For an eccentricity of 0.92 and semi major axis length of 9500 km, de – McqOptions

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1.	For an eccentricity of 0.92 and semi major axis length of 9500 km, determine the apogee velocity for a satellite in elliptical orbit. Take μ = 3.986 x 1014 m3/sec2.
A.	1349.54 m/s
B.	1439.45 m/s
C.	1233.33 m/s
D.	1322.21 m/s
Answer» E.

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