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eci2ecf
G = eci2ecf(Geci) [R, V] = eci2ecf(TALO,Reci,[Veci],[eRate])
Converts coordinate frame from earth-centered inertial (ECI), in which the coordinate frame is fixed at a specific time, to earth-centered fixed (ECF), in which the coordinate frame is fixed to the rotating earth.
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Parameters |
Description |
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Geci [struct/list] |
ECI geometry structure or comma-separated list of (TALO,Reci,[Veci],[eRate]) |
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TALO [vector] |
Column vector (Nx1) of the sample times (sec) |
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Reci [Nx3 matrix] |
N 3-element eci position vectors (m) |
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Veci [Nx3 matrix] |
(Optional) N 3-element eci velocity vectors (m/s) |
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eRate [scalar] |
(Optional) Earth rotation rate (rad/s). Must pass in Veci (can be []) to specify earth rotation rate. |
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Return Values |
Description |
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G [struct] |
If Geci is a structure, the output G will be a structure with position and velocity vectors in ECF coordinates. |
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R [Nx3 matrix] |
ECF position vectors (m) |
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V [Nx3 matrix] |
ECF velocity vectors (m/s) |
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Copyright (c) 2009. All rights reserved.
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Description