Simulation and modelling of orbital debris environment by equivalent breakups

Ganeshan, A. S.; Ananthasayanam, M. R.

doi:10.1016/s0273-1177(97)00019-7

Cited by 5 publications

(5 citation statements)

References 2 publications

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“…All forms of stored energy are safed in order to prevent an in-orbit explosion (Adimurthy and Ganeshan, 2006). A number of analytical models of fragmentation events have been designed and developed to compute the evolution of breakups in orbits (Ganeshan et al, 1988;Ganeshan and Ananthasayanam, 1996;1997;Ganeshan et al, 2001;Ananthasayanam et al, 2003;Ananthasayanam et al, 2002;Sharma et al, 2002;Bandyopadhyay et al, 2004). A detailed study of hypervelocity impacts on space systems is done using finite element techniques (Shone, 2003).…”

Section: Earlier Space Debris Mitigation Activities In Isromentioning

confidence: 99%

Overview of Space Debris Mitigation Activities in ISRO

Kosambe

2019

Journal of Aircraft and Spacecraft Technology

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For several decades orbital debris has been identified as a serious concern by all space-faring agencies and nations as it potentially threatens the current and future space endeavors. The Indian Space Research Organization (ISRO) is well aware of the present space debris scenario and is aimed towards achieving the goal of preserving outer-space for humanity. ISRO works on different aspects to effectively manage the threats due to space debris. This paper provides an overview of past activities carried out in ISRO towards the implementation of space debris mitigation guidelines. One of the significant step taken is the implementation of end of life passivation of the cryogenic upper stage of ISRO's Geosynchronous Satellite Launch Vehicle (GSLV). Another one is the successful design and development of propellant venting system for the upper stage of ISRO's Polar Satellite Launch Vehicle (PSLV). ISRO's constellation of communication and navigation satellites orbiting in GSO's are designed with adequate propellant so that it can re-orbit to the higher graveyard orbit at the end of their operational lifetime. A typical successful re-orbiting and decommissioning operation of INSAT-3E is described in detail. ISRO has successfully designed and developed the models and software to predict the atmospheric re-entry of satellites and launch vehicle upper stages, and also to compute the collision risk between the debris and the operational satellites. ISRO has also developed models to study the evolution of the space debris environment in LEO and GEO region. ISRO enthusiastically works with the United Nations Committee on the Peaceful Uses of Outer Space (UNCOPUOS) and Inter-Agency Space Debris Coordination Committee (IADC) to further improve the space debris mitigation guidelines.

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Section: Earlier Space Debris Mitigation Activities In Isromentioning

confidence: 99%

Overview of Space Debris Mitigation Activities in ISRO

Kosambe

2019

Journal of Aircraft and Spacecraft Technology

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“…In the area of analytical modeling related to fragmentation, a number of approaches are developed to study the evolution of break up fragments [3][4][5][6][7][8][9][10][11]. Further modeling of fragmentation and subsequent decay of space objects in LEO and Geostationary Transfer orbit (GTO) are in progress [12,13].…”

Section: Over View Of Space Debris Activities In Isromentioning

confidence: 99%

“…1. Different deterministic and stochastic models, developed in ISRO, for fragmentation events, are reported in [3][4][5][6][7][8][9][10][11] The decommissioning of INSAT-2C was planned along the lines of International Guidelines of Space Debris management by targeting apogee and perigee heights above GSO. The maneuvers had to be planned and executed having observed the propellant-depleted condition.…”

Section: Passivation Of Upper Stagesmentioning

confidence: 99%

Space debris mitigation measures in India

Adimurthy

Ganeshan

2006

Acta Astronautica

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“…In the earlier approaches [4,5] one commences from Block 2 and proceeds to Block 1 to simulate the orbital characteristics. Block 3 characteristics are independently simulated and are related to Block 2 through empirical relations connecting size or area to mass ratio A/m to V , the incremental velocity.…”

Section: Earlier Approaches Of Breakup Modelingmentioning

confidence: 99%

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

2005

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A posterior modeling approach for on-orbit breakup, named ASSEMBLE (A Semi-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 an on-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 I provide further confidence in the present model for orbital debris studies.

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Simulation and modelling of orbital debris environment by equivalent breakups

Cited by 5 publications

References 2 publications

Overview of Space Debris Mitigation Activities in ISRO

Overview of Space Debris Mitigation Activities in ISRO

Space debris mitigation measures in India

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

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