The Collier Report of U.S. Government Contracting

Sampling of Federal Government Funding Actions/Set Asides

In order by amount of set aside monies.

• $749,681 - Friday the 10th of July 2015
  National Aeronautics And Space Administration
  NASA SHARED SERVICES CENTER
  IGF::OT::IGF OTHER FUNCTION - DEPLOYABLE SPACE SYSTEMS, INC. (DSS) WILL FOCUS THE PROPOSED NASA PHASE 2 EFFORT ON THE DEVELOPMENT AND TRL 5/6 MATURATION OF OUR INNOVATIVE FUNCTIONAL ADVANCED CONCENTRATOR TECHNOLOGY (FACT) FOR STANDARD MULTI-JUNCTION AND ADVANCED IMM PHOTOVOLTAICS. FACT IS A HIGHLY-AFFORDABLE, PRACTICAL, HIGH-EFFICIENCY, ULTRA-LIGHTWEIGHT PHOTOVOLTAIC CONCENTRATOR BLANKET ASSEMBLY THAT CAN BE ROLLED OR Z-FOLDED IN A STOWED CONFIGURATION. FACT COUPLED TO AN ULTRA-LIGHTWEIGHT SOLAR ARRAY STRUCTURAL PLATFORM WILL PROVIDE GAME-CHANGING PERFORMANCE METRICS AND UNPARALLELED AFFORDABILITY. FACT WILL ENABLE EMERGING SEP SPACE SCIENCE AND EXPLORATION MISSIONS THROUGH ITS ULTRA-AFFORDABILITY, ULTRA-LIGHTWEIGHT, ULTRA-COMPACT STOWAGE VOLUME, AND PRACTICAL/USER-FRIENDLY OFF-POINTING VERSUS POWER CHARACTERISTICS. THE FACT TECHNOLOGY PROMISES TO PROVIDE NASA/INDUSTRY A NEAR-TERM AND LOW-RISK FLEXIBLE BLANKET TECHNOLOGY FOR ADVANCED SOLAR ARRAY SYSTEMS. THE FACT TECHNOLOGY PROVIDES REVOLUTIONARY PERFORMANCE IN TERMS OF: HIGH SPECIFIC POWER (>260W/KG BOL WITH ZTJ/XTJ AND ~400W/KG BOL WITH IMM PV WHEN COUPLED TO ROSA-ARRAY); AFFORDABILITY (>40% COST SAVINGS WHEN COUPLED TO ROSA-ARRAY); FLEXIBLE BLANKET COMPATIBILITY / ARCHITECTURE FLEXIBILITY (ACCOMMODATES ROLLED OR Z-FOLDED BLANKETS); USER-FRIENDLY OFF-POINTING VERSUS POWER CHARACTERISTICS; COMPACT STOWAGE VOLUME (>50KW/M3); HIGH DEPLOYMENT RELIABILITY; HIGH RADIATION TOLERANCE AND HIGH VOLTAGE OPERATION CAPABILITY; APPLICABILITY/SCALABILITY TO MANY MISSIONS (500W-1MW+ SIZES); LILT/HIHT OPERATION CAPABILITY; AND ADAPTABLE TO STANDARD RIGID HONEYCOMB PANEL ARRAYS.

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• $749,191 - Monday the 23rd of February 2015
  National Aeronautics And Space Administration
  NASA SHARED SERVICES CENTER
  IGF::OT::IGF OTHER FUNCTION - DEPLOYABLE SPACE SYSTEMS (DSS) WILL FOCUS THE PROPOSED PHASE 2 SBIR PROGRAM ON THE HARDWARE-BASED DEVELOPMENT AND TRL ADVANCE OF A HIGHLY-MODULARIZED AND EXTREMELY-SCALABLE SOLAR ARRAY (MEGA-ROSA) THAT PROVIDES IMMENSE POWER LEVEL RANGE CAPABILITY FROM 100KW TO MANY MEGAWATTS IN SIZE. MEGA-ROSA WILL ENABLE EXTREMELY HIGH POWER SPACECRAFT APPLICATIONS, INCLUDING: SOLAR ELECTRIC PROPULSION (SEP) SPACECRAFT, SEP SPACE-TUG, AND LARGE-SCALE PLANETARY AND HUMAN EXPLORATION MISSIONS BECAUSE OF ITS GROUND-BREAKING STOWED PACKAGING EFFICIENCY, HIGH DEPLOYED STIFFNESS / STRENGTH, LOW-COST AND STRAIGHTFORWARD GROUND TEST CAPABILITY. THE INNOVATIVE AND SYNERGISTIC MEGA-ROSA SOLUTIONS, TO BE VALIDATED TO A TRL 6 LEVEL DURING THE PROPOSED PHASE 2 PROGRAM, WILL ENABLE FUTURE HIGH POWER MISSIONS THROUGH LOW COST (25-50% COST SAVINGS DEPENDING ON PV AND BLANKET TECHNOLOGY), HIGH SPECIFIC POWER (>200 W/KG TO 400 W/KG BOL AT THE WING LEVEL DEPENDING ON PV AND BLANKET TECHNOLOGY), EXTREMELY COMPACT STOWAGE VOLUME (>50 KW/M3 FOR VERY LARGE ARRAYS), HIGH DEPLOYMENT RELIABILITY, PLATFORM SIMPLICITY (LOW PARTS COUNT AND REDUCED POTENTIAL FAILURE MODES), HIGH DEPLOYED STRENGTH/STIFFNESS (>5X STIFFER AND STRONGER THAN RIGID PANEL ARRAYS OF SIMILAR SIZES), HIGH VOLTAGE CAPABILITY, SCALABILITY TO ULTRA-HIGH POWER (100KW TO SEVERAL MEGAWATTS), AND OPERABILITY IN UNIQUE ENVIRONMENTS (HIGH/LOW ILLUMINATION, HIGH/LOW SUN INTENSITY AND HIGH RADIATION).

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• $52,400 - Friday the 21st of September 2012
  National Aeronautics And Space Administration
  GLENN RESEARCH CENTER
  DEVELOPMENT AND DEMONSTRATION OF LOW COST MODULE INTEGRATION APPROACHES FOR LARGE POWER SOLAR ARRAYS BASED ON THE ROLL-OUT SOLAR ARRAY (ROSA)

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• $50,000 - Saturday the 29th of March 2014
  National Aeronautics And Space Administration
  NASA SHARED SERVICES CENTER
  DEPLOYABLE SPACE SYSTEMS (DSS), IN PARTNERSHIP WITH ATK SPACE AND EMCORE, IS FOCUSING ON THE DESIGN DEVELOPMENT AND OPTIMIZATION OF THE MOST PROMISING ADVANCED SPACE PHOTOVOLTAIC SUBSYSTEM NOW AVAILABLE: EMCORE'S ULTRA-THIN 33% BOL-EFFICIENT INVERTED METAMORPHIC MULTIJUNCTION (IMM) SOLAR CELL THAT IS INTERCONNECTED INTO MODULE FORM AND INTEGRATED ONTO AN ADVANCED FLEXIBLE BLANKET (GORE); SPECIFICALLY FOR IMPLEMENTATION ON THE LIGHTEST SOLAR ARRAY STRUCTURAL SYSTEM CURRENTLY IN USE, ATK'S ULTRAFLEX. THE INNOVATIVE AND SYNERGISTIC SOLUTIONS CONCEPTUALLY DEVELOPED DURING THE PHASE 1 EFFORT PRODUCED A NEAR-TERM, LOW-RISK SOLAR ARRAY SYSTEM THAT PROVIDES BREAKTHROUGH PERFORMANCE IN TERMS OF HIGHEST SPECIFIC POWER (>380 W/KG BOL), LIGHT WEIGHT, SCALABILITY TO LARGE (>15 KW) WING SIZES, HIGH DEPLOYED STIFFNESS, HIGH DEPLOYED STRENGTH, COMPACT STOWAGE VOLUME (>40 KW/M3 BOL), HIGH VOLTAGE OPERATION CAPABILITY, RELIABILITY, AFFORDABILITY, AND RAPID COMMERCIAL READINESS. THE PHASE 2 STUDY WILL SUCCESSFULLY FURTHER INCREASE THE DESIGN FIDELITY (TRL) OF THE MOST PROMISING IMM-INTEGRATED ONTO ULTRAFLEX-SPECIFIC TRIANGULAR GORE BLANKET SOLUTIONS CONFIGURED TO MEET KEY HIGH-VOLTAGE SEP / DEEP SPACE SCIENCE MISSION REQUIREMENTS. THE DEVELOPMENT, AS PERFORMED ON THE COST-EFFECTIVE PHASE 2 SBIR PLAN STRUCTURED IN DETAIL, WILL ALLOW FOR AN EXPEDIENT AND LOW-RISK COMMERCIAL INFUSION OF THE ULTRA-LIGHTWEIGHT INTEGRATED IMM PV ULTRAFLEX SOLAR ARRAY TECHNOLOGY VIA CONTINUED HARDWARE-BASED AND TEST-VALIDATED DEVELOPMENT, AND ENABLES FUTURE MISSIONS, INCLUDING NEAR-TO-MEDIUM TERM NASA OUTER PLANETS AND SOLAR ELECTRIC PROPULSION (SEP) SCIENCE MISSIONS.

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• $50,000 - Monday the 17th of March 2014
  National Aeronautics And Space Administration
  NASA SHARED SERVICES CENTER
  DSS'S RECENTLY COMPLETED SUCCESSFUL NASA SBIR PHASE 1 PROGRAM HAS ESTABLISHED A TRL 3/4 CLASSIFICATION FOR AN INNOVATIVE IMM PV INTEGRATED MODULAR BLANKET ASSEMBLY (IMBA) THAT CAN BE ROLLED OR Z-FOLDED AND ENABLES NASA'S EMERGING HIGH VOLTAGE SOLAR ELECTRIC PROPULSION (SEP) MISSIONS. SIGNIFICANT CONCEPT FEASIBILITY, DESIGN/ANALYSIS, TRADE STUDY/EVALUATION, AND PROOF-OF-CONCEPT HARDWARE BUILD/TEST EFFORTS EXECUTED DURING THE NASA SBIR PHASE 1 PROGRAM HAVE VALIDATED DSS'S IMM PV IMBA TECHNOLOGY AS A POTENTIALLY REVOLUTIONARY FLEXIBLE PHOTOVOLTAIC BLANKET ASSEMBLY THAT PROVIDES HIGH PERFORMANCE IN TERMS OF; HIGH VOLTAGE OPERABILITY, HIGH SPECIFIC POWER / LIGHTWEIGHT (>1000 W/KG BOL AT THE BLANKET SUBSYSTEM LEVEL, AND>500 W/KG BOL AT THE ARRAY LEVEL), COMPACT STOWAGE VOLUME (>50 KW/M3 BOL), ROLLABLE OR Z-FOLDABLE FOR STOWAGE, RELIABILITY, MODULARITY&RAPID PRODUCTION, FLEXIBILITY/DURABILITY AND ROBUSTNESS, AFFORDABILITY, AND ADAPTABILITY TO ALL EXISTING INDUSTRY FLEXIBLE BLANKET SOLAR ARRAY PRODUCTS. DSS'S IMBA TECHNOLOGY ALSO ACCOMMODATES STANDARD ZTJ PV DEVICE TECHNOLOGIES TO PROVIDE SIGNIFICANTLY IMPROVED PERFORMANCE OVER CURRENT STATE-OF-THE-ART.

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• $2,300,000 - Tuesday the 8th of January 2013
  National Aeronautics And Space Administration
  GLENN RESEARCH CENTER
  IGF::CT::IGF NEW CPFF CONTRACT WITH DEPLOYABLE SPACE SYSTEMS, INC. (DSS) FOR THE PROGRAM ENTITLED "TECHNOLOGY MATURATION&ADVANCEMENT OF THE MISSION-ENABLING MEGA-ROSA SOLAR ARRAY FOR SEP APPLICATIONS".

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• $200,000 - Saturday the 29th of March 2014
  National Aeronautics And Space Administration
  NASA SHARED SERVICES CENTER
  DEPLOYABLE SPACE SYSTEMS (DSS), IN PARTNERSHIP WITH ATK SPACE AND EMCORE, IS FOCUSING ON THE DESIGN DEVELOPMENT AND OPTIMIZATION OF THE MOST PROMISING ADVANCED SPACE PHOTOVOLTAIC SUBSYSTEM NOW AVAILABLE: EMCORE'S ULTRA-THIN 33% BOL-EFFICIENT INVERTED METAMORPHIC MULTIJUNCTION (IMM) SOLAR CELL THAT IS INTERCONNECTED INTO MODULE FORM AND INTEGRATED ONTO AN ADVANCED FLEXIBLE BLANKET (GORE); SPECIFICALLY FOR IMPLEMENTATION ON THE LIGHTEST SOLAR ARRAY STRUCTURAL SYSTEM CURRENTLY IN USE, ATK'S ULTRAFLEX. THE INNOVATIVE AND SYNERGISTIC SOLUTIONS CONCEPTUALLY DEVELOPED DURING THE PHASE 1 EFFORT PRODUCED A NEAR-TERM, LOW-RISK SOLAR ARRAY SYSTEM THAT PROVIDES BREAKTHROUGH PERFORMANCE IN TERMS OF HIGHEST SPECIFIC POWER (>380 W/KG BOL), LIGHT WEIGHT, SCALABILITY TO LARGE (>15 KW) WING SIZES, HIGH DEPLOYED STIFFNESS, HIGH DEPLOYED STRENGTH, COMPACT STOWAGE VOLUME (>40 KW/M3 BOL), HIGH VOLTAGE OPERATION CAPABILITY, RELIABILITY, AFFORDABILITY, AND RAPID COMMERCIAL READINESS. THE PHASE 2 STUDY WILL SUCCESSFULLY FURTHER INCREASE THE DESIGN FIDELITY (TRL) OF THE MOST PROMISING IMM-INTEGRATED ONTO ULTRAFLEX-SPECIFIC TRIANGULAR GORE BLANKET SOLUTIONS CONFIGURED TO MEET KEY HIGH-VOLTAGE SEP / DEEP SPACE SCIENCE MISSION REQUIREMENTS. THE DEVELOPMENT, AS PERFORMED ON THE COST-EFFECTIVE PHASE 2 SBIR PLAN STRUCTURED IN DETAIL, WILL ALLOW FOR AN EXPEDIENT AND LOW-RISK COMMERCIAL INFUSION OF THE ULTRA-LIGHTWEIGHT INTEGRATED IMM PV ULTRAFLEX SOLAR ARRAY TECHNOLOGY VIA CONTINUED HARDWARE-BASED AND TEST-VALIDATED DEVELOPMENT, AND ENABLES FUTURE MISSIONS, INCLUDING NEAR-TO-MEDIUM TERM NASA OUTER PLANETS AND SOLAR ELECTRIC PROPULSION (SEP) SCIENCE MISSIONS.

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• $200,000 - Monday the 17th of March 2014
  National Aeronautics And Space Administration
  NASA SHARED SERVICES CENTER
  DSS'S RECENTLY COMPLETED SUCCESSFUL NASA SBIR PHASE 1 PROGRAM HAS ESTABLISHED A TRL 3/4 CLASSIFICATION FOR AN INNOVATIVE IMM PV INTEGRATED MODULAR BLANKET ASSEMBLY (IMBA) THAT CAN BE ROLLED OR Z-FOLDED AND ENABLES NASA'S EMERGING HIGH VOLTAGE SOLAR ELECTRIC PROPULSION (SEP) MISSIONS. SIGNIFICANT CONCEPT FEASIBILITY, DESIGN/ANALYSIS, TRADE STUDY/EVALUATION, AND PROOF-OF-CONCEPT HARDWARE BUILD/TEST EFFORTS EXECUTED DURING THE NASA SBIR PHASE 1 PROGRAM HAVE VALIDATED DSS'S IMM PV IMBA TECHNOLOGY AS A POTENTIALLY REVOLUTIONARY FLEXIBLE PHOTOVOLTAIC BLANKET ASSEMBLY THAT PROVIDES HIGH PERFORMANCE IN TERMS OF; HIGH VOLTAGE OPERABILITY, HIGH SPECIFIC POWER / LIGHTWEIGHT (>1000 W/KG BOL AT THE BLANKET SUBSYSTEM LEVEL, AND>500 W/KG BOL AT THE ARRAY LEVEL), COMPACT STOWAGE VOLUME (>50 KW/M3 BOL), ROLLABLE OR Z-FOLDABLE FOR STOWAGE, RELIABILITY, MODULARITY&RAPID PRODUCTION, FLEXIBILITY/DURABILITY AND ROBUSTNESS, AFFORDABILITY, AND ADAPTABILITY TO ALL EXISTING INDUSTRY FLEXIBLE BLANKET SOLAR ARRAY PRODUCTS. DSS'S IMBA TECHNOLOGY ALSO ACCOMMODATES STANDARD ZTJ PV DEVICE TECHNOLOGIES TO PROVIDE SIGNIFICANTLY IMPROVED PERFORMANCE OVER CURRENT STATE-OF-THE-ART.

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• $199,037 - Saturday the 29th of March 2014
  National Aeronautics And Space Administration
  NASA SHARED SERVICES CENTER
  DEPLOYABLE SPACE SYSTEMS (DSS), IN PARTNERSHIP WITH ATK SPACE AND EMCORE, IS FOCUSING ON THE DESIGN DEVELOPMENT AND OPTIMIZATION OF THE MOST PROMISING ADVANCED SPACE PHOTOVOLTAIC SUBSYSTEM NOW AVAILABLE: EMCORE'S ULTRA-THIN 33% BOL-EFFICIENT INVERTED METAMORPHIC MULTIJUNCTION (IMM) SOLAR CELL THAT IS INTERCONNECTED INTO MODULE FORM AND INTEGRATED ONTO AN ADVANCED FLEXIBLE BLANKET (GORE); SPECIFICALLY FOR IMPLEMENTATION ON THE LIGHTEST SOLAR ARRAY STRUCTURAL SYSTEM CURRENTLY IN USE, ATK'S ULTRAFLEX. THE INNOVATIVE AND SYNERGISTIC SOLUTIONS CONCEPTUALLY DEVELOPED DURING THE PHASE 1 EFFORT PRODUCED A NEAR-TERM, LOW-RISK SOLAR ARRAY SYSTEM THAT PROVIDES BREAKTHROUGH PERFORMANCE IN TERMS OF HIGHEST SPECIFIC POWER (>380 W/KG BOL), LIGHT WEIGHT, SCALABILITY TO LARGE (>15 KW) WING SIZES, HIGH DEPLOYED STIFFNESS, HIGH DEPLOYED STRENGTH, COMPACT STOWAGE VOLUME (>40 KW/M3 BOL), HIGH VOLTAGE OPERATION CAPABILITY, RELIABILITY, AFFORDABILITY, AND RAPID COMMERCIAL READINESS. THE PHASE 2 STUDY WILL SUCCESSFULLY FURTHER INCREASE THE DESIGN FIDELITY (TRL) OF THE MOST PROMISING IMM-INTEGRATED ONTO ULTRAFLEX-SPECIFIC TRIANGULAR GORE BLANKET SOLUTIONS CONFIGURED TO MEET KEY HIGH-VOLTAGE SEP / DEEP SPACE SCIENCE MISSION REQUIREMENTS. THE DEVELOPMENT, AS PERFORMED ON THE COST-EFFECTIVE PHASE 2 SBIR PLAN STRUCTURED IN DETAIL, WILL ALLOW FOR AN EXPEDIENT AND LOW-RISK COMMERCIAL INFUSION OF THE ULTRA-LIGHTWEIGHT INTEGRATED IMM PV ULTRAFLEX SOLAR ARRAY TECHNOLOGY VIA CONTINUED HARDWARE-BASED AND TEST-VALIDATED DEVELOPMENT, AND ENABLES FUTURE MISSIONS, INCLUDING NEAR-TO-MEDIUM TERM NASA OUTER PLANETS AND SOLAR ELECTRIC PROPULSION (SEP) SCIENCE MISSIONS.

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• $165,938 - Friday the 10th of July 2015
  National Aeronautics And Space Administration
  GLENN RESEARCH CENTER
  IGF::CT::IGF SCOPE AND TECHNICAL OBJECTIVES: THIS WORK CONTINUES FURTHER DEVELOPMENT, TECHNOLOGY EVALUATION, AND DESIGN MODIFICATIONS NECESSARY TO SUPPORT NASA MODULAR POWER SYSTEMS APPLICATIONS. THE ROSA SOLAR ARRAY DESIGN CONCEPT IS BEING DEVELOPED UNDER NASA SBIR CONTRACT # NNX11CA61C FOR VARIOUS VERY HIGH POWER AND SCIENCE MISSION APPLICATIONS. THIS SPECIFIC CONTRACT, SUPPORTED BY THE AMPS PROJECT AND AES PROGRAM, WILL FOCUS ON THE DEVELOPMENT OF TECHNOLOGY NECESSARY TO SUPPORT THE UNIQUE REQUIREMENTS NECESSARY FOR HIGHLY RECONFIGURABLE, MODULAR POWER SYSTEMS. THE TECHNICAL OBJECTIVES OF THIS EFFORT ARE TO 1) STUDY AND DETERMINE THE BEST APPROACH OF ADAPTING ROSA ARRAY TECHNOLOGY TO THE NEEDS OF THE AMPS PROJECT; 2) DESIGN, BUILD, AND TEST A FULLY DEPLOYABLE ROSA ARRAY SIZED AT 3 KW TOTAL POWER, (TEST HARDWARE TO CONSIST OF TWO IDENTICAL 1.5 KW WINGS); AND 3) DETERMINE, IN COLLABORATION WITH NASA GRC, THE OPTIMAL SOLAR CELL/BLANKET TECHNOLOGIES SUITABLE FOR USE WITH THIS ARRAY. TASK DESCRIPTION: IN ORDER TO ACHIEVE THE TECHNICAL OBJECTIVES DESCRIBED ABOVE, THIS CONTRACTUAL EFFORT WILL CONSIST OF THE FIVE (5) TECHNICAL TASKS DESCRIBED BELOW: TASK 1: CONDUCT TRADE STUDIES ON DESIGN OPTIONS TO CONSTRUCT AND DELIVER ROSA SOLAR ARRAY ENGINEERING DEVELOPMENT UNITS (EDU) COMPATIBLE WITH AMPS MISSION REQUIREMENTS. THE DESIGN WILL CONSIST OF TWO IDENTICAL 1.5 KW WINGS THAT ARE EASILY CONFIGURABLE, LOW MASS, LOW STOWED VOLUME, LOW COST, HIGH RELIABILITY AND CAN BE EASILY RETRACTED AND REDEPLOYED AS NEEDED. TASK 2: BASED ON OUTCOME OF TRADE STUDIES IN TASK 1, COMPLETE A DETAILED DESIGN OF AN EDU THAT CAN ACCOMMODATE INTEGRATION WITH THE MULTI-MISSION SPACE EXPLORATION VEHICLE (MMSEV) DEMONSTRATION VEHICLE. THE DESIGN WILL INCLUDE ALL GROUND SUPPORT EQUIPMENT (GSE) (SUCH AS OFF-LOADERS, SUPPORT FRAMES, DEPLOYMENT CONTROL MOTORS, ETC.) NECESSARY TO PERFORM A COMPLETE DEPLOYMENT AND RETRACTION OF THE EDU, BOTH IN A STANDARD STAND-ALONE HORIZONTAL CONFIGURATION AND WHEN ATTACHED TO THE MMSEV VEHICLE (PARTIALLY DEPLOYMENT DEMONSTRATIONS MAY BE ACCEPTABLE WHEN ATTACHED TO MMSEV). TASK 3: DESIGN A MODULAR SOLAR ARRAY BLANKET ELEMENT FOR THE EDU THAT IS REMOVABLE, REPLACEABLE, AND CONSISTENT WITH AMPS MISSION REQUIREMENTS. THE EDU BLANKET WILL CONSIST OF A REPRESENTATIVE AMOUNT OF MODULAR BLANKET ELEMENTS TO DEMONSTRATE THE ADVANTAGES OF MODULARITY, TESTABILITY, AND REPLACEABILITY. THE MODULAR BLANKET ELEMENTS USED ON THE EDU DO NOT HAVE TO INCLUDE ACTIVE SOLAR CELLS, FLIGHT-DESIGNED INTERCONNECT SCHEMES, OR SPACE-QUALIFIED MATERIALS; HOWEVER THEY SHOULD PROVIDE REPRESENTATIVE SAMPLES OF THE BLANKET TECHNOLOGY THAT NEEDS TO BE DEVELOPED. VIABLE OPTIONS FOR BLANKET TECHNOLOGY SUCH AS CELLS, INTERCONNECTS, COATINGS, ETC. MAY BE INCLUDED ON THE MODULAR BLANKET ELEMENTS IF SCHEDULE AND AVAILABILITY PERMIT. THE PRIMARY PURPOSE OF THE MODULAR BLANKET ELEMENTS, AS WELL AS THE REMAINDER OF THE SOLAR ARRAY BLANKET ON THE EDU, IS TO VISUALLY SIMULATE THE SOLAR CELLS ON A FLIGHT-TYPE ARRAY, PROVIDE AN APPROXIMATE MASS REPRESENTATION FOR THE SOLAR ARRAY BLANKET, AND DEMONSTRATE THE DEPLOYMENT, RETRACTION, AND STRUCTURAL DYNAMICS OF THE BLANKET AS RELATED TO THE ENTIRE SOLAR ARRAY STRUCTURE. THE SOLAR ARRAY BLANKET UNDER THIS CONTRACT IS NOT INTENDED TO CONTAIN ACTIVE PHOTOVOLTAIC DEVICES OR PRODUCE POWER UNDER INSOLATION. TASK 4: FABRICATE THE TWO 1.5KW EDUS BASED ON THE DESIGN FINALIZED UNDER TASKS 2 AND 3. SPACE FLIGHT-LIKE MATERIALS AND HARDWARE ARE TO BE USED AS APPROPRIATE AND AS SCHEDULE AND AVAILABILITY PERMIT (EXCEPT FOR THE SOLAR ARRAY BLANKET AS NOTED ABOVE UNDER TASK 3). FABRICATE ALL GROUND SUPPORT EQUIPMENT (GSE) (SUCH AS OFF-LOADERS, SUPPORT FRAMES, DEPLOYMENT CONTROL MOTORS, ETC.) NECESSARY TO PERFORM A COMPLETE DEPLOYMENT AND RETRACTION OF THE EDU, BOTH IN A STANDARD STAND-ALONE HORIZONTAL CONFIGURATION AND WHEN ATTACHED TO THE MMSEV VEHICLE (PARTIALLY DEPLOYMENT DEMONSTRATIONS MAY BE ACCEPTABLE

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