diff --git a/Ri2e.m b/Ri2e.m index 5193b7fd8781cd09b76685b13b5b240395202de7..e515cddeae279b38e01495ea8ae84ef1d0b2b2e6 100644 --- a/Ri2e.m +++ b/Ri2e.m @@ -4,7 +4,7 @@ function RotMati2e = Ri2e(grace_gps_time) % to an Earth-fixed Earth-centered coordinate system. The rotation matrix % is a simple Z-rotation, in which the rotation axes of the inertial and % the Earth-fixed frames coincide. It is an approximation of the realistic -% rotation matrix, by neglecting the contribuiton of the Precession, +% rotation matrix, by neglecting the contribution of the Precession, % Nutation and polar motion. % INPUT arguments: diff --git a/Ri2srf.m b/Ri2srf.m index bda4502a3c8979b1bbd80a3fbbceba44cefa66ff..5d3757c0a2bbc3170b7b8c95ecafd5ca49668391 100644 --- a/Ri2srf.m +++ b/Ri2srf.m @@ -1,7 +1,7 @@ function RotMat_i2srf = Ri2srf(Q) % this function computes the rotation matrix from inertial frame to -% satellite reference frame (SRF) based on the given quatrnions Q. +% satellite reference frame (SRF) based on the given quaternions (Q). % % INPUT: % quaterninons Q = [Q1, Q2, Q3, Q4] ... where Q4 = Q0 = cos(phi/2)