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32 Chapter 2 500 W, the other power levels are relatively insignificant. However, the thruster will have to be of sufficient size to radiate all this power to space at a reasonable temperature that the materials and construction are designed to handle. Unlike ion thrusters, power dissipation in Hall thrusters is not easily obtained from the external power supply readings. However, two techniques can be used to estimate the dissipated power. First, the dissipated power can be inferred from measurements of the thruster efficiency and the beam power (ion current and energy), which involves calculating the difference between the total beam power and the input electrical power. Another technique is to assume that the dissipated power is primarily the loss due to the electron current flowing from the exterior cathode through the thruster to the high voltage anode. If the fraction of the discharge current that becomes beam ions can be determined from the external diagnostics, then the difference between the discharge current and beam current times the discharge voltage is approximately the dissipated power. This technique neglects the ionization power and energy carried by the electrons in the beam, and so produces only a rough estimate. Hall thruster efficiency and performance useful in determining the power dissipation are described in detail in Chapter 7. 2.7 Neutral Densities and Ingestion in Electric Thrusters In electric propulsion thrusters, the propellant is injected as a neutral gas into a chamber or region where ionization takes place. Accurately knowing the flow rate of the propellant gas is important in determining the performance and efficiency of the thruster and allows the operator to find the impact of finite pumping speed of test chambers on the thruster operation. The gas flow into the thruster, which is sometimes called the throughput, is often quoted in a number of different units. The most common units are standard cubic centimeters per minute (sccm) for ion thrusters and mg/s for Hall thrusters. Additional flow rate units include atoms per second, equivalent amperes, and torr-liter per second (torr-l/s). Conversion factors between these systems of flow units are derived in Appendix B. The neutral pressure in the thruster discharge chamber or in the vacuum system follows standard gas law [1,2]: PV = N k T , (2.7-1) where P is the pressure in pascals, V is the volume, N is the number of particles, k is Boltzman’s constant (1.38 10–23 W/s/K), and T is the temperature in kelvins. Since there are 133.32 pascals per torr, the number density of the neutral gas isPDF Image | Fundamentals of Electric Propulsion: Ion and Hall Thrusters
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