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)
-- 
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