Architecture Team
Industry Day Briefing
17 January, 2002
Example Development Strategy
NASA Variant
2002 – 06
~2009 - ?
2012-2014
DoD 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
 Ground and Flight Demonstrations



Risk Reduction
Operability
Long Term S&T
 Leads to full system capabilities
in 2012-14


For Official U.S. Government Use Only
Converged Cargo/MSP
Requirements
Modular variant for Human Space
Flight
ONE.011_Arch-2
Integrated Architecture Elements
Launch Vehicle
Systems
On-Orbit
Transfer &
Servicing
Reusable
Orbital Vehicles
Upper Stages
Crew Transfer
Payloads
Strategic
Ground
Facilities
Spaceport
ELV’s
Tactical
Orbital Transfer
Vehicles
Cargo Transfer
Automated
Mission
Processing
Commercial
2nd Gen RLVs
Human
3rd Gen RLVs
Re-fueling/
Servicing
Space Maneuver
Vehicles
For Official U.S. Government Use Only
Scientific
ONE.011_Arch-3
System Classes Investigated
Representative Concepts that Bound the Trade Space
Far
Near
TSTO
Air Launch
ELV-RLV
Hybrid
For Official U.S. Government Use Only
SSTO/
Combined Cycle
ONE.011_Arch-4
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
For Official U.S. Government Use Only
ONE.011_Arch-5
Preliminary Sizing Assumptions
 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
For Official U.S. Government Use Only
ONE.011_Arch-6
2012 Vehicle Options: Optimized TSTO
Serial Burn
Design
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
15-25
klb to
LEO
~2009
2012-14
45+ klb
to LEO
15-25 klb
to LEO
Parallel
Burn Design
 Requires development of:
For Official U.S. Government Use Only
QuickTime™ and a
Photo - JPEG decompressor
are needed to see this picture.
- 4 operational stages
- 2- 4 operational engines
ONE.011_Arch-7
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
15-25
klb to
LEO
~2009
New
Booster
2012-14
45+ klb
to LEO
15-25 klb
to LEO
Additional
Booster
 Requires development of:
QuickTime™ and a
Photo - JPEG decompressor
are needed to see this picture.
QuickTime™ and a
Photo - JPEG decompressor
are needed to see this picture.
OR
- 1 or 2 operational stages
- 1 or 2 operational engines
For Official U.S. Government Use Only
ONE.011_Arch-8
Representative TSTO Architectures
Optimized
LH-LH
Optimized
RP-LH
Optimized
RP-RP
Non-Optimized
RP-RP
Bimese
LH-LH
Bimese
RP-RP
Trimese
LH-LH
Demonstrators
2012
Cargo
2012
Crewed
QuickTime™ and a
Photo - JPEG decompressor
are needed to see this picture.
QuickTime™ and a
Photo - JPEG decompressor
are needed to see this picture.
QuickTime™ and a
Photo - JPEG decompressor
are needed to see this picture.
QuickTime™ and a
Photo - JPEG decompressor
are needed to see this picture.
QuickTime™ and a
Photo - JPEG decompressor
are needed to see this picture.
QuickTime™ and a
Photo - JPEG decompressor
are needed to see this picture.
QuickTime™ and a
Photo - JPEG decompressor
are needed to see this picture.
Denotes common hardware for each 2012 concept
For Official U.S. Government Use Only
ONE.011_Arch-9
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
For Official U.S. Government Use Only
ONE.011_Arch-10
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
For Official U.S. Government Use Only
ONE.011_Arch-11
Dry Mass (lbs)
Example Sensitivity Study
0
15,000
25,000
35,000
45,000
55,000
65,000
75,000
85,000
95,000
105,000
Payload to 100 nmi@ 28.5
For Official U.S. Government Use Only
ONE.011_Arch-12