A satellite is in an elliptic orbit with e = 0.5. Using a starting value of Eo =M, determine the value ofE to an accuracy of104 radians at the time he satellite is one-quarter period past periapse passage. List all iterations, including the value of F(E) by:a) using the Newton algorithm, and b) using the Laguerre algorithm (2.43) c) Repeat parts a) and b) using the starting value of Eq. (2.16), d) Calculate the value of f for the solution. e) Determine, in terms of a the value of r for the solution, and f) Determine the radial and circumferential components of the velocity vector and its magnitude in units of /a).