Transformational Systems Concepts & Technologies for Future Space Missions

7/30/2019 Transformational Systems Concepts & Technologies for Future Space Missions

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ctober 2003 SRR_Page

TRANSFORMATIONAL SYSTEMS CONCEPTS & TECHNOLOGIESTRANSFORMATIONAL SYSTEMS CONCEPTS & TECHNOLOGIESFOR FUTURE SPACE MISSIONSFOR FUTURE SPACE MISSIONS

THE CHALLENGE BEFORE USTHE CHALLENGE BEFORE USto theto the

Space Resources RoundtableSpace Resources Roundtable

October 2003October 2003

John C. MankinsJohn C. MankinsAssistant Associate Administrator for Advanced Systems (act.)Assistant Associate Administrator for Advanced Systems (act.)

Chief Technologist, Space Flight EnterpriseChief Technologist, Space Flight EnterpriseOffice of Space Flight / NASA HeadquartersOffice of Space Flight / NASA Headquarters

Washington, D.C. 20546Washington, D.C. 20546


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INTRODUCTIONINTRODUCTION


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October 2003 TSCT_Overview_Page

2003 NASA Strategic Plan2003 NASA Strategic Plan

Stepping Stones to the FutureStepping Stones to the Future

We are developing a robust, integrated exploration strategy to guide our investments.We are developing a robust, integrated exploration strategy to guide our investments.Through our newThrough our new building blockbuildin

g block capabilitiesc

apabilitiesand scientific discoveries, we createand scientific discoveries, we create

stepping stonesst

epping stonesto the futureto the future


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INTRODUCTIONINTRODUCTIONStrategic Concept: Phased Exploration & DiscoveryStrategic Concept: Phased Exploration & Discovery

Sun-EarthSun-EarthL2L2

MarsMars(and its Moons)(and its Moons)

TheTheMoonMoon

Earth-MoonEarth-MoonL1L1

AsteroidsAsteroids

Low EarthLow Earth

OrbitOrbit High EarthHigh EarthOrbitOrbit

The Earths NeighborhoodThe Earths Neighborhood The Neighborhood ofThe Neighborhood ofMarsMars

Beyond...Beyond...

As Early as 2015 theAs Early as 2015 theCapability forCapability for

Initial 50-100 day Class Missions As Early as 2020-2025As Early as 2020-2025the Capability forthe Capability for

300-1000 day class InitialInterplanetary Missions

After 2025+ After 2025+

SustainableCampaigns

For Now..For Now..

GettingReady

With Diverse Opportunities to Enable

Continuing Commercial Development of Space


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CurrentConceptsandTechnologies

NewConcepts

New Technologies

CurrentConcepts and

NewTechnologies

New Concepts Using New

Technologies

RevolutionaryConcepts UsingBreakthroughTechnologies

Create InnovativeCreate InnovativeConcepts -- and Drive outConcepts -- and Drive outOpportunities/Needs forOpportunities/Needs forRevolutionary AdvancesRevolutionary Advances

in Technologyin Technology

New Conceptsand CurrentTechnologies

INTRODUCTIONINTRODUCTIONTechnology and Innovation Strategy -- EXAMPLESTechnology and Innovation Strategy -- EXAMPLES


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The View from the TopThe View from the Top

Systems Concepts

Technologies

Missions & Markets


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TSCT Technical Interchange MeetingsTSCT Technical Interchange Meetings


8/37October 2003 TSCT_Overview_Page

TSCT Technical Interchange Meeting SeriesTSCT Technical Interchange Meeting Series

New systems concepts and technologies are needed to achieveNASAs Vision and Mission

The Advanced Systems Office within the Office of Space Flight atNASA Headquarters (Code M-7) has undertaken a series ofbrainstorming town-hall type meetings at which to identifyoptions and opportunities for the future

The first Transformational Systems Concepts and Technologies(TSCT) Technical Interchange Meeting (TIM) was held at theAthenaem at the California Institute of Technology (CalTech) inPasadena, CA in January 2003

The focus was on identifying new concepts and technologies and vettingthe basic concept that a transformation in how the US approaches spaceexploration, research and discovery is possible

The second meeting was held at the National Space Science and

Technology Center (NSSTC) at the University of Alabama,Huntsville (UAH) in June 2003

The focus was on identifying and assessing candidate technology optionsand opportunities for the future

The 3rd TSCT TI was held at CalTech and at the NASA JetPropulsion Laboratory during October 14-17, 2003



TSCT TIM #3TSCT TIM #3Working Instructions / Ground RulesWorking Instructions / Ground Rules

TSCT TIM#3 will

Examine a baseline that uses the major technological elements ofan existing Design Reference Architecture (DRA)

Identify no fewer than 2-3 fundamentally different Alternate DesignArchitectures (ADAs)

Identify the key System Elements for both the DRA and the ADAs

Payloads including living systems will be considered as a key

trade for each OPTION and/or Design ArchitectureGround Rules

The time frame of interest for accomplishing the challenge is theperiod from 2010 to 2020 and beyond

New technology is acceptable--there is no presumption of riskaversion--however, risks must be characterized

The mission case is to be one of an ongoing campaign ofactivities Assume: one mission per year for not less than 10 years

Multiple applications for the Design Architectures is a goal

It is possible that a particular type of system may be useful inmeeting the requirements of more than one OPTION Alternatively, it is possible that a particular technology and/or subsystem will

be used to meeting the requirements of more than one OPTION



Potential Architecture CasesPotential Architecture Cases(Those elements of the Trade Space View Likely to Viable)(Those elements of the Trade Space View Likely to Viable)

DRA (ADA 1) - Reusable High Energy Solar/Cryo

Modular systems, high-energy electric and cryo propulsion, pre-positioning of logistics/fuel in space,highly autonomous, human capable, enabled by advanced technology OPTIONS 2 through 5

ADA 1b - Expendable NEP (Reusable Variation) Nuclear electric propulsion (NEP) replaces the SEP

OPTIONS 2-5

ADA 2a - Expendable Chemical (~Apollo-like) All-expendable, all-chemical with direct entry at Earth return, modest robotics, minimum use of new

technology

OPTIONS 1 - 2 ADA 2b - Expendable Cryogenic (Advanced Apollo)

All-expendable, cryogenic propulsion with direct entry at Earth return, all-up mission option, some useof new technology

OPTIONS 3-5

ADA 2c - Reusable Chem/Cryo - Aerobrake (~SEI-like) Reusable, all-chemical with aero-braking to orbit at Earth return, modest robotics, minimum use of new

technology; Variation on Reusable Aerobrake versus Expendable Ballute

OPTIONS 1 3-5

ADA 3 - Reusable ISRU, Surface Ops (Space Ops Variation) ADA 1, but with refueling on surface rather than in LLO enabled by ISRU (drops the SEP system);

Variation: launch of lunar propellants to LLO or L1

OPTIONS: 3-5

ADA 4 - Expendable NTR (Reusable Variation) Nuclear thermal propulsion (NTP) based, LOX-augmentation variation, fast-lunar trip enabling, no SEP,

no pre-positioning of logistics, requires cryo propulsion for excursion vehicle

OPTIONS 3-5

ADA 5 - Longer-Term Space Infrastructures Orbit-based slingers; maglev or rail guns on the Moon chemical for landing, RCS, etc.



Elements

Lunar ArchitectureL1 Architecture

GEO Servicing Architecture

BA

Low

Lunar

Orbit

Earth

Surface

Propulsive

Capture

XTV Refuels in

Lunar Orbit

Low

EarthOrbit

Crew Transfer

from OSP to

XTV

OSP

Crew

Launch

XTV Refuels in

Lunar Orbit

Solar Electric

Stages & Prop

Tankers Spiral

to LLO

Solar Electric

Stages Spiral to

LEO

Descent Ascent

Propellant Launches

(Qty TBD)

XTV Fuels

in LEO

OSP Crew

Landing

Outbound Leg

Landing Leg

Return

Leg

Crew Transfer

to OSP

LEO Tanker

and OSP

OSP OSP OSP

Propellant

Tankers

B

A

B

A

A

B

A

B

Plus MissionsPlus Missions

Alternate Design Architecture 1Alternate Design Architecture 1

GEO

Earth

Surface

Propulsive

Capture

XTV Refuels at

GEO

Low

Earth

Orbit

Crew Transfer

from OSP to

XTV

OSP

Crew

Launch

Solar Electric

Stages Spiral to

LEO

Propellant

Launch

XTV Fuels

in LEO

OSP Crew

Landing

Outbound Leg

Return

Leg

Crew Transferto OSP

LEO Tanker

and OSP

On-DemandPropellant

Tanker

OSP OSP OSP

GEO ASSET

Earth-

Moon

L1

Earth

Surface

Propulsive

Capture

XTV Refuels at L1

Low

Earth

Orbit

Crew Transfer

from OSP to

XTV

OSP

Crew

Launch

Solar Electric

Stages & Prop

Tankers Spiral

to L1

Solar Electric

Stages Spiral to

LEO

Propellant Launches

(Qty TBD)

XTV Fuels

in LEO

OSP Crew

Landing

Outbound Leg

Return

Leg

Crew Transfer

to OSP

LEO Tanker

and OSP

Propellant

Tankers

Sun-

Earth

L1

OSP OSP OSP

Observatories to-from

L via low-energy1

transfers



Why Reusable Systems? Cost per Mission ImprovementWhy Reusable Systems? Cost per Mission Improvement

Parametric Comparison of Levels ofParametric Comparison of Levels ofExpendabilityExpendability

Reusable Space Systems critical to reducing excessive expendable hardware costs

of Apollo-derived architectures.

111

RECURRINGBeyond LEO MISSION HARDWARE COST($,M)

111 111 111 111 1111 1111 1111 1111 1111

FLIGHTHARDWAREDRYMASS

(KG,1111

s)

11

5 5

11

111

111

111

Typical Dry Mass for a Human Lunar Mission - LOWER Limit

Typical Dry Mass for a Human Lunar Mission - UPPER Limit

% EXPENDED11 % EXPENDED11

% EXPENDED11

% EXPENDED11

% EXPENDED111

% EXPENDED1

Sustainable ApproachSustainable ApproachUpdated ApolloUpdated Apollo

FOR CONSUMED MISSION HARDWAREAVERAGING ABOUT $ , / kg11111 NOT

INCLUDING NEW CAPABILITY

Rangeof

Interest



Notional Example Comparing Lunar MissionNotional Example Comparing Lunar MissionHardwareHardware

Updated Apollo

Sustainable Approach

Initial M-1 M-2 M-3 M-4 M-5 M-6 M-7 M-8 M-9 M-10

Initial M-1 M-2 M-3 M-4 M-5 M-6 M-7 M-8 M-9 M-10

7x



Why Intelligent Modular Systems? Cost-RiskImprovement

Notional Example: Modular Systems in FutureNotional Example: Modular Systems in FutureMissionsMissions

Comparison of Cost-Risk Cases(Integrated vs. Modular Type w/ % "1 11

$( , . )111111

$( , . )111111

$( , . )111111

$( , . )111111

$( , . )111111

$( , . )111111

$-

Cost

($,

M)

Integrated $( , . )5 555 55 $( , . )111111 $( , . )5 555 55 $( , . )111111 $( . )11111

Modular $( , . )111111 $( . )11111 $( . )1111 $( . )1111 $( . )111

Class A ( %11

HW)

Class B ( %11

HW)

Class C ( %11

HW)

Class D ( %11

HW)

Class E ( %11

HW)

Mission Cost-Risk(Launch @ $5,000/kg, 95% Reliability)

Case A: Integrated

System systemmass @ ~25 t

Case B: ModularSystems systemredundancy @ 25%

Redundant, modular subsystems and interfaces critical to reliability of

reusable in-space systems. May also reduce non-recurring costs.



Mass Produced Aerospace Systems

Cost Estimation Relationship(s)

2000PriceperP

ound,

AerospaceS

ystems($/kg)

(Sys

temP

urchasedHardwareCostsOnly)

Number Aerospace Systems Manufactured/Sold

4000

6000

8000

10000

12000

14000

16000

250 500 750 1000 1250 150050

@ ~$10,000/kg for 125 IRIDIUM Constellation Satellites

@ ~$40,000-$ 80,000/kg Typical On order 5-10 Units GEO Constellation Satellites

@ ~$200,000/kg and greater One-of-a-kind Systems (e.g., ISS)

@ 1000 Boeing 747s

@ ~$40,000/kg for ~20 Units B-2 Bombers

ASSERTION:When assessing manufacturing

in Large Lot Sizes,

Space Systems/Subsystemsshould be cost-estimatedaccording to this type of curve

This suggests a strategicline of attack on the

challenge of AffordableSpace Systems

@ ~$4,000/kg for ~324 TELEDESIC Constellation Satellites



Why Autonomous / Intelligent Systems? Reduced OpsWhy Autonomous / Intelligent Systems? Reduced OpsCostsCosts

Parametric Comparison of Levels ofParametric Comparison of Levels ofStaffingStaffing

Intelligent systems critical to low recurring operations costs.

1

LOWER LIMIT ON OPERATIONS COST PER MISSION ($,M)[DUE TO MISSION OPERATIONS PERSONNEL COSTS ONLY]

111 5 5 5 111 111 111 111 111 111

T

OTALNUMBEROFBeyon

dLEOMISSIO

NS/YEAR

1

1

1

1

1

1

11

Assumes a Personnel Cost of$ , / Full-Time Equivalent 111111Includes Operations and

Supporting Engineering, etc.

1

Operations@ , People11111

Operations@ , People1111

Operations@ , People1111Operations

@ , People1111Operations@ People111

Rangeof

Interest

~ BeyondLEOMission EveryYear1

e.g.,~ BeyondLEOMissionsEveryYear1



High-energy electric propulsion critical to reducing excessive propellant mass

of reusable architectures.

InitialMass

inLEO

InitialMassinLEO

50 mT50 mT

100 mT100 mT

150 mT150 mT

200 mT200 mT

250 mT250 mT

300 mT300 mT

Apollo-TypeApollo-TypeExpendable,Expendable,

Chemical, with DirectChemical, with DirectEntryEntry

SustainableSustainableReusable, withReusable, withHigh EnergyHigh Energy

ModularModular

Excessive MassExcessive MassReusable, withReusable, with

Chemical PropulsionChemical Propulsion

> 400 mT> 400 mT

350 mT350 mT

Why High Energy Space Systems? Reduced Initial MassWhy High Energy Space Systems? Reduced Initial Massin LEOin LEO

Parametric Comparison of Major OptionsParametric Comparison of Major Options



Pre-Deployment of Logistics/Propellants critical to Timely-Payload Deliveryperformance for reusable architectures.

Payload

Payload

5 mT5 mT

10 mT10 mT

15 mT15 mT

MEO and GEOMEO and GEO Libration PointsLibration Points Lunar OrbitLunar Orbit

NoneNone

Pre-DeploymentPre-Deployment

NoneNone


NoneNone


Why Pre-Deploy Logistics/Propellants? PerformanceWhy Pre-Deploy Logistics/Propellants? Performance

Parametric Comparison of Major OptionsParametric Comparison of Major Options



Other BenefitsOther Benefits

Go Anywhere in the Earths NeighborhoodGo Anywhere in the Earths Neighborhood

HRE_ _Mankins_ 1111 11September1111 Pre-Decisional / Internal Use Only

Mapping Delta-VelocitiesMapping Delta-Velocitiesin the Earthin the EarthssNeighborhoodNeighborhood

EarthEarth

LEOLEO

GTO

GEO

S-E L1

LLO

Lunar SurfaceLunar Surface

LTO Lunar Transfer Orbit

LLO Low Lunar Orbit

SE L1 Sun-Earth Libration Point L1

EM L1 Earth-Moon Libration Point L1

GEO Geostationary Orbit

GTO GEO Transfer Orbit

LEO Low Earth Orbit

V ~ km/s11

V Low-T~ , m/s1111

V~ m/s111

V~ - m/s111111

S-E L1

E-M L1E-M L1

V High-T~ , m/s1111

V Low-T~ , m/s1111

V High-T~ , m/s3 3 33

V Low-T~ . m/s3 3 33

V High-T~ m/s1111

V Low-T~ , m/s3 3 33

V High-T~ , m/s1111

V Low-T~ m/s111

V High-T~ m/s111

V Low-T ~ , m/s1111

V High-T~ , m/s1111

V High-T~ , m/s1111

V High-T~ , m/s1111

V Low-T~ , m/s1111

V High-T~ , m/s1111

V High-T~ , m/s1111

Working Notes

EML to trans-lunar trajectory1 ~ m/s555

Lunar Orbit Insertion ~ m/s111

Deorbit & Landing ~ m/s5555

Total ~ m/s1111



What capabilities can the Reusable Injection Stage and SEP Stage provide to

other potential missions?

Mission Max Payload

Capability w/ No

Refueling

Max Payload

Capability w/

Refueling

Reusable

Injection Stage(1)

DoD Mid-Inclination Orbit 178 kg 13,561 kg

GEO Payload Deployment 793 kg 13,993 kg

Lunar L1 Halo Orbit 2,793 kg 15,437 kg

Lunar Orbit 2,805 kg 15,445 kg

GPS Orbit 3,254 kg 15,778 kg

GEO Transfer Orbit 28,135 kg N/A

Lunar Surface Cargo Delivery(2) 15,733 kg 27,775 kg

Trans-Mars Injection(3) 17,794 kg -

SEP Stage(4) Lunar Orbit 33,015 kg 36,438 kg

Lunar L1 44,170 kg 46,971 kg

GEO Payload Deployment 46,259 kg 48,967 kg

Reusable Injection Stage Specs* SEP Stage Specs*Dry Mass = 5,240 kg (no landing gear) Dry Mass = 10,000 kg (Xe tankage not included)

Propellant Capacity = 29,217 kg Propellant Capacity = 19,151 kg

Isp = 460 s Isp = 3,000 s

Propulsive Capture for LEO Return Max. Power = 500 kW

Starting/Return Orbit: LEO, 500 km, 28.5o Starting/Return Orbit: LEO, 500 km, 28.5o

Notes:1. RIS returns to LEO via propulsive capture

2. SEP delivers RIS and payload to lunar orbit. RIS is expended on lunar surface.

3. Mars/Deep Space missions assume RIS is expended

4. SEP Stage outbound trip times limited to no longer than 270 days

Injection Stage Capabilities to Various C s1

1

1

11

11

11

11

11

-1 1 1 11 11 11 11 11 11 11 11 11 111 111 111

C (km11/s

1)

No

minalPayloadMass(,

kg)

1111

Lunar L1Escape

Mars

GEO

Assumes RIS is ExpendedAssumes RIS is Expended

Jupiter Pluto

*Element Specs consistent with Space-based XTV /

LEO Propulsive Capture / LOR Architecture

Other BenefitsOther Benefits

Candidate Applications / MissionsCandidate Applications / Missions



TSCT TIM#3: The ChallengeTSCT TIM#3: The Challenge

The following functional requirements are to be satisfied

For the LOWEST (Life Cycle) COST DELIVER from KSC -- using one or more types of launchers

Not part of the detailed challenge for this meeting

To anywhere on the Lunar Surface where the sun shineswith precision (99.5% reliability)

A safe, functional PAYLOAD, (pressurized or un-pressurized) of OPTION 1 -- 20 kg

OPTION 2 -- 100 kg OPTION 3 -- 500 kg

OPTION 4 -- 2,500 kg

OPTION 5 -- 12,500 kg

AndRETURN to low Earth orbit Either to 28.5, 400 km circular, or to ISS

A safe, functional PAYLOAD, (pressurized or un-pressurized) of OPTION 1 -- 2 kg

OPTION 2 -- 10 kg

OPTION 3 -- 500 kg

OPTION 4 -- 2,500 kg

OPTION 5 -- 12,500 kg

With a total stay on the Lunar surface of < 14 days


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Integrated Technology AssessmentIntegrated Technology Assessment

TSCT #3 Architecture-Critical TechnologiesTSCT #3 Architecture-Critical Technologies

Design Arch. Architecture-Critical Technologies

Modular, Reusable,SEP/Cryogen Prop.

DA -No.

DRA(ADA-1)

NEP, Modular,Reusable Cryogen

Prop Excursion

Re-startable,Reliable andThrottleable

Cryo Propulsion

ADA-1b

Chemical / Expendable/ StagedADA-2a

Cryogenic /Expendable/ StagedADA-2b

Chem-/Cryo-Propulsion with

AerobrakingADA-2c

ISRU Enabled, LunarSurface Refueling and

OperationsADA-3

Expendable NTRShuttle, Reusable

Cryo-Prop ExcursionADA-4

Far-Term SpaceInfrastructuresADA-5

Long-Lived,High-Power, Low

Mass SolarElectric Power

Long-Lived,High-Power EM

Propulsion

Long-Duration,Low-LossCryogen

Mgt/Storage/xfer

High-EnergyDirect Entry

CryogenManagementand Storage

High-EnergyAerobraking at

Earth Return

Lunar Surface

ISRU Systems

Lunar Surface

Power

Nuclear ThermalPropulsion

Advanced,Robust

Structural TetherConcepts

ElectromagneticMass Drivers

and/or MagLev

PlusVarious


Cryo Propulsion

Long-Lived,High-Power EM

Propulsion

Long-Lived,High-Power, Low

Mass NEP


Mgt/Storage/xfer

Re-startable,Reliable and

ThrottleableCryo Propulsion


Cryo Propulsion


Cryo Propulsion

CryogenManagementand Storage

High-EnergyDirect Entry


Mgt/Storage/xfer

Lunar SurfaceInfrastructure

Systems

Long-Duration,Low-Loss

CryogenMgt/Storage/xfer

Lunar SurfaceInfrastructure

Systems

High-EnergyAerobraking at

Earth Return


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Architecture Design AlternativesArchitecture Design Alternatives

TSCT #3 Major Options AssessmentTSCT #3 Major Options Assessment

Design ArchictureAlternatives

Success vis--vis CriteriaDA -No.

ADA-1

ADA-1b

ADA-2a

ADA-2b

ADA-2c

ADA-3

ADA-4

ADA-5

Modular, Reusable,SEP/Cryogen Prop.


Prop Excursion

Chemical / Expendable/ Staged

Cryogenic /Expendable/ Staged


Aerobraking

ISRU Enabled, LunarSurface Refueling andOperations


Cryo-Prop Excursion

Far-Term SpaceInfrastructures

Low R&D

Risk Applications Dev. Cost Ops CostBenefits

Very high technical risk and high cost during period chosen (2010-2020)

High risk and high cost during period chosen (2010-2020)

Cannot satisfy full range of applications, nor provide benefits comparable toother options; also, operations costs higher than reusable cases

Cannot satisfy full range of applications, nor provide benefits comparable toother options; also, operations costs higher than reusable cases

High risk and high cost during period chosen (2010-2020); cannot satisfy fullrange of applications nor provide full scope of benefits


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Integrated Technology AssessmentIntegrated Technology AssessmentCommon Technologies - Most Viable ArchitecturesCommon Technologies - Most Viable Architectures

TIM#3TIM#3Design Arch. Multi-Architecture Common TechnologiesDA -No.

ADA-1

Advanced Materials & Structural Concepts

ADA-1b

ADA-2a

ADA-2b

ADA-2c

ADA-3

ADA-4

ADA-5 Thermal Protection Systems

Cryogenic Fluid Management, Storage, Transfer

Modular, Reusable,

SEP/Cryogen Prop.


Prop Excursion

Chemical / Expendable/ Staged

Cryogenic /Expendable/ Staged


Aerobraking

ISRU Enabled, LunarSurface Refueling and

Operations


Cryo- Prop Excursion

Far-Term SpaceInfrastructures

High-Power Electric/Electromagnetic Propulsion

High-Energy Solar Electric Power

Hazard Avoidance and Precision Landing

Intelligent Vehicle/System Health Management

Space Assembly, Maintenance and Servicing

Reliable on-Board PMAD Systems

Attitude Control/GN&C

Computing and Communications

Habitation, EVA and Bioastronautics

Space Environmental Effects

Reusable, Throttling Cryogenic Propulsion


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TSCT TIM #3 Case StudyTSCT TIM #3 Case Study

Meeting the Earth Neighborhood TransportationMeeting the Earth Neighborhood Transportation


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Meeting the Earth Neighborhood TransportationMeeting the Earth Neighborhood TransportationChallengeChallenge

Synthesizing Concepts & Technologies (Proof ofSynthesizing Concepts & Technologies (Proof ofPrinciple)Principle)

O-2

OPTION 3OPTION 2 (1?)

O-3

O-4

O-5

OPTION 4 OPTION 5

Modular

Elements

Multiple

Payload Classes

Diverse Options


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Team-X Session on 16 October 2003Team-X Session on 16 October 2003

Updated Guidelines - Day 2Updated Guidelines - Day 2

P/L

P/L

P/L

V

V

V

P/L = Payload

V = Vehicle

Lunar Surface

Polar Site, Illuminated, 14 day duration

P/L

V

500 kg

2,500 kg

Case A

Case B

LOX/LH2 Chem

Type 1 Type 2

500 kg

2,500 kg

LOX/LH2 Chem

12,500 kgCase C

Rough

12,500 kg

LOX/LH2 Chem

100 kgCase D

Rough

100 kg

LOX/LH2 Chem

Configuration Options for ExcursionConfiguration Options for Excursion


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Configuration Options for ExcursionConfiguration Options for ExcursionVehicle(s)Vehicle(s)

Team-X Cases and Additional AlternateTeam-X Cases and Additional AlternateOptionsOptions

500 kg p/l Case

Alternate

500 kg p/l Case

2,500 kg p/l Case

Alternate

2,500 kg p/l Case

R bl C i T f V hi lR bl C i T f V hi l


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Reusable Cryogenic Transfer VehicleReusable Cryogenic Transfer Vehicle(RCTV)(RCTV)

Team-X CasesTeam-X Cases

Leverage

100 kg(Rough)

500 kg500 kg 2,500 kg2,500 kg

Value(1,000

$/kg

)

Payload

10

20

30

40

500

1,000

1,500

2,000

R(SC Wet / Payload) Value ($/kg-payload)

20 kg(N/A)

12,500 kg(N/A)


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Advanced Systems, Technologies, ResearchAdvanced Systems, Technologies, Researchand Analysisand Analysis

Ad d S t T h l i R h dAd d S t T h l i R h d


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FlightProjects

System Test,Launch &

Operations

System/SubsystemDevelopment

TechnologyDemonstration

TechnologyDevelopment

Research toProve

Feasibility

BasicTechnologyResearch

TRL 9TRL 9

TRL 8TRL 8

TRL 7TRL 7

TRL 6TRL 6

TRL 5TRL 5

TRL 4TRL 4

TRL 3TRL 3

TRL 2TRL 2

TRL 1TRL 1

BasicResearch

Researchand

TechnologyBase

TechnologyPush

Capability-

FocusedTechnologyDevelopment

and DemoPrograms

ApplicationsPull

e.g., SSEOBPR e.g., OAT,OBPR e.g., SFE, SSE, ESE,OAT e.g., Specific FlightProjects

Primary Emphasis of theASTRA Road Maps

AdvancedDevelopment

Programs

SystemSpecific

Advanced Systems, Technologies, Research, andAdvanced Systems, Technologies, Research, and

AnalysisAnalysisStrategic Technology Model forStrategic Technology Model forASTRA (1 of 2)ASTRA (1 of 2)

d d h l i h dAd d S T h l i R h d


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Advanced Systems, Technologies, Research, andAdvanced Systems, Technologies, Research, andAnalysisAnalysis

Work Breakdown StructureWork Breakdown Structure

1.01.0Systems Integration,Systems Integration,Analysis, Concepts &Analysis, Concepts &

ModelingModeling

ASTRAASTRA1.11.1

Program andProgram andSystems IntegrationSystems Integration 1.21.2

Mission and MarketMission and MarketStudiesStudies

1.31.3Advanced ConceptsAdvanced Concepts

StudiesStudies 1.41.4Technology -SystemsTechnology -Systems

AnalysisAnalysis1.51.5

System andSystem andInfrastructureInfrastructure

ModelingModeling

1.61.6

Technology andTechnology andSystems VerificationSystems Verificationand Validationand Validation

2.02.0Advanced TechnologyAdvanced Technology

DevelopmentDevelopment

4.04.0Supporting Research andSupporting Research and

TechnologyTechnology

3.03.0Systems-Level TechnologySystems-Level Technology

DemonstrationsDemonstrations

2.32.3Habitation, Bio-Habitation, Bio-

astronautics, and EVAastronautics, and EVA

2.42.4Space Assembly,Space Assembly,

Maint., and ServicingMaint., and Servicing

2.52.5Surface ExplorationSurface Exploration

and Expeditionsand Expeditions

2.62.6SpaceSpace

TransportationTransportation

Level 1: Top TierLevel 1: Top TierLevel 2: Strategic ThemesLevel 2: Strategic Themes

2.12.1Self-Sufficient SpaceSelf-Sufficient Space

SystemsSystems

2.22.2Space Utilities andSpace Utilities and

PowerPower

3.53.5SAMS DemosSAMS Demos

3.63.6Lunar/PlanetaryLunar/Planetary

Exploration DemosExploration Demos

3.13.1Technology DemoTechnology DemoDefinition StudiesDefinition Studies

3.23.2Tech. Flt. ExperimentTech. Flt. Experiment

AccommodationsAccommodations

2.82.8Information andInformation andCommunicationsCommunications

2.72.7In Space InstrumentsIn Space Instruments

and Sensorsand Sensors

3.33.3High-Energy SpaceHigh-Energy Space

Systems DemosSystems Demos

3.4_Modular3.4_ModularSpace Platforms andSpace Platforms and

Systems DemosSystems Demos

4.34.3Power/ThermalPower/Thermal

TechnologyTechnology

4.44.4Electronics andElectronics and

SensorsSensors

4.54.5Software, Computing,Software, Computing,

and Intelligenceand Intelligence

4.64.6Mobility andMobility andManipulationManipulation

4.14.1Advanced MaterialsAdvanced Materials

4.24.2Structures andStructures and

ControlsControls

4.84.8Basic Physical andBasic Physical andChemical ResearchChemical Research

4.74.7Advanced PropulsionAdvanced Propulsion

4.104.10TBDTBD

4.94.9

Biological ResearchBiological Research


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Many, DiverseCompeting

Technologies ata Low Level ofFunding -- All

AddressingApproximatelythe samefunctional

capabilities...

Starting Point:TRL 3/4

SeveralCompetingTechnologies at

a ModerateLevel of Funding

Goal: TRL 5

In Most Cases1 or 2 BestCandidate

Technologies ata Substantial

Level of Funding

Goal: TRL 6

Where Necessary,Technology Flight

Experiments TechnologyReady toSupport Decisionsto Proceed withDevelopment ofThe DesiredCapability...

Where Needed1 or 2 BestCandidate

Systems-LevelTechnology

Flight Demosat a Significant

Level ofFunding

Goal: TRL 7

Technologies Dropped orDeferred to Future

Application Opportunities

Number of CompetingTechnologies Being

Funded

Total Resources BeingInvested in a specific technology

TIME

Strategic Investment ElementsStrategic Investment ElementsFocusing on Enabling CapabilitiesFocusing on Enabling Capabilities


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ConclusionConclusion


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WhatWhat MightMight Be Accomplished?Be Accomplished?

Increased Available Powerat Reduced Cost for Earth

Neighborhood SpaceSystems

Extension of EffectiveOperational Lifetime for

Systems Beyond Low EarthOrbit

Improvement in FuelEfficiency forTransportation in theEarths Neighborhood

Reduction in Operationsand Logistics Costs

2- to 5- FoldFactors-of

Improvement

in Several KeyEarth

NeighborhoodSpace SystemsCapabilities*

Increase in the Scale ofSystems Beyond LEO(without New Launchers)

Space Science

Missions

* In conjunction withkey CollaborativeInvestments

New Infrastructures

What ELSE Might beAccomplished??

New Industries

Communications

Satellites

NationalDefenseSystems


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Keeping PerspectiveKeeping Perspective

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Transformational Systems Concepts & Technologies for Future Space Missions

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