# Stanley McClister
# Section 12
# 9-23-13
#  main function
    # Step 1.  Display introductory message
    # Step 2.  Import math library
    # Step 3.  Request user input an integer for altitude of the orbit
    # Step 4.  Set that input to x 
    # step 5.  Add x to the constant radius of earth to get total radius. r = x + 6378.1370
    # Step 6.  Multiply r by a thousand to change the value from kilometers to meters. Set that to the constant R 
    # Step 7.  Set the given gravitational mass of Earth to the constant GM
    # Step 8.  Calculate the orbital velocity using the math library. v = sqrt(GM/R)
    # Step 9.  Calculate acceleration using past constants a = GM/(R**2)
    # Step 10. Calculate the orbital period in seconds p = sqrt((4(pi**2)R**3)/GM)
    # Step 11. Calculate the orbital period in minutes m = p/60 and round to 2 decimal places
    # Step 12. Output to the shell the orbital velocity in m/s
    # Step 13. Output to the shell the acceleration m/s**2
    # Step 14. Output to the shell the number of seconds in the orbital period
    # Step 15. Output to the shell the rounded number of minutes in the orbital period