Space debris proximity analysis in powered and orbital phases during satellite launch

Bandyopadhyay, Priyankar; Sharma, Ram Krishan; Adimurthy, V.

doi:10.1016/j.asr.2003.10.043

Cited by 6 publications

(5 citation statements)

References 1 publication

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“…Так, Индийская научно-исследовательская организация с 2001 г. использует планирование запусков своих РН PSLV и GSLV [5,6]. Примером использования этой системы является краткосрочный перенос на несколько минут запуска РН PSLV-C4 12 сентября 2002 г. Примечательно, что причиной этого являлась высокая вероятность столкновения с обломком другой индийской РН PSLV-C3 [6].…”

Section: анализ достижений и публикацийunclassified

Studying the motion of a launch vehicle and observed space debris objects during launch preparation

Holubek¹

2020

Kosm. teh. Raket. Vooruž

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Section: анализ достижений и публикацийunclassified

Studying the motion of a launch vehicle and observed space debris objects during launch preparation

Holubek¹

2020

Kosm. teh. Raket. Vooruž

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“…All estimated TLEs are compared with the corresponding NORAD TLE. 35–38 Notice that the CHAMP satellite was decayed in 2010, but its actual GPS data is available freely. 32…”

Section: Numerical Simulationmentioning

confidence: 99%

Estimation of Simplified General Perturbations model 4 orbital elements from global positioning system data by invasive weed optimization algorithm

Bolandi

Sedighy

et al. 2014

Proceedings of the Institution of Mechanical Engineers, Part G:

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In this paper, a novel approach is introduced to estimate the North American Aerospace Defense Command (NORAD)-type two-line elements (TLE) data based on the invasive weed optimization (IWO) method, which is a stochastic numerical optimization algorithm inspired by colonizing weeds. Many satellite applications use the NORAD Simplified General Perturbations model 4 (SGP4) for satellite position prediction. The input of SGP4 consists of TLEs which are published via NORAD freely through the worldwide web. Since it is generated irregular, a new TLE which is independent of NORAD is required to access data about the satellite location each time. An alternative to independent computation of TLE can be made feasible by the existing emersion of GPS receivers in the space project and using IWO. Using this stochastic algorithm increases the success probability to find a more accurate TLE. The estimation is performed for six Keplerian orbital elements and SGP4 drag term (B*) by using the satellite position data achieved from the GPS receiver. Also, the feasibility study of the concept is performed by using the actual GPS data of CHAMP and corresponding NORAD TLE. The time length of the GPS data used in the estimation is studied for practical application purposes. The results show that 500 samples of position data, with 1-min time intervals, are sufficient to keep the position error within 10 km in 3 days after epoch time in orbital elements with known drag term estimation. Moreover, for orbital elements with drag term estimation, 1000 samples of position, with 1-min time intervals, are sufficient to keep the position error within 15 km in 3 days after epoch time. If there is no considerable constraint for position-data time-length or time available for performing numerical computations, the estimated TLE can be more accurate than corresponding NORAD TLE.

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“…ISRO developed the models and software to predict the close approach of any of the debris to the functional satellites [2]. The software are being regularly used during the control and management of the orbiting spacecraft, and are specially useful during the relocation of the geo-stationary satellites from one orbital slot to another orbital slot.…”

Section: Over View Of Space Debris Activities In Isromentioning

confidence: 99%

“…For the spacecraft of interest, trajectory dispersions are obtained through Monte Carlo analysis and for a particular catalogued object, approximate trajectory dispersion values can be fixed by considering the age of the orbital information of the object and the type of orbit it represents. The procedural details are given in [2].…”

Section: Space Debris Proximity Analysis For Collision Avoidancementioning

confidence: 99%

Space debris mitigation measures in India

Adimurthy

Ganeshan

2006

Acta Astronautica

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Space debris proximity analysis in powered and orbital phases during satellite launch

Cited by 6 publications

References 1 publication

Studying the motion of a launch vehicle and observed space debris objects during launch preparation

Studying the motion of a launch vehicle and observed space debris objects during launch preparation

Estimation of Simplified General Perturbations model 4 orbital elements from global positioning system data by invasive weed optimization algorithm

Space debris mitigation measures in India

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