dahm chicago keynote
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1
Key Air Force Research Priorities
28 June 2010
Dr. Werner J.A. Dahm Chief Scientist of the U.S. Air Force
Air Force Pentagon (4E130) Washington, D.C.
UNCLASSIFIED
Headquarters U.S. Air Force
28 June 2010 AIAA Combined Conferences Keynote Presentation
2
The Air Force is Critically Dependent on Science & Technology Advances
The Air Force is in the capabilities business; achieving superior capabilities requires a continual source of science and technology advances, with occasional breakthroughs
3
Science & Technology Has Top-Level Representation in the Air Force
Chief of Staff Air Force (AF/CC)
Secretary of the Air Force
(SecAF)
Headquarters U.S. Air Force
Office of the USAF Chief Scientist
Air Force Chief Scientist
(AF/ST)
The Chief Scientist is the full-time scientific and technical advisor to the AF Chief of Staff and Secretary of the AF
Holds 3-star equivalent rank; is a full member of the Air Staff, the AF Council, and Headquarters Air Force
Provides independent technical advice on all existing and planned programs, and on technical opportunities
Has unrestricted access to all information and programs; can address any topics of interest or opportunity
Commander, Air Force Materiel Command
(AFMC/CC)
Commander, Air Force Research Laboratory
(AFRL/CC)
Air Vehicles
Directed Energy
Space Vehicles Propulsion
Materials & Manuf. Information
Human Perform.
Sensors
Munitions
AFOSR
Basic Res. (AFOSR)
NA NE NL
Since shortly after its formation from the Army Air Corps, the Air Force has maintained an independent full-time Chief Scientist in the Pentagon as a direct scientific and technical advisor to the Chief of Staff
Unclassified 28 June 2010 AIAA Combined Conferences Keynote Presentation
4
The Path from Science and Technology to New Air Force Capabilities
• Low Rate Initial Production (LRIP) • Initial Operational Test & Eval. (IOT&E) • Full Rate Production (FRP) • Initial Operational Capability (IOC) • Field • Sustain
TRL 1: Basic principles observed and reported TRL 2: Technology concept and/or application formulated TRL 3: Analytical or experimental proof of concept TRL 4: Component validation in laboratory environment TRL 5: Component validation in relevant environment TRL 6: System/subsystem demonstration in relevant environment TRL 7: System prototype demonstration in an operational environment TRL 8: Actual system completed and qualified through test and demo TRL 9: Actual system proven through successful mission operations
Technology Readiness Level (TRL): Definitions
Basic Research
Applied Research
Advanced Technology Development
Concept Refinement
Advanced Development
System Development & Demonstration
Production, Fielding,
Sustainment
Budget Activity 1 (6.1)
Budget Activity 2 (6.2)
Budget Activity 3 (6.3) Budget Activity 4
BA 5 BA 6,7
Materiel Development Decision (MDD) Milestone A Milestone B Milestone C
Research & Development Acquisition
Universities Air Force Research Laboratory
5
Overall Air Force RDT&E Investments
Operational Systems Development 61%
Basic Research (6.1) 2%
Applied Research (6.2) 4%
Advanced Technology Development (6.3)
2%
Concept Refinement and Advanced Dev.
9%
System Development and Demonstration
18%
RDT&E Management 4%
$28.06B FY09 Air Force RDT&E
Unclassified 28 June 2010 AIAA Combined Conferences Keynote Presentation
6
USAF S&T Core Investment in 6.1-6.3
6.2: Applied Research $1029M
55% Total FY09 Core/External $4.5B
6.1: Basic Research $310M
16% 6.3: Advanced Technology
Development $541M 29%
Unclassified 28 June 2010 AIAA Combined Conferences Keynote Presentation
Amounts shown are $2B/yr Air Force core
funds; does not include $2B/yr customer funds
$1.9B Direct AFRL funds + $2.2B Customer funds
+ 324M Congress adds
$4.5B total AFRL 6.1, 6.2, 6.3
7
USAF S&T Core Investment Distribution Across Air, Space, and Cyber Domains
Air Domain 46%
Space Domain 30%
Cyber Domain 24%
Nearly one-quarter of all Air Force S&T investment now goes into the cyber domain
$541M
$566M
$862M
8
Ten Technical Directorates Comprise the Air Force Research Laboratory
Space Vehicles
Directed Energy
Munitions
Propulsion
Human Effectiveness
Information
Air Vehicles Sensors
AFOSR
Materials & Manufacturing
Unclassified 28 June 2010 AIAA Combined Conferences Keynote Presentation
9
Total Annual Air Force S&T Enterprise Amounts to $4.5B/yr (6.1-6.3)
Amounts shown are $2B/yr Air Force core
funds; does not include $2B/yr customer funds
Unclassified 28 June 2010 AIAA Combined Conferences Keynote Presentation
$1.9B Direct AFRL funds + $2.2B Customer funds
+ 324M Congress adds
$4.5B total AFRL 6.1, 6.2, 6.3
10
What New S&T Advances Will Create the Next Generation of USAF Capabilities?
Maintaining superior capabilities over its adversaries requires the Air Force to continually seek new science and technology advances and integrate these into fieldable systems
11
U.S. Air Force “Technology Horizons”
“Technology Horizons” is the next in a succession of major S&T vision studies conducted at the Headquarters Air Force level to define the key Air Force S&T investments over the next decade
Toward New Horizons
1945
Project Forecast
1964
New World Vistas 1995
Technology Horizons
2010
1 3 6 7
Woods Hole Summer Study
1958
New Horizons II
1975
Project Forecast II
1986
2 4 5
1940s 1950s 1960s 1970s 1980s 1990s 2000s 2010+
Low-impact studies
High-impact studies
28 June 2010 AIAA Combined Conferences Keynote Presentation Unclassified
12
Air Force S&T Vision for 2010-2030 from “Technology Horizons”
28 June 2010 AIAA Combined Conferences Keynote Presentation Cleared for Public Release
New Types of Remotely-Piloted and/or Autonomous Air Vehicle Systems
Air Force Sensorcraft concept
Air Force Sensorcraft concept
13 28 June 2010 AIAA Combined Conferences Keynote Presentation Cleared for Public Release
Air Force Sensorcraft concept
Unmanned combat air vehicle concept General Atomics “Predator C”
Unmanned airborne platforms with large sensor suite capable of long-endurance loiter on station
Requires substantial advances in numerous technologies (e.g., multifunctional structures, propulsion integration, affordable LO, etc.)
Passive laminar flow control technologies may be essential to provide needed loiter times
Thermal management will be challenging; large sensor heat loads with few ram air openings
Special fuels may be needed to manage extreme heat and cold at various operating conditions
High-Altitude Long-Endurance (HALE) Air Vehicle Systems
14
New unmanned aircraft systems (VULTURE) and airships (ISIS) can remain aloft for years
Delicate lightweight structures can survive low-altitude winds if launch can be chosen
Enabled by solar cells powering lightweight batteries or regenerative fuel cell systems
Large airships containing football field size radars give extreme resolution/persistence
28 June 2010 AIAA Combined Conferences Keynote Presentation Cleared for Public Release
DARPA VULTURE HALE Aircraft Concept
DARPA VULTURE HALE Aircraft Concept
Airship-Based HALE ISR Systems
15
HALE airship platforms are being examined for numerous ISR and comm relay applications
Current DoD HALE Airship programs include: Long-Endurance Multi-INT Vehicle (LEMV) HALE Demonstrator (HALE-D) Blue Devil (Polar 400 airship + King Air A-90) Integrated Sensor is Structure (ISIS)
Potential fuel cost savings over traditional ISR aircraft; speed and vulnerability are concerns
28 June 2010 AIAA Combined Conferences Keynote Presentation Unclassified
Blue Devil “Polar 400” DARPA “ISIS”
HALE-D
Examples of Current DoD HALE Airship Programs
Medium-Altitude Global ISR & Communications (MAGIC) Platform
Medium altitude allows platform more similar to traditional aircraft
More rapid repositioning than is achievable with airship platforms
Can serve as ISR platform and as airborne communications relay
Designs could potentially allow far greater endurance than MQ-1/9
MAGIC-like JCTD may be used to assess technology readiness
16 28 June 2010 AIAA Combined Conferences Keynote Presentation Cleared for Public Release
One example of a possible MAGIC long-endurance platform
Comparison with MQ-1 Predator and MQ-9 Reaper
Hybrid Wing-Body (HWB) Aircraft
Hybrid wing-body with blended juncture has greater fuel efficiency than tube-and-wing
Body provides significant fraction of total lift; resulting volumetric efficiency is improved
Potential Air Force uses as airborne tanker or as cargo transport aircraft
Fabrication of pressurized body sections is enabled by PRSEUS technology
X-48B flight tests (NASA / AFRL / Boeing) have examined aerodynamic performance
17 28 June 2010 AIAA Combined Conferences Keynote Presentation Unclassified
Partially-Buoyant Cargo Airlifters
Hybrid airships achieve part of their lift from buoyancy and part aerodynamically from forward flight
Could provide fuel-efficiency benefits for large cargo airlifter in certain applications (e.g., relatively unprepared sites)
Lockheed Martin “Project 791” using tri-hull design flew in 2006; short manned flight
System-level studies must determine potential DoD utility Flight experiments needed to assess handling performance
18 28 June 2010 AIAA Combined Conferences Keynote Presentation Unclassified
Versatile Affordable Advanced Turbine Engines (VAATE) Program
19 Cleared for Public Release
Adaptive Versatile Engine Technology (ADVENT)
Highly Efficient Embedded Turbine Engine (HEETE)
Efficient Small Scale Propulsion (ESSP)
VAATE is the nation’s current major collaborative effort to develop a new
generation of advanced turbine engine technologies
28 June 2010 AIAA Combined Conferences Keynote Presentation
Key Efforts Within VAATE Program
20
LINE-OF-SIGHT BLOCKAGE/ FLOW
CONTROLLED INLET
INTEGRATED REAR FRAME &
AUGMENTOR DURABLE, VECTORING
EXHAUST SYSTEM
ROBUST, DAMAGE – TOLERANT DESIGN
VERSATILE WIDE-FLOW
RANGE COMPRESSOR
LIGHTWEIGHT, DISTORTION
TOLERANT FAN
COMPACT, EFFICIENT,
CONTROLLEDEMISSIONS
COMBUSTOR
EFFICIENT, FULL-LIFE,
EXTENDED HOT-TIME TURBINES
MODEL-BASED, NON-LINEAR,
ADAPTIVE CONTROL SYSTEM
INTEGRATED THERMAL
MANAGEMENT SYSTEM INTEGRATED
HEALTH MANAGEMENT
SYSTEM
INTEGRATED POWER
GENERATION
ADVANCED FUEL ADDITIVES/ THERMALLY STABLE HIGH HEAT SINK FUELS
Cleared for Public Release 28 June 2010 AIAA Combined Conferences Keynote Presentation
21
Adaptive Versatile Engine Technologies (ADVENT) Program
Constant mass flow of ADVENT engine provide large new heat sink capacity
Additional heat exchanger located in relatively low-temperature third stream
Provides heat sink for fuel-cooled cooling air (FCCA) or air-cooled cooling air (ACCA)
May be especially important for large heat loads in airborne directed energy systems
Cleared for Public Release 28 June 2010 AIAA Combined Conferences Keynote Presentation
22
Highly Efficient Embedded Turbine Engine (HEETE) Program
Cleared for Public Release 28 June 2010 AIAA Combined Conferences Keynote Presentation
23
Airbreathing Propulsion Integration
Serpentine inlets and nozzles to provide engine obscuration and embedding in airframe
Significant challenge to minimize flow distortion at aerodynamic interface plane (AIP)
Seeking to develop bleedless inlet technologies to avoid performance losses from bleed air
Passive and active flow control approaches being explored to avoid flow separation
Must allow for wide range of mass flow rates; nozzles, thrust vectoring, actuation
Cleared for Public Release 28 June 2010 AIAA Combined Conferences Keynote Presentation
Passive or active flow control to avoid separation in serpentine inlet/nozzle
24
Supersonic Propulsion Integration: Combined-Cycle Scramjet Systems
AEDC APTU tests under FaCET of common turbo-ramjet/scramjet flowpath
Cleared for Public Release 28 June 2010 AIAA Combined Conferences Keynote Presentation
25
Supersonic Inlets: Shock-Boundary Layer Interaction (SBLI) Control
Simulations of passive control of shock-boundary layer interaction control using micro-ramps (Galbraith et al. 2009)
Shock-boundary layer interaction measurements (Lapsa & Dahm 2009)
Bleedless mixed-compression inlets need methods to avoid BL separation
Maximize inlet pressure recovery Shock-boundary layer interaction (SBLI)
can trigger separation at or after shocks AFRL using experiments and numerical
simulations to develop suitable control Passive sub-boundary layer vortex
generator micro-ramps Alternative passive control elements
Cleared for Public Release 28 June 2010 AIAA Combined Conferences Keynote Presentation
26
Advanced Diagnostics for SBLI Data
Instantaneous (u, v, w) across 2D spanwise planes
Mean Strain Rate Fields
Sxx (x, y)
Cleared for Public Release 28 June 2010 AIAA Combined Conferences Keynote Presentation
Stereo Particle Imaging Velocimetry Data for Shock Boundary Layer Interactions
Computational Modeling & Simulation (M&S) to Support Air Force Needs
Properly integrated M&S can give large reductions in cost of physical testing
Continued improvements needed in CFD methods (incl. numerics and physics)
E.g., USAF Seek Eagle use of CFD to assess aircraft/stores compatibility
6-DOF time-accurate trajectory codes using dynamic offset grids
Platform/stores configurations exceed what can be tested directly
27 Unclassified 28 June 2010 AIAA Combined Conferences Keynote Presentation
Massive Ordnance Penetrator (MOP) Stores Separation from B-52
Computational aeromechanics support to Air Force Seek Eagle aircraft/stores compatibility and weapons integration
Miniature Air Launched Decoy (MALD) B-52 Heavy Stores Adapter
28
Hypersonic International Flight Research and Experimentation (HIFiRE) Program
HIFiRE flights use sounding rocket descent trajectories to explore fundamental hypersonics technologies
AFRL and Australian DSTO with NASA; rocket flights at Woomera, White Sands, and Pacific Missile Range
Primary focus on aerosciences and propulsion areas; also stability & control and sensors & instrumentation
Propulsion experiments on Flights 2 (US), 3 (AUS), and 6-9 (US/AUS)
Scramjet fueling/combustion, integration, performance
Unclassified 28 June 2010 AIAA Combined Conferences Keynote Presentation
29
Scramjet Engine Development
Ground Demo Engine (GDE-2) SJX61-1 Development Engine SJX61-2 Flight Clearance Engine
Hydrocarbon-fueled dual-mode ram/scramjet combustor allows operation over Mach range
Thermal management, ignition, flameholding GDE-1 was flight weight hydrocarbon fuel-
cooled but with open-loop fuel system GDE-2 was closed-loop hydrocarbon fuel-
cooled system intended for NASA X-43C SJX61-1,2 were closed-loop HC fuel-cooled
development/clearance engines for X-51A
Unclassified 28 June 2010 AIAA Combined Conferences Keynote Presentation
30
X-51A Scramjet Engine Demonstrator First Flight on 26 May 2010
240-sec of continuous JP-fueled scramjet combustion in fuel-cooled combustor
Four flight experiments beginning late 2009 B-52 underwing launch; ATACMS booster to
separation and scramjet ignition Actual first flight performance:
Total mission time = 210 sec Time on scramjet = 143 sec Total distance traveled = 170 mi Scramjet ethylene start and JP-7 transition Scramjet fuel control and cooling Fuel setting for 4.7 ≤ Mach ≤ 5.25 Actual scramjet Mach achieved was 4.9 TM lost before fuel setting for high Mach Possible seal leak at nozzle junction
Nearly all other test objectives were met on this initial flight experiment
Unclassified 28 June 2010 AIAA Combined Conferences Keynote Presentation
31
X-51A Scramjet Engine Demonstrator
Cleared for Public Release 28 June 2010 AIAA Combined Conferences Keynote Presentation
32
X-51A Scramjet Engine Demonstrator
Cleared for Public Release: WPAFB 08-2865
Cleared for Public Release 28 June 2010 AIAA Combined Conferences Keynote Presentation
33
X-51A Scramjet Engine Demonstrator
Cleared for Public Release 28 June 2010 AIAA Combined Conferences Keynote Presentation
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X-51A Scramjet Engine Demonstrator
Cleared for Public Release 28 June 2010 AIAA Combined Conferences Keynote Presentation
35
X-51A Scramjet Engine Demonstrator
300-sec of continuous JP-fueled scramjet combustion in fuel-cooled combustor
Four flight experiments beginning in 2010 B-52 underwing launch; ATACMS booster
~30 sec to separation and scramjet ignition
Cleared for Public Release 28 June 2010 AIAA Combined Conferences Keynote Presentation
36
Robust Scramjet Scale-Up Program
X-51A uses small-scale combustor Possible follow-on flights to test navigation and inert strike on target
AFRL Robust Scramjet program Scale-up and combustor
reconfiguration for 3X, 10X, 100X
scales?
Possible ISR or global strike vehicle
Large-scale vehicle
Potential step to a future airbreathing TSTO access-to-space system
Dual flowpaths, mode transitions, cocooning Combined TBCC nozzle
Cleared for Public Release 28 June 2010 AIAA Combined Conferences Keynote Presentation
Hypersonic Global ISR Vehicles
JP-fueled scramjet propulsion system could potentially enable a medium-size rapid-response ISR vehicle having operationally relevant range capability
Mach 6 limit avoids complex thermal management penalties at higher Mach
Vertical takeoff / horizontal landing (VTHL) enables single-stage rocket-based combined-cycle (RBCC) system having 5000 nmi range with 2000 lbs payload
Integral rocket boost to Mach 3.5 with ram-scram acceleration to Mach 6 Resulting notional vehicle is 80 ft long with 42,000 lbs empty weight
37 Unclassified 28 June 2010 AIAA Combined Conferences Keynote Presentation
Notional Mach 6 single-stage reusable VTHL ISR vehicle with 5000 nmi range (Astrox)
38
Airbreathing Two-Stage-to-Orbit (TSTO) Access to Space Vehicles
Airbreathing systems offer enormous advantages for TSTO access-to-space; reusable space access with aircraft-like operations
Air Force / NASA conducting joint configuration option assessments using Level 1 & 2 analyses
Reusable rockets (RR), turbine-based (TBCC) and rocket-based (RBCC) combined cycles
Cleared for Public Release 28 June 2010 AIAA Combined Conferences Keynote Presentation
Laser-Based Directed Energy Systems
Laser-based directed energy systems approaching operationally useful power, size, and beam quality
Distinction between tactical DE (e.g., ATL in C-130) vs. strategic DE (e.g., ABL in B747)
Tactical-scale systems enabled ultra-low collateral damage strike and airborne self-defense
Technology path from COIL lasers to bulk solid state (e.g., HELLADS) to fiber lasers to DPALs
Demonstration path leads to airborne test (ELLA)
39 Unclassified 28 June 2010 AIAA Combined Conferences Keynote Presentation
AFRL Fiber Laser Testbed
AFRL Rubidium DPAL Experiment
2012 2017 2010
General Atomics
Textron Unit Cells
North Oscura Peak (NOP) White Sands Missile Range
ELLA Flight Demonstration
Electric Laser on a Large Aircraft (ELLA): Integration of Laser DE in B-1B
ELLA seeks to integrate and demonstrate tactically relevant high-power laser DE in airborne platform
C-130 and B-1B platforms were considered; B-1B selected as most challenging (aero-optics)
Will integrated fully modular HELLADS-derived laser in forward weapons bay of B-1B
Thermal management integrates with existing PAO lines in weapons bay; full beam control
Current FY17 tests and demonstration planned
40
3 Weapons Bays
Unclassified 28 June 2010 AIAA Combined Conferences Keynote Presentation
USAF Chief Scientist Conducting ELLA Integration Assessment in B-1B
41
Emerging Roles and New Concepts for Large and Medium Size UAVs
UAS moving beyond traditional surveillance and kinetic strike roles
Longer-endurance missions require high-efficiency engine technologies
In-flight automated refueling will be key for expanding UAS capabilities
May include ISR functions beyond traditional electro-optic surveillance
LO may allow ops in contested or denied (non-permissive) areas
Electronic warfare (EW) by stand-in jamming is a possible future role
Wide-area airborne surveillance (WAAS) is increasingly important
Directed energy strike capability is likely to grow (laser and HPM)
Cleared for Public Release 28 June 2010 AIAA Combined Conferences Keynote Presentation
42
Current Unmanned Aircraft Systems of the U.S. Air Force and DoD
U.S. Army MQ-1C Warrior RQ-7 Shadow
RQ-11 Raven Wasp III BATMAV
U.S. Navy / Marines
RQ-2 Pioneer
RQ-11 Raven Scan Eagle
RQ-8 Fire Scout
U.S. Air Force RQ-4 Global Hawk
MQ-1 Predator MQ-9 Reaper
RQ-11 Raven
Wasp III BATMAV
RQ-170 Sentinel
Cleared for Public Release 28 June 2010 AIAA Combined Conferences Keynote Presentation
43
MAVs Involve New Aerodynamic Regimes With Strong Fluid-Structure Coupling
Micro UAVs open up new opportunities for close-in sensing in urban areas
Low-speed, high-maneuverability, and hovering not suited even to small UAVs
Size and speed regime creates low-Re aerodynamic effects; fixed-wing UAVs become impractical as size decreases
Rotary-wing and biomimetic flapping-wing configurations are best at this size
Requires lightweight flexible structures and unsteady aero-structural coupling
Cleared for Public Release 28 June 2010 AIAA Combined Conferences Keynote Presentation
44
Low Reynolds Number Flow Associated with Flapping-Wing Micro Air Vehicles
Unsteady aerodynamics w/ strong coupling to flexible structures is poorly understood
AFRL water tunnel with large pitch-plunge mechanism allows groundbreaking studies
Advanced diagnostics (SPIV) combined with CFD are giving insights on effective designs
MAV aerodynamics, structures, and control are accessible to university-scale studies
Cleared for Public Release 28 June 2010 AIAA Combined Conferences Keynote Presentation
45
Concluding Remarks
Air Force S&T priorities span across a wide range of technical areas
Technology Horizons gives the vision for key USAF S&T over next decade
Remote-piloted and autonomous air vehicle systems will play a central role
RPAs, HALE aircraft and airships
Technologies for reducing fuel costs will become increasingly important
Airships, HWB, VAATE programs High-speed systems for strike, ISR,
and access-to-space are advancing Laser-based directed-energy systems
are approaching operational utility
Unclassified 28 June 2010 AIAA Combined Conferences Keynote Presentation
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