Army 8. Small Business Innovation Research (sbir) Proposal Submission Instructions
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2. Pizhong Qiao,1 Mijia Yang,2 and Florin Bobaru, Impact Mechanics and High-Energy Absorbing Materials: Review, Journal of Aerospace Engineering, 21:4 (October 1, 2008), pp. 235-248; doi 10.1061. 3. Mertz, Harold, J, Irwin, Annette L., Prasad, Priya, Biomechanical and Scaling Bases for Frontal and Side Impact Injury Assessment Reference Values, Stapp Car Crash Journal, vol 43, (October 2003), pp. 155-188. 4. Qiao, Pizhong, Yan, Mijia, Bobaru, Florin, Impact Mechanics and High-Energy Absorbing Materials: Review, University of Nebraska-Lincoln, Digital Commons@University of Nebraska-Lincoln, (1October2008). 5. LaRue, Laura, Basily B., Elsayed, E.A., Cushioning Systems for Impact Energy Absorption, Department of Industrial and Systems Engineering, Rutgers University, elsayed@rci.rutgers.edu. KEYWORDS: Spall liner, thermal, HIC (Head Injury Criterion), Occupant Protection, Energy Absorption, material, Flame, smoke and toxicity resistant, Head injury, Occupant Centric, interior trim, acoustical, fragment
TECHNOLOGY AREA(S): Sensors OBJECTIVE: Develop affordable Electric Unmanned Ground Vehicle Force Protection Sensor System that provides a multi-modal sensors to improve Army Force Protection capabilities. DESCRIPTION: Army Force Protection requirements need to extend beyond perimeter sensor ranges. Previous Unmanned Ground Vehicle (UGV) Force Protection systems have been expensive and provided marginal unmanned sensor capabilities. Sophisticated yet inexpensive commercial sensors and driver-less automobile technology offer the opportunity to make significant advances in extending and lengthening base defense. Developing an affordable and effective Electric Unmanned Ground Vehicle Force Protection Sensor System that provides multi-modal sensors to improve Army Force Protection capabilities is achievable with today’s technology. Unmanned Ground Vehicle (UGV) shall be 100% electric driven, capable of operating (sensors on) for 2 hours (Threshold) or 6 hours (Objective) on smooth surfaces (roads and fields) with a range of 10 Km (Threshold) or 30Km (Objective), be able to maneuver safely around obstacles and people based on either a pre-programmed route or directed by the Force Protection Command and Control (C2) system. The UGV shall provide steerable flood light and audio (transmit and receive). The UGV shall not cost more than $25,000 (Threshold) or $15,000 (Objective) and no replaceable component may be more than $5,000. Network connectivity (i.e. radios) will be provided by the Army and not part of these requirements. Force Protection Sensor System shall consist of Electro Optics camera, Infrared (EO/IR) camera, Radar and/or LIDAR sensor(s), and Acoustic Sensors. Electro Optics camera shall provide High Definition (Threshold) or 4K Definition (Objective). Radar and/or LIDAR sensor(s) shall be capable of providing sensor data that can detection and track objects greater than 100 meters (Threshold) or 500 meters (Objective). Acoustic array sensors shall be capable of providing line of bearing within 5% (threshold) or 0.5% (Objective). All sensor data will be processed by the Force Protection C2 (i.e. minimal processing on-board). The Sensor suite shall not cost more than $25,000 (Threshold) or $15,000 (Objective) and with the exception of EO/IR sensors no replaceable component may be more than $5,000. PHASE I: Carry out a feasibility study for an affordable Electric Unmanned Ground Vehicle Force Protection Sensor System capability. This assessment will validate Electric UGV Force Protection Sensor System with a limited UGV and sensor demonstration. Phase I will define factors for a Phase II electric UGV Force Protection Sensor System prototype demonstration. PHASE II: Develop an affordable electric UGV Force Protection Sensor System prototype. Demonstrate electric UGV Force Protection Sensor System at an Army’s Research and Development location. PHASE III DUAL USE APPLICATIONS: Develop prototypes and transition proven technology to appropriate potential DoD customers/transition partners. End state vision is a demonstrated capability to acquire a high capability unmanned ground vehicle equipped with a force protection / intelligence sensor package that meets affordability and performance criteria identified in Phase 1. Army uses to include: extending the range of force protection and incident investigation around a Fixed Operating Base via UGV patrol; enabling remote intelligence collection via cheap UGV asset. Transition is targeted towards Product Director Force Protection Systems as proof of concept for new capability demonstrating extended range operations for possible future acquisition. Commercial applications could include facility security, civil law enforcement applications, homeland security and search & rescue applications. REFERENCES: 1. LOW-COST PLATFORM FOR AUTONOMOUS GROUND VEHICLE RESEARCH
2. The University of Pennsylvania MAGIC 2010 multi-robot unmanned vehicle system AUTHORS: J. Butzke, K. Daniilidis, A. Kushleyev, D.D. Lee, M. Likhachev, C. Phillips, M. Phillips, University of Pennsylvania DATE: 31 July 2012 JOURNAL: Journal of Field Robotics URL: http://onlinelibrary.wiley.com/doi/10.1002/rob.21437/full 3. Improving the Control Behavior of Unmanned Ground Vehicle (UGV) using Virtual Windows AUTHORS: Dr. Rosidah Sam, Ammar Hattab, Electrical Engineering Department, University Teknologi MARA DATE: 2014 JOURNAL: Research Paper URL: http://ammarhattab.com/resources%5Cpapers%5CUGV_researchPaper.pdf 4. Real-Time Obstacle Avoidance and Waypoint Navigation of an Unmanned Ground Vehicle AUTHORS: Hzkki Erhan Sevil, Pranav, Desai, Atilla Dogan, Brian Huff, University of Texas at Arlington, Arlington, TX DATE: 2012 JOURNAL: The American Society of Mechanical Engineers (ASME), ASME 2012 5th Annual Dynamic Systems and Control Conference joint with the JSME 2012 11th Motion and Vibration Conference URL: http://proceedings.asmedigitalcollection.asme.org/proceeding.aspx?articleid=1739118 5. Designing and control of autonomous Unmanned Ground Vehicle AUTHORS: SI Hassan, M Alam, NA Siddiqui DATE: 5 April 2017 JOURNAL: 2017 International Conference on Innovations in Electrical Engineering and Computational Technologies (ICIEECT) URL: http://ieeexplore.ieee.org/xpl/mostRecentIssue.jsp?punumber=7910138 6. Low-Cost Sensors for UGVs AUTHORS: Fenner Milton, Fene Klager, Thomas Bowan, CERDEC NVESD DATE: 10 July 2000 JOURNAL: Society of Photo-Optical Instrumentation Engineers SPIE URL: https://www.spiedigitallibrary.org/conference-proceedings-of-spie/4024/1/Low-cost-sensors-for-UGVs/10.1117/12.391628.short
TECHNOLOGY AREA(S): Electronics The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), which controls the export and import of defense-related material and services. Offerors must disclose any proposed use of foreign nationals, their country of origin, and what tasks each would accomplish in the statement of work in accordance with section 5.4.c.(8) of the Announcement. OBJECTIVE: New analog radio-frequency (RF) signal processing and enhanced electromagnetic (EM) interference mitigation capabilities afforded by devices based on high-quality magnetic materials are desired for existing and future military communications, signal intelligence (SIGINT), electronic warfare (EW), and radar systems. This topic seeks the development of an industrial domestic manufacturing capability for high quality Yttrium Iron Garnet Films (YIG) films to use in the production of Frequency Selective Limiters (FSLs) that are tunable to different frequency ranges. Of particular interest is the Seed substrate on which the epitaxial magnetic film is grown. DESCRIPTION: The number of systems relying on the use of the EM spectrum is increasing rapidly, in both military and commercial sectors. The rising spectral congestion is placing increasingly challenging requirements on the performance of components and modules that comprise the RF front-ends of communications, radar, and electronic warfare (EW) systems. Magnetic components, such as filters, phase shifters, delay lines, baluns, circulators, and isolators, among others, offer low insertion loss, high power handling capability, and low power consumption needed to improve the performance and reduce size, weight, power, and cost (SWaP-C) of these systems. In recent years, the use of single-crystal quality magnetic materials has resulted in significant performance improvements, as well as enabled new analog RF signal processing functionality, such as frequency-selective limiting (FSL) and signal-to-noise enhancement (SNE) devices. PHASE I: Demonstrate the synthesis of single-crystal quality magnetic substrates in 2 inch diameter or 1.5 by 1.5 inch square form factor. The thickness of the magnetic layer has to be at least 10 micrometers. Demonstrate ferrimagnetic resonance linewidth, delta-H, of <1 Oersted and spinwave linewidth, delta-Hk, of <0.2 Oersted. The thickness of the magnetic layer has to be uniform to within 3% over the entire area of the substrate. The density of dislocations has to be below 1 per square centimeter over an area covering at least 80% of the surface. PHASE II: Extend the single-crystal quality magnetic substrates synthesis technique to other magnetic material compositions to enable analog signal processing device applications 0.3 to 30 GHz. Demonstrate the synthesis of single-crystal quality magnetic substrates in 4 inch diameter or 3 by 3 inch square form factor. Demonstrate capability to produce magnetic layer thicknesses from 10 nm to 100 micrometers. Make a lot of 10 substrates available for verification testing to demonstrate quality, consistency and reproducibility. PHASE III DUAL USE APPLICATIONS: Develop and characterize an industrial grade synthesis process with >90% yield and production rate of no more than 4 hours per substrate per process line. Develop a manufacturing plan and production cost reduction plan. Produce at least 100 substrates and gather and analyze statistics on defects, uniformity, and repeatability. Make a lot of 10 substrates and 10 devices available for verification testing to demonstrate quality, consistency and reproducibility. REFERENCES: 1. J. D. Adam, "Mitigate the Interference: Nonlinear Frequency Selective Ferrite Devices," in IEEE Microwave Magazine, vol. 15, no. 6, pp. 45-56, Sept.-Oct. 2014. 2. H.L. Glass, “Growth of thick single-crystal layers of yttrium iron garnet by liquid phase epitaxy”, Journal of Crystal Growth, Volume 33, Issue 1, 1976, Pages 183-184, ISSN 0022-0248, 3. H.L. Glass, M.T. Elliot, “Attainment of the intrinsic FMR linewidth in yttrium iron garnet films grown by liquid phase epitaxy”, Journal of Crystal Growth, Volume 34, Issue 2, 1976, Pages 285-288 4. P.J. Besser, J.E. Mee, H.L. Glass, D.M. Heinz, S.B. Austerman, P.E. Elkins, T.N. Hamilton and E.C. Whitcomb, AIP Conf. Proc. No. 5 (1972) 125. KEYWORDS: Magnetic substrate, spinwaves, radio-frequency, analog signal processing
TECHNOLOGY AREA(S): Electronics OBJECTIVE: The objective of this effort is to develop an ultra-wideband ultra-Low Loss radome for very large antenna applications. DESCRIPTION: The US Army has programs that requires an ultra-wideband ultra-low loss radome to protect large antenna structures in various harsh environments. This radome will be designed to survive in temperatures between -70 degrees F and 180 degrees F and winds in excess of 100 mph. It is to have an operational temperature range between -40 degrees F and 150 degrees F. The diameter of the dome is to be no less than 24 feet in diameter. This radome will be incorporated into a transportable test RADAR system that is being developed for demonstration. It will require a non-disclosure agreement with the prime contractor and the development of the technology will be International Traffic in Arms Regulation (ITAR) restricted. The radome is expected to survive in a variety of environments, both land and maritime, with less than 1 dB of transmission loss over the design bandwidth and a minimal reflection coefficient. The transmitted electrical energy is to be greater than 10 terawatts (TW). The dome will be permanently installed as a part of the transportable RF system. At the present time there is no maximum weight requirement, but lighter weight solutions will be considered a better solution. There are presently no snow, lightning, or UV exposure requirements. As the objective system evolves, additional requirements may be added for a final phase III development. PHASE I: Develop ultra-wideband ultra-low loss radome design and develop proof-of-concept models to verify it can efficiently pass frequencies of interest (X-Ku Band), can withstand high peak powers (10 TW), a pulse length of 30 ns, and a pulse repetition frequency of 500 Hz. The Phase II contract will be classified at the Secret level and a Form DD254 will be required. The successful bidders should anticipate the start of a facilities clearance process, if it does not yet possess one. PHASE II: Based on the results of Phase I, build a proof of concept radome. Work with the systems developers to ensure that the antennas can meet the form factor requirements as well as other requirements for system integration. Baseline specification for new radome include: (1) A radome that operates efficiently in the frequency band from 9 - 20 GHz when incorporated into the RF transmitter systems.
The radome will also need to be hail resistant. Delivery of a full scale prototype is preferable, but may not be feasible with funding constraints. PHASE III DUAL USE APPLICATIONS: There are many military and commercial uses for radomes including communications, radars, and various sensors. In particular, the results of this effort will be of interest. Likewise, there are many military platforms that require broadband radomes including missiles, munitions of various types, and satellite communications systems. If successful, the most immediate transition path is the delivery of a new class of radome to Program Executive Office Missiles and Space (PEO MS). REFERENCES: 1. J.D. Kraus, Antennas, McGraw-Hill Book Company (1950). 2. R.A. Cairns and A.D.R. Phelps, Generation and Application of High Power Microwaves, Taylor and Francis (1997). 3. D.V. Giri, High-Power Electromagnetic Radiators: Nonlethal Weapons and Other Applications, IEEE Press (2001). 4. R.J. Barker and E. Schamiloglu, High-Power Microwave Sources and Technologies, Wiley-IEEE (2001). 5. J. Benford, J.A. Swegle, and E. Schamiloglu, High Power Microwaves, 2nd Edition, CRC Press (2007).
TECHNOLOGY AREA(S): Electronics OBJECTIVE: Develop and demonstrate Navigation-Grade MEMS inertial accelerometers that is applicable for use in precision gyro-compassing, tilt measurement, GPS denied navigation and guidance for various DoD assets; that reduces the Size, Weight, Power, and Cost (SWaP-C) of systems. DESCRIPTION: Although low-cost consumer-grade MEMS accelerometers are widely available in the commercial market, these devices have a higher noise floor, smaller range, and higher thermal sensitivity than required for navigation-grade accelerometers. There is a demand for navigation grade MEMS accelerometers to complement concurrent developments in the navigation grade MEMS gyroscopes. Navigation grade Inertial Navigation Systems (INS) contains 3 or more navigation grade MEMS gyros and accelerometers. Accelerometers play a significant role in the navigation performance when used with navigation grade gyroscopes in an INS. Research is required in the area of sensing mechanism(s) for the specific force measurements along with low noise electronics to develop a high-performance accelerometer. Some of the key performance parameters for the navigation grade accelerometers are as follows: # Accelerometer Parameters Threshold Values 1. Bias <1 mg 2. Bias stability coefficient 50 µg (s) 3. 1 year composite bias repeatability <200 µg 4. Bias ramp coefficient 3 µg/min 5. Noise coefficient (Velocity random walk) 5 µg/vHz 6. Thermal Sensitivity coefficient 200 µg/°C/min (s) 7. Non-linearity 50 µg/g2 (50-2000 Hz) 8. Input Range 20 g 9. Scale factor Error 10 ppm (s) 10.Bandwidth 300 Hz 11.Internal Axis misalignment <0.1 mrad (s) 12.Size <0.01 cu. In. 13.Weight <0.005 lb. 14.Power <3 mW 15.Survivability MIL-STD-810 PHASE I: Develop a preliminary design for the proposed accelerometer sensor technology. •Develop sensor error models and simulations to estimate the expected performance of the proposed. •Validate the error model and simulation results using representative data. •Deliver a final report that includes: o Accelerometer design, o Error model results and validation, o Feasibility of manufacturing the proposed concept to achieve desired performance o A plan for Phase II activity. PHASE II: Perform trade studies and conduct component test and evaluations. •Develop the final design for fabrication of the accelerometer sensor. •Fabricate three or more working prototypes (for concurrent independent government testing and characterization) •Conduct characterization testing and validation of the error models with the representative design; government test facilities can be provided for these characterization (if required) •Deliver a final report containing the trade studies, component test results, Final Design Documents, and test results. PHASE III DUAL USE APPLICATIONS: Productize the accelerometer design and integrate into an INS that can used in soldier-worn, soldier-borne, UAV or other platforms requiring navigation or Situational Awareness function. The accelerometer may be integrated into existing inertial navigation systems. Additionally, identify broader use commercialization and militarization options for this technology REFERENCES: 1. Honeywell, QA2000 Q-Flex® Accelerometer, https://aerospace.honeywell.com/en/~/media/aerospace/files/brochures/accelerometers/q-flexqa-2000accelerometer_bro.pdf 2. Safran, Colibrys, MS-9000 Accelerometer, http://www.colibrys.com/wp-content/uploads/2015/03/30S-MS9000.M.03.15-nod1.pdf KEYWORDS: Gyro-compassing, GPS Denied navigation, Precision tilt measurement, Navigation-Grade inertial Sensors
TECHNOLOGY AREA(S): Air Platform OBJECTIVE: Propose and develop next generation day Heads Up Display (HUD) capable of accepting an external video signal and projecting that video on an aviator helmet visor. DESCRIPTION: The current day HUD tested by the Army overlays data on vision, but forces the wearer to change his focal point when looking at the symbology vs looking at his environment, and has a limited field of view. A new HUD technology which creates a projected image so that it appears at the same focal distance of your eyes as the environment around the user is needed and allows a much greater field of view. A greater field of view will allow more symbology on the HUD display without interfering with direct line of sight or distracting the pilots. Number one complaint with current system is the inability to declutter enough symbols, which is directly linked to the 2nd complaint, reduced field of view (Final Test Report, Air Soldier System, Developmental Test for the CH-47F, May 2017, ATEC Project No. 2017-DT-RTC-AIRSS-G5960). Multiple companies are working on commercial HUD products for motorcycle helmets which can project symbology such as moving map display, instrument gages, and an interface for the motorcycle radio which is easy to use without taking eyes off the road. These new products are very light since crash standards for weight on a motorcycle helmet are very similar to Army aviation crash requirements. Projecting the display symbols on the visor have other advantages. As example, a projected image can be bright enough to see in bright sunlight at a programmable focal distance that can better serve the eyesight of different people as they age. Another advantage is that the display is far less susceptible to problems with glare. The proposed system must support an external video source of an existing HUD computer. The proposed display must be capable of projecting on or through a helmet visor equipped with laser protective properties. The proposed system must include system components to provide symbology on an aviation visor with the necessary reflective properties to see the symbology while still seeing through the visor in both day and night conditions. Cost target for production rates anticipated for fielding would be $10,000. In commercial quantities, would estimate that to be as low as $2,000, similar to the other commercial systems. The current motorcycle market in America does not have this product on the market, nor do commercial aviation helicopter helmets. Leverage of this technology could be easily applied to a HUD enhanced with moving map directions attached to a phone or Garmin. PHASE I: This effort shall generate a feasibility study which defines whether an existing or development commercial projection HUD product can be modified to fit on an Army HGU-56P helmet and project an image provided by a standard PC video input on the visor. The product proposed shall not introduce a new lens in front of one eye. The product proposed shall project an image in front of the pilot that is perceived at infinity. The visor in the product proposed shall support laser protective properties per the requirements of the Common Helmet Mounted Display (CHMD) specification AVNS-DTL-10868B. The study shall outline what technology can be leveraged from an existing product already in development or production. The vendor shall provide any supporting data already in existence to include performance, optical characteristics, distortion and the results of any testing that may have been performed, and provide analysis where data or testing is not available. Yüklə 0,91 Mb. Dostları ilə paylaş:
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