1. AAE450 Senior Spacecraft Design Fred Ricchio Week 6: February 22 nd, 2007 Propulsion Group MPD Thruster Design

2. AAE450 Senior Spacecraft Design MPD Current and Voltage Optimized Parameters –Specific impulse –Mass flow rate –Jet power Thruster Parameters –Outer electrode radius R2 –Inner electrode radius R1 Limitations –Electrode erosion occurs at high values of I sp Ricchio (1/4)

3. AAE450 Senior Spacecraft Design EP Trajectory Needs Ricchio (2/4) EP PathI sp (s)dm/dt (kg/s)P jet (MW)Current (A)Voltage (V) 173004.46 E -41.1410,233111.81 261007.73 E -41.3812,308112.37 3, 5, 750008.28 E -40.9911,53086.29 3a, 5a, 7a84002.53 E -40.868,264103.90 457008.84 E -41.3812,726108.57 673002.59 E -40.667,79085.11 873003.75 E -40.969,373102.41 9, 1350006.44 E -40.7710,17373.13 10, 1273002.28 E -40.587,30179.78 1150008.28 E -40.9911,53086.29 1465002.28 E -40.466,90067.13 15, 1671008.36 E -50.204,36646.39 17, 18, 1960008.00 E -41.3912,435111.68 20, 21, 2250001.64 E -40.205,12638.36

4. AAE450 Senior Spacecraft Design Calculations Ricchio (3/4)

5. AAE450 Senior Spacecraft Design References Humble, Ronald W., Henry, Gary N,, and Larson, Wiley J. Space Propulsion and Design, 1 st Edition-REVISED; New York, 1995 K. Toki and Y. Shimizu, Institute of Space and Astronautical Science, Kanagawa, Japan AIAA-2002-4115 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Indianapolis, Indiana, July 7-10, 2002 Ricchio (4/4)