1. AAE450 Senior Spacecraft Design Fred Ricchio Week 2: January 25 th, 2007 Propulsion Team Magnetoplasmadynamic (MPD) Thruster Performance Projections

2. AAE450 Senior Spacecraft Design MPD Analysis Power Requirement –P = 2.5 MW Specific Impulse –I sp = 6,000 s Power Efficiency –η = 0.7 Specific Mass –α = ~0.275 kg/kW Burn Time –t b = 200 d Propellant Mass –m prop = 17,457 kg Gilland, et al. STAIF 2006

3. AAE450 Senior Spacecraft Design Deliverable Payloads Mission PhaseΔv (km/s)M PL /M o HMO to MS3.10.95 LEO to HEO*6.80.89 HEO to MS10.40.84 HEO to HMO*11.30.83 LEO to MS13.20.80 LEO to HMO18.60.73

4. AAE450 Senior Spacecraft Design Calculations Propellant Mass Payload Ratio

5. AAE450 Senior Spacecraft Design References Gilland, James, McGuire, Melissa, Corle, Tyacie, and Clem, Michelle. Mission Performance of High-Power Electromagnetic Thruster Systems. Space Technology and Applications International Forum, American Institute of Physics, Albuquerque, New Mexico, February 12-16, 2006. Sutton, George P. and Biblarz, Oscar. Rocket Propulsion Elements, Seventh Edition. Wiley Interscience, New York, 2001