A possible trajectory for sending a spacecraft to Mars is an elliptical orbit with Earth at its perihelion and Mars at its aphelion. The craft would be launched out of low-Earth orbit by a quick burst of rockets into solar orbit, and would then “coast” until rockets fire again to slow it down into Mars orbit. Neglecting the acceleration and deceleration phases, how long would it take to get from low-Earth orbit to Mars along this “minimal-energy” trajectory? Assume circular orbits for Earth and Mars with radii 1AU and 1.52 AU respectively. Express your answer in years and round to two signific

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