Tether boostfacilitiesjun01
1 like559 views
This document summarizes research into using momentum exchange and electrodynamic tethers to provide propellantless boosts between orbits. It describes two types of tether boost facilities - one that uses momentum exchange to toss payloads into higher orbits, and one that uses electrodynamic thrusting to reboost the tether system orbit. The research aims to develop reusable tether transport systems as an alternative to chemical propulsion for cislunar and interplanetary cargo delivery. Initial designs are presented for 5 metric ton payload tether boost facilities in low Earth orbit.
Tether boostfacilitiesjun01
- 1. Tether Boost Facilities for In-Space Transportation Robert P. Hoyt, Robert L. Forward Tethers Unlimited, Inc. 1917 NE 143rd St., Seattle, WA 98125-3236 +1-206-306-0400 fax -0537 TU@tethers.com www.tethers.com John Grant, Mike Bangham, Brian Tillotson The Boeing Company 5301 Bolsa Ave., Huntington Beach, CA 92647-2099 (714) 372-5391
- 2. TUI/MMOSTT 2 NIAC Funded Tether Research ¥ Moon & Mars Orbiting Spinning Tether Transport (MMOSTT) ¥ Hypersonic Airplane Space Tether Orbital Launch (HASTOL) ¥ Objectives: Ð Perform Technical & Economic Analysis of Tether Transport Systems Ð Identify Technology Needs Ð Develop Conceptual Design Solutions Ð Prepare for Technology Development Efforts and Flight Experiments to Demonstrate Tether Transport Technology
- 3. TUI/MMOSTT 3 Momentum-Exchange Tether Boost Facility ¥ High-strength tether rotates around orbiting control station ¥ Tether picks payload up from lower orbit and tosses payload into higher orbit ¥ Tether facility gives some of its orbital momentum & energy to payload ¥ Tether facility orbit must be restored to enable it to toss additional payloads
- 4. TUI/MMOSTT 4 Electrodynamic Reboost Magnetic Field Thrust Current Plasma Contactors (Hollow Cathode, FEA, Bare Wire) ¥ Power supply drives current along tether ¥ Plasma contactors exchange current with ionosphere ¥ Plasma waves close current ÒloopÓ ¥ Current ÒpushesÓ against geomagnetic field via JxB Force
- 5. Momentum-Exchange/Electrodynamic-Reboost Tethers: TUI/MMOSTT 5 Summary of Advantages ¥ Tether Boost Facilities Can Provide a Fully-Reusable In-Space Propulsion Architecture Ð LEO Û MEO/GTO Ð LEO Û Lunar Surface Ð LEO Û Mars Ð ETO Launch, in combination with Hypersonic Airplane/RLV ¥ Momentum Exchange + Electrodynamic Tether Can Enable Propellantless Propulsion Beyond LEO ¥ Rapid Transfer Times Ð 5 days to Moon Ð 90-130 days to Mars ¥ Operational Tether System Can Be Tested Before Use With High- Value Payloads ¥ Reusable Infrastructure + Low Consumables Þ Lower Cost
- 6. Cislunar Tether Transport System ¥ Developed Orbital Architecture for Round Trip LEOÛLunar Surface Transport ¥ Whole System Launch Mass = 30x Payload Mass Ð LEO Tether Boost Facility Mass = 13x Payload Mass, Lunar Tether Facility = 17x Payload ¥ 13 Payloads/Year ¥ Incremental Commercial Development Path TUI/MMOSTT 6
- 7. Rapid Earth-Mars Transport ¥ Reusable Architecture for Round Trip Earth to Mars Transport ¥ Rapid Transfer Times (90-130 days) INTERPLANETARY TRANSPORT USING ROTATING TETHERS Payload pick-up Payload release Origin TUI/MMOSTT 7 Escape trajectory Interplanetary trajectory Destination Inbound trajectory Payload release Payload capture Patch point Tapered tether Loaded Tether Center of mass orbit Tapered tether Loaded Tether Center of mass orbit Patch point Earth’s gravitational sphere of influence Mars’ gravitational sphere of influence Sol
- 8. MXER Tethers Included in NASAÕs TUI/MMOSTT 8 IISTP Process ¥ NIAC Funded MMOSTT and HASTOL efforts have resulted in Momentum-Exchange/Electrodynamic Reboost Tethers being considered in NASAÕs In-Space Integrated Space Transportation Planning Process ¥ TUI & NASA/MSFC developed concept designs for Tether Boost Facilities for 4 classes of missions Ð Microsatellite Ð 1 mt Payloads Ð 5 mt Payloads Ð 10 mt Payloads ¥ IISTP Process evaluated these designs in trade studies for several different scientific missions ¥ ÒHigh-Risk/High PayoffÓ ¥ MXER Tethers scored well for several classes of missions Ð High Performance metric
- 9. TUI/MMOSTT 9 Tether Architecture for LEO-GTO-LTO-Mars Transport ¥ Tether facility serves as transport hub for multiple destinations ¥ Tether serves as a zero-propellant, reusable, high-Isp, high thrust ÒThird StageÓ
- 10. TUI/MMOSTT 10 5mt Payload Tether Boost Facility for In-Space Transportation Architecture ¥ Reusable In-Space Transportation Infrastructure ¥ Payload Launched to 325 km LEO ¥ Tether Boosts Payload to Elliptical Orbit ¥ Tether Uses Electrodynamic Thrust to Reboost Tether System Point Design: ¥ Boost 10,000 kg to GTO ¥ Boost 5,000 kg Vehicle to : Ð Highly Elliptical Orbit (C3=-1.9) Ð Lunar Transfer Trajectory Ð Escape Via Lunar Swingby ¥ Tether Facility Launch Mass: 63 mt Ð Deploy using 3 Delta-IV-H LVÕs Ð Retain Delta Upper Stages for Ballast Ð 200 kW EOL Power Supply for 1 Month Reboost Analysis of Other Propulsion Technologies with MX Tether Assist: ¥ Delta-II-Class LV Launches 5,000 kg Spacecraft ¥ Tether Boosts Spacecraft to C3Ê=Ê-1.9 km2/s2 ¥ High-Thrust Propulsion Systems: Ð Do Injection Burn at Perigee (570 km, 10.62 km/s) ¥ Low-Thrust Propulsion Systems: Ð Use Lunar Swingby to Escape EarthÕs Gravity Well
- 11. Net Payoff: Reduced Launch Costs To launch 5,000 kg to GTO: ¥ Using Rockets: Delta IVM+(4,2) or SeaLaunch TUI/MMOSTT 11 ~ $90M ¥ Using Rocket to LEO, Tether Boost to GTO: Ð Delta II 7920 (~$45M) or Dnepr 1 (~$13M) Ø1/2 to 1/7 the launch cost
- 12. TUI/MMOSTT 12 LEOðGTO 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: Requirement Value 2500 kg at IOC, can grow to follow market Payload Mass Pickup orbit 300 km equatorial Release orbit GTO Release insertion error < Delta IV/Ariane 5 Payload environment < Delta IV/Ariane 5 Turnaround time 30 days Mission life 10 years + Collision avoidance 100% of tracked spacecraft Operational orbit lifetime 15 days Payload pickup reliability 99%
- 13. TUI/MMOSTT 13 Mass Properties Breakdown LEO Control Station 10967 13267 2300 Thermal Control Subsys 1 15% 1104.5 1270.1 165.7 Cabling/Harnesses 33% 749.6 997.0 247.4 Structure 25% 2721.1 3401.3 680.3 Electr.Pwr. 4736.7 5409.6 673.0 PV array panels 1 1 13% 1782.9 1782.9 2014.6 Power Storage 1 1 15% 2860.5 2860.5 3289.5 PV array drive motors 8 2 13% 3.0 48.0 54.2 PMAD 1 2 13% 22.7 45.4 51.3 Downlink Comm Subsys 1.8 2.1 0.2 Downlink Transceiver 1 2 13% 0.7 1.4 1.56 Downlink antennae 2 1 13% 0.2 0.5 0.51 TFS Net Comm Subsys 1.8 2.1 0.2 Comm. antennae 2 1 13% 0.2 0.5 0.51 Transceiver 1 2 13% 0.7 1.4 1.6 C&DH 26.0 29.4 3.4 Computer 1 2 13% 13.0 26.0 29.4 TT&C 6.9 7.8 0.9 transponder 1 2 13% 3.5 6.9 7.8 ADCS 200.9 213.8 12.9 ED Tether Power Subsys 417.4 603.4 186.0 Plasma Contactor (FEAC) 1 2 25% 45.4 90.8 113.5 PMAD/PCUt 1 2 50% 163.3 326.6 489.9 Docking & I/C Subsys 0.5 0.54 0.04 Beacon 1 1 8% 0.5 0.5 0.54 Tether Deploy & Control 1000.0 1330.0 330.00 Tether reeling assembly 1 1 33% 1000.0 1000.0 1330.0 Mass Margin (kg) Mass with Contingency (kg) Mass with no margin (kg) Unit mass (kg) Mass Contin gency Redun dancy Qty Control Station Mass: 10,967 kg Tether Mass: 8,274 kg Grapple Mass: 650 kg GLOW: 19,891 kg Ð 15% margin w/in Delta IV-H payload capacity Expended Upper Stage 3,467 kg On-Orbit Mass: 23,358 kg
- 14. TUI/MMOSTT 14 Tether Boost Facility Control Station ¥ Solar Arrays, 137 kW @ BOL ¥ Battery/Flywheel Power Storage ¥ Command & Control ¥ Tether Deployer ¥ Thermal Management Tether (not shown to scale) ¥ Hoytether for Survivability ¥ Spectra 2000 ¥ 75-100 km Long ¥ Conducting Portion for Electrodynamic Thrusting Total Mass:ÊÊÊÊ 23,358 kg Payload Mass: 2,500 kg Grapple Assembly ¥ Power, Guidance ¥ Grapple Mechanism ¥ Small Tether Deployer Payload Accommodation Assembly (PAA) ¥ Maneuvering & Rendezvous Capability ¥ Payload Apogee Kick Capability Payload
- 15. NIAC Efforts Have Developed Improved Tether Analysis Tools Tether System Design: Ð Tapered tether design TUI/MMOSTT 15 ¥ Spectra 2000 Ð Orbital mechanics considerations to determine facility mass required Tether operation: TetherSimª ¥ Numerical Models for: Ð Orbital mechanics Ð Tether dynamics Ð Electrodynamics Ð Hollow Cathode & FEACs Ð Geomagnetic Field (IGRF) Ð Plasma Density (IRI) Ð Neutral Density (MSIS Ô90) Ð Thermal and aero drag models Ð Endmass Dynamics Ð Payload Capture/Release ¥ Interface to MatLab/Satellite Tool Kit
- 16. TUI/MMOSTT 16 LEOðGTO Boost Facility ¥ TetherSimª Numerical Simulation (10x real speed) Ð Tether Dynamics, Orbital Mechanics
- 17. TUI/MMOSTT 17 Technology Readiness Level ¥ Boeing & TUI Performed TRL Analysis of MXER Tether Technologies ¥ Many necessary components are already at high TRL ¥ TRL Analysis Indicates Areas for Future Work to Address: Ð Power management subsystem Ð Thermal control subsystem ¥ Higher power than previously flown systems Ð Electrodynamic Propulsion Subsystem ¥ Plasma contactors ¥ Dynamics control Ð Automated Rendezvous & Capture technologies ¥ Prediction & Guidance ¥ Grapple Assembly & Payload Adapter Ð Some work ongoing in HASTOL Ph II effort Ð Flight Control Software Ð Traffic Control/Collision Avoidance
- 18. TUI/MMOSTT 18 20 12 8 4 0 ÆZ (m) 16 -10 0 10 ÆX (m) Rendezvous ¥ Rapid AR&C Capability Needed ¥ Relative Motion is Mostly in Local Vertical ¥ Tether Deployment Can Extend Rendezvous Window ¥ Additional Tether Deployment Under Braking Can Reduce Shock Loads Payload Capture Vehicle descends towards Payload PCV Deploys More Tether PCV pays out tether and Payload maneuvers to dock with grapple PCV engages tether brake and begins to lift payload 1 0.8 0.6 0.4 0.2 0 0 10 20 Load Level 30 40 50 0.1 s braking 5 s braking 10 s braking 20 s braking Time (s) 30 s braking
- 19. Space Debris-Survivable Tether ¥ Micrometeoroids & Space Debris Will Damage Tethers ¥ Solution approach: spread tether material out in an open net structure with multiple redundant load/current paths TUI/MMOSTT 19 Primary Lines Secondary Lines (initially unstressed) 0.2 to 10's of meters 0.1- 1 meter Severed Primary Line Effects of Damage Localized Secondary Lines Transfer Load Around Damaged Section
- 20. TUI/MMOSTT 20 Proposed RETRIEVE Tether Experiment ¥ Candidate Secondary Experiment for XSS-11 ¥ $800K in Initial Development funds from AFRL ¥ Small ED tether system deorbits µSat at end of mission Ð Activated only after primary mission completed ¥ Mass: (CBE+Uncertainty): 6.5 kg ¥ Demonstrate Ð Controlled orbital maneuvering with ED tether Ð Long life tether Ð Stabilization of tether dynamics
- 21. µTORQUE: MX Tether to Boost µSat to ¥ Microsatellite Tethered Orbit Raising QUalification Experiment ¥ Build Upon RETRIEVE to Create Low-Cost Demo of MXER tether technology ¥ Secondary payload on GEO Sat launch ¥ µTORQUE boost microsat payload to lunar transfer or escape ¥ 0.4 km/s boost to payload ¥ Mass-competitive with chemical rocket TUI/MMOSTT 21 Lunar Transfer or Escape Launch vehicle places primary payload into GTO µTORQUE uses ED drag to spin up tether µTORQUE deploys tether & microsat above stage µTORQUE releases payload into lunar transfer/swingby
- 22. TUI/MMOSTT 22 µTORQUE on Delta IV ¥ Delta-IV Secondary Payload ¥ ~100 kg weight allocation ¥ Boost ~80kg microsat from LEO to low-MEO
- 23. Momentum Exchange/Electrodynamic Reboost NIAC Study ProSEDS TUI/MMOSTT 23 Tether Technology Roadmap GRASP Experiment µTORQUE Experiment ED-LEO Tug µPET LEO Û GTO Tether Boost Facility ISS-Reboost Terminator Tetherª Cislunar Tether Transport System ETO-Launch Assist Tether RETRIEVE 2001 2003 2005 2010 2013 2016 2025 2035
- 24. TUI/MMOSTT 24 Opportunities for NASA Technology Development ¥ Expand AR&C Capabilities for Rapid Capture ¥ High Power & High Voltage Space Systems ¥ Electrodynamic Tether Physics ¥ Debris & Traffic Control Issues ¥ Conduct Low-Cost Flight Demo of Momentum- Exchange Tether Boost Modest NASA Investment in Technology Development Will Enable Near-Term Space Flight Demonstration
- 25. TUI/MMOSTT 25 Contributors ¥ Boeing/RSS - John Grant, Jim Martin, Harv Willenberg ¥ Boeing/Seattle - Brian Tillotson ¥ Boeing/Huntsville - Mike Bangham, Beth Fleming, John Blumer, Ben Donohue, Ronnie Lajoie, Lee Huffman ¥ NASA/MSFC - Kirk Sorenson ¥ Gerald Nordley ¥ Chauncey Uphoff