Page 259 - MEMS and Microstructures in Aerospace Applications

Osiander / MEMS and microstructures in Aerospace applications DK3181_c011 Final Proof page 250 1.9.2005 12:31pm

250 MEMS and Microstructures in Aerospace Applications

TABLE 11.5
Performance Characteristics for Micro-Ion Engine

I sp 3184s
I-bit (if pulsed) DC
Rep. rate (if pulsed) DC
Power 43 W
Thrust 1.5 mN
Thrust or power 35 mN/W
Impulse or prop. 32.8 g
Feed mechan. Gas

needed and the minimum electron travel distance required for ionization, a pure
MEMS manufactured ion thruster does not appear possible. A summary of the
micro-ion engine is shown in Table 11.5, with a picture of the complete system
shown in Figure 11.14.

11.2.6 MICRO-RESISTOJET
Resistojets have a long-standing history in space propulsion. 32–37 Because of their
simplicity, they have become a workhorse of space propulsion. In principle these

FIGURE 11.14 Micro ion thruster. (Source: NASA.)

© 2006 by Taylor & Francis Group, LLC