diff options
Diffstat (limited to '')
| -rw-r--r-- | midterm.m | 77 | ||||
| -rw-r--r-- | uav.m | 107 | ||||
| -rw-r--r-- | uav_model.m | 54 | ||||
| -rw-r--r-- | uav_params.m | 17 |
4 files changed, 154 insertions, 101 deletions
diff --git a/midterm.m b/midterm.m deleted file mode 100644 index eca35bc..0000000 --- a/midterm.m +++ /dev/null @@ -1,77 +0,0 @@ -% Copyright (c) 2024, Naoki Sean Pross, ETH Zürich - -%% ------------------------------------------------------------------------ -% Clear environment and generate parameters - -clear; clc; close all; s = tf('s'); -params = uav_params(); - -%% ------------------------------------------------------------------------ -% Create nominal plant - -% Generate nominal model -model = uav_model(params); - -%% ------------------------------------------------------------------------ -% Define performance requirements - -alpha_max = params.actuators.ServoAbsMaxAngleDeg * pi / 180; -W_Palpha = tf(alpha_max,1); - -W_Pomega = tf(1,1); -W_Pxy = tf(1,1); -W_Pz = tf(1,1); - -figure(1); hold on; -bodemag(W_Palpha); -bodemag(W_Pomega); -bodemag(W_Pxy); -bodemag(W_Pz); - -grid on; -legend('$W_{P,\alpha}$', '$W_{P,\omega}$', ... - '$W_{P,xy}$', '$W_{P,z}$', ... - 'interpreter', 'latex', 'fontSize', 8); -title('Performance requirements'); - - -W_PP = blkdiag(W_Pxy * eye(2), W_Pz); - -perf = struct(... - 'FlapAngle', W_Palpha * eye(4), ... - 'Thrust', W_Pomega, ... - 'PositionAccuracy', W_PP); - -%% ------------------------------------------------------------------------ -% Define stability requirements - -% Mechanically, flaps are constrained to a max of 20~25 degrees, -% we assume a precision of -% also, flaps tend to get less precise at higher frequencies -alpha_max = 2 * pi * 20; -W_malpha = alpha_max / (s + 2) * eye(4); - -W_momega = tf(1,1); -W_mTheta = tf(1,1) * eye(3); -W_mOmega = tf(1,1) * eye(3); - -uncert = struct(... - 'FlapAngle', W_malpha, ... - 'Thrust', W_momega, ... - 'EulerAnglesApprox', W_mTheta, ... - 'AngularRateApprox', W_mOmega); - -%% ------------------------------------------------------------------------ -% Create uncertain system - -% Load simulink model with uncertainties -usys = linmod('uav_model_uncertain'); -G = ss(usys.a, usys.b, usys.c, usys.d); - -%% ------------------------------------------------------------------------ -% Perform H-infinity design - -%% ------------------------------------------------------------------------ -% Perform mu-Analysis & DK iteration - -% vim: ts=2 sw=2 et: @@ -0,0 +1,107 @@ +% Copyright (c) 2024, Naoki Sean Pross, ETH Zürich +% +% Controller design for a ducted fan VTOL micro-UAV. + +% ------------------------------------------------------------------------ +% Clear environment and generate parameters + +clear; clc; close all; s = tf('s'); +params = uav_params(); + +% ------------------------------------------------------------------------ +% Define performance requirements + +% Mechanically, flaps are constrained to a max of 20~25 degrees, +% and they have a maximal angular speed +alpha_max = params.actuators.ServoAbsMaxAngle; +alpha_dot_max = params.actuators.ServoNominalAngularVelocity; + +W_Palpha = (s + 100 * alpha_dot_max) / (s + alpha_dot_max); +W_Palpha = alpha_max * W_Palpha / dcgain(W_Palpha); % adjust gain + +% Mechanically we have a maximal angular velocity for the propeller in the +% thruster, also there are a lot of unmodelled dynamics in the thruster +omega_max = params.actuators.TurbineMaxSpeed; +W_Pomega = (s + 50 * omega_max) / (s + omega_max); + +% We want a nice and smooth movements +v_xy_max = params.performance.MaxHorizontalSpeed; +v_z_max = params.performance.MaxVerticalSpeed; + +W_Pxy = 1 / (s + 1 / v_xy_max); +W_Pz = 1 / (s + 1 / v_z_max); + +% Bode plots of performance requirements +figure; hold on; + +bodemag(1/W_Palpha); +bodemag(1/W_Pomega); +bodemag(1/W_Pxy); +bodemag(1/W_Pz); + +grid on; +legend('$W_{P,\alpha}$', '$W_{P,\omega}$', ... + '$W_{P,xy}$', '$W_{P,z}$', ... + 'interpreter', 'latex', 'fontSize', 8); +title('Performance requirements'); + +% Step response of position requirements +figure; hold on; +step(W_Pxy); step(W_Pz); +grid on; +legend('$W_{P,xy}$', '$W_{P,z}$', 'interpreter', 'latex', 'fontSize', 8); +title('Step responses of position performance requirements'); + +% Construct performance for position vector by combining xy and z +W_PP = blkdiag(W_Pxy * eye(2), W_Pz); + +perf = struct(... + 'FlapAngle', W_Palpha * eye(4), ... + 'Thrust', W_Pomega, ... + 'PositionAccuracy', W_PP); + +% ------------------------------------------------------------------------ +% Define stability requirements + +W_malpha = tf(1,1); +W_momega = tf(1,1); +W_mTheta = tf(1,1); +W_mOmega = tf(1,1); + +figure; hold on; + +bodemag(W_malpha); +bodemag(W_momega); +bodemag(W_mTheta); +bodemag(W_mOmega); + +grid on; +legend('$W_{m,\alpha}$', '$W_{m,\omega}$', ... + '$W_{m,\Theta}$', '$W_{m,\Omega}$', ... + 'interpreter', 'latex', 'fontSize', 8); +title('Uncertainties') + +uncert = struct(... + 'FlapAngle', W_malpha * eye(4), ... + 'Thrust', W_momega, ... + 'EulerAnglesApprox', W_mTheta * eye(3), ... + 'AngularRateApprox', W_mOmega * eye(3)); + +% ------------------------------------------------------------------------ +% Create UAV model + +model = uav_model(params, perf, uncert); + +% ------------------------------------------------------------------------ +% Perform H-infinity design + +Gnom = model.linear.StateSpace; +G = model.uncertain.StateSpace; + +% ------------------------------------------------------------------------ +% Verify performance satisfaction + +% ------------------------------------------------------------------------ +% Perform mu-Analysis & DK iteration + +% vim: ts=2 sw=2 et: diff --git a/uav_model.m b/uav_model.m index 5650946..ce7cddb 100644 --- a/uav_model.m +++ b/uav_model.m @@ -2,7 +2,9 @@ % % Compute model for UAV for given set of parameters. -function [model] = uav_model(params) +function [model] = uav_model(params, perf, uncert) + +model = struct(); % ------------------------------------------------------------------------ % Symbolic variables @@ -121,6 +123,17 @@ f = [ inv(J) * (tau - cross(Omega, J * Omega)); % rotational dynamics ]; +% Save function to compute the rotation matrix +model.FrameRot = @(pitch, roll, yaw) ... + subs(R, [phi, theta, psi], [pitch, roll, yaw]); + +% Save equations of non-linear model (algebraic) +model.nonlinear = struct(... + 'State', xi, ... + 'Inputs', u, ... + 'Dynamics', f ... +); + % ------------------------------------------------------------------------ % Linearization at equilibrium @@ -187,6 +200,14 @@ sys = ss(A, B, C, D); % T = params.actuators.MeasurementDelay; % sys = ss(A, B, C, D, 'OutputDelay', T); +% Save linearized dynamics (numerical) +model.linear = struct(... + 'Nx', nx, 'Nu', nu, 'Ny', ny, ... % number of states, inputs, and outputs + 'State', xi, 'Inputs', u, ... % state and input variables + 'StateEq', xi_eq, 'InputEq', u_eq, ... % where the system was linearized + 'StateSpace', sys ... % state space object +); + % ------------------------------------------------------------------------ % Check properties of linearized model eigvals = eig(A); @@ -242,27 +263,24 @@ if rank(Wo) < nx end % ------------------------------------------------------------------------ -% Save model +% Add uncertainties using SIMULINK model -model = struct(); +% Load simulink model with uncertainties and pass in parameters +h = load_system('uav_model_uncertain'); +hws = get_param('uav_model_uncertain', 'modelworkspace'); -% Function to compute the rotation matrix -model.FrameRot = @(pitch, roll, yaw) ... - subs(R, [phi, theta, psi], [pitch, roll, yaw]); +hws.assignin('model', model); +hws.assignin('perf', perf); +hws.assignin('uncert', uncert); -% Equations of non-linear model (algebraic) -model.nonlinear = struct(... - 'State', xi, ... - 'Inputs', u, ... - 'Dynamics', f ... -); +% Get uncertain model +ulmod = linmod('uav_model_uncertain'); +usys = ss(ulmod.a, ulmod.b, ulmod.c, ulmod.d); -% Linearized dynamics (numerical) -model.linear = struct(... - 'Nx', nx, 'Nu', nu, 'Ny', ny, ... % number of states, inputs, and outputs - 'State', xi, 'Inputs', u, ... % state and input variables - 'StateEq', xi_eq, 'InputEq', u_eq, ... % where the system was linearized - 'StateSpace', sys ... % state space object +% Save uncertain model +model.uncertain = struct(... + 'Simulink', ulmod, ... + 'StateSpace', usys ... ); end diff --git a/uav_params.m b/uav_params.m index 3ceda9e..0e82148 100644 --- a/uav_params.m +++ b/uav_params.m @@ -1,5 +1,5 @@ % Copyright (C) 2024, Naoki Sean Pross, ETH Zürich -% +% % Retrieve / compute parameters for UAV. function [params] = uav_params() @@ -34,16 +34,20 @@ params.mechanical = struct(... ); % ------------------------------------------------------------------------ -% Actuator limits +% Actuator limits and measurements % Cheap servos usually give a "speed" in seconds / 60 degrees without load servo_speed = 0.19; % seconds per 60 deg servo_angular_velocity = (pi / 3) / servo_speed; params.actuators = struct(... - 'TurbineMaxSpeed', 620.7, ... % In Hz - 'ServoAbsMaxAngleDeg', 25, ... % in Degrees - 'ServoNominalAngularVelocity', servo_angular_velocity, ... + 'TurbineMaxSpeed', 620.7, ... % in rad / s + 'ServoAbsMaxAngle', 25 * pi / 180, ... % in radians + 'ServoNominalAngularVelocity', servo_angular_velocity ... +); + +params.measurements = struct(... + 'SensorFusionBandwidth', 1e3, ... 'MeasurementDelay', 8e-3 ... % delay caused by sensor fusion algorithm ); @@ -87,7 +91,8 @@ params.linearization = struct(... % Performance requirements params.performance = struct(... - 'MaxHorizontalSpeed', 1, ... + 'MaxHorizontalSpeed', 1e-2, ... % in m / s + 'MaxVerticalSpeed', 5e-2 ... % in m / s ); end |