In Matlab, add J2 perturbations to your two body propagation. Comment on your findings. Also, how would you change your code if you had other things affecting the orbit. For example, solar radiation pressure, third body perturbations, or drag. Do you just add the accelerations together in the function?
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In Matlab, add J2 perturbations to your two body propagation. Comment on your findings. Also, how would you change your code if you had other things affecting the orbit. For example, solar radiation pressure, third body perturbations, or drag. Do you just add the accelerations together in the function?
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- I need help with a MATLAB code. I am trying to figure out how to add perturbation to the following code. I want to add J2 Perturbation, Drag, SRP, and third body effects and use that to replace the forbit function. Does MATLAB have an in built function that can help me here. I heard about the numericalPropagator function of MATLAB. Can that be used here? % 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); X = [RECI;VECI]*1e3; %========================================================================== % Propagation %========================================================================== h = 300; % Step Size (sec) steps = 300; % Number of Steps [X_RK] = RK_4(X,h,steps); % Orbit in ECI (PV) %% Funcitons function [X_RK] = RK_4(X,h,steps) X_init = X; for t=1:steps X=rk4orbit(t,X,h); XX(t)=X(1); YY(t)=X(2); ZZ(t)=X(3); VX(t)=X(4); VY(t)=X(5); VZ(t)=X(6); plot3(XX,YY,ZZ); % Plot…Please help me MatlabThe center of mass for a human body can be determined by a segmental method. Using cadavers, it is possible to determine the mass of individual body segments (as a proportion of total body mass) and the center of mass for each segment (often expressed as a distance from one end of the segment). Finding the overall body center of mass can be a complex calculation, involving more than 10 body segments. Below, we will look at a simplified model that uses just six segments: head, trunk, two arms, and two legs. Search y X As a percentage of total body mass, the head is 10%, the two arms are 10%, the trunk is 56%, and the two legs are 24%. The center of mass for each segment is given as an (x,y) coordinate, both units in cm: head = (0, 165), arms = (0, 115), trunk = (0, 95), and legs = (0, 35). Assume the body mass for the individual is 88 kg and their total height is 180 cm. Determine they and y coord 99+ H of mass
- I was trying to plot an orbit in MATLAB using my numerical propagator and a sgp4 propagator that i copied from MATLAB website. The plot of the two different propagators are shown in the image. I was plotting a GEO orbit. The numerical propagator took into account drag, solar radiation pressure, and J2 perturbations. I am wondering if the orbits are correct. Because the sgp4 orbit is perfectly circular while my numerical propagator orbit is more spiral like. Does sgp4 also take in account perturbations? Or, is it more of an ideal orbit?I am trying to find the gross liftoff mass of a 2 stage rocket for different values of n and plot it in MATLAB. I found the total liftoff mass for stage 1 and stage 2. Is the gross liftoff mass equal to m_i1 in the code or do you have to add m_i1 and m_i2? Also, the liftoff seems to be negative for some intial values of n? That is not feasible, right? % Constants delta_V_ideal = 9800; % m/s f_inert1 = 0.15; f_inert2 = 0.25; Isp_1 = 325; % s Isp_2 = 380; % s g0 = 9.81; % m/s^2 m_PL = 750; n = 0.3:0.01:0.7; % Initializing variables delta_v1 = zeros(size(n)); delta_v2 = zeros(size(n)); MR_2 = zeros(size(n)); m_prop2 = zeros(size(n)); m_inert2 = zeros(size(n)); m_i2 = zeros(size(n)); MR_1 = zeros(size(n)); m_prop1 = zeros(size(n)); m_inert1 = zeros(size(n)); m_i1 = zeros(size(n)); for i = 1:length(n) delta_v1(i) = n(i)*delta_V_ideal; delta_v2(i) = (1-n(i))*delta_V_ideal; MR_2(i) = exp(delta_v2(i)/(g0*Isp_2)); m_prop2(i) = (m_PL*(MR_2(i)-1)*(1-f_inert2))/(1-f_inert2*MR_2(i));…I created an orbit of the ISS in MATLAB. I want to validate my data. How and where can I get actual data of the ISS orbit? I would need the time history of the position vectors?
- Can you help me code the algorithm into MATLAB? The delta zero, delta one and so forth are equal to the determinats of a 3x3 matrix made of the three vectors.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 do this in MATLAB
- I need answer in 20 to 25 min asap and please dont give handwritten solutionTopics Discussed: Static of Rigid Bodies, Force Vector, Addition of a System of Coplanar Forces, Cartesian Vector Please re-compute and re-solve the given, This is my answer. But I also want to see your expert answer if we land in the same solutions and answers. Please show your complete solution. Thank you.Can you help me with a matlab code? I am trying to plot the keplerian orbital elements over time. I would usually find the orbit using cartesian system and then transform into keplerian orbital elements. Is there a way to directly integrate keplerian orbital elements?