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Hatfield skip
1. From Alpha to Orion
Skip Hatfield
Orion CEV Project Manager
2. 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
3. Components of Program Constellation
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 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 avionics
January 11, 2007 5
6. 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 Approach
January 11, 2007 6
7. 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 Support
January 11, 2007 7
8. 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
9. Decision Making Structure
Constellation Program 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 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 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-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/ADP
January 11, 2007 Projects 11
12. 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 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
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
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 General Arrangement
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 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 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 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
19. 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
20. 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
21. 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
Nozzle
Integrated Nozzle ALAS
ALAS
~147dB
604 mod 6 ~170dB
Baseline
~170dB ~149dB
ALAS Geometry Variations
January 11, 2007 21
22. Orion Spacecraft Crew Module
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
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 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
28. LIDS Interface
LID Attachment
Ring
LIDS-GFE
LID Attachment
Ring
LID Avionics
Wire Routing
January 11, 2007 28
29. Orion Spacecraft Service Module
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/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
2/1-2
January 11, 2007 30
32. 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 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
AVCO 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
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 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
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
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