Rework MTOW calculations and automate design point calculation process

- Fix time calculation bugs in MTOW
- Rework the way battery and fuel weight is calculated in MTOW function
- Add transition mission segment type
- Fix MATLAB's JSON output with `prettyjson` function
- Update mission plotting
- Update drag and lift slope calculation
- Automate design point calculation
- Update example project file

adt.m

@@ -4,11 +4,9 @@
 %
 % This file is subject to the license terms in the LICENSE file included in this distribution
 
-function data = adt(open_filename, varargin)
-close all;
-
+function data = adt(filename, varargin)
 %% Load project file
-data = load_project(open_filename);
+data = load_project(filename);
 
 %% Concept
 data.concept = ahp(data.concept);
@@ -18,30 +16,27 @@
 constants.g = 9.81; % m/s^2
 constants.e = 0.85; % Oswald efficiency number.
 
-data.aircraft.propulsion.total_efficiency = data.aircraft.propulsion.prop_efficiency * data.aircraft.propulsion.gear_efficiency * data.aircraft.propulsion.em_efficiency * data.aircraft.propulsion.esc_efficiency * data.aircraft.propulsion.dist_efficiency;
-data.mission.mf_prop = estimate_mf_prop(1.2, 0.04, 1.5, 0.3, 0.1, 0.5, data.aircraft.propulsion.config);
-data.mission.mf_subs = estimate_mf_subs(data.mission.mf_prop, data.mission.mf_struct);
-
-% Take-off mass estimation
-[data.mission, data.aircraft] = mtow(data.mission, data.aircraft, constants);
+% Build mission profile
+data.mission = build_mission(data.mission);
 
 %% Plot mission profile
 plot_mission(data.mission);
 
+% Take-off mass estimation
+[data.mission, data.aircraft] = mtow(data.mission, data.aircraft, constants);
+
 %% Design point calculation
 data.aircraft = design_point(data.mission, data.aircraft, constants);
 
-%% Engine selection
-data.mission.mf_prop = data.aircraft.propulsion.mass / data.aircraft.mass_to;
-
-%% Lifting surface design
-data.aircraft = lifting_surface(data.aircraft, data.mission.segments{3});
+% Recalculate take-off mass based on updated values from design point
+% [data.mission, data.aircraft] = mtow(data.mission, data.aircraft, constants);
+% data.aircraft = design_point(data.mission, data.aircraft, constants);
 
-%% Fuselage design
-data.aircraft = fuselage(data.aircraft, data.mission.segments{3});
+%% Lift curve slope
+data.aircraft = lift_slope(data.aircraft, data.mission);
 
 %% Drag buildup
-data.aircraft = drag_buildup(data.aircraft);
+data.aircraft = drag_buildup(data.aircraft, data.mission);
 
 %% Save new project file
 if ~isempty(varargin)

build_mission.m

@@ -0,0 +1,49 @@
+% Aircraft design tool
+%
+% Mario Bras ([email protected]) and Ricardo Marques ([email protected]) 2019
+%
+% This file is subject to the license terms in the LICENSE file included in this distribution
+
+function mission = build_mission(mission)
+
+% Iterate over mission segments
+for i = 1 : length(mission.segments)
+    [mission.segments{i}.temperature, mission.segments{i}.speed_sound, mission.segments{i}.pressure, mission.segments{i}.density] = atmosisa(mission.segments{i}.altitude);
+
+    if ~isfield(mission.segments{i}, 'velocity')
+        mission.segments{i}.velocity = 0;
+    end
+
+    if strcmp(mission.segments{i}.type, 'taxi') % Taxi segment
+        mission.segments{i}.range = 0;
+    elseif strcmp(mission.segments{i}.type, 'hover') % Hover segment
+        mission.segments{i}.range = 0;
+    elseif strcmp(mission.segments{i}.type, 'transition') % Transition segment
+        mission.segments{i}.range = mean(mission.segments{i}.velocity) * mission.segments{i}.time;
+    elseif strcmp(mission.segments{i}.type, 'climb') % Climb segment
+        mission.segments{i}.time = (mission.segments{i}.altitude(2) - mission.segments{i}.altitude(1)) / mission.segments{i}.velocity / sind(mission.segments{i}.angle);
+        mission.segments{i}.range = mission.segments{i}.velocity * mission.segments{i}.time * cosd(mission.segments{i}.angle);
+    elseif strcmp(mission.segments{i}.type, 'vertical_climb') % Vertical climb segment
+        mission.segments{i}.time = (mission.segments{i}.altitude(2) - mission.segments{i}.altitude(1)) / mission.segments{i}.velocity;
+        mission.segments{i}.range = 0;
+    elseif strcmp(mission.segments{i}.type, 'acceleration') % Acceleration segment
+        mission.segments{i}.range = mission.segments{i}.velocity * mission.segments{i}.time;
+    elseif strcmp(mission.segments{i}.type, 'cruise') % Cruise segment
+        mission.segments{i}.time = mission.segments{i}.range / mission.segments{i}.velocity;
+    elseif strcmp(mission.segments{i}.type, 'hold') % Hold segment
+        mission.segments{i}.range = mission.segments{i}.velocity * mission.segments{i}.time;
+    % elseif strcmp(mission.segments{i}.type, 'combat') % Combat segment
+    elseif strcmp(mission.segments{i}.type, 'descent') % Descent segment
+        mission.segments{i}.time = abs(mission.segments{i}.altitude(2) - mission.segments{i}.altitude(1)) / abs(mission.segments{i}.velocity) / abs(sind(mission.segments{i}.angle));
+        mission.segments{i}.range = abs(mission.segments{i}.velocity) * mission.segments{i}.time * abs(cosd(mission.segments{i}.angle));
+    elseif strcmp(mission.segments{i}.type, 'vertical_descent') % Vertical descent segment
+        mission.segments{i}.time = abs(mission.segments{i}.altitude(2) - mission.segments{i}.altitude(1)) / abs(mission.segments{i}.velocity);
+        mission.segments{i}.range = 0;
+    elseif strcmp(mission.segments{i}.type, 'landing') % Landing segment
+        mission.segments{i}.range = 0;
+    elseif strcmp(mission.segments{i}.type, 'drop') % Drop segment
+        mission.segments{i}.range = 0;
+    elseif strcmp(mission.segments{i}.type, 'load') % Load segment
+        mission.segments{i}.range = 0;
+    end
+end