Deployable Flexible Solar Panel Array For CubeSat Platform Jaime Sanchez de la Vega, Aerospace Engineering Mentor: Daniel White, PhD School for Engineering of Matter Transport and Energy Background The practicality of the CubeSat small satellite platform has created a desire to implement higher power applications than those feasible with current space solar power technologies. The objective of this research is to determine the best configuration to maximize power generation density for a deployable flexible solar panel array system. Methods Various configurations and materials where considered. Current configuration was selected based on trade studies on material price, thickness, mass, rigidity, off- gassing, and UV degradation. Power output is measured using handheld multimeter when solar array is within sun simulator. Design and Fabrication Discussion Designed solar array system shows potential for use outside its originally intended purpose. The array could be utilized in long-duration high altitude balloon missions to extend their mission life. The power provided by this array has the potential to enable unprecedented high-energy operations on nanosatellites. Potential missions include utilization of pulsed plasma thrusters capable of interplanetary travel and powering more sophisticated communication schemes. Future Work Construction of solar array is currently in progress. The solar array must be tested in order to characterize its power output once construction is finished. Design of deployment mechanism and interface with satellite structure are necessary for full functionality and utilization for its intended purpose. Following finalized design and construction, solar array system should be tested under vacuum and extreme temperature gradients before demonstration in space. How can high-power applications be performed with nanosatellites? References [1] I. Vertat and A. vobornik, “Efficient and Reliable Solar Panels for Small CubeSat Picosatellites,” International Journal of Photoenergy, vol. 2014, Jun. 2014. [2] The CubeSat Program, Ed., CubeSat Design Specification, 13th ed. [3] Space Foundation, “The Space Report,” The Space Report, no. 2016. Figure 1. Detail of off-the-shelf solar array in Phoenix CubeSat, an earth-observing nanosatellite being developed at ASU. Figure 2. Power generation curve for Phoenix CubeSat. Flexible Solar Panel array would provide 3 times more power. Figure 3. Exploded view of system. Solar cells and rigidizing material are located between two layers of clear HDPE film sown together. Figure 4. Flexible Solar Panel Array layout. Mount is to be connected to side of satellite structure. Design dimensions of deployed array are 0.3m x 1.4m x 0.002m. When in stowed configuration, array is no larger than 0.3m x 0.05m x 0.1m. Design power output is 75W under direct sunlight. Materials utilized are commercially available and relatively inexpensive. Solar cells, wiring, and rigidizing structure, consisting of metal strip, are placed between two layers of HDPE film and sown together utilizing nylon thread. Solar Array is rolled for storage during launch and deployment, and unrolled by tension provided by the rigidizing material. Figure 5. Deployment Scheme. System is rolled compactly for storage during launch and deployed by tension of rigidizing metal strip.

Deployable Flexible Solar Panel Array For CubeSat PlatformThe practicality of the CubeSat small satellite platform has created a desire to implement higher power applications than

Download PDF Report

Upload
others
View
5
Download
0

Embed Size (px)

Citation preview

Deployable Flexible Solar Panel Array For CubeSat Platform

Jaime Sanchez de la Vega, Aerospace EngineeringMentor: Daniel White, PhD

School for Engineering of Matter Transport and Energy

BackgroundThe practicality of the CubeSat small satellite platformhas created a desire to implement higher powerapplications than those feasible with current space solarpower technologies. The objective of this research is todetermine the best configuration to maximize powergeneration density for a deployable flexible solar panelarray system.

MethodsVarious configurations and materials where considered.Current configuration was selected based on tradestudies on material price, thickness, mass, rigidity, off-gassing, and UV degradation.Power output is measured using handheld multimeterwhen solar array is within sun simulator.

Design and Fabrication DiscussionDesigned solar array system shows potential for useoutside its originally intended purpose. The array couldbe utilized in long-duration high altitude balloon missionsto extend their mission life.The power provided by this array has the potential toenable unprecedented high-energy operations onnanosatellites. Potential missions include utilization ofpulsed plasma thrusters capable of interplanetary traveland powering more sophisticated communicationschemes.

Future WorkConstruction of solar array is currently in progress. Thesolar array must be tested in order to characterize itspower output once construction is finished.Design of deployment mechanism and interface withsatellite structure are necessary for full functionality andutilization for its intended purpose. Following finalizeddesign and construction, solar array system should betested under vacuum and extreme temperature gradientsbefore demonstration in space.

How can high-power applications be performed with nanosatellites?

References[1] I. Vertat and A. vobornik, “Efficient and Reliable Solar Panels forSmall CubeSat Picosatellites,” International Journal of Photoenergy, vol.2014, Jun. 2014.

[2] The CubeSat Program, Ed., CubeSat Design Specification, 13th ed.

[3] Space Foundation, “The Space Report,” The Space Report, no. 2016.

Figure 1. Detail of off-the-shelfsolar array in Phoenix CubeSat,an earth-observing nanosatellitebeing developed at ASU.

Figure 2. Power generation curve for PhoenixCubeSat. Flexible Solar Panel array wouldprovide 3 times more power.

Figure 3. Exploded view of system. Solar cells andrigidizing material are located between two layersof clear HDPE film sown together.

Figure 4. Flexible Solar Panel Array layout. Mountis to be connected to side of satellite structure.

Design dimensions of deployed array are 0.3m x 1.4m x 0.002m.When in stowed configuration, array is no larger than 0.3m x 0.05m x0.1m. Design power output is 75W under direct sunlight.Materials utilized are commercially available and relativelyinexpensive. Solar cells, wiring, and rigidizing structure, consisting ofmetal strip, are placed between two layers of HDPE film and sowntogether utilizing nylon thread.Solar Array is rolled for storage during launch and deployment, andunrolled by tension provided by the rigidizing material.

Figure 5. Deployment Scheme. System is rolled compactly for storage during launch and deployed bytension of rigidizing metal strip.