Hypersonic Airplane Space Tether Orbital Launch (HASTOL) System

Transcription

1 NIAC Fellows Meeting Atlanta, GA 9 November 1999 Hypersonic Airplane Space Tether Orbital Launch (HASTOL) System Thomas J. Bogar, Boeing - Phantom Works Robert L. Forward, Tethers Unlimited, Inc. Michal E. Bangham, Boeing - Huntsville Mark J. Lewis, University of Maryland

2 Discussion Topics HASTOL Concept Overview Hypersonic Vehicle Description Trajectory Analysis Results Tether Design Considerations

3 Hypersonic Airplane Space Tether Orbital Launch System

4 CardioRotovator Concept

5 Tillotson Two-Tier Tether (T4) Concept Two-Stage Rotovator Reduces Ratio Of Tether System Mass To Payload Mass

6 Rotovator Tether Mass Ratios Tether Length Orbital Radius Orbital Velocity Tip Velocity Hypersonic Airplane Velocity L R O V O V T V H = V O -V T -470 m/s M T /M P Tether to Payload Mass Ratio (km) (km) (m/s) (m/s) (m/s) Mach Spectra 2x 10x

7 CardioRotovator Tether Mass Ratios Tether Length Orbital Radius Orbital Velocity Tip Velocity Tip Accel. Hypersonic Airplane Velocity Tether to Payload Mass Ratio L R O V O V T a V H = V O -V T -470 m/s M T /M P (km) (km) (m/s) (m/s) (m/s 2 ) (m/s) Mach Spectra 2x 10x

8 High-strength Electrodynamic Force Tether (HEFT) Facility Plasma Contactors Tether Rotation Magnetic Field Current Electrodynamic Force HEFT Facility High Strength Tapered Survivable Hoytether Solar Array Power Supply

9 AIAA Dual-Fuel DF-9 Dual Role Vehicle SH2 Tanks JP-7 Tanks LOX (Below) Looking Aft Ramjet/Scramjet AceTRs (Internal) Crew Station Payload Linear Rocket Air Core Enhanced Turboramjets (AceTR) Ramjet/Scramjet ft GP cvs

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12 Matrix Of Payload Transfer Points Analyzed 120 km ,000 ft 350,000 Achievable Points Unachievable Points Altitude , ,000 8,000 9,000 10,000 11,000 12,000 ft/s 2,500 3,000 3,500 Velocity m/s

13 Normal Load Factor Along Descent Trajectory

14 Dynamic Pressure Along Descent Trajectory

15 Hoytether Failsafe Tether Design Primary Lines Secondary Lines (initially unstressed) 0.2 to 10's of meters First Level of Secondary Lines Redistributes Load to Adjacent Nodes Severed Primary Line Effects of Damage Localized Second Level of Secondary Lines Redistributes Load Back to Undamaged Portion of Primary Line meter a. b. c.

16 High Temperature Tether Materials Tensile Strength (GPa) vs. Temperature Material V C (km/s) Density d (g/cc) 20 C Spectra Zylon (PBO) Quartz Glass (SiO 2 ) ? S-glass ????? Carbon ????? Carbon/Ni-coated ????? Tyranno (SiTiCO) Textron β-sic β-sic/ti-coated Altex (Al 2 O 3 /SiO 2 ) Nextel (α-al 2 O 3 ) ????? 0.65 Nextel/Al-coated ???? Tungsten Wire C 600 C 800 C 1000 C 1200 C

17 HASTOL GRAPPLE ASSEMBLY High Temperature Tether With Embedded Conductor For Electrodynamic Tether Electric Power Generation Housing for Tether Reel, Avionics, RCS Fuel, Batteries, and Electrodynamic Tether Battery Recharging Circuits Tether Deployer and Retrieval Mechanism Mounting Structure for Reaction Control System Mounting Structure for Reaction Control System RCS Nozzles Flush with Surface to Minimize Drag and Heating Grapple

18 Grapple to Payload Attachment Option Grapple/End mass comes down on Payload 1 Grapple stops on Payload, levers on payload are in in-close position 2 Payload Surface 3 Attach Levers then move radially outward toward ring; sliding on rails. Once contact with ring is made, they latch to the ring securing the payload to the grapple. Grapple Ring

19 Conclusions The HASTOL System provides a system to deliver payloads to space with minimal reliance on rocket propulsion Tether designs using existing materials can provide required strength at required thermal loads The Hoytether design provides a survivable tether concept for long duration operation Issues to be addressed in future work include Grapple design refinement and payload transfer logisitics