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The angular position E along the elliptical orbit of a spacecraft is given by the following nonlinear equation:
f(E)=nt-E+esinE=0 (1)
where t is the time (in seconds) at which E is required, e is the eccentricity of the ellipse and u is the mean motion defined as:
u=(m/(a^3))^1/2
with being the...
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