A 355-kg satellite is launched into a circular orbit that has a period of 696 min and a radius of 20, 300 km around Earth. Determine the gravitational potential energy Uorbit of the satellite's orbit. Uorbit = J Estimate the energy ΔE required to place the satellite in orbit around Earth. ΔE =
![A spacecraft with mass 2070 kg is in circular orbit around Earth as shown with the green circle in the figure, at an altitude h = 690 km. What is the period of the orbit? Reminder: the radius of the orbit is the altitude plus RE, the radius of Earth. RE = 6.371×103 km. For reference, the mass of Earth, ME, is 5.98×1024 kg. T = s At point P in the orbit (see figure), the spacecraft reduces its speed by 1.7%, causing it to be in an elliptical orbit. What is the kinetic energy of the ship immediately after this slowing? (Note that the potential energy of orbit will not have changed since it is still at point P ). K = J [Note: use exponential notation to enter your answer: "9.99 e12" represent 9.99×1012. ] What is the semi-major axis of the new (elliptical) orbit? a = km What is the perigee distance for the new (elliptical) orbit? Rp = km](https://www.doubtrix.com/uploads/editor/6309357089jnyUuClMZS.png)
