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Entry Debris Field Estimation Methods and Application to Compton Gamma Ray Observatory DisposalFor public safety reasons, the Compton Gamma Ray Observatory (CGRO) was intentionally deorbited on June 4, 2000. This deorbit was NASA's first intentional controlled deorbit of a satellite, and more will come including the eventual deorbit of the International Space Station. To maximize public safety, satellite deorbit planning requires conservative estimates of the debris footprint size and location. These estimates are needed to properly design a deorbit sequence that places the debris footprint over unpopulated areas, including protection for deorbit contingencies. This paper details a method for estimating the length (range), width (crossrange), and location of entry and breakup debris footprints. This method utilizes a three degree-of-freedom Monte Carlo simulation incorporating uncertainties in all aspects of the problem, including vehicle and environment uncertainties. The method incorporates a range of debris characteristics based on historical data in addition to any vehicle-specific debris catalog information. This paper describes the method in detail, and presents results of its application as used in planning the deorbit of the CGRO.
Document ID
20010084992
Acquisition Source
Johnson Space Center
Document Type
Conference Paper
Authors
Mrozinski, Richard B.(NASA Johnson Space Center Houston, TX United States)
Date Acquired
August 20, 2013
Publication Date
June 1, 2001
Publication Information
Publication: 2001 Flight Mechanics Symposium
Subject Category
Astronautics (General)
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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IDRelationTitle20010084958Collected Works2001 Flight Mechanics Symposium20010084958Collected Works2001 Flight Mechanics Symposium
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