Rotate geocentric Earth-centered Earth-fixed vector to local north-east-down
returns vector components
wDown in a local north-east-down (NED) system corresponding
to vector components
W in a geocentric Earth-centered Earth-fixed (ECEF) system.
Specify the origin of the system with the geodetic coordinates
lon0. Each coordinate input
argument must match the others in size or be scalar.
[___] = ecef2nedv(___,
specifies the units for latitude and longitude. Specify
'degrees' (the default) or
Find the NED velocity components of an aircraft using its ECEF components.
Specify the geodetic coordinates of the aircraft in degrees and the ECEF velocity components in kilometers per hour.
lat0 = 61.64; lon0 = 30.70; U = 530.2445; V = 492.1283; W = 396.3459;
Calculate the NED components of the aircraft. The units for the NED components match the units for the ECEF components. Thus, the NED components are returned in kilometers per hour. The negative value of
wDown means the aircraft is ascending.
[uNorth,vEast,wDown] = ecef2nedv(U,V,W,lat0,lon0)
uNorth = -434.0403
vEast = 152.4451
wDown = -684.6964
Reverse the rotation using the
[U,V,W] = ned2ecefv(uNorth,vEast,wDown,lat0,lon0)
U = 530.2445
V = 492.1283
W = 396.3459
To transform coordinate locations instead of vectors, use the