Engineering, 19.11.2019 01:31, JJ143899

Let a spacecraft be in elliptical orbit around mars. let the orbital elements (with angles relative to a mars-centered inertial system) be a = 8000 km, e = 0.25, i=- radians, 12=5radians, w=radians and t = 1am pst (earth time), where we recall that t is the time of periapsis passage. what is the on of the vehicle (in the mars-centered inertial system) at 9am pst that same morning? note that jumars = gmmars ~ 42, 828 kuce you must include all your rotation matrices in the solution for full credit.

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Let a spacecraft be in elliptical orbit around mars. let the orbital elements (with angles relative...