Convert ECI to ECEF Coordinates

バージョン 1.8.0.0 (3.68 KB) 作成者: Darin Koblick
Transform ECI position, velocity and acceleration to ECEF position, velocity & acceleration.
4.2
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更新 2020/11/13

ライセンスの表示

Convert Pseudo Earth Fixed Inertial Coordinates to ECEF Coordinates. This function has been vectorized for speed.

Example Function Call:
>> [r_ECEF v_ECEF a_ECEF] = ECItoECEF(JD,r_ECI,v_ECI,a_ECI);

Where:
JD is the Julian Date vector [1 x N] (units are in days)
r_ECI is the position vector [3 x N] (any units are permitted)
v_ECI is the velocity vector [3 x N] (any units are permitted)
a_ECI is the acceleration vector [3 x N] (any units are permitted)

引用

Darin Koblick (2024). Convert ECI to ECEF Coordinates (https://www.mathworks.com/matlabcentral/fileexchange/28233-convert-eci-to-ecef-coordinates), MATLAB Central File Exchange. 取得済み .

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作成: R2007b
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ヒントを得たファイル: Julian Date to Greenwich Mean Sidereal Time

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バージョン 公開済み リリース ノート
1.8.0.0

Clarified that the ECI frame is in Pseudo Earth Fixed Coordinates (No Nutations are performed about the +Z axis for speed)
1.7.0.0

Updated mean obliquity of elliptic equation to be consistent with units. All units in this equation are in degrees.

1.5.0.0

Added another code attachment since the last attachment didn't appear to make it through.
1.4.0.0

Updated vector inputs and outputs to include the acceleration term.
1.1.0.0

Added acceleration transformation update to code. This now supports all position, velocity and acceleration vectors.
1.0.0.0