Engineering topics
Young, J.
Publications and source records attributed to Young, J..
Health and Environment Linked for Information Exchange in Atlanta (HELIX-Atlanta): A Pilot Tracking System
Objectives. To provide an overview of four environmental public health surveillance projects developed by CDC and its partners for the Health and Environment Linked for Information Exchange, Atlanta (HELIX-Atlanta) and to illustrate common issues and challenges encountered in developing an environmental public health tracking system. Methods. HELIX-Atlanta, initiated in October 2003 to develop data linkage and analysis methods that can be used by the National Environmental Public Health Tracking Network (Tracking Network), conducted four projects. We highlight the projects' work, assess attainment of the HELIX-Atlanta goals and discuss three surveillance attributes. Results. Among the major challenges was the complexity of analytic issues which required multidiscipline teams with technical expertise. This expertise and the data resided across multiple organizations. Conclusions:Establishing formal procedures for sharing data, defining data analysis standards and automating analyses, and committing staff with appropriate expertise is needed to support wide implementation of environmental public health tracking.
Space Technology 7 : Micropropulsion and Mass Distribution
The NASA New Millennium Program Space Technology 7 (ST7) project will validate technology for precision spacecraft control. The ST7 disturbance reduction system (DRS) will contain new micropropulsion technology to be flown as part of the European Space Agency's LISA (laser interferometer space antenna) Pathfinder project. After launch into a low Earth orbit in early 2010, the LISA Pathfinder spacecraft will be maneuvered to a halo orbit about the Earth-Sun LI Lagrange point for operations. The DRS will control the position of the spacecraft relative to a reference to an accuracy of one nanometer over time scales of several thousand seconds. To perform the control the spacecraft will use a new colloid thruster technology. The thrusters will operate over the range of 5 to 30 micro-Newtons with precision of 0.1 micro-Newton. The thrust will be generated by using a high electric field to extract charged droplets of a conducting colloid fluid and accelerating them with a precisely adjustable voltage. The control position reference will be provided by the European LISA Technology Package, which will include two nearly free-floating test masses. The test mass position and attitude will be sensed and adjusted using electrostatic capacitance bridges. The DRS will control the spacecraft position with respect to one test mass while minimizing disturbances on the second test mass. The dynamic control system will cover eighteen degrees of freedom, six for each of the test masses and six for the spacecraft. In the absence of other disturbances, the test masses will slowly gravitate toward local concentrations of spacecraft mass. The test mass acceleration must be minimized to maintain the acceleration of the enclosing drag-free spacecraft within the control authority of the micropropulsion system. Therefore, test mass acceleration must be predicted by accurate measurement of mass distribution, then offset by the placement of specially shaped balance masses near each test mass. The - acceleration is characterized by calculating the gravitational effect of over ten million modeled points of a nearly 500-kg spacecraft. This paper provides an overview of the mission technology and the process of precision mass modeling of the DRS equipment.
Space Technology 7 Disturbance Reduction System - precision control flight Validation
The NASA New Millennium Program Space Technology 7 (ST7) project will validate technology for precision spacecraft control. The Disturbance Reduction System (DRS) will be part of the European Space Agency's LISA Pathfinder project. The DRS will control the position of the spacecraft relative to a reference to an accuracy of one nanometer over time scales of several thousand seconds. To perform the control, the spacecraft will use a new colloid thruster technology. The thrusters will operate over the range of 5 to 30 micro-Newtons with precision of 0.1 micro- Newton. The thrust will be generated by using a high electric field to extract charged droplets of a conducting colloid fluid and accelerating them with a precisely adjustable voltage. The control reference will be provided by the European LISA Technology Package, which will include two nearly freefloating test masses. The test mass positions and orientations will be measured using a capacitance bridge. The test mass position and attitude will be adjustable using electrostatically applied forces and torques. The DRS will control the spacecraft position with respect to one test mass while minimizing disturbances on the second test mass. The dynamic control system will cover eighteen degrees of freedom: six for each of the test masses and six for the spacecraft. After launch in late 2009 to a low Earth orbit, the LISA Pathfinder spacecraft will be maneuvered to a halo orbit about the Earth-Sun L1 Lagrange point for operations.
Pluto's Lightcurve in 1999
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The charge distribution of heavy cosmic ray nuclei
In the analysis of data from a balloon flight of a detector of cosmic ray nuclei designed to study the isotopic composition, the charge composition has been measured with high resolution. Some 24,000 nuclei with Z not less than 10 have been measured with a charge resolution of 0.2 charge units. The limitations on the significance of these results are those due to the corrections for the effects of matter in the detectors and the residual atmospheric matter. These corrections are discussed and corrected results are compared with other high resolution charge spectra reported recently.
Photoelectric lightcurves of asteroids 42 Isis, 45 Eugenia, 56 Melete, 103 Hera, 532 Herculina, and 558 Carmen
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Five-color photoelectric photometry of asteroid 433 Eros
Five-color (UVBGR) photoelectric light curves of Eros are presented which were obtained on nine nights during the asteroid's 1974/75 close apparition. Indications that three reversals occurred in the relative depths of the two minima between late December 1974 and late January 1975 are noted along with definite evidence of phase reddening. The maximum amplitude observed was 1.44 magnitudes, and the absolute visual magnitude at primary maximum (corrected to zero phase and to 1 AU from the earth and the sun) was about 10.8 magnitudes. Since the observations indicate that Eros has no significant rotational color variations, it is suggested that the light-curve amplitudes are due primarily to the asteroid's shape and to shadowing effects. Based on its colors relative to the sun, it is concluded that Eros appears to be an S-type asteroid.
Preliminary S-193 RADSCAT oceanographic data for Skylab 2
There are no author-identified significant results in this report.
Photometric determination of the rotation period of 1566 Icarus
Icarus asteroid rotation period and brightness variation values obtained from photometric observations at Cassegrain reflector focus