SpaceWorks Engineering, Inc. (SEI)www.sei.aero

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AN OVERVIEW OF THE FIRM

Revision A21 November 2006

www.sei.aeroinfo@sei.aero1+770.379.80001+770.379.8001 (Fax)

SpaceWorks Engineering, Inc. (SEI)www.sei.aero

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Introduction

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About SpaceWorks Engineering, Inc. (SEI)

Overview:- Engineering services firm based in Atlanta (small business concern)- Founded in 2000 as a spin-off from the Georgia Institute of Technology- Averaged 130% growth in revenue each year since 2001 - 85% of SEI staff members hold degrees in engineering or science

Core Competencies:- Advanced Concept Synthesis for launch and in-space transportation systems- Financial engineering analysis for next-generation aerospace applications and markets- Technology impact analysis and quantitative technology portfolio optimization

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Dr. John R. OldsCEO

Dr. John E. BradfordPresident

Melinda S. OldsCFO

Advanced Concepts Group (ACG)Dr. Brad St. Germain

Director of Advanced Concepts

Economic Engineering Group (EEG)Mr. A.C. Charania

Senior Futurist

Business Operations Group (BOG)Dr. John E. Bradford

Acting Director

Technical Fellows & AffiliatesMr. Bill Escher (Senior Technical Fellow)Dr. Leroy Chiao (Affiliate)

Firm Organizational Structure

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Practice AreasSpace Systems Analysis | What is the System?Conceptual Level Engineering AnalysisConceptual Level Engineering DesignLife Cycle AssessmentCost EngineeringAdvanced / Robust Design Processes

Technology Prioritization | What are the Implications? Technology AnticipationTechnology Benefit AssessmentsTechnology Prioritization

Financial Engineering | Is the Project Viable?Business DesignFuture Venture Due DiligenceReal Options Analysis

Future Market Assessment | What is Next?Scenario PlanningMarket ForecastingMarket Analysis

Policy and Media Consultation | How to Express the Vision?Government InitiativesPolicy ConsultationTelevision, Film, Radio, Internet Presence

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From Vision to Concept

Including:- Engineering design and analysis- New concept design- Independent concept assessment- Full, life cycle analysis- Programmatic and technical analysis

Including:- Storyboards- Technical concept illustrations (marker and pastel in B&W and color)- 2-D line engineering drawings with technical layouts and dimensions- 3-D engineering CAD models of concept designs- High-resolution computer graphics imaging (renders) - Concept / architecture summary datasheets and single page handouts / flyers

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Including:- 2nd, 3rd, and 4th generation single-stage and two-stage Reusable Launch Vehicle (RLV) designs (rocket, airbreather, combined-cycle)- Human Exploration and Development of Space (HEDS) infrastructures including Space Solar Power (SSP)- Launch assist systems- In-space transfer vehicles and upper stages and orbital maneuvering vehicles- Lunar and Mars transfer vehicles and landers for human exploration missions- In-space transportation nodes and propellant depots- Interstellar missions- In-space and surface human habitats

Concepts and Architectures

Image sources: SpaceWorks Engineering, Inc. (SEI), Space Systems Design Lab (SSDL) / Georgia Institute of Technology

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Various Firm Engagements

DARPA: Hypersonic cruise vehicle operational and demonstrator system (HCV-OS, HCV-DS) under Northrop Grumman subcontract for FALCON program DARPA: Responsive Access Small Cargo Affordable Launch (RASCAL) program subcontract for performance analysis, aerodynamics, and mission effectivenessAFRL-WPAFB: Innovative concept development for MSP RLVs using combined-cycle propulsion systems for military applicationsAFRL-EAFB: IDIQ award to support launch vehicle trajectory analysis and simulationsU.S. Air Force: Phase I SBIR to develop new launch vehicle abort analysis capability (Phase II proposal under review)NASA Institute for Advanced Concepts (NIAC): Phase I Award for asteroid planetary defense architecture NASA Institute for Advanced Concepts (NIAC): Phase I Award for Mars telecommunication networks NASA Headquarters: Economic Development of Space (EDS): Examination and Simulation Project NASA Headquarters: RLV technology goals assessment NASA LaRC: Lunar exploration architecture design and analysis support (launch vehicles, in-space stages, lunar landers)NASA LaRC: Lunar exploration architecture technology prioritization and assessment support NASA LaRC: Next Generation Launch Vehicle (NGLT) architecture support NASA MSFC: ETO and In-Space trade tree concept studies for lunar exploration architecturesNASA MSFC: Simulating Emerging Space (SES) Small Business Innovative Research (SBIR) grantNASA MSFC: Lunar architecture design studies NASA MSFC: Small payload launch vehicle (SPLV) assessment NASA MSFC: Air-launch to orbit (ALTO) study support NASA MSFC: ARTS dual fuel RLV concept with launch assist NASA MSFC: 3rd Gen RLV concept assessment and engineering tool development for Advanced Concepts Group NASA MSFC: Space transportation technology prioritization for Integrated Technology Assessment Center (ITAC) NASA MSFC: Heavy-lift launch vehicle configurations predicated on SLI technologies for Program Planning Office NASA MSFC: Database and tool development for Revolutionary Aerospace Systems Concept (RASC) program NASA KSC: Design for Operations (D4Ops) space transportation study NASA KSC: Facilities and Ground Operations Analysis (FGOA) tool development for future space transportation systems NASA ARC: 2nd Gen RLV / Space Launch Initiative (SLI) Program: Advanced Engineering Environment (AEE) NASA GRC: Inter-center Value Stream Analysis Program: Micro and macro level technology implications for 3rd Gen RLVsSAIC and NAL (Japan): ATREX engine test program performance assessment Orbital Sciences Corporation: Space exploration architecture and technology roadmapping for NASA Concept Exploration and Refinement (CE&R) studyLockheed Martin Astronautics: Assessment of optimization codes for space transportation case studies Pratt Whitney Rocketdyne: Systems analysis and concept development for lunar exploration engine and power module studies

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Sample Client List

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Recent Exploration Experience

Including:- NASA Exploration Systems Mission Directorate (ESMD) Concept Exploration and Refinement (CE&R) Study Subcontractor- NASA Exploration Systems Mission Directorate (ESMD) Economic Development of Space (EDS) Project- NASA MSFC exploration architecture trade studies (launch vehicles, in-space stages, lunar landers)- NASA MSFC Prometheus follow-on study: Nuclear Electric Propulsion (NEP) mission to Pluto/Kuiper Belt- NASA LaRC Lunar Lander Preparatory Study Phase 1 Concept Design for NASA JSC- Rocketdyne propulsion technology assessment on lunar exploration architectures- Mission Scenario Analysis Tool (MSAT) architecture optimization tool development- Moonraker in-space stage and habitat sizing tool development- In-space trajectory tool development- Lunar exploration economic and life cycle cost analysis

Image sources: NASA

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- Ability to model complete life cycle of various space transportation and infrastructure systems (Earth-To-Orbit, In-Space, etc.), including performance, cost, operations, safety and economics (deterministically or probabilistically) in a collaborative design environment

- Power to create cogent and striking descriptions of concepts based upon mission objectives, engineering principles, and policy goals

- Advanced degrees in fields related to space vehicle design- Project work on conceptual and preliminary design phases

- Firm’s organizational structure allows for timely response to client needs- Favorably price-competitive with minimal contracting overhead

- Independent, unbiased assessments with no predisposition to push a particular concept or technology solution

- SBA small business that works with many NASA field centers and DoD- Firm setup allows for flexible contracting arrangements

Skills:

Experience:

Value:

Non-advocacy:

Firm Position:

SEI Strengths

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- Quick response life cycle (performance, economic, etc.) assessment of new concepts

- Use unique blend of engineering knowledge, creative skill, and organizational capabilities to distinguish proposals

- Exploration of trade space of current concepts- Independent review of current suite of concepts

- Develop justification for technology investment decisions

- Augment current manpower / tool expert requirements / tool development- Specific engineering labor for specific projects

- Suite of services to illustrate program concepts

Concept Design Creation:

Proposal Development and Assistance:

Concept Design Validation andIndependent Assessment:

Technology Prioritization:

Supplementary/Complementary Engineering Labor Services:

Visualization Services:

Potential Areas of Partnership

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Expertise

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Sample Suite of SEI Space Engineering Design Tools

SESAWSubsystems

CABAM, CABAM_A, NESC, NAFCOM (2002, 2004), TRANSCOST, SOCM, LMNoP, SSPATE, NASA Mission Market Models, Commercial Space Transportation Study (CSTS) market models, FAA COMSTAC market forecasts

Economics and Cost

historical databases, CONSIZ, INTROS, WATES, GT-Sizer, AC-Sizer, LVA, MoonRaker

Weights and Sizing

AATe, OCM-COMET, RMAT, MSAT, FGOAOperations

GTSafety-II, SAFE, PRISMSafety and Reliability

REPP, SCCREAM, ROCETS, SRGULL, RJPA, NEPP,

LRE Designer, REDTOP, REDTOP-2Propulsion

Miniver, TPS-X, SENTRYAeroheating and TPS

APAS, S/HABP, NASCART-GT (2-D, 3-D Euler and NS)Aerodynamics

OptWorks, ProbWorks, Crystal Ball, Evolver, SAS JMP, Matlab, DOT, ADS, ModelCenter©, Analysis Server©

System Engineering

POST 3DOF, POST II, OTIS, Chebytop, IPREP/LPREPTrajectory

SDRC I-DEAS, Solid Edge, CanvasCAD and Packaging

Tools, Models, SimulationsDiscipline

Vehicle Performance Toolsets

Economic Closure Toolsets

Design and Optimization

Note: SEI-Developed/Enhanced Tools

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Sample Performance Analyses

Note:Data generated through SENTRY model and exported to data visualization program for eventual display

Sample Thermal Analysis:Maximum RLV Orbiter Entry Surface Temperature (via SENTRY)

Sample Thermal Analysis:Maximum RLV Booster Entry Surface Temperature and TPS Tile Thickness (via SENTRY)

TOP VIEW UNDERSIDE VIEW

Sample Trajectory Analysis (via POST):

0.00.51.01.52.02.53.03.54.04.5

0 100 200 300 400 500 600Time (s)

Mlb

Thrust

Weight

Thrust and Weight vs. Flight Time

050

100150200250300350400450

0 100 200 300 400 500 600Time (s)

Altit

ude (

thou

sand

s of f

t)

Altitude vs. Flight Time

Optimized transitionto SSME-only

Relative Velocity and Mach vs. Flight Time

0

5,000

10,000

15,000

20,000

25,000

30,000

0 100 200 300 400 500 600

Relat

ive V

elocit

y (ft/

s)

0

5

10

15

20

25

30

Mach

Num

ber

Time (s)

Relative Velocity

Mach

“Net” ISP (SSME and RD-180) vs. Flight Time

0

100

200

300

400

500

0 100 200 300 400 500 600

Time (s)

ISP

(s)

SSME

RD-180“Net” Value

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Sample Computer Aided Design (CAD)

Xcalibur Two-Stage-To-Orbit (TSTO) Reusable Launch Vehicle (RLV)

ARTS Single-Stage-To-Orbit (SSTO) Reusable Launch Vehicle (RLV)

Booster Stage of Two-Stage-To-Orbit (TSTO) Reusable Launch Vehicle (RLV)

Shuttle Derived Crew Launch Vehicle (CLV)

Crew Exploration vehicle (CEV) –Command Module (CM)

Crew Exploration vehicle (CEV) –Service Module (SM)

Shuttle Derived Cargo Launch Vehicle (CaLV)

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Sample Economic Analyses

Human Exploration Cost Estimates Scenarios of Reusable Launch Vehicle (RLV) Price Sensitivity

500

1,500

2,500

3,500

4,500

25% 50% 75%Turn-Around-Time Reduction

Pric

e Pe

r Pou

nd P

aylo

ad [$

/lb]

20

40

60

80

100

120

140

Flig

ht R

ate

[Flig

hts

Per

Yea

r]

Price Per Flight [$/lb]

Flight Rate [Flights/Year]

500

1,500

2,500

3,500

4,500

25% 50% 75%Turn-Around-Time Reduction

Pric

e Pe

r Pou

nd P

aylo

ad [$

/lb]

20

40

60

80

100

120

140

Flig

ht R

ate

[Flig

hts

Per

Yea

r]

Price Per Flight [$/lb]

Flight Rate [Flights/Year]

1,0002,0003,0004,0005,0006,0007,0008,0009,000

10,000

25% 50% 75%Turn-Around-Time Reduction

Pric

e Pe

r Pou

nd P

aylo

ad [$

/lb]

20

25

30

35

40

Flig

ht R

ate

[Flig

hts

Per

Yea

r]

Price Per Flight [$/lb]

Flight Rate [Flights/Year]

1,0002,0003,0004,0005,0006,0007,0008,0009,000

10,000

25% 50% 75%Turn-Around-Time Reduction

Pric

e Pe

r Pou

nd P

aylo

ad [$

/lb]

20

25

30

35

40

Flig

ht R

ate

[Flig

hts

Per

Yea

r]

Price Per Flight [$/lb]

Flight Rate [Flights/Year]

Oper

atio

ns C

ost R

educ

tion

DDT&E AND TFU COST REDUCTION25% 75%

25%

75%

Components of LCC (FY06)

Other (Robotic/ISS/Shuttle)

CEV/CM

CLV

LSAM

CaLV-HLLV

EDS + CEV/SM

Technology Maturation Surface Systems

Facilities, Operations, and Flight Tests

0

2,000

4,000

6,000

8,000

10,000

12,000

14,000

16,000

2006 2007 2008 2009 2010 2011 2012 2013 2014 2015 2016 2017 2018 2019 2020 2021 2022 2023 2024 2025

Year

$M

$111.3 B (2006-2018) $53.4 B (2019-2025)$164.7 B

NASA FY06 Exploration-Related Budget

See: http://www.sei.aero/library/technical.html for more information and technical papers on above analyses

Space Tourism Economic Modeling International Space Station (ISS) Support Market

-100M

-50M

0M

50M

100M

0 2 4 6 8 10 12

Disc

ount

ed C

umul

ative

Ca

sh F

low

(US

$)

Project Year

Effect of Competition

Higher-End Operator

In Competition with Higher-End

Lower-End Operator

Effect of Market Entry Date

0 2 4 6 8 10 12Project Year

-40M-20M

0M20M40M60M80M

-60M-80M 2 Year Market Delay

4 Year Market Delay

Higher-End Operator

Lower-End Operator

5 Commercial Competitors + min. 2 CEV/Yr + Russian Competition

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Conceptual Design Processes Within ModelCenter© Environment: Case Study 1

Integrated Design Process

CASE STUDY: Lunar Transportation Architecture Optimization

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Conceptual Design Processes Within ModelCenter© Environment: Case Study 2

Integrated Design Process

CASE STUDY: Turbine-Based Combined Cycle (TBCC) Reusable Launch Vehicle (RLV)

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ATIES Technology Prioritization Method

Baseline Concept DeterminationRequirements = Objectives + Constraints

(i.e. New RLV)

A

Technology Alternatives

Technology Identification

Technology Evaluation

Physics-based Modeling and Simulation Environment:Potential Environment: Reduced Order Simulation for

Evaluation of Technologies and Transportation Architectures (ROSETTA MODEL)

Physics-based Modeling and Simulation Environment:Potential Environment: Reduced Order Simulation for

Evaluation of Technologies and Transportation Architectures (ROSETTA MODEL)

B

E

Technology Mixes Deterministic or StochasticImpact Factors

Technology Selection

F

Analytic Hierarchic Process (AHP)and / or

Pugh Evaluation Matrix (PEM)

Technique for Order Preference by Similarity to Ideal Solution (TOPSIS): Best Alternatives Ranked for

Desired Weightings

Individual Technology Comparison for

Resource Allocation

Technology Compatibility Matrix (TCM)

Technology Compatibility

C

Compatibility Matrix (1: compatible, 0: incompatible)

Com

posi

te W

ing

Com

posi

te F

usel

age

Circ

ulat

ion

Con

trol

HLF

C

Envi

ronm

enta

l Eng

ines

Flig

ht D

eck

Syst

ems

Prop

ulsi

on M

ater

ials

Inte

gral

ly, S

tiffe

ned

Alu

min

um

Airf

ram

e St

ruct

ures

(win

g)

Smar

t Win

g St

ruct

ures

(Act

ive

Aer

oela

stic

Con

trol)

Act

ive

Flow

Con

trol

Aco

ustic

Con

trol

T1 T2 T3 T4 T5 T6 T7 T8 T9 T10 T11

Composite Wing 1 1 1 0 1 1 1 0 0 0 0

Composite Fuselage 1 1 1 1 1 1 1 1 1 1

Circulation Control 1 1 1 1 1 1 1 1 1

HLFC 1 1 1 1 0 0 0 1

Environmental Engines 1 1 1 1 1 1 0

Flight Deck Systems 1 1 1 0 1 1

Propulsion Materials 1 0 1 1 1

Integrally, Stiffened Aluminum Airframe Structures (wing) 1 0 1 1

Smart Wing Structures (Active Aeroelastic Control) 1 1 1

Active Flow Control 1 1

Acoustic Control 1

Aircraft Morphing

Airc

raft

Mor

phin

g

Symmetric Matrix

Technology Impact Matrix (TIM)

Technology Impact

D

Com

posi

te W

ing

Com

posi

te F

usel

age

Circ

ulat

ion

Con

trol

HLF

C

Envi

ronm

enta

l Eng

ines

Flig

ht D

eck

Syst

ems

Prop

ulsi

on M

ater

ials

Inte

gral

ly, S

tiffe

ned

Alu

min

um

Airf

ram

e St

ruct

ures

(win

g)

Smar

t Win

g St

ruct

ures

(Act

ive

Aer

oela

stic

Con

trol)

Act

ive

Flow

Con

trol

Aco

ustic

Con

trol

T1 T2 T3 T4 T5 T6 T7 T8 T9 T10 T11Wing Weight -20% +5% -10% -5% +2%Fuselage Weight -25% -15%Engine Weight +1% +40% -10% +5%Electrical Weight +5% +1% +2% +5% +5% +2% +2%Avionics Weight +5% +2% +5% +2% +5% +2%Surface Controls Weight -5% +5% +5%Hydraulics Weight -5% +5%Noise Suppression -10% -1% -10%Subsonic Drag -2% -2% -10% -5%Supersonic Drag -2% -2% -15% -5%Subsonic Fuel Flow +1% +1% -2% -4% +1%Supersonic Fuel Flow +1% -2% -4%Maximum Lift Coefficient +15%O&S +2% +2% +2% +2% +2% +2% -2% +2% +2% +1%RDT&E +4% +4% +2% +2% +4% +2% +4% +5% +5% +5%Production costs +8% +8% +3% +5% +2% +1% +3% -3% -3% -3% -3%

Aircraft Morphing

Technical K_Factor Vector

1 -1 1-1-1 1

1 -1 1-1-1 1

1 -1 1-1-1 1

1 -1 1-1-1 1

1 -1 1-1-1 1

1 -1 1-1-1 1

1 -1 1-1-1 1

1 -1 1-1-1 1

+-+-++++

+-+-++++

+-+-++++

+-+-++++

+-+-++++

+-+-++++

+-+-++++

+-+-++++

Frequency Chart

lb

.000

.008

.016

.024

.032

0

8

16

24

32

42,500 46,875 51,250 55,625 60,000

1,000 Trials 0 Outliers

Forecast: Dry Weight

0% 1% 3% 4% 6%

J.8

Vehicle Influence Factors

(VIF)

TechnologiesSymmetric Matrix impact factors

Technologies

Technologies

Note: Based upon work performed at the Aerospace Systems Design Laboratory (ASDL) at the Georgia Institute of Technology

Alternatives1 2 3

Main Cruise Stage Propulsion Solar Electric Chemical rocket Solar ThermalMain Communications X band Orbiter link S bandMain Power Solar Nuclear Chemical BatteriesC

hara

cter

istic

s

Main Landing System Airbags Rocket thrusters Glider

0.91548

0.91534

0.91485

0.91461

0.91421

0.91391

0.91301

0.91262

0.91109

0.91060

0.910 0.915

Tech. Port. A

Tech. Port. B

Tech. Port. C

Tech. Port. D

Tech. Port. E

Tech. Port. F

Tech. Port. G

Tech. Port. H

Tech. Port. I

Tech. Port. J

Tech

nolo

gy C

ombi

natio

n (C

ase)

TOPSIS OEC

Probabilistic Output Data

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Case StudiesNote: The following are examples of work performed by the firm. For each case study, detailed technical and/or programmatic analysis was performed.

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EARTH

MOON

Earth Orbit

LunarOrbit

Earth To Orbit (ETO) Launch No. 1:Cargo Launch Vehicle (CaLV)Shuttle-Derived Heavy Lift Launch Vehicle (HLLV)Earth Departure Stage (EDS) + Lunar Surface Access Module (LSAM)

Earth To Orbit (ETO) Launch No. 2:Crew Launch Vehicle (CLV)Solid Rocket Booster (SRB) with new Upper StageCrew Exploration Vehicle (CEV) Command Module (CM) +Crew Exploration Vehicle (CEV) Service Module (SM) + Launch Escape System (LES)

LEO Rendezvous

Earth Arrival

Transfer to Moon (TLI + LOI) Return to Earth (TEI)EDS

(Performs TLI)Two-Stage LSAM

(Performs LOI + Descent + Ascent)CEV/SM

(Performs TEI) CEV/CM

Note: Notional representation of lunar exploration architecture. Architecture elements may not be in scale.

Lunar Descent Lunar Ascent

5 x RS-25f [LOX/LH2]2 x 5 segment SRB

2 x J-2S+ [LOX/LH2] 4 x RL-10+ [LOX/LH2] - Descent1 x New [LOX/CH4] - Ascent

1 x 4 segment SRB

1 x RS-25e [ LOX/LH2] 1 x LES SRM

1 x New [LOX/CH4] – Same as LSAM

Lunar Architecture Analysis

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Goliath Heavy-Lift Launch Vehicle Family

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Nominal Configuration

Strike Mission Configuration

Cargo Delivery Configuration

Takeoff from Military Space Port Mach 9 Staging Point SMV Orbit Delivery to 70x197 nmi. @ 28.5o

Quicksat Military Space Plane (MSP)

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Upperstage Space Maneuver Vehicle (SMV)

52.2 ft

Quicksat Military Space Plane (MSP) Configuration

(6) JP-7 Mach 4 Turbine Engines (4) JP-7 Dual-Mode Scramjet Engines (4) JP-7/H2O2 Tail-Rockets H2O2 Propellant Tanks (Main and RCS) JP-7 Propellant Tanks

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Sentinel Military Space Plane (MSP)

Space-Access Configuration Liftoff from Military Space Port

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MADMEN Asteroid Defense Architecture

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Nuclear Electric Propulsion (NEP) Mission to Pluto/Charon/Kuiper Belt

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Xcalibur: Two-Stage-To-Orbit (TSTO) Reusable Launch Vehicle (RLV)

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Multiple RLV Analyses: ACRE-92 and ARTS

29 ft78 ft

143 ft

LH2

TankLOX Tank

Payload Bay (15 ft dia.x 25 ft)

Main LOX/LH2 Engines (5)

He PressurantSpheres (4)Aft OMS/RCS Tanks (LOX/LH2)

Forward RCSTanks(LOX/LH2) OMSEngines (2)

ACRE

-92 A

ll Roc

ket R

LVAR

TS D

ual F

uel R

ocke

t RLV

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Martian Meteor Burst (MB) Communication Network Architecture

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Commercial Software Products

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REDTOP

SpaceWorks Engineering, Inc. (SEI) introduces the Rocket Engine Design Tool for Optimal Performance (REDTOP), an analysis code for quick and accurate prediction of liquid propellant rocket engine performance. REDTOP features a Graphical User Interface (GUI) for operating the tool on the PC platform (Windows XP, 2000, NT, and ME).

For a user specified propellant combination (bi or mono-propellant), chamber pressure, nozzle expansion ratio, and mixture ratio, REDTOP will compute performance parameters such as: ideal, sea-level, vacuum and ambient thrust and specific impulse (Isp), nozzle throat and exit area, chamber temperature, nozzle exit pressure, and mass flow-rate. REDTOP features a number of sizing options for the engine. These include designing for a required thrust level (at a specified ambient condition), sizing at a specified total mass flow-rate, or designing for a specific throat area.

This package is currently available for purchase through individual licenses. The full product suite includes self-installing executable, documentation with case study examples, and selected online support. Free site-wide university licenses are available.

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Oxygen Nitrogen Tetraoxide (NTO) Hydrogen Peroxide (at various purity levels of 100%,98%,95%,90%, and 85%)

Hydrogen Methane Propane Octane RP/Kerosene Monomethyl Hydrazine (MMH) Unsymmetrical Dimethyl Hydrazaine (UDMH)

Model generic fuel or oxidizer by specifying molecular structure and initial enthalpy

Performance corrections based on engine cycle type (e.g. Expander vs. Gas Generator), nozzleflow losses, degree of reaction, and combustor efficiency, efficiency used to correct the theoretical(ideal) engine's performance

User determined engine throttle range with new thrust, flow-rate, chamber pressure, and Isp

Built-in Oxidizer Propellant Options

Built-in Fuel Options

Other Propellant Options

Built-in Engine Efficiency Database

Throttled Engine Performance

REDTOP Input Screen REDTOP Output Screen

REDTOP Capabilities

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REDTOP-2

SpaceWorks Engineering, Inc. (SEI) introduces the Rocket Engine Design Tool for Optimal Performance (REDTOP)-2, an analysis code for the propulsion expert conducting conceptual and preliminary rocket engine design studies. REDTOP-2 features a Graphical User Interface (GUI) for operating the tool on the PC (Windows XP, 2000, NT, and ME) platform.

REDTOP-2 is capable of performing a steady-state engine power balance for a variety of cycles, predicting engine weight on a component basis, and computing the estimated development cost. REDTOP-2 allows for parametric engine design and sizing which include designing for a required thrust level (at a specified ambient condition), sizing at a specified total mass flow-rate, or designing for a specific throat area.

This package is currently available for purchase through individual licenses. The full product suite includes self-installing executable, documentation with case study examples, and selected online support.

^2

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Oxygen, Hydrogen Peroxide

Hydrogen, Methane, Propane, Octane, RP/Kerosene

Can easily add new fuel, oxidizers, and product species by supplying simple property table ofspecific heat, enthalpy, density, and entropy versus temperature and pressure.

Staged-Combustion, Gas Generator, Expander, and Tap-OffFuel and/or Oxidizer-Rich PreburnersDual versus Single PreburnerSeries versus Parallel Turbine Flow

Will size engine at maximum operating condition to determine weight, then analyze at throttledengine setting for performance assessment.

Detailed weight predictions for chamber(s), nozzle(s), valves, low and high pressurepumps/turbines, controllers, etc.

3 Cost Model Options: 1) New engine development, 2) Existing engine modification, 3) P&W-likecosting methodology. Computes DDT&E and first unit cost (TFU).

Built-in Oxidizer Propellant Options

Built-in Fuel Options

Generic Equilibrium Model

Cycle Options

Throttled Engine Analysis

Weight Breakdown Statement

Cost Modeling

REDTOP-2 Capabilities

REDTOP-2 Input Screen REDTOP-2 Output Screen

SpaceWorks Engineering, Inc. (SEI)www.sei.aero

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www.sei.aero

Business Address:SpaceWorks Engineering, Inc. (SEI)1200 Ashwood ParkwaySuite 506Atlanta, GA 30338 U.S.A.

Phone: 770-379-8000Fax: 770-379-8001

Internet:WWW: www.sei.aeroE-mail: info@sei.aero