A spacecraft is launched from a circular heliocentric orbit at 1.000 AU from the Sun into an elliptical heliocentric orbit that grazes Earth at aphelion and grazes Mercury's orbit at perihelion. Its mission is to match speeds with Mercury for the purpose of entering orbit about that planet. If the orbit is designed so that it grazes Mercury's orbit at Mercury's perihelion distance, the spacecraft will require a larger injection $\Delta V$, but it will overtake Mercury when Mercury is traveling faster, and therefore need a smaller second $\Delta V$ to match speeds. If it is instead targeted to intercept Mercury at aphelion, the launch from 1 AU circular orbit will be easier, but Mercury will be traveling slower when the spacecraft overtakes it. Which mission has the lower total $\Delta V$ requirement?