Moon & Mars Orbiting Spinning Tether Transport - Tethers Unlimited

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Payload Accommodation AssemblyConfiguration Drivers• Mimic Conventional Upper Stage InterfacesTo Payload And Booster• Track Grapple And Make RendezvousCorrections• Provide Circularization ∆VPayload with PAA• 1.9 m Dia x 1 M Long• 12 Thrusters, 0.7 M Dia Fuel Tank• 2 Primary Batteries• Communications & Guidance Systems• 3 Reaction WheelsTUI/MMOSTT 18
Baseline Orbital Design• Payload and Tether inSynchronous Orbits– Periodic RendezvousOpportunities• Design Accounts for:– Precessions Due to EarthOblateness– Tether Taper– Center of Mass ShiftsSystem Masses Tether CharacteristicsTether mass 8,274 kg Tether Length 100,000 mCS Active Mass 11,507 kg Tether mass ratio 3.31CS Ballast Mass 3490 kg Tether tip velocity at catch 1,267 m/sGrapple mass 650 kg Tether tip velocity at toss 1,147 m/sTotal Facility Mass 23,922 kg Tether angular rate 0.015515 rad/sGravity at Control Station0.64 gTotal Launch Mass 20,432 kg Gravity at payload 1.81 gRendezvous acceleration2.00 gPayload Mass2,500 kgPre-CatchJoinedSystem Post-TossPositions & Velocities Payload Tether Post-catch Tether Payloadresonance ratio 4 1 2 0 1 4.1perigee altitude km 325 407 399 391 473apogee altitude km 325 8445 7199 6104 35783perigee radius km 6703 6785 6777 6769 6851apogee radius km 6703 14823 13577 12482 42161perigee velocity m / s 7711 8978 8858 8738 10005apogee velocity m / s 7711 4109 4422 4739 1626CM dist. From Station m 18362 26087 18362CM dist. To Grapple m 81638 73913 81638∆V to Reboost m / s 240∆V to Correct Apogee m / s 0∆V to Correct Precess. m / s 0∆V To Circularize m / s 1449Basic Orbital Parameterssemi-major axis km 6703 10804 10177 9626 24506eccentricity 0.0 0.372 0.334 0.297 0.720inclination rad 0 0 0 0 0semi-latus rectum km 6703 9309 9041 8778 11787sp. mech. energy m2/s2 -2.97E+07 -1.84E+07 -1.96E+07 -2.07E+07 -8.13E+06vis-viva energy m2/s2 -5.95E+07 -3.69E+07 -3.92E+07 -4.14E+07 -1.63E+07period sec 5462 11176 10218 9399 38178period min 91.0 186.3 170.3 156.6 636.3station rotation period sec 405.0 405.0 405.0rotation ratio 27.6 25.2 23.2TUI/MMOSTT 19
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Tethers Unlimited, Inc.MMOSTT Final
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NIAC Funded Tether Research• Moon
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Electrodynamic Reboost• Power sup
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Cislunar Tether Transport System•
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MXER Tethers Included in NASA’sII
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5mt Payload Tether Boost Facilityfo
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LEOGTO Boost Facility• Initial Fa
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Tether Boost FacilityControl Statio
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LEOGTO Boost Facility• TetherSim
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Rendezvous• Rapid AR&C Capability
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Proposed RETRIEVE TetherExperiment
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µTORQUE on Delta IV• Delta-IV Se
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Opportunities for NASATechnology De
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AIAA 2000-3842COMMERCIAL DEVELOPMEN
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--Commercial Tether Transport AIAA
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-Commercial Tether Transport AIAA 2
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Commercial Tether Transport AIAA 20
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Commercial Tether Transport AIAA 20
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Momentum Exchange/Electrodynamic Re
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DESIGN AND SIMULATION OF A TETHER B
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Tether Boost Facility Design AIAA 2
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Tethers Unlimited, Inc.Cislunar Tet
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Interim Report Outline- Configurati
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Mission Definition¥ Payload Capaci
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Baseline Control Station DetailsTET
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Baseline Grapple AssemblyCAPTURES A
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LEO Facility System ArchitectureGRA
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Payload Adapter Assembly Subsystems
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Potential Reeling FunctionsReeling
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LEO Control Station Weights16
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Payload Adapter Assembly Weights18
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Tether Boost FacilityRequired Power
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Electrical Propulsion Voltage´ Spe
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Potential Reeling FunctionsReeling
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Preliminary Reeling AnalysisθθAss
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Tether Boost FacilitySystem Require
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Table of Contents1 Scope ..........
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2 ReferencesThis section lists docu
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The system shall measure and contro
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4 Ground Rules & AssumptionsThis se
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Appendix F: Tether Boost Facility D
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Appendix F Tether Boost Facility De
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Appendix F Tether Boost Facility De
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Appendix L: Tether Boost Facility D
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Page 172 and 173: Appendix L: Tether Boost Facility D
Page 194 and 195: Tethers Unlimited, Inc.Tether Rende
Page 206 and 207: Ongoing Tether Work Under NIAC Fund
Page 208 and 209: Cislunar Tether Transport System•
Page 210 and 211: Rapid Earth-Mars Transport• Reusa
Page 212 and 213: EarthMars Launch Windows• MMOSTT
Page 214 and 215: Incremental Development Path1. TORQ
Page 216 and 217: LEOGTO Boost Facility• TetherSim
Page 218 and 219: Tether Boost FacilityControl Statio
Page 220 and 221: Modular Design• Design Components
Page 224 and 225: Electrodynamic Thrusting• Drive c
Page 226 and 227: Tether Facility Reboost• Use Elec
Page 228 and 229: Rendezvous• Rapid Automated Rende
Page 230 and 231: Rendezvous Method: Preparation• P
Page 232 and 233: Development Issues• Automated Ren
Page 234 and 235: Potential Flight Experiments• Hig
Page 236 and 237: Opportunities for NASATechnology De
Page 238 and 239: Acknowledgements• Boeing/RSS - Jo
Page 240 and 241: IAF-99-A.5.10RAPID INTERPLANETARY T
Page 242 and 243: Rapid Interplanetary Tether Transpo
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IAF-00-S.6.04TETHER SYSTEMS FOR SAT
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IAF-00-S.6.04controlled very precis
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IAF-00-S.6.04Perigee Altitude (km)3
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IAF-00-S.6.04The LEO⇒GTO Tether B
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IAF-00-S.6.04AcknowledgmentsThis re
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Tethers Unlimited, Inc.Appendix K:
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Tethers Unlimited, Inc.at a rate of
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Tethers Unlimited, Inc.Appendix L -
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Tethers Unlimited, Inc.Appendixm M:
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Appendix N. MXER Tether for Deployi
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Electrodynamic Thrustingto Reboost
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100000 95000 90000 85000 80000 7500
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Momentum Exchange/Electrodynamic Re
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NOMENCLATURESymbol MeaningA payload
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DepartureangleA = 1.5π - (ω + u
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Tether material has a "characterist
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Rendezvous of Grapple with PayloadT
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adius vector to the new center of m
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days from payload pickup at one pla
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"JupiterandBeyond"Tether cut CUT:<
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Tethers Unlimited, Inc.Appendix Q:
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Tethers Unlimited, Inc.Appendix R:
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