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Thruster Principles 27 Using our previous example of a 10-deg half-angle beam divergence and a 10% doubles-to-singles ratio with a 90% propellant utilization of xenon [in Eq. (2.4-5)] at 1500 V, the Isp is 123.6*0.958*0.9* 1500 = 4127 s. Specific impulse is functionally equivalent to gas mileage in a car. Cars with high gas mileage typically don’t provide much acceleration, just as thrusters with high Isp don’t provide as much thrust for a given input electrical power. Of critical importance is the ratio of the thrust achieved to total power used, which depends on the electrical efficiency of the thruster (to be described in the next section). 2.5 Thruster Efficiency The mass utilization efficiency, defined in Eq. (2.4-6), describes the fraction of the input propellant mass that is converted into ions and accelerated in the electric thruster. The electrical efficiency of the thruster is defined as the beam power, Pb , out of the thruster divided by the total input power, PT : e = Pb = IbVb , (2.5-1) PT IbVb +Po where Po represents the other power input to the thruster required to create the thrust beam. Other power will include the electrical cost of producing the ions, cathode heater or keeper power, grid currents in ion thrusters, etc. The cost of producing ions is described by an ion production efficiency term, sometimes called the discharge loss: d = Power to produce the ions = Pd , (2.5-2) Current of ions produced Ib where d has units of watts per ampere (W/A) or equivalently electron-volts per ion (eV/ion). Contrary to most efficiency terms, it is desirable to have d as small as possible since this represents a power loss. For example, if an ion thruster requires a 20-A, 25-V discharge to produce 2 A of ions in the beam, the discharge loss is then 20*25/2 = 250 eV/ion. The performance of a plasma generator is usually characterized by plotting the discharge loss versus the propellant utilization efficiency. An example of this is shown in Fig. 2-3. At low propellant efficiencies, the neutral pressure in the thruster is high and the performance curves are relatively flat. As the propellant efficiency is increased, the neutral pressure in the thruster decreases, thePDF Image | Fundamentals of Electric Propulsion: Ion and Hall Thrusters
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