Session
Poster Session III
Event Website
https://www.smallsat.org/index
Abstract
CubeSats are becoming increasingly complex. New innovative technology allows for more powerful computational capabilities and more complex science instruments. With strict mass requirements CubeSats need to cut weight from structural material as much as possible while maintaining mission integrity to maximize mass to electronics and instrumentation. Once in space the system is not under much stress and does not require much structural integrity; however, during launch the rocket produces a tremendous amount of sound, averaging around 160 dB in the local area. This acoustic pressure can crack solar cells if the array wall deflects too much.
The University of Illinois at Urbana-Champaign has developed a CubeSat bus for 3U, 2U, and 1.5U sizes. Additionally they are working on designing a 6U bus to handle more science instruments and capabilities. The university has designed thin carbon fiber solar panel substrates which simultaneously act as the outer skin of the CubeSat bus. The solar cell arrays run down the substrates, connected by innovative ultrathin flexible power and data harness. To meet the power demands, these cells have a higher efficiency. The cells are very delicate and will crack if its center deflect approximately 1.8 mm relative to its edges.
To find the minimum thickness for the carbon fiber substrate, an analysis is conducted of the system under acoustic pressure. For worst case analysis, a 6U bus is chosen because it has the most surface area for acoustic pressure to act upon. On board electronics will fail if they are subjected to an acoustic pressure greater than 130 dB; this pressure level will serve as the upper bound to which the panels need to be subjected. The system is assumed to be a symmetrically supported thin plate. The deflection is solved numerically using Matlab to find the minimum thickness before the solar cells crack under deflection. A finite analysis model is used to validate the boundary conditions. Additionally, the university has a unique layer stack up for their carbon fiber panels as a result materials testing for structural properties which was performed to enhance the analysis.
Ultimately, this analysis allows for future CubeSats to be more efficient with structural components and sizing of materials to minimize the bus mass, in turn maximizing mass that can be allocated for scientific instruments and electronics.
Included in
Design of CubeSat Solar Panels Considering Acoustic Pressure
CubeSats are becoming increasingly complex. New innovative technology allows for more powerful computational capabilities and more complex science instruments. With strict mass requirements CubeSats need to cut weight from structural material as much as possible while maintaining mission integrity to maximize mass to electronics and instrumentation. Once in space the system is not under much stress and does not require much structural integrity; however, during launch the rocket produces a tremendous amount of sound, averaging around 160 dB in the local area. This acoustic pressure can crack solar cells if the array wall deflects too much.
The University of Illinois at Urbana-Champaign has developed a CubeSat bus for 3U, 2U, and 1.5U sizes. Additionally they are working on designing a 6U bus to handle more science instruments and capabilities. The university has designed thin carbon fiber solar panel substrates which simultaneously act as the outer skin of the CubeSat bus. The solar cell arrays run down the substrates, connected by innovative ultrathin flexible power and data harness. To meet the power demands, these cells have a higher efficiency. The cells are very delicate and will crack if its center deflect approximately 1.8 mm relative to its edges.
To find the minimum thickness for the carbon fiber substrate, an analysis is conducted of the system under acoustic pressure. For worst case analysis, a 6U bus is chosen because it has the most surface area for acoustic pressure to act upon. On board electronics will fail if they are subjected to an acoustic pressure greater than 130 dB; this pressure level will serve as the upper bound to which the panels need to be subjected. The system is assumed to be a symmetrically supported thin plate. The deflection is solved numerically using Matlab to find the minimum thickness before the solar cells crack under deflection. A finite analysis model is used to validate the boundary conditions. Additionally, the university has a unique layer stack up for their carbon fiber panels as a result materials testing for structural properties which was performed to enhance the analysis.
Ultimately, this analysis allows for future CubeSats to be more efficient with structural components and sizing of materials to minimize the bus mass, in turn maximizing mass that can be allocated for scientific instruments and electronics.
https://digitalcommons.usu.edu/smallsat/2016/Poster3/6
