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// Chapter 11 example 3
//------------------------------------------------------------------------------
clc;
clear;
// Given data
a1 = 18000; // semi major axis of the elliptical orbits of satellite 1
a2 = 24000; // semi major axis of the elliptical orbits of satellite 2
// Calculations
// T = 2*%pi*sqrt(a^3/u);
//let K = T2/T1;
K = (a2/a1)^(3/2); // Ratio of orbital periods
// Output
mprintf('The orbital period of satellite-2 is %3.2f times the orbital period of satellite-1',K);
//------------------------------------------------------------------------------
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