alternative architectures - direct - steve metschan (pdf, 26.9 - nasa
TRANSCRIPT
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DIRECT – Safer, Simpler and Sooner
Presentation before theReview of U.S. Human Space Flight Plans
CommitteeWashington DC, June 17th 2009
www.directlauncher.com
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DIRECT Implements the Policy within the Available Budget
Develop a heavy-lift launch vehicle using the personnel and infrastructure of the Shuttle
Minimize the Gap between the Shuttle retirement and its replacement
Learn how to mitigate the effects of space on the humans
Returning Americans to the Moon no later than 2020
Build the base for human surface missions to Mars on a timetable that is technically and fiscally possible
2005 NASA Authorization Act
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What is Jupiter?
Download from: http://www.directlauncher.com/media/video/STS_to_Jupiter-246.wmv
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National Launch System1992
Morton-Thiokol1978
Jupiter-DIRECT2006
Jupiter ‘is’ the Historic NASA STS Derived Approach
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1000+ pages detailing how to the utilize the existing infrastructure for an Inline design
The Jupiter Core Booster has Already Passed a NASA PDR
Minor Modifications for Loads Uses Existing Tooling
Uses Existing Factory Uses Existing Transportation
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Jupiter Builds upon Existing STS Hardware
New 5-Seg. SRB
New J-2X Engine
New Configuration
New Infrastructure
New Upper Stage
Existing 4-Seg. SRB
Existing SSME Engines
Existing Configuration
Existing Infrastructure
No Upper Stage
Operational Date
DIRECT Closes the Gap within the Current Budget
Ares-I
STS
Jupiter-130
$8.3 Billion$14.4 Billion*
March 2017
Total Development Cost
September 2012
*GAO Figure
$14.4 Billion for system that is less
capable than anEELV
$8.3 Billion for system that is much more capable than
an EELV
Orion is the Pacing Item not the Launch
System
Limited Orion Lunar Class Orion
Safety Requirements Reduced
Safety Requirements Achieved
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DIRECT Creates New Capabilities at a Lower Cost
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Two Different Launch Systems “Busts the Budget”
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DIRECT’s One Launch System Comfortably Fits the Budget
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DIRECT Eliminates the Workforce & Flight “GAP” at KSC
• Stretching out the shuttle flights will provide a safer transition • The STS Workforce is a asset for the Jupiter not a liability like with Ares• 12 IOC Jupiter vs. 1 Ares flight thru March 2017• The Jupiter-130 can fly 50mT of mission payload with every crew
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DIRECT Improves Mission Safety, Not Just Launch Safety
The Majority of Risk is Directly Related to the Mission not the Launch
The Elimination of key Safety Systems and Redundancy due to Ares-1 Limited Capability has Significantly Lowered Overall Mission Safety
Jupiter Restores Orion’s Safety, Capability while Speeding up Development and Lowering Cost thru Reusability
Launch Risk
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Jupiter Opens New Classes of Space Exploration Missions
Mars Sample Return Advancing Mars EDL
JWST Service & Upgrade
Discovering Other Earths in the Galaxy
Find New Life in the Solar
System
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Jupiter Opens New Classes of Earth Focused Missions
Space Solar Power
Earth ClimateMonitoring
Defense
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Jupiter will Lower the Cost to Orbit Significantly over STS
81mT/yr
*FY2009 Dollars at 5 Launches per Year
$32,385/kg
Payload
Cost11%
19%
11%23%
18%
18%
External TankSRB/SRMEnginesLaunch OpsOrbiterMission Ops
$2.6 Billion/yr*
Current STS
14%
19%
19%19%
Core StageSRB/SRMEnginesLaunch Ops
$1.9 Billion/yr*
Jupiter-130 CaLV
389mT/yr
72%
$4,815/kg
480%
Cost Effectiveness
6.7 Fold Improvement
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Jupiter will Also Lower the Cost of Spacecraft
Ground Integrated
One Launch
Space Integrated
>60 launches
“I hope we’re smart enough that we never again try to place such a large system in orbit by doing it in twenty-ton chunks.”*
>$100 Billion< $1 Billion
*NASA Administrator Dr. Griffin, Space Transportation Association, 22 January 2008
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The ESAS Appendix Confirms our Lunar Performance
ESAS Appendix 6:LV-25 + S1A
ESAS TLI Performance 74.3mTCxP Requirement: 71.1mT
A requirement the Ares-1 and Ares-5 still can’t meet.
NASA own leaked study proves that DIRECT approach has more than enough performance.
“The claims for the direct launcher we can't justify based on laws of physics.”
-NASA Associate Administrator Dr. Gilbrech toHouse Committee of Science and Technology, 3rd April, 2008
Page 57
Page 71
Identical to the :Jupiter-234 (SSME/RL-60)
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What About the Performance Needed for Mars?
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Wernher Von Braun Figured out Performance 46 Years Ago
“We found the Tanking Mode substantially superior to the Connecting Mode. The
performance margin could be enlarged almost indefinitely by the use of additional tankers.”
-Dr. Wernher Von Braun June 7, 1962
Most of the Mass Needed for a Mars Mission is Propellant
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Propellant Depots are the Bridge to Long Range Exploration
Flexible and Extensible Mission Designs
~70% of the Mission Mass is Open for Commercial & International Supply
Builds the Infrastructure needed for Leveraging Lunar Resources
Enables Reuse of Expensive Spacecraft
Amplifies the Capabilities of all Missions by Partner Nations
Negates the Need for Super Heavy Lift like the Ares-5
The DIRECT plan meets the advocates of an exclusive EELV/COTS approach more than half way
With more than enough demand to max out their existing facilities
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1) Minimize the gap in US based access to ISS2) Increase crew safety and mission success3) Leverage the existing infrastructure & workforce4) Build on the work already done5) Fit the near and long term budget6) Support new manned & unmanned missions7) Attract international participation8) Spur innovation and commercial competition
DIRECT efficiently addresses all the issues before the Commission within the limited time and budget that we have
Even now DIRECT is still our Best Option to:
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Appendix
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Why DIRECT is Important
America is about to experience the longest operational “GAP” since the Space Age began
KSC will suffer the most if we repeat the mistakes of the past and continue to dismantle America’s Second Heavy Lift System and Workforce
We must prevent a repeat of what happened the last time we shut down an operational system without a replacement
Fortunately thirty years ago NASA engineers designed a Shuttle Derived Heavy Lift Vehicle that will solve today’s problems within budget
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Jupiter is a More Capable & Safer Shuttle Replacement
ISS Service & Upgrade
Lunar Capable Orion
Hubble Service& Upgrade
Safer & Reusable Orion
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Jupiter Removes the Limits of Current Launch Systems
Cost overrun is now at 3x the launch cost
Cost overrun is now at 7x the launch cost
Jupiter Removes the Mass, Diameter and Volume Limits
Volume & Diameter Limited
Mass & Heat Shield Diameter Limited
Jupiter-130 (Ares-3)
Up to 12 meter
77mT3.5x
14x Volume, 2.5x Diameter
Jupiter-241 (Ares-4)
105mT
4.5x
5 meter
25mTEELV
JWST
MSL
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DIRECT Provides a Smooth Transition from the Ares
BoeingAres-1 Upper Stage
Pratt & WhitneyRocketdyne
Upper Stage Engine(J-2X)
ATKSolid Rocket
Booster
Current Contractors
BoeingInstrument Unit
Possible DIRECT Contractors
Pratt & WhitneyRocketdyne
Main Engine (SSME)
BoeingJupiter Upper Stage
Altair?
Pratt & WhitneyRocketdyne
Upper Stage Engine(J-2X/RL-10/RL-60)
Common Core Booster
Jupiter-130 Jupiter-24x
Payload Fairing?
Common Core Booster?
Aft Thrust Structure?
Lockheed MartinOrion
ATKLaunch Abort System
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DIRECT ‘s Proven Heritage Improves Safety, Cost and Time
Unproven 5-Seg. SRB
Unproven J-2X Engine
Proven 4-Seg. SRBdemonstrated 1 in 250
reliability
Proven SSME Enginesdemonstrated 1 in 362
reliability
Ares-I
STS
Jupiter-130
Sub-Orbital Staging Event All Engines are Ground Lit
Proven Thrust Oscillation Mitigation
Unproven Thrust Oscillation Mitigation
Proven SRB StagingUnproven SRB Staging
Unproven Dynamic Environment
Proven Dynamic Environment
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DIRECT Closes the Flight, Workforce and Performance Gap
Tooling is in place to begin construction of the Jupiter Core right now
Two-year Shuttle Extension to 2012 results in a seamless transition between Shuttle and the Jupiter/Orion Systems
The Shuttle workforce isn’t an additional expense when you actually need their skills
Jupiter-130 by using existing SSME requires no engine developments
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DIRECT Transforms the ISS into a Bridge to the VSE
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The ISS has a New Life as a Platform for Testing Habitats
ISS v2.0
Near Earth Object Mission
Lunar Base
MarsBase
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The Jupiter-130 Protects All Our Options Going Forward
Jupiter-130
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One Option Protected is Breakthrough Missions Beyond Earth
Jupiter-246
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Jupiter-241 (SSME/J-2X)
Jupiter-241
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“The most obvious split involves launching two identical vehicles”
We agree 100% with the agency that one Launch System is Superior.
“However… [this] is vastly over designed for ISS logistics.”
This is Constellation’s Single Point of Contention with DIRECT
“Costs are lower because of only one launch vehicle development”
“Recurring costs are amortized over a larger number of flights”
“Knowledge of system reliability is enhanced by … flight experience”
Without an upper stage the Jupiter is a close match for the ISS Crew + Logistics capabilities of Shuttle, only much safer and less expensive
NASA Admits the Benefits of One Launch System*
Regardless, commercial launch services should provide long term crew access and routine supply to ISS
The VSE and Jupiter’s primary focus is for beyond Earth missions
*NASA Administrator Dr. Griffin, Space Transportation Association, 22 January 2008
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Jupiter Enables an Apollo-8 Mission by 2014
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Jupiter Enables an Apollo-8 Mission by 2014
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Senior NASA Management Assessment of DIRECT is Wrong
Download at: www.directlauncher.com
“It’s got to get past the performance gate. If it
doesn’t, it doesn't make sense to look any further.”
-Steve Cook (NASA Ares 1 Project Manager) Interview
in Space News July 2008
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Engineering Experts Disagree with Senior NASA Management
“The Jupiter upper stage weight is very reasonable,
I would even call it conservative”
-Bernard Kutter,Manager of Advance Programs ULA
Popular Mechanics – Feb 09, p 57
DIRECT
Implements the Policy
Fits the Budget
Has Greater Performance than Ares
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Jupiter-24x (EDS) +Jupiter-140 (Crew)
Jupiter-24x (EDS) + Jupiter-24x (Crew)
Staged TLI (Requires LSAM Redesign)
Single TLI (LSAM Design Retained)
Ares-1 & Ares-5Low Performance
Very High Cost
DIRECT Performance and Cost Trade SpaceU
sefu
l Mas
s on
a T
LI, M
t
Jupiter Upper Stage Mass Margin over Centaur Class Upper Stage
Propellant Depot
5-Segment
5-Segment
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DIRECT’s Phase 2 Baseline EOR-LOR Lunar Architecture
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Expanded Performance via a Propellant Depot Architecture
Opens the Door to Both Commercial Launch Services and International Participation
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EOR-LOR with Staged TLI
Minimizes Descent Stage Size and maximizes Delivered Payload
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EML Architecture
Optimal Staging Architecture for future Lunar ISRU Propellant Supplies
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The Jupiter Core is the Path that Leads to all Better Options
i) EDS Performs LOI, LSAM DM is Cryogenicii) LSAM Performs LOI, LSAM DM is Cryogeniciii) CEV Performs LOI, LSAM DM is Cryogeniciv) EDS Performs LOI, LSAM DM is Hypergolicv) LSAM Performs LOI, LSAM DM is Hypergolicvi) CEV Performs LOI, LSAM DM is Hypergolicvii) Staged Descent
Spacecraft Options
Option 1: J-246 CLV + J-246 EDS (SSME/RL-10B-2)Option 2: J-244 CLV + J-244 EDS (SSME/RL-60)Option 3: J-241 CLV + J-241 EDS (SSME/J-2X)Option 4: J-130 CLV + J-246 EDS (SSME/RL-10B-2)Option 5: J-130 CLV + J-244 EDS (SSME/RL-60)Option 6: J-130 CLV + J-241 EDS (SSME/J-2X)Option 7: J-130 Heavy CLV + J-246 Heavy EDS (SSME/RL-10B-2)Option 8: J-130 Heavy CLV + J-244 Heavy EDS (SSME/RL-60)Option 9: J-130 Heavy CLV + J-241 Heavy EDS (SSME/J-2X)Option 10: J-130 Heavy CLV + J-246 Heavy EDS (SSME/RL-10B-2)Option 11: J-130 Heavy CLV + J-244 Heavy EDS (SSME/RL-60)Option 12: J-130 Heavy CLV + J-241 Heavy EDS (SSME/J-2X)
Launch System Options
A) EOR-LORB) EOR-LOR + DepotC) EOR-LOR Staged TLID) EML-1E) LOR-LORF) Lunar ISRUG) EML-1 + Depot
Architecture Options First Destination Optionsi) Moonii) Near Earth Objectiii) Mars Orbitiv) Mars Surface
And All 2,352 Options- cost less
- have higher performance- can be fielded sooner
Than Ares
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Jupiter Enables an Efficient Clean Pad Approach
Launch system and payload are both fully integrated in the VAB
The Clean Pad approach enables a “14 Days at the Pad” launch cycle
Fixed tower elements already fabricated thanks to Ares-1
Ares-1 TowerMLUT
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Shuttle-C Continues all the Inefficiencies of the Shuttle
Sub-Orbital Staging EventPayload Carries the Weight of OrionMust Human-rate an Upper StageMust Human-rate an Upper Stage Engine
Unsafe Crew PositionExtensive Integration at the Pad
Two Different Systems, Core + Side mount
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The Critical Decisions before America Right Now
Ares-I/V
No
EELV/COTS
Yes
DIRECT
YesDo we continue
United States access to the ISS ?
Do we save the United States’ second Heavy Lift system ?
No No Yes
Do we remain the leading space faring
nation ? No No Yes
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DIRECT Continuously Increases our Exploration Capability
Surface Access
Space Habitat
EELV-Upper Stage
Orion
Jupiter Core
NewHorizons
LunarSortieNEO
Jupiter-Upper Stage
Jupiter
New ISSOptions
EELV - 5x
NewMissions
Up to 14x Volume &Mass 2x
Propellant Depot
Mars EDL
MarsMars
Precursor
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DIRECT Roadmap09 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35
5-10 ton Lunar Surface Delivery 15 ton Lunar Surface Delivery Mars EDL System50 ton Lunar Surface Delivery
Mars Ascent VehicleMars EDL System
AltairOrion
Space ShuttleOrbiterSRB &External Tank
Jupiter-130 (Ares-3) 50 ton Medium Lift with Large Volume CapacityJupiter-246 (Ares-4) 100 ton Heavy Lift with Large Volume Capacity
EELV Human Launch CapabilitiesEELV Launch Capabilities
10-25 ton DoD Satellites10-25 ton NASA Satellites & Probes10-25 ton Commercial Payloads
Commercial Refueling (400-800 tons Per Year)
International Refueling (400-800 tons Per Year)
International Space StationLong Duration Habitat – Extend ISS Life
Long Duration Habitat – NEO/Deep Space TransportLong Duration Habitat – Lunar Surface Habitat
Long Dur Hab – Mars TransportLong Dur Hab – Mars Habitat
Lunar Surface AccessLunar Surface Equipment
Lunar Surface ISRUMars & NEO ISRUMars Surface Equipment
Mars Surface Access
COTS Launch CapabilitiesCOTS Human Launch Capabilities (Phase D)
Propellant Depot EML & SEL Support
HubbleUltra High Resolution “Other Earths” Detection Space Telescope
James Webb Servicing
50 ton Class 100 ton Class Heavy Lift / High dV / Large Volume Robotic Missions
Servicing
NEO Mission Opportunities
ShuttleRetires
1st
Crew1st ISSCrew
NEOPrecursor
1st LunarLanding
NEO CrewOpportunity 1
NEO CrewOpportunity 2
Mars Crew Landing
“Apollo 8”Flyby
6-monthCrew Mission
1st LunarLanding
Mars EngineTests at Moon
Small Mars Sample Return (via Jupiter-232)
Large Mars Sample Return (via Jupiter-232 + Depot)
Un-CrewedMars Test
Mars CrewLanding
NA
SA
Com
mercial
InternationalE
xploration
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www.directlauncher.com
The Next 3 Months will Determine the Next 3 Decades
“America is too great for small dreams” - Ronald Reagan
Do we want to be the “world’s leading space faring nation”?- John F. Kennedy
Fifty years after the Space Age began, America must again answer the same question….
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DIRECT - Phase 1
ISS and LEO Operations
Launch Vehicle Option 1
Jupiter-120
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DIRECT - Phase 1
ISS and LEO Operations
Launch Vehicle Option 2(Recommended)
Jupiter-130
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DIRECT - Phase 1
ISS and LEO Operations
Launch Vehicle Option 3
Jupiter-120 Heavy
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DIRECT - Phase 1
ISS and LEO Operations
Launch Vehicle Option 4
Jupiter-130 Heavy
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DIRECT - Phase 2
Exploration Operations
Launch Vehicle Option A
Jupiter-241(J-2X)
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DIRECT - Phase 2
Exploration Operations
Launch Vehicle Option B
Jupiter-244(RL-60)
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DIRECT - Phase 2
Exploration Operations
Launch Vehicle Option C
Jupiter-246(RL-10A-4-2)
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DIRECT - Phase 2
Exploration Operations
Launch Vehicle Option D(Recommended)
Jupiter-246(RL-10B-2)
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DIRECT - Phase 2
Exploration Operations
Launch Vehicle Option E
Jupiter-247(RL-10A-4-2)
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DIRECT - Phase 2
Exploration Operations
Launch Vehicle Option F
Jupiter-241 Heavy(J-2X)
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DIRECT - Phase 2
Exploration Operations
Launch Vehicle Option G(Alternative Recommendation)
Jupiter-244 Heavy(RL-60)
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DIRECT - Phase 2
Exploration Operations
Launch Vehicle Option H
Jupiter-246 Heavy(RL-10A-4-2)
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DIRECT - Phase 2
Exploration Operations
Launch Vehicle Option I
Jupiter-246 Heavy(RL-10B-2)
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DIRECT - Phase 2
Exploration Operations
Launch Vehicle Option J
Jupiter-247 Heavy(RL-10A-4-2)
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