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Duxbury, J. H.

Publications and source records attributed to Duxbury, J. H..

9 records
All sourcesNASA NTRSDOE OSTI
NASA NTRS1996

Cassini tour cost reductions

The original design of the Cassini tour violated the cost constraint for the mission operations and data analysis by more than 30 percent. This challenge was addressed by performing tradeoffs in order to establish a modified risk and performance posture for the operations organization. This new posture accepted more data acquisition risk with minimal impact to the mission objectives, and brought the operation costs to within the program's constraints. The methodology employed within the Cassini program in order to address the tour cost, risk and performance parameters is presented.

Duxbury, J. H.↗
NASA NTRS1983

U.S. data processing for the IRAS project

The JPL's Scientific Data Analysis System (SDAS), which will process IRAS data and produce a catalogue of perhaps a million infrared sources in the sky, as well as other information for astronomical records, is described. The purposes of SDAS are discussed, and the major SDAS processors are shown in block diagram. The catalogue processing is addressed, mentioning the basic processing steps which will be applied to raw detector data. Signal reconstruction and conversion to astrophysical units, source detection, source confirmation, data management, and survey data products are considered in detail.

Duxbury, J. H.↗
NASA NTRS1980

Infrared Astronomical Satellite /IRAS/ Scientific Data Analysis System

The Infrared Astronomical Satellite (IRAS), to be launched in 1982, is discussed. It will systematically survey the entire sky over a large percentage of the infrared spectrum, in the wavelength region of 8 to 120 microns, at sensitivities a hundred times greater than previously achieved from high-altitude observatories, aircraft, balloons or sounding rockets. The Scientific Data Analysis System (SDAS), an off-line data processing facility, is examined. Its primary function is to produce a catalog of inertially fixed infrared-emitting point sources (mainly stars and galaxies) observed during the IRAS survey. Details for source detection and confirmation are given. It is estimated that the catalog will contain approximately a million objects having a brightness of 10 amtowatts per square centimeter or greater; 125,000 SDAS detections, if spurious events of signal-to-noise ratios greater than 2.5 are included, will be made every day.

Duxbury, J. H.↗
NASA NTRS1977

A candidate mission using the Shuttle and solar electric propulsion

It is suggested that an out-of-the-ecliptic solar electric propulsion (SEP) mission be performed. Data would be gathered pertaining to the three-dimensional structure of solar features at radio and X-ray wavelengths, the properties of the solar wind as a function of latitude and time, the configuration of the interplanetary field and its relation to solar fields, and the modulations of cosmic rays to determine the spectrum of interstellar cosmic rays. The mission would also, it is thought, demonstrate the capability of SEP for use in Shuttle missions. The SEP spacecraft and the ongoing development of related systems are examined. The weight of a SEP stage is contrasted with the weight of a chemical rocket stage.

Duxbury, J. H.↗
NASA NTRS1975

A Jupiter Orbiter mother/daughter spacecraft concept

The feasibility of a tandem launch of a mother/daughter spacecraft pair with a single launch vehicle for a 1981 Mariner Jupiter Orbiter mission is described. The mother is a close derivative of the three-axis stabilized Mariner Jupiter Saturn 1977 spacecraft with the addition of a Viking-type propulsion module for orbit capture; it concentrates on the planetology and satellite science objectives. The daughter is a small, simple spin-stabilized spacecraft taking advantage of the mother's transit and delivery capabilities; it obtains in-situ measurements of the surrounding planetary environment. A conceptual design of the daughter spacecraft is presented.

Duxbury, J. H.↗
NASA NTRS1975

Solar electric propulsion mission and spacecraft capabilities for outer planet exploration

This paper provides an update on solar electric-propulsion (SEP) technology by describing how SEP, as currently understood, performs relative to chemical-ballistic options on a limited set of missions for exploring the outer planets. A spacecraft design for these missions is discussed which embodies the findings of a study and development effort by NASA's Office of Space Science and Office of Advanced Systems Technology.

Atkins, K. L.↗
NASA NTRS1974

Interplanetary spacecraft design using solar electric propulsion

Emphasis of the electric propulsion technology program is now on the application of solar electric propulsion to scientific missions. Candidate planetary, cometary, and geosynchronous missions are being studied. The object of this paper is to describe a basic spacecraft design proposed as the means to accomplish (1) a comet Encke slow flyby, (2) a comet Encke rendezvous, and (3) an out-of-the-ecliptic mission. The discussion includes design differences foreseen for the various missions and indicates those areas where spacecraft design commonality is possible. Particular emphasis is placed on a solar electric propulsion module design which permits an attractive degree of design inheritance from mission to mission.

Duxbury, J. H.↗
NASA NTRS1974

Interplanetary spacecraft design using solar electric propulsion - A circular 1.0 AU out-of-the-ecliptic mission

A preliminary study has been conducted to investigate the utility of solar electric propelled spacecraft for delivering a scientific payload to high heliographic latitudes to study cosmic rays, the sun, and its influence on environments within our solar system. The mission is considered a candidate for launch in the early 1980's by both the United States and Europe and has the potential of becoming a cooperative space venture. A brief description of the science objectives, mission design and spacecraft design is presented for a circular 1.0 AU heliocentric orbit and a 15 kW solar electric propulsion module. Particular emphasis is placed upon the performance available from this approach.

Duxbury, J. H.↗