Moon & Mars Orbiting Spinning Tether Transport - Tethers Unlimited

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Appendix L: <strong>Tether</strong> Boost Facility Design Final Report3 CONTROL STATION DESIGN3.1 ADCS/GN&C3.1.1 Design Requirements, Drivers, and AssumptionsAttitude determination and control system requirements are driven mainly by acombination of spin maneuver requirements and solar panel pointing requirements.The following are preliminary requirements based on the current top-level sizing doneto date.• Attitude Knowledge: +/- .05 deg / axis• Attitude Hold Capability (non-maneuvering): +/- 1.0 deg / axis• Attitude Maneuver Axis Accuracy: (spin axis): +/- 1.0 deg (non-spin axis):+/- 1.0 deg• Attitude Rate Accuracy (non-maneuvering): +/- 0.1 deg/sec/axis• Attitude Rate Accuracy (maneuvering): +/- 0.1 deg/sec/axis• Position Knowledge: (GPS Receive)• Velocity Knowledge: (GPS Receive)• Orbit Positioning Accuracy: Inclination, Ascending Node, Arg. of Latitude,etc.: TBDAttitude maneuver capability requirements for spinning the control station whilenot using expendable propellant will require the use of control moment gyros. Thefollowing discussion explains the design drivers for using CMGs and some possibleconcepts for desaturation that also do not use consumables.Reaction wheels provide control torques by changing wheel speed, ie.converting stored momentum into torque (Tj = d (hj)/dt). Control moment gyros(CMGs) provide control torques by changing the direction of the wheel momentumvector (gyroscopic torque). Both reaction wheels and CMGs can have large storedmomentum but the maximum reaction wheel torque available is limited by powerconsiderations, as shown in Figure 3-1.An example: RW Power (@ 6000 rpm) = 1 ft -lb @ 1300 watts or 3 ft-lbs @3900 wattsReaction wheels require large power to produce torques due to changingmomentum by accelerating/decelerating a spinning disc about a fixed axis. However,CMGs (see Figure 3-2) can produce very large torques by changing momentumvector direction (using fairly small input torques) of a large spinning disc. CMG discsusually take long periods for spin-up since the spin motors are not sized nearly aslarge as a reaction wheel motor.L-55
Appendix L: <strong>Tether</strong> Boost Facility Design Final Report4000350030001500 RPM3000 RPM6000 RPM250020001500100050000 0.5 1 1.5 2 2.5 3 3.5Output Torque (ft-lbs)Figure 3-1. Reaction Wheel Power vs. Output TorqueFigure 3-2. Control Moment Gyro for the International Space Station3.1.2 New Issues and Requirements IdentifiedTypically, double-gimbal CMGs are used for control torques from 3 to 300 ft-lbsand single-gimbal CMGs are used for applications requiring more than 300 ft-lbs.Skylab was designed to use two double-gimbal CMGs, each having a capability of +/-160 ft-lbs (a third unit was installed as a backup). Skylab mass was 76295 kg anddesign power with all solar panels working was 11 kW average for the entireworkshop system. Both reaction wheels and CMGs usually require desaturation if alarge amount of maneuvers are required or if system biases cause long durationL-56
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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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Page 194 and 195: Tethers Unlimited, Inc.Tether Rende
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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
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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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Moon & Mars Orbiting Spinning Tether Transport - Tethers Unlimited

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