 7
    • Orion Lockheed Martin Industry Team • Environmental Control & Life Support • Systems & Design Engineering • Active Thermal Control Support LM GRC • System Power Management • Propulsion • SM Liaison Office • Launch Abort System • Safety & Mission Assurance • Avionics LM LaRC • Integrated System • LAS Liaison Office Health Management • Crew Interface KSC • Mission Ground Ops Support • Final Assembly • Checkout • Acceptance Test • Sustaining Engineering• Program Management • Spacecraft Refurbishment• Systems Integration• Crew Module Development • Operator Interfaces Michoud• Service Module Development • Ground Processing • CM and SM• Qualification Test • Mission Flight Planning Structures• Software Development • Software Development January 11, 2007 8
    • Decision Making StructureConstellation Program Level II Level I Boards Boards PM (Cost/Sched/Tech) AccountabilityOrion Project CPCB CEV Risk Mgmt NASA Issue Communication Coord Panel Tech Integration NASA Led Reviews NASA CAM/org/panelLockheed Led Reviews LM Prog communication and CEV Integ T&V Integ SR&QA Review issue/position Panel Panel Panel Board (PRB) coordination before Ops Integ FT Panel WG ERB/PRB Cockpit FTA WG WG LM Eng Review Communication GEM Board (ERB) with NASA orgs Panel and/or panels LM GFE/ADP “Tabletop” LM/NASA Projects Reviews IPTs/SPTs/IWGs January 11, 2007 9
    • Independent Technical Authority is Adapted to the Orion-CEV Management Strategy Administrator OCE JSC Center GRC Center LaRC Center AA Director Director Director Cx Program JSC Eng GRC Eng LaRC Eng Cx CE Manager Director Director DirectorCEV Project CEV CE Manager SM SM All module Issues will be CAM PLE “Passed Through” CEV CE Contractor If CEV CE and module PLE disagree, PM LAS LAS then TA proceeds up parallel Center Chains CAM PLE If JSC/module Eng disagree then goes to CDContractor CE If JSC/module Center Directors disagree then January 11, 2007 goes up to OCE 10
    • Proposed Joint LM-NASA Decision Structure: Decision protocol within contract scope PRB • Contract baseline control Formal • Technical baseline control ERB Decision Process • Verify Horizontal integration complete “Tabletop” • Management Review Reviews Horizontal Integration Integrated Product IPT Teams IPT IPT Integration Working Subsystem Product Functional IWG Groups Functional Teams Functional IWG IWG Integration Teams Integration Teams Integration Teams NASA GFE/ADPJanuary 11, 2007 Projects 11
    • Orion Team Refining Requirements and Design Systematically 2005 2006 2007 Aug Sept Oct Nov Dec Jan Feb Mar April May June July Aug Sept Oct Nov Dec Jan Feb Phase 1 Draft SRD CEV Arch CxP Face- Phase 2 CxP CEV SRR CEV SRR ATP Release Changes CFI ICPR to-Face ATP SRR Data Drop (Board)CEV MajorMilestones 501 LM 502 LM 503 LM 504 601 602 LM 603 LM 604 CICP Approval RAC-1 RAC-2 RAC-3 DAC1 CRC-1CEV CRC-1A CEV-CLVAnalysis DAC Outbrief NASA ––LM Team NASA LM TeamCycles CRC-2 CRC-1 CRC-3 CRC-1A “605” Config 606 NASA-LM Reconciled CRC-2 Configuration CRC-3 RAC = Requirements Analysis Cycle CRC = CEV Reference Configuration January 11, 2007 12
    • Orion System ElementsOrion consists of four functional modules Launch Abort System -- emergency escape during launch Crew Module – crew and cargo transport Service Module – propulsion, electrical power, fluids storage Spacecraft Adapter – structural transition to launch vehicle January 11, 2007 13
    • Converging the designs • Post-award integration involved maturation of requirements and reconciliation of design differences between the NASA CRC3 and LM 604 vehicle configurations. CRC-3 604 • 605 did not close on all requirements – i.e. control masses. • Category 1 action assigned from 605 ERB to conduct a Pre- DAC1 requirements and weight summit and form a joint integration panel. – Identify opportunities for design solution and requirements changes that will close 606 Point of Departure configuration.January 11, 2007 14
    • Orion Spacecraft General ArrangementMission Summary Mission SummaryNo. Crew 44 (lunar), 6 (ISS) (lunar), 6 (ISS) No. CrewCrewed Mission Duration 18 days (lunar) Crewed Mission Duration 18 days (lunar)Quiescent Duration Quiescent Duration 210 days 210 days SMTotal ΔV 5864 ft/s Total ΔV 5864 ft/sConfiguration Summary CM Configuration SummaryDiameter (CM & SM) 16.5 ftft Diameter (CM & SM) 16.5 3Pressurized Volume (Total) 691.8 ftft3 Pressurized Volume (Total) 691.83Habitable Volume (Net) 342 ftft3 Habitable Volume (Net)SM Propellant 342 MMH/N2O4 LAS SM Propellant MMH/N2OCM Propellant GO2/GCH4 4 CM Propellant GO2/GCH4Payload (Lunar Return) 220 lbs Payload (Lunar Return) 220 lbsBlock 22 Mass Properties Summary Block Mass Properties SummaryGLOW 61,860 lb GLOW 61,860 lbEMO (1/8 LAS Partial) 50,231 lb EMO (1/8 LAS Partial) 50,231 lbJanuary 11, 2007 15
    • Launch Abort System Summary Nose Cone Attitude Control Motor Configuration Summary (Eight Nozzles) Configuration Summary Abort Motor Abort Motor Canard Section No. of Nozzles: 44 No. of Nozzles: (Stowed Configuration) Nozzle Cant Angle (to CL): 25º Nozzle Cant Angle (to CL): 25º Isp (sea level): 250 ss Jettison Motor Isp (sea level): 250 Thrust (Total in Vehicle Axis; vac.): 518,670 lbf Thrust (Total in Vehicle Axis; vac.): 518,670 lbf (Four Aft, Scarfed Nozzles) Burn Time: 4.0 ss Burn Time: 4.0 Attitude Control Motor Interstage Attitude Control Motor No. of Nozzles: 88 No. of Nozzles: Nozzle Cant Angle (to CL): 90º Nozzle Cant Angle (to CL): 90º Abort Motor Isp (vac): 227s Isp (vac): 227s(Four Exposed, Reverse Flow Nozzles) Thrust (per Nozzle; vac.): 3,000 lbf Thrust (per Nozzle; vac.): 3,000 lbf Burn Time: 20 ss Burn Time: 20 Jettison Motor Jettison Motor No. of Nozzles: 44 No. of Nozzles: Nozzle Cant Angle (to CL): 35º Nozzle Cant Angle (to CL): 35º Isp (vac.): 221 ss Isp (vac.): 221 Thrust (Total in Vehicle Axis; vac.): 40,975 lbf Thrust (Total in Vehicle Axis; vac.): 40,975 lbf Burn Time: 1.5 ss Burn Time: 1.5 Adapter Cone Mass Properties Summary Mass Properties Summary Dry Mass 8,184 lbsBoost Protective Cover Dry Mass Propellant 8,184 lbs 5,546 lbs (BPC) Propellant 5,546 lbs GLOW 14,428 lbs GLOW 14,428 lbs Crew Module (CM)January 11, 2007 Launch Abort Vehicle (LAV): Crew Module + LAS 16
    • Launch Abort Sequence LAS pulling CM safely free of CLV during abort Attitude Control Motor Reorientation for LAS Jettison LAS Jettison From CM LAS Abort & Attitude Control Motors Ignited CM Drogue DeploymentJanuary 11, 2007 17
    • LAS Control Motor Description LAS Control Motor [Rev.-R] Function LAV Pitch & Yaw Control Maximum Thrust (Vacuum) in Any 7,000 lbf Axis Maximum Thrust (Vacuum) Per 3,000 lbf Nozzle Thrust Axis (from LAS Center Line) 90 deg Burn Time 20 sec Nozzles Located Isp (Nozzle Center Line, Sea Level) 227 sec Radially Redundant Thermal Response Rate @ MEOP < 0.05 sec to 90% ThrustComposite Batteries and Case Throttle Capability 0 to 100% Thrust Electronics Surface Thermal Protection 0.035” ABL-5 Cork Bonded 0.01” RTV Propellant Grain AAB-3751 Titanium Power Two Thermal Batteries Plenum # Nozzles 8 Nozzle Positions Every 45° Starting at Zero Motor Length 40 in Motor Diameter 32 in Motor Weight (Inert / Propellant) 477 / 622 lbm Thermal (w/WGA) Batteries & Interfaces 1) To Nose Cone: Common Attach Ring, Electronics Carbon-SiC Bolted Pintle & Throat 2) To Interstage: Common Attach Ring, January 11, 2007 Bolted 18 3) To Raceway: Bolted Interface
    • LAS Abort Motor Description LAS Abort Motor [Rev.-R] Function Provides Abort Impulse Maximum Total Axial Thrust 518,670 lbf, 70° F (Vacuum) Burn Time > 4.0 sec Flow Nozzle Ramp Up to 90% Thrust 150 millisec Deflector Manifold Isp (Nozzle Center Line, Sea Level) 255 sec Nozzle Type / # 4 Reverse Flow, Exposed Surface Thermal Protection 0.14” ABL-5 Cork Bonded 0.01” RTV MEOP 1,750 psi Propellant Igniter Propellant Grain DL-H503; 6% Al DL-H503 Assembly Nozzle Cant Angle 25 degSteel Nozzle Assembly Thrust Axial Alignment 2 deg Motor Length 216 in Motor Diameter 36 in Motor Weight (Inert / Propellant) 3479 / 4581 lbm (w/WGA) Graphite Composite Case Interfaces 1) To Interstage: Common Attach Ring, Bolted 2) To Adapter Cone: Bolted 3) To Raceway: Bolted January 11, 2007 Interface 19
    • LAS Adapter Cone Description LAS Adapter Cone [Rev.-R] Gr / Ep Stainless Function 6-Point Physical Interface Between LAS &Monocoque Steel Rings CM; Carries Abort Loads Structure and Feet Adapter Rings / Feet 15-5PH Stainless Steel Adapter Structure M55J / 977 Graphite / Epoxy Thermal Protection 0.12” ABL-5 Cork Bonded 0.01” RTV Separation Mechanism Bolts & Bolt Extractors Total Length 106 in Weight (w/WGA) 1799 lbm Interfaces 1) To Abort Motor: Bolted 2) To Crew Module: Six Point Attachment 3) To BPC: Counter Sunk Fasteners 4) To LIDS or APAS or APAS/LIDS: Three Cables or Rigid Linkages Abort Mechanism Pyro Separation Adapter from CM extension Removable Nominal Cables or Linkages sep-nut Launch Are Severed access panels Cable or Linkage Disconnecting LAS from Mechanism Attachments to Base of Mechanism January 11, 2007 20
    • NESC Alternate LAS Phase 2 (1/2)• CLV Stack Aerodynamic • CEV Aeroacoustic Performance Performance – Analytical quantification of ALAS improvement of aerodynamic noise source on CM and SM as – Phase 1 axisymetric CFD indicated an effective compared to baseline LAS geometry (LM Draft: mass-to-orbit increase of 1,000 lbs for an 21 Dec; Prelim: 15 Feb; Final: 15 April) idealized LAS aerodynamic shape – Plan acoustic measurements on ALAS in Ames – Plan stack wind tunnel testing in Boeing UPWT (piggyback on planned acoustic test 16- Polysonic Tunnel (Completion: 30 Jan) AA) (Completion: 30 April) – Trajectory analysis will quantify mass-to-orbit benefits (Prelim Results: 15 Feb; Final Results: 15 April) Baseline ALAS w/scarfed Exposed LAS Nozzles NozzleIntegrated Nozzle ALAS ALAS ~147dB 604 mod 6 ~170dB Baseline ~170dB ~149dB ALAS Geometry Variations January 11, 2007 21
    • Orion Spacecraft Crew Module PICA Heatshield, ML- 440WSO Coating Docking Roll windows 2PLConfiguration Summary Configuration Summary thrustersDiameter 16.5 ftft Diameter 16.5Ref Hypersonic Lift to Drag Ratio .34 @ 157°α Ref Hypersonic Lift to Drag Ratio .34 @ 157°α 2PL Horizon 3Pressurized Volume (Total) 691.8 ftft3 windows 2PL Pressurized Volume (Total)Habitable Volume (Net) 691.8 3 342 ftft3 Pitch Habitable Volume (Net) 342 3 thrustersHabitable Volume per 44 CM CM 85.4 ftft3 Habitable Volume per 85.4 SLA-561VCM Propellant CM Propellant GO2/GCH4 GO2/GCH 2PLTotal CM Delta VV Total CM Delta 164 ft/s 4 164 ft/s backshell TPSRCS Engine Thrust 160 lbf AZ93 coating RCS Engine Thrust 160 lbf HatchLunar Return Payload 220 lbs Lunar Return Payload 220 lbsMass Properties Summary Yaw Forward bay access Mass Properties Summary panels 6PLDry Mass 17,396.8 lbs thrusters Dry MassPropellant Mass 17,396.8 lbs 385.1 lbs Drogue deployment Propellant Mass 385.1 lbs 2PL hatch for Fwd bay Lower backshellOxygen / / Nitrogen Mass / Water Oxygen Nitrogen Mass / Water 282.8 lbs 282.8 lbsCM Landing Wt. 16,174.3 lbs cover jettison Panels 5PL CM Landing Wt. 16,174.3 lbsGLOW 18,900 lbs GLOW 18,900 lbs 99% Male 1% Unpressurized FemaleMain Parachutes (3) 3% spinal growth Main deployment pilot chutes (3) 8 inches seat WMS stroke (x, y, z) (toilet) Drogue mortars parallel deploy (2) ECLSS BayJanuary 11, 2007 Avionics bays 22
    • CM Configuration OverviewBackplane Side ForwardStowage Window Window Docking Tunnel Side Docking Hatch HatchJanuary 11, 2007 23
    • Aft Bay Configuration Deleted Fourth Thruster StringSwapped 1:00. 3:00, (5 plcs)9:00 and 11:00 Changed to 160lb ThrustersWedges to Match (15 plcs)Hatch Swap to –Y Resized RCS Tankage for Increased Residuals (8 plcs) Reformatted Backup Landing Battery Rearranged Batteries, Split Cold Plates (6 plcs) Added Phase- Change Heat Exchangers Added Vertical Retro (2 plcs) Added Horizontal Rockets Retro Rockets (4 plcs) (4 plcs)Relocated 1RCS CH4Tank Deleted ATCS Freon Tanks and Manifolds (4 items) January 11, 2007 Interferences with PCS Tankage, Note 24 ATCS Exchangers, and Horizontal Retros Relocated 1 RCS GOX Tank
    • Crew Cabin Configuration (Block 2) Operator 1 and 2(Position provides forward view for docking Late stowage areasand view of horizon during ascent & entry) (Near hatch and not underneath seated crew) Hard Lockers (Provide solid footing for crew ingress/egress thru hatch) Galley (Physically separate from WMS) Avionics ECLSS (Redundant strings physically (Co-located with avionics in floor for separated & accessible on orbit. shorter cable lengths & improved CM C.G.) Spacing accommodates cable bends. Orientation eliminates blind connectors.) Block 1A ConfigurationJanuary 11, 2007 25
    • Crew Console Center Display Controls Cabin Lights Pilot Display Controls Communications Emergency Re-entry Temperature Control Initiation, Pyro Inhibits, ECLSS modeMain Caution and Warning Lights(2 sets) 10 Generic Emergency Re-entry Switches Commander Display Controls EPS Inhibits - Breakers Fire SuppressionECLSS Holesumbilical 1310 Displays (x3) Keyboard January 11, 2007 26
    • Heatshield and Crushable Structure Jettison Heat shieldCrushable Core w/ Face Sheets: (~7 ft/s)• light blue 3” thk Core, 0.020” face sheets• dark blue 1” thk, 0.010” face sheets New stiffeners on Pressure Volume Core support frame Backshell January 11, 2007 27
    • LIDS Interface LID Attachment Ring LIDS-GFE LID Attachment Ring LID AvionicsWire Routing January 11, 2007 28
    • Orion Spacecraft Service ModuleRadiator Panel Ultra-Flex(301 ft2 Radiating Area) Umbilical Housing (Fully Deployed RCS Thruster Pods (4 PL) Each Pod: 6 Thrusters (25lbf (vac)) TEI Backup (+X Engines) (4PL) Each Pod: 2 Thrusters (125lbf (vac)) Lunar Science PayloadSystemsAccess MMOD BlanketPanels (Protect Engine)(2 PL) OME Engine (7500 lbf (vac)) Ultra-Flex (Mid-Deploy)Ultra-flex Solar Array High Gain Configuration Summary Configuration Summary(388 ft2 Generating Area) Antenna Structural Configuration 33Rings Structural Configuration Rings 66Longerons Longerons Propulsion Configuration 2x2 Serial Feed Propulsion Configuration 2x2 Serial Feed RCS & TEI Backup SM Propellant SM Propellant MMH/N2O4 MMH/N O Total SM ΔV Total SM ΔV 5700 ft/s2 4 5700 ft/s TEI Backup (+X Main Engine Thrust 7500 lbfRCS Thruster Pod Main Engine Thrust 7500 lbf Engines) RCS Thruster Thrust 25 & 125 lbfBlock Swap Geometry RCS Thruster Thrust 25 & 125 lbf R4D 125lbf, Solar Array Area Solar Array Area 388 ft2 2 388 ftR1E 25lbf, radiation radiation Solar Array Power Solar Array Power 9.15 Kw 9.15 Kwcooled Radiator Area 310 ft2 2 29 January 11, 2007 cooled Radiator Area 310 ft (Four Places)
    • Alternate Service Module/Spacecraft Adapter • Technical trade studies by NASA and External Longeron Internal Longeron LM identified that an encapsulated SM offered mass savings between SM and Config (ELC) Config (ILC) SA • CEV Weight Reduction Team approved trade on 18 Dec • Alternate SM/SA Benefits – Fairing jettisons after aero loads SA Interface diminish Internal longerons – Reduction of aero thermal loads on External radiators (w/ insertion orbit changes) longerons or truss) SA Interface – Improved packaging solutions (e.g. arrays) – Protected environment at pad – Avionics / ECLS Ring provides modularity to improve integration January & test Tasks Week of 1/7 Week of 1/14 Week of 1/21 Week of 1/28 • Team investigating two SM Primary Structure CAD Model Available 1/9 Avionics ring 1/11 Prop module/SA implementations of concept Populate Model w/Subsys • Ongoing results continue to show CAD Model Available for Subsys Review & Analysis 1/15 significant mass savings Model Rvw w/GRC & MSFC 1/16 1/22 Design feedback, MEL’s available • Final results to be presented at LM Subsystem Analysis Cycle FEM Development 1st resize complete Primary structure engineering review board on 6 Feb Tabletop Preps mass props Tabletop Review 1/25 ERB Preps Feasibility (Go-No Go) ERB 1/29 Final Summit Outbrief 2/1-2January 11, 2007 30
    • Nominal Ascent Sequence Encapsulated SM (External Longeron) Press to MECO Longeron Separation 4 – Frangible Bolts 4 – Gas Thrusters Fairing Jettison 4 – Hinged Longerons Fairing Separation (2 Panels) 4 – FLSC 2 – Thrust RailsJanuary 11, 2007 31
    • Major NASA Technology Applications to Meet the Mission. Initial Controlled Climb to Pull-Up Atmospheric En try Exit Pre- Ball istic Skip Final WX Fin Update a lG TD-3 hrs lid e 8 Edge of Docking Systems Atmosphere Landing Site Skip ReentryAutomated Rendezvous & Docking Aero Sciences TPS “Heat Shield” Parachutes Landing Impact AttenuationJanuary 11, 2007 32
    • Thermal Protection System Advanced Development Project (ADP)• Purpose is select the best overall performing material for the Crew Module heat shield – Lunar return conditions (Block II) is primary focus • Mitigation plan is to develop materials for ISS return conditions (Block I) if the lunar solution cannot be developed in time – Includes thermal performance, structural and materials properties and manufacturability to the 198 in diameter• Managed by the Ames Research Center• Phase I – Lunar Return (Block II) – Select up to 5 materials for initial investigation of material Back properties for suitablility - Complete shell• Phase II – Lunar Return – Boeing/FMI team selected to produce PICA heatshield – Larger coupon testing slated to start late January• Block 1 Heatshield (LEO only) back-up contract in work for SLA materialJanuary 11, 2007 Heat shield 33
    • TPS Advanced DevelopmentAVCO technicians injecting ablator into honeycomb Ablative TPS Development Test in an Arcjet(CM had 300,000 cells) Goal: reduce uncertainty levels by validation with flight data January 11, 2007 34
    • CEV Aerosciences Project Mach Mach 25 40 Entry Heating Phase CEV LEO Direct or Atmospheric Entry Service Ballistic Reference Entries Service Module Jettison On-Orbit Module Environment PlumesEnvironment Jettison CSM droop CEV Lunar Direct, Skip, or Ballistic Hypersonic Abort Reference Entries LAT Nominal Jettison Mach ~7.5, ~200k ft alt LAT Sep for high altitude LAS abort Service Plume Heating Module Ascent Abort Jettison Separation Environment Transonic, Supersonic High Q, High Drag Abort Mach 0.9 to 4, 30k to 150k ft alt LAV uses canards to stabilize vehicle Mach ~0.5 Recovery LAT Sep Systems Turn-around Deploy At 25k ft maneuver Parachute Cover Sep Pad Abort Main Chutes Mach Parachute System Deploy ~0.1 Lockheed design has retro rockets January 11, 2007 35
    • Low Impact Docking System (LIDS)• Background – LIDS has been in advanced development since approximately 1996 – Baselined to have flight hardware complete in 2010 – To be used on first CEV launch to ISS with an APAS adapter – Fully androgynous system with both soft and hard capture features • Soft capture uses electromagnetic • Hard capture uses hooksJanuary 11, 2007 36
    • Active LIDS vs. Proposed Passive LIDS for AdapterActive LIDS• All passive functions plus: – Fully Androgynous – 6-DOF Soft Capture Platform – Electromagnets (soft capture) – Latches (hard capture) – Primary/secondary latch drives – Pyro sep system – Push-off system for sep – Seals• Avionics boxesPassive LIDS for Adapter• Passive functions – Soft capture ring • Guide Petals • Magnetic striker plates – Latch tabs (passive hooks) – Umbilical connectors and cables• Custom LIDS tunnel interfaces to APAS• Static structure to support soft capture ringJanuary 11, 2007 37
    • ISS LIDS/APAS Adapter• Orion will dock to ISS via existing APAS mechanisms, leaving adapter for LIDS on subsequent missions S-band System ATLAS PMA Node Power MBSU Passive Converter A Active A LIDS LIDS P P APAS A A 120V Power Avionics S S VMC ISS CCA 1394 28vdc GN&C Crew Docking 1553 ISS MDM Module Target(s) Navigation Sensor(s) January 11, 2007 38
    • Propulsion Isolation Valve Advanced Development Developing a low mass, variable speed propellant isolation valve – Surge pressure (waterhammer) control – 28 VDC bus voltage – Scalable to other applications (variable regulator, main engine isolation) – Originally for LOX/CH4, also candidate for MMH/N2O4 service He He P S S S S S S S S S S P NTO NTO MMH MMH PMD PMD PMD PMD S S S S S S S S M M M M M M M M M M M M M M M M M M DAC2 case 4 (parallel) Thruster Pod 1 Thruster Pod 2 Thruster Pod 3 Thruster Pod 4 S S S S S S A C D C E E A C A C E C S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S S E D A D A C E D E D A E S S S SJanuary 11, 2007 39
    • Cryogenic Visor Valve OperationJanuary 11, 2007 40
    • Orion Flight Schedule Overview FY06 FY07 FY08 FY09 FY10 FY11 FY12 FY13 FY14 FY15 SRR SDRProject Requirements Prime Award IE W V PDR CDRProject Design RE Max q Nom Abort Transonic E R Devt. LAS Abort Proto LAS Max q Off-Nom Abort First Human Launch D PA PA 10/2013Development / QualTesting UN Orion/Ares 2 Orbit Orion/Ares 1 Flight Hi Alt Ares I-X Abort FTFlight Article (1st stage test)ProductionIntegrated ARES-OrionLaunches January 11, 2007 41
    • Flight Test Program -- Progress Toward First Flight• Formally approved the agreement with USAF to develop the Abort Test Boosters (ATB) for the Flight Test Program• Committed to first flight test in late 2008January 11, 2007 42
    • CAP Aerosciences - Testing and Development Facilities Ames UPWT (11’ & 9’x7’) Aberdeen Proving Grounds Langley TDT (16’)NASA “Columbia” Supercomputing Facility Langley UPWT (4’x4’ high and low) and Mach 10 Ames Range Complex: EAST, HFFAF, GDF Langley Hypersonic Complex CUBRC LENS I, LENS II, LENS-X AEDC Hypersonic Tunnels B, C, 9Mach 6 Air, Mach 6 CF4, others January 11, 2007 43
    • Orion Production Infrastructure is Coming On-Line!• KSC / Operations & Checkout Building – Highbay for all CEV final assembly – Highbay cleanout underway – Handover completed on 30 Jan 2007January 11, 2007 44
    • ORION Operations at Michoud Assembly Facility MAF CEV Bldg 103 Manufacturing Area Crew Exploration Vehicle Alt 1 MAF Use Working Group Proposal Area Offered NOW Alt 2 Detailed Area Layout 4 Export Controlled Information PMR #2 DraftJanuary 11, 2007 45
    • CEV Vehicle-Level Qualification Test Facilities• Baseline to use LM Denver facilities • Contingent on ability to reduce predicted acoustic vibration levels for CEV during flight – ALAS activity – 6 months to complete wind tunnel testing and further design assessments – GRC SPF option as a backup • Develop capabilities in parallel for 6 monthsJanuary 11, 2007 46
    • CEV Avionics Integration Laboratory (CAIL) Facility Status• CAIL is key avionics and software integration for development and mission support• Government facility located at Johnson Space Center• New build facilityJanuary 11, 2007 47
    • Orion Advances the Human Exploration Vision• Orion is the next generation crew piloted spacecraft – Human access to Low Earth Orbit … – … and to the Moon and Mars• Orion has a talented management team and workforce which utilizes unique personnel and facility strengths from across NASA and industry • We have an exciting path to bring Orion to meet the mission – Finalize requirements – Mature the technology – Design the Systems and Modules – Produce the hardware and software – Test the Systems – Prepare for first flight operations • We are committed to meeting the national priorities for Orion!January 11, 2007 48