Аннотации:
The object of this study is the process
of deorbiting the KazEOSat-1 spacecraft,
which has completed its active service life
in low Earth orbit. The main problem is the
lack of an effective technique to deorbit
KazEOSat-1, taking into account its technical characteristics, orbital parameters,
and the need to minimize risks to the environment and other objects in orbit.
As part of the work, a software model
was built that takes into account the initial
orbital parameters of the device, which are
essential for planning and performing deorbiting maneuvers. The model is designed to
accurately calculate the descent trajectory, taking into account the laws of celestial
mechanics and the influence of atmospheric
conditions. The optimal deorbiting strategy
was selected based on an analysis of various methods for calculating orbital maneuvers aimed at reducing fuel consumption
and minimizing environmental risks. This
included a comparative analysis of existing approaches and the selection of the
most suitable ones under the given mission
parameters.
The results of the simulation using precise modeling methods in the MATLAB software environment allowed us to determine
the main deorbiting parameters, such as
the altitude at which the maneuvers begin,
the required velocity impulses, the total fuel
consumption, and the expected time before
entering the dense layers of the atmosphere. Based on the obtained data, practical recommendations were formulated for
the KazEOSat-1 deorbit. The first stage,
the active controlled deorbit, is carried
out by operating the low-thrust engine and
braking by the Earth’s atmosphere, allowing the spacecraft to descend from 758 km
to 444 km in 2.5 days. The second stage, the
passive uncontrolled deorbit, continues the
descent to 103 km in 969 days, using only
atmospheric braking. The third stage, the
uncontrolled drop, begins after reaching
103 km and ends with a drop to the Earth
in 834 seconds
