You observe a near-Earth satellite with the inertial position and velocity vectors: N r=(-4069.503,2861.786,4483.608) km N v=(-5.114,-5.691,-1.000)
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Question:
You observe a near-Earth satellite with the inertial position and velocity vectors:
Nr=(-4069.503,2861.786,4483.608) km
Nv=(-5.114,-5.691,-1.000) km/s
where the vector components are taken with respect to an inertial frame.
a) Using the energy equation, determine what type of orbit this is.
b) Compute the eccentricity of this orbit using the eccentricity vector expression.
c) Determine the periapsis radius. Will the satellite his the Earth (ignoring atmospheric effects)?
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