Aerospace Toolbox

lla2ecef

Convert geodetic coordinates to Earth-centered Earth-fixed (ECEF) coordinates

Syntax

p = lla2ecef(lla)
p = lla2ecef(lla, model)
p = lla2ecef(lla, f, Re)

Description

p = lla2ecef(lla) converts an m-by-3 array of geodetic coordinates (latitude, longitude and altitude), lla, to an m-by-3 array of ECEF coordinates, p. lla is in [degrees degrees meters]. p is in meters. The default ellipsoid planet is WGS84.

p = lla2ecef(lla, model) is an alternate method for converting the coordinates for a specific ellipsoid planet. Currently only 'WGS84' is supported for model.

p = lla2ecef(lla, f, Re) is another alternate method for converting the coordinates for a custom ellipsoid planet defined by flattening, f, and the equatorial radius, Re, in meters.

Examples

Determine ECEF coordinates at a latitude, longitude, and altitude:

p = lla2ecef([0 45 1000])


p =

  1.0e+006 *

    4.5107    4.5107         0

Determine ECEF coordinates at multiple latitudes, longitudes, and altitudes, specifying WGS84 ellipsoid model:

p = lla2ecef([0 45 1000; 45 90 2000], 'WGS84')


p =

  1.0e+006 *

    4.5107    4.5107         0
    0.0000    4.5190    4.4888

Determine ECEF coordinates at multiple latitudes, longitudes, and altitudes, specifying custom ellipsoid model:

f = 1/196.877360;
Re = 3397000;
p = lla2ecef([0 45 1000; 45 90 2000], f, Re)


p =

  1.0e+006 *

    2.4027    2.4027         0
    0.0000    2.4096    2.3852

See Also

ecef2lla, geoc2geod, geod2geoc

leapyear

load (Aero.Body)