Statistics – Applications
Scientific paper
Jan 2002
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2002iaf..confe.804r&link_type=abstract
IAF abstracts, 34th COSPAR Scientific Assembly, The Second World Space Congress, held 10-19 October, 2002 in Houston, TX, USA.,
Statistics
Applications
Scientific paper
Humanity has dreamed of expanding their realm to include space, and other planetary bodies and to use space to improve our own planet. Space solar power is one methods of improving our own planet through the use of space. However, before this becomes practical the cost of access to space must be reduced drastically. Bifrost is one of many concepts designed to reduce the cost of access to space, and hence enable projects such as space solar power. The overall architecture consists of a magnetic-levitation launch track with one end elevated to approximately 20 kilometers. Logistics modules with attached propulsion modules and aerodynamic fairings are accelerated down the track at speeds varying according to the desired orbit. The propulsion module attached to each logistics module must then provide the velocity to achieve the desired final orbit. Bifrost is set up to launch a common hybrid logistics module size with a number of different propulsion modules suited for different in space applications. This paper concentrates on the low thrust propulsion module. After release from the magnetic-levitation track the propulsion module must be capable of circularizing the hybrid logistics module in geosynchronous orbit from geostationary transfer orbit.The initial transfer orbit would cause the spacecraft to re-enter on a subsequent periapsis pass if no velocity addition was provided by the propulsion module. This places a minimum thrust, and reliability constraint on the propulsion module. Volume constraints are imposed by the launch tube diameter and aerodynamic fairings on the vehicle. A solar electric propulsion system was chosen to provide thrust since the time of flight was not constrained, and the high specific impulse would allow a large payload to reach geosynchronous orbit. Several concepts exist for solar electric propulsion systems including the traditional rigid solar wings, thin film solar arrays, solar concentrators using lenses, and solar concentrators using reflectors. The reflector system was chosen, allowing the array to be placed very close to the high power components, requiring less power distribution and management, and hence improving system efficiency. Additionally, inflatable reflectors offer a significant weight advantage over rigid solar wings on satellites. The reduced number of solar cells in a concentrator design also lowers the cost per kilowatt of the power generation system. System configuration details will be included in the paper along with cutaway drawings and pictures of the demonstration unit. Analytically a comparison will be made between the concentrator design and the traditional rigid solar wing design. The scaled prototype will be used to prove the viability of the solar concentrator design. Summary figures will be provided showing overall system mass for both concentrator and traditional power generation systems as a function of logistics module mass.
Grillmayer G.
Olds J. R.
Rohrschneider Reuben R.
Sakai Tôru
Steffes S.
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