cxp istim outbrief to jsc engineering mgmt -...

EA4/Labbe/Dill/Prevett 11-28-07

CxP ISTIM Outbrief to JSC Engineering Mgmt

♦ ISTIM - 228 issues• 750+ people supporting• 63 splinter sessions running Nov 5-16

− GRC/Gati; KSC/Delgado, Parrish; MSFC/Otte, Linner; JSC/Dill, Prevett− Technical Agreements documented in splinter protocols− From/To’s developed by Issue Owner, submitted with protocols

• 67 splinter session outbriefs to Team 0 (Labbe)− 494 Issue Forms submitted

• 419 From/To’s in Access database• Additional captured outside database for ADD, Ops Con, C3I, Vol 4

• From/To’s collected by book and reviewed in “book-centric splinters”• Reviewed at Nov 20 CxCB and Nov 26 & 28 SECB

♦ ISTIM products• Mgmt Directive released today to support 12/7 Orion contract (~1 ft3 of paper)• CR/D to be released 12/13 to baseline CxP documentation with thumbs up/down at 12/19

CxCB

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♦ CARD Fault Tolerance requirement CA0214-PO update: TheConstellation Architecture shall control hazards that can lead tocatastrophic events with no less than single failure tolerance, exceptfor areas approved to use Design for Minimum Risk. The level of failuretolerance must be determined using the hazard identification andmitigation process described in CxP 70038, Constellation ProgramHazard Analyses Methodology. The failure tolerance requirementcannot be satisfied by use of EVA, emergency operations or emergencysystems.

♦ Block 1 SM to have unpressurized cargo capability, Block 2 SM to haveSIM Bay, not working ISS pressurized cargo but keeping requirementas placeholder for lunar capabiliity

♦ Landing mode - Nominal coastal water landing, contingency-only landlanding, cease/desist working nominal land landing, water landingenvironment definition per Team 0 recommendation, landing accuracyincreased from 5 km to 10 km

♦ 36-hr post-landing - reduced DSNE max sea surf temp from 36 to 31 Cconsistent with likely landing locations, added flight constraints forlanding in warmer locations, IDAC-4 TDS for probability of off-nominallanding and Orion ECLSS enhancement by March 7 checkpoint, newEVA SRD requirement for 1-g suit doffing within 15 minutes (no TBR)

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♦ Lunar launch sequence - baseline Ares V first with 4 consecutiveattempts, 90 minute separation, Orion/CLV 7 consecutive attempts(protects 4 CLV attempts after CaLV launch on its fourth attempt), 6 dayturnaround to next TLI, then 4 more attempts (11 total)• APO and GO only planning for 10 CLV attempts (flt hdwr cryo cycle certification,

commodity availability) link to backup• Orion/CLV first sequence to be evaluated in IDAC-4 (RAD)

♦ Launch day consumables – IDAC-4 TDS to trade use of contingencyrepress gas for launch scrubs, T-0 dry air, add low press O2 to T-0, orreservice at pad

♦ Unpressurized/expedited return duration• return from lunar surface to Earth surface within 132 hrs• Orion to transfer from LLO to LRO within 6 hrs• Orion to return crew to Earth surface within 120 hrs of docking in LRO• Lander shall dock with Orion in LLO within 6 hrs of launch• Orion shall support crew return with unpressurized cabin for at least 144 hrs (24

hrs margin over 120 hr requirement)

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♦ ISS concern with LIDS spring separation removal duringOVEIWG weight scrub, IDAC-4 TDS to evaluate requirement

♦CxCB directed PEP instead of OVEIWG baselined PUP (fixed 28-volt, no data) to eliminate separate voltage converters forportable equipment

♦MMOD – ISS Node 2 fwd and Node 1 nadir docking locations tobe evaluated assuming no port swap (210 days)

♦Lightning monitoring - program requirements clarified thatvehicle onboard monitoring not required

♦CxP 70137 Structural Loads Control Plan – updated that Orionwill design to structural loads for ascent aborts based on 0.9773probability of not being exceeded (“2-sigma loads”)

♦CxP 70028 Orion-GS IRD – deleted 1 of 3 EPS power channelsconsistent with 606C redesign

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♦Dissimilar voice - X-band approved with IDAC-4 TDS forpostlanding gap closure (UHF/AM NATO & military SAR, VHF-AM civil SAR, VHF/FM maritime)

♦C000130 reduced reliance on ground networks• Orion 192 Kbps ascent link via Space Network from T-0• Ares upper stage 15 Mbps engineering link via AF (Tel-4 or new

Consolidated Instrumentation Facility (CIF)) then handoff to SN at LOS(200 Kbps)

• C-band tracking from launch main/wing sites & Wallops♦Gigabit ethernet approved for Orion/Ares critical data bus -

ESMD CE requested IRMA risk be opened due to low TRL♦Data recording – no crash survivable recorder, Orion to record

20 GB of Ares data (200 Mbps)

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♦PSE recommended nominal delta-V reduced from 1,760 m/s to1,492 m/s (17426 lbs) with tanks sized for additional 68 m/s (1300lbs) to be covered from Program Mgr reserve link to backup

♦CLV injection accuracy reduced• Semi-major axis from 5 nmi to 8 nmi• Orbit plane from 0.05 deg to 0.07 deg• 48 lb impact to Orion propellant (included in PSE recommended delta-V)

♦Mass properties and margins reconciled link to backup• 675 kg for Flight Crew Equipment, EVA, and flight crew mass in Orion for

lunar, 1047 kg for ISS• EVA System control mass 171.5 kg in Orion for lunar, 284.4 kg for ISS• FCE control mass 133.8 kg in Orion for lunar, 220.4 kg for ISS

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♦ GO decisions• CEV purge 0.5 psi assumed for IDAC-4, no SM propellant low point

drain access, add LAS & frustum access, ALAS interstage purge• Implement End-to-end RF test capability in VAB to support early

operations• C000203 GO pushbacks

− NASA-STD-5005 (GSE design) rev B with CxP 70013 SEMP tailoring insteadof rev C

− Add GS capability to initiate pad abort− delete allocation of standards/specs to GO

- CxP 70036 CEQATR- CxP 70050 Power Quality Spec• CxP 70135 SDVR• JSC 62550 Structural Design and Verification Criteria for Glass, Ceramics, Windows• NASA-STD-5017 Design and Development Requirements for Mechanisms, Sect 1-4• NASA-STD-(I)-5019 Fracture Control Requirements for Spaceflight Hardware• NASA-STD-(I)-6016 Standard Materials and Processes Requirements for Spacecraft

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♦Ares decisions• GPS metric tracking - Ares based solution selected for Ares I/V

commonality and protect for non-Orion payloads− OI director to negotiate delayed availability (Orion 4) with range

• Automated flight termination− Waiver for Ares I-Y and Orion 1− scar now (potential Ares block upgrade)

• Launch pad stabilization and damping – separate midstay and damperT-0 interfaces approved link to backup

• C000207 cryo helium for upper stage pressurization• C000208 first stage extended nozzle deferred to lunar but will proceed

with MLP launch mount (adapter) to minimize impact of laterincorporation

• Add rollout purges

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Orion Top 10 Decisions Coming out of ISTIM

1. Mass # Re-Allocation Agreements – Issue # 532. LOC/LOM Allocation Agreements – Issue # 2213. Level 2 Earth Landing Direction, strategy for

Earth-based landings in general (water versusland) – Issue # 109-R1, 110-R1, 111-R1

4. Thrust Oscillation GO FORWARD Plan –Issue # 157

5. Agreement to focus on ISS Variant duringDAC#2 and PDR (including boundingconditions for Ares). – No Issue #

6. Agreement with Orion Block Update Strategy.– Issue # 197

7. Requirements From/To Management Directivewhich supports 12/7 Contract letting

8. Ares/Orion MOU agreements: FEM Deliveries,LA3 versus LC4, etc.

9. Ascent/Post-Landing CommunicationsStrategy (Orion Real-time downlink, Aresdownlink, Ares data recorded onboard). –Issue # 4-R2/c, 11, 22-R1, 23-R1, 106, 178

10. Resolve the discrepancy between the CARDdelta V and the Orion SRD delta V

Updated CARDrqmtsNo change in rqmts

Assess 606C in DACBring to Admin

Water is b/l – Orion DAC forcontingency land landing

Working Group11/15-16

Officialize w/IDAC/ODAC plans

MD coming outof 11/20 CxCB

ILSM Splinter

CR 130

Agreed to delta V

Team formed to work –no longer scope of ISTIM

606C does not meetp/l comm reqts

Officialize w/reqt applicability matrix

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Ares I Top Issues for ISTIMPRIORITY 1 Issues♦ Update Ares Mass Allocations/Payload Requirements in CARD – Issue # 53♦ Cryo Helium – Issue # 80♦ Stabilization & Damping Trade (T-Zero) – Issue # 93♦ Ares Roll Out Purge Requirements – Issue # 108♦ Fault Tolerance Requirements – Issue # 84b♦ Integrated Vehicle Debris Approach – Issue # 36♦ CR-130 Reduced Reliance on Ground Networks – Issue # 106♦ SDVR TCM – Issue # 162

♦ First Stage Induced Thrust Oscillation – Issue # 157

♦ First Stage Nozzle Extension CR – Issue # 73

PRIORITY 2 Issues♦ LOC/LOM Requirements – Issue # 221♦ Abort Conditions & Design Requirements – Issue # 158♦ Orbit & Insertion Accuracy – Issue # 53♦ Ops TBR Push Backs – Issue # 207 ♦ CR-203 Requirements – Issue # 84f♦ First Stage Frustum Door – Issue # 74♦ Integrated Vehicle C3I Requirements – Issue # 170♦ Ares Flight IT Security Requirements – Issue # 202♦ Ares Timing Requirements – Issue # 203♦ Ares Software Build Requirements – Issue # 7♦ Common bulkhead servicing/pad – Issue # 80♦ ISDS - Auto Destruct/FTS – Issue # 190

♦ FS reusability – Issue # 86

♦ GPS Tracking Requirement on Ares – Issue # 9

These Issues wereagreed upon and areClosed

Ares/Gary Lyles is leading resolution

Action to Ares to provide block upgrade plan by PDR

These Issues wereagreed upon and areClosed

Team 0 to recommend to the CxCB to try topush back on the timing of the implementationof GPS to defer near term costs.

Separate briefing provided

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♦Ambient to Cold GHe supply – Issue # 80-R1♦VAB access to FS Frustum Door – Issue # 74-

R1♦One non T-0 Damper Arm to two T-0

Stabilization & Damper Arms (ISTIM) – Issue #93-R2

♦FS Nozzle Extension – Issue # 73, 81, 105♦RF testing in VAB – Issue # 211♦Ares I ECS Purge During Rollout♦Hyper servicing/SCAPE access to Orion ESM

thru IU (ISTIM) – Issue # 82, 88-R2♦Mono-propellant RCS for the CM (ISTIM) –

Issue # 60, 62r1, 63r1,148♦Additional post-landing GSE (ISTIM) – Issue #

148♦Access for LAS GSE removal, dessicant

removal, purge connection in VAB – Issue # 77♦Continuous Orion purge, including ALAS

purge, during integrated operations – Issue #108-R1, 127

GO – Threats to GO Baseline Architecture

11/6 CxCB approved designand CofF funding

Tech agreement, cost impact

Tech Agreement, cost impact

Team 0 on 11/16

Team 0 decision to push CR

0.5 psi purge agreed; techagreement for ALAS purge,cost impact on ALAS purge

Impacts servicing, recoveryand deservicing, cost impact


Tech agreement, no accessrequired



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MO ISTIM Top Issues♦MOD ISTIM Top Needs:

• MO had few issues needing resolution going in to TIM:− Predominantly developmental issues pertaining to C3I Spec Requirements,

Communications (MCC Architecture) and IBT/IBP.• Successes:

− Great deal of progress on Communication architecture affecting MCCdevelopment.

− Agreement with SAVIO on C3I Volume 4 Revision content delivery to meetMCC milestones.

• Open Issues:− Data Architecture Annexes were dropped on November 1st:

• Constitutes approximately 900 pages of protocols and requirements.• Need additional time to review and comment:

• MO meetings set up for week after Thanksgiving.− C3I Volume 8:

• Guidance needed options:• Maintain MCC milestones without content, slip MCC milestones, accelerate

content resolution.• SECB Agenda Item.

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EVA – Expectations and Needs out of the ISTIM

♦Better understanding of the post landing crewsurvival scenario – Issue # 148, 149• Key driving scenario for EVA• 36 hour post landing requirement changes and

allocation to the EVA System• Firm up our understanding between EVA System

and FCE hardware♦Refinement of the landing load cases EVA needs

to assess, design, and certify to – Issue # 40• Including the ascent thrust oscillation and loads

associated with it♦Reassessment of the Program risks:

• Orion suit leak check scenario and capability –Issue # 141, 42

• Orion suit loop isolation capability – Issue # 41♦Orion/EVA ECLSS Interface (ECLSS 5)

• Suit umbilical pressure drop – Issue # 43• LCG coolant supply pressure – Issue # 138• LCG coolant gas amount/trap – Issue # 137

Discussed in splinter and twice inTeam 0. No agreement to defaultto operational workaround (doffingsuit) for hot cases. Orion willperform further analysis. EVA willadd self-imposed time-based doffrequirement for overall operability

Splinter held 11/14. Focuswas mostly on process andforward work for Loads DataBook. EVA will participate inOrion analysis

Agreements reached inJoint EVA/ECLSS splinterheld 11/7. Results briefedand Team 0 concurred on11/14.

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Initial Capability ArchitecturePOD High-Level Overview

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Typical International Space Station (ISS)Reference Mission

Orio

n

LowEarthOrbit

EARTHEARTH

Direct EntryContinental US Landing

Service ModuleExpended

Crew of 1 to 6 1047 kg (2308 lbm) ofcrew & equipment

ISS orbit407 km (220 nm), 51.6º

-20.4 x 185 km(-11x100 nm),70 NM Altitude

8 NM deliv error 51.6º

Orion Control Mass 19.3 mt (42,540 lbm)Ares-I Delivered Mass 20.4 mt (44,780 lbm)

10 min launch window

New

NewOrion CM Op limit: [9,525kg (21,000 lbm)]

Updated

Decision

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Integrated Stack TIM StatusMajor Issues technically Addressed (CxCB)♦ New Control Mass and Reserve Levels♦ Program Technical Margins (MMP)♦ Delta-V Adjustment/Alignment♦ V/I & I/V Launch Seq/Separation - 90min♦ 26 to 6 Day Vehicle Turnaround♦ Flight Rate Clarity♦ Fault Tolerance Implementation♦ LOC/LOM Refinement & Plan Fwd♦ Purge Vent on Rollout/Pad♦ GHe Tank Pressurization/Cryo Preps♦ Orion/Ares Access Platforms♦ T0 Support Structure & Damper♦ GPS Tracking Implementation♦ Ground Network Reliance (CR130)♦ Dissimilar Voice-X Band B/L-Study MUOS♦ Cmd & Control of Integrated Stack (GbE)♦ Comm Freq + Data Rate Plan + E-T-E perf♦ Lightning monitoring (not incl)/ GS needs♦ SRB Nozzle Extension (Lunar)♦ Portable Equip Pwr & Data Port (PEP/PUP)♦ ECLSS/Suit Interfaces and Isolation♦ Nominal Landing Mode Recommendations♦ 36 Hour Post Landing Fwd Plan♦ IDAC4 RAD/SIAP Sync’d Analyses Plan♦ Thrust Oscillation Fwd Plan♦ Structural Loads Control Plan/Cycles♦ Fairing Separation Analysis Fwd Plan

Drive to THE baseline for Balance of SDRs & PDR

Orio

n

LowEarthOrbit

EARTH

Direct EntryContinental US Landing

Service ModuleExpended

Crew of 1 to 6 1047 kg (2308 lbm) ofcrew & equipment

ISS orbit407 km (220 nm), 51.6º

-20.4 x 185 km(-11x100 nm),70 NM Altitude

8 NM deliv error 51.6º

Orion Control Mass 19.3 mt (42,540 lbm)Ares-I Delivered Mass 20.4 mt (44,780 lbm)

10 min launch window

New

NewOrion CM Op limit: [9,525kg (21,000 lbm)]

Updated

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6 crew and cargo (1047 kg 2308 lbm)

Initial Capability Flight Elements

Ares I A103 rev ALaunch Vehicle Characteristics

GLOMLaunch Abort System and ESM Jettison

Mass

923,676 kg 2,036,356 lbm8,380 kg 18,475 lbm

Upper Stage(J2-X)Propellants

Useable PropellantPropellant Offload

Stage pmfDry Mass

Burnout MassInterstage Mass

# Engines / TypeEngine Thrust (100%)

Engine Isp (100%)Mission Power Level

LOX/LH2137,080 kg 302,210 lbm0.0 %0.882315,694 kg 34,599 lbm18,282 kg 40,306 lbm4,878 kg 10,755 lbm1 / J-2X1,308 kN 294,000 lbf @ Vac448.0 s @ Vac100.0 %

First Stage (SRB)Propellants

Useable PropellantStage pmf

Burnout Mass# Boosters / Type

Booster Thrust (@ 0.6 secs)Booster Isp (@ 0.6 secs)

PBAN (16606 Trace)525,431 kg 1,381,043 lbm0.8575105,139 kg 231,792 lbm1 / 5 Segment SRM15,333 kN 3,447,034 lbf @ Vac265.5 s @ Vac

Delivery Orbit

Gross PayloadInsertion Altitude

T/W @ LiftoffMax Dynamic Pressure

Max g’s Ascent BurnT/W @ Booster Separation

T/W Second Stage

Exploration Mission-20 x 185 km @ 28.5°-11 x 100 nmi25.5 mt 56,253 lbm129.6 km 70.0 nmi1.5735.3 kPa 739 psf3.75 g0.070.72

Delivery Orbit

Gross Payload

ISS Mission-20 x 185 km @ 51.6°-11 x 100 nmi19,296 kg 42,540 lbm

GLOM 27,676 kg 61,015 lbmCM Mass 9,525 kg 21,000 lbmPressurized Volume 63.7 m3 683 cu ftCrew Habitable Volume 9.7m3 286 ft3

CM Propellant Mono-prop HydrazineCM Delta V 61.7 m/s 136 ft/sNumber of Crew 1-6Nominal L/D 0.27LLO crewed nominal power mode 3014 WRadiator sizing 23 m2 248 ft2

RIU channels 113S-Band commTotal Equivalent ∆V (tank sizing) 2,407 m/s 5,306 ft/sSM Propellant MMH / N204OME Thrust (vac): 33.4 kN 7,500 lbfOME Isp (min vac) 326s16 x R1E RCS Thrusters Isp: 220-280 s Thrust (vac): 111.2 N 25 lbf8 x R4D TEI Aux. Engines Isp: 311s

Thrust (vac): 489 N 110 lbfSolar Array Area (power generating): ~47.2 m2 ~506 ft2

Spacecraft Adapter 1,227+408 kg 2,705+900 lbmLAS Mass 7,153 kg 15,770 lbmLAS Isp (sea level): 250sLAS Thrust (Total in Vehicle Axis): 223 kN 499,111 lbfLAS Burn Time: 2.0 sLAS T/W: 15:1

Orion 606CCrew Vehicle Characteristics

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Orion Spacecraft Architecture POD Highlights

Key Architectural Changes (606-C)• Nominal water landing (CONUS)• CM mono-propellant hydrazine• Reduced mass LIDS docking mechanism• TPS – tile backshell• ECLSS – separate cabin and suit ventilation loops• Fault tolerance reductions• Expanded Emergency Capability Including all

orbital & entry phases• High rate data comm & dissimilar voice

Crew Module

Service Module

SpacecraftAdapter

LaunchAbortSystem

♦Spacecraft configuration deltas from 606 Rev A• Lower mass vehicle• Added Alternate Launch Abort System (ALAS-11 Rev 3)• Repackaged the Crew Module to reflect hardware changes• Service Module design updates from the configuration study

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Ares I Highlighted Architecture Enhancements Since PBS

Upper Stage• Composite interstage material down-select August 2007• Common bulkhead material changed to Al 2014

First Stage• Relocated Booster Deceleration Motors to Aft Skirt• Located Access Door on Frustum

Upper Stage EngineUpper Stage Engine•• Changed Nozzle Extension C-C Material from Changed Nozzle Extension C-C Material from NaxecoNaxeco to to NoveltexNoveltex (RL-10) (RL-10)•• Incorporated Hydrostatic Bearing in Fuel Incorporated Hydrostatic Bearing in Fuel TurbopumpTurbopump•• Switched to Showerhead-type Main Propellant ValvesSwitched to Showerhead-type Main Propellant Valves

DAC 2 TR 5

Stack Integration• Incorporated Single Fault Tolerant Avionics Architecture• Adjustments to ALAS-11R3• Accounted for CEV-606 w/ Conical SMA

12/8/07

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Ground Systems Overview

• Single-stringprocessingflow

• Orion offlinehyperservicing(Multi-ProcesingPayloadFacilify)

• Integrated test& closeouts inthe VehicleAssy Bldg(VAB)

• Clean padapproach

• Minimalrecovery ops

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Ground Operations Architecture Baseline

Ground Ops BAAStudiesComplete: 11/06

Ares IHypergolsProcessingComplete: 1/07

OrionHypergolsProcessingComplete: 1/07

OrionProcessingPDKComplete: 1/07

Emergency EgressSystemComplete: 12/06

Baseline06/06

AdjustedBaseline

10/07

Current/Future Trades

Completed Trades

Project Trades: quick-couplers, Ares I stabilization, ML launch mount, RF Testing etc.

OrionHPF &TransportersComplete:3/07

Stacking & Int.ArchitectureComplete: 10/07

IntegratedHypersProcessingComplete: 5/07

Launch Sys.ArchitectureComplete: 5/07

CR 150Orion Servicing

CR 149FS Platforms

CR 196HB2 Design

Ares IVAB HB3

Ares INew ML-1

Ares ILC 39B

Ares ICrawler-Transporter

Ares I B/L single-string – 2012 ORD

Some Adjustments Due to Orion

Some Adjustments Due to Ares

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Ground System Baseline Adjustments

Ares 1 Driven Adjustments♦ Ambient to Cold GHe supply (CR 207 – CxCB on 11/6/07 approved design work and CofF

funding)• Design/build/maintain ML H2 heat exchanger, pad flare stack

♦ VAB access to FS Frustum Door (CxCB 11/20)• Modification to existing platform

♦ Two T-0 Stabilization & Damper Arms (CxCB 11/20)• Design/build/maintain two T-0 stabilization/damper arms on the ML

♦ ECS purge during roll-out (CxCB 11/20)• Modification to ML ECS Infrastructure

♦ US 28V flight battery (Li-Ion) charging• Retrofit battery lab, charging in VAB and at Pad

Orion Driven Adjustments♦ Land vs. water landing (CxCB 11/20)

• Land vs. water suitable recovery assets (in-shore)♦ CM, SM, ALAS purge requirements from rollout of O&C through launch (except stacking

operations) (CxCB 11/20)• Design/procure/install new ECS capabilities (mobile and fixed) at KSC

♦ Mono-propellant RCS for the CM (CxCB 11/20)• Hydrazine safing/deservicing (landing site/MPPF)• Post-landing handling and transportation (nominal and contingency)

♦ Access for LAS GSE removal in VAB (CxCB 11/20)• Additional VAB platform

♦ RF Testing in VAB – both Orion and Ares I (Pending CR)• Add C&T station, including checkout and troubleshooting equipment• VAB antenna access

Not Comprehensive List - Refer to Part 2 SBU Agenda

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Extra-Vehicular Activity (EVA) System

RemovedBody Seal Closure

Removed HipBearings

Thigh DisconnectRetained formodularity

Two ‘shortie‘ cores

Shoulder bearingretained for mobility

IVA Gloves

Change to soft rearentry design

LEA/Microgravity EVA Suit(Configuration 1)

Since Cx PBS, conducted ‘Architecture Assessment’ that focused on mitigation of occupantprotection and mass/volume issues associated with first EVA System Reference (ESR 1)* –

resulted in ESR 2 (shown below)

* Overall EVA System architecture approach defined new modular, reconfigurable, component-based, lower mass architecture that meets various mission objectives

Lunar Surface EVA Suit(Configuration 2)

Commonhelmet

Commonlower arms

Commonlegs/boots

PLSS (8 Hr EVA)

Enhanced shouldermobility

Rear entry hatch

TMG/MLI for relevantenvironment – incl.boot covers

Waist Bearing

Multi-hip Bearing

EVA Gloves

Key features ofLunar config remainunchanged in ESR 2

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Phase 1 and Phase 2Planning Schedules

November 20, 2007

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CxP Forward Plan - 5 Month Look-ahead (11/19/2007)(CxCB Approved Sep 25, 2007)

CxP

HQ

8/30 CEV SDROrion Project

Re-synch Configuration 10/05

Update Buy Back Analysis 9/20

Ares Project

Integrated AnalysisOrion delivers ALAS-11

Rev 3 FEM 10/1

GO Project

MO ProjectEVA Project EVA SRRs

Complete 8/31

ARES SDRKO 9/10

ARES USSDR KO 9/12

SM/US TIM (MSFC)9/13-14 CLV/CEV/GO TIM (MFSC) 10/2-3

LA-2 (ESM)

Safety Buybacks 9/30

Mission Success Buybacks 10/19

Interim Status CPCB 10/16

CSERP 9/17-20

2007 2008

Integrated Stack TIM11/5-16 CR/D Release 12/13 Integrated Stack

Convergence Review12/19

PMR 08 Development

SEP OCT NOV DEC JAN

11/1 Final CPCB

ODAC 2POD ERB 11/16ODAC-2 ANALYSIS K/O

POD Vehicle Integration 10/31

ARES SDR BD10/30

ARES US10/23 SDR BD

LA-3 ALAS-11

11/28CLV Loads to Orion 2/14

IDAC-4A

• CR/D Approved• PPBE/PMR Guidelines

Recon TIM9/18-21

CEV/EVA TIM 9/19-20

LETF PDR 10/11VAB HB PDR 1/30

MO IRD Drop 1/22

IDAC 4 andADAC 2BKO 11/19

OPS CAP IRDs (4) 10/29

9/15 ATLAS SRR

ADD/CSADD BAR 9/27

Complete 6/9

Complete 5/13

NASA AdministratorStatus Briefing 11/15-16

ORION IRDs (8): 9/27

TRR/MPR 10/4-5

SECB 10/11ARES IRDs (3) 11/4

SECB 10/25

Ground Element SRRsComplete 2/28

1/14

Contract Restructuring11/15

ADAC-2B Complete 8/7

MCCS SRR 11/1Kick-off

Integration andVerification

Orion proposed “from/to” changes

Cost NTE 9/4-24

LA-1

CSADD TIM 10/15-17

CxTF RQMTSSummit 8/21

MCCSPresentation

11/15

MO SRD UpdateComplete 1/31

POD Buyback

IDAC-3

Orion proposed “from/to” vetting 10/1-11/9

ICD TIM GO/ARES 10/25-26

CSERP TIM 10/23-25

CICP Checkpoint 10/26

ORION/MS/DATA Exch. TIM 10/23-25

MPR 10/31

RECON TIM #21/15

Through April

10/1 Level II Document Drop

Ares PNAR 12/13

IS DOC Review 10/16

Req. Allocation & LevelingTIM #1 12/4-10

Req. Allocation & LevelingTIM #2 1/8-14

FSW SRR 10/5

SD

R to

PD

R S

ched

ule

Draft DSIL ConOpsreleased 8/31

DSIL ConnectivityDemo 11/14

DSIL ConOps FinalReleased 12/1

12/17 DSIL Timing &Latency Demo

10/15

RFP Release 10/1EVA/GO I/F TIM 11/28-30

SIP BAR 12/17

CPCB-DRTT FinalApproval for ContractMod 11/29-30

SRD Rev B 12/15

ODAC-2 PODERB 11/16

Updated Doc Dropw/ERRATA 12/6

Through 4/1

LA-2 (ESM)

SRD U/D10/23

SRD U/D11/10

Ares I-XGS PDR11/15

Ares I-X Avionics CDR12/5

Ares I-X CM/LASCDR 12/19

Ares I-X USSCDR .

1/25

Ares I-XFS MDR

1/18

Ares I-XPDR11/28-29

CSERP (J2X)11/26-30

MCCS SRR Board 1/11

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2007 2008Aug Sep Oct Nov Dec Jan Feb Mar Apr May Jun Jul Aug Sep Oct

Integrated Path to PAR (11/8/2007 version)

HQ

CxP

Orion Project

Ares Project

MO Project

EVA Project

GO Project

NASA AdministratorStatus Briefing 11/15-16

PAR9/17

PMR 08 DevelopmentUpdate PM R

PMRSubmit

Integrated Stack TIM 11/5-16

Lunar F2F #212/12 (Concept Downselect)

CxP Risk Review8/19

CR/D Release 12/13

Lunar F2F #32/14 (Tech B/L Freeze)

CxP SDR PBS & LCCR-T 6/17 6/19

-CR/D Approved-PPBE/PMR Guidelines

Integrated Stack Convergence Review 12/19

SCIP SRR2/20

Lunar F2F #44/10 (Analysis Compl)

5/15 SCIP SDROrion PNAR3/3CEV SDR

8/30 Final CPCB11/1

POD BuybackContract Restructuring

12/6 Updated DocDrop w/ERRATA

2/1Propsl Dvlpmt Complete

3/1Negotiations Complete

Signed Contract4/1

Ares PNAR12/13

Ares SDR 9/10 10/30

MCCS SRR 11/1 MO PNAR5/2MO SDR IRD

Drop 1/22MO SRD Update Comp 1/31

MOD SDR 2/5 3/18

EVA SRDUpdate 10/23

EVA PNAR7/15EVA SRD

Update 3/15EVA SDR 4/1 5/13

GS-SRD Rev A PRB/PCB 1/9

GO PNAR6/23GO SDR IRD

Drop 1/22GO Element SRRs 1/14 2/28

GO SDR 3/4 4/22

.

From CxP SRR PBS (5/23/07)

Integrated Path to PAR (11/19/2007 version)

www.nasawatch.com


2007 2008 2009Oct Nov Dec Jan Feb Mar Apr May Jun Jul Aug Sep Oct Nov Dec Jan

Path to PDR-1 (11/8/2007 version)

HQ

CxP

Orion Project

Ares Project

IntegratedAnalysis

MO Project

EVA Project

GO Project

NASA AdministratorStatus Briefing 11/15-16 PMR 08 Development PMR

SubmitPAR9/17 PMR 09 Development

Integrated Stack TIM 11/5-16

Lunar F2F #212/12 (Concept Downselect)

CxP Risk Review8/19

CxP PDR-1 12/15

CR/D Release 12/13

Lunar F2F #32/14 (Tech B/L Freeze)

CxP SDR PBS & LCCR-T 6/17

Integrated Stack Convergence Review 12/19

IS DACCheckpoint 3/7

Lunar F2F #44/10 (Analysis Comp)

LC-T SRR KO 1/13

-CR/D Approved-PPBE/PMR Guidelines

Req Allocation & Leveling TIM #1 12/4-10

Req Allocation &Leveling TIM #21/8-14

Orion Subsys Spec3/15

NAR10/316/30

Subsytem Design Reviews(19 Subsys; 16 Data Books)

8/1 ERB

Orion PDR KO 8/12 9/26 Orion PDR BoardLvl II ICDInitial Draft 1/11

Lvl II ICDDraft Release 8/12

Lvl II ICDDraft B/L CR/D 10/30

US Subsytems PDRsPDR KO 6/24 PDR Board 8/7

2/1 4/30

Dev Engine CDR 3/8NAR9/22

1st Stage PDR KO 4/8 1st Stage PDR BD 6/5US PDR KO 5/15 US PDR BD 6/26

FSW PDR KO 9/4 FSW PDR BD 10/21Lvl II ICDInitial Draft

Lvl II ICDDraft Rel 6/24

Lvl II ICDDraft B/L CR/D 9/4Orion Delivers

ALAS-11Rev 3 FEM 10/1

IDAC-4AIDAC Checkpoint3/7 IDAC-4B

ADAC-2B US DAC-2B complete 5/2 Loads Review10/31LA-3 ALAS LC-4

LA-2 (ESM)

11/16POD ERB

ODAC-2 1/22Arch TradesAssmt Results

CLV Loads to Orion 2/15 2/29

M id-Term ERB

M id-Term Checkptto PDR3/7

4/1POD FEM to Ares

5/8 M odule M ELs Complete

6/9 ODAC-2Checkpoint

6/9 ODAC-2 Analysis Complete

MOD SDR 2/5 3/18 MCCS PDR KO 11/26MCCS PDR1/7Lvl II ICD

Initial DraftContractATP 6/16 6/30 7/11 Veh I/F PDR

EVA SDR 4/1 5/13Under Review

VAB HB3 PDR 1/30 ML PDR 3/19

CCC PDR 4/11

PAD PDR6/2

CEV GSEPDR 8/13

GO PDRKO 10/1

GO PDR11/12

VAB CDR 1/23

PAD B EmergencyEgress PDR 2/19

Lvl II ICDInitial Draft

Lvl II ICDDraft Rel 10/1

Lvl II ICDDraft B/L 12/12

GO SDR 3/4 4/22

.

Integrated Path to PDR-1 PBS (11/19/2007 version)

IS DACCheckpoint 6/9

www.nasawatch.com

2007 2008

CxPCR/D .

Release 12/13

Integrated StackConvergence Review

12/19

PMR 08 developmentPAR 9/17

DEC JAN FEB MAR APR MAY JUN JUL AUG SEP OCT NOV DEC

HQ

PDR KO 8/12

ODAC-2 AnalysisComplete 6/9

607 POD FEMto Ares 3/1

Orion Project

Subsystem Design Reviews(19 Subsystems; 16 Data Books)

J2-X CDRBD 8/29

PDR BD8/7Ares Project

PDR KO6/24

1st stage PDR KO 4/81st stage PDR BD 6/5

US PDR KO 5/15 US PDR BD 6/26

J2-X CDRKO 7/23

Integrated Analysis

LA-3 ALAS LC-4CLV Loads to Orion 2/8 Need Date

9/19

IDAC-4A IDAC-4B

• CR/D Approved• PPBE/PMR Guidelines

CxTF SDR10/1

GO Project

MO Project

EVA Project

MO SDRKO 2/5

MO SDR BD3/18

VAB HB PDR 1/30

ML PDR

MCCS SDRCxTF 7/1

CCC PDR

PAD PDR6/2

CEV GSE PDR8/13

8/16/30

CxRS SDR 11/1

GO IRD Drop (2) 2/19

EVA SDR BD5/13

SDR KO 3/4 SDR BD4/22

PMR Submit

Integration andVerification

SCIP SRR2/20

SCIP SDR5/15

PDR Board9/26

EVA SDR K/O4/1

SWRR 4/23

ADAC-2B 8/7

MCCS SDR4/21

5/20

10/31

MO IRD Drop(2)1/22

MO SRD UpdateComplete 1/31

MORS MCR1/10

Ground Element SRRsStart

1/14

Complete2/28

6/2

MORS SRR 7/15/20

CxTF SDR 8/20

MORS SDR 11/3MORS SDR 9/22

JAN

2009

MCCSS PDR11/26

MCCSS PDR 1/7

RECON TIM#2 1/15

CxP SDR PBS& LCCR-T

IU IBR 5/28

ARES PNAR 12/13

US IBR 6/30

IBR 6/30

CxP PDR-1

GO PDR 11/12

LC SRR-T K/O 1/13

Orion PNAR 3/3

CAIL PDR 5/16

MO PNAR5/2

EVA PNAR 7/15

GO PNAR 6/23

Lunar F2F #2(ConceptsDownselect)

12/12

SIP BAR 12/17

SIP SECB

Lunar F2F #3(Tech B/L Freeze)

SARD Draft #1

IRD App.E Joint Verif. Comp.

SARD Draft #2

SIP CR Release

Lunar F2F #4 (Analysis Comp.)4/10

2/14

3/3

2/28 3/28

2/4

ISS SIP BAR

SIP SECB/ISS SIP4/24

CR Release

Joint Verif. BEA Comp.6/2

6/17-19

ISS SIP SECB6/24

L2 TVRs

12/15

12/1

Thru 2/5

Req. Allocating and

Leveling TIM #1

12/4-10Req. Allocating & Leveling TIM #2

18-14

1st Stage PD-TIMs Comp.3/11

Dev. Engine CDR 3/8

US Subsystem PDRs 4/302/1 FSW PDR K/O 9/4FSW PDR Board

10/21

PAD B Emergency

2/19 Egress PDR 3/19 4/11

LETF CDR 10/24

CCC CDR 12/15

SD

R to

PD

R S

ched

ule

US DAC 2B complete5/2

12/17 DSIL Timing &

Latency DemoDSIL ConOps

Final Rel.

12/1

DSIL SCAN Emulator Integ. Demo3/24

ML CDR7/15 PAD B VAB

Turnover

10/1

DSIL CA/IU Build2 Integ. Demo9/29

VAB CDR 1/23

DSIL EDL & SDILInteg. Demo

12/19

2/45/14

VEH I/F PDR6/30 7/11

Contract ATP 6/16

ODAC 2

Updated Doc Dropw/ERRATA

12/6Contract Restructuring

Proposal DevelopmentComplete 2/1

NegotiationsComplete 3/1

Signed Contract 4/1

ERBSRD Rev B 12/15

Arch. TradesAssessment 1/22

DRDs Due 8/12

IDAC Checkpoint3/7

LoadsReview 10/31

SRD U/D12/10

Integrated CxP Forward Plan (11/8/2007)

IDAC Checkpoint 3/7

Ares I-XAvionics/GS .

CDR 12/4-5

Ares I-X

CM/LAS CDR12/19

Ares I-X

FS MDR1/18

Ares I-X USS CDR1/25

Ares I-X CDR2/4

CxP Risk Review

8/1-2

Ares 1-X Element Delivery to GO for Processing Thru 2/158/8

RSRM &Nozzle

10/22

CM/LAS

12/2

USS

12/15

AftSkirt

1/30

Fwd Assy& 5th Seg

www.nasawatch.com


Phase 1 SDR to PDR Challenges

♦ Phase 1 Challenges• Significant number of

major Program/Project reviews• From April 08 through September 08:

− Program Level• SDR PBS• Phase 2 MCR• PAR

− Project Level• 3 SDRs• 3 PDRs• 3 PNARs

− Element Level• 2 SRRs• 2 SDRs• 6 PDRs• 2 CDRs

♦ Phase 1 Right-to-Left Challenges• Traditional DDT&E Timelines show 16

months between PDR and CDR is themost aggressive to schedule to

• Ares I based on changes - ~18 mos• Orion based on changes - ~12 mos• Program

− CxP PDR 1 to CxP CDR - ~23 mos− CxP PDR 2 to CxP CDR - ~13 mos

− Orion appears overly aggressive andProgram CDR seems to allowmovement now or downstream ifrequired (assessment based only onCDR timing and is not assessed toManifest needs)

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Lunar Capability Phase 2

♦Phase 2 Schedule Quick-Assessment• Assess the current milestones and activities for Phase 2 (Lunar

Capability Transportation)• Identify conflicts with the IC schedules and resource constraints• Identify options to deconflict issues

♦The Challenge• Reconcile Phase 2 resource constraints with the ability to affect the

Phase 1 architecture to effectively and efficiently support Phase 2 and3− Phase 2 Program MCR and SRR is not separated too far from Lander and

Ares V SRRs to be irrelevant− Phase 2 Program MCR and SRR is not separated too far from Phase 1

Project milestones to be ineffective in affecting Phase 1 designs− Balance Program and Project resources for Phase 1 and 2 activities

www.nasawatch.com


Integrated CxP Forward Plan (11/19/2007)C

urre

nt “P

hase

2” M

ilest

ones

: 200

7 –

2013

Gap between Program SRR andProject SRRs too big

www.nasawatch.com


Proposed Schedule Update

♦ Ph2 LCCR (MCR) in June 2008 (per plan)• Review EARD, NGOs, Ops Con*, ADD*

− Ops Con and ADD updates to be released on CR subsequently

♦ Ph2 ICPR in January 2009 (per plan, with following scope)• Review and comment on key Technical Baseline Documents (Ops Con, ADD, CARD, SRDs)

− Only those books with key driving requirements (KDRs)− Ares V and Lander Technical Baseline Documents are in draft form− Does NOT include review of process documents or D&C specifications

• Only exceptions are those D&C specs that need to be updated for lunar environments and constraints, such as the DSNE

• Products to meet Lander and Ares V MCR Criteria− Project MCRs can be rolled into ICPR as the criteria will clearly be met by then (Mission Need,

Workable concept, Ops Con…)♦ Ph2 CxP SRR in June 2010 (prior to Ph1 CDR)

• Full SRR review for lunar transportation architecture− All Technical Baseline Documents are RIDable− Roll Lunar Surface products into this review (as appropriate to glue architecture together)

♦ Conduct Project Ph2 SRRs in 2011• Ares V, Lander, LSS elements (as required)

♦ Cx SRR PBS in March 2012• Orion/EVA/MO/GO to complete update of the Ph2 technical baseline documentation prior to this event

♦ Post SRR Scheduling Assumptions• 8-9 months between SRR & SDRs• 1 yr between SDR & PDR• 18 months between PDR & CDR• 2 yrs between CDR & SAR• 18 months between SAR & 1st flight• EVA Ph2 milestones from the current IMS are unchanged

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Pro

pose

d “P

hase

2” M

ilest

ones

: 200

7 –

2013


NET 1Q ‘121Q ‘08Ph3 LCCR

3Q ‘111Q ’12Lander

2Q ‘113Q ’11Ares V

ToFromChangeHighlights

www.nasawatch.com


Pro

pose

d “P

hase

2” M

ilest

one:

200

8 –

2022


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4 consecutive Ares V attempts

7 consecutive Ares I tankings

6 Days

= scrubbed Ares V Attempt

= Launched Ares V

= tanked/scrubbed Ares I due to Ares V launch scrub

Legend• Ares I must tank for eachattempt of the Ares V plus foreach of its own attempts after asuccessful Ares V launch leadingto a potential for 7 consecutivetankings of the Ares I before themissed TLI window

TLI 1

Consecutive Launch Attempts

TLI 2

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Orion SM Delta-V & Propellant Load Sizing RecommendationsPresented for Feedback at HQs Brief 11/16 - Well Received

♦ Recommendation strikes a balance between mission design capabilitiesand Spacecraft mass constraints

♦ Current nominal delta-V is 1,492 m/s (equivalent prop. load 7,904 kg, 17426lb) and provides for the following mission capabilities at worst time andlongitude:• Polar sortie to 4 degree for nominal return to CONUS or CA coast within ~17 days• Polar sortie to 2 degree with expedited (emergency) return within in-suit (120 hr) and

total time from surface to TD (130 hr) timeline requirements• Global sortie with 100% temporal and 100% surface coverage (with loiter) with return to

CONUS or CA coast within 21.1 days• Global sortie with expedited return from worst case locations ~4-6 hours beyond in-suit

and total time from surface to TD timelines♦ Recommend sizing for additional 68 m/s (590 kg, 1300 lb) as Program Mgr

reserve which adds:• Polar sortie nominal and expedited return timelines shortened by ~20 hr or extends

latitude access to 4 degree latitude for expedited returns• Global sortie with expedited return from worst case locations within in-suit and total

time from surface to TD timelines• Capability to add dry mass/margin (~250 kg) to CM while meeting timeline

requirements♦ Mission design will also need to consider Lander performance, which may

also restrict the timing and band of viable latitudes.

www.nasawatch.com


Ares I 3σ Performance Parameters: 1,539 (698kg)

Ares I Mass Delivered Req. (Proposed, Unchng): 44,780 (20,312 kg)

Orion Control Mass (Proposed, Unchng) : 42,540 (19,296 kg)

Ares I Mean Gross Mass Delivered Capability 51,127 lbm (23,191 kg)

Mas

s D

eliv

ered

lbm

(kg)

Orion Target 606-C Mass (w/MGA) : 36,250 (16,440 kg)

Ares I Launch Window Allocation: 1000 (454 kg)

Ares I PM Reserve: 3,808 (1,727 kg)

Ares I Net Mass Delivered: 48,588 (22,039 kg)

ISS Capabilities and ReservesProposed New CARD

♦ Includes corrections for liens including ALAS-11 OML loads impact. Doesnot include Ares extended nozzle. No other threats/opportunities

Cx Pg Mgr’s Reserve: 2,240 (1,016 kg)

Total MR for Ares: 6,048 (2,743 kg) Total MR for Orion: 6,290* (2853 kg)

Orion PM Mgr’s Reserve:6290* (2853 kg)

* Operational limit of Orion 606-C for abort is less thancontrol mass and represents actual limit for Orion design

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Ares I 3σ Perf. Parameters: 1,585 (719 kg)

Ares I Mass Delivered Req. (Proposed CARD): 51,290 (23,265 kg)

Orion Control Mass (Proposed CARD) : 48,231* (21,877 kg)

Ares I Mean Gross Mass Delivered Capability: 56,200 lbm (25,492 kg)

Mas

s D

eliv

ered

lbm

(kg)

Orion Target 607 Mass (predicted) : 46,263 (20,084 kg)

Ares I Launch Window Allocation: 500 (227 kg)

Ares I Net Mass Delivered: 54,115 (24,546 kg)

Lunar Capabilities and ReservesProposed New CARD

Cx Pg Mgr’s Reserve:3,059 (1388 kg)

Orion PM MR: 1968 (893 kg)

Ares I PM MR: 2,825 (1281 kg)

Total MR for Ares: 4,884 (2,215 kg)Total MR for Orion: 1,968 (893 kg)

*Includes land landing scar and injection errormake-up

♦ Summary shows proposed CARD-based requirements (to be approvedby SECB) with corrections for major liens and threats and opportunities.

www.nasawatch.com


FwdEnd ofIU

AftEnd ofIUStabilization

Damping Key Criteria for Locations• Satisfy Lateral Motion

Requirements• CLV Structural Stability

With Minimal MassIncrease

• MLP Real Estate ForStay & Damper w/ MinInterference w/ CLVSystems

• Clearance If T-0 System• ML Tower Interface

EitherLocatio

n OK

Best Choice• Structural

“hardpoint”

• No sepjoint

• Natural“T-0”clearance

• No TPS

Tie down

Ares Trade Study Overview with GO and E&CSIG/ILSM/GMO SIG support

www.nasawatch.com


With Mid-Stay Still Attached& Damper Released, WIOLock-In to 90% of SteadyState Occurs in Less Than 1Min For 1st Mode

With Mid-Stay & DamperReleased, WIO Lock-In to 90%of Steady State Occurs in LessThan 40 Sec For 2nd Mode

Wind Induced Oscillation (WIO) Lock In

Release At T-0 Avoids Recapture Issues Due To WIO.Requires Design & Extensive Testing Of Highly Reliable, Fast Acting Arm.

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