Engineering topics
Stultz, J. W.
Publications and source records attributed to Stultz, J. W..
Thermal design of the Wide Field/Planetary Camera
The Wide Field/Planetary Camera is an imaging system developed by the Jet Propulsion Laboratory for the NASA Hubble Space Telescope currently scheduled to be launched in December 1989 aboard the space shuttle. The temperature control design of the instrument utilizes multilayered insulation, electric resistance heaters, aluminum/ammonia heat pipes, thermoelectric coolers, temperature control coatings, and space radiators. A feedback control system maintains stable sensor temperatures. Thermal capacitance maintains stable optics and electronics temperatures during transient conditions. Schedule slips and launch delays have allowed extensive thermal testing of the instrument. Six instrument thermal vacuum tests and a spacecraft thermal vacuum test were performed. Several modifications have been made to the instrument to correct icing and contamination problems that have been discovered during thermal vacuum testing. This paper describes the thermal design, last instrument thermal vacuum test, results, and thermal model correlation.
Thermal design for the Comet Rendezvous Asteroid Flyby spacecraft
The mission overview of the Comet Rendezvous Asteroid Flyby (CRAF) spacecraft, which is planned to rendezvous with Comet Kopff in 1998, is presented, together with the CRAF mission trajectory. The preliminary thermal design of the CRAF spacecraft is discussed, with emphasis placed on the Low Precision Pointing Platform, Bus, Propulsion Module, and Comet Penetrator, the thermal design of which was impacted most by the comet environment. Model simulations showed the design of the bus and the propulsion module subsystems to be adequate. Configuration diagrams are included.
Combined photovoltaic and thermal-storage module
Module uses phase change heat absorbing wax to reduce peak temperatures, increasing electrical efficiency. Wax makes module more cost effective than conventional thermomodules by also storing thermal energy for air and water heating.
Thermal and other tests of photovoltaic modules performed in natural sunlight
The nominal operating cell temperature (NOCT), an effective way to characterize the thermal performance of a photovoltaic module in natural sunlight, is developed. NOCT measurements for more than twenty different modules are presented. Changes in NOCT reflect changes in module design, residential roof mounting, and dirt accumulation. Other test results show that electrical performance is improved by cooling modules with water and by use of a phase change wax. Electrical degradation resulting from the marriage of photovoltaic and solar water heating modules is demonstrated. Cost-effectiveness of each of these techniques is evaluated.
Thermal and other tests of photovoltaic modules performed in natural sunlight
The bulk of the testing was the characterization of twenty-nine modules according to their nominal operating cell temperature (NOCT) and the effect on NOCT of changes in module design, various residential roof mounting configurations, and dirt accumulation. Other tests, often performed parallel with the NOCT measurements, evaluated the improvement in electrical performance by cooling the modules with water and by channeling the waste heat into a phase change material (wax). Electrical degradation resulting from the natural marriage of photovoltaic and solar water heating modules was also demonstrated. Cost effectiveness of each of these techniques are evaluated in light of the LSA cost goal of $0.50 per watt.
Thermal analysis of a high energy propulsion system /hydrazine and liquid fluorine/ for a rover class Mars Orbiter
Maintaining cryogenic fluorine at a -189 C during the interplanetary cruise period to Mars is a major thermal problem. At this low temperature the heat rejection by radiation is severely limited and the allowable thermal load to the fluorine tank is less than approximately 8 watts. Previous studies generally constrain the spacecraft to an inline tank configuration which tends to maximize the fluorine tank's view and heat rejection to space. With the Inertial Upper Stage, sufficient stack height may not be available on the Shuttle for an inline tank configuration. Therefore, this study addresses the more thermally constraining side by side tank configuration.
The Viking Mars Orbiter 1975 solar energy controller
The Jet Propulsion Laboratory is responsible for the Viking Orbiter System, which is part of the overall Viking Project managed by the Viking Project Office at Langley Research Center for NASA. The spacecraft will be launched on a Titan IIIE/-Centaur Launch Vehicle in August 1975. Solar energy for temperature control purposes is introduced into the propulsion module of the Orbiter. The energy enters by way of four individually commandable solar energy controllers (SECs). This paper summarizes the SEC thermal development, design and test results. Test results are presented for the prototype unit and for the flight units.
A new arc heater shroud test technique for thermo-structural testing of full-scale, nose-tip skirt materials
An arc heater shroud test technique was developed for thermostructural testing of full-scale, missile nose tip-skirt assemblies. Reentry trajectory simulation is provided by changing the arc heater operation in a prescribed manner through manual and automatic controls. Excellent test repeatability allows screening of materials by direct comparison of test results. Continuous recordings of model surface temperature, pressure, heat flux, and model internal temperatures are made at several locations during the test.
Solar absorptance of second surface mirrors for high angles of incidence
Recent measurements have indicated an increase rather than a decrease in the solar absorptivity of second surface mirrors at angles of incidence greater than 80 deg. These observations stimulated an analytical effort which revealed that the increase does occur. Using electromagnetic wave theory, the solar absorptance equations for the mirror configurations commonly encountered in application are developed. An increase in mirror solar absorptance has also been deduced from the temperatures of a second surface mirrored radiator being monitored on the Nimbus E microwave spectrometer experiment. Test and calculated results substantiating the solar absorptance increase are presented.
Thermal control of a Mars entry capsule.
Thermal control of Mars entry capsule with fiberglass honeycomb sandwich shell analyzed with and without aft thermal curtain, emphasizing cruise-flight phase
Thermal control of a Mars entry capsule.
Thermal control of Mars entry capsule with fiberglass honeycomb sandwich shell analyzed with and without aft thermal curtain, emphasizing cruise-flight phase