[refactoring-ode][functions] Updated descentParachute

functions/odeFunctions/descentParachute.m

-function [dY, parout] = descentParachute(t, Y, rocket, environment, wind, parachute, newSettings, descent_data)
+function [dY, parout] = descentParachute(t, Y, rocket, environment, wind, parachute, settings, descentData)
 arguments
     t
     Y
@@ -6,8 +6,8 @@ arguments
     environment     Environment
     wind            WindCustom {mustBeA(wind, {'WindCustom', 'WindMatlab'})}
     parachute       Parachute
-    newSettings     Settings
-    descent_data    struct
+    settings        Settings
+    descentData    struct
 end
 %{
 descentParachute - ode function of the descent with parachute
@@ -40,23 +40,23 @@ SPDX-License-Identifier: GPL-3.0-or-later
 %% recalling the state
 % x = Y(1);
 % y = Y(2);
-z = Y(3);
+altitude = -Y(3);
 u = Y(4);
 v = Y(5);
 w = Y(6);
 
 %% CONSTANTS          
 
-if newSettings.simulator.stochNumber > 1
+if isfield(settings.simulator.stochNumber)
     % para = settings.stoch.para;
 else
-    para = descent_data.para; % defined in stdRun {para = i; settings.paraNumber = para;}
+    para = descentData.para; % defined in stdRun {para = i; settings.paraNumber = para;}
 end
-stage = descent_data.stage;
+stage = descentData.stage;
 
-S = parachute(para, stage).S;          % [m^2]   Surface
-CD = parachute(para, stage).CD;        % [/] Parachute Drag Coefficient
-CL = parachute(para, stage).CL;        % [/] Parachute Lift Coefficient
+S = parachute(para, stage).surface;          % [m^2]   Surface
+CD = parachute(para, stage).cd;        % [/] Parachute Drag Coefficient
+CL = parachute(para, stage).cl;        % [/] Parachute Lift Coefficient
 
 if stage == 1
     m = rocket.motor.structureMass - sum(rocket.stagesMass) - sum([parachute(:, stage+1:end).mass]);
@@ -64,13 +64,13 @@ else
     m = rocket.stagesMass(stage-1) + sum([parachute(:, stage).mass]);
 end
 
-g = environment.g0/(1 + (-z*1e-3/6371))^2;                                         % [N/kg]  module of gravitational field
+g = environment.g0/(1 + (altitude*1e-3/6371))^2;                                         % [N/kg]  module of gravitational field
 
 %% ADDING WIND (supposed to be added in NED axes);
 if isa(wind, 'WindMatlab')
-    [uw, vw, ww] = wind.getVels(z, t);
+    [uw, vw, ww] = wind.getVels(altitude, t);
 else
-    [uw, vw, ww] = wind.getVels(-z);
+    [uw, vw, ww] = wind.getVels(altitude);
 end
 
 windVels = [uw vw ww];
@@ -83,8 +83,8 @@ wr = w - windVels(3);
 V_norm = norm([ur vr wr]);
 
 %% ATMOSPHERE DATA
-absoluteAltitude = -z + environment.z0;
-[~, a, P, rho] = atmosphereData(absoluteAltitude, g, local);
+absoluteAltitude = altitude + environment.z0;
+[~, ~, P, rho] = atmosphereData(absoluteAltitude, g, local);
 
 %% REFERENCE FRAME
 % The parachutes are approximated as rectangular surfaces with the normal