Air force 14. 1 Small Business Innovation Research (sbir) Proposal Submission Instructions

PHASE I: Demonstrate the feasibility of accurately predicting fuel spurts due to hydrodynamic ram within a generic fluid-filled fuel tank. Demonstrate the ability to accurately represent fuel spurt volume and droplet size as a function of time.

PHASE II: Fully develop the simulation tools demonstrated in Phase I and validate the models and tools on a typical fuel tank having internal stiffening structure and clutter components. Fully validate the ability to accurately represent fuel spurt volume and droplet size as a function of time.

PHASE III DUAL USE APPLICATIONS: Commercialize the code for application all commercial and military air, ground, and sea vehicles that have fluid-filled fuel tanks.

REFERENCES:

1. Fry, Phillip F., “A Review of the Analysis of Hydrodynamic Ram,” AFFDL-TR-75-102, DTIC ADA031996, August, 1976.

AF141-225 TITLE: Advanced Infrared Emitter Array (AIREA)

OBJECTIVE: Develop and demonstrate an IR scene projector (IRSP) based on advanced emitter technology that operates in the mid-wave region with high spatial resolution and high radiant intensity output.

DESCRIPTION: Hardware-in-the-Loop (HITL) test and evaluation of advanced precision guided munitions requires the capability to stimulate sensors and seekers under test with synthetic IR imagery via real-time IR scene projection. An IRSP must be capable of displaying realistic scenes at required refresh rates with sufficient resolution, dynamic range, pixel response times, and accurate radiant intensity output to properly stimulate the unit under test (UUT). Historically, HITL testing has relied on IRSPs that utilize resistor array emitter technology to project IR imagery to the UUT. However, resistor array based IRSPs are constrained in radiant intensity output and spatial resolution due to material composition and fabrication limitations. These restrictions leave resistor arrays incapable of projecting high resolution high temperature IR imagery needed to adequately test next-generation sensors and seekers. Advancements in IR seeker and sensor resolution, sensitivity, and field of view are exceeding IR scene projection capabilities. Analogous advancements in IRSP performance are needed for HITL testing of advanced IR sensors and seekers. In particular, a suitable IRSP must provide the capability to project at least 1k by 1k pixel imagery with maximum temperatures up to 3000K at 400Hz or greater. Also, IRSPs must operate in a non-flickering mode.
Recent developments in alternative IR emitter technology may satisfy requirements to test next generation IR sensors and seekers. In particular, IR LED emitter technology has shown promise in emulating IR scenes that will meet future test requirements. These emitters have demonstrated the capability to present mid-wave IR imagery with high temperature emission in a 512 by 512 pixel format using 48µm pixel pitch technology. Although the IR LED emitters have demonstrated the ability to emulate high temperature IR scene elements, they have not yet demonstrated the ability to support higher resolutions. Also, other technologies exist such as vertical cavity surface emitting lasers that may serve as an alternative IRSP for certain applications.
Novel techniques are required to increase spatial resolution of advanced emitter arrays. Investigation and analysis must be performed to identify approaches for fabricating high resolution emitter arrays and determine the feasibility of implementing these approaches. With an increased resolution, it is desired that the proposed high temperature high resolution emitter array designs maintain the well-established footprint of current generation IR arrays of 48µm pixel pitch with formats of 512 by 512 pixels to ensure compatibility of existing optical components in HITL test configurations.

PHASE I: Identify approaches to increase spatial resolution of advanced emitter arrays. Provide an analysis of alternatives that evaluates the feasibility of each approach and identifies the best approach to pursue. Provide a system performance prediction for the chosen approach.

PHASE II: Design, deliver, and demonstrate a prototype emitter array (greater than 1k x 1k).

PHASE III DUAL USE APPLICATIONS: An advanced IRSP would benefit closed-loop HITL and open-loop testing of advanced IR sensors and seekers. Military uses include test & evaluation of PGMs and aircraft protection systems. Commercial uses include testing of fire/security systems, and thermal imagers used for inspection activities.

REFERENCES:

1. Das, N. C., Shen, P., Simonis, George, Gomes, J., & Oliver, K. (2005). Light emitting diode arrays for HWIL sensor testing. Proc. of SPIE, Technologies for Synthetic Environments: Hardware-in-the-Loop Testing, 5785, 14-23.

AF141-226 TITLE: Real Time Static and Dynamic Flight External Loads Analysis

OBJECTIVE: Research and develop analysis techniques and tools to develop a predictive combined static and dynamic external loads tool using non-proprietary physics-based models and existing flight-test data in a real-time environment.

DESCRIPTION: Airframe external loads (both static and dynamic loads) are dependent on a number of different parameters. For example, horizontal tail loads (bending moment, torsion, shear) may be dependent on Mach number, dynamic pressure, normal load factor (Nz), angle of attack, horizontal tail position, trailing edge flap position, control surface rates, as well as structural dynamics, surface shock waves, etc. In a real-time flight-test monitoring environment, it is critical to be able to accurately and quickly analyze measured external loads to determine what parameters are primarily driving the loads, why there are differences between measured and predicted loads, what is causing the differences in predicted loads, and whether or not the next point in the test point series should be attempted (given a set of expected input parameters). The intent of this topic is to develop a real-time tool that can be used to analyze flight-test data and extrapolate external loads trends within the subsonic, transonic, and supersonic flight regimes.
As a result of contractual constraints, the aircraft structural and aerodynamic models that are developed by the prime contractors are not typically available to the Air Force. Therefore, the tool should be able to incorporate all available sources of information (to potentially include reduced order aerodynamic and/or structural models), but should only require sources of data that would be expected to be available to the Air Force Test Center (AFTC) (analytically predicted component loads for a given set of conditions, allowable load envelopes, and flight test measured data).
The tool should also be able to be integrated into the AFTC real-time control room environment, and should be able to utilize all previously acquired flight-test data to project expected loads for test points yet to be flown given a set of input parameters.

PHASE I: Research in this phase should focus on development of analysis methodology, analysis of alternatives, and predictive techniques, concept of operation, and any analysis needed to demonstrate readiness for Phase II.

PHASE II: Research in this phase should include development of the tool and incorporation into real-time flight-test environment at Edwards Air Force Base, CA.

PHASE III DUAL USE APPLICATIONS: This is an enabling technology that, if successful, will provide improved predictive and flight-test analysis capabilities leading to safer and more efficient loads envelope expansion. If successfully developed, this tool should also have broader use within the commercial flight test community.

REFERENCES:

1. Sims, R., McCrosson, P., Ryan, R., and Rivera, J., X-29A Aircraft Structural Loads Flight Testing, NASA Technical Memorandum 101715.

AF141-227 TITLE: Rule-Based XML Validation for T&E (RuBX)

OBJECTIVE: Develop methods for capturing semantic rules of Test & Evaluation metadata and automate validation of related XML instances.

DESCRIPTION: The use of the eXtensible Markup Language (XML) to define instrumentation metadata for test setup in Test & Evaluation (T&E) is growing rapidly. In particular, the IRIG 106 Telemetry Standard [1] has recently incorporated a translation of the Telemetry Attributes Standard (TMATS) into XML and has added the XML-based Instrumentation Hardware Abstraction Language (IHAL) [2]. Further, the intent is to incorporate the integrated Network Enhanced Telemetry (iNET) Metadata Description Language (MDL) into IRIG 106 in the near future. It is likely that other existing XML-based standards will be used in conjunction with these standards and that new XML-based structures will be developed in the years or decades to come.
The XML standard itself primarily defines syntax, although it also captures some very simple conditions, such as data typing. However, specific instances of XML used in testing must also follow a variety of semantic rules in order to be valid. A simple example of this is that the value of one parameter (say, primary gain) may affect the allowable values of another parameter (say, secondary gain). As the complexity of a T&E instrumentation system increases, the complexity of the rules and difficulty of validation increases as well. In particular, the iNET program will greatly enhance the ability to have multi-vendor systems and a complete XML instance may be created by piecing together segments of XML from different vendors. Estimates for a complete XML instance of a large data system are on the order of a million lines of XML. This requires a system-level validation that cannot be accomplished manually or by the individual vendors. For example, there may be timing constraints imposed by one vendor’s devices that can affect the timing of other vendor’s devices. In the extreme case, there may be conflicts between vendor’s setups that must be deconflicted.
The validation process thus has several levels. First, the rules themselves must be captured, both at an individual device (or vendor) level and at a system level. Second, these rules must be applied against specific XML instances. Third, any conflicts must be identified. If automated approaches to deconfliction can be developed, then there is the potential for some level of automated optimization of the overall setup as well.
As described in [3], this is part of a larger vision to provide automated instrumentation support that allows test engineers to focus on requirements and analysis. The overall problem is a constraint satisfaction problem [4] as described in [5]. The basic mechanisms of automating rule-based validation are being developed in efforts such as The Rule Markup Initiative [6][7] and approaches to optimization include Multi-Constraint Optimization techniques [8]. Part of this effort would be to evaluate what standards and efforts are useful or need to be interfaced with.

PHASE I: Research and develop structures that define instrumentation setup rules for XML-based T&E metadata. Establish theoretical foundations for capturing these rules, for using these rules to automate validation of XML, and to deconflict and optimize multi-vendor instrumentation test system setups.

PHASE II: Refine and expand the rule structures and the mechanisms for capturing the rules developed in Phase I. Work towards standardizing these structures and the non-software based mechanisms (as a non-proprietary standard). Develop software to automate the validation process and, to the extent possible, the deconfliction and optimization processes.

PHASE III DUAL USE APPLICATIONS: Applicable to systems that use instrumentation to collect measurement data, i.e., systems going through developmental T&E, including commercial aircraft, automobiles, heavy equipment, as well as areas such as structures monitoring, general manufacturing, and equipment quality assurance processes.

REFERENCES:

1. Telemetry Standards, IRIG STANDARD 106, Secretariat, Range Commanders Council, White Sands Missile Range, New Mexico, https://wsmrc2vger.wsmr.army.mil/rcc/PUBS/pubs.htm.

AF141-228 TITLE: Arc jet Test-Article Surface Recession Rate Monitor

OBJECTIVE: Develop and demonstrate a three-dimensional Recession Rate Monitor system for real-time test article surface contour mapping in arc jet facilities.

PHASE I: Develop an innovative concept for recession rate monitoring for test articles in the AEDC arc jet facilities and demonstrate the spatial and temporal resolution for 2-D images.

PHASE II: Develop and demonstrate the final prototype in the AEDC Arc Heater Facilities, or a comparable operational environment.

PHASE III DUAL USE APPLICATIONS: Diagnostic systems would have direct applicability for thermal protection system material development for military hypersonic systems. Commercial applications include arc jet testing for civil space access/reentry such as those currently under development by NASA and its various contractors.

REFERENCES:

1. Wright, Michael J., Grinstead, Jay H., and Bose, Deepak, "A Risk-Based Approach for Aerothermal/TPS Analysis and Testing", in Experiment, Modeling and Simulation of Gas-Surface Interactions for Reactive Flows in Hypersonic Flights (pp. 17-1 – 17-24). Educational Notes RTO-EN-AVT-142, Paper 17. Neuilly-sur-Seine, France: RTO. Available from: http://www.rto.nato.int/abstracts.asp.

AF141-229 TITLE: Non-Intrusive, Seedless Global Velocimetry for Large Scale Hypersonic Wind Tunnels

OBJECTIVE: Develop and validate a non-intrusive seedless velocity measurement system for instantaneous global velocimetry at high repetition rates in nitrogen-based hypersonic ground test facilities.

PHASE I: Demonstrate the feasibility of a 1-dimensional global seedless velocity measurement for canonical turbulent hypersonic flows in a small scale supersonic or hypersonic wind tunnel at a low repetition rate.

PHASE II: Develop a high repetition rate 2-dimensional global seedless velocimetry system and demonstrate the prototype measurements for canonical laminar and turbulent hypersonic flows in a government-furnished hypersonic wind-tunnel environment. The system can be marketed to customers involved in any high-speed wind tunnel testing as most facilities operate with flowfields containing nitrogen.

PHASE III DUAL USE APPLICATIONS: A global seedless velocimetry measurement system is vital to the development of next generation hypersonic vehicles and munitions.

REFERENCES:

1. Bathel, B.F., Johansen, C., Inman, J.A., Jones, S.B. and Danehy, P.M., “Review of Fluorescence-Based Velocimetry Techniques to Study High-Speed Compressible Flows”, AIAA 2013-0339.

AF141-230 TITLE: Large Scale Combustion Air Heater Laser Ignition System

OBJECTIVE: Develop a laser ignition system for the CAH at AEDC burning liquid isobutane in air at pressures between 50 psia and 500 psia. Other systems may also be considered as long as no unsafe gases or liquids such as hydrogen or Triethylaluminum are used.

PHASE I: Perform a comprehensive evaluation and documentation of the current state-of-the-art of this technology, identifying existing applications of the technology. Provide a rigorous description of the required hardware and software to be employed in developing and demonstrating a working system.

PHASE II: Based on Phase I results, build and demonstrate a prototype laser ignition system using flowing air as the oxidizer and atomized liquid isobutane as the fuel. Prototype system must operate with a combustion chamber pressure over 50 psia. Provide a conceptual design for integrating the system in with the CAH in place of the existing hydrogen / air torches.

PHASE III DUAL USE APPLICATIONS: A commercially viable laser ignition system would have military and commercial applications for a variety of internal combustion and gas turbine engines.

REFERENCES:

1. Garrard, Glenn, “Development of the Combustion Air Heater Ignition Sequence at the Aerodynamic and Propulsion Test Unit,” AIAA 2009-7359, 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference, October 2009.

AF141-231 TITLE: Alternative Approach to Contact Type Analogue Data Slipring

OBJECTIVE: Develop an approach for robust and reliable, non-contact, data transmission of up to 300 channels of dynamic and steady-state measurements streaming from instrumentation rotating up to 2048 RPM.

PHASE I: Design a transmission scheme meeting the parameters above including wiring diagrams, component identification and manufacturers specifications meeting or exceeding system requirements. Document the final design in a formal report detailing design approach and process and market survey elements.

PHASE II: Build and demonstrate system functionality in a “bench top” arrangement. Document all system changes and operational settings and tweaks that differ from phase I design.

PHASE III DUAL USE APPLICATIONS: System integration with research test rig used for tilt rotor hub and blade system in full scale wind tunnel applications.

REFERENCES:

1. Moog Sliprings: http://www.moog.com/products/slip-rings/.

AF141-232 TITLE: Temperature-Compensated Pressure Sensitive Paint (PSP) for use in Nitrogen

Environments of Large-Scale Blowdown Hypersonic Facilities
KEY TECHNOLOGY AREA(S): Sensors

OBJECTIVE: Develop a temperature-compensated, pressure sensitive paint system capable of measuring global surface pressure on test articles in a nitrogen-based, large-scale production hypersonic ground test facility.

PHASE I: Demonstrate feasibility of temperature compensated PSP measurements in a nitrogen environment on a stainless steel surface non-intrusive to standard wind tunnel surface instrumentation such as pressure transducers and thermocouples. Generate coating manufacturing and application procedures for use by AEDC personnel.

PHASE II: Develop and deploy the PSP system in a government-furnished large-scale nitrogen-based blowdown hypersonic wind tunnel. Test article and wind tunnel time will be provided by the government. The coating possibly would be a true pressure sensor and could be used for multiple non-wind tunnel measurement applications where oxygen is not present or known, such as combustion or water measurements.

PHASE III DUAL USE APPLICATIONS: A pressure sensitive measurement system that meets these requirements could be useful for multiple testing disciplines as the requirements listed do not prohibit its use in other test facilities or even for other than wind tunnels.

REFERENCES:

1. Kurits, I., Norris, J. D., "Hypersonic Global Heat-Transfer measurements During Continuous Pitch Sweeps at AEDC Tunnel 9", AIAA Paper 2010-4802.

AF141-239 This topic has been removed from the solicitation.

AF141-243 TITLE: Advanced Space Antenna for GPS
KEY TECHNOLOGY AREA(S): Space Platforms
The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Kristina Croake, kristina.croake@us.af.mil.

OBJECTIVE: Develop an advanced, space antenna with a steerable, formable beam for GPS satellites.

DESCRIPTION: GPS satellites currently use fixed beam L-band antennas to provide hemispherical coverage of the earth. Basically, each signal broadcast has to be strong enough to be received by user equipment even at the far edges of the hemisphere. The current design uses a bank of helical antennas and can provide enough tuning capability to broadcast at a higher power toward the edges of the hemisphere. Using this technique, the received signals can all have roughly the same received power in the center of the hemisphere as they do on the edge of the hemisphere.
GPS support for the military is sometimes compromised by weak signals due to the terrain, active spoofing of the GPS signals, active jamming of the GPS signals, interference from background radiation, etc. With the current, fixed beam, hemispherical broadcast approach, there is no way to increase the GPS signal power to a specific area of interest. There is a need to be able to focus the GPS broadcast on a specific area of interest, steer it to maintain the beam on that area, and provide a minimum of 5 dB higher signal strength for better general reception, overcoming a jammer, etc.
This could be accomplished by steering the beam in the same manner as phased array radar. A phased array antenna is typically constructed from multiple Transmit/Receive (T/R) elements and uses phase shifting to steer the beam electrically. This could also be accomplished with an array of stacked patch antennas, an array of helix antennas, etc. It is desirable to avoid mechanically steering the beam due to size, weight and power (SWaP) and cost issues. However, a mechanical beam steering system could be considered if it can be shown to have equal or better performance, SWaP, and cost as an electrical beam steering system. Cost goal for this antenna <$1M/m2 when produced in quantity. Careful attention should be paid to reducing each SWaP element by >10% over current antenna, and minimizing electro-magnetic interference (EMI). The proposed antenna should be suitable for use in a MEO space environment including radiation hardening. The radiation-hardness requirements for the electronically steerable antenna are:

Effect: Units: Level:

Total Ionizing Dose rad(Si) 1e6

Single-Event Upset Err/bit-day 1e-10

Single-Event Latchup None

Dose-Rate Upset rads(Si)/s 1e10

Dose-Rate Survivability rads(Si)/s 1e12
Proposals should clearly indicate how the result of the effort would be shown to improve the GPS system's capabilities through a test and validation plan. Testing and validation of risk reduction components of the overall effort in Phase I is encouraged.
Offerors are encouraged to work with PNT system prime contractors to help ensure applicability of their efforts and begin work towards technology transition. Offerors should clearly indicate in their proposals what government furnished property or information are required for effort success. Requests for other-DoD contractor intellectual property will be rejected.

PHASE I: Design and simulate a steerable beam antenna for space-based, L-band GPS applications. The antenna design should focus on high efficiency, low power, and lightweight. A brassboard is desirable for this effort.

PHASE II: The selected company will fabricate and produce a brassboard and space-qualifiable flight prototype antenna for test and evaluation. Phase II efforts should include ensuring compatibility with ICD supporting overall payload and space vehicle reference designs as part of their commercialization effort. ICD will be supplied to Phase I awardees invited to propose for Phase II.

PHASE III DUAL USE APPLICATIONS: The selected company will work with a major GPS contractor to include the results of this effort in a GPS satellite test flight/upgrade.

REFERENCES:

1. Fenn, A. J.; Temme, D.H.; Delaney, W.P.; and Courtney, W.E. "The Development of Phased-Array Radar Technology." 2000. Lincoln Laboratory Journal, Vol 12, No. 2.

AF141-244 TITLE: Distributed Sensor Management for RSO Detection, Classification and Tracking

OBJECTIVE: Develop innovative sensor management methods and algorithms to enable effective resident space object detection, classification and tracking under challenging communication environments.

DESCRIPTION: Current ground-based radar, telescopes and space-borne space surveillance assets that comprise the space surveillance network can be augmented to provide full characterization of every resident space object (RSO) in orbit from birth-to-death. This would allow persistent space situational awareness from the knowledge of traditional large satellites to picosatellites and orbital debris at Low-Earth-Orbit (LEO), Medium-Earth-Orbit (MEO), and Geosynchronous-Earth-Orbit (GEO) altitudes. Innovative approaches are sought through a combination of new and existing sensing resources with a carefully designed distributed sensor management scheme. Current plans are to augment the radar and optical telescopes in the existing space surveillance network with a 3.5-m Space Surveillance Telescope (SST), the Space Based Space Surveillance (SBSS) system, and the S-band Space Fence system. These will address the detection, classification and tracking of space objects, but determining the object’s intent or its potential capabilities will be difficult when sensing resources are limited.
As expected, a distributed sensor management scheme that best utilizes the available sensing resources will improve the capability of RSO detection, classification and tracking. Particularly, new sensor management method and associated algorithms are sought to address the following aspects: i) The goal of sensor management is to learn the global objective function online and efficiently allocate sensing assets in a distributed manner with quantifiable performance gap to the optimal solution (which is computationally prohibitive to obtain); ii) The scheme has to consider maneuver detection and nonlinear orbital state estimation with explicit models of intentional evasive motions; iii) The method has to address how to fuse heterogeneous sensor measurements and improve the existing constellation from the dynamic reconfiguration of sensing assets; iv) The solution should follow open source standard for the software development that can process heterogeneous sensory data; and v) Data sharing and onboard processing to reduce bandwidth requirements are subject to unreliable inter-satellite link (ISL) communications due to high relative angular velocity between space-based sensors and inter-plane ISL shut-offs at certain high latitudes. The proposer should develop sensor management simulation testbed and demonstrate agile sensor scheduling capability in orbital maneuver detection and collision alert.

PHASE I: Develop and demonstrate feasibility of the proposed sensor management method and algorithms with realistic space surveillance scenarios. Model the intent of object’s maneuver for accurate early collision alert. Quantify the benefit of dynamic reconfiguration for tracking multiple LEO and GEO objects of various sizes, attributes and maneuver capabilities.

PHASE II: Refine detailed designs for the Phase I sensor management, algorithms, and suitable proof-of-concept. Demonstrate potential and feasibility of the algorithm(s) using simulated data generated by 3 geographically dispersed and cooperative ground and space-based radar and electro-optical sites. Characterize algorithm performance using metrics/trade parameters. Phase II efforts should include ensuring compatibility with JMS component interfaces.

PHASE III DUAL USE APPLICATIONS: Technology should be matured and transitioned to Joint Space Operations Center (JSpOC) and potentially interested commercial and other government agencies (e.g., NASA).

REFERENCES:

1. D. Hall, “Surface Material Characterization from Multi-band Optical Observations,” Proceedings of the Advanced Maui Optical and Space Surveillance Technologies Conference, pp. 60-74, 2010.

AF141-245 TITLE: L-Band Wide Bandwidth High Performance Diplexer, Triplexer, and Quadruplexer

OBJECTIVE: Develop diplexer, triplexer, and quadruplexer for multi-carrier RF combining on Global Positioning System satellites.

DESCRIPTION: As GPS became a ubiquitous global utility, both for civil and military use, the number of digital signals has more than doubled from the original system. A flexible navigation payload is a requirement for the GPS III system, to include digital waveform generation and potentially new signals. To support flexible signal generation, new n-plexers should support wider bandwidths on the GPS carriers, especially for L1 and L2. Additionally, the higher signal powers for modernized GPS has increased the risk of multipaction. Careful consideration is required to ensure sufficient margin to support even higher power requirements in the future.
These devices should accommodate bandwidths up to 45 MHz, while avoiding multipaction for up to 500 Watts and achieving insertion loss of less than 0.5 dB.
Proposals should clearly indicate how the result of the effort would be shown to improve the GPS system's capabilities through a test and validation plan. Testing and validation of risk reduction components of the overall effort in Phase I is encouraged.
Offerors are encouraged to work with PNT system prime contractors to help ensure applicability of their efforts and begin work towards technology transition.
Offerors should clearly indicate in their proposals what government furnished property or information are required for effort success. Requests for other-DoD contractor intellectual property will be rejected.

PHASE I: Develop an innovative concept for new diplexer, triplexer, and quadraplexer designs for GPS L-Band signals.

PHASE II: The effort will design and build a brassboard or prototype for one or more of the designs (diplexer, triplexer, or quadraplexer), for ground test and evaluation. Phase II efforts should include ensuring compatibility with component interface descriptions supporting overall payload and space vehicle reference designs as part of their commercialization effort. Interface descriptions will be supplied to Phase I awardees invited to propose for Phase II.

PHASE III DUAL USE APPLICATIONS: Military application: Successful completion of the space qualification tests and transition to production for inclusion in GPS satellites. Commercial application: Wide Area Augmentation System (WAAS). Commercialization in a Phase III motivates partnerships with GPS system contractors.

REFERENCES:

1. GLOBAL POSITIONING SYSTEM: THEORY AND APPLICATIONS, Vol 1, Bradford W. Parkinson and James J. Spilker, Jr., editors, 119, p. 217, 230-232.

AF141-248 TITLE: Improved satellite catalog processing for rapid object characterization

OBJECTIVE: Develop algorithms to enable rapid cataloging and characterization of space objects in support of space situation awareness and orbital safety.

PHASE I: Using a representative space catalog and space environment, develop and demonstrate a set of algorithms that would provide rapid correlation of observed objects with cataloged objects. Techniques should demonstrate improvements in uncertainty and demonstrate scalability. Demonstrate a proof-of-concept.

PHASE III DUAL USE APPLICATIONS: The target program is the SMC JSpOC Mission Systems (JMS) program. Targeted technologies would be matured through the SMC and AFRL led JMS Testbed effort.

REFERENCES:

1. Theresa Hitchens, "Ante Up on Space Situational Awareness," Space News, Mar. 12, 2007. For the official definition of SSA, see Air Force Doctrine Document (AFDD) 2-2, Space Operations, Nov. 27, 2006, p. 55.

AF141-250 TITLE: 64MB+ Radiation-Hardened, Non-Volatile Memory for Space

OBJECTIVE: Develop and commercialize 64MB (min, MB=1,000,000 bytes of memory, 1 byte=8 bits), radhard, nonvolatile memory (RHNVM) for space applications.

DESCRIPTION: The lack of low-cost high-density Radiation-Hardened (RH) Non-Volatile Memory (NVM) continues to be a severely limiting factor in the design of systems for use in space environments. Present solutions rely on inefficient hardening techniques, such as radiation hardening by design (RHBD), which are implemented either in layout or in the application architecture and not in the fabrication process. Many of these solutions are based on redundancy and result in a performance penalty. Moreover, most aerospace applications preclude the use of moving parts, such as the one in a hard disk. Thus, an ultra-high density storage solution is completely lacking. Efforts over the last two decades to develop a practical NVM solution for space have fallen short of the density and performance needs. A radiation-hard NVM that can achieve high density is needed.
Commercial NVMs have greatly increased in density while reducing cost in recent years, creating a gap of more than six orders of magnitude between commercial and RH devices. Universal Serial Bus (USB) drives or Secure Digital Input/Output (SDIO) memory cards have achieved the density of hard drives over just a couple of years. While these commercial devices are not suitable for space applications, some technologies used by these commercial devices are inherently RH and could be used to build a device suitable for space applications. The suitable technologies then need to be developed into high density, space-qualified NVM devices. This call solicits efforts to develop and commercialize high-density high-performance RH NVM technology to serve space markets.
Radhard reqs for RHNVM:

Effect: Units: Level:

Total Ionizing Dose rad(Si) 1e6

Single-Event Upset Err/bit-day 1e-10

Single-Event Latchup None

Dose-Rate Upset rads(Si)/s 1e10

Dose-Rate Survivability rads(Si)/s 1e12
Proposals should clearly indicate how the result of the effort would be shown to improve the GPS system's capabilities through a test and validation plan. Testing and validation of risk reduction components of the overall effort in Phase I is encouraged.
Offerors are encouraged to work with PNT system prime contractors to help ensure applicability of their efforts and begin work towards technology transition.
Offerors should clearly indicate in their proposals what government furnished property or information are required for effort success. Requests for other-DoD contractor intellectual property will be rejected.

PHASE I: Review existing NVM technology literature and evaluate and incorporate (if appropriate) findings to this effort. Based on these results and other available metrics such as device uniformity, endurance, reliability, commercial viability, and design flexibility; complete the design of a NVM using the most promising technology.

PHASE II: The selected company will partner with an appropriate foundry to produce working prototypes that are suitable for space applications, then test and evaluate the prototypes for reliability and radiation hardness. Phase II efforts should include ensuring compatibility with CID supporting overall payload &space vehicle reference designs as part of their commercialization effort. CID will be supplied to Phase I awardees invited to propose for Phase II.

PHASE III DUAL USE APPLICATIONS: The selected company will build and commercialize a RH NVM with a density of at least 64MB for space applications.

REFERENCES:

1. Chua, L. O. "Memristor - The Missing Circuit Element." IEEE Trans. Circuit Theory 1971: 18, 507-19.