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A02-152 TITLE: Hypervelocity Missile Stage Separation TECHNOLOGY AREAS: Weapons OBJECTIVE: To develop innovative models which describe the fundamental coupled fluid dynamics and kinematics that control stage separation in hypervelocity missiles designs. DESCRIPTION: Because of the necessity to produce compact, low drag, hypervelocity missiles, it is imperative to develop multi-stage missile designs with imbedded kinetic energy penetrators. Inherent in this design process, is the problem of producing a clean stage separation with a minimum weight, reliable, system. Even slight geometric shifts between missile stages can produce unacceptable results. A high fidelity simulation is sought to model the fluid dynamics interactions that take place as the imbedded missile stages are being separated. Optional designs to be considered should include: (a) passive drag separation, (b) pyrotechnic driven stage separation, and (c) ignition of a center body sustain motor. The dynamics of this process require three-dimensional geometry and time-accurate computational fluid dynamics (CFD) technology as wel as computational fluid dynamic models which account for the two-phase and finite-rate chemical kinetics processes in solid propellant rocket exhaust plumes with coupled body flowfields. New, innovative, and improved, yet practical, approaches must give special consideration to each of the following key areas: 1. The modeling architecture must incorporate the existing and extensive time-accurate, finite-volume, Reynolds-averaged, Navier-Stokes flowfield solution methodology including models for two-phase, gas-particle flows, and finite-rate chemistry. 2. Dynamic and adaptive grid development to achieve adequate grid resolution both spatially and temporally to capture the flowfield features possibly using hybrid structured/ unstructured grids as appropriate. 3. Strongly coupled fluid dynamics and multi-body kinematics. 4. Intelligent processor control for domain decomposition among multiprocessors coupled with flowfield interrogation to identify the dominant physical processes at the local level and apply the most applicable solution methodology to each domain. 5. Innovative solution techniques such that the required transient physical processes can be modeled while achieving solutions in a reasonable time period. PHASE I: Phase I proposals must demonstrate: (1) a thorough understanding of the Topic area, (2) technical comprehension of key areas for model development, and (3) previous computational fluid dynamics experience in modeling two-phase, nonequilibrium gas-particle, chemically reacting flows with a CFD code possessing those capabilities. Technical approaches will be formulated in Phase I to address each of the above key areas for consideration. If proven to be feasible, at least one hypervelocity missile stage separation event will be modeled during Phase I to demonstrate innovation in stage separation methodology and to assess the potential for Phase II success. PHASE II: The additional model improvements formulated in Phase I will be incorporated as a prototype computational fluid dynamics model. This protype computational fluid dynamics model will be run blind for a series of hypervelocity stage separation test cases for which detailed flowfield and body force/moment data will be available to demonstrate the advanced capabilities for analyzing and modeling stage separation. PHASE III DUAL USE APPLICATIONS: For military applications, this technology is directly applicable to all staged guided missile systems; hence, the additional model improvements formulated in Phase I could be finalized, documented, coded, and incorporated into an existing Government computational fluid dynamics code. For commercial applications, this technology is directly applicable to advanced propulsion techniques for commercial applications such as high speed supersonic transports and multi-stage orbit launch systems. REFERENCES: 1) Simmons, F. S., Rocket Exhaust Plume Phenomenology, ISBN 1-884989-08-X, AIAA, 2000. 2) Snyder, G., "CKEM Technology," AIAA 2000 Missile Sciences Conference, 7-9 November 2000. KEYWORDS: Stage separation; Unstructured grids; Computational fluid dynamics; Hybrid grids; Multi-body kinematics; Dynamic grid generation; Structured grids; Numerical methods A02-153 TITLE: Rheometer for Time Dependent Non-Newtonian Gel Propellants TECHNOLOGY AREAS: Weapons ACQUISITION PROGRAM: Common Missile Project Office OBJECTIVE: Develop a rheometer capable of determining the time-dependent rheology of gel propellants and use it to determine the pressure drop vs. flow rate characteristics as a function of both time and temperature for gelled propellants based on monomethyl hydrazine (MMH), inhibited red fuming nitric acid (IRFNA), and dimethylaminoazide (DMAZ). DESCRIPTION: The key capabilities of the rheometer are: 1) to be able to measure the pressure drop vs. flow rate of gel propellants at temperatures between -40°C and +70°C, 2) to use fixtures designed to determine the time dependence of their rheological behavior, and 3) to be made with materials compatible with the gelled propellants. All the rheological characterization of these propellants has been done using short straight tubes that characterize their shear-thinning characteristics. There are two important time dependencies that are difficult to determine. The first is thixotropy, the decrease in viscosity as the gel flows through a tube at constant shear rate. The second is viscosity restoration, or how fast the viscosity of a gel increases after flow stops. This phenomenon occurs following every flow perturbation, such as turns, passage size, and passage shape. These dependencies are time dependent and shear rate dependent. Complete understanding of gel propellant rheology is important in the design of gel propulsion manifolds and engines. PHASE I: Develop a rudimentary time, temperature, and shear rate dependent rheological model to determine the key parameters needed to be measured by the rheometer. Determine the test fixtures that will accurately measure the time-dependent characteristics of gel propellants that are applicable within the flow passages of a gel propulsion system. PHASE II: Refine the model from Phase I to include quantitative description of the flow process of gel propellants through a gel propulsion system. Fabricate a rheometer and test fixtures designed to determine the time dependency of gel propellant rheology. Validate the model by determining the time dependency of gel propellant rheology between -40°C and +70°C and shear rates from 5,000 sec-1 and 200,000 sec-1. Modify the model, if necessary, to agree with test results. PHASE III DUAL USE APPLICATIONS: NASA can use gel bi-propulsion systems on launch vehicles, spacecraft, and satellites. They are applicable for simple boosters as well as where variable thrust is required. The increased safety of gels over hypergolic liquids decreases the hazards of manned space flights. The versatility of gel engines can reduce the number of engines on spacecraft. For instance, a single engine could be used for changing from low to high earth orbits as well as precision positioning of the satellite for operational purposes, such as detecting leaking dams or mapping crop infestations. This rheometer can also be used by industry for commercial applications such as food products, hygiene products, and gelled cleaners/lubricants. OPERATING AND SUPPORT COST (OSCR) REDUCTION: A verified tool that optimizes gel propulsion system flow passages to minimize pressure drop will minimize the cost and schedule for the development of gel propulsion systems for either tactical or missile defense applications. For tactical applications, the versatility of gel propulsion systems could be leveraged into a single missile that could replace several single use systems currently deployed. Such a system would greatly reduce logistics and training costs. The precision of the thrust control provided by gel engines increases kill probability and multi-mission flexibility, thereby reducing the number of missiles needed in the arsenal. The savings to the government could exceed 1 billion dollars if a single missile using a gel propulsion system replaces several existing systems. If multiple systems are to be retained, a common set of engine hardware could be horizontally integrated into TOW, Javelin, Hellfire, and possibly Stinger type missile systems. Gel systems used for divert and attitude control systems (DACS) are much safer than liquids and will greatly reduce the cost of manufacture, storage, and transportation. These cost savings could approach $500 million dollars if gel propulsion is used by the Army’s THAAD, NMD, and the Navy’s Upper Tier. REFERENCES: 1) William M. Chew, Douglas L. May, and Darren M. Thompson, “Non-Newtonian Rheology of Gelled Propellants,” Proceedings of the 21st Army Science Conference, 15-17 June 1998; Norfolk, VA. 2) R. Byron Bird, Robert C. Armstrong, and Ole Hassager, “Dynamics of Polymeric Liquids, Volume 1: Fluid Mechanics,” John Wiley & Sons, New York, 1977. 3) G. Bohme, “Non-Newtonian Fluid Mechanics,” North-Holland, New York, 1987. KEYWORDS: gel propellants, thixotropy, gel flow properties, non-Newtonian rheology A02-154 TITLE: Compact Laser with Active/Passive Cooling for LADAR Applications TECHNOLOGY AREAS: Sensors OBJECTIVE: The objective of this task is to investigate and develop specific active and/or passive techniques for a very compact, self-contained cooling system as an integral part of a high repetition rate, solid-state laser transmitter, which must operate in military environments for limited duty cycles in an airborne platform or munition. Two separate applications, with two different duty cycles are envisioned: a short duty cycle of perhaps 1-3 minutes, and a longer duty cycle up to 30 minutes. For military applications, the laser transmitter might be part of an expendable laser radar or other laser communication system, where only one-time operation might be required. Commercial applications might include remotely emplaced laser transmitters, perhaps part of environmental sensors, that must operate only intermittently, but due to packaging or temperature constraints, require unique cooling functions. This investigation will require detailed experience in solid-state lasers and electro-optical designs, with their associated power supplies and electronics, and thermal analysis of sources of heat (in particular, that of the pump laser diode stacks in very high repetition rate lasers). The task should not be considered as a marrying of existing commercial lasers and laser cooling systems. Emphasis should be placed on a compact, lightweight, and electrically efficient design, ruggedized for high-speed airborne applications over temperature extremes. The cited references include a listing of commercial cooling systems typically used in laboratory testing of lasers, but which are not suitable for airborne military environments. The outcome of this research will be laser device(s) with compact, integral cooling systems. DESCRIPTION: This task will concentrate on the active/passive cooling system for the laser transmitter device. The laser transmitter may have the following typical characteristics: solid-state, diode-pumped laser operating at 1.06 or 1.5 microns nominal wavelength, pulse repetition rates typically 20-30 KHz, average laser output power 5-15 watts. Individual laser pulses may be on the order of 0.5-1.0 millijoule with pulse widths of 5-20 nanoseconds, for peak powers near 25-100 Kw. The laser cooling system is envisioned as a near-integral, but ideally separable part of the laser transmitter. Laser radars for military applications are still somewhat in their developmental phases. The internal laser transmitters typically use conventional cooling techniques, such as flowing liquids, fans, external refrigerating coolers and chillers, cryogenics, or thermo-electric coolers that are generally not suitable for final tactical configurations because of size, ruggedness, and/or power requirements. Cooling techniques based on a large external air flow (such as for an aircraft or missile in flight) may not be practical for all applications, and are not available for static experiments, testing, and checkout operations. Cooling techniques for the shorter operating cycle may be quite different than what is required for the longer operating cycle. Techniques that might be explored include passive heat conduction to a thermal sink and/or a cooldown technique using pressurized gas. The thermal sink might involve a large thermal mass, a material that undergoes a phase change (change of state) from solid to liquid, heat pipes, or other innovative approaches. Thermo-electric techniques may also be employed. Even though the military application might be a one-time operation, ideally the cooling capability will be reversible and reusable, both for testing purposes and for most commercial applications. PHASE I: In Phase I, an assessment will be made of the heat load requirements of typical laser configurations as well as the requirements for temperature stabilization of the pump laser diodes, to maintain proper emission wavelength and overall laser output energy. A survey will be conducted of the various types of cooling techniques that might be applicable. Recommendations for investigating the most promising techniques will be developed for both the short-term and long-term laser duty cycles. These recommendations will serve as a plan for Phase II hardware construction and testing. PHASE II: In Phase II, a laser design(s) with integral cooling will be developed, for each duty cycle application. After testing of laboratory prototype configurations, the most promising design(s) will be implemented in laser hardware to demonstrate proper laser operation at the two duty cycles. The laser hardware will be fully packaged, suitable for delivery to the Army for testing and field experiments. Follow on activities by the Army are planned for insertion of the laser transmitter configuration into a complete laser radar system for ground and captive flight tests. PHASE III: Commercial applications include indoor uses for portable lasers in such diverse areas as medical fields, inspection and monitoring, process control, production flow, etc. Outdoor applications include environmental monitoring, unattended sensors, remote operation of sensors in hazardous environments, etc. In many of these applications a compact, self-contained, high-efficiency laser cooling system is required. A reusable laser cooling system will be desired. REFERENCES: Journal Articles 1) "An Introduction to Thermoelectric Coolers", Sara Godfrey, Electronics Cooling, Sept. 1996, Vol 2, No 3. 2) "Forced Convection Cooling of Airborne Electronics", Yannick Assouad, Electronics Cooling, May 1997, Vol 3, No 3) "Test Methods for Characterizing the Thermal Transmission Properties of Phase-Change Thermal Interface Materials", Electronics Cooling, May 1999, Vol 5, No 2. 4) “Thermal Management of Highly Integrated Electronic Packages in Avionics Applications”, Claude Sarno and Georges Moulin, Electronics Cooling, Nov. 2001, Vol 7, No 4, pgs 12-20. 5) "Light from Crystals, Back to Basics: Diode-Pumped Lasers", Stephen J. Matthews, Laser Focus World, Nov. 2001, Vol 37, No 11, pgs 115-122. 6) "Diode-Pumped Lasers Begin to Fulfill Promise", Larry Marshall, Laser Focus World, June 1998, Vol 34, No 6, pgs 63-72. 7) "Diode Arrays Boost Efficiency of Solid-State Lasers", Eric J. Lerner, Laser Focus World, Nov 1998, Vol 34, No 11, pgs 97-103. 8) "DPSS Lasers Move Forward", Lasers & Optronics, Oct 1998, pgs 13-14.
9) Lydall/Affinity Industries, Inc., P.O. Box 1000, Ossipee, NH 03864, (603) 539-3600, www.affinitychillers.com 10) Melcor, 1040 Spruce Street, Trenton, NJ 08648, (609) 393-4178, www.melcor.com 11) PolyScience, 6600 West Touhy Avenue, Niles, IL 60714, (800) 229-7569, www.polyscience.com 12) Solid State Cooling Systems, 20 Pleasant View Road, Pleasant Valley, NY 12569, (845) 635-5500, www.sscooling.com 13) Thermo NESLAB, P.O. Box 1178, Portsmouth, NH 03802-1178, (800) 4NESLAB 14) Thorlabs, Inc., 435 Route 206, P.O. Box 366, Newton, NJ 07860-0366, (973) 579-7227, www.thorlabs.com
15) Electronics Cooling magazine, www.electronics-cooling.com Organization 16) CoolingZone, LLC, PMB 405, 290 Turnpike Road, Westborough, MA 01581, (508) 870-0240, www.coolingzone.com KEYWORDS: laser cooling, electronics cooling, passive cooling, cooling systems, heat removal, heat sink, temperature controller, thermo-electric cooler, heat exchanger A02-155 TITLE: Computer Simulation for the Design of Radar Absorbing Material (RAM) TECHNOLOGY AREAS: Materials/Processes OBJECTIVE: Develop a unique computational electromagnetic model (CEM) to simulate the performance of radar absorbing material (RAM) within an anechoic test chamber. Recent advances in computational power and memory efficiency for the electromagnetic analysis of complicated geometries should be leveraged [1,2]. The RAM should be modelled as a lossy diffraction grating. The objective of the simulation is to enable the design of RAM to operate over a wide bandwidth. DESCRIPTION: The choice of electromagnetic analysis method for computing the diffraction from the layer will be determined by the contractor. One possible approach is to use a technique known as rigorous coupled wave analysis (RCWA). This technique was recently implemented to simulate diffraction of one-dimensional gratings [3]. It has also been used to study radiation within, and scattering from, three-dimensional inhomogeneous shells [4]. Time oscillation and higher order generation may also be included [5]. There is a need for RAM that can operate over a wide range of bandwidth with a minimum amount of angular dependence. In the future, lethal unmanned combat air vehicles may require RAM to increase platform survivability. Also, unmanned air vehicles for delivery of valuable cargo or other logistics operations might justify the use of RAM. PHASE I: Develop the conceptual framework and architecture for the computer simulation of RAM as a lossy diffraction grating. PHASE II: Build the prototype computer simulation according to the architecture developed in Phase I. PHASE III: Commercial applications exist in the automotive industry to study the electromagnetic interference produced by the on-board electronics. REFERENCES: 1) G D Kondylis, F D Flaviis, G J Pottie, and T Itoh, "A Memory-Efficient Formulation of the Finite-Difference Time-Domain Method for the Solution of Maxwell Equations", IEEE Transactions on Microwave Theory and Techniques, vol. 49, no. 7, pp.1310-1320, July 2001. 2) Y. Ke, M. Yu, and J. Dai, "A New Method for the Electromagnetic Simulation of 3D Microwave Integrated Curcuits", Canadian Conference on Electrical and Computer Engineering, vol. 1, pp. 201-205, May 2001. 3) X. Niu, N. Jakatdar, J. Bao, and C J Spanos,"Specular Spectroscopic Scatterometry", IEEE Transactions on Semiconductor Manufacturing, vol. 14, no. 2, pp.97-111, May 2001. 4) J M Jarem, "A Rigorous Coupled-Wave Analysis and Crossed -Diffraction Grating Analysis of Radiation and Scattering from Three-Dimensional Inhomogeneous Objects", IEEE Transactions on Antennas and Propagation, vol. 46, no. 5, pp. 740-741, May 1998. 5) P. P. Banerjee and J M Jarem, "Rigorous coupled wave analysis of induced photorefractive gratings", Proceedings of the IEEE, vol. 87,no. 11, pp. 1870-1896, November 1999. KEYWORDS: Rigorous coupled wave analysis; diffraction gratings; electromagnetic simulation; radar absorbing material; spectroscopic scatterometry. A02-156 TITLE: PC-Based Realtime Infrared/Millimeter Wave Scene Generator TECHNOLOGY AREAS: Weapons ACQUISITION PROGRAM: Common Missile OBJECTIVE: The objective of this topic is the research, development and application of a novel and modularized personal computer (PC) - based infrared (IR) target, countermeasure, and background high resolution imaging scene generator (SG) whose underlying algorithms are applicable to both digital and real-time hardware-in-the-loop (HWIL) simulations. The PC-based SG should use innovative and existing hardware, software, and interface techniques to provide an unprecedented SG capability. To date, no such imaging SG technology exists on a PC platform that allows scene stimulation for high speed (>100Hz), high resolution (12-16 bits), and dynamic viewpoint (>100Hz) of 3 dimensional-world scenes and is therefore a high technology risk subject. The SG must be configurable for a variety of imaging IR sensors employing state of the art signal processing techniques. In addition, the PC IRSG must be easily integrated into a common simulation/software framework environment and multiple semi-active laser and millimeter wave scene generators and sensors (e.g., THAAD, Common Missile, NMD, AIT, etc.). The technology is applicable to both military and commercial sensor development and testing. Potential commercial applications include simulations for development and testing of infrared, SAL, and millimeter wave communications and imaging systems. DESCRIPTION: At present, digital simulations and HWIL for IR sensor development and testing are custom-designed by the seeker vendor and are verified, validated, and operated by both the vendor and government in simulation-based acquisition. These sensors require an imaging scene generator (SG) that outputs high speed (>100Hz), high resolution (12-16 bits), and dynamic viewpoints (>100Hz) of 3-dimensional-world scenes. A typical competition may involve several vendors, each requiring high resolution target and background models for proper exercise of seeker algorithms. To date, no such SG technology exits to allow scene stimulation at the required speeds, resolution, and dynamic viewpoint. In the interest of competition fairness, there is a need to assure commonality in these models, which are generally supplied by the government. There is also the need and desire by both the government and sensor vendors to eliminate costly re-design and re-development of digital and HWIL simulations. Additional efficiencies are realized by assuring commonality between digital and HWIL simulation IR SGs. Most importantly, due to the rising cost of main frame computers, special purpose graphics cards and associated maintenance, a novel PC-based SG design is desired to leverage the low cost and always performance increasing PC and video graphics card market. Development of a PC-based IRSG software/hardware system is needed that is portable, open architecture, open-source, object-oriented, and platform independent. The PC-based IR scene generator must be capable of integration with both digital and HWIL MMW and multi-mode seeker simulations. The generator must present a scene having resolution sufficient to current and future seeker signal processing technologies, frame rates (>100Hz), spatial resolutions (up to 1024 x 1204), bit resolutions (up to single color 16-24 bits) including multiple and simultaneous mid wave, long wave IR imaging applications. The PC IR scene generator must be capable of supporting detection, acquisition and sensors tracking modes of the sensor under test. Algorithms employed in the scene generator must be optimized and configurable to support real-time IR scene generation in an HWIL simulation environment. The PC IR SG must provide external outputs for the streaming scene data from the graphics card and or memory at the specifications listed above to either internal shared memory and in an industry standard video output formats. PHASE I: Study existing common simulation environments, including digital and HWIL simulations, and current state of the art seeker designs, for input, output, and computational requirements. Design a specification for a PC-based IR scene generator which will allow integration of the scene generator into these simulation environments. Develop a software and hardware specification for a PC IR scene generator meeting the requirements of the description above. PHASE II: Implement the PC IR scene generator based on software and hardware specifications determined in Phase I. Demonstrate the performance of prototype PC IR scene generator in a verifiable environment of contractor's choice. PHASE III DUAL USE APPLICATIONS: Commercial applications for this technology might be found in virtual prototyping of IR imaging sensors for communications and imaging systems development. The scene generator developed under this topic would provide an excellent simulation environment to support the conceptual design and testing of single mode and multi-mode infrared systems used in communications and imaging applications. The PC-based IRSG would also support the development and testing of imaging IR sensors used in medical imaging, police surveillance, fire prevention/detection, auto collision avoidance systems and intrusion detection systems. OPERATING AND SUPPORT COST (OSCR) REDUCTION: This technology would fit within the OSCR by drastically reducing the cost of developing simulations for testing systems under design in a simulation based acquisition environment. Savings will result from reduction of simulation developments. The use of a PC IR scene generator will eliminate the need for costly platforms and maintenance to clone and verify disparate simulations and provide an unprecedented performance capability. REFERENCES: 1) Technologies for Synthetic Environments: Hardware-in-the-loop Testing, Proc. SPIE, Vol. 2741, April 1996. 2) Technologies for Synthetic Environments: Hardware-in-the-loop Testing III, Proc. SPIE, Vol. 3368, April 1998. 3) Technologies for Synthetic Environments: Hardware-in-the-loop Testing IV, Proc. SPIE, Vol. 3697, April 1999. 4) Technologies for Synthetic Environments: Hardware-in-the-loop Testing V, Proc. SPIE, Vol. 4027, April 2000.
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