Architecture Team

Industry Day Briefing

17 January, 2002

ONE.011_Arch-2For Official U.S. Government Use Only

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

ONE.011_Arch-3For Official U.S. Government Use Only

Integrated Architecture Elements

Launch Vehicle Systems

Reusable Orbital Vehicles

PayloadsOn-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

HumanHuman

Scientific

GroundFacilities

Orbital Transfer Vehicles

Spaceport

AutomatedMission

Processing

ONE.011_Arch-4For Official U.S. Government Use Only

System Classes Investigated

TSTO Air Launch ELV-RLV Hybrid

SSTO/Combined Cycle

Representative Concepts that Bound the Trade Space

Near Far

ONE.011_Arch-5For Official U.S. Government Use Only

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

ONE.011_Arch-6For Official U.S. Government Use Only

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

ONE.011_Arch-7For Official U.S. Government Use Only

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 2012-1445+ klb to LEO

15-25 klb to LEO

15-25 klb to LEO

Requires development of: - 4 operational stages

- 2- 4 operational engines

QuickTime™ and aPhoto - JPEG decompressor

are needed to see this picture.

Sample

ONE.011_Arch-8For Official U.S. Government Use Only

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 2012-1445+ klb to LEO

OR

15-25 klb to LEO

15-25 klb to LEO

Requires development of: - 1 or 2 operational stages

- 1 or 2 operational engines

AdditionalBooster

NewBooster

QuickTime™ and aPhoto - JPEG decompressor

are needed to see this picture.QuickTime™ and aPhoto - JPEG decompressor

are needed to see this picture.

Sample

ONE.011_Arch-9For Official U.S. Government Use Only

Representative TSTO Architectures

QuickTime™ and aPhoto - JPEG decompressor

are needed to see this picture.

QuickTime™ and aPhoto - JPEG decompressor

are needed to see this picture.

QuickTime™ and aPhoto - JPEG decompressor

are needed to see this picture.QuickTime™ and a

Photo - JPEG decompressorare needed to see this picture.

QuickTime™ and aPhoto - JPEG decompressor

are needed to see this picture.

QuickTime™ and aPhoto - JPEG decompressor

are needed to see this picture.

QuickTime™ and aPhoto - JPEG decompressor

are needed to see this picture.

Demonstrators

2012 Cargo

2012Crewed

OptimizedLH-LH

OptimizedRP-LH

OptimizedRP-RP

Non-OptimizedRP-RP

BimeseLH-LH

BimeseRP-RP

TrimeseLH-LH

Denotes common hardware for each 2012 concept

ONE.011_Arch-10For Official U.S. Government Use Only

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

ONE.011_Arch-11For Official U.S. Government Use Only

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

ONE.011_Arch-12For Official U.S. Government Use Only

Example Sensitivity Study

015,000 25,000 35,000 45,000 55,000 65,000 75,000 85,000 95,000 105,000

Payload to 100 nmi@ 28.5

Dry

Mass (

lbs)

Total Dry W

eight

Booster Dry Weight

Orbiter Dry Weight