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O lixo espacial IRIDIUM 61 [P] está previsto para reentrar Sábado, 29 Jun 2019 as 02:32 UTC +/- 8 hours
IRIDIUM 61 [P]

Previsão de Reentrada IRIDIUM 61 [P]


Atualizado Terça-feira, 25 Jun 2019 22:07 UTC

O mapa acima mostra a possível localização da reentrada do lixo espacial IRIDIUM 61 [P] (25263U), previsto por modelagem de evolução orbital até que o satélite ou fragmento atinja a altura nominal de ruptura.

De acordo com a previsão, a reentrada do objeto ocorrerá Sábado, 29 Jun 2019 as 02:32 UTC, acima das coordenadas mostradas no mapa.

Satellite Launch Norad Incl.
degrees
Apogee
Km
Perigee
Km
Period
min
Options
STARLINK AB
Reentry: (YMD) 2019-06-12
201944260U53º45344394Reentered!
Forecast
IRIDIUM 61 [P]
Reentry: (YMD) 2019-06-29
199825263U86º74926295Forecast
STARLINK Z
Reentry: (YMD) 2019-07-1
201944258U53º55254796Forecast
CZ-3B R/B
Reentry: (YMD) 2019-07-2
201943921U27º5843118150Forecast
CZ-3B R/B
Reentry: (YMD) 2019-07-9
201843604U55º494399139Forecast
BANXING-2
Reentry: (YMD) 2019-07-20
201641834U43º24422889Forecast
NJUST-1
Reentry: (YMD) 2019-07-29
199842722U52º27025990Forecast
STARLINK AV
Reentry: (YMD) 2019-08-10
201944278U53º40339593Forecast
DELTA 2 R/B(2) (PAM-D)
Reentry: (YMD) 2019-08-31
200832712U40º106317697Forecast
CZ-11 DEB
Reentry: (YMD) 2019-09-1
201944328U45º57926793Forecast
CZ-3B R/B
Reentry: (YMD) 2019-09-4
201843583U55º9119104191Forecast
SL-12 R/B(AUX MOTOR)
Reentry: (YMD) 2019-09-4
200833113U47º19422108340Forecast
EPSILON R/B
Reentry: (YMD) 2019-09-30
201943939U97º41820691Forecast
CZ-11 DEB
Reentry: (YMD) 2019-10-28
201944327U45º60326993Forecast
CZ-11 DEB
Reentry: (YMD) 2019-11-4
201944326U45º61427093Forecast
CZ-11 DEB
Reentry: (YMD) 2019-12-4
201944319U45º62226993Forecast
CZ-11 DEB
Reentry: (YMD) 2019-12-7
201944320U45º61427093Forecast
STARLINK AK
Reentry: (YMD) 2019-12-16
201944268U53º55154896Forecast
STARLINK C
Reentry: (YMD) 2020-01-10
201944237U53º55254996Forecast




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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