Data from 2nd order ode mathematica

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SUMMARY

This discussion focuses on extracting time data from a second-order ordinary differential equation (ODE) using Mathematica. The provided code simulates the 2-body problem, specifically modeling the trajectory of a spacecraft influenced by Earth's gravity. Key functions utilized include NDSolve for solving the ODEs and ParametricPlot3D for visualizing the trajectory. Additional suggestions include using Table to generate numerical results alongside graphical outputs for better data representation.

PREREQUISITES
  • Familiarity with Mathematica programming language
  • Understanding of second-order ordinary differential equations (ODEs)
  • Knowledge of numerical methods, specifically NDSolve in Mathematica
  • Basic concepts of gravitational physics and orbital mechanics
NEXT STEPS
  • Explore advanced features of NDSolve in Mathematica for complex systems
  • Learn about visualizing 3D trajectories in Mathematica using ParametricPlot3D
  • Investigate the use of Table and TableForm for data extraction and presentation
  • Study the principles of orbital mechanics to enhance understanding of the 2-body problem
USEFUL FOR

Researchers, physicists, and engineers involved in computational physics, particularly those working with orbital simulations and numerical analysis in Mathematica.

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How can I extract time data from a system 2nd order ODEs in Mathematica?
 
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Can you post the ODE's and your Mathematica code so far?
 
Ackbach said:
Can you post the ODE's and your Mathematica code so far?

Code:
Numerical Simulation of the 2-Body Problem

ClearAll["Global`*"];

We begin with of the the necessary data for this problem...

M = 5974*10^21; (* mass of Earth, kg *)

m = 1000; (* mass of  spacecraft , kg *)

\[Mu] = 3.986*10^5; (* gravitaional parameter, based on km units of length, \
km/s for velocity *)

Rearth = 6378; (* radius of the Earth, km *)Simulation Inputs

r0 = {3950.55, 43197.9, 0};(* initial position vector, km *)
v0 = {3.3809, -7.25046, 0}; (* initial velocity vector, km *)
Days = 1/10; (* elapsed time of simulation days *)

\[CapitalDelta]t = Days*24*3600;(* convert elapsed days to seconds *)

s = NDSolve[
   {
    x1''[t] == -(\[Mu]/(Sqrt[x1[t]^2 + x2[t]^2 + x3[t]^2])^3)*x1[t],
    x2''[t] ==  -(\[Mu]/(Sqrt[x1[t]^2 + x2[t]^2 + x3[t]^2])^3)*x2[t],
    x3''[t] ==  -(\[Mu]/(Sqrt[x1[t]^2 + x2[t]^2 + x3[t]^2])^3)*x3[t],
    
    x1[0] == r0[[1]], (* intial x-position of satellite *)
    
    x2[0] == r0[[2]],(* intial y-position of satellite *)
    
    x3[0] == r0[[3]],(* intial y-position of satellite *)
    
    x1'[0] == v0[[1]],(* intial vx-rel of satellite *)
    
    x2'[0] == v0[[2]],(* intial vy-rel of satellite *)
    
    x3'[0] == v0[[3]](* intial vy-rel of satellite *)
    
    },
   {x1, x2, x3},
   {t, 0, \[CapitalDelta]t} 
   ];

Plot of the Trajectory Relative to Earth

g1 = ParametricPlot3D[
   Evaluate[{x1[t], x2[t], x3[t]} /. s], {t, 0, \[CapitalDelta]t},  
   PlotStyle -> {Red, Thick}];
g2 = Graphics3D[{Blue, Opacity[0.6], Sphere[{0, 0, 0}, Rearth]}];Show[g2, g1, Boxed -> False]
 
I'm not certain exactly what you are expecting when you "extract time data", but perhaps something in this will help.What if you replaceShow[g2, g1, Boxed -> False]

with

g3 = Graphics3D[Table[Point[{x1[t], x2[t], x3[t]} /. s[[1]]], {t, 0, Δt, Δt/10}]];
g4 = Graphics3D[Table[Text[ToString[t], {x1[t], x2[t], x3[t]} /. s[[1]], {1, 0}], {t, 0, Δt, Δt/10}]];
Show[g2, g1, g3, g4, Boxed -> False]That will place points along your path and label each point with the associated value of t. You can adjust the step size and the label position next to each point as needed.

If that doesn't provide you with the necessary level of detail then you might try using

Table[{t,x1[t],x2[t],x3[t]}/.s[[1]], {t,0,Δt,Δt/10}]//TableForm

with appropriate step size to give you the numerical results to go along with your plot.
 

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