# Presentation: 177789

## September 2005

**September 2005**

***MSFC and Exploration:******Our Path Forward***

## A Bold Vision for Space Exploration

**Complete the International Space Station**
**Safely fly the Space Shuttle until 2010**
**Develop and fly the Crew Exploration Vehicle no later than 2014 (goal of 2012)**
**Return to the Moon no later than 2020**
**Extend human presence across the solar system and beyond**
**Implement a sustained and affordable human and robotic program**
**Develop supporting innovative technologies, knowledge, and infrastructures**
**Promote international and commercial participation in exploration**

***“******It is time for America to take the next steps.***
***Today I announce a new plan to explore space and extend a human presence across our solar system. We will begin the effort quickly, using existing programs and personnel. We’ll make steady progress – one mission, one voyage, one landing at a time”***
***President George W. Bush – January 14, 2004***

## NASA’s Exploration Roadmap

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**Lunar Heavy Launch Development**

**Earth Departure Stage Development**

**1st Human CEV Flight**

**7th Human Lunar Landing**

**Robotic Precursors**

***Mars Development***

**Lunar Lander Development**

**Surface Systems Development**

**Commercial Crew/Cargo for ISS**

**Space Shuttle**

***Lunar Outpost Buildup***

**CEV Development**

**Crew Launch Development**

## Meet all U.S. human spaceflight goals
Significant advancement over Apollo
Double the number of crew to lunar surface
Four times number of lunar surface crew-hours
Global lunar surface access with anytime return to the Earth
Enables a permanent human presence while preparing for Mars and beyond
Can make use of lunar resources
Significantly safer and more reliable
Minimum of two lunar missions per year
Provides a 125 metric ton launch vehicle for lunar and later Mars missions and beyond
Higher ascent crew safety than the Space Shuttle
1 in 2,000 for the Crew Launch Vehicle
1 in 220 for the Space Shuttle
U.S. system capable of servicing the International Space Station
Orderly transition of the Space Shuttle workforce
Requirements-driven technology program
Annual “go-as-you-pay” budget planning

**Meet all U.S. human spaceflight goals**
**Significant advancement over Apollo**
- Double the number of crew to lunar surface
- Four times number of lunar surface crew-hours
- Global lunar surface access with anytime return to the Earth
- Enables a permanent human presence while preparing for Mars and beyond
- Can make use of lunar resources
- Significantly safer and more reliable
**Minimum of two lunar missions per year**
**Provides a 125 metric ton launch vehicle for lunar and later Mars missions and beyond**
**Higher ascent crew safety than the Space Shuttle**
- 1 in 2,000 for the Crew Launch Vehicle
- 1 in 220 for the Space Shuttle
**U.S. system capable of servicing the International Space Station**
**Orderly transition of the Space Shuttle workforce**
**Requirements-driven technology program**
**Annual “go-as-you-pay” budget planning**

***A Safe, Accelerated, Affordable and Sustainable Approach***

***The Right Architecture for the Challenge***

## We Are Creating Our Future

***We Are Creating Our Future***

## NASA’sExplorationArchitecture

***NASA’s******Exploration******Architecture***

## The Moon - the 1st Step to Mars and Beyond....

**Gaining significant experience in operating away from Earth’s environment**
- Space will no longer be a destination visitedbriefly and tentatively
- “Living off the land”
- Field exploration techniques
- Human support systems
- Dust mitigation and planetary protection
**Developing technologies needed for opening the space frontier**
- Crew and cargo launch vehicles (125 metric ton class)
- Earth entry system – Crew Exploration Vehicle
- Mars ascent and descent propulsion systems(liquid oxygen/liquid methane)
**Conduct fundamental science**
- Astrobiology, historical geology, exobiology,astronomy, physics

***Next Step in Fulfilling Our Destiny As Explorers***

## 4 – 5 assembly flights to low Earth orbit with a 100 metricton class launch system

Pre-deployed Mars surface outpost before the crew launches
Habitat and support systems
Power
Communications
Mars ascent / descent vehicle

180 day transit time to/from Mars
6 crewmembers
Dedicated in-space crew transit vehicle
Dedicated Earth entry system (CEV)

500 days on the surface 
Capability to explore large regions of the surface
Multi-disciplinary science investigations 
In-Situ resource utilization
Consumables:  Oxygen and water
Propellants: Liquid oxygen and methane

**4 – 5 assembly flights to low Earth orbit with a 100 metric****ton class launch system**
**Pre-deployed Mars surface outpost before the crew launches**
- Habitat and support systems
- Power
- Communications
- Mars ascent / descent vehicle
**180 day transit time to/from Mars**
- 6 crewmembers
- Dedicated in-space crew transit vehicle
- Dedicated Earth entry system (CEV)
**500 days on the surface **
- Capability to explore large regions of the surface
- Multi-disciplinary science investigations
- In-Situ resource utilization
- Consumables:  Oxygen and water
- Propellants: Liquid oxygen and methane

***How We Will Get to Mars***

## Paving the Way – Robotic Precursor Missions

***Paving the Way – Robotic Precursor Missions***

**Provide early information for human missions****to the Moon**
- Key knowledge needed for human safety andmission success
- Infrastructure elements for eventual human benefit
- Scientific results to guide human exploration
**May be evolvable to later human systems**
**Most unknowns are associated with the North****and South Poles – a likely destination for a ****lunar outpost**
**Key requirements involve establishment of**
- Support infrastructure – navigation/ communication, beacons
- Knowledge of polar environment – temperatures,lighting, etc.
- Polar deposits – composition and physical nature
- Terrain and surface properties

## Human Exploration Missions

**Crew *****to and from***** the lunar surface**
- 7 day missions to anywhere on the surface
- Crew rotation to lunar outpost
**Cargo *****to***** the lunar surface**
- One-way delivery of cargo to support longer
- 	duration missions
**Crew *****to and from***** Mars**
- 500 days on the surface
**International Space Station resupply capability – if commercial services****are unavailable**
- Ferry crew up and down
- Cargo up and down

## High Priority Lunar Exploration Sites

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**Aristarchus Plateau**

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**Oceanus**
**Procellarum**

**Mare Tranquillitatis**

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**Rima Bode**

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**Orientale Basin**
**Floor**

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**Mare Smythii**

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**Central Farside**
**Highlands**

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**South Pole-Aitken Basin**
**Floor**

**South Pole**

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**North Pole**

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***Near Side***

***Far Side***

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**Luna**

**Surveyor**

**Apollo**

## Possible South Pole Outpost

***Possible South Pole Outpost***

**The lunar South Pole is a likely candidate****for outpost site**
**Elevated quantities of hydrogen, possibly water ice (e.g., Shackelton Crater)**
**Several areas with greater than 80%****sunlight and less extreme temperatures**
**Incremental deployment of systems –****one mission at a time**
- Power system
- Communications/navigation
- Habitat
- Rovers
- Etc.

## Lunar Surface Activities

***Lunar Surface Activities***

**Initial demonstration of human exploration beyond earth orbit**
- Learning how to operate away from the Earth
**Conduct scientific investigations**
- Use the moon as a natural laboratory
- Planetary formation/differentiation, impact cratering, volcanism
- Understand the integrated effects of gravity, radiation, andthe planetary environment on the human body
**Conduct in-situ resource utilization (ISRU) demonstrations**
- Learning to “live off the land”
- Excavation, transportation and processing of lunar resources
**Begin to establish an outpost - one mission at a time**
- Enable longer term stays
**Testing of operational techniques and demonstration of technologies needed for Mars and beyond.....**

## Slide 15

## ISS – Moon – Mars Architecture Linkages

***ISS – Moon – Mars Architecture Linkages***

- Mars 6 crew departure and return

- 3 to 6 crew + payload
- Crew rotation
- ISS cargo

**Operations and Systems**
- Autonomous operations
- Partial gravity systems
- EVA, Surface mobility

**Crew Exploration Vehicle**

- 4 crew Earth-moon transfer

- Autonomous operations
- Partial gravity systems
- EVA, Surface mobility

- AR&D
- Autonomous operations

**Earth-to-Orbit Transportation**
- Safe crew launch
- 125 mt-class Heavy Payload Launch
- Large Volume Payloads

- Safe crew launch

- Safe crew launch
- Multiple, Heavy Payload Launches
- Large Volume Payloads

**Technology Maturation**
- ISRU Systems
- Oxygen-Methane propulsion (CEV SM. LSAM ascent)

- Oxygen-Methane propulsion (CEV SM)

- ISRU Systems
- Oxygen-Methane propulsion (CEV SM, Mars lander)

## A blunt body capsule is the safest, most affordable andfastest approach
Separate Crew Module and Service Module configuration 
Vehicle designed for lunar missions with 4 crew 
Can accommodate up to 6 crew for Mars and Space Station missions
System also has the potential to deliver pressurized and unpressurized 
	cargo to the Space Station if needed

5.5 meter diameter capsule scaled from Apollo
Significant increase in volume 
Reduced development time and risk 
Reduced reentry loads, increased landing stabilityand better crew visibility

**A blunt body capsule is the safest, most affordable and****fastest approach**
- Separate Crew Module and Service Module configuration
- Vehicle designed for lunar missions with 4 crew
- Can accommodate up to 6 crew for Mars and Space Station missions
- System also has the potential to deliver pressurized and unpressurized
- 	cargo to the Space Station if needed
**5.5 meter diameter capsule scaled from Apollo**
- Significant increase in volume
- Reduced development time and risk
- Reduced reentry loads, increased landing stabilityand better crew visibility

***How We Plan to Return to the Moon***Crew Exploration Vehicle

## Servicing the International Space Station

**NASA will invite industry to offer commercial crew and cargo delivery service to and from the Station **
**The CEV will be designed for lunar missions but, if needed, can service the International Space Station.  Annually, the CEV has the potential for:**
- 2 crew flights
- 3 pressurized cargo flights
- 1	unpressurized cargo flight
**The CEV will be able to transport crew to and from the station and stay for 6 months**

## Lunar Lander and Ascent Stage

**4 crew to and from the surface **
- Seven days on the surface
- Lunar outpost crew rotation
**Global access capability**
**Anytime return to Earth**
**Capability to land 21 metric tons of dedicated cargo **
**Airlock for surface activities**
**Descent stage:**
- Liquid oxygen / liquid hydrogen propulsion
**Ascent stage:**
- Liquid oxygen / liquid methane propulsion

## Rely on the EELV fleet for scientific and International Space Station cargo missions in the 5-20 metric ton range to the maximum extent possible.
New, commercially-developed launch capabilities will be allowed to compete.

The safest, most reliable, and most affordable way to meet exploration launch requirements is a 25 metric ton system derived from the current Shuttle solid rocket booster and liquid propulsion system.  
Capitalizes on human-rated systems and 85% of existing facilities.
The most straightforward growth path to later exploration super heavy launch.
Ensures national capability to produce solid propellant fuel at current levels.

125 metric ton lift capacity required to minimize on-orbit assembly and complexity – increasing mission success
A clean-sheet-of-paper design incurs high expense and risk.
EELV-based designs require development of two core stages plus boosters - increasing cost and decreasing safety/reliability.
Current Shuttle lifts 100 metric tons to orbit on every launch.
20 metric tons is payload/cargo; remainder is Shuttle Orbiter.
Evolution to exploration heavy lift is straightforward.

- New, commercially-developed launch capabilities will be allowed to compete.
**The *****safest, most reliable, and most affordable *****way to meet exploration launch requirements is a 25 metric ton system derived from the current Shuttle solid rocket booster and liquid propulsion system.  **
- Capitalizes on human-rated systems and 85% of existing facilities.
- The most straightforward growth path to later exploration super heavy launch.
- Ensures national capability to produce solid propellant fuel at current levels.
**125 metric ton lift capacity required to minimize on-orbit assembly and complexity – increasing mission success**
- A clean-sheet-of-paper design incurs high expense and risk.
- EELV-based designs require development of *two* core stages plus boosters - increasing cost and decreasing safety/reliability.
- Current Shuttle lifts 100 metric tons to orbit on every launch.
- 20 metric tons is payload/cargo; remainder is Shuttle Orbiter.
- Evolution to exploration heavy lift is straightforward.

***Launch Systems***

## Crew Launch Vehicle

**Serves as the long term crew launch capability for the U.S.**
**4 Segment Shuttle Solid Rocket Booster**
**New liquid oxygen / liquid hydrogen upperstage **
- 1 Space Shuttle Main Engine
**Payload capability**
- 25 metric tons to low Earth orbit
- Growth to 32 metric tons with a 5th solid segment

## Lunar Heavy Cargo Launch Vehicle

**5 Segment Shuttle Solid Rocket Boosters**
**Liquid Oxygen / liquid hydrogen core stage **
- Heritage from the Shuttle External Tank
- 5 space Shuttle Main Engines
**Payload Capability**
- 106 metric tons to low Earth orbit
- 125 Metric tons to low Earth orbit using Earth departure stage
- 55 metric tons trans-lunar injection capability using Earth departure stage
**Can be certified for crew if needed **

## Comparison with Saturn V

***Comparison with Saturn V***

- 55mT to Trans-Lunar Injection
- 67mT to TLI in Dual Launch Mode with CLV

- 51mT to Trans-Lunar Injection

**Cargo Launch Vehicle**

**Saturn V**

*5 F-1 Engines*

*5 Expendable SSMEs*

**Lander**

**S-IVB**

**S-II**

**S-IC**

**Lander**

**Earth Departure Stage**

**Core Stage**

**5 Segment RSRB**

**Crew**

## Earth Departure Stage

**Liquid oxygen / liquid hydrogen stage **
- Heritage from the Shuttle External Tank
- J-2S engines (or equivalent)
**Stage ignites suborbitally and delivers the lander to low-Earth orbit**
- Can also be used as an upper stage for low-Earth orbit missions
**The CEV later docks with this system and the Earth departure stage performs a trans-lunar injection burn **
**The Earth departure stage is then discarded**

## Recap of Major Launch/EDS Trades

**CLV Systems (11 system classes)**
- Atlas V-H and Delta IV-H
- RSRB Derivative (4 and 5 segment) with new upperstage(SSME, J-2S,new engine)
- New Core with new upperstage
- 5.4m and 8m
**Lunar Crew+Cargo (10 system classes)**
- SSME-based core with RSRB
- No upperstage (2 launch solution)
- Upperstage (1.5 launch solution)
- RD180-based core with Atlas V / Phase 2 Boosters with Upperstage
- RS68-based core with Delta/Atlas (below payload requirement) andRSRB Boosters with Upperstage
**Earth Departure Stage (22 options)**
- Commonality with CLV/Lunar upperstage
- Stage / engine thrust level
- All-up and split missions
- Delta-V splits (TLI, LOI, Plane Change)

## Potential Launch Vehicle FamiliesShuttle Derived (4-5 Segment RSRB)

**LEO **
**Crew**
*(20-32mT)*

**Inline Options**
- RSRB+Upperstage ISS Crew
- RSRB+SSME Core Lunar

**Lunar **
**Crew+Cargo**
*(74-106mT - 125mT w/upperstage)*

**Sidemount Options**
- RSRB+Upperstage Crew
- RSRB+SSME Sidemount Cargo

**LEO+Lunar **
**Crew**
*(20-32mT)*

**Lunar **
**Cargo**
*(67-80mT)*

## Potential Launch Vehicle FamiliesEELV Derived

**Atlas Phase 2/3**
- (New, Common 5.4m Core)

**LEO Crew ***(23mT)*

**Lunar Crew+Cargo ***(94mT)*

**Delta IV / Atlas V Heavy**
- (Existing + New 8m Core)

**Lunar Crew+Cargo ***(95mT)*

**LEO Crew ***(70mT)*

**Lunar Crew+Cargo ***(95mT)*

**Atlas Phase X**
- (New, Common 8m Core)

**LEO **
**Crew**
*(20-30mT)*

***or***

***Potential Launch Vehicle Families***EELV Derived

## Crew Launch Vehicle Description (25mT Payload)

**1.8Mlb Gross Liftoff Weight**
**283 ft in length**

**Upperstage**
**360klb LOx/LH****2**** stage**
**Aluminum-Lithium structures**
**5.5m diameter **
**Separate avionics system**

**First Stage**
**Derived from current Shuttle RSRM/B**
**4 segments**
**Recoverable**
**New forward adapter**

**Upperstage Engine**
**Derived from current Shuttle main engine (RS-25)**
**Altitude start capability**
**Expendable engine**

***Crew Launch Vehicle Description (25mT Payload)***

## Physical Size Comparison 

**Representations to Scale**

## Crew Launch Vehicle Design Assessment

***Crew Launch Vehicle Design Assessment***

**Design**
- Simple Designs with Heritage
- Minimal modifications to existing hardware
- RSRM Existing
- SSME Modified for Start
- SSME TVC with Orbiter Like APU
- SRB & TVC - Existing
- BSM - Existing
- Primary Structures
- AL-Li
- Avionics Heritage Hardware with New Software
- Fail Safe/Fail Operational
**Performance**
- Margins applied to reference trajectories
- Dispersion analyses have begun (3-dof & 6-dof)

**Controls**
- Controllability Assessment shows ActiveControl Required with Fins Not Required
- SSME & SRB within TVC Requirements
- RCS Sized with Storable Propellants
**Liftoff**
- Calculated Hold Down Loads within SRB Capability
**Separation**
-  Separation Dynamics and Clearances Analyzed with FORTRAN
**Abort**
- Simulations reflect Accelerations & Abort Regions Acceptable
**Recovery**
- Pilot & Drogue chutes need to be re-designed for supersonic operation

**Loads**
- CalculatedLoads within SRB designcapabilities
- Analyzed Active FlightControl with Flexibility
**Thermal**
- Nominal Trajectory Ascent Environments are not major design drivers
- Nominal Trajectory Re-entry environments will require localized increases in TPS thicknesses

## SSME Evolution for Exploration

**Phase I**
**(RS-25)**

**Phase II**
**(RS-25a)**

**Block 1/1a**
**(RS-25b)**

**Block 2a**
**(RS-25c)**

**Block 2**
**(RS-25d)**

**RS-25d  **
**Residual STS assets to support early launches.**

**Evolution **
**of engine during STS**

**Evolution of engine for exploration**

**RS-25e  **
**Minimal changes SSME for expendable applications**
- New Controller
- HIP bonded Main Chamber
- Flex ducts
- Simplified Tube wall nozzle
- Low Pressure Turbopump modifications

**RS-25f**
**Expendable SSME for****low cost manufacture****and operation**
- Channel Wall Nozzle
- Brazed Injector/Cast HGM
- High Pressure Turbomachinery simplifications

## Shuttle Derived RSRB is a Safe Boost Stage for Future Crewed Launch Systems

***Historically Low Rates of Flight Failure*** - Only the Challenger event marred a perfect record in 226 SRB flights. This results in a 0.996 launch success rate (combined 50 flights of the SRM and 176 flights of the RSRM).
***3. ******	******Design Robustness*** - Test results and physics-based simulations show the SRB launch vehicle design is robust and resistant to crew adverse catastrophic failure even for the most severe failure modes
***4. ******	******Non-Catastrophic Failure Mode Propensity*** - Solid rocket booster history and SRB design features suggest gradual failures that are less likely to threaten the crew
***5. ******	******Process Control  and Inspection*** - Proposed design offers benefits of propulsion suppliers with mature process control and inspection systems to minimize in-factory and-post manufacturing human error, a significant contributor to the currentlaunchers risk
***6. ******	******Failure Precursor Identification and Correction*** - The design capitalizes on the significant failure precursor identification and elimination benefit from recovery, and post flight inspection of the recovered SRBs
***It is a combination of these six factors that enable a launch vehicle that is forecasted to produce significant crew safety risk benefits***

***Shuttle Derived RSRB is a Safe Boost Stage for Future Crewed Launch Systems***

## NASA’s Exploration Architecture

***NASA’s Exploration Architecture***

**We need to build beyond our current capability to ferry astronauts and cargo to low Earth orbit.**
**Our steps should be evolutionary, incremental, and cumulative. **
**To reach for Mars and beyond we must first reach for the moon.**
***	***

***A safe, accelerated, affordable, and sustainable approach to achieving the Vision for Space Exploration.***

## Preparing Marshall for Success

## Preparing for Success

***Preparing for Success***

**DISCIPLINE**

**INTEGRATION**

**ACCOUNTABILITY**

## Marshall: Integral to NASA’s Missions

**Infusing our “Lessons Lived” into Developmental Engineering for Exploration**
- Human-Rated spaceflight programs and projects
- Scientific spaceflight programs, projects and scientific research
- Integrated scientific programs within the context of Human Space Flight

**Human****Space Flight****Systems**

**Scientific****Space Flight****& Research****Systems**

**Integrated****Systems**

**SSME**
**SRB**
**External Tank**
**ECLSS**
**ISS Construction**
**Saturn V**
**Lunar Rover**

**GBM/GLAST**
**GPB**
**Solar B**
**LIS/TRMM**
**TIDE/UVI**
**High-energy astrophysics**
**HEAO Series**

**ISS Research**
**Spacelab**
**Microgravity Science**
**BATSE/CGRO**
**Chandra**
**Hubble**
**Skylab**

***Marshall: Integral to NASA’s Missions***

## The Marshall Leadership Team

**MSFC Center Director -       D. King**
**Deputy Center Director  -    C. Chitwood**
**Associate Center Director- R. Henderson**

**Instrument &**
**Payload System**
**Department**
**S. Pearson**

**Propulsion**
**Systems**
**Department**
**P. Jones**

**Mission**
**Operations**
**Laboratory**
**A. McNair**

**Test Laboratory**
**P. Rodriguez**

**Materials &**
**Processes**
**Laboratory**
**R. Carruth**

**Engineering**
**Directorate**
**M. Rudolphi**

**Safety & Mission**
**Assurance **
**Directorate**
**J. Davis**

**Office of **
**Human**
**Capital**
**T. Washington**

**Office of **
**Center**
**Operations**
**J. Carter**

**Office of**
**Equal**
**Opportunity**
**A. Robinson**

**Office of the**
**Chief Counsel**
**W. Hicks**

**Office of the**
**Chief Information**
**Officer**
**J. Ellis**

**Office of the**
**Chief Financial**
**Officer**
**S. Foster**

**Office of **
**Procurement**
**S. Beale**

**Spacecraft & **
**Vehicle**
** ****Systems Department**
**J. Bullman**

**Office of**
**Strategic Analysis &**
**Communications**
**R. Henderson, acting**

**Shuttle **
**Propulsion **
**Office**
**R. Lightfoot**

**Science & **
**Mission Systems**
**Office**
**C. Chitwood, acting**

**Exploration Launch**
**Office**
**S. Cook**

***The Marshall Leadership Team***

- Pending NASA Headquarters approval

- Executive Staff

- B. Sackheim
- S. Cloud
- J. Bilbro
- C. Seabrook

## Exploration Launch Office

**First Stage**

- Chief Engineer

- Chief Engineer

- Chief Engineer

**Advanced Planning**

***Exploration Launch Office***

**SE&I**

**Upper Stage**

**Upper Stage Engine**

**Program Planning & Control**

**Chief Engineer**

**   ****Manager:  S. Cook****   Deputy:    D. Dumbacher**

**IMPLEMENTATION LEADERS:**
**Burt ****	****	****Davis****	****	****Kynard**
**Morris****	****	****Pollard****	****	****Reuter**
**Snoddy ****	****	****Sumrall****	****	****Tyson**

## Marshall:  Building the Systems to Explore

***Marshall:  Building the Systems to Explore***