Figure 10.11 shows that for electrical propulsion withthe optimum specific impulse would b...

Figure 10.11 shows that for electrical propulsion with

the optimum specific impulse would be about 2000 s, which is too high for chemical rockets and too low for ion thrusters. The∆u was calculated for a one-month earth-moon transfer. Using the data of Table 10.8 and assuming α/η = 10 kg/kW, determine the optimum specific impulse for a 0.7-year transfer from low earth orbit (LEO) to Mars orbit.