Form 9.B Project Summary

Chron:

970945

Proposal

Number:

01.01-3155A

Project Title:

Knowlede Complementarity Assessment

Program

Technical Abstract (Limit 200 words)

Intelligent Automation, Inc. will develop and

evaluate the "Knowledge Complementarity

Assessment Program" (KCAP), an automated

approach to assessing the effectiveness of

individual and crew/team training. KCAP is an

innovative combination of Latent Semantic Analysis

(LSA), a statistical procedure for text analysis, and

Intelligent Agents for Instruction (IAI), an

agent-based technology to optimize resource

selection for instruction. KCAP assesses individual

and team performance and training requirements;

evaluates the relative merits of training resources

to enhance each team members' knowledge and

performance for these requirements; and provides

adaptive, individualized training for each team

member, based on their role in a team. KCAP is a

context-independent, low-cost alternative to

domain-specific intelligent tutors. It can be used

developmentally (to monitor and plan training as it

progresses), summatively (to evaluate the team and

individuals at the completion of a sequence) and to

monitor learning retention over time. We will

explore new methods of using KCAP to assess

team members' training during their performance of

real tasks. These advances supports NASA in

evaluating training effectiveness for individual/crew

performance, and in reducing error in tasks such as

aircraft maintenance. KCAP can develop into an

affordable new training and assessment technology,

suitable for use in many operational environments.

Potential Commercial Applications (Limit 200 words)

The proposed work will result in development of a

powerful technology that will be effective and

efficient in providing methods to assess the

effectiveness of training for groups or individuals,

and to use that information to guide training

programs. Using the Web, small training programs,

without sufficient financial resources to conduct

significant evaluation studies alone could use

KCAP through a "fee-for-service website."

Another product/service will be providing

KCAP-based validations of performance based

assessments, which could be provided through the

Web or through typical commercial software

distribution mechanisms. These will complement

IAI's other education and training-oriented Web

services and products.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Dr. Jacqueline A. Haynes

Intelligent Automation,Inc.

2 Research Place, Suite 202

Rockville , MD 20850

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Joseph E. Schwartz, Ph.D.

Intelligent Automation, Inc.

2 Research Place, Suite 202

Rockville , MD 20850

Form 9.B Project Summary

Chron:

970968

Proposal Number:

01.01-7100

Project Title:

Collaborative Decision Making

Airspace Visualization Tool

Technical Abstract (Limit 200 words)

This effort will develop a collaborative decision

making visualization

tool that will benefit dispatchers at Airline

Operations Centers

(AOCs), aircraft flight crews, Air Traffic

Management (ATM), and

scientific researchers who are designing decision

support systems for

these decision makers. As new Free Flight

procedures remove jetway

routing, positive control, and other constraints, an

added emphasis

will be placed on collaborative ATM techniques and

distributed

control. Our innovation provides a visual tool for

monitoring

information and collaborating with a common visual

model. This tool

can assist in keeping track of aircraft, negotiating

conflict

detection and resolution options, observing weather

systems and

special use airspace constraints, and viewing

operations data - these

data are dynamic and originate from multiple

sources. Before any of

Free Flight changes take place, scientific

researchers can use this

tool to visualize solutions to problems associated

with the AOC, the

flight crew, and the ATM system. Additionally,

researchers may

visualize conflict detection and resolution results for

analysis, and

evaluate distributed systems concepts like

collaborative decision

making. This visualization tool will assist NASA

achieve effective

and safe control of multiple aircraft in the National

Airspace System

(NAS) through the visual integration of air and

ground-based air

traffic information.

Potential Commercial Applications (Limit 200 words)

The commercial potential for a collaborative

decision making system is

very high because (a) air traffic continues to grow

worldwide and the

demand for more timely, efficient, reliable air travel

is strong on

the part of the airlines and the traveling public; and

(b) the trend

in air traffic control is towards giving airlines more

and more

autonomy while maintaining safety. The FAA,

CAAs, airlines and other

fleet operators will require collaboration tools to

assist with

providing Free Flight operations.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Jimmy Krozel, Ph.D.

Seagull Technology, Inc.

16400 Lark Avenue

Los Gatos , CA 95032-2547

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Jan Betke

Seagull Technology, Inc.

16400 Lark Avenue

Los Gatos , CA 95032-254

Form 9.B Project Summary

Chron:

971184

Proposal Number:

01.02-3474

Project Title:

Air Traffic Controller Agent Model for

Free Flight

Technical Abstract (Limit 200 words)

We propose to examine the human factors needs of

air traffic controllers operating under free flight

through the development of a modeling and analysis

tool based on an agent representation of the overall

controller/air traffic system. The approach relies on

a multi-stage agent-based representation of the

controller's SA and decision-making behavior, and

a multidimensional metric that reflects SA,

performance, and error propensity. We propose to

incorporate the controller agent into a simulated

free flight environment that contains a set of

semi-autonomous pilot agent models. Our objective

is to develop a simulation tool that will support the

development of rules and procedures for free flight

implementation, via simulation-based analysis of

controller behavior and airspace system safety

under alternate free flight configurations. One of

the key innovative features of the resulting free

flight simulation tool is a distributed

decision-making model embedded into the

multi-agent architecture, which will provide air

traffic management system designers with a basis

for the formulation of effective decision allocation

between ground control and pilots in free flight.

Potential Commercial Applications (Limit 200 words)

The proposed technology will directly support

closing the human factors loop on the development

of free flight ATM concepts. The underlying

modeling approach will also support human factors

assessments in other domains (e.g., nuclear power

plants, chemical processing centers, power dispatch

stations, intelligent vehicle highway system control

centers, etc.) where it is desirable to determine how

system design affects operator awareness and

performance before committing to a specific

configuration. We also plan to extract the belief

network algorithm that emulates air traffic

controller situation assessment in the presence of

uncertainty, and develop a commercial-quality

software tool for computer-based reasoning under

uncertainty.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Sandeep M. Mulgund

Charles River Analytics

55 Wheeler Street

Cambridge , MA 02138-1125

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Greg L. Zacharias

Charles River Analytics

55 Wheeler Street

Cambridge , MA 02138-1125

Form 9.B Project Summary

Chron:

971007

Proposal

Number:

01.02-6070

Project Title:

A Turbulence/Vortex Detection System

Using Optical Scintillation Techniques

Technical Abstract (Limit 200 words)

NASA, FAA, and U.S. Air Force have identified the

need to detect the aircraft trailing wake turbulence

generated by aircraft during take-off and landing

operations. At the present time, one of the major

problems of wake turbulence assessment is the lack

of an operational system to measure it in real-time.

As a result, FAA instituted operational and physical

guidelines to reduce the vortex wake hazard. These

conservative procedures put extra limits on airport

capacity and efficiency.

Scientific Technology, Inc. (ScTi) proposes to

develop a vortex/ turbulence detection system

including a set of scintillometers deployed in the

airport to measure ground and near ground runway

crosswind, turbulence, and wake vortex using

atmospheric turbulence- induced optical

scintillations. ScTi will perform system analysis and

design of the proposed system to detect

occurrences, location, magnitude, and persistence

of wake turbulence. With the simultaneous

measurements of crosswind and turbulence, the

sensor may even be able to forecast the arrival

time of the airplane generated wake vortex drifting

to a nearby runway. Successful development of the

system will serve as a decision support tool to ATC

for the next generation Air-Traffic Management

system to accommodate growth in air traffic while

reducing the aircraft accident rate.

Potential Commercial Applications (Limit 200 words)

Accurate crosswind, turbulence, and wake vortex

measurements are critical for improving airport

safety and efficiency. Successful development of

the proposed sensor technology will lead to the

large scale deployment of the proposed systems at

commercial and military airports around the world.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Dr. Ting-i Wang

Scientific Technology, Inc.

205 Perry Parkway, Suite 14

Gaithersburg , MD 20877

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Dr. Chung-Dyi Hsu

Scientific Technology, Inc

205 Perry Parkway, Suite 14

Gaithersburg , MD 20877

Form 9.B Project Summary

Chron:

971402

Proposal

Number:

01.02-7569A

Project Title:

Navigation and Situation Awareness for

Landing and Runway Crossing

Technical Abstract (Limit 200 words)

Faced with a projected increase in air traffic in

excess of 30% in the United States over the next

decade, government agencies such as NASA and

the Federal Aviation Administration (FAA) are

developing advanced technologies to increase

traffic-handling capacity at existing airports. Efforts

to increase airport capacity approach the problem

on two fronts: the first obvious solution is to

increase the number of runways (i.e. quantity), and

the second approach is to develop new technologies

to achieve reduction in aircraft separation and

consequently a corresponding increase in landing

rate per runway (i.e. efficiency). Both approaches

have to be accomplished without compromising

safety. The first approach based on increasing

usable runways also imposes new technical

problems. Modifying an existing airport layout

increases surface traffic complexity with increased

volume of aircraft and surface vehicle traffic,

resulting in increased occurrences of runway

crossing. The innovations advanced in this proposal

include both automatic and manual control of the

aircraft for runway crossing that will be tightly and

seamlessly integrated with products currently being

developed under the NASA TAP program. In

addition, the proposed effort includes performance

and benefit analyses to identify the maximum

possible capacity impact, and the potential

achievable benefits from such technologies.

Potential Commercial Applications (Limit 200 words)

Like most of the products being developed under

the NASA Terminal Area Productivity program, the

technologies developed under this SBIR proposal

are targeted for civil aviation. As the global travel

volume increases and the major airports execute

their plans to increase capacity through expansion,

runway crossing will quickly become a major issue

at these airports. The technologies to be developed

under this SBIR will be useful for developing new

avionics systems for improving ground traffic.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Dr. Victor H.L. Cheng

Optimal Synthesis

450 San Antonio Road, Suite 46

Palo Alto , CA 94306-4638

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Dr. P.K. Menon

Optimal Synthesis

450 San Antonio Road, Suite 46

Palo Alto , CA 94306-4638

Form 9.B Project Summary

Chron:

970768

Proposal Number:

01.02-8123

Project Title:

SafePath for Airport Surface

Movement

Technical Abstract (Limit 200 words)

Safety and efficiency are primary concerns in the

planning and conduct of vehicle movement on the

airport surface area; yet in many areas of

transportation management and system logistics,

safety and efficiency are competing goals. During

this Phase I SBIR effort Wyndemere Incorporated

proposes to study a system that will meet these two

challenges in a complementary manner through the

development of a detailed plan for airport surface

movement. This plan, formulated through

constraint-based optimization methods to increase

efficiency, will also allow warnings to be issued

when vehicles deviate from the plan, rather than

when an incursion or incident is imminent. The

innovation proposed is the research and prototyping

of a constraint-satisfaction based algorithm for the

generation of efficient airport surface movement

paths. This innovation will provide the fundamental

technology for a complete decision support system

to increase both safety and efficiency in airport

surface movement, considering aircraft and other

airport vehicles during normal, low-visibility and

emergency conditions. This technology will fit well

with NASA's Surface Movement Advisor project

and the recent demonstration of the Low Visibility

Landing and Surface Operations program at

Atlanta's Hartsfield Airport.

Potential Commercial Applications (Limit 200 words)

Technology aimed at increasing the safety and

efficiency of airport surface movement is in rising

demand. The United States has set aggressive

goals for the reduction of the aviation accident rate

in general, and runway incursions in particular. It is

expected that significant investment in safety

improvements will be made by the US government

and international aviation authorities over the next

few years. For airlines and air cargo operators,

ground movement efficiency is a major cost

concern; potential losses from aviation delays

creates a strong market for technology and

products that can increase the efficiency of airport

surface operations. In this regard, Wyndemere has

been working cooperatively with Federal Express to

identify the characteristics of traffic flow, airspace,

airport layout and air traffic control procedures that

contribute to inefficiency in their air cargo

operation. FedEx is interested in supporting the

research, development and use of this proposed

technology at Memphis International Airport, and

in-kind contributions have been committed to

Wyndemere by FedEx to support this Phase I SBIR

study.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

William S. Pawlak

Wyndemere Incorporated

660 Northstar Court

Boulder , CO 80304

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Susan S. Nedell

Wyndemere Incorporated

660 Northstar Court

Boulder , CO 80304

Form 9.B Project Summary

Chron:

971050

Proposal Number:

01.04-4097

Project Title:

Multi-Formal Hardware Verification

System

Technical Abstract (Limit 200 words)

Levetate Design Systems, Inc., as the prime

contractor, and Derivation Systems, Inc., as a

subcontractor, propose to develop an advanced

system for verifying digital electronic hardware

systems. The system addresses the problem of

verifying gate- or register transfer-level design

models against abstract specifications represented

as state machines. Innovative aspects of this

system include: (I) new methods to address the

problem of state explosion in large systems, (ii) new

methods based on theorem proving algorithms

implemented as user- friendly tools featuring

automated operation, fast execution times, and

effective debug support, and (iii) new methods to

implement rigorous, proof-based verifications that

feature automated construction of the proof steps

required by existing mechanical proof checkers.

The proposed research addresses elements of

NASA subtopic 01.04, Reliable and Safety-Critical

Software, by constructing

automated tools to support developing

safety-critical systems. The objective of the

proposed research is to develop a verification

system into an advanced prototype suitable for beta

testing by the end of Phase II. The successful

completion of this goal would go a long way in

moving the electronics design industry towards

methods of greater rigor and automation.

Potential Commercial Applications (Limit 200 words)

The main commercial applications for our proposed

work are electronic design automation (EDA) tools

for digital hardware design and verification. The

commercial potential for tools offering this

combination of automation, verification speed, and

proof security is, conservatively, well above $100

million.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Dr. David A. Fura

Levetate Design Systems, Inc.

4756 Univ. Village Pl. NE, #168

Seattle , WA 98105

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Dr. David A. Fura

Levetate Design Systems, Inc.

4756 Univ. Village Pl. NE, #168

Seattle , WA 98105

Form 9.B Project Summary

Chron:

970624

Proposal Number:

01.06-1313

Project Title:

Wave Turbine Engines: Improvements

to an Existing Wave Turbine Test

Platform

Technical Abstract (Limit 200 words)

Wave rotors are a key technology to enable

significantly increased gas turbine peak

temperatures. Higher specific power results,

providing a more compact unit with the additional

benefit of increased efficiency. These benefits are

realized especially for small gas turbines since

self-cooling is a fundamental feature of the cycle.

Self-cooling is especially applicable to the

improvement of auxiliary power units (APU's) and

small turboshaft engines. Because the expansion

and compression processes occur on the same

rotor, part count and engine complexity is reduced.

The objective of the proposed research is to

determine the requirements for upgrading an

existing wave turbine and, in Phase II, fabricate and

test the resulting upgrades. The primary goal is to

design for improved start-up operation, addressing

an important issue in wave rotor engines. This wave

turbine, the only known operating engine of its

class, was recently resurrected, meticulously

characterized, and partially tested to determine

problems, limitations, and requirements for

continued research. The proposed approach will

minimize the time and cost of developing this timely

technology for improving the APU's specific power,

efficiency, and simplicity. The upgraded

demonstration unit will serve as a research test

platform and an engine demonstration to encourage

commercialization by engine manufacturers.

Potential Commercial Applications (Limit 200 words)

Wave turbine engines have the potential to improve

a wide range of emgine products; in particular,

small engines for propulsion and power (i.e.,

auxiliary power units, APU's). Having established

its benefits in the small gas turbine market, wave

turbine engines can be expanded to larger power

class systems including off-the-road vehicles, high

bypass turbofans, and turboshaft engines.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

John F. Crittenden

UNISTRY Associates, Inc.

1901 Darby Road

Havertown , PA 19083

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Robert M. Carroll

UNISTRY Associates, Inc.

1901 Darby Road

Havertown , PA 19083

Form 9.B Project Summary

Chron:

971138

Proposal

Number:

01.07-0003

Project Title:

Active Combustion Control Using

Micro-Fabricated Sensors and Actuators

Technical Abstract (Limit 200 words)

Physical Sciences Inc. (PSI) proposes to develop a

closed-loop combustion control system for gas

turbine engines utilizing micro-fabricated sensors

and actuators. In previous and on-going work, PSI

has demonstrated the feasibility of active control

systems to suppress combustion instabilities and

improve combustor pattern factor, both of which can

lead to improved engine performance and

efficiency. The primary motivation for incorporating

micro-fabricated components into the system design

is to achieve a compact and highly-integrated

control system which is compatible with the size and

weight constraints of operating within a gas turbine

engine. Additionally, micro-fabricated components

have the potential to provide improved performance

over their macroscopic counterparts, allowing a

wider range of control strategies to be

implemented. PSI proposes to integrate a

micro-fabricated valve directly into a commercial

gas turbine fuel injector for active fuel flow control.

Additionally, strategies for actively controlling

spray patternation with embedded micro-actuators

will be developed. The active fuel injector designed

in the Phase I program will be fabricated and tested

in the Phase II program as part of an overall

combustion control system.

Potential Commercial Applications (Limit 200 words)

Successful development of the proposed technology

will represent one of the first commercial insertions

of micro-fabricated sensors and actuators in gas

turbine engines. A higher level of control over the

operation of gas turbine combustors will be

achieved with the proposed system, and along with

it, improvements in engine performance and

efficiency over the entire life of the engine. The

micro-actuator and sensor based combustion

control system also has the potential to lower the

costs of gas turbine engine development by relaxing

some of the constraints on the combustor design

process.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Michael F. Miller

Physical Sciences Inc.

20 New England Business Center

Andover , MA 01810

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

George E. Caledonia

Physical Sciences, Inc.

20 New England Business Center

Andover , MA 01810

Form 9.B Project Summary

Chron:

970195

Proposal Number:

01.07-8641

Project Title:

Hi Temp.Fiber Optic Eng.Mtd.

Ceramic Press. Transducer

Technical Abstract (Limit 200 words)

The demand of advanced aircraft propulsion

systems on sensor technologies to operate at

extended

temperature ranges has to date been primarily

focused on redesigning existing measurement

system

techniques. This proposed program will show the

feasibility of a new remote fly-by-light technology

made

possible by the availability of high temperature

air-clad sapphire optical fibers. The LEL concept

for

applying this technology to pressure and related

measurements is electrically passive-optically

active. No

electrically active parts reside in the sensor,

minimizing temperature effect on the sensor output.

The

sensor's input and output optical fibers can be

integrated in the engine's composite structure or

passed

through traditional wire ways to traditional

electronic components which are located remotely

from the

sensor. A primary feature of this new sensor design

concept is to measure differential motion as

opposed

to absolute motion, typical of diaphragm designs. A

properly designed differential motion sensor

measures only the input parameter not the side

effects caused by temperature and induced

stresses,

both static and dynamic. This fiber optic

miniaturized ceramic transducer is "Thermally

Hardened" by

material modifications allowing it to operate in a

high temperature (1000 degrees C) environment. It

does

not require active temperature compensation or

linearization to achieve specified accuracy.

Potential Commercial Applications (Limit 200 words)

The disclosed pressure transducer will provide an

essential input to an engine monitoring system

for the prediction of engine maintenance and stall.

In addition, this sensor technology can be used by

industries such as oil drilling, petrochemicals,

hydraulics, heavy construction equipment,

geothermal, geopressure wells, metal cutting, oceanography,

nuclear power plants and research organizations,

with similar gains in performance and reduced cost.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Charles A Liucci

LEL Corporation

5 Burns Place

Cresskill , NJ 07626

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Charles A Liucci

LEL Corporation

5 Burns Place

Cresskill , NJ 07626

Form 9.B Project Summary

Chron:

970576

Proposal

Number:

02.01-7115

Project Title:

Thin Film Sensors for Measurement of

Engine Emissions

Technical Abstract (Limit 200 words)

Emissions from aircrafts and automobiles are of

significant environmental concern. Various

communities are aggresively planning to set tighter

emission limits for exhausts including those from

aeronautical and aerospace operations. NASA's

goal is to reduce emissions of future aircrafts by a

factor of three within 10 years and five within 20

years. A key enabling technology for this goal are

exhaust sensors for NOx, SOx, HOx, atomic

oxygen, and hydrocarbons. Nanomaterials

Research Corporation (NRC) seeks to develop and

demonstrate nano-precision engineered sensors for

emissions monitoring. Phase I will systematically

establish the proof-of-concept; Phase II will

optimize, scale-up and fabricate prototype devices

for exhaust applications; Phase III will

commercialize the technology.

Potential Commercial Applications (Limit 200 words)

Emission sensors will enable intelligent operation of

sub-sonic engines to prevent pollution and to

increase fuel efficiencies. Spin-off applications

include emission sensors for catalyst monitors in

automobiles (mandated by law in the U.S., Japan,

and Europe), sensors for diesel engines and

turbines.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Charlie Xu, Ph.D.

Nanomaterials Research Corporation

2849 East Elvira Rd

Tucson , AZ 85706-7126

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Tapesh Yadav, Ph.D.

Nanomaterials Research Corporation

2849 East Elvira Rd

Tucson , AZ 85706-7126

Form 9.B Project Summary

Chron:

971578

Proposal Number:

02.01-8614

Project Title:

A Catalytically Stabilized Lean Direct

Injection Combustor for Advanced

Subsonic Technology Emissions

Reduction

Technical Abstract (Limit 200 words)

A catalytic lean direct injection (LDI) design is a

practical approach for achieving NOx emissions

reduction for the Advanced Subsonic Technology

(AST) combustor. Our novel catalytic LDI design

integrates the underlying catalytic combustion

principles behind Precision Combustion's prior lean

premixed prevaporized(LPP)designs with effective

LDI principles applied to liquid fuels. This combines

the benefits of LDI, including avoiding preignition,

with the improved stability and ultra-low NOx

emissions of catalytically stabilized combustion.

Catalytic enhancement of flame stability offers

potential breakthroughs for NASA's advanced

subsonic program gas turbine engine through very

low pressure drop, high inlet duct velocity, high

turndown and stability, and low NOx at pressure.

Potential Commercial Applications (Limit 200 words)

High efficiency and low emissions are twin

objectives of future aerospace gas turbine engines.

This design approach contributes to these

objectives by enhancing stability, mixing, and

turndown of Lean Direct Injection Designs, offering

design flexibility to engine designers. This

combustor is being developed with a focus upon

ease of implementation into engine manufacturers

Advanced Subsonic Technology combustors

designs, and has the potential to create significant

value-added for the aircraft engine manufacturers.

Spinoff low NOx dual fuel stationary gas turbine

applications for this technology also show

significant promise.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Gilbert Kraemer

Precision Combustion, Inc.

25 Science Park, MS 24

New Haven , CT 06511-1968

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Paul Donahe

Precision Combustion, Inc

25 Science Park, MS 24

New Haven , CT 06511-1968

Form 9.B Project Summary

Chron:

971228

Proposal Number:

03.01-332

Project Title:

Rotorcraft Blade Vortex Interaction

Control with Induced-Strain Actuation

of Blade Twist

Technical Abstract (Limit 200 words)

Systems Planning and Analysis, Inc. (SPA)

proposes to develop a Mach-scaled smart

helicopter rotor with on embedded piezoceramic

elements for blade-vortex interaction (BVI) noise

reduction. SPA will use directionally attached

piezoceramics as actuators and sensors, for

closed-loop higher harmonic pitch control of the

main rotor blades. These pitch perturbations will

generate unsteady blade loads that would in turn

counteract loads generated by the BVI, with little

impact on the nominal steady-state rotor thrust. In

the proposed Phase I effort, SPA will use

Euler/Navier-Stokes computational fluid dynamics

(CFD) codes as a Òvirtual experimentÓ to examine

the 3-D interaction of a simplified vortex system

with a rotating blade (for low-speed descent flight)

and the associated aeroacoustic noise to establish

the required performance metrics (i.e., blade twist

deflection, actuator power, frequency response,

etc.) to reduce BVI by 10dB. The calculated leading

edge pressure differentials at several spanwise

stations in the outboard (60 to 90 percent of span)

region of the blade will be used as inputs to simple

control algorithms for determining the appropriate

twist actuation required for BVI noise suppression.

Finally, the CFD calculations will be repeated with

the variable twisting actuation to determine the

actual noise reduction achieved.

Potential Commercial Applications (Limit 200 words)

The successful development of a smart rotor

system will offer unprecedented benefits to military

and commercial rotorcraft. Reductions of BVI and

low frequency rotor noise (and the associated

higher-harmonic rotor vibrations) will reduce the

detectability of military platforms during Nap of

Earth (NOE) operations, while improving the rotor

performance for air-to-air combat. For commerical

rotorcraft, reductions in rotor noise would allow for

operation in urban environments with aircraft noise

restrictions. Furthermore, the reduction of harmonic

blade loads would reduce the maintenance

requirements and associated high cost of all

rotorcraft systems subject to premature failure of

rotor components due to high dynamic stresses.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Peter C. Chen, Ph.D.

Systems Planning and Analysis, Inc.

2000 N. Beauregard St. Suite 400

Alexandria , VA 22311

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Phillip E.Lantz

Systems Planning and Analysis, Inc.

2000 N. Beauregard St. Suite 400

Alexandria , VA 22311

Form 9.B Project Summary

Chron:

971171

Proposal Number:

03.02-0818

Project Title:

Advanced Prediction Tool for

Simulation of Turbomachinery Noise

Sources

Technical Abstract (Limit 200 words)

Serious concerns regarding the adverse

environmental impact of aircraft noise have led to

increasingly stringent regulations on the allowable

acoustic emissions from commercial transport

aircraft. To facilitate future growth in air

transportation while ensuring compliance with

international noise regulations, urgent attention to

noise prediction and reduction technologies is

required at this time. The perceived aircraft noise

levels during both takeoff and approach phases are

controlled by the turbomachinery noise, in

particular, its fan component. Here, an accurate yet

highly efficient numerical technique based on a

(high-order) computational aeroacoustics (CAA)

algorithm is proposed for simulating

turbomachinery noise. This approach is innovative

in tapping the potential of CAA to provide an

enhanced physical understanding of and integrated

prediction methodology for turbomachinery noise.

In addition to providing guidance and checks for

preliminary design tools, simulation tools of this

kind will minimize the overall design cycle time and

significantly enhance the competitiveness of U.S.

engine manufacturers in the global aviation market.

Potential Commercial Applications (Limit 200 words)

Turbomachinery design, engine noise reduction

technologies for subsonic commercial transports,

aerodynamic and aeroacoustic prediction, validation

of analytical prediction tools for turbomachinery

noise, computational electromagnetics, radar

detection and avoidance, wireless communications.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Meelan M. Choudhari

High Technology Corporation

28 Research Drive

Hampton , VA 23666

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Mujeeb R. Malik

High Technology Corporation

28 Research Drive

Hampton , VA 23666

Form 9.B Project Summary

Chron:

971349

Proposal Number:

03.02-8533

Project Title:

Active Control of Broadband

Rotor/Stator Noise in Turbofan

Engines

Technical Abstract (Limit 200 words)

The proposed innovation is a compact active control

system for reduction of tonal and broadband noise

radiated by rotor/stator interaction in turbofan

engines. The concept employs pressure transducers

on stators (outlet guide vanes) to capture signals

correlated with radiated noise. The signals are

processed and distributed to circumferential arrays

of actuators that serve as anti-sound sources to

cancel the rotor/stator noise. Circumferential

arrays of sensor microphones provide error signals

for the adaptive control system. Correlations

between stator vane fluctuating surface pressures

and radiated noise will be measured in the

NASA/LeRC ANCF fan to assess the feasibility of

the concept. Favorable results will lead to a

computer simulation of a simple active noise control

system and implementation of an in-situ

demonstration on the ANCF fan.

Potential Commercial Applications (Limit 200 words)

If successful, the proposed active noise control

system would suppress the lower frequency

(between 0.5 and 1.5 BPF) range of rotor/stator

noise. This would allow passive engine liners to

more effectively target high frequency noise in the

2 BPF to 4 BPF range and to be shallower, taking

less space.

The design concept of the system is such that the

actuator arrays could be integrated with active

control systems directed at tones.

There may be non-aircraft applications for the

concept, such as compact silencers for industrial

axial flow fans commonly used for air exhaust in

power generation systems, mining, parking

garages, etc. where personnel or community noise

exposure are often critical issues.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Bruce E. Walker

Hersh Acoustical Engineering, Inc.

780 Lakefield Road, Unit G

Westlake Village , CA 91361

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Alan S. Hersh

Hersh Acoustical Engineering, Inc.

780 Lakefield Road, Unit G

Westlake Village , CA 91361

Form 9.B Project Summary

Chron:

970560

Proposal Number:

04.01-4755b

Project Title:

Low-Cost Surface Treatment for

Bonding Titanium Panels

Technical Abstract (Limit 200 words)

High speed travel requires reliable airframe

structure and low-cost fabrication technology.

Current adhesive joining methods for Ti panels are

not cost-effective. The resultant junctions are also

limited by the operating temperature under 430K

and the lack of long-term durability. This project

will develop new surface treatment processes to

create unique surface texture and chemistry for

strong and durable bonding with advanced

high-temperature adhesives. Phase I will

demonstrate the feasibility of two physicochemical

surface treatment processes to produce strong and

stable adhesive bonding for Ti panels. Phase II will

select one or two promising processes to optimize

performance, uniformity and cost effectiveness.

These surface treatment processes will be applied

to both monolithic and composite materials, and

titanium and other high-temperature metals, to

achieve a greater thermal stability of adhesive

bonding. Phase III will involve the development of

practical treatment procedures and equipment for

small-scale applications.

Potential Commercial Applications (Limit 200 words)

Physicochemical treatments are needed to prepare

stable metal surfaces for high-temperature

adhesive bonding. High performance and durable

adhesive bonding resulting from these new

processes could be used in high-temperature

aircraft and ground transportation applications. By

using little or no hazardous chemicals, these

processes could also reduce environmental

concerns associated with the use of hazardous and

toxic chemicals.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Dr. Rong Wang

Wamax, Inc.

4473 142nd Ave SE

Bellevue , WA 98006

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Dora F. Wang

Wamax, Inc.

4473 142nd Ave SE

Bellevue , WA 98006

Form 9.B Project Summary

Chron:

971227

Proposal Number:

04.01-5773

Project Title:

Variable Cell Blanket Sandwich Panel

Technology

Technical Abstract (Limit 200 words)

This project's purpose is to determine the viability

of mathematically modeling the load transfer

properties of uninterrupted variable cell blanket

structures. Variable cell blanket sandwich panel

technology integrates varying density areas into a

laser welded expanded honeycomb core structure

without the need for costly core splicing. The fully

integrated varying cell blanket configuration

creates an uninterrupted load transfer from one cell

size to another.

This effort will consist of the physical testing and

mathematicaly modeling of the properties of

samples of laser welded titanium honeycomb core in

a variety of cell sizes, and foil thicknesses. It is

anticipated that a viable approach to the modeling

of variable cell blanket structures will be

developed. This approach will be the model used in

designing low cost titanium sandwich panel

fabrications.

Variable cell blanket sandwich panels offer reduced

weight, lower cost and higher strength over other

fabricated panel structures. NASA and the

aerospace industry will benefit for this improved

structural design concept. Complex aircraft designs

requiring both low weight and strength can utilize

this technology to stay within their design

parameters.

Potential Commercial Applications (Limit 200 words)

Initially, the aerospace industry, both commercial

and military, will receive the greatest benefit from

variable cell blanket technology. Variable cell

technology offers decreased cost, decreased weight

and increased strength for all honeycomb sandwich

structures. There are a number of commercial

markets that will potentially benefit from this

technology. It is expected that the significantly

lower cost and flexible design possibilities afforded

by this product will encourage the use of

honeycomb in industries such as automobile,

construction, and shipbuilding.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Jeffrey Johnson

Benecor, Inc.

5320 West Main

Parsons , KS 67357-8830

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Kristen Johnson

Benecor, Inc.

5320 West Main

Parsons , KS 67357-8830

Form 9.B Project Summary

Chron:

971093

Proposal Number:

04.01-9101

Project Title:

Low Cost Processable High

Performance Materials for High Speed

Research Applications

Technical Abstract (Limit 200 words)

Imitec proposes to make processable low molecular

weight polyimides such as LaRC-PETI-5 and

LaRC-LV type resins from solvent free or low

solvent procedures using simulated extrusion

conditions. The proposed "melt" process is an

innovation because polyimides are traditionally

synthesized using solution polymerization

techniques generating significant quantities of

waste. Efforts will focus on the types of polyimides

currently being tested in NASA's High Speed

Research Program. The project objectives include

the successful synthesis of polyimides via extrusion

like melt processes with resin properties equal or

better than traditional routes and suitable for low

cost fabrications. NASA and the aerospace industry

have significant demands for high performance

polyimides in the need to replace metal components

with light weight composites. Polyimide powders are

becoming more desirable to prepreggers as stricter

environmental regulations are being enforced. In

addition, solvent free polyimides are needed in

various fabrication techniques both by NASA and

the aerospace industry. These techniques include

Advanced Tow Placement (ATP) and Resin

Transfer Molding (RTM). The anticipated results

of polyimides made this way are better composite

properties due to absence of residual solvents and

better wet out because low molecular weight

polymer chains are not extracted.

Potential Commercial Applications (Limit 200 words)

Advanced Tow Placement and Resin Transfer

Molding to make large aerospace components out

of composites. Low density structural foam

insulation.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Betty Tung

Imitec, Inc.

1990 Maxon Road

Schenectady , NY 12308

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Stephen T. Terney

Imitec, Inc.

1990 Maxon Road

Schenectady , NY 12308

Form 9.B Project Summary

Chron:

970286

Proposal Number:

04.02-1100

Project Title:

Reducing Cost, Weight, and NOx of

Combustors by Incorporating Novel

Mixing Techniques.

Technical Abstract (Limit 200 words)

This program introduces novel mixing techniques

for supersonic transport propulsion low emission

combustor designs to dramatically reduce cost,

weight and complexity and to improve performance.

This innovation employs advanced multi-staged

lobed mixers to very rapidly mix fuel and air, both

temporally and spatially, with minimum momentum

loss to the flows. In demonstrations for other

applications, the concept has proven to improve the

transition from air/air mixing to liquid/air mixing.

This proposed work builds upon and extrapolates

the existing body of knowledge to develop a

predic-tive model for the HSCT combustor

environment. The Phase I results will be an

analyti-cal proof-of-concept, characterization of the

anticipated benefits and generation of mixer

designs suitable for verification testing in Phase II.

This program targets the de-fined Subtopic need for

environmentally and economically compatible

improvements directed at combustors for

supersonic transport propulsion systems.

Potential Commercial Applications (Limit 200 words)

The proposed multi-staged-lobe-mixer devices can

find commercial application in a multitude of

aerosol spray devices where a liquid must be

dispersed into a co-flowing, non-reacting gas

stream. Applications include air/fuel mixers for

supersonic transport propulsion systems in addition

to other flight and land-based gas turbines. Other

appli-cations which will be pursued include paint

sprayers, humidifiers and, snow making de-vices.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Stuart S. Hay

FTS Inc.

5448 Westchester Rd

Westchester , OH 45069

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Julio E. hernandez

FTS Inc.

5448 Westchester Rd

Westchester , OH 45069

Form 9.B Project Summary

Chron:

971074

Proposal

Number:

04.02-2200a

Project Title:

A MULTI-SPECTRAL AIRBORNE

RADIOMETER FOR RANGE

RESOLVED HIGH-ALTITUDE AIR

TEMPERATURE MEASUREMENTS

Technical Abstract (Limit 200 words)

Precise air temperature measurements currently

can not be made from high-speed aircraft. We

propose to solve this problem by using a

remote-sensing radiometer. The High-altitude Air

Temperature Radiometer (HATR) will operate in

the 15um CO2 absorption band, near the peak of

the thermal emission for stratospheric air

temperatures. This wavelength region has not been

used for commercialradiometers but has been

explored at Ophir. Using multispectral polarization

modulation and detection techniques, combined with

Ophir's experience and innovations in radiometer

design, we will minimize errors from housing and

window thermal radiance thereby permitting

accurate air temperature measurements on high

speed/high altitude aircraft such as the High Speed

Civil Transport. The unique design will enable the

radiometer to measure true air temperature out of

aircraft traveling at Mach 2.4 at altitudes up to

20km with 0.3C precision, corresponding to a Mach

number uncertainty of 0.002. These air temperature

measurements will be needed for precise control

ofsupersonic engine operation to maximize fuel

efficiency. A multiple wavelength design will allow

prediction of upcoming air temperature variations

to prevent engine unstarts.

Potential Commercial Applications (Limit 200 words)

Potential Commercial Applications

The proposed radiometer will enable accurate air

temperature measurements from high-speed

aircraft and could become an important component

of the HSCT program. In addition, range-resolved

temperature measurements will warn of potential

engine unstart conditions.

The proposed radiometer may find an immediate

market on commercial aircraft providing warning of,

and possibly permitting avoidance of, clear air

turbulence. Additionally, it may allow detection of

approaching icing conditions.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Dr. Stuart P. Beaton

OPHIR Corporation

10184 West Belleview Avenue, Suite 200

Littleton , CO 80127

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Mr. James F. Miller

OPHIR Corporation

10184 West Belleview Avenue, Suite 200

Littleton , CO 80127

Form 9.B Project Summary

Chron:

970422

Proposal Number:

04.02-4447

Project Title:

LOW NOISE EXHAUST NOZZLE

FOR A HIGH FLOW,LOW

PRESSURE HSCT ENGINE

Technical Abstract (Limit 200 words)

Environmental acceptability and economic viability

are crucial issues in the development of the next

generation HSCT (High Speed Civil Transport) and

low noise exhaust nozzle technology has a

significant impact on both issues. The design noise

level requirement for the next generation HSCT is

the FAR36 Stage III subsonic rule, with margins.

Since the propulsion system jet is nearly the sole

contributor to the community and sideline noise, the

technology for low noise exhaust nozzle is key to

the HSCT environmental acceptability. To be

economically viable, the low noise exhaust nozzle

must be simple, light weight, and have good

aerodynamic performance throughout its operating

range. A simple axisymmetric plug suppressor

nozzle is presented that reduces the jet velocity at

takeoff, to meet FAR36 Stage III noise levels,

including margin requirements; delivers high

specific thrust at transonic and supersonic cruise;

and delivers high nozzle efficiencies (greater than

0.95), for high performance, at takeoff, transonic

acceleration, subsonic and supersonic cruise flight

conditions. A conceptual design study is proposed

to investigate a low pressure axisymmetric

suppressor nozzle. The conceptual design will

address acoustics, aerodynamic performance, and

mechanical design requirements, as well as their

effects on aircraft takeoff gross weight (TOGW), of

FAR36 Stage III compliance and good nozzle

performance.

Potential Commercial Applications (Limit 200 words)

This effort will provide conceptual design of a low

pressure, axi-plug suppression exhaust nozzle for a

high flow, low pressure (VFX) engine concept. The

proposed nozzle concept utilizes proven suppression

technology that will reduce jet noise, provide good

aerodynamic performance, while save nozzle weight

and reducing mechanical complexity. When applied

to a HSCT or supersonic aircraft, the proposed

exhaust nozzle in conjunction with a VFX engine

cycle has a unique advantage over MFTF engine

cycles using ejector/suppressor nozzles, in its ability

to meet FAR 36 Stage III noise requirements, with

margin, at takeoff conditions.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Bernard Niehaus

Diversitech, Inc.

110 Boggs Lane, Suite 325

Cincinnati , 0h 45246

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

James Askew

Diversitech, Inc.

110 Boggs Lane, Suite 325

Cincinnati , OH 45246

Form 9.B Project Summary

Chron:

971033

Proposal Number:

05.01-1700A

Project Title:

Pilot Voice Recognition for GA Aircraft

Technical Abstract (Limit 200 words)

The innovation proposed by Advanced Creations,

inc.(ACi) is to provide

a generic hands-free interface for general aviation

avionics systems.

ACi will analyze the impact of aircraft vibration,

ambient noise

levels, stress, G forces and atmospheric pressure

changes on the

accuracy of speech recognition algorithms,

developing the basis for an

innovative speech interface that will be low cost,

highly noise

immune, and capable of high level word command

recognition. The ACi

development will leverage the extensive speech

recognition research

funded by the banking community, Wright

Patterson AFB, and others,

coupled with advanced headphone/microphone

technology research being

performed by the cellular phone industry, and the

cockpit research

performed by the military. While tremendous

speech recognition

progress has been made, the existing research has

focused on rather

benign environments when compared to the cockpit.

Incorporation of

solutions for reducing the effects of ambient noise

through integrated

microphone/ headphones will be vital to program

success. We will

utilize the research results from various Air Force

and military

research programs via a Cooperative Research and

Development Agreement

already in place. The interface redundancy offered

by the proposed

system will ensure that performance and safety

levels in general

aviation cockpits increase significantly.

Potential Commercial Applications (Limit 200 words)

The achievement of the objectives of this proposed

SBIR program will

result in a readily exploited commercial product

with tremendous

market demand. An affordable generic hands off

interface will permit

the 21st century pilot to take full advantage of the

advanced avionics

systems being developed under the AGATE

program and others.

Achievement of the full potential of the AGATE

developments will

demand full utilization of the latest avionics systems

that permit the

pilot access to real-time weather and traffic data

and rapid

replanning capabilities. To fully utilize these

advances in a high

stress environment, a hands off pilot-system

interface will contribute

toward increased pilot performance and enhanced

safety.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Mr. Curtis W. Wray

Advanced Creations, Inc.

4403 Dayton-Xenia Rd.

4403 Dayton-Xenia Rd , OH 45432

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Mr. Raymond C. Wabler

Advanced Creations, Inc.

4403 Dayton-Xenia Rd.

Dayton , OH 45432

Form 9.B Project Summary

Chron:

970778

Proposal

Number:

05.01-4565

Project Title:

Automated Manufacturing System For

Grid Stiffened Structures For General

Aviation Aircraft

Technical Abstract (Limit 200 words)

In the 1980's, the General Aviation Industry went

into a tailspin due to liability issues. During the

subsequent hiatus in activity, several proof of

concept developments appeared. These concepts

have matured in the 1990's, under the impluse of

the Advanced General Aviation Transport

Experiments Program and others. As a result the

industry has renewed technical potential to

revitalize.

To date innovative lightweight/low cost, dolphin

shaped, composite airframes, which blend the wings

and the engines into the structure at their ideal

location, have been designed and test flown.

Superior strength/weight performance has been

obtained with structures which are Grid-Stiffened

along geodesic lines. Additionally many first time

observers are stunned by the amount of

unobstructed space available within the airframe.

What is currently lacking is an automated

manufacturing capability for grid stiffened

(geodesic) structures. This issue, if unresolved, will

keep the General Aviation Industry from

developing beyond the level of prototyping and

therefore revitalization would almost certainly be

out of the question.

W. Brandt Goldsworthy & Associates, Inc.

(WBG&AI) propose to solve this problem by

integrating current composites winding and

fiber-tow placement technology with blow-molding

technology to form a liner.

The results, which we need to obtain to consider

this program a success, is a turnkey composites

manufacturing cell which is capable of making a

dozen airframes per day. This challenge is so

profound that it will require entirely new ways of

thinking, and and it will likely have to include the

advantages of thermoplstics technology.

At the end of Phase I we expect to have developed

the concepts and designs necessary to automate

grid stiffened structures manufacturing.

Potential Commercial Applications (Limit 200 words)

The benefit, as described in the abstract, is that a

sorely needed manufacturing capability is created.

This will give rise to high technology and affordable

general aviation aircraft. There is also a significant

potencial to use this manufacturing technology for

producing components and tankage for the big

commercial airliners. As commercial space

initiatives continue to develop WBG&AI also

expects that payload shrouds and rocket tanks will

be made with the automated grid stiffened

manufacturing technology.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

W. Brandt Goldsworthy

W. Brandt Goldsworthy & Associates, Inc.

23930-40 Madison Street

Torrance , CA 90505

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

George Korzeniowski

W. Brandt Goldsworthy & Associates, Inc.

23930-40 Madison Street

Torrance , CA 90505

Form 9.B Project Summary

Form 9.B Project Summary

Chron:

971218

Proposal

Number:

05.01-9859

Project Title:

A HIGH LIFT GENERATION AND

STALL/SPIN RECOVERY SYSTEM

Technical Abstract (Limit 200 words)

The proposal concerns a novel flight control

system, called "Delta Flaps" (Patent Pending) for

the generation of high lift and for stall/spin recovery

of General Aviation (GA) aircraft. The invention

addresses the need to reduce GA aircraft cost while

improving utility, performance and safety.

Compared to conventional high lift devices (HDLs)

such as flaps, the new invention requires much less

installed weight. It is simpler to integrate into the

wing design and can be deployed when the aircraft

is already in a stalled mode. The objective of the

proposed work is to generate a data base that

proves that the proposed high lift concept works

and can be used toward the development of a

generic design for the GA market. The Phase I

effort calls for flow visualization tests, for the

measurement of the polar of the model wings in a

wind tunnel, a first analysis of the aerodynamics of

the proposed HLD and flight tests of a radio

controlled airplane model with fully functional Delta

Flaps.

Potential Commercial Applications (Limit 200 words)

Delta Flaps serve as high lift generating device

during take-off and landing of aircraft, as lift

enhancing device for existing onventional flaps and

as stall/spin recovery device with either hand

operated or automatic deployment. They can be

used as either original or as retrofit system.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Dr. Dieter Nowak

MICRON CORPORATION

158 ORCHARD LN

WINCHESTER , TN 37398

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Dr. Dieter Nowak

MICRON CORPORATION

158 ORCHARD LN

WINCHESTER , TN 37398

Form 9.B Project Summary

Chron:

971548

Proposal Number:

05.02-1400

Project Title:

Low-Cost Piston Engine Health

Monitoring and Control System for

General Aviation

Technical Abstract (Limit 200 words)

The innovation proposed is a unique combination of

low cost sensors coupled with advanced adaptive

signal processing. The resulting system will

simultaneously provide vital engine diagnostics, and

advanced engine control. Sensors utilized in Phase

1 will include accelerometers and in-cylinder

pressure transducers. Event isolation will be

accomplished using active noise suppression

techniques. It is expected that by utilizing low-cost

multi-use sensors and on-board processing, the

diagnostic components of the system will more than

offset their costs due to a reduction in maintenance

requirements. Phase 1 will concentrate on

development and validation of an innovative

approach to diagnosing engine mechanical fault

conditions. The approach will be demonstrated on

two mechanical faults: excessive connecting rod

bearing wear and compression loss due to piston

ring wear. It is anticipated that the same approach

will be applicable to early detection of a number of

additional mechanical faults including piston skirt

slap, valve seating anomalies, maladjusted valve

train components, and preignition. The diagnostic

components of the production system would provide

failure prediction, thereby enhancing safety,

reducing scheduled maintenance costs, and

extending the required time between overhauls.

The control components will reduce emissions,

enhance performance and efficiency, extend enginelife, and enable single lever control.

Potential Commercial Applications (Limit 200 words)

This engine monitoring and control system

developed for piston powered general aviation

engines has direct commercial potential in the

aviation market. While very few piston powered

general aviation airplanes have been manufactured

recently, there is a promising future for growth in

the market as existing airplanes disappear from the

market and there is great potential for retrofitting

the system to existing airplanes either before or

during engine overhaul. Also, the system or a

similar system could be used in much larger

numbers in automobiles, commercial diesel, marine,

and industrial motors. Finally, adaptations of the

system could be used on turbine engines, electric

motors, or any other rotating machinery.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Keith D. Hoffler

ViGYAN, Inc.

30 Research Drive

Hampton , VA 23666

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

E. Richard White

ViGYAN, Inc.

30 Research Drive

Hampton , VA 23666

Form 9.B Project Summary

Chron:

970441

Proposal

Number:

05.02-5963

Project Title:

Lightweight Aircraft Diesel Utilizing

Carbon-Carbon Technology

Technical Abstract (Limit 200 words)

DeltaHawk proposes to utilize carbon-carbon

technology in a lightweight 2-cycle diesel engine we

are developing for general aviation use. Our

engine's design represents substantial

improvements over the current fleet's engines:

lighter weight, smaller, fewer parts, lower BSFC,

smoother running, preferred fuel type, liquid

cooling, no electromagnetic interference,

single-lever power operation, and lower cost.

Carbon-carbon pistons and liners would provide our

engine with additional improvements in:

Efficiency -- Carbon-carbon components provide

the potential for increased thermodynamic

efficiency by reducing heat transfer from the

working gas through the liner, piston crown and

cylinder fireplate. Thermodynamic efficiency

translates in operation to improved fuel efficiency.

Pollution reduction -- Higher cylinder surface

temperatures promote more complete combustion

and shorter ignition delay, and therefore less

pollutants. This benefit would augment the

inherently lower pollution levels of the engine's

diesel (excess air) combustion cycle and use of

unleaded Jet-A fuel.

Weight reduction -- The higher strength and lower

density of the carbon-carbon material can reduce

engine weight by allowing lighter pistons and

smaller crankshaft counterweights.

Potential Commercial Applications (Limit 200 words)

Many dynamics are driving the general aviation

marketplace interest in diesel engines: the need to

migrate to a non-leaded fuel; the need to reduce

emissions; fuel availability, reduced flammability

and price advantages of diesel or Jet-A over

100LL; simplicity of operation; track record of

durability; and fuel economy. The DeltaHawk

diesel technical design will provide these benefits,

and has advantages over known diesel prototypes.

DeltaHawk is within six to eight months of

producing (in Experimental status) the first aviation

diesel in our business plan: the standard upright

V-4 200 hp model. Future development, phased

over the next 2 years, includes an offset drive V-4,

standard and offset-drive 400 hp V-8 models and

potentially V-4 100 hp models (all designed for the

general aviation market). The FAA Certification

process will be initiated for each model as soon as

design is stable. The DeltaHawk 200-400 hp models

will be suitable for most aircraft currently using

150-500 hp gasoline piston engines. Sales are

anticipated for new Experimental aircraft,

replacement engines for both Experimental and

Certificated aircraft, and potentially for new

Certificated aircraft.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Douglas A. Doers

DeltaHawk, Inc.

10698 S. 76th Street

Franklin , WI 53132-9541

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Diane E. Doers

DeltaHawk, Inc.

10698 S. 76th Street

Franklin , WI 53132-9541

Form 9.B Project Summary

Chron:

971107

Proposal

Number:

06.01-0818

Project Title:

An advanced system for dynamic model

deformation and angle-of-attack

measurements

Technical Abstract (Limit 200 words)

The development of a commercially viable model

deformation and angle-of-attack measurement

system is proposed. The system will have a

real-time dynamic measurement capability of at

least 60 Hz, and an accuracy of 0.005 degrees or

better. The Phase I effort focuses on performing a

thorough optimization study and selecting an

appropriate implementation, along with the

demonstration of a prototype system. A follow-on

Phase II effort would result in a ruggedized

commercial version for operation in major NASA

wind-tunnel facilities. The significance of such a

system is that it has the potential to replace the

conventional accelerometer-based angle-of-attack

system under difficult dynamic load conditions. In

addition, it can shorten the wind-tunnel testing

process by providing accurate wind-on model

deformation information for the proper

interpretation of loads data. The approach is

innovative in its combination of the convenient

single-camera photogrammetric approach with

modern digital video systems and a new real-time

target-tracking process. By providing an accurate,

easy-to-use, non-contact measurement of several

very important model parameters, the system will

reduce wind-tunnel testing cycle time and improve

the value of performance data.

Potential Commercial Applications (Limit 200 words)

Current video-based photogrammetry systems in

use at NASA wind tunnels are still in the

development stage, and the importance of these

systems is widely recognized. In the area of

angle-of-attack measurements, there is a clear

need for an optical method to replace the current

accelerometer-based system under dynamic

conditions. Commercial active-target systems have

already been used in some NASA facilities, showing

that a market clearly exists for these systems.

Since it is built with off-the-shelf technology, the

proposed system has the potential to provide

optical angle of attack at a substantially reduced

cost compared to existing systems. In addition to

wind-tunnel applications, there is a huge market for

remote optical measurements in many other areas.

Machine vision systems are now routinely used in

factory environments for quality inspection and

process control. Other industrial applications

include architectural and terrestrial surveying, and

forensic reconstruction. In the medical field, the list

of potential applications includes the diagnosis of

muscular and skeletal problems, studies of

anatomy, and reconstructive surgery. Many of

these applications could benefit from the dynamic

capabilities of our proposed system.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Ronald H. Radeztsky, Jr.

High Technology Corporation

28 Research Drive

Hampton , VA 23666

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Mujeeb R. Malik

High Technology Corporation

28 Research Drive

Hampton , VA 23666

Form 9.B Project Summary

Chron:

971588

Proposal Number:

06.01-7833a

Project Title:

Fiber Bragg Grating Sensors for

Simultaneous Measurement of Shear

Force, Strain, and Temperature for

Aerospace Applications

Technical Abstract (Limit 200 words)

SEACOM proposes to develop new fiber Bragg

grating (FBG) sensors for wind tunnel

instrumentation to measure shear force, strain, and

temperature simultaneously. Innovations include:

· a pair of cross-tilted FBG's subjected to shear

force producing Bragg wavelength shifts in opposite

directions while producing strain and thermally

induced shifts in the same direction. A differential

measurement of Bragg shifts gives a measure of

the shear force independent of strain and

temperature. Currently such an instrument is not

commercially available;

· a dual wavelength method using co-written Bragg

gratings to measure strain and temperature

simultaneously during structural deformation of

wind tunnel models.

The Phase I research objective is to verify the

proposed concepts by conducting experiments on

FBG's subjected to fluid flow, mechanical strain and

thermal stress. In the Phase II research, sensors

will be developed that are capable of distributed or

multi-point measurement to provide more data per

tunnel-occupancy-hour. The all-optical nature of

FBG sensors makes them suitable for remote

operation and for measurement in a severe

environment of electromagnetic interference or

vibration. The proposed FBG sensors will be useful

to NASA for both cryogenic and high temperature

testing of wind tunnel models.

Potential Commercial Applications (Limit 200 words)

Commercial Applications:

- Remote and distributed flow measurement in an

explosive environment such as oil and gas pipes

- Water flow measurement in hydroelectric power

generation

- Industrial processes requiring flow and

temperature measurements

- Shear force measurements in the design of

hydrofoils

- Health monitoring of structures such as bridges

and buildings

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Jianli Zheng

Science & Engineering Applications Company

(SEACOM)

4317 Country Club Circle

Virginia Beach , VA 23455

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Arnel C. Lavarias

Science & Engineering Applications Company

(SEACOM)

4317 Country Club Circle

Virginia Beach , VA 23455

Form 9.B Project Summary

Chron:

970003

Proposal Number:

06.02-2748

Project Title:

Vibrostatic Buffeting Alleviation

Technical Abstract (Limit 200 words)

NASA Langley Aeroelasticity Branch is addressing

aircraft lifecycle costs by actively reducing the

vertical tail buffeting due to vortices originating at

wing/fuselage leading edge extensions ("LEX")

during short duration high-alpha maneuvers. In a

departure from previous methods, the system uses

an piezoelectic induced strain actuation ("ISA")

mechanism. As applied to the 1/6 scale F/A-18

Transonic Dynamic Tunnel ("TDT") model, the