From bcd3f3d9a120999a0a5f180818b961a6fc0bfdd7 Mon Sep 17 00:00:00 2001
From: Marcodagostino2 <mcdago25@gmail.com>
Date: Fri, 11 Apr 2025 19:13:02 +0200
Subject: [PATCH] [test-9K] Modified autoMatProtubConfig in order to test a 9K
 rocket.

---
 autoMatricesProtub/autoMatProtubConfig.m |  8 ++++----
 autoMatricesProtub/mainAutoMatProtub.m   |  1 +
 simulator/simulatorConfig.m              | 10 +++++-----
 3 files changed, 10 insertions(+), 9 deletions(-)

diff --git a/autoMatricesProtub/autoMatProtubConfig.m b/autoMatricesProtub/autoMatProtubConfig.m
index 3dc509dc..e6312853 100644
--- a/autoMatricesProtub/autoMatProtubConfig.m
+++ b/autoMatricesProtub/autoMatProtubConfig.m
@@ -24,19 +24,19 @@ set(groot,'defaultLegendInterpreter','latex');
 
 %% STATES
 % State values in which the aerodynamic coefficients will be computed
-vars.mach = 0.05:0.05:1;
+vars.mach = 0.1:0.1:1.6;
 vars.alpha = [-22 -15 -10 -7.5 -5 -2.5 -1 -0.5 -0.1 0 0.1 0.5 1 2.5 5 7.5 10 15 22];
 vars.beta = [-13 -8 -5 -2.5 -0.1 0 0.1 2.5 5 8 13];
-vars.alt = (0:400:4000);         % above local ground (env.z0 will be added in main)
+vars.alt = (0:1000:10000);         % above local ground (env.z0 will be added in main)
 
 % xcg discretization
 vars.Nxcg = 3;                   % Number of wanted xcgs in order to generate N aerodynamic matrices
 
 %% HIGH AOA
-varsHighAOA.mach = 0.05:0.05:0.7;
+varsHighAOA.mach = 0.1:0.1:1.4;
 varsHighAOA.alpha = [-170 -130 -115 -90.1 -60 -35 -10 -5 -1 0 1 5 10 35 60 90.1 115 130 170];
 varsHighAOA.beta  = [-170 -130 -115 -90.1 -60 -35 -10 -5 -1 0 1 5 10 35 60 90.1 115 130 170];
-varsHighAOA.alt = (0:400:4000);  % above local ground (env.z0 will be added in main)
+varsHighAOA.alt = (0:1000:10000);  % above local ground (env.z0 will be added in main)
 
 %% FINS CN partial output
 saveFinsCN = false;
\ No newline at end of file
diff --git a/autoMatricesProtub/mainAutoMatProtub.m b/autoMatricesProtub/mainAutoMatProtub.m
index 5dcd6e0d..5257e59a 100644
--- a/autoMatricesProtub/mainAutoMatProtub.m
+++ b/autoMatricesProtub/mainAutoMatProtub.m
@@ -37,6 +37,7 @@ end
 %% CHOICE OF NUMBER OF XCG
 timeXcgTotal = rocket.motor.time;
 xcgTotal = rocket.xcg;
+nXcg = autoMatSettings.vars.Nxcg;
 
 if nXcg == 1
     chosenXcg = xcgTotal(1);
diff --git a/simulator/simulatorConfig.m b/simulator/simulatorConfig.m
index bd5af2b6..9d540798 100644
--- a/simulator/simulatorConfig.m
+++ b/simulator/simulatorConfig.m
@@ -10,14 +10,14 @@
 % SPDX-License-Identifier: GPL-3.0-or-later
 
 %% SIMULATION FLAGS
-simulator.parafoil = true;         % True if parafoil open loop descent needs to be performed
+simulator.parafoil = false;         % True if parafoil open loop descent needs to be performed
 % simulator.descent6DOF = false;    % True in order to start a 6DOF parachute descent phase
-simulator.ballistic = false;         % True to run a ballistic (without parachutes) simulation
+simulator.ballistic = true;         % True to run a ballistic (without parachutes) simulation
 
 % NOTE: airbrakes flag is set in rocketConfig
 %% PLOTS
 simulator.prints = false;           % True to print data after simulation
-simulator.plots = false;            % True to plot data after simulation
-simulator.landingMap = true;        % True to run geoplots
+simulator.plots = true;            % True to plot data after simulation
+simulator.landingMap = false;        % True to run geoplots
 simulator.satellite3D = false;      % True to plot trajectory on 3D map
-simulator.SMonly = true;            % True to plot only SM (useful during design!)
\ No newline at end of file
+simulator.SMonly = false;            % True to plot only SM (useful during design!)
\ No newline at end of file
-- 
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