Air force 12. 1 Small Business Innovation Research (sbir) Proposal Submission Instructions
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2. Kuchta, D. M., P. Pepeljugoski, and Y. Kwark, "VCSEL Modulation at 20 Gb/s over 200 m of Multimode Fiber using a 3.3 v SiGe Laser Driver IC," Tech. Dig. LEOS Summer Topical Meeting, pp. 49–50, 2001. 3. Suzuki, N., H. Hatakeyama, K. Fukatsu, T. Anan, K. Yashiki, and M. Tsuji, "25-Gbps operation of 1.1-mm-range InGaAs VCSELs for High-speed Optical Interconnections," Proc. Optical Fiber Communications Conf. Paper, 2006. KEYWORDS: satellite fiber-optic components, Vertical Cavity Surface Emitting Laser (VCSEL), optical signal distribution AF121-060 TITLE: High Conductance Thermal Interface Material for Use in Space Applications TECHNOLOGY AREAS: Materials/Processes, Space Platforms Technology related to this topic is restricted under the International Traffic in Arms Regulation (ITAR) (DFARS 252.204-7009). As such, export-controlled data restrictions apply. Offerors must disclose any proposed use of foreign citizens, including country of origin, type of visa/work permit held, and the Statement of Work (SOW) tasks to be performed. In addition, this acquisition involves technology with military or space application. Therefore, only U.S. contractors registered and certified with the Defense Logistics Services Center (DLSC), Federal Center, Battle Creek MI 49017-3084, (800) 352-3572, are eligible for award. If selected, the firm must submit a copy of an approved DD Form 2345, Militarily Critical Technical Data Agreement. OBJECTIVE: Develop a space-qualifiable, high-conductance, passive, Thermal Interface Material (TIM) for use in space-based flanged heat-pipe-to-heat-pipe joints or for mounting relatively small area units with stiff baseplates and high power loads. DESCRIPTION: To meet emerging demands for high-capacity satellite communications, digital and radio frequency (RF) waveform processing requirements are anticipated to grow for the foreseeable future; implementationof these requirements will lead to generation of increasing amounts of waste heat. To minimize the thermal impact of waste heat on digital and RF component performance as well as improve component reliability, this effort is focused on providing a high-conductance thermal interface material (TIM) to be used for space-based flanged heat-pipe-to-heat-pipe joints or for cooling high dissipating, small area unit baseplates, such as Traveling Wave Tube Amplifiers (TWTAs). Goals of this research include a heat transfer coefficient >45,000 W/m2-K over an area of 2.5 inches x 3.0 inches, when conventionally fastened to the baseplate. To facilitate ground testing, the thermal conductance should not be impacted by environment (e.g. vacuum, humidity) or orientation. The TIM should be capable of operating over a temperature range of -40C to 125C along with 30,000 thermal cycles with a temperature difference of 15 C per cycle. In addition to the high conductance required, the TIM should be easily separable, debris-free, and require no significant cure time or elevated temperature. The TIM should be workmanship independent by utilizing materials, processes and controls that minimize the thermal vacuum testing required for recurring designs. PHASE I: Develop concepts to provide a robust, reliable TIM that has the potential to provide a heat transfer coefficient >45,000 W/m2-K. Demonstrate by analysis and/or test the feasibility of such concepts to meet all requirements stated above, including surviving the temperature range and thermal cycles, debris-free. PHASE II: Optimize and fully demonstrate a TIM capable of providing an effective heat transfer coefficient of >45,000 W/m2-K. Perform thermal performance testing and thermal cycling to confirm all above requirements have been met. PHASE III DUAL USE COMMERCIALIZATION: Military Application: This research would benefit all military satellite programs, including Wideband Global Satellite Communications (SATCOM) and global positioning satellite programs. TIMs are required for all high power electronic components used on military systems. Commercial Application: This research benefits virtually all commercial satellite programs requiring thermal management. Additionally, high conductivity TIMs have applications for computer processor heat sinks, commercial electronics, and personal/portable electronics.
1. Liu, J., T. Wang, B. Carlberg, and M. Inoue, "Recent Progress of Thermal Interface Materials," ESTC (2008), 2nd, pp. 351-358, 1-4 Sept. 2008. 2. Zhang, Yan, Cong Yue, Johan Liu, Zhaonian Cheng and Jing-yu Fan, "Study of the Filler Effect on the Effective Thermal Conductivity of Thermal Conductive Adhesive", ICEP, 638-642, 2009. 3. Carlberg, R., T. Wang, Y. Fu, J. Liu, and D. Shangguan, "Nanostructured Polymer-Metal Composite for Thermal Interface Material Applications", 978-1-4244-223, Electronic Components and Technology Conference, 2008. 4. Gilmore, D. G., “Spacecraft Thermal Control Handbook Volume I: Fundamental Technologies,” 2nd Ed, The Aerospace Press, El Segundo, CA, 2002. KEYWORDS: thermal management, thermal interface material, TIM, heat pipe joints, TWTA mounting AF121-061 TITLE: Spacecraft Autonomy TECHNOLOGY AREAS: Space Platforms Technology related to this topic is restricted under the International Traffic in Arms Regulation (ITAR) (DFARS 252.204-7009). As such, export-controlled data restrictions apply. Offerors must disclose any proposed use of foreign citizens, including country of origin, type of visa/work permit held, and the Statement of Work (SOW) tasks to be performed. In addition, this acquisition involves technology with military or space application. Therefore, only U.S. contractors registered and certified with the Defense Logistics Services Center (DLSC), Federal Center, Battle Creek MI 49017-3084, (800) 352-3572, are eligible for award. If selected, the firm must submit a copy of an approved DD Form 2345, Militarily Critical Technical Data Agreement. OBJECTIVE: Develop software solutions supporting autonomous spacecraft operation. DESCRIPTION: The command and control link between a satellite and the ground station can occasionally experience periods of outage from events ranging from high intensity space weather to periods in which the satellite is repositioned to a new orbital slot to accommodate changing mission requirements. The capability to autonomously implement an operational plan, which is a set of commands scheduled for execution at predetermined moments in time, ensures critical spacecraft operations can be carried out in the event the ground station-to-spacecraft communications link is lost. Recent research, principally by NASA, has shown artificial intelligence research has matured to become a viable means of maintaining short-term autonomous spacecraft control. The purpose of this topic is to support research towards increasing spacecraft autonomy while maintaining a high level of confidence in the spacecraft’s operational availability and, at the same time, minimizing the consumption of spacecraft resources. Research should seek compatibility with the existing command and control infrastructure such as the Air Force Satellite Ground Link System (SGLS) and the Air Force Consolidated Space Operations Center (CSOC). SGLS interfaces are available through the Internet. The introduction of autonomous operations into the spacecraft poses a significant risk and, therefore, research should strive to develop a progressive autonomy approach that can be gradually introduced to provide mission management with confidence in the technology and to evaluate benefits before fully committing to autonomous control. PHASE I: Develop a fully-supported autonomous spacecraft concept and conduct feasibility for such a satellite system, including most major systems' self-supporting operation for a suitable Ops life. A limited scope, proof-of-concept of some aspect of that autonomous system is desired. PHASE II: Address two threats, proposed solutions, tradeoffs, and scalability. For at least one of those threats, develop an autonomous-spacecraft prototype. Characterize for reliability. Demonstrate in a relevant environment. PHASE III DUAL USE COMMERCIALIZATION: Military Application: All military satellite programs, including Wideband Global Satellite Communications (SATCOM), Global Positioning System (GPS) and Mobile User Objective System (MUOS) could benefit from this research. Commercial Application: All commercial satellite programs could likewise benefit.
1.Chien, S., B. Smith, G. Rabideau, N. Muscetolla, and K. Rajan, “Automated Planning and Scheduling for Goal-Based Autonomous Spacecraft,” IEEE Intelligent Systems, Vol. 13, No. 5, pp. 50-55, 1998. 2. Bernard, D., et. al., “Spacecraft Autonomy Flight Experience: The DS1 Remote Agent Experiment,” Proc. AIAA 1999, Albuquerque NM, 1999. 3. Cardoso, L.S., et al, “An Intelligent System for Generation of Automatic Flight Operation Plans for the Satellite Control Activities at INPE”, Proc. 9th Int. Conf. on Space Operations, Rome, Italy, June 2006. 4. Truzkowski, W., “Progressive Autonomy: A Method for Gradually Introducing Autonomy into Space Missions,” Proc. 27th Annual NASA Goddard/IEEE Software Engineering Workshop (SEW-27’02), 2002. KEYWORDS: spacecraft, autonomy, intelligent agent, command and control, progressive autonomy, artificial intelligence AF121-062 TITLE: Light Weight Shielding for Satellite Protection from Severe Space Weather TECHNOLOGY AREAS: Space Platforms Technology related to this topic is restricted under the International Traffic in Arms Regulation (ITAR) (DFARS 252.204-7009). As such, export-controlled data restrictions apply. Offerors must disclose any proposed use of foreign citizens, including country of origin, type of visa/work permit held, and the Statement of Work (SOW) tasks to be performed. In addition, this acquisition involves technology with military or space application. Therefore, only U.S. contractors registered and certified with the Defense Logistics Services Center (DLSC), Federal Center, Battle Creek MI 49017-3084, (800) 352-3572, are eligible for award. If selected, the firm must submit a copy of an approved DD Form 2345, Militarily Critical Technical Data Agreement. OBJECTIVE: Develop cost-effective, lightweight shielding materials to protect satellites from severe space weather effects. DESCRIPTION: Both military and commercial satellites are at risk from large solar radiation events. High-energy-charged particles produced by the sun can cause geomagnetic storms in the earth’s upper atmosphere, creating current surges within the satellite spacecraft that overstress microelectronics and lead to premature failure of the satellite as a result of latch-up and single event effects. In addition, high-performance commercial microelectronics will play an increasingly critical role in future generations of communications satellite if they are to meet user demands for greater performance. Advanced microelectronics provide substantial performance benefits relative to microelectronics from radiation-hardened foundries if ways can be found to address space environmental hazards through system design measures such as shielding. In addition, shielding can serve multiple applications, such as structural support, thermal management, electromagnetic interference isolation, and radiation protection over 4-pi-steradian coverage. The purpose of this topic is to develop innovative ways of shielding spacecraft from severe space weather that permit the use of advanced commercial microelectronics through the utilization of a systems-engineering design approach meeting multiple objectives, thereby minimizing overall weight by comprehensively addressing structural, electrical, radiation, and thermal issues. PHASE I: Review current spacecraft shielding practices. Explore space weather radiation & other radiation sources as discussed in references. Explore shielding materials to materially reduce weight for a standard level of shielding & develop spacecraft-shielding design. Consider design approaches to be integrated into the structure for symbiotic performance PHASE II: Fabricate and demonstrate shielding designs and/or materials. PHASE III DUAL USE COMMERCIALIZATION: Military Application: Military satellites--communications satellites, in particular--would like to leverage commercial microelectronics performance while minimizing weight associated with shielding their use. Commercial Application: A large variety of commercial sateliites could derive lifetime and mission-assurance benefits from this technology.
1. Fan, Wesley C., Clifton R. Drumm, Stanley B. Roeske, and Gary J. Scrivner, “Shielding Considerations for Satellite Microelectronics,” IEEE Trans on Nuclear Science, Vol. 43, No. 6, 1996. 2. Mukati, A., "A survey of memory error correcting techniques for improved reliability," Journal of Network and Computer Applications, Vol. 34, pp. 517-522, 2011. 3. Shin, M., and M. Kim, "An evaluation of radiation damage to solid state components flown in Low Earth Orbit satellites," Radiation Protection Dosimetry, Vol. 108, Issue 4, pp. 279-291, 2004. KEYWORDS: shielding, microelectronics, bremsstrahlung, high Z materials, electron scattering, cosmic rays, spacecraft AF121-063 TITLE: Joint Processing of Multi-band Signals with Information Assurance TECHNOLOGY AREAS: Information Systems, Space Platforms Technology related to this topic is restricted under the International Traffic in Arms Regulation (ITAR) (DFARS 252.204-7009). As such, export-controlled data restrictions apply. Offerors must disclose any proposed use of foreign citizens, including country of origin, type of visa/work permit held, and the Statement of Work (SOW) tasks to be performed. In addition, this acquisition involves technology with military or space application. Therefore, only U.S. contractors registered and certified with the Defense Logistics Services Center (DLSC), Federal Center, Battle Creek MI 49017-3084, (800) 352-3572, are eligible for award. If selected, the firm must submit a copy of an approved DD Form 2345, Militarily Critical Technical Data Agreement. OBJECTIVE: Develop and demonstrate advanced signal processing algorithms to enhance military Global Positioning System (GPS) receiver performance with information assurance. DESCRIPTION: Multiple radio navigation signals are, or soon will be, available from each Global Positioning System (GPS) satellite (L1, L2, and L5) and from other Global Navigation Satellite System (GNSS) constellations. Current GNSS receiver design utilizes traditional separate code and carrier tracking loops, one for each signal, which are designed and operated separately. There are benefits to tracking all signals from each satellite using a joint tracking loop to mitigate frequency-dependent disturbance and interference, such as ionospheric and multipath effects. A joint-tracking filter is more realistic to implement than a vector-tracking filter, which involves multiple satellites and lengthy times to get the tracking loop closed. The same idea can be extended to working with multiple constellations. However, offsets in clock and reference standards must be taken into account to ensure interoperability. However, civilian signals are more easily spoofed than military P(Y) and/or M-code. It would be even easier for an adversary to spoof signals from other, non-US controlled constellations. There is a clear need to address Information Assurance for position, navigation and time (PNT) solutions. It is relatively easy for a single frequency signal to be spoofed. However, it would be more difficult to spoof two or more frequency signals in exactly the same way at the same time. As a result, joint processing of multi-frequency signals provides a means for integrity check prior to combining them to formulate a solution. In the same vein, cross-validation of solutions from different constellations may also serve as a means against spoofing. Such a joint processing will make it costly, if not impossible, to deploy a spoofing scheme attempt against all GNSS constellations. In addition, other means and techniques may be used for GNSS signals for information assurance. One example is signal characteristic-based intruder detection used in wireless communications networks. PHASE I: Determine the feasibility of developing advanced multiband signal processing algorithms that improve navigation accuracy in the presence of ionospheric and multipath effects and also develop an approach to validate signal integrity. PHASE II: Develop a prototype of multiple frequency GNSS receiver and demonstrate the candidate algorithms on the prototype in realistic environments and signal conditions. PHASE III DUAL USE COMMERCIALIZATION: Military Application: Develop the hardware and software modules for transitioning the technology to current and future military receivers. Commercial Application: Technology developed under this effort will have potential applications to commercial GNSS receivers in surveying markets and urban environments and also in aviation applications, particularly as concerns about spoofing civilian signals arise.
1. Hurskainen, Heikki, Tommi Paakki, Zhongqi Liu, Jussi Raasakka, and Jari Nurmi, "GNSS Receiver Reference Design," Department of Computer Systems,Tampere University of Technology, August 2008. 2: Hurskainen, Heikki, Tapani Ahonen, and Jari Nurmi, “Interface Specification - Navstar GPS Space segment/User segment L1C Interfaces,” IS-GPS-800, 04 August 2007. 3. Proakis, John, and Masoud Salehi, "Communication Systems Engineering," Second Edition 2002, Prentice Hall, ISBN 0-13-061793-8. 4: Joint Chiefs of Staff (authors) - “Information Assurance Legal, Regulatory, Policy and Organizational Considerations” – 4th Edition, August 1999. 5. Weijian, Wan and D. Fraser, “Multisource data fusion with multiple self-organizing maps,” Geoscience and Remote Sensing, IEEE Transactions, Volume 37, Issue 3, May 1999. KEYWORDS: GPS information assurance, joint processing data fusion, multi-band signal methodology AF121-064 TITLE: A Small Satellite-based System for Active and Passive Sounding of the Ionosphere, Direct Current (DC) through High Frequency (HF) TECHNOLOGY AREAS: Space Platforms Technology related to this topic is restricted under the International Traffic in Arms Regulation (ITAR) (DFARS 252.204-7009). As such, export-controlled data restrictions apply. Offerors must disclose any proposed use of foreign citizens, including country of origin, type of visa/work permit held, and the Statement of Work (SOW) tasks to be performed. In addition, this acquisition involves technology with military or space application. Therefore, only U.S. contractors registered and certified with the Defense Logistics Services Center (DLSC), Federal Center, Battle Creek MI 49017-3084, (800) 352-3572, are eligible for award. If selected, the firm must submit a copy of an approved DD Form 2345, Militarily Critical Technical Data Agreement. OBJECTIVE: Develop a novel satellite sensor for double probe electric field sensing and radio Topside Ionospheric Sounding (TIS). DESCRIPTION: The radio sounding of the ionosphere from space (TIS) has been established as a powerful technique for specifying the Electron Density Profile, EDP, of the topside ionosphere. In spite of EDP being a top Air Force Space Command (AFSPC) priority in Space Situational Awareness Environmental Monitoring, SSA-EM, this technique has yet to be advanced to an acquirable technology because of a number of shortcomings in technology readiness level (TRL), such as Electromagnetic Interference (EMI), practical size weight and power (SWAP), antenna technology, and, most importantly, onboard data processing. Early demonstration with the Alouette 1 & 2, and ISIS 1 & 2 missions (1970s), while scientifically successful, resulted in raw data files that took years to analyze and process. The more recent IMAGE mission improved significantly on data conditioning, weight, power, and EMI, but was still limited by a spinning wire boom deployment system that cannot provide continual nadir sounding as needed for operational EM, nor be expected to survive in the Low Earth Orbit (LEO) micro debris environment. TIS uses a radio transmitter to emit a swept or stepped range of frequencies and a receiver to analyze the reflection from points where the plasma frequency equals the radio frequency, thus giving the density at a range determined from delay. Two orthogonal dipoles are needed to transmit and detect the desired polarization, and a third axis can provide angle of arrival information that can be useful in sensing a turbulent and structured ionosphere. The optimal dipole lengths are about 15 meters tip-to-tip (tuned for 10 MHz). Another important ionospheric parameter is the electric field, which specifies the dynamic state of the ionosphere and is vital to early detection of RF signal scintillation, another key AFSPC SSA-EM objective. The Double Probe (DP) technique for measuring the electric field is relevant to this topic as it uses booms similar or identical to the TIS. This topic calls for any or all components of a system that would ideally combine both the TIS and DP techniques in an instrument suitable for flight on small dedicated satellites or operational missions, in combination with other EM sensors, although a combined instrument is not required. The envisioned platforms would accommodate slow rotation for sensor calibration, sun pointing, communications, and navigation requirements, but spin deployed booms are not expected to meet requirements. Boom development is not the focus of this effort, although boom specifications are anticipated. The desired sensor will meet or beat as many of the following objectives as possible: TIS and DP sounding period between 0.5 and 5 sec. Size as small as a 3U cubesat 10x10x30cm, or multiples of that format. Power and weight < 10 W avg and 10 kg (excluding booms). Electric field range = ±500 mV/m with a sensitivity and precision of 0.1 mV/m. EDP at 5% from 104cm-3 to 107cm-3. It is also expected that all parts will be capable of surviving the thermal, vacuum and radiation environment of low Earth orbit, or have functionally direct replacements that will meet survival requirements without redesign. PHASE I: The Phase I effort will perform requirements analysis to determine the optimal sensing strategy consistent with current technology. A system block diagram should be developed, critical engineering challenges identified, and limited breadboard testing accomplished to demonstrate system feasibility. PHASE II: The Phase II effort should build and deliver a complete breadboard system with simulated booms suitable for bench-top evaluation, and a design suitable for subsequent fabrication for spaceflight. PHASE III DUAL USE COMMERCIALIZATION: Military Application: Air Force Space Situational Awareness. This system will address Key Performance Parameters, EDP and ionospheric turbulence leading to disruption of communication and navigation satellite signals. Commercial Application: Environment monitoring architectures being planned now suggest a minimum of 3 to 30 orbiting platforms. A successful design would enjoy commercial success in supplying AFSPC, NOAA, and NASA needs.
1. Bilitza, D., “Topside Models: Status and Future Improvements,” Adv. Space Res., 47(12), pp. 12(17) to 12(26), 1994. 2. Bilitza, D., X. Huang, B. W. Reinisch, R. F. Benson, H. K. Hills, and W. B. Schar, “Topside ionogram scaler with true height algorithm (TOPIST): Automated processing of ISIS topside ionograms,” Radio Sci., 39(1), RS1S27, doi:10.1029/2002RS002840, 2004. 3. Benson, R. F., “Plasma physics using space-borne radio sounding,” CP974, Radio Sounding and Plasma Physics, edited by P. Song, et al., American Institute of Physics, Lowell, Massachusetts, pp. 20-33, 2008. 4. Chen, J., Z. Li, and C. S. Li, “A novel strategy for topside ionosphere sounder based on spaceborne MIMO radar with FDCD," Progress In Electromagnetics Research, Vol. 116, 381-393, 2011. Directory: osbp -> sbir -> solicitations -> sbir20121 solicitations -> Navy sbir fy09. 1 Proposal submission instructions solicitations -> Army 16. 3 Small Business Innovation Research (sbir) Proposal Submission Instructions solicitations -> Army 14. 1 Small Business Innovation Research (sbir) Proposal Submission Instructions solicitations -> Navy small business innovation research program submitting Proposals on Navy Topics solicitations -> Navy small business innovation research program solicitations -> Armament research, development and engineering center solicitations -> Army 17. 1 Small Business Innovation Research (sbir) Proposal Submission Instructions solicitations -> Navy 11. 3 Small Business Innovation Research (sbir) Proposal Submission Instructions solicitations -> Department of the navy (don) 16. 2 Small Business Innovation Research (sbir) Proposal Submission Instructions introduction sbir20121 -> Air force 12. 1 Small Business Innovation Research (sbir) Proposal Submission Instructions Download 1.28 Mb. Share with your friends:
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