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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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This paper documents radiation effects observed in selected spacecraft at the system and subsystem levels, and where possible, relates them to predicted radiation effects in parts.
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Various attempts have been made to reconcile data from the CRRES IDM space experiment, and other space experiments with ground test results, with modeling and with guidelines.
We have undertaken an imaging survey of 34 nearby galaxies in far-ultraviolet(FUV, [sim]1500 u and optical (UBVRI) passbands to characterize galaxy morphology as a function of wavelength. This sample, which includes a range of classical Hubble types from elliptical to irregular, with emphasis on spirals at low inclination angle, provides a valuable database for comparison with images of high-z galaxies whose FUV light is redshifted into the optical and near-infrared bands.
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Global ionospheric mapping (GIM) is a new, emerging technique for determining global ionospheric TEC (total electron content) based on measurements from a worldwide network of Global Positioning System (GPS) receivers.
Scattering Calculations of none-spherical particles have been carried out in order to explain observed optical properties of cometary dust. We focused on two optical properties of cometary dust sensitive to particle shape.
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We present (Lamda)=1.3 and 3mm aperture sysnthesis imaging of the multiple T Tauri system UZ Tauri.
We present results of concurrent maximum likelihood restoration implementations with spatially-.
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High resolution interpretations relating gravity and topography data for Venus should be restricted to the equatorial regions at this time.
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We present VLBI and Australia Telescope Compact Array images, and derive source frame radio-core brightness temperatures for three prominent, flat-spectrum extragalactic radio sources, notable because they have not been detected as gamma-ray sources with the EGRET instrument.
The premise of this paper is taht there is a useful analogy between evaluation of proposed problem solutions and evaluation of requirements engineering research itself. Both of these application areas face the challenges of evaluation early in the lifecycle, of the need to consider a wide variety of factors, and of the need to combine inputs from multiple stakeholders in making thse evaluation and subsequent decisions.
Loop Heat Pipes (LHP) have gained acceptance as a viable means of heat transport in many spacecraft in recent years. However, applications using LHP technology tend to only remove waste heat from a single component to an external radiator. Removing heat from multiple components has been done by using multiple LHPs. This paper discusses the development and implementation of a Loop Heat Pipe based thermal architecture for spacecraft. In this architecture, a Loop Heat Pipe with multiple evaporators and condensers is described in which heat load sharing and thermal control of multiple components can be achieved. A key element in using a LHP thermal architecture is defining the need for such an architecture early in the spacecraft design process. This paper describes an example in which a LHP based thermal architecture can be used and how such a system can have advantages in weight, cost and reliability over other kinds of distributed thermal control systems. The example used in this paper focuses on a Mars Rover Thermal Architecture. However, the principles described here are applicable to Earth orbiting spacecraft as well.