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36 Chapter 2 6. 7. a. What is the thrust-to-power ratio (usually expressed in mN/kW) for each thruster? b. What is the Isp for each engine? c. For a 1000-kg spacecraft, what is the fuel mass required to achieve a 5-km/s delta-v? d. What is the trip time to expend all of the fuel for each thruster type if the thrusters are on 90% of the time? The thrust correction factor for multiply ionized species is based on the current of charges in the beam (see Eq. (2.3-12) for singles and doubles). a. Derive an expression for the number of atoms of each ionized species in the beam for a given value of I++/I+ and I+++/I+. b. If I++/I+ = 10% and I+++/I+ = 5%, what are the actual percentages of the number of atoms of each species in the beam compared to the total beam current? An ion thruster is being tested in a vacuum chamber with a measured xenon pressure of 1 10–5 torr at room temperature (300°C). The thruster grids have a 25-cm grid diameter and a Clausing factor of 0.5. a. If the thruster is producing a 3-A beam with 15% double ions with a total of 50 sccm of xenon gas flow into the thruster, what is the mass utilization efficiency neglecting gas ingestion? b. What is the mass utilization efficiency including the effects of ingestion?PDF Image | Fundamentals of Electric Propulsion: Ion and Hall Thrusters
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