Moon & Mars Orbiting Spinning Tether Transport - Tethers Unlimited

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LEOGTO Boost Facility• Initial Facility Sized to Boost 2500 kg Payloads to GTO• First Operational Capability Can Be Launched on 1 Delta IV-H• Modular Design Enables Capability to be Increased• Top Level Mission Requirements:RequirementPayload MassPickup orbitRelease orbitRelease insertion errorPayload environmentTurnaround timeMission lifeCollision avoidanceOperational orbit lifetimePayload pickup reliability2500 kg at IOC, can grow to followmarket300 km equatorialGTO< Delta IV/Ariane 5< Delta IV/Ariane 530 days10 years +100% of tracked spacecraft15 days99%ValueTUI/MMOSTT 12
Mass Properties BreakdownControl StationMass: 10,967 kgTether Mass:LEO Control StationThermal Control SubsysQty1RedundancyMassContingency15%Unitmass(kg)Mass withno margin(kg)109671104.5Mass withContingency(kg)132671270.1MassMargin(kg)2300165.78,274 kgCabling/HarnessesStructure33%25%749.62721.1997.03401.3247.4680.3Grapple Mass:650 kgGLOW: 19,891 kg– 15% margin w/in DeltaIV-H payload capacityElectr.Pwr.PV array panelsPower StoragePV array drive motorsPMADDownlink Comm SubsysDownlink TransceiverDownlink antennaeTFS Net Comm Subsys11811211222113%15%13%13%13%13%1782.92860.53.022.70.70.24736.71782.92860.548.045.41.81.40.51.85409.62014.63289.554.251.32.11.560.512.1673.00.20.2Expended Upper Stage3,467 kgC&DHComm. antennaeTransceiverComputer21112213%13%13%0.20.713.00.51.426.026.00.511.629.429.43.4TT&C6.97.80.9On-Orbit Mass:ADCStransponder1213%3.56.9200.97.8213.812.923,358 kgED Tether Power SubsysPlasma Contactor (FEAC)1225%45.4417.490.8603.4113.5186.0PMAD/PCUt1250%163.3326.6489.9Docking & I/C Subsys0.50.540.04Beacon118%0.50.50.54Tether Deploy & Control1000.01330.0330.00TUI/MMOSTT 13Tether reeling assembly1133%1000.01000.01330.0
Page 2 and 3: Tethers Unlimited, Inc.MMOSTT Final
Page 24 and 25: NIAC Funded Tether Research• Moon
Page 26 and 27: Electrodynamic Reboost• Power sup
Page 28 and 29: Cislunar Tether Transport System•
Page 30 and 31: MXER Tethers Included in NASA’sII
Page 32 and 33: 5mt Payload Tether Boost Facilityfo
Page 36 and 37: Tether Boost FacilityControl Statio
Page 38 and 39: LEOGTO Boost Facility• TetherSim
Page 40 and 41: Rendezvous• Rapid AR&C Capability
Page 42 and 43: Proposed RETRIEVE TetherExperiment
Page 44 and 45: µTORQUE on Delta IV• Delta-IV Se
Page 46 and 47: Opportunities for NASATechnology De
Page 48 and 49: AIAA 2000-3842COMMERCIAL DEVELOPMEN
Page 50 and 51: --Commercial Tether Transport AIAA
Page 52 and 53: -Commercial Tether Transport AIAA 2
Page 54 and 55: Commercial Tether Transport AIAA 20
Page 56 and 57: Commercial Tether Transport AIAA 20
Page 58 and 59: Momentum Exchange/Electrodynamic Re
Page 60 and 61: DESIGN AND SIMULATION OF A TETHER B
Page 62 and 63: Tether Boost Facility Design AIAA 2
Page 70 and 71: Tethers Unlimited, Inc.Cislunar Tet
Page 82 and 83: 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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Tethers Unlimited, Inc.Tether Rende
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Ongoing Tether Work Under NIAC Fund
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Cislunar Tether Transport System•
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Rapid Earth-Mars Transport• Reusa
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EarthMars Launch Windows• MMOSTT
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Incremental Development Path1. TORQ
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LEOGTO Boost Facility• TetherSim
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Tether Boost FacilityControl Statio
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Modular Design• Design Components
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Payload Accommodation AssemblyConfi
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Electrodynamic Thrusting• Drive c
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Tether Facility Reboost• Use Elec
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Rendezvous• Rapid Automated Rende
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Rendezvous Method: Preparation• P
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Development Issues• Automated Ren
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Potential Flight Experiments• Hig
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Opportunities for NASATechnology De
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Acknowledgements• Boeing/RSS - Jo
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IAF-99-A.5.10RAPID INTERPLANETARY T
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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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