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.
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|
|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|
Actions (login required)