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// Chapter 11 example 8
//------------------------------------------------------------------------------
clc;
clear;
// Given data
Apogee = 30000; // Apogee pt of satellite elliptical orbit
Perige = 1000; // perigee pt of satellite elliptical orbit
// Calculations
a = (Apogee + Perige)/2; // semi major axis
// output
mprintf('Semi-major axis = %d Km',a);
//------------------------------------------------------------------------------
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