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                   242                       MEMS and Microstructures in Aerospace Applications


                   With the radius of curvature of such a cone being approximately 10 –7  m and the
                   electrodes being 1 mm apart, voltages of the order of kilovolts are sufficient to obtain
                   the necessary high electric fields. Applying voltages of few kilovolts (5–7 kV) results
                   in ion currents of 10–100 mA from a single needle source with low energy spread.
                       The thrust can be calculated directly (for Gallium) from the following equa-
                   tions:
                                                  T ¼ _ mmv                     (11:12)

                                                      m Ga
                                                 _ m m ¼ I E                    (11:13)
                                                       e
                                                    r ffiffiffiffiffiffiffiffi
                                                       eV
                                                 v ¼                            (11:14)
                                                      m Ga
                                                   r ffiffiffiffiffiffiffiffi
                                                     m Ga  p ffiffiffiffi
                                             ) T ¼       I E V                  (11:15)
                                                      e
                   where
                     T ¼ thrust (N),
                     m ˙ ¼ mass flow (kg/sec),
                     v ¼ velocity (m/sec),
                     I E ¼ emission current (A),
                     V ¼ extraction voltage (V),
                     e ¼ 1.6 10 –19  C, and
                     m Ga ¼ 1.16 10 –25  kg

                   While this calculation does not account for the beam spread it will nevertheless
                   result in a close (80%) estimate of the thrust produced. Small thrust noise and very
                   stable operation are characteristics of this propulsion system. High mass efficien-
                   cies for FEEP thrusters can be obtained at small extraction currents on the order of a
                   few microamperes. At higher extraction voltages, which translate into higher
                   currents, droplets and clusters are formed, which obtain significantly smaller
                   exhaust velocities and, therefore, lead to lower system efficiency.

                   11.2.3.2  System Requirements
                   The FEEP thruster is a very capable low-thrust, low-noise system. Reported
                   efficiency and thrust-to-power ratios are high and the possibility of MEMS-produced
                   ion sources exist. These MEMS structures are based on the usage of a large number of
                   emission sites. First concepts have been evaluated using microtips immersed in liquid
                   metal as emission sites as shown in Figure 11.9. Another approach involves the use of
                   small tubes that lead the liquid metal with the help of capillary forces from a bulk
                   reservoir to the emission site. Highly accurate manufacturing is necessary as small
                   geometrical differences result in the formation of so-called hot spots, where individ-
                   ual pixels attract the majority of the emission current, which can lead to unwanted





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