function [TransMatrixNED2ECI]=TransformNED2ECI(phi,lambdac)
%function [TransMatrixNED2ECI]=TransformNED2ECI(phi,lamdac)
%Generate the transformation matrix to transform a vector from
%North-East-Down coordinates coordinates to
%Earth-Centered-Inertial coordinates.
%V(ECI)=TransMatrixNED2ECI*V(NED)
%phi:=Geodetic Latitude (rad)
%lambdac:=Geocentric(Geodetic) Longitude (rad)
cphi=cos(phi);
sphi=sin(phi);
clambdac=cos(lambdac);
slambdac=sin(lambdac);
TransMatrixNED2ECI=[-sphi*clambdac  -slambdac -cphi*clambdac;
   				    -sphi*slambdac   clambdac -cphi*slambdac;
   						  cphi             0       -sphi];
