If you plan to plot the orbit with all the elements or want to plot a ground plot and so on, then get the initial values and use the support files in this MATLAB Answers page. It results in plotting the orbit in an Earth centric frame. Mu = 3.986e5 %graviational parameter of the Earth R = h rE %radius of the circular orbit km H = 400 %assumed altitude of the circular orbit km RE = 6471 %average radius of the Earth km We shall start with scalar operations, for which MATLAB acts like a very powerful calculator. As the name MATLAB (MATrix LABoratory) suggests, most of the commands work with matrices and these will be discussed in due course. Theta = deg2rad(0) %initial value of true anomaly MATLAB already has an extensive vocabulary: however we will learn that we can expand this set. Here's an example I wrote with a very basic integrator. Now you can provide the initial value and propagate with whatever integrator you prefer. MATLAB can be used as a very powerful calculator and its operations fall into two basic groups:unaryandbinary, the former operating on one quan- tity and the latter on two. Since rate of change of true anomaly d_theta would be nothing but the angular velocity, using $\omega = \frac Instantly plot and visualize the orbit from the data. Calculate classical or Keplerian, Kepler orbital elements from position and velocity vectors. If that's the case, assuming a circular orbit, the vis-viva equation gives: An orbital elements calculator and plotter using relative units (DU and TU). the true anomaly theta at a given time t. Since you mention that you want to plot a satellite's orbit in MATLAB, in the most basic sense (since you haven't mentioned other keplerian elements), I take it that you know the altitude of the orbit, and want to know where the satellite will be, i.e. See for more details gereshes Matlab-Astrodynamics-Library Star master 1 branch 0 tags Code 4 commits Failed to load latest commit information. Also, you would need the initial values of elements you want to propagate. reader code converted from MATLAB into the Julia Language for use in astrodynamics. GitHub - gereshes/Matlab-Astrodynamics-Library: A repo of matlab functions related to astrodynamics. Thus, we have implemented our own numerical simulator in Python that starting from a set of initial state vectors of positions and velocities, user and constellation satellite positions are. Like the comment above mentions, you wouldn't need mass of the satellite unless its a Deathstar.
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