1. The problem statement, all variables and given/known data Flight to Mars. To send a satellite from Earth to Mars, a rocket must accelerate the satellite until it is in the correct elliptical orbit around the sun. The satellite does not travel to Mars under rocket power, because that would require more fuel than it could carry. It just moves on a Keplerian orbit under the influence of the sun's gravity. The satellite orbit must have perihelion r = 1 AU, and aphelion r = 1.52 AU. What is the semimajor axis of the satellite's orbit? (this works out to 1.26 AU; answer is correct) Calculate the time for the satellite's journey. Express the result in days. 2. Relevant equations ω(t)=2∏/T v(t)=R*dω/dt-R2 3. The attempt at a solution My brain goes a little wonky when I try to calculate travel time without a velocity. I tried using G*M/r^2=a and plugging in the mass of the sun and the gravitational constant as well as our semi-major axis as r to find the acceleration due to gravity of the sun. Of course the radius is changing and due to the square the acceleration is not a linear function so using the semi-major axis (effectively an average) is highly inaccurate. I'm just not sure what else to use. You could differentiate the function but I don't know how to represent the radius as a function (an ellipse) given only the perihelion and aphelion. Once you find the acceleration due to gravity you can plug it in to our a=R*(dω/dt)-R*ω^2 and solve for T (ω=2*pi/T). Using what I have, though, the answers I have come up with are not correct. (516.3 days) Does anyone have any suggestions?