I am having trouble with the folloiwng MATLAB code. I am getting an error that says "unrecognized function or variable 'numericalPropogatorOptions". I have the aerospace toolbox and the aerospace blockset added. what add on do I have to download to use that function. How do I make this code work?     % Define Keplerian Elements a = 29599.8; e = 0.0001; i = 0.9774; Omega = 1.3549; w = 0; M = 0.2645; [RECI, VECI] = Kepler2RV(a, e, i, Omega, w, M); initialState = [RECI * 1e3; VECI * 1e3]; % Initial position (m) and velocity (m/s)   % Define constants mu = 3.986004418e14; % Gravitational constant (m^3/s^2) earthRadius = 6378.1363 * 1e3; % Earth radius in meters j2 = 1.08263e-3; % J2 perturbation coefficient   % Define propagator options propOptions = numericalPropagatorOptions('CentralBody', 'Earth', ... 'GravitationalParameter', mu, ... 'InitialState', initialState, ... 'OutputTimeStep', 300); % Output every 300 seconds   % Add perturbations addGravityModel(propOptions, 'Degree', 2, 'Order', 0); % J2 effect addDragModel(propOptions, 'AtmosphereModel', 'Exponential', ... 'ReferenceArea', 1.0, 'DragCoefficient', 2.2, ... 'Mass', 500); % Atmospheric drag addSolarRadiationPressureModel(propOptions, 'ReferenceArea', 1.0, ... 'Reflectivity', 1.3, 'Mass', 500); % SRP addThirdBodyGravity(propOptions, 'Moon'); % Third-body effect from the Moon addThirdBodyGravity(propOptions, 'Sun'); % Third-body effect from the Sun   % Propagate the orbit endTime = 300 * 300; % 300 steps, each of 300 seconds [t, state] = numericalPropagator(endTime, propOptions);   % Extract position and velocity for plotting position = state(:, 1:3); % Position in ECI (meters) velocity = state(:, 4:6); % Velocity in ECI (meters/second)   % Plot the orbit plot3(position(:, 1), position(:, 2), position(:, 3)); xlabel('X (m)'); ylabel('Y (m)'); zlabel('Z (m)'); title('Simulated Orbit with Perturbations in ECI'); grid on;       function [RECI, VECI] = Kepler2RV(a, e, i, Omega, w, M) mu = 398600.441799999971; % Earth's Standard Gravitational Parameter (GM) Eps = 2.22044604925031e-8; % Machine epsilon E = SolveKepler(M,e,Eps); % Eccentric Anomaly from Mean Anomaly M = 2*atan(sqrt((1+e)/(1-e))*tan(E/2)); % True Anomaly obtained from Eccentric Anomaly p = a*(1 - e^2); % Semiparameter (km) % Position Coordinates in Perifocal Coordinate System x = (p*cos(M)) / (1 + e*cos(M)); % x-coordinate (km) y = (p*sin(M)) / (1 + e*cos(M)); % y-coordinate (km) z = 0; % z-coordinate (km) vx = -(mu/p)^(1/2) * sin(M); % velocity in x (km/s) vy = (mu/p)^(1/2) * (e + cos(M)); % velocity in y (km/s) vz = 0; % velocity in z (km/s) % Transformation Matrix (3 Rotations) t_rot = [cos(Omega)*cos(w)-sin(Omega)*sin(w)*cos(i) ... (-1)*cos(Omega)*sin(w)-sin(Omega)*cos(w)*cos(i) ... sin(Omega)*sin(i); ... sin(Omega)*cos(w)+cos(Omega)*sin(w)*cos(i) ... (-1)*sin(Omega)*sin(w)+cos(Omega)*cos(w)*cos(i) ... (-1)*cos(Omega)*sin(i); ... sin(w)*sin(i) cos(w)*sin(i) cos(i)]; % Transformation Perifocal xyz to ECI RECI = t_rot*[x y z]'; VECI = t_rot*[vx vy vz]'; end       function E = SolveKepler(M,e,Eps) % Iterative Solution of Kepler's equation (M = E-e*sin(E)) %========================================================================== % Inputs: M = Mean Anomaly (rad) % e = Eccentricity % Eps = Machine epsilon % Output: E = Eccentric Anomaly (rad) %========================================================================== E0 = M; E1 = E0 - (E0 - e*sin(E0) - M)/(1 -e*cos(E0)); while (abs(E1-E0) > Eps) E0 = E1; E1 = E0 - (E0 - e*sin(E0) - M)/(1 - e*cos(E0)); end E = E1; end

Could you please fix my code it’s supposed to look like the graph that’s on the picture. But the lines do not cross eachother at the beginning. Could you make the lines look like the lines on the graph? Use this code in MATLAB and fix it. % Sample data for Diesel and Petrol cars carPosition = linspace(1, 60, 50); % Assumed positions of cars % Define your seed here seed = 50; rand('seed',seed); % Set the seed for reproducibility % Assumed CO2 emissions for Diesel and Petrol CO2Diesel = 25 + 5*cos(carPosition/60*2*pi) + randn(1, 50)*5; % Random data for Diesel CO2Petrol = 20 + 5*sin(carPosition/60*2*pi) + randn(1, 50)*5; % Random data for Petrol % Fit polynomial curves with a reduced degree of 2 pDiesel = polyfit(carPosition, CO2Diesel, 2); pPetrol = polyfit(carPosition, CO2Petrol, 2); % Generate points for best fit lines fitDiesel = polyval(pDiesel, carPosition); fitPetrol = polyval(pPetrol, carPosition); % Plotting the data figure; hold on; % Plot Diesel best fit line…

This code keeps on generating graphs with different curves. The picture that you see two different graphs comes from the same code but both of them have different curves. I need the curve to look like the picture that only has one graph. I basically need the line to have a slight curve and every time I run the code it will come up as the same graph every time. Use this code on MATLAB and fix it % Sample data for Diesel and Petrol cars carPosition = linspace(1, 60, 50); % Assumed positions of cars % Use the 'seed' function instead of 'rng' seed = 50; % Define your seed here rand('seed',seed); % Assumed CO2 emissions for Diesel and Petrol CO2Diesel = 25 + 5*cos(carPosition/60*2*pi) + randn(1, 50)*5; % Random data for Diesel CO2Petrol = 20 + 5*sin(carPosition/60*2*pi) + randn(1, 50)*5; % Random data for Petrol % Fit polynomial curves with a reduced degree of 2 pDiesel = polyfit(carPosition, CO2Diesel, 2); pPetrol = polyfit(carPosition, CO2Petrol, 2); % Generate points for best fit…

I need help with a MATLAB code. I am trying to solve this question. Based on the Mars powered landing scenariosolve Eq. (14) via convex programming. Report the consumed fuel, and discuss the results with relevant plots. I am using the following MATLAB code and getting an error. I tried to fix the error and I get another one saying something about log and exp not being convex. Can you help fix my code and make sure it works.   The error is CVX Warning:  Models involving "log" or other functions in the log, exp, and entropy  family are solved using an experimental successive approximation method.  This method is slower and less reliable than the method CVX employs for  other models. Please see the section of the user's guide entitled      The successive approximation method  for more details about the approach, and for instructions on how to  suppress this warning message in the future.Error using  .*  (line 173)Disciplined convex programming error:   Cannot perform the operation:…

Use MATLAB please make code for this.

I need help in the following MATLAB code. How do I add the code to answer the following question "Do you find more object detections in the image than the one that is cropped out? Explain how you would discriminate that from a dead pixel, a hot pixel, or a cosmic ray event."   fname = '00095337.fit'; fInfo = fitsinfo(fname); img = fitsread(fname);   % Crop the image to show just the object: img_cropped = img(1980:2030,1720:1780);   % Load the labeled image img_labeled = imread('00095337_labeled_stars.png'); img_labeled = img_labeled(102:863,605:1363,:);   % Get rid of "hot" pixels (cosmic rays, disfunctional pixels) max_acceptable_value = 1300; img(img>max_acceptable_value) = max_acceptable_value;     % Plot the images f1 = figure(); tgroup1 = uitabgroup('Parent',f1); tab(1) = uitab('Parent', tgroup1, 'Title', 'Raw image'); ax(1) = axes('parent',tab(1)); imagesc(img) axis equal axis([0,size(img,2),0,size(img,1)]+0.5) colormap(gray(256)); xlabel('x [px]') ylabel('y [px]')…

I need help with my MATLAB code. I am trying to plot the semi major axis and eccentricity with the following code with rungge kutta method. I have two different nnn's in the code which produce two different step sizes. So, I am wondering why both give the same exact plots for semi-major axis and eccentricity. The orbital dynamics fucntion considers J2, drag, SRP, and third body effects.   % Orbital elements obtained from TLE inc = 63.5000118; % Inclination (degs) raan = 19.999977; % RAAN (degs) ecc = 0.001; % Eccentricity argp = 120.02165342; % argument of perigee (degs) v = 0; % True anomaly (degs)   a = 6584.697271; % Semi-major axis (km)   mu = 3.986e5; period = (2*pi*sqrt((a^3)/mu));     % Calculating the state vector in eci frame [x, y, z, vx, vy, vz] = kep2cart(a, ecc, inc, raan, argp, v); Y = [x, y, z, vx, vy, vz];   options = odeset('RelTol', 1e-12, 'AbsTol', 1e-12);   nnn1 = 800; t_step1 = period/nnn1; m6 = 50; h_step6 = t_step1/m6; t_total6 = 0:h_step6:10*period;   [t6,…

Please help Matlab

MULTIPLE CHOICE -The answer is one of the options below please solve carefully and circle the correct option Please write clear .

Help me solve this using MATLAB