A Hohmann orbit transfer is to be arranged to send a satellite from a circular l

Question

A Hohmann orbit transfer is to be arranged to send a satellite from a circular low earth orbit (altitude 300 km) to an elliptical orbit about the sun with a semimajor axis of 500times106 km and e = 0.3 to study the asteroid belt. Assume the Earth has a circular orbit about the sun at a distance of 149.6 times 106 km. Compute the velocity of the low earth orbit relative to the Earth assuming an Earth radius of 6400 km. Compute the maximum velocity of the satellite relative to the sun while in LEO. Compute the distance from the sun and velocity at perigee of the new elliptical orbit. Assuming the Hohmann transfer orbit will intercept the new-elliptical orbit at perigee, compute the semimajor axis of the Hohmann transfer orbit. Compute the delta V required to leave LEO and enter the Hohmann transfer orbit and the delta V required to leave the Hohmann transfer orbit and enter the new elliptical orbit.

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