Air Force sbir 04. 1 Proposal Submission Instructions
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| PHASE I: Develop one or more beamformer architectures, including identification of the types of components recommended. Use analysis and simulation to illustrate and quantify performance of the proposed approaches. Produce a transmit loss budget, a receive G/T (Gain/Temperature) budget, and directivity patterns. Quantify the bandwidth, and estimate the weight. Address other performance issues that are unique to the architecture.
PHASE II: Fabricate and demonstrate samples of the critical components of the selected Phase I beamformer. Combine demonstrated results with analysis and simulation to illustrate large array beamsteering, transmit loss, receive G/T, directivity patterns, and bandwidth. Validate that the beamsteering timing and control supports typical communications track functions DUAL USE COMMERCIALIZATION: The technology developed under this effort is directly applicable to phased-array antennas used for communications, in both commercial and military applications. Use of large antennas in a communications link increases the transmit gain and the receive power-collecting area. This enables increased data rates; decreased error rates; lower transmit power; and higher receive noise temperature. REFERENCES: KEYWORDS: Communications, Radar, Antenna, Phased-Array, Beamformer, Space Feeds, Beamsteering AF04-025 TITLE: Novel Methods to Improve Efficiency of Copper-Indium-Gallium-diSelenide Solar Cells TECHNOLOGY AREAS: Materials/Processes, Space Platforms OBJECTIVE: Increase the efficiency of Copper-Indium-Gallium-diSelemnide thin-film solar cells through novel processing schemes or materials. DESCRIPTION: Flexible Thin-Film Photovoltaics (FTFPV) are a revolutionary new solar power generation technology that, combined with lightweight array support structures being designed, promises a 5X reduction in solar array cost, a 5X reduction in stowed volume, and increased radiation resistance compared to state-of-the-art rigid panel solar arrays. In trade studies for a 20 kW GEO (Geosynchronous Earth Orbit) mission, these advantages have been found to hold despite the 2.5-times larger size of FTFPV arrays. These conservative calculations show that rigid panel arrays are limited to <110 W/kg, even with 35% efficient solar cells, while thin-film solar arrays on metal foil substrates will yield >160 W/kg, at end-of-life. FTFPV on reduced mass substrates will result in even higher specific power levels, but maximum specific power requires both lightweight substrates and increases in efficiency beyond the 8-10% AM0 (Air Mass Zero) efficiency typically found currently for large area FTFPV. Opportunities for increased efficiency of FTFPV remain. Copper-Indium-Gallium-diSelenide (CIGS) thin-film solar cells (and other alloys of Copper-Indium-Gallium-diSelemnide) show promise for efficiencies of 15-20%, and laboratory-scale 15% AM0 efficiency cells have been demonstrated. However, efficiencies typically decline as cell size increases, and innovative designs are needed to boost performance. The bandgap of CIGS cells has not increased substantially above 1 eV, far from optimal for the solar spectrum. Ga (Gallium) has been added to CIS ( Copper-Indium-diSelenide) but this has increased open circuit voltages less than expected. Partial replacement of Se (diSelenide) with S (Sulfide) to increase the bandgap has been achieved with some success. CIGS multijunction cells have not yet been successfully fabricated. Potential methods of achieving increased efficiency are alloying to increase the material bandgap or novel processing schemes that avoid undesirable compositional changes at the CIGS/CdS (Copper-Indium-Gallium-diSelenide/Cadmium Sulfide) interface. Other innovative methods expected to result in large area CIGS solar cells with efficiencies >15% AM0 are also sought. The processing methods proposed must be capable of depositing the cells on high temperature polymers or lightweight metal foils for space FTFPV arrays of high specific power. PHASE I: Develop innovative methods for increasing the efficiency of CIGS cells by increasing the cell bandgap, producing a multijunction cell or, improving processing. Phase I will demonstrate the feasibility of the proposed design/processing scheme. The method should be economical with respect to processing conditions and material use and must be capable of production scale-up. PHASE II: Finalize development of all deposition processes necessary to demonstrate the feasibility of the design developed during Phase I (in a laboratory environment). Demonstrate the feasibility of using the resultant process for fabrication of a candidate thin- film solar cell array. Large area CIGS solar cells will be provided to the Air Force Research Laboratory for evaluation. DUAL USE COMMERCIALIZATION: Dual use commercialization would occur through the development of the technology, and the process must yield a competitive cost per watt, watt per kilogram, and long-lived solar arrays available for DoD and commercial space systems. The demand for DoD space systems is strong. REFERENCES: 1. K. Kushiya, "Improvement of electrical yield in the fabrication of CIGS-based thin-film modules," Thin Solid Films, vol. 387, 2001, pp. 257-261. 2. T. Negami, Y. Hashimoto, S. Nishiwaki, "Cu(In,Ga)Se2 thin-film solar cells with an efficiency of 18%," Solar Energy Materials & Solar Cells, vol. 67, 2001, pp. 331-335. KEYWORDS: Satellite Electrical Power, Power Generation, Solar Cells, Thin-Film Photovoltaics, Conversion Efficiency, Photovoltaics, CIS, CIGS AF04-026 TITLE: Multifunctional Phased Array Antenna Modules TECHNOLOGY AREAS: Sensors, Electronics, Battlespace OBJECTIVE: Develop and demonstrate high efficiency, phased-array antenna with integrated energy storage and enhanced array pointing precision. DESCRIPTION: Current spaceborne communication and surveillance spacecraft employ sophisticated, single purpose phased-array antennae for transmission (and/or reception) of RF (Radio Frequency) energy. Integral to the performance of these devices are the separate power and thermal management subsystems, typically developed independently as part of the spacecraft bus. Precise pointing requirements for both communications and surveillance require precise knowledge and control of dimensional tolerances that are adversely affected by thermal distortions induced by waste heat from RF components. Because phased array antennas typically occupy large areas that tend to radiate heat rapidly in space, keeping transmit/receive modules warm enough is usually of more concern than keeping them cool. Power distribution for large phased-array antennas may entail power transmission over relatively large distances that in turn lead to high power distribution losses and inefficient spacecraft operation. The combined effect of pointing requirements, thermal management and power distribution tend to increase the overall weight of the "assembled" spacecraft. Significant reductions in spacecraft weight may be enabled by direct integration of power and thermal management functions at the component level of the phased array. The objective of this project is to develop technology that enables energy storage and thermal management at the components level of transmit/receive antenna modules. Potential system level benefits of this technology would be mass reduction and/or affordability improvement through higher level integration of payload with supporting technologies. PHASE I: Develop and demonstrate innovative electronic packaging concepts to enable the integration of energy storage and thermal management is conventional phased- array transmit/receive antenna subsystems that will provide significant overall spacecraft mass reduction. Invent, develop, and demonstrate of proof-of-principle breadboard designs that enable integration of energy storage and thermal management into transmit/receive antenna module (TRAM) devices. Conduct concept designs, thermal analysis and energy management/thermal vacuum experiments (if appropriate and as needed) to 1) demonstrate applicability of the multifunctional phased-array antenna architecture to communications and surveillance systems of interest to the Air Force and DoD, 2) validate concept feability in representative operating environments through appropriate modeling and/or experiments, and 3) demonstrate system level benefit in terms of antenna mass/unit area of the proposed multifunctional phased- array antenna. PHASE II: Develop and demonstrate sub-scale RF transmit/receive phased-array antenna incorporating integrated energy storage and thermal management modules. Validate RF performance using appropriate ground simulation and testing. DUAL USE COMMERCIALIZATION: Application of this technology would permit next generation commercial satellite communication systems to display higher efficiency RF operation and higher transmitted output with existing energy generation technologies. REFERENCES: 1. Harvey, Tim, "The Use of Neural Networks in A Smart Battery Charger," University of Missouri-Rolla, 1995. 2. Spacecraft Integrated Electronic Structures (SIES), Suraj Rawal, Lockheed-Martin, AFRL-VS-TR-1997-1011. KEYWORDS: Phased Array Antennas, Multifunctional Structures, Energy Storage, Power Distribution, TRAM, Thermal Management AF04-027 TITLE: Encryption, Decryption Field Programmable Gate Array Using Specialized Software TECHNOLOGY AREAS: Information Systems, Sensors, Electronics, Battlespace OBJECTIVE: Develop reconfigurable hardware and software tools to support FPGAs optimized for advanced encryption/decryption algorithms. DESCRIPTION: Communications security (COMSEC) is essential to commercial and military satellite communications links. As encryption/decryption computer platforms such as supercomputers and quantum computers become more capable and exhibit greater computing speed, existing encryption/decryption algorithms can become obsolete. This opens opportunity for more sophisticated algorithms and integrated circuits to commensurate with increased computer capability and greater computing speed. Continuing developments in reconfigurable computing and Field Programmable Gate Array (FPGA) technology advance the potential for application of FPGA-supported, reconfigurable logic as a replacement for spacecraft-based, hardwired Application Specific Integrated Circuit (ASIC) chip systems. The purpose of this topic is to exploit advances in FPGAs and associated software tools to develop advanced encryption/decryption algorithms. The primary goal is maximize throughput (parallelism is possible), while maintaining flexibility in protocols for encryption/decryption with maximum growth in the future. If possible, the SBIR seeks a breakthrough domain-specific FPGA technology that is rad-hard. It is also possible to consider a wider range of possibilities, such as using high-density FPGAs that are commercially available by using a combination of supplemental circuitry, design techniques, and programming tools. Approaches that maintain capability while ensuring resilience to radiation effects, including total dose, latch-up, single event upset and dose rate are most highly sought after. PHASE I: Develop a feasible basis for an FPGA architecture and approach for efficient identification and migration of encryption / decryption algorithms. If a domain-specific architecture is proposed, identify the process technology and steps taken to ensure radiation hardness (through design and/or process). PHASE II: Extend Phase I results to develop a feasibility demonstration, capable of implementing extremely high-throughput encryption / decryption algorithms (plural). Demonstrate ability to perform in the presence of single event effects. Also demonstrate the ability to easily up-grade algorithms within system. Plan and conduct a demonstration of a mutually agreed-upon, government-furnished unclassified encryption and decryption algorithm using the prototype FPGA. Demonstration must include throughput and implementation of a government/contractor agreed, government supplied encryption and decryption algorithm. DUAL USE COMMERCIALIZATION: Commercial applications of encryption technology include banking transactions, transfers of data containing proprietary information, and medical records, or, in general, digital rights management and privacy protection. Military applications include encryption for satellite and terrestrial communications systems. In design, the protection of intellectual property is an important common concern. REFERENCES: 1. Mosanya, E et.al. "CryptoBooster: A Reconfigurable and Modular Crytptographic Coprocesor," Crytopgraphic Hardware and Embedded Systems, 1999, v. 1717,p.246-256. 2. Karri, R.et.al. "Fault-Based Side-Channel Cryptanalysis Tolerant Rijndael Symmetric Block Cipher Architecture," IEEE International Workshop on Defect and Fault Tolerance in VLSI Systems; 2001; p. 427-435. 3. Kean, Tom, "Crytographic Rights Management of FPGA Intellectual Property Cores," Algotronix Ltd, 2002. 4. Kean, Tom, "Secure Configuration of Field Programmable Gate Arrays," Proceedings of IPL 2001, Belfast, UK. KEYWORDS: Encryption, Algorithm, Applications Specific Integrated Circuit, Microcomputer, Communications Security, Field Programmable Gate Array AF04-028 TITLE: MicroElectroMechanical Systems Based Electronically Steerable Antenna TECHNOLOGY AREAS: Sensors, Electronics, Battlespace OBJECTIVE: Develop and demonstrate a MicroElectroMechanical Systems based electronically steerable antenna. DESCRIPTION: Phased array antennas have several advantages over mechanically steered antennas. They are lighter in weight, more agile, and induce no angular momentum to the satellite when redirecting the beam. Phased array antennas have traditionally used MMIC (Monolithic Microwave Integrated Circuit) phase shifters, which have two key weaknesses. They can contribute substantially to the cost of fabrication and tend to introduce a relatively high insertion loss, reducing the phased array antenna's effective EIRP (Effective Isotropic Radiated Power. Multibit MEMS (MicroElectroMechanical Systems) controlled phase shifters have recently been demonstrated that show promise in lowering cost and insertion loss. The purpose of this topic is to develop and demonstrate MEMS controlled phase shifters in a subarray design with a minimum of two elements that are capable of space qualification. PHASE I: Design a multibit MEMS phase shifter. In concert with the Air Force, select an operating frequency band and simulate operation including phase delay and insertion loss across the frequency band. Develop a manufacturing plan to build a working subarray. Describe the production approach and provide projected costs. PHASE II: Manufacture and integrate a minimum of 10 multibit MEMS phase shifters into a phased array antenna subarray. Characterize their performance over the operating frequency band and compare against theoretical performance. Describe next generation modifications for improved performance. Document the results. DUAL USE COMMERCIALIZATION: Commercial communications satellites in LEO (Low Earth Orbit) and MEO (Medium Earth Orbit) could benefit from this technology by reducing costs and insertion losses. Military communications systems could also use this technology to produce lighter weight and thus cheaper satellite systems. REFERENCES: 1. C. Goldsmith, T.H. Lin, B. Powers, W.R. Wu, and B. Norvell, "Micromechanical Membrane Switches for Microwave Applications," 1995 IEEE MTT-S Dig., pp. 91-94. 2. Y. Liu, A. Borgioli, A. Nagra, R. York, "K-Band 3-Bit Low-Loss Distributed MEMS Phase Shifter", 2000, IEEE M&GW Letters. 3. Brown, Elliott, "On the Gain of a Reconfigurable-Aperture Antenna" IEEE Transactions on Antennas and Propagation", Oct. 2001. KEYWORDS: MEMS, Antenna, Phase Shifter, Phase Delay, Transmission Line, Phased Array AF04-029 TITLE: Radiation-Resistant Solar Cell Coverglass TECHNOLOGY AREAS: Materials/Processes, Space Platforms OBJECTIVE: Develop innovative solar cell coverglass materials and coatings with increased radiation resistance. DESCRIPTION: The end-of-life (EOL) power generation performance of satellite solar arrays would be improved by the use of coverglass materials and coatings with an increased resistance to radiation-induced darkening, especially in higher radiation orbits such as Half-Geo (geosynchronous earth orbit). Today's high performance multijunction solar cells require equally high performance broadband coatings and coverglass materials. Ceria and other dopants are typically incorporated into solar cell coverglasses in order to decrease the darkening effects of radiation and to protect the coverglass adhesive from UV (ultraviolet) exposure. The coverglass can incorporate antireflective, conductive, and UV and near IR (infrared) reflector coatings. Commercially available solar cell coverglasses are capable of withstanding 15 years in GEO and 10 years in LEO (low earth orbit) without darkening. New materials and innovative solutions are sought to obtain similar lifetimes for coverglass in high radiation (Half-Geo) orbits, and the materials must demonstrate resistance to electron and proton radiation profiles found in the half-GEO orbit. These new materials must maintain a high degree of spectral broadband transmissivity, withstand UV exposure, have high thermal emissivity, and possess a high index of refraction. PHASE I: Develop and validate innovative technologies for the fabrication of solar cell coverglasses with increased radiation resistance combined with broadband transmission and high emissivity. Provide demonstration of coverglass material. PHASE II: Optimize one or more materials developed in Phase I and demonstrate radiation resistance on prototype coverglass samples. DUAL USE COMMERCIALIZATION: This technology is applicable to both military and commercial satellite solar arrays and is enabling for higher radiation orbits. The improved EOL power generation capabilities of this technology will have broad application in future military space systems. REFERENCES: 1. Aiken, D. J., High Performance Anti-Reflection Coatings for Broadband Multi-Junction Solar Cells, Solar Energy Materials & Solar Cells, 64 (2000), 393-404. 2. Summers, G.P.; Messenger, S.R.; Burke, E.A.; Xapsos, M.A., Walters, R.J., ?Contribution of low-energy protons to the degradation of shielded GaAs solar cells in space?, Progress in Photovoltaics: Research and Applications, 5 (1997) 407-413. KEYWORDS: Solar Cell Coverglass, Coating Deposition Technologies, Solar Arrays, Optical Properties, Radiation Environments, Multijunction Solar Cells. AF04-030 TITLE: Small Launch Vehicles (SLV) Technologies TECHNOLOGY AREAS: Sensors, Electronics, Battlespace, Weapons OBJECTIVE: Develop innovative Small Launch Vehicle (SLV) technologies that provide responsive, cost effective spacelift solutions for Small-Sat and Common Aero Vehicle (CAV) architectures. DESCRIPTION: Both Small-Sat and CAV payloads are showing increasing promise in improved mission capability. Small-Sat and CAV payloads will need a complementary responsive, cost-effective SLV capability. Innovative technologies are being sought that address SLV responsiveness and cost reduction in the areas of avionics, propulsion, airframe and structures, manufacturing, integration, and/or operations. A vehicle focus identifies enabling SLV technologies using a SBIR time-phased, risk reduction approach. Development of these technologies will make possible the eventual acquisition and operation of a responsive and cost-effective SLV-based system capable of rapidly deploying small satellites (200-1000lbs) and CAVs (under 2000lbs.) to low earth orbit (LEO). At the end of Phase I and II, the contractor is expected to have developed and tested technologies that are enabling to their SLV design in terms of addressing proposed SLV responsiveness and affordability goals. The result of these technology demonstrations will determine whether they are feasible to warrant consideration for a Phase III flight test program. PHASE I: Conduct sub-orbital booster design analysis with proposed component technology requirements. All proposed sub-orbital booster technologies shall be traceable to an orbit capable SLV, whereby specific technologies are identified for Phase II development/test. Specifically, proposed Phase II SLV technology demonstrations must address a unique combination of improved launch responsiveness and cost reduction technologies. This will require technology risk mitigation plans that addresses identification, rationale, and test exit criteria of proposed high-risk component(s) in meeting advertised improvements to SLV launch responsiveness and cost. PHASE II: Develop prototype sub-orbital booster components identified under Phase I. Refine the design of the sub-orbital booster as knowledge is gained through the critical component development process. The prototype hardware shall emphasize launch responsiveness and cost reduction technologies, and possess sufficient design information to fabricate, integrate, and operate the selected high-risk component(s) for demonstration. The contractor shall perform prototype ground test and evaluation of the enabling components per the Phase I technology risk mitigation plan. Phase II shall demonstrate critical booster component technologies that address launch responsiveness and/or cost reduction, which sufficiently meet required subsystem performance and reliability requirements. DUAL USE COMMERCIALIZATION: Based on an in-depth USAF evaluation of Phase II results, a non-SBIR funded Phase III sub-orbital flight program will be considered. Dual use applications include target vehicles, sounding rockets, Ballistic Missile Replacement (BMR) and strap-on boosters. Enabling technologies that evolve from this program are directly traceable to a new responsive and low cost SLV for both commercial and military applications. A responsive SLV would enhance the launching of military tactical satellites for theater Intelligence and/or Surveillance and Reconnaissance (ISR). A low cost SLV would enhance the deployment of commercial LEO Communications Constellations (e.g., Store and forward paging communication systems). Other dual use variants of this technology include booster and/or upper stages systems for larger launch vehicles. If Phase II technical exit criteria are met and commercial and/or government (non-SBIR) program funds are identified for Phase III, the contractor shall design, fabricate, integrate, and flight-test the sub-orbital vehicle as defined under Phases I-II. REFERENCES: 1. Steven J. Isakowitz, "International Reference To Space Launch Systems," AIAA, Second Edition, 1991. 2. George P. Sutton, Rocket Propulsion Elements, John Wiley & Sons, Sixth Edition, 1992. 3. James R. Wertz and Wiley J. Larson (editors), "Reducing Space Mission Cost," Microcosm/Kluwer, 1996. KEYWORDS: Launch Vehicle Design, Sub-Orbital Vehicle, Satellite Micro-Miniaturization, Common Aero Vehicle, Technology Risk Mitigation, Flight Test and Evaluation, Small Launch Vehicle AF04-031 TITLE: Thermal Protection System (TPS) for Agressive Reentry Trajectories of Space Vehicles TECHNOLOGY AREAS: Materials/Processes, Space Platforms OBJECTIVE: Develop innovative lightweight TPS for vehicles with agressive reentry trajectories. DESCRIPTION: The need for hypersonic vehicles to meet emerging Department of Defense (DoD) requirements has necessitated the development of a new generation of robust TPS systems. Extended mission times in areas of high reentry heat loads have exceeded the current limits of the state-of-the-practice TPS designs. Current TPS designs and materials are incapable of providing the level of protection required by these mission scenarios without significant increases in allocated TPS weight and volume. The combination of large integrated heat loads, large surface heat fluxes, and long duration flights (time > 4100 seconds) for emerging DoD, National Aeronautics and Space Administration, and commercial vehicles; requires new TPS designs and materials to accommodate quantum leaps in demands exerted by new missions. Also, hypersonic vehicles such as the Common Aero Vehicle (CAV) will have flight trajectories that make the utilization of high temperature coatings difficult due to the high shear experienced during extreme maneuvers employed during the terminal portion of the vehicle’s trajectory. 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