Nasa Ares I & V Launch Vehicle - July 2009 Status Report

National Aeronautics and Space Administration

Constellation Launch Vehicles Overview Part 1

July 29, 2009 www.nasa.gov

Current Development for Future Exploration Capabilities Deep Space Robotics

Asteroids and Near-Earth Objects

Commercial and Civil Low Earth Orbit (LEO)

Mars Surface, Phobos, Deimos

International Space Station and Other LEO Destinations/Servicing Lunar Orbit, Lunar Surface (Global)

National Aeronautics and Space Administration

7764.2

Part 1 Agenda Ares Overview • Ares Family

• Legacy Launch Systems • Ares I/V Commonality • Benefits of the Ares Approach • Top-level Breakout of the Ares I Vehicle • State-by-state National Team • Ares I Schedule • Earned Value Management • Quality, Safety, Teamwork

The Ares I Safety Story Ares I Element Overviews National Aeronautics and Space Administration

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National Aeronautics and Space Administration

Ares Launch Vehicles

www.nasa.gov

Ares Family of Launch Vehicles

Shuttle-derived launch vehicle family for LEO and beyond missions Common boosters, upper stage engines, manufacturing, subsystem technologies, and ground facilities Investment in Ares I (~one year post-Preliminary Design Review (PDR)) for Initial Capability reduces funding required and risk on Ares V (postMission Concept Review (MCR)) for lunar capability National Aeronautics and Space Administration

7764.5

Building on 50 Years of Proven Experience – Launch Vehicle Comparisons – 400 ft

Overall Vehicle Height

Crew 300 ft

200 ft

Altair

Lunar Lander S-IVB (One J-2 Liquid Oxygen/Liquid Hydrogen (LOX/LH2) engine) S-II (Five J-2 LOX/ LH2 engines)

100 ft

S-IC (Five F-1 LOX/ RP-1 engines)

Orion

Earth Departure Stage (1 J-2X LOX/LH2 engine)

Upper Stage (One J-2X LOX/LH2 engine)

Two 4-Segment Reusable Solid Rocket Boosters (RSRBs)

Core Stage (Six RS-68 LOX/LH2 engines)

One 5-Segment RSRB Two 5.5-Segment RSRBs

0

Height Gross Liftoff Mass (GLOM)

Payload Capability

Saturn V: 1967–1972

Space Shuttle: 1981–Present

Ares I: First Flight 2015

Ares V: First Flight 2018

360.0 ft

184.2 ft

325.0 ft

381.1 ft

6,500.0K lbm

4,500.0K lbm

2,057.3K lbm

8,167.1K lbm

24.9 mT to LEO

71.1 mT to TLI with Ares I 62.8 mT to TLI ~161.0 mT to LEO

44.9 mT Trans-Lunar Injection (TLI) 118.8 mT to LEO

25.0 mT to LEO

DAC 2 TR7 LV 51.00.48 National Aeronautics and Space Administration

7764.6

Why Ares I for Crew Launch

“Top-down” design indicates high Ares I+V design synergy possible

“Bottoms-up” design indicates expectation of a highly reliable/safe vehicle

Serves as risk-reduction for exploration

National Aeronautics and Space Administration

♦ Same J-2X upper stage engine ♦ Significant Solid Rocket Motor commonality ♦ MAF production capacity ♦ Minimize unique elements – lower lifecycle cost ♦ Heritage from Shuttle RSRM combined with continued post-flight recovery and inspection ♦ Heritage from Saturn J-2 human-rated upper-stage engine ♦ Probabilistic risk assessment indicates at least twice as safe as any other assessed approach ♦ Provides test of Orion on cost effective vehicle • Crew ascent • Long duration in-space tests ♦ Stepping stone to largest rocket ever developed • First new human launch system in 3 decades • Shuttle transition / industrial base ♦ First Stage and J-2X performance, flight behavior ♦ Dependable U.S. human access to space 7764.7

Why Ares V for Cargo Launch

Ares V-class launcher is a “gamechanger” in expanding U.S. capabilities in space science and human space exploration

The U.S. is in a unique position to develop and operate such a system

♦ 7x lift capacity, much larger payload volume compared to any existing system • Many launches of existing vehicles prohibitive from a mission risk posture ♦ Ares V is enabling for diverse advanced missions • Human Moon, Mars, asteroid missions* • Large aperture space telescopes in remote orbits* • “Flagship” outer planet missions*

♦ Legacy production capability from Saturn, Shuttle, Delta IV programs • MAF, RS-68 main engines, Solid Rocket Motors, J-2 upper stage engine ♦ Legacy launch infrastructure from Saturn, Shuttle programs • Vehicle Assembly Building, pads, crawlers, mobile launch platforms, etc.

♦ If this national capability is lost, it may never be recovered *National Research Council, “Launching Science: Science Opportunities Provided by NASA‟s Constellation System”, 2008 National Aeronautics and Space Administration

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Ares Architecture Enables Architectures Under Evaluation A B C

Lunar base (Constellation light) D Lunar global E Moons to Mars (DRM-5)

Mars First (Mars light) Flexible Destinations

Note: TLI to LEO scale comparison is approximate

Mars Launch Assembly (Single Launch Eq ~750t-1250t+)

E

C

Mars Moons

D

Increasing Distance from Earth

Near Earth Objects (~2020) A B Lunar Surface (2 Launches Req‟d for Crew)

Lagrange Only

Saturn V

Ares I 0 0

Ares I & V

E

Circum Lunar

10

20 50

30

40 100

50 150

60

70 200

80

90 250

100

TLI - t

300 LEO equiv - t

Single Launch Equivalent Gross Capability National Aeronautics and Space Administration

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National Aeronautics and Space Administration

Overview of Ares I Launch Vehicle

www.nasa.gov

Ares I Acquisition Model

Instrument Unit NASA Design/ Boeing Production ($0.83B)

Orion Crew Exploration Vehicle Upper Stage NASA Design/Boeing Production ($1.16B)

Upper Stage Engine Pratt and Whitney Rocketdyne ($1.28B)

First Stage ATK Launch Systems ($1.98B)

Overall Integration NASA-led Multi-generational program Lessons learned from DoD: robust internal systems engineering, tightly managed requirements NASA becomes “smart buyer” downstream Marries best of NASA and industry skills DAC 2 TR 7 National Aeronautics and Space Administration

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4,000 Ares Team Members Nationwide 324 Organizations in 38 States ATK Space Systems Glenn Research Center

NASA HQ JPL Marshall Space Flight Center

Langley Research Center

Pratt & Whitney Rocketdyne

Ames Research Center

National Aeronautics and Space Administration

Johnson Space Center

Michoud Assembly Facility

Boeing

Kennedy Space Center Stennis Space Center

7645.12

Ares I Schedule

To date, the Ares I project has completed a total of 204 design reviews, ranging from components up through subsystems, elements, and the integrated Ares launch vehicle. National Aeronautics and Space Administration

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Earning Value – Rigorous Implementation of EVM

Vehicle Integration

First Stage

Upper Stage

Upper Stage Engine

Cost Variance

–4.2%

0.2%

–1.4%

2.0%

Schedule Variance

–7.7%;

0.0%

–4.7%

-1.7%

CPI Cum

0.96

1.00

0.99

0.98

SPI Cum

0.92

1.00

0.95

1.00

Project has implemented a practice of Earned Value Management (EVM) to monitor deviations from cost and schedule baselines early enough to make corrections Awarded the NASA EVM Award of Excellence in June 2009 for the progress made in implementing earned value on a Governmentmanaged project

National Aeronautics and Space Administration

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Ensuring Quality, Safety, and Teamwork Ares Projects Team Norms HAVE FUN Once in a career opportunity! We are running a marathon, not a sprint – not in 24/7 emergency mode all the time.

RESPECT OUR FAMILIES AND OURSELVES – HEALTHY BALANCE BETWEEN WORK AND FAMILY IS ESSENTIAL INTEGRITY IS EXPECTED Look each other straight in the eye, tell the truth, full disclosure. TEAMWORK IS ESSENTIAL „Our‟ instead of „my‟. „We‟ instead of „I‟. „Us‟ rather than „me‟… ‟we‟re all important‟ INTEGRATION AMONG THE PROJECT AND WITH PARTNER ORGANIZATIONS (E.G., ENGINEERING, S&MA, OTHER CENTERS, PROGRAM/PROJECTS) IS ESSENTIAL Communicate, communicate, communicate with each other. Don‟t wait on someone else to initiate BELIEVE THE BEST ABOUT EACH OTHER (ASSUME NO MALICIOUS INTENT) CONSTRUCTIVE CONFLICT LEADING TO DECISIONS (CLOSURE) AND ONCE MADE DON‟T CARRY IT PERSONALLY IF IT DID NOT GO YOUR WAY WE WILL HOLD EACH OTHER ACCOUNTABLE AND MEET OUR COMMITMENTS Our ultimate commitment is a safe, reliable, affordable delivery of Orion to orbit FAILURE IS ACCEPTABLE DURING DEVELOPMENT We are willing to take calculated risks to further our knowledge EARLY IDENTIFICATION AND HIGHLIGHT OF ISSUES

National Aeronautics and Space Administration

People Integration • Walking the talk – leaders modeling/ living values • Encouraging openness and diversity of people, ideas • Communicate, communicate, communicate! • Measuring management performance • Motivation through a simple, straightforward mission: “go build the rocket”

Leadership Challenges • Retooling “overseers” into “producers” • Ensuring a sense of “confident humility” • Instilling ownership and accountability • Managing workload • Integration among Ares elements and other Constellation projects • Getting every team member to think as a “systems engineer” • Focus on lean thinking

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National Aeronautics and Space Administration

The Path to a Safer Crew Launch Vehicle: The Ares I Story

www.nasa.gov

Premise of New CLV Design

“The design of the system [that replaces the current Space Shuttle] should give overriding priority

to crew safety, rather than trade safety against other performance criteria, such as low cost and reusability, or against advanced space operation capabilities other than crew transfer.” Columbia Accident Investigation Team Report, Section 9.3, page 211

“The Astronaut Office recommends that the next human-rated launch system add abort or

escape systems to a booster with ascent reliability at least as high as the Space Shuttle‟s, yielding a predicted probability of 0.999 or better for crew survival [1 in 1000 LOC] during ascent. The system should be designed to achieve or exceed its reliability requirement with 95% confidence*.” “Astronaut Office Position on Future Launch System Safety”, Memo from CB Chief, Astronaut Office to CA Director, Flight Crew Operations, May 4, 2004 *Interpreted to mean 95% certainty

National Aeronautics and Space Administration

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Historical context Architectural trades, in quest of a safer launcher, date back to Challenger before ESAS

♦ The progression of safety driven analyses, since Challenger, led to the development of the “single stick” booster concept, and the combination of heritage-reliability, performance and cost mandated the solid booster option from ESAS National Aeronautics and Space Administration

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Premise Establishing crew safety goals - the value of an escape system .95

.97 .98

.987 .99

.995

® ® ® ®

1 in 100,000

Soyuz

Current ELV Performance

Ariane Saturn Delta Atlas

Crew Safety per Launch

1 in 1,000,000

®

1 in 10,000 .95 .9 1 in 1,000

Apollo Forecast

Target from crew memo

1 in 100

.8 .7

Shuttle with 80% escape

.95

Shuttle with 50% escape

.9

Shuttle with current escape

.8 .7 1 in 10 1 in 1

Crew Escape Reliability

1 in 10

1 in 20

1 in 33

1 in 100

1 in 200

1 in 1,000

1 in 10,000

Failure Frequency per Launch National Aeronautics and Space Administration

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Ares I Risk-Informed Design Continuing analyses and modeling using flight data for application to future flights and missions

(Exploration Systems Architecture Study)

ESAS Heritage-based analysis of design potential (System Requirements Review)

SRR Physics of failure sensitivities and understanding of major risk drivers (System Definition Review)

SDR Design specific scenarios with bounding physical modeling

DCR/Flight (Preliminary Design Review)

PDR

(Design Certification Review)

Focused analysis with detailed design data (Critical Design Review)

From: Ares CSR National Aeronautics and Space Administration

CDR 7764.20

First Order Look at Configurations Shuttle Derived Side Mount (SSME)

Shuttle

Hold-down & Separation Strap-Ons Upper Stage & Engine

Ares-I ESAS

Ares-I RSRM V

Core Engine & Stage

Add LAS Add Upper Stage

Ares-V Crewed

Adapt SRB

Increasing Performance EELV 3.2* *does not meet performance requirements

EELV 4.1-100%

Add multiple RL10 On Upper Stage Man Rated Certification Program riskThrust Imbalance Loss of Control National Aeronautics and Space Administration

Program riskAero acoustic loads Aerodynamics (length) Aero Start SSME

Program riskNew Engine Thrust Oscillation New Propellant

EELV 4.1-75%

EELV- J-2X

Program riskNew Engine New Propellant Man Rated Certification

Add Engine Out

Program riskVehicle Software impact Engine Out Testing

Program riskNew Engine 7764.21

Failure Environments ♦ Ares CSR detailed „physics of failure‟ models estimate the probability of successful crew escape (abort effectiveness, AE) for each failure environment, each configuration Element PRAs

“Top Down” Orion & LAS Design/Vulner ability

LOC/Abort Effectiveness Calculation

Ares GN&C Goldsim Dynamic Risk Simulation Model (Monte Carlo)

For each trigger set, integrated analysis determines impact to Loss of Crew

From: Ares CSR

Failure Mode Effects Analysis

10 8 6 4 2 0 -20 -4

20 40 60 80 Failure Time

LOM Calculation VI PRA LOC Environments

100 120

Quantification of Scenarios & Branches (Mapping to Scenarios)

Failure Scenario Characteristics (Reliability Data + Trigger Info)

Functional Fault Analysis Element Design Hazard Analysis

Ascent Risk Assessment Cut Sets

Scenario Diagramming (Trigger & Timing Assignment) Timing Abort Conditions & Triggers

Candidate Trigger Set

Common Failure Scenarios & Near-Field Consequences (LOM Environments)

“Bottoms Up”

♦ This study uses results of the detailed model to apply a relative AE factor to each failure environment bin (mildest environment = best abort effectiveness gets 100% factor) National Aeronautics and Space Administration

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Relative Results of an Independent Assessment Relative error bars are smaller than absolute values • Errors on building blocks shared between different configurations • Errors on common assumptions made in the modeling of all stages

Relative error bars confirm the mature Ares I is the safest of all options with high confidence

LOM, LOC Relative Error Bars (compared to Ares I) Ratio of vehicle probability of failure to Ares I‟s probability

LOM LOC

Increase Risk Factor Over Ares I

6 5 4 3 2 1

Ares I Baseline

0 Ares I

Ares V

National Aeronautics and Space Administration

Shuttle C

EELV 3.2*

EELV 4.1 100%

EELV 4.1 75%

EELV J2X

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National Aeronautics and Space Administration

Ares I Elements

www.nasa.gov

Ares I First Stage

Tumble Motors (from Shuttle) C-Spring isolators

Asbestos free insulation/liner

New 150 ft diameter parachutes

Same propellant as Shuttle (PBAN)optimized for Ares application

Modern electronics

Same cases and joints as Shuttle

Same aft skirt and thrust vector control as Shuttle

Booster Deceleration Motors (from Shuttle)

Wide throat nozzle

DAC 2 TR 7 National Aeronautics and Space Administration

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First Stage Accomplishments

Ares I-X Forward Skirt Extension Separation Test Promontory, UT

Ares I-X Motor En Route to KSC Corinne, UT

Main Parachute Drop Test Yuma Proving Ground, AZ

Ares I-X Forward Assembly Transfer to VAB Kennedy Space Center, FL

National Aeronautics and Space Administration

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First Stage Accomplishments

(A)

(B)

Built-up Thrust Vector Control/Discrete Interface Module Cincinnati, OH

Thrust Oscillation Flexure Design (A) and Testing (B) San Luis Obispo, CA

DM-1 Igniter Test Promontory, UT

DM-1 Installation into Test Stand Promontory, UT

National Aeronautics and Space Administration

7764.28

First Stage Accomplishments

DM-1 in T-97 Test Stand Promontory, UT National Aeronautics and Space Administration

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National Aeronautics and Space Administration

Ares I Elements

www.nasa.gov

Ares I Upper Stage

Propellant Load: 308K lbm Total Mass: 355K lbm Dry Mass: 36K lbm Dry Mass (Interstage): 10K lbm Length: 84 ft Diameter: 18 ft LOX Tank Pressure: 50 psig LH2 Tank Pressure: 42 psig

Instrument Unit (Modern Electronics) Helium Pressurization Bottles

LH2 Tank

AI-Li Orthogrid Tank Structure

LOX Tank

Feed Systems Ullage Settling Motors Common Bulkhead

Composite Interstage

DAC 2 TR 7

Roll Control System

National Aeronautics and Space Administration

Common Bulkhead

Thrust Vector Control 7764.31

Upper Stage Avionics

The Upper Stage Avionics will provide: • Guidance, navigation, and control (GN&C) • Command and data handling • Preflight checkout

Interstage Avionics

Instrument Unit Avionics

Avionics Mass: 2,425 lbm Electrical Power: 5,145 Watts National Aeronautics and Space Administration

Thrust Cone Avionics

Aft Skirt Avionics

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Upper Stage Accomplishments

Manufacturing Development Centers Marshall Space Flight Center, AL

First Manufacturing Demonstration Article Gore-Gore Weld Marshall Space Flight Center, AL

First Friction Stir Weld of ET Dome Gore Panels Marshall Space Flight Center, AL

Development of the Ares Vertical Milling Machine Chicago, IL

National Aeronautics and Space Administration

7764.33

Upper Stage Accomplishments

Common Bulkhead Seal Weld Process Development Marshall Space Flight Center, AL

Aluminum-Lithium (Al-Li) 2295 Y-Ring Delivery Marshall Space Flight Center, AL

Delivery of FSW Tooling with Weld Head Michoud Assembly Facility, LA

Al-Li Panel Structural Buckling Testing Marshall Space Flight Center, AL

National Aeronautics and Space Administration

7764.34

Upper Stage Accomplishments

Ullage Settling Motor System (USMS) Heavy Weight Motor Hot-Fire Test Marshall Space Flight Center, AL

Reaction Control System (ReCS) Development Test Article Delivery Marshall Space Flight Center, AL National Aeronautics and Space Administration

Ares I Roll Control Engine Test Sacramento, CA

Thrust Vector Control (TVC) 2-Axis Test Rig Glenn Research Center, OH 7764.35

National Aeronautics and Space Administration

Ares I Elements

www.nasa.gov

Upper Stage Engine Used on Ares I and Ares V Turbomachinery • Based on J-2S MK-29 design • Beefed up to meet J-2X performance • Altered to meet current NASA design standards Gas Generator • Scaled from RS-68 design Engine Controller • RS-68-based design and software architecture

Regeneratively Cooled Nozzle Section • Based on long history of RS-27 success

Flexible Inlet Ducts (Scissors Ducts) • Based on J-2 & J-2S ducts • Altered to meet current NASA design standards

Open-Loop Pneumatic Control • Similar to J-2 & J-2S design Valves • Ball-sector (XRS-2200 and RS-68)

HIP-bonded MCC • Based on RS-68 demonstrated technology

Turbine Exhaust Gas Manifold • Performance and cooling of Nozzle extension

Mass: 5,396 lbm Thrust: 294K lbm (vac) Isp: 448 sec (vac)

Metallic Nozzle Extension • Spin-formed, Chemically milled

Height: 15.4 ft Diameter: 10 ft National Aeronautics and Space Administration

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Upper Stage Engine Testing/Production Status

Fuel Turbopump Nozzle Work Horse Gas Generator Testing

Fuel Turbopump Volute Casting

Main Combustion Chamber Forward Manifold Casting National Aeronautics and Space Administration

Main Combustion Chamber Spun Liner

Nozzle Turbine Exhaust Manifold Base Ring Forging 7645.38

Upper Stage Engine Accomplishments

J-2X Powerpack 1A Testing Stennis Space Center, MS

J-2X Powerpack Removal from A-1 Test Stand Stennis Space Center, MS

Powerpack 1A Disassembly Canoga Park, CA

E3 Subscale Diffuser Test Stennis Space Center, MS

National Aeronautics and Space Administration

7764.39

Upper Stage Engine Accomplishments

J-2X Workhorse Gas Generator Manufacturing Canoga Park, CA

Workhorse Gas Generator Test Marshall Space Flight Center, AL

Test Stand A-3 Construction Stennis Space Center, MS

J-2X Valve Actuator Design Buffalo, NY

National Aeronautics and Space Administration

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National Aeronautics and Space Administration

Constellation Launch Vehicles Overview Part 2

www.nasa.gov

Part 2 Agenda Progress on Key Ares I Risks Ares I-X Overview and Update Ares V Overview Summary

National Aeronautics and Space Administration

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National Aeronautics and Space Administration

Progress on Ares Risks

www.nasa.gov

Progress on Key Risks Ares uses a thorough active approach to identifying and mitigating technical issues and risks • Applying appropriate resources in order to manage and retire risks and issues as they arise

The current top Ares I systems risks analyzed and being actively mitigated are : • First Stage Thrust Oscillation • Mobile Launch Platform Lift-off Clearance • Separation System Pyro-shock • Upper Stage Vibroacoustics • Ares I Payload Mass Performance

The program expects to retire these while identifying new challenges as the program proceeds to CDR National Aeronautics and Space Administration

7764.44

First Stage Thrust Oscillation (TO) Background: Actual flexible system tunes with forcing function

If system were rigid Response

psi

Graphical Reference Only (Not to Scale)

g's

4.0

Response

TO “Football” ~12 Hz

3.5 time

time

3.0 Acceleration (g‟s)

0.16 g‟s

2.5

Liftoff <10 Hz Staging

2.0 1.5

Max Q 3-100 Hz

1.0

0.5

Abort Scenarios

Manual Control

0 0

50

100

150

200

250

300

MET (sec)

Pressure Oscillation psi

Pressure Oscillation psi

time

100,000 lb

time

100,000 lb

Four basic ways to attack problem:  Reduce forcing function  Detune system response away from forcing function frequency  Actively create an opposing forcing function  Passively absorb forcing function  Mitigation Options

National Aeronautics and Space Administration

 Baseline Design 7764.45

First Stage Thrust Oscillation Status: June Program Review was completed with decision to baseline and implement Dual Plane (DP) Isolation • Baseline design established as a DP isolation system with the first plane between first stage and upper stage with a reference stiffness of 8M lb/in and an upper plane between US and Orion, on the US side of the interface with a reference stiffness of 1.2M lb/in • The crew testing yielded in a requirement recommendation of 0.21 g‟s root mean square over a 5-second period and not to exceed 0.7 g‟s PEAK at 99.865% ( in order to maintain Crew situational awareness) • The performance analysis shows that DP isolators are very close to meeting this requirement with 93.8% for Lunar and 98.1% for International Space Station (ISS) cases • Orion will provide the design changes necessary to achieve 99.865% • Upper Stage will begin design efforts to include the second plane isolator and coordinate interface design requirements with Orion

Integrating project level risks into single program level risks Response

Mitigation: Crew testing Requirements for crew seat responses Design updates to the ISS Orion configuration Design/analysis/model verification of Loads Analysis 4 Finite Element Models TO forcing function verification Update Monte Carlo analysis for crew seat response Quantify TO mitigation baseline design margin required to cover structural uncertainty National Aeronautics and Space Administration

Structural mode

Thrust forcing function

7764.46

Comparison of Mitigation Options Working Baseline Dual-Plane Isolation

National Aeronautics and Space Administration

Risk Mitigation Options Propellant Damper Single-Plane Isolation

Active RMAs plus Single-Plane Isolation

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Tower Lift-Off Clearance Background: First stage thrust misalignment and launch site winds result in launch vehicle drift and potential tower and/or launch mount re-contact Launch drift can result in tower damage due to plume impingement and can increase refurbishment cost and schedule between flights Apollo Saturn V had similar issues and used active steering

Mitigation: An active steering solution has been developed that reduces launch drift and meets tower re-contact requirements with no performance impact (Saturn V approach) The Mobile Launcher launch mount design has been modified to increase liftoff clearances Planned forward work to further mitigate this risk includes:

Current 3-sigma drift curve

May 2008, 3-sigma drift curve

SM/US Umbilical

• Pursue southerly wind placarding to increase tower clearance and reduce the probability of plume damage to the tower • The Ground Operations team is evaluating thermal protection (e.g., water deluge) and tower equipment hardening options to reduce plume damage as necessary

Status: Recent analysis refinements include specific updates to the nozzle configuration, flight control algorithm call rate, and thrust misalignment model. The analysis update confirmed the effectiveness of the active steering solution National Aeronautics and Space Administration

Launch Mount (actual mount not shown)

North (drift curves not exact, for illustration only) 7764.48

Separation System Pyro-Shock Background: The first stage–upper stage separation approach used a linear shaped charge (LSC) device with a pyrotechnic load of 55-grains/ft. Shock levels were conservatively predicted using 75 grains/ft, yielding very high pyro-shock levels, especially at nearby components. Shock panel testing showed that the 55-grains/ft shock levels were too high for the nearby avionics to tolerate without significant design and mass impacts External Debris Shield/

Mitigation: The NASA Design Team, Boeing, and Ensign Bickford developed and traded several options for reducing the shock load. Two candidate approaches were traded: a 30-grains/ft frangible joint and a 30-grains/ft LSC The frangible joint was selected because it generates the lowest shock levels and was judged to be a lower overall risk for the upper stage design Further panel testing is planned to verify the shock levels at the avionics. It is expected that this testing will show that the shock levels at the avionics components are within acceptable limits National Aeronautics and Space Administration

Ring Forging with 30-gr/ft LSC and 0.18″ Groove

Compression Ring Linear Shaped Charge

Splice Plates

Stage separation wind tunnel test Arnold Air Force Base, TN 7764.49

Upper Stage Vibroacoustics Background: Ares I has a high dynamic pressure trajectory resulting in significant induced vibroacoustic environments. This results in design challenges that may result in additional component development and / or qualification. Mitigation: A layered mitigation strategy has been developed to mitigate the redesign risk to the Program, including: • Confirm vibroacoustic environments are accurate and appropriate, given the Ares I trajectory and configuration based on the latest trajectory, wind tunnel data, and latest configuration. This activity is underway but not yet complete • Investigate possible global solutions for affected subsystems and components. This activity includes removing external protuberances, if possible, and is complete unless an unforeseen opportunity is found • Design components and subsystems to survive the environment. To date, four components are being assessed in detail RCS thrusters, RCS propellant tank, interstage avionics, and aft skirt avionics

National Aeronautics and Space Administration

Rigid buffet model testing in transonic dynamic tunnel Langley Research Center, VA 7764.50

Upper Stage Vibroacoustics (cont‟d) Mitigation: Several options are available to mitigate the high vibration, including: • Moving components to an area with less stressing environments • Developing systems to absorb transmitted energy and isolate components from the environment. The figures illustrate the concept of using a group of wire rope isolators to reduce vibration loads on the panelized components. Early testing has shown a 50–60% reduction in transmitted energy. This activity is underway and additional tests are planned

• Combining components into panels or manifolds to change the structural response. As components are combined, detailed analysis will be conducted to determine the effectiveness and the resulting structural loads on the connecting and the primary structures • Hardening the components to withstand the vibration levels or develop the isolation system

National Aeronautics and Space Administration

7764.51

Initial Capability (ISS Mission) Injected June 2009 AresI1and & Orion Target(130 (130km/70 km/70nmi) nmi) Ares Orionfor for ISS ISS Ascent Ascent Target with with Orion Orion44Crew CrewEstimates Estimates 25,000 24,000 23,000

Ares Gross Performance Ares Net Performance 3σ Performance Knockdowns Net w/ T&O & pending

Mass (kg)

22,000

A-106

ARES 1 Project Margin =1926 kg (9.5%)

21,000

20,312 kg (CA1000-PO)

20,000

Level II (Program) Reserve

19,296 kg (CA4164-PO)

Predicted w/ T&O

19,000

Project Margin 974 kg (8.4%)

18,000

606-G 4 crew members *ESTIMATE*

Orion Predicted Mass

17,000 Current MGA = 1481 kg (12.7%)

16,000

Orion Basic Mass

15,000 Oct 08

Nov 08

Dec 08

Jan 09

Feb 09

Mar 09

Apr 09

Color of arrow indicates current status: Green is compliant; Yellow is acceptable but at risk; Red is noncompliant Direction of arrow indicates trend from last data point: Up is improved; Right is unchanged; Down is worsened National Aeronautics and Space Administration

May 09

Jun 09

Jul 09

Aug 09 Orion PDR

Sep 09

Status/Trend* Ares I Total Margin

22.5%

Orion Total Margin

21.1%

7764.52

Progress on Key Risks The current top Ares I systems risks analyzed and being actively mitigated are : • First Stage Thrust Oscillation – Plan in place, baseline selected and being implemented • Mobile Launch Platform Lift-off Clearance -- Re-Contact resolved mitigating plume tower interaction • Separation System Pyro-shock – Mitigation in place with selection of separation system • Upper Stage Vibroacoustics – Using total vehicle approach to refine environments and develop component solutions • Ares I Payload Mass Performance –Meeting requirements and holding adequate mass margins. Mass is continually monitored as a top performance metric.

The program expects to retire these while identifying new challenges as the program proceeds to CDR National Aeronautics and Space Administration

7764.53

National Aeronautics and Space Administration

Ares I-X Overview

www.nasa.gov

Ares I-X Flight Test Overview Ares I-X is a Constellation Program developmental flight test for the Ares I project • There are five primary flight test objectives – P1 through P5 • Ares I-X is an un-crewed suborbital test ~150,000 feet

P2) Perform in-flight separation/staging ~130,000 feet

P5) Characterize integrated vehicle roll torque

P1) Demonstrate controllability

Flight Test Profile National Aeronautics and Space Administration

Vehicle Height: Weight at Ignition: Max. Acceleration: Max. Speed:

327 feet 1.8 M-lbm 2.5 g Mach 4.8

P4) Demonstrate first stage entry dynamics and post staging sequencing of events (e.g. employ booster tumble motors and deploy parachutes)

Upper Stage/ Crew Module/ Launch Abort System Simulator free fall into ocean First Stage recovery

P3) Demonstrate assembly and recovery of an Ares I similar first stage

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Ares I-X Status First Stage: Motor from Space Shuttle inventory delivered to Kennedy Space Center (KSC) in March 2009. Aft skirt and forward structures completed in May 2009. Turned over to System/Ground Operations in June 2009 Upper Stage Simulator (USS): Hardware completed and delivered to KSC in November 2008 Roll Control System (RoCS): Modules A and B delivered to KSC April 2009. Installed in the USS interstage Avionics: Sensor, harnesses, airborne avionics boxes, and support ground subsystems delivered to KSC except for inertial navigation unit (INU). INU in test Crew Module/Launch Abort System Simulator: Hardware completed and delivered to KSC in January 2009 Ground Operations: Operational Readiness Reviews November 2008 – August 2009. Stacking of full vehicle in the KSC Vehicle Assembly Building (VAB) started in July 2009 Ground Systems: Launch Pad modification to be complete August 2009 Launch scheduled for October 31, 2009 National Aeronautics and Space Administration

First Stage center motor segment mated with its aft motor segment

Orion Simulator

RoCS with USS segments in the background

Aft motor segment with aft skirt

Avionics Module

Superstack I in the VAB 7764.56

National Aeronautics and Space Administration

Ares V Overview

www.nasa.gov

Ares V Elements Current Point-of-Departure Gross Liftoff Mass: 8,167.1K lbm Performance to TLI: 157K lbm Integrated Stack Length: 381.1 ft

Altair Lunar Lander

Payload Adapter Loiter J-2X Skirt Payload Shroud

Interstage

Earth Departure Stage (EDS) • One Saturn-derived J-2X LOX/LH2 engine (expendable) • 33 ft diameter stage • Aluminum-Lithium (Al-Li) tanks • Composite structures, instrument unit, and interstage • Primary Ares V avionics system Core Stage • Six Delta IV-derived RS-68B LOX/LH2 engines (expendable) • 33 ft diameter stage • Composite structures • Al-Li tanks National Aeronautics and Space Administration

Solid Rocket Boosters • Two recoverable 5.5-segment PBAN-fueled, steel-case boosters (derived from current Ares I first stage) • Option for new design

Six RS-68B Engines

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Ares I and Ares V Commonality Upper Stage-Derived Vehicle Systems

Builds Up Flight Reliability on the Smaller Vehicle Earlier Lowers Life Cycle Cost

J-2X Upper Stage Engine

Elements from Shuttle

U.S. Air Force RS-68B from Delta IV RS-68

First Stage (5-Segment RSRB)

Elements from Ares I

Ares I

National Aeronautics and Space Administration

Range: full stage to case/nozzle/booster systems

Ares V

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Ares V Status NASA has begun preliminary concept work on vehicle. Over 1,700 alternatives investigated since ESAS Focused on design of EDS, payload shroud, core stage, and RS-68 core stage engines Recent point of departure update following the Lunar Capability Concept Review • Adds additional performance margin using an additional RS-68 • Adds half segment on the first stage boosters

Shroud size dictated by eventual size of Altair lunar lander Also investigating alternate uses for Ares V not related to human space exploration • Astronomy applications (e.g., large aperture telescopes) • Deep space missions • DoD applications • Other applications

National Aeronautics and Space Administration

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Architecture Flexibility Enables New Science Applications Mars C3 = 9 km2/s2 9 mos

Ares V with Centaur Ares V Ares I with Centaur

Payload (t)

Deltas IV-H

Ceres C3 = 40 km2/s2 1.3 yrs

Large Payload Volume and Lift Capability

At 5.7 mT, the Cassini spacecraft is the largest interplanetary probe and required a C3 of 20 km2/s2 and several planetary flyby „gravity assist‟ manuevers. Ares V can support about 40 mT for this same C3.

Cassini spacecraft ~ to scale for comparison

Jupiter C3 = 80 km2/s2 2.7 yrs Saturn C3 = 106 km2/s2 Uranus 6.1 yrs Neptune C3 = 127 km2/s2 C3 = 136 km2/s2 15.8 yrs 30.6 yrs

Ares V will have the largest payload volume capability of any existing launch system

C3 Energy (km2/sec2) “It is very clear from the outset that the availability of the Ares V changes the paradigm of what can be done in planetary science.” – Workshop on Ares V Solar System Science “Exciting new science may be enabled by the increased capability of Ares V. The larger launch mass, large volume, and increased C3 capability are only now being recognized by the science community.” – National Academy of Science‟s “Science Opportunities by NASA‟s Constellation Program” National Aeronautics and Space Administration

Current Capability

Ares V Enabled Capability (>10x Collection Area)

8-9 m

16+ m 7764.61

Range of Architecture Options Enabled A Few Examples (Payload to TLI)

Crew Capability using Ares I Upper Stage with Ares V Core (35 t)

Crew Capability (45–51 t)

Single Launch Capability (55–63 t)

Baseline (71 t with Ares I) National Aeronautics and Space Administration

Common First Stage with Ares I (68 t with Ares I)

Advanced Solid First Stage (75 t with Ares I) 7764.62

National Aeronautics and Space Administration

Summary

www.nasa.gov

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Advancing Technology: Partnerships with Industry and Researchers Working with commercial, non aerospace industries (e.g., shipbuilding) to further mature/spinoff friction stir welding technology

Innovative approach to dampening in-flight vibrations using on-board liquid oxygen

Fabrication of large (10 m diameter) composites for Ares V Shroud, Earth Departure Stage (EDS), and Core Stages to save weight • Working with industry to identify innovative autoclave or “out of autoclave” approaches including assembly of smaller composites

Development of asbestos-free insulation for Ares solids to reduce environmental impact and increase worker safety • Material may also be used in protective equipment for firefighters National Aeronautics and Space Administration

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Summary Ares I and V development is the fastest and most prudent path to closing the human spaceflight gap while enabling exploration of the Moon and beyond Selection of the Ares architecture was made after systematic evaluation of hundreds of competing concepts and represents the lowest cost, highest safety/reliability, and lowest risk solution to meeting Constellation‟s requirements Ares is built on a foundation of proven technologies, capabilities, and infrastructure The Ares I team has met all key milestones since Project inception, including four major prime contract awards and a successful Preliminary Design Review • Unanimous PDR Board and independent Standing Review Board (SRB), agreement that Ares I is ready to proceed to CDR • Progress includes release of over 1,800 Ares I design drawings

Ares V project is well underway • Draft Phase I Request for Proposal released November 2008; Industry proposals under review

Ares V will be considered a national asset with unprecedented performance and payload volume that can enable or enhance a range of future missions • Current architecture delivers ~60% more mass to TLI than Saturn V and ~35% more mass to LEO than Saturn V

External assessments continue to validate the architectures • National Advisory Council: “The NAC is confident that the current plan is viable and represents a well-considered approach . . .” – October 2008 • Government Accountability Office: “NASA has taken steps toward making sound investment decisions for Ares I.” – November 2007 • Standing Review Board: “The SRB believes that the Project is managing and executing the vehicle development appropriately, including visibility of the individual risk items.” • National Research Committee: “The unprecedented mass and volume capabilities of NASA‟s planned Ares V cargo launch vehicle enable entire new mission concepts.” National Aeronautics and Space Administration

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Ares Online Outreach http://www.facebook.com/NASA.Ares

http://twitter.com/NASA_Ares

http://www.youtube.com/AresTV

http://streaming.msfc.nasa.gov/podcast/ares/ARES.xml http://streaming.msfc.nasa.gov/podcast/ares/ARES_SD.xml

http://www.thefutureschannel.com/dockets/space/ares/ http://www.teachertube.com/videoList.php?pg=videonew&cid=38

http://www.nasa.gov/ares

National Aeronautics and Space Administration

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