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Project Management Challenge 2010 A I X R ll C t lS t D l t Project Management Challenge 2010 A I X R ll C t lS t D l t Ares I-X Roll Control System Development Ares I-X Roll Control System Development Ron Unger/NASA Marshall Space Flight Center Ed Massey/Teledyne Brown Engineering Ron Unger/NASA Marshall Space Flight Center Ed Massey/Teledyne Brown Engineering Ed Massey/Teledyne Brown Engineering February 2010 Ed Massey/Teledyne Brown Engineering February 2010 www.nasa.gov

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Project Management Challenge 2010A I X R ll C t l S t D l tProject Management Challenge 2010A I X R ll C t l S t D l tAres I-X Roll Control System DevelopmentAres I-X Roll Control System Development

Ron Unger/NASA Marshall Space Flight CenterEd Massey/Teledyne Brown EngineeringRon Unger/NASA Marshall Space Flight CenterEd Massey/Teledyne Brown EngineeringEd Massey/Teledyne Brown Engineering

February 2010

Ed Massey/Teledyne Brown Engineering

February 2010

www.nasa.gov

jposton
Text Box
Used with permission
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Ares I-X Roll Control System Project Management Model

The Ares I-X Roll Control System (RoCS) represents a successful project management model of a rapid-development, functionally complex, flight hardware system. The Integrated Product Team (IPT) d l t d t th R CS l l t ith th(IPT) model was executed at the RoCS level concurrent with the other Ares I-X IPTs to support the successful Ares I-X launch on October 28, 2009.

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Ares I-X Roll Control System Overview

Description – Roll Control System provides

rotational azimuth control for: mitigation against adverse

vehicle roll torques (self-and aero-induced).

antenna and simulated crew launch positioning.

Salient Features– The Roll Control System is an

integral modular bi-propellantintegral, modular, bi propellant propulsion system installed in the Ares I-X Upper Stage Simulator Interstage.

– RoCS utilized off-the-shelf and Government-furnished components that have been harvested from USAF

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harvested from USAFPeacekeeper Stage IV, then re-integrated into a system.

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The Challenge

Deliver the requisite Roll Control System to Ares I-X: on time … support April 15, 2009 (original) launch date

within budget $24 7M budget guideline within budget … $24.7M budget guideline

and of high quality.

How we did: RoCS modules delivered to KSC on February 5, 2009, were fully integrated

i U S b A il 26 2009 ( ll ff h i i i i l h)into Upper Stage by April 26, 2009 (well off the integration critical path).

Current cost – over guideline by 3%, attributable to launch date changes requiring standing team.

Flight hardware accepted by Ares I-X May 27, 2009. All waivers and verifications closed by July 14, 2009. Noticeably low number of KSC problem reports were generated for a first article prototype system.

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Major Keys to Success

Description Stakeholder Value

Establish small, “badgeless,” accountable team between contractor and NASA, while maintaining compliance with governance model/Independent Technical Authorities

Efficient decision-making.

governance model/Independent Technical Authorities.

Development of early Memorandum of Understanding and Agreement with USAF and Task Agreement with White Sands Test Facility.

Clear lines of responsibilities.

y

Designing for robustness, anticipating upward movement of loads levels.

Structural problems averted over a series of changing loads.

Early identification and development of waivers Waiver acceptance justification builtEarly identification and development of waivers. Waiver acceptance justification built into test and analysis plans.

Front end load the schedule with design and testing activities, waiver submittal, and verification closures.

Avoid bow wave of activities and related resources availability issues.

Co-location of MSFC Engineering Lead System Engineer to Teledyne Brown facility.

Rapid issue definition and resolution planning.

Maintain cognizance of the end game. Primary and urgent issues resolved

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first. Secondary issues pushed down to lower levels.

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Ares I-X Roll Control System Organization

Roll Control System IPT

PK AXE Test & Stage PK Propellant Tanks

Ron UngerNASA MSFC

IPT LeadComponent Salvaging

PK Propellant Tanks

Schedules

NASA / WSTF and Hill AFB USAF / Davis Monthan AFB

Pyrotechnics Procurement

Resource Office

NASA/MSFC David Chafee

Karen Russell/Teledyne Brown

Data Management

Mike Staton/COLSA

NASA/GRC

System Design & Hardware Integration

Systems Engineering& Integration

Design Insight GroundOperations

Safety & Mission

Assurance

Lead Engineer Integration & Integration

Dave Tomasic

Melinda Delacruz

Assurance

Patton Downey

Jennifer SpurgeonEd Massey

Teledyne Brown Engineering

MSFC EngineeringResources

TechnicalSupport

Contractors

Test, Design & Salvage Support

Pratt & Whitney/Rocketdyne

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Peacekeeper Hardware Acquisition

Hill AFB Peacekeeper Stage IV

NASA/MSFCMOUA to utilize PK hardwareDavis-Monthan AFB

PK Prop TanksTask Agreement to

NASA/WSTF Decommisioning PK

Unused Hardware to Scrap

Task Agreement to “harvest” PK hardware

Decommisioning PK

Teledyne Brown Eng

to Scrap

Each RoCS Module utilized from PK:

Teledyne Brown Eng

The RoCS Team ended up with enough hardware for:

Two Propellant Tanks Pressurization Subsystem Two PK Axial Engines Two Propellant Filters

g Three Flight Modules Ground Test Cold Flow Module Hot-Fire Engine Tests Dynamic Tests Two Propellant Filters

Four Pressurant Check Valves Pyrovalve Ordnance

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Dynamic Tests Plus Odds and Ends Spares > $10M Cost Avoidance

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Peacekeeper Hardware Acquisition

Axial Engine

Propellant Tank Pressurization Subsystem

g

Propellant Filter

Check

PyrovalveOrdnance

Check Valve

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Design for Robustness and Growth

Robustness Implementation of two independent RoCS modules provided system redundancy. Ares

I-X could complete its mission with reduced roll control capability using one module.

In-line mounting configuration minimized opening in Interstage sidewall and provided rugged platform to support components in the axial direction.

Single regulator with high quality performance selected as most reliable option.g g g y

Multiple temperature sensors provided back-up for Launch Commit Criteria in case of sensor failures.

Positive monitoring of Helium tank pressure switch sensor provided immediatePositive monitoring of Helium tank pressure switch sensor provided immediate indication of system leak well before launch.

Redundant pyrotechnic trains provided system reliability for initiation. Pyrotechnic activation of modules shown to be simple and reliable.

Offline fueling of modules reduced impacts to vehicle integration schedule.

Spare RoCS module available as line replaceable unit in case of module failure during integration flow.

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g

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Design for Robustness and Growth

Growth Separate pressurant and propellant systems provided approximately double the

required resources for accomplishing mission profile.

Peacekeeper engines provided capability for growth in thrust requirements.

Module structure was intentionally over-designed to address changing loads.

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Early Identification of Waivers

C i t f R CS C iti l D i R i (CDR) i i Coming out of RoCS Critical Design Review (CDR), six waiver situations were identified for Peacekeeper hardware, either against NASA standards or Ares I-X requirements. No Vibro-Acoustics Acceptance Testing Planned for Flight Components or Assemblies No Vibro-Acoustics Acceptance Testing Planned for Flight Components or Assemblies Pressure Testing Levels on the Propellant Filter Assemblies Heritage Pyro Component Quantities not Available to Meet Lot Acceptance Requirements No Vibro-Acoustics Qualification Testing Planned for Propellant Tanks No Vibro-Acoustics Qualification Testing Planned for Pyro Valves and Ordnance No Vibro-Acoustics Qualification Testing Planned for Pyro Valves and Ordnance Pressure Testing Levels on the Engine Bi-Prop Valve

Drafting of waivers, including Engineering rationale for acceptance g , g g g pand the residual risks, began in July 2008. First three were approved at Ares I-X Control Board September 2008. Second three came later in verification process as loads matured and test results became

availableavailable.

Early identification and draft development allowed RoCS to start “talking up” the waivers within the Ares I-X community, so that whentalking up the waivers within the Ares I X community, so that when final product was presented, everyone was on board.

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Front-End Loaded Schedule

Dry run procedures with real hardware or physical facsimiles to work hardware form, fit, function, and procedural bugs out early, well in advance of handling the flight hardware.

Pressurant and propellant tank filling (with helium and water,

respectively) at KSC’s

Module installation and translation exercise using

installation tables Interstage lip

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respectively) at KSC s Hypergolic Maintenance Facility

installation tables, Interstage lip mock-up, and RoCS mass

simulator, with KSC personnel

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Front-End Loaded Schedule

W k ll l th b d t ll t i t i f ll b k ti Work parallel paths, as budget allows, to maintain fall-back options. Use past precedents from prior contracts as models for

documentation – modification of an existing document rather than generating a new template and/or authoring from scratch. As such, Teledyne was able to have many of the motherhood documents (Safety Plan,

Quality Plan, Configuration Management Plan, etc., put behind us before new technical requirements even showed up )requirements even showed up.)

Engineering Development Unit (one of four units built and intended for eventual cold flow testing) validated hardware process development and assembly fit checks before committing to finaldevelopment and assembly fit checks before committing to final fabrication and assembly of flight units (two, plus one flight spare).

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Front-End Loaded Schedule

0

Apr‐08

May‐08

Jun‐08

Jul‐0

8

Aug

‐08

Sep‐08

Oct‐08

Nov

‐08

Dec

‐08

Jan‐09

Feb‐09

Mar‐09

Apr‐09

May‐09

Jun‐09

Jul‐0

9

Aug

‐09

Sep‐09

10

20

30

40

50mpl

ete

50

60

70

% C

om

80

90

EIS Closures

ERD Closures

SEI/XCB Closures

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Waiver Approvals

PSR AR1 AR2PSR AR1 AR2

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Co-location of MSFC Lead System Engineer to Teledyne Brown Facility

Greatly facilitated communications between NASA and the Contractor Team.

Immediate customer interface for the resolution of issues found Immediate customer interface for the resolution of issues found during the design, fabrication, assembly, and test flow.

Provided on-site support for interfacing with other IPTs for resolution of interface issues.

Provided direct customer interface to report status and progress.

Provided immediate direction to keep project on schedule.

Provided for expedited verification closure processing.

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Maintain Cognizance of the End Game

This flight was designated as an unmanned test flight A mindset This flight was designated as an unmanned, test flight. A mindset shift from Shuttle was in order.

The original plan to deliver the modules before the end of 2008 ld h t d th i i l A il 15 2009 l h d t dwould have supported the original April 15, 2009 launch date, and

was holding through the fall of 2008. Delivery of fairing aero buffet loads and changing vibro-acoustic

environments in December 2008 delayed completion of component testing.

Teledyne-provided field modifications to fairings were implemented y p g pat KSC in parallel with off-line propellant/pressurant loading of the modules, minimizing impacts to integration schedule.

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Maintain Cognizance of End Game

Work “good eno gh” options no need to ork optimi ation for a Work “good enough” options, no need to work optimization for a single test flight● Better is the enemy of good enough.

•Module installation was cartooned out in an hour by:

•RoCS IPT Lead (MSFC)•RoCS IPT Lead (MSFC)• Interstage Lead (GRC)•Ground Ops Rep (KSC)•Mechanical Designer (Teledyne)

•Ground Support Equipment “ownership” was maintained by Teledyne

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The End Result

Final RoCS Module Shipment

February 5 2009February 5, 2009

Final Integration into InterstageApril 26, 2009

Final Acceptance Review

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May 27, 2009

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Looking Forward

Fuel

0 psig0 psig

79 F

79 F 79 F

79 F

Fuel

190 psig

100 F100 F

190 psig

B1 2

A1 2

He He

15 psia 15 psia290 psia290 psia

OFFOFF B1 2

A1 2 psia15 psia 15 psia

15 psia15 psia

79 F 79 F

290 psia290 psia

290 psia290 psia

OxidizerOxidizer

0 psig 0 psig

79 F

79 F 79 F

79 F

190 psig

100 F 100 F

190 psig

ST

Launch – October 28, 2009RoCS Performance - Notional

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Summary

Establish roles and responsibilities Maintain independence of government Technical Authorities (S&MA and

Engineering) per NASA governance model

Keep team small and focused A small team of cross-trained individuals with the necessary core

competencies can make decisions quickly and execute plans efficiently

Use proven Systems Engineering processes Start early, keep the End Game in mind Design conservatively wherever possible Design conservatively, wherever possible Develop

Multiple open communications channels while respecting protocol Ownership Ownership Trust Friendship

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Question and Answer Session

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