V1 Consider the TBP governing equation of motion in 3D. As mentioned, this equation governs thebehavior of satellites or space vehicles in the Earth Centered Inertial Frame (ECI).TBP Governing Equation of Motioni HEarth =398,600 km³ /s?r(0) = 16001+ 5310J+ 3800K (km)ř(0)=-7.3501 + 0.4600J + 2.470K (km/s)Perform the following tasks:i. Use the initial condition of and arbitrary satellite given below to propagate its orbit for at leastone complete period (the orbit is closed). You can tabulate the position and velocity componentsand magnitude with time for At = 100 Sec.ii. Show (plot) the resulting satellite 3D trajectory for one complete period.iii. Show the satellite ground track or its geographical position on the Earth surface. This can besimply shown as a graph of the satellite latitude versus its longitude for one period. See thesample given below.Ground Tracker60N60N40N40N20N20N20s20540s60'S100W120°E180EM.ort

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Consider the TBP governing equation of motion in 3D. As mentioned, this equation governs the behavior of satellites or space vehicles in the Earth Centered Inertial Frame (ECI). TBP Governing Equation of Motion Si MEarh =398,600 km /s r(0) = 16001+ 5310J + 3800K (km) F(0) =-7.3501+ 0.4600J + 2.470K (km/s) Perform the following tasks: i. Use the initial condition of and arbitrary satellite given below to propagate its orbit for at least

Consider the TBP governing equation of motion in 3D. As mentioned, this equation governs the behavior of satellites or space vehicles in the Earth Centered Inertial Frame (ECI). TBP Governing Equation of Motion Si MEarh =398,600 km /s r(0) = 16001+ 5310J + 3800K (km) F(0) =-7.3501+ 0.4600J + 2.470K (km/s) Perform the following tasks: i. Use the initial condition of and arbitrary satellite given below to propagate its orbit for at least