Statement of work 1.0 introduction and background this project is to develop very high performance solar array technology for use in extreme environments typically exemplified by trajectories to and…

This is a $3,425,836.00 cost-plus-fixed-fee contract awarded by the National Aeronautics and Space Administration (NASA) Glenn Research Center to The Johns Hopkins University Applied Physics Laboratory LLC (APL) to develop very high performance solar array technology for use in extreme environments, such as missions to Jupiter.

The contract is the result of a proposal submitted by APL in response to NASA's Space Technology Research, Development, Demonstration, and Infusion 2015 solicitation. The scope of work includes designing and demonstrating a transformational solar array at Technology Readiness Level 5 that can achieve over 47% beginning-of-life cell efficiency at 5 AU and -125°C, over 32% end-of-life efficiency at the blanket level, and over 300 W/kg at end-of-life. The contract has a base period and two option periods. No set-aside designation is mentioned.

APL is a not-for-profit, university-affiliated research center that has provided a wide range of R&D, engineering, and technical services to NASA and other federal agencies through both prime contracts and subcontracts. This award aligns with NASA's priorities in developing advanced solar power technologies to enable deep space exploration missions.

Statement of work 1.0 introduction and background this project is to develop very high performance solar array technology for use in extreme environments typically exemplified by trajectories to and orbiting jupiter. The environments are low temperature, about -125 degrees c low irradiance, about 50 w per square meter, and high charged particle density. The project array is also intended to develop very high performance solar array technology in earth orbit. This statement of work is the result of a proposal submitted by the johns hopkins university applied physics laboratory, jhuapl, for award under the NASA headquarters space technology mission directorate, stmd, NASA research announcement, NRA, entitled space technology research, development, demonstration, and infusion 2015, appendix NNH15ZOA001N-15GCD-C3. 2.0 scope of work the scope of this project is to design and demonstrate at TRL-5 a transformational solar array over three successive phases, base, option i, and option II, with the following goals. -over 47 percent beginning of life cell efficiency at 5 AU and -125 degrees c -over 32 percent end of life efficiency at the blanket level at 50 w m-2, -125 degrees c and 4E15 1 MEV e CM-2 -over w KG-1 at EOL for the entire array including structure and deployment mechanisms -a stowed packaging density of 60 KW m-3 computed at BOL for 1,345 w m-2 -an ability to survive launch and numerous deploy retract cycles without degradation -an output higher than 300 v -an ability to operate in a plasma generated a by xenon thrusters, typically 1E8 CM-3 ions with an average energy of 2EV -a design compatible with electrostatic and magnetic cleanliness -solar cells that have no anomalous flat spot behavior at low irradiance and low temperature -a design compatible with electrostatic and magnetic cleanliness -record breaking IMM6 solar cells -a mock-up production line for the inexpensive manufacture of spacecraft blanket arrays 3.0 applicable documents and background aiaa standard s-112, qualification and quality requirements for electrical components on space solar panels 4.0 description of contract and technical requirements 4.1 base. System design, component test and analysis -describe IMM cells, fabrication techniques, and previous work on surviving stowage and launch and operating at greater than 330V -35 percent BOL goal --calculate IMM efficiency at 5 AU and -125 c. --define plan to eliminate lilt, fabricate and test IMM cells at lilt to be certain to show they harmful lilt, and test cells at lilt before and after 4.5E15 1 MEV e -28 percent at blanket --fabricate IMM scas for outgassing tests with DC93-500 and low outgas adhesive and optimized quantity of microspheres --measure and reduce outgassing of scas made with ultra-low outgassing adhesive filled with microspheres -fabricate best outgassing scas for DSS blanket samples and test at APL -report IMM solar cell mass and power at 5 AU and EOL -report power and packaging density for 5 KW, 50 KW and 100 KW -describe deployment design and mechanism -design magnetically and electrostatically clean array -document reduction in cost and cell inspection 4.2 option i, test hardware -35 percent BOL goal --eliminate lilt phenomenon in IMM5 solar cells --fabricate sample IMM5 cells and test at lilt to be sure harmful lilt phenomenon are cured --test sample of IMM5 cells to be sure that harmful lilt is gone at EOL, 50 w per square meter, -125 c, and 4E15 1 MEV e per square centimeter. -28 percent at blanket --refine concentrator coating, eliminate delamination, evaluate ultra-low outgassing adhesive for back of wing --manufacture sufficient IMM5 SCA strings for two NASA150MM x 150MM blankets --manufacture two 150MM x 150MM blankets with back-wiring and ultralow outgassing cell to substrate adhesives --estimate expected array mass and performance at BOL --functionally test and expose a blanket to environments --EV