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Interstellar Probe on Space Launch System (Sls)

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Interstellar Probe on Space Launch System (Sls) INTERSTELLAR PROBE ON SPACE LAUNCH SYSTEM (SLS) David Alan Smith SLS Spacecraft/Payload Integration & Evolution (SPIE) NASA-MSFC December 13, 2019 0497 SLS EVOLVABILITY FOUNDATION FOR A GENERATION OF DEEP SPACE EXPLORATION 322 ft. Up to 313ft. 365 ft. 325 ft. 365 ft. 355 ft. Universal Universal Launch Abort System Stage Adapter 5m Class Stage Adapter Orion 8.4m Fairing 8.4m Fairing Fairing Long (Up to 90’) (up to 63’) Short (Up to 63’) Interim Cryogenic Exploration Exploration Exploration Propulsion Stage Upper Stage Upper Stage Upper Stage Launch Vehicle Interstage Interstage Interstage Stage Adapter Core Stage Core Stage Core Stage Solid Solid Evolved Rocket Rocket Boosters Boosters Boosters RS-25 RS-25 Engines Engines SLS Block 1 SLS Block 1 Cargo SLS Block 1B Crew SLS Block 1B Cargo SLS Block 2 Crew SLS Block 2 Cargo > 26 t (57k lbs) > 26 t (57k lbs) 38–41 t (84k-90k lbs) 41-44 t (90k–97k lbs) > 45 t (99k lbs) > 45 t (99k lbs) Payload to TLI/Moon Launch in the late 2020s and early 2030s 0497 IS THIS ROCKET REAL? 0497 SLS BLOCK 1 CONFIGURATION Launch Abort System (LAS) Utah, Alabama, Florida Orion Stage Adapter, California, Alabama Orion Multi-Purpose Crew Vehicle RL10 Engine Lockheed Martin, 5 Segment Solid Rocket Aerojet Rocketdyne, Louisiana, KSC Florida Booster (2) Interim Cryogenic Northrop Grumman, Propulsion Stage (ICPS) Utah, KSC Boeing/United Launch Alliance, California, Alabama Launch Vehicle Stage Adapter Teledyne Brown Engineering, California, Alabama Core Stage & Avionics Boeing Louisiana, Alabama RS-25 Engine (4) Aerojet Rocketdyne = In Progress California, Mississippi = Completed 0676 ARTEMIS I SOLID ROCKET BOOSTERS COMPLETE 0458 ARTEMIS I RS-25 FLIGHT ENGINES COMPLETE 0676 SLS PROGRESS TOWARD ARTEMIS I: FLIGHT ARTICLES 0689 ARTEMIS I CORE STAGE ASSEMBLED 0458 CORE STAGE STRUCTURAL TESTING 0676 AN INTERSTELLAR ROCKET 0497 SLS BLOCK 1B CARGO CONFIGURATION 8.4m Fairing, Short Primary Payload Payload Adapter (PLA) Solid Rocket Booster (2) RL10 Engine (4) Exploration Upper Stage (EUS) Interstage Core Stage RS-25 Booster Engine (4) 0497 SLS VEHICLE AND PERFORMANCE Block 2 Block 1B Block 1B evolution path: Block 1 • Initial configuration (2025) – Heritage RS-25 running at 109% RPL • Intermediate (2026-2028) – New production RS-25 engines running at 111% RPL • Final (2029-??) - New production RS-25 engines and enhanced performance boosters Vehicle Predicted Performance • Predicted masses for all elements • Nominal performance for RS25s and RL10s • Booster performance quoted for February temperatures • Manager’s reserve is held back SLS Block 1B future upgrades further increase performance SLS quoted performance is conservative 0497 RECENT DEVELOPMENTS Block 2 Block 1B Block 1 Block 1B vehicle updates • EUS is now optimized for lunar destinations • Additional system mass savings, flight techniques and other propulsion system enhancements were implemented • Payload cryogenic propellant loading is currently planned for the Block 1B Mobile Launch Platform (MLP) Block 1B Booster Obsolescence and Life Extension (BOLE) • Design Analysis Cycle 1 (DAC1) is underway • Following results reflect the updated booster design Look for an announcement later today about SLS 0497 SLS C3 PERFORMANCE Block 2 Block 1B Block 1 SLS performance is optimized for lunar destinations Additional stages are needed for higher C3 destinations 0497 ADDITIONAL STAGES FOR HIGHER C3 DESTINATIONS • Manager’s Reserve – Allocated across all upper stages (incl. EUS) based on the stage wet mass – Approach preserves staging benefits at varying C3s • Fairing: – All 3rd and 4th stages are encapsulated under the 8.4m short Payload Fairing (PLF) – Minimizes the risk of stage requalification – Removes alternate configurations for the SLS vehicle (OML changes) • Upper stages: – Existing stages in production – Estimated Flight Performance Reserve – Solid performance nominal – 3rd Stages Assessed: • Castor 30B (NGIS provided data) • Castor 30XL (NGIS provided data) • Centaur (Government Estimate) – 4th Stages Assessed: • Star 48 BV (NGIS provided data) • Star48 GXV (NGIS provided data) • Stage adapters: – Sized with NASA MSFC sizing tool, Launch Vehicle Analysis (LVA) • 35 years of heritage – Composite Adaptor (CF +Al-HC) with interface rings – 18% MGA Using existing hardware and a low risk engineering approach 0575 UPDATED C3 PERFORMANCE Spacecraft 4th Stage 3rd Stage SLS EUS & Adapter New Horizons 2 3 1 Low C3 Range High C3 Range 1) Passive Jupiter Flyby 2) Jupiter Powered Flyby 3) Solar Oberth Maneuver REPRESENTATIVE TRAJECTORY Recall Specific Energy of the Orbit Centaur Burn = = Star48BV Burn EUS Separation E 2 +∆ 퐶 The deeper in the gravity well the maneuver 2 2 the greater the increase in orbital− energy (Oberth Effect) Centaur Separation EUS Ascent Burn nd EUS Parking Orbit (1rev) EUS 2 Burn Core Stage Separation EUS Orbit Insertion Core Stage Flight EUS Separation SLS CAN ENABLE BREAKTHROUGH SCIENCE MISSIONS • SLS is America’s heavy-lift vehicle for strategic human exploration and scientific missions • Manufacturing is complete for the first flight; SLS is nearing the integration phase • SLS has a flexible architecture and an evolvable upgrade path • Discussions with the science community are ongoing to determine how SLS can enable breakthrough science missions, such as sending a probe to interstellar space 0575 0575.
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