From 1f000094eeb477ef937b4a6636c0b9158f1f2fb9 Mon Sep 17 00:00:00 2001 From: Axel Schnitger <axel.schnitger@aei.mpg.de> Date: Thu, 8 Jun 2017 11:21:11 +0200 Subject: [PATCH] Fixed typos. --- Ri2e.m | 2 +- Ri2srf.m | 2 +- 2 files changed, 2 insertions(+), 2 deletions(-) diff --git a/Ri2e.m b/Ri2e.m index 5193b7f..e515cdd 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 bda4502..5d3757c 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) -- GitLab