Addendum to Informatics for Health 2017: Advancing both science and practice

This article presents presentation and poster abstracts that were mistakenly omitted from the original publication

Publications of the Jet Propulsion Laboratory 1989

This bibliography describes and indexes by primary author the externally distributed technical reporting, released during 1989, that resulted from scientific and engineering work performed, or managed, by JPL. Three classes of publications are included: JPL publications in which the information is complete for a specific accomplishment; articles from the quarterly Telecommunications and Data Acquisition (TDA) Progress Report; and articles published in the open literature

Mass Hierarchy Determination Using Neutrinos from Multiple Reactors

We report the results of Monte Carlo simulations of a medium baseline reactor neutrino experiment. The difference in baselines resulting from the 1 km separations of Daya Bay and Ling Ao reactors reduces the amplitudes of 1-3 oscillations at low energies, decreasing the sensitivity to the neutrino mass hierarchy. A perpendicular detector location eliminates this effect. We simulate experiments under several mountains perpendicular to the Daya Bay/Ling Ao reactors, considering in particular the background from the TaiShan and YangJiang reactor complexes. In general the hierarchy can be determined most reliably underneath the 1000 meter mountain BaiYunZhang, which is 44.5 km from Daya Bay. If some planned reactors are not built then nearby 700 meter mountains at 47-51 km baselines gain a small advantage. Neglecting their low overhead burdens, hills near DongKeng would be the optimal locations. We use a weighted Fourier transform to avoid a spurious dependence on the high energy neutrino spectrum and find that a neural network can extract quantities which determine the hierarchy marginally better than the traditional RL + PV.Comment: 22 pages, added details on the neural network (journal version

Helicopter Ship Board Landing System

Relative navigation of an aircraft (fixed wing or helicopter) close to ships at sea is a unique navigation problem. Shipboard helicopter operations provide a difficult operational environment. Wind over deck and wake turbulence shed by ship super structure offer challenging and unpredictable conditions during takeoff and landing. This is especially true in the operational environment that includes sea-state six, with its associated twenty-foot waves and thirty-three knot winds. Anything other than calm seas can create pitch, roll, yaw, and heave of the landing platform. Different sea going vessels behave in a variety of ways due to their size, hull design, stabilization systems, etc. Of particular concern in this environment is the performance consistency during takeoff, landing and sling load re-supply operations. A helicopter pilot operating off such a platform must observe the heave, pitch, and roll motion of the landing platform and determine the landing contact time based on human reaction time as well as aircraft performance. In an attempt to automate this difficult task, a relative navigation system prototype has been jointly developed by Novatel and Boeing. This paper describes such a system. The relative navigation system consists of a pair of integrated Inertial Differential Global Positioning System (IDGPS) systems communicating with standard RTCA messages. A fixed integer carrier based solution enables the relative system to reduce the uncorrelated low latency position error between the two systems to less than 50 cm. The shipbased inertial unit provides its position, attitude, pseudorange and carrier measurements, as well as the position of an eccentric point (the landing mark) to the helicopter-based unit. The helicopter generates a precise carrier-based vector between the vessel and its antenna and uses this to compute a GPS position that has a high relative accuracy to the ship-based unit. This in turn is used to update the helicopter inertial unit so a low latency position can be generated there. From this, a high accuracy, low latency relative position is generated at the helicopter, along with the relative motion and attitude data required for safe and consistent landing or slinging operations. The system requirements and design are detailed, and an attempt is made to provide insight into the implementation difficulties and solutions. Test setup details and results are provided. Reprinted with permission from The Institute of Navigation (http://ion.org/) and The Proceedings of the 18th International Technical Meeting of the Satellite Division of The Institute of Navigation, (pp. 979-988). Fairfax, VA: The Institute of Navigation

Geodesics on an ellipsoid of revolution

Algorithms for the computation of the forward and inverse geodesic problems for an ellipsoid of revolution are derived. These are accurate to better than 15 nm when applied to the terrestrial ellipsoids. The solutions of other problems involving geodesics (triangulation, projections, maritime boundaries, and polygonal areas) are investigated.Comment: LaTex, 29 pages, 16 figures. Supplementary material is available at http://geographiclib.sourceforge.net/geod.htm

Polynomial Time Algorithms for Multi-Type Branching Processes and Stochastic Context-Free Grammars

We show that one can approximate the least fixed point solution for a multivariate system of monotone probabilistic polynomial equations in time polynomial in both the encoding size of the system of equations and in log(1/\epsilon), where \epsilon > 0 is the desired additive error bound of the solution. (The model of computation is the standard Turing machine model.) We use this result to resolve several open problems regarding the computational complexity of computing key quantities associated with some classic and heavily studied stochastic processes, including multi-type branching processes and stochastic context-free grammars

Gear optimization

The use of formal numerical optimization methods for the design of gears is investigated. To achieve this, computer codes were developed for the analysis of spur gears and spiral bevel gears. These codes calculate the life, dynamic load, bending strength, surface durability, gear weight and size, and various geometric parameters. It is necessary to calculate all such important responses because they all represent competing requirements in the design process. The codes developed here were written in subroutine form and coupled to the COPES/ADS general purpose optimization program. This code allows the user to define the optimization problem at the time of program execution. Typical design variables include face width, number of teeth and diametral pitch. The user is free to choose any calculated response as the design objective to minimize or maximize and may impose lower and upper bounds on any calculated responses. Typical examples include life maximization with limits on dynamic load, stress, weight, etc. or minimization of weight subject to limits on life, dynamic load, etc. The research codes were written in modular form for easy expansion and so that they could be combined to create a multiple reduction optimization capability in future

Gearing

Gearing technology in its modern form has a history of only 100 years. However, the earliest form of gearing can probably be traced back to fourth century B.C. Greece. Current gear practice and recent advances in the technology are drawn together. The history of gearing is reviewed briefly in the Introduction. Subsequent sections describe types of gearing and their geometry, processing, and manufacture. Both conventional and more recent methods of determining gear stress and deflections are considered. The subjects of life prediction and lubrication are additions to the literature. New and more complete methods of power loss predictions as well as an optimum design of spur gear meshes are described. Conventional and new types of power transmission systems are presented