Position and velocity vectors in Earth-centered inertial mean-equator mean-equinox

`[`

calculates the position vector in the Earth-centered inertial mean-equator mean-equinox
(J2000) coordinate system for a given position vector in the Earth-centered Earth-fixed
(ECEF) coordinate system at a specific Universal Coordinated Time (UTC). `r_eci`

] = ecef2eci(`utc`

,`r_ecef`

)

`[`

calculates the position and velocity vectors for given position and velocity vectors. `r_eci`

,`v_eci`

] = ecef2eci(___,`v_ecef`

)

`[`

calculates the position, velocity, acceleration vectors for given position, velocity, and
acceleration vectors. `r_eci`

,`v_eci`

,`a_eci`

] = ecef2eci(___,`a_ecef`

)

`[`

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

,`v_eci`

,`a_eci`

] = ecef2eci(___,`Name,Value`

)

The `ecef2eci`

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`

| `eci2ecef`

| `generateAccessTable`

| `greenwichsrt`

| `polarMotion`