Army 14. 1 Small Business Innovation Research (sbir) Proposal Submission Instructions
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1. Barringer, M., Thole, K., Breneman, D., Tham, K-M, and Laurello, V., “Effects of Centrifugal Forces on Particle Deposition for a Representative Seal Pin Between Two Blades”, Proceedings of the ASME IGTI Turbo Expo 2012, Copenhagen, Denmark, Paper GT2012-68777. 2. Walsh, W. S., Thole, K. A., and Joe Chris, "Effects of Sand Ingestion on the Blockage of Film Cooling Holes," in Proceedings of the ASME Turbo Expo 2006, vol. 3, Part A, pp. 81-90, 2006 3. Cardwell, N. D., Thole, K. A., and Burd, S. W., "Investigation of Sand Blocking within Impingement and Film Cooling Holes," in Proceedings of the ASME Turbo Expo 2008, pp. 1147-1159, 2008. 4. Musgrove, G. O., Barringer, M. D., Thole, K. A., Grover, E., and Barker, J., "Computational design of a louver particle separator for gas turbines," in Proceedings of the ASME Turbo Expo 2009, pp. 1313-1323, 2009. 5. Patent-Publication # US7803213 B2 “Apparatus and method for enhancing filtration” by Don H. Hess September 28, 2010. KEYWORDS: size, electrostatic, separation, conglomeration, deflection, turbine engine, dust filtration, particle separator A14-005 TITLE: Electronic Health Monitoring System Power Source TECHNOLOGY AREAS: Electronics ACQUISITION PROGRAM: PEO Aviation 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 5.4.c.(8) of the solicitation. OBJECTIVE: Contractor shall develop a power source system for electronic health monitoring systems capable of providing a fixed voltage (between 1.5 and 3.3 volts) at 100 microamps for 20 years over the industrial temperature range. DESCRIPTION: Contractor shall develop an electronic system health monitoring power source to meet the following requirements: (1) Conventional battery technology, nuclear batteries, hybrid battery/capacitor/etc. power sources that meet all the requirements are acceptable solutions. We are not interested in thermal energy conversion. We are not interested in energy harvesting, since there are little to no opportunities for scavenging energy in a storage environment as described in Bradford [1]; (2) the power source output voltage shall be a fixed voltage between 1.5 volts and 3.3 volts; (3) the power source shall have a 20 year lifetime for operation and storage; (for example, the power source shall be capable of 19 years 364 days of storage, and 1 day of operation, 19 years 364 days of operation and 1 day of storage, 10 years of storage and 10 years of operation, etc.); (3) the power source’s temperature range shall cover the industrial temperature range of -40 C to +85 C with a wider temperature range up to full military temperature range of -55 C to +125 C desired; (4) the power source shall provide 100 microamps average current, a 1 milliamp current pulse for 1 second every hour, one-time current pulse of 10 milliamps for 1 second; (5) the power source shall be environmentally friendly, with minimal disposal issues. (conventional chemical and nuclear batteries will be given equal technical evaluation weighting; however, nuclear batteries shall include a plan for obtaining a NRC license and a life-cycle management plan.); (6) a power source that can be certified flight worthy; (7) the power source shall be no larger than 2 by 2 by 1 inches; and, (8) the power source shall weigh no more than 2.5 ounces (no more than 70 grams).
[1] P. Bradford: “Power Consumption and Health Monitoring Systems,” Redstone Arsenal Energy 2010 Workshop, Redstone Arsenal, AL, September 2010. Available from https://rsic.redstone.army.mil. [2] D. Linden and T. Reddy: “Handbook of Batteries,” McGraw-Hill Companies, 2001, ISBN: 0071359788. [3] R. Kaushik, and S. Prasad: “Low Voltage CMOS VLSI Circuit Design,” Wiley, 1999, ISBN: 047111488X. [4] F. Shearer: “Power Management in Mobile Devices,” December 2007, ISBN-13: 9780750679589. [5] N. Nguyen and S. Wereley: “Fundamentals and Applications of Microfluidics, Second Edition,” Artech House, 2006, ISBN: 1580539726. [6] N. Weste, and D. Harris: “CMOS VLSI Design: A Circuits and Systems Perspective,” Addison Wesley, 2004. ISBN: 0321149017. [7] G. Yakubova: “Nuclear batteries with tritium and promethium-147 radioactive sources,” BiblioLabs II, July 2012. ISBN-13: 9781249041771 [8] L. Surhone, et al.: “Optoelectric Nuclear Battery,” Betascript Publishing, May 2011. ISBN-13: 9786135496741. [9] Phys.org: “Batteries: Scientists see how and where disruptive structures form and cause voltage fading,” Phys.org, Jan 2013. http://phys.org/news/2013-01-batteries-scientists-disruptive-voltage.html KEYWORDS: Battery, beta battery, long shelf life, low current, health monitoring system, electronic health monitoring system, power source, hybrid power source, hybrid battery, capacitor, ultracapacitor, supercapacitor A14-006 TITLE: Ultra Low Power Electronic Health Monitoring System TECHNOLOGY AREAS: Electronics ACQUISITION PROGRAM: PEO Aviation 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 5.4.c.(8) of the solicitation. OBJECTIVE: Research and develop an electronic health monitoring system with ultra-low power sensors and signal processing chain(s). DESCRIPTION: The purpose of this SBIR is to research and develop ultra-low power sensors and signal processing (analog and digital) chains for electronic health monitoring applications. Current electronic health monitoring systems spend most of their time in an ultra-low power sleep mode. We are interested in an electronic health monitoring system that can run continuously on less than 100 microamps current. A typical health monitoring system consists of a sensor, analog signal processing, an analog-to-digital converter, microcontroller and digital signal processing. We are interested in an electronic health monitoring system with less than 100 microwatts continuous power consumption. A low power sensor by itself does not meet the low power system requirement for this topic. Due to the low current requirement, this topic is for a wired health monitoring system. Offeror may propose a wireless system; however, the offeror still must meet the 100 microamp average current requirement. For example, a typical pressure sensor may output a voltage, current or frequency proportional to the applied pressure. Analog signal processing may be required to appropriately scale the sensor's output signal for an analog-to-digital converter. Digital signal processing may be required to linearize the pressure transfer function. For example, a typical industrial pressure sensor outputs a current. A gain stage is required to convert the sensor output current to a 0 to 3 volt range for a 12 bit analog-to-digital converter. A digital signal processing step is required to convert the 12 bit digital code number 0 through 4095 (0x0000 through 0x0fff) to a 0.0 to 100.0 psi (0.0 to 7.00 bar) floating point number. The entire sensor system is required to be ultra-low power. Missiles may be placed in long term storage for 10 to 20 years or longer. Health monitoring systems require, extremely low power sensors and extremely low power analog and digital signal processing to achieve more than 10 years of operation. Batteries to power health monitoring systems are a separate concern. This SBIR topic is not seeking any battery research or development. This SBIR topic is not seeking any chemical sensor development. PHASE I: Contractor shall research the feasibility of developing an ultra-low power electronic health monitoring system with less than 100 microwatts continuous power consumption. We are interested in sensors for humidity, temperature, rate of temperature change, pressure, and battery charge level (e.g. percentage of battery life remaining). Contractor shall select 4 of 5 sensors for the health monitoring system. The technical merit for the phase I proposals will be evaluated based on the following criteria: 25% weighting for sensor and sensor performance, 25% for analog and digital signal processing chains, and 50% for low power. Phase I proposals are required to address the three criteria above. For the Phase I proposal, the contractor shall provide a system block diagram and describe the system operation: (1) the proposed sensors, (2) the analog signal processing chain(s), (3) the analog-to-digital converter(s), (4) digital signal processing chain(s), and (5) any post digital processing, and/or linearization required to convert the digitized sensor values to measurement values (for example V/m, Pascals, Kelvins, etc. in floating point or fixed point). To demonstrate the feasibility of the proposed health monitor system, the contractor may develop models, simulations, and/or prototypes. The contractor shall provide midterm and final reports. The final report shall describe health monitor system (1) operation, (2) estimated system performance, (3) estimated power consumption for each individual element, and the total system power, (4) estimated operating temperature range, (5) estimated operational vibration limits, (6) estimated operational lifetime, and (7) estimated non-powered lifetime (shelf lifetime). PHASE II: Contractor shall develop the electronic health monitoring system based on the phase I research. The electronic health monitoring system (without battery) shall have a volume smaller than (1 x 1 x 0.2 inches) and weigh less than 0.36 ounce (10 grams). Contractor shall have an independent source, with government concurrence, test and evaluate the performance of the electronic health monitoring system. Contractor shall provide a copy of the test and evaluation report to the government. Contractor shall provide 2 electronic health monitoring systems to the government point of contact for test and evaluation. Contractor shall provide a preliminary datasheet for electronic health monitoring system. Contractor shall provide a final report describing the electronic health monitoring system. Contractor shall provide the government a 2 day on site training for the electronic health monitoring system. PHASE III: Military, aerospace, medical and industrial applications are always looking for lower weight, and lower power technologies. Automotive applications require rugged, low power electronic health monitoring systems for diagnostics and prognostics. Military systems (missiles, aircraft, ships, and vehicles) are interested in ultra-low power electronic health monitoring systems for system monitoring, diagnostics and prognostics. For the medical industry, battery powered systems like heart pacemakers, blood glucose monitors, etc. would benefit from ultra-low power electronic health monitoring systems. REFERENCES: [1] P. Bradford: “Power Consumption and Health Monitoring Systems,” Redstone Arsenal Energy 2010 Workshop, Redstone Arsenal, AL, September 2010. Available from https://rsic.redstone.army.mil. [2] R. Kaushik, and S. Prasad: “Low Voltage CMOS VLSI Circuit Design,” Wiley, 1999, ISBN: 047111488X. [3] F. Shearer: “Power Management in Mobile Devices,” December 2007, ISBN-13: 9780750679589. [4] Phys.org: "A 'dirt cheap' magnetic field sensor from 'plastic paint': Spintronic device uses thin-film organic semiconductor," 12 June 2012, http://phys.org/news/2012-06-dirt-cheap-magnetic-field-sensor.html. [5] Phys.org: "Team develops world's most powerful nanoscale microwave oscillators," June 2012, http://phys.org/news/2012-06-team-world-powerful-nanoscale-microwave.html. [6] Y. Bando, and D. Golberg: “Synthesis and properties of nanotubes filled with solids, liquids and gases,” 5th IEEE Conference on Nanotechnology, pp. 1-2, 2005. [7] Phys.org: "New semiconductor research may extend integrated circuit battery life tenfold," 20 Jan 2013. http://phys.org/news/2013-01-semiconductor-circuit-battery-life-tenfold.html KEYWORDS: electronic health monitoring, diagnostics, prognostics, low power, signal processing, DSP, microcontroller A14-007 TITLE: Ceramic Matrix Composite Materials for Transpiration Cooling TECHNOLOGY AREAS: Weapons 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 5.4.c.(8) of the solicitation. OBJECTIVE: To develop and demonstrate ceramic matrix composite materials for missile applications with transpiration cooling. DESCRIPTION: The advantages of external transpiration walls for cooling and drag reduction of hypersonic air vehicles are well known[1,2]. These same advantages have been applied to internal gas turbine combustor walls[3] and should equally apply to airbreathing missiles – ducted rockets, ramjets, and particularly scramjet powered air vehicles. Transpiration refers to the transport of fluid through a porous wall at near zero momentum; i.e., an "oozing" or "bleeding" process. This transpiration cooling process provides for a layer of fluid to insulate and convect heat away from the porous wall and, additionally, reduce the viscous drag of the cross flow. The application of transpiration cooling to missile systems has been inhibited, at least in part, to the added complexity plus the high cost and time required to fabricate porous transpiration walls from heat resistant metals. Even for scramjet engine applications where the internal viscous drag may well exceed the external form or pressure drag, the advantages of the technology have largely been deferred while addressing the fundamental problems of engine design and operation. Ceramic matrix composites (CMC)[4], however, may well provide an alternative to the tedious and expensive production process for metal transpiration surfaces. Ceramic matrix composites offer unique properties for high temperature applications. Most commonly proposed as a structural material for rocket nozzles, motor cases, and airframes, they should provide adequate strength over the required range of operating temperatures with the potential for weight savings and increased propellant loading since insulation materials may be reduced or eliminated. Indeed, those strength and temperature characteristics are now being exploited for uncooled turbine shrouds and high pressure turbine static seals for advanced turbojet engine designs[5,6]. More uniquely, in an unfilled form, these porous ceramic matrix composites could prove ideal as transpiration materials for combustor walls or external air vehicle surfaces. CMCs such as Carbon (C), silicon carbide (SiC), and alumina (Al2O3) are often manufactured by a process that results in a highly porous product after the first step (often as much as 20% porosity). In subsequent steps they are filled and processed so as to reduce the porosity. The reduction in porosity improves both structural and high temperature properties which are beneficial for the applications mentioned above. CMCs with porosity may have applications for transpiration cooling but their properties need further investigation to determine the optimum combination of porosity, strength, and temperature capabilities. Hence, the technology for ceramic matrix composite production is now well established but innovation will be required for transpiration boundaries in terms of fabrication and properties to include thermo-structural properties, containment fixtures, porosity, and fluid flow characteristics. What is needed then is a clear demonstration of porous CMCs for missile transpiration cooling applications, specifically for scramjet engine internal combustor walls and for hypersonic air-vehicle external walls. Success in those applications should assure equal success in many commercial applications as well. Metrics for success would be an area weight of half that for a fabricated steel transpiration surface at one-fifth the cost. Additionally, the unfilled CMC material should show a degradation of no more than fifty percent for any time period at elevated temperatures. PHASE I: Innovative technical approaches will be formulated leading to the development of ceramic matrix composite materials for transpiration cooling as a marketable product. Preliminary analysis of test article concepts will be performed for structural and thermal requirements. PHASE II: To demonstrate and validate the technical approaches of Phase I, plans will be formulated for the completion of two ground based tests in a Government test facility[7]. The first test will be of a CMC transpiration cooled and/or fueled planar wall in an existing supersonic combustion duct[8]. The second test will be of a CMC transpiration cooled external wall section in an exiting conical body at hypersonic velocities[2]. Additionally, prototype ceramic matrix composite coupons for these tests will be delivered to the Government for high temperature strength testing and fluid flow characterization. These two tests will require both planar and conical CMC transpiration surfaces. The combustion duct will employ two planar transpiration walls of approximately 0.10 m width by 1.2 m length. The 10.5 degree (half angle) conical body will use a transpiration wall of approximately 0.76 m in length with a base diameter of 0.34 m. Additional geometric details are given in references 1,2, and 8. The two ground based tests will be run to validate the use of ceramic matrix composite materials for transpiration cooled combustor and air vehicle walls. Testing will require detailed analysis for thermal and structural requirements, fabrication of the required composite transpiration wall materials, installation in the existing combustor and conical tunnel model, and completion of the ground testing. Deliverables will consist of the resultant test data to demonstrate structural integrity and aerothermal characteristics of the transpiration cooled installations. Metrics for success in these ground based tests will be (1) structural integrity for a test time of 50 ms with and without transpiration, (2) a reduction of viscous surface drag by a factor of ten with active transpiration, and (3) a reduction in surface heat flux by a factor of ten with active transpiration. PHASE III: The end result of this research effort will be a validated approach for the production of composite materials for transpiration cooling as a marketable product. For military applications, this technology is directly applicable to all rocket propulsion missile systems as an advanced material for nozzles, motor cases, and airframes with the additional application to combustors for airbreathing missiles. Gas turbine applications, both military and commercial, to include both turbo shaft and turbojet variants have already employed CMC materials for combustor walls and variants of transpiration cooling for combustor walls and turbine blades[9,3]. This advancement for transpiration with porous CMC materials will have direct application to this large commercial arena. For strictly commercial applications, this technology is directly applicable to all commercial launch systems such as the NASA Aries, and the Delta and Atlas families. Additionally many industries utilizing high temperature combustors – petroleum, cement, power generation, and food processing to name but a few – could employ this technology. REFERENCES: 1. Holden, M.S., et.al., “An Experimental Study of Transpiration Cooling on the Distribution of Heat Transfer and Skin Friction to a Sharp Slender Cone at Mach 11 and 13,” AIAA-90-0308, AIAA 28th Aerospace Sciences Meeting 8-11 January 1990. 2. Holden, M.S., et.al., “An Experimental Study of the Effects of Injectant Properties on the Aerothermal Characteristics of Transpiration-Cooled, Cones in Hypersonic Flow,” AIAA-90-1487, AIAA 21st Fluid Dynamics and Lasers Conference, 18-20 June 1990. 3. Cerri, G., et.al., “Advances in Effusive Cooling Techniques of Gas Turbines,” Applied Thermal Engineering, 27 (2007), 692-698. 4. Zok, F.W. And Levi, C.G., "Mechanical Properties of Porous-Matrix Ceramic Composites", Advanced Engineering Materials, 2001, 3, No. 1-2. 5. “Betting on the Future,” Aviation Week & Space Technology, 1 July 2013, pp. 18-20. 6. “Carbon Redux,” Aviation Week & Space Technology, 15 July 2013, p. 21. 7. Holden, M.S., et.al. “Experimental Studies in the LENS Supersonic and Hypersonic Tunnels for Hypervelocity Vehicle Performance and Code Validation,” AIAA-2008-2505, AIAA 15th International Space Planes and Hypersonic Systems and Technologies Conference, 28 April-1 May 2008. 8. Wadhams, T.P., Holden, M.S., and MacLean, M., “Mach 6 Clean Air Studies of Mixing and Combustion in the CUBRC Combustion Duct,” 58th JPL/44th Combustion/32nd Airbreathing Propulsion Joint Subcommittee Meeting, JANNAF Paper 1786, Arlington, VA, April 20, 2011. 9. Awolola, A., “Gas Turbine Combustor Wall Cooling,” Ph.D. Thesis, University of Leeds, 2 July 2012 KEYWORDS: ceramic, composite, matrix, transpiration, combustor, wall A14-008 TITLE: Wide Field of View Primary Optic for Semi-Active Laser Sensor TECHNOLOGY AREAS: Weapons ACQUISITION PROGRAM: PEO Missiles and Space |