We want to place a spacecraft moving in a circular orbit 500 km above the Pluto's surface in a circular orbit 1000 km above the earth's surface. To do this, first give the satellite a speed increase of ikenv while it is in the 1st green orbit and place it in the 2nd yellow elliptical orbit, and then, when the elliptical orbit reaches a distance of 1000 km from the ground, it gives it a second Δv 'velocity and allows the satellite to settle in the 3rd red circular orbit.

a) What is the total speed increase Δvtoplam = Δv + Δv 'to be given to the satellite?
b) How many seconds does the satellite change from 500 km orbit to 1000 km orbit?

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Given that radius of earth R 6371 km say r1 500 km from the surface ... View the full answer