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ecf2eci
G = ecf2eci(Gecf,[eRate]) [R, V] = ecf2eci(TALO,Recf,[Vecf],[eRate])
Converts coordinate frame from earth-centered fixed (ECF), in which the coordinate frame is fixed to the rotating earth, to earth-centered inertial (ECI), in which the coordinate frame is fixed at a specific time.
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Parameters |
Description |
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Gecf [struct] |
ECF geometry structure or comma separated list of (TALO,Recf,[Vecf],...) |
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TALO [vector] |
Column vector (Nx1) of the sample times (sec) |
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Recf [Nx3 matrix] |
N 3-element ECF position vectors (m) |
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Vecf [Nx3 matrix] |
(Optional) N 3-element ECF velocity vectors (m/s) |
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eRate [scalar] |
(Optional) Earth rotation rate (rad/s). Must pass in Vecf (can be []) to specify earth rotation rate. |
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Return Values |
Description |
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G [struct] |
If Gecf is a structure, the output G will be a structure with position and velocity vectors in ECI coordinates. |
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R [Nx3 matrix] |
ECI position vectors (m) |
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V [Nx3 matrix] |
ECI velocity vectors (m/s) |
Doc-O-Matic.|
Copyright (c) 2009. All rights reserved.
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Description