diff --git a/missions/2024_Lyra_Portugal_October/config/rocketConfig.m b/missions/2024_Lyra_Portugal_October/config/rocketConfig.m
index 9b88a3d3b8e17eb63ee26a135ec5aee167792a9e..9b7419166b9891f4ed0bbc68232828d3eb6bb486 100644
--- a/missions/2024_Lyra_Portugal_October/config/rocketConfig.m
+++ b/missions/2024_Lyra_Portugal_October/config/rocketConfig.m
@@ -18,32 +18,32 @@ rocket.lengthCenterNoMot = []; % [m]
%% PLD - Includes Payload + Nose
payload = Payload();
-payload.length = 638.89 * 1e-3; % [m] Total bay length
-payload.mass = 4.441; % [kg] Total bay mass
-payload.inertia = 1e-9*[12431765; 106903809; 106823939]; % [kg*m^2] Total bay inertia (Body reference)
-payload.xCg = 479.24 * 1e-3; % [m] Cg relative to bay upper side
+payload.length = 647.25 * 1e-3; % [m] Total bay length
+payload.mass = 4.401; % [kg] Total bay mass
+payload.inertia = 1e-9*[12531966; 109986813; 109930516]; % [kg*m^2] Total bay inertia (Body reference)
+payload.xCg = 487.78 * 1e-3; % [m] Cg relative to bay upper side
payload.noseLength = 0.32; % [m] Nosecone length
payload.noseType = 'MHAACK'; % [-] Nosecone shape
payload.nosePower = 3/4; % [-] Nosecone power type parameter
-payload.nosePMod = 1.291586e+00; % [-] P coefficient for modified nosecone shapes
-payload.noseCMod = 9.272342e-03; % [-] C coefficient for modified nosecone shapes
+payload.nosePMod = 1.250152e+00; % [-] P coefficient for modified nosecone shapes
+payload.noseCMod = 1.799127e-01; % [-] C coefficient for modified nosecone shapes
%% RCS
recovery = Recovery();
-recovery.length = 856 * 1e-3; % [m] Total bay length
+recovery.length = 826 * 1e-3; % [m] Total bay length
recovery.mass = 4.065; % [kg] Total bay mass
recovery.inertia = 1e-9*[13422459; 217223325; 217296702]; % [kg*m^2] Total bay inertia (Body reference)
-recovery.xCg = 564.41 * 1e-3; % [m] Cg relative to bay upper side
+recovery.xCg = 549.41 * 1e-3; % [m] Cg relative to bay upper side
%% ELC
electronics = Electronics();
-electronics.length = 440.5 * 1e-3; % [m] Total bay length
-electronics.mass = 2.474; % [kg] Total bay mass
-electronics.inertia = 1e-9*[8827093; 48462702; 48034980]; % [kg*m^2] Total bay inertia (Body reference)
-electronics.xCg = 231.35 * 1e-3; % [m] Cg relative to bay upper side
+electronics.length = 433.5 * 1e-3; % [m] Total bay length
+electronics.mass = 2.551; % [kg] Total bay mass
+electronics.inertia = 1e-9*[9358415; 49265825; 48770607]; % [kg*m^2] Total bay inertia (Body reference)
+electronics.xCg = 229.9 * 1e-3; % [m] Cg relative to bay upper side
%% ARB
airbrakes = Airbrakes();
@@ -55,7 +55,7 @@ airbrakes.mass = 0.936; % [kg] Tota
airbrakes.inertia = 1e-9*[3086650; 1931082; 1889047]; % [kg*m^2] Total bay inertia (Body reference)
airbrakes.xCg = 30.54 * 1e-3; % [m] Cg relative to bay upper side
-airbrakes.enabled = true; % If true, multiple and smooth airbrakes opening will be simulated
+airbrakes.enabled = false; % If true, multiple and smooth airbrakes opening will be simulated
airbrakes.extension = [1]; % aerobrakes, 1-2-3 for 0%, 50% or 100% opened
airbrakes.deltaTime = [0]; % aerobrakes, configurations usage time
@@ -75,7 +75,7 @@ airbrakes.servoTau = 0.0374588;
%% MOTOR
motor = Motor();
-motor.name = 'HRE_ARM_30_ZK_mass_T0303'; % [-] Motor name
+motor.name = 'HRE_ARM_RU60SFT5'; % [-] Motor name
motor.cutoffTime = []; % [s] OVERRIDE Cutoff time
motor.ignitionTransient = 0.3; % [s] Ignition transient
motor.cutoffTransient = 0.3; % [s] Cut-off transient
@@ -95,7 +95,7 @@ rear.boatFinalDiameter = 0.125; % [m] Boat
rear.finsRootChord = 0.3; % [m] attached chord length
rear.finsFreeChord = 0.12; % [m] free chord length
-rear.finsHeight = 0.13; % [m] fin height
+rear.finsHeight = 0.12; % [m] fin height
rear.finsDeltaXFreeChord = 0.12; % [m] start of Chord 2 measured from start of Chord 1
rear.nPanel = 3; % [m] number of fins
rear.finsLeadingEdgeRadius = [0 0]; % [deg] Leading edge radius at each span station
diff --git a/missions/2024_Lyra_Roccaraso_September/config/paraConfig.m b/missions/2024_Lyra_Roccaraso_September/config/paraConfig.m
index b2d2a74a2b6d930293dc22b687718ca1e8514fa1..6c8e9277f399c7d1e2dc20c9446d8db419ada0ae 100644
--- a/missions/2024_Lyra_Roccaraso_September/config/paraConfig.m
+++ b/missions/2024_Lyra_Roccaraso_September/config/paraConfig.m
@@ -3,95 +3,100 @@
para(1, 1) = Parachute();
para(1, 1).name = 'DROGUE chute';
-para(1, 1).surface = 1.2219; % [m^2] Surface
-para(1, 1).mass = 0.15; % [kg] Parachute Mass
-para(1, 1).cd = 0.96; % [/] Parachute Drag Coefficient
-para(1, 1).cl = 0; % [/] Parachute Lift Coefficient
-para(1, 1).openingTime = 1; % [s] drogue opening delay
-para(1, 1).finalAltitude = 350; % [m] Final altitude of the parachute
-para(1, 1).cx = 1.4; % [/] Parachute Longitudinal Drag Coefficient
-para(1, 1).chordLength = 1.5; % [m] Shock Chord Length
-para(1, 1).chordK = 7200; % [N/m^2] Shock Chord Elastic Constant
-para(1, 1).chordC = 0; % [Ns/m] Shock Chord Dynamic Coefficient
-para(1, 1).m = 1; % [m^2/s] Coefficient of the surface vs. time opening model
-para(1, 1).nf = 12; % [/] Adimensional Opening Time
-para(1, 1).expulsionSpeed = 5; % [m/s] Expulsion Speed
-para(1, 1).forceCoefficient = 1.8; % [-] Empirical coefficient to obtain correct peak force at deployment
-% parachute(1,1).deployTime = 0.1; % [s] Time to get the parachute to full aperture
+para(1, 1).surface = 0.6; % [m^2] Surface
+para(1, 1).mass = 0.15; % [kg] Parachute Mass
+para(1, 1).cd = 0.75; % [/] Parachute Drag Coefficient
+para(1, 1).cl = 0; % [/] Parachute Lift Coefficient
+para(1, 1).openingTime = 1.1; % [s] drogue opening delay
+para(1, 1).finalAltitude = 350; % [m] Final altitude of the parachute
+para(1, 1).cx = 1.4; % [/] Parachute Longitudinal Drag Coefficient
+para(1, 1).chordLength = 1.5; % [m] Shock Chord Length
+para(1, 1).chordK = 7200; % [N/m^2] Shock Chord Elastic Constant
+para(1, 1).chordC = 0; % [Ns/m] Shock Chord Dynamic Coefficient
+para(1, 1).m = 1; % [m^2/s] Coefficient of the surface vs. time opening model
+para(1, 1).nf = 12; % [/] Adimensional Opening Time
+para(1, 1).expulsionSpeed = 5; % [m/s] Expulsion Speed
+para(1, 1).forceCoefficient = 1.8; % [-] Empirical coefficient to obtain correct peak force at deployment
% parachute 2
para(2, 1) = Parachute();
para(2, 1).name = 'MAIN chute';
-para(2, 1).surface = 7.34; % [m^2] Surface
-para(2, 1).mass = 1.05; % [kg] Parachute Mass
-para(2, 1).cd = 1.75; % [/] Parachute Drag Coefficient
-para(2, 1).cl = 0; % [/] Parachute Lift Coefficient
-para(2, 1).openingTime = 0.9;
-para(2, 1).finalAltitude = 0; % [m] Final altitude of the parachute
-para(2, 1).cx = 1.2; % [/] Parachute Longitudinal Drag Coefficient
-para(2, 1).chordLength = 6; % [m] Shock Chord Length
-para(2, 1).chordK = 3000; % [N/m^2] Shock Chord Elastic Constant
-para(2, 1).chordC = 0; % [Ns/m] Shock Chord Dynamic Coefficient
-para(2, 1).m = 1; % [m^2/s] Coefficient of the surface vs. time opening model
-para(2, 1).nf = 8.7; % [/] Adimensional Opening Time
-para(2, 1).expulsionSpeed = 0; % [m/s] Expulsion Speed
-para(2, 1).forceCoefficient = 2.2; % [-] Empirical coefficient to obtain correct peak force at deployment
-% parachute(2,1).deployDuration = 0.9; % [s] Time to get the parachute to full aperture
+para(2, 1).surface = 14; % [m^2] Surface
+para(2, 1).mass = 1.05; % [kg] Parachute Mass
+para(2, 1).cd = 0.6; % [/] Parachute Drag Coefficient
+para(2, 1).cl = 0; % [/] Parachute Lift Coefficient
+para(2, 1).openingTime = 0.9; % [s] drogue opening delay
+para(2, 1).finalAltitude = 0; % [m] Final altitude of the parachute
+para(2, 1).cx = 1.15; % [/] Parachute Longitudinal Drag Coefficient
+para(2, 1).chordLength = 6; % [m] Shock Chord Length
+para(2, 1).chordK = 3000; % [N/m^2] Shock Chord Elastic Constant
+para(2, 1).chordC = 0; % [Ns/m] Shock Chord Dynamic Coefficient
+para(2, 1).m = 1; % [m^2/s] Coefficient of the surface vs. time opening model
+para(2, 1).nf = 8.7; % [/] Adimensional Opening Time
+para(2 ,1).expulsionSpeed = 0; % [m/s] Expulsion Speed
+para(2, 1).forceCoefficient = 2.2; % [-] Empirical coefficient to obtain correct peak force at deployment
%% PAYLOAD CHUTES
% parachute 1
para(1, 2) = Parachute();
para(1, 2).name = "Payload DROGUE";
-para(1, 2).surface = 0.11; % [m^2] Surface
-para(1, 2).mass = 0.15; % [kg] Parachute Mass
-para(1, 2).cd = 1.2; % [/] Parachute Drag Coefficient
-para(1, 2).cl = 0; % [/] Parachute Lift Coefficient
-para(1, 2).openingTime = 1; % [s] drogue opening delay
-para(1, 2).finalAltitude = 300; % [m] Final altitude of the parachute
-para(1, 2).cx = 1.4; % [/] Parachute Longitudinal Drag Coefficient
-para(1, 2).chordLength = 1.5; % [m] Shock Chord Length
-para(1, 2).chordK = 7200; % [N/m^2] Shock Chord Elastic Constant
-para(1, 2).chordC = 0; % [Ns/m] Shock Chord Dynamic Coefficient
-para(1, 2).m = 1; % [m^2/s] Coefficient of the surface vs. time opening model
-para(1, 2).nf = 12; % [/] Adimensional Opening Time
-para(1, 2).expulsionSpeed = 10; % [m/s] Expulsion Speed
-para(1, 2).forceCoefficient = 0; % [-] Empirical coefficient to obtain correct peak force at deployment
+para(1, 2).surface = 0.11; % [m^2] Surface
+para(1, 2).mass = 0.15; % [kg] Parachute Mass
+para(1, 2).cd = 1.2; % [/] Parachute Drag Coefficient
+para(1, 2).cl = 0; % [/] Parachute Lift Coefficient
+para(1, 2).openingTime = 1; % [s] drogue opening delay
+para(1, 2).finalAltitude = 450; % [m] Final altitude of the parachute
+para(1, 2).cx = 1.4; % [/] Parachute Longitudinal Drag Coefficient
+para(1, 2).chordLength = 1.5; % [m] Shock Chord Length
+para(1, 2).chordK = 7200; % [N/m^2] Shock Chord Elastic Constant
+para(1, 2).chordC = 0; % [Ns/m] Shock Chord Dynamic Coefficient
+para(1, 2).m = 1; % [m^2/s] Coefficient of the surface vs. time opening model
+para(1, 2).nf = 12; % [/] Adimensional Opening Time
+para(1, 2).expulsionSpeed = 10; % [m/s] Expulsion Speed
+para(1, 2).forceCoefficient = 0; % [-] Empirical coefficient to obtain correct peak force at deployment
% parachute 2
para(2, 2) = Parafoil();
para(2, 2).name = "Payload AIRFOIL";
-para(2, 2).mass = 0.50; % [kg] Parachute Mass
-para(2, 2).finalAltitude = 0; % [m] Final altitude of the parachute
-para(2, 2).openingTime = 0;
+para(2, 2).mass = 0.50; % [kg] Parafoil Mass
+para(2, 2).openingTime = 0; % [s] Parafoil opening delay
-para(2, 2).surface = 0.11; % [m^2] Surface
-para(2, 2).deltaSMax = 0.1;
+para(2, 2).surface = 0.11; % [m^2] Surface
+para(2, 2).deltaSMax = 0.1; % max value
-para(2, 2).semiWingSpan = 2.55/2; % [m] settings.para(2, 2).b: semiwingspan - vela nuova: 2.55/2; - vela vecchia: 2.06/2;
-para(2, 2).MAC = 0.8; % [m] mean aero chord
-para(2, 2).surface = 2.04; % [m^2] parafoil surface - vela nuova 2.04; - vela vecchia: 1.64;
+uMax = 0;
+uMin = 0;
+identification = 0;
+deltaATau = 0;
+maxSpeed = 0;
+
+para(2, 2).semiWingSpan = 2.55/2; % [m] settings.para(2, 2).b: semiwingspan - vela nuova: 2.55/2; - vela vecchia: 2.06/2;
+para(2, 2).MAC = 0.8; % [m] mean aero chord
+para(2, 2).surface = 2.04; % [m^2] parafoil surface - vela nuova 2.04; - vela vecchia: 1.64;
para(2, 2).inertia = [0.42, 0, 0.03;
0, 0.4, 0;
0.03, 0, 0.053]; % [kg m^2] [3x3] inertia matrix parafoil
+para(2, 2).finalAltitude = 0;
+
para(2, 2).cd0 = 0.25;
para(2, 2).cdAlpha = 0.12;
-para(2, 2).cdSurface = 0.01;
+para(2, 2).cdSurface = 0.01;
para(2, 2).cl0 = 0.091;
para(2, 2).clAlpha = 0.9;
-para(2, 2).clSurface = -0.0035;
+para(2, 2).clSurface = -0.0035;
para(2, 2).cLP = -0.84;
para(2, 2).cLPhi = -0.1;
-para(2, 2).cLSurface = -0.0035;
+para(2, 2).cLSurface = -0.0035;
para(2, 2).cM0 = 0.35;
para(2, 2).cMAlpha = -0.72;
para(2, 2).cMQ = -1.49;
para(2, 2).cNR = -0.27;
-para(2, 2).cNSurface = 0.0115;
+para(2, 2).cNSurface = 0.0115;
\ No newline at end of file
diff --git a/missions/2024_Lyra_Roccaraso_September/config/rocketConfig.m b/missions/2024_Lyra_Roccaraso_September/config/rocketConfig.m
index b51a163ce7e2ad578eb35d2f5ffc7afd5c983033..87301e76fd58ed55c391969c13363b3c6217fe38 100644
--- a/missions/2024_Lyra_Roccaraso_September/config/rocketConfig.m
+++ b/missions/2024_Lyra_Roccaraso_September/config/rocketConfig.m
@@ -1,28 +1,27 @@
-% CONFIG - This script sets up control parameters
+% CONFIG - This script sets up rocket's parameters
%% ROCKET - OVERRIDES BAYS CONFIG
rocket = Rocket();
-rocket.diameter = 0.15; % [m] Rocket diameter
-rocket.length = []; % [m] OVERRIDE total length
-rocket.mass = []; % [kg] OVERRIDE total mass
-rocket.massNoMotor = [15.6348]; % [kg] OVERRIDE mass without motor
-rocket.inertia = []; % [kg*m^2] OVERRIDE total inertia - Axibody reference
-rocket.inertiaNoMotor = [
- 0.06535397;
- 12.07664659;
- 12.07701314]; % [kg*m^2] OVERRIDE inertia without motor
-rocket.xCg = []; % [m] OVERRIDE total xCg
-rocket.xCgNoMotor = [1.28]; % [m] OVERRIDE xCg without motor
+rocket.diameter = 0.15; % [m] Rocket diameter
+rocket.massNoMotor = []; % [kg] OVERRIDE mass without motor
+rocket.inertiaNoMotor = []; % [kg*m^2] OVERRIDE inertia without motor - body axes reference
+rocket.xCgNoMotor = []; % [m] OVERRIDE xCg without motor
+rocket.lengthCenterNoMot = []; % [m] OVERRIDE Center length - no nose, no motor
+
+% rocket.diameter = 0.15; % [m] Rocket diameter
+% rocket.massNoMotor = 17.0; % [kg] OVERRIDE mass without motor
+% rocket.inertiaNoMotor = [0.06535397; 17.21019828; 17.21056483]; % [kg*m^2] OVERRIDE inertia without motor - body axes reference
+% rocket.xCgNoMotor = 1.28; % [m] OVERRIDE xCg without motor
+% rocket.lengthCenterNoMot = 1.778; % [m] OVERRIDE Center length - no nose, no motor
%% PLD - Includes Payload + Nose
payload = Payload();
-payload.length = 0.6; % [m] Total bay length
-payload.mass = 3.38512; % [kg] Total bay mass
-payload.inertia = ...
- [1032892397; 5461775539; 5450863094]*1e-9; % [kg*m^2] Total bay inertia (Body reference)
-payload.xCg = 0.22734; % [m] Cg relative to bay upper side
+payload.length = 647.25 * 1e-3; % [m] Total bay length
+payload.mass = 4.401; % [kg] Total bay mass
+payload.inertia = 1e-9*[12531966; 109986813; 109930516]; % [kg*m^2] Total bay inertia (Body reference)
+payload.xCg = 487.78 * 1e-3; % [m] Cg relative to bay upper side
payload.noseLength = 0.32; % [m] Nosecone length
payload.noseType = 'MHAACK'; % [-] Nosecone shape
@@ -33,78 +32,74 @@ payload.noseCMod = 1.799127e-01; % [-] C coefficient f
%% RCS
recovery = Recovery();
-recovery.length = 0.9469; % [m] Total bay length
-recovery.mass = 4.05091; % [kg] Total bay mass
-recovery.inertia = ...
- [1335996937; 2133707079; 2133851442]*1e-9; % [kg*m^2] Total bay inertia (Body reference)
-recovery.xCg = 0.56607; % [m] Cg relative to bay upper side
+recovery.length = 826 * 1e-3; % [m] Total bay length
+recovery.mass = 4.065; % [kg] Total bay mass
+recovery.inertia = 1e-9*[13422459; 217223325; 217296702]; % [kg*m^2] Total bay inertia (Body reference)
+recovery.xCg = 549.41 * 1e-3; % [m] Cg relative to bay upper side
%% ELC
electronics = Electronics();
-electronics.length = 0.4305; % [m] Total bay length
-electronics.mass = 2.56618; % [kg] Total bay mass
-electronics.inertia = ...
- [909714504; 4749092145; 4715845883]*1e-9; % [kg*m^2] Total bay inertia (Body reference)
-electronics.xCg = 0.22968; % [m] Cg relative to bay upper side
+electronics.length = 433.5 * 1e-3; % [m] Total bay length
+electronics.mass = 2.551; % [kg] Total bay mass
+electronics.inertia = 1e-9*[9358415; 49265825; 48770607]; % [kg*m^2] Total bay inertia (Body reference)
+electronics.xCg = 229.9 * 1e-3; % [m] Cg relative to bay upper side
%% ARB
airbrakes = Airbrakes();
-airbrakes.length = 0.0548; % [m] Total bay length
-airbrakes.mass = 0.99429; % [kg] Total bay mass
-airbrakes.inertia = ...
- [78545425; 41163849; 41163849]*1e-9; % [kg*m^2] Total bay inertia (Body reference)
-airbrakes.xCg = 0.03967; % [m] Cg relative to bay upper side
+airbrakes.length = 54.8 * 1e-3; % [m] Total bay length
+airbrakes.mass = 0.936; % [kg] Total bay mass
+airbrakes.inertia = 1e-9*[3086650; 1931082; 1889047]; % [kg*m^2] Total bay inertia (Body reference)
+airbrakes.xCg = 30.54 * 1e-3; % [m] Cg relative to bay upper side
-airbrakes.enabled = false; % If true, multiple and smooth airbrakes opening will be simulated
-% airbrakes.angles = [0, 45, 68];
+airbrakes.enabled = false; % If true, multiple and smooth airbrakes opening will be simulated
airbrakes.extension = [1]; % aerobrakes, 1-2-3 for 0%, 50% or 100% opened
airbrakes.deltaTime = [0]; % aerobrakes, configurations usage time
airbrakes.n = 3; % [-] number of brakes
airbrakes.height = linspace(0, 0.0363, 3); % [m] Block airbrakes opening coordinate ( First entry must be 0! )
+airbrakes.angleFunction = ...
+ @(x) 1*x^4 + 2*x^3 + 3*x^2 + 4*x; % [-] Relation between angle and extension height
airbrakes.angleFunction = ...
@(x) 1*x^4 + 2*x^3 + 3*x^2 + 4*x; % [-] Relation between angle and extension height
airbrakes.width = 0.1002754821; % [m] brakes width (normal)
airbrakes.thickness = 0.008; % [m] brakes thickness
airbrakes.xDistance = 1.517;
-% airbrakes.minTime = 0; % [s] time after which the airbrakes can be used
airbrakes.maxMach = 0.8; % [-] Maximum Mach at which airbrakes can be used
airbrakes.servoOmega = 150*pi/180; % [rad/s] Servo-motor angular velocity
%% MOTOR
motor = Motor();
-motor.name = 'HRE_ARM_Rocc_U06_T03T03'; % [-] Motor name
-motor.cutoffTime = []; % [s] OVERRIDE Cutoff time
-motor.ignitionTransient = 0.4; % [s] Ignition transient
-motor.cutoffTransient = 0.3; % [s] Cut-off transient
+motor.name = 'HRE_ARM_RU60SFT5'; % [-] Motor name
+motor.cutoffTime = []; % [s] OVERRIDE Cutoff time
+motor.ignitionTransient = 0.3; % [s] Ignition transient
+motor.cutoffTransient = 0.3; % [s] Cut-off transient
%% REAR - Includes Fincan + Boat
rear = Rear();
-rear.position = 1.086;
-rear.length = 0.5585; % [m] Total bay length
-rear.mass = 1.61926; % [kg] Total bay mass
-rear.inertia = ...
- [13054773; 44192627; 44193468]*1e-9; % [kg*m^2] Total bay inertia (Body reference)
-rear.xCg = 0.25358; % [m] Cg relative to bay upper side
-
-rear.boatType = 'OGIVE'; % [-] Boat type
-rear.boatLength = 0.114; % [m] Boat length
-rear.boatFinalDiameter = 0.125; % [m] Boat end diameter
-
-rear.finsRootChord = 0.3; % [m] attached chord length
-rear.finsFreeChord = 0.14; % [m] free chord length
-rear.finsHeight = 0.1; % [m] fin height
-rear.finsDeltaXFreeChord = 0.13; % [m] start of Chord 2 measured from start of Chord 1
-rear.nPanel = 3; % [m] number of fins
-rear.finsLeadingEdgeRadius = [0 0]; % [deg] Leading edge radius at each span station
-rear.finsAxialDistance = 0.012; % [m] distance between end of root chord and end of center body
-rear.finsSemiThickness = 0.00175; % [m] fin semi-thickness
-rear.finsMaxThicknessPosition = 0.00175; % [m] Fraction of chord from leading edge to max thickness
+rear.position = 1.090; % [m] offset from
+rear.length = 547 * 1e-3; % [m] Total bay length
+rear.mass = 1.623; % [kg] Total bay mass
+rear.inertia = 1e-9*[13074201; 44271226; 44270124]; % [kg*m^2] Total bay inertia (Body reference)
+rear.xCg = 253.77 * 1e-3; % [m] Cg relative to bay upper side
+
+rear.boatType = 'OGIVE'; % [-] Boat type
+rear.boatLength = 0.114; % [m] Boat length
+rear.boatFinalDiameter = 0.125; % [m] Boat end diameter
+
+rear.finsRootChord = 0.3; % [m] attached chord length
+rear.finsFreeChord = 0.12; % [m] free chord length
+rear.finsHeight = 0.12; % [m] fin height
+rear.finsDeltaXFreeChord = 0.12; % [m] start of Chord 2 measured from start of Chord 1
+rear.nPanel = 3; % [m] number of fins
+rear.finsLeadingEdgeRadius = [0 0]; % [deg] Leading edge radius at each span station
+rear.finsAxialDistance = -0.044; % [m] distance between end of root chord and end of center body
+rear.finsSemiThickness = 0.00175; % [m] fin semi-thickness
+rear.finsMaxThicknessPosition = 0.00175; % [m] Fraction of chord from leading edge to max thickness
%% PITOT
pitot = Pitot();
diff --git a/missions/2024_Lyra_Roccaraso_September/data/aeroCoefficients.mat b/missions/2024_Lyra_Roccaraso_September/data/aeroCoefficients.mat
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--- a/missions/2024_Lyra_Roccaraso_September/data/aeroCoefficients.mat
+++ b/missions/2024_Lyra_Roccaraso_September/data/aeroCoefficients.mat
@@ -1,3 +1,3 @@
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diff --git a/missions/2024_Lyra_Roccaraso_September/data/aeroCoefficientsHighAOA.mat b/missions/2024_Lyra_Roccaraso_September/data/aeroCoefficientsHighAOA.mat
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--- a/missions/2024_Lyra_Roccaraso_September/data/aeroCoefficientsHighAOA.mat
+++ b/missions/2024_Lyra_Roccaraso_September/data/aeroCoefficientsHighAOA.mat
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diff --git a/missions/2024_Lyra_Roccaraso_September/data/motors.mat b/missions/2024_Lyra_Roccaraso_September/data/motors.mat
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--- a/missions/2024_Lyra_Roccaraso_September/data/motors.mat
+++ b/missions/2024_Lyra_Roccaraso_September/data/motors.mat
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