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?

12. Ponnappan - AOARD Power

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