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Preprints of the Keldysh Institute of Applied Mathematics, 2015, 032, 32 pp. (Mi ipmp1995)  

Deorbiting of low-earth orbit spacecraft using a sail for solar radiation pressure force augmentation

S. P. Trofimov
References:
Abstract: The efficient mechanism to deorbit a small satellite from low-earth orbits higher than 700 km using a sail augmenting the solar radiation pressure force is presented. It is shown that a dramatic gain in deorbit time is achieved in comparison with the common drag sail approach when the sail normal is stabilized along the satellite velocity vector direction. The issue of stability with respect to both initial conditions and sailcraft parameters is studied for the desired quasiperiodic attitude motion of a sailcraft.
Keywords: deorbiting, small satellite, solar sail, low-earth orbit, solar radiation pressure.
Document Type: Preprint
Language: Russian
Citation: S. P. Trofimov, “Deorbiting of low-earth orbit spacecraft using a sail for solar radiation pressure force augmentation”, Keldysh Institute preprints, 2015, 032, 32 pp.
Citation in format AMSBIB
\Bibitem{Tro15}
\by S.~P.~Trofimov
\paper Deorbiting of low-earth orbit spacecraft using a sail for solar radiation pressure force augmentation
\jour Keldysh Institute preprints
\yr 2015
\papernumber 032
\totalpages 32
\mathnet{http://mi.mathnet.ru/ipmp1995}
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  • https://www.mathnet.ru/eng/ipmp/y2015/p32
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    Препринты Института прикладной математики им. М. В. Келдыша РАН
     
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