Liquid & Solid Propulsion Overview Dr. Richard Cohn Chief, Liquid Engines Branch Propulsion Directorate Air Force Research Laboratory [email protected]661-275-5198 Not STINFO Approved. Distribution A – Public release, unlimited distribution. Release Number
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Liquid & Solid Propulsion Overview Dr. Richard Cohn Chief, Liquid Engines Branch Propulsion Directorate Air Force Research Laboratory [email protected].
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Liquid & Solid Propulsion Overview
Dr. Richard CohnChief, Liquid Engines Branch
Propulsion DirectorateAir Force Research Laboratory
Not STINFO Approved. Distribution A – Public release, unlimited distribution. Release Number
3
Joint government and industry effort focused on developing affordable technologies for revolutionary, reusable and/or rapid response military global reach capability, sustainable strategic
missiles, long life or increased maneuverability spacecraft capability and high performance tactical missile capability
SMV/SOVSMV/SOV
Air-to-Air MissilesAir-to-Air Missiles
High Energy High Energy Upper StagesUpper Stages
ELVsELVs ICBMsICBMs
SLBMsSLBMs SatellitesSatellites
Micro-SatellitesMicro-Satellites
Integrated High Payoff Rocket Propulsion Technology (IHPRPT)
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• Service life prediction technology
• Assessment of critical defects
• Propellant damage model development
• Environmental effects on material life
• Integrated motor life management
• Integrated sensor/data/analysis system
• Smart sensor technology
• Long term data warehousing
• Automated non-destructive evaluation
Aging and Surveillance Technology
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AFRL Edwards Rocket Site: LiquidRocket Technology Development
Air Force Programs
Air Force Proposed
Other Programs
X-33
XRS-2200
AFRL HC
Boost
On-Demand Launch(RBS)
Space Vector 1
AFRL Aerospike Tech
AFRL Thrust Cell Program
Military Space Plane & SOV
AFRL IPD
Concept Engine
AFRL XLR-129
SpaceShuttle
SSME
X-15
AFRL XLR-99
RL-10
Centaur Upper Stage
CL-400 Suntan
DC-X
J2X
RS 68- A/B ARES
Four Decades of Leadership in Rocket Engine TechnologyNot STINFO Approved. Distribution A – Public release, unlimited distribution. Release Number
Increasing Reusability
Rapid turn 4 hrs
100X lower ops cost
Vehicle reliability
All Wx availability
• 4X Sortie Airframe4X Sortie Airframe
• 5X Sortie Propulsion 5X Sortie Propulsion & Systems& Systems
Rapid turn 24 hrs
10X lower ops cost
Vehicle reliability
All Wx availability
• 2X Sortie Airframe
• 2.5X Sortie Propulsion & Systems
Rapid turn 48 hrs
3X lower ops cost
Vehicle reliability
All Wx availability
• High Sortie Airframe
• High Sortie Propulsion & Systems
Far TermMid TermNear Term
BASELINEEELV, Shuttle,Aircraft Ops
Responsive Space AccessTime Phased Plans
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Liquid Rocket
• Drive towards Modeling and Simulation
• Rocket Engine Development Programs– IPD (LOx/LH2 Booster)
– USET (LOx/LH2 Upper Stage)
– Hydrocarbon Boost (LOx/RP-2 Booster)
– 3GRB (LOx/LCH4 Booster)
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Drive Towards Model Driven Development
• There is a need to improve 30-40 year old modeling, simulation, & analysis (MS&A) tools
– Existing tools old and empirically based and require hundreds of tests
– Industry losing grey beards and thus design and analysis capability
– Could not handle new technologies like hydrostatic bearings
– Current and future computational capabilities allow use of physics-based tools to supplement testing
– Testing drives the cost of rocket programs
• Necessary
• Need to be smart
Test Driven Development
(TDD)
Model Driven Development
(MDD)
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Integrated Powerhead Demo (IPD)
• Joint program between AF, NASA, and Industry
• Supports sortie-like launch for Operationally Responsive Space (ORS)
• Payoffs: – 200 Mission Life (20X improvement)
– 100 MTBR
• First known full scale demonstration of Full Flow Staged Combustion Cycle in the World!
IPD Ground Engine: E1 Test Stand NASA SSC, Test 014TA: Standard Start to 85%PL, (Actual 89%PL) w/ Steady State; Test Profile SA, December 15th, 2005
IPD Ground Demonstrator Engine installed in E1 Complex Cell 1
IPD Ground Engine: E1 Test Stand NASA SSC, Test 013TA: Standard Start to 80%PL, 87%PL w/ Short Hold;
Test Profile RA, November 10th, 2005
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USET Objective
• Objective: Develop and demonstrate the next generation Model Driven Design (MDD) tools on an upper stage engine component
– Selected Turbopump
• Approach:
– Link commercial design tools with rocket specific empirical data, rocket specific material & propellant libraries, and user defined functions
– Replace targeted legacy design tools with physics based tools
• Enable Multi-Disciplinary Models, Time Accurate Solutions & Interconnected Models
– Reduced design time, more design iterations
– Higher fidelity analysis earlier in process
– Multi-disciplinary optimization
– Use Tools to design validation turbopump assembly
• Validation: provide sealed envelope predictions to compare with test data
Models & design tools applicable to other Liquid Boost & OTV Applications
- Range of Thrust - Range of Propellants - Range of Engine Cycles
Models & design tools applicable to other Liquid Boost & OTV Applications
- Range of Thrust - Range of Propellants - Range of Engine CyclesNot STINFO Approved. Distribution A – Public release, unlimited distribution. Release Number