diff --git a/missions/2021_Lynx_Roccaraso_September/config/paraConfig.m b/missions/2021_Lynx_Roccaraso_September/config/paraConfig.m
index fbd7712f52d6a5598e8a29d4bf22f2b7c0b9f45d..e1fffd92040d1de3350d65930ef2a2744e8da606 100644
--- a/missions/2021_Lynx_Roccaraso_September/config/paraConfig.m
+++ b/missions/2021_Lynx_Roccaraso_September/config/paraConfig.m
@@ -35,61 +35,4 @@ para(2, 1).chordC = 0;                    % [Ns/m] Shock Chord Dynamic Coefficie
 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 = [];        % [-] 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 = 0.05;                   % [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 = [];          % [-] 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 = 0.45;                   % [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;              % 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;
-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;              % [m] Final altitude of the parachute
-% CD
-para(2, 2).cd0           =  0.25; 
-para(2, 2).cdAlpha       =  0.12;
-para(2, 2).cdSurface      =  0.01;
-% CL
-para(2, 2).cl0           =  0.091;
-para(2, 2).clAlpha       =  0.9;
-para(2, 2).clSurface      = -0.0035;
-para(2, 2).cLP           = -0.84;
-para(2, 2).cLPhi         = -0.1;
-para(2, 2).cLSurface      = -0.0035;
-% CM
-para(2, 2).cM0           =  0.35; 
-para(2, 2).cMAlpha       = -0.72;
-para(2, 2).cMQ           = -1.49;
-% CN
-para(2, 2).cNR           = -0.27;
-para(2, 2).cNSurface      =  0.0115;
\ No newline at end of file
+para(2, 1).forceCoefficient = [];        % [-] Empirical coefficient to obtain correct peak force at deployment
\ No newline at end of file