Optimal Reentry Time Estimation of an Upper Stage from Geostationary Transfer Orbit

Mutyalarao, M.; Sharma, Ram Krishnan

doi:10.2514/1.44147

Cited by 13 publications

(3 citation statements)

References 6 publications

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“…The law of gravitation is used here is as, In this study eccentricity and ballistic coefficient are considered as uncertain parameters [5]. The ballistic coefficient depends on the mass of the object, drag coefficient and the effective area.…”

Section: Working With Npoe and Matlabmentioning

confidence: 99%

Re-Entry of Space Objects from Low Eccentricity Orbits

Lawrence¹,

Sharma²

2019

IJAA

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This paper deals with the re-entry predictions of the space objects from the low eccentric orbit. Any re-entering object re-enters the Earth's atmosphere with a high orbital velocity. Due to the aerodynamic heating the object tends to break into multiple fragments which later pose a great risk hazard to the population. Here a satellite is considered as the space object for which the re-entry prediction is made. This prediction is made with a package where the trajectory path, the time of re-entry and the survival rate of the fragments is done. The prediction is done using DRAMA 2.0-ESA's Debris Risk Assessment and Mitigation Analysis Tool suite, MATLAB and Numerical Prediction of Orbital Events software. The predicted re-entry time of OSIRIS 3U was found to be on 7th March 2019, 7:25 (UTC), whereas the actual re-entry time was on 7th March 2019, 7:03 (UTC). The trajectory path found was 51.5699 deg. (Lat), −86.5738 deg. (Long.) with an altitude of 168.643 km. But the actual trajectory was 51.76 deg. (Lat), −89.01deg. (Long.) with an altitude of 143.5 km.

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Section: Working With Npoe and Matlabmentioning

confidence: 99%

Re-Entry of Space Objects from Low Eccentricity Orbits

Lawrence¹,

Sharma²

2019

IJAA

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“…Since the semimajor axis is directly related to the period of an orbit, it can be easily measured. Hence, the eccentricity and the ballistic coefficient which depends on the drag coefficient C D , the mass of the object m , and the effective area A are considered as uncertain parameters [5]. …”

Section: Introductionmentioning

confidence: 99%

“…In this paper, a method to perform the lifetime estimation of an upper stage in GTO is presented as an optimal estimation problem [5, 6]. Using this method we predict the reentry time of the cryogenic stage of the Indian geosynchronous satellite launch vehicle GSLV-D5, employing the orbital data of the rocket body (R/B) in the form of two-line element sets (TLEs), which were downloaded from the Space Track Organization website (http://www.spacetrack.org/) from February 11, 2014, to April 6, 2014.…”

Section: Introductionmentioning

confidence: 99%

Lifetime Estimation of the Upper Stage of GSAT-14 in Geostationary Transfer Orbit

David

Sharma

2014

International Scholarly Research Notices

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The combination of atmospheric drag and lunar and solar perturbations in addition to Earth's oblateness influences the orbital lifetime of an upper stage in geostationary transfer orbit (GTO). These high eccentric orbits undergo fluctuations in both perturbations and velocity and are very sensitive to the initial conditions. The main objective of this paper is to predict the reentry time of the upper stage of the Indian geosynchronous satellite launch vehicle, GSLV-D5, which inserted the satellite GSAT-14 into a GTO on January 05, 2014, with mean perigee and apogee altitudes of 170 km and 35975 km. Four intervals of near linear variation of the mean apogee altitude observed were used in predicting the orbital lifetime. For these four intervals, optimal values of the initial osculating eccentricity and ballistic coefficient for matching the mean apogee altitudes were estimated with the response surface methodology using a genetic algorithm. It was found that the orbital lifetime from these four time spans was between 144 and 148 days.

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