diff --git a/classes/@Rocket/Rocket.m b/classes/@Rocket/Rocket.m
index a06283be4bc00d80338e94a9fc570771dfda416d..825e8360ef8caa2d09ce9628731c6f6616e89d73 100644
--- a/classes/@Rocket/Rocket.m
+++ b/classes/@Rocket/Rocket.m
@@ -50,9 +50,11 @@ classdef Rocket < Config
properties
pitot Pitot % [-] Pitot component
parachutes cell % [-] (nParachutes, nStages) Parachutes onboard
+
+ dynamicDerivatives (1, 1) logical % [-] True if dynamic derivatives will be loaded
- coefficients struct % [-] Aerodynamic coefficients
- coefficientsHighAOA struct % [-] Aerodynamic coefficients at high angle of attack
+ coefficients Coefficient % [-] Aerodynamic coefficients
+ coefficientsHighAOA Coefficient % [-] Aerodynamic coefficients at high angle of attack
end
properties(Access = private)
@@ -138,22 +140,62 @@ classdef Rocket < Config
obj.parachutes = paraLoader.parachutes;
if options.loadCoefficients
- obj = obj.loadData();
+ if obj.dynamicDerivatives
+ coeffName = obj.motor.name;
+ else
+ coeffName = 'generic';
+ end
+
+ obj.coefficients = Coefficient( ...
+ fullfile(mission.dataPath, 'aeroCoefficients.mat'), ...
+ coeffName);
+
+ obj.coefficientsHighAOA = Coefficient( ...
+ fullfile(mission.dataPath, 'aeroCoefficientsHighAOA.mat'), ...
+ coeffName);
+
answer = '';
- if isempty(obj.coefficients) || isempty(obj.coefficientsHighAOA)
+
+ if isempty(obj.coefficients.static) || isempty(obj.coefficientsHighAOA.static)
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?']);
+ elseif options.checkGeometry
+ [check, summary] = obj.checkGeometry();
+
+ if ~all(check)
+ disp(summary);
+ answer = questdlg(['Coefficient matrices differ from rocket geometry. ' ...
+ 'Do you want to create new matrices?']);
+ end
end
switch answer
case 'Yes'
+ % Check for required tools
+ isMsa = exist(mission.msaPath, "file");
+ isDissile = exist(mission.dissilePath, "file");
+
+ if ~all([isMsa, isDissile])
+ msg = 'The following toolkits are required to update coefficients:';
+
+ if ~isMsa
+ msg = sprintf(...
+ '%s\n - <a href="https://git.skywarder.eu/afd/msa/msa-toolkit">msa-toolkit</a>:\n\t In %s\n', ...
+ msg, mission.msaPath);
+ end
+
+ if ~isDissile
+ msg = sprintf('%s\n - <a href="https://git.skywarder.eu/afd/msa/dissilematcom">dissilematcom</a>:\n\t In %s\n', ...
+ msg, mission.dissilePath);
+ end
+ error(msg);
+ end
+
+ % Start coefficient creation
parserPath = fullfile(mission.msaPath, 'autoMatricesProtub');
addpath(genpath(parserPath));
- mainAutoMatProtub(obj);
- obj = obj.loadData();
+ [obj.coefficients, obj.coefficientsHighAOA] = ...
+ mainAutoMatProtub(obj);
case 'Cancel'
error('Rocket creation aborted')
otherwise
@@ -164,7 +206,7 @@ classdef Rocket < Config
methods
[coeffsValues, angle0] = interpCoeffs(obj, t, alpha, mach, beta, alt, c)
- checks = checkGeometry(obj)
+ [checks, summary] = checkGeometry(obj)
img = plot(obj)
end
diff --git a/classes/@Rocket/checkGeometry.m b/classes/@Rocket/checkGeometry.m
index e61422f40605ed733434a8ef1bc5dbd9ff23c935..d07a5cf08a494897f485a498a731819234d28d9e 100644
--- a/classes/@Rocket/checkGeometry.m
+++ b/classes/@Rocket/checkGeometry.m
@@ -1,11 +1,16 @@
-function checks = checkGeometry(obj)
+function [checks, summary] = 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
-
+
+ names = ["Initial xcg"; "Final xcg"; "Ogive type"; "Diameter"; "Nose Length";
+ "Nose p Mod"; "Nose c Mod"; "Center Length"; "Fins root chord";
+ "Fins free chord"; "Fins height"; "Fins XLE"; "Fins number";
+ "Boat Length"; "Boat final diameter"; "Boat type"];
+
xCgRocket = round([ ...
obj.xcg(1); ...
obj.xcg(end) ...
@@ -15,69 +20,78 @@ function checks = checkGeometry(obj)
obj.coefficients.geometry.xcg(1);
obj.coefficients.geometry.xcg(end);
], 3);
+
+ noseTypeCheck = strcmp(obj.coefficients.geometry.ogType, obj.parafoil.noseType);
+
+ geometryRocket = round([
+ obj.diameter;
+ obj.parafoil.noseLength;
+ 0; 0; % Placeholders for nose p and c mod
+ obj.lengthCenter;
+ obj.rear.finsRootChord;
+ obj.rear.finsFreeChord;
+ obj.rear.finsHeight;
+ obj.rear.finsDeltaXFreeChord;
+ obj.rear.nPanel;
+ obj.rear.boatLength;
+ obj.rear.boatFinalDiameter;
+ ], 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;
+ geometryTest = round([
+ obj.coefficients.geometry.diameter;
+ obj.coefficients.geometry.lNose;
+ 0; 0; % Placeholders for nose p and c mod
+ 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);
+
+ if (obj.parafoil.noseCMod && obj.parafoil.nosePMod)
+ geometryRocket([3, 4]) = round([ ...
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);
+ obj.parafoil.nosePMod;], 4);
+
+ geometryTest([3, 4]) = round([ ...
+ obj.parafoil.noseCMod;
+ obj.parafoil.nosePMod;], 4);
end
-
+
+ boatTypeCheck = strcmp(obj.coefficients.geometry.boatType, obj.rear.boatType);
+
checks = [
- xCgRocket == xCgTest;
- strcmp(obj.coefficients.geometry.ogType, obj.parafoil.noseType);
+ ~obj.dynamicDerivatives | (xCgRocket == xCgTest);
+ noseTypeCheck;
geometryRocket == geometryTest;
- strcmp(obj.coefficients.geometry.boatType, obj.rear.boatType)
+ boatTypeCheck;
];
+
+ if nargout == 2
+ % Summarize data and leave placeholders
+ ogiveType = ["CONE", "OGIVE", "POWER", "HAACK", "KARMAN", "MHAACK"];
+ boatType = ["CONE", "OGIVE"];
+
+ % Convert text to DATCOM standard. !TODO: Would be more robust if
+ % enums were used
+ boatRocket = find(strcmp(obj.rear.boatType, boatType), 1, 'first') - 1;
+ boatTest = find(strcmp(obj.coefficients.geometry.boatType, boatType), 1, 'first') - 1;
+
+ ogRocket = find(strcmp(obj.parafoil.noseType, ogiveType), 1, 'first') - 1;
+ ogTest = find(strcmp(obj.coefficients.geometry.ogType, ogiveType), 1, 'first') - 1;
+
+ rocketData = [xCgRocket; ogRocket; geometryRocket; boatRocket];
+ testData = [xCgTest; ogTest; geometryTest; boatTest];
+ checkNames = names(~checks);
+
+ if isempty(checkNames)
+ summary = table;
+ else
+ summary = table(rocketData(~checks), testData(~checks), ...
+ 'RowNames', checkNames, 'VariableNames', ["Rocket", "Coefficients"]);
+ end
+ end
end
\ No newline at end of file
diff --git a/classes/Mission.m b/classes/Mission.m
index 12cb70f968581a8259100b1fdc7c29d7196c1d7c..749a695bf4e4b1af095e867d0db0798836280f94 100644
--- a/classes/Mission.m
+++ b/classes/Mission.m
@@ -23,6 +23,9 @@ classdef Mission < Config
configPath char
dataPath char
msaPath char
+ prpPath char
+ gncPath char
+ dissilePath char
end
properties(Access = private)
@@ -98,6 +101,12 @@ classdef Mission < Config
obj.dataPath = fullfile(obj.currentPath, obj.name, 'data');
obj.msaPath = trimPath( ...
fullfile(obj.currentPath, '..', '..', '..', 'msa-toolkit'));
+ obj.prpPath = trimPath( ...
+ fullfile(obj.currentPath, '..', '..', '..', 'prp-toolkit'));
+ obj.gncPath = trimPath( ...
+ fullfile(obj.currentPath, '..', '..', '..', 'matlab-simulator'));
+ obj.dissilePath = trimPath( ...
+ fullfile(obj.currentPath, '..', '..', '..', 'dissilematcom'));
end
function updateMatlabPath(obj)
diff --git a/classes/misc/Coefficient.m b/classes/misc/Coefficient.m
new file mode 100644
index 0000000000000000000000000000000000000000..f7eb51b09518ae3395228fd0af572ef5f7ac421e
--- /dev/null
+++ b/classes/misc/Coefficient.m
@@ -0,0 +1,270 @@
+classdef Coefficient
+ % Coefficient: Manages the coefficients associated with a rocket
+ %
+ % Constructor:
+ % - Coefficient: Creates an instance of the Coefficient class.
+ % Loaded config: -
+ % Loaded data: aeroCoefficients.mat
+ % Arguments:
+ % - filePath: char, path to coefficient file to load
+ % - name: (optional) coefficient name. Used when dynamic
+ % derivatives are also needed
+ %
+ % Coefficients are retrieved from DATCOM in the following format:
+ % Coefficient matrix: double (15, nAlpha, nMach, nBeta, nAlt, nAbk, nXcg)
+ % Where the 15 coefficients are
+ % - CA Axial force
+ % - CYB Side force derivative wrt beta
+ % - CY0 Side force
+ % - CNA Normal force derivative wrt alpha
+ % - CN0 Normal force
+ % - Cl Rolling moment
+ % - Clp Rolling moment derivative wrt roll rate
+ % - Cma Pitching moment derivative wrt alpha
+ % - Cm0 Pitching moment
+ % - Cmad Pitching moment derivative wrt alpha dot
+ % - Cmq Pitching moment derivative wrt pitch rate
+ % - Cnb Yawing moment derivative wrt beta
+ % - Cn0 Yawing moment
+ % - Cnr Yawing moment derivative wrt yaw rate
+ % - Cnp Yawing moment derivative wrt roll rate
+ %
+ % Coefficients are then stored in the following format:
+ % static: double (6, nAlpha, nMach, nBeta, nAlt, nAbk)
+ % Where the 6 coefficients are:
+ % - [CA, CY, CN, Cl, Cm, Cn]
+ % dynamic: double (5, nAlpha, nMach, nBeta, nAlt, nAbk, nXcg)
+ % - [Clp, Cmad, Cmq, Cnr, Cnp]
+ %
+ % NOTE: When dynamic derivatives are not loaded, the matrix will be
+ % 6-D, as there will be no need to interpolate wrt to the xcg: moment
+ % transport formulas will be used instead
+ %
+ % NOTE: Coefficients in an interpolants are stored on the last
+ % dimension, instead of the first, to improve performance
+
+ properties(Dependent)
+ total double % Coefficients stored in DATCOM format
+ geometry struct % Reference geometry
+ state struct % Flight envelope
+ end
+
+ properties
+ finsCN double % Fins-only CN
+ end
+
+ properties(Dependent, SetAccess = private)
+ static double % Static coefficients: [CA, CY, CN, Cl, Cm, Cn]
+ dynamic double % Dynamic derivatives: [Clp, Cmad, Cmq, Cnr, Cnp]
+ end
+
+
+ properties(SetAccess = private)
+ isReady (1, 1) logical % Whether all coefficients are loaded and of the right size
+ isDynamic (1, 1) logical % Whether to load dynamic derivatives. Adds XCG dependece
+ end
+
+ properties(Access = private)
+ TOTAL % Cached variable for total
+ GEOMETRY % Cached variable for geometry
+ STATE % Cached variable for state
+ end
+
+ properties(Access = private)
+ staticInterpolant (1, 1) griddedInterpolant
+ dynamicInterpolant (1, 1) griddedInterpolant
+ end
+
+ methods
+ function obj = Coefficient(filePath, name)
+ arguments
+ filePath (1, :) char = ''
+ name (1, :) char = 'generic'
+ end
+
+ if isempty(filePath), return; end
+
+ obj = obj.loadData(filePath, name);
+ obj.isReady = obj.checkProperties();
+ obj = obj.updateInterpolants();
+ end
+
+ function coefficients = get(obj, alpha, mach, beta, altitude, airbakes, xcg)
+ % GET: Retrieve aerodynamic coefficients for specified flight conditions
+ %
+ % This method interpolates the aerodynamic coefficients based on
+ % the provided flight conditions and adjusts them for the given
+ % center of gravity (xcg).
+ %
+ % Arguments:
+ % - alpha double, angle of attack [rad]
+ % - mach double, Mach number [-]
+ % - beta double, sideslip angle [rad]
+ % - altitude double, altitude [m]
+ % - airbakes double, airbrake deployment [-]
+ % - xcg double, center of gravity position [m]
+ %
+ % Returns:
+ % - coefficients: double (11, 1), aerodynamic coefficients
+ % [CA, CY, CN, Cl, Cm, Cn, Clp, Cmad, Cmq, Cnr, Cnp]
+ %
+ % NOTE: Static coefficients are interpolated and adjusted for
+ % the specified xcg. Dynamic derivatives are included only if
+ % loadDynamic is true.
+
+ if ~obj.isReady, error('Cannot interpolate coefficients: check that all dimensions match'); end
+
+ coefficients = zeros(11, 1);
+ coefficients(1:6) = obj.staticInterpolant(alpha, mach, beta, altitude, airbakes);
+ % Transporting static coefficients to new xcg
+
+ % C_B = C_A + d / c * [0; -CN; CY]_A <- NOTE: Non torna il meno su CN
+ d = xcg - obj.GEOMETRY.xcg(1);
+ l = obj.GEOMETRY.diameter;
+
+ CY = coefficients(2); CN = coefficients(3);
+ forceCoeffs = [0; CN; CY];
+
+ coefficients(4:6) = coefficients(4:6) + d/l * forceCoeffs;
+
+ if ~obj.isDynamic, return; end
+ coefficients(7:11) = obj.dynamicInterpolant(alpha, mach, beta, altitude, airbakes, xcg);
+ end
+ end
+
+ methods % Getters
+ function value = get.total(obj)
+ value = obj.TOTAL;
+ end
+
+ function value = get.static(obj)
+ if isempty(obj.TOTAL), value = []; return; end
+ value = obj.TOTAL([1, 3, 5, 6, 9, 13], :, :, :, :, :, 1);
+ end
+
+ function value = get.dynamic(obj)
+ if ~obj.isDynamic || isempty(obj.TOTAL), value = []; return; end
+ value = obj.TOTAL([7, 10, 11, 14, 15], :, :, :, :, :, :);
+ end
+
+ function value = get.geometry(obj)
+ value = obj.GEOMETRY;
+ end
+
+ function value = get.state(obj)
+ value = obj.STATE;
+ end
+ end
+
+ methods % Setters
+ function obj = set.total(obj, value)
+ obj.TOTAL = value;
+ obj.isDynamic = size(value, 7) ~= 1;
+ obj.isReady = obj.checkProperties();
+ obj = obj.updateInterpolants();
+ end
+
+ function obj = set.geometry(obj, value)
+ obj.GEOMETRY = value;
+ obj.isReady = obj.checkProperties();
+ obj = obj.updateInterpolants();
+ end
+
+ function obj = set.state(obj, value)
+ obj.STATE = value;
+ obj.isReady = obj.checkProperties();
+ obj = obj.updateInterpolants();
+ end
+ end
+
+ methods(Access = private)
+ function obj = loadData(obj, filePath, name)
+ % Load the coefficients from the specified file
+ % filePath: char, path to coefficient file to load
+ % name: (optional) coefficient name. Used when dynamic
+ % derivatives are also needed
+ %
+ % NOTE: Coefficient alpha and beta derivatives are not loaded
+ % as coefficients are already interpolated linearly
+
+
+ if ~exist(filePath, 'file'), return; end
+ warning('off'); % Disable warning in case coefficients are not present
+ dataCoeffs = load(filePath, name);
+ warning('on');
+
+ if ~isfield(dataCoeffs, name), return; end
+ dataCoeffs = dataCoeffs.(name);
+
+ obj.finsCN = dataCoeffs.finsCN;
+ obj.GEOMETRY = dataCoeffs.geometry;
+ obj.STATE = dataCoeffs.state;
+
+ % Load coefficients
+ obj.total = dataCoeffs.total;
+ end
+
+ function ready = checkProperties(obj)
+ % Check if STATIC, DYNAMIC, GEOMETRY, and STATE are non-empty
+ ready = ~isempty(obj.static) && ...
+ ~isempty(obj.GEOMETRY) && ~isempty(obj.STATE) && ...
+ ~(isempty(obj.dynamic) && obj.isDynamic);
+
+ if ~ready, return; end
+
+ alpha = obj.STATE.alphas;
+ mach = obj.STATE.machs;
+ beta = obj.STATE.betas;
+ altitude = obj.STATE.altitudes;
+ airbakes = obj.STATE.hprot;
+ xcg = obj.GEOMETRY.xcg;
+
+ gridVecs = {alpha, mach, beta, altitude, airbakes, xcg};
+ dims = cellfun(@(x) length(x), gridVecs);
+ dims(dims == 0) = 1; % Empty case is the same as scalar case
+
+ ready = all(size(obj.total, 2:7) == dims);
+ end
+
+ function obj = updateInterpolants(obj)
+ % Update static and dynamic interpolants
+ if ~obj.isReady, return; end
+
+ %% Retrieve flight conditions
+ alpha = obj.STATE.alphas*pi/180; % Converting to rad
+ mach = obj.STATE.machs;
+ beta = obj.STATE.betas*pi/180; % Converting to rad
+ altitude = obj.STATE.altitudes;
+ xcg = obj.GEOMETRY.xcg;
+
+ if isempty(obj.STATE.hprot), airbakes = 0;
+ else, airbakes = obj.STATE.hprot/obj.STATE.hprot(end); % Normalizing on height
+ end
+
+ gridVecs = {alpha, mach, beta, altitude, airbakes, xcg};
+
+ % Find singleton dims (last dimension is coefficients and will not be of length 1)
+ singletonDims = cellfun(@(x) isscalar(x) || isempty(x), gridVecs);
+ gridVecs(singletonDims) = deal({[0, 1]});
+
+ %% Create interpolants
+ staticCoeffs = permute(obj.static, [2, 3, 4, 5, 6, 1]);
+ staticCoeffs = repmat(staticCoeffs, singletonDims(1:end-1) + 1); % Exclude xcg for static coefficients
+
+ obj.staticInterpolant = griddedInterpolant(gridVecs(1:end-1), staticCoeffs, 'linear', 'nearest');
+
+ if ~obj.isDynamic, return; end
+
+ %% Handle dynamic derivatives
+ dynamicCoeffs = permute(obj.dynamic, [2, 3, 4, 5, 6, 7, 1]);
+
+ % Flip xcg in case of descending order
+ if ~isscalar(xcg) && xcg(2) < xcg(1)
+ gridVecs{end} = flip(xcg);
+ dynamicCoeffs = flip(dynamicCoeffs, 7);
+ end
+
+ obj.dynamicInterpolant = griddedInterpolant(gridVecs, dynamicCoeffs, 'linear', 'nearest');
+ end
+ end
+end
\ No newline at end of file
diff --git a/classes/misc/Wind.m b/classes/misc/Wind.m
index f3eb9a9ae50e9225468ea9dddb03e517aac0b9f6..f3d6707c6f1fa867cfb842e397469bb4ddb7a7ef 100644
--- a/classes/misc/Wind.m
+++ b/classes/misc/Wind.m
@@ -9,6 +9,7 @@ classdef Wind < Config
% - mission: Mission, mission object
% - varIn: (optional) config source. Alternative to config.m
% file
+
properties(Dependent)
altitudes (1, :)
@@ -25,6 +26,9 @@ classdef Wind < Config
end
properties(Access = private)
+ isReady (1, 1) logical % true if all properties are set
+ dataInerpolant (1, 1) griddedInterpolant % [-] Interpolates [magnitude, azimuth, elevation]
+
ALTITUDES
MAGNITUDE_DISTRIBUTION = ''
@@ -41,77 +45,71 @@ classdef Wind < Config
elevation
magnitude
end
-
- properties(Access = private)
- checks (1, 3) logical % true if #[magnitude, azimuth, elevation] == #altitudes
- end
properties(Constant, Access = protected)
configName = 'windConfig.m'
variableName = 'windCustom'
end
- methods % Getters / Setters
- function obj = set.altitudes(obj, value)
- if length(value) ~= length(obj.ALTITUDES)
- obj.ALTITUDES = value;
- obj.magnitude = obj.updateDistribution(obj.MAGNITUDE_DISTRIBUTION, obj.MAGNITUDE_PARAMETERS);
- obj.azimuth = obj.updateDistribution(obj.AZIMUTH_DISTRIBUTION, obj.AZIMUTH_PARAMETERS);
- obj.elevation = obj.updateDistribution(obj.ELEVATION_DISTRIBUTION, obj.ELEVATION_PARAMETERS);
- else
- obj.ALTITUDES = value;
- end
+ methods % Getters
+ function value = get.altitudes(obj), value = obj.ALTITUDES; end
+
+ function value = get.magnitudeDistribution(obj), value = obj.MAGNITUDE_DISTRIBUTION; end
+ function value = get.azimuthDistribution(obj), value = obj.AZIMUTH_DISTRIBUTION; end
+ function value = get.elevationDistribution(obj), value = obj.ELEVATION_DISTRIBUTION; end
+
+ function value = get.magnitudeParameters(obj), value = obj.MAGNITUDE_PARAMETERS; end
+ function value = get.azimuthParameters(obj), value = obj.AZIMUTH_PARAMETERS; end
+ function value = get.elevationParameters(obj), value = obj.ELEVATION_PARAMETERS; end
+ end
- obj.checks(1) = length(obj.magnitude) == length(obj.ALTITUDES);
- obj.checks(2) = length(obj.azimuth) == length(obj.ALTITUDES);
- obj.checks(3) = length(obj.elevation) == length(obj.ALTITUDES);
+ methods % Setters
+ function obj = set.altitudes(obj, value)
+ obj.ALTITUDES = value;
+ obj = obj.updateAll();
end
function obj = set.magnitudeDistribution(obj, value)
obj.MAGNITUDE_DISTRIBUTION = value;
+ obj.isReady = obj.checkProperties();
obj.magnitude = obj.updateDistribution(value, obj.MAGNITUDE_PARAMETERS);
- obj.checks(1) = length(obj.magnitude) == length(obj.ALTITUDES);
+ obj = obj.updateInterpolant();
end
function obj = set.magnitudeParameters(obj, value)
obj.MAGNITUDE_PARAMETERS = value;
+ obj.isReady = obj.checkProperties();
obj.magnitude = obj.updateDistribution(obj.MAGNITUDE_DISTRIBUTION, value);
- obj.checks(1) = length(obj.magnitude) == length(obj.ALTITUDES);
+ obj = obj.updateInterpolant();
end
function obj = set.azimuthDistribution(obj, value)
obj.AZIMUTH_DISTRIBUTION = value;
+ obj.isReady = obj.checkProperties();
obj.azimuth = obj.updateDistribution(value, obj.AZIMUTH_PARAMETERS);
- obj.checks(2) = length(obj.azimuth) == length(obj.ALTITUDES);
+ obj = obj.updateInterpolant();
end
function obj = set.azimuthParameters(obj, value)
obj.AZIMUTH_PARAMETERS = value;
+ obj.isReady = obj.checkProperties();
obj.azimuth = obj.updateDistribution(obj.AZIMUTH_DISTRIBUTION, value);
- obj.checks(2) = length(obj.azimuth) == length(obj.ALTITUDES);
+ obj = obj.updateInterpolant();
end
function obj = set.elevationDistribution(obj, value)
obj.ELEVATION_DISTRIBUTION = value;
+ obj.isReady = obj.checkProperties();
obj.elevation = obj.updateDistribution(value, obj.ELEVATION_PARAMETERS);
- obj.checks(3) = length(obj.elevation) == length(obj.ALTITUDES);
+ obj = obj.updateInterpolant();
end
function obj = set.elevationParameters(obj, value)
obj.ELEVATION_PARAMETERS = value;
+ obj.isReady = obj.checkProperties();
obj.elevation = obj.updateDistribution(obj.ELEVATION_DISTRIBUTION, value);
- obj.checks(3) = length(obj.elevation) == length(obj.ALTITUDES);
+ obj = obj.updateInterpolant();
end
-
- function value = get.altitudes(obj), value = obj.ALTITUDES; end
-
- function value = get.magnitudeDistribution(obj), value = obj.MAGNITUDE_DISTRIBUTION; end
- function value = get.azimuthDistribution(obj), value = obj.AZIMUTH_DISTRIBUTION; end
- function value = get.elevationDistribution(obj), value = obj.ELEVATION_DISTRIBUTION; end
-
- function value = get.magnitudeParameters(obj), value = obj.MAGNITUDE_PARAMETERS; end
- function value = get.azimuthParameters(obj), value = obj.AZIMUTH_PARAMETERS; end
- function value = get.elevationParameters(obj), value = obj.ELEVATION_PARAMETERS; end
end
methods
@@ -123,18 +121,8 @@ classdef Wind < Config
obj@Config(mission, varIn);
end
- function obj = updateAll(obj)
- obj.magnitude = obj.updateDistribution(obj.MAGNITUDE_DISTRIBUTION, obj.MAGNITUDE_PARAMETERS);
- obj.azimuth = obj.updateDistribution(obj.AZIMUTH_DISTRIBUTION, obj.AZIMUTH_PARAMETERS);
- obj.elevation = obj.updateDistribution(obj.ELEVATION_DISTRIBUTION, obj.ELEVATION_PARAMETERS);
-
- obj.checks(1) = length(obj.magnitude) == length(obj.ALTITUDES);
- obj.checks(2) = length(obj.azimuth) == length(obj.ALTITUDES);
- obj.checks(3) = length(obj.elevation) == length(obj.ALTITUDES);
- end
-
function [uw, vw, ww] = getVels(obj, z)
- if ~all(obj.checks)
+ if ~obj.isReady
error(['Parameters and distributions must be the same ' ...
'size as altitudes or scalar']);
end
@@ -144,18 +132,52 @@ classdef Wind < Config
vw = round( - obj.magnitude * sin(obj.azimuth) * cos(obj.elevation), 6);
ww = round( - obj.magnitude * (-sin(obj.elevation)), 6);
else
- mag = interpLinear(obj.altitudes, obj.magnitude, z, true);
- az = interpLinear(obj.altitudes, obj.azimuth, z, true);
- el = interpLinear(obj.altitudes, obj.elevation, z, true);
+ data = obj.dataInerpolant(z);
+ mag = data(1); az = data(2); el = data(3);
uw = round( - mag * cos(az) * cos(el), 6);
vw = round( - mag * sin(az) * cos(el), 6);
ww = round( - mag * (-sin(el)), 6);
end
end
+
+ function obj = updateAll(obj)
+ obj.magnitude = obj.updateDistribution(obj.MAGNITUDE_DISTRIBUTION, obj.MAGNITUDE_PARAMETERS);
+ obj.azimuth = obj.updateDistribution(obj.AZIMUTH_DISTRIBUTION, obj.AZIMUTH_PARAMETERS);
+ obj.elevation = obj.updateDistribution(obj.ELEVATION_DISTRIBUTION, obj.ELEVATION_PARAMETERS);
+
+ obj.isReady = obj.checkProperties();
+ obj = obj.updateInterpolant();
+ end
+
+ function obj = updateInterpolant(obj)
+ % UPDATEINTERPOLANT: Interpolates [magnitude; azimuth; elevation] based on altitude
+ %
+ % Returns:
+ % - interpolant: griddedInterpolant for [magnitude; azimuth; elevation]
+
+ if ~obj.isReady, return; end
+ if isscalar(obj.ALTITUDES), return; end
+
+ % Prepare data for interpolation
+ data = [obj.magnitude; obj.azimuth; obj.elevation];
+ gridVec = obj.ALTITUDES;
+
+ % Create gridded interpolant
+ obj.dataInerpolant = griddedInterpolant(gridVec, data', 'linear', 'nearest');
+ end
end
methods(Access = private)
+ function ready = checkProperties(obj)
+ % Check if STATIC, DYNAMIC, GEOMETRY, and STATE are non-empty
+
+ ready = ...
+ length(obj.magnitude) == length(obj.ALTITUDES) && ...
+ length(obj.azimuth) == length(obj.ALTITUDES) && ...
+ length(obj.elevation) == length(obj.ALTITUDES);
+ end
+
function vec = updateDistribution(obj, dist, parameters)
s = length(obj.ALTITUDES);
vec = [];
diff --git a/functions/odeFunctions/ballistic.m b/functions/odeFunctions/ballistic.m
index 0e16abd4f74355055c66f1839180c1d248e7e8fb..d08b3069d7274836e0f686c19963919facaec233 100644
--- a/functions/odeFunctions/ballistic.m
+++ b/functions/odeFunctions/ballistic.m
@@ -96,11 +96,13 @@ if theta < tb
m = interpLinear(rocket.motor.time, rocket.mass, theta);
T = interpLinear(rocket.motor.time, rocket.motor.thrust, theta);
Pe = interpLinear(rocket.motor.time, rocket.motor.pe, theta);
+ xcg = interpLinear(rocket.motor.time, rocket.xcg, theta);
T = T + rocket.motor.ae*(Pe - P);
I = interpLinear(rocket.motor.time, rocket.inertia, theta);
Idot = interpLinear(rocket.motor.time, rocket.inertiaDot, theta);
else % for theta >= tb the flight condition is the empty one (no interpolation needed)
+ xcg = rocket.xcg(end);
m = rocket.cutoffMass;
T = 0;
@@ -143,53 +145,20 @@ betaOut = beta;
%% INTERPOLATE AERODYNAMIC COEFFICIENTS:
-if abs(alpha)>25*pi/180 || abs(beta)>25*pi/180
- coeffsValues = interpN( rocket.coefficientsHighAOA.total,...
- {rocket.coefficientsHighAOA.state.alphas, rocket.coefficientsHighAOA.state.machs, ...
- rocket.coefficientsHighAOA.state.betas, rocket.coefficientsHighAOA.state.altitudes}, ...
- [alpha, mach, beta, absoluteAltitude]);
- angle0 = [alpha beta];
+if abs(alpha) > rocket.coefficients.state.alphas(end)*pi/180 || ...
+ abs(beta) > rocket.coefficients.state.betas(end)*pi/180
+ coeffsValues = rocket.coefficientsHighAOA.get(alpha, mach, beta, absoluteAltitude, extension, xcg);
else
- %[coeffsValues, angle0] = rocket.interpCoeffs(theta, alpha, mach, beta, absoluteAltitude, opening);
- [coeffsValues, angle0] = interpCoeffs(rocket.coefficients, theta, rocket.motor.cutoffTime, ...
- alpha, mach, beta, absoluteAltitude, extension);
+ coeffsValues = rocket.coefficients.get(alpha, mach, beta, absoluteAltitude, extension, xcg);
end
% Retrieve Coefficients
-CA = coeffsValues(1); CYB = coeffsValues(2); CY0 = coeffsValues(3);
-CNA = coeffsValues(4); CN0 = coeffsValues(5); Cl = coeffsValues(6);
-Clp = coeffsValues(7); Cma = coeffsValues(8); Cm0 = coeffsValues(9);
-Cmad = coeffsValues(10); Cmq = coeffsValues(11); Cnb = coeffsValues(12);
-Cn0 = coeffsValues(13); Cnr = coeffsValues(14); Cnp = coeffsValues(15);
-
-% Clb = coeffsValues(16);
-% XCP_value = coeffsValues(16);
-
-% compute CN,CY,Cm,Cn (linearized with respect to alpha and beta):
-alpha0 = angle0(1); beta0 = angle0(2);
-
-CN = (CN0 + CNA*(alpha - alpha0));
-CY = (CY0 + CYB*(beta - beta0));
-Cm = (Cm0 + Cma*(alpha - alpha0));
-Cn = (Cn0 + Cnb*(beta - beta0));
-
-% XCPlon = Cm/CN;
-if abs(alpha) <= pi/180
- XCPlon = Cma/CNA;
-else
- XCPlon = Cm/CN;
-end
-
-% XCPlat = Cn/CY;
-if abs(beta) <= pi/180
- XCPlat = Cnb/CYB;
-else
- XCPlat = Cn/CY;
-end
+CA = coeffsValues(1); CY = coeffsValues(2); CN = coeffsValues(3);
+Cl = coeffsValues(4); Cm = coeffsValues(5); Cn = coeffsValues(6);
+Clp = coeffsValues(7); Cmad = coeffsValues(8); Cmq = coeffsValues(9);
+Cnr = coeffsValues(10); Cnp = coeffsValues(11);
-% if Cn == 0 && CY == 0
-% XCPlat = -5;
-% end
+XCPtot = NaN;
%% RAMP / FREE FLIGHT
if altitude < environment.effectiveRampAltitude % No torque on the launchpad
@@ -209,14 +178,10 @@ if altitude < environment.effectiveRampAltitude % No
betaOut = NaN;
fY = 0;
fZ = 0;
- XCPlon = NaN;
- XCPlat = NaN;
if T < Fg % No velocity untill T = Fg
du = 0;
end
-
- XCPtot = NaN;
else
%% FORCES
% first computed in the body-frame reference system
@@ -255,8 +220,6 @@ else
CMaTot = cos(phi)*Cm - sin(phi)*Cn;
if CFaTot ~= 0
XCPtot = CMaTot/CFaTot;
- else
- XCPtot = XCPlon;
end
dAngle = 0;
@@ -331,19 +294,12 @@ if nargout == 2 || ~isempty(wrapper)
parout.accelerometer.body_acc = ([-fX+T, fY, -fZ]')/m;
parout.coeff.CA = CA;
- parout.coeff.CYB = CYB;
- parout.coeff.CNA = CNA;
parout.coeff.Cl = Cl;
parout.coeff.Clp = Clp;
- %parout.coeff.Clb = Clb;
- parout.coeff.Cma = Cma;
parout.coeff.Cmad = Cmad;
parout.coeff.Cmq = Cmq;
- parout.coeff.Cnb = Cnb;
parout.coeff.Cnr = Cnr;
parout.coeff.Cnp = Cnp;
- parout.coeff.XCPlon = XCPlon;
- parout.coeff.XCPlat = XCPlat;
parout.coeff.XCPtot = XCPtot;
parout.uncertanty = [];
diff --git a/missions/2021_Lynx_Portugal_October/config/rocketConfig.m b/missions/2021_Lynx_Portugal_October/config/rocketConfig.m
index 4df34a1b48f4d03c4a6cdcb791b8c8c5985a17ec..160c5b09b850ef81406e13cf89dfcda9005c2e9c 100644
--- a/missions/2021_Lynx_Portugal_October/config/rocketConfig.m
+++ b/missions/2021_Lynx_Portugal_October/config/rocketConfig.m
@@ -16,6 +16,11 @@ rocket.inertiaNoMotor = [0.0786; 12.972; 12.972]; % [kg*m^2] OVERRIDE iner
rocket.xCgNoMotor = 1.6025; % [m] OVERRIDE xCg without motor
rocket.lengthCenterNoMot = 1.7640; % [m] OVERRIDE Center length - no nose, no motor
+% If dynamic derivatives are loaded, coefficient will depend on rocket xcg
+% When false, coefficients are saved with current motor's name
+% When true, coefficients are saved as 'generic'
+rocket.dynamicDerivatives = false; % [-] True if dynamic derivatives will be loaded
+
%% PLD - Includes Parafoil + Nose
parafoil = Parafoil();
diff --git a/missions/2021_Lynx_Roccaraso_September/config/rocketConfig.m b/missions/2021_Lynx_Roccaraso_September/config/rocketConfig.m
index 83f64760123f82fd1703c408e2543fa3d76f8e12..d0dc3df55356e3aebc59d51214a30794f8668dc1 100644
--- a/missions/2021_Lynx_Roccaraso_September/config/rocketConfig.m
+++ b/missions/2021_Lynx_Roccaraso_September/config/rocketConfig.m
@@ -16,6 +16,11 @@ rocket.inertiaNoMotor = [0.06; 7.511; 7.512]; % [kg*m^2] OVERRIDE inertia
rocket.xCgNoMotor = 1.1986; % [m] OVERRIDE xCg without motor
rocket.lengthCenterNoMot = 1.7840; % [m] OVERRIDE Center length - no nose, no motor
+% If dynamic derivatives are loaded, coefficient will depend on rocket xcg
+% When false, coefficients are saved with current motor's name
+% When true, coefficients are saved as 'generic'
+rocket.dynamicDerivatives = false; % [-] True if dynamic derivatives will be loaded
+
%% PLD - Includes Parafoil + Nose
parafoil = Parafoil();
diff --git a/missions/2022_Pyxis_Portugal_October/config/rocketConfig.m b/missions/2022_Pyxis_Portugal_October/config/rocketConfig.m
index 8cdcf2b5942b6f6ef50f8c2a627b7111452abc46..2f949bfb46c9b09dd02fea6a1c87253e9c6c5b20 100644
--- a/missions/2022_Pyxis_Portugal_October/config/rocketConfig.m
+++ b/missions/2022_Pyxis_Portugal_October/config/rocketConfig.m
@@ -16,6 +16,11 @@ rocket.inertiaNoMotor = [0.06303; 9.62497; 9.62524]; % [kg*m^2] OVERRIDE i
rocket.xCgNoMotor = 1.2239; % [m] OVERRIDE xCg without motor
rocket.lengthCenterNoMot = 1.4470; % [m] OVERRIDE Center length - no nose, no motor
+% If dynamic derivatives are loaded, coefficient will depend on rocket xcg
+% When false, coefficients are saved with current motor's name
+% When true, coefficients are saved as 'generic'
+rocket.dynamicDerivatives = false; % [-] True if dynamic derivatives will be loaded
+
%% PLD - Includes Parafoil + Nose
parafoil = Parafoil();
diff --git a/missions/2022_Pyxis_Roccaraso_September/config/rocketConfig.m b/missions/2022_Pyxis_Roccaraso_September/config/rocketConfig.m
index bec3d20b753eb2ec6b956c9924e12353c7cd6e2b..ee3a3c71bd73ab263db92f3e929db488a6a5735c 100644
--- a/missions/2022_Pyxis_Roccaraso_September/config/rocketConfig.m
+++ b/missions/2022_Pyxis_Roccaraso_September/config/rocketConfig.m
@@ -18,6 +18,11 @@ rocket.xCgNoMotor = 1.2957; % [m]
% settings.Lcenter - motors(iMotor).L/1000
rocket.lengthCenterNoMot = 1.61; % [m] OVERRIDE Center length - no nose, no motor
+% If dynamic derivatives are loaded, coefficient will depend on rocket xcg
+% When false, coefficients are saved with current motor's name
+% When true, coefficients are saved as 'generic'
+rocket.dynamicDerivatives = false; % [-] True if dynamic derivatives will be loaded
+
%% PLD - Includes Parafoil + Nose
parafoil = Parafoil();
diff --git a/missions/2023_Gemini_Portugal_October/config/rocketConfig.m b/missions/2023_Gemini_Portugal_October/config/rocketConfig.m
index 610966af09dd387c856d5e559e8b6bd6020f4e8e..401c415be5e782af00b4318e62db4d13ea6ef5ca 100644
--- a/missions/2023_Gemini_Portugal_October/config/rocketConfig.m
+++ b/missions/2023_Gemini_Portugal_October/config/rocketConfig.m
@@ -15,6 +15,12 @@ rocket.inertiaNoMotor = [0.06535397; 17.21019828; 17.21056483]; % [kg*m^2]
rocket.xCgNoMotor = 1.254; % [m] OVERRIDE xCg without motor
rocket.lengthCenterNoMot = 1.517; % [m] OVERRIDE Center length - no nose, no motor
+% If dynamic derivatives are loaded, coefficient will depend on rocket xcg
+% When false, coefficients are saved with current motor's name
+% When true, coefficients are saved as 'generic'
+rocket.dynamicDerivatives = false; % [-] True if dynamic derivatives will be loaded
+
+
%% PLD - Includes Parafoil + Nose
parafoil = Parafoil();
diff --git a/missions/2023_Gemini_Roccaraso_September/config/rocketConfig.m b/missions/2023_Gemini_Roccaraso_September/config/rocketConfig.m
index 600065acce5a8ab60dc9e917019745567596d1d1..fc2715bc0dd7d61dd740e20b3138c8552440dcf1 100644
--- a/missions/2023_Gemini_Roccaraso_September/config/rocketConfig.m
+++ b/missions/2023_Gemini_Roccaraso_September/config/rocketConfig.m
@@ -15,6 +15,11 @@ rocket.inertiaNoMotor = [0.06535397; 12.07664659; 12.07701314]; % [kg*m^2]
rocket.xCgNoMotor = 1.149; % [m] OVERRIDE xCg without motor
rocket.lengthCenterNoMot = 1.517; % [m] OVERRIDE Center length - no nose, no motor
+% If dynamic derivatives are loaded, coefficient will depend on rocket xcg
+% When false, coefficients are saved with current motor's name
+% When true, coefficients are saved as 'generic'
+rocket.dynamicDerivatives = false; % [-] True if dynamic derivatives will be loaded
+
%% PLD - Includes Parafoil + Nose
parafoil = Parafoil();
diff --git a/missions/2024_Lyra_Portugal_October/config/rocketConfig.m b/missions/2024_Lyra_Portugal_October/config/rocketConfig.m
index 2369c08ce6c490b4ff849c682698f0d112a784d3..f87640c176ca52f0ab3274f1b32602462a1489ff 100644
--- a/missions/2024_Lyra_Portugal_October/config/rocketConfig.m
+++ b/missions/2024_Lyra_Portugal_October/config/rocketConfig.m
@@ -9,6 +9,11 @@ rocket.inertiaNoMotor = []; % [kg*m^
rocket.xCgNoMotor = []; % [m] OVERRIDE xCg without motor
rocket.lengthCenterNoMot = []; % [m] OVERRIDE Center length - no nose, no motor
+% If dynamic derivatives are loaded, coefficient will depend on rocket xcg
+% When false, coefficients are saved with current motor's name
+% When true, coefficients are saved as 'generic'
+rocket.dynamicDerivatives = false; % [-] True if dynamic derivatives will be loaded
+
%% PLD - Includes Parafoil + Nose
parafoil = Parafoil();
diff --git a/missions/2024_Lyra_Roccaraso_September/config/rocketConfig.m b/missions/2024_Lyra_Roccaraso_September/config/rocketConfig.m
index b2ca5cb545dec731f15e540e33c3f05711f8e027..2939db0ce6550575817cdd355d8b2f6ca2e68943 100644
--- a/missions/2024_Lyra_Roccaraso_September/config/rocketConfig.m
+++ b/missions/2024_Lyra_Roccaraso_September/config/rocketConfig.m
@@ -15,6 +15,11 @@ rocket.lengthCenterNoMot = []; % [m]
% rocket.xCgNoMotor = 1.28; % [m] OVERRIDE xCg without motor
% rocket.lengthCenterNoMot = 1.778; % [m] OVERRIDE Center length - no nose, no motor
+% If dynamic derivatives are loaded, coefficient will depend on rocket xcg
+% When false, coefficients are saved with current motor's name
+% When true, coefficients are saved as 'generic'
+rocket.dynamicDerivatives = false; % [-] True if dynamic derivatives will be loaded
+
%% PLD - Includes Parafoil + Nose
parafoil = Parafoil();
diff --git a/missions/2025_Orion_Portugal_October/config/rocketConfig.m b/missions/2025_Orion_Portugal_October/config/rocketConfig.m
index c8791602b6261e955857793796d59d896bd004bc..6a13ec2512f1ba80b938af94064c3038be076bfd 100644
--- a/missions/2025_Orion_Portugal_October/config/rocketConfig.m
+++ b/missions/2025_Orion_Portugal_October/config/rocketConfig.m
@@ -3,12 +3,17 @@
%% ROCKET - OVERRIDES BAYS CONFIG
rocket = Rocket();
-rocket.diameter = 0.15; % [m] Rocket diameter
+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
+% If dynamic derivatives are loaded, coefficient will depend on rocket xcg
+% When false, coefficients are saved with current motor's name
+% When true, coefficients are saved as 'generic'
+rocket.dynamicDerivatives = false; % [-] True if dynamic derivatives will be loaded
+
%% PRF - Includes Parafoil + Nose
parafoil = Parafoil();
@@ -69,7 +74,7 @@ airbrakes.servoTau = 0.0374588;
%% MOTOR
motor = Motor();
-motor.name = 'HRE_ARM_OPT_3_Update';
+motor.name = 'HRE_ARM_EuRoC_2024';
motor.cutoffTime = []; % [s] OVERRIDE Cutoff time
motor.ignitionTransient = 0.3; % [s] Ignition transient
diff --git a/missions/2025_Orion_Roccaraso_September/config/rocketConfig.m b/missions/2025_Orion_Roccaraso_September/config/rocketConfig.m
index dfc372f3e3e1f47af69fd4b9e1dc3d80f730052a..c4e1ffcee38a736e09fe06543010f7699fe3a553 100644
--- a/missions/2025_Orion_Roccaraso_September/config/rocketConfig.m
+++ b/missions/2025_Orion_Roccaraso_September/config/rocketConfig.m
@@ -15,6 +15,11 @@ rocket.lengthCenterNoMot = []; % [m]
% rocket.xCgNoMotor = 1.28; % [m] OVERRIDE xCg without motor
% rocket.lengthCenterNoMot = 1.778; % [m] OVERRIDE Center length - no nose, no motor
+% If dynamic derivatives are loaded, coefficient will depend on rocket xcg
+% When false, coefficients are saved with current motor's name
+% When true, coefficients are saved as 'generic'
+rocket.dynamicDerivatives = false; % [-] True if dynamic derivatives will be loaded
+
%% PLD - Includes Parafoil + Nose
parafoil = Parafoil();