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Position, velocity, and acceleration vectors in Earth-centered Earth-fixed (ECEF) coordinate system

`[`

calculates position, velocity, and acceleration vectors in Earth-centered Earth-fixed (ITRF)
coordinate system for given position, velocity, and acceleration vectors in the
Earth-centered inertial mean-equator mean-equinox (J2000) coordinate system at a specific
Universal Coordinated Time (UTC).`r_ecef`

,`v_ecef`

,`a_ecef`

] = eci2ecef(`utc`

,`r_eci`

,`v_eci`

,`a_eci`

)

`[`

calculates the position, velocity, and acceleration vectors at a higher precision using
Earth orientation parameters.`r_ecef`

,`v_ecef`

,`a_ecef`

] = eci2ecef(`utc`

,`r_eci`

,`v_eci`

,`a_eci`

,`Name,Value`

)

The `eci2ecef`

function is available only by installing the Aerospace Blockset™ CubeSat Simulation Library from the Add-On
Explorer.

[1] Vallado, D. A.
*Fundamentals of Astrodynamics and Applications*. alg. 4. New York:
McGraw-Hill, 1997.

`aeroReadIERSData`

| `asbCubeSatMissionAnalysis`

| CubeSat Vehicle | `dcmeci2ecef`

| `deltaCIP`

| `deltaUT1`

| `ecef2eci`

| `generateAccessTable`

| `greenwichsrt`

| `polarMotion`