Hello,

I have been trying to plot a shaded area (right y-axis) behind two lines (left y-axis), as shown in the code below. However, the shaded area always appears last, covering up the two lines. I’ve done this kind of graph before but have never had this issue. Best I can tell, it is because the right y-axis is plotted last. Is there a way to make the right y-axis plotted first? I can’t simply switch which data is on the axis, unfortunately: they need to be in this order. Thanks for any help!

clear; clc; close all;
Data = xlsread("FigureOfMeritResults.xlsx");
% Extract data
Date = Data(469:1908,1);
FoM = Data(469:1908,3);
GHI = Data(469:1908,4);
% Calculate the running average over 5 data points
FoM_avg = movmean(FoM, 5);
GHI_avg = movmean(GHI, 5);
dFoM = zeros(length(FoM),1) + mean(FoM);
ticks = {’12:00AM’,’4:00AM’,’8:00AM’,’12:00PM’,’4:00PM’,’8:00PM’,’12:00AM’};
fz = 15;
%%
fig = figure;
set(gcf,’Color’,’w’,’Units’,’inches’)
set(gcf,’Position’,[1,1,5,6])
GHI_color = [0.8 0.8 1];
yyaxis left;
p1 = scatter(Date, FoM, ‘Marker’, ‘.’, ‘SizeData’, 15, ‘MarkerFaceColor’, "#0072BD");
hold on;
p2 = scatter(Date, dFoM, ‘Marker’, ‘_’, ‘SizeData’, 15, ‘MarkerFaceColor’, ‘black’);
hold on;
ax = gca;
ax.YColor = ‘k’;
yyaxis right;
xData = [Date; flipud(Date)];
yData = [zeros(size(GHI)); flipud(GHI)];
fillHandle = fill(xData, yData, GHI_color,’EdgeColor’,’none’);
hold on;
ax = gca;
ax.YColor = ‘k’;
xlabel(‘Time of Day (hrs)’, ‘FontSize’, fz);
numTicks = length(ticks);
tickPositions = linspace(min(Date), max(Date), numTicks);
xticks(tickPositions);
xticklabels(ticks);

set(gca, ‘FontSize’, fz);
ax = gca;
box on;
set(ax,’BoxStyle’,’full’,’LineWidth’,2,’XGrid’,’off’,’XMinorTick’,’off’,’YGrid’,’off’,…
‘YMinorTick’,’on’);Hello,

I have been trying to plot a shaded area (right y-axis) behind two lines (left y-axis), as shown in the code below. However, the shaded area always appears last, covering up the two lines. I’ve done this kind of graph before but have never had this issue. Best I can tell, it is because the right y-axis is plotted last. Is there a way to make the right y-axis plotted first? I can’t simply switch which data is on the axis, unfortunately: they need to be in this order. Thanks for any help!

clear; clc; close all;
Data = xlsread("FigureOfMeritResults.xlsx");
% Extract data
Date = Data(469:1908,1);
FoM = Data(469:1908,3);
GHI = Data(469:1908,4);
% Calculate the running average over 5 data points
FoM_avg = movmean(FoM, 5);
GHI_avg = movmean(GHI, 5);
dFoM = zeros(length(FoM),1) + mean(FoM);
ticks = {’12:00AM’,’4:00AM’,’8:00AM’,’12:00PM’,’4:00PM’,’8:00PM’,’12:00AM’};
fz = 15;
%%
fig = figure;
set(gcf,’Color’,’w’,’Units’,’inches’)
set(gcf,’Position’,[1,1,5,6])
GHI_color = [0.8 0.8 1];
yyaxis left;
p1 = scatter(Date, FoM, ‘Marker’, ‘.’, ‘SizeData’, 15, ‘MarkerFaceColor’, "#0072BD");
hold on;
p2 = scatter(Date, dFoM, ‘Marker’, ‘_’, ‘SizeData’, 15, ‘MarkerFaceColor’, ‘black’);
hold on;
ax = gca;
ax.YColor = ‘k’;
yyaxis right;
xData = [Date; flipud(Date)];
yData = [zeros(size(GHI)); flipud(GHI)];
fillHandle = fill(xData, yData, GHI_color,’EdgeColor’,’none’);
hold on;
ax = gca;
ax.YColor = ‘k’;
xlabel(‘Time of Day (hrs)’, ‘FontSize’, fz);
numTicks = length(ticks);
tickPositions = linspace(min(Date), max(Date), numTicks);
xticks(tickPositions);
xticklabels(ticks);

set(gca, ‘FontSize’, fz);
ax = gca;
box on;
set(ax,’BoxStyle’,’full’,’LineWidth’,2,’XGrid’,’off’,’XMinorTick’,’off’,’YGrid’,’off’,…
‘YMinorTick’,’on’); Hello,

I have been trying to plot a shaded area (right y-axis) behind two lines (left y-axis), as shown in the code below. However, the shaded area always appears last, covering up the two lines. I’ve done this kind of graph before but have never had this issue. Best I can tell, it is because the right y-axis is plotted last. Is there a way to make the right y-axis plotted first? I can’t simply switch which data is on the axis, unfortunately: they need to be in this order. Thanks for any help!

clear; clc; close all;
Data = xlsread("FigureOfMeritResults.xlsx");
% Extract data
Date = Data(469:1908,1);
FoM = Data(469:1908,3);
GHI = Data(469:1908,4);
% Calculate the running average over 5 data points
FoM_avg = movmean(FoM, 5);
GHI_avg = movmean(GHI, 5);
dFoM = zeros(length(FoM),1) + mean(FoM);
ticks = {’12:00AM’,’4:00AM’,’8:00AM’,’12:00PM’,’4:00PM’,’8:00PM’,’12:00AM’};
fz = 15;
%%
fig = figure;
set(gcf,’Color’,’w’,’Units’,’inches’)
set(gcf,’Position’,[1,1,5,6])
GHI_color = [0.8 0.8 1];
yyaxis left;
p1 = scatter(Date, FoM, ‘Marker’, ‘.’, ‘SizeData’, 15, ‘MarkerFaceColor’, "#0072BD");
hold on;
p2 = scatter(Date, dFoM, ‘Marker’, ‘_’, ‘SizeData’, 15, ‘MarkerFaceColor’, ‘black’);
hold on;
ax = gca;
ax.YColor = ‘k’;
yyaxis right;
xData = [Date; flipud(Date)];
yData = [zeros(size(GHI)); flipud(GHI)];
fillHandle = fill(xData, yData, GHI_color,’EdgeColor’,’none’);
hold on;
ax = gca;
ax.YColor = ‘k’;
xlabel(‘Time of Day (hrs)’, ‘FontSize’, fz);
numTicks = length(ticks);
tickPositions = linspace(min(Date), max(Date), numTicks);
xticks(tickPositions);
xticklabels(ticks);

set(gca, ‘FontSize’, fz);
ax = gca;
box on;
set(ax,’BoxStyle’,’full’,’LineWidth’,2,’XGrid’,’off’,’XMinorTick’,’off’,’YGrid’,’off’,…
‘YMinorTick’,’on’); plot, area MATLAB Answers — New Questions

​

So I’ve been trying to simulate a parachute descent (very basic model, almost a mass body with a coefficient of drag), from a height. While simulating only in the axial direction(z axis), the results coincide with kinematics equations. However, when I give a non-zero initial condition, the outputs go crazy (definitely not correct) with periodic solutions to related terms. I seem to have checked my equations, they seem to be right. Is there anything with ‘odeset’ I can work this out around.
Zero non-axial initial condition:
x0 = [0; 0; -100; 0; 0; 1; 0; 0; 0; 0; 0; 0];

Non-zero IC:
x0 = [0; 0; -100; 0; 1; 1; 0; 0; 0; 0; 0; 0];

0

this is the code i’ve used for these plots. Please feel free to ask any clarifications
%% 6DOF fucntion definition
function [dxdt, aoa_series] = six_DOF_dynamics(t,x)

M_para = 5; %mass of the parachute in Kgs
g = 9.81; %gravitational acceleration in m/s^2
I_x = 1; I_y = 1; I_z = 3; %Inertia matrix diagonal principal of the parachute in kg-m^2
CD_para = 0.9; %coefficient of drag of parachute
CL_para = 0; %coefficient of lift of parachute
rho = 1; %density of the atmosphere in Kg/m^3
x_com = 0; y_com = 0; z_com = -5; %position of COM of the paarchute from the integrated system’s COM(body axis origin) in m
A = 10; %parachute area in m^2

%state variables defining
x_pos = x(1); y_pos = x(2); z_pos = x(3); %postion variables
u = x(4); v = x(5); w = x(6); %velocity variables
phi = x(7); theta = x(8); psi = x(9); %attitude/euler angles variables
p = x(10); q = x(11); r = x(12); %euler angular rate variables

%rate of change of postion -> velocity
dx_pos = u;
dy_pos = v;
dz_pos = w;

%Gravity moment of the parachute along x,y and z components
GravityMoment_para_x = M_para*g*cos(theta)*(y_com*cos(phi) – z_com*sin(phi));
GravityMoment_para_y = M_para*g*(z_com*sin(theta) – x_com*cos(theta)*cos(phi));
GravityMoment_para_z = M_para*g*(x_com*cos(theta)*sin(phi) + y_com*sin(theta));

V_total = sqrt(u^2 + v^2 + w^2); %net speed

persistent angle_of_attack %defining this variable to take it as a output outside ode45

alpha = acos(w/V_total); %angle of attack calculated in radians

angle_of_attack = [angle_of_attack; alpha]; %concatinating current iterated angle of attack in global variable

%Componetize CD and CL into tangential and normal force coefficients
CT = CD_para*cos(alpha) – CL_para*sin(alpha);
CN = CL_para*cos(alpha) + CD_para*sin(alpha);

% Aerodynamic force along x,y,z axes F = 0.5*rho*v^2*A
if (u == 0 & v == 0)
Aerodynamic_force_x = 0;
Aerodynamic_force_y = 0;
Aerodynamic_force_z = -0.5*rho*CT*V_total*V_total*A;
else
Aerodynamic_force_x = -0.5*rho*CN*V_total*V_total*A*(u/(u^2 + v^2)^0.5);
Aerodynamic_force_y = -0.5*rho*CN*V_total*V_total*A*(v/(u^2 + v^2)^0.5);
Aerodynamic_force_z = -0.5*rho*CT*V_total*V_total*A;
end

%Moment caused by aerodynamic force along x,y,x
Aerodynamic_moment_x = y_com*Aerodynamic_force_z – z_com*Aerodynamic_force_y;
Aerodynamic_moment_y = z_com*Aerodynamic_force_x – x_com*Aerodynamic_force_z;
Aerodynamic_moment_z = x_com*Aerodynamic_force_y – y_com*Aerodynamic_force_x;

%rate change of velocity definition
du = v*r – w*q + g*sin(theta) + Aerodynamic_force_x/M_para;
dv = -u*r + w*p + g*cos(theta)*sin(phi) + Aerodynamic_force_y/M_para;
dw = u*q – v*p + g*cos(theta)*cos(phi) + Aerodynamic_force_z/M_para;

%rate change of euler angles definition
dphi = p + (r*cos(phi) + q*sin(phi))*tan(theta);
dtheta = q*cos(phi) – r*sin(phi);
dpsi = (cos(theta)^-1)*(r*cos(phi) + q*sin(phi));

%rate change of angular rates definition
dp = (1/I_x)*(Aerodynamic_moment_x + GravityMoment_para_x);
dq = (1/I_y)*(Aerodynamic_moment_y + GravityMoment_para_y);
dr = (1/I_z)*(Aerodynamic_moment_z + GravityMoment_para_z);

dxdt = [dx_pos; dy_pos; dz_pos; du; dv; dw; dphi; dtheta; dpsi; dp; dq; dr];

%block to output angle of attack
if nargout>1
aoa_series = angle_of_attack;

end

end

tspan = [0 3];

x0 = [0; 0; -100; 0; 1; 1; 0; 0; 0; 0; 0; 0];

[t, x] = ode45(@six_DOF_dynamics, tspan, x0);

[~, aoa_series] = six_DOF_dynamics(t,x);

%adding alpha as a part of x

% Plot results
figure;
subplot(4,1,1);
plot(t, x(:,1:3));
title(‘Position’);
legend(‘x’, ‘y’, ‘z’);

subplot(4,1,2);
plot(t, x(:,4:6));
title(‘Velocity’);
legend(‘u’, ‘v’, ‘w’);

subplot(4,1,3);
plot(t, x(:,7:9));
title(‘Euler Angles’);
legend(‘phi’, ‘theta’, ‘psi’);

subplot(4,1,4);
plot(t, x(:,10:12));
title(‘Euler Rates’);
legend(‘p’, ‘q’, ‘r’);So I’ve been trying to simulate a parachute descent (very basic model, almost a mass body with a coefficient of drag), from a height. While simulating only in the axial direction(z axis), the results coincide with kinematics equations. However, when I give a non-zero initial condition, the outputs go crazy (definitely not correct) with periodic solutions to related terms. I seem to have checked my equations, they seem to be right. Is there anything with ‘odeset’ I can work this out around.
Zero non-axial initial condition:
x0 = [0; 0; -100; 0; 0; 1; 0; 0; 0; 0; 0; 0];

Non-zero IC:
x0 = [0; 0; -100; 0; 1; 1; 0; 0; 0; 0; 0; 0];

0

this is the code i’ve used for these plots. Please feel free to ask any clarifications
%% 6DOF fucntion definition
function [dxdt, aoa_series] = six_DOF_dynamics(t,x)

M_para = 5; %mass of the parachute in Kgs
g = 9.81; %gravitational acceleration in m/s^2
I_x = 1; I_y = 1; I_z = 3; %Inertia matrix diagonal principal of the parachute in kg-m^2
CD_para = 0.9; %coefficient of drag of parachute
CL_para = 0; %coefficient of lift of parachute
rho = 1; %density of the atmosphere in Kg/m^3
x_com = 0; y_com = 0; z_com = -5; %position of COM of the paarchute from the integrated system’s COM(body axis origin) in m
A = 10; %parachute area in m^2

%state variables defining
x_pos = x(1); y_pos = x(2); z_pos = x(3); %postion variables
u = x(4); v = x(5); w = x(6); %velocity variables
phi = x(7); theta = x(8); psi = x(9); %attitude/euler angles variables
p = x(10); q = x(11); r = x(12); %euler angular rate variables

%rate of change of postion -> velocity
dx_pos = u;
dy_pos = v;
dz_pos = w;

%Gravity moment of the parachute along x,y and z components
GravityMoment_para_x = M_para*g*cos(theta)*(y_com*cos(phi) – z_com*sin(phi));
GravityMoment_para_y = M_para*g*(z_com*sin(theta) – x_com*cos(theta)*cos(phi));
GravityMoment_para_z = M_para*g*(x_com*cos(theta)*sin(phi) + y_com*sin(theta));

V_total = sqrt(u^2 + v^2 + w^2); %net speed

persistent angle_of_attack %defining this variable to take it as a output outside ode45

alpha = acos(w/V_total); %angle of attack calculated in radians

angle_of_attack = [angle_of_attack; alpha]; %concatinating current iterated angle of attack in global variable

%Componetize CD and CL into tangential and normal force coefficients
CT = CD_para*cos(alpha) – CL_para*sin(alpha);
CN = CL_para*cos(alpha) + CD_para*sin(alpha);

% Aerodynamic force along x,y,z axes F = 0.5*rho*v^2*A
if (u == 0 & v == 0)
Aerodynamic_force_x = 0;
Aerodynamic_force_y = 0;
Aerodynamic_force_z = -0.5*rho*CT*V_total*V_total*A;
else
Aerodynamic_force_x = -0.5*rho*CN*V_total*V_total*A*(u/(u^2 + v^2)^0.5);
Aerodynamic_force_y = -0.5*rho*CN*V_total*V_total*A*(v/(u^2 + v^2)^0.5);
Aerodynamic_force_z = -0.5*rho*CT*V_total*V_total*A;
end

%Moment caused by aerodynamic force along x,y,x
Aerodynamic_moment_x = y_com*Aerodynamic_force_z – z_com*Aerodynamic_force_y;
Aerodynamic_moment_y = z_com*Aerodynamic_force_x – x_com*Aerodynamic_force_z;
Aerodynamic_moment_z = x_com*Aerodynamic_force_y – y_com*Aerodynamic_force_x;

%rate change of velocity definition
du = v*r – w*q + g*sin(theta) + Aerodynamic_force_x/M_para;
dv = -u*r + w*p + g*cos(theta)*sin(phi) + Aerodynamic_force_y/M_para;
dw = u*q – v*p + g*cos(theta)*cos(phi) + Aerodynamic_force_z/M_para;

%rate change of euler angles definition
dphi = p + (r*cos(phi) + q*sin(phi))*tan(theta);
dtheta = q*cos(phi) – r*sin(phi);
dpsi = (cos(theta)^-1)*(r*cos(phi) + q*sin(phi));

%rate change of angular rates definition
dp = (1/I_x)*(Aerodynamic_moment_x + GravityMoment_para_x);
dq = (1/I_y)*(Aerodynamic_moment_y + GravityMoment_para_y);
dr = (1/I_z)*(Aerodynamic_moment_z + GravityMoment_para_z);

dxdt = [dx_pos; dy_pos; dz_pos; du; dv; dw; dphi; dtheta; dpsi; dp; dq; dr];

%block to output angle of attack
if nargout>1
aoa_series = angle_of_attack;

end

end

tspan = [0 3];

x0 = [0; 0; -100; 0; 1; 1; 0; 0; 0; 0; 0; 0];

[t, x] = ode45(@six_DOF_dynamics, tspan, x0);

[~, aoa_series] = six_DOF_dynamics(t,x);

%adding alpha as a part of x

% Plot results
figure;
subplot(4,1,1);
plot(t, x(:,1:3));
title(‘Position’);
legend(‘x’, ‘y’, ‘z’);

subplot(4,1,2);
plot(t, x(:,4:6));
title(‘Velocity’);
legend(‘u’, ‘v’, ‘w’);

subplot(4,1,3);
plot(t, x(:,7:9));
title(‘Euler Angles’);
legend(‘phi’, ‘theta’, ‘psi’);

subplot(4,1,4);
plot(t, x(:,10:12));
title(‘Euler Rates’);
legend(‘p’, ‘q’, ‘r’); So I’ve been trying to simulate a parachute descent (very basic model, almost a mass body with a coefficient of drag), from a height. While simulating only in the axial direction(z axis), the results coincide with kinematics equations. However, when I give a non-zero initial condition, the outputs go crazy (definitely not correct) with periodic solutions to related terms. I seem to have checked my equations, they seem to be right. Is there anything with ‘odeset’ I can work this out around.
Zero non-axial initial condition:
x0 = [0; 0; -100; 0; 0; 1; 0; 0; 0; 0; 0; 0];

Non-zero IC:
x0 = [0; 0; -100; 0; 1; 1; 0; 0; 0; 0; 0; 0];

0

this is the code i’ve used for these plots. Please feel free to ask any clarifications
%% 6DOF fucntion definition
function [dxdt, aoa_series] = six_DOF_dynamics(t,x)

M_para = 5; %mass of the parachute in Kgs
g = 9.81; %gravitational acceleration in m/s^2
I_x = 1; I_y = 1; I_z = 3; %Inertia matrix diagonal principal of the parachute in kg-m^2
CD_para = 0.9; %coefficient of drag of parachute
CL_para = 0; %coefficient of lift of parachute
rho = 1; %density of the atmosphere in Kg/m^3
x_com = 0; y_com = 0; z_com = -5; %position of COM of the paarchute from the integrated system’s COM(body axis origin) in m
A = 10; %parachute area in m^2

%state variables defining
x_pos = x(1); y_pos = x(2); z_pos = x(3); %postion variables
u = x(4); v = x(5); w = x(6); %velocity variables
phi = x(7); theta = x(8); psi = x(9); %attitude/euler angles variables
p = x(10); q = x(11); r = x(12); %euler angular rate variables

%rate of change of postion -> velocity
dx_pos = u;
dy_pos = v;
dz_pos = w;

%Gravity moment of the parachute along x,y and z components
GravityMoment_para_x = M_para*g*cos(theta)*(y_com*cos(phi) – z_com*sin(phi));
GravityMoment_para_y = M_para*g*(z_com*sin(theta) – x_com*cos(theta)*cos(phi));
GravityMoment_para_z = M_para*g*(x_com*cos(theta)*sin(phi) + y_com*sin(theta));

V_total = sqrt(u^2 + v^2 + w^2); %net speed

persistent angle_of_attack %defining this variable to take it as a output outside ode45

alpha = acos(w/V_total); %angle of attack calculated in radians

angle_of_attack = [angle_of_attack; alpha]; %concatinating current iterated angle of attack in global variable

%Componetize CD and CL into tangential and normal force coefficients
CT = CD_para*cos(alpha) – CL_para*sin(alpha);
CN = CL_para*cos(alpha) + CD_para*sin(alpha);

% Aerodynamic force along x,y,z axes F = 0.5*rho*v^2*A
if (u == 0 & v == 0)
Aerodynamic_force_x = 0;
Aerodynamic_force_y = 0;
Aerodynamic_force_z = -0.5*rho*CT*V_total*V_total*A;
else
Aerodynamic_force_x = -0.5*rho*CN*V_total*V_total*A*(u/(u^2 + v^2)^0.5);
Aerodynamic_force_y = -0.5*rho*CN*V_total*V_total*A*(v/(u^2 + v^2)^0.5);
Aerodynamic_force_z = -0.5*rho*CT*V_total*V_total*A;
end

%Moment caused by aerodynamic force along x,y,x
Aerodynamic_moment_x = y_com*Aerodynamic_force_z – z_com*Aerodynamic_force_y;
Aerodynamic_moment_y = z_com*Aerodynamic_force_x – x_com*Aerodynamic_force_z;
Aerodynamic_moment_z = x_com*Aerodynamic_force_y – y_com*Aerodynamic_force_x;

%rate change of velocity definition
du = v*r – w*q + g*sin(theta) + Aerodynamic_force_x/M_para;
dv = -u*r + w*p + g*cos(theta)*sin(phi) + Aerodynamic_force_y/M_para;
dw = u*q – v*p + g*cos(theta)*cos(phi) + Aerodynamic_force_z/M_para;

%rate change of euler angles definition
dphi = p + (r*cos(phi) + q*sin(phi))*tan(theta);
dtheta = q*cos(phi) – r*sin(phi);
dpsi = (cos(theta)^-1)*(r*cos(phi) + q*sin(phi));

%rate change of angular rates definition
dp = (1/I_x)*(Aerodynamic_moment_x + GravityMoment_para_x);
dq = (1/I_y)*(Aerodynamic_moment_y + GravityMoment_para_y);
dr = (1/I_z)*(Aerodynamic_moment_z + GravityMoment_para_z);

dxdt = [dx_pos; dy_pos; dz_pos; du; dv; dw; dphi; dtheta; dpsi; dp; dq; dr];

%block to output angle of attack
if nargout>1
aoa_series = angle_of_attack;

end

end

tspan = [0 3];

x0 = [0; 0; -100; 0; 1; 1; 0; 0; 0; 0; 0; 0];

[t, x] = ode45(@six_DOF_dynamics, tspan, x0);

[~, aoa_series] = six_DOF_dynamics(t,x);

%adding alpha as a part of x

% Plot results
figure;
subplot(4,1,1);
plot(t, x(:,1:3));
title(‘Position’);
legend(‘x’, ‘y’, ‘z’);

subplot(4,1,2);
plot(t, x(:,4:6));
title(‘Velocity’);
legend(‘u’, ‘v’, ‘w’);

subplot(4,1,3);
plot(t, x(:,7:9));
title(‘Euler Angles’);
legend(‘phi’, ‘theta’, ‘psi’);

subplot(4,1,4);
plot(t, x(:,10:12));
title(‘Euler Rates’);
legend(‘p’, ‘q’, ‘r’); 6dof, parachute, periodic MATLAB Answers — New Questions

​

I am new to machine learning classifiers.
I want to develop a Random Forest classification model with my IMU data.
I used the code below, and my question is: Can I call it a Random Forest model, or should I just call it a bagging ensemble model?
baggedEnsemble = fitcensemble(data_train(:,2:end), data_train(:,1),’Method’,’Bag’,’NumLearningCycles’,100);I am new to machine learning classifiers.
I want to develop a Random Forest classification model with my IMU data.
I used the code below, and my question is: Can I call it a Random Forest model, or should I just call it a bagging ensemble model?
baggedEnsemble = fitcensemble(data_train(:,2:end), data_train(:,1),’Method’,’Bag’,’NumLearningCycles’,100); I am new to machine learning classifiers.
I want to develop a Random Forest classification model with my IMU data.
I used the code below, and my question is: Can I call it a Random Forest model, or should I just call it a bagging ensemble model?
baggedEnsemble = fitcensemble(data_train(:,2:end), data_train(:,1),’Method’,’Bag’,’NumLearningCycles’,100); machine learning, random forest, ensemble, bagging, classification MATLAB Answers — New Questions

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Hi,
I’m programming a DSP TMS320F28069M using Simulink. I have successfully received data and unpack that receive data via uint16 format. And I use a matlab function block. This reason that I used, to compare the required bits for Modbus communication. Although byte unpack block output type is uint16, I couldn’t use this receive value. For example, let the SCI received data be ’01 02 00 00 00 00 02 10′. First of compare the first byte. If first byte is 01, transmits the eighth byte. But if not sends second byte. I always saw the second byte was gone. I guess received or compare data type is wrong but I couldn’t find it. I changed the value C1 instead of 01 in the if loop. When I enter the C1 byte into the system, an error occurs How can I do this?

Inside the function block:Hi,
I’m programming a DSP TMS320F28069M using Simulink. I have successfully received data and unpack that receive data via uint16 format. And I use a matlab function block. This reason that I used, to compare the required bits for Modbus communication. Although byte unpack block output type is uint16, I couldn’t use this receive value. For example, let the SCI received data be ’01 02 00 00 00 00 02 10′. First of compare the first byte. If first byte is 01, transmits the eighth byte. But if not sends second byte. I always saw the second byte was gone. I guess received or compare data type is wrong but I couldn’t find it. I changed the value C1 instead of 01 in the if loop. When I enter the C1 byte into the system, an error occurs How can I do this?

Inside the function block: Hi,
I’m programming a DSP TMS320F28069M using Simulink. I have successfully received data and unpack that receive data via uint16 format. And I use a matlab function block. This reason that I used, to compare the required bits for Modbus communication. Although byte unpack block output type is uint16, I couldn’t use this receive value. For example, let the SCI received data be ’01 02 00 00 00 00 02 10′. First of compare the first byte. If first byte is 01, transmits the eighth byte. But if not sends second byte. I always saw the second byte was gone. I guess received or compare data type is wrong but I couldn’t find it. I changed the value C1 instead of 01 in the if loop. When I enter the C1 byte into the system, an error occurs How can I do this?

Inside the function block: modbus, sci MATLAB Answers — New Questions

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Chapter and section number is not increased in report generator.
I use mlreportgen.report, mlerportgen.dom class.Chapter and section number is not increased in report generator.
I use mlreportgen.report, mlerportgen.dom class. Chapter and section number is not increased in report generator.
I use mlreportgen.report, mlerportgen.dom class. simulink, report generator, mlreportgen MATLAB Answers — New Questions

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Hi everyone,

I have two arrays, one of which stores EMG readings in mV from a hand and the second storing time in seconds. I have plotted these against eachother and am now trying to segregate the signal into separate cycles. I want to segragate the signal from the start of 1 activity to the beginning of the next activation (please see attached photo). Please could you give me any ideas of how I might do this.
Thanks,Hi everyone,

I have two arrays, one of which stores EMG readings in mV from a hand and the second storing time in seconds. I have plotted these against eachother and am now trying to segregate the signal into separate cycles. I want to segragate the signal from the start of 1 activity to the beginning of the next activation (please see attached photo). Please could you give me any ideas of how I might do this.
Thanks, Hi everyone,

I have two arrays, one of which stores EMG readings in mV from a hand and the second storing time in seconds. I have plotted these against eachother and am now trying to segregate the signal into separate cycles. I want to segragate the signal from the start of 1 activity to the beginning of the next activation (please see attached photo). Please could you give me any ideas of how I might do this.
Thanks, emg, signal processing MATLAB Answers — New Questions

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testtest test testing test, testing test s MATLAB Answers — New Questions

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when I build the model I get the name mismatch error for two calibratable signals . The signals are in the data dictionary , and I use them in the model by pulling from the dd with the same name . can anyone point me out what possibly cause this error?when I build the model I get the name mismatch error for two calibratable signals . The signals are in the data dictionary , and I use them in the model by pulling from the dd with the same name . can anyone point me out what possibly cause this error? when I build the model I get the name mismatch error for two calibratable signals . The signals are in the data dictionary , and I use them in the model by pulling from the dd with the same name . can anyone point me out what possibly cause this error? simulink, embedded coder, build model MATLAB Answers — New Questions

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What is the solution for writing legends for MATLAB figures with subscripts?What is the solution for writing legends for MATLAB figures with subscripts? What is the solution for writing legends for MATLAB figures with subscripts? figure, legend, subscript MATLAB Answers — New Questions

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In the past two years, MATHWORKS has updated the image viewer and audio viewer, giving them a more modern interface with features like play, pause, fast forward, and some interactive tools that are more commonly found in typical third-party players. However, the video player has not seen any updates. For instance, the vision.VideoPlayer could benefit from a more modern player interface. Perhaps I haven’t found a suitable built-in player yet. It would be great if there were support for custom image processing and audio processing algorithms that could be played in a more modern interface in real time.
Additionally, I found it quite challenging to develop a modern video player from scratch in App Designer.
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BTW，the following picture shows the built-in function uihtml function showing a more modern playback interface with controls for play, pause and so on. But can not add real-time image processing algorithms.In the past two years, MATHWORKS has updated the image viewer and audio viewer, giving them a more modern interface with features like play, pause, fast forward, and some interactive tools that are more commonly found in typical third-party players. However, the video player has not seen any updates. For instance, the vision.VideoPlayer could benefit from a more modern player interface. Perhaps I haven’t found a suitable built-in player yet. It would be great if there were support for custom image processing and audio processing algorithms that could be played in a more modern interface in real time.
Additionally, I found it quite challenging to develop a modern video player from scratch in App Designer.
—————————————————————————————————————–
BTW，the following picture shows the built-in function uihtml function showing a more modern playback interface with controls for play, pause and so on. But can not add real-time image processing algorithms. In the past two years, MATHWORKS has updated the image viewer and audio viewer, giving them a more modern interface with features like play, pause, fast forward, and some interactive tools that are more commonly found in typical third-party players. However, the video player has not seen any updates. For instance, the vision.VideoPlayer could benefit from a more modern player interface. Perhaps I haven’t found a suitable built-in player yet. It would be great if there were support for custom image processing and audio processing algorithms that could be played in a more modern interface in real time.
Additionally, I found it quite challenging to develop a modern video player from scratch in App Designer.
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BTW，the following picture shows the built-in function uihtml function showing a more modern playback interface with controls for play, pause and so on. But can not add real-time image processing algorithms. video player, image processing, computer vision, appdesigner MATLAB Answers — New Questions

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