diff --git a/classes/Bay.m b/classes/Bay.m
index b7e177537439bdf53a6a95443e04992d00bc8022..beb567f262e799b62d746aac808f6c43e4eccf94 100644
--- a/classes/Bay.m
+++ b/classes/Bay.m
@@ -12,7 +12,7 @@ classdef Bay < Component & matlab.mixin.Heterogeneous
methods (Static, Sealed, Access=protected)
function default = getDefaultScalarElement
- default = Payload;
+ default = Parafoil;
end
end
end
diff --git a/classes/Rocket.m b/classes/Rocket.m
index da1e33e3f621b7b925f4f2fcc1d56d004f927e12..0088c2cc31dc65486d83f765dca38ca44d082d77 100644
--- a/classes/Rocket.m
+++ b/classes/Rocket.m
@@ -11,7 +11,7 @@ classdef Rocket < Component
% file
properties
- payload Payload % [-] Payload bay
+ parafoil Parafoil % [-] Parafoil bay
recovery Recovery % [-] Recovery bay
electronics Electronics % [-] Electronics bay
airbrakes Airbrakes % [-] Airbrakes bay
@@ -76,21 +76,21 @@ classdef Rocket < Component
absPositions = cumsum([-shift(1); shift(1:end-1)]);
absPositions = absPositions + ...
- (obj.payload.length - obj.payload.noseLength);
+ (obj.parafoil.length - obj.parafoil.noseLength);
obj.absolutePositions = dictionary(keys(bDictionay), absPositions);
end
function updateGeometry(obj)
if ~isempty(obj.lengthCenterNoMot)
- obj.length = obj.lengthCenterNoMot + obj.motor.length + obj.payload.noseLength;
+ obj.length = obj.lengthCenterNoMot + obj.motor.length + obj.parafoil.noseLength;
else
- obj.length = (obj.absolutePositions("rear") + obj.bays("rear").length) + obj.bays("payload").noseLength;
+ obj.length = (obj.absolutePositions("rear") + obj.bays("rear").length) + obj.bays("parafoil").noseLength;
obj.lengthCenterNoMot = obj.absolutePositions("motor");
end
if isempty(obj.crossSection)
obj.crossSection = 0.25*pi*obj.diameter^2;
end
- obj.lengthCenter = obj.length - obj.payload.noseLength - obj.rear.boatLength;
+ obj.lengthCenter = obj.length - obj.parafoil.noseLength - obj.rear.boatLength;
end
function updateMassNoMotor(obj)
@@ -156,11 +156,11 @@ classdef Rocket < Component
end
function updateStagesMass(obj)
- stage1 = obj.cutoffMass - (obj.parachutes(1,2).mass + obj.parachutes(2,2).mass + obj.payload.mass);
- % Everything at cut off without payload, payload drogue and
- % payload airfoil
+ stage1 = obj.cutoffMass - (obj.parachutes(1,2).mass + obj.parachutes(2,2).mass + obj.parafoil.mass);
+ % Everything at cut off without parafoil, parafoil drogue and
+ % parafoil airfoil
stage2 = obj.cutoffMass - stage1;
- % only payload: payload, payload drogue and payload airfoil
+ % only parafoil: parafoil, parafoil drogue and parafoil airfoil
obj.stagesMass = [stage1 stage2];
end
@@ -246,7 +246,7 @@ classdef Rocket < Component
end
vars = obj.getConfig(mission); % Load config once and apply to other bays
- obj.payload = Payload(mission, vars);
+ obj.parafoil = Parafoil(mission, vars);
obj.recovery = Recovery(mission, vars);
obj.electronics = Electronics(mission, vars);
obj.motor = Motor(mission, vars);
@@ -366,10 +366,10 @@ classdef Rocket < Component
obj.coefficients.geometry.xcg(end);
], 3);
- if (obj.payload.noseCMod & obj.payload.nosePMod) == 0 % KARMAN ogive case, no modified p and c coefficients
+ if (obj.parafoil.noseCMod & obj.parafoil.nosePMod) == 0 % KARMAN ogive case, no modified p and c coefficients
geometryRocket = round([
obj.diameter;
- obj.payload.noseLength;
+ obj.parafoil.noseLength;
obj.lengthCenter;
obj.rear.finsRootChord;
obj.rear.finsFreeChord;
@@ -395,10 +395,10 @@ classdef Rocket < Component
else % MHAAK ogive case, modified p and c coefficients
geometryRocket = round([
obj.diameter;
- obj.payload.noseLength;
+ obj.parafoil.noseLength;
obj.lengthCenter;
- obj.payload.noseCMod;
- obj.payload.nosePMod;
+ obj.parafoil.noseCMod;
+ obj.parafoil.nosePMod;
obj.rear.finsRootChord;
obj.rear.finsFreeChord;
obj.rear.finsHeight;
@@ -426,7 +426,7 @@ classdef Rocket < Component
checks = [
xCgRocket == xCgTest;
- strcmp(obj.coefficients.geometry.ogType, obj.payload.noseType);
+ strcmp(obj.coefficients.geometry.ogType, obj.parafoil.noseType);
geometryRocket == geometryTest;
strcmp(obj.coefficients.geometry.boatType, obj.rear.boatType)
];
diff --git a/classes/bays/Payload.m b/classes/bays/Parafoil.m
similarity index 86%
rename from classes/bays/Payload.m
rename to classes/bays/Parafoil.m
index 0f9f7edb3f5528648e3142d3cb85cfe508438e49..378fb88708e41030e60d487c5e5c11f3be4bbcee 100644
--- a/classes/bays/Payload.m
+++ b/classes/bays/Parafoil.m
@@ -1,9 +1,9 @@
-classdef Payload < Bay
- % Payload: Represents nose + payload configuration for a rocket.
+classdef Parafoil < Bay
+ % Parafoil: Represents nose + parafoil configuration for a rocket.
%
% Constructor:
- % - Payload: Creates an instance of the Payload class.
- % Loaded config: rocketConfig.m > payload
+ % - Parafoil: Creates an instance of the Parafoil class.
+ % Loaded config: rocketConfig.m > parafoil
% Loaded data: -
% Arguments:
% - mission: Mission, mission object
@@ -33,12 +33,12 @@ classdef Payload < Bay
properties(Access = protected)
configName = 'rocketConfig.m'
- variableName = 'payload'
+ variableName = 'parafoil'
mission Mission = Mission()
end
methods
- function obj = Payload(mission, varIn)
+ function obj = Parafoil(mission, varIn)
arguments(Input)
mission Mission = Mission()
varIn = []
diff --git a/classes/components/Para.m b/classes/components/Para.m
index ef74338bcccc5f29d0943eaa1efb635286f06495..fb7388e7c1af52dd9afab7f6dde18e6aceb35883 100644
--- a/classes/components/Para.m
+++ b/classes/components/Para.m
@@ -35,8 +35,8 @@ classdef Para < matlab.mixin.Heterogeneous & Component
% In case of homogeneous type, forces conversion to
% heterogeneous Para array
case 'Parachute'
- obj(1, 1, 2) = Parafoil();
- case 'Parafoil'
+ obj(1, 1, 2) = Wing();
+ case 'Wing'
obj(1, 1, 2) = Parachute();
otherwise
end
diff --git a/classes/components/Parafoil.m b/classes/components/Wing.m
similarity index 87%
rename from classes/components/Parafoil.m
rename to classes/components/Wing.m
index 6a60eb018c5948f77be088bb00f59e76cb6aa4f0..4e47f9e3a9938d03e714c9721344f2da8e712c57 100644
--- a/classes/components/Parafoil.m
+++ b/classes/components/Wing.m
@@ -1,4 +1,4 @@
-classdef Parafoil < Para
+classdef Wing < Para
% Parachute: Represents a parachute component.
%
% Constructor:
@@ -15,13 +15,13 @@ classdef Parafoil < Para
surface double % [m^2] Surface
deltaSMax double % [-] Aerodynamic control coefficient - symmetric, max value
- mass double % [kg] Parafoil Mass
- openingTime double % [s] Parafoil opening time (delay + time to get fully open)
+ mass double % [kg] Wing Mass
+ openingTime double % [s] Wing opening time (delay + time to get fully open)
inertia % [kg*m^2] 3x3 Inertia Matrix (the diagonal is made of the inertia vector values)
finalAltitude double % [m] Final altitude of the parafoil
- semiWingSpan double % [m] Parafoil semiwingspan
- MAC double % [m] Parafoil mean aero chord
+ semiWingSpan double % [m] Wing semiwingspan
+ MAC double % [m] Wing mean aero chord
cd0 double % [-] aerodynamic control coefficient - asymetric, CD0
cdAlpha double % [-] aerodynamic control coefficient - asymetric, CDAlpha
@@ -50,7 +50,7 @@ classdef Parafoil < Para
end
methods
- function obj = Parafoil(mission, varIn)
+ function obj = Wing(mission, varIn)
arguments(Input)
mission Mission = Mission()
varIn = []
diff --git a/functions/miscellaneous/createDissileInput.m b/functions/miscellaneous/createDissileInput.m
index cd655d6503991c1cb7638f98510bdb799505889c..f6c07fdb849fafb3a37c0d8d0284b7ba59a80ce1 100644
--- a/functions/miscellaneous/createDissileInput.m
+++ b/functions/miscellaneous/createDissileInput.m
@@ -80,13 +80,13 @@ input.refq.LATREF = rocket.diameter;
input.axibod.about = 'Axisymmetric body quantities';
%%% nose
-input.axibod.TNOSE = find(strcmp(noses, rocket.payload.noseType))-1; % [0=CONICAL, 1=OGIVE, 2=POWER, 3=HAACK, 4=KARMAN, 5=MHAACK] ogive type
-if strcmp(rocket.payload.noseType, 'MHAACK')
- input.axibod.MHAACKCP = [rocket.payload.noseCMod rocket.payload.nosePMod]; % [-] CMOD PMOD mhaack parameters, set CMOD = 1/3 and PMOD = 1 to get a haack
-elseif strcmp(rocket.payload.noseType, 'POWER')
- input.axibod.POWER = rocket.payload.nosePower; % [-] Exponent of the power series, set a value between 0 and 1
+input.axibod.TNOSE = find(strcmp(noses, rocket.parafoil.noseType))-1; % [0=CONICAL, 1=OGIVE, 2=POWER, 3=HAACK, 4=KARMAN, 5=MHAACK] ogive type
+if strcmp(rocket.parafoil.noseType, 'MHAACK')
+ input.axibod.MHAACKCP = [rocket.parafoil.noseCMod rocket.parafoil.nosePMod]; % [-] CMOD PMOD mhaack parameters, set CMOD = 1/3 and PMOD = 1 to get a haack
+elseif strcmp(rocket.parafoil.noseType, 'POWER')
+ input.axibod.POWER = rocket.parafoil.nosePower; % [-] Exponent of the power series, set a value between 0 and 1
end
-input.axibod.LNOSE = rocket.payload.noseLength; % [m] Nose length
+input.axibod.LNOSE = rocket.parafoil.noseLength; % [m] Nose length
input.axibod.DNOSE = rocket.diameter; % [m] Nose diameter at base
input.axibod.TRUNC = false;
diff --git a/functions/simulations/stdDescent.m b/functions/simulations/stdDescent.m
index 5f8a2c8c63ba3ab524ab36760e4f75928749ce92..10076a50420c1eebfeb8d08f78897831964e4192 100644
--- a/functions/simulations/stdDescent.m
+++ b/functions/simulations/stdDescent.m
@@ -121,7 +121,7 @@ for i = 1:nParachutes
solution = ode113(@descentParachute, [t0, tf], Y0, options, ...
rocket, environment, wind, descentData, wrapper);
- case 'Parafoil'
+ case 'Wing'
if ~settings.simulator.parafoil, continue; end
if i == 1
error("Cannot simulate parafoil as fist descent stage");
diff --git a/missions/2021_Lynx_Portugal_October/config/rocketConfig.m b/missions/2021_Lynx_Portugal_October/config/rocketConfig.m
index 7f6e832c27ac4b328210b941a6f5904610309359..692225f5b4e3c32bcf79eda9037257dedb8f2565 100644
--- a/missions/2021_Lynx_Portugal_October/config/rocketConfig.m
+++ b/missions/2021_Lynx_Portugal_October/config/rocketConfig.m
@@ -16,21 +16,21 @@ rocket.inertiaNoMotor = [0.0786; 12.972; 12.972]; % [kg*m^2] OVERRIDE iner
rocket.xCgNoMotor = 1.6025; % [m] OVERRIDE xCg without motor
rocket.lengthCenterNoMot = 1.7640; % [m] OVERRIDE Center length - no nose, no motor
-%% PLD - Includes Payload + Nose
-payload = Payload();
+%% PLD - Includes Parafoil + Nose
+parafoil = Parafoil();
% !!!!!
-payload.length = 0.31; % [m] Total bay length
-payload.mass = 0; % [kg] Total bay mass
-payload.inertia = zeros(3,1); % [kg*m^2] Total bay inertia (Body reference)
-payload.xCg = 0; % [m] Cg relative to bay upper side
+parafoil.length = 0.31; % [m] Total bay length
+parafoil.mass = 0; % [kg] Total bay mass
+parafoil.inertia = zeros(3,1); % [kg*m^2] Total bay inertia (Body reference)
+parafoil.xCg = 0; % [m] Cg relative to bay upper side
% !!!!!
-payload.noseLength = 0.26; % [m] Nosecone length
-payload.noseType = 'KARMAN'; % [-] Nosecone shape
-payload.nosePower = 0; % [-] Nosecone power type parameter
-payload.nosePMod = 0; % [-] P coefficient for modified nosecone shapes
-payload.noseCMod = 0; % [-] C coefficient for modified nosecone shapes
+parafoil.noseLength = 0.26; % [m] Nosecone length
+parafoil.noseType = 'KARMAN'; % [-] Nosecone shape
+parafoil.nosePower = 0; % [-] Nosecone power type parameter
+parafoil.nosePMod = 0; % [-] P coefficient for modified nosecone shapes
+parafoil.noseCMod = 0; % [-] C coefficient for modified nosecone shapes
%% RCS
recovery = Recovery();
diff --git a/missions/2021_Lynx_Roccaraso_September/config/rocketConfig.m b/missions/2021_Lynx_Roccaraso_September/config/rocketConfig.m
index 7b4fd7790c981a2b17cc1c06e4b8786cc575fba9..fa072151371f40a081cdde8f4e2d92bcde9f4fcc 100644
--- a/missions/2021_Lynx_Roccaraso_September/config/rocketConfig.m
+++ b/missions/2021_Lynx_Roccaraso_September/config/rocketConfig.m
@@ -16,21 +16,21 @@ rocket.inertiaNoMotor = [0.06; 7.511; 7.512]; % [kg*m^2] OVERRIDE inertia
rocket.xCgNoMotor = 1.1986; % [m] OVERRIDE xCg without motor
rocket.lengthCenterNoMot = 1.7840; % [m] OVERRIDE Center length - no nose, no motor
-%% PLD - Includes Payload + Nose
-payload = Payload();
+%% PLD - Includes Parafoil + Nose
+parafoil = Parafoil();
% !!!!!
-payload.length = 0.31; % [m] Total bay length
-payload.mass = 0; % [kg] Total bay mass
-payload.inertia = zeros(3,1); % [kg*m^2] Total bay inertia (Body reference)
-payload.xCg = 0; % [m] Cg relative to bay upper side
+parafoil.length = 0.31; % [m] Total bay length
+parafoil.mass = 0; % [kg] Total bay mass
+parafoil.inertia = zeros(3,1); % [kg*m^2] Total bay inertia (Body reference)
+parafoil.xCg = 0; % [m] Cg relative to bay upper side
% !!!!!
-payload.noseLength = 0.26; % [m] Nosecone length
-payload.noseType = 'KARMAN'; % [-] Nosecone shape
-payload.nosePower = 0; % [-] Nosecone power type parameter
-payload.nosePMod = 0; % [-] P coefficient for modified nosecone shapes
-payload.noseCMod = 0; % [-] C coefficient for modified nosecone shapes
+parafoil.noseLength = 0.26; % [m] Nosecone length
+parafoil.noseType = 'KARMAN'; % [-] Nosecone shape
+parafoil.nosePower = 0; % [-] Nosecone power type parameter
+parafoil.nosePMod = 0; % [-] P coefficient for modified nosecone shapes
+parafoil.noseCMod = 0; % [-] C coefficient for modified nosecone shapes
%% RCS
recovery = Recovery();
diff --git a/missions/2022_Pyxis_Portugal_October/config/paraConfig.m b/missions/2022_Pyxis_Portugal_October/config/paraConfig.m
index fbd7712f52d6a5598e8a29d4bf22f2b7c0b9f45d..a1e6cf6757e9ed3e3c74a5ca7fe1111c2524e3c5 100644
--- a/missions/2022_Pyxis_Portugal_October/config/paraConfig.m
+++ b/missions/2022_Pyxis_Portugal_October/config/paraConfig.m
@@ -41,7 +41,7 @@ para(2, 1).forceCoefficient = []; % [-] Empirical coefficient to obtain c
% parachute 1
para(1, 2) = Parachute();
-para(1, 2).name = "Payload DROGUE";
+para(1, 2).name = "Parafoil DROGUE";
para(1, 2).surface = 0.11; % [m^2] Surface
para(1, 2).mass = 0.05; % [kg] Parachute Mass
para(1, 2).cd = 1.2; % [/] Parachute Drag Coefficient
@@ -58,11 +58,11 @@ para(1, 2).expulsionSpeed = 10; % [m/s] Expulsion Speed
para(1, 2).forceCoefficient = []; % [-] Empirical coefficient to obtain correct peak force at deployment
% parachute 2
-para(2, 2) = Parafoil();
+para(2, 2) = Wing();
-para(2, 2).name = "Payload AIRFOIL";
-para(2, 2).mass = 0.45; % [kg] Parafoil Mass
-para(2, 2).openingTime = 0; % [s] Parafoil opening delay
+para(2, 2).name = "Parafoil AIRFOIL";
+para(2, 2).mass = 0.45; % [kg] Wing Mass
+para(2, 2).openingTime = 0; % [s] Wing opening delay
para(2, 2).surface = 0.11; % [m^2] Surface
para(2, 2).deltaSMax = 0.1; % max value
diff --git a/missions/2022_Pyxis_Portugal_October/config/rocketConfig.m b/missions/2022_Pyxis_Portugal_October/config/rocketConfig.m
index ca08ee541f7c90d0f4681805d3d81ff604f88663..285238c5c2518d36cb6a8d38167988f19013390b 100644
--- a/missions/2022_Pyxis_Portugal_October/config/rocketConfig.m
+++ b/missions/2022_Pyxis_Portugal_October/config/rocketConfig.m
@@ -16,21 +16,21 @@ rocket.inertiaNoMotor = [0.06303; 9.62497; 9.62524]; % [kg*m^2] OVERRIDE i
rocket.xCgNoMotor = 1.2239; % [m] OVERRIDE xCg without motor
rocket.lengthCenterNoMot = 1.4470; % [m] OVERRIDE Center length - no nose, no motor
-%% PLD - Includes Payload + Nose
-payload = Payload();
+%% PLD - Includes Parafoil + Nose
+parafoil = Parafoil();
% !!!!!
-payload.length = 0.31; % [m] Total bay length
-payload.mass = 0; % [kg] Total bay mass
-payload.inertia = zeros(3,1); % [kg*m^2] Total bay inertia (Body reference)
-payload.xCg = 0; % [m] Cg relative to bay upper side
+parafoil.length = 0.31; % [m] Total bay length
+parafoil.mass = 0; % [kg] Total bay mass
+parafoil.inertia = zeros(3,1); % [kg*m^2] Total bay inertia (Body reference)
+parafoil.xCg = 0; % [m] Cg relative to bay upper side
% !!!!!
-payload.noseLength = 0.31; % [m] Nosecone length
-payload.noseType = 'MHAACK'; % [-] Nosecone shape
-payload.nosePower = 0; % [-] Nosecone power type parameter
-payload.nosePMod = 1.293318e+00; % [-] P coefficient for modified nosecone shapes
-payload.noseCMod = 1.864832e-01; % [-] C coefficient for modified nosecone shapes
+parafoil.noseLength = 0.31; % [m] Nosecone length
+parafoil.noseType = 'MHAACK'; % [-] Nosecone shape
+parafoil.nosePower = 0; % [-] Nosecone power type parameter
+parafoil.nosePMod = 1.293318e+00; % [-] P coefficient for modified nosecone shapes
+parafoil.noseCMod = 1.864832e-01; % [-] C coefficient for modified nosecone shapes
%% RCS
recovery = Recovery();
diff --git a/missions/2022_Pyxis_Portugal_October/old/simulationsData.m b/missions/2022_Pyxis_Portugal_October/old/simulationsData.m
index 75e03f84c194a2c333b7479bfe7498f8e01473fa..029a27be320decf5794836a37884931ed800e39d 100644
--- a/missions/2022_Pyxis_Portugal_October/old/simulationsData.m
+++ b/missions/2022_Pyxis_Portugal_October/old/simulationsData.m
@@ -201,7 +201,7 @@ settings.para(2, 1).nf = 8.7; % [/] Adimensional Opening Time
%%% PAYLOAD CHUTES
% parachute 1
-settings.para(1, 2).name = "Payload DROGUE";
+settings.para(1, 2).name = "Parafoil DROGUE";
settings.para(1, 2).S = 0.11; % [m^2] Surface
settings.para(1, 2).mass = 0.05; % [kg] Parachute Mass
settings.para(1, 2).CD = 1.2; % [/] Parachute Drag Coefficient
@@ -217,7 +217,7 @@ settings.para(1, 2).nf = 12; % [/] Adimensional Opening Time
settings.para(1, 2).Vexit = 10; % [m/s] Expulsion Speed
% parachute 2
-settings.para(2, 2).name = "Payload AIRFOIL";
+settings.para(2, 2).name = "Parafoil AIRFOIL";
settings.para(2, 2).mass = 0.45; % [kg] Parachute Mass
settings.para(2, 2).z_cut = 0; % [m] Final altitude of the parachute
diff --git a/missions/2022_Pyxis_Roccaraso_September/config/paraConfig.m b/missions/2022_Pyxis_Roccaraso_September/config/paraConfig.m
index 4da985ac28611efc91e22060593b999d0a2f4e44..4f9430b62015522460793d1ad756809ac2cc414d 100644
--- a/missions/2022_Pyxis_Roccaraso_September/config/paraConfig.m
+++ b/missions/2022_Pyxis_Roccaraso_September/config/paraConfig.m
@@ -41,7 +41,7 @@ para(2, 1).forceCoefficient = []; % [-] Empirical coefficient to obtain c
% parachute 1
para(1, 2) = Parachute();
-para(1, 2).name = "Payload DROGUE";
+para(1, 2).name = "Parafoil DROGUE";
para(1, 2).surface = 0.11; % [m^2] Surface
para(1, 2).mass = 0.05; % [kg] Parachute Mass
para(1, 2).cd = 1.2; % [/] Parachute Drag Coefficient
@@ -58,11 +58,11 @@ para(1, 2).expulsionSpeed = 10; % [m/s] Expulsion Speed
para(1, 2).forceCoefficient = []; % [-] Empirical coefficient to obtain correct peak force at deployment
% parachute 2
-para(2, 2) = Parafoil();
+para(2, 2) = Wing();
-para(2, 2).name = "Payload AIRFOIL";
-para(2, 2).mass = 0.45; % [kg] Parafoil Mass
-para(2, 2).openingTime = 0; % [s] Parafoil opening delay
+para(2, 2).name = "Parafoil AIRFOIL";
+para(2, 2).mass = 0.45; % [kg] Wing Mass
+para(2, 2).openingTime = 0; % [s] Wing opening delay
para(2, 2).surface = 0.11; % [m^2] Surface
para(2, 2).deltaSMax = 0.1; % max value
diff --git a/missions/2022_Pyxis_Roccaraso_September/config/rocketConfig.m b/missions/2022_Pyxis_Roccaraso_September/config/rocketConfig.m
index 55ca1f299e9bf3bb6fd291863bffc224d46b6c96..ed371b1804110fe4ef4f76aff71217eaf5935fce 100644
--- a/missions/2022_Pyxis_Roccaraso_September/config/rocketConfig.m
+++ b/missions/2022_Pyxis_Roccaraso_September/config/rocketConfig.m
@@ -18,21 +18,21 @@ rocket.xCgNoMotor = 1.2957; % [m]
% settings.Lcenter - motors(iMotor).L/1000
rocket.lengthCenterNoMot = 1.61; % [m] OVERRIDE Center length - no nose, no motor
-%% PLD - Includes Payload + Nose
-payload = Payload();
+%% PLD - Includes Parafoil + Nose
+parafoil = Parafoil();
% !!!!!
-payload.length = 0.31; % [m] Total bay length
-payload.mass = 0; % [kg] Total bay mass
-payload.inertia = zeros(3,1); % [kg*m^2] Total bay inertia (Body reference)
-payload.xCg = 0; % [m] Cg relative to bay upper side
+parafoil.length = 0.31; % [m] Total bay length
+parafoil.mass = 0; % [kg] Total bay mass
+parafoil.inertia = zeros(3,1); % [kg*m^2] Total bay inertia (Body reference)
+parafoil.xCg = 0; % [m] Cg relative to bay upper side
% !!!!!
-payload.noseLength = 0.31; % [m] Nosecone length
-payload.noseType = 'MHAACK'; % [-] Nosecone shape
-payload.nosePower = 0; % [-] Nosecone power type parameter
-payload.nosePMod = 1.293318e+00; % [-] P coefficient for modified nosecone shapes
-payload.noseCMod = 1.864832e-01; % [-] C coefficient for modified nosecone shapes
+parafoil.noseLength = 0.31; % [m] Nosecone length
+parafoil.noseType = 'MHAACK'; % [-] Nosecone shape
+parafoil.nosePower = 0; % [-] Nosecone power type parameter
+parafoil.nosePMod = 1.293318e+00; % [-] P coefficient for modified nosecone shapes
+parafoil.noseCMod = 1.864832e-01; % [-] C coefficient for modified nosecone shapes
%% RCS
recovery = Recovery();
diff --git a/missions/2022_Pyxis_Roccaraso_September/old/simulationsData.m b/missions/2022_Pyxis_Roccaraso_September/old/simulationsData.m
index 8c241bbc49fdda0edfcd54044351e94274f0cd40..11aa4bf5e05b9221de2de54b1afcb7ad19159e80 100644
--- a/missions/2022_Pyxis_Roccaraso_September/old/simulationsData.m
+++ b/missions/2022_Pyxis_Roccaraso_September/old/simulationsData.m
@@ -197,7 +197,7 @@ settings.para(2, 1).nf = 8.7; % [/] Adimensional Opening Time
%%% PAYLOAD CHUTES
% parachute 1
-settings.para(1, 2).name = "Payload DROGUE";
+settings.para(1, 2).name = "Parafoil DROGUE";
settings.para(1, 2).S = 0.11; % [m^2] Surface
settings.para(1, 2).mass = 0.05; % [kg] Parachute Mass
settings.para(1, 2).CD = 1.2; % [/] Parachute Drag Coefficient
@@ -213,7 +213,7 @@ settings.para(1, 2).nf = 12; % [/] Adimensional Opening Time
settings.para(1, 2).Vexit = 10; % [m/s] Expulsion Speed
% parachute 2
-settings.para(2, 2).name = "Payload AIRFOIL";
+settings.para(2, 2).name = "Parafoil AIRFOIL";
settings.para(2, 2).mass = 0.45; % [kg] Parachute Mass
settings.para(2, 2).z_cut = 0; % [m] Final altitude of the parachute
diff --git a/missions/2023_Gemini_Portugal_October/config/paraConfig.m b/missions/2023_Gemini_Portugal_October/config/paraConfig.m
index 3ce7ff1798f83ba17360ff34b07766addb630b6e..2785d5acdefde8e03952e407aace6d7de605f3ea 100644
--- a/missions/2023_Gemini_Portugal_October/config/paraConfig.m
+++ b/missions/2023_Gemini_Portugal_October/config/paraConfig.m
@@ -41,7 +41,7 @@ para(2, 1).forceCoefficient = []; % [-] Empirical coefficient to obtain
% parachute 1
para(1, 2) = Parachute();
-para(1, 2).name = "Payload DROGUE";
+para(1, 2).name = "Parafoil 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
@@ -58,11 +58,11 @@ para(1, 2).expulsionSpeed = 10; % [m/s] Expulsion Speed
para(1, 2).forceCoefficient = []; % [-] Empirical coefficient to obtain correct peak force at deployment
% parachute 2
-para(2, 2) = Parafoil();
+para(2, 2) = Wing();
-para(2, 2).name = "Payload AIRFOIL";
-para(2, 2).mass = 4.20; % [kg] Parafoil Mass
-para(2, 2).openingTime = 0; % [s] Parafoil opening delay
+para(2, 2).name = "Parafoil AIRFOIL";
+para(2, 2).mass = 4.20; % [kg] Wing Mass
+para(2, 2).openingTime = 0; % [s] Wing opening delay
para(2, 2).surface = 0.11; % [m^2] Surface
para(2, 2).deltaSMax = 0.1; % max value
diff --git a/missions/2023_Gemini_Portugal_October/config/rocketConfig.m b/missions/2023_Gemini_Portugal_October/config/rocketConfig.m
index 2af81681af3442580829818fca7d07f47c6954c7..24d971d4ffc602aa29673b73b4770b31418f33c5 100644
--- a/missions/2023_Gemini_Portugal_October/config/rocketConfig.m
+++ b/missions/2023_Gemini_Portugal_October/config/rocketConfig.m
@@ -15,21 +15,21 @@ rocket.inertiaNoMotor = [0.06535397; 17.21019828; 17.21056483]; % [kg*m^2]
rocket.xCgNoMotor = 1.254; % [m] OVERRIDE xCg without motor
rocket.lengthCenterNoMot = 1.517; % [m] OVERRIDE Center length - no nose, no motor
-%% PLD - Includes Payload + Nose
-payload = Payload();
+%% PLD - Includes Parafoil + Nose
+parafoil = Parafoil();
% !!!!!
-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
+parafoil.length = 638.89 * 1e-3; % [m] Total bay length
+parafoil.mass = 4.441; % [kg] Total bay mass
+parafoil.inertia = 1e-9*[12431765; 106903809; 106823939]; % [kg*m^2] Total bay inertia (Body reference)
+parafoil.xCg = 479.24 * 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 = 1.250152e+00; % [-] P coefficient for modified nosecone shapes
-payload.noseCMod = 1.799127e-01; % [-] C coefficient for modified nosecone shapes
+parafoil.noseLength = 0.32; % [m] Nosecone length
+parafoil.noseType = 'MHAACK'; % [-] Nosecone shape
+parafoil.nosePower = 3/4; % [-] Nosecone power type parameter
+parafoil.nosePMod = 1.250152e+00; % [-] P coefficient for modified nosecone shapes
+parafoil.noseCMod = 1.799127e-01; % [-] C coefficient for modified nosecone shapes
%% RCS
recovery = Recovery();
diff --git a/missions/2023_Gemini_Portugal_October/old/simulationsData.m b/missions/2023_Gemini_Portugal_October/old/simulationsData.m
index 5f62802dcbccea003ff1862ad56da4693c42d8e2..1fd821dcb8b21d4fe04d9468c5c3029ab8183c71 100644
--- a/missions/2023_Gemini_Portugal_October/old/simulationsData.m
+++ b/missions/2023_Gemini_Portugal_October/old/simulationsData.m
@@ -271,7 +271,7 @@ settings.para(2, 1).nf = 8.7; % [/] Adimensional Opening Time
%%% PAYLOAD CHUTES
% parachute 1
-settings.para(1, 2).name = "Payload DROGUE";
+settings.para(1, 2).name = "Parafoil DROGUE";
settings.para(1, 2).S = 0.11; % [m^2] Surface
settings.para(1, 2).mass = 0.15; % [kg] Parachute Mass
settings.para(1, 2).CD = 1.2; % [/] Parachute Drag Coefficient
@@ -287,7 +287,7 @@ settings.para(1, 2).nf = 12; % [/] Adimensional Opening Time
settings.para(1, 2).Vexit = 10; % [m/s] Expulsion Speed
% parachute 2
-settings.para(2, 2).name = "Payload AIRFOIL";
+settings.para(2, 2).name = "Parafoil AIRFOIL";
settings.para(2, 2).mass = 0.50; % [kg] Parachute Mass
settings.para(2, 2).z_cut = 0; % [m] Final altitude of the parachute
diff --git a/missions/2023_Gemini_Roccaraso_September/config/paraConfig.m b/missions/2023_Gemini_Roccaraso_September/config/paraConfig.m
index 3d3ae9cc1676c4566ca344c381e24efc1e8ff5eb..c7cf8e7bd8ea5b823ff73a663f60ad9b7e7087d3 100644
--- a/missions/2023_Gemini_Roccaraso_September/config/paraConfig.m
+++ b/missions/2023_Gemini_Roccaraso_September/config/paraConfig.m
@@ -41,7 +41,7 @@ para(2, 1).forceCoefficient = []; % [-] Empirical coefficient to obtain c
% parachute 1
para(1, 2) = Parachute();
-para(1, 2).name = "Payload DROGUE";
+para(1, 2).name = "Parafoil 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
@@ -58,11 +58,11 @@ para(1, 2).expulsionSpeed = 10; % [m/s] Expulsion Speed
para(1, 2).forceCoefficient = []; % [-] Empirical coefficient to obtain correct peak force at deployment
% parachute 2
-para(2, 2) = Parafoil();
+para(2, 2) = Wing();
-para(2, 2).name = "Payload AIRFOIL";
-para(2, 2).mass = 4.20; % [kg] Parafoil Mass
-para(2, 2).openingTime = 0; % [s] Parafoil opening delay
+para(2, 2).name = "Parafoil AIRFOIL";
+para(2, 2).mass = 4.20; % [kg] Wing Mass
+para(2, 2).openingTime = 0; % [s] Wing opening delay
para(2, 2).surface = 0.11; % [m^2] Surface
para(2, 2).deltaSMax = 0.1; % max value
diff --git a/missions/2023_Gemini_Roccaraso_September/config/rocketConfig.m b/missions/2023_Gemini_Roccaraso_September/config/rocketConfig.m
index 142705caba9a8cedc760f82688f025c527a15ce5..c15b52c089b524b75ed1a3495c1f078c557d347b 100644
--- a/missions/2023_Gemini_Roccaraso_September/config/rocketConfig.m
+++ b/missions/2023_Gemini_Roccaraso_September/config/rocketConfig.m
@@ -15,21 +15,21 @@ rocket.inertiaNoMotor = [0.06535397; 12.07664659; 12.07701314]; % [kg*m^2]
rocket.xCgNoMotor = 1.149; % [m] OVERRIDE xCg without motor
rocket.lengthCenterNoMot = 1.517; % [m] OVERRIDE Center length - no nose, no motor
-%% PLD - Includes Payload + Nose
-payload = Payload();
+%% PLD - Includes Parafoil + Nose
+parafoil = Parafoil();
% !!!!!
-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
+parafoil.length = 638.89 * 1e-3; % [m] Total bay length
+parafoil.mass = 4.441; % [kg] Total bay mass
+parafoil.inertia = 1e-9*[12431765; 106903809; 106823939]; % [kg*m^2] Total bay inertia (Body reference)
+parafoil.xCg = 479.24 * 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 = 1.250152e+00; % [-] P coefficient for modified nosecone shapes
-payload.noseCMod = 1.799127e-01; % [-] C coefficient for modified nosecone shapes
+parafoil.noseLength = 0.32; % [m] Nosecone length
+parafoil.noseType = 'MHAACK'; % [-] Nosecone shape
+parafoil.nosePower = 3/4; % [-] Nosecone power type parameter
+parafoil.nosePMod = 1.250152e+00; % [-] P coefficient for modified nosecone shapes
+parafoil.noseCMod = 1.799127e-01; % [-] C coefficient for modified nosecone shapes
%% RCS
recovery = Recovery();
diff --git a/missions/2023_Gemini_Roccaraso_September/old/simulationsData.m b/missions/2023_Gemini_Roccaraso_September/old/simulationsData.m
index 9ad12523b74895fe9301ade2c6f86ae07c6eb9f0..457db24c06259857971c3da2ae46b017aced06a2 100644
--- a/missions/2023_Gemini_Roccaraso_September/old/simulationsData.m
+++ b/missions/2023_Gemini_Roccaraso_September/old/simulationsData.m
@@ -269,7 +269,7 @@ settings.para(2, 1).nf = 8.7; % [/] Adimensional Opening Time
%%% PAYLOAD CHUTES
% parachute 1
-settings.para(1, 2).name = "Payload DROGUE";
+settings.para(1, 2).name = "Parafoil DROGUE";
settings.para(1, 2).S = 0.11; % [m^2] Surface
settings.para(1, 2).mass = 0.15; % [kg] Parachute Mass
settings.para(1, 2).CD = 1.2; % [/] Parachute Drag Coefficient
@@ -285,7 +285,7 @@ settings.para(1, 2).nf = 12; % [/] Adimensional Opening Time
settings.para(1, 2).Vexit = 10; % [m/s] Expulsion Speed
% parachute 2
-settings.para(2, 2).name = "Payload AIRFOIL";
+settings.para(2, 2).name = "Parafoil AIRFOIL";
settings.para(2, 2).mass = 0.50; % [kg] Parachute Mass
settings.para(2, 2).z_cut = 0; % [m] Final altitude of the parachute
diff --git a/missions/2024_Lyra_Portugal_October/config/paraConfig.m b/missions/2024_Lyra_Portugal_October/config/paraConfig.m
index aa0a50ac796b31cba74b8cfdbbfc0fab3bea103d..109d02346c12d345675cc2412c831e6d9c4cfb86 100644
--- a/missions/2024_Lyra_Portugal_October/config/paraConfig.m
+++ b/missions/2024_Lyra_Portugal_October/config/paraConfig.m
@@ -41,7 +41,7 @@ para(2, 1).forceCoefficient = 2.2; % [-] Empirical coefficient to obtain
% parachute 1
para(1, 2) = Parachute();
-para(1, 2).name = "Payload DROGUE";
+para(1, 2).name = "Parafoil DROGUE";
para(1, 2).surface = 0.11; % [m^2] Surface
para(1, 2).mass = 0.1; % [kg] Parachute Mass
para(1, 2).cd = 1.2; % [/] Parachute Drag Coefficient
@@ -58,11 +58,11 @@ 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) = Wing();
-para(2, 2).name = "Payload AIRFOIL";
-para(2, 2).mass = 0.40; % [kg] Parafoil Mass
-para(2, 2).openingTime = 0; % [s] Parafoil opening delay
+para(2, 2).name = "Parafoil AIRFOIL";
+para(2, 2).mass = 0.40; % [kg] Wing Mass
+para(2, 2).openingTime = 0; % [s] Wing opening delay
para(2, 2).surface = 0.11; % [m^2] Surface
para(2, 2).deltaSMax = 0.1; % max value
diff --git a/missions/2024_Lyra_Portugal_October/config/rocketConfig.m b/missions/2024_Lyra_Portugal_October/config/rocketConfig.m
index 6bc8bb289b77386b83d9899382fae46e4855e16b..be779ec9220dbdcb5797577e7417102f0504ad35 100644
--- a/missions/2024_Lyra_Portugal_October/config/rocketConfig.m
+++ b/missions/2024_Lyra_Portugal_October/config/rocketConfig.m
@@ -9,19 +9,19 @@ rocket.inertiaNoMotor = []; % [kg*m^
rocket.xCgNoMotor = []; % [m] OVERRIDE xCg without motor
rocket.lengthCenterNoMot = []; % [m] OVERRIDE Center length - no nose, no motor
-%% PLD - Includes Payload + Nose
-payload = Payload();
-
-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 = 1.250152e+00; % [-] P coefficient for modified nosecone shapes
-payload.noseCMod = 1.799127e-01; % [-] C coefficient for modified nosecone shapes
+%% PLD - Includes Parafoil + Nose
+parafoil = Parafoil();
+
+parafoil.length = 647.25 * 1e-3; % [m] Total bay length
+parafoil.mass = 4.401; % [kg] Total bay mass
+parafoil.inertia = 1e-9*[12531966; 109986813; 109930516]; % [kg*m^2] Total bay inertia (Body reference)
+parafoil.xCg = 487.78 * 1e-3; % [m] Cg relative to bay upper side
+
+parafoil.noseLength = 0.32; % [m] Nosecone length
+parafoil.noseType = 'MHAACK'; % [-] Nosecone shape
+parafoil.nosePower = 3/4; % [-] Nosecone power type parameter
+parafoil.nosePMod = 1.250152e+00; % [-] P coefficient for modified nosecone shapes
+parafoil.noseCMod = 1.799127e-01; % [-] C coefficient for modified nosecone shapes
%% RCS
recovery = Recovery();
diff --git a/missions/2024_Lyra_Roccaraso_September/config/paraConfig.m b/missions/2024_Lyra_Roccaraso_September/config/paraConfig.m
index 80f10dae397f28bea09650adb0ab541f5f1d2090..18e99a4d078ba90f4d3c4254cfa6244b24c642ff 100644
--- a/missions/2024_Lyra_Roccaraso_September/config/paraConfig.m
+++ b/missions/2024_Lyra_Roccaraso_September/config/paraConfig.m
@@ -42,7 +42,7 @@ para(2, 1).forceCoefficient = 2.2; % [-] Empirical coefficient to obtain
% parachute 1
para(1, 2) = Parachute();
-para(1, 2).name = "Payload DROGUE";
+para(1, 2).name = "Parafoil DROGUE";
para(1, 2).surface = 0.11; % [m^2] Surface
para(1, 2).mass = 0.1; % [kg] Parachute Mass
para(1, 2).cd = 1.2; % [/] Parachute Drag Coefficient
@@ -59,11 +59,11 @@ 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) = Wing();
-para(2, 2).name = "Payload AIRFOIL";
-para(2, 2).mass = 0.40; % [kg] Parafoil Mass
-para(2, 2).openingTime = 0; % [s] Parafoil opening delay
+para(2, 2).name = "Parafoil AIRFOIL";
+para(2, 2).mass = 0.40; % [kg] Wing Mass
+para(2, 2).openingTime = 0; % [s] Wing opening delay
para(2, 2).surface = 0.11; % [m^2] Surface
para(2, 2).deltaSMax = 0.1; % max value
diff --git a/missions/2024_Lyra_Roccaraso_September/config/rocketConfig.m b/missions/2024_Lyra_Roccaraso_September/config/rocketConfig.m
index bcc3bb6fcdf2897a46ea8920d80f6cc3ad9fdee6..4f90b9bebe7737b782d435d3ed75aa38a31a52e4 100644
--- a/missions/2024_Lyra_Roccaraso_September/config/rocketConfig.m
+++ b/missions/2024_Lyra_Roccaraso_September/config/rocketConfig.m
@@ -15,19 +15,19 @@ rocket.lengthCenterNoMot = []; % [m]
% 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 = 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 = 1.250152e+00; % [-] P coefficient for modified nosecone shapes
-payload.noseCMod = 1.799127e-01; % [-] C coefficient for modified nosecone shapes
+%% PLD - Includes Parafoil + Nose
+parafoil = Parafoil();
+
+parafoil.length = 647.25 * 1e-3; % [m] Total bay length
+parafoil.mass = 4.401; % [kg] Total bay mass
+parafoil.inertia = 1e-9*[12531966; 109986813; 109930516]; % [kg*m^2] Total bay inertia (Body reference)
+parafoil.xCg = 487.78 * 1e-3; % [m] Cg relative to bay upper side
+
+parafoil.noseLength = 0.32; % [m] Nosecone length
+parafoil.noseType = 'MHAACK'; % [-] Nosecone shape
+parafoil.nosePower = 3/4; % [-] Nosecone power type parameter
+parafoil.nosePMod = 1.250152e+00; % [-] P coefficient for modified nosecone shapes
+parafoil.noseCMod = 1.799127e-01; % [-] C coefficient for modified nosecone shapes
%% RCS
recovery = Recovery();
diff --git a/missions/2025_Orion_Portugal_October/config/paraConfig.m b/missions/2025_Orion_Portugal_October/config/paraConfig.m
index aa0a50ac796b31cba74b8cfdbbfc0fab3bea103d..109d02346c12d345675cc2412c831e6d9c4cfb86 100644
--- a/missions/2025_Orion_Portugal_October/config/paraConfig.m
+++ b/missions/2025_Orion_Portugal_October/config/paraConfig.m
@@ -41,7 +41,7 @@ para(2, 1).forceCoefficient = 2.2; % [-] Empirical coefficient to obtain
% parachute 1
para(1, 2) = Parachute();
-para(1, 2).name = "Payload DROGUE";
+para(1, 2).name = "Parafoil DROGUE";
para(1, 2).surface = 0.11; % [m^2] Surface
para(1, 2).mass = 0.1; % [kg] Parachute Mass
para(1, 2).cd = 1.2; % [/] Parachute Drag Coefficient
@@ -58,11 +58,11 @@ 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) = Wing();
-para(2, 2).name = "Payload AIRFOIL";
-para(2, 2).mass = 0.40; % [kg] Parafoil Mass
-para(2, 2).openingTime = 0; % [s] Parafoil opening delay
+para(2, 2).name = "Parafoil AIRFOIL";
+para(2, 2).mass = 0.40; % [kg] Wing Mass
+para(2, 2).openingTime = 0; % [s] Wing opening delay
para(2, 2).surface = 0.11; % [m^2] Surface
para(2, 2).deltaSMax = 0.1; % max value
diff --git a/missions/2025_Orion_Portugal_October/config/rocketConfig.m b/missions/2025_Orion_Portugal_October/config/rocketConfig.m
index 7a1c447354e008038928afde85dd6dbd2ea4cea8..6a9b264fdfd6f0b1978160f24a21db1517929d95 100644
--- a/missions/2025_Orion_Portugal_October/config/rocketConfig.m
+++ b/missions/2025_Orion_Portugal_October/config/rocketConfig.m
@@ -9,19 +9,19 @@ rocket.inertiaNoMotor = []; % [kg*m^
rocket.xCgNoMotor = []; % [m] OVERRIDE xCg without motor
rocket.lengthCenterNoMot = []; % [m] OVERRIDE Center length - no nose, no motor
-%% PLD - Includes Payload + Nose
-payload = Payload();
-
-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 = 1.250152e+00; % [-] P coefficient for modified nosecone shapes
-payload.noseCMod = 1.799127e-01; % [-] C coefficient for modified nosecone shapes
+%% PLD - Includes Parafoil + Nose
+parafoil = Parafoil();
+
+parafoil.length = 647.25 * 1e-3; % [m] Total bay length
+parafoil.mass = 4.401; % [kg] Total bay mass
+parafoil.inertia = 1e-9*[12531966; 109986813; 109930516]; % [kg*m^2] Total bay inertia (Body reference)
+parafoil.xCg = 487.78 * 1e-3; % [m] Cg relative to bay upper side
+
+parafoil.noseLength = 0.32; % [m] Nosecone length
+parafoil.noseType = 'MHAACK'; % [-] Nosecone shape
+parafoil.nosePower = 3/4; % [-] Nosecone power type parameter
+parafoil.nosePMod = 1.250152e+00; % [-] P coefficient for modified nosecone shapes
+parafoil.noseCMod = 1.799127e-01; % [-] C coefficient for modified nosecone shapes
%% RCS
recovery = Recovery();
diff --git a/missions/2025_Orion_Roccaraso_Settember/config/paraConfig.m b/missions/2025_Orion_Roccaraso_Settember/config/paraConfig.m
index 80f10dae397f28bea09650adb0ab541f5f1d2090..18e99a4d078ba90f4d3c4254cfa6244b24c642ff 100644
--- a/missions/2025_Orion_Roccaraso_Settember/config/paraConfig.m
+++ b/missions/2025_Orion_Roccaraso_Settember/config/paraConfig.m
@@ -42,7 +42,7 @@ para(2, 1).forceCoefficient = 2.2; % [-] Empirical coefficient to obtain
% parachute 1
para(1, 2) = Parachute();
-para(1, 2).name = "Payload DROGUE";
+para(1, 2).name = "Parafoil DROGUE";
para(1, 2).surface = 0.11; % [m^2] Surface
para(1, 2).mass = 0.1; % [kg] Parachute Mass
para(1, 2).cd = 1.2; % [/] Parachute Drag Coefficient
@@ -59,11 +59,11 @@ 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) = Wing();
-para(2, 2).name = "Payload AIRFOIL";
-para(2, 2).mass = 0.40; % [kg] Parafoil Mass
-para(2, 2).openingTime = 0; % [s] Parafoil opening delay
+para(2, 2).name = "Parafoil AIRFOIL";
+para(2, 2).mass = 0.40; % [kg] Wing Mass
+para(2, 2).openingTime = 0; % [s] Wing opening delay
para(2, 2).surface = 0.11; % [m^2] Surface
para(2, 2).deltaSMax = 0.1; % max value
diff --git a/missions/2025_Orion_Roccaraso_Settember/config/rocketConfig.m b/missions/2025_Orion_Roccaraso_Settember/config/rocketConfig.m
index bcc3bb6fcdf2897a46ea8920d80f6cc3ad9fdee6..4f90b9bebe7737b782d435d3ed75aa38a31a52e4 100644
--- a/missions/2025_Orion_Roccaraso_Settember/config/rocketConfig.m
+++ b/missions/2025_Orion_Roccaraso_Settember/config/rocketConfig.m
@@ -15,19 +15,19 @@ rocket.lengthCenterNoMot = []; % [m]
% 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 = 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 = 1.250152e+00; % [-] P coefficient for modified nosecone shapes
-payload.noseCMod = 1.799127e-01; % [-] C coefficient for modified nosecone shapes
+%% PLD - Includes Parafoil + Nose
+parafoil = Parafoil();
+
+parafoil.length = 647.25 * 1e-3; % [m] Total bay length
+parafoil.mass = 4.401; % [kg] Total bay mass
+parafoil.inertia = 1e-9*[12531966; 109986813; 109930516]; % [kg*m^2] Total bay inertia (Body reference)
+parafoil.xCg = 487.78 * 1e-3; % [m] Cg relative to bay upper side
+
+parafoil.noseLength = 0.32; % [m] Nosecone length
+parafoil.noseType = 'MHAACK'; % [-] Nosecone shape
+parafoil.nosePower = 3/4; % [-] Nosecone power type parameter
+parafoil.nosePMod = 1.250152e+00; % [-] P coefficient for modified nosecone shapes
+parafoil.noseCMod = 1.799127e-01; % [-] C coefficient for modified nosecone shapes
%% RCS
recovery = Recovery();