Ok, say there is a space probe orbitting the sun at 1 AU and it needs to be put in an orbit that will encounter mars using the least amount of energy. The orbit hsa perihelion at earths orbit and apelion at mar's orbit. In the problem we are asked to solve for stuff like the eccentricity of the orbit and change in orbital velocity to achieve the orbit. No need to do the question for me, but I'm just a little confused about what information we can get from the original question. Seems like it's not enough information to solve the problems. Any ideas on what I'm missing? thanks.