1. The problem statement, all variables and given/known data Hi, I have a question on my homework that I'm absolutely stuck at. I'm not sure how to go about this. Can someone help me through the steps to solve it? there are more after this similar to it so learning how to do this one would help me do the other ones by my self. Thanks a lot! Your trip to Mars is accomplished by using an elliptic transfer orbit going from Earth to Mars as shown in Fig. 1. This trajectory assumes that Earth at departure, the Sun, and Mars at arrival, are aligned. Also, we will assume that Earth's and Mars' orbits are circular, with radiuses R = 149,943,160 km and 228,189,693 km, respectively. What is, in meters, the semi-major axis, a, of this transfer orbit? Hint: determine its radiuses at aphelion and perihelion. http://as370.socialhwk.com/engr370/hw/midterm/264x340xfig1-hw3.gif.pagespeed.ic.sqq5I9yIl4.png [Broken] 2. Relevant equations I found these in a lesson online. http://as370.socialhwk.com/engr370i/ch04/ch4_8/IMG00020.GIF [Broken] http://as370.socialhwk.com/engr370i/ch04/ch4_8/IMG00023.GIF [Broken] http://as370.socialhwk.com/engr370i/ch04/ch4_8/IMG00024.GIF [Broken] http://as370.socialhwk.com/engr370i/ch04/ch4_8/IMG00026.GIF [Broken] 3. The attempt at a solution I know R1 is 149,943,160 km and r2 is 228,189,693 km. However, I'm not sure what Gmp and therefore can't solve for V1 and V2. And even if I find out V1 and V2, how would I find out the semi-major axis? Or the aphelion or perihelion. Thanks a lot for your help!