diff --git a/classes/@Rocket/Rocket.m b/classes/@Rocket/Rocket.m
index 825e8360ef8caa2d09ce9628731c6f6616e89d73..30c76a48b95e72217938671ddc07ed5db368dd17 100644
--- a/classes/@Rocket/Rocket.m
+++ b/classes/@Rocket/Rocket.m
@@ -52,7 +52,8 @@ classdef Rocket < Config
parachutes cell % [-] (nParachutes, nStages) Parachutes onboard
dynamicDerivatives (1, 1) logical % [-] True if dynamic derivatives will be loaded
-
+ highAOACoefficients (1, 1) logical % [-] True if highAOACoefficients are loaded
+
coefficients Coefficient % [-] Aerodynamic coefficients
coefficientsHighAOA Coefficient % [-] Aerodynamic coefficients at high angle of attack
end
@@ -150,13 +151,16 @@ classdef Rocket < Config
fullfile(mission.dataPath, 'aeroCoefficients.mat'), ...
coeffName);
- obj.coefficientsHighAOA = Coefficient( ...
- fullfile(mission.dataPath, 'aeroCoefficientsHighAOA.mat'), ...
- coeffName);
+ if obj.highAOACoefficients
+ obj.coefficientsHighAOA = Coefficient( ...
+ fullfile(mission.dataPath, 'aeroCoefficientsHighAOA.mat'), ...
+ coeffName);
+ end
answer = '';
- if isempty(obj.coefficients.static) || isempty(obj.coefficientsHighAOA.static)
+ if isempty(obj.coefficients.static) || ...
+ (obj.highAOACoefficients && isempty(obj.coefficientsHighAOA.static))
answer = questdlg(['Coefficient matrices not found. ' ...
'Do you want to create new matrices?']);
elseif options.checkGeometry
@@ -195,7 +199,7 @@ classdef Rocket < Config
parserPath = fullfile(mission.msaPath, 'autoMatricesProtub');
addpath(genpath(parserPath));
[obj.coefficients, obj.coefficientsHighAOA] = ...
- mainAutoMatProtub(obj);
+ mainAutoMatProtub(obj, 'computeHighAOA', obj.highAOACoefficients);
case 'Cancel'
error('Rocket creation aborted')
otherwise
diff --git a/classes/enums/CoeffType.m b/classes/enums/CoeffType.m
new file mode 100644
index 0000000000000000000000000000000000000000..85e051cba449a53e81cbc4661ab2025987e83284
--- /dev/null
+++ b/classes/enums/CoeffType.m
@@ -0,0 +1,7 @@
+classdef CoeffType
+ enumeration
+ AlphaTotPhi
+ AlphaBeta
+ end
+end
+
diff --git a/classes/bays/MotorType.m b/classes/enums/MotorType.m
similarity index 100%
rename from classes/bays/MotorType.m
rename to classes/enums/MotorType.m
diff --git a/classes/misc/Coefficient.m b/classes/misc/Coefficient.m
index f7eb51b09518ae3395228fd0af572ef5f7ac421e..219bca89f335199a1d25633b8622f4105ac6cb97 100644
--- a/classes/misc/Coefficient.m
+++ b/classes/misc/Coefficient.m
@@ -58,10 +58,12 @@ classdef Coefficient
dynamic double % Dynamic derivatives: [Clp, Cmad, Cmq, Cnr, Cnp]
end
-
properties(SetAccess = private)
- isReady (1, 1) logical % Whether all coefficients are loaded and of the right size
- isDynamic (1, 1) logical % Whether to load dynamic derivatives. Adds XCG dependece
+ type CoeffType % Wheter based on alphaTot-phi or alpha-beta
+ symmetry (1, 1) logical % Apply axial simmetry: valid for alphaTot-phi
+
+ isReady (1, 1) logical % Whether all coefficients are loaded and of the right size
+ isDynamic (1, 1) logical % Whether to load dynamic derivatives. Adds XCG dependece
end
properties(Access = private)
@@ -89,7 +91,7 @@ classdef Coefficient
obj = obj.updateInterpolants();
end
- function coefficients = get(obj, alpha, mach, beta, altitude, airbakes, xcg)
+ function [coefficients] = get(obj, alpha, mach, beta, altitude, airbakes, xcg)
% GET: Retrieve aerodynamic coefficients for specified flight conditions
%
% This method interpolates the aerodynamic coefficients based on
@@ -114,10 +116,31 @@ classdef Coefficient
if ~obj.isReady, error('Cannot interpolate coefficients: check that all dimensions match'); end
+ % Interpolating coefficients
coefficients = zeros(11, 1);
- coefficients(1:6) = obj.staticInterpolant(alpha, mach, beta, altitude, airbakes);
- % Transporting static coefficients to new xcg
+ if obj.type == CoeffType.AlphaBeta
+ coefficients(1:6) = obj.staticInterpolant(alpha, mach, beta, altitude, airbakes);
+ else
+ [alphaTot, phi] = getAlphaPhi(alpha, beta);
+ phi = wrapTo2Pi(phi);
+
+ finAngle = 2*pi / obj.GEOMETRY.nPanel; % Angle between two fin panels
+ n = floor(phi / finAngle);
+ deltaPhi = n*finAngle;
+ psi = phi - deltaPhi; % Angle wrapped to finAngle
+
+ coefficients(1:6) = obj.staticInterpolant(alphaTot, mach, psi, altitude, airbakes); % Get coeffs in limited range
+
+ if n > 0 % If necessary, perform rotation on different frame
+ R = [cos(deltaPhi), -sin(deltaPhi);
+ sin(deltaPhi), cos(deltaPhi)];
+
+ coefficients([2, 3]) = R * coefficients([2, 3]);
+ coefficients([5, 6]) = R' * coefficients([5, 6]);
+ end
+ end
+ % Transporting static coefficients to new xcg
% C_B = C_A + d / c * [0; -CN; CY]_A <- NOTE: Non torna il meno su CN
d = xcg - obj.GEOMETRY.xcg(1);
l = obj.GEOMETRY.diameter;
@@ -128,6 +151,9 @@ classdef Coefficient
coefficients(4:6) = coefficients(4:6) + d/l * forceCoeffs;
if ~obj.isDynamic, return; end
+ if obj.type == CoeffType.AlphaTotPhi
+ error('Alpha-Phi coefficients do not support dynamic derivatives yet')
+ end
coefficients(7:11) = obj.dynamicInterpolant(alpha, mach, beta, altitude, airbakes, xcg);
end
end
@@ -165,12 +191,28 @@ classdef Coefficient
end
function obj = set.geometry(obj, value)
+ if ~isempty(obj.STATE) && isfield(obj.STATE, 'phis') && ~isempty(obj.STATE.phis)
+ obj.symmetry = (360/obj.STATE.phis(end) == value.nPanel);
+ end
+
obj.GEOMETRY = value;
obj.isReady = obj.checkProperties();
obj = obj.updateInterpolants();
end
function obj = set.state(obj, value)
+ if isfield(value, 'phis') && ~isempty(value.phis)
+ if ~isempty(value.betas)
+ error('Cannot set both alpha, beta and phi');
+ end
+ if ~isempty(obj.GEOMETRY)
+ obj.symmetry = (360/value.phis(end) == obj.GEOMETRY.nPanel);
+ end
+ obj.type = CoeffType.AlphaTotPhi;
+ else
+ obj.type = CoeffType.AlphaBeta;
+ end
+
obj.STATE = value;
obj.isReady = obj.checkProperties();
obj = obj.updateInterpolants();
@@ -198,7 +240,7 @@ classdef Coefficient
obj.finsCN = dataCoeffs.finsCN;
obj.GEOMETRY = dataCoeffs.geometry;
- obj.STATE = dataCoeffs.state;
+ obj.state = dataCoeffs.state;
% Load coefficients
obj.total = dataCoeffs.total;
@@ -214,12 +256,17 @@ classdef Coefficient
alpha = obj.STATE.alphas;
mach = obj.STATE.machs;
- beta = obj.STATE.betas;
altitude = obj.STATE.altitudes;
airbakes = obj.STATE.hprot;
xcg = obj.GEOMETRY.xcg;
- gridVecs = {alpha, mach, beta, altitude, airbakes, xcg};
+ if obj.type == CoeffType.AlphaBeta
+ theta = obj.STATE.betas; % Converting to rad
+ else
+ theta = obj.STATE.phis; % Converting to rad
+ end
+
+ gridVecs = {alpha, mach, theta, altitude, airbakes, xcg};
dims = cellfun(@(x) length(x), gridVecs);
dims(dims == 0) = 1; % Empty case is the same as scalar case
@@ -233,15 +280,20 @@ classdef Coefficient
%% Retrieve flight conditions
alpha = obj.STATE.alphas*pi/180; % Converting to rad
mach = obj.STATE.machs;
- beta = obj.STATE.betas*pi/180; % Converting to rad
altitude = obj.STATE.altitudes;
xcg = obj.GEOMETRY.xcg;
if isempty(obj.STATE.hprot), airbakes = 0;
else, airbakes = obj.STATE.hprot/obj.STATE.hprot(end); % Normalizing on height
end
+
+ if obj.type == CoeffType.AlphaBeta
+ theta = obj.STATE.betas*pi/180; % Converting to rad
+ else
+ theta = obj.STATE.phis*pi/180; % Converting to rad
+ end
- gridVecs = {alpha, mach, beta, altitude, airbakes, xcg};
+ gridVecs = {alpha, mach, theta, altitude, airbakes, xcg};
% Find singleton dims (last dimension is coefficients and will not be of length 1)
singletonDims = cellfun(@(x) isscalar(x) || isempty(x), gridVecs);
diff --git a/functions/miscellaneous/createDissileInput.m b/functions/miscellaneous/createDissileInput.m
index 39bc2b0b88f53030d739d657bdb7668c3fae7f6f..1c3f5eee6da918539abc97779c31585e5bc65d75 100644
--- a/functions/miscellaneous/createDissileInput.m
+++ b/functions/miscellaneous/createDissileInput.m
@@ -49,12 +49,12 @@ if not(any(vars.alpha == 1))
error('vars.alpha does not contains 1');
end
-if not(any(vars.alpha == -1))
- error('vars.alpha does not contains -1');
+if isempty(vars.phi) && not(any(vars.alpha == -1))
+ error('vars.alpha does not contain -1 in alpha-beta configuration');
end
-if not(isequal(vars.alpha, -fliplr(vars.alpha)))
- error('vars.alpha is not symmetric');
+if isempty(vars.phi) && not(isequal(vars.alpha, -fliplr(vars.alpha)))
+ error('vars.alpha is not symmetric in alpha-beta configuration');
end
% if any(vars.abk > 1)
@@ -69,6 +69,7 @@ input.fltcon.about = 'Flight conditions quantities';
input.fltcon.MACH = vars.mach;
input.fltcon.ALPHA = vars.alpha;
input.fltcon.BETA = vars.beta;
+input.fltcon.PHI = vars.phi;
input.fltcon.ALT = vars.alt;
%% REFQ
diff --git a/functions/odeFunctions/ballistic.m b/functions/odeFunctions/ballistic.m
index d08b3069d7274836e0f686c19963919facaec233..fed5600a547105015d3835c998120ef8accf7f44 100644
--- a/functions/odeFunctions/ballistic.m
+++ b/functions/odeFunctions/ballistic.m
@@ -134,7 +134,7 @@ end
if not(abs(ur) < 1e-9 || velsNorm < 1e-9)
alpha = atan(wr/ur);
beta = atan(vr/ur); % beta = asin(vr/V_norm) is the classical notation, Datcom uses this one though.
- % alpha_tot = atan(sqrt(wr^2 + vr^2)/ur); % datcom 97' definition
+ alphaTot = atan(sqrt(wr^2 + vr^2)/ur); % datcom 97' definition
else
alpha = 0;
beta = 0;
@@ -144,14 +144,17 @@ alphaOut = alpha;
betaOut = beta;
%% INTERPOLATE AERODYNAMIC COEFFICIENTS:
-
-if abs(alpha) > rocket.coefficients.state.alphas(end)*pi/180 || ...
- abs(beta) > rocket.coefficients.state.betas(end)*pi/180
- coeffsValues = rocket.coefficientsHighAOA.get(alpha, mach, beta, absoluteAltitude, extension, xcg);
+if rocket.coefficients.type == CoeffType.AlphaBeta
+ if abs(alpha) > rocket.coefficients.state.alphas(end)*pi/180 || abs(beta) > rocket.coefficients.state.betas(end)*pi/180
+ coeffsValues = rocket.coefficientsHighAOA.get(alpha, mach, beta, absoluteAltitude, extension, xcg);
+ end
+elseif abs(alphaTot) > rocket.coefficients.state.alphas(end)*pi/180
+ coeffsValues = rocket.coefficientsHighAOA.get(alpha, mach, beta, absoluteAltitude, extension, xcg);
else
coeffsValues = rocket.coefficients.get(alpha, mach, beta, absoluteAltitude, extension, xcg);
end
+
% Retrieve Coefficients
CA = coeffsValues(1); CY = coeffsValues(2); CN = coeffsValues(3);
Cl = coeffsValues(4); Cm = coeffsValues(5); Cn = coeffsValues(6);
diff --git a/missions/2021_Lynx_Portugal_October/config/rocketConfig.m b/missions/2021_Lynx_Portugal_October/config/rocketConfig.m
index 160c5b09b850ef81406e13cf89dfcda9005c2e9c..cb264015ae392fd9ed08b661398f6b5efb8f1d2e 100644
--- a/missions/2021_Lynx_Portugal_October/config/rocketConfig.m
+++ b/missions/2021_Lynx_Portugal_October/config/rocketConfig.m
@@ -20,6 +20,7 @@ rocket.lengthCenterNoMot = 1.7640; % [m]
% When false, coefficients are saved with current motor's name
% When true, coefficients are saved as 'generic'
rocket.dynamicDerivatives = false; % [-] True if dynamic derivatives will be loaded
+rocket.highAOACoefficients = false; % [-] True if separate matrix for high AOA will be loaded
%% PLD - Includes Parafoil + Nose
parafoil = Parafoil();
diff --git a/missions/2021_Lynx_Roccaraso_September/config/rocketConfig.m b/missions/2021_Lynx_Roccaraso_September/config/rocketConfig.m
index d0dc3df55356e3aebc59d51214a30794f8668dc1..0851f94e15aa603fff564f4dd2d8ed15c0e56bf8 100644
--- a/missions/2021_Lynx_Roccaraso_September/config/rocketConfig.m
+++ b/missions/2021_Lynx_Roccaraso_September/config/rocketConfig.m
@@ -20,6 +20,7 @@ rocket.lengthCenterNoMot = 1.7840; % [m]
% When false, coefficients are saved with current motor's name
% When true, coefficients are saved as 'generic'
rocket.dynamicDerivatives = false; % [-] True if dynamic derivatives will be loaded
+rocket.highAOACoefficients = false; % [-] True if separate matrix for high AOA will be loaded
%% PLD - Includes Parafoil + Nose
parafoil = Parafoil();
diff --git a/missions/2022_Pyxis_Portugal_October/config/rocketConfig.m b/missions/2022_Pyxis_Portugal_October/config/rocketConfig.m
index 2f949bfb46c9b09dd02fea6a1c87253e9c6c5b20..17d63ca520136746a7f874cb8e2d9c34c726670b 100644
--- a/missions/2022_Pyxis_Portugal_October/config/rocketConfig.m
+++ b/missions/2022_Pyxis_Portugal_October/config/rocketConfig.m
@@ -20,6 +20,7 @@ rocket.lengthCenterNoMot = 1.4470; % [m]
% When false, coefficients are saved with current motor's name
% When true, coefficients are saved as 'generic'
rocket.dynamicDerivatives = false; % [-] True if dynamic derivatives will be loaded
+rocket.highAOACoefficients = false; % [-] True if separate matrix for high AOA will be loaded
%% PLD - Includes Parafoil + Nose
parafoil = Parafoil();
diff --git a/missions/2022_Pyxis_Roccaraso_September/config/rocketConfig.m b/missions/2022_Pyxis_Roccaraso_September/config/rocketConfig.m
index ee3a3c71bd73ab263db92f3e929db488a6a5735c..5b7406a3e5a8362c54c1caddde3a35c9fa1798cc 100644
--- a/missions/2022_Pyxis_Roccaraso_September/config/rocketConfig.m
+++ b/missions/2022_Pyxis_Roccaraso_September/config/rocketConfig.m
@@ -22,6 +22,7 @@ rocket.lengthCenterNoMot = 1.61; % [m]
% When false, coefficients are saved with current motor's name
% When true, coefficients are saved as 'generic'
rocket.dynamicDerivatives = false; % [-] True if dynamic derivatives will be loaded
+rocket.highAOACoefficients = false; % [-] True if separate matrix for high AOA will be loaded
%% PLD - Includes Parafoil + Nose
parafoil = Parafoil();
diff --git a/missions/2023_Gemini_Portugal_October/config/rocketConfig.m b/missions/2023_Gemini_Portugal_October/config/rocketConfig.m
index 401c415be5e782af00b4318e62db4d13ea6ef5ca..f9d6d4c6f95e6d93445e6289d5115b9bba35837a 100644
--- a/missions/2023_Gemini_Portugal_October/config/rocketConfig.m
+++ b/missions/2023_Gemini_Portugal_October/config/rocketConfig.m
@@ -19,7 +19,7 @@ rocket.lengthCenterNoMot = 1.517; % [m]
% When false, coefficients are saved with current motor's name
% When true, coefficients are saved as 'generic'
rocket.dynamicDerivatives = false; % [-] True if dynamic derivatives will be loaded
-
+rocket.highAOACoefficients = false; % [-] True if separate matrix for high AOA will be loaded
%% PLD - Includes Parafoil + Nose
parafoil = Parafoil();
diff --git a/missions/2023_Gemini_Roccaraso_September/config/rocketConfig.m b/missions/2023_Gemini_Roccaraso_September/config/rocketConfig.m
index fc2715bc0dd7d61dd740e20b3138c8552440dcf1..cadbc7ef2b84f7f504eae85f73766ece8a83ec9c 100644
--- a/missions/2023_Gemini_Roccaraso_September/config/rocketConfig.m
+++ b/missions/2023_Gemini_Roccaraso_September/config/rocketConfig.m
@@ -19,6 +19,7 @@ rocket.lengthCenterNoMot = 1.517; % [m]
% When false, coefficients are saved with current motor's name
% When true, coefficients are saved as 'generic'
rocket.dynamicDerivatives = false; % [-] True if dynamic derivatives will be loaded
+rocket.highAOACoefficients = false; % [-] True if separate matrix for high AOA will be loaded
%% PLD - Includes Parafoil + Nose
parafoil = Parafoil();
diff --git a/missions/2024_Lyra_Portugal_October/config/rocketConfig.m b/missions/2024_Lyra_Portugal_October/config/rocketConfig.m
index f87640c176ca52f0ab3274f1b32602462a1489ff..1d90d15565d46515b3ca9ef5bcc7677b369fd810 100644
--- a/missions/2024_Lyra_Portugal_October/config/rocketConfig.m
+++ b/missions/2024_Lyra_Portugal_October/config/rocketConfig.m
@@ -13,6 +13,7 @@ rocket.lengthCenterNoMot = []; % [m]
% When false, coefficients are saved with current motor's name
% When true, coefficients are saved as 'generic'
rocket.dynamicDerivatives = false; % [-] True if dynamic derivatives will be loaded
+rocket.highAOACoefficients = false; % [-] True if separate matrix for high AOA will be loaded
%% PLD - Includes Parafoil + Nose
parafoil = Parafoil();
diff --git a/missions/2024_Lyra_Roccaraso_September/config/rocketConfig.m b/missions/2024_Lyra_Roccaraso_September/config/rocketConfig.m
index 2939db0ce6550575817cdd355d8b2f6ca2e68943..133be74e22c422360b80e924c6fb291a147c61db 100644
--- a/missions/2024_Lyra_Roccaraso_September/config/rocketConfig.m
+++ b/missions/2024_Lyra_Roccaraso_September/config/rocketConfig.m
@@ -19,6 +19,7 @@ rocket.lengthCenterNoMot = []; % [m]
% When false, coefficients are saved with current motor's name
% When true, coefficients are saved as 'generic'
rocket.dynamicDerivatives = false; % [-] True if dynamic derivatives will be loaded
+rocket.highAOACoefficients = false; % [-] True if separate matrix for high AOA will be loaded
%% PLD - Includes Parafoil + Nose
parafoil = Parafoil();
diff --git a/missions/2025_Orion_Portugal_October/config/environmentConfig.m b/missions/2025_Orion_Portugal_October/config/environmentConfig.m
index a667f90e589c2892f397076c5dff8a46325de11f..4820fb5e013c53054f22b4f9412002d944a7ff8b 100644
--- a/missions/2025_Orion_Portugal_October/config/environmentConfig.m
+++ b/missions/2025_Orion_Portugal_October/config/environmentConfig.m
@@ -11,7 +11,7 @@ environment.omega = 85*pi/180; % [deg] Launchpad elevation
environment.phi = 133*pi/180; % [deg] Launchpad azimuth
environment.pin1Length = 0.5603; % [m] Distance from the upper pin to the upper tank cap
environment.pin2Length = 0.2055; % [m] Distance from the lower pin to the lower tank cap
-environment.rampLength = 12; % [m] Total launchpad length
+environment.rampLength = 10; % [m] Total launchpad length
% environment.temperature = []; % [K] Ground temperature correction
% environment.pressure = []; % [Pa] Ground pressure correction
diff --git a/missions/2025_Orion_Portugal_October/config/rocketConfig.m b/missions/2025_Orion_Portugal_October/config/rocketConfig.m
index 6a13ec2512f1ba80b938af94064c3038be076bfd..d47071cd692009e5f9df6998f671e48b73ba8691 100644
--- a/missions/2025_Orion_Portugal_October/config/rocketConfig.m
+++ b/missions/2025_Orion_Portugal_October/config/rocketConfig.m
@@ -12,7 +12,8 @@ rocket.diameter = 0.15; % [m]
% If dynamic derivatives are loaded, coefficient will depend on rocket xcg
% When false, coefficients are saved with current motor's name
% When true, coefficients are saved as 'generic'
-rocket.dynamicDerivatives = false; % [-] True if dynamic derivatives will be loaded
+rocket.dynamicDerivatives = false; % [-] True if dynamic derivatives will be loaded
+rocket.highAOACoefficients = false; % [-] True if separate matrix for high AOA will be loaded
%% PRF - Includes Parafoil + Nose
parafoil = Parafoil();
@@ -74,7 +75,7 @@ airbrakes.servoTau = 0.0374588;
%% MOTOR
motor = Motor();
-motor.name = 'HRE_ARM_EuRoC_2024';
+motor.name = 'HRE_ARM_SFT_2';
motor.cutoffTime = []; % [s] OVERRIDE Cutoff time
motor.ignitionTransient = 0.3; % [s] Ignition transient
diff --git a/missions/2025_Orion_Portugal_October/data/aeroCoefficients.mat b/missions/2025_Orion_Portugal_October/data/aeroCoefficients.mat
index b3c1b232046a3a87cdee3944653945372648719d..3aa85db1d0c630e6edcc2dbcc2e69b32a96925dc 100644
--- a/missions/2025_Orion_Portugal_October/data/aeroCoefficients.mat
+++ b/missions/2025_Orion_Portugal_October/data/aeroCoefficients.mat
@@ -1,3 +1,3 @@
version https://git-lfs.github.com/spec/v1
-oid sha256:75ad0a581c512de8f345a79f16d8e3d2bf681547eb386ce000434c66d6b292e0
-size 288267248
+oid sha256:f4ad48c4d016c33811361e5823e3fb0c87ae64679ff148293e2fcbb48c52f056
+size 300753532
diff --git a/missions/2025_Orion_Portugal_October/data/aeroCoefficientsHighAOA.mat b/missions/2025_Orion_Portugal_October/data/aeroCoefficientsHighAOA.mat
index 9bd98f086dcafb9f9cdb22dcf40d83a9c8ea127d..00d9ce5686896e88b5ebfa31fd23bb911eaa6da2 100644
--- a/missions/2025_Orion_Portugal_October/data/aeroCoefficientsHighAOA.mat
+++ b/missions/2025_Orion_Portugal_October/data/aeroCoefficientsHighAOA.mat
@@ -1,3 +1,3 @@
version https://git-lfs.github.com/spec/v1
-oid sha256:da4a2977b055341314ba88e9698ffbac9702c2e57e9b876c67ea2da01631b783
-size 40438794
+oid sha256:1659d1dc6b19ea13c3cdd75b8f9627d42123c4cb6dff535d93618247a17ab9d1
+size 46224320
diff --git a/missions/2025_Orion_Portugal_October/data/motors.mat b/missions/2025_Orion_Portugal_October/data/motors.mat
index b559afdbe21f341efd934abc7f80827c590d3dcf..679c796c6f3db7766946ec48f5a9adbc8167c206 100644
--- a/missions/2025_Orion_Portugal_October/data/motors.mat
+++ b/missions/2025_Orion_Portugal_October/data/motors.mat
@@ -1,3 +1,3 @@
version https://git-lfs.github.com/spec/v1
-oid sha256:c61e85655bf70ce3494f1f60ceafe391437e566c54e5451cfbcc652a2bf26871
-size 382167
+oid sha256:30f01e10ad8f07a578c9dcbdd18982ffb77eab23057ef003df0f20e51bea5bc2
+size 597957
diff --git a/missions/2025_Orion_Roccaraso_September/config/rocketConfig.m b/missions/2025_Orion_Roccaraso_September/config/rocketConfig.m
index c4e1ffcee38a736e09fe06543010f7699fe3a553..e320c1583c941f7fe5b25b5c54d0a4ee114c5e15 100644
--- a/missions/2025_Orion_Roccaraso_September/config/rocketConfig.m
+++ b/missions/2025_Orion_Roccaraso_September/config/rocketConfig.m
@@ -19,6 +19,7 @@ rocket.lengthCenterNoMot = []; % [m]
% When false, coefficients are saved with current motor's name
% When true, coefficients are saved as 'generic'
rocket.dynamicDerivatives = false; % [-] True if dynamic derivatives will be loaded
+rocket.highAOACoefficients = false; % [-] True if separate matrix for high AOA will be loaded
%% PLD - Includes Parafoil + Nose
parafoil = Parafoil();