Transcription of SpaceX Propulsion
1 SpaceX Propulsion Tom Markusic Space Exploration Technologies 46th AIAA/ASME/SAE/ASEE. Joint Propulsion Conference July 28, 2010. Friday, August 6, 2010. SpaceX Propulsion Tom Markusic Space Exploration Technologies 46th AIAA/ASME/SAE/ASEE. Joint Propulsion Conference July 28, 2010. Friday, August 6, 2010. Overview Inverse Hyperbolic Bessel Functions Friday, August 6, 2010. Near-term Propulsion Needs Friday, August 6, 2010. Near-term Propulsion Needs HLLV Propulsion Merlin 2 uses scaled-up, flight proven Merlin 1 design J-2X SpaceX can develop and flight qualify the Merlin 2 engine in ~3.
2 Years at a cost of ~$1B. Production: ~$50M/engine J-2X development already in progress under Constellation Merlin 2 J-2X. program Propellant LOX/RP LOX/LH2. Merlin 2 Thrust (vac) [klbf] 1,700 292. Isp (vac) [sec] 322 448. T/W [lbf/lbm] 150 55. Friday, August 6, 2010. Near-term Propulsion Needs HLLV Propulsion Solar Electric Propulsion for Cargo Tug Merlin 2 uses scaled-up, flight Cluster of ~5 high TRL thrusters proven Merlin 1 design NEXT process 100 kWe solar power J-2X SpaceX can develop and flight Ion Thruster Next generation tug uses single qualify the Merlin 2 engine in ~3 high power thruster, such as NASA.
3 Years at a cost of ~$1B. 457M. Production: ~$50M/engine Third generation tug uses nuclear J-2X development already in electric Propulsion at megawatt progress under Constellation levels NEXT BHT-20 457M. Busek BHT-20K k Merlin 2 J-2X Propellant Xenon Xenon Xenon program Hall Thruster Propellant LOX/RP LOX/LH2 Power [kWe] 7 20 96. Merlin 2 Thrust (vac) [klbf] 1,700 292. Thrust [mN] 236 1080 3300. Isp (vac) [sec] 322 448. NASA 457M Isp [sec] 4100 2750 3500. T/W [lbf/lbm] 150 55 Hall Thruster Efficiency [%] 70 72 58. Friday, August 6, 2010. Near-term Propulsion Needs HLLV Propulsion Solar Electric Propulsion for Cargo Tug Merlin 2 uses scaled-up, flight Cluster of ~5 high TRL thrusters proven Merlin 1 design NEXT process 100 kWe solar power J-2X SpaceX can develop and flight Ion Thruster Next generation tug uses single qualify the Merlin 2 engine in ~3 high power thruster, such as NASA.
4 Years at a cost of ~$1B. 457M. Production: ~$50M/engine Third generation tug uses nuclear J-2X development already in electric Propulsion at megawatt progress under Constellation levels NEXT BHT-20 457M. Busek BHT-20K k Merlin 2 J-2X Propellant Xenon Xenon Xenon program Hall Thruster Propellant LOX/RP LOX/LH2 Power [kWe] 7 20 96. Merlin 2 Thrust (vac) [klbf] 1,700 292. Thrust [mN] 236 1080 3300. Isp (vac) [sec] 322 448. NASA 457M Isp [sec] 4100 2750 3500. T/W [lbf/lbm] 150 55 Hall Thruster Efficiency [%] 70 72 58. Nuclear Thermal Propulsion for Mars Stage NERVA derived technology Total thrust ~ 60 klbf, using 2 to 6.
5 NDR. Propellant: hydrogen, Isp ~ 930 sec ISRU or pre-deployed propellant for return mission Technology has been verified with >17. Hours of hot-fire tests, including restarts. No additional developmental, terrestrial tests (with nuclear) fuel are required. Extensive Russian knowledge can be leveraged. Friday, August 6, 2010. Near-term Propulsion Needs HLLV Propulsion Solar Electric Propulsion for Cargo Tug Merlin 2 uses scaled-up, flight Cluster of ~5 high TRL thrusters proven Merlin 1 design NEXT process 100 kWe solar power J-2X SpaceX can develop and flight Ion Thruster Next generation tug uses single qualify the Merlin 2 engine in ~3 high power thruster, such as NASA.
6 Years at a cost of ~$1B. 457M. Production: ~$50M/engine Third generation tug uses nuclear J-2X development already in electric Propulsion at megawatt progress under Constellation levels NEXT BHT-20 457M. Busek BHT-20K k Merlin 2 J-2X Propellant Xenon Xenon Xenon program Hall Thruster Propellant LOX/RP LOX/LH2 Power [kWe] 7 20 96. Merlin 2 Thrust (vac) [klbf] 1,700 292. Thrust [mN] 236 1080 3300. Isp (vac) [sec] 322 448. NASA 457M Isp [sec] 4100 2750 3500. T/W [lbf/lbm] 150 55 Hall Thruster Efficiency [%] 70 72 58. Nuclear Thermal Propulsion for Mars LOX/Methane Propulsion for Ascent/Desc Stage NERVA derived technology ISRU-derived methane will be used for ascent/descent Total thrust ~ 60 klbf, using 2 to 6 Propulsion NDR Strong developmental programs currently underway at Propellant: hydrogen, Isp ~ 930 sec Aerojet, ATK/XCOR.
7 ISRU or pre-deployed propellant for return SpaceX Merlin 1 engine may be reconfigurable to for LOX/. mission methane, providing a large (~100 klbf) GG cycle engine for Technology has been verified with >17 ascent/descent Hours of hot-fire tests, including restarts. No additional developmental, terrestrial tests (with nuclear) fuel are required. Extensive Russian knowledge can be leveraged. Aerojet, T = k-lbf, Isp = ATK/XCOR, T = k-lbf, Isp 350 sec =? Friday, August 6, 2010. Friday, August 6, 2010. Testing Survey This slide may contain SpaceX proprietary and/or ITAR sensitive content.
8 Friday, August 6, 2010. Friday, August 6, 2010. Raptor Friday, August 6, 2010. HLLV 1st Stage Propulsion LOX/RP versus LOX/LH2 Booster Fundamentals Simple 1-D dynamic model used to compare LOX/RP and LOX/LH2 first stage performance for a HLLV. First, for both propellants, propellant mass was chosen to yield the same V ( km/s) for a given payload ( 750 MT), consistent with Saturn V, but with no external forces. Typical engine performance and tank mass fractions assumed. Initial T/W fixed at for both cases. Ballistic trajectory. Equations of motion again integrated using assumptions and boundary conditions above, but with gravity and aerodynamic drag included.
9 Friday, August 6, 2010. HLLV 1st Stage Propulsion LOX/RP versus LOX/LH2 Booster Fundamentals Trade Studies Simple 1-D dynamic model used to compare LOX/RP and Recent NASA-led Heavy Lift Launch Vehicle Study . LOX/LH2 first stage performance for a HLLV compared many configurations of LOX/LH2, LOX/RP, SRB. First, for both propellants, propellant mass was Propulsion for a HLLV. chosen to yield the same V ( km/s) for a given Configuration with 6 Lox/RP engine first stage payload ( 750 MT), consistent with Saturn V, but competitive with all concepts in performance and with no external forces.
10 Mission capture metrics Typical engine performance and tank mass Configuration with 6 Lox/RP engine first stage fractions assumed. shown to provide benefits in safety and annual Initial T/W fixed at for both cases. Ballistic Operations recurring cost metrics above all LOX/LH2 and SRB. trajectory. Handling. configurations Equations of motion again integrated using Deep cryogenic (-432 F) vs room temperature for RP. assumptions and boundary conditions above, but LH2 has high infrastructure investment for test and launch with gravity and aerodynamic drag included. Safety.
