1. AAE450 Spring 2009 Tony Cofer Power Group TLI Phase 03/05/09 Power Limitations for Arbitrary Payload Tony Cofer] [Power] page 1

2. AAE450 Spring 2009 Assumptions  Arrays no larger than those on ISS 34 m X 12m  No active structures i.e. configuration changes  Arrays must be symmetric about center of mass  Must be single wing design to avoid over - shadow [Tony Cofer] [Power] Page 2

3. AAE450 Spring 2009 Max Payload Sizes [Tony Cofer] [Power] Page 3 Launch Vehicle Max Power (kW) Max Payload to LEO (kg) Max OTV wet mass + Payload from LEO to LLO (kg) Max Payload to LLO (kg)recommend Dnepr454,40012,7304,023 X Falcon 9122.69,90034,02710,750 X Falcon 9H25227,50073,44022,100 X Titan iv23021,00066,09620,300 X Ares V252188,00073,44022,100

4. AAE450 Spring 2009 Backup slide  Ratio OTV to total length = 0.42  Power to wet LEO to LLO mass = 3.5 W/kg  Power to payload mass = 11.4 W/kg  Power per area = 300 W/m^2 [Tony]Cofer [Power] Page 3

5. AAE450 Spring 2009 Backup Slide ISS Arrays  34 X 12 m per wing  Stows 0.51m X 4.57m X 12m  Two rows per wing  32.8 kW per wing [Tony Cofer] [Power] Page 4

6. AAE450 Spring 2009 Backup Slide [Tony Cofer] [Power] Page 5 Launch Vehicle max payload to LEO (kg) Fairing length (m) OTV length (m) Max. Power (kW) Max OTV wet mass + Payload from LEO to LLO (kg) Max Payload to LLO (kg) Dnepr4,4005.22.18444553.612729.63908.211 Falcon 99,90013.95.838119095.234027.210446.95 Falcon 9H27,50041.717.5142570407344022547.37 Titan iv21,0002711.342313366609620292.63 Ares v188,0003012.62570407344022547.37