diff --git a/classes/components/Environment.m b/classes/components/Environment.m
index 7ee1a91d3532686e58dbb53ce4c369a3f1e907ca..c0c5cd98a47f9a85b479ae6a64526dc10db4d427 100644
--- a/classes/components/Environment.m
+++ b/classes/components/Environment.m
@@ -28,7 +28,9 @@ classdef Environment < Component
     end
 
     properties(SetAccess = private)
-        g0                      double        % [-] Gravity costant at launch latitude and altitude
+        g0                      double        % [-] Gravity costant at launch latitude and z = 0m
+        g0Centrifugal           double        % [m/s^2] Gravity due to earth rotation at launch latitude and z = 0m
+        earthRadius             double        % [m] Radius used for g computation
         local                   double        % [-] Vector conatining inputs for atmosphereData
         pinDistance             double        % [m] Distance of the upper pin from the rail base (upper pin-boat + boat-rail base)
         effectiveRampLength     double        % [m] Total launchpad length
@@ -64,6 +66,8 @@ classdef Environment < Component
     methods
         function updateAll(obj)
             obj.updateG0;
+            obj.updateG0Centrifugal;
+            obj.updateEarthRadius;
             obj.updatePinDistance;
             obj.updateRamp;
             obj.updateLocal;
@@ -76,7 +80,30 @@ classdef Environment < Component
         end
 
         function obj = updateG0(obj)
-            obj.g0 = gravitywgs84(obj.z0, obj.lat0);
+            if(~isempty(obj.lat0))
+                obj.g0 = gravitywgs84(0, obj.lat0);
+            end
+        end
+
+        function obj = updateG0Centrifugal(obj)
+            if(~isempty(obj.lat0))
+                earthOmega = 2*pi/86164;                                    % [rad/s] Earth angular velocity 
+                aEarth = 6378122;                                           % [m] Earth semi major axis (radius at the equator)
+                eEarth = 0.08182;                                           % [/] Earth's ellipsoid eccentricity
+                lat0rad = deg2rad(obj.lat0);
+                obj.g0Centrifugal = - earthOmega^2 * aEarth * ((cos(lat0rad)^2)/(sqrt(1 - eEarth^2*(sin(lat0rad)^2))));
+            end
+        end
+
+        function obj = updateEarthRadius(obj)
+            if(~isempty(obj.lat0))
+                earthOmega = 2*pi/86164;
+                R0 = 6370000;
+                lat0rad = deg2rad(obj.lat0);
+                mu = 3.986e14;                                              % [m^3/s^2] Earth's gravitational constant (GM)
+                f = @(R) obj.g0 - (mu/(R^2)) + earthOmega^2*R*(cos(lat0rad)^2);
+                obj.earthRadius = fzero(f, R0);
+            end
         end
 
         function obj = updatePinDistance(obj)
diff --git a/functions/odeFunctions/ballistic.m b/functions/odeFunctions/ballistic.m
index 0194eff2564ba79ba00e30e47181915a47a14891..391f3c366d3b40b5668dae44678659c9e4b7b6ce 100644
--- a/functions/odeFunctions/ballistic.m
+++ b/functions/odeFunctions/ballistic.m
@@ -58,7 +58,11 @@ dY = zeros(14, 1);
 %% GETTING DATA
 S = rocket.crossSection;                                                    % [m^2]   cross surface
 C = rocket.diameter;                                                        % [m]     caliber
-g = environment.g0/(1 + (altitude*1e-3/6371))^2;                            % [N/kg]  module of gravitational field
+earthOmega = 2*pi/86164;                                                    % [rad/s] Earth's angular velocity
+g = (environment.g0 - environment.g0Centrifugal)/...
+    ((1 + ((altitude + environment.z0)/environment.earthRadius))^2) + ...
+    environment.g0Centrifugal - earthOmega^2*...
+    (altitude + environment.z0)*(cos(environment.lat0*pi/180)^2);           % [N/kg]  module of gravitational field
 tb = rocket.motor.cutoffTime;                                               % [s]     Burning Time
 theta = t-t0;                                                               % [s]     Time shift (needed for control)
 local = environment.local;                                                  % vector containing inputs for atmosphereData