Stephen Bluestone February 14 2008 Propulsion Propellants MAT

Stephen Bluestone February 14, 2008 Propulsion – Propellants – MAT Model Analysis & Moderate Thrust Engines AAE 450 Spring 2008 1

Model Analysis – Propellant – 5 kg Cost Ranges - Propellant - 5 kg $2 000 $1 800 000 $1 600 000 Total Cost $1 400 000 $1 200 000 Cryogenic Hybrid $1 000 Solid $800 000 Storable $600 000 $400 000 $200 000 $0 0 10 20 30 40 50 AAE 450 Spring 2008 Propulsion – Propellants 60 70 80 2

Moderate Thrust Engines § Increased modeling indicates potential need for higher thrust engines § Higher thrust will require heavier and larger engines Future Work § Detailed catalog of moderate thrust engines § Refined MAT work AAE 450 Spring 2008 Propulsion - Propellants 3

References § All charts created from data submitted by Model Analysis Teams. § Credit to Danielle Yaple for organizing the data and creation of 200 g chart (see slide 6) § Isakowitz, Steven J. , Hopkins, Joshua B. , Hopkins, Joshua P Jr. International Reference Guide to Space Launch Systems. Fourth Edition. AIAA, Reston, VA 2004 AAE 450 Spring 2008 4

Model Analysis – Propellant – 1 kg Cost Ranges - Propellant - 1 kg $1 800 000 $1 600 000 $1 400 000 Total Cost $1 200 000 $1 000 Cryogenic Hybrid $800 000 Solid Storable $600 000 $400 000 $200 000 $0 0 10 20 30 40 Axis Title 50 AAE 450 Spring 2008 60 70 80 5

Model Analysis – Propellant –. 2 kg Cost Ranges - Propellant - 200 g $ 1 600 000 $ 1 400 000 $ 1 200 000 Total Cost $ 1 000 Cryogenic Hybrid $ 800 000 Solid Storable $ 600 000 $ 400 000 $ 200 000 $0 10 20 Chart Created by Danielle Yaple 30 40 50 AAE 450 Spring 2008 60 70 80 6

Engine Name RL 10 A-4 -1 RL 10 A-4 -2 HM 7 B Vinci GEM 40 GEM 46 RL 10 B-2 Vehicle Atlas IIA/IIAS Atlas IIIA Atlas IIIB and V Ariane 5 ESC-A Ariane 5 ESC-B Delta II GEM 40 Delta Heavy II Delta IV-M Delta IV-H Delta II Star 48 B 7925, 7425, 7325 Star 37 FM Delta II 7326 LE-5 B H-IIA FG-46/Spa. B-17 LM-3 A, 3 B, 3 C Orion 50 XL Minotaur Orion 38 Pegasus Orion 50 XL Taurus HPM PSLV and GSLV KVD-1 PSLV and GSLV RL 10 A-3 -3 A Centaur SRM-1, Orbus 21 Titan Sr. M-2, Orbus 6 E Titan Zefiro 9 Vega S 40 VLS and VLM S 43 VLS and VLM Thrust (avg) Thrust (avg-sl) k. N 185. 2 198. 4 99. 2 198. 4 64. 8 180 446 499. 2 537. 7 608. 1 110 Propellant LOX/LH 2 LOX/LH 2 HTPB LOX/LH 2 Isp (vac) sec Isp (sl) sec 449 450. 5 445. 5 465 274 245. 4 224 242 462. 4 Expansion Ratio 85 85 83 240 10. 65 14 285 O-F 5. 5 4. 86 5. 8 N/A 5. 5 Burn time (nominal) sec 370 740 900 970 Throttle (Y/N) No No No 63. 3 75. 2 850 1125 No No 66. 4 45. 8 137 2 x 78. 5 154 47. 2 115 260 75 73 HTPB LOX/LH 2 HTPB LOX/LH 2 292. 2 291. 8 447 440 289 287 290. 2 295 460 444 54. 8 43. 7 110 80 58. 6 67. 5 65 69 200 61 N/A 5 5 N/A N/A 6 5 87. 1 66. 4 534 470 72. 5 68. 5 75. 1 115 500 600 No No Yes No No 186 HTPB 294 63. 8 N/A 153 No 76. 5 230 202 305 HTPB 289. 6 294 272 265 49. 3 56 26 12. 9 N/A N/A 104 117 58 60 No No AAE 450 Spring 2008 From International Reference Guide to Space Launch Systems 7