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
--
GitLab