Assembly and Operation of a “Tin Can” SPS
- Paper number
IAC-16,C3,1,7,x32630
- Coauthor
Prof. Peter Schubert, Indiana University-Purdue University Indianapolis, United States
- Coauthor
Ms. Shen Mi Khoo, Indiana University-Purdue University Indianapolis, United States
- Coauthor
Mr. Mukish Munyady, Indiana University-Purdue University Indianapolis, United States
- Coauthor
Mr. Pravinjit Singh, Indiana University-Purdue University Indianapolis, United States
- Year
2016
- Abstract
A cylindrical shell solar power satellite (SPS) contains no moving parts and is amenable to fabrication from in-space resources. This “tin can” configuration has integral thermal management by using the non-illuminated portions of the shell as a radiating heat shield, maintaining the solar cells within workable temperature ranges. The tethers holding the shell to the central conductor spire present a complex radiative environment which is studied further herein to obtain a more precise measurement of high and low temperature limits. Heat generated by the transmitting antenna and its power electronics is also studied to understand its impact on the requirements imposed on components and subsystems. Achieving a slow rotation of a very large diameter cylindrical shell with minimal internal strength interacts with the assembly process through tradeoffs between propellant, assembly jigs, and construction spacecraft. Vibrations induced in the cylindrical shell are studied including transient behavior during spin-up. The panel-to-panel forces expected during spin-up, and during on-going operations as gravity gradients excite low-frequency modes are studied in order to derive specifications for linkage rotation and strength. Finally, the results of imperfect assembly, lost parts, and meteorite strikes are investigated to assess risk to other spacecraft. Solar wind pressure is evaluated to determine station-keeping requirements. Assembly in an orbit slightly higher than GEO may be selected to minimize collateral damages, and means of adjusting the orbit are studied to derive overall architecture propellant requirements, anticipating a mixture of in situ propellant options versus earth-sourced propellants.
- Abstract document
- Manuscript document
IAC-16,C3,1,7,x32630.pdf (🔒 authorized access only).
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