Effect of the Semi-Synchronous Orbit Protected Region on the MEO Debris Environment (Invited)

Jenkin, Alan B.; Yoo, B. B.; McVey, John P.; Sorge, Marlon E.; Peterson, Glenn E.

doi:10.2514/6.2014-4229

Cited by 2 publications

(2 citation statements)

References 2 publications

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“…Of the current generation of debris models almost all [24] make use of the EVOLVE 4.0 NASA Standard Breakup Model making it of particular interest for further investigation. The only notable exception to this is Aerospace Corporation's ADEPT model which uses an in house tool known as IMPACT [25]. In the NASA model, first described in 2000, debris fragments are generated using the size, or characteristic length (Lc), as the independent variable which is then used to generate the mass, AMR, and ejection velocity.…”

Section: Newspace and Debris Modellingmentioning

confidence: 99%

NewSpace and its implications for space debris models

Diserens

Lewis

Fliege

2020

Journal of Space Safety Engineering

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Until two decades ago, the dominance of the space industry by national governments shaped the key characteristics of the spacecraft population and hence the space debris models used to anticipate future orbital populations. The rise of `NewSpace' with the growth of private sector involvement has brought innovations, disrupting the status quo and changing to the physical characteristics and mission orbits of commercial spacecraft. Analysis of shifts in mass and launch traffic for spacecraft launched between 1980 and 2019 (source: ESA's DISCOS database) suggests significant impacts for debris modelling. Results emphasised the ongoing change towards a more commercially focused space sector. 742 spacecraft were launched in the 1980s, of which 34 were labelled as commercial. By contrast, there were 1292 commercial missions out of 2325 launched in the 2010s-an increase from 4.6% to 55.6%. These increases correlate with a rise in the number of different organisations operating spacecraft and a clear trend can be seen towards smaller, lower mass spacecraft. This is likely to alter the distributions of fragments generated in collisions compared with the distributions obtained from empirical methods, such as the NASA Standard Breakup model, derived from the fragmentation of larger spacecraft in the 600-1,000 kg range. A study of observed breakup events indicates that the NASA Standard Breakup Model overestimates the number of large debris released during fragmentations due to collisions or explosion of satellites while also underestimating the number of small debris. It is believed that this will have a significant impact on the outcomes of simulations of the future debris environment where these fragmentation modes are expected to dominate the generation of new debris over the propulsion based explosions which have been historically prevalent.

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Section: Newspace and Debris Modellingmentioning

confidence: 99%

NewSpace and its implications for space debris models

Diserens

Lewis

Fliege

2020

Journal of Space Safety Engineering

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“…The impulses required to correct these perturbations are ∆V and may cause atmospheric reentry over medium to long time scales (from decades to hundreds of years) [32,33,34]. However, if left uncontrolled, a satellite in an inclined geosynchronous orbit quickly enters the GEO protected ring.…”

Section: Estimation Of Total Station-keeping Costmentioning

confidence: 99%

Geosynchronous inclined orbits for high-latitude communications

et al. 2017

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We present and discuss a solution to the growing demand for satellite telecommunication coverage in the high-latitude geographical regions (beyond 55 • N), where the signal from geostationary satellites is limited or unavailable. We focus on the dynamical issues associated to the design, the coverage, the maintenance and the disposal of a set of orbits selected for the purpose. Specifically, we identify a group of highly inclined, moderately eccentric geosynchronous orbits derived from the Tundra orbit (geosynchronous, eccentric and critically inclined). Continuous coverage can be guaranteed by a constellation of three satellites in equally spaced planes and suitably phased. By means of a highprecision model of the terrestrial gravity field and the relevant environmental perturbations, we study the evolution of these orbits. The effects of the different perturbations on the ground track (which is more important for coverage than the orbital elements themselves) are isolated and analyzed. The physical model and the numerical setup are optimized with respect to computing time and accuracy. We show that, in order to maintain the ground track unchanged, the key * Corresponding author: elena.fantino@gmail.com (E. Fantino)Preprint submitted to Acta Astronautica August 9, 2017 parameters are the orbital period and the argument of perigee. Furthermore, corrections to the right ascension of the ascending node are needed in order to preserve the relative orientation of the orbital planes. A station-keeping strategy that minimizes propellant consumption is then devised, and comparisons are made between the cost of a solution based on impulsive maneuvers and one with continuous thrust. Finally, the issue of end-of-life disposal is discussed.

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Effect of the Semi-Synchronous Orbit Protected Region on the MEO Debris Environment (Invited)

Cited by 2 publications

References 2 publications

NewSpace and its implications for space debris models

NewSpace and its implications for space debris models

Geosynchronous inclined orbits for high-latitude communications

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