diff --git a/classes/@Rocket/Rocket.m b/classes/@Rocket/Rocket.m
new file mode 100644
index 0000000000000000000000000000000000000000..61d7be1f25676c96bd1604232b6c8e6f1264ffb5
--- /dev/null
+++ b/classes/@Rocket/Rocket.m
@@ -0,0 +1,226 @@
+classdef Rocket < Config
+ % Rocket: Contains and manages all bays
+ %
+ % Constructor:
+ % - Rocket: Creates an instance of the Rocket class.
+ % Loaded config: rocketConfig.m > rocket (for overrides)
+ % Loaded data: -
+ % Arguments:
+ % - mission: Mission, mission object
+ % - varIn: (optional) config source. Alternative to config.m
+ % file
+
+ %% Derived properties
+ properties(SetAccess = private)
+ time double % [s] Timestamps vector
+ cutoffTime (1, 1) double % [s] Shutdown time
+ cutoffMass (1, 1) double % [m] Total mass at motor cutoff
+ cutoffInertia (3, 1) double % [kg*m^2] Total inertia at motor cutoff
+ inertiaDot (3, :) double % [kg*m^2/s]Total inertia time derivative
+
+ stagesMass double % [kg] Mass of stage 2, 3, .. without chutes
+ crossSection (1, 1) double % [m^2] Rocket cross sectional area
+ end
+
+ properties(Dependent)
+ %% BAYS
+ parafoil Parafoil % [-] Parafoil bay
+ recovery Recovery % [-] Recovery bay
+ electronics Electronics % [-] Electronics bay
+ airbrakes Airbrakes % [-] Airbrakes bay
+ motor Motor % [-] Motor bay
+ rear Rear % [-] Rear bay
+
+ %% GEOMETRY
+ length (1, 1) double % [m] Total length
+ lengthCenter (1, 1) double % [m] Center length - no nose, boat
+ lengthCenterNoMotor (1, 1) double % [m] Center length - no nose, boat, motor
+ diameter (1, 1) double % [m] Diameter
+
+ %% MASS PROPERTIES
+ mass (1, :) double % [kg] Total mass
+ massNoMotor (1, 1) double % [kg] Mass without motor
+ inertia (3, :) double % [kg*m^2] Total inertia - Axibody reference
+ inertiaNoMotor (3, 1) double % [kg*m^2] Inertia without motor
+ xcg (1, :) double % [m] Total xCg
+ xcgNoMotor (1, 1) double % [m] xCg without motor
+ end
+
+ properties
+ pitot Pitot % [-] Pitot component
+ parachutes cell % [-] (nParachutes, nStages) Parachutes onboard
+
+ coefficients struct % [-] Aerodynamic coefficients
+ end
+
+ properties(Access = private)
+ bays string % [-] Ordered list of bay names
+ baysNoMotor string % [-] Ordered list of bay names, without motor
+ bayStatus dictionary % [-] Dictionary containing initialisation flag for bays
+ overrides dictionary % [-] Dictionary containing overrides
+ mission Mission
+ end
+
+ %% Cached properties
+ properties(Access = private)
+ PARAFOIL
+ RECOVERY
+ ELECTRONICS
+ AIRBRAKES
+ MOTOR
+ REAR
+
+ LENGTH
+ LENGTH_CENTER
+ LENGTH_CENTER_NO_MOTOR
+ DIAMETER
+
+ MASS
+ MASS_NO_MOTOR
+
+ INERTIA
+ INERTIA_NO_MOTOR
+
+ XCG
+ XCG_NO_MOTOR
+ end
+
+ %% Config implementation
+ properties(Constant, Hidden, Access = protected)
+ configName = 'rocketConfig.m'
+ variableName = ''
+ end
+
+ methods
+ function obj = Rocket(mission, varsIn, options)
+ arguments
+ mission Mission = Mission()
+ varsIn struct = []
+ options.loadCoefficients logical = true
+ options.checkGeometry logical = true
+ end
+ obj@Config(mission, varsIn);
+ if isempty(mission.name), return; end
+
+ %% Initialize base properties
+ bayNames = camel2UpperSnake(obj.getProperties(Superclass='Bay'));
+ bayStatus = cellstr(bayNames);
+ [bayStatus{2, :}] = deal(false);
+ obj.bayStatus = dictionary(bayStatus{:});
+ obj.bays = bayNames;
+ obj.baysNoMotor = setdiff(bayNames, "MOTOR", 'stable');
+
+ % Remove bays from overridables, as they do not require override
+ overridables = camel2UpperSnake( ...
+ obj.getProperties('Dependent', true, 'SetAccess', 'public'));
+ overridables = cellstr(setdiff(overridables, bayNames));
+ [overridables{2, :}] = deal(false);
+ obj.overrides = dictionary(overridables{:});
+
+ %% Loading data
+ if isempty(varsIn)
+ varsIn = obj.getConfig(mission.configPath);
+ end
+
+ obj.parafoil = Parafoil(mission, varsIn);
+ obj.recovery = Recovery(mission, varsIn);
+ obj.electronics = Electronics(mission, varsIn);
+ obj.motor = Motor(mission, varsIn);
+ obj.airbrakes = Airbrakes(mission, varsIn);
+ obj.rear = Rear(mission, varsIn);
+
+ obj.pitot = Pitot(mission, varsIn);
+ paraLoader = ParaLoader(mission);
+ obj.parachutes = paraLoader.parachutes;
+
+ if options.loadCoefficients
+ obj.loadData();
+ answer = '';
+ if isempty(obj.coefficients) || isempty(obj.coefficientsHighAOA)
+ answer = questdlg(['Coefficient matrices not found. ' ...
+ 'Do you want to create new matrices?']);
+ elseif options.checkGeometry && ~all(obj.checkGeometry())
+ answer = questdlg(['Coefficient matrices differ from rocket geometry. ' ...
+ 'Do you want to create new matrices?']);
+ end
+
+ switch answer
+ case 'Yes'
+ parserPath = fullfile(mission.msaPath, 'autoMatricesProtub');
+ addpath(genpath(parserPath));
+ mainAutoMatProtub(obj);
+ obj.loadData();
+ case 'Cancel'
+ error('Rocket creation aborted')
+ otherwise
+ end
+ end
+ end
+ end
+
+ methods
+ [coeffsValues, angle0] = interpCoeffs(obj, t, alpha, mach, beta, alt, c)
+ checks = checkGeometry(obj)
+ img = plot(obj)
+ end
+
+ methods(Access = private)
+ obj = loadData(obj)
+ obj = updateBay(obj, bayName, value)
+ obj = updateNoMotor(obj);
+ obj = update(obj);
+ end
+
+ methods
+ function obj = set.parafoil(obj, value), obj = obj.updateBay('PARAFOIL', value); end
+ function obj = set.recovery(obj, value), obj = obj.updateBay('RECOVERY', value); end
+ function obj = set.electronics(obj, value), obj = obj.updateBay('ELECTRONICS', value); end
+ function obj = set.airbrakes(obj, value), obj = obj.updateBay('AIRBRAKES', value); end
+ function obj = set.motor(obj, value)
+ obj = obj.updateBay('MOTOR', value);
+ obj.time = value.time;
+ obj.cutoffTime = value.cutoffTime;
+ end
+ function obj = set.rear(obj, value), obj = obj.updateBay('REAR', value); end
+
+
+ function obj = set.length(obj, value), obj = obj.updateOverridable('LENGTH', value); end
+ function obj = set.lengthCenter(obj, value), obj = obj.updateOverridable('LENGTH_CENTER', value); end
+ function obj = set.lengthCenterNoMotor(obj, value), obj = obj.updateOverridable('LENGTH_CENTER_NO_MOTOR', value); end
+ function obj = set.diameter(obj, value)
+ obj.DIAMETER = value;
+ obj.crossSection = 0.25*pi*value^2;
+ end
+
+ function obj = set.mass(obj, value), obj = obj.updateOverridable('MASS', value); end
+ function obj = set.massNoMotor(obj, value), obj = obj.updateOverridable('MASS_NO_MOTOR', value); end
+ function obj = set.inertia(obj, value), obj = obj.updateOverridable('INERTIA', value); end
+ function obj = set.inertiaNoMotor(obj, value), obj = obj.updateOverridable('INERTIA_NO_MOTOR', value); end
+ function obj = set.xcg(obj, value), obj = obj.updateOverridable('XCG', value); end
+ function obj = set.xcgNoMotor(obj, value), obj = obj.updateOverridable('XCG_NO_MOTOR', value); end
+ end
+
+ methods
+ function value = get.parafoil(obj), value = obj.PARAFOIL; end
+ function value = get.recovery(obj), value = obj.RECOVERY; end
+ function value = get.electronics(obj), value = obj.ELECTRONICS; end
+ function value = get.airbrakes(obj), value = obj.AIRBRAKES; end
+ function value = get.motor(obj), value = obj.MOTOR; end
+ function value = get.rear(obj), value = obj.REAR; end
+
+ function value = get.length(obj), value = obj.LENGTH; end
+ function value = get.lengthCenter(obj), value = obj.LENGTH_CENTER; end
+ function value = get.lengthCenterNoMotor(obj), value = obj.LENGTH_CENTER_NO_MOTOR; end
+ function value = get.diameter(obj), value = obj.DIAMETER; end
+
+ function value = get.mass(obj), value = obj.MASS; end
+ function value = get.massNoMotor(obj)
+ value = obj.MASS_NO_MOTOR;
+ end
+ function value = get.inertia(obj), value = obj.INERTIA; end
+
+ function value = get.inertiaNoMotor(obj), value = obj.INERTIA_NO_MOTOR; end
+ function value = get.xcg(obj), value = obj.XCG; end
+ function value = get.xcgNoMotor(obj), value = obj.XCG_NO_MOTOR; end
+ end
+end
\ No newline at end of file
diff --git a/classes/@Rocket/checkGeometry.m b/classes/@Rocket/checkGeometry.m
new file mode 100644
index 0000000000000000000000000000000000000000..95ce79caa9f4ce858921943986cf6d60914ca6fc
--- /dev/null
+++ b/classes/@Rocket/checkGeometry.m
@@ -0,0 +1,83 @@
+function checks = checkGeometry(obj)
+ % checkGeometry - This methods checks if the rocket geometry
+ % is consistent with the geometry of the
+ % aerodynamic matrices
+ %
+ % OUTPUTS:
+ % - checks (n fields of geometry, 1): boolean value of the geometry checks
+
+ xCgRocket = round([ ...
+ obj.xCg(1); ...
+ obj.xCg(end) ...
+ ], 3);
+
+ xCgTest = round([
+ obj.coefficients.geometry.xcg(1);
+ obj.coefficients.geometry.xcg(end);
+ ], 3);
+
+ if (obj.parafoil.noseCMod & obj.parafoil.nosePMod) == 0 % KARMAN ogive case, no modified p and c coefficients
+ geometryRocket = round([
+ obj.diameter;
+ obj.parafoil.noseLength;
+ obj.lengthCenter;
+ obj.rear.finsRootChord;
+ obj.rear.finsFreeChord;
+ obj.rear.finsHeight;
+ obj.rear.finsDeltaXFreeChord;
+ obj.rear.nPanel;
+ obj.rear.boatLength;
+ obj.rear.boatFinalDiameter;
+ ], 3);
+
+ geometryTest = round([
+ obj.coefficients.geometry.diameter;
+ obj.coefficients.geometry.lNose;
+ obj.coefficients.geometry.lCenter;
+ obj.coefficients.geometry.chord1;
+ obj.coefficients.geometry.chord2;
+ obj.coefficients.geometry.height;
+ obj.coefficients.geometry.deltaXLE;
+ obj.coefficients.geometry.nPanel;
+ obj.coefficients.geometry.boatL;
+ obj.coefficients.geometry.boatD;
+ ], 3);
+ else % MHAAK ogive case, modified p and c coefficients
+ geometryRocket = round([
+ obj.diameter;
+ obj.parafoil.noseLength;
+ obj.lengthCenter;
+ obj.parafoil.noseCMod;
+ obj.parafoil.nosePMod;
+ obj.rear.finsRootChord;
+ obj.rear.finsFreeChord;
+ obj.rear.finsHeight;
+ obj.rear.finsDeltaXFreeChord;
+ obj.rear.nPanel;
+ obj.rear.boatLength;
+ obj.rear.boatFinalDiameter;
+ ], 3);
+
+ geometryTest = round([
+ obj.coefficients.geometry.diameter;
+ obj.coefficients.geometry.lNose;
+ obj.coefficients.geometry.lCenter;
+ obj.coefficients.geometry.cMod;
+ obj.coefficients.geometry.pMod;
+ obj.coefficients.geometry.chord1;
+ obj.coefficients.geometry.chord2;
+ obj.coefficients.geometry.height;
+ obj.coefficients.geometry.deltaXLE;
+ obj.coefficients.geometry.nPanel;
+ obj.coefficients.geometry.boatL;
+ obj.coefficients.geometry.boatD;
+ ], 3);
+ end
+
+ checks = [
+ xCgRocket == xCgTest;
+ strcmp(obj.coefficients.geometry.ogType, obj.parafoil.noseType);
+ geometryRocket == geometryTest;
+ strcmp(obj.coefficients.geometry.boatType, obj.rear.boatType)
+ ];
+end
\ No newline at end of file
diff --git a/classes/@Rocket/interpCoeffs.m b/classes/@Rocket/interpCoeffs.m
new file mode 100644
index 0000000000000000000000000000000000000000..717934a3fb9a0cd0a39823a199f29a9fa22490bd
--- /dev/null
+++ b/classes/@Rocket/interpCoeffs.m
@@ -0,0 +1,63 @@
+function [coeffsValues, angle0] = interpCoeffs(obj, t, alpha, mach, beta, alt, c)
+% interpCoeffs - interpolation of aerodynamic coefficients.
+%
+% INPUTS:
+% - t, double [1,1], integration time, [s];
+% - alpha, double[1,1], angle of attack, [];
+% - mach, double[1,1], mach number, [];
+% - beta, double[1,1], sideslip angle, [];
+% - alt, double[1,1], altitude, [m];
+% - c, double[1,1], aerobrakes control variable, [];
+%
+% OUTPUTS:
+% - coeffsValues, array [16,1], aerodynamic coefficients;
+% - angle0, array [2,1], array of the reference aerodynamic angles.
+
+if mach > obj.airbrakes.maxMach
+ c = 0;
+end
+h = c*obj.coefficients.state.hprot(end);
+
+[nearAlpha, indexAlpha] = nearestValSorted(obj.coefficients.state.alphas*pi/180, alpha);
+[~, indexMach] = nearestValSorted(obj.coefficients.state.machs, mach);
+[nearBeta, indexBeta] = nearestValSorted(obj.coefficients.state.betas*pi/180, beta);
+[~, indexAlt] = nearestValSorted(obj.coefficients.state.altitudes, alt);
+[~, indexControl] = nearestValSorted(obj.coefficients.state.hprot, h);
+
+angle0 = [nearAlpha; nearBeta];
+
+if t >= obj.motor.cutoffTime
+ % Interpolate on airbrake control
+ % Uses end xCg, even if tCutOff < tBurnTime
+ num = length(obj.coefficients.state.hprot);
+ index1 = indexControl;
+ index2 = indexControl + 1;
+ if index2 > num
+ if num == 1
+ coeffsValues = obj.coefficients(:, indexAlpha, indexMach, indexBeta, indexAlt, 1, end);
+ return;
+ else
+ index2 = index2 - 1;
+ index1 = index1 - 1;
+ end
+ end
+
+ VF = obj.coefficients.total(:, indexAlpha, indexMach, indexBeta, indexAlt, index1, end);
+ VE = obj.coefficients.total(:, indexAlpha, indexMach, indexBeta, indexAlt, index2, end);
+
+ deltaH = obj.coefficients.state.hprot(index2) - obj.coefficients.state.hprot(index1);
+ coeffsValues = ( (h - obj.coefficients.state.hprot(index1))/deltaH)*(VE - VF) + VF;
+else
+ % Interpolate on xCg, close airbrakes
+ num = 1:1:length(obj.coefficients.state.xcgTime)-1;
+ indexXcg = t >= obj.coefficients.state.xcgTime(1:end-1) & t < obj.coefficients.state.xcgTime(2:end);
+ index1 = num(indexXcg);
+ index2 = index1 + 1;
+
+ VF = obj.coefficients.total(:, indexAlpha, indexMach, indexBeta, indexAlt, indexControl, index1);
+ VE = obj.coefficients.total(:, indexAlpha, indexMach, indexBeta, indexAlt, indexControl, index2);
+
+ deltaT = obj.coefficients.state.xcgTime(index2) - obj.coefficients.state.xcgTime(index1);
+ coeffsValues = ( (t - obj.coefficients.state.xcgTime(index1))/deltaT)*(VE - VF) + VF;
+end
+end
\ No newline at end of file
diff --git a/classes/@Rocket/loadData.m b/classes/@Rocket/loadData.m
new file mode 100644
index 0000000000000000000000000000000000000000..78b4e6d8bbcc3d16d245183558059641baca8036
--- /dev/null
+++ b/classes/@Rocket/loadData.m
@@ -0,0 +1,40 @@
+function obj = loadData(obj)
+if isempty(obj.motor)
+ return;
+end
+
+varNames = {'total', 'geometry', 'state', 'finsCN'};
+motorName = obj.motor.name;
+aeroPath = fullfile(obj.mission.dataPath, 'aeroCoefficients.mat');
+aeroHighAOAPath = fullfile(obj.mission.dataPath, 'aeroCoefficientsHighAOA.mat');
+
+if ~(exist(aeroPath, 'file') && exist(aeroHighAOAPath,'file'))
+ return;
+end
+dataCoeffs = load(aeroPath);
+dataCoeffsHighAOA = load(aeroHighAOAPath);
+
+if isfield(dataCoeffs, motorName) && isfield(dataCoeffsHighAOA, motorName)
+ dataCoeffs = dataCoeffs.(motorName);
+ dataCoeffsHighAOA = dataCoeffsHighAOA.(motorName);
+else
+ return;
+end
+
+if isfield(dataCoeffs, "finsCN") && ...
+ isfield(dataCoeffsHighAOA, "finsCN")
+ obj.coefficients.finsCN = dataCoeffs.finsCN;
+ obj.coefficientsHighAOA.finsCN = dataCoeffsHighAOA.finsCN;
+end
+
+varNames = varNames{1:end - 1};
+if all(and(isfield(dataCoeffs, varNames), ...
+ isfield(dataCoeffsHighAOA, varNames)))
+ obj.coefficients.total = dataCoeffs.total;
+ obj.coefficientsHighAOA.total = dataCoeffsHighAOA.total;
+ obj.coefficients.geometry = dataCoeffs.geometry;
+ obj.coefficientsHighAOA.geometry = dataCoeffsHighAOA.geometry;
+ obj.coefficients.state = dataCoeffs.state;
+ obj.coefficientsHighAOA.state = dataCoeffsHighAOA.state;
+end
+end
\ No newline at end of file
diff --git a/classes/@Rocket/plot.m b/classes/@Rocket/plot.m
new file mode 100644
index 0000000000000000000000000000000000000000..7b87f9326de7648497d2c15b4169880b77e44315
--- /dev/null
+++ b/classes/@Rocket/plot.m
@@ -0,0 +1,116 @@
+function img = plot(obj)
+arguments
+ obj Rocket
+end
+
+deltaXLE = obj.rear.finsDeltaXFreeChord;
+r = obj.diameter/2;
+height = obj.rear.finsHeight;
+C1 = obj.rear.finsRootChord;
+C2 = obj.rear.finsFreeChord;
+
+Lcent = obj.lengthCenter;
+Lnos = obj.parafoil.noseLength;
+
+Xle1 = Lcent + Lnos - obj.rear.finsAxialDistance - C1;
+
+Daft = obj.rear.boatFinalDiameter;
+Laft = obj.rear.boatLength;
+
+xNos = Lnos - Lnos*cos(linspace(0, pi/2, 50));
+if strcmp(obj.parafoil.noseType, 'KARMAN')
+ theta = @(x) acos( 1 - ( (2*x)./Lnos ) );
+ Karman = @(x) ( r/sqrt(pi) ) * sqrt( theta(x) - ( sin(2*theta(x))./ 2 ) );
+ yNos = Karman(xNos);
+elseif strcmp(obj.parafoil.noseType, 'HAACK')
+ theta = @(x) acos( 1 - ( (2*x)./Lnos ) );
+ Haack = @(x) ( r/sqrt(pi) ) * sqrt( theta(x) - ( sin(2*theta(x))./ 2 ) + (1/3)*sin(theta(x)).^3 );
+ yNos = Haack(xNos);
+elseif strcmp(obj.parafoil.noseType, 'OGIVE')
+ rho = (r^2 + Lnos^2)/(2*r);
+ Ogive = @(x) sqrt(rho^2 - (Lnos - x).^2) + r - rho;
+ yNos = Ogive(xNos);
+elseif strcmp(obj.parafoil.noseType, 'POWER')
+ power = obj.parafoil.nosePower;
+ Power = @(x) r * (x/Lnos).^(power);
+ yNos = Power(xNos);
+elseif strcmp(obj.parafoil.noseType, 'MHAACK')
+ p = obj.parafoil.nosePMod;
+ c = obj.parafoil.noseCMod;
+ xMod = @(x, p) (x/Lnos).^(p)*Lnos;
+ thetaMod = @(x, p) acos( 1 - ( (2*xMod(x, p))./Lnos ) );
+ haackSeriesMod = @(x, p, C) ( r/sqrt(pi) ) * sqrt( thetaMod(x, p) ...
+ - ( sin(2*thetaMod(x, p))./ 2 ) + C*sin(thetaMod(x, p)).^3 );
+ yNos = haackSeriesMod(xNos, p, c);
+end
+
+if strcmp(obj.rear.boatType, 'OGIVE') % [-] Boat-tail shape. 0: Cone, 1: Tangent Ogive
+ [xBoat, yBoat] = computeTangentBoatPoints(2*r, Daft, Laft);
+else
+ xBoat = [0 Laft];
+ yBoat = [r Daft/2];
+end
+
+%%% figure begin
+img = figure();
+hold on
+
+%%% NOSECONE
+plot(xNos, yNos, 'k');
+plot(xNos, -yNos, 'k');
+plot([Lnos Lnos], [-r r], 'k');
+
+%%% CENTERBODY
+plot([Lnos Lnos+Lcent], [r r], 'k');
+plot([Lnos Lnos+Lcent], [-r -r], 'k');
+plot([Lnos+Lcent Lnos+Lcent], [-r r], 'k');
+
+%%% BOAT-TAIL PLOT
+plot(xBoat+Lnos+Lcent, yBoat, 'k');
+plot(xBoat+Lnos+Lcent, -yBoat, 'k');
+plot([Lnos+Lcent+Laft Lnos+Lcent+Laft], [-Daft/2 Daft/2], 'k');
+
+%%% FINS PLOT
+% top
+plot([Xle1 Xle1+deltaXLE], [r r+height],'k');
+plot([Xle1+C1 Xle1+deltaXLE+C2], [r r+height],'k');
+plot([Xle1+deltaXLE Xle1+deltaXLE+C2], [r+height r+height],'k');
+plot([Xle1 Xle1+C1], [r r], 'k');
+% bottom
+plot([Xle1 Xle1+deltaXLE], [-r -r-height],'k');
+plot([Xle1+C1 Xle1+deltaXLE+C2], [-r -r-height],'k');
+plot([Xle1+deltaXLE Xle1+deltaXLE+C2], [-r-height, -r-height],'k');
+plot([Xle1 Xle1+C1], [-r -r], 'k');
+
+% plot([Xle1 Xle1+deltaXLE], [r+height r+height], 'k--')
+% plot([Xle1+deltaXLE Xle1+deltaXLE], [r+height r],'k--')
+
+%%% BAYS
+lengths = obj.absolutePositions.values + 2*Lnos;
+baysBody = obj.absolutePositions.keys;
+iMotor = find(strcmp(obj.absolutePositions.keys,"motor"));
+xline(0,'r-.', 'Label', 'NOSE', ...
+ 'LabelOrientation', 'aligned', 'LabelVerticalAlignment', 'bottom', ...
+ 'LabelHorizontalAlignment', 'right');
+for i = 1:length(lengths)
+ if i == iMotor
+ line([lengths(i) lengths(i)], [-1 1], 'LineStyle', '--', 'Color', 'b'); % Draw the line
+ text(lengths(i), -1 + 0.3, baysBody(i), 'VerticalAlignment', 'top', ...
+ 'HorizontalAlignment', 'right', 'Rotation', 90, 'Color', 'b');
+ else
+ line([lengths(i) lengths(i)], [-1 1], 'LineStyle', '--', 'Color', 'k'); % Draw the line
+ text(lengths(i), 1 + 0.1, baysBody(i), 'VerticalAlignment', 'top', ...
+ 'HorizontalAlignment', 'right', 'Rotation', 90);
+ end
+end
+boatPlotLength = obj.length - obj.rear.boatLength;
+xline(boatPlotLength,'r-.', 'Label', 'BOAT-TAIL', ...
+ 'LabelOrientation', 'aligned', 'LabelVerticalAlignment', 'bottom', ...
+ 'LabelHorizontalAlignment', 'right');
+
+axis equal
+% set(gca, 'xlim', [-100, Lnos+Lcent+Laft+100]);
+
+%%% TITLE
+title(string(strrep(obj.mission.name, '_', ' ')));
+end
diff --git a/classes/@Rocket/update.m b/classes/@Rocket/update.m
new file mode 100644
index 0000000000000000000000000000000000000000..4400d73971f1171aa8da36f1e1899ddd58a1c526
--- /dev/null
+++ b/classes/@Rocket/update.m
@@ -0,0 +1,45 @@
+function obj = update(obj)
+% Updates all properties without motor
+
+override = obj.overrides;
+
+%% Geometry
+if ~override('LENGTH')
+ obj.LENGTH = obj.rear.position + obj.rear.length + obj.parafoil.noseLength;
+end
+
+if ~override('LENGTH_CENTER')
+ obj.LENGTH_CENTER = obj.length - obj.parafoil.noseLength - obj.rear.boatLength;
+end
+
+%% Mass
+if ~override('MASS')
+ obj.MASS = obj.massNoMotor + obj.motor.mass;
+end
+
+if ~override('XCG')
+ obj.XCG = (obj.xcgNoMotor*obj.massNoMotor + ...
+ obj.motor.mass.*(obj.motor.xcg+obj.lengthCenterNoMotor))./ ...
+ obj.mass;
+end
+
+if ~override('INERTIA')
+ % [3xN] Ix, Iy, Iz
+ % Assumption: xCgs are close to rocket axis
+ motorInertia = obj.motor.inertia(2:3, :) + ...
+ (obj.xcg - (obj.motor.position + obj.motor.xcg)).^2 .* obj.motor.mass;
+ baysInertia = obj.inertiaNoMotor(2:3, :);
+
+ obj.inertia = [obj.motor.inertia(1, :) + obj.inertiaNoMotor(1, :);
+ motorInertia + baysInertia];
+
+ obj.inertiaDot = diff(obj.inertia, 1, 2)./diff(obj.motor.time);
+ obj.inertiaDot(:, end + 1) = obj.inertiaDot(:, end);
+end
+
+%% Cutoff
+obj.cutoffMass = interp1(obj.time, obj.mass, obj.cutoffTime, "linear", 'extrap');
+obj.cutoffInertia = interp1(obj.time, obj.inertia', obj.cutoffTime, "linear", 'extrap')';
+
+end
+
diff --git a/classes/@Rocket/updateBay.m b/classes/@Rocket/updateBay.m
new file mode 100644
index 0000000000000000000000000000000000000000..4fb11c5f836abec619d623cb3da2045213d89b61
--- /dev/null
+++ b/classes/@Rocket/updateBay.m
@@ -0,0 +1,18 @@
+function obj = updateBay(obj, bayName, value)
+obj.(bayName) = value;
+
+obj.bayStatus(bayName) = true;
+if ~all(values(obj.bayStatus)), return; end
+bays = obj.bays;
+
+%% Update positions
+obj.(bays(1)).position = 0;
+for i = 2:length(bays)
+ bay = bays(i);
+ prevBay = bays(i-1);
+ obj.(bay).position = obj.(prevBay).position + obj.(prevBay).length + obj.(bay).offset;
+end
+
+obj = obj.updateNoMotor();
+obj = obj.update();
+end
\ No newline at end of file
diff --git a/classes/@Rocket/updateNoMotor.m b/classes/@Rocket/updateNoMotor.m
new file mode 100644
index 0000000000000000000000000000000000000000..ae7f461cbee0f6c0dd1351a88236310893b176be
--- /dev/null
+++ b/classes/@Rocket/updateNoMotor.m
@@ -0,0 +1,39 @@
+function obj = updateNoMotor(obj)
+% Updates all properties without motor
+
+override = obj.overrides;
+bayNames = obj.baysNoMotor;
+nBays = length(bayNames);
+bays(nBays) = obj.(bayNames(end));
+
+for i = 1:nBays - 1, bays(i) = obj.(bayNames(i)); end
+
+positions = [bays.position];
+masses = [bays.mass];
+xcgs = positions + [bays.xcg];
+inertias = cat(1, bays.inertia)';
+
+massNoMotor = sum([bays.mass]);
+
+%% Geometry
+if ~override('LENGTH_CENTER_NO_MOTOR')
+ obj.LENGTH_CENTER_NO_MOTOR = obj.motor.position;
+end
+
+%% Mass
+if ~override('MASS_NO_MOTOR')
+ obj.MASS_NO_MOTOR = massNoMotor;
+end
+
+if ~override('XCG_NO_MOTOR')
+ obj.XCG_NO_MOTOR = (xcgs*masses')/massNoMotor;
+end
+
+if ~override('INERTIA_NO_MOTOR')
+ % [3x1] Ix, Iy, Iz
+ % Assumption: xCgs are close to rocket axis
+ IRaw = inertias(2:3, :) + (obj.xcgNoMotor - xcgs).^2 .* masses;
+ obj.INERTIA_NO_MOTOR = [sum(inertias(1, :)); sum(IRaw, 2)];
+end
+end
+
diff --git a/classes/@Rocket/updateOverridable.m b/classes/@Rocket/updateOverridable.m
new file mode 100644
index 0000000000000000000000000000000000000000..7c0197415d6a0ef146996f2971063a33a0778cac
--- /dev/null
+++ b/classes/@Rocket/updateOverridable.m
@@ -0,0 +1,10 @@
+function obj = updateOverridable(obj, name, value)
+obj.(name) = value;
+obj.overrides(name) = true;
+
+if isempty(value)
+ obj.overrides(name) = false;
+ obj = obj.updateNoMotor();
+ obj = obj.update();
+end
+end
\ No newline at end of file
diff --git a/classes/Bay.m b/classes/Bay.m
index beb567f262e799b62d746aac808f6c43e4eccf94..1e143c3215ddefba2b605ca7ce57469bc8bcc570 100644
--- a/classes/Bay.m
+++ b/classes/Bay.m
@@ -1,19 +1,26 @@
-classdef Bay < Component & matlab.mixin.Heterogeneous
+classdef(Abstract) Bay < Config & matlab.mixin.Heterogeneous
% Bay: Represents an abstraction layer for all bays
% Arrays of bay subclasses will be represented as [mxn Bay] arrays
+ properties
+ offset (1, 1) double % [m] Position offset relative to previous bay, default: 0
+ length double % [m] Total bay length
+ end
+
properties(Abstract)
- position % [m] OVERRIDE Position, relative to previous component -
- length % [m] Total bay length
- mass % [kg] Total bay mass
- inertia % [kg*m^2] Total bay inertia (Body reference)
- xCg % [m] Cg relative to bay upper side
+ mass (1, :) double % [kg] Total bay mass
+ inertia (1, :) double % [kg*m^2] Total bay inertia (Body reference)
+ xcg (1, :) double % [m] Xcg wrt bay top
+ end
+
+ properties(SetAccess = ?Rocket)
+ position double % [m] Absolute position wrt ogive base
end
- methods (Static, Sealed, Access=protected)
- function default = getDefaultScalarElement
- default = Parafoil;
- end
+ methods (Static,Sealed,Access = protected)
+ function obj = getDefaultScalarElement()
+ obj = Electronics();
+ end
end
end
diff --git a/classes/Component.m b/classes/Component.m
deleted file mode 100644
index 7407018396451bed304a0490b789b80b86a7ec67..0000000000000000000000000000000000000000
--- a/classes/Component.m
+++ /dev/null
@@ -1,121 +0,0 @@
-classdef Component < Config & matlab.mixin.Copyable
-% Component: Represents an abstraction layer for all components
-% Components standardize object construction, config and data loading
-%
-% Constructor:
-% - Component: Creates an instance of the Component class.
-% Arguments:
-% - mission: Mission, mission object, used to find config
-% files
-% - varsIn: If present, data is read from this variable
-% instead of config file
-%
-% Options:
-%
-% - elementWise:
-% - if true, data is copied element-by-element
-% into target class
-% - if false, the loaded data substitutes target class
-
- properties(Abstract, Access = protected)
- mission Mission
- end
-
- methods
- function obj = Component(mission, varsIn, options)
- % Component: Contains and manages all bays
- %
- % Constructor:
- % - Rocket: Creates an instance of the Rocket class.
- % Loaded config: rocketConfig.m > rocket (for overrides)
- % Loaded data: -
- % Arguments:
- % - mission: Mission, mission object
- % - varIn: (optional) config source. Alternative to config.m
- % file
-
- arguments (Input)
- mission Mission = Mission()
- varsIn = []
- options.elementWise logical = true
- end
-
- if isempty(mission.name)
- return;
- end
-
- if isempty(varsIn)
- varsIn = obj.getConfig(mission);
- end
-
- fileName = obj.configName;
- varName = obj.variableName;
- if isempty(varName)
- varName = strtok(fileName, 'C');
- end
-
- if ~isfield(varsIn, varName)
- error(['Class not found inside the config folder: %s\n' ...
- 'With name: %s\n' ...
- 'Check that the correct mission is set in your component ' ...
- 'and the config file is correct'], fileName, varName);
- end
-
- configObj = varsIn.(varName);
-
- if options.elementWise
- fields = configObj.getProperties('writable');
- for field = fields
- if isempty([configObj.(field)]), continue; end
- obj.(field) = configObj.(field);
- end
- else
- obj = configObj;
- end
-
- [obj.mission] = deal(mission);
- end
- end
-
- methods
- function m = getMission(obj)
- m = obj.mission;
- end
- end
-
- methods(Access = protected)
- function cp = copyElement(obj)
- fields = obj.getProperties('readable', NonCopyable = 0);
- cp = copyElement@matlab.mixin.Copyable(obj); %shallow copy of all elements
-
- for field = fields
- if isa(obj.(field), 'matlab.mixin.Copyable')
- cp.(field) = copy(obj.(field));
- end
- end
- end
-
- function outputVariables = getConfig(obj, mission)
- fileName = obj.configName;
- filePath = mission.configPath;
- file = fullfile(filePath, fileName);
-
- if ~isfile(file)
- error(['File not found inside the config folder: %s\n' ...
- 'Check that the correct mission is set in your component ' ...
- 'and the config file exists'], fileName);
- end
-
- variables = [who(); "variables"];
- run(file);
- loadedVariables = who();
- loadedVariables(ismember(loadedVariables, variables)) = [];
-
- outputVariables = struct();
- for i = 1:length(loadedVariables)
- outputVariables.(loadedVariables{i}) = eval(loadedVariables{i});
- end
- end
- end
-end
-
diff --git a/classes/Config.m b/classes/Config.m
index cec711a4737ba8e95eb0bc2c54ae6732da94de76..5c7b954c1ea39db7d9e46312d9bb3663dd138ff0 100644
--- a/classes/Config.m
+++ b/classes/Config.m
@@ -1,16 +1,51 @@
-classdef(Abstract) Config < handle
+classdef(Abstract) Config
% Config: Represents an abstraction layer for all config-dependent Classes
-% Config standardizes property management and declares fundemental
-% methods (see doc for more info)
+% Config standardizes property management, and config loading and
+% declares fundemental methods (see doc for more info) and
-
- properties(Abstract, Access = protected)
+ properties(Abstract, Constant, Access = protected)
configName {mustBeTextScalar}
variableName char
end
methods
+ function obj = Config(pathIn, varsIn)
+ % Component: Contains and manages all bays
+ %
+ % Constructor:
+ % - Rocket: Creates an instance of the Rocket class.
+ % Loaded config: rocketConfig.m > rocket (for overrides)
+ % Loaded data: -
+ % Arguments:
+ % - filePath: Path containing config file
+ % - varIn: (optional) config source. Alternative to config.m
+ % file
+
+ arguments (Input)
+ pathIn {mustBeA(pathIn, {'char', 'string', 'Mission'})} = ''
+ varsIn = []
+ end
+
+ if isa(pathIn, 'Mission')
+ path = pathIn.configPath;
+ else
+ path = pathIn;
+ end
+
+ if isempty(path), return; end
+ if isempty(varsIn)
+ varsIn = obj.getConfig(path);
+ end
+
+ obj = obj.loadConfig(varsIn);
+ end
+
function structOut = toStruct(obj)
+ % This function converts the object to a struct
+ %
+ % WARNING: A struct does not posses update capabilities and only
+ % publicly readable fields are copied. Use this method carefully
+
structOut = struct();
fields = obj.getProperties('readable');
for j = 1:size(fields, 2), structOut.(fields{j}) = obj.(fields{j}); end
@@ -31,9 +66,8 @@ classdef(Abstract) Config < handle
arguments
obj
- preset char {mustBeMember(preset, {'readable', 'writable', ''})} = ''
+ preset char {mustBeMember(preset, {'readable', 'writable', ''})} = ''
options.Superclass char = ''
- options.Heterogeneous logical = 0
attributes.GetAccess char {mustBeMember(attributes.GetAccess, {'public', 'private', ''})} = ''
attributes.SetAccess char {mustBeMember(attributes.SetAccess, {'public', 'private', ''})} = ''
attributes.Dependent logical {mustBeMember(attributes.Dependent, [0, 1])} = []
@@ -53,7 +87,6 @@ classdef(Abstract) Config < handle
attributes.Hidden = 0;
case 'writable'
attributes.SetAccess = 'public';
- attributes.Dependent = 0;
attributes.Constant = 0;
attributes.Abstract = 0;
attributes.Hidden = 0;
@@ -87,50 +120,57 @@ classdef(Abstract) Config < handle
propertiesOut = string(properties(1:ii));
if nargout == 2
- if isempty(options.Superclass) || ~options.Heterogeneous
- valuesOut = cell(1, ii);
- for i = 1:ii, valuesOut{i} = obj.(propertiesOut(i)); end
- else
- valuesOut(ii) = obj.(propertiesOut(1));
- for i = 1:ii, valuesOut(i) = obj.(propertiesOut(i)); end
- end
+ valuesOut = cell(1, ii);
+ for i = 1:ii, valuesOut{i} = obj.(propertiesOut(i)); end
end
end
end
- methods(Hidden)
- function lh = addlistener(varargin)
- lh = addlistener@handle(varargin{:});
- end
- function notify(varargin)
- notify@handle(varargin{:});
- end
- function delete(varargin)
- delete@handle(varargin{:});
- end
- function Hmatch = findobj(varargin)
- Hmatch = findobj@handle(varargin{:});
- end
- function p = findprop(varargin)
- p = findprop@handle(varargin{:});
- end
- function TF = eq(varargin)
- TF = eq@handle(varargin{:});
- end
- function TF = ne(varargin)
- TF = ne@handle(varargin{:});
- end
- function TF = lt(varargin)
- TF = lt@handle(varargin{:});
- end
- function TF = le(varargin)
- TF = le@handle(varargin{:});
- end
- function TF = gt(varargin)
- TF = gt@handle(varargin{:});
+ methods(Access = protected)
+ function outputVariables = getConfig(obj, filePath)
+ fileName = obj.configName;
+ file = fullfile(filePath, fileName);
+
+ if ~isfile(file)
+ error(['File not found inside the config folder: %s\n' ...
+ 'Check that the correct mission is set in your component ' ...
+ 'and the config file exists'], fileName);
+ end
+
+ variables = [who(); "variables"];
+
+ % try run(file);
+ % catch ME, throwAsCaller(ME); end
+ run(file);
+ loadedVariables = who();
+ loadedVariables(ismember(loadedVariables, variables)) = [];
+
+ outputVariables = struct();
+ for i = 1:length(loadedVariables)
+ outputVariables.(loadedVariables{i}) = eval(loadedVariables{i});
+ end
end
- function TF = ge(varargin)
- TF = ge@handle(varargin{:});
+
+ function obj = loadConfig(obj, varsIn)
+ fileName = obj.configName;
+ varName = obj.variableName;
+ if isempty(varName)
+ varName = strtok(fileName, 'C');
+ end
+
+ if ~isfield(varsIn, varName)
+ error(['Class not found inside the config folder: %s\n' ...
+ 'With name: %s\n' ...
+ 'Check that the correct mission is set in your component ' ...
+ 'and the config file is correct'], fileName, varName);
+ end
+
+ configObj = varsIn.(varName);
+ fields = configObj.getProperties('writable');
+ for field = fields
+ if isempty([configObj.(field)]), continue; end
+ obj.(field) = configObj.(field);
+ end
end
- end
+ end
end
\ No newline at end of file
diff --git a/classes/components/Environment.m b/classes/Environment.m
similarity index 100%
rename from classes/components/Environment.m
rename to classes/Environment.m
diff --git a/classes/Mission.m b/classes/Mission.m
index 25b1eacfaf872d1f9adc39b94eb550516a2ca167..12cb70f968581a8259100b1fdc7c29d7196c1d7c 100644
--- a/classes/Mission.m
+++ b/classes/Mission.m
@@ -10,10 +10,14 @@ classdef Mission < Config
% - loadConfig: bool, Whether to load config file or return
% an empty mission
- properties
+ properties(Dependent)
name char % Mission name, used to access <mission> folder
end
+ properties(Access = private)
+ NAME char % Mission name cache
+ end
+
properties(SetAccess = protected)
currentPath char
configPath char
@@ -21,17 +25,20 @@ classdef Mission < Config
msaPath char
end
- properties(Access = protected)
+ properties(Access = private)
+ changeMatlabPath (1,1) logical
+ end
+
+ properties(Constant, Access = protected)
configName = 'missionConfig.m'
variableName = ''
- changeMatlabPath (1,1) logical
end
methods
function obj = Mission(mission, options)
arguments
mission {mustBeA(mission, {'logical', 'string', 'char'})} = false
- options.changeMatlabPath = true;
+ options.changeMatlabPath = false;
end
if nargin == 0
@@ -41,16 +48,21 @@ classdef Mission < Config
filePath = fullfile(fileparts(mfilename("fullpath")), '..', 'missions');
filePath = trimPath(filePath);
- obj.changeMatlabPath = options.changeMatlabPath;
obj.currentPath = filePath;
+ obj.changeMatlabPath = options.changeMatlabPath;
if isa(mission, 'char') || isa(mission, 'string')
obj.name = mission;
else
- obj.loadConfig();
+ vars = obj.getConfig(filePath);
+ obj.name = vars.mission.name;
end
end
- function set.name(obj, name)
+ function name = get.name(obj)
+ name = obj.NAME;
+ end
+
+ function obj = set.name(obj, name)
if strcmp(name,'design')
filePath = fullfile(fileparts(mfilename("fullpath")), '..', 'missions');
filePath = trimPath(filePath);
@@ -64,47 +76,34 @@ classdef Mission < Config
'Only one file can be selected at a time.',''}, ...
'SelectionMode','single','ListSize', [250,150], ...
'ListString',names);
- obj.name = names{indx};
+ obj.NAME = names{indx};
else
if ~isempty(obj.currentPath) && ...
- ~isfolder(fullfile(obj.currentPath, name)) %#ok<MCSUP>
+ ~isfolder(fullfile(obj.currentPath, name))
error('Invalid mission: %s', name)
end
- obj.name = name;
+ obj.NAME = name;
end
- obj.updatePath();
+
+ obj = obj.updatePath();
obj.updateMatlabPath();
end
end
- methods(Access = protected)
- function loadConfig(obj)
- fileName = obj.configName;
- filePath = obj.currentPath;
-
- if ~isfile(fullfile(filePath, fileName))
- error(strcat("File not found inside the config folder: ", filePath));
- end
-
- varName = strtok(fileName,'C');
- run(fileName);
- configObj = eval(varName);
- obj.name = configObj.name;
- end
-
- function updatePath(obj)
+ methods(Access = private)
+ function obj = updatePath(obj)
if isempty(obj.name) || isempty(obj.currentPath), return; end
obj.configPath = fullfile(obj.currentPath, obj.name, 'config');
obj.dataPath = fullfile(obj.currentPath, obj.name, 'data');
obj.msaPath = trimPath( ...
- fullfile(obj.currentPath, '..', '..', '..', 'msa-toolkit') ...
- );
+ fullfile(obj.currentPath, '..', '..', '..', 'msa-toolkit'));
end
function updateMatlabPath(obj)
if isempty(obj.name) || isempty(obj.currentPath), return; end
if ~obj.changeMatlabPath, return; end
+
matlabPath = path;
% Checking if other missions are in path
pattern = 'missions\\[^\\/]*;'; % Matches any config folder under mission in path
@@ -125,8 +124,4 @@ classdef Mission < Config
end
end
end
-
- methods(Static, Access = protected)
- function loadData(), end
- end
end
\ No newline at end of file
diff --git a/classes/Rocket.m b/classes/Rocket.m
deleted file mode 100644
index 3a18b2201da10673175704b71007e0cebe4511f7..0000000000000000000000000000000000000000
--- a/classes/Rocket.m
+++ /dev/null
@@ -1,558 +0,0 @@
-classdef Rocket < Component
- % Rocket: Contains and manages all bays
- %
- % Constructor:
- % - Rocket: Creates an instance of the Rocket class.
- % Loaded config: rocketConfig.m > rocket (for overrides)
- % Loaded data: -
- % Arguments:
- % - mission: Mission, mission object
- % - varIn: (optional) config source. Alternative to config.m
- % file
-
- properties
- parafoil Parafoil % [-] Parafoil bay
- recovery Recovery % [-] Recovery bay
- electronics Electronics % [-] Electronics bay
- airbrakes Airbrakes % [-] Airbrakes bay
- motor Motor % [-] Motor bay
- rear Rear % [-] Rear bay
-
- pitot Pitot % [-] Pitot component
- parachutes Para % [-] (nParachutes, nStages) Parachutes onboard
-
- length double % [m] Total length
- lengthCenter double % [m] Center length - no nose, boat
- lengthCenterNoMot double % [m] Center length - no nose, no motor
- diameter double % [m] Diameter
- mass double % [kg] Total mass
- massNoMotor double % [kg] Mass without motor
- inertia double % [kg*m^2] Total inertia - Axibody reference
- inertiaNoMotor double % [kg*m^2] Inertia without motor
- xCg double % [m] Total xCg
- xCgNoMotor double % [m] xCg without motor
-
- stagesMass double % [kg] Mass of stage 2, 3, .. without chutes
-
- coefficients % [-] Aerodynamic coefficients
- coefficientsHighAOA % [-] Aerodynamic coefficients for high angle of attacks
- end
-
- properties(SetAccess = protected)
- crossSection % [m^2] Rocket cross sectional area
- inertiaDot double % [kg*m^2/s]Total inertia time derivative
- cutoffInertia double % [kg*m^2] Total inertia at motor cutoff
- cutoffMass double % [m] Total mass at motor cutoff
- absolutePositions dictionary ... % [m] Bay start positions - 0 is set at nose base
- = dictionary()
- bays dictionary ... % [Bay] All bays
- = dictionary()
- end
-
- properties(Access = protected, Hidden)
- configName = 'rocketConfig.m'
- variableName = ''
- mission Mission
- end
-
- methods % Updaters
- function updateAbsolutePositions(obj)
- bDictionay = obj.bays;
- b = values(bDictionay);
-
- if ~isempty(obj.lengthCenterNoMot)
- obj.absolutePositions = dictionary(["motor", "rear"], ...
- [obj.lengthCenterNoMot, obj.lengthCenterNoMot + obj.rear.position]);
- return
- end
- % Populate shift vectors (how much each bay shifts the next one back)
- % Shift overrides are applyed to the previous bay
- shift = zeros(size(b));
- overrides = ~cellfun(@isempty, {b.position});
- overridesShift = logical([overrides(2:end), 0]);
-
- if any(overrides)
- shift(overridesShift) = b(overrides).position;
- end
-
- if any(~overrides)
- shift(~overridesShift) = [b(~overridesShift).length];
- end
-
- absPositions = cumsum([-shift(1); shift(1:end-1)]);
- absPositions = absPositions + ...
- (obj.parafoil.length - obj.parafoil.noseLength);
- obj.absolutePositions = dictionary(keys(bDictionay), absPositions);
-
- end
- function updateGeometry(obj)
- if ~isempty(obj.lengthCenterNoMot)
- obj.length = obj.lengthCenterNoMot + obj.motor.length + obj.parafoil.noseLength;
- else
- obj.length = (obj.absolutePositions("rear") + obj.bays("rear").length) + ...
- obj.bays("parafoil").noseLength;
- obj.lengthCenterNoMot = obj.absolutePositions("motor");
- end
- if isempty(obj.crossSection)
- obj.crossSection = 0.25*pi*obj.diameter^2;
- end
- obj.lengthCenter = obj.length - obj.parafoil.noseLength - obj.rear.boatLength;
- end
-
- function updateMassNoMotor(obj)
- if ~isempty(obj.massNoMotor)
- return;
- end
- bNoMotor = values(remove(obj.bays, 'motor'));
- obj.massNoMotor = sum([bNoMotor.mass]);
- end
-
- function updateMass(obj)
- obj.mass = obj.massNoMotor + obj.motor.mass;
- end
-
- function updateXCgNoMotor(obj)
- if ~isempty(obj.xCgNoMotor)
- return;
- end
- bNoMotor = values(remove(obj.bays, 'motor'))';
- aPosNoMotor = values(remove(obj.absolutePositions, 'motor'))';
- obj.xCgNoMotor = ((aPosNoMotor + [bNoMotor.xCg])* ...
- [bNoMotor.mass]')/obj.massNoMotor;
- end
-
- function updateXCg(obj)
- obj.xCg = (obj.xCgNoMotor*obj.massNoMotor + ...
- obj.motor.mass.*(obj.motor.xCg+obj.lengthCenterNoMot))./ ...
- obj.mass;
- end
-
- function updateInertiaNoMotor(obj)
- if ~isempty(obj.inertiaNoMotor)
- return;
- end
- bNoMotor = values(remove(obj.bays, 'motor'))';
- aPosNoMotor = values(remove(obj.absolutePositions, 'motor'))';
- % [3x1] Ix, Iy, Iz
- % Assumption: xCgs are close to rocket axis
- inertias = [bNoMotor.inertia];
- temp = inertias(2:3, :) + ...
- (obj.xCgNoMotor' - (aPosNoMotor + [bNoMotor.xCg])).^2 .* [bNoMotor.mass];
- obj.inertiaNoMotor = [sum(inertias(1, :)); sum(temp, 2)];
- end
-
- function updateInertia(obj)
- % [3xN] Ix, Iy, Iz
- % Assumption: xCgs are close to rocket axis
- motorInertia = obj.motor.inertia(2:3, :) + ...
- (obj.xCg - (obj.absolutePositions('motor') + obj.motor.xCg)).^2 .* obj.motor.mass;
- baysInertia = obj.inertiaNoMotor(2:3, :) + ...
- (obj.xCg - obj.xCgNoMotor).^2 .* obj.massNoMotor;
-
- obj.inertia = [obj.motor.inertia(1, :) + obj.inertiaNoMotor(1, :);
- motorInertia + baysInertia];
-
- obj.inertiaDot = diff(obj.inertia, 1, 2)./diff(obj.motor.time);
- obj.inertiaDot(:, end + 1) = obj.inertiaDot(:, end);
- end
-
- function updateCutoff(obj)
- obj.cutoffInertia = interpLinear(obj.motor.time, obj.inertia, obj.motor.cutoffTime);
- obj.cutoffMass = interpLinear(obj.motor.time, obj.mass, obj.motor.cutoffTime);
- end
-
- function updateStagesMass(obj)
- stage1 = obj.cutoffMass - (obj.parachutes(1,2).mass + obj.parachutes(2,2).mass + obj.parafoil.mass);
- % Everything at cut off without parafoil, parafoil drogue and
- % parafoil airfoil
- stage2 = obj.cutoffMass - stage1;
- % only parafoil: parafoil, parafoil drogue and parafoil airfoil
- obj.stagesMass = [stage1 stage2];
- end
-
- function updateAll(obj)
- % Note: properties without motor must be updated first
- % if obj.motor.isHRE
- obj.updateAbsolutePositions;
- obj.updateGeometry;
- obj.updateMassNoMotor;
- obj.updateMass;
- obj.updateXCgNoMotor;
- obj.updateXCg;
- obj.updateInertiaNoMotor;
- obj.updateInertia;
- obj.updateCutoff;
- obj.updateStagesMass;
- % end
- % obj.updateAbsolutePositions;
- % obj.updateGeometry;
- % obj.updateMassNoMotor;
- % obj.updateMass;
- % obj.updateXCgNoMotor;
- % obj.updateInertiaNoMotor;
- % obj.updateStagesMass;
- end
- end
-
- methods(Access = protected) % Loaders
- function obj = loadData(obj)
- if isempty(obj.motor)
- return;
- end
- varNames = {'total', 'geometry', 'state', 'finsCN'};
- motorName = obj.motor.name;
- aeroPath = fullfile(obj.mission.dataPath, 'aeroCoefficients.mat');
- aeroHighAOAPath = fullfile(obj.mission.dataPath, 'aeroCoefficientsHighAOA.mat');
-
- if ~(exist(aeroPath, 'file') && exist(aeroHighAOAPath,'file'))
- return;
- end
- dataCoeffs = load(aeroPath);
- dataCoeffsHighAOA = load(aeroHighAOAPath);
-
- if isfield(dataCoeffs, motorName) && isfield(dataCoeffsHighAOA, motorName)
- dataCoeffs = dataCoeffs.(motorName);
- dataCoeffsHighAOA = dataCoeffsHighAOA.(motorName);
- else
- return;
- end
-
- if isfield(dataCoeffs, "finsCN") && ...
- isfield(dataCoeffsHighAOA, "finsCN")
- obj.coefficients.finsCN = dataCoeffs.finsCN;
- obj.coefficientsHighAOA.finsCN = dataCoeffsHighAOA.finsCN;
- end
-
- varNames = varNames{1:end - 1};
- if all(and(isfield(dataCoeffs, varNames), ...
- isfield(dataCoeffsHighAOA, varNames)))
- obj.coefficients.total = dataCoeffs.total;
- obj.coefficientsHighAOA.total = dataCoeffsHighAOA.total;
- obj.coefficients.geometry = dataCoeffs.geometry;
- obj.coefficientsHighAOA.geometry = dataCoeffsHighAOA.geometry;
- obj.coefficients.state = dataCoeffs.state;
- obj.coefficientsHighAOA.state = dataCoeffsHighAOA.state;
- end
- end
- end
-
- methods
- function obj = Rocket(mission, varIn, options)
- arguments
- mission Mission = Mission()
- varIn struct = []
- options.loadCoefficients logical = true
- options.checkGeometry logical = true
- end
- obj@Component(mission, varIn);
-
- %% Loading data
- if isempty(mission.name)
- return;
- end
-
- vars = obj.getConfig(mission); % Load config once and apply to other bays
- obj.parafoil = Parafoil(mission, vars);
- obj.recovery = Recovery(mission, vars);
- obj.electronics = Electronics(mission, vars);
- obj.motor = Motor(mission, vars);
- obj.airbrakes = Airbrakes(mission, obj.motor, vars);
- obj.rear = Rear(mission, vars);
- obj.pitot = Pitot(mission, vars);
- paras = Para(mission);
- obj.parachutes = paras(:, :, 1);
-
- [bayNames, bayValues] = obj.getProperties(Superclass='Bay', Heterogeneous=1);
- obj.bays = dictionary(bayNames, bayValues);
- obj.updateAll();
-
- if options.loadCoefficients
- obj.loadData();
- answer = '';
- if isempty(obj.coefficients) || isempty(obj.coefficientsHighAOA)
- answer = questdlg(['Coefficient matrices not found. ' ...
- 'Do you want to create new matrices?']);
- elseif options.checkGeometry && ~all(obj.checkGeometry())
- answer = questdlg(['Coefficient matrices differ from rocket geometry. ' ...
- 'Do you want to create new matrices?']);
- end
-
- switch answer
- case 'Yes'
- parserPath = fullfile(mission.msaPath, 'autoMatricesProtub');
- addpath(genpath(parserPath));
- mainAutoMatProtub(obj);
- obj.loadData();
- case 'Cancel'
- error('Rocket creation aborted')
- otherwise
- end
- end
- end
-
- function [coeffsValues, angle0] = interpCoeffs(obj, t, alpha, mach, beta, alt, c)
- % interpCoeffs - interpolation of aerodynamic coefficients.
- %
- % INPUTS:
- % - t, double [1,1], integration time, [s];
- % - alpha, double[1,1], angle of attack, [];
- % - mach, double[1,1], mach number, [];
- % - beta, double[1,1], sideslip angle, [];
- % - alt, double[1,1], altitude, [m];
- % - c, double[1,1], aerobrakes control variable, [];
- %
- % OUTPUTS:
- % - coeffsValues, array [16,1], aerodynamic coefficients;
- % - angle0, array [2,1], array of the reference aerodynamic angles.
-
- if mach > obj.airbrakes.maxMach
- c = 0;
- end
- h = c*obj.coefficients.state.hprot(end);
-
- [nearAlpha, indexAlpha] = nearestValSorted(obj.coefficients.state.alphas*pi/180, alpha);
- [~, indexMach] = nearestValSorted(obj.coefficients.state.machs, mach);
- [nearBeta, indexBeta] = nearestValSorted(obj.coefficients.state.betas*pi/180, beta);
- [~, indexAlt] = nearestValSorted(obj.coefficients.state.altitudes, alt);
- [~, indexControl] = nearestValSorted(obj.coefficients.state.hprot, h);
-
- angle0 = [nearAlpha; nearBeta];
-
- if t >= obj.motor.cutoffTime
- % Interpolate on airbrake control
- % Uses end xCg, even if tCutOff < tBurnTime
- num = length(obj.coefficients.state.hprot); %#ok<CPROPLC>
- index1 = indexControl;
- index2 = indexControl + 1;
- if index2 > num
- if num == 1
- coeffsValues = obj.coefficients(:, indexAlpha, indexMach, indexBeta, indexAlt, 1, end);
- return;
- else
- index2 = index2 - 1;
- index1 = index1 - 1;
- end
- end
-
- VF = obj.coefficients.total(:, indexAlpha, indexMach, indexBeta, indexAlt, index1, end);
- VE = obj.coefficients.total(:, indexAlpha, indexMach, indexBeta, indexAlt, index2, end);
-
- deltaH = obj.coefficients.state.hprot(index2) - obj.coefficients.state.hprot(index1);
- coeffsValues = ( (h - obj.coefficients.state.hprot(index1))/deltaH)*(VE - VF) + VF;
- else
- % Interpolate on xCg, close airbrakes
- num = 1:1:length(obj.coefficients.state.xcgTime)-1; %#ok<CPROPLC>
- indexXcg = t >= obj.coefficients.state.xcgTime(1:end-1) & t < obj.coefficients.state.xcgTime(2:end);
- index1 = num(indexXcg);
- index2 = index1 + 1;
-
- VF = obj.coefficients.total(:, indexAlpha, indexMach, indexBeta, indexAlt, indexControl, index1);
- VE = obj.coefficients.total(:, indexAlpha, indexMach, indexBeta, indexAlt, indexControl, index2);
-
- deltaT = obj.coefficients.state.xcgTime(index2) - obj.coefficients.state.xcgTime(index1);
- coeffsValues = ( (t - obj.coefficients.state.xcgTime(index1))/deltaT)*(VE - VF) + VF;
- end
- end
-
- function img = plot(obj)
- arguments
- obj Rocket
- end
- deltaXLE = obj.rear.finsDeltaXFreeChord;
- r = obj.diameter/2;
- height = obj.rear.finsHeight;
- C1 = obj.rear.finsRootChord;
- C2 = obj.rear.finsFreeChord;
-
- Lcent = obj.lengthCenter;
- Lnos = obj.parafoil.noseLength;
-
- Xle1 = Lcent + Lnos - obj.rear.finsAxialDistance - C1;
-
- Daft = obj.rear.boatFinalDiameter;
- Laft = obj.rear.boatLength;
-
- xNos = Lnos - Lnos*cos(linspace(0, pi/2, 50));
- if strcmp(obj.parafoil.noseType, 'KARMAN')
- theta = @(x) acos( 1 - ( (2*x)./Lnos ) );
- Karman = @(x) ( r/sqrt(pi) ) * sqrt( theta(x) - ( sin(2*theta(x))./ 2 ) );
- yNos = Karman(xNos);
- elseif strcmp(obj.parafoil.noseType, 'HAACK')
- theta = @(x) acos( 1 - ( (2*x)./Lnos ) );
- Haack = @(x) ( r/sqrt(pi) ) * sqrt( theta(x) - ( sin(2*theta(x))./ 2 ) + (1/3)*sin(theta(x)).^3 );
- yNos = Haack(xNos);
- elseif strcmp(obj.parafoil.noseType, 'OGIVE')
- rho = (r^2 + Lnos^2)/(2*r);
- Ogive = @(x) sqrt(rho^2 - (Lnos - x).^2) + r - rho;
- yNos = Ogive(xNos);
- elseif strcmp(obj.parafoil.noseType, 'POWER')
- power = obj.parafoil.nosePower;
- Power = @(x) r * (x/Lnos).^(power);
- yNos = Power(xNos);
- elseif strcmp(obj.parafoil.noseType, 'MHAACK')
- p = obj.parafoil.nosePMod;
- c = obj.parafoil.noseCMod;
- xMod = @(x, p) (x/Lnos).^(p)*Lnos;
- thetaMod = @(x, p) acos( 1 - ( (2*xMod(x, p))./Lnos ) );
- haackSeriesMod = @(x, p, C) ( r/sqrt(pi) ) * sqrt( thetaMod(x, p) ...
- - ( sin(2*thetaMod(x, p))./ 2 ) + C*sin(thetaMod(x, p)).^3 );
- yNos = haackSeriesMod(xNos, p, c);
- end
-
- if strcmp(obj.rear.boatType, 'OGIVE') % [-] Boat-tail shape. 0: Cone, 1: Tangent Ogive
- [xBoat, yBoat] = computeTangentBoatPoints(2*r, Daft, Laft);
- else
- xBoat = [0 Laft];
- yBoat = [r Daft/2];
- end
-
- %%% figure begin
- img = figure();
- hold on
-
- %%% NOSECONE
- plot(xNos, yNos, 'k');
- plot(xNos, -yNos, 'k');
- plot([Lnos Lnos], [-r r], 'k');
-
- %%% CENTERBODY
- plot([Lnos Lnos+Lcent], [r r], 'k');
- plot([Lnos Lnos+Lcent], [-r -r], 'k');
- plot([Lnos+Lcent Lnos+Lcent], [-r r], 'k');
-
- %%% BOAT-TAIL PLOT
- plot(xBoat+Lnos+Lcent, yBoat, 'k');
- plot(xBoat+Lnos+Lcent, -yBoat, 'k');
- plot([Lnos+Lcent+Laft Lnos+Lcent+Laft], [-Daft/2 Daft/2], 'k');
-
- %%% FINS PLOT
- % top
- plot([Xle1 Xle1+deltaXLE], [r r+height],'k');
- plot([Xle1+C1 Xle1+deltaXLE+C2], [r r+height],'k');
- plot([Xle1+deltaXLE Xle1+deltaXLE+C2], [r+height r+height],'k');
- plot([Xle1 Xle1+C1], [r r], 'k');
- % bottom
- plot([Xle1 Xle1+deltaXLE], [-r -r-height],'k');
- plot([Xle1+C1 Xle1+deltaXLE+C2], [-r -r-height],'k');
- plot([Xle1+deltaXLE Xle1+deltaXLE+C2], [-r-height, -r-height],'k');
- plot([Xle1 Xle1+C1], [-r -r], 'k');
-
- % plot([Xle1 Xle1+deltaXLE], [r+height r+height], 'k--')
- % plot([Xle1+deltaXLE Xle1+deltaXLE], [r+height r],'k--')
-
- %%% BAYS
- lengths = obj.absolutePositions.values + 2*Lnos;
- baysBody = obj.absolutePositions.keys;
- iMotor = find(strcmp(obj.absolutePositions.keys,"motor"));
- xline(0,'r-.', 'Label', 'NOSE', ...
- 'LabelOrientation', 'aligned', 'LabelVerticalAlignment', 'bottom', ...
- 'LabelHorizontalAlignment', 'right');
- for i = 1:length(lengths)
- if i == iMotor
- line([lengths(i) lengths(i)], [-1 1], 'LineStyle', '--', 'Color', 'b'); % Draw the line
- text(lengths(i), -1 + 0.3, baysBody(i), 'VerticalAlignment', 'top', ...
- 'HorizontalAlignment', 'right', 'Rotation', 90, 'Color', 'b');
- else
- line([lengths(i) lengths(i)], [-1 1], 'LineStyle', '--', 'Color', 'k'); % Draw the line
- text(lengths(i), 1 + 0.1, baysBody(i), 'VerticalAlignment', 'top', ...
- 'HorizontalAlignment', 'right', 'Rotation', 90);
- end
- end
- boatPlotLength = obj.length - obj.rear.boatLength;
- xline(boatPlotLength,'r-.', 'Label', 'BOAT-TAIL', ...
- 'LabelOrientation', 'aligned', 'LabelVerticalAlignment', 'bottom', ...
- 'LabelHorizontalAlignment', 'right');
-
- axis equal
- % set(gca, 'xlim', [-100, Lnos+Lcent+Laft+100]);
-
- %%% TITLE
- title(string(strrep(obj.mission.name, '_', ' ')));
- end
-
-
- function checks = checkGeometry(obj)
- % checkGeometry - This methods checks if the rocket geometry
- % is consistent with the geometry of the
- % aerodynamic matrices
- %
- % OUTPUTS:
- % - checks (n fields of geometry, 1): boolean value of the geometry checks
-
- xCgRocket = round([ ...
- obj.xCg(1); ...
- obj.xCg(end) ...
- ], 3);
-
- xCgTest = round([
- obj.coefficients.geometry.xcg(1);
- obj.coefficients.geometry.xcg(end);
- ], 3);
-
- if (obj.parafoil.noseCMod & obj.parafoil.nosePMod) == 0 % KARMAN ogive case, no modified p and c coefficients
- geometryRocket = round([
- obj.diameter;
- obj.parafoil.noseLength;
- obj.lengthCenter;
- obj.rear.finsRootChord;
- obj.rear.finsFreeChord;
- obj.rear.finsHeight;
- obj.rear.finsDeltaXFreeChord;
- obj.rear.nPanel;
- obj.rear.boatLength;
- obj.rear.boatFinalDiameter;
- ], 3);
-
- geometryTest = round([
- obj.coefficients.geometry.diameter;
- obj.coefficients.geometry.lNose;
- obj.coefficients.geometry.lCenter;
- obj.coefficients.geometry.chord1;
- obj.coefficients.geometry.chord2;
- obj.coefficients.geometry.height;
- obj.coefficients.geometry.deltaXLE;
- obj.coefficients.geometry.nPanel;
- obj.coefficients.geometry.boatL;
- obj.coefficients.geometry.boatD;
- ], 3);
- else % MHAAK ogive case, modified p and c coefficients
- geometryRocket = round([
- obj.diameter;
- obj.parafoil.noseLength;
- obj.lengthCenter;
- obj.parafoil.noseCMod;
- obj.parafoil.nosePMod;
- obj.rear.finsRootChord;
- obj.rear.finsFreeChord;
- obj.rear.finsHeight;
- obj.rear.finsDeltaXFreeChord;
- obj.rear.nPanel;
- obj.rear.boatLength;
- obj.rear.boatFinalDiameter;
- ], 3);
-
- geometryTest = round([
- obj.coefficients.geometry.diameter;
- obj.coefficients.geometry.lNose;
- obj.coefficients.geometry.lCenter;
- obj.coefficients.geometry.cMod;
- obj.coefficients.geometry.pMod;
- obj.coefficients.geometry.chord1;
- obj.coefficients.geometry.chord2;
- obj.coefficients.geometry.height;
- obj.coefficients.geometry.deltaXLE;
- obj.coefficients.geometry.nPanel;
- obj.coefficients.geometry.boatL;
- obj.coefficients.geometry.boatD;
- ], 3);
- end
-
- checks = [
- xCgRocket == xCgTest;
- strcmp(obj.coefficients.geometry.ogType, obj.parafoil.noseType);
- geometryRocket == geometryTest;
- strcmp(obj.coefficients.geometry.boatType, obj.rear.boatType)
- ];
- end
- end
-end
\ No newline at end of file
diff --git a/classes/bays/@Motor/Motor.m b/classes/bays/@Motor/Motor.m
new file mode 100644
index 0000000000000000000000000000000000000000..e49fe4e8e208374bcbca4b702cc473a9b5580502
--- /dev/null
+++ b/classes/bays/@Motor/Motor.m
@@ -0,0 +1,137 @@
+classdef Motor < Bay
+ % Motor: Represents the motor configuration for a rocket.
+ %
+ % Constructor:
+ % - Motor: Creates an instance of the Motor class.
+ % Loaded config: rocketConfig.m > motor
+ % Loaded data: motors.mat
+ % Arguments:
+ % - mission: Mission, mission object
+ % - varIn: (optional) config source. Alternative to config.m file
+
+ %% Bay Implementation
+ properties(Dependent)
+ name char % [-] Motor name
+ mass % [kg] Total bay mass
+ inertia % [kg*m^2] Total bay inertia (Body reference)
+ xcg % [m] Xcg wrt bay top
+ end
+
+ properties(Access = private)
+ NAME % [-] Motor name
+ MASS % [kg] Total bay mass
+ INERTIA % [kg*m^2] Total bay inertia (Body reference)
+ XCG % [m] Xcg wrt bay top
+ end
+
+ %% Motor properties
+ properties(SetAccess = private)
+ type (1, 1) MotorType % [-] Motor type - Solid, Hybrid, Liquid
+ thrust (1, :) double % [N] Engine thrust vector
+ propellantMass (1, :) double % [Kg] Propellant Mass in time
+ chamberPressure (1, :) double % [Pa] Pressure inside combustion chamber
+ pe (1, :) double % [Pa] Eflux pressure
+ end
+
+ properties
+ time double % [s] Engine time vector
+ cutoffTime double % [s] Shutdown time
+ ignitionTransient double % [s] Ignition transient duration
+ cutoffTransient double % [s] Cutoff transient duration
+ tankLength double % [m] Tank length
+ fuelMass double % [kg] Fuel grain initial mass
+ oxidizerMass double % [kg] Oxidizer initial mass
+ structureMass double % [kg] Engine Structural Mass
+ fuselageMass double % [kg] Fuselage of the engine only
+ ae double % [Pa] Eflux Area
+ end
+
+ properties(Constant, Access = protected)
+ configName = 'rocketConfig.m'
+ variableName = 'motor'
+ end
+
+ properties(Access = private)
+ mission Mission = Mission()
+ end
+
+ methods
+ function obj = Motor(mission, varIn)
+ arguments(Input)
+ mission Mission = Mission()
+ varIn = []
+ end
+ obj@Bay(mission, varIn);
+ obj.mission = mission;
+ obj = obj.loadData();
+ end
+ end
+
+ methods (Access = private)
+ obj = loadData(obj)
+ out = validateTimeDependent(obj, value)
+ end
+
+ %% Bay implementation
+ % Getters
+ methods
+ function value = get.name(obj)
+ value = obj.NAME;
+ end
+
+ function value = get.mass(obj)
+ value = obj.MASS;
+ end
+
+ function value = get.inertia(obj)
+ value = obj.INERTIA;
+ end
+
+ function value = get.xcg(obj)
+ value = obj.XCG;
+ end
+ end
+
+ % Setters
+ methods
+ function obj = set.name(obj, name)
+ obj.NAME = name;
+ obj = obj.loadData();
+ end
+
+ function obj = set.mass(obj, mass)
+ value = obj.validateTimeDependent(mass);
+ obj.MASS = value;
+ end
+
+ function obj = set.inertia(obj, inertia)
+ value = obj.validateTimeDependent(inertia);
+ obj.INERTIA = value;
+ end
+
+ function obj = set.xcg(obj, xcg)
+ value = obj.validateTimeDependent(xcg);
+ obj.XCG = value;
+ end
+
+ function obj = set.thrust(obj, thrust)
+ value = obj.validateTimeDependent(thrust);
+ obj.thrust = value;
+ end
+
+ function obj = set.propellantMass(obj, propellantMass)
+ value = obj.validateTimeDependent(propellantMass);
+ obj.propellantMass = value;
+ end
+
+ function obj = set.chamberPressure(obj, chamberPressure)
+ value = obj.validateTimeDependent(chamberPressure);
+ obj.chamberPressure = value;
+ end
+
+ function obj = set.pe(obj, pe)
+ value = obj.validateTimeDependent(pe);
+ obj.pe = value;
+ end
+ end
+end
\ No newline at end of file
diff --git a/classes/bays/@Motor/loadData.m b/classes/bays/@Motor/loadData.m
new file mode 100644
index 0000000000000000000000000000000000000000..460082b873ab45a33d5a0976ae5453187832f353
--- /dev/null
+++ b/classes/bays/@Motor/loadData.m
@@ -0,0 +1,50 @@
+function obj = loadData(obj)
+
+if isempty(obj.name) || isempty(obj.mission.name)
+ return;
+end
+load(fullfile(obj.mission.dataPath, 'motors.mat'), 'motors');
+chosenMotor = motors(strcmp({motors.MotorName}, obj.name));
+
+if ~(isempty(obj.name) || isvarname(obj.name))
+ error('Motor name is not a valid MATLAB variable name')
+end
+
+if isempty(chosenMotor)
+ error(strcat('Unable to find engine: ', obj.name));
+end
+
+[obj.time, iUniqueTime] = unique(chosenMotor.t);
+obj.thrust = chosenMotor.T(iUniqueTime);
+obj.propellantMass = chosenMotor.m(iUniqueTime);
+obj.structureMass = chosenMotor.mc;
+
+if contains(obj.name, 'HRE')
+ obj.type = "Hybrid";
+else
+ obj.type = "Solid";
+end
+
+if obj.type == "Hybrid"
+ obj.length = chosenMotor.L;
+ obj.tankLength = chosenMotor.Ltank;
+ obj.fuelMass = chosenMotor.mFu;
+ obj.oxidizerMass = chosenMotor.mOx;
+ inertiaRaw = [chosenMotor.Ixx;chosenMotor.Iyy;chosenMotor.Izz];
+ obj.INERTIA = inertiaRaw(:, iUniqueTime);
+ obj.XCG = chosenMotor.xcg(iUniqueTime);
+ obj.pe = chosenMotor.Pe(iUniqueTime);
+ obj.ae = chosenMotor.Ae;
+ obj.fuselageMass = chosenMotor.mFus;
+ obj.chamberPressure = chosenMotor.Pc;
+ obj.MASS = obj.propellantMass + obj.structureMass;
+else
+ obj.length = chosenMotor.L/1000; % lengths are saved in mm for solid motors
+ obj.xcg = obj.length/2 * ones(1, size(obj.time, 2));
+end
+
+if isempty(obj.cutoffTime) || obj.cutoffTime > obj.time(end)
+ obj.cutoffTime = obj.time(end);
+end
+
+end
\ No newline at end of file
diff --git a/classes/bays/@Motor/validateTimeDependent.m b/classes/bays/@Motor/validateTimeDependent.m
new file mode 100644
index 0000000000000000000000000000000000000000..458350973afe3cdf66fbb27d8f146029cdbaa86c
--- /dev/null
+++ b/classes/bays/@Motor/validateTimeDependent.m
@@ -0,0 +1,14 @@
+function out = validateTimeDependent(obj, value)
+len = length(obj.time);
+
+if isempty(obj.time), out = value; return; end
+if size(value, 2) == 1, out = repmat(value, 1, len); return; end
+if length(value) ~= length(obj.time)
+ error = MException( ...
+ 'MSA:badInput', ...
+ 'Incorrect dimensions: %s and time vector must be the same size', ...
+ property);
+ throwAsCaller(error);
+end
+out = value;
+end
\ No newline at end of file
diff --git a/classes/bays/Airbrakes.m b/classes/bays/Airbrakes.m
index dbb8478838af27fba4ea60be0c2c1bb4c559b74e..73495d58137e2a369b6d84114c164aca63367222 100644
--- a/classes/bays/Airbrakes.m
+++ b/classes/bays/Airbrakes.m
@@ -10,6 +10,13 @@ classdef Airbrakes < Bay
% - varIn: (optional) config source. Alternative to config.m
% file
+ %% Bay Implementation
+ properties
+ mass % [kg] Total bay mass
+ inertia % [kg*m^2] Total bay inertia (Body reference)
+ xcg % [m] Xcg wrt bay top
+ end
+
properties
enabled logical % If false, airbrakes will be kept closed during flight
identification logical % If false,
@@ -24,52 +31,44 @@ classdef Airbrakes < Bay
servoTau double
servoOmega double % [rad/s] Servo-motor angular velocity
- extension double % aerobrakes, 1-2-3 for 0%, 50% or 100% opened
+ extension double % aerobrakes, 0-1 for 0-100% opened
deltaTime double % aerobrakes, configurations usage time
maxMach double % [-] Maximum Mach at which airbrakes can be used
height double % [m] Block airbrakes opening coordinate ( First entry must be 0! )
angleFunction function_handle % [-] Relation between angle and extension height
+ end
- position % [m] Offset with respect to other bays (negative -> shift forward)
- length % [m] Total bay length
- mass % [kg] Total bay mass
- inertia % [kg*m^2] Total bay inertia (Body reference)
- xCg % [m] Cg relative to bay upper side
+ properties(SetAccess = ?Rocket, GetAccess = private)
+ minTime % [s] Minimum time since engine fire at which airbrakes can open
end
-
- properties(Access = protected)
- configName = 'rocketConfig.m'
- variableName = 'airbrakes'
- mission Mission = Mission()
- motor Motor = Motor()
- end
- properties(Access = public)
+ properties(SetAccess = private)
time double
end
- methods
- function obj = Airbrakes(mission, motor, varIn)
- arguments(Input)
- mission Mission = Mission()
- motor Motor = Motor()
- varIn = []
- end
- obj@Bay(mission, varIn);
- obj.motor = motor;
+ properties(Constant, Access = protected)
+ configName = 'rocketConfig.m'
+ variableName = 'airbrakes'
+ end
+
+ methods
+ function obj = set.minTime(obj, minTime)
+ obj.minTime = minTime;
+ obj = obj.updateTime();
end
-
- function set.motor(obj, motor)
- obj.motor = motor;
- obj.updateTime;
+
+ function obj = set.deltaTime(obj, deltaTime)
+ obj.deltaTime = deltaTime;
+ obj = obj.updateTime();
end
- end
- methods
- function updateTime(obj)
- obj.time = cumsum(obj.deltaTime) + obj.motor.cutoffTime;
+ function obj = updateTime(obj)
+ if isempty(obj.deltaTime) || isempty(obj.minTime), return; end
+ obj.time = cumsum(obj.deltaTime) + obj.minTime;
end
+ end
+ methods
function extension = angle2Extension(obj, angle)
extension = obj.angleFunction(angle) / obj.height(end);
end
diff --git a/classes/bays/Electronics.m b/classes/bays/Electronics.m
index a9448aa834efea6ca915ddce4ebf3b4b97b7e4aa..7f87a9879973869974a126062b575f7f5b08996b 100644
--- a/classes/bays/Electronics.m
+++ b/classes/bays/Electronics.m
@@ -9,28 +9,16 @@ classdef Electronics < Bay
% - mission: Mission, mission object
% - varIn: (optional) config source. Alternative to config.m
% file
+
+ %% Bay Implementation
properties
- offset = 0
- position % [m] Absolute position, relative to nose base
- length % [m] Total bay length
- mass % [kg] Total bay mass
- inertia % [kg*m^2] Total bay inertia (Body reference)
- xCg % [m] Cg relative to bay upper side
+ mass % [kg] Total bay mass
+ inertia % [kg*m^2] Total bay inertia (Body reference)
+ xcg % [m] Xcg wrt bay top
end
- properties(Access = protected)
+ properties(Constant, Access = protected)
configName = 'rocketConfig.m'
variableName = 'electronics'
- mission Mission = Mission()
- end
-
- methods
- function obj = Electronics(mission, varIn)
- arguments(Input)
- mission Mission = Mission()
- varIn = []
- end
- obj@Bay(mission, varIn);
- end
end
end
\ No newline at end of file
diff --git a/classes/bays/Motor.m b/classes/bays/Motor.m
deleted file mode 100644
index 39f6ed2d790b8a95a4acc8d1e12fab435921fe39..0000000000000000000000000000000000000000
--- a/classes/bays/Motor.m
+++ /dev/null
@@ -1,135 +0,0 @@
-classdef Motor < Bay
- % Motor: Represents the motor configuration for a rocket.
- %
- % Constructor:
- % - Motor: Creates an instance of the Motor class.
- % Loaded config: rocketConfig.m > motor
- % Loaded data: motors.mat
- % Arguments:
- % - mission: Mission, mission object
- % - varIn: (optional) config source. Alternative to config.m file
-
- properties
- name {mustBeTextScalar} = '' % [-] Motor name
- position % [m] Absolute position, relative to nose base
- length % [m] Total length (motor + tank)
- inertia % [kg*m^2] Total Motor inertia (Body reference)
- cutoffTime double % [s] Shutdown time
- tankLength double % [m] Tank length
- ignitionTransient double % [s] Ignition transient duration
- cutoffTransient double % [s] Cutoff transient duration
- time double % [s] Engine time vector
- thrust double % [N] Engine thrust vector
- fuelMass double % [kg] Fuel (grain) initial mass
- oxidizerMass double % [kg] Oxidizer initial mass
- propellantMass double % [Kg] Propellant Mass (in time)
- structureMass double % [kg] Engine Structural Mass
- fuselageMass double % [kg] Fuselage of the engine only
- chamberPressure double % [Pa] Pressure inside combustion chamber
- xCg % [m] Engine xcg from tank tip
- pe double % [Pa] Eflux pressure
- ae double % [Pa] Eflux Area
- end
-
- properties
- mass % [kg] Total Motor mass
- fuselageXCg double % [m] xcg of the engine fuselage only from tank tip
- end
-
- properties(Access = protected)
- configName = 'rocketConfig.m'
- variableName = 'motor'
- mission Mission = Mission()
- end
-
- properties(SetAccess = protected)
- isHRE logical % [-] Flag relateed to the type of motor: true if HRE
- end
-
- properties(Access = private)
- isBeingUpdated logical = false % [-] Flag used internally when some properties are being updated
- end
-
- methods
- function obj = Motor(mission, varIn)
- arguments(Input)
- mission Mission = Mission()
- varIn = []
- end
- obj@Bay(mission, varIn);
- obj.loadData();
- obj.updateAll();
- end
-
- function set.name(obj, name)
- obj.name = name;
- obj.changeState();
- obj.loadData();
- obj.updateAll();
- obj.changeState();
- end
-
- function updateAll(obj)
- obj.updateMass();
- end
-
- function changeState(obj)
- obj.isBeingUpdated = not(obj.isBeingUpdated);
- end
-
- function updateMass(obj)
- obj.fuselageXCg = (obj.length - ...
- obj.tankLength)/2 + obj.tankLength;
- obj.mass = obj.propellantMass + obj.structureMass;
- end
- end
-
- methods (Access = protected)
- function obj = loadData(obj)
- if isempty(obj.mission.name) || isempty(obj.name)
- return;
- end
- load(fullfile(obj.mission.dataPath, 'motors.mat'), 'motors');
- chosenMotor = motors(strcmp({motors.MotorName}, obj.name));
-
- if ~(isempty(obj.name) || isvarname(obj.name))
- error('Motor name is not a valid MATLAB variable name')
- end
-
- if isempty(chosenMotor)
- error(strcat('Unable to find engine: ', obj.name));
- end
-
- [obj.time, iUniqueTime] = unique(chosenMotor.t);
- obj.thrust = chosenMotor.T(iUniqueTime);
- obj.propellantMass = chosenMotor.m(iUniqueTime);
- obj.structureMass = chosenMotor.mc;
-
- obj.isHRE = contains(obj.name, 'HRE');
-
- if obj.isHRE
- obj.length = chosenMotor.L;
- obj.tankLength = chosenMotor.Ltank;
- if isempty(obj.tankLength)
- obj.tankLength = chosenMotor.LtankPr + chosenMotor.LtankOx;
- end
- obj.fuelMass = chosenMotor.mFu;
- obj.oxidizerMass = chosenMotor.mOx;
- inertiaRaw = [chosenMotor.Ixx;chosenMotor.Iyy;chosenMotor.Izz];
- obj.inertia = inertiaRaw(:, iUniqueTime);
- obj.xCg = chosenMotor.xcg(iUniqueTime);
- obj.pe = chosenMotor.Pe(iUniqueTime);
- obj.ae = chosenMotor.Ae;
- obj.fuselageMass = chosenMotor.mFus;
- obj.chamberPressure = chosenMotor.Pc;
- else
- obj.length = chosenMotor.L/1000; % lengths are saved in mm for solid motors
- obj.xCg = obj.length/2 * ones(1, size(obj.time, 2));
- end
-
- if isempty(obj.cutoffTime) || obj.cutoffTime > obj.time(end) || obj.isBeingUpdated
- obj.cutoffTime = obj.time(end);
- end
- end
- end
-end
\ No newline at end of file
diff --git a/classes/bays/MotorType.m b/classes/bays/MotorType.m
new file mode 100644
index 0000000000000000000000000000000000000000..56cce1cbef4baa9218dafc21705d9e8b0f410155
--- /dev/null
+++ b/classes/bays/MotorType.m
@@ -0,0 +1,8 @@
+classdef MotorType
+ enumeration
+ Solid
+ Hybrid
+ Liquid
+ end
+end
+
diff --git a/classes/bays/Parafoil.m b/classes/bays/Parafoil.m
index 378fb88708e41030e60d487c5e5c11f3be4bbcee..f87d709d87937f566beb4ae0d21bda9a230e4855 100644
--- a/classes/bays/Parafoil.m
+++ b/classes/bays/Parafoil.m
@@ -9,7 +9,14 @@ classdef Parafoil < Bay
% - mission: Mission, mission object
% - varIn: (optional) config source. Alternative to config.m
% file
-
+
+ %% Bay Implementation
+ properties
+ mass % [kg] Total bay mass
+ inertia % [kg*m^2] Total bay inertia (Body reference)
+ xcg % [m] Xcg wrt bay top
+ end
+
properties
noseLength double % [m] Nosecone length
noseType {mustBeMember(noseType, { ...
@@ -19,22 +26,15 @@ classdef Parafoil < Bay
nosePower double % [-] Nosecone power type parameter
nosePMod double % [-] P coefficient for modified nosecone shapes
noseCMod double % [-] C coefficient for modified nosecone shapes
-
- position % [m] Absolute position, relative to nose base
- length % [m] Total bay length
- mass % [kg] Total bay mass
- inertia % [kg*m^2] Total bay inertia (Body reference)
- xCg % [m] Cg relative to bay upper side
end
- properties (Dependent)
- inverseInertia double
- end
+ % properties (Dependent)
+ % inverseInertia double
+ % end
- properties(Access = protected)
+ properties(Constant, Access = protected)
configName = 'rocketConfig.m'
variableName = 'parafoil'
- mission Mission = Mission()
end
methods
@@ -47,9 +47,9 @@ classdef Parafoil < Bay
end
end
- methods
- function inverseInertia = get.inverseInertia(obj)
- inverseInertia = inv(obj.inertiaMatrix);
- end
- end
+ % methods
+ % function inverseInertia = get.inverseInertia(obj)
+ % inverseInertia = inv(obj.inertiaMatrix);
+ % end
+ % end
end
\ No newline at end of file
diff --git a/classes/bays/Rear.m b/classes/bays/Rear.m
index 65d561d73eb9973703fe104184df2805f0981cd7..2e713d59def14c04a6ef9920d638bc43a8d37e75 100644
--- a/classes/bays/Rear.m
+++ b/classes/bays/Rear.m
@@ -10,13 +10,14 @@ classdef Rear < Bay
% - varIn: (optional) config source. Alternative to config.m
% file
+ %% Bay Implementation
+ properties
+ mass % [kg] Total bay mass
+ inertia % [kg*m^2] Total bay inertia (Body reference)
+ xcg % [m] Xcg wrt bay top
+ end
+
properties
- position % [m] Absolute position, relative to nose base
- length % [m] Total bay length
- mass % [kg] Total bay mass
- inertia % [kg*m^2] Total bay inertia (Body reference)
- xCg % [m] Cg relative to bay upper side
-
boatType {mustBeMember(boatType, { ...
'', 'CONE', 'OGIVE'})} = '' % [] Boat type
boatLength double % [m] Boat length
@@ -34,20 +35,9 @@ classdef Rear < Bay
finsMaxThicknessPosition double % [m] Fraction of chord from leading edge to max thickness
end
- properties(Access = protected)
+ properties(Constant, Access = protected)
configName = 'rocketConfig.m'
variableName = 'rear'
- mission Mission = Mission()
- end
-
- methods
- function obj = Rear(mission, varIn)
- arguments(Input)
- mission Mission = Mission()
- varIn = []
- end
- obj@Bay(mission, varIn);
- end
end
end
diff --git a/classes/bays/Recovery.m b/classes/bays/Recovery.m
index b5d10de236fb9b2668a0c71493442c1cf19b903b..40c7147bf7ac6d1ebfa75ca8acbe60086a7999e5 100644
--- a/classes/bays/Recovery.m
+++ b/classes/bays/Recovery.m
@@ -10,27 +10,15 @@ classdef Recovery < Bay
% - varIn: (optional) config source. Alternative to config.m
% file
+ %% Bay Implementation
properties
- position % [m] Absolute position, relative to nose base
- length % [m] Total bay length
- mass % [kg] Total bay mass
- inertia % [kg*m^2] Total bay inertia (Body reference)
- xCg % [m] Cg relative to bay upper side
+ mass % [kg] Total bay mass
+ inertia % [kg*m^2] Total bay inertia (Body reference)
+ xcg % [m] Xcg wrt bay top
end
- properties(Access = protected)
+ properties(Constant, Access = protected)
configName = 'rocketConfig.m'
variableName = 'recovery'
- mission Mission = Mission()
- end
-
- methods
- function obj = Recovery(mission, varIn)
- arguments(Input)
- mission Mission = Mission()
- varIn = []
- end
- obj@Bay(mission, varIn);
- end
end
end
\ No newline at end of file
diff --git a/classes/components/Para.m b/classes/misc/ParaLoader.m
similarity index 51%
rename from classes/components/Para.m
rename to classes/misc/ParaLoader.m
index fb7388e7c1af52dd9afab7f6dde18e6aceb35883..0046722c475f09e8bd4fb23ba750ebd7f756b421 100644
--- a/classes/components/Para.m
+++ b/classes/misc/ParaLoader.m
@@ -1,4 +1,4 @@
-classdef Para < matlab.mixin.Heterogeneous & Component
+classdef ParaLoader < Config
% Parachute: Represents a parachute component.
%
% Constructor:
@@ -15,38 +15,28 @@ classdef Para < matlab.mixin.Heterogeneous & Component
% the third dimension can be trimmed away.
% Do NOT consider the third dimension as valid
- properties(Access = protected)
+ properties
+ parachutes
+ end
+
+ properties(Constant, Access = protected)
configName = 'paraConfig.m'
variableName = 'para'
- mission Mission
end
methods
- function obj = Para(mission, varIn)
+ function obj = ParaLoader(mission, varsIn)
arguments(Input)
mission Mission = Mission()
- varIn = []
+ varsIn = []
end
- obj@Component(mission, varIn, "elementWise", false);
-
- %% Forcing creation of heterogeneous array
- if any(size(obj) > 1)
- switch class(obj)
- % In case of homogeneous type, forces conversion to
- % heterogeneous Para array
- case 'Parachute'
- obj(1, 1, 2) = Wing();
- case 'Wing'
- obj(1, 1, 2) = Parachute();
- otherwise
- end
+
+ if isempty(mission.configPath), return; end
+ if isempty(varsIn)
+ varsIn = obj.getConfig(mission.configPath);
end
- end
- end
- methods (Static,Sealed,Access=protected)
- function default = getDefaultScalarElement
- default = Parachute;
+ obj.parachutes = varsIn.para;
end
end
end
\ No newline at end of file
diff --git a/classes/components/Parachute.m b/classes/misc/Parachute.m
similarity index 85%
rename from classes/components/Parachute.m
rename to classes/misc/Parachute.m
index e16eb69be8156fcb408dd3c03960d2015a70df64..c706a1f9c2bd234b5d8e009f38a016d83aee8d12 100644
--- a/classes/components/Parachute.m
+++ b/classes/misc/Parachute.m
@@ -1,4 +1,4 @@
-classdef Parachute < Para
+classdef Parachute
% Parachute: Represents a parachute component.
%
% Constructor:
@@ -28,17 +28,5 @@ classdef Parachute < Para
nf double % [-] Adimensional Opening Time
forceCoefficient double % [-] Empirical coefficient to obtain correct peak force at deployment
end
-
- methods
- function obj = Parachute(mission, varIn)
- arguments(Input)
- mission Mission = Mission()
- varIn = []
- end
-
- obj@Para(mission, varIn);
- obj = obj(:, :, 1);
- end
- end
end
diff --git a/classes/components/Pitot.m b/classes/misc/Pitot.m
similarity index 81%
rename from classes/components/Pitot.m
rename to classes/misc/Pitot.m
index 1d8cd4885a8e90c1f0fcb17f681edfdbf77f5118..dd2d023d35cbdf0cf1f13c6290e38abd3845b470 100644
--- a/classes/components/Pitot.m
+++ b/classes/misc/Pitot.m
@@ -1,4 +1,4 @@
-classdef Pitot < Component
+classdef Pitot < Config
% Pitot: Represents a pitot tube.
%
% Constructor:
@@ -19,19 +19,19 @@ classdef Pitot < Component
finalConeDiameter double % [m] Pitot final conic section diameter
end
- properties(Access = protected)
+ properties(Constant, Access = protected)
configName = 'rocketConfig.m'
variableName = 'pitot'
- mission Mission = Mission()
end
methods
- function obj = Pitot(mission, varIn)
- arguments(Input)
+ function obj = Pitot(mission, varsIn)
+ arguments (Input)
mission Mission = Mission()
- varIn = []
+ varsIn = []
end
- obj@Component(mission, varIn);
+
+ obj@Config(mission.configPath, varsIn);
end
end
end
\ No newline at end of file
diff --git a/classes/components/WindCustom.m b/classes/misc/WindCustom.m
similarity index 100%
rename from classes/components/WindCustom.m
rename to classes/misc/WindCustom.m
diff --git a/classes/components/WindMatlab.m b/classes/misc/WindMatlab.m
similarity index 100%
rename from classes/components/WindMatlab.m
rename to classes/misc/WindMatlab.m
diff --git a/classes/components/Wing.m b/classes/misc/Wing.m
similarity index 85%
rename from classes/components/Wing.m
rename to classes/misc/Wing.m
index 4e47f9e3a9938d03e714c9721344f2da8e712c57..abab7f9dba8385a9377fd5db562dfa381fdbb7bf 100644
--- a/classes/components/Wing.m
+++ b/classes/misc/Wing.m
@@ -1,4 +1,4 @@
-classdef Wing < Para
+classdef Wing
% Parachute: Represents a parachute component.
%
% Constructor:
@@ -18,7 +18,6 @@ classdef Wing < Para
mass double % [kg] Wing Mass
openingTime double % [s] Wing opening time (delay + time to get fully open)
- inertia % [kg*m^2] 3x3 Inertia Matrix (the diagonal is made of the inertia vector values)
finalAltitude double % [m] Final altitude of the parafoil
semiWingSpan double % [m] Wing semiwingspan
MAC double % [m] Wing mean aero chord
@@ -45,29 +44,27 @@ classdef Wing < Para
controlParams = [] % Struct containing all the control parameters
end
+ properties(Dependent)
+ inertia % [kg*m^2] 3x3 Inertia Matrix (the diagonal is made of the inertia vector values)
+ end
+
properties(SetAccess = private)
inverseInertia
end
- methods
- function obj = Wing(mission, varIn)
- arguments(Input)
- mission Mission = Mission()
- varIn = []
- end
-
- obj@Para(mission, varIn);
- obj = obj(:, :, 1);
- end
+ properties(Access = private)
+ INERTIA
+ end
- function set.inertia(obj, inertia)
- obj.inertia = inertia;
- obj.updateAll();
+ methods
+ function obj = set.inertia(obj, inertia)
+ obj.INERTIA = inertia;
+ if isempty(obj.inertia), return; end
+ obj.inverseInertia = obj.INERTIA\eye(3);
end
- function updateAll(obj)
- if isempty(obj.inertia), return; end
- obj.inverseInertia = obj.inertia\eye(3);
+ function inertia = get.inertia(obj)
+ inertia = obj.INERTIA;
end
end
end
\ No newline at end of file
diff --git a/functions/miscellaneous/camel2UpperSnake.m b/functions/miscellaneous/camel2UpperSnake.m
new file mode 100644
index 0000000000000000000000000000000000000000..a1d852b7755c5d919b8bdd544b085cf3c7d0b250
--- /dev/null
+++ b/functions/miscellaneous/camel2UpperSnake.m
@@ -0,0 +1,6 @@
+function result = camel2UpperSnake(camelStr)
+ % Convert a camelCase string to UPPER_SNAKE_CASE
+ modifiedStr = regexprep(camelStr, '([A-Z])', '_$1');
+ upperStr = upper(modifiedStr);
+ result = regexprep(upperStr, '^_', ''); % Remove leading underscore if present
+end
\ No newline at end of file
diff --git a/missions/2025_Orion_Portugal_October/config/rocketConfig.m b/missions/2025_Orion_Portugal_October/config/rocketConfig.m
index 71e89f1b36a4ea8678b67abdd027b886e92a11aa..70935bb21235288b69d68c21e73dcf373140ea95 100644
--- a/missions/2025_Orion_Portugal_October/config/rocketConfig.m
+++ b/missions/2025_Orion_Portugal_October/config/rocketConfig.m
@@ -1,13 +1,13 @@
% CONFIG - This script sets up rocket's parameters
%% ROCKET - OVERRIDES BAYS CONFIG
-rocket = Rocket();
-
-rocket.diameter = 0.15; % [m] Rocket diameter
-rocket.massNoMotor = []; % [kg] OVERRIDE mass without motor
-rocket.inertiaNoMotor = []; % [kg*m^2] OVERRIDE inertia without motor - body axes reference
-rocket.xCgNoMotor = []; % [m] OVERRIDE xCg without motor
-rocket.lengthCenterNoMot = []; % [m] OVERRIDE Center length - no nose, no motor
+% rocket = Rocket();
+%
+% rocket.diameter = 0.15; % [m] Rocket diameter
+% rocket.massNoMotor = []; % [kg] OVERRIDE mass without motor
+% rocket.inertiaNoMotor = []; % [kg*m^2] OVERRIDE inertia without motor - body axes reference
+% rocket.xCgNoMotor = []; % [m] OVERRIDE xCg without motor
+% rocket.lengthCenterNoMot = []; % [m] OVERRIDE Center length - no nose, no motor
%% PRF - Includes Parafoil + Nose
parafoil = Parafoil();
@@ -15,7 +15,7 @@ parafoil = Parafoil();
parafoil.length = 646.2 * 1e-3; % [m] Total bay length
parafoil.mass = 5; % [kg] Total bay mass
parafoil.inertia = 1e-9*[10514313; 92235828; 92322682]; % [kg*m^2] Total bay inertia (Body reference)
-parafoil.xCg = 453.55 * 1e-3; % [m] Cg relative to bay upper side
+parafoil.xcg = 453.55 * 1e-3; % [m] Cg relative to bay upper side
parafoil.noseLength = 0.327; % [m] Nosecone length
parafoil.noseType = 'MHAACK'; % [-] Nosecone shape
@@ -29,7 +29,7 @@ recovery = Recovery();
recovery.length = 826 * 1e-3; % [m] Total bay length
recovery.mass = 4.452; % [kg] Total bay mass
recovery.inertia = 1e-9*[11889636; 274548189; 275245205]; % [kg*m^2] Total bay inertia (Body reference)
-recovery.xCg = 459 * 1e-3; % [m] Cg relative to bay upper side
+recovery.xcg = 459 * 1e-3; % [m] Cg relative to bay upper side
%% ELC
electronics = Electronics();
@@ -37,7 +37,7 @@ electronics = Electronics();
electronics.length = 422.5 * 1e-3; % [m] Total bay length
electronics.mass = 3.3271; % [kg] Total bay mass
electronics.inertia = 1e-9*[10041478; 49742634; 50292878]; % [kg*m^2] Total bay inertia (Body reference)
-electronics.xCg = 221.11 * 1e-3; % [m] Cg relative to bay upper side
+electronics.xcg = 221.11 * 1e-3; % [m] Cg relative to bay upper side
%% ARB
airbrakes = Airbrakes();
@@ -47,7 +47,7 @@ airbrakes.identification = false; % Control parameter
airbrakes.length = 54.8 * 1e-3; % [m] Total bay length
airbrakes.mass = 0.96; % [kg] Total bay mass
airbrakes.inertia = 1e-9*[1886729; 1931082; 3088968]; % [kg*m^2] Total bay inertia (Body reference)
-airbrakes.xCg = 35.2 * 1e-3; % [m] Cg relative to bay upper side
+airbrakes.xcg = 35.2 * 1e-3; % [m] Cg relative to bay upper side
airbrakes.enabled = false; % If true, multiple and smooth airbrakes opening will be simulated
airbrakes.extension = [1]; % aerobrakes, 1-2-3 for 0%, 50% or 100% opened
@@ -82,7 +82,7 @@ rear.position = []; % [m] offse
rear.length = 477 * 1e-3; % [m] Total bay length
rear.mass = 1736.32 *1e-3; % [kg] Total bay mass
rear.inertia = 1e-9*[13662070; 47529495; 47528846]; % [kg*m^2] Total bay inertia (Body reference)
-rear.xCg = 236.82 * 1e-3; % [m] Cg relative to bay upper side
+rear.xcg = 236.82 * 1e-3; % [m] Cg relative to bay upper side
rear.boatType = 'OGIVE'; % [-] Boat type
rear.boatLength = 0.240; % [m] Boat length