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Commit d1922167 authored by giuliaghirardini's avatar giuliaghirardini Committed by Marco Luigi Gaibotti
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[refactoring-missions][2021_Lynx_Roccaraso_September] No parafoil needed for...

[refactoring-missions][2021_Lynx_Roccaraso_September] No parafoil needed for Lynx, deleted parafoil data
parent ed1396e0
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1 merge request!5Refactoring missions
...@@ -36,60 +36,3 @@ para(2, 1).m = 1; % [m^2/s] Coefficient of the surface v ...@@ -36,60 +36,3 @@ para(2, 1).m = 1; % [m^2/s] Coefficient of the surface v
para(2, 1).nf = 8.7; % [/] Adimensional Opening Time para(2, 1).nf = 8.7; % [/] Adimensional Opening Time
para(2 ,1).expulsionSpeed = 0; % [m/s] Expulsion Speed para(2 ,1).expulsionSpeed = 0; % [m/s] Expulsion Speed
para(2, 1).forceCoefficient = []; % [-] Empirical coefficient to obtain correct peak force at deployment 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
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