POPULAR, INC.

IGF::CL::IGF TO STRENGTHEN THE COMMITMENT AND THE CAPABILITIES OF GOVERNMENT OF MEXICO (GOM) AND CIVIL SOCIETY INSTITUTIONS TO OPERATE HUMAN RIGHTS PROTECTION SYSTEMS THAT PREVENT AND DETER VIOLATIONS, IMPROVE PREVENTION EFFORTS, AND REDUCE HIGH IMPUNITY, WHILE INCREASING VISIBLE POLITICAL LEADERSHIP AND BROADENING POPULAR DEMAND, IN ORDER TO IMPROVE PROTECTION OF JOURNALISTS AND HUMAN RIGHTS DEFENDERS IN MEXICO

UNIVERSAL RECONFIGURABLE TRANSLATOR MODULE CURRENTLY, PRINTED CIRCUIT BOARDS (PCBS) ARE DESIGNED AND BUILT TO A SPECIFIC STANDARD INTERFACE. THESE PCBS ARE NOT EASILY RE-USABLE WITH OTHER STANDARD INTERFACES. USUALLY, A UNIQUE ONE-TIME-USE ADAPTOR IS DESIGNED AND BUILT OR THE PCB IS RE-DESIGNED AND BUILT. EITHER APPROACH COSTS TIME AND MONEY. A SOLUTION TO THIS PROBLEM WOULD BE IMPORTANT TO THE INTEROPERABILITY OF RECONFIGURABLE COMPUTING RESOURCES FOR MANNED EXPLORATION, AS WELL AS REALIZE A COST SAVINGS FROM REUSABILITY AND REDUCED SPARES FOR COMPUTING/COMMUNICATIONS DESIGNS. THE PROPOSED URTM IMPLEMENTS A RECONFIGURABLE PROTOCOL TRANSLATION MODULE (RPTM) AND PHYSICAL INTERFACE MODULES (PIM) TO PROVIDE A RECONFIGURABLE SOLUTION TARGETED FOR VARIOUS STANDARD SERIAL LINKS (MIL-STD-1553B, SPACEWIRE, AND FIREWIRE). THE PIM SIMPLY PLUGS INTO THE RPTM AND THE INTERNAL IMPLEMENTATION OF THE RPTM AUTOMATICALLY CONFIGURES WITH APPROPRIATE COMPUTING CORES FOR THE ATTACHED PIMS TO ACHIEVE THE DESIRED SERIAL LINK. STUDY THE FEASIBILITY OF A CONFIGURABLE URTM TO TRANSLATE SERIAL LINK DATA AND RESOLVE TECHNICAL ISSUES, AND OF USING THE CONCEPT FOR A UNIVERSAL SERIAL INTERFACE TO SPACE COMPUTER AND/OR COMMUNICATION BOARDS. BASED ON THE RESULTS, DESIGN, DEVELOP, DOCUMENT, AND DELIVER ENGINEERING PROTOTYPE MODEL OF THE URTM WITH A PATH TO SPACEFLIGHT. THE SPECIFIC OBJECTIVES OF THE URTM ARE: DESIGN AND DEVELOP AN ENGINEERING PROTOTYPE OF AN UNIVERSAL SERIAL LINK TRANSLATOR ADAPT ANY TWO POINT-TO-POINT DATA LINKS LOGICALLY, ELECTRICALLY, AND MECHANICALLY SUPPORT POPULAR DATA LINKS FOR SPACE APPLICATIONS AUTOMATIC RECONFIGURATION WITH PLUG-AND-PLAY SIMPLY CONNECT THE PHYSICAL INTERFACE MODULES (PIM) ON EITHER END OF THE RPTM THE RPTM THEN SELF CONFIGURES VIA A LIBRARY OF INTERFACE TRANSLATION FUNCTIONS THUS ALLOWING THE TWO DATA LINKS TO COMMUNICATE SEAMLESSLY SCOPE OF WORK: WORK AREAS INCLUDE RESEARCH AND TRADE STUDIES, PROCUREMENT, HARDWARE DEVELOPMENT AND BUILD, VHDL DEVELOPMENT, TEST DEVELOPMENT, PROTOTYPE TEST AND DELIVER, MODELING, DOCUMENTATION AND DESIGN DELIVERY, AND REVIEWS.

WATER TENDER TO ASSIST FIRE DEPARTMENT IN NEW ORLEANS

IGF::OT::IGF TODAY'S CUBESATS LACK STORABLE, GREEN, SAFE PROPULSION OPTIONS FOR COMPLEX SCIENCE MISSIONS THAT MAY INVOLVE LARGE DELTA-V CHANGES, PROXIMITY OPERATIONS, AND ATTITUDE CONTROL SYSTEMS (ACS) FOR POINTING, SPIN-UP, AND SPIN-DOWN. DIGITAL SOLID STATE PROPULSION (DSSP) IS DEVELOPING PROPULSION FOR CUBESATS AND WILL LEVERAGE EXISTING RESEARCH EFFORTS INTO A NEW SYSTEM FOR NASA. A KEY TECHNOLOGY IDENTIFIED IN THE PHASE I SOLICITATION IS A CUBESAT PROPULSION SYSTEM THAT WILL ENABLE DEEP-SPACE CUBESATS, WHICH OPERATE OUTSIDE OF EARTH'S MAGNETIC FIELD, TO DESATURATE REACTION WHEELS. THESE TYPES OF MISSIONS CANNOT USE THE MAGNETORQUERS THAT ARE COMMON ON THE EARTH ORBITING CUBESATS THAT ARE POPULAR TODAY. DSSP PROPOSES CONTINUED DEVELOPMENT OF A MULTI-PULSE SOLID ROCKET MOTOR (MPM), WHICH USES GREEN, SAFE ELECTRIC SOLID PROPELLANTS (ESPS). THIS MPM FOR CUBESATS WILL ENABLE DESATURATION OF REACTION WHEELS ON 6U AND 12U INTERPLANETARY MISSIONS WITH LOWER MASS SYSTEMS THAN CONVENTIONAL COLD GAS BASED SOLUTIONS. THE BASELINE PERFORMANCE REQUIREMENT FOR THIS APPLICATION IS ESTIMATED TO BE 0.3 N*SEC OF IMPULSE PER PULSE OF THE THRUSTER IN A SHORT TIME AND WITH LOW POWER IMPACT ON THE SATELLITE. THIS VALUE IS DETERMINED FROM A REACTION WHEEL THAT HAS A 30 MN*M*S MAXIMUM MOMENTUM AND A MAXIMUM THRUSTER MOMENT ARM OF 10 CM. DSSP ALREADY HAS A CUBESAT AGILE PROPULSION SYSTEM (CAPS) AT TRL8, A CLOSE RELATIVE OF WHICH DEPLOYED SAFELY ON SPINSAT FROM THE ISS IN NOVEMBER 2014, AND DSSP'S EXPERIENCE AT QUALIFYING AND DELIVERING FLIGHT HARDWARE FOR THAT PROGRAM CAN BE LEVERAGED FOR NASA. THE SPINSAT MISSION HAS ALREADY DEMONSTRATED THAT ESPS ARE SO INSENSITIVE TO ACCIDENTAL IGNITION THAT THEY CAN BE LAUNCHED AS SOFT STOW CARGO TO THE PRESSURIZED SECTION OF THE ISS AND THAT THE NEW MPM FOR CUBESATS COULD EVEN POTENTIALLY BE BROUGHT ABOARD THE ISS ALSO FOR LATER DEPLOYMENT.

NASA RESEARCH ANNOUCEMENT (NRA) FOR MOODULAR GENERALIZED FRAMEWORK FOR ASSESSING AIRCRAFT AERO-PROPULSIVE, STABILITY, AND CONTROL CHARACTERISTICS NASA CONTINUES TO INVESTIGATE THE POTENTIAL OF ADVANCED, INNOVATIVE PROPULSION AND AIRFRAME CONCEPTS TO IMPROVE EFFICIENCY FOR FUEL AND NOISE REDUCTION AND TO ENABLE NEW VISIONS FOR FLEXIBLE, ON-DEMAND TRAVEL FOR THE PUBLIC. THE POTENTIAL BENEFITS OF ADVANCED VEHICLE DESIGNS SUCH AS BLENDED WING BODIES AND DISTRIBUTED ELECTRIC PROPULSION HAVE LONG BEEN KNOWN, BUT THESE DESIGNS HAVE BEEN SLOW TO TRANSITION INTO THE COMMERCIAL AND PUBLIC DOMAIN BECAUSE OF GAPS IN THE ABILITY TO EFFICIENTLY AND RELIABLY MODEL THEM IN THE DESIGN TOOL SETS. MODELING THESE DESIGNS IS PARTICULARLY CHALLENGING FOR THE CONCEPTUAL DESIGN PHASE WHERE MISSION TARGETS AND PERFORMANCE GOALS ARE FIRST TRANSLATED INTO POTENTIAL AIRCRAFT DESIGNS THAT CAN MEET THOSE GOALS. HOWEVER, CONCEPTUAL DESIGN AND ANALYSIS OF UNCONVENTIONAL AIRFRAME (GEOMETRIES THAT DIFFER FROM THE HISTORICALLY POPULAR WING-AND-TUBE DESIGN OR WHICH TAKE ADVANTAGE OF FLOW AUGMENTATION TO IMPROVE LIFT/DRAG CHARACTERISTICS) AND UNCONVENTIONAL PROPULSION (ENERGY FROM SOURCES OTHER THAN CARBON LIQUID FUEL) CONCEPTS AND TECHNOLOGIES ARE CURRENTLY USED WITHIN NASA FOR TECHNOLOGY PORTFOLIO INVESTMENT PLANNING, DEVELOPMENT OF ADVANCED CONCEPTS TO PROVIDE TECHNOLOGY PULL, AND INDEPENDENT TECHNICAL ASSESSMENT OF NEW CONCEPTS. NASA S SYSTEMS ANALYSTS NEED IMPROVED CONCEPTUAL DESIGN AND ANALYSIS TOOLS TO SUPPORT THESE EFFORTS. MANY TRADITIONAL METHODS OF SIZING AIRCRAFT CONTROL SURFACES AND ASSURING ACCEPTABLE HANDLING QUALITIES HAVE LOST THEIR VALIDITY AS MORE UNCONVENTIONAL AIRCRAFT ARE BEING STUDIED, AND ADDITIONAL DYNAMIC MODES MIGHT BECOME UNSTABLE. NASA IS SEEKING TO DEVELOP METHODS FOR ANALYSIS OF AIRCRAFT STATIC AND DYNAMIC STABILITY CHARACTERISTICS SUITABLE FOR UNCONVENTIONAL AIRCRAFT IN THE CONCEPTUAL DESIGN STAGE. THE METHODS SHOULD BE VERIFIED AND DEMONSTRATED THROUGH SIMULATION OF THE DYNAMICS OF UNCONVENTIONAL FIXED-WING AIRCRAFT CONFIGURATIONS WITH TIGHT COUPLING OF PROPULSION AND AERODYNAMICS CHARACTERISTICS, INCLUDING EVALUATION OF ACTIVE CONTROL SYSTEMS TO ENABLE DESIGN OF UNCONVENTIONAL AIRCRAFT. THIS STATEMENT OF WORK IS THE RESULT OF A PROPOSAL SUBMITTED BY RESEARCH IN FLIGHT, LLC FOR AWARD UNDER THE NASA HEADQUARTERS ARMD NASA RESEARCH ANNOUNCEMENT (NRA) ENTITLED RESEARCH OPPORTUNITIES IN AERONAUTICS 2018, AMENDMENT NNH18ZEA001N, SUBTOPIC 2.1.6. THE CONTRACTOR SHALL DEVELOP TOOLS, PROCESSES, AND METHODS THAT ALLOW THE CONCEPTUAL DESIGNER OR ANALYST TO ASSESS AND EVALUATE THE STABILITY AND CONTROL CHARACTERISTICS OF UNCONVENTIONAL AIRCRAFT CONFIGURATIONS.

TAS::75 0943::TAS POPULAR OPINION LEADERS FOR IPV/SV PREVENTION

IGF::OT::IGF THE GOAL OF THE PROPOSED WORK IS TO STUDY THE GLOBAL EDDY-FIELD AT SCALES AS SMALL AS 20 KM USING THE AVAILABLE LONG-TERM ALTIMETRIC RECORDS. BY ACCESSING THE HIGH SPATIAL RESOLUTION THAT IS PRESENT IN THE ALONG-TRACK ALTIMETER DATA, WE ARE ABLE TO RESOLVE THE IMPACTS OF EDDIES AT SCALES 2.5-10 TIMES SMALLER THAN IS POSSIBLE USING THE PRESENT GENERATION OF BLENDED MULTI-SATELLITE MAPS THAT ARE CURRENTLY WIDELY USED FOR EDDY-RELATED STUDIES. NEW RESEARCH HAS REVEALED AN EDDY FIELD - EXTENDING DOWN TO TENS OF KILOMETERS AND EVEN SMALLER-THAT IS CONSIDERABLY MORE ACTIVE, AND MORE IMPORTANT TO THE CLIMATE SYSTEM, THAN PREVIOUSLY BELIEVED. YET THE CURRENT GENERATION OF MAPPED PRODUCTS IS CREATED WITH THE EXPLICIT INTENT TO AVERAGE OVER RATHER THAN RESOLVE SUCH MESOSCALE AND SUBMESOSCALE EDDY STRUCTURES. THE FAVORED MAPPING METHOD IN SATELLITE ALTIMETRY-OPTIMAL INTERPOLATION OR OI - INITIALLY BECAME POPULAR IN OCEANOGRAPHY AT A TIME WHEN DATA DENSITY WAS A FRACTION OF WHAT IT IS TODAY. BECAUSE THERE WAS SO LITTLE DATA, IT WAS DESIRABLE TO AVERAGE OVER MESOSCALE FLUCTUATIONS IN ORDER TO MAP THE LARGE-SCALE FIELD. THERE IS NOW BOTH THE INTEREST AND THE DATA DENSITY TO SUBSTANTIALLY RESOLVE THE MESOSCALE; YET THE LARGE SMOOTHING SCALES OF 01 ARE STILL EMPLOYED. BY INCORPORATING MAPPING ACHIEVEMENTS TOGETHER WITH AN ALTERNATE APPROACH TO MAPPING EDDY KINETIC ENERGY, WE WILL PROTOTYPE A NEW CLASS OF GRIDDED ALTIMETRIC PRODUCTS WITH SMOOTHING SCALES THAT CHANGE ADAPTIVELY IN ORDER TO MAKE BEST USE OF ALL AVAILABLE DATA. THE VARIABILITY OBSERVED IN THESE NEW MAPS, PARTICULARLY THE EDDY KINETIC ENERGY, WILL THEN BE COMPARED WITH THE RESULTS FROM AN ALONG TRACK EDDY CENSUS IN ORDER TO ISOLATE THE CONTRIBUTIONS FROM EDDY-LIKE SEA SURFACE HEIGHT ANOMALIES HAVING PARTICULAR RADII, VELOCITIES OR ROSSBY NUMBERS, AND POLARITIES (CYCLONES VS. ANTICYCLONES). THIS APPROACH USES AN EVENT DETECTION ALGORITHM TO LOCATE INDIVIDUAL ANOMALIES IN THE ALONG-TRACK DATA, WHICH IN TURN THEN FORM THE BASIS FOR AN ESTIMATION OF THE LOCAL POPULATIONS AND PROPERTIES OF THE UNDERLYING EDDY FIELD USING AN INVERSE METHOD APPROACH. CAREFUL ATTENTION WILL BE GIVEN TO DISTINGUISHING THE DIFFERING CONTRIBUTIONS OF EDDIES VERSUS CURRENT MEANDERS OR EXCURSIONS WITHIN THE CONTEXT OF THIS CENSUS. THE NET RESULT WILL BE AN ABILITY TO ESTIMATE THE LOCAL CONTRIBUTIONS TO EDDY KINETIC ENERGY AND CIRCULATION ASSOCIATED DIRECTLY WITH COHERENT EDDIES, AND TO IDENTIFY THE REGIONS IN WHICH THESE ARE SIGNIFICANT. SINCE WE WILL BE WORKING WITH CONSIDERABLY HIGHER RESOLUTION THAN WAS POSSIBLE IN PREVIOUS STUDIES, NEW RESULTS CONCERNING THE NATURE OF THE EDDY FIELD AT THESE UNRESOLVED SCALES ARE ANTICIPATED. ANALYSIS TOOLS AND DATA PRODUCTS CREATED HERE ARE EXPECTED TO BE OF BROAD INTEREST AND WILL BE DISTRIBUTED TO THE COMMUNITY.

MOBILE APPLICATION DEVELOPMENT (MAD) TASK ORDER AGAINST DOL BPA 1605TA-21-A-0006 TO DEVELOP, MAINTAIN AND CONTINUALLY IMPROVE PUBLIC-FACING MOBILE APPLICATIONS DESIGNED TO RUN ON POPULAR MOBILE PLATFORMS (CURRENTLY IOS AND ANDROID).

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.

THE VSU REQUIRES AN IP DOME CAMERA THAT IS VERY POPULAR WITH THE FIELD AND IS VERY EASY TO SETUP AND INSTALL FOR SPECIAL EVENTS AND OUTDOOR SURVEILLANCE. OUR FIELD OPERATORS ARE FAMILIAR WITH THE AXIS P6044E PTZ DOME NETWORK CAMERA: AND WE REQUEST E