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// Chapter 11 example 9
//------------------------------------------------------------------------------
clc;
clear;
// Given data
farth = 30000; // farthest point in satellite elliptic eccentric orbit
closest = 200; // closest point in satellite elliptic eccentric orbit
Re = 6370; // Radius of earth in km
// Calculations
Apogee = farth + Re; // Apogee in km
Perigee = closest + Re; // perigee in km
a = (Apogee + Perigee)/(2); // semi-major axis
e = (Apogee - Perigee)/(2*a); // orbit eccentricity
// Output
mprintf('Apogee = %d km\n Perigee = %d km\n orbit eccentricity = %3.3f',Apogee,Perigee,e);
//------------------------------------------------------------------------------
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