Deployable Solar Array - Mission to Mars G1:3 TEAM: Daniel Bain, Craig Patton, Andrew Tendean ADVISOR: Dr. Adeel Khalid ISYE 4803 Spring 2019 PROBLEM STATEMENT DESIGN, ANALYSIS & OPTIMIZATION CURRENT SOLAR  TECHNOLOGY AIAA request-for-proposal for a deployable solar array for a manned mission to mars. Array will provide 250kW of power for the onboard equipment of the spacecraft. Structure must be hinge less, deployed autonomously and survived the launch and deployed parameter described in the RFP. Existing Space Mission Solar Array  Thickness Silicone Base(Mfg: SpectroLab, Tecstar) 50-200μm​ High Efficiency Silicone Base  (Mfg: ASE, Sharp) 76μm​ Single Junction Ga-As   (Mfg: SpectroLab, Tecstar) 140-175μm​ Dual Junction  (Mfg: SpectroLab, Tecstar) Triple Junction   (Mfg: Emcore, SpectroLab, Tecstar) MATERIAL SELECTION 2040 Theoretical Model In-Situ Vapor Deposited Parylene Substrate Solar Cells Thickness: <1.3um Mass per unit surface area: 3.6 g/m^2 Power output per unit surface area: 21.6W/ m^2 Endurance: 100,000 h (11 years) at 220c in vacuum environment Parylene- C (poly-chloro-p-xylylene) Substrate 2020 Deliverable Model MicroLink’s Epitaxial Lift-Off (ELO) Photovoltaic Cells Thickness: <40 um Mass per unit surface area: 250 g/m^2 Power output per unit surface area: 250 W/ m^2 Both models use Nitinol wire and electric current to unfold the solar arrays. 2020 Model – Dynamic Harmonic Analysis of 1G at 1.5 Hz (Mesh) Spacecraft Mission Profile System Block Diagram DESIGN REQUIREMENTS 2020 Model – Dynamic Harmonic Analysis of 1G at 1.5 Hz (Stress) MATERIAL COMPARISONS Common Sheet Thickness  Thickness Standard Aluminum Foil 16 μm​ Standard weight Printing Paper 24 μm​ Standard Weight Plastic Wrap 12.5μm​ Mylar Space Blanket 15μm​ Deployed 2020 Model AIAA Given RFP Requirements FINAL DESIGN SPECIFICATIONS Updated RFP (March 26th) 250 kW is total power supplied by multiple arrays Each array will be limited to 9.5 kW because of solar flux Stowed volume is for an individual array 2020 Model – Dynamic Harmonic Analysis of 1G at 1.5 Hz (Displacement) SOLUTION PROPOSAL Multiple-array configuration to reach target output of 250KW with each array subjected to 1.5 m radius limit and utilizing Nitinol wires as a deploying mechanism. With today’s current technology, the thinnest photovoltaic cells in production for space missions are 40um thick​. Therefore the Technology Readiness Level (TRL) for this project is at Level 1.  The team prepared two separate models. 2040 Model This model will specify technology requirements to meet RFP requirements, as current technology cannot satisfy them In-situ Vapor deposited Parylene Substrate Organic Photovoltaic Cells Will satisfy deployed radius and volume requirements 2020 Model This model will use current technology and attain as many RFP requirements as possible MicroLink’s  epitaxial lift-off (ELO) solar cells Will satisfy deployed radius requirement, and will not contain hinges Volume will be a minimum while using current solar cell technology Ability to operate after small impact Satisfy launch and deployed vibrational analysis Folded 2020 Model PROTOTYPE 2020 Model – Dynamic Harmonic Analysis of 15G at 100 Hz (Mesh) 2020 Model – Closeup of Folds at Center Materials Used: Mylar Space Blanket (12.3 microns) Black Plastic Sheeting (50 microns) Clear Tape Made as close as possible to size of 2020 Model 2020 Model – Dynamic Harmonic Analysis of 15G at 100 Hz (Stress) Note: No damage because of incomplete SolidWorks material data