Implemented UI.

eclipse.m

@@ -1,21 +1,20 @@
-function dTdt = eclipse(time_eclipse, initial_T)
-%ECLIPSE Thermal transient for the satellite's eclipse period.
-    load('satellite_properties');
+function dTdt = eclipse(time_eclipse, initial_T, satprop)
+%ECLIPSE Thermal transient analysis for the satellite's eclipse period.
 
     % Stefan-Boltzmann constant
     sigma = 5.67e-8; % W/(m^2*K^4)
 
-    % No power absorbed by the surface.
+    % No power absorbed by the surface (qa).
     % Because during eclipse the Solar Constant S = 0.
-    % So sat.qa = 0.
+    % So qa = 0.
 
     % Power emitted by the surface:
-    qe = sat.epsilon * sat.Ae * sigma * initial_T^4;
+    qe = satprop.coating.epsilon * satprop.Ae * sigma * initial_T^4;
 
-    % No external heating source during eclise so sat.qs = 0.
-    % This means that (sat.qs / (sat.m * sat.c) = 0
+    % No external heating source during eclise so satprop.radiating_heat = 0.
+    % This means that satprop.radiating_heat / (satprop.mass * satprop.thermal_capacity) = 0
 
     % The transient expression becomes:
-    dTdt = -qe / (sat.m * sat.c);
+    dTdt = -qe / (satprop.mass * satprop.thermal_capacity);
 
 end

simulate.m

@@ -0,0 +1,43 @@
+function [time_span, T_C] = simulate(orbit, satprop)
+%SIMULATE Simulates the satellite's thermal transience and returns it's
+    % temperature data over time (in Celsius and minutes respectively).
+
+    % List that will contain data to plott.
+    time_span = []
+    T_K = []
+
+    % ode45 options.
+    options = odeset('RelTol', 1e-8, 'AbsTol', 1e-8); % Accuracy.
+
+    m = 0;
+    n = 0;
+
+    for i = (1: 1: orbit.num)
+
+        % Eclipse phase.
+        if exist('T_sun', 'var') == 1
+            satprop.T0_K = T_sun(end);
+        end
+
+        tspan = [m * orbit.T_ecl + n * orbit.T_sun_ill: 1: (m+1) * orbit.T_ecl + n * orbit.T_sun_ill];
+        [time_eclipse, T_eclipse] = ode45(@(t,y) eclipse(t, y, satprop), tspan, satprop.T0_K, options);
+
+        m = m + 1;
+
+        % Sun illuminated phase.
+        satprop.T0_K = T_eclipse(end);
+        tspan = [m * orbit.T_ecl + n * orbit.T_sun_ill: 1: m * orbit.T_ecl + (n+1) * orbit.T_sun_ill];
+        [time_sun, T_sun] = ode45(@(t,y) sun(t, y, satprop), tspan, satprop.T0_K, options);
+
+        n = n + 1;
+
+        time_span = [time_span; time_eclipse; time_sun];
+        T_K = [T_K; T_eclipse; T_sun];
+    end
+
+    % Time span in minutes.
+    time_span = time_span / 60; 
+
+    % Temperature in Celsius.
+    T_C = T_K - 273;
+end

sun.m

@@ -1,19 +1,18 @@
-function dTdt = sun(time_sun, initial_T)
-%SUN Thermal transient for the satellite's sun illuminated period.
-    load('satellite_properties');  
-
+function dTdt = sun(time_sun, initial_T, satprop)
+%SUN Thermal transient analysis for the satellite's sun illuminated period.
+
     % Stefan-Boltzmann constant.
     sigma = 5.67e-8; % W/(m^2*K^4)
 
     % Solar constant.
     S = 1378;
 
     % Power absorbed by the surface.
-    qa = sat.alpha * sat.Aa * S;
+    qa = satprop.coating.alpha * satprop.Aa * S;
 
     % Power emitted by the surface.
-    qe = sat.epsilon * sat.Ae * sigma * initial_T^4;
+    qe = satprop.coating.epsilon * satprop.Ae * sigma * initial_T^4;
 
-    dTdt = (1 / (sat.m * sat.c)) * (qa - qe) + (sat.qs / (sat.m * sat.c));
+    dTdt = (1 / (satprop.mass * satprop.thermal_capacity)) * (qa - qe) + (satprop.radiating_heat / (satprop.mass * satprop.thermal_capacity));
 end