A posterior semi-stochastic low Earth debris on-orbit breakup simulation model

Anilkumar, AK and Ananthasayanam, MR and Rao, PVS (2005) A posterior semi-stochastic low Earth debris on-orbit breakup simulation model. In: Acta Astronautica, 57 (9). pp. 733-746.

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Abstract

A posterior modeling approach for on-orbit breakup, named ASSEMBLE (ASemi-Stochastic Environment Modeling of Breakup in LEO), is proposed.The main objectives of this paper are the statistical characterization of the orbital and physical parameters of the fragments generated by a non-orbit breakup. The analysis of two line element (TLE) data of the fragments of some fragmentation events, such as the Indian PSLV-TES rocket body breakup, showed their orbital parameters obey statistical distributions. The apogee or perigee height, limited by breakup altitude, and the inclination follow Laplace distributions, while the eccentricity a Lognormal distribution. Subsequently, suitable empirical relations in the literature help to expand the fragmentation scenario to mass, effective area, and ballistic coefficient. Lastly, the simulation of well-known historical breakups of (i) SPOT I rocket body,(ii) COSMOS 1813, (iii) STEP II rocket body, and (iv) CBERS I/ SAC Iprovide further confidence in the present model for orbital debrisstudies.

Item Type:	Journal Article
Publication:	Acta Astronautica
Publisher:	Pergamon-Elsevier Science Ltd
Additional Information:	Copyright for this article belongs to Elsevier.
Department/Centre:	Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering)
Date Deposited:	21 Sep 2005
Last Modified:	19 Sep 2010 04:20
URI:	http://eprints.iisc.ac.in/id/eprint/3699

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