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Award ID | Description | Recipient | Total Value | Awarding Agency | Funding Agency | Set Aside | NAICS | PSC | Award Date | Start Date | End Date | |
|---|---|---|---|---|---|---|---|---|---|---|---|---|
| SENSITIVE CIRCUIT EVALUATION OF LIGHTNING TRANSIENT DAMAGE THRESHOLDS. | AI SOLUTIONS INC | $74,204 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541330Engineering Services | AR35 | Jun 23, 2020 | Jun 23, 2020 | Apr 30, 2021 | ||
| DISTANT LIGHTING COUPLING TO UMBILICAL TESTING | AI SOLUTIONS INC | $167,301 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541330Engineering Services | AR35 | Mar 18, 2020 | Mar 18, 2020 | Jun 30, 2022 | ||
| PACE SOLAR ARRAY PANELS | SOLAERO TECHNOLOGIES CORP. | $2,427,320 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 334413Semiconductor and Related Device Manufacturing | AR35 | Oct 4, 2019 | Oct 4, 2019 | Dec 3, 2021 | ||
| THE PURPOSE OF THIS TASK ORDER IS TO SPECIFY REQUIREMENTS AND ASSOCIATED CHARACTERISTICS THAT WILL FACILITATE VENDOR DESIGN FOR A SPACE VEHICLE IN-FLIGHT DISCONNECT (IFD). | AI SOLUTIONS INC | $45,393 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541330Engineering Services | AR35 | Aug 15, 2019 | Aug 14, 2019 | Nov 30, 2019 | ||
| THE PRIMARY MISSION FOR THE CUBESAT IS TO MEASURE THE TEMPERATURE OF A SMALL METALLIC OBJECT COATED WITH THE CRYOGENIC SELECTIVE SURFACE COATING IN SPACE. THESE ARE THE PRIMARY SCIENCE REQUIREMENTS FOR THE CUBESAT SYSTEM. THE CUBESAT SHALL PROVIDE ADEQUATE SHIELDING FROM EARTHS ALBEDO RADIATION AND FROM THE HEAT GENERATED BY THE CUBESAT ITSELF USING SUCH THAT THE COATED SAMPLE IS NOT ADVERSELY HEATED. THE CUBESAT SHALL INCLUDE A METHOD OF ATTACHING THE SAMPLE TO THE CUBESAT SUCH THAT MINIMAL HEAT IS CONDUCTED TO THE SAMPLE UNDER TEST. THE CUBESAT SHALL MAINTAIN ORIENTATION OF THE COATED SAMPLE TOWARD DEEP SPACE. TWO TEMPERATURE SENSORS PER EACH SAMPLE WHERE ONE SHALL BE USED TO MEASURE THE SAMPLE TEMPERATURE LOCATED IN THE SMALL METALLIC OBJECT UNDER THE COATING AND THE OTHER SHALL BE USED TO MEASURE THE TEMPERATURE OF THE WALL AND STRUCTURE CLOSEST TO THE SAMPLE. HUNDREDS OF PAPERS HAVE BEEN PUBLISHED ON DESIGNING SURFACES THAT REFLECT ONE WAVELENGTH RANGE WHILE ABSORBING ANOTHER IN ORDER TO ACHIEVE SIGNIFICANT TEMPERATURE INCREASES OR DECREASES OF THESE SURFACES IN SUNLIGHT. THE MAJORITY OF THIS WORK WAS DEVOTED TO ACHIEVING HIGH TEMPERATURES TO SUPPORT, FOR EXAMPLE, SOLAR FURNACE OPERATION, BUT A SIGNIFICANT PORTION WAS DIRECTED TO COOLING. COATINGS HAVE BEEN DEVELOPED TO ALLOW A SURFACE IN SUNLIGHT TO COOL BELOW AMBIENT, BUT ATMOSPHERIC LIMITATIONS, INFRARED TRANSMISSION WINDOWS AND CONVECTIVE WARMING, PREVENT SIGNIFICANT COOLING. HOWEVER, HIBBARD, OF THE LEWIS RESEARCH CENTER, REALIZED THAT IN SPACE, AWAY FROM THESE ATMOSPHERIC LIMITATIONS, THAT SIGNIFICANTLY GREATER COOLING COULD BE ACHIEVED. SINCE THEN, A SIGNIFICANT AMOUNT OF TESTING HAS BEEN COMPLETED ON MANY DIFFERENT COATING MATERIALS. THE RESULTS OF THIS TESTING SHOW THAT WHEN COMBINED WITH MULTI-LAYER INSULATION TO SHIELD FROM EARTH RADIATION, IT SHOULD BE POSSIBLE TO PASSIVELY COOL A COMPONENT TO SIGNIFICANTLY LOW TEMPERATURES. THESE TEMPERATURES SHOULD BE ENOUGH TO PASSIVELY STORE CRYOGENS IN SPACE FOR AN EXTENDED PERIOD OF TIME. CUBESATS RECENTLY HAVE BECOME POPULAR IN THE SCIENTIFIC COMMUNITY. CUBESAT IS A TYPE OF SPACECRAFT THAT TYPICALLY USES COMMERCIAL, OFF-THE-SHELF ELECTRONIC COMPONENTS IN A SCALABLE CUBESAT FORM FACTOR WITH A MASS OF ONE KG AND A VOLUME OF TEN CUBIC CENTIMETERS. THESE SMALL FORM FACTOR SATELLITES PROVIDE A LOW COST OPTION TO PERFORM SCIENTIFIC RESEARCH AND DEMONSTRATE NEW SPACE TECHNOLOGIES IN ORBIT. | AI SOLUTIONS INC | $514,784 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541330Engineering Services | AR35 | Apr 15, 2019 | Apr 15, 2019 | Sep 30, 2022 | ||
| NESTED CAVITY RECIPROCAL FIELD STUDY STATEMENT OF WORK THE OBJECTIVE OF THIS ADDITIONAL SUPPORT IS TO DEVELOP THE TEST CASE AND ASSOCIATED STATISTICAL ANALYSIS TO DEMONSTRATE THE APPLICABILITY OF RECIPROCITY THEORY IN THE CHARACTERIZATION OF AN EXTERNAL REVERBERANT ENVIRONMENT USING AN INTERNAL SMALLER CAVITY (WHERE THE RESULTS ARE MORE READILY OBTAINED). BACKGROUND LAUNCH SERVICES PROGRAM (LSP)HAS WORKED WITH AI SOLUTIONS AND OKLAHOMA STATE UNIVERSITY TO STATISTICALLY CHARACTERIZE A CAVITY BY USING AN OUTER REVERBERATION CHAMBER CAPABILITY. THIS STUDY WILL EXAMINE THE RECIPROCAL NATURE OF THE NESTED CAVITY RADIATED AND INCIDENT FIELDS. CHARACTERIZING THE EXTERNAL ENVIRONMENT USING RECIPROCITY THEORY WILL SIGNIFICANTLY REDUCE THE COMPUTATION TIME REQUIRED TO VALIDATE AN INTERNAL ELECTROMAGNETIC ENVIRONMENT IN LAUNCH VEHICLE FAIRINGS. CURRENTLY ONLY SPOT CHECKS OF THIS EXTERNAL ENVIRONMENT CAN BE PERFORMED. TASKS PERFORM A SERIES OF TEST CASES TO SUPPORT AN ANALYSIS OF THE RECIPROCITY CONCEPT IN THE REVERBERANT NESTED CAVITY CONDITION. TEST WILL BE TEST BOX IN BOTH THE ANECHOIC CHAMBER TO REPRESENT THE RECIPROCAL PROBLEM INCLUDING SERIES OF MEASUREMENTS UNDER DIFFERENT CONDITIONS SUCH AS A SHORT PROBE, A LONG PROBE, DIFFERENT APERTURES, OVER-MODED AND UNDER-MODED SMALL CAVITY. O A. INTERNAL TUNER TEST O B. INTERNAL AND EXTERNAL TUNER TESTS. ANALYSIS ANALYZE THE TEST CASE AND RESULTS TO DEMONSTRATE THAT THE FULL STATISTICS OF THE NESTED CAVITY TEST CAN BE CAPTURED BY THE RADIATION TEST IN THE ANECHOIC CHAMBER. REPORT SHOULD INCLUDE A COMPARISON OF THIS WORK TO RELATED RECIPROCAL NUMERICAL RESULTS IN THE AREA OF INPUT IMPEDANCE AND FREQUENCY STIRRING STATISTICS AS WELL AS A SUMMARY OF PRACTICAL APPLICATIONS/BENEFITS TO THIS RECIPROCAL PRINCIPAL TO ELECTRICALMAGNETIC COMPATIBILITY (EMC) COMMUNITY. DELIVERABLES TEST PLAN TEST REPORT (INCLUDING ELECTRONIC DATA) ANALYSIS REPORT INCLUDING ANTICIPATED BENEFITS/PRACTICAL APPLICATIONS TO EMC COMMUNITY. ANTICIPATED PROJECT MILESTONES SCHEDULE (IN ATP PLUS) PHASE I 2 MONTHS - DEVELOP TEST PLAN 2-4 MONTH - PERFORM TESTING PHASE 4-6 MONTHS - ANALYSIS PHASE AND ADDITIONAL TESTING DEFINED BY THE ANALYSIS 7 MONTH - FINAL ANALYSIS AND TEST REPORT. DELIVERABLE FINAL REPORT OF TEST RESULTS, STATISTICAL ANALYSIS WITH SUMMARY OF PRACTICAL APPLICATIONS FOR THE EMC COMMUNITY. | AI SOLUTIONS INC | $74,994 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541330Engineering Services | AR35 | Mar 21, 2019 | Mar 21, 2019 | Feb 15, 2020 | ||
| THE PLANKTON, AEROSOL, CLOUD, OCEAN ECOSYSTEM (PACE) MISSION IS A STRATEGIC CLIMATE CONTINUITY MISSION THAT WAS DEFINED IN THE 2010 DOCUMENT RESPONDING TO THE CHALLENGE OF CLIMATE AND ENVIRONMENTAL CHANGE: NASAS PLAN FOR CLIMATE CENTRIC ARCHITECTURE FOR EARTH OBSERVATIONS AND APPLICATIONS FROM SPACE (REFERRED TO AS THE CLIMATE INITIATIVE). THE CLIMATE INITIATIVE COMPLEMENTS NASAS IMPLEMENTATION OF THE NATIONAL RESEARCH COUNCILS DECADAL SURVEY OF EARTH SCIENCE AT NASA, NOAA, AND USGS, ENTITLED EARTH SCIENCE AND APPLICATIONS FROM SPACE: NATIONAL IMPERATIVES FOR THE NEXT DECADE AND BEYOND. PACE WILL EXTEND THE HIGH QUALITY OCEAN ECOLOGICAL, OCEAN BIOGEOCHEMICAL, CLOUD, AND AEROSOL PARTICLE DATA RECORDS BEGUN BY NASA IN THE 1990S, BUILDING ON THE HERITAGE OF THE SEA-VIEWING WIDE FIELD-OF-VIEW SENSOR (SEAWIFS), THE MODERATE RESOLUTION IMAGING SPECTRORADIOMETER (MODIS), THE MULTI-ANGLE IMAGING SPECTRORADIOMETER (MISR), AND THE VISIBLE INFRARED IMAGING RADIOMETER SUITE (VIIRS). THE MISSION WILL BE CAPABLE OF COLLECTING RADIOMETRIC AND POLARIMETRIC MEASUREMENTS OF THE OCEAN AND ATMOSPHERE, FROM WHICH THESE BIOLOGICAL, BIOGEOCHEMICAL, AND PHYSICAL PROPERTIES WILL BE DETERMINED. PACE DATA PRODUCTS WILL NOT ONLY ADD TO EXISTING CRITICAL CLIMATE AND EARTH SYSTEM RECORDS, BUT ALSO ANSWER NEW AND EMERGING ADVANCED SCIENCE QUESTIONS RELATED TO EARTHS CHANGING CLIMATE. THE CONTRACTOR SHALL PROVIDE THE FACILITIES, PERSONNEL, SERVICES, TOOLS, EQUIPMENT, AND MATERIALS NECESSARY TO DESIGN, ANALYZE, MANUFACTURE, TEST, AND DELIVER THE HARDWARE AND DATA IN ACCORDANCE WITH THE REQUIREMENTS OF THIS SOW AND THE DOCUMENTS REFERENCED HEREIN. | MOOG INC. | $1,069,191 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 336415Guided Missile and Space Vehicle Propulsion Unit and Propulsion Unit Parts Manufacturing | AR35 | Oct 15, 2018 | Oct 15, 2018 | Dec 31, 2020 | ||
| THIS TASK ORDER IS A COST-PLUS-FIXED-FEE, FULLY FUNDED TASK ORDER UNDER CONTRACT NNK17LA01C. THE PURPOSE OF THIS TASK ORDER IS TO AUTHORIZE WORK ON SPECIAL STUDY LSP-18-012 MULTIPLATFORM TRANSIENT RECORDER STUDY OBJECTIVE: THE OBJECTIVE IS TO STUDY IS TO PROVIDE A FEASIBILITY STUDY REPORT AND PROTOTYPE HARDWARE OF AN EXPLOSION PROOF TRANSIENT RECORDER DESIGNED TO DETECT ELECTRIC/MAGNETIC FIELDS AND UMBILICAL CURRENTS DURING ALL PRE-LAUNCH PHASES INCLUDING VEHICLE ROLL-OUT/ERECTION BACKGROUND: SINCE ALL MISSIONS CAN BE EXPOSED TO LIGHTNING AND MANY AT REMOTE LOCATIONS HAVE MINIMAL LIGHTNING PROTECTION SYSTEMS, LIGHTNING MONITORING AND LIGHTNING EFFECTS MONITORING ARE COMMONLY REQUESTED BY OUR SPACECRAFT AND VEHICLES. THE CURRENT PORTABLE LIGHTNING INSTRUMENTATION SYSTEM CAN ONLY BE USED BEFORE ROLL-OUT. WHEN THE HIGH-SPEED TRANSIENT RECORDER IS INTEGRATED INTO THE PROPOSED SUPPORTING INFRASTRUCTURE DESCRIBED IN THIS STUDY, THE NEW LIGHTNING INSTRUMENTATION SYSTEM WOULD ALLOW OPERATORS TO ACCURATELY DETECT AND QUANTIFY ALL CONDUCTED AND RADIATED LIGHTNING-RELATED TRANSIENTS THAT MAY HAVE DELETERIOUS EFFECTS ON THE VEHICLE AND PAYLOAD. TASKS: EXPLORE THE POWER CONDITIONING/FILTERING, PURGING, ENVIRONMENTAL/ELECTROMAGNETIC SHIELDING, COMMUNICATION, AND RAPID DATA REPORTING FEATURES THAT WOULD BE REQUIRED TO SUPPORT THE INSTALLATION OF AN INTEGRATED, MULTI-CHANNEL HIGH-SPEED TRANSIENT RECORDER TO MONITOR THE VEHICLE/PAYLOAD DURING ALL PHASES OF LAUNCH OPERATIONS. THE STUDY WILL ALSO ADDRESS INSTALLATION FEASIBILITY OF THIS RUGGEDIZED TRANSIENT RECORDER AT BOTH THE ATLAS AND DELTA LAUNCH PADS IN ADDITION TO THE SPACEX TRANSPORTER ERECTOR. THE STUDY WILL: 1. CHASSIS: A. WITH THE POWER, THERMAL MANAGEMENT, AND COMMUNICATION INFRASTRUCTURE (IF THE STAND-ALONE OPTION IS PURSUED), OR B. THE HARDWARE REQUIRED TO PERFORM THE INTEGRATION INSIDE AN EXISTING JUNCTION BOX TO FULFILL THE REQUIREMENTS LISTED ABOVE. 2. TEST REPORT -THE PROTOTYPE DEVELOPMENT STUDY WOULD INCLUDE THERMAL TESTING TO VERIFY OUTDOOR AND CLASS 1 DIV II OPERATIONS. 3. FINAL REPORT DESCRIBING HARDWARE CHOICES AND INTERFACES. THE PROTOTYPES INCLUDE ALL THE REQUIRED INFRASTRUCTURE BUT THE DATA ACQUISITION PCB. | AI SOLUTIONS INC | $79,247 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541330Engineering Services | AR35 | Sep 28, 2018 | Oct 1, 2018 | Sep 30, 2019 | ||
| THIS PROJECT IS MEANT TO INVESTIGATE THE FEASIBILITY OF USING A CRYOGENIC SELECTIVE SURFACE COATING AS A NEW, MORE EFFICIENT WAY OF PASSIVELY COOLING COMPONENTS IN SPACE. INITIAL TESTS ON THE GROUND PROVE THIS COATING SHOULD PROVIDE A MUCH HIGHER REFLECTANCE OF THE SUN'S IRRADIANT POWER THAN ANY EXISTING COATIN, WHILE STILL PROVIDING FAR-INFRARED POWER EMISSION. THE SCOPE OF THIS STUDY WILL INCLUDE THE DEVELOPMENT OF A CONCEPTUAL STUDY FOR A CUBESAT THAT CAN TEST THE PERFORMANCE OF THE COATING IN SPACE. THE PRIMARY MISSION FOR THE CUBESAT IS TO MEASURE THE STEADY STATE TEMPERATURE OF A SMALL METALLIC OBJECT COATED WITH THE CRYOGENIC SELECTIVE SURFACE COATING IN SPACE. THESE ARE THE PRIMARY SCIENCE REQUIREMENTS FOR THE CUBESAT SYSTEM: 1. THE CUBESAT SHALL PROVIDE ADEQUATE SHIELDING FROM EARTH RADIATION AND FROM THE CUBESAT ITSELF USING, FOR EXAMPLE, MLI, SUCH THAT THE COATED SAMPLE IS NOT ADVERSELY HEATED. 2. THE CUBESAT SHALL INCLUDE A METHOD OF ATTACHING THE SAMPLE TO THE CUBESAT SUCH THAT MINIMAL HEAT IS CONDUCTED TO THE SAMPLE UNDER TEST. THE CUBESAT SHALL ORIENT THE COATED SAMPLE TOWARD DEEP SPACE (NOT TOWARD THE EARTH). 3. THE CUBESAT SHALL INCLUDE A MINIMUM OF 3 TEMPERATURE SENSORS THAT ARE RATED FOR AT LEAST 40K A. ONE SHALL BE USED TO MEASURE THE SAMPLE TEMPERATURE-LOCATED IN THE SMALL METALLIC OBJECT UNDER THE COATING B. ONE SHALL BE USED TO MEASURE THE TEMPERATURE OF THE WALL/STRUT CLOSEST TO THE SAMPLE C. ONE SHALL BE USED TO MEASURE THE TEMPERATURE OF THE INFRARED SHIELD 4. THE CUBESAT SHALL HAVE A MINIMUM OPERATIONAL LIFE OF 76 HOURS. 5. THE CUBESAT SHALL BE CAPABLE OF TRANSMITTING ALL COLLECTED DATA (MINIMUM 76 HOURS) BACK TO EARTH. THE CONTRACTOR SHALL DEVELOP A CONCEPTUAL STUDY OF THE CUBESAT AND DEVELOP A SERIES OF GEOMETRIC CONCEPTS FOR THE CUBESAT AND EXPERIMENTAL SETUP. FROM THESE CONCEPTS, THE CONTRACTOR SHALL DEVELOP SYSTEM REQUIREMENTS, AND TRADE STUDIES TO GIVE RATIONALE FOR THE BEST CONCEPT TO COMPLETE THE MISSION. THE CONTRACTOR SHALL HOLD BI-WEEKLY TELECONFERENCES WITH LSP, GIVE STATUS UPDATES AND PROVIDE MONTHLY WRITTEN STATUS REPORTS. | AI SOLUTIONS INC | $69,586 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541330Engineering Services | AR35 | Sep 13, 2018 | Sep 15, 2018 | Feb 15, 2019 | ||
| WEATHER SYSTEM FOLLOW-ON - MICROWAVE - SYSTEM DESIGN OF SATELLITE WITH MICROWAVE RADIOMETER AND SENSOR | BAE SYSTEMS SPACE & MISSION SYSTEMS INC. | $48,621,652 | DEPT OF THE AIR FORCE | DEPT OF THE AIR FORCE | — | 336414Guided Missile and Space Vehicle Manufacturing | AR35 | Nov 8, 2017 | Nov 15, 2017 | Jan 15, 2028 | ||
| IGF::OT::IGF BUILDING 839 UPGRADES PROJECT IN ACCORDANCE WITH THE STATEMENT OF WORK DATED JULY 2016 | AI SOLUTIONS INC | $474,817 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541330Engineering Services | AR35 | Sep 21, 2016 | Sep 21, 2016 | Mar 20, 2017 | ||
| IGF::OT::IGF SEARCH AND RESCUE SATELLITE (SARSAT) ANTENNA REMOVAL, PLATFORM DEMOLITION, AND LIGHTNING PROTECTION SYSTEM GRID COMPLETION PROJECT | AI SOLUTIONS INC | $57,885 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541330Engineering Services | AR35 | Aug 19, 2016 | Aug 19, 2016 | Oct 24, 2016 | ||
| IGF::OT::IGF NASA RESEARCH ANNOUNCEMENT AWARD - ADVANCED TUNABLE SEED LASER EFFORT TO BE CONDUCTED UNDER THIS CONTRACT: THE GOAL OF THIS EFFORT IS TO ACHIEVE A LOW COST, SIZE, WEIGHT AND POWER SEED DIODE LASER THAT WILL TIP THE SCALES FOR MARKET PENETRATION OF METHANE DETECTION SYSTEMS IN COMMERCIAL AND GOVERNMENT APPLICATIONS, INCLUDING NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (NASA) REMOTE SENSING APPLICATIONS. THIS LASER REPRESENTS A TIPPING POINT TECHNOLOGY IMPROVEMENT IN THE SEED LASER TECHNOLOGY AND WILL ENABLE SEVERAL DIFFERENT ROBUST AND COMPACT IMPLEMENTATIONS OF A LIDAR TRANSMITTERS FOR A METHANE INSTRUMENT, NEEDED FOR HIGH SPATIAL RESOLUTION, ACCURACY AND PRECISION MEASUREMENTS FROM ORBIT OR FROM UAV PLATFORMS. THE SAME TECHNOLOGY HAS SEVERAL COMMERCIAL APPLICATIONS SUCH AS PIPELINE LEAK DETECTION AND METHANE STORAGE FACILITIES MONITORING. THIS EFFORT IS THE RESULT OF A PROPOSAL SUBMITTED BY FREEDOM PHOTONICS 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-15STMD-001. OVERSIGHT FOR THIS DEVELOPMENT EFFORT WILL BE THROUGH STMDS GAME CHANGING DEVELOPMENT (GCD) PROGRAM OFFICE. THE SCOPE OF THIS EFFORT IS AS FOLLOWS: FREEDOM PHOTONICS WILL WORK IN COLLABORATION WITH OUR NASA GODDARD SPACE FLIGHT CENTER (GSFC) PARTNERS TO DEVELOP A SEED LASER TO BE USED IN THE EXISTING GSFC METHANE LIDAR TO DEMONSTRATE AND VALIDATE METHANE MEASUREMENTS ON THE GROUND AND FROM AN AIRBORNE PLATFORM (IF POSSIBLE). THE LASER WILL BE ELECTRICALLY FAST-TUNABLE AROUND THE METHANE ABSORPTION LINE AND IT WILL GENERATE OPTICAL POWER WITH A NARROW LINEWIDTH. THE LASER WILL CONSIST OF A FAST TUNABLE DBR LASER INTEGRATED WITH A HIGH-POWERED, TAPERED OPTICAL AMPLIFIER, USING BUTT-JOINT GROWTH TECHNOLOGY. THIS EFFORT WILL CULMINATE WITH HARDWARE DELIVERABLES TO GSFC MEETING APPLICATION PERFORMANCE REQUIREMENTS. | FREEDOM PHOTONICS LLC | $1,644,583 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541712 | AR35 | Aug 12, 2016 | Aug 12, 2016 | Aug 15, 2019 | ||
| IGF::OT::IGF MODIFIED ADVANCED CREW ESCAPE SUIT (ACES) THE CREW AND THERMAL SYSTEMS DIVISION SPACE SUIT AND CREW SURVIVAL BRANCH (EC5) AT JSC IS DEVELOPING THE LAUNCH/ENTRY SUIT FOR ORION. THIS SUIT IS A MODIFIED VERSION OF THE SPACE SHUTTLE PROGRAM (SSP) MODEL S1035 ADVANCED CREW ESCAPE SUIT (ACES). THE ACES WAS DEVELOPED AND QUALIFIED FOR IVA AND CREW BAILOUT MODALITIES, HOWEVER EXPERIENCE TO DATE HAS SUGGESTED THAT THE ENSEMBLE MAY POSSESS SOME INHERENT CAPABILITIES TO CONDUCT EVA. IN ORDER TO ASSESS THE CURRENT S1035 ACES BASELINE IN THIS REGARD, FEASIBILITY ASSESSMENTS ARE BEING PERFORMED FOR THE ORION PROGRAM AND THE ADVANCED EXPLORATION SYSTEMS (AES) OFFICE TO CHARACTERIZE PRESSURIZED MOBILITY AND OPERABILITY OF THE MODIFIED ACES. THESE ASSESSMENTS ARE BEING PERFORMED AT THE NASA JSC SONNY CARTER FACILITY NEUTRAL BUOYANCY LABORATORY (NBL). TO SUPPORT THIS TESTING, SEVERAL NEW COMPONENTS AND ALTERATIONS MUST BE ADDED TO THE ACES TO MAKE IT SUITABLE FOR THE UNDERWATER ASSESSMENTS. THIS ORDER WILL BE TO PROCURE THE NECESSARY HARDWARE AND SERVICES REQUIRED TO SUCCESSFULLY COMPLETE THESE ASSESSMENTS. THIS TASK WILL CONSIST OF MODIFYING/BUILDING FOUR SUITS (ALL CLASS III-W) THAT WILL BE FOR NBL USE: QTY-1 SIZE MEDIUM-REGULAR ORION BASELINE MODIFIED ACES (MACES) NOTE: THIS SUIT IS CURRENTLY IN USE IN THE NBL AND WILL BE UPDATED VIA THIS PROCUREMENT QTY-1 SIZE LARGE-REGULAR ORION BASELINE MODIFIED ACES (MACES) QTY-1 SIZE MEDIUM-REGULAR ORION BASELINE MODIFIED ACES WITH ARM BEARINGS (MACES-AB) QTY-1 SIZE LARGE-REGULAR ORION BASELINE MODIFIED ACES WITH ARM BEARINGS (MACES-AB) THE SUITS WILL BE PROVIDED TO THE VENDOR FROM NASA INVENTORY AS REQUIRED FOR MODIFICATIONS AND ASSEMBLY. ALL HARDWARE WILL BE DELIVERED AS PROTOTYPE AND WILL NOT BE CONSIDERED CERTIFIED FOR FLIGHT. THERE ARE NO SHELF LIFE REQUIREMENTS ASSOCIATED WITH THIS SOW. REPORTING REQUIREMENTS FOR THE ACCEPTABILITY OF HARDWARE WILL ONLY INCLUDE THE TESTING PERFORMED AND THE MATERIALS OF CONSTRUCTION USED. EACH ITEM OF A NEW CONFIGURATION SHALL BE ASSIGNED A UNIQUE PART NUMBER FOR TRACKING PURPOSES. NASA WILL BE RESPONSIBLE FOR QUALIFYING THE HARDWARE FOR USE IN THE NBL. | DAVID CLARK COMPANY INCORPORATED | $298,845 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 339113Surgical Appliance and Supplies Manufacturing | AR35 | Aug 5, 2013 | Aug 5, 2013 | Jan 10, 2014 | ||
| IGF::OT::IGF - CONTRACTOR SHALL DELIVER A DSCOVR FC USER'S GUIDE THAT INCLUDES AND EMERGENCY INSTRUMENT OPERATIONS AND COMMANDING. - CONTRACTOR SHALL DELIVER A DSCOVR FC ALGORITHM DOCUMENT THAT DETAILS PHYSICAL AND COMPUTATIONAL ALGORITHMS TO CONVERT THE RAW FC TELEMETRY INTO SOLAR WIND KEY PARAMETERS. - CONTRACTOR SHALL DELIVER A TEST CODE THAT IMPLEMENTS THE FC DATA PROCESSING ALGORITHMS FOR A SIMULATED TELEMETRY FILE. - CONTRACTOR SHALL PROVIDE EXPERT TECHNICAL CONSULTATION SUPPORT TO THE DSCOVR PROJECT WHILE THE OPERATIONAL FC GROUND SEGMENT IS IMPLEMENTED AND TESTED. | SMITHSONIAN INSTITUTION | $191,084 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541712 | AR35 | Jun 27, 2013 | Jun 27, 2013 | Nov 30, 2015 | ||
| IGF::OT::IGF - THE DEPLOYABLE VEGETABLE PRODUCTION SYSTEM (VEGGIE) WAS ORIGINALLY CONCEIVED BY ORBITEC IN 1996 AS A WAY TO PRODUCE PALATABLE, NUTRITIOUS, AND SAFE FRESH FOOD IN A SPACE HABITAT WITH MINIMAL RESOURCES. IN 2003 A SBIR PHASE I GRANT WAS AWARDED TO PROVIDE DEVELOPMENT OF THE VEGGIE CONCEPT. THE SYSTEM WAS FURTHER DEVELOPED UNDER A SUBSEQUENT PHASE II SBIR AWARDED IN 2004 (CONTRACT NO. NNK04OA5C). THESE TWO SBIR S HAVE LED TO ORBITEC PARTICIPATING IN THE VEGGIE INNOVATIVE PARTNERSHIP PROGRAM (IPP) IN 2009-2010 (PHASE III CONTRACT NNK09EA88P) WITH NASA S KENNEDY SPACE CENTER (KSC). AS PART OF THE VEGGIE IPP, ORBITEC ADVANCED THE DESIGN OF THE VEGGIE UNIT CLOSER TO A FLIGHT QUALIFIABLE PACKAGE, DEVELOPED AN UPDATED PROTOTYPE (FIGURE 1) AND CONDUCTED PRELIMINARY VERIFICATION TESTING ON THIS HARDWARE WHICH WAS THEN DELIVERED TO KSC. THIS PROPOSED PHASE III EFFORT UTILIZES THE WORK PREVIOUSLY CONDUCTED TO FABRICATE, VERIFY, AND PROVIDE VEGGIE FLIGHT UNITS TO KSC FOR USE ON ISS. 1.1 OBJECTIVES AND EXPECTED SIGNIFICANCE THE OBJECTIVE OF THE PROPOSED PROJECT IS TO RAPIDLY PROVIDE TWO (2) VEGGIE FLIGHT HARDWARE SYSTEMS FOR TESTING (IN THE FORM OF A DETAILED TEST OBJECTIVE (DTO)) ABOARD THE ISS. IT IS DESIRABLE TO IMPLEMENT THESE SYSTEMS WHILE A LONG-DURATION MICROGRAVITY TEST PLATFORM (ISS) IS AVAILABLE, AND SO THAT THE TECHNOLOGY CAN BE ADEQUATELY PROVEN IN TIME FOR IMPLEMENTATION FOR FUTURE MISSIONS SUCH AS THE LUNAR SURFACE AND A MARS TRANSIT ENVIRONMENT. THE PROPOSED PROJECT WOULD LEVERAGE PREVIOUS VEGGIE WORK TO ACCELERATE THE HARDWARE DEVELOPMENT AND REDUCE PROGRAM RISK. 1.2 HARDWARE OVERVIEW THE VEGGIE CONCEPT IS BASED ON THE USE OF COLLAPSIBLE GROWING MODULES THAT CAN BE STORED IN A SMALL VOLUME (FIGURE 2). APPROXIMATELY 1M2 OF GROWING AREA CAN BE STOWED WITHIN A CARGO TRANSFER BAG (JSC-39233 REV. D, CARGO TRANSFER BAG INTERFACE DESIGN DOCUMENT). VEGGIE PROVIDES LIGHTING AND WATER/NUTRIENT DELIVERY, BUT UTILIZES THE CABIN ENVIRONMENT FOR TEMPERATURE CONTROL AND AS A SOURCE OF CO2 TO MINIMIZE COMPLEXITY AND POWER REQUIREMENTS. THE VEGGIE SYSTEM COMPRISES THREE MAJOR COMPONENTS: THE LIGHT CAP, THE ENCLOSURE, AND THE ROOTING MAT. THE CORE OF THE VEGGIE SYSTEM IS THE SOLID-STATE LIGHTING UNIT. THE COMPACT CONFIGURATION OF THIS SYSTEM IS ONLY POSSIBLE USING VERY LOW PROFILE ARRAYS OF LEDS. THESE SOLID-STATE LIGHTS HAVE PROPERTIES THAT CAN BE MANIPULATED TO PRODUCE HIGH LIGHT LEVELS WITH LESS POWER THAN OTHER LIGHTING TECHNOLOGIES. LEDS ALSO ELIMINATE MANY OF THE HAZARDS OF STANDARD LIGHTING SYSTEMS LIKE HIGH TOUCH TEMPERATURES AND THE USED OF TOXIC MATERIALS LIKE MERCURY. THE VEGGIE ENCLOSURE IS IN A BELLOWS CONFIGURATION AS THIS FORM REQUIRES MINIMUM HARDWARE (LIGHTWEIGHT AND LOW VOLUME), ALLOWS RAPID DEPLOYMENT AND RE-STOW, PROVIDES A SOFT ENCLOSURE FOR THE GROWING AREA, SUPPORTS ELEVATED HUMIDITY LEVELS IN THE GROWING AREA, AND ALLOWS ADJUSTMENT TO MAINTAIN A FIXED DISTANCE BETWEEN THE GROWING PLANT CANOPY AND THE LIGHT CAP. DIFFERENT TYPES OF ROOTING SYSTEMS CAN BE USED WITH THE VEGGIE DESIGN. THE ORIGINAL ROOTING SYSTEM DESIGN CONSISTS OF A CAPILLARY ROOTING MAT TO PROVIDE WATER AND NUTRIENT DELIVERY IN REDUCED GRAVITY. THE SYSTEM USES A THIN MAT FORMED FROM NOMEX THAT CAN ACCOMMODATE A VARIETY OF HORTICULTURAL CROPS AND CAN BE SWAPPED OUT OF THE GROWING UNIT WHEN DESIRED. THE ROOT MAT CAN ACCOMMODATE A NUTRIENT SOLUTION SUPPLY SUFFICIENT FOR SEVERAL DAYS, DEPENDING ON THE CROP, AND MEETS ALL NASA SAFETY REQUIREMENTS. THE NOMEX MAT IS PARTIALLY SEALED INTO A TEFLON RESERVOIR, AND HOUSED IN AN OPAQUE TEFLON POUCH. WATER OR NUTRIENT SOLUTION IS WICKED FROM THE SEALED RESERVOIR INTO THE NOMEX MAT. NOMEX WAS USED BECAUSE IT IS A GOOD WICKING MATERIAL WHILE ALSO MEETING NASA FLAMMABILITY AND OUTGASSING REQUIREMENTS. THESE MATS ARE THIN ENOUGH TO BE DISPOSABLE, BUT ALSO ROBUST ENOUGH TO BE DISINFECTED IN SITU USING FOOD GRADE DISINFECTANTS SO THAT EACH ROOT MAT COULD GROW MULTIPLE CROPS, REDUCING RESUP | ORBITAL TECHNOLOGIES CORPORATION | $121,240 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541712 | AR35 | Dec 6, 2012 | Dec 6, 2012 | Nov 30, 2013 | ||
| THIS PROCUREMENT CONSISTED OF THE MACHINING OF HD3 TEST SECTION AND HD3 CLOSEOUT PARTS, AND THE PARTS ARE BEING PURCHASED FOR EP, PROPULSION AND POWER DIVISION. NASA IS PURCHASING THE INTERNAL AND EXTERNAL COMPONENTS OF A LIQUID METHANE VAPORIZATION EXPERIMENT. THESE TWO CUSTOM MACHINED STAINLESS STEEL PARTS ARE DESIGNED TO FIT TOGETHER, AND WHEN BRAZED INTO ONE PART, WILL CREATE A SEALED HIGH-FLOW HEAT EXCHANGER. THE PRECISION OF THESE PARTS IS OF THE UTMOST IMPORTANT TO THIS EFFORT TO MAINTAIN CONSISTENCY THROUGHOUT THE EXPERIMENT. THE COMPLETED PARTS MUST BE MACHINED TO TIGHT TOLERANCES ON FIT AND FINISH, (<=0.005 TOLERANCE TO MODEL, SURFACE FINISH 125 UINCH IN THE RIBS AND<30 UINCH ELSEWHERE), SO THAT THE EXPERIMENT WILL FUNCTION CORRECTLY. THE PURPOSE OF THE EXPERIMENT IS TO VALIDATE A COMPUTER MODEL THAT WILL BE USED TO DESIGN A FULL-SIZE HEAT EXCHANGER IN THE FUTURE. THE PARTS SHOULD BE MADE OF 304 OR 316 STAINLESS STEEL AND SHOULD BE MADE BY THE SAME VENDOR, SO THAT THE CLOSE FIT CAN BE TESTED DURING MANUFACTURE. THE VENDOR WILL FOLLOW THE COMPUTER AIDED DESIGN DRAWINGS SUPPLIED BY THE NASA PROPULSION AND DIVISION. THE ANALYSIS FOR THIS EXPERIMENT WAS PERFORMED USING A COMPUTER CODE DEVELOPED SPECIFICALLY AT JSC FOR THIS PURPOSE. THE CODE WILL BE MODIFIED TO MATCH THE AS-BUILT PART, SO STRINGENT CONTROL OF THE TOLERANCES AND SURFACE FINISH ARE NOT AS IMPORTANT AS DETERMINING THE AS-BUILT DIMENSIONS. THESE PARTS COULD BE MANUFACTURED IN A VARIETY OF MEANS, AND THE PROPULSION. MILLING THE PARTS FROM A SOLID BLOCK IS PREFERRED BUT CASTING THE PART WITH POST-PROCESS SMOOTHING OR USING ADDITIVE MANUFACTURING TO BUILD UP THE PART WITH POST-PROCESS MACHINING ARE ALTERNATIVES. IF MILLING IS NOT CHOSEN AS THE MANUFACTURING METHOD, COUPONS WITH REPRESENTATIVE MATERIAL PROPERTIES NEED TO BE PROVIDED BY THE VENDOR. | RAILFLYER MODEL PROTOTYPES INC | $0 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 332710Machine Shops | AR35 | Jul 25, 2012 | Jul 25, 2012 | Aug 6, 2012 | ||
| HEAT STRAP MODIFICATIONS AND MIRI SHIELD STRAP. THIS EFFORT ENTAILS TWO MAJOR TASKS REQUIRED TO SUPPORT THE JAMES WEBB SPACE TELESCOPE PROJECT: 1. MODIFICATIONS TO EXISTING PROTO FLIGHT HEAT STRAPS AND THEIR COMPOSITE SUPPORT FLEXURES TO ACCOMMODATE RECENTLY MANDATED INTERFACE CHANGES TO THE MOUNT SURFACES ON THE BACKPLANE SUPPORT FIXTURE (BSF). INCLUDED WITH THIS TASK IS THE MINOR MODIFICATION TO EXISTING STRAP END-BLOCKS TO ACCOMMODATE SMALL HEATERS AND TEMPERATURE SENSORS FOR TESTING AT GSFC, AND 2. FABRICATION ORA SINGLE PROTOF1IGHT HEAT STRAP OF HIGH PURITY ALUMINUM TO COUPLE THE MIRI SHIELD WITH TBE COOLER HEAT EXCHANGER. | UTAH STATE UNIVERSITY SPACE DYNAMICS LABORATORY | $819,527 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 334511Search, Detection, Navigation, Guidance, Aeronautical, and Nautical System and Instrument Manufacturing | AR35 | May 16, 2011 | May 13, 2011 | Aug 31, 2013 | ||
| CARGO MISSION CONTRACT (CMC2) | LEIDOS, INC. | $199,493,641 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541690Other Scientific and Technical Consulting Services | AR35 | Dec 10, 2010 | Jan 1, 2011 | Mar 31, 2018 | ||
| LUNAR ATMOSPHERE DUST ENVIRONMENT EXPLORRER (LADEE) ULTRAVIOLET SPECTROMETER (UVS) PER THE ATTACHED STATEMENT OF WORK. ATTACHMENT J.1 | The Charles Stark Draper Laboratory, Inc. | $1,136,457 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541330Engineering Services | AR35 | Sep 30, 2010 | Sep 30, 2010 | Jul 31, 2013 | ||
| CONSTELLATION SPACE SUITE SYSTEM/CSSS CONTRACT IS TO DESIGN, DEVELOP, TEST, EVALUATE, CERTIFY, PRODUCE, PROCESS, AND PROVIDE SUSTAINING ENGINEERING FOR HARDWARE AND ASSOCIATED SOFTWARE TO SUPPORT THE MULTIPLE CONSTELLATION MISSION REQUIREMENTS DEFINED HEREIN. SPECIFICALLY THE CSSS HARDWARE WILL PROVIDE FOR LEA AND 0-G EVA CAPABILITY FOR INDIVIDUAL CREWMEMBERS DURING ORION MISSIONS. ADDITIONALLY, THIS CONTRACT WILL PROVIDE HARDWARE FOR CREW SURVIVAL AND SURFACE EVA CAPABILITY FOR LUNAR MISSIONS. TO SUPPORT THESE CAPABILITIES, THE CSSS CONTRACT WILL INCLUDE SPACE SUIT HARDWARE, VEHICLE INTERFACE HARDWARE, GROUND SUPPORT EQUIPMENT (GSE), AND ANCILLARY EVA RELATED HARDWARE AS DEFINED HEREIN. | OCEANEERING INTERNATIONAL INC | $1,120,202,245 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541712 | AR35 | Feb 27, 2009 | Feb 27, 2009 | Sep 30, 2020 | ||
| THE GOVERNMENT IS PROCURING THE NEXT-GENERATION GEOSTATIONARY OPERATIONAL ENVIRONMENTAL SATELLITES (GOES) SERIES TO CONTINUE ITS MISSION THROUGH NEW REQUIREMENTS SPECIFIED IN THE GOES-R LEVEL I REQUIREMENTS DOCUMENT AND MISSION REQUIREMENTS DOCUMENT (MRD). THE FIRST SATELLITE OF THIS NEW SERIES, DESIGNATED AS GOES-R, WILL PROVIDE THE FIRST MAJOR IMPROVEMENT IN INSTRUMENT TECHNOLOGY SINCE GOES-I LAUNCHED IN 1994. THE GOES-R SERIES WILL INTRODUCE OTHER NEW TECHNOLOGIES IN BOTH THE SPACE AND GROUND SEGMENTS. THESE ADVANCES WILL IMPROVE THE NATION'S ABILITY TO MONITOR AND FORECAST WEATHER AND ENVIRONMENTAL PHENOMENA WITH A SIGNIFICANT INCREASE IN THE NUMBER OF PRODUCTS. ONE OF NOAA'S PRINCIPAL MISSIONS IS TO PROVIDE FORECASTS AND WARNINGS FOR THE UNITED STATES, ITS TERRITORIES, ADJACENT WATERS AND OCEAN AREA FOR THE PROTECTION OF LIFE AND PROPERTY AND ENHANCEMENT OF THE NATIONAL ECONOMY. THIS MISSION REQUIRES THE CAPABILITY TO ACQUIRE, PROCESS, AND DISSEMINATE ENVIRONMENTAL DATA ON AN EXTENSIVE SPATIAL RANGE (GLOBAL, REGIONAL AND LOCAL) ON A VARIETY OF TIME SCALES. THESE DATA INCLUDE, BUT ARE NOT LIMITED TO: GLOBAL IMAGERY; CLOUD AND PRECIPITATION PARAMETERS; ATMOSPHERIC PROFILES OF TEMPERATURE, MOISTURE, WINDS, AEROSOLS, AND OZONE; SURFACE CONDITIONS CONCERNING ICE, SNOW AND VEGETATION; OCEAN PARAMETERS AND SEA-SURFACE TEMPERATURE; AND SOLAR AND IN-SITU SPACE ENVIRONMENT CONDITIONS. THE STATEMENT OF WORK (SOW) DEFINES THOSE TASKS TO DESIGN, ANALYZE, VALIDATE, DEVELOP, FABRICATE, ASSEMBLE, INTEGRATE, TEST, VERIFY, EVALUATE, DELIVER GOES-R SERIES SATELLITES AND SUPPORT LAUNCH AND POST LAUNCH, SUPPLY AND MAINTAIN THE GROUND SUPPORT EQUIPMENT (GSE), AND SUPPORT THE NOAA SATELLITE OPERATIONS CONTROL CENTER (SOCC). THE CONTRACTOR SHALL PROVIDE THE PERSONNEL, MATERIALS, FACILITIES, AND OTHER RESOURCES TO DESIGN, VALIDATE, FABRICATE, ASSEMBLE, INTEGRATE, TEST, VERIFY, AND DELIVER GOES-R SERIES SATELLITES AND PROVIDE PRE-LAUNCH, LAUNCH, AND POST-LAUNCH SUPPORT AND TRAINING UNDER THE BASIC CONTRACT, AND OPTIONS WHEN EXERCISED BY THE GOVERNMENT. | LOCKHEED MARTIN CORP | $2,127,139,419 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL OCEANIC AND ATMOSPHERIC ADMINISTRATION | — | 336414Guided Missile and Space Vehicle Manufacturing | AR35 | Dec 4, 2008 | Dec 4, 2008 | Apr 30, 2039 | ||
| INTEGRATED MISSION OPERATIONS CONTRACT (IMOC) PROVIDES SUPPORT AND PRODUCTS FOR THE MISSION OPERATIONS DIRECTORATE (MOD) AND FLIGHT CREW OPERATIONS DIRECTORATE (FCOD) GROUND-BASED HUMAN SPACEFLIGHT OPERATIONS CAPABILITY DEVELOPMENT AND EXECUTION. THIS INCLUDES THE SUPPORT TO MISSION PREPARATION (PLAN), CREW AND FLIGHT CONTROLLER TRAINING (TRAIN), AND REAL-TIME MISSION EXECUTION (FLY) ACTIVITIES RELATED TO EXPLORATION OPERATIONS AND THE INTERNATIONAL SPACE STATION (ISS) OPERATIONS (POST SHUTTLE RETIREMENT). OPERATIONS CAPABILITY DEVELOPMENT SUPPORT IS REQUIRED FROM THE CONTRACTOR AS NASA DEFINES OPERATIONS REQUIREMENTS ASSOCIATED WITH THE EMERGING PROGRAMS FOR THE EXPLORATION INITIATIVES (PRIMARILY THE CONSTELLATION PROGRAM, BUT TO A LESSER EXTENT THE LUNAR PRECURSOR ROBOTIC PROGRAM, THE HUMAN RESEARCH PROGRAM, THE EXPLORATION TECHNOLOGY PROGRAM, AND THE COMMERCIAL CREW AND CARGO PROGRAM). INITIALLY, THE IMOC CONTRACT WILL PROVIDE FOR HUMAN SPACEFLIGHT OPERATIONS CAPABILITY DEVELOPMENT EXCLUSIVE OF THE SPACE SHUTTLE PROGRAM (SSP) AND INTERNATIONAL SPACE STATION PROGRAM (ISSP). POST SHUTTLE RETIREMENT, THIS CONTRACT WILL ALSO INCLUDE SUPPORT AND PRODUCTS FOR THE ISS PLAN-TRAIN-FLY (PTF) MISSION OPERATIONS. THE IMOC WILL INITIALLY PROVIDE NASA CONSTELLATION PROGRAM (CXP) PTF SUPPORT THAT FULLY REPLACES THE NASA CXP SUPPORT TASKS PERFORMED UNDER THE STATEMENT OF WORK (SOW) SECTION 1.10, CONSTELLATION SUPPORT PROVISIONING, OF THE SPACE PROGRAM OPERATIONS CONTRACT (SPOC). UPON COMPLETION OF THE NASA WORK FOR THE SSP MISSIONS, THE IMOC WILL TAKE OVER THE NASA ISS SUPPORT PREVIOUSLY PERFORMED UNDER THE SPOC CONTRACT. THE GOVERNMENT WILL LEAD AND IS RESPONSIBLE FOR MISSION EXECUTION AND REQUISITE MISSION PREPARATION TASKS, NEW CAPABILITY DEVELOPMENT, NON-MISSION SPECIFIC PROGRAMMATIC SUPPORT TASKS, AND DISPOSITION OF ANOMALIES. THE CONTRACTOR WILL PROVIDE TECHNICAL INFORMATION, ANALYSIS, AND RELEVANT PERSPECTIVES GAINED THROUGH OPERATIONAL EXPERIENCE. THE GOVERNMENT, USING SUBJECTIVE JUDGMENT, WILL DEFINE REQUIREMENTS AND DEVELOP SPECIFICATIONS FOR FUTURE USE. THE CONTRACTOR WILL NOT BE REQUIRED TO PREPARE, OR ASSIST IN PREPARING, WORK STATEMENTS, SPECIFICATIONS, OR REQUIREMENTS TO BE USED IN COMPETITIVELY ACQUIRING SERVICES, OR TO PROVIDE MATERIAL LEADING DIRECTLY, PREDICTABLY, AND WITHOUT DELAY TO SUCH WORK STATEMENTS, SPECIFICATIONS, OR REQUIREMENTS UNLESS THE INTENDED PROCUREMENT IS A SOLE SOURCE TO THE CONTRACTOR, THE CONTRACTOR HAS PARTICIPATED IN THE DEVELOPMENT AND DESIGN WORK, OR UNLESS MORE THAN ONE CONTRACTOR HAS BEEN INVOLVED IN PREPARING THE WORK STATEMENT. IN ADDITION, THE CONTRACTOR WILL NOT BE REQUIRED TO EVALUATE ITS CONTRACTUAL PERFORMANCE OR PRODUCTS OR THAT OF ITS COMPETITORS. | UNITED SPACE ALLIANCE, LLC | $0 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541712 | AR35 | Oct 28, 2008 | Nov 1, 2008 | Sep 30, 2014 | ||
| CONSTELLATION SPACE SUIT SYSTEMS THE PURPOSE OF THE CSSS CONTRACT IS TO DESIGN, DEVELOP, TEST EVALUATE, CERTIFY AND PRODUCT, PROCESS AND PROVIDE SUSTAINING ENGINEERING FOR HARDWARE AND ASSOCIATED SOFTWARE TO SUPPORT THE MULTIPLE CONSTELLATION MISSION REQUIREMENTS. SPECIFICALLY THE CSSS HARDWARE WILL PRODUCE FOR LEA AND O-G EVA CAPABILITY FOR INDIVIDUAL CREWMEMBERS DURING ORION MISSIONS. ADDITIONALLY, THIS CONTRACT WILL PROVIDE HARDWARE FOR CREW SURVIVAL AND SURFACE EVA CAPABILITY FOR LUNAR MISSIONS TO SUPPORT THESE CAPABILITIES, THE CSSS CONTRACT WILL INCLUDE SPACE SUITE HARDWARE, VEHICLE INTERFACE HARDWARE, GROUND SUPPORT EQUIPMENT, (GSE) AND ANCILLARY EVA RELATED HARDWARE. THE CSSS CONTRACT IMPLEMENTATION STRATEGY REQUIRES A PHASED DEVELOPMENT AND CERTIFICATION APPROACH TO COMPLEMENT THE PHASED CXP MISSION REQUIREMENTS WHILE MINIMIZING THE NECESSITY TO DEVELOP MULTIPLE UPGRADES AND/OR CONTINUALLY RECERTIFY EVA ELEMENTS. THIS IS ACHIEVED BY IMPLEMENTING A SPACE SUIT SYSTEM CONSISTING OF A MINIMUM SET OF HARDWARE REQUIRED TO MEET ALL MISSION PHASE REQUIREMENTS. THIS IS EXECUTED BY DEVELOPING A SET OF COMPONENTS WITH AS MUCH COMMONALITY BETWEEN MISSION PHASES AS TECHNICALLY PRACTICAL AND PROVIDING A MODULAR, OPEN ARCHITECTURE DESIGN TO ALLOW FOR COST EFFECTIVE UPGRADES. THE RESULTING SPACE SUIT SYSTEM CONCEPT WILL REDUCE THE NUMBER OF SUIT COMPONENTS THAT DIFFER BETWEEN EACH MISSION PHASE, THEREBY REDUCING OVERALL UP-MASS AND LIFE CYCLE COST. | OCEANEERING INTERNATIONAL INC | $1,011,672 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541712 | AR35 | Jun 12, 2008 | Jun 30, 2008 | Jul 17, 2008 | ||
| THE MK-III SPACE SUIT TECHNOLOGY DEMONSTRATOR WAS DEVELOPED IN THE 1980S AS A PROTOTYPE TO SERVE AS A TEST BED TO INVESTIGATE DIFFERENT TYPES OF SUIT JOINT MOBILITY SYSTEMS THAT CAN BE USED IN THE DESIGN OF FUTURE PLANETARY EXPLORATION SPACE SUITS. THE HARDWARE ON THE SPACE SUIT WAS- AND STILL IS- FABRICATED AND DESIGNED BY AIR-LOCK, INC.; THE SOFT GOODS WERE A PRODUCT OF ILC DOVER. OVER THE PAST 20 YEARS, THE USES FOR THE MK-III SPACE SUIT TECHNOLOGY DEMONSTRATOR HAVE BEEN QUITE VARIED. MOST RECENTLY THE SUIT HAS BEEN SERVING IN COMPARATIVE SPACE SUIT TESTING WITH OTHER STYLES OF PROTOTYPE SPACE SUITS AND CURRENT FLIGHT PROGRAM SPACE SUIT CONFIGURATIONS. THE COMPARATIVE ANALYSIS ALLOWS ENGINEERS TO PUT QUANTITATIVE VALUES TO THE SUBJECTIVE DATA THAT HAS BEEN COLLECTED WITH RESPECT TO SUIT MOBILITY. TEST DATA IS BEING USED BY THE EXPLORATION PROGRAM TO DEVELOP REQUIREMENTS FOR LUNAR SURFACE EXTRA VEHICULAR ACTIVITY TASKS. FUNCTIONAL MOBILITY RANGE OF MOTION TESTING HAS INCLUDED THE FOLLOWING ACTIVITIES: WALKING, CRAWLING, KNEELING, ASCENDING AND DESCENDING A LADDER, TRANSLATING UP AND DOWN AN INCLINED SURFACE, SHOVELING, HAMMERING, INGRESSING AND EGRESSING SEATS, AND THE OPERATION OF MULTIPLE HATCH ACTUATION CONCEPTS. FURTHER THE MK-III, HAS BEEN UTILIZED ON THE REDUCED GRAVITY AIRCRAFT FOR INTERFACE FEASIBILITY TESTING WITH THE CONSTELLATION PROGRAM ORION VEHICLE SIDE HATCH, THE LOW IMPACT DOCKING SYSTEM TUNNEL, AND MICRO-GRAVITY SPACE SUIT DON AND DOFF TESTING. THE MK-III SPACE SUIT TECHNOLOGY DEMONSTRATOR ALSO SERVES AS THE PRIMARY SUIT FOR THE DESERT RESEARCH AND TECHNOLOGY STUDIES CONDUCTED EACH YEAR IN ARIZONA. THE DESERT RESEARCH AND TECHNOLOGY STUDIES ACTIVITIES CENTER AROUND THE DEVELOPMENT AND TESTING OF HARDWARE AND MISSION OPERATIONS ANTICIPATED FOR FUTURE PLANETARY EXPLORATION PROGRAMS. MOST NOTABLY, THE MK-III SPACE SUIT TECHNOLOGY DEMONSTRATOR HAS BE USED TO STUDY THE INTERFACES BETWEEN A SUITED SUBJECT AND THE SCIENCE, CREW, OPERATIONS AND UTILITY TEST BED (SCOUT), WHICH IS A COMBINATION PLANETARY ROVING VEHICLE AND ROBOTIC ASSISTANT. THE INTERFACES STUDIED INCLUDE THE SUIT TO SEAT INTERFACE, THE SUIT TO DISPLAYS INTERFACE, AND THE SUIT TO CONTROLS INTERFACE. | AIR-LOCK, INCORPORATED | $40,379 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | — | 332510Hardware Manufacturing | AR35 | Sep 7, 2007 | Sep 10, 2007 | Mar 31, 2008 |