Mid-Earth Orbit Momentum Transfer Tether for Reduced Space Access Costs
- Paper number
IAC-08.D4.2.1
- Author
Mr. Roger X. Lenard, Sandia National Laboratories, United States
- Year
2008
- Abstract
Heliosat, Inc, has developed a concept of a mid-Earth orbiting, gravity gradient stabilized tether that enables dramatically reduced to-orbit costs, but is feasible with existing technologies. The concept was generated primarily in response to large up-lift needs of space solar power systems, but can be applied for a range of payloads. The objective payload mass for the system is 25 T and use of available fiber technologies such as M5 have been evaluated. We demonstrate the concept involving a 4300 km long tether can be integrated with evolved reusable launch systems such as the Kistler K-1 vehicle with dramatic improvements in payload sent to space with attendant reductions in launch costs. Preliminary tether dynamic and rendezvous analyses have been performed and the power demands for orbit maintenance have also been assessed. We find that to tether costs of less than 500/ kg are feasible in the relative near term, with to− orbit ( orbit dependent) cost of 1,000/kg or less are feasible. Significant features of this tether include the fact that for most of its operational orbital period the tether system does intrude on the vast majority of commercial, civil or military orbital trajectories. The concept also provides a research platform for fractional gravity research. This paper describes the tether, research performed to date, and analysis of tether dynamics and finally addresses a potential developmental schedule supporting near-term space operations.
- Abstract document
- Manuscript document
IAC-08.D4.2.1.pdf (🔒 authorized access only).
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