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SpaceWorks Engineering, Inc. (SEI)www.sei.aero
1
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
SpaceWorks Engineering, Inc. (SEI)www.sei.aero
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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
SpaceWorks Engineering, Inc. (SEI)www.sei.aero
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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
SpaceWorks Engineering, Inc. (SEI)www.sei.aero
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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
SpaceWorks Engineering, Inc. (SEI)www.sei.aero
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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
SpaceWorks Engineering, Inc. (SEI)www.sei.aero
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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)
SpaceWorks Engineering, Inc. (SEI)www.sei.aero
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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)
SpaceWorks Engineering, Inc. (SEI)www.sei.aero
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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
SpaceWorks Engineering, Inc. (SEI)www.sei.aero
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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.
SpaceWorks Engineering, Inc. (SEI)www.sei.aero
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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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26
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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35
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
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