12. ponnappan - aoard power
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AOARD POWER/ENERGY,PROPULSION AND SPACE17 March 2011
Dr. R. PonnappanProgram Manager
AFOSR/RSZ
Air Force Office of Scientific Research
AFOSR
Distribution A: Approved for public release; distribution is unlimited. 88ABW-2011-0799
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2011 AFOSR SPRING REVIEWAOARD PORTFOLIO OVERVIEW
NAME: Pon R. Ponnappan
BRIEF DESCRIPTION OF PORTFOLIO:
Research collaborations in Asia-Pacific region tosupport AFRL R&D mission in:
- Power/energy- Propulsion- Space
LIST SUB-AREAS IN PORTFOLIO:- Energy conversion/transport/storage- Nanomaterials, thermal management- Hypersonics, plasma studies
- Space situational awareness/weather
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Scientific Challenges
Theme Challenge Rationale
Power &Energy
Batteries matchinggasoline in energy density
Solid-state refrigeration
near room temperature
Li-air battery has thepotential
Magnetocaloric cooling
looks promising!
PropulsionHypersonics
Reliable high Mach flights
Plasma properties atnanosecond resolution
Potential in Australasia: HIFiRE 6.1 needs
Knowledge base forthrusters & actuators
Space Ensuring safety of spaceassets
Space situationalawareness(SSA): Orbital space debris
tracking & mitigation
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Transformational Opportunities
Power & Energy:- Li-air battery
Up to 10 times more energy density than Li-ion
- Magnetocaloric cooling Low-Gd alloy for near room temperature operation Thermal management applications for aerospace
Plasma dynamics. Spatial- and time-resolved plasma properties
For electric propulsion, thrusters, etc.
Space situational awareness. To alleviate threats to space assets
Space debris monitoring and tracking
New global interest/initiative
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Other OrganizationsFunding Related Work
Li-air battery [Niche: Scalability and rechargeability] AFRL/RZ high interest DOE, Argonne National Lab, auto industry
Magnetocaloric [Niche: Corrosion-free alloy; near room tempaerospace use]
AFRL/RX and RZ high and new interest area ARO ONR (Mark Spector) funds Astronautics Corp NEDO (Japan), China and EU Initiative
Hypersonics [Niche: 6.1 basic research with academia] Highly leveraged with Australias DSTO programs NASA
Space [Niche: Support AFRL/RV; Orbital debris tracking] NRL, AFRL/RV, Japan and Europe
Space debris: NASA, JAXA and ESA
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Recent Transitions
R&D Project Themes Transition (TR)
Magnetocaloric Cooling RX; RZ (Ajit Roy; Paul Barnes)Li-air / Li-ion Batteries RZP (Larry Scanlon; Thom Reitz)Space Situational Awareness RV; AFOSR (Keith Groves; Kent Miller)Beamed Energy Propulsion RZS; AFOSR (P. Kessel; Mitat Birkan)Hypersonics RB; AFOSR (D. Gaitonde; J. Schmisseur)
Plasma Properties RZS; AFOSR (Bill Hargus; C. Fesen)Thermal management RZP (Cindy Obringer)
AsiaPower/Energy
Meetings
India
Thailand
AOARD co-organized focused workshops:
- Found PIs - Initiated research programs
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Lithium - Air Battery
PI: M. Nookala, Indian Institute of Science, Bangalore, IndiaTD POC: Larry Scanlon, AFRL/RZPS
Advantages of Li-Air:
Use O2 in air; no need to store
High electrochemical potential
High energy density achievable
Challenge: Can Li-air batteries match gasoline in energy density?
Research Challenges: Stable electrolyte
Stabilization of Li anode
Charge/discharge life cycles
Power density
Rechargeability / Advanced catalyst
Practically achieved/achievableenergy density (Wh/Kg) comparison
of various energy systems
40 40 50160
370 350
1700 1700
0200
400600
8001000
12001400
16001800
EnergyDensity,W
h/Kg
This work istargeting
500Wh/Kg
Source: Li-Air Battery: Promise and Challenges, G. Girishkumar, et al.,IBM research, J. Phys. Chemistry Letters., 2010, 1, 2193-2203
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Lithium - Air Battery (cont.)
Accomplishments:- Scalability possible- Capacity 3850 mAh/g of carbon
- 22 hr load testing at 2 mA & 2.5 V- Calculated energy density=326 Wh/Kg Future Work:- Rechargeability; new catalysts
0 20000 40000 60000 80000
1.6
1.8
2.0
2.2
2.4
2.6
2.8
3.0
3.2
3.4
Voltage/V
Time / s
40mm Li-Air Test CellAir electrode : Carbon/ MnO2 /PTFEDiffusion Material: Carbon/ PTFECurrent collector: Stainless steel meshElectrolyte : Propylene carbonate +
diethyl carbonate + LiPF6 (1 M)Separator : Absorbent glass matrixAnode/cathode: Li foil / oxygen
DoD Applications:- Portable power for the BAO kit- UAV power- Aircraft and DEW applications
Al rod forLi contact
O2 supply
tubing
Teflon Cell Assembly
Volts,V
Time, s
40mm Li-Air Test CellDischarge Characteristics
Disharge current = 2 mA at 2.5 Vavg
Electrical loadMotor/fan
40 mmcell 10 mmcell
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Magnetocaloric Cooling
Magnetocaloric Cooling Principle:Applied H orients magnetic dipoles .T
Removal of H increases magnetic entropy T
Features: Carnot efficiencies possible Uses benign heat transfer media Tunable Curie temperature Large entropy change of
induced martensitic transitions Minimize Gd usage
Entropy Change vs. Temp(Fe-Co-B and Fe-Gd-Cr-B alloys)
Challenge:
- New corrosion-free Gd alloy characterization for near room temp use- Thermal management applications in aerospace
PI: R. V. Ramanujan, Nanyang Technological University, SingaporeTD POC: AFRL/RX; ARO co-sponsor
Scope:Synthesis, characterization and propertyevaluation of Fe-Cr-B-Gd based materials formagneto-caloric effect (MCE)
Refrigeration Capacity:
RC = S x T (J kg-1)
Magnetocaloricmaterial
mask
http://upload.wikimedia.org/wikipedia/commons/0/08/Magnetocaloric_effect1_04a.svghttp://upload.wikimedia.org/wikipedia/commons/0/08/Magnetocaloric_effect1_04a.svghttp://upload.wikimedia.org/wikipedia/commons/0/08/Magnetocaloric_effect1_04a.svg -
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bRC H
Universal curve behavior
J.Y. Law, R.V. Ramanujan and V.Franco, J. Alloys. Comp. 508, (2010), p.14.
peak n
M
S H
Calculated SM from expt.
Magnetocaloric effect of Fe-Cr-B-Gd alloys
Magnetocaloric Cooling (cont.)
Alloy Development Results: Field dependence of SM and RC:
excellent agreement between expt.
and NTU model
Universal curve for SM(T):
excellent predictive capabilities
Fe79 Gd1B12Cr8 (Gd1 alloy) gives
33% higher SM than Fe80B12Cr828% more RC than Gd5Si2Ge1.9Fe1.9RC = 459 J/kg (better than current
gold standard MCE material
Gd5Si2Ge1.9Fe1.9 )
Next: Thermal responseand AFRL/RZ testing
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Air Breathing Propulsion forHypersonic BEP-propelled Vehicles
Why Air-breathing Lightcraft? Able to ride laser beams through the atmosphere to flight speeds of Mach 10+
Useful for rapid launching of many nano-satellites with ~2 kg payload
PI: Con Doolan/Dave Froning, U. Adelaide; TD POC: Mitat Birkan, AFOSR
Objective: Develop air-breathing lightcraft for 6angle of attack (AOA)
Challenge: Prevent inlet un-start due to high AOAApproach:
- Develop unique inlet stream-tracingdesign- Verify using CFD and experimentsPayoff:- Low cost, - efficient access to space,- Enable BEP extended to hypersonic regime,- Cross-over tech transfer to scramjet vehiclesProgress:- A range of stream-traced inlets designed andsimulated using CFD and methodology developed- Novel laser detonation wave model
incorporated into design
Flow
UA lightcraft design withmodular inlets
Mach 8 CFD solutionshowing no inlet un-start
at 6 AOA
Flow
Next Step: Testing at U. Queensland T4 tunnel
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Electric-field-induced CoherentRaman Scattering
Interest: Electric propulsion Thrusters Electric field Plasmas
Need spatial- and time-resolved measurements of critical plasma propertiesin order to build and validate models
Payoff: Further understanding of fast plasma dynamics Improvement of plasma applications (plasma actuator, thrusters, etc.)
PI: Tsuyohito Ito, Osaka U.; TD POC: Bish Ganguly & Bill Hargus, AFRL/RZ
Scope: Simple and direct laser electric field measurements High temporal and spatial resolutions
Environment: Open air environment(300 K, 50% humidity)
Gap length Lg: 0.85 mmDielectric barrier: 0.15 mm thick glass platePower supply: Nanosecond pulsed power
Time duration: 15 nsPeak voltage: -3.5 kVRepetition rate: 10 kHz
Discharge test: Brass electrodes
0.15 mm glass dielectric barrier
PlasmaDischarge
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Electric-field-induced CoherentRaman Scattering (cont.)
0 10 20 30 40 50 60 70 80
-4
-2
0
2
4
-10
-5
0
5
10
Electric field
Measured
Nominal (see caption)
Electricfield[
kV/mm]
Time [ns]
Current
Current[A/cm
2]
Netplasmacharge
:Qp
Results: The measurements - Reveal interesting very-fast dynamics atthe initial state of the discharge
- Indicate significant distortion of potential
profile at very early stage, beforedetectable optical emissions
Current Status of the measurements:- Temporal resolution decided by the laser pulse:3-4 ns (improvement expected with shorter-pulse)
- Spatial resolution: ~0.15 mm (focus size)
- Electron density measurements in-progress
First successful laser electric field measurement in
open-air discharge environments by E-CRS
Color map:optical emissionintensity map
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Effective Detection ofLow-luminosity GEO Objects
Strategy overview of effective detection
Problem/Challenge: Non-resolved GEO objects
Large part of the non-resolved objects (= small pieces from spacecraft fragmentations) Difficulties on the detection of small fragments Low-luminosity objects Uncertainty in position and velocity vector distribution (= CRITICAL PROBLEM)
Approach: Population and Motion Predictions of the fragments applying spacecraft
fragmentation model & precise orbital propagator & Monte-Carlo method
Effective observationof fragments viapredicted population
Effective detection offragments via predictedmotion
PI: Yukihito Kitazawa, IHI Corp, Japan; TD POC: Kent Miller, AFOSR
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Measured motion vectors of 6 UCTs& 2 CT debris (68081K,J) are insidepredicted region
Measured motion vectors of 10 CTdebris (not derived from 68081E) &4 UCTs are out of predicted region
PI fully integrated with US team
Possibility to identify the UCTs insidepredicted region as uncataloged68081E fragments (various size)
Search observation of fragments from Titan3CTranstage (68081E) explosion on 1992.2.21
8 Fragments (68081G,H,J,K,L,M,N,P) of 68081E are catalogued at the Space-track
Planned: Origin confirmation of the UCTs
Fainter object detection trial bynew detection algorithm
Effective Detection ofLow-luminosity GEO Objects (cont.)
-1000
-500
0
500
1000
-1000 -500 0 500 1000
LatitudinalMotioninanImageSeries[pixels]
Longitudinal Motion in an Image Series [pixels]
UCT
CT
CT(68081J)
CT(68081K)Predicted Region
Higher
Presence
Region
Predicted vs. Measured motion vector distributionProgress:
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Program Trends
POWER / ENERGY / THERMAL
Li-air battery Nanoparticle decorated graphene Li-ion battery-ultra charge rate High power electronic chip thermal dissipation Magnetocaloric cooling Microgap cooling
PROPULSION / HYPERSONICS
BEP light craft Electric propulsion(EFI-CRS-study) Shock tunnel experiment Hypersonics engine inlet sensor Wing-root heating Plasma physics
SPACE
Object detection in GEO (orbital debris tracking)
Study of equatorial ionospheric irregularities ROCSAT-1 data analysis
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Summary
Focused joint workshops lead to top PIs and US interest
- 6.1 dollars invested in niche areas
Australasia picking up momentum in Power & Energy
Australia is fully engaged in hypersonics
Japan engaged in SSA
AFRL TDs are accessing foreign researchers
Thanks ! Questions?