sling-on-a-ring: a realizable space elevator to leo?
- Paper number
IAC-08.D4.1.5
- Author
Dr. Andrew Meulenberg, HiPi Consulting, United States
- Coauthor
Mr. Shivram Ramanathan, National Institute of Technology Karnataka, India
- Coauthor
Mr. Rahul Suresh, National Institute of Technology Karnataka, India
- Coauthor
Mr. Karthik Balaji P.S., National Institute of Technology Karnataka, Surathkal, India
- Year
2008
- Abstract
A new concept of space elevator is proposed. This space transport system is based on a new approach, design, and implementation of an “orbital-ring-system”. It offers less-expensive and environmentally-less-damaging transportation of payloads to LEO with near-present material technology and existing launch capabilities. Development of this system could start today.
Starting with an assumption that a "circum-terra" conductive ring can be deployed in LEO (see “A LEO ARCHIPELAGO T M ,” Symposium D.3 ), a mass-lifting system is proposed that would utilize the spatial stability, momentum-transfer capability, and electrical power-generation, -storage, and -transfer ability of an accessorized orbital ring. This is the 3rd of a series of “Stepping Stones” proposed to get man into space in a realizable (rather than just a physically possible) manner.
The experimental stage (Step 1) of a LEO-ring system (prior to deployment of a full fiber-optic communication ring and of the “sling” system) would involve testing and development of the control and stability of the ring structures, of the ring-based solar-power and communication systems, and of the interactions of the combined systems under various circumstances. In particular, the procedures, operation, and dynamics of a scaled version of the sling-on-a-ring T M will be thoroughly tested.
Phase 1 of the mass-lifter system would be LEO deployment of a second high-tensile-strength, equatorial, circum-terra, conductive fiber, followed by the associated solar-power and station-keeping units, and finally the sling module itself. Successful deployment and testing of the control and stability of the ring and sling structures would be followed by a slight “spin-up” of the ring and attached components, thereby putting the ring under tension. Phase 2 consists of testing and adjusting the ring and sling-module dynamics so that, at “periodic” perigee, the sling module descends to 60 km. The sling (rotating about its module so that its end point, as it penetrates the atmosphere, will match the earth’s rotational velocity) will be able to enter the atmosphere with only a vertical velocity. With split-second timing, a payload is attached from aircraft (at as low as ∼40000 feet) and jerked into space by the momentum of the sling. Each sling-on-a-ring module would have the capability to repeatedly lift one-ton masses to LEO. In Phase 3, a multi-sling system would commence hourly transfer of large payloads (1 ton or more) to LEO from aircraft.
This sling-on-a-ring system and its comparison with other space-elevator concepts are dealt with in the paper.
- Abstract document
- Manuscript document
IAC-08.D4.1.5.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.