Model Peluruhan Dan Reentri Orbit Satelit LEO  

Oleh:

Manurung, S.L. ; Sinambela, Wilson ; Rachman, Abd

Jenis: Article from Journal - ilmiah nasional
Dalam koleksi: Jurnal Sains Dirgantara vol. 5 no. 1 (Dec. 2007), page 71-82.
Topik: Peluruhan Orbit; Rentri Satelit

Ketersediaan

Perpustakaan Pusat (Semanggi) Nomor Panggil: SS49.1 Non-tandon: 1 (dapat dipinjam: 0) Tandon: tidak ada

Lihat Detail Induk

Isi artikel

Based to the non-central Earth's gravity causing the sekuler variation on the semi mayor axis and ecentricity of the LEO's satellite the software of orbital decay has been developed. The input for the software is the height, eccentricity existed in TLE (Two Line Element table), an approximated ballistic coeffient and the atmospheric density on various solar activity. The software has been used to predict the time of reentry of Bepposax and SNOE satellites. The deviation of reentry time is 5 to 10%, and the error will such a week before satellite reentry. The software can be used to apporaximate the ballistic coefficient of a satellite.

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