generate typical wave spectra for deep and shallow waters, models forwave kinematics as affected by flat or sloping bottoms, and models forforces and moments on submersibles due to these surface waves. Forcesand moments are computed using two alternative methods. One is a fastmethod based on analytical integration of dynamic pressure forces overthe surface of an elongated ellipsoidal body. It gives first-order forces andmoments limited to horizontal and restrained bodies. The secondmethod, based on the Froude-Krylov approach, uses numericalintegration of dynamic pressures to give forces and moments on anyshape hull in any attitude. Unlike the first method, it can be extended toinclude broaching of the sea surface by the body. Hydrodynamic forcesdue to an unrestrained body’s motion are accounted for with “addedmass” terms. These mathematical models have been implemented in theC language in a real-time computer simulation. They are actively used tostudy the dynamic performance and control of submersibles at periscopedepths.Conley, J. F., Jr.; Lenahan, P. M.; Cole, P.Predictive model of SOI buried oxide charging based onstatistical mechanics and spin resonance data1997 IEEE International SOI Conference Proceedings(Cat. No.97CH36069), pp. 176-177In partially depleted NMOS transistors on SOI, back-channel leakageproblems are caused by radiation-induced hole trapping at point defectprecursors in the Buried Oxide (BOX). Thus, a predictive model of thesehole traps would be quite useful. We show that a model developedrecently for hole trapping in poly-capped thermally-grown oxides alsoeffectively predicts trapped hole densities in Unibond and SIMOX buriedoxides. The model is based on statistical thermodynamics and ElectronSpin Resonance (ESR) measurements of defects known as E’ centers.Connelly, J. H.; Brand, G. N.Advances in micromechanical systems for guidance,navigation, and controlProceedings of the AIAA Guidance, Navigation, and Control Conference,New Orleans, LA, August 1997<strong>Draper</strong> <strong>Laboratory</strong> and Boeing North American (formerly the RockwellCorporation) have formed an alliance to develop and manufacturemicromachined inertial sensors and systems. Initial products serve highvolumecommercial markets with target prices below $25 per instrument.Recent performance improvements, however, will enable new systems formany military and space applications. One such application is theaddition of guidance to low-end, previously unguided artillerymunitions. This paper reviews existing and potential new applicationareas and describes micromachined inertial sensor design, operation, andfabrication methods. Development activities for a flexible productionbase to serve DoD/NASA needs are presented. Also included are thelatest test data, projected performance improvements, and new conceptsfor low-cost, miniature, multi-axis systems.Connelly, J. H.; Barbour, N.; Brand, G. N.Manufacturing micromachined inertial sensor systemsProceedings of the Saint Petersburg International Conference onIntegrated Navigation Systems, 4th, St. Petersburg, Russia (A97-3086907-35), pp. 362-370, May 1997A flexible production base is being created to serve DoD system needs atthe low cost enabled by high-volume commercial markets. This paperreviews current micromachined inertial instruments and fabricationmethods, and presents ongoing development activities in low-costmanufacturing for higher-performance applications. The majorchallenges for military systems and improvement plans for cost, size, andperformance are discussed, and concepts for multi-axis systemconfigurations are proposed.Cunningham, B. T.; Bernstein, J. J.Wide-bandwidth silicon nitride membrane microphonesProceedings of the 1997 SPIE Symposium on Micromachining andMicrofabrication, The International Society for Optical Engineering,Issue 3223, pp. 56-63, 1997Small, low-cost microphones with high sensitivity at frequencies greaterthan 20 kHz are desired for applications such as ultrasoniccommunication links. To minimize stray capacitance between themicrophone and its amplifier circuit, process compatibility between themicrophone and on-chip circuitry is also desired to facilitate integration.In this work, we have demonstrated micromachined microphonespackaged with hybrid Junction Field Effect Transistor (JFET) amplifiercircuitry with frequency response extending to 100 kHz, and voltagesensitivity of 1.0 mV/Pa at 40 kHz at a bias voltage of 13.5 V. Themicrophones are fabricated with membranes and fixed backplates madeof low-temperature Plasma-Enhanced Chemical Vapor Deposited(PECVD) silicon nitride. Because the maximum temperature of thefabrication process is 300ºC, microphones may be built on silicon wafersfrom any commercial Complementary Metal-Oxide Semiconductor(CMOS) foundry without affecting transistor characteristics, allowingintegration with sophisticated amplifier circuitry. Low-stress siliconnitride deposition was used to produce membranes up to 2.0-mmdiameter and 0.5-mm thickness with ±0.10-mm flatness as measuredwith a WYCO TM optical interferometer. The excellent planarity of boththe diaphragm and the backplate, combined with a narrow sense gap (~2mm) results in high-output capacitance (up to 7.0 pF). The high-outputcapacitance results in noise spectral density that is approximately 3xlower than silicon diaphragm microphones previously fabricated by theauthors. Diaphragms with corrugations were fabricated to relieve tensilestress, to increase deflection per unit pressure, and to increase deflectionlinearity with pressure. Corrugated and uncorrugated microphonemeasurements are compared.De Fazio, T. L.; Delchambre, A.; De Lit, P.Disassembly for recycling of office electronic equipmentEuropean Journal of Mechanical Engineering, Vol. 42, No. 1,pp. 25-31, Spring 1997Office electronic equipment continues to proliferate and to be discardedfor a variety of reasons. This paper outlines the magnitude of theproblem and why we chose Personal Computers (PCs) as our majorconsideration. The problems associated with discarding PCs are impliedby or embodied in various details of PCs and in the customs of their use.These details and the manner in which they affect the disposal issue arereviewed, and the key issues affecting discarding computers and what isdone in Europe and USA are presented. An attempt is made to captureand predict what the future may bring regarding the goal of reducingelectronic office machinery mass going to the landfill, and policy issuesare reviewed.De Fazio, T. L.; Rhee, S. J.; Whitney, D. E.Design-specific approach to Design-For-Assembly (DFA)for complex mechanical assembliesProceedings of the 1997 IEEE International Symposium on Assembly andTask Planning, ISATP’97DFA issues of complex assemblies are addressed. Complex assemblieshave very high parts counts, offer limited redesign options, and theirassembly is an assembly of subassemblies. Conventional DFA isinadequate for complex assemblies as it omits the combinatorial aspectsof assembly such as assembly sequence choice and partitioningsubassemblies. Here, Assembly Sequence Analysis (ASA) is used as abasis for complex-assembly DFA. Searches for favorable subassemblypartitioning and assembly sequences minimize assembly difficulty as1997 Published Papers4
measured by kinematic degrees of freedom secured in assembly moves,while logical constraints that part geometry imposes on sequence choiceare satisfied. Findings are: ASA can expose assembly issues and pinpointDFA redesign candidates; limitations on redesign favor designingfunction-defining parts first; logically characterized issues dominate thequantitatively characterized issues when choosing sequences orpartitioning; once the former issues are addressed, a quantitativesequence choice criterion often duplicates historic assembly sequencechoices; and a quantitative sequence choice criterion favors sequentialover branched assembly lines.DeBitetto, P. A.; Johnson, E. N.; Bosse, M. C.; Trott, C. A.The <strong>Draper</strong> <strong>Laboratory</strong> small autonomous aerial vehicleProceedings of the SPIE, The International Society for OpticalEngineering Conference, 1997The Charles Stark <strong>Draper</strong> <strong>Laboratory</strong>, Inc. and students from theMassachusetts Institute of Technology and Boston University havecooperated to develop an autonomous aerial vehicle that won the 1996International Aerial Robotics Competition. This paper describes theapproach, system architecture, and subsystem designs for the entry. Thisentry represents a combination of many technology areas: navigation,guidance, control, vision processing, human factors, packaging, power,real-time software, and others. The aerial vehicle, an autonomoushelicopter, performs navigation and control functions using multiplesensors: differential GPS, inertial measurement unit, sonar altimeter, anda flux compass. The aerial transmits video imagery to the ground. Aground-based vision processor converts the image data into targetposition and classification estimates. The system was designed, built,and flown in less than 1 year, and has provided many lessons aboutautonomous vehicle systems, several of which are discussed. Ourcurrent research in augmenting the navigation system with vision-basedestimates is presented in an appendix.DeBitetto, P. A.; Johnson, E. N.Modeling and simulation for small autonomous helicopter developmentProceedings of the AIAA Guidance, Navigation, and Control Conference,New Orleans, LA, August 1997The Charles Stark <strong>Draper</strong> <strong>Laboratory</strong>, Inc., the Massachusetts Institute ofTechnology, and Boston University have cooperated to develop anAutonomous Aerial Vehicle (AAV) that competed in and won the 1996International Aerial Robotics Competition, sponsored by the Associationfor Unmanned Vehicle Systems, International (AUVSI). Development ofthe vehicle continues to support ongoing research in the area ofautonomous systems. A simulation capability has been developed tosupport the design, development, and test of the navigation, control,guidance, and vision processing subsystems, as well as human-machineinterfaces and procedures. The use of the simulation described in thispaper is identified as a key factor in the success of the program at thecompetition and operations since then.Dowdle, J. R.; Connelly, J.; Gustafson, D.; Marinis, T.; Prestero, M.Technologies for precision-guided munitionsProceedings of the Submarine Technology Symposium, Applied Physics<strong>Laboratory</strong>, Laurel, MD, May 1997Precision-guided projectile efforts underway aim to develop newprojectiles and to transform the current large inventory of low-accuracyprojectiles into highly accurate precision strike resources. Theseobjectives are to be accomplished by developing a low-cost Guidance,Navigation, and Control (GN&C) system consisting of an integratedGlobal Positioning System (GPS)/Microelectromechanical System(MEMS) Inertial Measurement Unit (IMU), and an associated flightcontrol system. This GN&C system can be installed in place of the fuzein projectiles in the inventory. A succession of Navy-sponsoreddemonstrations are involved with this development. The combination oflow-cost MEMS inertial sensors and the miniaturization of electronicspackages in Multichip Modules (MCMs) suitable for inexpensive, highvolumeproduction yet able to withstand the severe gun launchenvironment have enabled this development. Details of the adaptation ofthese technologies to this application and the trade-off analyses thatdemonstrated concept feasibility are presented.Dowdle, J. R.; Thorvaldsen, T. P.; Kourepenis, A. S.A GPS/INS guidance system for Navy 5-in projectilesProceedings of the AIAA Guidance, Navigation, and Control Conference,New Orleans, LA, August 1997This paper describes the design, operation, test, and critical performanceissues of the Extended-Range Guided Munition (ERGM) DemonstrationGPS/MMIMU (Micromechanical Inertial Measurement Units), which isthe guidance system for the Navy’s 5-in ERGM Demonstration Round.This guidance system combines GPS position data with micromechanicalinertial sensor measurements to produce the navigation solution, anduses the navigation data with a prespecified aimpoint location togenerate guidance commands. In addition to the GPS receiver and theMicromechanical Inertial Sensor Assembly, the system includes ag-hardened reference oscillator, the guidance and navigation electronics,and the power conversion electronics, all packaged in an 8-lb(f)cylindrical volume 8.4 in long with a 4.35-in diameter.D’Souza, C. N.An optimal guidance law for planetary landingProceedings of the AIAA Guidance, Navigation, and Control Conference,New Orleans, LA, August 1997A guidance law that minimizes the commanded acceleration along withthe (weighted) final time is developed. This guidance law is a linearfunction of the states (relative to the landing point) and a nonlinearfunction of the time-to-go. The time-to-go is obtained as a solution to aquartic equation that is solved analytically. The advantage of thisguidance law is that it does not involve any iterations whatsoever. It isthe exact solution to the two-point boundary-value problem associatedwith the first variation necessary conditions. It also satisfies the secondvariation necessary conditions for a minimum. An example of a lunarlanding is given to demonstrate the optimality of this guidance law.Elwell, J.GPS/INS guidance of terradynamic penetratorsProceedings of the AIAA Guidance, Navigation, and Control Conference,New Orleans, LA, August 1997<strong>Draper</strong> has been developing hardware and performing flight testsemploying miniature low-cost precision guidance systems, incorporatinginertial sensors that are capable of surviving significant Earth penetration.One objective of these developments has been to enable penetrators thatare targetable against both shallow and deeply buried targets. GPS/INSis now being examined for such applications since integration providesimportant capabilities over that of unaided GPS. The inertial systemprovides an ongoing navigational capability should the GPS system loselock, and also permits the carrier and code track loops to narrow theireffective bandwidth, considerably enhancing the antijam capability of thesystem. Because of the high-shock survivability of silicon inertialinstruments, concepts such as navigation within the Earth have becomea consideration. Such capability will allow us to consider smart fuzingconcepts, incorporating terradynamic navigation for Earth penetratorssubsequent to ground entry.1997 Published Papers5
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Letter from thePresident and CEO,Vi
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Information TechnologyMilton AdamsE
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Table 2. ATFM performance evaluatio
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[3] Wambsganss, Michael C. “Colla
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Guidance, Navigation,and ControlJim
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clock and ephemeris errors, as well
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tightly-coupled system, however, ca
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Advanced Fault-TolerantComputing fo
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autonomy. It must have the ability
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chosen to be 24, for a total of 48
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process step. Process information i
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User Accuracy as aFunction of Simul
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AcknowledgmentR.L. Greenspan, J.A.
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Systems IntegrationRich MartoranaPe
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control is employed to maintain the
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