Vectorized Orbital Decay Routine For Space Objects Between 180 and 500 km Altitude.

バージョン 1.0.0.0 (3.75 KB) 作成者: Darin Koblick
Fully vectorized routine will estimate the decay time for Earth orbiting objects
ダウンロード: 573
更新 2016/2/26

ライセンスの表示

This routine will estimate the amount of time it will take for an object, initially placed at an altitude between 180-500 km, provided that its orbital eccentricity is less than 0.1. To run, simply call the routine in your command prompt:
>> [P,t] = computeOrbitalDecay(a,e,A,Cd,m0,F107,Ap)
Where
a = semi-major axis (km)
e = eccentricity
A = space object cross-sectional area (m^2)
Cd = space object drag coefficient
m0 = space object mass (kg)
F107 = solar radio flux at 10.7 cm
ap = solar magnetic index
Note that P is a vector of the orbital period (sec) with respect to t, the propagation time elapsed (sec).
This routine was inspired by the work of the Australian Space Weather Agency titled "Satellite Orbital Decay Calculations" which described this procedure in a technical report written under the Australian Bureau of Meteorology.

引用

Darin Koblick (2024). Vectorized Orbital Decay Routine For Space Objects Between 180 and 500 km Altitude. (https://www.mathworks.com/matlabcentral/fileexchange/55371-vectorized-orbital-decay-routine-for-space-objects-between-180-and-500-km-altitude), MATLAB Central File Exchange. 取得済み .

MATLAB リリースの互換性
作成: R2013b
すべてのリリースと互換性あり
プラットフォームの互換性
Windows macOS Linux
カテゴリ
Help Center および MATLAB AnswersCubeSat and Satellites についてさらに検索

Community Treasure Hunt

Find the treasures in MATLAB Central and discover how the community can help you!

Start Hunting!
バージョン 公開済み リリース ノート
1.0.0.0

Updated description
Updated description of routine
Updated description to include more generic terminology.