New items (01/14/2001) in BLUE

 

AURORA FLIGHT SCIENCES CORP.

9950 Wakeman Drive

Manassas, VA 20110 Phone:

PI:

Topic#: (703) 369-3633

Glenn Jackson

DARPA 00-007 Title: CUAV for Precise Deployment of Communications/Sensor Packages Abstract: The best solution to deliver small, covert communications/ sensor packages is an autonomous airborne vehicle that operates outside the enemy's threat envelope: the Clandestine Unmanned Aerial Vehicle (CUAV). Aurora Flight Sciences proposes to explore CUAV designs that emulate natural or common airborne objects to deploy covert packages on the highest local terrain "perch" for maximum line-of-sight viewing. This strategy enables the delivery vehicle to loiter or cruise in the enemy's area of operation and identify the optimal site for covert package delivery. Aurora will apply its expertise in UAV configuration synthesis, flight control design, and scene interpretation to create a CUAV system to meet the Concept of Operations. Aurora will investigate a range of designs, trading cost, covertness, and military effectiveness and using the requirements to down-select for Phase II prototyping and system demonstration. Aurora Flight Sciences is an internationally recognized leader in the development and rapid prototyping of unconventional military and civilian UAV configurations. Aurora has 10 years of successful UAV design, fabrication, and operation experience, including high-altitude UAVs, Micro-Air Vehicles, Vertical Take-off and Landing UAVs, planetary UAVs, and aerodynamically unstable Unmanned-Combat Aerial Vehicle (UCAV) prototypes.

 

PHYSICAL OPTICS CORP. Engineering & Products Div. 20600 Gramercy Place, Torrance, CA 90501

Phone: PI: Topic#: (310) 320-3088 Andrew Kostrzewski AF 00-181

Title: Real-Time, Low Bandwidth, Detachable Damage Assessment Eye

Abstract: Physical Optics Corporation (POC) proposes to develop beyond-line-of-sight video processing, compression, and transmission with communications capability for ranges out to few hundred kilometers. The proposed Smart Munition Smart Sensor (SMSS) system will be capable of sending sensor data to a ground or air station, fully compressed at 2000:1 while preserving high signal quality and integrity. The sensor data will include full motion, high resolution video/IR data, and still imagery, GPS positioning and sensor fusion control. SMSS will send messages and video at extended ranges for real-time target identification, target location, and battle damage indication. The proposed research will be in two areas: high fidelity video compression to low bandwidth with minimum digital video artifacts; and wireless, real-time transmission of video from the munition to the base and control signals from the base to the munition. The R&D effort will be carried out as algorithm, software, and hardware development for both encoding and decoding as well as efficient wireless communication. The supercomputer-class (8BOPS) digital video processing, based on soft-computing technology (where POC has a leadership) will be sufficiently fast to support semi-autonomous and in near-future, fully-autonomous on-the-fly target reassignment by real-time BDI.

 


AERODYNE RESEARCH, INC.
45 Manning Road,
Billerica, MA 01821 Phone:
PI:
Topic#: (508) 663-9500
David Stickler
DARPA 96-080 Title: High Performance UAV System Design Based on High Power Microturbine Technology Abstract: A radical, high performance system design concept for UAV missions is proposed. Its characteristics derive directly from propulsion and power generation capabilities inherent in microturbine technology under development at MIT. The proposed vehicle configurations is an oblate spheroid, giving a high package volume with sufficient fuel capacity for hover duration of about one hour. Thrust from multiple microturbines is used directly for propulsion, maneuver and hover, with control implemented via pulsed on-off operation of selected engines. The result is a High Performance Aerial Vehicle (HIPERAV), carrying a large instrument package, which incorporates sensor, data transmitter, and mission/vehicle control functions. This is conceived as an interchangeable plug-in unit, with programmable capability. Electrical power is taken from one or more of the propultion turbines, resulting in very high power for data transmission. This implies both a high data rate capability, and potential for satallite interfacing, despite the limited antenna size and efficiency. Specific approaches for implementation of this concept, and their mission and vehicle implications are outlined in the proposal. Based on this, a preliminary system definition study of vehicle and mission utilization is proposed. It will address mission and hardware interpendence, and define key technology limitations requiring Phase II development.


AEROVIRONMENT, INC.
4685-3H Industrial Street,
Simi Valley, CA 93063 Phone:
PI:
Topic#: (805) 581-2187
Matt Keennon
DARPA 96-080 Title: Micro Unmanned Aerial Vehicle (UAV) System Design and Operation Abstract: Aerovironmet Inc. proposes to undertake Phase I of DDARPA SBIR 962-080 to develop and assess operational utility of micro air vehicles (micro AV) for unique military applications. We will downselect from nine general categories of airframes, four general categories of propulsion systems to a minimum of five conceptual designs. These design concepts will be evaluated against notional mission scenarios, using analytical and empirical testing of partially completed systems to establish a figure of merit (FOM) for each design relative mission. The FOM analysis will be used to select 3 configurations of flight test and evaluation of operation. Flights will be documented with video, and the designs will be documented with level 2 drawings and preliminary cost metric of the system. Vehicle and complete, developed micro AV system cost metrics will also be developed. Specific missions are expected to be best met by specific micro AV operational concepts, system concepts, and predicted performance parameters.


ALPHATECH, INC.
50 Mall Rd.
Burlington, MA 01803

Phone:
PI:
Topic#:
(617) 273-3388
Nils Sandell
DARPA 96-050
Title: Advanced Collection Management
Abstract: The objective of the research effort will be to apply optimization technology to developing a coordinated collection plan for a set of airborne platforms. This problem is important because of the imminent addition of the Tier2+ (Global Hawk) and Tier3- (Dark Star) Unmanned Air Vehicles (UAVs) to current intelligence, Surveillance, and Reconnaissance assets. It is difficult because of the large number of variables and numerous constraints that must be satisfied by the collection plan. Our approach is to decompose the problem into computationally feasible sub-problems to determine collection platform tacks, target-to-track assignments, and collection schedules. In Phase I, we will demonstrate a solution to the assignment and scheduling subproblems based upon algorithms for solution of large scale combinatorial optimization problems developed by ALPHATECH researchers. We will implement a capability for a user to view targets and platform tracks on a map background, algorithms to set up and solve the corresponding assignment and scheduling problems, and graphical display of the results. The Phase II effort will extend Phase I by implementing a comprehensive solution methodology and developing a plan for insertion in the theatre level collection management systems such as the Joint Collection Management Tool (JCMT).

AMERICAN ELECTRONICS, INC.
8229 Boone Blvd., Suite 200
Vienna, VA 22182

Phone:
PI:
Topic#:
(703) 883-0506
Patrick Johnson
DARPA 96-081
Title: Micro-Unmanned Aerial Vehicle (MUAV) Critical-Technologies-Communications Architecture
Abstract: This proposal addresses the requirements for a Micro Aerial Vehicle (uAV) communications systems. The RF link between an airborne uAV and uAV Ground Control Station (MGCS) presents significant technical challenges. The central issue is the competing requirements of communications system complexity necessary to overcome the multiple communication link degradations versus the necessity for miniaturization to accomodate the size and weight constraints of the uAV platform. An approach is considered which would maximize the leverage possible from existing infrastructure and communications systems. The existing commercial cellular phone network is a possibility for the uAV/MGCS link. PCMCIA cards are considered simultaneously as part of the airframe and ground station and, as a "snap in and snap out" uAV communication system modules which are selected and installed in response to mission requirements. This proposal will result in a Preliminary Design for prototype uAV/MGCS communications system which will be developed and demonstrated in Phase II. The Preliminary Design will be sufficiently detailed to demonstrate the feasibility of the proposed Phase II prototype.

AURORA FLIGHT SCIENCES, CORP.
9950 Wakeman Drive,
Manassas, VA 20110 Phone:
PI:
Topic#: (703) 369-3633
Ben Motazed
DARPA 96-081 Title: Aerodynamics and Flight Control Design for Hovering MUAVs Abstract: Aurora Flight Sciences, with expertise in designing and manufacturing low Reynolds number high-altitude aircraft, proposes to develop new aerodynamics computational tools and flight control solutions to enable the development of 15cm and smaller hovering micro unmanned aerial vehicles (MUAV)s. The objective of this project is to validate the analytical approach, and refine the proposed MUAV design by proof-of-concept experiments and demonstrations. The Phase I project will result in the development of an aerodynamically efficient hovering MAUV, augmented by a passive stabilization control scheme, to exhibit functional hovering and control performance to accommodate the integration of miniaturized electronic subcomponents in Phase II.


GORCA SYSTEMS, INC.
P.O. Box 2325
Cherry Hill, NJ 08034

Phone:
PI:
Topic#:
(609) 273-8200
Hesham Attia
DARPA 96-070
Title: A Micro SAR Sensor for Small UAVs
Abstract: A synthetic aperture radar (SAR) micro sensor of extremely low weight and power, and small size is proposed. The sensor offers a low-cost, all-weather/all-visibility-conditions high-resolution imaging capability from a small UAV to individuals and small units for surveillance and targeting purposes. In addition to being able to see through smoke, fog, etc. and its around-the-clock mission capability, SAR provides the valuable range information and it's particularly sensitive to man-made metallic objects such as tanks, artillery pieces, and various ground vehicles. A special proprietary radar configuration, made possible by GORCA's data-adaptive motion compensation techniques, results in the ultra-lightweight/low-cost construction. The sensor does not require the placement of INS or IMU equipment on board the UAV. Depending on system parameters, the total weight of the proposed imaging payload is expected to range between 0.1 and 0.5 lb. A side-looking, lightweight, low-profile microstrip SAR antenna is to be employed. The rest of the payload is expected to occupy few cubic inches. Phase I will consist of concept development, trade-off analysis of system parameters (impacting size, weight, and power), performance assessment, and a detailed design of a prototype to be built and demonstrated during Phase II.

IGR ENTERPRISES, INC.
11000 Cedar Ave.
Cleveland, OH 44106

Phone:
PI:
Topic#:
(216) 464-1255
Arnold Gordon
DARPA 96-081
Title: Low Weight, Zero Maintenance Long Endurance SOFC for MUAV
Abstract: The overall objective of this SBIR project is to design and demonstrate an enabling technology for the power supply of micro unmanned aerial vehicles. This MAUV power technology is lightweight and very high in energy density. IGR will develop a stainless steel/ductile-ceramic-composite SOFC, using pre-loaded carbon fuel, to meet the power supply needs of MUAVs. The technology provides for long endurance flights with zero maintenance requirements. The use of powered C(s) in the fuel plenum of each cell eliminates all fuel tanks, pumps, lines and processing. The maintenance free shelf-life of all solid-state system is essentially unlimited.

 

INTELLIGENT AUTOMATION, INC.
2 Research Place, Suite 202
Rockville, MD 20850

Phone:
PI:
Topic#:
(301) 590-3155
Joseph Iseman
DARPA 96-080
Title: Micro Unmanned Aerial Vehicle (MUAV) System Design and Operation
Abstract: A small 15cm Micro Unmanned Aerial Vehicle (MUAV), applicable in military and civilian environments, is feasible within the near future. The MUAV will meet realistic operational requirements including payload weight of up to 20 gm, maximum speed of 100 kts, range to 60 km, endurance of 20 min, altitudes up to 10,000 ft with capabilities to dash and loiter/hover, agility to maneuver upon command, and covertness of operation. It will operate in benign and hazardous (nuclear, chemical, biological) environments as dictated by battlefield mission strategies and civilian and commercial applications. Our system design study will analyze a) composite materials for airframe structural strength and skin aerodynamics; b) multi-use of structural components which double as surface-mount PC boards for electronic processing and signal and power routing; c) matched propulsion system (engine, propeller, exhaust, fuels), d) flight control systems; e) navigation and guidance systems, f) communications systems for grounded-based control up links and MUAV-developed video down links; and g) crew supported launch and recovery systems. Our operational study will consider the air vehicle, sensor camera (video and perhaps gas sampling) and other payloads, ground-mobile based unit, and crew support. We plan to use existing simulation capability final specifications. Because of the weight and size limitations in a 15cm MAUV, our concepts include a ground-based visual autopilot applying automated machine vision from down-linked video; IAI's virtual hover mythology; and launch and recovery systems. Another concept is a MAUV swarm mode.

M-DOT, INC.
3418 S. 48th Street, Suite 3
Phoenix, AZ 85040

Phone:
PI:
Topic#:
(602) 921-4128
Jon Sherbeck
DARPA 96-081
Title: Design and Test of an Unmanned Vehicle Micro-Turbine Engine
Abstract: M-DOT proposes to design, fabricate and test a tiny gas turbine which will be configured as a turbojet. The design will be based on the aerodynamic flow path of M-DOT's DARPA-funded TPR80-1 turboprop engine which is currently under test. The engine as projected, will be approximately 1/5 scale, have a static thrust of 6.2 newtons (1.4 lbs), a maximum diameter less than 4.0 cm and approximate mass of 85 g. As a gas generator supplying a tip-jet driven fan, maximum power output would be 0.75 kw (1.0 hp). On a micro UAV with characteristic length of 15 cm, this engine will afford vertical takeoff, 100 kph dash capability, hover capability and 1-hour mission duration using heavy fuel. Phase I Technical Objectives are: 1) Perform a mission and vehicle analysis to identify desired engine performance characteristics, interfaces and installation envelope, 2) Determine the engine scale that best meets the performance requirements identified by the mission study, 3) Conduct a system trade study that compares an integrated electrical generator and power conditioning electronics to a battery, 4) Design, fabricate and text a prototype turbojet, and 5) Create a Phase II program plan for design refinement, fabrication and flight test of the engine and tip-jet-driven lift fan.

PHOTO EMISSION TECH., INC.
766 Lakefield Road, Suite H
Westlake Village, CA 91361

Phone:
PI:
Topic#:
(805) 495-7817
Mantosh Chawla
DARPA 95-001
Title: Advanced Control Techniques for Autonomous Helicopters
Abstract: A behavior-based architecture for control of miniature autonomous helicopters is proposed. The architecture is hierarchical, with the lowest level behaviors ensuring craft survival and higher level behaviors performing such tasks as navigation and target location. The design and fabrication of a model helicopter embodying these principles is described, using a multitude of sensors and on-board computation. Deliverables from the study include a methodology for design and fabrication of low cost autonomous helocopters, an approach to automatic tuning of parameters to different craft,and a demonstration of autonomous, vision-guided flight. PET is interested in using autonomous helicopters for structural monitoring applications. We plan to integrate MIR technology, proposed to be developed under another SBIR proposal, on to this type of vehicle. Anticipated Military Benefits/Potential Commercial Application of the Research or Development: The autonomous helicopter when mounted with multi-sensors can be used to survey an area for detection, identifying location and type of land mines. It can also be used to help dispose of the discovered mines. The proposed project has enormous potential commercial applications. These applications include structural monitoring, scientific data gathering, crop spraying, traffic surveillance, identification of unexploded land mines, delivery of supplies to stranded travellers or hikers and photographing hazardous or hostile areas.
SCIENTIFIC SYSTEMS COMPANY, INC.
500 W. Cummings Park, Suite 3950
Woburn, MA 01801
Phone:
PI:
Topic#:
(617) 933-5355
R.K. Mehra
DARPA 95-001
Title: Low Cost Fault Tolerant Flight Controls for UAV's Using Neural Networks, System Identification & Robust Control
Abstract: Modern fligt control systems rely on hardware redundancy to overcome failures of sensors and actuators. This is an expensive approach which does not make use of analytical redundancy present in a flight control system. Analytical redundancy is achieved by comparison of sensor outputs over time and across sensors using physical and identified models. We propose here methods to detect failures using analytic redundancy and to compensate for these failures by reconfiguration of the control systems. The proposed innovation for UAV reconfigurable flight controls builds on the previous work by Scientific Systems and other companies under the sponsorship of AF on the Self-Repairing Control Systems for F-15 and integrates recent developments in the fields of Systems Identification, Robust Control and Neural Networks. Phase I will involve the following major tasks: (i) failure detection and identification using Neural Networks and on-line parameter identification (ii) reconfigurable controller design using robustcontrol theory and (iii) implementation and testing using Bell's Eagle Eye UAV simulation. Phase II will involve hardware-in-the-loop real time simulation or flight testing of the proposed system on a UAV. Bell Helicopter Textron, a manufacturer of Eagle Eye UAV will provide data and evaluation support during Phases I & II and commercialize the results during Phase III. Anticipated Military Benefits/Potential Commercial Applications of the Research or Development: The technologies of low cost fault detection, identification and reconfiguration have applications in Electric Power Systems, IVHS, Civil Aviation, Automated Manufacturing, telecommunications and Process Control.

YANKEE SCIENTIFIC, INC.
93 West Street
Medfield, MA 02052

Phone:
PI:
Topic#:
(508) 359-7999
David Brownell
DARPA 96-040
Title: Alternate Power Sources for Aerostats
Abstract: A feasibility study for the development of a Fuel-to-Aerostat Shuttling Transporter (FAST) is proposed. This powered vehicle would transport liquid fuel from the ground to an aerostat, guided by the non-powered control tether. The fuel carried to the aerostat will be used to produce electricity by running existing liquid-fueled generators on-board the ship. By allowing for the delivery of fuel on a daily basis, the aerostat can be kept on station definitely. This would have significant advantages for medium-altitude (25,000 ft) aerostats that may be used for early warning of incoming airborne threats. The objectives for this program include the full assessment of the technical and economic feasibility of the proposed FAST system. This will include a review of the requirements that exist in the civilian sector for aerostat fuel transport systems. Evaluations will be made of the energy efficiency of the propulsion system, the control requirements and the mechanics of the docking and tether guide connections. Also, a detailed conceptual design will be developed for a demonstration FAST system that could be constructed in a Phase II effort.

CREARE, INC.
PO BOX 71
HANOVER, NH 03755

Phone:
PI:
Topic#:
(603) 643-3800
DR. MICHAEL G. IZENSON
AF 98-173
Title: Hybrid Convector/Radiator for High Altitude UAVs
Abstract: The objective of this project is to enable unmanned aircraft to fly at higher altitudes with larger payloads for longer-duration missions using turbocharged, internal combustion engines. Heat rejection typically limits the performance of these aircraft. We propose to develop a compact, lightweight heat rejection system that provides intercooling for the multi-stage turbocharging system and engine cooling. Innovative heat exchangers and optical coatings enable the aircraft to make optimal use of thermal radiation and ram-air for heat rejection. In Phase I we prove the feasibility of this system through design and analysis of the system components.

THERMACORE, INC.
780 EDEN RD
LANCASTER, PA 17601

Phone:
PI:
Topic#:
(717) 569-6551
ALFRED L. PHILLIPS
AF 98-173
Title: Hybrid LHP/Composite Heat Rejection Panels for UAV
Abstract: Ongoing work should lead to a flight test of a Loop Heat Pipe based anti icing system in late 1998 or early 1999 aboard the Global Hawk UAV. The Loop Heat Pipe condenser tubing will be integrated into the composite skin of the engine inlet cowl. This essentially turns the composite skin into a radiator panel. The proposed program will address and quantify the use of these panels as heat rejection radiators. Such radiator panels can be applied to most of the upper surface of the aircraft and are equally suited for convective or radiative heat rejection. The concept supports a self-contained by-pass system which will autonomously switch in additional panels as the system temperature rises in response to diminished convective heat loss with altitude so the system will passively maintain operating temperature limits. The avionics compartment of the Global Hawk is presently cooled by pumping fuel through the compartment. The proposed system will keep the fuel out of the avionics compartment and also increase operating margins for end-of-mission conditions.

GENEVA AEROSPACE, INC.
PO Box 613018
Dallas, TX 75261

Phone:
PI:
Topic#:
(972) 317-3124
David A. Felio
AF 98-177
Title: Examination of an Integrated Autopilot Design for Simplified UAV Flight Control
Abstract: In order to be truly versatile, Unmanned Aerial Vehicle (UAV) Systems must be usable to individuals who's training is more focused on the requirements of a given mission or on the usability of the payload, rather than on the aviation of the air vehicle. This suggests that flight control systems must respond to higher level, more intuitive remote commands such as "go left", "go right", "climb", or "dive". Modern embedded guidance and control processing methods such as those used for autonomously guided cruise missiles or advanced military aircraft demonstrate that low-level stick-and-rudder commands can be eliminated as a requirement on the remote operator. In addition to a more intuitive command-response autopilot, Geneva Aerospace has developed a design which allows the integration of intuitive "mission-level" remote commands into the guidance system, significantly reducing the work-load on the operator as it pertains to the aviation of the UAV. The guidance system is evaluated on the Freewing Tilt-Body airframe, which provides unique inherent acamera stabilization and "Extremely" Short Take-off and Landing properties. The integrated guidance design and systems engineering approach proposed provides a modular core structure that can easily be upgraded and can grow with increasing technology.

ENIGMATICS, INC.
P.O. BOX 39111
WASHINGTON, DC 20016

Phone:
PI:
Topic#:
(202) 244-4392
DAAVID L. BOOK
AF 98-232
Title: Small Air Breathing Vector Thrust PDE (VTPDE) for UAV and Other Applications
Abstract: This SBIR Phase I proposal is aimed at increasing power density, enhancing modularity, and reducing cost through the use of Pulse Detonation Engines (PDEs). The proposed propulsion system is based on a new engine concept that provides higher specific impulse than rockets or tubojets. It is more efficient than conventional engines because of its constant-volume, nonsteady operating cycle and has no moving parts in the power productin section. In PDEs a detonation wave is initiated in a mixture of aspirated air and fuel and propagates axially in the detonation chamber. Thurst is generated when the wave impinges on the thrust wall. The use of multiple chambers allows thrust vectoring and enhances engine reliability and efficiency. PDEs are more efficient than tubojets at small scale, require no exotic materials, and are less expensive to build. Their structural efficiency is greater than that of IC engines and they can operate at higher speeds. They avoid the power density limitations of electric power generation and the low specific impulse of solid propellants, and can incorporate thrust vectoring and thrust level control, which enhances maneuverability. We will develop and demonstrate a low-cost air-breathing propulsion system that can be used for existing systems and adapted to future advanced programs.

AVEOX, INC.
331324 VIA COLINAS #103
WESTLAKE VILLAGE, CA 91362

Phone:
PI:
Topic#:
(818) 597-8915
DAVID PALOMBO
AF 98-234
Title: HIGH PERFORMANCE ELECTRIC MOTOR FOR UAV
Abstract: Electric-powered Unmanned Aerial Vehicles (UAV) are becoming more prominent component of the militaries' arsenal. Brushless DC motors are the most efficient and lightest weight of all motor topologies, and is the most common type of motor used for propulsion. Aveox proposes to develop a state-of-the art brushless electric motor system for a high altitude UAV. This motor will drive a 6ft Dia. propeller without the use of a gear box. The basis for the design will be a continuation of the work that Aveox has been doing under a Joint Sponsored Research Project (JSR) with Boeing Aircraft, UCLA and NASA. The motor currently under development incorporates advanced materials and promises to set a new standard for power density and efficiency. Aveox proposes to further optimize the motor through three separate efforts: 1) Design a light-weight cooling system incorporating heat pipes, 2) Create an extremely light weight housing made from carbon fiber and 3) Further optimize the magnetic circuit via length and widing changes. the results of Aveox's efforts will be a motor system design suitable for flight tests inthe Phae II development.

AVEOX, INC.
31324 VIA COLINAS #103
WESTLAKE VILLAGE, CA 91362

Phone:
PI:
Topic#:
(818) 597-8915
DAVID PALOMBO
AF 98-234
Title: HIGH PERFORMANCE ELECTRIC MOTOR FOR UAV
Abstract: Electric-powered Unmanned Aerial Vehicles (UAV) are becoming more prominent component of the militaries' arsenal. Brushless DC motors are the most efficient and lightest weight of all motor topologies, and is the most common types of motor used for propulsion. Aveox proposes to develop a state-of-the-art brushless electric motor system for a high altitude UAV. This motor will drive a 6 ft Dia. propeller without the use of a gear box. The basis for the design will be a continuation of the work that Aveox has been doing under a Joint Sponsored Research Project (JSR) with Boeing Aircraft, UCLA and NASA. The motor currently under development incorporated advanced materials and promises to set a new standard for power density and efficiency. Aveox proposes to further optimize the motor through three separate efforts: 1.) Design a light-weight cooling system incorporating heat pipes, 2.) Create an extremely light weight housing made from carbon fiber and 3.) Futher optimize the magnetic circuit via length and winding changes. The results of Aveox's efforts will be a motor system design suitable for flight tests in the Phase II development.

PHYSICAL SCIENCES, INC.
20 NEW ENGLAND BUSINESS CENTER
ANDOVER, MA 01810
Phone:
PI:
Topic#:
(978) 689-0003
MICHAEL C. KIMBLE
AF 98-234
Title: REGENERATIVE MICRO-FUEL CELL FOR UAVS
Abstract: This Small Business Innovative Research Phase I Project develops a compact regenerative proton exchange membrane fuel cell. The design approach for this project is specific to the development of an electrolyzer and fuel cell unit giving an energy storage capability greater than 250 W-hr/kg. A modular arrangement of membrane and electrode assemblies gives a wide variety of fuel cell designs for variable power and voltage applications while maintaining low weights. The improved packaging design allows power densities much greater than 1 kW/liter to be obtained. Coupled with the innovative design, the electrochemical reactions for both anode and cathode are optimized to take advantage of the design approach. The major benefits of the proposed approach are a higher power density and specific energy density that are attainable independent of orientation, a feature that allows wider applicability and usage of the fuel cell and electrolyzer unit.

D-STAR ENGINEERING
4 Armstrong Rd,
Shelton, CT 06484
Phone:
PI:
Topic#:
(203) 925-7630
S. Dev
DARPA 98-005
Title: D' HovRobot: Sensor Elevating System Capable of Tethered Hover and Free Flight
Abstract: D'HovRobot is a rotor-less V/STOL UAV to meet the needs for tactical sensor elevation. It can operate on a tether, using cabled electrical power, or as a free-flyer, using an engine. It have a VTOL version for close-range operation, and a STOVL version for longer-range / helicopter-escort missions. The rotorless UAV can fly safely close to trees, wires and buildings. D'HovRobot is designed for carriage within, and deployment from, one HMMMV. It has a swappable power module with dual electric motors when tethered, or with lightweight D-STAR Diesel engine for free flight. The tethered hovering UAV can have empty fuel tanks, but can then support the weight of 300 feet of tether cable. Phase I scope of work includes design of a prototype vehicle and its transportation, deployment and stowage systems, definition of subsystems, projection of performance envelope, evaluation and selection of enabling technologies, evaluation of system feasibility, and definition of plans for fabrication and testing of a prototype. The team includes Teledyne Ryan, AAI Corp., Electronic Power Conversion, and Mechanical Power Conversion, as subcontractors. They are expected to play more significant roles in Phase II, and may play lead roles in Phase III.

PERCEPTRONICS, INC.
21010 Erwin Street,
Woodland Hills, CA 91367

Phone:
PI:
Topic#:
(818) 884-7470
Tom Lubaczewski
DARPA 98-005
Title: Development of the Commander's Observation Vehicle for Elevated Reconnaissance (COVER)
Abstract: Perceptronics and its team members Moller International and Flyer Group will design a complete elevated sensing system for forward-deployed combat units. The system, called COVER (Commander's Observation Vehicle for Elevated Reconnaissance), features an existing compact, electrically-tethered, ducted-fan lifting vehicle (Aerobot) mated to an existing highly-mobile, transportable vehicle (Flyer II ) that is representative of future scout and reconnaissance vehicles. The Phase I Design Study includes: 1) Review of mission applications, focusing on those currently identified for the RST-V and similar advanced vehicles; 2) Design of COVER system architecture and constituent COVER sub-systems, focusing on ease of deployment and use and on the identification of commercial off-the-shelf components that can meet immediate mission needs; 3) Analysis of key technical and tactical problem areas potentially impacting system effectiveness, such as detectability, stability, FOV, maneuverability, etc., including evaluation of their severity and direction for solution. The output for the Phase I Design Study will provide: 1) The technical and tactical basis for immediate Phase II production of the prototype COVER system; and 2) A guide to general application of the COVER concept for other DoD organizations and commercial users, including contractors participating in the RST-V and related advanced vehicle programs.

INFRAMETRICS, INC.
16 Esquire Road,
North Billerica, MA 01862

Phone:
PI:
Topic#:
(978) 670-5555
Richard McMorrow
DARPA 98-006
Title: Lightweight Imaging Sensor System
Abstract: This program will produce a design for a cost effective sensor suite suitable for mid to long range surveillance, integrated into a small, mobile, lifting body. In Phase I, tradeoffs of the two most expensive components, the camera sensor and the platform stabilizer, will be examined. InSb and the newer uncooled microbolometer detectors will be compared taking into account system performance (driven primarily by the detector and optics selection) and costs involved. Platform stabilization addressing gyro stabilized gimbals and lower cost pan and tilts will be examined and compared for an aerostat platform with a goal of deriving a lower cost pan and tilt with adequate performance. Findings will be reviewed with the customer to determine the optimal low cost airborne surveillance system. Preliminary costing estimates indicate system cost could be substantially reduced. After the sensor selection is made, a system prototype design will determine the instrumentation suite, which includes the sensors, position control, platform stabilization, communication, receiving console, monitors and control for a stationary aerostat platform. Phase I will also provide detailed information on the production power, weight, cost, and performance, worked in tandem with the design. In Phase II, Inframetrics will draw on this information to build and demonstrate a prototype sensor suite, designed in Phase I. IR system modules and technology from former development efforts will be leveraged for prototype construction and test.

SONOMA DESIGN GROUP, LLC
400 Breezewood Drive,
Geyserville, CA 95441

Phone:
PI:
Topic#:
(707) 857-2010
John Speicher
DARPA 98-006
Title: Lightweight, Low Cost Imaging Sensor System
Abstract: Sonoma Design Group LLC (SDG) will design an ultra-lightweight low-cost long stand-off reconnaissance system for use on a small aerostat. The system includes the hand control, monitor, recorder, airborne data link, gimbal, IR imager and Daylight TV. Airborne weight is 25 lbs. The system will identify men from 15 km and trucks from 45 km. The gimbal will have 360 deg continuous azimuth rotation capability and will stabilize the sensors to 5 microrad RMS. The system will operate on <300 w and be easy to apply to any low speed airborne vehicle. SDG will work to a cost goal of $150k in low rate production. SDG has formed a team of capable companies to carry the effort from design to production. During Phase I and II, SDG will do the initial system and gimbal design and fabrication, other members of our team will supply proven standard imagers, gimbal sub-components, and data link technology. Upon completion of Phase II, our team will carry the reconnaissance system into production.

FOSTER-MILLER, INC.
350 Second Avenue
Waltham, MA 02154

Phone:
PI:
Topic#:
(781) 684-4233
Roger Demler
NAVY 98-112
Title: Small, Rugged Internal Combustion Engine
Abstract: A small twin cylinder 4-cycle engine will be developed to propel a gun launched UAV. The technology exists to start and run this engine on relatively safe jet fuels at high efficiency and relatively low noise and thermal signature. Fuel consumption will be half that of a comparable 2-cycle. Relatively conservative ratings compared to automotive practice suggests long life and reliability that will be more important in other continuous duty and reusable military applications such as generator sets, robot propulsion and portable tools.

SONEX RESEARCH, INC.
23 Hudson Street
Annapolis, MD 21401

Phone:
PI:
Topic#:
(410) 266-5556
Dr. Andrew A. Pouring
NAVY 98-112
Title: Sonex Combustion System (SCS) Small, Rugged Internal Combustion Engine Operating on Heavy Fuels
Abstract: Sonex Research, Inc. proposes to develop a small (5 lb.), rugged (gun- launchable), low-cost, spark-ignited (SI) internal combustion engine that runs on a shipboard-safe heavy fuel for application to aircraft propulsion and electric power generation. The design will use an innovative extension of the Sonex Combustion System (SCS). SCS itself is now being applied to convert gasoline fueled engines to use heavy fuels in small Unmanned Aerial Vehicles (UAV's) such as EXDRONE and is undergoing UAV testing at the U.S. Naval Research Laboratory (NRL), the USMC Systems Command in Quantico, and the U.S. Naval Air Warfare Center, Patuxent River. Commercial SI gasoline engines will be identified and their SCS conversion potential assessed. The SCS NRL design will be scaled to the engine most suitable for this application. Under subcontract, Science Applications International Corporation (SAIC) of McLean, VA will help design modifications to the engine necessary to meet the 9000g setback acceleration and other SBIR transition interface requirements. The contract deliverable will be a Final Report detailing the project objectives, work performed, results obtained, including testing on a prototype engine, and estimates of technical feasibility.

VERITAY TECHNOLOGY, INC.
4845 Millersport Highway, PO Box 305
East Amherst, NY 14051

Phone:
PI:
Topic#:
(716) 689-0177
James T. Barnes
NAVY 98-112
Title: Small, Rugged Internal Combustion Engine
Abstract: The Department of Defense has a growing interest in unmanned aerial vehicles (UAVs) to provide over-the-horizon surveillance, detection, classification and destruction of time-critical surface targets. Forward Area Support Munition (FASM), a Navy ATD program approved for FY99 start, is a 5-inch gun-launched projectile that transforms into a propeller propelled UAV. A future engine for the system must sustain 9000 g gun launch, generate 4 Bhp, integrate into a 5-inch diameter-18-inch long cavity, and reliably start and function using a heavy low vulnerability fuel such as JP-5. To meet these requirements, Veritay proposes a compact uniquely configured 2-stroke cycle-2 cylinder cluster engine concept that exhibits inherent acceleration hardening characteristics and many other beneficial features. The proposed Phase I effort includes conceptual engine design to meet system requirements, experimental demonstration of a heavy fuel operating concept using a modified conventional engine, and analysis to show the ability of the engine design to survive a high-g gun launch. Detailed engine and control component design will occur during the Phase I optional program to permit fabrication and test early in Phase II.

AURORA FLIGHT SCIENCES CORP.
9950 Wakeman Dr.
Manassas, VA 20110

Phone:
PI:
Topic#:
(703) 369-3633
Dr. John Langford
NAVY 98-150
Title: Optical TCAS For UAVs
Abstract: In order to operate outside military ranges, UAVs need a means of achieving "see and avoid" at least equivalent to that achieved in manned aircraft. In this project, we propose to take low-cost visual image processing devices currently being developed by Mercedes-Benz as collision avoidance devices for the automotive market and adapt them for use in UAVs. We will use the analysis tools and encounter logic developed for the Traffic Alert and Collision Avoidance System (TCAS) to create an "Optical TCAS" that operates passively and can be installed at extremely low cost. We will use unique panospheric mirrors to achieve 360 degree coverage around the UAV without the need for complex and expansive scanning systems. Development and testing of this system will be facilitated through the use of Aurora's "Chiron" optionally piloted aircraft, which will allow continuous testing aboard an actual UAV operating in the National Airspace System. In Phase I, we will collect data on component performance and perform system trade studies. In Phase II, we will fabricate a prototype system, conduct ground tests, install the system Aurora's optionally piloted aircraft, the "Chiron," and fly actual test encounters to measure in-field effectiveness.

LYNNTECH, INC.
7610 Eastmark Drive, Suite 202
College Station, TX 77840

Phone:
PI:
Topic#:
(409) 693-0017
Alan Cisar
DARPA 99-004
Title: Integrated Energy Supply and Wing Structure for Micro Unmanned Aerial Vehicles
Abstract: Interest in micro unmanned aerial vehicles (abbreviated as MAVs and defined as less than 6 inches in their longest dimension) is increasing due to their ability to avoid detection and give combat forces a flexible and immediate intelligence source. While vehicle concepts abound, they all face a common problem; very low-speed flight requires proportionately more power than higher speed flight. This creates a need for a small, light weight, high energy density power supply. One way to achieve the needed energy density is to build the power supply function into another part of the vehicle through the use of multifunctional structures. This can be done by fabricating wings with monopolar fuel cells as their external surfaces, serving as both wing surface and power supply. This produces only a minimal increase in drag, and forward motion supplies air, with only 50 cm2 of cell area required to supply 5 watts of power. The internal portion of the wing serves as the fuel tank, with the fuel cell stack as one surface. Further weight reductions can be achieved by using the metal current collectors within the fuel cells as antennas.

ADVANCED POWER TECHNOLOGIES, INC.
1250 24th Street, NW Suite 850
Washington, DC 20037

Phone:
PI:
Topic#:
(202) 223-8808
Dr. Peter Koert
NAVY 99-152
Title: Power Beaming of Millimeter-Waves for UAVs
Abstract: The Navy has a requirement for remotely powering UAV's to permit prolonged duration missions; and to eliminate the requirement for tethering during near-ship operations. A capability to power UAV's by beaming millimeter-wave power from a transmitter to the UAV, and converting the received energy into electrical power by means of a rectenna (a half-wave dipole array with integrated diode rectifiers) offers a uniquely versatile solution to both requirements. APTI possesses unique knowledge and expertise in rectenna technology; and has been granted two patents on mm-wave rectenna. APTI proposes to apply unique knowledge, patented rectenna technology and related mmw expertise to these requirements. The application of APTI's extensive high power microwave and millimeter wave technology expertise and of its experience with complex system integration will enable full consideration to the system design and operating frequency determination. Through the use of innovative high density designs and advanced materials APTI will address the critical issues of high efficiency and very lightweight packaging. APTI will use experience gained in previous 35 GHz and 94 GHz rectennas to assure optimal performance capabilities. This will lead to lightweight high efficiency power systems suitable for UAV and Micro-UAV sustained mission applications.