Consideration of lifetime limitation for spent stages in GTO

End-of-life disposal of high elliptical orbit missions: The case of INTEGRAL

“…The perigee is driven below the decay altitude by luni-solar gravity only. This approach minimizes the possibility of a complete circularization of the orbit in the real scenario as pointed out by Sharma et al (2004). This consideration is especially valid for the high energetic orbits considered in this work.…”

Space debris mitigation measures in India

“…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].…”

“…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.…”

“…During this period, following the cross-over point, the perigee altitude then continues to fall marginally. The evolution of the spent upper stage of GSLV-D1 was studied and it was predicted that the reentry is expected to take place around December 2002/January 2003 [11]. The actual decay took place on January 18, 2003.…”

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

“…The effect of lunar-solar perturbations in reducing the orbital lifetime of high eccentricity orbits is also the topic of interest of earlier studies [1–3]. An accurate simulation of the process requires a good estimate of the initial state [4]. Since the semimajor axis is directly related to the period of an orbit, it can be easily measured.…”