Air Force sbir 04. 1 Proposal Submission Instructions
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| An integrated hot structure with an integral thermal protection system offers significant promise in meeting the restrictive weight and volume goals already envisioned by several DoD programs. However, developing such structures requires characterization of these systems in areas of thermal insulation, ablation, and structural integrity. Additional development issues that need investigation are component attachment, vehicle integration, manufacturing techniques, and cost. Proposing entities are encouraged to develop a working relationship with TPS system integrators and supporting government offices for future demonstration efforts. A strategy to incorporate selected technologies in current and future spacecraft is encouraged.
PHASE I: Develop conceptual designs or techniques that provide significant TPS improvements compared to current state-of-the-practice techniques. As part of Phase I, a program plan for risk mitigation strategies is required. A proof of concept subscale hardware demonstration is encouraged. PHASE II: Demonstrate the feasibility of technology identified in Phase I. Tasks shall include, but are not limited to, a detailed demonstration of key technical parameters that can be accomplished at a subscale level, although a full-scale demonstration is encouraged if feasible. A detailed performance analysis of the technology is also required. DUAL USE COMMERCIALIZATION: There are numerous and far-ranging possibilities of commercial applications for a heavy-duty yet ultra-lightweight, durable, and reliable TPS system in commercial launch vehicles such as the next generation shuttle and other NASA vehicles. Also an innovative integrated TPS technique, that integrates hot structure and thermal components into one unit, may have potential applications in the hot parts of automobile engines and autoclaves. REFERENCES: 1. Air Force Space Command Strategic Master Plan for FY2025 and Beyond, 9 February 2000. 2. Air Force Space Command Concept of Operations for the Phase I Space Operations Vehicle System, 6 February 1998. 3. Bootle, John, “High Thermal Conductivity Composite Structures,” TR-1000-0282 (ADA371758). 4. Lt Col Henry Baird; Maj Steven Acenbrak; Maj William Harding; LCDR Mark Hellstern; Maj Bruce Juselis; “Spacelift 2025, The Supporting Pillar for Space Superiority”, Aug 1996. 5. Gnoffo, Peter A.; Weilmuenster, K. James; Hamilton, H. Harris II; Olynick, David R.; Venkatapathy, Ethiraj; “Computational Aerothermodynamic Design issues for Hyperspace Vehicles”, Journal of Spacecraft and Rockets; Jan 1999. KEYWORDS: Thermal Control, Thermal Insulation, Shock Resistance, Vibration Resistance, G Tolerance, Lightweight, Low Density, Thermal Management AF04-032 TITLE: Programmable Satellite Transceiver (PST) for Dual Band Command and Control TECHNOLOGY AREAS: Electronics, Space Platforms OBJECTIVE: Design, build, and test a miniaturized programmable satellite transceiver (PST) for command and control (C2) that operates in both the Space Ground Link Subsystem (SGLS) and Unified S-Band (USB) frequency bands. DESCRIPTION: The Department of Defense, National Aeronautics and Space Administration, and National Oceanic and Atmospheric Administration jointly developed a transition plan for implementing an integrated architecture for satellite operations (SATOPS) with the goals of reducing SATOPS costs and increasing interoperability between military and civil space and ground systems. Currently, military space systems use the SGLS frequency band consisting of 1755 – 1850 MHz, whereas civil space systems use the USB frequency band between 2025 – 2110 MHz. Ongoing discussions between the DoD, National Telecommunications and Information Administration, and the Federal Communications Commission may allow for military space systems to use both the SGLS frequency spectrum as well as USB. While the AF Satellite Control Network (AFSCN) Remote Tracking Stations are being upgraded to operate in both SGLS and USB, many of the military satellites are prevented from hosting both SGLS and USB capabilities due to size, power, weight, interface, and cost concerns of the existing available transponders. As a result, the integrated SATOPS architecture will be difficult to attain unless both the military and civil space systems as well as the related ground systems used for command and control can use both frequency bands. The goal of this initiative is to develop a miniature Programmable Satellite Transceiver (PST) that will enable DoD satellite C2 interoperability with NASA and NOAA. Capable of operating in both SGLS and USB, the PST will have the ability to change frequency bands, waveforms, and protocols on-orbit. In addition to offering jam-resistant command and control of the satellite, its size, power consumption, and weight will be much less than today’s transponders. PHASE I: Develop a PST subscale demonstration unit for identifying technical limitations, evaluating technology options, and demonstrating potential capabilities. Based upon completed designs and experimental tests, define PST performance goals and provide a blueprint for developing a space-qualified demonstration unit. Work with Space and Missile Center to address integration issues to support future space validation activities. PHASE II: Further refine the Phase I PST design, and based on that final design, develop a space-qualified PST demonstration unit. Provide a preliminary plan for the PST flight demonstration and validation. DUAL USE COMMERCIALIZATION: Upon successful development and flight validation of the Programmable Satellite Transceiver (PST), it is anticipated that the PST will enter production and be used on military and civil satellites. Potential military users include the many DoD, AF and Navy space programs. Civil applications include NASA and NOAA earth observing, meteorological, and science missions. REFERENCES: 1. Singer, J., Defense Dept to Keep Radio Spectrum, Space News, July 29, 2002. 2. Takach, J.E.; Davidovich, S.M.; Weakley, C.K., "The Application of advanced communication technology to the Air Force Satellite Control Network", Military Communications Conference, 11 Oct 1992, pp. 888-892. 3. Comparetto, G.M., "Future space/ground link alternatives for the AFSCN", Military Communications Conference, 5 Nov 1995, pp. 809-813. KEYWORDS: Integrated Satellite Control, Satellite Command and Control (C2), Transceiver/Transponder, Air Force Satellite Control Network (AFSCN), Space Ground Link Subsystem (SGLS), Unified S-Band (USB) AF04-033 TITLE: Low-Cost Thermal Protection System (TPS) For Reentry Vehicles TECHNOLOGY AREAS: Materials/Processes, Space Platforms OBJECTIVE: Develop low-cost innovative reusable Thermal Protection System (TPS) for future reentry spacecraft. DESCRIPTION: Over the past few years, Air Force strategists have envisioned the Air Force migrating into an Air and Space Force. Consequently, the Air Force is developing an aircraft-like spacecraft that has a 25% to 35% payload mass fraction, and a 48 to 72 hour turn-around cycle (~ 120 launches/year) to provide quick turn-around to replenish/deploy new space assets. The vehicle must have a significantly lower TPS-mass contribution to the total dry vehicle mass to achieve greater than 25% payload mass fraction. Hence, an innovative low-cost TPS system, unlike any current system that attaches to the vehicle’s outside structure, is envisioned to be integrated/woven into the structure to achieve the volume and mass savings needed. In essence, a revolutionary change in both the TPS design approach, the use of innovative materials that can survive long durations in a hypersonic environment without significant ablation, and low maintenance are needed to yield a low-cost TPS system. All proposing entities are encouraged to develop a working relationship with TPS system integrators and supporting government offices for future demonstration efforts. A strategy to incorporate selected technologies in current and future spacecraft is encouraged. Additionally the envisioned low-cost TPS system has to be: · Ultra safe and reliable – the new system has to increase the durability of TPS surfaces and system and be resistant to space micrometeoroid impacts. · Significant capability increase – integrated TPS structure system must have higher temperature tolerance to support quick turn-around. · Little or no ablation of TPS system surfaces – due to its mass fraction requirement, the leading hot surfaces should not shed as a way to control heat flux into the spacecraft and its contents. · Significant decrease in operational cost – increase the time between overhauls, repairs, replacement of components, and required inspections. PHASE I: Develop conceptual designs or techniques that provide significant TPS improvements compared to current state-of-the-practice techniques. As part of Phase I, a program plan for risk mitigation strategies is required. A proof of concept subscale hardware demonstration is encouraged. PHASE II: Demonstrate the feasibility of technology identified in Phase I. Tasks shall include, but not be limited to, a detailed demonstration of low cost production and key technical parameters, which can be accomplished at a subscale level, although a full-scale demonstration is encouraged if feasible. A detailed performance analysis of the technology is also required. DUAL USE COMMERCIALIZATION: There are numerous and far-ranging possibilities of commercial applications for an ultra-lightweight, durable, and reliable TPS system in commercial launch vehicles and National Aeronautics and Space Administration in addition to military reusable space vehicles such as the Common Aero Vehicle, Small Maneuverable Vehicle, and Solar Orbit Vehicle. Also an integrated TPS technique, which integrates structural and thermal components into one unit, may have potential applications in the hot parts of an automobile engine such as pistons and rods and autoclaves. REFERENCES: 1. Lt Col Henry Baird; Maj Steven Acenbrak; Maj William Harding; LCDR Mark Hellstern; Maj Bruce Juselis; “Spacelift 2025, The Supporting Pillar for Space Superiority”, Aug 1996. 2. Gnoffo, Peter A.; Weilmuenster, K. James; Hamilton, H. Harris II; Olynick, David R.; Venkatapathy, Ethiraj; “Computational Aerothermodynamic Design issues for Hyperspace Vehicles”, Journal of Spacecraft and Rockets; Jan 1999. 3. Paolozzi, A.; Felli, F; Valente, T.; Caponero, M.A.; Tului, M.; “Preliminary Tests for an Intelligent Thermal Protection System for Space Vehicles”, The International Society for Optical Engineering; 2001. 4. Daryabeigi, Kamran; “Thermal Analysis and Design Optimization of Multilayer Insulation for Reentry Aerodynamic Heating”, Journal of Spacecraft and Rockets, July/August 2002. 5. Rasky, D.J.; Milos, F.S.; Squire, T.H.; “Thermal Protection System Material and Costs for Future Reusable Launch Vehciles”, Journal of Spacecraft and Rockets, March/April 2001. KEYWORDS: Thermal Control, Thermal Insulation, Lightweight, Shock Resistance, Vibration Resistance, and G Tolerance Thermal Management System AF04-034 TITLE: Advanced Thermal Protection System (TPS) for Future Multiple Entry Vehicles TECHNOLOGY AREAS: Materials/Processes, Space Platforms OBJECTIVE: Develop an innovative Thermal Protection System (TPS) for future reusable spacecraft with aircraft-like reliability and duty cycle. DESCRIPTION: In recent years, the need to develop flight vehicles and systems with the capability to operate for extended periods in a hypersonic environment has necessitated the development of a revolutionary TPS concept that is lightweight, robust, and maintainable. And are state-of-the-practice TPS systems are not robust, require too many hours to refurbish, heavy, fragile, moisture sensitive, and burdensome to maintain. As an example, TPS waterproofing is currently a time consuming, toxic, serial procedure, seriously affecting turn times. The TPS system currently planned for the X-37 requires all other work be stopped while waterproofing is accomplished. The waterproofing coating is toxic and must be done in a sealed facility to prevent toxic fumes from escaping. Bunny suits are required while personnel apply the coating and the X-37 must then be dried in the sealed facility for 28-32 hours before any other work can be accomplished. Another example is the amount of manpower required to inspect, replace, and waterproof the TPS on the shuttle. Over 18,000 maintenance man-hours (MMH) per sortie are required for TPS alone. This compares to the 20-50 MMH required to completely turn a modern fighter for its next sortie (shuttle 100,000 MMH/sortie total). Future military space vehicles have flight profiles that require a long duration hypersonic flight. Currently planned Reusable Launch Vehicle systems are designed to maximum instantaneous heating rate of 50 BTU/ft2-s with integrated heating of 850 Btu/ft2 with zero ablation because of TPS limitations. While these rates are not severe, the requirements for these vehicles demand the vehicle achieve several successful flights through this environment before refurbishment of the TPS due to a low system maintenance requirement (40 MMH per sortie). Even at relatively low heat rates and loads, this level of reusability and rapid refurbishment time cannot be accomplished with any contemporary TPS design. To remain within these relatively low heating limits, current TPS systems require flight at angles of attack (AOA) which are compromised toward heat survivability and not toward generating maximum cross-range. To maximize cross-range, the vehicle needs to be flown at its maximum hypersonic lift to drag (L/D) ratio. Current TPS systems would burn up if flown at max L/D, especially leading edges and nose tips. Reusability factors mandate that these vehicles cannot accommodate TPS erosion common in most typical TPS designs for expendable reentry vehicles. In addition, mass fractions of reusable launch vehicles are critical, and TPS can make up as much as 25% of total vehicle dry weight. To improve mass fraction, the TPS must not only provide minimal levels of ablation, but also be exceedingly lightweight. A revolutionary change in both the TPS design approach and the use of innovative materials that can survive long durations in a hypersonic environment without significant ablation is needed. Lightweight, low erosion, fine edge shapeable, low conductivity materials coupled with an integrated hot-structure design that eliminates the bond line and the substructure would result in a revolutionary technology allowing a program such as the Space Maneuver Vehicle (SMV) to attain its objectives. All proposing entities are encouraged to develop a working relationship with TPS system integrators and supporting government offices for future demonstration efforts. A strategy to incorporate selected technologies in current and future spacecraft is encouraged. PHASE I: Develop conceptual designs or techniques that provide significant TPS improvements compared to current state-of-the-practice techniques. As part of Phase I, a program plan for risk mitigation strategies is required. Goals could be TPS materials and systems that could be waterproof, low maintenance, machineable to fine edges, mechanically attached, eliminate support structure, or tolerate extremely high temperatures repeatedly. A proof of concept subscale hardware demonstration is encouraged. PHASE II: Demonstrate the feasibility of technology identified in Phase I. Tasks shall include, but are not limited to, a detailed demonstration of key technical parameters that can be accomplished at a subscale level, although a full-scale demonstration is encouraged if feasible. Initial testing would include coupon samples followed by subscale structures and eventual flight test. A detailed performance analysis of the technology is also required. DUAL USE COMMERCIALIZATION: Commercial applications for an ultra-lightweight, durable, and reliable TPS system may have applications in the next National Aeronautics and Space Adinistration generation NASA shuttle. Also an integrated heavy duty TPS technique, which integrates hot structure and thermal components into one unit, may have potential applications in the autoclave business and hot parts of an automobile engine such as pistons and rods. REFERENCES: 1. Technical Requirements Document for a Space Maneuver Vehicle, Air Force Research Laboratory, Military Spaceplane, System Technology Program Office, Version: 1.8, 3 March 2000. 2. Bootle, John, “High Thermal Conductivity Composite Structures,” TR-1000-0282 (ADA371758). 3. Paolozzi, A.; Felli, F; Valente, T.; Caponero, M.A.; Tului, M.; “Preliminary Tests for an Intelligent Thermal Protection System for Space Vehicles”, The International Society for Optical Engineering; 2001. 4. Gnoffo, Peter A.; Weilmuenster, K. James; Hamilton, H. Harris II; Olynick, David R.; Venkatapathy, Ethiraj; “Computational Aerothermodynamic Design issues for Hyperspace Vehicles”, Journal of Spacecraft and Rockets; Jan 1999. 5. Rasky, D.J.; Milos, F.S.; Squire, T.H.; “Thermal Protection System Material and Costs for Future Reusable Launch Vehciles”, Journal of Spacecraft and Rockets, March/April 2001. KEYWORDS: Thermal Control, Insulation, Heat Sinks, Thermal Management AF04-035 TITLE: Energetic Polymeric Nanomaterials for Satellite Power Systems Design TECHNOLOGY AREAS: Materials/Processes, Sensors, Electronics, Battlespace OBJECTIVE: Develop biomimetic energetic polymer-based nanomaterials for photonic energy transduction to space-based satellite power needs. DESCRIPTION: Materials design at the nanomolecular level could have a significant beneficial impact on polymer-based photonic energy transduction devices for use in space-based satellite power systems. One particularly interesting area of materials design at the nanomolecular level is the development of biomimetic transduction polymers that transduce radiation and photonic energy into electronic energy, particularly when doped with heavy metal chiral centers. Effective models for synthetic modification of nitrosylated quasi-phenolic and orthoquinone-based for catechol/diol-based polymer architectures, such as those originally derived from thermophilic, aquatic or insect environments, hold promise in meeting photonic to electronic energy transduction goals for future space systems hardware. Incorporation of molecular rotor components within such polymeric architectures may significantly enhance their inherent potential for power generation and its efficiency. Regenerating nanomaterial assemblies of such electronic acceptor/donor biomimetic polymer systems could be incorporated within or laminated onto satellite surface materials to enhance power generation and optimization performance characteristics of entire satellite architecture scaffolds or even of specialized micorocircuity and on-board extendable or activatable robotic microdevices. Innovative ideas that have the potential to increase the conversion efficiency of photonic energy to current through design at the nanomolecular level are sought. PHASE I: Develop advanced polymer-based photonic energy transduction proof-of-concept devices. This activity could include developing modular organic and recombinant synthetic pathways for candidate biomimetic energetic nitrosylated polymer architectures, displaying rare earth and other metal chelation and electron acceptor or donor behavior. Using natural source and synthetic derived energetic polymer nanomaterials, demonstrate Radio Frequency and photonic to current transduction behavior, output, and efficiency. Develop a laboratory model for initial proof-of-concept. PHASE II: Refine and scale-up organic and/or recombinant synthesis of energetic polymers and assemble into nanomaterial arrays suitable for enveloping complex structures or developing outer energetic polymer sheaths for microelectronics and robotic devices. Optimize molecular design for maximum photonic to electronic transduction and high current electrical power output using more extensive molecular rotor constructs mounted on the polymer-based nanomolecular array. Demonstrate commercial and production feasibility of proposed polymer-based energetic nanomaterials systems. DUAL USE COMMERCIALIZATION: Advances in biomimetic polymer-based energetic nanomaterials have the potential to yield revolutionary advances in military aviation and robotic designs of the future, and to have a significant impact on the design and innovation of space technology. Of even greater commercial significance, the development of highly efficient energetic polymeric nanomaterials could offer a rich and fertile potential for exploitation in the photoconductive sensor, radiofrequency sensor and solar energy technology market, particularly in the efficiency/cost context. Development of versatile energetic materials will offer substantive promise for their incorporation in energetic bionanomaterials and implantable bionic devices. REFERENCES: 1. Kirshboim S: Ishay JS Silk produced by hornets: thermophotovoltaic properties-a review. Comp Biochem Physiol A Mol Integr Physiol 2000 Sep; 127(1):1-20. 2. Wagner-Brown KB; Ferris KF; Kiel JL; Albanese RA Morphology Dependent Optical Properties of DALM Related Materials. Mat Res Soc Symp Proc 1998 488;909-914. 3. Wagner-Brown KB; Ferris KF; Kiel JL; Albanese RA Optical Properties and Conformational Influences on the Electronic Structure of DALM. Bulletin of the APS, 1998 Texas Section Spring Meeting Section D Condensed Matter 19-21 March 1998. 4. Kinosita K Jr. Linear and rotary molecular motors. Adv Exp Med Biol. 1998;453:5-13. 5. Koumura N, Zijlstra RW, van Delden RA, Harada N, Feringa BL. Light-driven monodirectional molecular rotor. Nature. 1999 Sep 9;401(6749): 152-5. KEYWORDS: Energetic Materials, Nitrosylated Biomimetic Polymers, Nanomolecular Assemblies, Rare Earth Chelation, Solar Power, Satellite Design, Photovoltaics, Renewable Energy Sources AF04-036 TITLE: Scene Generation for Simulations of Satellite-Based MTI Radars TECHNOLOGY AREAS: Information Systems, Space Platforms OBJECTIVE: Develop an inexpensive capability to rapidly create simulated, global radar scenes to support space based air and ground moving target indication modeling, simulation, and analysis. DESCRIPTION: Current military and political affairs require a reliable and global capability to track air and ground moving targets. Using radar Doppler is an effective method of tracking moving targets of interest. Unfortunately, air-borne Moving Target Indication (MTI) assets are limited in coverage and access. Space based radar promises greater coverage and is not limited by airspace constraints. However, space based MTI is hindered by the vast amount of clutter data that must be processed in order to track the Doppler effect of the air and ground moving targets of interest. The current approach to clutter modeling relies heavily on statistically based background clutter on a geo-specific location. This approach to building radar clutter scenes has proven inefficient, costly and provides less than desired MTI results. There is a need for the capability to rapidly generate radar clutter scenes for any area of interest on the Earth’s surface such that reliable space based moving target indication can be performed. It is recommended to leverage the extensive geodetic data owned by the National Imagery and Mapping Agency (NIMA). Common commercially available software should be used when possible to support data management and exploitation. PHASE I: Develop an approach to rapidly generate global radar clutter scenes to support space-based air and ground moving target indication. Identify the necessary scene data required to support reliable space based air and ground MTI . Demonstrate this methodology by developing a preliminary prototype system that provides necessary radar background clutter over a limited area resulting in reliable space based air and ground MTI. PHASE II: Upon completion of Phase I, expand the area of interest and the associated geodetic database to support rapid, global radar clutter scene generation. Develop a flexible Graphical User Interface (GUI) that supports an interface to known space based MTI radar system(s) and the capability to support autonomous radar scene generation. Emphasis is placed on the ability to generate radar scenes quickly at minimal cost while limiting fidelity to the level necessary to support reliable air and ground MTI, not image quality. 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