The unique advantages of fusion rocket propulsion systems for distant missions are explored using the magnetic dipole configuration as an example. The dipole is found to have features well suited to space applications. Parameters are presented for a system producing a specific power of 1 kW/kg, capable of interplanetary flights to Mars in 90 days and to Jupiter in 1 yr and of extra-solar-system flights to 1000 astronomical units (the Tau mission) in 20 yr. This is about ten times better specific power performance than nuclear electric fission systems. Possibilities to further increase the specific power toward 10 kW/kg are discussed, as is an approach to implementing the concept through proof testing on the moon.