Hung D. Nguyen, Gynelle C. Steele, and Jessica R. Morris

Glenn Research Center, Cleveland, Ohio

An Overview of 2014 SBIR Phase I and Phase II

Air-Breathing Propulsion

NASA/TM—2015-218905

December 2015
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Hung D. Nguyen, Gynelle C. Steele, and Jessica R. Morris

Glenn Research Center, Cleveland, Ohio

An Overview of 2014 SBIR Phase I and Phase II

Air-Breathing Propulsion

NASA/TM—2015-218905

December 2015

National Aeronautics and

Space Administration

Glenn Research Center

Cleveland, Ohio 44135
Available from

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This report is available in electronic form at http://www.sti.nasa.gov/ and http://ntrs.nasa.gov/
Contents 

Abstract ......................................................................................................................................................... 1

Development of X-ray Computed Tomography (CT) Imaging Method for the Measurement of 

Complex 3D Ice Shapes ................................................................................................................... 3

UAS Power Amplifier for Extended Range of Non-Payload Communication Devices ........................ 4

Advanced Technology MEMS-based Acoustic Array ........................................................................... 5

Phased Array Technique for Low Signal-to-Noise Ratio Wind Tunnels ............................................... 6

Compact Kinetic Mechanisms for Petroleum-Derived and Alternative Aviation Fuels ........................ 7

Physics-based Radiator Design, Sizing, and Weight Estimation Tool ................................................... 8

Hybrid Electric Propulsion System for a VTOL/Multirotor Aircraft ..................................................... 9

Digital Schlieren System for Flow Diagnosis ...................................................................................... 10

High Temperature Fiber Optic Thermal Imaging System .................................................................... 11

NASA/TM—2015-218905 iii

An Overview of 2014 SBIR Phase I and Phase II 

Air-Breathing Propulsion 

Hung D. Nguyen, Gynelle C. Steele, and Jessica R. Morris1

National Aeronautics and Space Administration 

Glenn Research Center 

Cleveland, Ohio 44135 

Abstract 

NASA’s Small Business Innovation Research (SBIR) program focuses on technological innovation 

by investing in development of innovative concepts and technologies to help NASA mission directorates 

address critical research needs for Agency programs. 

This report highlights nine of the innovative SBIR 2014 Phase I and Phase II projects that emphasize 

one of NASA Glenn Research Center’s six core competencies—Air-Breathing Propulsion. The 

technologies cover a wide spectrum of applications such as development of X-ray computed tomography 

(CT) imaging method for the measurement of complex 3D ice shapes, phased array techniques for low 

signal-to-noise ratio wind tunnels, compact kinetic mechanisms for petroleum-derived and alternative 

aviation fuels, and hybrid electric propulsion systems for a multirotor aircraft. Each featured technology 

describes an innovation, technical objective, and highlights NASA commercial and industrial 

applications. 

This report provides as an opportunity for NASA engineers, researchers, and program managers to 

learn how NASA SBIR technologies could help their programs and projects, and lead to collaborations 

and partnerships between the small SBIR companies and NASA that would benefit both. 

                                                            

1

 Lewis’ Educational and Research Collaborative Internship Project (LERCIP). 

NASA/TM—2015-218905 1

Development of X-ray Computed 

Tomography (CT) Imaging Method 

for the Measurement of Complex 3D 

Ice Shapes

A non-intrusive method of measurement

When ice accretes on a wing or other aerodynamic surface, it can produce 

extremely complex shapes. The development of larger ice shapes is generally 

believed to be influenced or built up from smaller scale surface structures. It is 

important to characterize the geometries of these ice shapes, not only to ensure 

an adequate representation of the geometry for subsequent aerodynamic effects 

studies but also to provide data to validate icing codes, understand the basic 

physics involved with the ice accretion, and provide a basis for modeling the ice 

accretion. To address the above issue, Spectral Energies proposes to use an Xray computed tomography (CT) imaging method to demonstrate that X-ray CT 

scanning can be used to measure 3D ice features. Spectral Energies also 

proposes to conduct a preliminary trade/design analysis to establish directions 

for a more detailed Phase II study that would address specific recommendations 

to integrate X-ray CT imaging with icing wind tunnels.

Applications

NASA

► Characterize and measure 

complex 3D ice shapes

► Use for measurement of ice 

shapes at NASA Glenn’s icing 

wind tunnels 

Commercial

► Characterize complex 3D wing icing, 

engine icing, and icing for commercial 

testing facilities 

Phase I Objectives

► Demonstrate that X-ray CT scanning 

can be used to visualize surface and 

internal features in ice that are 

consistent with aircraft ice accretion 

► Assess the visualization of those 

features in the presence of 

“obstructing” materials

► Provide a preliminary assessment of 

the feasibility of X-ray CT methods for 

use with NASA and other icing tunnels 

Benefits

► Fully visualize complex 3D shapes 

including 3D features of ice

► Non-intrusive method

► Can generate data sets that can be 

used for numerical simulations 

Firm Contact

Sivaram Gogineni

Spectral Energies, LLC

5100 Springfield Street, Suite 301

Dayton, OH, 45431-1262

PHONE: (937) 266-9570

FAX: (937) 256-7702

Proposal number: A1.02-8970

NASA/TM—2015-218905 3
UAS Power Amplifier for Extended 

Range of Non-Payload 

Communication Devices

Combining unmatched power efficiencies with linear amplifier 

performance to support a variety of RF communication data 

links and waveforms.

The high-efficiency and linear UPEND RF C-band power amplifier was 

designed, simulated and partially prototyped in Phase I to provide range 

extension for the NASA/Rockwell Collins Control and Non-Payload 

Communication (CNPC) data link. In Phase II NuWaves will address the needs 

of both amplitude-modulated and constant-envelope waveforms by developing 

multiple MMICs and packaging them together as needed. Separate die will be 

fabricated for the Doherty amplifier and the linearizer circuits, wire bonded and 

packaged into two different component-level integrated circuits – one with and 

one without the linearizer. Two different connectorized PA module variants will 

be developed using these two component-level ICs, adding the necessary power 

supply circuitry, supporting circuitry, and mechanical and thermal design to 

address different NASA and commercial market needs.

Applications

NASA

► Non-payload command and 

control for UAS in the context of 

NAS integration

► UAS payload communications 

(video and sensor data)

► Telemetry, tracking, and 

telecommand

► Deep-space communications

► Synthetic Aperture Radar (SAR)

► Airborne weather radar systems 

Commercial

► Unmanned systems command and 

control and payload communications

► Terrestrial and airborne tactical 

communication radios

o

► Broadcast communications, such as 

television camera-mounted data links

► Telemetry and training systems

► SAR

Phase II Objectives

► Design, develop, prototype and test:

1) A high-efficiency linear C-band 

PA for amplitude-modulated 

waveforms 

2) A high-efficiency C-band PA for 

constant-envelope waveforms

► Transition the initial MMIC design into 

two die, one of which will be integral in 

both PA variants, the other of which 

will be incorporated into the linear PA 

only.

Benefits

Range extension for wide variety of systems 

and platforms due to extremely low size, 

weight and power (SWaP), broad power 

supply range

► Optional bidirectional circuitry for halfduplex / time division duplex (TDD) 

data link support

► Scalable to higher frequencies such as 

X-, Ku-, K-, and Ka-bands

Firm Contact

Jeff Wells

Nu Waves Ltd.

122 Edison Drive

Middletown, OH, 45044-3269

PHONE: (513) 360-0800

FAX: (513) 360-0888

Proposal number: A2.01-9239

NASA/TM—2015-218905 4
Advanced Technology MEMS-based 

Acoustic Array 

The Interdisciplinary Consulting Corporation (IC2) in collaboration with the 

University of Florida proposes the development of large-channel count, highdensity, relatively-inexpensive directional microphone arrays for noise source 

measurement using microelectromechanical systems (MEMS) based 

piezoelectric microphones and advanced packaging technology. The goal of this 

research is to develop an advanced phased-array technology to revolutionize

array measurement capabilities within economic viability constraints. 

Specifically, this array technology will be developed to "Phased array and 

acoustic holography techniques to measure source noise in low signal-to-noise 

ratio wind tunnel environments." as per Subtopic A3.02 Quiet Performance of 

the NASA FY 2014 SBIR/STTR Solicitation. This work is aimed at meeting the

aerospace industries' need for economically viable array technology that meets 

required performance metric. MEMS-based piezoelectric microphones are 

proposed which will enable compact, high-density acoustic arrays. The approach 

is designed from the ground-up to leverage mass-producible microphones, 

electronics and packaging to fully enable future commercial production. The end 

result is a development path towards a high-density, high-channel count, fully 

integrated, acoustic array realized in a cost-effective production-ready 

architecture. The work plan involves a two stage development process that will 

lead to a number of stand-alone products. A prototype, single-package, 

microphone will be developed to demonstrate the performance of individual 

channels in an array. A large number of prototype microphones will be 

integrated into a hybrid array to compare to existing arrays based on industry 

standard, research-grade microphones used in wind tunnel testing. The 

commercialized production techniques used in the hybrid array will be leveraged 

to develop an integrated array to demonstrate high-density microphone array 

placement.

Applications

NASA

► Wind tunnel instrumentation for 

phased-array beamforming to 

enable noise source localization

► Ground and flight testing 

environments

► Support for multiple NASA GRC 

facilities such as:

o Aero-Acoustics Propulsion 

Laboratory

o Small Hot Jet Acoustic Rig

o Nozzle Acoustic Test Rig

o Advanced Noise Control 

Fan Rig

Commercial

► Wind tunnel instrumentation for 

phased-array beamforming to enable 

noise source localization on commercial 

aerospace components

► Ground and flight testing of commercial 

aircraft

► Monitoring acoustic dose for OSHA 

standards for:

o Condition based maintenance

o HVAC systems

o Gas turbine power plants

o Automotive industry 

Phase I Objectives

► Design microphone using formal 

optimization

► Identify commercial foundries to fabricate 

microphone

► Develop packaging technology and 

package several prototype devices

► Characterize device

► Identify commercial packaging houses to 

package microphones

► Prototype deployment to NASA centers 

and industry customers

Benefits

► Dramatic reduction of cost per channel, 

which allows for larger channel counts

► Increased dynamic range required for low 

SNR wind tunnels

► Greater flexibility in array placement in 

wind tunnels

► Enables access to high fidelity arrays for 

an expanded base of researchers 

Firm Contact

Leonard Kubik

Interdisciplinary Consulting Corporation

5745 SW 75th, #364

Gainesville, FL, 32608-5504

PHONE: (352) 359-7796

FAX: (256) 960-9500

Proposal number: A3.02-8995

NASA/TM—2015-218905 5
Phased Array Technique for Low 

Signal-to-Noise Ratio Wind Tunnels 

A testing method for UAV noise measurements

Noise measurement of aerospace vehicles is difficult and usually requires

expensive, specialized facilities. With the proliferation of UAVs there is a need 

for noise data, both for ISR and non-military vehicles. Wind tunnel testing is 

common and much less expensive. The innovation is a novel in-flow 

microphone array combined with the state of the art Functional Beamforming 

algorithm that makes it practical to measure UAV noise in a non-acoustic wind 

tunnel. 

Applications

NASA

► Noise measurement in acoustic 

and non-acoustic wind tunnels, 

including but not limited to:

o AAPL at NASA 

Glenn

o 9-by-15 wind tunnel 

at NASA Glenn

o NFAC at NASA 

Ames

Commercial

► Noise measurement testing for 

organizations such as:

o UAV manufacturers

o Northwest UAV

o Air Force 

o Navy

Phase II Objectives

► Determine the measurement noise 

floor of the wing array design in a 

representative non-acoustic wind 

tunnel as a function of frequency

► Determine the measurement noise 

floor of a wall array design in a 

representative non-acoustic wind 

tunnel as a function of frequency

► Evaluate both array types for 

representative UAV noise sources

► Construct and test arrays in Kirsten 

Wind Tunnel

► Perform in-situ calibration

Benefits

► Decreased cost

► Possible to measure UAV noise in a 

non-acoustic wind tunnel 

Firm Contact

Robert Dougherty

OPTINAV, Inc.

10914 Northeast

Bellevue, WA, 98004-2928

PHONE: (425) 891-4883

FAX: (425) 467-1119

Proposal number: A3.02-9794

NASA/TM—2015-218905 6
Compact Kinetic Mechanisms for 

Petroleum-Derived and Alternative 

Aviation Fuels 

A model for replication of specific real fuel combustion kinetic 

behavior 

To be useful for computational combustor design and analysis using tools like 

the National Combustion Code (NCC), low-dimensional chemical kinetic 

mechanisms for modeling of real fuel combustion chemistry must be sufficiently 

compact so that they can be utilized in multi-dimensional, multi-physics, 

reacting computational fluid dynamics (CFD) simulations. Despite advances in 

CFD-appropriate kinetic mechanism reduction for kerosene-range fuels, 

significant combustion property variation among current and prospective 

certified fuels remains a challenge for meaningful CFD-advised design of high 

pressure, low-emissions combustors. The proposed project will leverage 

Princeton's ongoing work in aviation fuel surrogate formulation and modeling as 

well as kinetic mechanism development for emissions and high pressure 

combustion to produce and demonstrate a meta-model framework for automated 

generation of fuel-flexible compact chemical kinetic mechanisms appropriate for 

3-D combustion CFD codes.

Applications

NASA

► Computational design of lowemissions, efficient combustors via 

NCC and other codes

► Physics-based CFD development 

of next-generation engines

► Reacting flow simulation platforms 

such as NASA’s National 

Combustion Code

Commercial

► Noise measurement testing for 

organizations such as:

o UAV manufacturers

o Northwest UAV

o Air Force 

o Navy

Phase II Objectives

► Develop a stand-alone software 

application for generation of tailormade, fuel-specific compact 

mechanisms

► Demonstrate compact mechanism 

performance in computation-intensive

CFD applications

Benefits

► Accurately represents global 

combustion properties of specific fuels

► Allows for evaluation of fuel property 

effects on combustor performance and 

emissions

► Generates detailed and 

mathematically reduced kinetic models

► Replicates specific real fuel 

combustion kinetic behavior

Firm Contact

Sivaram Gogineni

Spectral Energies, LLC

5100 Springfield Street, Suite 301

Dayton, OH, 45431-1262

PHONE: (937) 266-9570

FAX: (937) 256-7702

Proposal number: A3.03-9123

NASA/TM—2015-218905 7
Physics-based Radiator Design, 

Sizing, and Weight Estimation Tool 

For conceptual design of more-, hybrid- and all-electric next gen 

aircraft 

Hybrid electric distributed propulsion (HEDP) systems have proven worthy for 

further consideration by approaching NASA's goals for N+2 and N+3 energy 

consumption, noise, emission and field length. The thermal management 

associated with these systems has been recognized as a major challenge to be 

overcome. ESAero's recent 2012 Phase I SBIR (NNX13CC24P) identified the 

radiator as a driving component within the thermal management system (TMS). 

Its design has profound first order effects on the weight, performance, and 

aerodynamic drag of the TMS, and second order effects on the weight and 

performance of the overall propulsion system. During the proposed Phase I 

SBIR, ESAero will upgrade the existing physics-based radiator design, analysis, 

and weight estimation conceptual design tool by improving the flexibility and 

fidelity of thermodynamic analysis and predicting the effects of integrating the 

radiator core within a well-designed duct. These modifications are expected to 

dramatically improve the predicted weight and performance of the radiator and 

negate nearly all of the radiator drag.

Applications

NASA

► Facilitation of conceptual design of 

HEDP systems on aircraft to 

benefit multiple NRA projects

► Investigation for several nuances 

native to vastly different HEDP 

propulsion system architectures

► Support for the motivation for 

HEDP systems

Commercial

► Guide aerospace primes and AFRL 

toward the identification of feasible 

HEDP architectures

Phase I Objectives

► Develop an improved radiator design, 

sizing and analysis tool 

► Configure radiator core and upgrade 

analysis system

► Establish radiator duct design 

algorithm

► Verify and validate tool

► Integrate into overall framework 

Benefits

► Shows promise for meeting NASA’s 

goals for energy consumption, 

emissions, noise, and field length

► Profound first order effects on weight, 

performance, and aerodynamic drag of 

the TMS

► Second order effects on weight and 

performance of the overall propulsion 

system

► Improves the flexibility and fidelity of 

thermodynamic analysis 

Firm Contact

Andrew Gibson

Empirical Systems Aerospace, Inc.

P.O. Box 595

Pismo Beach, CA, 93448-9665

PHONE: (805) 275-1053

FAX: (805) 275-10590

Proposal number: A3.05-9369

NASA/TM—2015-218905 8
Hybrid Electric Propulsion System 

for a VTOL/Multirotor Aircraft 

A scalable electric propulsion system with increased endurance, 

safety, and reliability

Distributed Electric Propulsion and multirotor Electric Aircraft open up new 

aircraft design paradigms and enable new vehicle capabilities. These electric 

propulsion systems have low flight endurance due to the poor energy density of 

batteries. The multiple electrical systems involved may also lead to an increased 

failure rate due to the high number of components.

LaunchPoint Technologies proposes to build a scalable hybrid electric 

propulsion system that will achieve extended flight endurance and high 

reliability. 

During Phase I, LaunchPoint showed the feasibility of a manned hybrid electric 

VTOL vehicle that can achieve the endurance, speed, and fuel efficiency of a 

high aspect fixed wing aircraft while still providing VTOL capability for a 

commuter-type application. High energy density aviation fuel provides energy 

storage and a power dense gen-set converts the fuel to electricity for the system 

continuous power requirement in parallel with a battery pack for peak power 

demand. This results in a much longer endurance than a battery electric vehicle 

while still reaping the design benefits of electric propulsion technology. Fly-B yWire design techniques are applied to the electric aircraft propulsion system

leading to a highly reliable architecture called "Propulsion-B y-Wire", which 

provides a tremendous increase in reliability and safety of the vehicle.

In Phase II LaunchPoint Technologies will develop the hybrid power source of a 

"Propulsion-B y-Wire" system for two power levels. LaunchPoint will build 

and fly a long endurance 1 kW hybrid electric multirotor vehicle and will build 

and bench test a 6 kW hybrid power source to demonstrate scalability to larger 

systems.

Applications

NASA

► NASA’s Greased Lightning project 

/ GL-10, led by Bill Fredricks

► Leaptech vehicle demonstrator 

► Heist project 

Commercial

► Extend range on existing electric UAS 

vehicles 

► Highly reliable electric propulsion for 

eventual FAA certified UAS flight over 

people for news gathering, public safety

Phase II Objectives

► Develop a 1 kW “Propulsion by Wire” 

hybrid power system for a 12 kg class 

multirotor

► Integrate the “Propulsion by Wire” power 

system with a small commercially 

available multirotor and conduct free flight 

testing, demonstrate increased 

endurance

► Develop and bench test the 6 kW Hybrid 

Power Source component for a scaled up 

Propulsion by Wire system 

Benefits

► Increased endurance for multirotor 

electric and distributed electric propulsion 

vehicles

► Highly reliable architectures

► Increase in safety compared to 

conventional VTOL systems

► Meets notional airworthiness 

requirements for flight over people

► Increased fuel efficiency 

Firm Contact

Vicki Young

LaunchPoint Technologies, Inc.

5735 Hollister Avenue, Suite B

Goleta, CA, 93117-6410

PHONE: (805) 683-9659

FAX: (805) 683-9671

Proposal number: A3.06-9495

NASA/TM—2015-218905 9
Digital Schlieren System for Flow 

Diagnosis 

A versatile, robust, portable digital focusing schlieren system for 

wind tunnel applications

The innovation of this program was the development of a new digital focusing 

schlieren technology for flow diagnostics in high speed wind tunnels. The key 

challenge was to adapt to high speed illumination with a projection system that 

would have minimal impact on the wind tunnel surface. Adapting the 

illumination system for projection through windows was also addressed.

Applications

NASA

► Aerodynamic research and 

development problems associated 

with:

o Turbulent flow fields

o Boundary layers

o Shock waves 

o Flow interactions

o Aero optics

o Flow control

o Drag

o Boundary layer 

transition

o Flow separation.

Commercial

► Viewing large-scale phase objects 

in transparent media

► Aero-optics

► Flow diagnostics

► Flow-control

► Heating, ventilation, air conditioning

► Refrigeration

► Thermal management

► Air drying systems

► Ballistics

► Leak detection

.

Phase I Objectives

► Develop a versatile, robust, portable, 

user-friendly digital focusing schlieren 

system that will be useful for a wide range 

of wind tunnel applications

Benefits

► Robust

► User friendly

► Productive

► Useable in test facilities and 

environments previously prohibitive of 

such testing

► Reduced manufacturing costs

► Reduced size and weight

► High power instrument 

Firm Contact

Benjamin Buckner

Spectabit Optics LLC

22941 Mill Creek Dr.

Laguna Hills, CA, 92653-1215

PHONE: (949) 553-0688x270

www.spectabit.com

Proposal number: A4.01-8702

NASA/TM—2015-218905 10
High Temperature Fiber Optic 

Thermal Imaging System

A non-intrusive method of measurement

A prototype high temperature, single optical fiber thermal imaging system will 

be developed, tested, and delivered to GRC. The components of the instrument 

will be specified in detail, designed, fabricated, and purchased where 

appropriate. The illumination and imaging system will be assembled and system 

tests will be performed. Given a set of calibration images produced by the 

diagnostic, the image analysis needed to recover a thermal image of a surface 

will be developed and demonstrated. System resolution tests will be performed. 

The thermal imaging laboratory system will be modified to be appropriate to a 

prototype commercial instrument. The thermal imaging prototype will be tested 

and debugged at Thoughtventions and its operating characteristics defined. The 

thermal imaging system and operating manual will be completed and delivered 

and field tested at GRC for their ongoing use.

Applications

NASA

► Jet engine turbine and combustor 

ground test facilities

► Engine test facility at NASA Glenn

► High temperature facilities with 

limited optical analysis where 

thermal mapping is crucial for 

equipment diagnosis

Commercial

► Fiber thermal imaging systems for sale 

for use in jet engine research programs 

and later, production. Companies of 

interest include:

o Air force

o Pratt & Whitney

o General Electric

o Rolls Royce

o SNECMA.

Phase I Objectives

► Develop the illumination and imaging 

system by completing the design, 

fabricating and purchasing 

components, and assembling the 

system

► Develop image analysis system and 

perform resolution tests

► Develop instrument by modifying the 

thermal imaging system

► Test, document, and deliver system

Benefits

► Provides data on engine thermal 

issues that are of critical importance

► Provides turbo machinery and 

combustor imaging at high 

temperatures

► Overcomes problems with optical 

access, illumination, pressure sealing, 

image spatial and temporal resolution, 

and instrumentation ruggednes

Firm Contact

Stephen Bates

Thoughtventions Unlimited

40 Nutmeg Lane

Glastonbury, CT, 06033-2314

PHONE: (860) 657-9014

Proposal number: A4.01-9869

NASA/TM—2015-218905 11