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![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% Thrust
Composite 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](https://image.slidesharecdn.com/hatfieldskip-120725121936-phpapp01/85/Hatfield-skip-18-320.jpg)
![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 deg
Steel 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](https://image.slidesharecdn.com/hatfieldskip-120725121936-phpapp01/85/Hatfield-skip-19-320.jpg)
![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](https://image.slidesharecdn.com/hatfieldskip-120725121936-phpapp01/85/Hatfield-skip-20-320.jpg)
Hatfield skip
- 1. From Alpha toOrion Skip Hatfield Orion CEV Project Manager
- 2. Orion - CrewExploration 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 partner January 11, 2007 2
- 3. Components of ProgramConstellation Earth Departure Stage Orion - Crew Exploration Vehicle Heavy Lift Launch Vehicle Lunar Lander Crew Launch Vehicle January 11, 2007 3
- 4. 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 capability January 11, 2007 4
- 5. Approach for AchievingSystem 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 avionics January 11, 2007 5
- 6. Orion Leverages FlightCertified 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 Approach January 11, 2007 6
- 7. Project Orion isLeveraging 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 Support January 11, 2007 7
- 8. Orion Lockheed MartinIndustry 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
- 9. Decision Making Structure ConstellationProgram Level II Level I Boards Boards PM (Cost/Sched/Tech) Accountability Orion Project CPCB CEV Risk Mgmt NASA Issue Communication Coord Panel Tech Integration NASA Led Reviews NASA CAM/org/panel Lockheed 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
- 10. Independent Technical Authorityis 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 Director CEV 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 CD Contractor CE If JSC/module Center Directors disagree then January 11, 2007 goes up to OCE 10
- 11. Proposed Joint LM-NASADecision 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/ADP January 11, 2007 Projects 11
- 12. Orion Team RefiningRequirements 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 Major Milestones 501 LM 502 LM 503 LM 504 601 602 LM 603 LM 604 CICP Approval RAC-1 RAC-2 RAC-3 DAC1 CRC-1 CEV CRC-1A CEV-CLV Analysis DAC Outbrief NASA ––LM Team NASA LM Team Cycles 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
- 13. Orion System Elements Orionconsists 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
- 14. 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
- 15. Orion Spacecraft GeneralArrangement Mission Summary Mission Summary No. Crew 44 (lunar), 6 (ISS) (lunar), 6 (ISS) No. Crew Crewed Mission Duration 18 days (lunar) Crewed Mission Duration 18 days (lunar) Quiescent Duration Quiescent Duration 210 days 210 days SM Total ΔV 5864 ft/s Total ΔV 5864 ft/s Configuration Summary CM Configuration Summary Diameter (CM & SM) 16.5 ftft Diameter (CM & SM) 16.5 3 Pressurized Volume (Total) 691.8 ftft3 Pressurized Volume (Total) 691.83 Habitable Volume (Net) 342 ftft3 Habitable Volume (Net) SM Propellant 342 MMH/N2O4 LAS SM Propellant MMH/N2O CM Propellant GO2/GCH4 4 CM Propellant GO2/GCH4 Payload (Lunar Return) 220 lbs Payload (Lunar Return) 220 lbs Block 22 Mass Properties Summary Block Mass Properties Summary GLOW 61,860 lb GLOW 61,860 lb EMO (1/8 LAS Partial) 50,231 lb EMO (1/8 LAS Partial) 50,231 lb January 11, 2007 15
- 16. Launch Abort SystemSummary 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 lbs Boost 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
- 17. 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 Deployment January 11, 2007 17
- 18. LAS Control MotorDescription 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% Thrust Composite 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
- 19. LAS Abort MotorDescription 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 deg Steel 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
- 20. LAS Adapter ConeDescription 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
- 21. NESC Alternate LASPhase 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 Nozzle Integrated Nozzle ALAS ALAS ~147dB 604 mod 6 ~170dB Baseline ~170dB ~149dB ALAS Geometry Variations January 11, 2007 21
- 22. Orion Spacecraft CrewModule PICA Heatshield, ML- 440WSO Coating Docking Roll windows 2PL Configuration Summary Configuration Summary thrusters Diameter 16.5 ftft Diameter 16.5 Ref Hypersonic Lift to Drag Ratio .34 @ 157°α Ref Hypersonic Lift to Drag Ratio .34 @ 157°α 2PL Horizon 3 Pressurized Volume (Total) 691.8 ftft3 windows 2PL Pressurized Volume (Total) Habitable Volume (Net) 691.8 3 342 ftft3 Pitch Habitable Volume (Net) 342 3 thrusters Habitable Volume per 44 CM CM 85.4 ftft3 Habitable Volume per 85.4 SLA-561V CM Propellant CM Propellant GO2/GCH4 GO2/GCH 2PL Total CM Delta VV Total CM Delta 164 ft/s 4 164 ft/s backshell TPS RCS Engine Thrust 160 lbf AZ93 coating RCS Engine Thrust 160 lbf Hatch Lunar Return Payload 220 lbs Lunar Return Payload 220 lbs Mass Properties Summary Yaw Forward bay access Mass Properties Summary panels 6PL Dry Mass 17,396.8 lbs thrusters Dry Mass Propellant Mass 17,396.8 lbs 385.1 lbs Drogue deployment Propellant Mass 385.1 lbs 2PL hatch for Fwd bay Lower backshell Oxygen / / Nitrogen Mass / Water Oxygen Nitrogen Mass / Water 282.8 lbs 282.8 lbs CM Landing Wt. 16,174.3 lbs cover jettison Panels 5PL CM Landing Wt. 16,174.3 lbs GLOW 18,900 lbs GLOW 18,900 lbs 99% Male 1% Unpressurized Female Main 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 Bay January 11, 2007 Avionics bays 22
- 23. CM Configuration Overview Backplane Side Forward Stowage Window Window Docking Tunnel Side Docking Hatch Hatch January 11, 2007 23
- 24. Aft Bay Configuration Deleted Fourth Thruster String Swapped 1:00. 3:00, (5 plcs) 9:00 and 11:00 Changed to 160lb Thrusters Wedges 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 1 RCS CH4 Tank 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
- 25. Crew Cabin Configuration(Block 2) Operator 1 and 2 (Position provides forward view for docking Late stowage areas and 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 Configuration January 11, 2007 25
- 26. Crew Console Center Display Controls Cabin Lights Pilot Display Controls Communications Emergency Re-entry Temperature Control Initiation, Pyro Inhibits, ECLSS mode Main Caution and Warning Lights (2 sets) 10 Generic Emergency Re-entry Switches Commander Display Controls EPS Inhibits - Breakers Fire Suppression ECLSS Holes umbilical 1310 Displays (x3) Keyboard January 11, 2007 26
- 27. Heatshield and CrushableStructure Jettison Heat shield Crushable 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
- 28. LIDS Interface LID Attachment Ring LIDS-GFE LID Attachment Ring LID Avionics Wire Routing January 11, 2007 28
- 29. Orion Spacecraft ServiceModule Radiator 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 Payload Systems Access MMOD Blanket Panels (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 lbf RCS Thruster Pod Main Engine Thrust 7500 lbf Engines) RCS Thruster Thrust 25 & 125 lbf Block Swap Geometry RCS Thruster Thrust 25 & 125 lbf R4D 125lbf, Solar Array Area Solar Array Area 388 ft2 2 388 ft R1E 25lbf, radiation radiation Solar Array Power Solar Array Power 9.15 Kw 9.15 Kw cooled Radiator Area 310 ft2 2 29 January 11, 2007 cooled Radiator Area 310 ft (Four Places)
- 30. Alternate Service Module/SpacecraftAdapter • 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 2/1-2 January 11, 2007 30
- 31. 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 Rails January 11, 2007 31
- 32. Major NASA TechnologyApplications 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 Reentry Automated Rendezvous & Docking Aero Sciences TPS “Heat Shield” Parachutes Landing Impact Attenuation January 11, 2007 32
- 33. 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 material January 11, 2007 Heat shield 33
- 34. TPS Advanced Development AVCOtechnicians 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
- 35. 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 Plumes Environment 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
- 36. Low Impact DockingSystem (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 hooks January 11, 2007 36
- 37. Active LIDS vs.Proposed Passive LIDS for Adapter Active 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 boxes Passive 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 ring January 11, 2007 37
- 38. 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
- 39. 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 S January 11, 2007 39
- 40. Cryogenic Visor ValveOperation January 11, 2007 40
- 41. Orion Flight ScheduleOverview FY06 FY07 FY08 FY09 FY10 FY11 FY12 FY13 FY14 FY15 SRR SDR Project Requirements Prime Award IE W V PDR CDR Project 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 10/2013 Development / Qual Testing UN Orion/Ares 2 Orbit Orion/Ares 1 Flight Hi Alt Ares I-X Abort FT Flight Article (1st stage test) Production Integrated ARES-Orion Launches January 11, 2007 41
- 42. 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 2008 January 11, 2007 42
- 43. 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, 9 Mach 6 Air, Mach 6 CF4, others January 11, 2007 43
- 44. Orion Production Infrastructureis Coming On-Line! • KSC / Operations & Checkout Building – Highbay for all CEV final assembly – Highbay cleanout underway – Handover completed on 30 Jan 2007 January 11, 2007 44
- 45. ORION Operations atMichoud 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 Draft January 11, 2007 45
- 46. CEV Vehicle-Level QualificationTest 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 months January 11, 2007 46
- 47. CEV Avionics IntegrationLaboratory (CAIL) Facility Status • CAIL is key avionics and software integration for development and mission support • Government facility located at Johnson Space Center • New build facility January 11, 2007 47
- 48. 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