1. Architecture Team Industry Day Briefing 17 January, 2002

2. For Official U.S. Government Use Only ONE.011_Arch-2 Example Development Strategy DoD Variant NASA Variant  Option for Early Capability  To improve operations knowledge base for the next vehicle  To serve as technology test platform  To provide limited operational capability  Leads to full system capabilities in 2012-14  Converged Cargo/MSP Requirements  Modular variant for Human Space Flight 2002 – 06 ~2009 - ? 2012-2014  Ground and Flight Demonstrations  Risk Reduction  Operability  Long Term S&T

3. For Official U.S. Government Use Only ONE.011_Arch-3 Integrated Architecture Elements Launch Vehicle Systems Reusable Orbital Vehicles Payloads On-Orbit Transfer & Servicing ELV’s 2nd Gen RLVs 3rd Gen RLVs Upper Stages Re-fueling/ Servicing Crew Transfer Cargo Transfer Space Maneuver Vehicles Commercial Strategic Tactical Human Scientific Ground Facilities Orbital Transfer Vehicles Spaceport Automated Mission Processing

4. For Official U.S. Government Use Only ONE.011_Arch-4 System Classes Investigated TSTOAir LaunchELV-RLV Hybrid SSTO/ Combined Cycle Representative Concepts that Bound the Trade Space Near Far

5. For Official U.S. Government Use Only ONE.011_Arch-5 Operability, Reliability, & Affordability  All architectures will be evaluated for  Operability / Responsiveness  Safety / Reliability  Affordability  Performance / Design Reference Missions  Sensitivity studies are being performed to help USAF and NASA  Understand the impact of payload lift requirements  Identify the benefit that can be achieved from common NASA/USAF architectures

6. For Official U.S. Government Use Only ONE.011_Arch-6  Common Groundrules Max Axial Acceleration 3g’s for Manned and Side Mount Vehicles While Mated 5g’s for Unmanned Vehicle 650 psf Max Q for Winged Vehicles Mass Margin Allowing 35% Weight Growth Throttle for full engine out capability New LOX/LH2 and/or LOX/RP engines  2012 Cargo Variant 15-25 klbs to 100 nmi Circular 28.5° Payload Envelope 12 ft X 30 ft Cylindrical, External, Reusable, 9.65 klbs  2012 Crewed Variant 45+ klbs to 100 nmi Circular 28.5° Payload Envelope 15 ft X 55 ft Cylindrical, External, Reusable, 20 klbs Preliminary Sizing Assumptions

7. For Official U.S. Government Use Only ONE.011_Arch-7 2012 Vehicle Options: Optimized TSTO Description  Two Stages- Smaller stage delivers payload to orbit  Booster stages fly back to launch site on jet engines  Design intent: Minimize weight and size of the vehicle Propellants  Hydrogen and/or Hydrocarbon fuels are viable design paths Sample Development Path Serial Burn Design Parallel Burn Design ~2009 2012-14 45+ klb to LEO 15-25 klb to LEO  Requires development of: - 4 operational stages - 2- 4 operational engines Sample

8. For Official U.S. Government Use Only ONE.011_Arch-8 2012 Vehicle Options: Modular TSTO Description  Two nearly-identical stages  Booster stages glide back to launch site.  Design intent: Maximize commonality; Reduce number of stages to be developed Propellants  Hydrogen or Hydrocarbon fuels are viable design paths Sample Development Path ~2009 2012-14 45+ klb to LEO OR 15-25 klb to LEO  Requires development of: - 1 or 2 operational stages - 1 or 2 operational engines Additional Booster New Booster Sample

9. For Official U.S. Government Use Only ONE.011_Arch-9 Representative TSTO Architectures Demonstrators 2012 Cargo 2012 Crewed Optimized LH-LH Optimized RP-LH Optimized RP-RP Non-Optimized RP-RP Bimese LH-LH Bimese RP-RP Trimese LH-LH Denotes common hardware for each 2012 concept

10. For Official U.S. Government Use Only ONE.011_Arch-10 Air Launch Vehicles  Description: Combination of aircraft and expendable / reusable launch systems  Design Intent:  Aircraft altitude and velocity reduces energy requirements on launch system  Mobile infrastructure enables greater variety of launch sites and less asset vulnerability  Vehicle combinations consist of aircraft combined with  Solid motor launch vehicles  Expendable launch vehicles  Reusable launch vehicles  Key Considerations  Carrier aircraft limits total mass of launch system  Separation of the launch vehicle from aircraft poses challenges

11. For Official U.S. Government Use Only ONE.011_Arch-11 Hybrid Vehicles  Description: Combination of expendable and reusable stages  Design Intent:  Increase the range of missions and lift capacities provided by reusable vehicles alone  Reduce the number of new reusable stages that must be developed  Improve the cost effectiveness of the overall vehicle architecture  Vehicle combinations consist of RLV stages combined with  Expendable upper stages (liquids & solids)  Expendable booster vehicles  Solid strap-ons  Expendable drop tanks  Key Considerations  Staging velocities and recovery of RLV stages  Basing modes  Impact on operability, affordability, and responsiveness

12. For Official U.S. Government Use Only ONE.011_Arch-12 Example Sensitivity Study 0 15,00025,00035,00045,00055,00065,00075,00085,00095,000105,000 Payload to 100 nmi@ 28.5 Dry Mass (lbs) Total Dry Weight Booster Dry Weight Orbiter Dry Weight