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The space junk is forecast to reentry at UTC +/- 8 hours

Forecast for Reentry


Update Sun 10-Jun-2018 14:13 UTC

The map above shows the location of the possible reentry of the space junk () predicted by modeling of orbital evolution until the fragment or satellite reaches the altitude of nominal burst.

According to the forecast made by Satview.org, the object's reentry will occur in at UTC, above the coordinates shown on map.

Satellite Launch Norad Incl.
degrees
Apogee
Km
Perigee
Km
Period
min
Options
EAGLE 2
Reentry: (YMD) 2018-05-18
201339436U9822019689Reentered!
Lat=-63.9   Lon=121.2
DELTA 2 R/B(2) (PAM-D)
Reentry: (YMD) 2018-05-23
200428476U3919014088Reentered!
Lat=-21.3   Lon=245.3
ANTARES R/B
Reentry: (YMD) 2018-06-5
201843475U5215313787Reentered!
Lat=-49.4   Lon=57.3
IRIDIUM 67 [P]
Reentry: (YMD) 2018-06-10
199825290U8670755897Reentered!
Lat=8   Lon=140.6
SL-4 R/B
Reentry: (YMD) 2018-06-11
201843494U5219517088Reentered!
Lat=12.7   Lon=24.3
FLOCK 2E-1
Reentry: (YMD) 2018-06-18
199841483U5225123789Reentered!
Lat=-13.6   Lon=277.7
SS-520-5 R/B
Reentry: (YMD) 2018-06-21
201843202U3166817093Reentered!
Lat=-21.1   Lon=320.1
FLOCK 2E'-17
Reentry: (YMD) 2018-07-3
199841776U5228527190Reentered!
Lat=-50.2   Lon=99.5
FLOCK 2E'-5
Reentry: (YMD) 2018-07-6
199841567U5228227390Reentered!
Lat=34.7   Lon=152.2
PSLV R/B
Reentry: (YMD) 2018-07-31
201742796U9526926390Forecast
CHALLENGER
Reentry: (YMD) 2018-08-22
199842721U5231731091Forecast
FALCON 9 DEB
Reentry: (YMD) 2018-09-1
201843483U8949447094Forecast
CZ-4B R/B
Reentry: (YMD) 2018-09-21
201742762U4335723890Forecast
SL-4 R/B
Reentry: (YMD) 2018-09-25
201641395U9831826690Forecast
LINK
Reentry: (YMD) 2018-10-9
199842714U5233433091Forecast
ICECUBE
Reentry: (YMD) 2018-10-12
199842705U5233633291Forecast
IRIDIUM 40 [-]
Reentry: (YMD) 2018-10-17
199725041U8642126091Forecast
ATLAS 2A CENTAUR R/B
Reentry: (YMD) 2018-10-25
200227567U274022157129Forecast
LEMUR-2-AUSTINTACIOUS
Reentry: (YMD) 2018-10-25
199842068U5233032391Forecast
WASEDA-SAT3
Reentry: (YMD) 2018-10-29
199841933U5232632191Forecast
FLOCK 2E'-18
Reentry: (YMD) 2018-11-25
199841769U5235434892Forecast
FLOCK 2E'-15
Reentry: (YMD) 2018-11-26
199841764U5235534992Forecast
AOBA-VELOX 3
Reentry: (YMD) 2018-12-1
199841935U5233432891Forecast
FLOCK 2E-5
Reentry: (YMD) 2018-12-16
199841564U5231531291Forecast
FLOCK 2E'-14
Reentry: (YMD) 2018-12-21
199841762U5235134591Forecast
IRIDIUM 90 [-]
Reentry: (YMD) 2018-12-24
200227373U8664424793Forecast




The Satellite Path


The path to be followed by satellite (dotted line) does not change due to the fact that the satellite is falling and can be used to assess the trajectory of the object before and after possible fall. In the graph, each point marks the range of 1 minute.

Solar Flux and Other Variables


As much as the institutes and space agencies strive to provide correct data of the point where the space debris will fall, several factors may interfere with the accuracy of the prediction. Among the most important, the solar flux is the most critical because it determines the conditions of the upper atmosphere, increasing or decreasing the drag on the object.

Besides the solar flux acting on the aerodynamic characteristics, another variable rather difficult to be computed is the resistance of materials used in the construction of the object and the shape of the structure. Combined, these factors may determine different altitudes for the moment of rupture, causing errors of more than 30 km in altitude reentry provided.

Other variables that affect the calculation of reentry, although less important, are the gravitational perturbations of the Sun and Moon and also those exercised by large mountain ranges, above or below sea level.

The modeling used by Satview to compute the time of reentry uses solar flux data obtained at the time of modeling, and prediction of the behavior of the sun for the next 5 days. With this, the margin of error of prediction is + / - 3 revolutions for satellites or debris in uncontrolled reentry.

Altitude of Reentry


Spacecraft reentering the atmosphere without control usually break between 72 and 84 km altitude due to temperature and aerodynamic forces acting on the structure.

The nominal breakup altitude is 78 km, but big satellites that have larger and denser structures survive longer and break down at lower altitudes. Usually, solar panels are destroyed before any component, at altitudes between 90 and 95 km.

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