Again making the appropriate substitution, the density function for r, assuming time a random variable, becomes: From equation 1.8, we may now determine some elementary statistics regarding the average position (r) of a satellite in a classical elliptic orbit. While this expectation (or average value) of r can be considerably greater than the semi-minor axis value (a V 1 — e2), equation 1.9 is statistically more representative of a true orbit. To find the variance value of r, we need to solve the following equation:
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