Air Force sbir 04. 1 Proposal Submission Instructions
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| DUAL USE COMMERCIALIZATION: Reliable MTI of enemy and civilian items of interest is necessary to support precision targeting. This capability should limit collateral damage and optimize warfare resources. This capability also gives our diplomatic assets the early warning and evidence needed to diplomatically stymie enemy intent. This capability has significant role in peacetime also by providing realistic data to support war gaming and training exercises. The spin-off to support commercial applications and homeland security concerns is significant. Search and rescue and traffic analysis are only a few practical applications of MTI.
REFERENCES: 1. Lauer, C.J. “A Clutter Model for Space Based Radar.” Mission Research Corp., Santa Barbara, CA; November 1983. 2. Quick, Darrell A. “Developing Map-Based Graphics for the Theater War Exercise.” Air Force Institute of Technology School of Engineering, Wright-Patterson AFB, OH; December 1988. 3. Jao, Jen K. and Goggins, William B. “Efficient, Closed-Form Computation of Airborne Pulse-Doppler Radar Clutter.” Massachusetts Institute of Technology Lexington Lincoln Lab, Hanscom AFB, MA; May 1985. 4. Sparrow, David A. “Modeling Radar Clutter.” Institute for Defense Analyses, Alexandria, VA; May 1991. 5. Gierull, Christoph, "Analysis of the Small Sample Size Performance of Fast Fully Adaptive STAP Techniques for MTI Radar", Defence Research Institute Ottawa, Canada, Oct 1, 2001 KEYWORDS: radar, space-based, moving target indication (MTI), background, clutter, modeling, simulation AF04-037 TITLE: Innovative Rapid Satellite Prototyping, Integration, and Manufacturing TECHNOLOGY AREAS: Materials/Processes, Space Platforms OBJECTIVE: Develop and implement new methods to design, manufacture, and test satellites that will enable rapid production, simplified integration and significantly reduced manufacturing costs. DESCRIPTION: The Air Force has an operational need to be able to launch satellites on demand for a variety of missions. One critical capability that is required to achieve this goal is the rapid fabrication of satellites and integration onto the launch vehicle. Currently, satellites are built using a “design from scratch” methodology where the spacecraft and launch are specifically tailored for the individual mission. Not only are wiring harness and software totally customized for each satellite/mission combination, but often the combination of “commodity” components (defined as spacecraft subsystems and components that are largely reusable) requires the development of many custom interfaces. This approach has been very successful in producing highly capable satellites with minimized mass. Unfortunately, it is also the most costly way to produce a satellite. While these maximum capability satellites will always be required for some space missions, this solicitation is designed to explore advances in satellite design and manufacture that will produce a product with slightly reduced capability, slightly increased mass, and major decreases in cost and fabrication time. There are several avenues whereby small relaxations in the satellite capability and mass requirements can afford large decreases in development, time and cost. Using commercial-off-the-shelf (COTS) components might result in additional mass or in unnecessary excess capacity but will greatly reduce the cost and fabrication time. The development of standardized satellite sub-systems (e.g., power, avionics, telemetry, attitude determination and control, bus) could enable a modular architecture of components that would be rapidly integrated to produce a satellite for a selected mission. These are felt as necessary, but not sufficient conditions for ultra-rapid development of flight systems. It is necessary to investigate creative solutions to avoid the need to develop custom hardware, software, and interfaces. Ideally, complex interactions can be managed by script-driven interface concepts, blending a number of software and hardware concepts together. More primitive implementations of this concept have been referred to as “plug-and-play." More advanced embodiments can dramatically reduce the time to create a complex spacecraft system by reducing many complicated interface decisions to simpler ones. Self-organizing networking protocols (wireless examples include the Bluetooth standard) can potentially simplify not only interface design but reduce the burden of complex software development. Proposed concepts should strive for techniques that can eventually achieve a fabrication and integration time of a few days. In the near term, these techniques should cut fabrication time in half and decrease cost to about $2M for a small satellite. Rapid, cost-effective methods to test and prototype new satellites will greatly enhance the entire satellite community. However, proposed concepts should focus on small satellites attractive for technology demonstration, in-theatre support, and on-orbit mobility. Proposals can address the entire spacecraft, selected sub-systems of the spacecraft bus, individual payloads, or focus on the rapid integration of the components onto the spacecraft bus or the spacecraft onto the launch vehicle. In either case, proposers should seek approaches that can deliver low-cost and rapid prototyping, design, fabrication and/or integration over the widest range of relevant capability. PHASE I: Develop and mature a technique for rapid fabrication of small satellite at low cost. Perform analysis to identify AF and commercial missions that could benefit using the proposed concept. If appropriate, develop engineering designs for the proposed concept. Where appropriate, work with Air Force technical personnel to define specifications, performance, manufacturability, and cost guidelines. PHASE II: Demonstrate the feasibility of technologies identified in the Phase I. Specific processes and designs will be perfected and tested. Prototype level (or higher) hardware will be built for testing and demonstration. DUAL USE COMMERCIALIZATION: The successful development of a low-cost, rapid fabrication, small satellite will realize high commercialization potential from DoD, NASA, and industry. REFERENCES: 1. J. Miller, D. Goldstein, T. Robinson - AeroAstro, Inc.; S. Buckley, J. Guerrero – AFRL, “Spaceframe: Modular Spacecraft Building Blocks for Plug and Play Spacecraft,” 16th Annual AIAA/Utah State University Conference on Small Satellites,” Utah State University, Logan, Utah, 13 August 2002. 2. Rapid Spacecraft Development: Results and Lessons Learned by William A. Watson, Rapid Spacecraft Development Office, GSFC 2002 IEEE Aerospace Conference, Big Sky, Montana. 3. Integration and Test for Small Shuttle Payloads by Michael R. Wright, Flights Systems, Integration and Test, GSFC 2002 IEEE Aerospace Conference, Big Sky, Montana. KEYWORDS: Manufacturability, Bus, Spacecraft, Payload, Satellite, Structures, Modular AF04-038 TITLE: Controlling Stability and Load Limits of Aerodynamically Induced Forces on Very Large Assymetric Fairing Designs TECHNOLOGY AREAS: Air Platform, Space Platforms, Weapons OBJECTIVE: Evaluate and develop means of providing stabilization, control, and structural structure load mitigation resulting from launch forces on large fairings with asymmetric profiles. DESCRIPTION: DOD is interested in developing new large diameter fairings to support launch of very large diameter optics experiments (greater than 6 meters in at least one cross-axis dimension). The intent is to provide accommodations for precision dish-shaped structures at the limit of lift capacity for the Evolved Expendable Launch Vehicle heavy launch vehicles. One means of delivery for payloads is to develop asymmetric fairing designs presenting a reduce profile to aerodynamic loading. In the past such designs have presented severe constrains on primary launch vehicle control systems. Very large peak bending moments have also results at the fairing attachment to the launch vehicle. The objective of this project is to develop novel structural fairing design concepts that minimize in-flight instability conditions and reduce lateral force induced peak stresses in the fairing. The systems or features developed must provide these control features in a manner that minimize the need for additional requirements of the launch vehicle guidance, navigation, and control (GNC) system. The proposed effort should address issues such as reliability, safety, weight, manufacturing/integration, acoustic and structural vibration mitigation, configuration flexibility, and aerodynamic loading. The use of manufacturing technology that will allow inclusion of multi-functional features into the overall structure design such as integral acoustic mitigation, connection features for separation systems, structural vibration mitigation systems, or thermal mitigation systems is advantageous. PHASE I: Develop system level conceptual structural design addressing stability and failure criteria in a fairing with at most two planes of symmetry. The fairing design must attempt to optimize containment of large dish-shaped payloads to be specified by the Air Force. Demonstrate the potential range of capability of the concept by analysis. The effort can include the production of a sub-scale engineering model for use in model/concept validation. PHASE II: Develop, with the Air Force, a mutually agreed upon sub-scale prototype fairing manufacturing and test plan. Design, fabricate, and test a sub-scale fairing shell per an agreed-on test plan under wind tunnel load conditions. Air Force facilities for these efforts may be available as Government Funded Equipment for these efforts. DUAL USE COMMERCIALIZATION: Currently, there is a growing interest in satellite launch missions requiring fairings suitable to support larger payloads consisting of mirror or dish-shape precision alignment structures. The development of fairing designs that support pre-launch final assembly and precision alignment can greatly reduce the cost of satellite development costs and can result in dramatic improvements in DOD surveillance activities and commercial investigation and management of natural resources. REFERENCES: 1. Title: Limit-cycle oscillation induced by nonlinear aerodynamic forces Author: Dotson, K. W.; Baker, R. L.; Sako, B. H. Affiliation: Aerospace Corporation, Los Angeles, CA 90009-2957, United States Journal: AIAA Journal ; November 2002; v.40, no.11, p.2197-2205 Journal Abbr.
Author: Ericsson, L. E.; Pavish, D. Affiliation: Boeing Co, Huntington Beach, CA, USA Journal: Journal of Spacecraft and Rockets ; Jan-Feb 2000; v.37, no.1, p.28-38. KEYWORDS: Fairing, Multi-Functional, Spacecraft, Controls, Mechanism, Stability, Separation, Composites AF04-039 TITLE: Advanced Technology Development Cost Estimation Methodology TECHNOLOGY AREAS: Materials/Processes, Space Platforms OBJECTIVE: Develop capability to derive accurate cost estimates for space technology development projects. DESCRIPTION: The advancement of technologies for space concepts or system applications is a high risk, high payoff investment that enhances national security and war-fighting capabilities. The ability to accurately estimate cost and risk associated with Technology Readiness Level (TRL) progression is key to effective project management of space technology programs. Historically, the use of parametric cost analysis techniques proved adequate for estimating project costs, however, future space concepts will integrate non-traditional and new technologies like reconfigurability, miniaturization, autonomy and system of systems constructs. These new design domains lack a well-defined and valid cost estimation methodology. The inability to accurately assess technical risk and the associated costs has resulted in significant program cost over-runs and even project cancellations. The capability to provide more reliable technology cost information will also help Air Force Space Command plan and budget for the Life Cycle Cost (LCC) of future operational space systems. The Air Force is seeking innovative technology investment cost estimating methodologies and tools that will give the space technology project manager reliable cost projection and risk insight into the complex space technology being managed. PHASE I: Research AF costing methodologies and cost analysis tools used to support space technology programs. The AF will provide limited, relevant project data to support case study analysis and access to existing AF cost tools. The SBIR contractor will identify the deficiencies of the current cost/risk analysis tools and develop an improved methodology that remedies these deficiencies and provides a better forecast of costs associated with a technology program's TRL progression. Results from this phase should be clearly documented and presented to the AF with a recommendation, rationale and plan for phase II refinement and implementation. PHASE II: The innovative cost methodologies developed in phase 1 will be further refined and implemented through the development of a cost management capability. This capability will help government project officers analytically understand cost implications associated with programmatic and technical options presented in their technology program. This capability should leverage innovative and intuitive user interfaces and be easily adaptable to the dynamic circumstances of modern space technology programs. This capability should be parameterized to handle a wide range of variations (programmatic, risk, cost, schedule, performance, system, etc.) and present a reliable cost forecast to the project manager. This capability will be validated by comparing its output to actual Air Force Research Laboratory experience. DUAL USE COMMERCIALIZATION: positive contribution to space technology development by giving the project manager analytical insight into the cost implications of management decisions. Project risk will be better mitigated through the ability to forecast technology investment costs and build in an analytically grounded management reserve that better handles the unknowns associated with space technology development. This capability could then be marketed to the Air Force as a proven technology cost management tool. The problem of understanding cost with respect to technology investment is not limited to space programs, in fact, all industries that rely on Research & Development and innovation to compete will benefit from the reliable cost estimating capability defined in this SBIR. REFERENCES: 1. Gilliam, Windell, "Innovative Design, Low Cost Microsatellites," Report Number AFRL-vs-TR-2001-1095XC-AFRL-VS. 2. Disselkoen, A; "Adv. Tech/Cost Assessment," Accession Number DF081153. 3. Technology Readiness Levels and their Definitions 4. http://www.jsc.nasa.gov/bu2/resources.html. KEYWORDS: Advanced Cost Model, Technology Readiness Level, Advanced Space Concepts, Subsystems, Cost Estimating, Cost Analysis AF04-040 TITLE: Plasmaspheric and Enhanced Ionospheric Total Electron Content Monitoring TECHNOLOGY AREAS: Materials/Processes, Sensors, Electronics, Battlespace OBJECTIVE: Develop a ground-based methodology and instrumentation for monitoring contributions to the Total Electron Content (TEC) from the ionosphere and plasmasphere. DESCRIPTION: The ionosphere critically affects the operation of numerous surveillance, navigation, geolocation, and other Radio Frequency systems. Ionospheric TEC (I-TEC) is a key measured parameter that is either exploited directly or used to drive real-time ionospheric models in order to assess system impacts or to support correction/mitigation. Increasing accuracy of ionospheric TEC is needed to support current and future system requirements. Today's leading source of ionospheric TEC (I-TEC) measurement is dual-frequency GPS receiver monitor systems. However, since Global Positioning System satellites operate at altitudes of ~20,200 km the GPS TEC measurement combines electron content from both the ionosphere (approximately 100 - 1000 km altitude) and the plasmasphere (altitudes greater than 1,000 km). Although the plasmaspheric TEC (P-TEC) is typically a relatively low value, representing less than 10% of the GPS TEC, when the ionospheric TEC is itself low P-TEC can be of comparable size. For example, nighttime GPS TEC is often 50% P-TEC for wide regions of the globe. In absolute terms, existing I-TEC accuracy requirements have an objective of ~1 'TEC unit', and plasmaspheric contributions to GPS TEC can vary from <1 to ~10 TEC units. Thus P-TEC is a serious source of error in using GPS TEC to meet ionospheric TEC monitoring requirements. As an example of the objective of this SBIR, development of a methodology to separate the P-TEC and I-TEC portions of GPS TEC would significantly improve the accuracy of ionospheric TEC monitoring to specify ionospheric effects on RF systems. However, the P-TEC data would also be an entirely new source of valuable space weather data. Specifying the near-Earth space environment is becoming increasingly important in order to specify and forecast effects on space vehicles. There is currently no ground-based means of wide-scale monitoring of the plasmasphere. Thus there is a critical lack of observational data to establish better climatological models and develop/validate real-time models. A methodology to accurately separate P-TEC from GPS TEC could open up vast existing data sets of GPS observations for extraction of plasmaspheric data, and provide means to obtain real-time data to drive specification models. PHASE I: Design a methodology and instrumentation for accurate separation of the P-TEC and I-TEC portions of ground-based measurements of columnar TEC. Provide evidence or analysis supporting both the feasibility of the methodology and the expected accuracy of the data. PHASE II: Develop and test instrumentation and software that implements the Phase I design and methodology. Validate the accuracy of resulting data by studies and experimental measurements providing comparison with other sensing techniques such as incoherent scatter radar measurements or Topex satellite TEC data. If the methodology supports it, develop algorithms applying the methodology to "mine" existing GPS TEC data archives to obtain both P-TEC data and more accurate I-TEC. DUAL USE COMMERCIALIZATION: An inexpensive, highly-accurate, ground-based sensing methodology/instrument that can achieve significantly improved I-TEC monitoring (by removing P-TEC) would support both dedicated monitoring for DoD RF systems and would significantly advance scientific research. A software methodology would have potential to be retrofitted into existing GPS monitors, enhancing their performance and improving AF system support. P-TEC measurements/monitoring would provide an entirely new source of valuable Space Weather data to support specification and forecast of space environment effects on space vehicles. A software P-TEC separation methodology could mine existing data sets of GPS TEC for production of possibly an entire solar cycle of globally-observed plasmasphere data. REFERENCES: 1. Ciraolo L, Spalla P., Comparison of ionospheric total electron content from the Navy Navigation Satellite System and the GPS, Radio Science, Vol. 32, N. 3, Pages 1071- 1080, May June 1997.
Rao, and G. J. Bishop, Autonomous estimation of plasmasphere content using GPS measurements, Radio Sci., November, 2002.
AF04-041 TITLE: Distributed Optical Imaging of the Upper Atmosphere TECHNOLOGY AREAS: Sensors, Electronics, Battlespace, Space Platforms OBJECTIVE: Develop and demonstrate low-cost automated weatherproof low-light optical imaging sensors for ground-based space weather monitoring networks. DESCRIPTION: Imaging of sub-visual optical emissions is one of the few means available to determine upper atmospheric conditions over large regions for purposes of monitoring, modeling, and forecasting space weather phenomena including equatorial plumes, auroral arcs, or polar cap patches. Ground-based imaging systems are affordable, flexible, and accessible compared to space-based instruments, but are limited in operational utility primarily by tropospheric weather conditions. However, as the field of view of a ground-based upper atmospheric imaging system is typically greater than the decorrelation distance for terrestrial cloud cover, a network of multiple imaging systems distributed up to hundreds of kilometer apart but with overlapping fields of view could provide high-quality real-time, space environment information even under adverse weather conditions at many of the individual sites. When favorable conditions allow for multiple overlapping observations, such a network could also provide additional high-value products including tomographic reconstructions, ionospheric drift measurements, unambiguous emission heights, and neutral density determinations. Typical low-light imagers are custom-built research units that operate in a controlled observatory environment and often require significant maintenance or operator attention. Establishment of a practical distributed imaging system, however, requires development of sensitive low-light imagers that can be manufactured in quantity for an order of magnitude smaller cost than traditional research-type instruments; can be easily transported to and installed in remote locations without specialized training; can operate reliably and autonomously when exposed to the weather for many months at a time; and can feed data directly to a network without any inputs other than electrical power, i.e., a sensor that provides the plug-and-play functionality of a weatherproof digital web-cam combined with the sensitivity needed to detect and image faint emissions from the upper atmosphere. Software algorithms, infrared observations, or other automated means of identifying image regions affected by clouds are also expected to be an important part of such a sensor network. We seek innovative solutions taking advantage of modern digital imaging and computer technologies to create a practical and effective automated imaging sensor system for distributed monitoring of the upper atmosphere. Innovations allowing simultaneous imaging at multiple wavelengths and elimination of moving parts while remaining within the constraints of a low-cost ruggedized sensor concept are especially desired. PHASE I: Design a fully automated all-sky imaging sensor and demonstrate its capability to detect sub-visual upper atmospheric emissions by constructing a working laboratory demonstrator unit that can deliver live sky images to a network in real time without human intervention. The design should be capable of being produced in quantity for costs on the order of $10,000; be compatible with portability, weatherproofing, and reliability considerations; and be able to be reconfigured for observations at other wavelengths if multi-wavelength capability is not inherent. PHASE II: Further refine the Phase I design, incorporating necessary changes identified through testing of the initial demonstration unit. Develop a prototype portable, ruggedized, weatherproof sensor based on the final design. Construct at least three prototype units and operate them exposed to the weather at multiple ground sites to demonstrate capability to form a distributed sensor network automatically acquiring and feeding live sky data to a central location in real time. Develop, implement, and demonstrate image processing algorithms or other means to automatically determine which image regions are free from clouds and to create mosaic images combining cloud-free data from multiple sites. 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