Moon & Mars Orbiting Spinning Tether Transport - Tethers Unlimited

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IAF-00-S.6.04AcknowledgmentsThis research was supported by Phase I and Phase IIgrants from NASAÕs Institute for Advanced Conceptsas well as a Phase II SBIR contract fromNASA/MSFC. The author acknowledges contributionsfrom Dr. Robert L. Forward of TUI, Nicole Meckel andDoug Smith of Primex Aerospace, and Michal Bangham,John Grant, Brian Tillotson, Beth Fleming, JohnBlumer, Ben Donahue, Bill Klus, and Harvey Willenbergof the Boeing Company.References1. Forward, R.L., Hoyt, R.P., Uphoff, C., ÒApplication ofthe Terminator Tetherª Electrodynamic Drag Technologyto the Deorbit of Constellation SpacecraftÓ,AIAA Paper 98-3491, 34th Joint Propulsion Conference,July 1998.2. Sanmart’n, J.R., Mart’nez-S‡nchez, M., Ahedo, E.,ÒBare Wire Anodes for Electrodynamic Tethers,Ó J.Propulsion and Power, 7(3), pp. 353-360, 1993.3. Drell, S.P., Foley, H.M., Ruderman, M.A., Drag andPropulsion of large satellites in the ionosphere: AnAlfv n Engine in spaceÓ, J. Geophys. Res., 70(13), pp.3131-3145, July 1, 1965.4. Estes, R.D., ÒAlfv n waves from an electrodynamictethered satellite systemÓ, J. Geophys. Res., 93 (A2),pp 945-956, Feb. 1, 1988.5. Forward R.L., Hoyt, R.P. "Failsafe Multiline HoytetherLifetimes," AIAA paper 95-2890, 31stAIAA/SAE/ASME/ASEE Joint Propulsion Conference,San Diego, CA, July 1995.6. Spindt, C.A., et al., ÒField Emitter Arrays for VacuumMicroelectronics,Ó IEEE Transactions on ElectronDevices, Vol. 38, No. 10, p. 2355, Oct. 1991.7. Hoyt, R.P., Forward, R.L., ÒThe Terminator Tether ª :Autonomous Deorbit of LEO Spacecraft for Space DebrisMitigation,Ó Paper AIAA-00-0329, 38 th AerospaceSciences Meeting & Exhibit, 10-13 Jan 2000, Reno,NV.8. Hoyt, R.P. Uphoff, C.W., ÒCislunar Tether TransportSystemÓ, J. Spacecraft and Rockets, 37(2), March-April 2000, pp. 177-186.9. Hoyt, R.P., ÒCislunar Tether Transport SystemÓ, TethersUnlimited, Inc. Final Report on NASA Institute forAdvanced Concepts Phase I Contract 07600-011, May1999. Downloadable from www.niac.usra.edu.10. Forward, R.L., Nordley, G., ÒMERITT: Mars-EarthRapid Interplanetary Tether Transport System Ð InitialFeasibility Study,Ó AIAA Paper 99-2151, 35 th JointPropulsion Conference, Los Angeles, CA, 20-24 June1999.11. Carroll, J.A, Preliminary Design of a 1 km/sec TetherTransport Facility, March 1991, Tether ApplicationsFinal Report on NASA Contract NASW-4461 withNASA/HQ.12. Forward, R.L., ÒTether Transport from LEO to the LunarSurface,Ó AIAA paper 91-2322, 27th AIAA/ASME/ASE/ASEE Joint Propulsion Conference, July 1991.13. Hoyt, R.P., ÒTether System for Exchanging PayloadsBetween Low Earth Orbit and the Lunar Surface,Ó AIAAPaper 97-2794, 33rd AIAA/ASME/ ASE/ASEE JointPropulsion Conference, Seattle, WA, 6-9 July 1997.14. Bangham, M, Lorenzini, E., Vestal, L. Tether TransportSystem Study, NASA TP-1998-206959.15. Bogar, T.J., et al., Hypersonic Airplane Space TetherOrbital Launch System, Boeing-STL Final Report onPhase I NIAC Contract 07600-018, January 7, 2000. APDF version of the document is downloadable fromwww.niac.usra.edu.16. Hoyt, R.P., ÒDesign and Simulation of Tether Facilitiesfor the HASTOL Architecture,Ó AIAA Paper 2000-3615, 36 th Joint Propulsion Conference, Huntsville,AL, 17-19 July 2000.17. Hoyt, R.P., ÒDesign And Simulation of A Tether BoostFacility For LEO⇒GTO Transport,Ó AIAA Paper 2000-3866, 36 th Joint Propulsion Conference & Exhibit,17-19 July 2000, Huntsville, AL.9
Tethers Unlimited, Inc.Appendix K: Facility Reboost StudyAppendix KTETHER FACILITY REBOOSTRob HoytTethers Unlimited, Inc.IntroductionA key factor in the economic viability of a Tether Boost Facility will be the frequency with which thefacility can boost payloads. The throughput capacity of a tether facility will be determined largely by thetime required to restore the facility’s orbit after each payload boost operation. In this document wepresent analytical methods for calculating the changes in a tether facility’s orbit due to a boost operation,and use numerical simulation to estimate the time required to reboost the facility orbit using electrodynamictether propulsion.Changes In Momentum-Exchange Tether Facility Orbit:When the facility catches and tosses a payload, it imparts a fraction of its orbital energy andmomentum to the payload, and thus its orbit is lowered. In this section we present a brief summary of ananalytical method for calculating the facility orbit changes. This method assumes that the orbits areKeplerian.Useful equations for calculating the semimajor axis and eccentricity of an orbit from the velocity andradius at perigee or apogee are:Semimajor Axis:Eccentricity:2⎡2V ⎤a = ⎢ −⎣ r µe⎥⎦re =± ( − )a−11 , where sign is (+) for values calculated at perigee, (2)and (–) for apogeeWhen the tether boost facility and payload rendezvous, the tether facility has a center of mass radiusr facility,0 and velocity V facility,0 , and the payload has radius and velocity r payload,0 & V payload,0 .. In calculatingthe facility position and velocity, one must account for the tether. The Tether Boost Facility will use atapered tether to minimize the tether’s mass; the location of the tether’s center-of-mass (COM) relative tothe facility is computed numerically.Facility+Payload Orbit After Payload Acquisition:After catching the payload, the new system COM radius and velocity are:(1)rCOM,1=r, 0( M + M )+ r, 0MM + M + Mfacility facility tether payload payloadfacility tether payload(3)VCOM,1V, 0( M + M )+ V, 0M=M + M + Mfacility facility tether payload payloadfacility tether payloadand we use Eqns. (1) & (2) to calculate the new semimajor axis a 1 and eccentricity e 1 ., (4)Tether System Tip VelocityWhen the facility catches the payload, the rotational inertia of the system is conserved, and thus theangular velocity ω remains constant. However, the COM of the system shifts closer to the payload end ofthe tether when the mass of the payload is added to the system. Thus the tip velocity of the systemdecreases. The new velocity of the tether tip relative to the system’s COM can be estimated as:V= ω L , (5)tip,1 1K-1
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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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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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Tethers Unlimited, Inc.Appendix R:
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