Implement the Runge-Kutta method in MatLab for the numerical solution of the equation of motion for the 2-Body Problem for the orbit specified in the question

Implement the Runge-Kutta method in MatLab for the numerical

solution of the equation of motion for the 2-Body Problem for the

orbit specified in the question:

(i) Use MatLab to calculate the numerical orbit time period.

Define a stopping criterion for the time integration loop in

MatLab and save the time variable upon meeting the stopping

criterion. Analytical calculations for the orbit’s time period will

not be considered.

(ii) Plot the orbit trajectory using MatLab’s default plotting

functions and compare the result with the analytical solution.

The analytical solution can be obtained either in Matlab or

Excel. If you decide to go with Excel for the analytical solution

then also upload the Excel file in Wiseflow.

(iii) Plot the magnitude of the spacecraft’s velocity versus time

for the Runge-Kutta method

[Steven Lord]

This sounds like a homework assignment. If it is, show us the code you've written to try to solve the problem and ask a specific question about where you're having difficulty and we may be able to provide some guidance.

If you aren't sure where to start because you're not familiar with how to write MATLAB code, I suggest you start with the free MATLAB Onramp tutorial to quickly learn the essentials of MATLAB.

If you aren't sure where to start because you're not familiar with the mathematics you'll need to solve the problem, I recommend asking your professor and/or teaching assistant for help.