AAE450 Spring 2009 Launch Vehicle Selection Zarinah Blockton Mission Ops~Group Earth to LEO~Phase March 5, 2009

AAE450 Spring 2009 [Blockton] [OPS] Arbitrary Payload Case  Goal: Minimize $/kg to LLO (low lunar orbit)  Additional Launch Vehicles –Delta IV (All configurations) –Atlas V –Long March 2C, 2E –PSLV –Falcon 9 Heavy  Iterate between propulsion and mission ops code  Notables –Biggest assumption ~ structural mass scale-up –Parking orbit = 400 km –Time of Flight = 351 days

AAE450 Spring 2009 [Blockton] [OPS] LV Mass (kg) to LEO Thrust (mN) Number of Thrusters Mass (kg) to LLO($/kg) LL0 Dnepr , , Falcon , , Falcon 9 H , ,821.80

AAE450 Spring 2009 Back-up Slide [Blockton] [OPS] LVAltitude (km)Mass (kg)Thrust (mN) Number of Thrustersmdot_optMpay (kg) Power Required (W)Mprop (kg) Dnepr E-052, , Falcon E-066, , , Delta IV H E-0618, , , Atlas V E-067, , , LM 2C E-051, , LM 2E E-054, , , PSLV E-052, , Delta IV M E-066, , , Delta IV M(4,2) E-068, , , Delta IV M (5,2) E-067, , , Delta IV M (5,4) E-069, , , Falcon 9 H E-0622, , , Ares V E E E E+04

AAE450 Spring 2009 Back-up Slide LV2009 Launch CostTotal $ LLO($/kg) LL0($/kg) LEO Dnepr21,257, E+0712, , Falcon 938,201, E+076, , Delta IV H308,289, E+0817, , Atlas V122,699, E+0816, , LM 2C31,886, E+0723, , LM 2E70,858, E+0717, , PSLV44,194, E+0722, , Delta IV M161,427, E+0826, , Delta IV M(4,2)167,495, E+0819, , Delta IV M (5,2)182,060, E+0824, , Delta IV M (5,4)194,197, E+0820, , Falcon 9 H98,232, E+084, , Ares V500,000, E+086, , [Blockton] [OPS]

AAE450 Spring 2009 [Blockton] [OPS] Back-up Slide  Spring Calculation  PE = ½*k*x 2  KE = PE  KE = ½*m*v 2  V yf = V y0 – g moon *t  ∆x = V X0 *t

AAE450 Spring 2009 Spring Cannon Conclusions  100g case (7.6kg ball) For 1s impact time we can get to 720m and be under 30g's at impact For.5s impact we can get to 180m and be under 30g's at impact  10kg case (18.5kg ball) For 1s impact time we can get to 667m and be under 30g's at impact For.5s impact we can get to 148m and be under 30g's at impact  However if we launch to our maximum distance the length of the springs grows. Therefore here are my recommendations  100g case (7.6kg ball) D = 180m 30g's at launch 15g's at landing for 1s impact time 30g's at landing for 0.5s impact time 6m distance spring is extended  10kg case (18.5kg ball) D = m 30g's at launch 13g's at landing for 1s impact time 27g's at landing for 0.5s impact time 5m distance spring is extended I haven't found a spring that meets these requirements yet, however I think one could be custom made to meet our needs either in-house or through a contract company. If we can determine that using a spring that extends to a length over 6m is possible/feasible, then we could launch to a greater distance. As of right now the spring length and launch g's are the limiting factors in this design. [Blockton] [OPS]

AAE450 Spring 2009 [Blockton] [OPS] Back-up Slide Part #x(m)# Springsm (kg)t (s)D (m)Max Height (m)Takeoff G's Landi ng G’s (1s impact) Landing G's (0.5s impact) Spring 30 g's LHC 250U 08M kg case

AAE450 Spring 2009 [Blockton] [OPS] Back-up Slide Part #x(m)# Springsm (kg)t (s)D (m)Max Height (m)Takeoff G's Landi ng G’s (1s impact) Landing G's (0.5s impact) Spring 30 g's LHC 250U 08M g case