Convert ECI to ECEF Coordinates
Transform ECI position, velocity and acceleration to ECEF position, velocity & acceleration.
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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)
Cite As
Darin Koblick (2026). Convert ECI to ECEF Coordinates (https://in.mathworks.com/matlabcentral/fileexchange/28233-convert-eci-to-ecef-coordinates), MATLAB Central File Exchange. Retrieved .
Acknowledgements
Inspired by: Julian Date to Greenwich Mean Sidereal Time
General Information
- Version 1.8.0.0 (3.68 KB)
MATLAB Release Compatibility
- Compatible with any release
Platform Compatibility
- Windows
- macOS
- Linux
| Version | Published | Release Notes | Action |
|---|---|---|---|
| 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) |
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| 1.7.0.0 | Updated mean obliquity of elliptic equation to be consistent with units. All units in this equation are in degrees. |
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| 1.5.0.0 | Added another code attachment since the last attachment didn't appear to make it through. |
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| 1.4.0.0 | Updated vector inputs and outputs to include the acceleration term. |
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| 1.1.0.0 | Added acceleration transformation update to code. This now supports all position, velocity and acceleration vectors. |
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| 1.0.0.0 |
