Satellite orbital conjunction reports assessing threatening encounters in space (SOCRATES)

Kelso, T. S.; Alfano, Salvatore

doi:10.1117/12.665612

Cited by 26 publications

(14 citation statements)

References 3 publications

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“…Any space debris in Region B will remain there almost forever. Kelso and Alfano (2005) introduced Satellite Orbital Conjunction Reports Assessing Threatening Encounters (SOCRATES) for GEO satellite collision avoidance. Additionally, optical tracking systems, such as the International Scientific Optical Network (ISON), continue to perform GEO ring surveillance for satellite and space debris collision avoidance research (Molotov et al, 2008).…”

Section: Introductionmentioning

confidence: 99%

Analysis of the angle-only orbit determination for optical tracking strategy of Korea GEO satellite, COMS

Choi

Roh

et al. 2015

Advances in Space Research

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Section: Introductionmentioning

confidence: 99%

Analysis of the angle-only orbit determination for optical tracking strategy of Korea GEO satellite, COMS

Choi

Roh

et al. 2015

Advances in Space Research

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“…This method is comparable to that of the Satellite Orbital Conjunction Reports Assessing Threatening Encounters in Space (SOCRATES) (Kelso and Alfano 2006). Typically, the latest TLE is used in a routine all-on-all conjunction assessment.…”

Section: Conjunction Analysismentioning

confidence: 67%

An analysis of the 2016 Hitomi breakup event

Flegel¹,

Bennett²,

Lachut³

et al. 2017

Earth Planets Space

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The breakup of Hitomi (ASTRO-H) on 26 March 2016 is analysed. Debris from the fragmentation is used to estimate the time of the event by propagating backwards and estimating the close approach with the parent object. Based on this method, the breakup event is predicted to have occurred at approximately 01:42 UTC on 26 March 2016. The Gaussian variation of parameters equations based on the instantaneous orbits at the predicted time of the event are solved to gain additional insight into the on-orbit position of Hitomi at the time of the event and to test an alternate approach of determining the event epoch and location. A conjunction analysis is carried out between Hitomi and all catalogued objects which were in orbit around the estimated time of the anomaly. Several debris objects have close approaches with Hitomi; however, there is no evidence to support the breakup was caused by a catalogued object. Debris from both of the largest fragmentation events-the Iridium 33-Cosmos 2251 conjunction in 2009 and the intentional destruction of Fengyun 1C in 2007-is involved in close approaches with Hitomi indicating the persistent threat these events have caused in subsequent space missions. To quantify the magnitude of a potential conjunction, the fragmentation resulting from a collision with the debris is modelled using the EVOLVE-4 breakup model. The debris characteristics are estimated from two-line element data. This analysis is indicative of the threat to space assets that mission planners face due to the growing debris population. The impact of the actual event to the environment is investigated based on the debris associated with Hitomi which is currently contained in the United States Strategic Command's catalogue. A look at the active missions in the orbital vicinity of Hitomi reveals that the Hubble Space Telescope is among the spacecraft which may be immediately affected by the new debris.

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“…The CA tool monitors more than two satellites based on the Joint Space Operations Center (JSpOC) conjunction summary message (CSM) or TLE data from the North-American Aerospace Defense Command (NORAD). 10) The CA tool plots the radial, along-track, and cross-track differences, and the distances between the operating satellite and the approaching satellites.…”

Section: Collocation and Conjunction Analysismentioning

confidence: 99%

Development of a Novel Core Component-based Flight Dynamics Subsystem Software Platform

Hwang

Lee

2019

Trans. Japan Soc. Aero. S Sci.

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The flight dynamics subsystem (FDS) of a geostationary satellite ground control system conducts estimates of the orbital states, keeping within its mission box, and calculating the satellite operational parameters to be uploaded. A new FDS has been designed and implemented by dividing it into core-and bus-dependent modules for a recent Korean geostationary satellite ground control system. The core modules include orbit determination and prediction, event prediction, and station-keeping and relocation (SKR) planning; whereas the bus-dependent modules include fuel accounting, thruster modeling and maneuver reconstructions of SKR, and calculate all of the bus-dependent parameters. In particular, separate designs based on the components of the SKR planning and maneuver reconstruction using thruster modeling allow the system to be reusable and replaceable. We also designed and implemented a conjunction analysis tool and collocation control and monitoring units for multiple-satellite control. A FDS database has been developed and is managed using SQLite, which is freely distributed. The FDS is easy to develop and operate thanks to a novel separation concept introduced for the core-platform and spacecraft bus-dependent modules. It is the same concept used for operation and the graphical user interfaces (GUIs) applicable to the FDS. All of the FDS modules for new geostationary satellites have been validated through function and performance testing, and have proven to work successfully after the launch of satellites.

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Satellite orbital conjunction reports assessing threatening encounters in space (SOCRATES)

Cited by 26 publications

References 3 publications

Analysis of the angle-only orbit determination for optical tracking strategy of Korea GEO satellite, COMS

Analysis of the angle-only orbit determination for optical tracking strategy of Korea GEO satellite, COMS

An analysis of the 2016 Hitomi breakup event

Development of a Novel Core Component-based Flight Dynamics Subsystem Software Platform

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