DEFENSE ADVANCED RESEARCH PROJECTS AGENCY
FY2008.2 SBIR Proposal Submission
DARPA’s charter is to help maintain U.S. technological superiority over, and to prevent technological surprise by, its potential adversaries. Thus, the DARPA goal is to pursue as many highly imaginative and innovative research ideas and concepts with potential military and dual-use applicability as the budget and other factors will allow.
DARPA has identified technical topics to which small businesses may respond in the fiscal year (FY) 2008 SBIR solicitation (FY2008.2). Please note that these topics are UNCLASSIFIED and only UNCLASSIFIED proposals will be entertained. Although they are unclassified, the subject matter may be considered to be a “critical technology” and may be subject to ITAR restrictions. If you plan to employ NON-U.S. Citizens in the performance of a DARPA SBIR contract, please inform the Contracting Officer who is negotiating your contract. These are the only topics for which proposals will be accepted at this time. A list of the topics currently eligible for proposal submission is included followed by full topic descriptions. The topics originated from DARPA technical program managers.
ALL PROPOSAL SUBMISSIONS TO DARPA MUST BE SUBMITTED ELECTRONICALLY THRU WWW.DODSBIR.NET.
It is mandatory that the complete proposal submission
-- DoD Proposal Cover Sheet, entire
Technical Proposal with any appendices, Cost Proposal, and the Company
Commercialization Report -- be submitted electronically through the DoD SBIR
website at http://www.dodsbir.net/submission.
Each of these documents is to be submitted separately through the website.
Your complete proposal must be submitted via the submissions site
on or before the 6:00am EST, 18 June 2008 deadline. If you have
any questions or problems with electronic submission, contact the DoD SBIR Help
Desk at 1-866-724-7457 (8am to 5pm EST).
Acceptable Format for On-Line Submission: All technical proposal files must be in Portable Document Format (PDF) for evaluation purposes. The Technical Proposal should include all graphics and attachments but should not include the Cover Sheet or Company Commercialization Report (as these items are completed separately). Cost Proposal information should be provided by completing the on-line Cost Proposal form. This itemized listing should be placed as the last page(s) of the Technical Proposal Upload. (Note: Only one file can be uploaded to the DoD Submission Site. Ensure that this single file includes your complete Technical Proposal and the additional cost proposal information.)
Technical Proposals should conform to the limitations on margins and number of pages specified in the front section of this DoD solicitation. However, your cost proposal will only count as one page and your Cover Sheet will only count as two, no matter how they print out after being converted. Most proposals will be printed out on black and white printers so make sure all graphics are distinguishable in black and white. It is strongly encouraged that you perform a virus check on each submission to avoid complications or delays in submitting your Technical Proposal. To verify that your proposal has been received, click on the “Check Upload” icon to view your proposal. Typically, your proposal will be uploaded within the hour. However, if your proposal does not appear after an hour, please contact the DoD Help Desk.
DARPA recommends that you complete your submission early, as computer traffic gets heavy near the solicitation closing and slows down the system. DARPA will not be responsible for proposals being denied due to servers being “down” or inaccessible. Please assure that your e-mail address listed in your proposal is current and accurate. By the end of May, you will receive an e-mail acknowledging receipt of your proposal.
PLEASE DO NOT ENCRYPT OR PASSWORD PROTECT TECHNICAL PROPOSAL
HELPFUL HINTS:
Additional DARPA requirements:
· DARPA Phase I awards will be Firm Fixed Price contracts.
· If you collaborate with a University, please highlight the research that they are doing and verify that the work is FUNDAMENTAL RESEARCH.
· Phase I proposals shall not exceed $99,000, and are generally 6 months in duration. Phase I contracts cannot be extended.
· DARPA Phase II proposals must be invited by the respective Phase I DARPA Program Manager. Phase 2 invitations will be based on the technical results reflected in the Phase I contract and/or final reports as evaluated by the DARPA Program Manager utilizing the criteria in Section 4.3. DARPA Phase II proposals must be structured as follows: the first 10-12 months (base effort) should be approximately $375,000; the second 10-12 months of incremental funding should also be approximately $375,000. The entire Phase II effort should generally not exceed $750,000.
Prior to receiving a contract award, the small business MUST be registered in the Centralized Contractor Registration (CCR) Program. You may obtain registration information by calling 1-888-227-2423 or Internet: http://www.ccr.gov.
The responsibility for implementing DARPA’s Small Business Innovation Research (SBIR) Program rests with the Contracts Management Office.
DEFENSE ADVANCED RESEARCH PROJECTS AGENCY
Attention: DIRO/SBIR/STTR
3701 North Fairfax Drive
Arlington, VA 22203-1714
(703) 526-4170
Home Page http://www.darpa.mil
SBIR proposals submitted to DARPA will be processed by DARPA and distributed to the appropriate technical office for evaluation and action.
DARPA selects proposals for funding based on technical merit and the evaluation criteria contained in this solicitation document. DARPA gives evaluation criterion a., “The soundness, technical merit, and innovation of the proposed approach and its incremental progress toward topic or subtopic solution” (refer to section 4.2 Evaluation Criteria - Phase I - page 7), twice the weight of the other two evaluation criteria. PLEASE NOTE THAT MANY OF THE WEAKEST PROPOSALS SCORED LOW ON EVALUATION CRITERIA “C” “THE POTENTIAL FOR COMMERCIAL (GOVERNMENT OR PRIVATE SECTOR) APPLICATION AND THE BENEFITS EXPECTED TO ACCRUE FROM THIS COMMERCIALIZATION. DARPA IS PARTICULARLY INTERESTED IN THE POTENTIAL TRANSITION OF SBIR RESULTS TO THE U.S. MILITARY, AND EXPECTS EXPLICIT TREATMENT OF A TRANSITION VISION IN THE COMMERCIALIZATION-STRATEGY PART OF THE PROPOSAL. THAT VISION SHOULD INCLUDE IDENTIFICATION OF THE PROBLEM OR NEED IN THE DEPARTMENT OF DEFENSE THAT THE SBIR RESULTS WOULD ADDRESS, A DESCRIPTION OF HOW WIDE-SPREAD AND SIGNIFICANT THE PROBLEM OR NEED IS, AND IDENTIFICATION OF THE POTENTIAL END-USERS (ARMY, NAVY, AF, SOCOM, ETC) WHO WOULD LIKELY USE THE RESULTS. THE SMALL BUSINESS MUST DEMONSTRATE UNDERSTANDING OF THE END USE OF THEIR EFFORT AND THE END USERS.
ALL SELECTION/NON-SELECTION LETTERS WILL BE SENT TO THE PERSON LISTED AS THE “CORPORATE OFFICIAL” ON THE PROPOSAL.
As funding is limited, DARPA reserves the right to select and fund only those proposals considered to be superior in overall technical quality and highly relevant to the DARPA mission. As a result, DARPA may fund more than one proposal in a specific topic area if the technical quality of the proposal(s) is deemed superior, or it may not fund any proposals in a topic area. Each proposal submitted to DARPA must have a topic number and must be responsive to only one topic.
DARPA SBIR 082 Topic Index
SB082-001 Nonlinear Plasmonic Devices
SB082-002 Autonomous Detection, Acquisition, Pointing, and Tracking of Small UAVs
SB082-003 Mode-Locked TEA CO2 Laser
SB082-004 Femtosecond UV Laser Pulse Expander
SB082-005 Low Cost Radar Receivers
SB082-006 Ultra Lightweight, Low Power Thermal Camera for Micro-Platforms
SB082-007 Advanced Development for Defense Science and Technology
SB082-008 Integrated Structural Insulation to Eliminate Multi-Layer Insulation for Satellites
SB082-009 Reconfigurable Thermal Networks (RTN)
SB082-010 Small Engines Designed for High Efficiency, High Power Density and Quiet Operations
SB082-011 High Power Density Electric Motors for Hybrid Electric Air Platforms
SB082-012 Universal Sample Preparation Device for Biological Detection
SB082-013 Radiation Resistant Fabrics
SB082-014 Single Wall Carbon Nanotube Printed Integrated Circuits
SB082-015 Portable Medical Recorder
SB082-016 Multi Input Wireless Look-Through Heads Up Display (HUD) for Use in Multiple Extreme
Environments
SB082-017 High-Power, Narrow Linewidth Laser Diodes for Alkali Atoms
SB082-018 Novel Software Tools for Analyzing Massive Datasets
SB082-019 Ground Moving Target Indicator (GMTI) Radar Discrimination of Combatants versus Animals in
Severe Clutter
SB082-020 Robust Wideband Waveforms for Synthetic Aperture Radar (SAR) and Ground Moving Target
Indication (GMTI) Applications
SB082-021 Functional Interpretation of Activities and Objects
SB082-022 Summarization, Visualization and Browsing of Massive Video Archives
SB082-023 Query Refinement for Content-Based Video Retrieval
SB082-024 Novel Accelerator Architectures for Critical DoD Application
SB082-025 Tactical Telehaptic Communication (HAPTAC)
SB082-026 Open Source Information Tactical Exploitation (ONSITE)
SB082-027 Dismount Tracking in Urban Scenes
SB082-028 High Resolution 3D Reconstruction from Wide-Area Video
SB082-029 Detecting and Tracking Multiple Moving Objects from a Moving Platform
SB082-030 Path Planner for Dynamic Environments
SB082-031 Activity Models for Robots
SB082-032 Exposing Latent Information in Folksonomies for Reasoning
SB082-033 Hardware Independent Networked Active Sensor Middleware
SB082-034 Wireless Connectivity for Streaming Video
SB082-035 High Accuracy, Non-GPS Pose Estimation and Real-Time Depth Sensing
SB082-036 Capturing Insights from Firefights to Improve Training
SB082-037 Platform Independent Omni-Directional Antennas
SB082-038 Electro-Optic Frequency-Agile Modulators
SB082-039 Lithium Niobate (LiNbO3) Device with Improved Efficiency and RF Filtering Applications
SB082-040 Self-Seeded Programmable Parametric Fiber Comb Source
SB082-041 Extended Duration Arbitrary Waveform Generation over Large Bandwidths
SB082-042 High Power Parametric Fiber Blue-Green Source
SB082-043 Template-Based Lithography for Advanced Low-Volume Electronics
SB082-044 Highly Integrated Silicon (Si)-based RF Electronics
SB082-045 Innovative Approaches to Low Power, Sub-Threshold Electronic Circuits
SB082-046 Compact Multi-Spectral Micro-Optic Imager
SB082-047 Ultra-Low Noise, Wide Bandwidth Constant Current Sources for Driving Laser Diode Arrays
SB082-048 Beam Combining for High Power Quantum Cascade Laser Arrays
SB082-049 Electrically-Pumped III-Nitride Intersubband Lasers
SB082-050 Coherently Synchronized Distributed Signal Generation
SB082-051 Efficient Small Antennas
SB082-052 Indium Gallium Nitride (InGaN) Solar Cell
SB082-053 Low-Cost Device Relevant Indium Gallium Nitride (InGaN) or Alternatives
SB082-054 Explosion-Proof Solid State Lighting Fixture for Extreme Environments
SB082-055 A Spectrally Dynamic Berth Light for Active Circadian Cycle Management
SB082-056 Mobile Offshore Platform for Wind Turbine Power Generation
SB082-057 Non-Line-of-Sight Ultraviolet (UV) Communication Networks
SB082-058 Mission Assured Networking (MAN)
SB082-059 Continuous Detonation Rocket and Air Breathing Engines
SB082-060 Wireless Avionics Architecture for Payload Delivery Launch Systems
SB082-061 Transformational Close Air Support
SB082-062 Leap-Ahead Control Theoretic Applications
SB082-063 Energy Rejection Systems for Very High Altitude Aircraft
SB082-064 Metal Hydride Energy Sources for Very High Altitude Aircraft Propulsion
DARPA SBIR 082 Topic Descriptions
SB082-001 TITLE: Nonlinear Plasmonic Devices
TECHNOLOGY AREAS: Sensors, Electronics
ACQUISITION PROGRAM: N/A
OBJECTIVE: Full integration of electronics and photonics on a single chip has been frustrated by the huge differences in device sizes. While electronic miniaturization has proceeded rapidly to record breaking transistor sizes of only 35 nm, photonic waveguides and devices have been limited to sizes of a few optical wavelengths ~3,000 nm. For applications in integrated circuits, the comparatively huge dimensions of photonic devices relative to electronic devices have prohibited the valuable use of the large bandwidths associated with photonics. Recently, the field of plasmonics has emerged as a likely candidate to provide photonic waveguides and devices with the sizes comparable to electronic circuits. Plasmonic waveguides have been under development for several years but the technology for plasmonic devices is lacking. The objective of the Phase I is to perform a feasibility study of a nonlinear plasmonic device with dimensions much smaller than current photonic devices.
DESCRIPTION: The huge information carrying capacity of optical fiber networks is a result of the high frequency of an optical electromagnetic wave. Unfortunately, the wavelength of the electromagnetic radiation used in fiber networks, and consequently the photonic device size, is approximately one hundred times larger than typical electronic components. Increasing the electromagnetic frequency to reduce the wavelength would lead to the need for X-ray waveguides, sources, and switches. The other approach is to stay at optical frequencies but use high index dielectrics to shrink the wavelength by a factor proportional to the index of refraction. Unfortunately the latter approach can only provide a wavelength reduction of five or less.
A surface plasmon is a collective oscillation of electrons at the surface of a metal[1]. These surface waves oscillate at optical frequencies and propagate along the surface of the metal. The wavelength of a surface plasmon can be very small and comparable to the dimensions of electronic circuits. In addition, the plasmons are tightly confined to the surface with transverse decay lengths on the order of the skin depth, 10 nm. Plasmonic waveguides[2], while lossy compared with optical fibers, only need to carry information several centimeters across a chip. Thus, plasmonics is expected to be the bridge that links electronics with photonics[3-5].
It has recently been proposed that electromagnetic radiation at optical frequencies can be focused to a spot size of only 5 nm through the use of surface plasmons[6]. This extremely tight confinement of electromagnetic waves provides opportunities to fabricate photonic devices with sizes comparable to state of the art electronic devices. In accompaniment with the small volume will be large field strengths and high intensities but at very low energies. These are the ideal conditions for third order nonlinear optical devices that will have very low switching threshold energies and fast response times. Second order nonlinear optical devices for harmonic generation, etc., will also benefit from the features inherent in plasmonic devices. As seen in a recent survey of plasmonics in Ref. 7, almost no work has been done in the area of plasmonic devices. The purpose of this task is to stimulate research in the area of second and third order nonlinear optical devices based on plasmonics.
PHASE I: Conduct a feasibility analysis of a nonlinear plasmonic device with size dimensions compatible with electronic circuitry. Suggested devices include, but are not limited to, all-optical switch, optical limiter, frequency up-conversion, frequency down-conversion, self focusing, self phase modulation, and Raman scattering.
PHASE II: Finalize the device and material parameters from the Phase I. Conduct basic experimental observation of the expected performance of the plasmonic device. Design and fabricate a prototype, ultra-compact plasmonic device.
PHASE III: Possible applications for this technology span both the military and commercial arenas. The rapid increase in the clock speed of computers has slowed in recent years due to the interconnect bottlenecks on the chip itself. A plasmonic architecture is expected to alleviate the problems associated with the large size of present day optical components. In the near term, for applications not requiring an entire plasmonic ensemble of waveguides, sources, detectors, and devices, individual advances in plasmonic devices will help to couple photonics to the rapidly developing field of nanotechnology.
REFERENCES:
1. R.H. Ritchie, Plasma Losses by Fast Electrons in Thin Films, Physical Review 106, 874 (1957).
2. J.A. Dionne, L.A. Sweatlock, H.A. Atwater, and A. Polman, Plasmon slot waveguides: Towards chip-scale propagation with subwavelength-scale localization, Phys. Rev. B 73, 035407 (2006).
3. Harry A. Atwater, Stefan Maier, Albert Polman, Jennifer A. Dionne, and Luke Sweatlock, The New "p–n Junction": Plasmonics Enables Photonic Access to the Nanoworld, Materials Research Society Bulletin 30, 385 (2005).
4. Rashid Zia, Jon A. Schuller and Mark L. Brongersma, Plasmonics: The Next Chip-Scale Technology, Materials Today 9, 20 (2006).
5. S. A. Maier, M. L. Brongersma, P. G. Kik, S. Meltzer, A. A. G. Requicha, H. A. Atwater, Plasmonics - A Route to Nanoscale Optical Devices, Advanced Materials 13, 1501 (2001).
6. J. Conway, S. Vedantam, H. Lee, J. Tang, and E. Yablonovitch, What is the Smallest Volume Into Which Light Can Be Focused, Efficiently?, International Nano-Optoelectronics Workshop, i-NOW'07, p. 77 (2007).
7. E. Ozbay, Plasmonics: Merging Photonics and Electronics at Nanoscale Dimensions, Science 311, 189 (2006).
KEYWORDS: Plasmonics, Surface Plasmon, Plasmon Waveguides, Thin Films
SB082-002 TITLE: Autonomous Detection, Acquisition, Pointing, and Tracking of Small UAVs
TECHNOLOGY AREAS: Ground/Sea Vehicles, Sensors, Electronics, Weapons
ACQUISITION PROGRAM: N/A
The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), which controls the export and import of defense-related material and services. Offerors must disclose any proposed use of foreign nationals, their country of origin, and what tasks each would accomplish in the statement of work in accordance with section 3.5.b.(7) of the solicitation.
OBJECTIVE: The objective of this effort is to provide the capability to autonomously detect, acquire, declare, point, and track on small scale UAVs to range of 1 kilometer and altitude of 500 meters. The system will control a telescope with a Coude path that allows integration of a high power laser to neutralize the sensors and/or airframe.
DESCRIPTION: The use of Unmanned Aerial Vehicles (UAVs) in both Military and Civilian markets has skyrocketed in the last 3-5 years. On the battlefield, the commanders have unprecedented capability to perform Intelligence, Surveillance, and Reconnaissance (ISR) missions. UAVs are also evolving into lethal platforms1, further enhancing the Army’s ability to See First, Understand First, Act First, and Finish Decisively. Unfortunately, with the emergence of low-cost, hobbyist type aircraft with the capability to carry visible and Infrared (IR) cameras and to fly on Global Positioning System (GPS) waypoints, our adversary is rapidly encroaching on our ability to “See First”. Also, the utility of these small UAVs for terrorist activities in the civilian sector are endless2.
The use of RADARs to search an area for small UAVs have had limited success. This is due to the low Radar Cross Section (RCS) of the composite structures typically employed on these vehicles. This effort is intended to focus on the use of novel methods including, but not limited to, acoustical, Electro-Optical-Infrared (EO-IR), and polarimetry to search and monitor the civilian and military airspace. Both active and passive techniques will be considered.
PHASE I: Prepare a feasibility study that provides the framework to detect, acquire, declare, point, and track on a small UAV. For the purposes of this effort, a small scale UAV is defined as having a wingspan of less than 1 meter, a range of 1 kilometer (or better), and an operational altitude of 500 meters. The UAV structure may be constructed of foam or composite material and the propulsion system may be electric or fossil fuel. During Phase I, the performer will propose techniques for detecting and acquiring the position of the UAV and subsequent handoff to an optical pointing and tracking subsystem. The design of the optical pointing and tracking subsystem shall include a Coude path allowing the integration of a high power (~2kW) laser. Formal design of the concept will be performed, a preliminary design review conducted, and the final report generated. As part of the final report, plans for Phase II will be proposed.
PHASE II: The design from Phase I will be finalized. The detection hardware and software will be developed and integrated into the pointing and tracking optical subsystem. The pointing and tracking optical subsystem shall have the following minimum requirements:
1) Velocity (Az) > 80 deg/sec, Velocity (El) > 50 deg/sec.
2) Acceleration (Az) > 80deg/sec2, Acceleration (El) > 50 deg/sec2.
3) Maintain tracking accuracy to less than 50 microradians.
A critical design review will be performed to finalize the design and a breadboard system will be assembled. The system will be subjected to a series of qualification tests to verify and validate the design and its performance. Finally, the system will be delivered to the Weapons Sciences Directorate, AMRDEC, Redstone Arsenal, AL.
PHASE III DUAL USE APPLICATIONS: Military applications of this effort include Counter-Intelligence, Surveillance, and Reconnaissance (C-ISR) and Counter Airborne Improvised Explosive Device (C-AIED) missions. There are also several commercial applications of this technology that address possible counter-terrorist threat activities in the civilian sector.
REFERENCES:
1. Osborn, K., Army Records First UAV Kills, Army Times, 17 Sept 2007.
2. Miasnikov, E., Threat of Terrorism Using Unmanned Aerial Vehicles, Center for Arms Control, Energy, and Environmental Studies, 2005.
KEYWORDS: UAV, CUAV, Airborne IED, Pointing, Tracking, High Energy Laser
SB082-003 TITLE: Mode-Locked TEA CO2 Laser
TECHNOLOGY AREAS: Chemical/Bio Defense, Materials/Processes, Sensors, Battlespace, Weapons
ACQUISITION PROGRAM: N/A
OBJECTIVE: Perform a feasibility study to develop (Phase I) and construct (Phase II) a powerful mode-locked, transverse excitation atmospheric (TEA) carbon dioxide (CO2) laser. The laser should produce pulses shorter than 100 ps, tunable over the 9-11 micron wavelength region, preferably with peak fluence in excess of 10 mJ per pulse.
DESCRIPTION: Stand off spectroscopic detection of chemical agents and explosives has been accomplished using a variety of techniques, including LIDAR, Fourier-transform infrared (FTIR) spectroscopy, and most recently terahertz (THz) spectroscopy. THz spectroscopy of molecular rotational levels provides superior specificity for the identification of many gas-phase analytes, but THz systems have not been fielded widely because of a combination of challenges including poor THz sources and obfuscating atmospheric effects. THz sources in the 0.1-1.0 THz region, though comparatively weak, have matured dramatically in recent years and are now commercially available. Atmospheric line broadening, attenuation, and fluctuations, however, remain as hurdles.
Recently, a new methodology for performing stand-off agent detection has been proposed.[1] This technique overcomes the inherent limitations of atmospheric THz attenuation by exciting the agent cloud with a high power, mode-locked TEA CO2 laser.[2] The technique overcomes the limitations of line broadening because the laser pulses induce a brief terahertz transient absorption or emission, unique to the analyte interrogated, which may be observed with a THz transceiver. The CO2 laser is relatively unattenuated by the atmosphere, dramatically lowering the THz power requirements for the THz transceiver. Significantly, the collisional relaxation of rotational states at atmospheric pressures occurs on time scales faster than 100 ps, requiring the laser to produce intense pulses (>10 mJ/pulse) at least that fast.
PHASE I: Prepare a feasibility study demonstrating how a powerful (preferably >10 mJ/pulse), wavelength tunable (9-11 microns), mode-locked TEA CO2 laser would be constructed and tested. In the proposal, the performer will outline key attributes of the conceptual laser and identify key research obstacles to be addressed in Phase I. During Phase I, formal design of the concept will be performed, and a preliminary design review and report will be generated, specifically including performance and noise estimates. Experimental work to remove key obstacles is not required for Phase I but may be undertaken at the proposer’s discretion. As part of the final report, plans for Phase II will be proposed.
PHASE II: The design from Phase I will be finalized. All appropriate engineering testing and validation of design issues will be performed. A critical design review will be performed to finalize the design, and a prototype unit meeting the specifications will be manufactured and tested. By the end of Phase II, the working laser must be thoroughly characterized, quantifying both performance and noise over the design space. The laser and all related hardware (e.g. power supplies and electronic control) will be delivered to the Army Aviation and Missile RDEC, located at Redstone Arsenal, AL, for extensive test and evaluation.
PHASE III: Perhaps the most likely application of a mode-locked CO2 laser is in atmospheric monitoring of the distribution of trace gases. Of particular interest is the analysis of trace gases emitted from smokestacks, factories, and other fixed facilities that need to be monitored at a distance for long durations. A secondary application will be the study of laser-induced effects on surfaces and materials. There is potential military application of this laser for infrared targeting and countermeasures.
REFERENCES:
1. F.C. De Lucia, D.T. Petkie, and H.O. Everitt, “A double resonance approach to submillimeter/terahertz remote sensing at atmospheric pressure,” Chemical Physics 0710.5887, (2007) and references therein, especially references 17-21.
2. H. Houtman and J. Meyer, “Ultrashort CO2 laser pulse generation by square-wave mode locking and cavity dumping,” Optics Letters Vol. 12, p. 87 (1987).
3. D.G. Youmans, F. Corbett, G. Dryden, and M. Kovacs, “Theoretical and Monte Carlo analyses of the range-Doppler imaging capabilities of mode-locked CO2 ladars,” SPIE Vol. 2702 (0-8194-2076-X), p. 40 (1996) and references therein.
KEYWORDS: Infrared Laser, Modelocked Laser, Molecular Spectroscopy, Double Resonance
SB082-004 TITLE: Femtosecond UV Laser Pulse Expander
TECHNOLOGY AREAS: Chemical/Bio Defense, Materials/Processes, Sensors, Weapons
ACQUISITION PROGRAM: N/A
OBJECTIVE: Perform a feasibility study to develop (Phase I) and construct (Phase II) an external laser pulse expander for femtosecond pulses in the ultraviolet (UV)-blue spectral range (minimally 350-450 nm). The expander must be capable of expanding input pulses of 100 fs width to any user-specified pulse width up to at least 1 ns. The design should accommodate input laser pulses with repetition rates 1 kHz – 80 MHz and input fluences as high as 100 microjoules.
DESCRIPTION: Military interest in the ultraviolet portion of the spectrum comes in two forms: as a unique spectral window for sensing targets, and for spectroscopic identification of trace amounts of explosives, chem/bio agents, and toxic chemicals. In both applications, development of more powerful laser sources (and increasingly sensitive detectors) has been required for practical fieldable systems to be contemplated. Femtosecond laser pulses are commonly generated at UV wavelengths by frequency-converting near infrared (IR) femtosecond pulses from Ti:sapphire lasers using nonlinear optical techniques. The pulse width of a UV laser beam generated in this fashion is comparable to that of the original near IR beam (~100 fs). However, because different chemical and biological processes occur on various sub-nanosecond time scales, it is of interest to probe these systems with laser pulses of adjustable width. Variation of laser pulse width also allows for very predictable changes in peak power delivered to targets such as sensor arrays.
Femtosecond pulses are routinely expanded to several tens or hundreds picoseconds for the purpose of chirped pulse amplification; however, in addition to being chirped, the pulses exit such pulse stretchers with very specific pulse widths suitable for specific types of amplification. More flexibility is afforded by dispersion-free pulse shaping schemes wherein a femtosecond pulse of arbitrary shape can be generated using gratings in conjunction with lithographic masks [1], liquid crystal modulators [2-3], acousto-optic modulators [4], and deformable mirrors [5]. Pulse shapers have historically been used primarily to create novel pulses and pulse trains still characterized by sub-picosecond pulse widths, whereas the interest here is keeping the pulse shape simple (for example, square) but adjusting the pulse width over several orders of magnitude.
To address potential military applications in the ultraviolet, the pulse expander should at least span the tuning range of a (customer provided) frequency doubled Ti:Sapphire laser (350-450 nm), and preference will be given to solutions that go farther into the UV. The primary requirement of the expander will be to generate a stable, minimally chirped output pulse of adjustable width from 100 fs to at least 1 ns. The expander should be able to accommodate UV pulse fluences from nJ to ~100 uJ energy. Attention should be paid to minimizing the insertion and operational loss of the pulse expander (e.g. by modulating the phase rather than the amplitude of the spectrally dispersed pulse) while minimizing induced pulse-to-pulse width and amplitude variability so that pulse fluence and stability is maintained as much as possible from input through the expander. Finally, the qualitative temporal shape of the pulse should remain approximately square over the pulse width tuning range. Solutions that permit the generation of other user-specified pulse shapes or chirp are welcomed but not required.
PHASE I: Prepare a feasibility study demonstrating how a femtosecond UV pulse expander would be constructed and tested. In the proposal, the performer will outline key attributes of the conceptual expander and identify key research obstacles to be addressed in phase I. During phase I, formal design of the concept will be performed, and a preliminary design review and report will be generated, specifically including performance estimates. Experimental work to remove key obstacles is not required for Phase I but may be undertaken at the proposer’s discretion. As part of the final report, plans for Phase II will be proposed.
PHASE II: The design from Phase I will be finalized. All appropriate engineering testing and validation of design issues will be performed. A critical design review will be performed to finalize the design, and a prototype unit meeting the Phase I specifications will be assembled and tested. By the end of Phase II, the working pulse expander must be thoroughly characterized for performance and noise. The expander and all related hardware and software (excluding test laser[s]) will be delivered to the Army Aviation and Missile RDEC, located at Redstone Arsenal, AL, for further testing and evaluation.
PHASE III: Related commercial applications of an adjustable pulse width, sub-nanosecond UV laser include spectroscopic tools tailored to investigations of novel UV materials and phenomena, particularly wide band gap semiconductors, organic/inorganic hybrid materials, and plasmonics. Also of commercial interest is the analysis of trace gases emitted from smokestacks, factories, and other fixed facilities that need to be monitored at a distance for long durations. A third application could be the study of laser-induced effects on surfaces and materials. Because many chem/bio agents absorb UV light, a potential military application is the optical detection and/or identification of such agents. Other potential military applications of this modulated laser include UV targeting and countermeasures.
REFERENCES:
1. Weiner, A.M., Heritage, J.P., and Kirschner, E.M., "High-resolution Femtosecond Pulse Shaping," J. Opt. Soc. Am. B, Vol. 5, No. 8, pp. 1563-1572, 1988.
2. Weiner, A.M., "Femtosecond Pulse Shaping Using Spatial Light Modulators," Rev. Sci. Instrum., Vol. 71, No. 5, pp. 1929-1960, 2000.
3. Zheng, Z., Leaird, D.E., et al., " 20-fs Pulse Shaping with a 512-Element Phase-Only Liquid Crystal Modulator," IEEE J. Sel. Top. Quantum Electron., Vol. 7, No. 4, pp. 718-727, 2001.
4. Fetterman, M.R., Goswami, D., et al., "Ultrafast Pulse Shaping: Amplification and Characterization," Opt. Express, Vol. 3, No. 10, pp. 366-375, 1998.
5. Garduno-Mejia, J., Greenaway, A.H., and Reid, D.T., "Programmable Spectral Phase Control of Femtosecond Pulses by Use of Adaptive Optics and Real-time Pulse Measurement," J. Opt. Soc. Am. B, Vol. 21, No. 4, pp. 833-843, 2004.
KEYWORDS: Optical Modulator, Pulse Expander, Ultraviolet Laser, Ultrafast Laser, Agent Detection
SB082-005 TITLE: Low Cost Radar Receivers
TECHNOLOGY AREAS: Materials/Processes, Electronics
ACQUISITION PROGRAM: N/A
OBJECTIVE: Develop low cost radar receivers and processing techniques for manufacturing integrated cooling capability which is ruggedized to meet military requirements.
DESCRIPTION: Current microwave and millimeter wavelength radar systems use high cost materials and hence have suboptimal packaging, have a relatively high parts count, and have quite limited degree of parts standardization. There is a need to reduce the cost of receivers to achieve low cost radars.
It is known that improved radar receiver cost and performance can be achieved by reducing or eliminating high cost materials and processing, reducing parts count, standardizing parts, and integrating packaging. Potential means of reducing high cost materials and their associated processing are cooling the receiver and achieving high density packaging. The degree of cooling and cooling mechanisms has not been extensively studied to date. There are cost
and performance tradeoffs in terms of cooling and packaging to be determined prior to implementation. A low cost radar receiver technology seeking to lower the cost of components such as the low noise amplifier, mixer and interconnects in conjunction with improved packaging and testing is desired for potential radar applications.
PHASE I: Feasibility Study to identify the potential for low cost receivers to achieve near or equivalent performance with current receivers for X, Ku, and Ka band. Identify cost and performance matrix for receivers based on such options as packaging, parts count, standardization and cooling. Identify various technologies and materials and provide current status of how these can meet DoD aviation and missile requirements including extreme environments. List any shortfalls as areas for further research. Develop a list of materials, manufacturing and process technology needed to make system capable of meeting aviation and missile requirements. Consider technology which will enhance commercially available technology for this use. Material considerations should include performance, corrosion, environmental, cost, and processing hazards. System configuration should be easily assembled and use readily available materials to the greatest extent possible. Hardware of interest includes the Low Noise Amplifier, mixer and interconnects.
PHASE II: Fabricate a bench top receiver to demonstrate proof of principle. Investigate methods of achieving low cost and system requirements. Create a cost, performance, and issues matrix to determine challenges for the prototype materials, processing, and integration techniques. Develop technology and fabrication processes to meet military aviation and missile requirements for an X band receiver. This should be performed in concert with the government as a result of the best alternative from PHASE I. Consider system requirements to include environmental such as temperature extremes from operation and storage, and shock and vibration induced environments. Design approaches needed to provide adequate performance while not adding significantly to receiver size, weight, power requirements, and cost. Based on information acquired from iterations in design, fabrication, and testing, down select design, materials, and processes deemed to have the most promise with sufficient maturity, at a reasonable cost to allow development of a stable prototype design and process by the end of Phase II. Electronic and thermal performance, material costs, processing costs, and expected yields should be considered in the down select. Demonstrate a low cost receiver operation during a physically simulated takeoff of an aircraft or missile. Performance and structural integrity required to maintain performance during the mission needs to be achieved. Perform bench test following the test with a simulated shock to further verify performance. Physically inspect the receiver and associated hardware. Note any changes from pretest physical configuration. Some physical changes may be permissible but only to the extent that performance is not degraded. Refine the initial design of receiver and associated manufacturing processes and develop low cost methods for testing the receiver unit. Investigate potential applications for tactical missiles and short range Unmanned Aerial Vehicles (UAVs.) Note and recommend system and processing changes which could be used to expand applicability to longer mission systems.
Develop a draft business plan showing potential commercial and military applications and production/product costs and schedule for implementation in medium and high volumes.
PHASE III: Candidate applications for this technology span both the military and commercial arenas. In general terms, the linearized analog photonic link components to be developed will be used in avionics, communication, radar/telemetry, electronic warfare, WiFi, CATV, instrumentation and other commercial and DoD transmission and signal processing applications. Some specific military uses include high bandwidth, multi-wavelength, fiber-optic signal transmission systems as well as optical time delay modules for broadband signal processing and phased-array antenna applications. Wideband electronic warfare receivers are another prime military insertion point for this technology. On the commercial side, radio frequency receivers are used in a wide variety of products and thus this technology could provide for significant commercial market impact.
REFERENCES:
1. Lucas, Michael R., Turley, Alfred P., Marcelli, Carmine, Adil, Farhan, Montano, Sergio, Suko, Scott, and Fudem, Howard, Office of Naval Research Report, Mixed-Signal SiGe Radar-on-a-Chip, 20 March 2006.
2. Zampardi, Pete, SiRf 2007 Conference paper, Performance and Modeling of Si and SiGe for Power Amplifiers, Jan 2007.
KEYWORDS: Low Cost Microwave Receiver, Low Cost Millimeter Wavelength Receiver, Silicon Germanium, Gallium Arsenide
SB082-006 TITLE: Ultra Lightweight, Low Power Thermal Camera for Micro-Platforms
TECHNOLOGY AREAS: Sensors, Electronics
ACQUISITION PROGRAM: N/A
The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), which controls the export and import of defense-related material and services. Offerors must disclose any proposed use of foreign nationals, their country of origin, and what tasks each would accomplish in the statement of work in accordance with section 3.5.b.(7) of the solicitation.
OBJECTIVE: The objective of the Phase I effort is to develop technologies for extremely lightweight, low power thermal micro-cameras for use on micro-vehicles. Proposed research should investigate and exploit innovative approaches that will enable revolutionary advances in lightweight, low power infrared (IR) cameras.
DESCRIPTION: The increasing number of applications for small platforms in military operations has led to an emphasis on nighttime imaging payloads, compatible with micro-platforms. Similarly, the increased demands placed on the individual warfighter for situational awareness, require high performance, lightweight thermal imaging systems. Current Concept of Operations is driving the military to utilize remote sensing assets such as micro-air vehicles, robots, and distributed sensors systems. These platforms suffer from limited payload capability – weight, size, and power. With these constraints in mind, a new generation of imagers are needed that will provide the warfighter with “over the hill” and “around the corner” surveillance needed for nighttime dominance.
To meet the applications described above, a thermal camera having a weight less than 15 grams and power consumption less than 200 mW is desired. The total camera weight includes optics, packaged detector, and electronics. The sensor field of regard should be forty (40) degrees. Ultimate system performance should be recognition of a one (1) meter target at one-hundred (100) meter range with a high probability of detection, and detection of low contrast targets with a delta temperature relative to the background of 1 degree C. Unique signal processing may be implemented on the platform to reduce data rates, extract significant information, and enhance image quality. Pixel level data could be sent to a remote ground station for processing to reduce the burden on the on-board electronics, however, bandwidth limitations need to be considered and download data rates need to be compatible with standard video transmission formats. A trade study should be conducted comparing processing on the platform versus processing at a collection site.
PHASE I: Develop overall thermal camera system design that addresses size, weight and power. Proposed designs must describe any revolutionary advances in technology needed to meet the thermal camera goals. Any advances in materials, detectors, focal plane arrays, micro-packaging, optics, electronics and signal processing that enable the development of an extremely lightweight, low power IR camera must be completely explained. Current limitations with existing technologies must be addressed. As part of the final report, plans for Phase II will be proposed.
PHASE II: Prototype Phase I design to demonstrate and validate new thermal camera concept. The prototype must demonstrate the capability to achieve the desired final system design goals – total weight less than 15 grams, system power consumption less than 200mW, field of regard of forty degrees, recognition of a one (1) meter target at one-hundred (100) meter, and detection of low contrast targets with a delta temperature relative to the background of 1 degree C.
PHASE III: The technology developed under this SBIR can be used in military and civilian IR cameras. Thermal imagers are being integrated into automobiles for collision avoidance, home and business surveillance systems, and being used by law enforcement and firefighters.
REFERENCES:
1. Kostishack, D.F., Micro Air Vehicles for Optical Surveillance, The Lincoln Laboratory Journal, Number 2, 1996.
2. Michelson, R.C., Update on Flapping Wing Micro Air Vehicles Research, 13th Bristol International RPV Conference, Bristol England, 30 March - 1 April 1998.
3. Brady, D.J., Compressive Imaging Sensors, Proceedings of SPIE. Vol. SPIE-6232, pp. 43-51. (2006).
4. McMichael, J. M., Micro Air Vehicles - Toward a New Dimension in Flight, DARPA, USA. 1997.
5. Bohorquez, F., Design and Development of a Biomimetic Device for Micro Air Vehicles, Proc. SPIE Vol. 4701, p. 503-517, Smart Structures and Materials 2002.
6. http://www.darpa.mil/dso/thrusts/materials/multfunmat/wasp/index.htm
KEYWORDS: Micro Air Vehicles, Thermal Imaging, Thermal Sensors, Light Weight IR Camera
SB082-007 TITLE: Advanced Development for Defense Science and Technology
TECHNOLOGY AREAS: Materials/Processes
ACQUISITION PROGRAM: N/A
OBJECTIVE: Identify and develop innovative technology in the Physical, Engineering, and Life Sciences for enabling defense technology.
DESCRIPTION: Novel technology which relies on innovations in science and engineering has provided a critical advantage to our national defense. To this end, DSO is soliciting proposals for advanced technology development in a variety of enabling technical areas which include:
- Application and development of advanced mathematics for DoD applications.
- New and innovative approaches to biosensor technology and biological technology for maintaining the warfighters performance, capabilities and survival in battlefield conditions.
- Remote interrogation and control of biological systems at the system/organ/tissue/cellular/molecular scales and new technologies to drastically reduce the logistics burden of medical treatment in the field.
- Novel interface and sensor designs for interacting with the central (cortical and subcortical structures) and peripheral nervous systems, with a particular emphasis on non-invasive and/or non-contact approaches.
- New dual-use processes and materials that translate biomolecular mechanisms to innovative, highly advantages new routes for material and device systems.
- New materials and processes that provide revolutionary capability to DoD platforms and weapon systems.
- New tools to predict the performance of complex systems across a variety of domains (e.g., materials, physics, biology, etc.).
- New technology for training individuals and teams, including embedded training and simulation; technologies which lead to understanding and improving team performance; and new approaches to improve rapid decision-making in chaotic or data-poor environments.
PHASE I: Conduct a feasibility study which would investigate and define the proposed idea or device and its feasibility.
PHASE II: Develop the research and technology advances and methods identified in Phase I to demonstrate a proof-of-concept prototype.
PHASE III: The technology developed under this SBIR will be used in both the military and civilian commercial sector.
REFERENCES:
1. “Director, Defense Research & Engineering Home Page,” Department of Defense. http://www.dod.mil/ddre/mainpage.htm
2. “DDR&E Science & Technology Home Page,” Department of Defense. http://www.dod.mil/ddre/scitech.htm
3. “Office of Science and Technology Policy,” Executive Office of the President. http://ostp.gov/
KEYWORDS: Sensor Array, Biotechnology, Novel Materials, Embedded Training, Decision Making,
SB082-008 TITLE: Integrated Structural Insulation to Eliminate Multi-Layer Insulation for Satellites
TECHNOLOGY AREAS: Space Platforms
ACQUISITION PROGRAM: N/A
OBJECTIVE: Develop and validate alternative integrated structural insulation concepts to eliminate the need for multi-layer insulation for spacecraft systems.
DESCRIPTION: Multi-Layer Insulation (MLI) is the most common thermal control technology used on spacecraft. The reason for this is its outstanding thermal properties. Traditionally, MLI is a complex system incorporating up to 30 layers of alternating low conductivity and low emissivity materials. Because of the alternating layers, the performance of MLI is outstanding with an effective emissivity on the order of 0.015 to 0.030. However, because of the multiple low conductivity layers it has virtually no compression strength and is fragile. In addition, it is complex to design, requires hours of touch labor to fabricate and install, and is difficult to quantify its performance. To design, fabricate, and install MLI on a small complex component can exceed two months. As a result, MLI is expensive, difficult to work with, and a major contributor to satellite development time. A significant improvement is needed in satellite insulation materials and surface treatments. Eliminating the need for MLI or integrating the insulating function into satellite structural panels would provide significant advantages for all military satellite systems including responsive satellites.
PHASE I: Explore revolutionary materials and designs based on prototypical requirements. Perform sufficient design analysis and/or physical testing to verify feasibility of proposed solution relative to typical satellite system requirements. Validation of feasibility shall be demonstrated to a level satisfactory to indicate the practicality of the design in meeting requirements and objectives.
PHASE II: Demonstrate the technology identified in Phase I. Tasks shall include, but are not limited to, a detailed demonstration of key technical parameters that can be accomplished and a detailed performance analysis of the technology. A subscale demo is acceptable, but a full-scale demo is encouraged. Also, model validation testing, a detailed evaluation report, and recommendations are required.
PHASE III: Candidate applications for this technology span both the military and commercial spacecraft arenas, since nearly all satellites currently use MLI. Of particular benefits will be commercial and military satellites that are being designed to rapidly respond to emerging changes in space operations as a result of reduced design times and the ability to provide potentially generic thermal solutions to a multitude of satellite applications. While the primary use is anticipated to be limited to military and commercial satellites, the continued growth of, and reliance on, space assets assures that sufficient market demand will accompany any potential technological breakthroughs.
REFERENCES:
1. Gilmore, David G., Spacecraft Thermal Control Handbook Volume I: Fundamental Technologies, 2nd Ed, The Aerospace Press, El Segundo, CA, 2002.
2. Jilla, Cyrus D. and Dr. David W. Miller, “Satellite Design: Past, Present, and Future,” International Journal of Small Satellite Engineering, 12 Feb 1997.
KEYWORDS: Multi-Layer Insulation, Insulation, Thermal Management, Spacecraft, Responsive Space
SB082-009 TITLE: Reconfigurable Thermal Networks (RTN)
TECHNOLOGY AREAS: Space Platforms
ACQUISITION PROGRAM: N/A
OBJECTIVE: Develop and validate a reconfigurable thermal network that provides on-the-fly reconfigurability for space missions.
DESCRIPTION: The traditional approach to satellite design is a customized and highly optimized satellite bus. The primary design driver is to minimize mass but often at the expense of time and money. This design driver is maintained throughout the design of the entire spacecraft. A secondary design driver is system reliability. Since spacecrafts are expensive, complex, and nearly impossible to repair once on orbit, system reliability is also important. As a result of these two constraints, every aspect of the system’s design must be carefully considered, analyzed, and tested. The results are a specialized point design for each mission and a long and arduous design process.
Currently, the design, integration, and testing of the thermal control system (TCS) requires years to complete and is a leading contributor to satellite development time. The design time for an average small satellite is one to three years. Due to the long design cycle time and the rapid evolution of technology, satellites are obsolete before they are even launched. For these reasons, technologies that will significantly reduce design time by taking advantages of advances in microelectronics, MEMS, adaptive control theory, plug-and-play electronics, and other fields are required.
For a system to be considered a reconfigurable thermal network, it must have the following characteristics:
1. Maintain all components within acceptable temperature ranges autonomously.
2. Adapt to a wide range of component sizes, locations, heat loads, and operating temperatures.
3. Switch between high conductance and low conductance states as dictated by the components.
4. Route heat from hot components to cold components to maximize efficiency.
5. Provide plug-and-play like connectivity between components, panels, and radiators.
The goal is a RTN that can be tailored on-the-fly to the needs of the satellite, the mission, and the space environment. The ultimate goal is a robust and adaptable system that will eliminate the need for point designs and reduce the design cycle from one to three years to one to three days.
PHASE I: Perform sufficient experimentation, testing, and/or analysis to verify the feasibility of materials and designs that satisfy spacecraft thermal management demands and demonstrate reconfigurable thermal control. Develop revolutionary materials and conceptual designs of RTN based on preliminary analysis. Experiments and/or analysis shall be conducted to indicate the practicality of the design in meeting requirements and objectives of typical spacecraft configurations.
PHASE II: Demonstrate the technology identified in Phase I. Tasks shall include, but are not limited to, a detailed demonstration of key technical parameters that can be accomplished and a detailed performance analysis of the technology. A subscale demo is acceptable, but a full-scale demo is encouraged. Also, model validation testing, a detailed evaluation report, and recommendations are required.
PHASE III: Potential military applications are responsive satellites, research satellites, aircraft, and unmanned aerial vehicles. Potential commercial applications for reconfigurable thermal management include aircraft, automobile, microelectronic applications, or any sector where high power densities are required.
REFERENCES:
1. Williams, Andrew and Palo, Scott, “Issues and Implications of the Thermal Control System on Responsive Space Missions.” Proceedings from the 20th Annual AIAA/USU Conference on Small Satellites, Logan, UT, August 2006.
2. Gilmore, David G., Spacecraft Thermal Control Handbook Volume I: Fundamental Technologies, 2nd ed. The Aerospace Press: El Segundo, CA, 2002.
3. Lee, Douglas E., “Space Reform,” Air and Space Power Journal, Summer 2004: pp. 103-112.
4. Lyke, Jim, et al., “Space Plug-and-Play Avionics,” AIAA 3rd Responsive Space Conference, Paper No. RS3-2005-5001, Los Angeles, CA, 25 – 28 April 2005.
KEYWORDS: Thermal Management, Reconfigurable Thermal Control, Thermal Networks
SB082-010 TITLE: Small Engines Designed for High Efficiency, High Power Density and Quiet Operations
TECHNOLOGY AREAS: Air Platform, Ground/Sea Vehicles, Materials/Processes
ACQUISITION PROGRAM: N/A
The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), which controls the export and import of defense-related material and services. Offerors must disclose any proposed use of foreign nationals, their country of origin, and what tasks each would accomplish in the statement of work in accordance with section 3.5.b.(7) of the solicitation.
OBJECTIVE: The objective of this program is the development of small modular engines (10 HP) with the power density and efficiency of large engines (greater than 300 HP). The performance goals are a power density greater than 1 Horsepower per pound (HP/lb.), and greater than 25% thermal efficiency. The engine must also be able to operate on logistically available heavy fuel such as JP8. Furthermore, the engine shall be designed to be mated with an electric generator to gain the advantage of operation at an optimal design point as part of a hybrid electric propulsion system. Small engines typically run at higher rotational speeds than large engines and are a good match with high power density generators. Engine designs which have the potential to be very quiet for systems where a reduced acoustic signature is required are particularly desired.
DESCRIPTION: The design of engines for propulsion has been extensively studied with internal combustion engines (1-5) and gas turbine engines (6) representing mature technology. Small engines (10 HP and below) which are the focus of this topic have not been as extensively developed and optimized, and present design challenges for high performance Defense applications. Hybrid electric propulsion systems (7) are attractive at power levels of interest in this topic, where the engine can be optimized for ‘cruise conditions’ and battery power can be used for peak power requirements to optimize system performance. Electric power consumption for sensors and communication is also provided by a hybrid electric system. Innovation is required to develop small engines with high performance as described in this topic.
There are a large variety of engine types that could in principle be adapted such that they meet topic goals for power density (> 1 HP/lb.), efficiency (>25%) and quiet operation. Each engine type has its own design specific advantages and challenges. Internal combustion (IC) engines are usually simple 2 stroke engines in this power range with exhaust ports instead of valves. Designs for a small 4 or more stroke engine with enhanced performance will need to address the problems associated with valve actuation at high rpm. IC engine may require 4 or more cylinders for reduced acoustic signatures desired and this would increase thermal losses while also increasing friction in the engine. Turboelectric designs at small size scale also present design challenges including stabilizing the combustion and dealing with thermal losses. Rotary engines are also a design option with seal wear and friction being just one problem to overcome.
Meeting topic goals may require innovation in both materials of construction as well as design. Higher operating temperatures may be required to increase engine efficiency requiring higher temperature capable materials. Increased surface to volume in small engines may require use of insulating materials not needed in larger engine variants. Frictional losses in small engines may require new tribological approaches.
PHASE I: Feasibility study to show that innovative concepts in the design of the small engine meets or exceeds program goals taking into account the thermomechanical and tribological aspects of the design.
PHASE II: Build the engine designed in phase I including the electrical generator and measure the noise levels, power density, efficiency and durability of the engine.
PHASE III: A quiet engine in the 10 HP range would be ideal for emergency electric power backup for homes. It would also be useful for quiet marine propulsion systems such as those used for recreational fishing. Electric delivery vehicles designed for use in urban environments could also make use of a small engine to recharge batteries while making deliveries.
REFERENCES:
1. Internal combustion engine, From Wikipedia, http://en.wikipedia.org/wiki/Internal-combustion_engine
2. Philip Hill, Carl Peterson, "Mechanics and Thermodynamics of Propulsion, 2nd Edition", Prentice Hall, 1991.
3. Richard Stone, “Introduction to Internal Combustion Engines, 3rd Edition”, Co-published by SAE and Macmillan, 1999.
4. Gordon Blair, “Design and Simulation of Four-Stroke Engines”, Society of Automotive Engineers, Warrendale, PA, 1999.
5. Kevin L Hoag, “Vehicular Engine Design”, Springer-Verlag New York, LLC, 2005.
6. J.L. Kerrebrock, Aircraft Engines and Gas Turbines, Second Edition, The MIT Press, London, 1992.
7. Hybrid Vehicle, Wikipedia http://en.wikipedia.org/wiki/Hybrid_vehicle
KEYWORDS: Engines, Hybrid Electric, Turboelectric, Internal Combustion Engine, Rotary Engine
SB082-011 TITLE: High Power Density Electric Motors for Hybrid Electric Air Platforms
TECHNOLOGY AREAS: Air Platform, Materials/Processes
ACQUISITION PROGRAM: N/A
The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), which controls the export and import of defense-related material and services. Offerors must disclose any proposed use of foreign nationals, their country of origin, and what tasks each would accomplish in the statement of work in accordance with section 3.5.b.(7) of the solicitation.
OBJECTIVE: Design and prototype high power density electric motors for an all electric vertical takeoff and landing uninhabited air vehicle.
DESCRIPTION: Hybrid electric propulsion offers increased architectural flexibility in both ships and land vehicles, but much less attention has been given to air vehicles. The military utility of helicopters is currently limited by high maintenance costs and vulnerability to small arms fire while landing in hostile territory. The power plant of choice for helicopters is a gas turbine engine due to its high power density. However, the high shaft rpm of a turboprop gas turbine requires a large transmission which may weigh more than the engine due to the much lower rpm rotor which provides lift to the helicopter. If the transmission can be replaced with a motor-generator pair, many of the high maintenance components in the drive train can be eliminated, resulting in reduced operation and support cost comparable to fixed wing aircraft. A hybrid electric drive would also allow the use of a larger number of smaller rotors or electric driven ducted fans, and even the elimination of the tail rotor, which would reduce vulnerability to small arms through redundant systems.
One obstacle to hybrid electric motors is the relative low power density of available electric motors. Commercial off the shelf electric motors have been designed for high efficiency, but power densities are low (~0.1 Horse Power per pound, HP/lb). Electric motors developed for aircraft propulsion have power densities between 1 and 2 HP/lb. Power density of electric motors/generators increase with the operating speed and so direct drive generators can have extremely high power densities (greater than 5 HP/lb).
The challenging problem for this topic is to design and prototype a 7 HP electric motor with a power density greater than 5 HP/lb, efficiency greater than 95% and an operating RPM of less than 10,000 revolutions per minute (RPM). The electric motor produced would be useful for powering a ducted fan (less than 12 inches in diameter) and capable of producing a high thrust to weight for small vertical takeoff and landing UAVs. These goals are intended to push the state of the art in high energy density electric motors. It is anticipated that innovation in both design and materials will be needed to meet these goals. High energy product magnetic materials will be useful in shrinking the size of the motor. Ring motors may be particularly suitable for ducted fans although novel designs using a central shaft may also be appropriate.
PHASE I: Feasibility study to show that the innovative approach in the design of the motor meets or exceeds program goals taking into account the mechanical and electrical aspects of the design.
PHASE II: Refine the design from Phase I and build a prototype ducted fan and electric motor meeting the program goals (7 HP, 8,400 RPM, greater than 5HP/lb, and efficiency greater than 95%).
PHASE III: Electric motors with power densities greater than 5 HP/lb will enable vertical takeoff and landing aircraft with operational and support costs similar to fixed wing aircraft. Commercial applications include short haul air transportation and emergency air vehicles for evacuation of accident victims. The use of the electric motors in lift fans within wings offer the potential for longer range air transport. Higher power density motors also have applications in reducing the weight of consumer products with electric motors such as vacuum cleaners.
REFERENCES:
1. Uninhabited Air Vehicles: Enabling Science for Military Systems, The National Academies Press, 2000. http://www.nap.edu/books/0309069831/html/R2.html
2. Jeffrey J. Berton, Joshua E. Freeh, and Timothy J. Wickenheiser. “An Analytical Performance Assessment of a Fuel Cell-Powered, Small Electric Airplane,” NASA/TM-2003-212393, Glenn Research Center, Cleveland, Ohio, June 2003, Available electronically at http://gltrs.grc.nasa.gov
3. Guerrero I., Londenberg K., Gelhausen P., Myklebust A. “A Powered Lift Aerodynamic Analysis for the Design of Ducted Fan UAVs,” AIAA-2003-6567, 2nd AIAA “Unmanned Unlimited” Conf and Workshop and Exhibit, San Diego, CA, Sept 15-18, 2003.
4. Freeh, Joshua et. al. “Electrical Systems Analysis at NASA Glenn Research Center: Status and Prospects.” NASA/TM-2003-212520. http://www-psao.grc.nasa.gov/publications/TM-2003-212520.pdf
KEYWORDS: Electric Motor, Helicopter, Hybrid Electric, Ducted Fan
SB082-012 TITLE: Universal Sample Preparation Device for Biological Detection
TECHNOLOGY AREAS: Biomedical
ACQUISITION PROGRAM: N/A
OBJECTIVE: Create a nucleic acid sample preparation system which will rapidly generate a sample that can be used in many biological detector systems.
DESCRIPTION: DARPA is interested in developing a biological sample preparation system that will produce samples capable of being used in many different assay systems. One of the major hurdles to deployment of reliable and functional biological sensor instruments is simplification of rapid, reliable and consistent sample collection and preparation [1, 2]. Several factors make “in the field” sample collection difficult. First, there is currently no single sample method that is universally applicable to many sample sources. Additionally, in a deployed situation, a sterile working environment is not available, so contaminants are often present in the sample being processed. Finally, sample preparation protocols are often complex and difficult to perform for untrained users. In military situations, deploying scientifically trained personnel to every location that sampling needs to be performed is not possible. The need for a simple, near universal system for biological sample preparation in both military and civilian arenas is clear.
This SBIR solicits development of an easy-to-use, deployable, reliable sample preparation method for nucleic acids that rapidly generates a sample ready for use in a wide variety of diagnostic equipment. The sample preparation system should be entirely self-contained, and allow rapid sample preparation from a wide range of input materials. Ultimately, this SBIR seeks to develop a product for sample generation that will enable the end user to perform a minimal procedure to prepare the sample in a sample device that will be directly attached to the biological detector for assaying.
PHASE I: Feasibility study of a method of nucleic acid preparation. Feasibility study should demonstrate reliable production of analysis-ready sample from no less than two sample matrices.
PHASE II: Further develop method from Phase I into field-applicable product. This product should generate a sample from many different sources that is suitable for use in several detector platform methods. Additionally, the final prepared sample should be in a chamber that enables direct delivery of the sample to the detector from the sample preparatory apparatus.
PHASE III: Testing technologies developed through this SBIR have wide application in military field testing, military medical diagnostic testing. Additionally, this technology would be well suited for use in civilian homeland defense testing situations. This technology may be evaluated for specific sample materials relevant in clinical settings.
REFERENCES:
1. “Current and Developing Technologies for Monitoring Agents of Bioterrorism and Biowarfare” Lim DV, Simpson JM, Kearns EA, and MF Kramer. Clinical Microbiology Reviews. 2005, 18(4) 583-607.
2. “Nucleic Acid Approaches for Detection and Identification of Biological Warfare and Infectious Disease Agents” Ivntski D, O’Neil DJ, Gattuso A, Schlicht R, Calidonna M, and R Fisher. Biotechniques 2003, 35(4) 862-869.
KEYWORDS: Biomedical
SB082-013 TITLE: Radiation Resistant Fabrics
TECHNOLOGY AREAS: Materials/Processes
ACQUISITION PROGRAM: N/A
OBJECTIVE: Prepare a Phase I feasibility study to develop new fabrics or materials that block radiation, and that compare favorably to commercially available radiation-blocking materials in terms of performance and cost-effectiveness.
DESCRIPTION: Radiation is a danger faced by the warfighter, the physician, and the first-responder in many different scenarios. Traditionally, radiation protection for these individuals has been virtually non-existent, or consisted of shields created from lead and other heavy, dense metals. More recently, new material substances have been developed to replace lead in this role [1]. These new material substances are most often integrated into garments as protective sheets or layers of polymer that add protective properties to a