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- W2140272932 abstract "The final location of reentry debris depends on a multitude of factors. Such factors include initial dy namic conditions, orbital parameters, reentry breakup conditions, environmental conditions, satellite materials, configuration, and design. Upon breakup of a satellite, only a few key parts are expected to survive unless there is sufficient heat shielding . Which parts survive reentry depends on their material constituents, mass, and shape. Of those parts that are likely to survive, a baseline trajectory can be formulated. By varying environmental uncertainty factors and initial conditions, a footprint fo r each object can be determined. Overlaying the object footprints will result in a picture of the debris field. This paper is the second of two parts that describes a complex reentry model that accounts for trajectory analysis, spinning object dynamics, h eating, structural failure, and a number of uncertainties . This part focuses on heating and structural failure modeling ." @default.
- W2140272932 created "2016-06-24" @default.
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- W2140272932 date "2006-06-25" @default.
- W2140272932 modified "2023-09-27" @default.
- W2140272932 title "Reentry Envelope Determination Part II: Structural Failure Due To Atmospheric Heating" @default.
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- W2140272932 doi "https://doi.org/10.2514/6.2006-6275" @default.
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