A ground-based station is tracking a military satellite that is in a near-equatorial, high-eccentricity orbit. At epoch time t 1 , the satellite’s ECI position vector is           Carry out the...

A ground-based station is tracking a military satellite that is in a near-equatorial, high-eccentricity orbit. At epoch time t₁, the satellite’s ECI position vector is

Carry out the p-iteration algorithm calculations to show that p = 10,596.1 km satisfies Lambert’s problem for the flight time between these two position vectors. In addition, compute the satellite’s eccentricity, semimajor axis, and period.