Nasa 156298main Orion Handout

Crew Exploration Vehicle Project Office

Project Orion Overview And Prime Contractor Announcement Skip Hatfield Orion CEV Project Manager

August 31, 2006

Crew Exploration Vehicle Project Office

Contract Selection Continues our Pursuit of the Vision for Space Exploration • •

Planning for Orion began with the VSE announcement in Jan 2004 Selection of Lockheed Martin today is informed by – NASA architecture and reference configuration studies – NASA Advanced Development Project early technology studies – Two Contractor teams performing initial designs in Phase 1

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The Orion Team merges today to begin development phase with a strong base of experience Aug 2004 Phase 1 RFP Development Starts

Jan 2004 VSE Announced

July 2005 Phase 1 CEV Contract Start

Mar 2004 Project Office Formed

January 2006 Phase 2 RFP Release Oct 2005 ADPs Start

Mar/Apr 2006 Proposals Aug 2006 Selection

Orion Oriontargets targetsfirst firstmission missionto toSpace SpaceStation Stationno nolater laterthan than2014 2014 and andto tothe themoon moonno nolater laterthan than2020 2020

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Crew Exploration Vehicle Project Office

Orion Missions are Critical to Future Space Exploration Lunar Mission • Orion and Lunar Lander boosted to lunar orbit – Up to 4 crew onboard

• • • • Capable of ISS Missions • Transport up to 6 crew members on Orion for crew rotation • 210 day stay time • Emergency lifeboat for entire ISS crew • Deliver pressurized cargo for ISS resupply • Orion returns crew to Earth

Lander descends to lunar surface for up to 7 day sortie Orion is uninhabited during lunar surface operations Lander upper stage returns to Orion in lunar orbit Orion returns crew to Earth

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Crew Exploration Vehicle Project Office

The Lockheed Martin Orion System Elements

Orion 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 4

Crew Exploration Vehicle Project Office

CEV Crew Module Configuration ConfigurationSummary Summary Diameter 16.5 Diameter 16.5ftft Ref RefHypersonic HypersonicLift LifttotoDrag DragRatio Ratio .34 .34@@157°α 157°α 3 Pressurized Volume (Total) 691.8 Pressurized Volume (Total) 691.83ftft3 Habitable 361 HabitableVolume Volume(Net) (Net) 361ftft33 Habitable Volume per 4 CM 90.3 Habitable Volume per 4 CM 90.3ftft3 CM GO 4 CMPropellant Propellant GO2/GCH 2/GCH4 Total CM Delta V 164 ft/s Total CM Delta V 164 ft/s RCS Engine Thrust 100 RCS Engine Thrust 100lbf lbf Lunar Return Payload 220 Lunar Return Payload 220lbs lbs Mass MassProperties PropertiesSummary Summary Dry DryMass Mass Propellant PropellantMass Mass Oxygen / Nitrogen Oxygen / NitrogenMass Mass/ /Water Water CM Landing Wt. CM Landing Wt. GLOW GLOW

Roll thrusters 2PL Pitch thrusters 2PL Yaw thrusters 2PL

17396.8 17396.8lbs lbs 385.1 385.1lbs lbs 282.8 282.8lbs lbs 16174.3 16174.3lbs lbs 18706.3 18706.3lbs lbs

• PICA Heatshield, ML-440WSO Coating

• SLA-561V Backshell TPS panel, AZ93 thermal coating

Forward bay cover

Docking windows 2PL

Nextel & kevlar MMOD blankets 32.5°

R237.6 in

Horizon windows 2PL

198.0 in

Hatch Forward bay access panels 6PL OML/IML 6 in offset Lower backshell Panels 5PL

130.0 in 5

Crew Exploration Vehicle Project Office

Launch Abort System Summary Configuration ConfigurationSummary Summary

Nose Cone Attitude Control Motor (Eight Nozzles)

Canard Section (Stowed Configuration)

Jettison Motor (Four Aft, Scarfed Nozzles)

Interstage Abort Motor (Four Exposed, Reverse Flow Nozzles)

Adapter Cone Boost Protective Cover (BPC)

Abort AbortMotor Motor No. No.ofofNozzles: Nozzles: Nozzle NozzleCant CantAngle Angle(to (toCL): CL): Isp (sea level): Isp (sea level): Thrust Thrust(Total (TotalininVehicle VehicleAxis): Axis): Burn BurnTime: Time: T/W: T/W: Attitude AttitudeControl ControlMotor Motor No. of Nozzles: No. of Nozzles: Nozzle NozzleCant CantAngle Angle(to (toCL): CL): Isp (vac): Isp (vac): Thrust Thrust(per (perNozzle): Nozzle): Burn Time: Burn Time: Jettison JettisonMotor Motor No. No.ofofNozzles: Nozzles: Nozzle NozzleCant CantAngle Angle(to (toCL): CL): Isp (vac.): Isp (vac.): Thrust Thrust(per (perNozzle): Nozzle): Burn Time: Burn Time:

Mass MassProperties PropertiesSummary Summary Dry DryMass Mass Propellant Propellant GLOW GLOW lbs lbs

44 30º 30º 250s 250s 506,408 506,408lbs lbs 2.0s 2.0s 15:1 15:1 88 90º 90º 227s 227s 2500 2500lbs lbs 20s 20s 44 35º 35º 221s 221s 9668 9668lbs lbs 1.5 1.5ss 8148 8148lbs lbs 5468 5468lbs lbs 13616 13616

Crew Module (CM) Launch Abort Vehicle (LAV): Crew Module + LAS

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Crew Exploration Vehicle Project Office

CEV Service Module Ultra Flex Solar Array

Strobe Light RCS thruster modules 4PL

Array Pointing Gimbal

Configuration ConfigurationSummary Summary Structural Configuration Structural Configuration Propulsion PropulsionConfiguration Configuration SM Propellant SM Propellant Total TotalSM SMΔV ΔV Main MainEngine EngineThrust Thrust RCS Thruster RCS ThrusterThrust Thrust Solar Array Area Solar Array Area Solar SolarArray ArrayPower Power Radiator RadiatorArea Area Thermal ThermalDissipation Dissipation

T zero panel

Serial N2O4 tanks 2PL CM umbilical

Composite radiators (MMOD bumper)

Comms Avionics on HGA

33Rings Rings/ /66Longerons Longerons 2x2 Serial Feed 2x2 Serial Feed MMH/N 4 MMH/N2O 2O4 6086 ft/s 6086 ft/s 7500 7500lbf lbf 100 lbf 100 lbf 2 388 388ftft2 9.15 9.15Kw Kw 2 334 334ftft2 6.3 6.3Kw Kw

Oxygen tank 2 PL

OME 1PL

(Thrust chamber inside structure for MMOD shielding)

(5000 psi COPV)

Systems bay 2PL

S-Band Patch Serial MMH tanks 2PL Antenna (Location minimizes CG shift)

Payload

Longerons 6PL (Shear web)

Ring frames 3PL

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Crew Exploration Vehicle Project Office

CEV Spacecraft Adapter Configuration ConfigurationSummary Summary Panel IM7/977-3 PanelMaterial Material IM7/977-3sandwich sandwich Longeron Material 7075 aluminum Longeron Material 7075 aluminum Ring RingFrame FrameMaterial Material 2024 2024aluminum aluminum Mass MassProperties PropertiesSummary Summary GLOW 1281.4 GLOW 1281.4lbs lbs

SA umbilical 3PL

SM separation bolts 6PL

198 in ML-440WSO white silicone thermal control coating

130.3 in

Vent holes 9PL Bolted CLV field joint

Access panel for solar array and HGA 2PL

216.5 in 8

Crew Exploration Vehicle Project Office

Orion Lockheed Martin Industry Team

• Systems & Design Engineering Support

LM GRC

• Environmental Control & Life Support • Active Thermal Control • System Power Management

• SM Liaison Office

• Propulsion

• Launch Abort System • Safety & Mission Assurance

LM LaRC

• Avionics • Integrated System Health Management • Crew Interface • Mission Ground Ops Support

• • • • • •

Program Management Systems Integration Crew Module Development Service Module Development Qualification Test Software Development

• LAS Liaison Office

KSC • • • • • • • • •

Operator Interfaces Ground Processing Mission Flight Planning Software Development

Final Assembly Checkout Acceptance Test Sustaining Engineering Spacecraft Refurbishment

Michoud • CM and SM Structures

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Crew Exploration Vehicle Project Office

Project Orion is Leveraging Unique Skills Throughout NASA Ames

Glenn

• Lead Thermal Protection System ADP • Aero-Aerothermal database • Software and GN&C support

• Lead Service Module and Spacecraft Adapter integration

Dryden • Lead Abort Flight Test Integ/Ops • Abort Test Booster procurement • Flight Test Article Devt/Integ

• Flight Test Article “Pathfinder” fabrication • SE&I Support

Goddard

Orion Project Management

Langley • Lead Launch Abort System integration

JPL • Thermal Protection System support

• Lead landing system ADP • SE&I Support

Johnson

Kennedy

• Lead Crew Module integration • Orion Spacecraft Integration • GFE projects management • Flight Test Program

• Communications Support

Marshall

• Ground processing • Launch operations • Recovery operations

• LAS and SM SE&I Support 10

Orion Advances the Human Exploration Vision

Crew Exploration Vehicle Project Office

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Orion is the next generation crew piloted spacecraft – Human access to Low Earth Orbit … – … and to the Moon and Mars

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Orion has a talented management team and workforce which utilizes unique personnel and facility strengths from across NASA and industry

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We have an exciting path to bring Orion to meet the mission – – – – –

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Finalize requirements Mature the technology Design the Systems Test the Systems Prepare for first flight operations

We are committed to meeting the national priorities for Orion! 11