Determine the parameters of the new satellite trajectory

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Reference no: EM131401241

An earth satellite is in an elliptical orbit with the perigee at 600 km altitude and an eccentricity of e = 0.866. Determine the parameters of the new satellite trajectory, if a rocket propulsion system is fired in the direction of flight giving an incremental velocity of 200 m/sec when

(a) fired at apogee,

(b) fired at perigee, and

Reference no: EM131401241

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