Department of the navy (don) 17. 1 Small Business Innovation Research (sbir) Proposal Submission Instructions introduction
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PHASE III DUAL USE APPLICATIONS: Refine the developed photonic switch, perform any required testing and demonstrate the capability at a technology readiness level of 6 or higher. Produce a minimum of 20 numbers of switches for final testing and transition the technology onto appropriate platforms via PMA-272. Private Sector Commercial Potential: This technology would have application to the telecommunication industry and the medical profession. REFERENCES: 1. Tada, K. & Hinton, H.S. (Editors). “Photonic Switching II: Proceedings of the International Topical Meeting”, Kobe, Japan, April 12-14, 1990. Springer Series in Electronics and Photonics. 2. Midwinter, J. E. “Photonics in Switching, Background and Components, Volume 1” Academic Press, 02 December 2012 - KEYWORDS: Photonic; switch; laser; fiber-port; fiber-optic; fiber-coupling Questions may also be submitted through DoD SBIR/STTR SITIS website.
TECHNOLOGY AREA(S): Human Systems, Information Systems, Sensors ACQUISITION PROGRAM: PMA 266 Multi-Mission Tactical Unmanned Aircraft System (UAS) Program Office OBJECTIVE: Develop an innovative advanced human-machine interface (HMI) for a dynamic sensor suite control system that exploits all available platform data in real-time to reduce operator workload and provide timely actionable information. DESCRIPTION: The process of detection, tracking, and identifying targets in complex environments is very difficult. The ability to prosecute agile maritime or overland threats amid rapidly changing conditions requires sensor operators to optimally use the capabilities of their airborne sensor suites. This requires sensor operators to very quickly analyze and assess the situation based on real-time sensor data products, distill and convey the actionable information, and then modify the sensor tasking based on the evolving tactical picture. The resulting workload can easily overwhelm the sensor operator and dramatically reduce mission effectiveness. In order to reduce sensor operator overload and increase mission effectiveness, an innovative advanced HMI is needed that will intelligently guide the operator through the use of resource management and automated analysis tools to support the derivation of actionable information from existing naval airborne sensor systems (radar, EO/IR, ESM, etc.) in a fashion that minimizes operator touch time and dramatically improves mission effectiveness. The HMI should be an integrated processor that supports sensor information analysis and exploitation methodologies along with data visualization, threat behavior analysis, and hypothesis testing. In order to maximize mission success, these tools should also identify and recommend short-term (a few minutes) and long-term (tens of minutes) sensor resourcing options based on general mission collection priorities such as maritime transit escort, maritime area patrol or maritime find and follow as well as responding to evolving conditions. Candidate transition platforms include the MQ-8C, MQ-4C, P-8A and MH-60R aircraft. An innovative advanced HMI for an automated sensor exploitation management system can result in potential dramatic improvements in maritime situational awareness and mission planning as measured by mission level classification and tracking metrics. PHASE I: Determine the technical feasibility of creating an advanced HMI for a dynamic system of sensor exploitation tools for existing naval airborne platforms. Identify the specific nature of the analysis and exploitation algorithms and the HMI to be used, establish interfaces with the sensor resource management framework and decision logic, and develop a detailed implementation plan. PHASE II: Develop an advanced HMI prototype for a sensor exploitation management system for candidate sensor suites. Demonstrate non-real-time processing using government-provided data (will be provided at beginning of Phase II) with sufficient fidelity to enable a usability assessment (per ISO/IEC 25022:2016) of operator workload reduction, algorithm tuning, and sensor utilization. Demonstrate the functionality, performance, and correctness of all components. Prepare a Phase III integration plan to complete the development and transition of the toolset into candidate sensor suites. PHASE III DUAL USE APPLICATIONS: Finalize the HMI design and working with the Navy sponsor transition the toolset into Navy platform sensor control suites such as the Navy’s Minotaur application. Develop commercial version for maritime applications. Private Sector Commercial Potential: The HMI capability to interact with automated software control applications is applicable to an extremely broad set of commercial applications including the optimal utilization of large scale industrial manufacturing systems, optimal utilization of logistical operations and as an interface for tactical decision aids. REFERENCES: 1. ISO/IEC 25022:2016. Systems and software quality requirements and evaluation (SQuaRE) -- Measurement of quality in use. http://www.iso.org/iso/home/store/catalogue_ics/catalogue_detail_ics.htm?csnumber=35746 2. ISO/IEC 25010:2011. Systems and software Quality Requirements and Evaluation (SQuaRE) -- System and software quality models. http://www.iso.org/iso/home/store/catalogue_tc/catalogue_detail.htm?csnumber=35733- KEYWORDS: human-machine interface; automated resource management; maritime surveillance; sensors; autonomous control; visualization Questions may also be submitted through DoD SBIR/STTR SITIS website.
TECHNOLOGY AREA(S): Air Platform, Sensors, Weapons ACQUISITION PROGRAM: JSF – F35, Joint Strike Fighter OBJECTIVE: Develop a low cost, reliable advanced fiber optic ferrule material and fabrication technology able to self-align the core of the optical fiber with the center of a lens, each with different outer diameters. DESCRIPTION: Fiber optic ferrules are connector/terminus components used to terminate and mate two optical fibers within fiber optic connectors/termini. Bare fibers are inserted and epoxied into the ferrule bodies leaving a millimeter or less of optical waveguide protruding from the end-face boundary of the ferrule. Depending on the length of the protruded glass, the end-face is either cleaved and polished or just polished to provide a clear path for optical digital and analog data transmittance. Cleanliness of the optics within the ferrule end-face is a challenge due to contaminants and maintenance activities; it has been identified as the main cause of fiber optic system failure experienced by fleet/field maintenance personnel. The Joint Fiber Optic Working Group (JFOWG) is addressing this source of failure on different fronts. One solution is to use a lens connector/terminus to mitigate contamination in the beam path. Current vendor solutions propose using a smaller diameter ferrule to house the optical fiber with a sleeve fitted over this ferrule to house the lens. This approach is workable, however not preferred. Interoperability tolerances are looser between the two parts resulting in degraded performance. Field cable assembly fabrication and maintenance of the lens connector/terminus becomes more cumbersome at best. JFOWG has been hosting meetings for the “military lens termini specification development effort”. These meetings are a joint Government-industry (terminus vendor) effort to define non-proprietary requirements that will foster product interoperability. One critical component deficiency is lack of a single ferrule that contains a stepped (internal dual diameter) cavity. Requirements defined at these meetings for a ferrule with an internal stepped cavity (stepped ferrule) are:
Other features are to be proposed and approved as part of the review. Currently, the primary sources of supply for ferrules have the same diameter cavity in the center throughout the length of the ferrule. The intent is to develop a stepped ferrule with production cost that remains under $100. Application implementation consideration is being evaluated for analog Radio Frequency (RF) over fiber; Wave Division Multiplexing (WDM); Dense WDM (DWDM) in the L, C and S wavelength bands of operation; Low Cost VCSEL WDM; Fibre Channel Networks 2.125 Gbps and higher; and 128G-Coarse Wave Division Multiplexing (CWDM) -4 and Ethernet: 100G-SR, 400G-Sr, 1600G-SR16 networks. Current military standards investigating incorporating fiber optic lens terminus inter-connects are listed in the reference section. PHASE I: Design and demonstrate the feasibility for the development of a stepped ferrule prototype for single mode fiber optic cable test jumpers. Develop and finalize stepped ferrule requirements bounded by dimensional parameters, which will ensure worst case performance stack up is taken into consideration. PHASE II: Based on the Phase I effort, complete the design of and fabricate a minimum of 12 stepped ferrule prototypes. Demonstrate that the stepped ferrule prototypes can achieve the required measurement accuracy and repeatability when tested for insertion loss within the entire range of nominally specified fiber core/cladding sizes currently used in military applications (e.g., 9/125 um, 50/125 um, 62.5/125 um, etc.). In addition to insertion loss, perform operational testing and evaluation to evaluate optical, mechanical and environmental performance. PHASE III DUAL USE APPLICATIONS: Conduct performance testing on the developed Fiber Optic Ferrule that yields a product with a functioning baseline Technology Readiness Level (TRL) of 6 or greater. Further improvement and refinement, as required, will focus on increasing the product’s TRL and Manufacturing Readiness Level (MRL) for program, Fleet and commercial transitions. Private Sector Commercial Potential: Successful technology development would be utilized in commercial aerospace platforms, Information Technology applications and the telecommunications industry. REFERENCES: 1. MIL-STD-1760E. “AIRCRAFT/STORE ELECTRICAL INTERCONNECTION SYSTEM, HARDWARE OPEN SYSTEMS TECHNOLOGIES (HOST).” Technical Standard for Future Airborne Capability Environment. (FACE™), Edition 2.1. Available at http://everyspec.com/MIL-STD/MIL-STD-1700-17 2. MIL-STD-1678-1. “FIBER OPTIC CABLING SYSTEMS REQUIREMENTS AND MEASUREMENTS (Part 1: DESIGN, INSTALLATION AND MAINTENANCE REQUIREMENTS).” Available at https://www.document-center.com/standards/show/MIL-STD-1678/1 3. MIL-STD-1678-6. "FIBER OPTIC CABLINGSYSTEMS REQUIREMENTS AND MEASUREMENTS (Part 6: PARTS AND SUPPORT EQUIPMENT COMMONALITY AND STANDARDIZATION REQUIREMENTS)." Available at http://everyspec.com/MIL-STD/MIL-STD-1600-1699/MIL-STD-1678_6_42190- 4. Additional information from TPOC providing diagram of dimensional requirements, 1 page (uploaded in SITIS on 1/4/17). KEYWORDS: Expanded Beam; Stepped Ferrule; Fiber Optic Networking; Lens Termini; Optical Fiber Interconnects; interoperability Questions may also be submitted through DoD SBIR/STTR SITIS website.
TECHNOLOGY AREA(S): Air Platform ACQUISITION PROGRAM: PMA-299, H-60 Helicopter Program OBJECTIVE: Develop a modular system that can be configured to fatigue test a variety of main rotor hub and shaft assemblies with minimal fixture components unique to each assembly. DESCRIPTION: Safe-life criteria for the Navy’s dynamic components require fatigue testing of rotor components prior to flight certification [Ref 1] to establish life limits. Rotor components are grouped into assemblies and fatigue tested separately to replicate the actual dynamic and mechanical environment of the subject specimen. For example, the hub assembly is tested independently from the blade assembly and the yoke/cuff/adapter assembly. Current test rigs, along with the software for loads input, are mechanically complicated and developed for each individual platform, increasing costs associated with fatigue tests, with each easily costing in the order of millions to conduct. An innovative modular test rig and methodology capable of testing main rotor head and shaft assemblies as one unit for multiple platforms, such as H-1, H-60, V-22, MQ-8B, and MQ-8C, is needed. Fatigue testing is generally performed with design loads that are different between platforms, therefore for this modular test rig, the actuators should be robust enough to provide the proper input loads (i.e., Centrifugal loads [20,000 pound-force (lbf) min], bending [100,000 in-lbf min], torsion [400,000 in-lbf min]) for multiple platforms. This new modular test system would decrease costs associated with fatigue tests by minimizing the need for unique test fixture designs. PHASE I: Develop an innovative concept for a modular fatigue test rig that is capable of fatigue testing a variety of main rotor head and shaft assemblies with minimal unique test fixtures. Demonstrate the feasibility of fitting main rotor head and shaft assemblies of different platforms through modeling and simulation. PHASE II: Develop a sub-scale prototype of the modular fatigue test rig system that was conceived in Phase I including any software required to control and synchronize the actuators of the test rig. Demonstrate the prototype’s ability to apply proper loading amplitude individually and collectively, synchronize applied loading rates, and adjust the loading control for each of the Phase I rotor head configurations. PHASE III DUAL USE APPLICATIONS: Develop and validate a full-scale version of the modular fatigue test rig prototype developed in Phase II. Validate full-scale system against fatigue test data already available for multiple platforms. Transition the newly developed full-scale test system to fatigue test rotor head components in new and current navy rotorcraft platforms. Private Sector Commercial Potential: Commercial helicopters also require fatigue tests for part certification [Ref. 2, 3]. The test rig can be used in the private sector to perform fatigue tests on commercial helicopter rotor heads. This could allow cost savings and faster schedules to certify new commercial helicopter rotor head parts. REFERENCES: 1. Advisory Group for Aerospace Research and Development. (November, 1983). AGARD-AG-292, Helicopter Fatigue Design Guide. Retrieved from http://www.dtic.mil/dtic/tr/fulltext/u2/a138963.pdf 2. Federal Aviation Administration. (July 25, 2014). Advisory Circular 27-1B, Certification of Normal Category Rotorcraft. Retrieved from http://www.faa.gov/documentLibrary/media/Advisory_Circular/AC_27- 1B_thru_Chg_6.pdf 3. Federal Aviation Administration. (July 25, 2014). Advisory Circular 29-2C, Certification of Transport Category Rotorcraft. Retrieved from http://www.faa.gov/documentLibrary/media/Advisory_Circular/AC_29- 2C_thru_Chg_6_.pdf- KEYWORDS: Fatigue; Rotor Head; Fatigue Test; Rotorcraft; Modular Test System; Safe Life Questions may also be submitted through DoD SBIR/STTR SITIS website.
TECHNOLOGY AREA(S): Air Platform, Battlespace, Electronics ACQUISITION PROGRAM: PMA-234, Airborne Electronic Attack Systems 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 Announcement. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. OBJECTIVE: Create an Airborne Electronic Attack (AEA) antenna capable of operating simultaneously at very high frequency (VHF) and ultra-high frequency (UHF) while being electrically-small, efficient, and capable of high power handling. DESCRIPTION: Current constraints on antennas for AEA systems in VHF and UHF bands are the size and impedance. This translates to shorter mission durations, aerodynamic drag, greater power consumption, and unfocused radiated energy. The antenna will accept and radiate more of the power from its source to its intended target versus reflecting it back to the source and damaging it. More power on target means less power consumed thermally, longer mission duration, greater operating range, higher reliability, and lower constraint for thermal management components. Electrically small antennas offer opportunities for operation at lower frequencies. Technologies and techniques are sought to develop physically small antennas with dimensions of 26 inches in the minor diameter to 5.5 feet in the major length. The antenna prototype must achieve a voltage standing wave ratio (VSWR) of 3:1 at the low end of the band and 2:1 at the high end of the band. A sustained power handling capability of greater than 1000 Watts is desired while residing within a wavelength of the aircraft platform and still retaining good elevation field of regard (FOR) for vertical, horizontal and circular polarizations. Work produced in Phase II may become classified. Note: The prospective contractor(s) must be U.S. owned and operated with no foreign influence as defined by DoD 5220.22-M, National Industrial Security Program Operating Manual, unless acceptable mitigating procedures can and have been implemented and approved by the Defense Security Service (DSS). The selected contractor and/or subcontractor must be able to acquire and maintain a secret NAVY – 45 level facility and Personnel Security Clearances, in order to perform on advanced phases of this project as set forth by DSS and NAVAIR in order to gain access to classified information pertaining to the national defense of the United States and its allies; this will be an inherent requirement. The selected company will be required to safeguard classified material IAW DoD 5220.22-M during the advanced phases of this contract. PHASE I: Determine the feasibility for the development of a prototype Compact, Broadband, Efficient and High Power Transmit Antenna for Airborne Electronic Attack Platforms that can achieve the capabilities in the description. Provide assessment of concept performance through modeling in free space and in a representative environment. PHASE II: Develop, produce and demonstrate a prototype Compact, Broadband, Efficient and High Power Transmit Antenna for Airborne Electronic Attack Platforms based on Phase I work. Measure the prototype’s antenna pattern and VSWR performance within the proximity of a large ground plane of representative size in a representative environment. PHASE III DUAL USE APPLICATIONS: Optimize Compact, Broadband, Efficient and High Power Transmit Antenna for Airborne Electronic Attack Platforms prototype and demonstrate the antenna performance with high power on AEA aircraft. Provide support to the Navy for testing and validation to certify and qualify the system for Navy use. Transition finalized technology to appropriate platforms. Private Sector Commercial Potential: A broadband electrically small antenna can take on the capabilities of multiple narrow band antennas and provide weight savings. It is physically smaller than a nominal antenna of the same frequency, so lower operating frequency is feasible for applications with size constraints. It also has less surface area for drag. Law enforcement or commercial avionics would benefit from a successful outcome of this technology development. REFERENCES: 1. Zhang, Y. j., Chen, A. x., Su, D. l. & Jiang, T. h., (2008). Optimal design of a broadband matching network for an electrically small antenna. Antennas, Propagation and EM Theory, 2008. ISAPE 2008. 8th International Symposium on Antennas, Propagation a 2. Turner, E., (1972). A regenerative broadband electrically small folded dipole antenna, Antennas and Propagation Society International Symposium, 1972, Williamsburg, VA, USA, pp. 348-351. http://ieeexplore.ieee.org/xpl/articleDetails.jsp?reload=true&arnumber=1146967. 3. Bennett, W. S., (1988). Antenna to ground-plane mutual coupling measurements on open-field test sites, Electromagnetic Compatibility, 1988. Symposium Record., IEEE 1988 International Symposium on, Seattle, WA, pp. 277-283. http://ieeexplore.ieee.org/xpl/login.jsp?tp=&arnumber=14129&url=http%3A%2F%2Fieeexplore.ieee.org%2Fxpls%2Fabs_all.jsp%3Farnumber%3D14129. 4. Zhang, W. & Hall, P. S., (2007). Mutual coupling investigation of two wideband dipole antennas on EBG ground plane, 2007 International workshop on Antenna Technology: Small and Smart Antennas Metamaterials and Applications, Cambridge, pp. 35-38. https://www.researchgate.net/publication/4252195_Mutual_coupling_investigation_of_two_wideband_dipole_antennas_on_EBG_ground_plane. 5. Chen, Z. N., Yang, F. & See, T. S. P., (2010). Mutual coupling between multi-band antennas on small ground plane Proceedings of the Fourth European Conference on Antennas and Propagation, Barcelona, Spain, pp. 1-4. http://ieeexplore.ieee.org/xpl/login.jsp?tp=&arnumber=5505736&url=http%3A%2F%2Fieeexplore.ieee.org%2Fiel5%2F5497865%2F5504894%2F05505736.pdf%3Farnumber%3D5505736.- KEYWORDS: Electrically Small Antenna; Broadband; High Power; Mismatch Loss; Low Frequency; Large Ground Plane Coupling Questions may also be submitted through DoD SBIR/STTR SITIS website.
TECHNOLOGY AREA(S): Biomedical, Human Systems ACQUISITION PROGRAM: PMA-202 Aircrew Systems OBJECTIVE: Develop a low cost solution to provide aircrew with the capability of bladder relief during flight. DESCRIPTION: Current mission profiles and the ability for mid-air refueling have led to longer flight times for military aircrew. Flight planning, for many military aircrew, starts the day before by watching what they eat and drink to alleviate the need and difficulty to urinate, and the inability to defecate during flight. Many aircrew personnel resort to “tactical” dehydration in order to avoid the difficulties of having to relieve themselves in flight. Dehydration can result in reduced physical and cognitive performance and situational awareness, including intense headaches and affected vision which can be particularly dangerous when landing on an aircraft carrier at night. The lack of bladder relief can also lead to distraction when the bladder is full. Military aircrew, especially those in aircraft where they remain restrained in a seat throughout the flight, require the capability to urinate multiple times during flight without removal of restraint systems and life support equipment. Attempting to use external systems in the cockpit to collect urine can require releasing the restraint system and then maneuvering to use the device which can lead to urine leaking onto seats and equipment, thus creating a health hazard requiring use of manpower for cleaning the aircraft and resulting in possible corrosion of aircraft components that come into contact with the urine. Holding urine can create the growth of bacteria in the bladder leading to urinary tract infections and other medical issues. The Navy and Joint Strike Fighter program is in need of a system that is easy to use without interfering with in-flight operations and will allow aircrew to remain hydrated and urinate in stride with minimum disruption throughout the flight. Directory: osbp -> sbir -> solicitations -> sbir20171 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 sbir20171 -> Army 17. 1 Small Business Innovation Research (sbir) Proposal Submission Instructions solicitations -> Navy 11. 3 Small Business Innovation Research (sbir) Proposal Submission Instructions sbir20171 -> Air force 17. 1 Small Business Innovation Research (sbir) Phase I proposal Submission Instructions sbir20171 -> Department of the navy (don) 17. 1 Small Business Innovation Research (sbir) Proposal Submission Instructions introduction Download 1.17 Mb. Share with your friends:
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