diff --git a/aerodynamicsOptimization/mainOptimization.m b/aerodynamicsOptimization/mainOptimization.m
index ad493fb45b2c5176bdb19f43a263f2ca61bd277a..c541bc760bd6831eb12a4a888e528bb62448adca 100644
--- a/aerodynamicsOptimization/mainOptimization.m
+++ b/aerodynamicsOptimization/mainOptimization.m
@@ -141,7 +141,7 @@ vars.mach = 0.1:0.2:0.9;
vars.alpha = [-20 -15 -10 -5 -2.5 -1 -0.1 0 0.1 1 2.5 5 10 15 20];
vars.beta = [-20 -15 -10 -5 -2.5 -1 -0.1 0 0.1 1 2.5 5 10 15 20];
vars.alt = environment.z0 + (0:1000:4000);
-vars.xcg = rocket.xCg;
+vars.xcg = rocket.xcg;
vars.hprot = [];
% vars.hprot = rocket.airbrakes.height;
diff --git a/aerodynamicsOptimization/src/OptimizationGA.m b/aerodynamicsOptimization/src/OptimizationGA.m
index 69a43fd8b6f69ae33892ad4ed7974d9cc32381ff..ffd593901e6d265ddce180c8eb74692b1eca9ca8 100644
--- a/aerodynamicsOptimization/src/OptimizationGA.m
+++ b/aerodynamicsOptimization/src/OptimizationGA.m
@@ -49,7 +49,7 @@ input.fltcon.NALPHA = length(input.fltcon.ALPHA); % [-] Number of alphas
input.fltcon.NMACH = length(input.fltcon.MACH);
%%% aerodynmics coefficient - full
-input.refq.XCG = rocket.xCg([1, length(rocket.xCg)]);
+input.refq.XCG = rocket.xcg([1, length(rocket.xcg)]);
% state.xcgTime = state.xcgTime([1, end]);
input.flagXCP = false;
[coeff] = dissileMatcom(input);
diff --git a/aerodynamicsOptimization/src/XCPcheck.m b/aerodynamicsOptimization/src/XCPcheck.m
index a07bb62d0928025bab0a7db7778fb016cb9eaca7..da16982b84ce406067fb6657bbfe1809982cd197 100644
--- a/aerodynamicsOptimization/src/XCPcheck.m
+++ b/aerodynamicsOptimization/src/XCPcheck.m
@@ -106,7 +106,7 @@ nCases = length(launchpad.indexAlpha);
%%% both lateral and longitudinal XCP involved
% the launchpad dynamics is used to write the aerodynamics states
-xcg = rocket.xCg;
+xcg = rocket.xcg;
%%% aerodynamics coefficient @launchpad exit only
diff --git a/autoMatricesProtub/mainAutoMatProtub.m b/autoMatricesProtub/mainAutoMatProtub.m
index ad85f77314cd2613799be1050520bcfbee2865a7..ba18176b90822310ccdaaed54fa0d027b1bdf7e2 100644
--- a/autoMatricesProtub/mainAutoMatProtub.m
+++ b/autoMatricesProtub/mainAutoMatProtub.m
@@ -36,8 +36,7 @@ end
%% CHOICE OF NUMBER OF XCG
timeXcgTotal = rocket.motor.time;
-xcgTotal = rocket.xCg;
-nXcg = autoMatSettings.vars.Nxcg;
+xcgTotal = rocket.xcg;
if nXcg == 1
chosenXcg = xcgTotal(1);
@@ -76,7 +75,7 @@ end
tic
%% COMPUTE HIGH AOA AERODYNAMIC COEFFICIENTS
-autoMatSettings.varsHighAOA.xcg = rocket.xCg(end);
+autoMatSettings.varsHighAOA.xcg = rocket.xcg(end);
if length(autoMatSettings.varsHighAOA.alpha) > 20 || ...
length(autoMatSettings.varsHighAOA.mach) > 20
error("automatrices with Dissile and alpha/mach" + ...
diff --git a/common b/common
index 7589b2690bf66066247dd1236f27eb2ee7c52cbd..bc61b5b9265bde0f30dfc53db0bf5820e3c69b04 160000
--- a/common
+++ b/common
@@ -1 +1 @@
-Subproject commit 7589b2690bf66066247dd1236f27eb2ee7c52cbd
+Subproject commit bc61b5b9265bde0f30dfc53db0bf5820e3c69b04
diff --git a/sensitivityAnalysis/src/stochParameters/initParameter.m b/sensitivityAnalysis/src/stochParameters/initParameter.m
index 1d9db0add415adba11358e2d106ba17337477bc3..f00667535ec5a68b704a5e237a045ec0ce22df05 100644
--- a/sensitivityAnalysis/src/stochParameters/initParameter.m
+++ b/sensitivityAnalysis/src/stochParameters/initParameter.m
@@ -86,7 +86,7 @@ for i = 1:length(parameters)
parameters(i).value = rocket.lengthCenter;
parameters(i).udm = 'm';
case 'centerOfMass'
- parameters(i).value = rocket.xCg;
+ parameters(i).value = rocket.xcg;
parameters(i).udm = 'm';
case 'finsRootChord'
parameters(i).value = rocket.rear.finsRootChord;
diff --git a/sensitivityAnalysis/src/stochParameters/updateData.m b/sensitivityAnalysis/src/stochParameters/updateData.m
index e6e858eb13715fbac02489e0843c42070f490253..f36cefd6e7ecf7ee69674f3c1a4ecd24e9defdb0 100644
--- a/sensitivityAnalysis/src/stochParameters/updateData.m
+++ b/sensitivityAnalysis/src/stochParameters/updateData.m
@@ -83,7 +83,7 @@ for i = 1:length(parameters)
case 'rocketLCenter'
rocket.lengthCenter = value;
case 'centerOfMass'
- rocket.xCg = value;
+ rocket.xcg = value;
case 'finsRootChord'
rocket.rear.finsRootChord = value;
case 'finsFreeChord'
diff --git a/stabilityAnalysis/mainStabilityAnalysis.m b/stabilityAnalysis/mainStabilityAnalysis.m
index 28208bb1299ae3d8e63dafe8aa8491b0edd0eee7..1fc32daafebb97c85a167bca9ed97ec50e40177d 100644
--- a/stabilityAnalysis/mainStabilityAnalysis.m
+++ b/stabilityAnalysis/mainStabilityAnalysis.m
@@ -50,7 +50,7 @@ if isempty(settings), settings = Settings('stabilityAnalysis', 'ode'); end
% Settings.read(settings, options, 'stability');
settings.stability.dissile.alt = environment.z0;
-settings.stability.dissile.xcg = rocket.xCg(1);
+settings.stability.dissile.xcg = rocket.xcg(1);
%% LAUNCHPAD DYNAMICS
% states to compute the exit pad velocity
@@ -73,7 +73,7 @@ solution = ode113(@ballistic, [0, 10], Y0, options, ...
vExit = solution.y(4, end);
machExit = vExit/a;
settings.stability.dissile.fltcon.MACH = machExit; % Mach @launchpad
-settings.stability.dissile.refq.XCG = interpLinear(rocket.motor.time, rocket.xCg, solution.x(end));
+settings.stability.dissile.refq.XCG = interpLinear(rocket.motor.time, rocket.xcg, solution.x(end));
settings.stability.dissile.fltcon.ALT = environment.z0; % Altitude @launchpad
diff --git a/utils/rocketpyData/exportRocketpy.m b/utils/rocketpyData/exportRocketpy.m
index 14af13de3f524454412c7a65f845983c5286ecfb..c7dc066a46824cfa82b00d4a5839e7da505a24a9 100644
--- a/utils/rocketpyData/exportRocketpy.m
+++ b/utils/rocketpyData/exportRocketpy.m
@@ -35,34 +35,34 @@ CA_3 = squeeze(cat(3, rocket.coefficients.total(1, alpha0, 1:iOpen, beta0, 1, 3,
rocket.coefficients.total(1, alpha0, iOpen+1:end, beta0, 1, 1, 1)));
%% bays details
-total_center_of_mass = rocket.xCg(end);
+total_center_of_mass = rocket.xcg(end);
rocket_mass = rocket.massNoMotor;
rocket_center_of_mass = rocket.xCgNoMotor;
booster_mass = rocket.stagesMass(1);
payload_mass = rocket.stagesMass(2);
-booster_center_of_mass = ((rocket.parafoil.noseLength + rocket.xCg(end))*rocket.mass(end) ...
- - rocket.parafoil.xCg*rocket.parafoil.mass)/rocket.stagesMass(1) - rocket.parafoil.length;
-payload_center_of_mass = rocket.parafoil.xCg;
+booster_center_of_mass = ((rocket.parafoil.noseLength + rocket.xcg(end))*rocket.mass(end) ...
+ - rocket.parafoil.xcg*rocket.parafoil.mass)/rocket.stagesMass(1) - rocket.parafoil.length;
+payload_center_of_mass = rocket.parafoil.xcg;
% parafoil
mPld = rocket.parafoil.mass;
lPld = rocket.parafoil.length;
-xcgPld = rocket.parafoil.xCg;
+xcgPld = rocket.parafoil.xcg;
% recovery
mRcs = rocket.recovery.mass;
lRcs = rocket.recovery.length;
-xcgRcs = rocket.recovery.xCg;
+xcgRcs = rocket.recovery.xcg;
% electronics
mElc = rocket.electronics.mass;
lElc = rocket.electronics.length;
-xcgElc = rocket.electronics.xCg;
+xcgElc = rocket.electronics.xcg;
% airbrakes
mArb = rocket.airbrakes.mass;
lArb = rocket.airbrakes.length;
-xcgArb = rocket.airbrakes.xCg;
+xcgArb = rocket.airbrakes.xcg;
% motor
propMass = rocket.motor.propellantMass;
@@ -70,7 +70,7 @@ usedPropMass = propMass - propMass(end);
time = rocket.motor.time;
propMassDot = diff(usedPropMass)./diff(time);
propMassDot(end + 1) = propMassDot(end);
-propCG = (rocket.xCg.*(usedPropMass + total_center_of_mass) - total_center_of_mass*total_center_of_mass)./usedPropMass;
+propCG = (rocket.xcg.*(usedPropMass + total_center_of_mass) - total_center_of_mass*total_center_of_mass)./usedPropMass;
propCG(end) = propCG(end - 1);
propCG = propCG - rocket.absolutePositions("motor");
burn_time = time(end);
@@ -78,15 +78,15 @@ thrust = rocket.motor.thrust;
motor_dry_mass = rocket.motor.structureMass;
lMot = rocket.motor.length;
-xcgMotWet = rocket.motor.xCg;
+xcgMotWet = rocket.motor.xcg;
motor_center_of_dry_mass = 1/rocket.motor.structureMass *...
- (rocket.motor.xCg(1) * (rocket.motor.structureMass + rocket.motor.propellantMass(1)) - ...
+ (rocket.motor.xcg(1) * (rocket.motor.structureMass + rocket.motor.propellantMass(1)) - ...
rocket.motor.propellantMass(1) * propCG(1));
% rear (fins + fincan + boat, it overlaps with motor)
mRear = rocket.rear.mass;
lRear = rocket.rear.length;
-xcgRear = rocket.rear.xCg;
+xcgRear = rocket.rear.xcg;
%% inertia details
% inertia without motor
@@ -96,9 +96,9 @@ rocket_I_33 = rocket.inertiaNoMotor(1);
% propellant inertia
prop_I_11 = (rocket.inertia(2, :) - rocket.inertia(2, end)) - ...
- usedPropMass .* (rocket.xCg - (rocket.absolutePositions("motor") + propCG)).^2;
+ usedPropMass .* (rocket.xcg - (rocket.absolutePositions("motor") + propCG)).^2;
prop_I_22 = (rocket.inertia(3, :) - rocket.inertia(3, end)) - ...
- usedPropMass .* (rocket.xCg - (rocket.absolutePositions("motor") + propCG)).^2;
+ usedPropMass .* (rocket.xcg - (rocket.absolutePositions("motor") + propCG)).^2;
prop_I_33 = (rocket.inertia(1, :) - rocket.inertia(1, end));
% motor inertia
@@ -114,10 +114,10 @@ motor_I_33_dry = motor_I_33(1) - prop_I_33(1);
% booster inertia
deltaDistance = rocket.absolutePositions("parafoil") + rocket.parafoil.length;
-booster_I_11 = rocket.inertia(2, end) + rocket.mass(end) * (rocket.xCg(end) - deltaDistance - booster_center_of_mass)^2 - ...
- (rocket.parafoil.inertia(2, end) + rocket.parafoil.mass * (rocket.parafoil.length - rocket.parafoil.xCg + booster_center_of_mass)^2);
-booster_I_22 = rocket.inertia(3, end) + rocket.mass(end) * (rocket.xCg(end) - deltaDistance - booster_center_of_mass)^2 - ...
- (rocket.parafoil.inertia(3, end) + rocket.parafoil.mass * (rocket.parafoil.length - rocket.parafoil.xCg + booster_center_of_mass)^2);
+booster_I_11 = rocket.inertia(2, end) + rocket.mass(end) * (rocket.xcg(end) - deltaDistance - booster_center_of_mass)^2 - ...
+ (rocket.parafoil.inertia(2, end) + rocket.parafoil.mass * (rocket.parafoil.length - rocket.parafoil.xcg + booster_center_of_mass)^2);
+booster_I_22 = rocket.inertia(3, end) + rocket.mass(end) * (rocket.xcg(end) - deltaDistance - booster_center_of_mass)^2 - ...
+ (rocket.parafoil.inertia(3, end) + rocket.parafoil.mass * (rocket.parafoil.length - rocket.parafoil.xcg + booster_center_of_mass)^2);
booster_I_33 = rocket.inertia(1, end) - rocket.parafoil.inertia(1, end);
% parafoil inertia