Nasa Orion Crew Exploration Vehicle - 2007

From Alpha to Orion

Skip Hatfield Orion 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 partner

January 11, 2007

2

Components of Program Constellation Earth Departure Stage

Orion - Crew Exploration Vehicle Heavy Lift Launch Vehicle Lunar Lander Crew Launch Vehicle

January 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 capability

January 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 Power system Launch Abort System performance – size for margin

SM OME and RCS

Power Supply A Power Supply B

•

Design for state-of-the-art where technology is rapidly advancing – – – – –

Low power equipment Small size electronic packaging Commercial software Software reuse – Open source software Flexible, state-of-the-art avionics

January 11, 2007

Interconnect

Arbiter

Prox Ops / Arbiter Flash memory

Network Gateway Video Card

Isolated interconnect between Flt-critical and Non-Flt-critical processing partitions

Audio Card Serial I/O Comm Discrete & Analog I/O 1394B card 1553 card (2-ch) SDC Processor Interconnect

Graphics card Arbiter

Discrete & Analog I/O Flight Critical Processor

1553 card (2-Ch)

Backplane I/O Connector area

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 Modularity Approach P3I, Continuous Process Improvements ICE/IDE & Tools

Avionics Systems – – – –

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

• Structures – – –

TPS & Analytical Tools Friction Stir Welding, Al-Li Composites in SoA Applications (JSF Experience)

• Propulsion – –

Non-toxic (CM) Propellants SMME Approach

January 11, 2007

787 Avionics

Phoenix Solar Array & TPS

Friction Stir Welded Orthogrid Al-Li JSF Composite Materials & Manufacturing

6

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 • Communications Support

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 January 11, 2007

Marshall

• Ground processing • Launch operations • Recovery operations

• LAS and SM SE&I Support 7

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 January 11, 2007

• 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 8

Decision Making Structure Constellation Program

LM Prog Review Board (PRB) LM Eng Review Board (ERB)

LM “Tabletop” Reviews

January 11, 2007

Level I Boards

PM (Cost/Sched/Tech) Accountability

CPCB

CEV Risk Mgmt Panel

NASA CAM/org/panel communication and issue/position coordination before ERB/PRB Communication with NASA orgs and/or panels

LM/NASA

Communication

NASA Issue Coord Tech Integration

CEV Integ Panel

T&V Integ Panel

Ops Integ WG Cockpit WG

NASA Led Reviews

Lockheed Led Reviews

Orion Project

Level II Boards

SR&QA Panel

FT Panel FTA WG

GEM Panel

GFE/ADP Projects

IPTs/SPTs/IWGs 9

Independent Technical Authority is Adapted to the Orion-CEV Management Strategy Administrator OCE

JSC Center GRC Center LaRC Center Director Director Director

AA Cx Program Manager

Cx CE

CEV Project Manager

Contractor PM Contractor CE January 11, 2007

JSC Eng Director

GRC Eng Director

LaRC Eng Director

CEV CE

SM CAM

SM PLE

LAS CAM

LAS PLE

All module Issues will be “Passed Through” CEV CE If CEV CE and module PLE disagree, then TA proceeds up parallel Center Chains If JSC/module Eng disagree then goes to CD If JSC/module Center Directors disagree then 10 goes up to OCE

Proposed Joint LM-NASA Decision Structure: Decision protocol within contract scope

Formal Decision Process

PRB

• Contract baseline control

ERB

• Technical baseline control

“Tabletop” Reviews

Horizontal Integration

Integrated Product IPT Teams IPT IPT

Integration Working IWG Groups IWG IWG

January 11, 2007

• Verify Horizontal integration complete • Management Review

Subsystem Product Functional Functional Teams Functional Integration Teams Integration IntegrationTeams Teams

NASA GFE/ADP Projects

11

Orion Team Refining Requirements and Design Systematically 2005 Aug

Sept

Phase 1 ATP CEV Major Milestones

501

2006 Oct

Nov

Dec

Jan

Draft SRD Release

LM 502

Feb

Mar

CEV Arch Changes

April

May

CxP ICPR

CFI

June

July

2007 Aug

Sept

Phase 2 ATP

Faceto-Face

Oct

Nov

CxP SRR

Dec

CEV SRR Data Drop

Jan

Feb

CEV SRR (Board)

LM 504

LM 503

601 602 CICP Approval

LM 603

RAC-1

LM 604 RAC-2

DAC1

RAC-3

CRC-1 CRC-1A

CEV Analysis Cycles

CEV-CLV DAC Outbrief

NASA NASA––LM LMTeam Team

CRC-2

CRC-1 CRC-3

CRC-1A 606

“605” Config NASA-LM Reconciled Configuration

CRC-2 CRC-3 RAC = Requirements Analysis Cycle

January 11, 2007

CRC = CEV Reference Configuration

12

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 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 PreDAC1 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

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Orion Spacecraft General Arrangement Mission MissionSummary Summary No. No.Crew Crew Crewed CrewedMission MissionDuration Duration Quiescent QuiescentDuration Duration Total TotalΔV ΔV

44(lunar), (lunar),66(ISS) (ISS) 18 days (lunar) 18 days (lunar) 210 210days days 5864 5864ft/s ft/s

Configuration ConfigurationSummary Summary Diameter Diameter(CM (CM&&SM) SM) Pressurized PressurizedVolume Volume(Total) (Total) Habitable HabitableVolume Volume(Net) (Net) SM SMPropellant Propellant CM CMPropellant Propellant Payload Payload(Lunar (LunarReturn) Return)

16.5 16.5ftft 3 691.8 691.83ftft3 342 342ftft3 MMH/N 2OO 4 MMH/N 2 4 GO /GCH 2 4 GO2/GCH4 220 220lbs lbs

SM CM LAS

Block Block22Mass MassProperties PropertiesSummary Summary GLOW 61,860 GLOW 61,860lblb EMO 50,231 EMO(1/8 (1/8LAS LASPartial) Partial) 50,231lblb

January 11, 2007

15

Launch Abort System 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)

Configuration ConfigurationSummary Summary

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

Mass MassProperties PropertiesSummary Summary Dry DryMass Mass Propellant Propellant GLOW GLOW

44 25º 25º 250 250ss 518,670 518,670lbf lbf 4.0 4.0ss 88 90º 90º 227s 227s 3,000 3,000lbf lbf 20 s 20 s 44 35º 35º 221 221ss 40,975 40,975lbf lbf 1.5 1.5ss 8,184 8,184lbs lbs 5,546 5,546lbs lbs 14,428 14,428lbs 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 Deployment January 11, 2007

17

LAS Control Motor Description LAS Control Motor [Rev.-R]

Nozzles Located Radially Composite Case

Redundant Thermal Batteries and Electronics

Function

LAV Pitch & Yaw Control

Maximum Thrust (Vacuum) in Any Axis

7,000 lbf

Maximum Thrust (Vacuum) Per Nozzle

3,000 lbf

Thrust Axis (from LAS Center Line)

90 deg

Burn Time

20 sec

Isp (Nozzle Center Line, Sea Level)

227 sec

Response Rate @ MEOP

< 0.05 sec to 90% Thrust

Throttle Capability

0 to 100% Thrust

Surface Thermal Protection

0.035” ABL-5 Cork Bonded 0.01” RTV

Propellant Grain

AAB-3751

Titanium Power Plenum # Nozzles

Thermal Batteries & Electronics January 11, 2007

Two Thermal Batteries 8

Nozzle Positions

Every 45° Starting at Zero

Motor Length

40 in

Motor Diameter

32 in

Motor Weight (Inert / Propellant)

477 / 622 lbm

(w/WGA)

Carbon-SiC Pintle & Throat

Interfaces

1) To Nose Cone: Common Attach Ring, Bolted 2) To Interstage: Common Attach Ring, 18 Bolted 3) To Raceway: Bolted Interface

LAS Abort Motor Description LAS Abort Motor [Rev.-R]

Nozzle Manifold

Flow Deflector

Propellant DL-H503

Igniter Assembly

Steel Nozzle Assembly

Graphite Composite Case

January 11, 2007

Function

Provides Abort Impulse

Maximum Total Axial Thrust (Vacuum)

518,670 lbf, 70° F

Burn Time

> 4.0 sec

Ramp Up to 90% Thrust

150 millisec

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 Grain

DL-H503; 6% Al

Nozzle Cant Angle

25 deg

Thrust Axial Alignment

2 deg

Motor Length

216 in

Motor Diameter

36 in

Motor Weight (Inert / Propellant)

3479 / 4581 lbm

(w/WGA)

Interfaces

1) To Interstage: Common Attach Ring, Bolted 2) To Adapter Cone: Bolted 3) To Raceway: Bolted Interface 19

LAS Adapter Cone Description LAS Adapter Cone [Rev.-R] Gr / Ep Monocoque Structure

Stainless Steel Rings and Feet

Function

6-Point Physical Interface Between LAS & CM; Carries Abort Loads

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 from CM

Adapter extension Removable sep-nut access panels January 11, 2007

Nominal Launch Cable or Linkage Attachments to Base of Mechanism

Cables or Linkages Are Severed Disconnecting LAS from Mechanism 20

NESC Alternate LAS Phase 2 (1/2) • CEV Aeroacoustic Performance

• CLV Stack Aerodynamic Performance –

– –

–

Phase 1 axisymetric CFD indicated an effective mass-to-orbit increase of 1,000 lbs for an idealized LAS aerodynamic shape Plan stack wind tunnel testing in Boeing Polysonic Tunnel (Completion: 30 Jan) Trajectory analysis will quantify mass-to-orbit benefits (Prelim Results: 15 Feb; Final Results: 15 April)

Integrated Nozzle ALAS

Exposed Nozzle ALAS

–

Analytical quantification of ALAS improvement of aerodynamic noise source on CM and SM as compared to baseline LAS geometry (LM Draft: 21 Dec; Prelim: 15 Feb; Final: 15 April) Plan acoustic measurements on ALAS in Ames UPWT (piggyback on planned acoustic test 16AA) (Completion: 30 April)

Baseline LAS

ALAS w/scarfed Nozzles

~147dB 604 mod 6 Baseline

~170dB

~170dB

~149dB

ALAS Geometry Variations

January 11, 2007

21

Orion Spacecraft 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 342 HabitableVolume Volume(Net) (Net) 342ftft33 Habitable Volume per 4 CM 85.4 Habitable Volume per 4 CM 85.4ftft3 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 160 RCS Engine Thrust 160lbf 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

17,396.8 17,396.8lbs lbs 385.1 385.1lbs lbs 282.8 282.8lbs lbs 16,174.3 16,174.3lbs lbs 18,900 18,900lbs lbs

Main Parachutes (3) Main deployment pilot chutes (3)

PICA Heatshield, ML440WSO Coating

Horizon windows 2PL SLA-561V backshell TPS AZ93 coating

Hatch Yaw thrusters 2PL

Docking windows 2PL

Drogue deployment hatch for Fwd bay cover jettison

Forward bay access panels 6PL Lower backshell Panels 5PL

99% Male Unpressurized 3% spinal growth

1% Female

8 inches seat stroke (x, y, z)

WMS (toilet)

Drogue mortars parallel deploy (2) ECLSS Bay January 11, 2007

Avionics bays

22

CM Configuration Overview

Backplane Stowage

Side Window

Side Hatch

January 11, 2007

Forward Window

Docking Tunnel

Docking Hatch

23

Aft Bay Configuration Deleted Fourth Thruster String (5 plcs) Changed to 160lb Thrusters (15 plcs)

Swapped 1:00. 3:00, 9:00 and 11:00 Wedges to Match Hatch Swap to –Y

Resized RCS Tankage for Increased Residuals (8 plcs)

Rearranged Batteries, Split Cold Plates (6 plcs)

Reformatted Backup Landing Battery

Added PhaseChange Heat Exchangers Added Horizontal (2 plcs) Retro Rockets (4 plcs)

Added Vertical Retro Rockets (4 plcs)

Relocated 1 RCS CH4 Tank Deleted ATCS Freon Tanks and Manifolds (4 items) Note Interferences with PCS Tankage, January 11, 2007 ATCS Exchangers, and Horizontal Retros

Relocated 1 RCS GOX Tank

24

Crew Cabin Configuration (Block 2) Operator 1 and 2 (Position provides forward view for docking and view of horizon during ascent & entry)

Late stowage areas (Near hatch and not underneath seated crew)

Hard Lockers (Provide solid footing for crew ingress/egress thru hatch)

Galley (Physically separate from WMS)

ECLSS (Co-located with avionics in floor for shorter cable lengths & improved CM C.G.)

Avionics (Redundant strings physically separated & accessible on orbit. Spacing accommodates cable bends. Orientation eliminates blind connectors.)

Block 1A Configuration January 11, 2007

25

Crew Console Center Display Controls

Cabin Lights

Communications

Pilot Display Controls Emergency Re-entry Initiation, Pyro Inhibits, ECLSS mode

Temperature Control Main Caution and Warning Lights (2 sets)

10 Generic Emergency Re-entry Switches

Commander Display Controls EPS Inhibits - Breakers Fire Suppression Holes

ECLSS umbilical

1310 Displays (x3) Keyboard January 11, 2007

26

Heatshield and Crushable Structure

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

LIDS Interface

LID Attachment Ring LIDS-GFE LID Attachment Ring Wire Routing

January 11, 2007

LID Avionics

28

Orion Spacecraft Service Module Radiator Panel (301 ft2 Radiating Area)

Umbilical Housing

Ultra-Flex (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 Panels (2 PL)

MMOD Blanket (Protect Engine) OME Engine (7500 lbf (vac)) Ultra-Flex (Mid-Deploy)

Ultra-flex Solar Array (388 ft2 Generating Area)

High Gain Antenna

RCS & TEI Backup TEI Backup (+X Engines) R4D 125lbf, radiation cooled

RCS Thruster Pod Block Swap Geometry R1E 25lbf, radiation cooled January 11, 2007

(Four Places)

Configuration ConfigurationSummary Summary Structural StructuralConfiguration Configuration 33Rings Rings 66Longerons Longerons Propulsion Configuration 2x2 Propulsion Configuration 2x2Serial SerialFeed Feed SM Propellant MMH/N O 2 4 SM Propellant MMH/N2O4 Total SM ΔV 5700 Total SM ΔV 5700ft/s ft/s Main 7500 MainEngine EngineThrust Thrust 7500lbf lbf RCS Thruster Thrust 25 & 125 RCS Thruster Thrust 25 & 2125lbf lbf Solar Array Area 388 ft 2 Solar Array Area 388 ft Solar Array Power 9.15 Solar Array Power 9.15Kw Kw 2 Radiator 310 RadiatorArea Area 310ftft2 29

Alternate Service Module/Spacecraft Adapter •

• •

Technical trade studies by NASA and LM identified that an encapsulated SM offered mass savings between SM and SA CEV Weight Reduction Team approved trade on 18 Dec Alternate SM/SA Benefits – – – – –

• • •

Fairing jettisons after aero loads diminish Reduction of aero thermal loads on radiators (w/ insertion orbit changes) Improved packaging solutions (e.g. arrays) Protected environment at pad Avionics / ECLS Ring provides modularity to improve integration & test

Team investigating two implementations of concept Ongoing results continue to show significant mass savings Final results to be presented at LM engineering review board on 6 Feb

External Longeron Config (ELC)

Internal Longeron Config (ILC)

SA Interface Internal longerons

External longerons or truss)

SA Interface

January Tasks SM Primary Structure CAD Model Available

Week of 1/7

Week of 1/14

Week of 1/21

Week of 1/28

1/9 Avionics ring 1/11 Prop module/SA

Populate Model w/Subsys CAD Model Available for Subsys Review & Analysis

1/15 1/16

Model Rvw w/GRC & MSFC Subsystem Analysis Cycle FEM Development

1st resize complete

1/22

Design feedback, MEL’s available Primary structure mass props

Tabletop Preps Tabletop Review

1/25

ERB Preps Feasibility (Go-No Go) ERB Final Summit Outbrief

January 11, 2007

1/29 2/1-2

30

Nominal Ascent Sequence Encapsulated SM (External Longeron)

Press to MECO

Fairing Jettison

Longeron Separation 4 – Frangible Bolts 4 – Gas Thrusters 4 – Hinged Longerons

Fairing Separation (2 Panels) 4 – FLSC 2 – Thrust Rails

January 11, 2007

31

Major NASA Technology Applications to Meet the Mission . En Pre-

try

Initial Pull-Up

Controlled Climb to Atmospheric Exit

Ball

Skip

a Fin

Final WX Update TD-3 hrs

istic

lG e lid

8

Docking Systems Automated Rendezvous & Docking

TPS “Heat Shield” January 11, 2007

Edge of Atmosphere

Landing Site

Skip Reentry

Aero Sciences

Parachutes

Landing Impact Attenuation32

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 properties for suitablility - Complete

•

Back 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

TPS Advanced Development

AVCO technicians injecting ablator into honeycomb (CM had 300,000 cells)

Ablative TPS Development Test in an Arcjet Goal: reduce uncertainty levels by validation with flight data

January 11, 2007

34

CEV Aerosciences Project Mach 25

Mach 40

On-Orbit Plumes Environment

Entry Heating Phase CEV LEO Direct or Ballistic Reference Entries

Service Module Jettison

Atmospheric Entry Environment

Service Module Jettison CSM droop

CEV Lunar Direct, Skip, or Ballistic Reference Entries

Hypersonic Abort LAT Nominal Jettison Mach ~7.5, ~200k ft alt

LAT Sep for high altitude LAS abort Service Module Jettison

Plume Heating

Ascent Abort 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

Turn-around maneuver

Mach ~0.5 Recovery Systems Deploy

LAT Sep At 25k ft

Parachute Cover Sep Pad Abort Parachute System Deploy

Main Chutes Mach ~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 hooks

January 11, 2007

36

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

ISS LIDS/APAS Adapter Orion will dock to ISS via existing APAS mechanisms, leaving adapter for LIDS on subsequent missions

S-band System

Power Converter

MBSU

APAS Avionics VMC

Crew Module

PMA

ATLAS Passive LIDS Active LIDS

•

A P A S

A P A S

Node 120V Power ISS CCA

1394 28vdc

GN&C Docking Target(s)

1553 ISS MDM

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

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January 11, 2007

C

Thruster Pod 4

Thruster Pod 3

Thruster Pod 2

A

S

Thruster Pod 1

E

39

Cryogenic Visor Valve Operation

January 11, 2007

40

Orion Flight Schedule Overview FY06

FY07 SRR

FY08

FY09

Prime Award PDR

Project Design

FY12

FY13

FY14

FY15

W E I V E R R CDR

Max q Nom Abort

E D N U

Devt. LAS PA

Flight Article Production

FY11

SDR

Project Requirements

Development / Qual Testing

FY10

Ares I-X FT (1st stage test)

Transonic Abort

Proto LAS PA

Max q Off-Nom Abort

Orion/Ares 1 Hi Alt Abort

First Human Launch 10/2013

Orion/Ares 2 Orbit Flight

Integrated ARES-Orion Launches 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 2008

January 11, 2007

42

CAP Aerosciences - Testing and Development Facilities

Ames UPWT (11’ & 9’x7’)

NASA “Columbia” Supercomputing Facility

Langley Hypersonic Complex Mach 6 Air, Mach 6 CF4, others

January 11, 2007

Aberdeen Proving Grounds

Langley UPWT (4’x4’ high and low) and Mach 10

CUBRC LENS I, LENS II, LENS-X

Langley TDT (16’)

Ames Range Complex: EAST, HFFAF, GDF

AEDC Hypersonic Tunnels B, C, 9

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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 2007

January 11, 2007

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ORION Operations at Michoud Assembly Facility

MAF

CEV Bldg 103 Manufacturing Area Crew Exploration Vehicle

Alt 1 Proposal

MAF Use Working Group Area Offered

NOW Alt 2

Detailed Area Layout 4 PMR #2 Draft

January 11, 2007

Export Controlled Information

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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 months

January 11, 2007

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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 facility

January 11, 2007

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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 – – – – – –

• January 11, 2007

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! 48