Air force 14. 1 Small Business Innovation Research (sbir) Proposal Submission Instructions
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| The eventual size goal is: Full IMU (3 Gyros + 3 Accelerometers + IMU sensor Processing & Data Interfaces) < 50 Cubic inches (with objective = 34 Cubic inches, which is the size of the HG 1700 JDAM IMU) (Note that HG9900 is about 103 Cubic inches). For position accuracy, the goal is less than 0.03 m (3D; 1-Sigma) in a 100 seconds of inertial only flight (assume initial alignment) reflecting current gravity weapon dynamics.
For consideration, assume improving current gyro bias to less than 0.0005 degree/hour will produce a position error of 0.015 m in 100 seconds. The accelerometer bias of 100 nano-G will likewise produce a position error about 0.005 m in 100 seconds. Therefore, the overall IMU position error should be in the 0.03 m range given a 100 seconds time of flight. The major contributors to the final position error will be the mechanization errors such as algorithmic, misalignment, etc. Other errors for new sensors IMU will have apart from the most obvious ones, such as the misalignment and algorithmic, must be assessed and identified. The characterization phase of the IMU sensors should provide that info. The 0.03 m error due to gyro and accelerometer biases simply means that biases are no longer the limitations, and their contributions wash out when compared to other errors. The goals for an advanced IMU sensor are: Near Term (3-5 Years) Gyro 0.003 Deg/Hr; size less than 100 cubic inches. For Mid- Term Goals (5-10 Years), assume an angular drift rate approaching 0.0003 Deg/Hr and size of less than 50 cubic inches. For long term applications (10 years out), an angular drift rate of 0.00003 Deg/Hr or less total volume of < 10 Cubic inches is the desired goal. A tactical IMU including gyros and accelerometers cost goal is unit production cost of under $15 K. Tasks to get to a weapons grade IMU from sensors to be addressed include: characterization of errors to develop a full error budget for gyro and accelerometer triads; inertial navigation performance analysis including covariance and/or Monte-Carlo simulations In a weapon flight time (degraded GPS, fully denied-GPS); and laboratory/flight simulation qualification under weapon dynamics and environments. PHASE I: Research novel wide operating temperature triaxial angular rate sensors (Gyros) that can augment current and future weapon IMUs for long range navigation without GPS. Demonstrate principals of physics with critical lab experiments and show by analysis and modeling the extrapolation based on packaging and manufacturing technology maturity and transition for a five-year insertion goal. PHASE II: Develop, integrate, and test prototype IMU sensor components. Demonstrate through laboratory and simulated flight environment testing suitability for high sensitivity with low drift rates. Show through analysis, test and modeling that the proposed technology approach is compatible, supportable and improves current weapons IMU navigation systems performance. Develop hardware in the loop or flight test experiment modules for detailed characterization in simulated weapon trajectory environment. PHASE III DUAL USE APPLICATIONS: Develop and transition technology to DoD weapon and platform applications, commercial vehicle and aircraft navigation, and underground transportation applications with degraded GPS signals. REFERENCES: 1. Barbour, N; Elwell, J; et.al., "Inertial Instruments: Where to Now?," AIAA-92-4414, Conference Proceedings, The Charles Stark Draper Laboratory, Inc., Cambridge, Massachusetts, 02139, http://resenv.media.mit.edu/classes/MAS836/Inertialnotes/DraperOverview.pdf. 2. Shkel, A; "Precision Navigation, Timing, and Targeting enabled by Microtechnology: Are we there yet?," 6th Annual Precision Navigation and Timing Symposium Nov 2012 Presentation, http://scpnt.stanford.edu/pnt/PNT12/2012_presentation_files/08-Shkel_-approved_public_release.pdf. 3. Kenny, T; Goodson, K; "PNT at DARPA and Stanford," PNT09 Presentation, 2009. 3rd Precision Navigation and Timing Conference presentation, OCT 2009, Stanford Center for Position Navigation and Time. http://scpnt.stanford.edu/pnt/PNT09/presentation_slides/17_Kenny_Advances_MEMS.pdf. KEYWORDS: Inertial Measurement Unit, angular rate sensors, gyros, triaxial, Laser Gyro, Rate Gyro, drift, GPS Denied AF141-134 TITLE: Integrated Opto-Electronic Components for Multiaxis Inertial Measurement Units KEY TECHNOLOGY AREA(S): Weapons The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Kristina Croake, kristina.croake@us.af.mil. OBJECTIVE: Develop integrated opto-electronic technologies that can provide for miniaturization, integration, and weapons environment operation of atomic interferometric, superluminal, resonant photonics, magneto resonant gyros and accelerometers for weapons. DESCRIPTION: The Air Force is developing advanced technologies leading to small compact weapon systems, which need micro-inertial measurement systems far beyond current state of the art. These applications range from unmanned air systems (UAS), micro-air-vehicles (MAVS), miniature precision guided weapons, compact high performance missile and air launched interceptors, and advanced laser beam pointing/steering systems. A pervasive need is for robust small footprint inertial sensors that have robust environmental characteristics and extreme sensitivity. Continued navigation, sensor direction, and operation either in a GPS jammed environment, terrain masking scenarios, or other severe environments is a persistent Air Force need. Recent DARPA, Air Force, and MDA, developments have demonstrated gyros, rate sensors, and other instruments based on optically pumped rubidium and cesium using single frequency semiconductor lasers precisely tuned to the atomic resonance transition. These experiments using “atom” optics have shown great potential but have a long path to small system insertion. Recent experiments with “Fast Light” have shown promising results to provide nearer term insertion with small footprint and an order of magnitude accuracy improvement. Rubidium and cesium atomic sensor devices have shown promise for compact inertial microsystem applications, but are a long way from transition into practical, ruggedized 3-axis flight and ground system applications. Basic research experiments as derivatives of chip scale atomic clocks have shown that hybrid integrated optical-fast light devices could potentially have large expensive laser ring gyro performance in sizes as small as 1 cubic centimeter. A key stumbling block is application of integrated optronics to miniaturize the racks of electronics used support these novel sensors into a compact weapon footprint IMU. This topic seeks to exploit integrated electro-optics to miniaturize and share common functions to achieve the IMU 10-cubic- inch size goals for precision weapons. Recent breakthroughs in single frequency semiconductor laser diodes and bidirectional amplifiers have enabled a conceptual integration into a single laser driven multi-axis inertial sensors with sense nodes on sub-centimeter cubed scale. These lasers are marginally available today from an offshore supplier, but DoD users and other contacts report long delivery times, low reliability, and frequent failure to meet published specifications. Emerging domestic suppliers must be developed to ensure stable sources of supply of these precision lasers. Miniaturized, frequency-agile, robust laser systems that can operate autonomously while locked to atomic transitions with prescribed offsets up to 10 GHz are also needed. The SBIR topic solicits novel concepts and technologies in design, development, and demonstration of components, subsystems, and systems to support integrated optical atomic/quantum 3-axis IMUs for rotational and linear inertial sensing (Inertial Measurement Units), replacement of digital compasses, and target weapon fuzing. Key components should provide for stable operation of the drive and probe lasers, feedback and control of frequency and stability, microwave modulation of frequency for offsets (e.g., Rb 85 and Rb 87 at 795 and 780 nanometers or Cesium D1 and D2 lines at 894 and 852 nanometers respectively). The sensing system should be able to withstand missile and tactical fighter aircraft temperature, acceleration, and vibration environments and not be sensitive to electro-magnetic interference (EMI). PHASE I: Investigate integrated opto-electronics for advanced angular rate and acceleration sensors. By simulation and/or critical component experiments, show feasibility of the proposed approach. Investigate lasers, modulators, detectors and electro-optic components for inertial sensors. Address stability, performance, and single frequency laser power technology. Address integration into weapon IMUs. PHASE II: Design, develop, and characterize prototypes of the proposed technologies and demonstrate functionality. Demonstrate feasibility and engineering scale-up of technology; identify and address technological hurdles. Demonstrate applicability to selected military weapon systems and aircraft/spacecraft environments, including vacuum, cryogenic operation, and radiation exposure. Desired demonstration in laboratory inertial test environments simulating weapon, missile flight dynamic environments. PHASE III DUAL USE APPLICATIONS: Develop and execute a plan to manufacture the micro-optical atomic inertial component, subsystem, or system developed in Phase II. Assist the Air Force in transitioning this technology to the appropriate prime contractor for the system development and demonstration phase. REFERENCES: 1. “Superluminal ring laser for hypersensitive sensing,” H.N. Yum, M. Salit, J. Yablon, K. Salit, Y. Wang, and M.S. Shahriar, Optics Express, Vol. 18, Issue 17, pp. 17658-17665 (2010). 2. “Coupled resonator gyroscopes: what works and what does not,” M. Terrel, M. Digonnet, and S. Fan, Proc. SPIE, Vol. 7612, 76120B (2010). 3. New Innovations in Chip Scale Atomic Clocks (CSAC), Honeywell Inc. Fact Sheet, http://www.honeywell.com/sites/portal?smap=aero&page=aerotechmagazinearchive3_two&theme=T4&catID=CAJGEVG59TXDA5SO8CM5CU9WUV3N2ZISW&id=HHOI131WCWZ6DPPWJT4KBLDJMFPKZ5GAJ&sel=3. 4. Shkel, A; "Precision Navigation, Timing, and Targeting enabled by Microtechnology: Are we there yet?," 6th Annual Precision Navigation and Timing Symposium Nov 2012 Presentation, http://scpnt.stanford.edu/pnt/PNT12/2012_presentation_files/08-Shkel_-approved_public_release.pdf. KEYWORDS: inertial navigation, microwave photonics, attitude, MEMS, fast-light enhanced laser gyro, integrated optics, grating outcoupled single frequency laser diode, integrated optics, attitude determination, Micro Air Vehicle, Integrated Targeting Device AF141-135 TITLE: High Performance Accelerometers for Precision Attack Weapons KEY TECHNOLOGY AREA(S): Weapons The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Kristina Croake, kristina.croake@us.af.mil. OBJECTIVE: Develop high performance accelerometers in a tactical size and cost range to dramatically enhance tactical IMU’s to strategic grade for long range weapons guidance without GPS. DESCRIPTION: This topic is to address investigations of novel approaches for compact strategic grade accelerometers suited for tactical munitions. The goal is to develop high performance, compact form factor, ruggedized accelerometer to improve tactical IMUs for long duration guidance without GPS. Current accelerometers limit IMU accuracy as much as deficiencies in gyro rate sensors. There have been several advanced MEMS-based resonant structure accelerometers investigated for space applications that are approaching 1 micro G or better sensitivities but the severe vibration and heat environment range for tactical application limits their suitability. The environment ranges from very cold at start up -40 degrees C to above 70 degrees C ambient with severe vibration and heat. Very little investment in precision inertial measurement unit (IMU) technologies for tactical weapons has been made in recent years due to reliance on GPS and other radio navigation technologies. The goal of this research is to address gaps in high performance accelerometers improve tactical IMUs to strategic grade for long duration guidance without GPS. A good form factor to consider is the Honeywell HG1700 fiber laser gyro IMU. It provides reasonable performance under a wide range of operations when disciplined with periodic GPS inputs. The drift rates of the fiber laser and accelerometer errors cause navigation errors over longer flight times for weapon and RPA platforms. Sixty seconds of flight time without GPS results in meters of error. Several hours can result in kilometers of error. Improvements to existing IMU acceleration sensors are needed to improve long term guidance without GPS update at an affordable cost. A small IMU footprint is needed for weapon IMUs (i.e., the performance of a Honeywell HG9900 or Northrop Grumman LN250 in a Honeywell HG1700 form factor). The IMUs are typically mounted at the rear of a weapon and can experience severe vibration and heat. To minimize impact to existing weapon loadout and form factor, the goal is to fit into existing IMU packages with a sensor goal footprint of 1 cubic centimeter or better for a Tri-Axial accelerometer package with integrated electronics. This area also includes the support electronics/electro-optics to transition into integrated radiation and severe environment packages. The eventual size goal is: Full IMU package (3 Gyros + 3 Accelerometers + IMU sensor Processing & Data Interfaces) in less than 50 Cubic inches (with objective of 34 Cubic Inches, which is the size of the HG 1700 IMU). The position accuracy goal is less than 0.03 m (3D 1-Sigma) in 100 seconds of inertial only flight (assume initial alignment) for current gravity drop weapons. (Note that HG9900 IMU is about 103 Cubic inches) For consideration, assuming that just improving current IMU gyro bias to less than 0.0005 deg/hr will produce a position error of 0.015 m in 100 sec. The other impact is improving accelerometer bias. An accelerometer bias of 100 nano-G will likewise produce a position error about 0.005 m in 100 sec. The overall IMU position error should be in the 0.03 m range given a 100 sec time of flight. The major contributors to the final position error will be the mechanization errors such as algorithmic, misalignment, etc. Other errors for new sensors IMU will have apart from the most obvious ones such as the misalignment and algorithmic must be assessed and identified. The characterization phase of the IMU sensors should provide that info. The 0.03 m error due to gyro and accelerometer biases simply means that biases are no longer the limitations, and their contributions washes out when compared to other errors. The goals for IMU acceleration sensor are: Near-term (3-5 Years), accelerometer sensitivity 25 Micro-G with IMU size less than 100 cubic inches. For mid-term goals (5-10 years), assume an acceleration sensitivity of 2.5 Micro-G and IMU size of less than 50 cubic inches. For long term applications (10 years out), acceleration sensitivity of less than 1 Micro-G with total volume smaller than 20 cubic inches is the desired goal. A tactical IMU cost goal, including angular rate and accelerometer sensors, is a unit production cost of under $15 K. Tasks to get to a weapons grade IMU from sensors to be addressed include the following: characterization of errors to develop a full error budget for gyro and accelerometer triads; inertial navigation performance analysis including covariance and/or Monte-Carlo simulations in a weapon flight time (limited GPS); and laboratory/flight simulation qualification under weapon dynamics, and flight environments. It is desired that in phase II prototype modules be available for government HWIL and flight testing at the end of Phase II and in Phase III. PHASE I: Research novel wide operating temperature compact triaxial acceleration sensors that can augment current and future weapon IMUs for long range navigation without GPS. Demonstrate principals of physics with critical lab experiments and show by analysis and modeling the extrapolation based on packaging and manufacturing technology maturity and transition for a five year insertion goal. PHASE II: Develop and test prototype accelerometers with IMU components. Demonstrate, through laboratory and simulated flight environment testing, suitability for high sensitivity with low drift rates. Show through analysis, test, and modeling that the proposed technology approach is compatible, supportable and improves current weapons IMU navigation systems performance. Develop hardware in the loop or flight test experiment modules for detailed characterization in simulated weapon trajectory environment. PHASE III DUAL USE APPLICATIONS: Develop and transition technology to DoD weapon and platform applications, commercial vehicle and aircraft navigation, and underground transportation applications with degraded GPS signals. REFERENCES: 1. Trusov, A; Zotov, S; et.al.; "Silicon Accelerometer with Differential Frequency Modulation and Continuous Self-Calibration," IEEE MEMS 2013 Conference, Taipei, Taiwan, January 20 – 24, 2013, http://mems.eng.uci.edu/publications/AATrusov_IEEE_MEMS_2013.pdf. 2. Shkel, A; "Precision Navigation, Timing, and Targeting enabled by Microtechnology: Are we there yet?", 6th Annual Precision Navigation and Timing Symposium Nov 2012 Presentation, http://scpnt.stanford.edu/pnt/PNT12/2012_presentation_files/08-Shkel_-approved_public_release.pdf. 3. Miao, H, Srinivasan, K. et.al., "A microelectromechanically controlled cavity optomechanical sensing system", New Journal of Physics 14, 075015 (2012). dx.doi.org/10.1088/1367-2630/14/7/075015. 4. Krause, A; Winger, M; et.al., "A high-resolution microchip optomechanical accelerometer", Nature Photonics, Volume 6, Pages 768–772, (2012), doi:10.1038/nphoton.2012.245, 14 October 2012. 5. Kasevich, M., "Precision Navigation Sensors Based on Atom Interferometry", 2012 PNT Challenges and Opportunities Symposium -November 13 & 14, Stanford University 2012, http://scpnt.stanford.edu/pnt/PNT12/2012_presentation_files/07-Kasevich_presentation.pdf. KEYWORDS: Inertial Measurement Unit, Accelerometers, triaxial, drift, GPS Denied, fiber optic accelerometer, integrated optics, MEMS, atomic optics AF141-136 TITLE: Dual Mode Seeker/Sensor -LADAR/RF KEY TECHNOLOGY AREA(S): Weapons The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Kristina Croake, kristina.croake@us.af.mil. OBJECTIVE: Research and develop dual-mode LADAR/RF seeker with hand-off operation capable of detection and targeting in GPS-degraded and GPS-denied environment. DESCRIPTION: As part of an analysis of operating in GPS-degraded and GPS-denied environments, the Air Force has identified potential shortcomings in the terminal seeker technology of its existing arsenal of air-to-ground and stand-off weapons. The expected long ingress ranges and the high likelihood of encountering electronic counter-measures (such as GPS jamming) make it necessary to pursue robust weapon seekers possessing the best characteristics of both LADAR/IR and RF systems. Existing seekers do not currently possess the ability to detect targets at the desired long ranges and are not dual-mode capable of terminal high-resolution imaging.
PHASE I: Investigate the potential for hybrid designs of dual-mode (ladar/RF) seekers consistent with size, weight and power requirements of an extended-detection range flex/modular air-launched weapon for SEAD/DEAD missions. Bidder should propose a solution for resolving target images from multi-hit ladar data, making use of foliage penetration (FOPEN) and other advanced ladar processing techniques. Directory: wp-content -> uploads -> 2016 2016 -> 2017 afoCo Landmark Scholarship Program 2016 -> Instructions for the Preparation of Camera-Ready Contributions to the Conference Proceedings 2016 -> Step student Scholarships for Year 10-13 2016 -> The united church of canada 2016 -> Idan raichel biography – May 2016 Brief Producer, keyboardist, Lyricist, composer and Performer Idan Raichel 2016 -> An introduction to centre’s interventions expanding access to justice 2016 -> Sanchar Shakti 2016 -> Unit analysis should help here. We want number of bananas 2016 -> The Autobiography of Elder Joseph Bates 2016 -> The Great Heat and the Rhode Island Deep Water Bay Scallop (Argopecten irradians) Fishery 1875-1905 Download 1.72 Mb. Share with your friends:
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