Jet Propulsion Laboratory Awarded Contracts | Federal Compass

Jet Propulsion Laboratory Awarded Contracts

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80NM0018D0004 - THIS CONTRACT IS THE SPONSORING AGREEMENT BETWEEN THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (NASA) AND THE CALIFORNIA INSTITUTE OF TECHNOLOGY (CONTRACTOR), A PRIVATE NONPROFIT EDUCATIONAL INSTITUTION, WHICH ESTABLISHES THE RELATIONSHIP FOR THE OPERATION OF THE FEDERALLY FUNDED RESEARCH AND DEVELOPMENT CENTER (FFRDC) KNOWN AS THE JET PROPULSION LABORATORY (JPL). THIS CONTRACT IS THE ONLY DOCUMENT THAT CONSTITUTES THE SPONSORING AGREEMENT BETWEEN THE PARTIES.
IDC - Operation of the Federally Funded Research and Development Center (FFRDC) JPL - 541715 Research and Development in the Physical, Engineering, and Life Sciences
Contractor
California Institute of Technology (CALIFORNIA INSTITUTE OF TECHNOLOGY)
Contracting Agency/Office
National Aeronautics and Space Administration»Jet Propulsion Laboratory
Effective date
06/29/2018
Obligated Amount
$16.2B
NNX17ED28P - CP3500 LASER MAINTENANCE SERVICE
Purchase Order - 333249 Other Industrial Machinery Manufacturing
Contractor
PRIMA NORTH AMERICA (PRIMA ELECTRO NORTH AMERICA, LLC)
Contracting Agency/Office
National Aeronautics and Space Administration»Mission Support Directorate»NASA Shared Services Center
Effective date
05/23/2017
Obligated Amount
$8.4k
SJA80014M0770 - - NASA - UC FOR INTERPRETER SERVICE
Purchase Order - 541930 Translation and Interpretation Services
Contractor
Miscellaneous Foreign Contractors (MISCELLANEOUS FOREIGN AWARDEES)
Contracting Agency/Office
State
Effective date
06/02/2014
Obligated Amount
$8k
NNN12AA01C - THIS CONTRACT IS THE SPONSORING AGREEMENT BETWEEN THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (NASA) AND THE CALIFORNIA INSTITUTE OF TECHNOLOGY (CONTRACTOR), A PRIVATE NONPROFIT EDUCATIONAL INSTITUTION, WHICH ESTABLISHES THE RELATIONSHIP FOR THE OPERATION OF THE FEDERALLY FUNDED RESEARCH AND DEVELOPMENT CENTER (FFRDC) KNOWN AS THE JET PROPULSION LABORATORY (JPL).
IDC - JPL FFRDC - 541712 Research and Development in the Physical, Engineering, and Life Sciences (except Biotechnology)
Contractor
California Institute of Technology (CALIFORNIA INSTITUTE OF TECHNOLOGY)
Contracting Agency/Office
National Aeronautics and Space Administration»Jet Propulsion Laboratory
Effective date
08/16/2012
Obligated Amount
$12.1B
NNX12CE61P - THIS PROJECT PROPOSES TO DEVELOP AN OCCULTER OPTICAL EDGE AND OPTICAL EDGE MEASUREMENT VERIFICATION SYSTEM SUITABLE FOR ASTROPHYSICS MISSIONS INCLUDING JWST AND THE OCCULTING OZONE OBSERVATORY (O3). THE OPTICAL EDGE HAS TIGHT CROSS-SECTION REQUIREMENTS IN ORDER TO PRODUCE THE CORRECT DIFFRACTION AS LIGHT PASSES OVER THE EDGE. IT IS ALSO OF IMPORTANCE IS THE OPTICAL EDGE PROFILE TOLERANCE. THIS REQUIRES PRECISION MACHINING AND THAT THE OPTICAL EDGE BE THERMALLY STABLE. KEY TECHNICAL CHALLENGES LIE IN MANUFACTURING AN OPTICAL EDGE WITH A CROSS-SECTION APPROPRIATE FOR AN OCCULTER AS WELL AS IN MEASURING THAT EDGE TO THE DEGREE OF PRECISION REQUIRED. DUE TO THE THERMAL STABILITY REQUIREMENTS, INNOVATIVE MATERIALS OR COMBINATIONS OF MATERIALS MUST BE USED. THE FOCUS OF THIS RESEARCH WILL BE TO PRODUCE AN OPTICAL EDGE WITH THE REQUIRED CROSS-SECTION AND TO MEASURE THAT EDGE ACCURATELY. ADVANCED MACHINING TECHNIQUES WILL BE INVESTIGATED WHICH MAY INCLUDE MILLING, ELECTRICAL DISCHARGE MACHINING, GRINDING, AND LASER MACHINING. MEASUREMENT TECHNIQUES WILL INCLUDE SCANNING LASER DISPLACEMENT TRANSDUCER AND COMPUTERIZED MEASUREMENT MACHINE. THIS TECHNOLOGY COULD BE EXTENDED TO A FULL SCALE OPTICAL EDGE WITH THE CORRECT PROFILE IN A PHASE II PROGRAM.
Purchase Order - 541712 Research and Development in the Physical, Engineering, and Life Sciences (except Biotechnology)
Contractor
VANGUARD SPACE TECHNOLOGIES, INC.
Contracting Agency/Office
National Aeronautics and Space Administration»Mission Support Directorate»NASA Shared Services Center
Effective date
02/23/2012
Obligated Amount
$125k
NNX12CE59P - NASA FACES DIFFICULTIES IN IMAGING AND CHARACTERIZING FAINT ASTROPHYSICAL OBJECTS WITHIN THE GLARE OF BRIGHTER STELLAR SOURCES. ACHIEVING A VERY LOW BACKGROUND REQUIRES CONTROL OF BOTH SCATTERED AND DIFFRACTED LIGHT. ALIGNED ARRAYS OF CARBON NANOTUBES HAVE RECENTLY BEEN RECOGNIZED AS HAVING WORLD-LEADING OPTICAL ABSORPTION, FAR ABOVE COMPETING STATE OF THE ART MATERIALS. THE GSFC TEAM NOTED THAT NANOTUBE ARRAYS HAVE THE "POTENTIAL TO PROVIDE ORDER-OF-MAGNITUDE IMPROVEMENT OVER CURRENT SURFACE TREATMENTS AND A RESULTING FACTOR OF 10,000 REDUCTION IN STRAY LIGHT WHEN APPLIED TO AN ENTIRE OPTICAL TRAIN." WHILE EXCELLENT PERFORMERS, NANOLAB RECOGNIZES THAT THE NUANCES OF THE ARRAY STRUCTURE, SUCH AS ANGULAR ALIGNMENT, DIAMETER, LENGTH, AND TOP-SURFACE ROUGHNESS OF THE ARRAY PLAY A MAJOR ROLE IN THEIR OPTICAL PROPERTIES, AND THESE NEED TO BE CHARACTERIZED IF WE WISH TO CONTROL AND TAILOR THESE MATERIALS FOR SPECIFIC APPLICATIONS. FURTHER, THE ARRAYS GROWN TO DATE ARE OFTEN POORLY ADHERED TO THEIR SUBSTRATES, WHICH ARE TYPICALLY SILICON. NANOLAB PLANS TO DEVELOP PROCESSES GROW ARRAYS ON FLEXIBLE, TOUGHER SUBSTRATES SUCH AS TI AND STAINLESS STEEL FOILS, SO THEY CAN BE FORMED AND INSERTED INTO OPTICAL SYSTEMS WITHOUT DAMAGE. WE WILL CORRELATE THE VIS-IR OPTICAL PROPERTIES TO THE ARRAY STRUCTURE AND TO THE PROCESS PARAMETERS THAT GENERATE THEM. BALL AEROSPACE WILL ASSIST NANOLAB IN THIS EFFORT WITH BRDF AND OTHER OPTICAL MEASUREMENTS.
Purchase Order - 541712 Research and Development in the Physical, Engineering, and Life Sciences (except Biotechnology)
Contractor
NANOLAB, INC
Contracting Agency/Office
National Aeronautics and Space Administration»Mission Support Directorate»NASA Shared Services Center
Effective date
02/23/2012
Obligated Amount
$124.6k
NNX11CB24C - THE ELECTROMAGNETIC PLASMOID THRUSTER (EMPT) IS A REVOLUTIONARY ELECTRIC PROPULSION THRUSTER AND POWER PROCESSING (PPU) SYSTEM THAT WILL ALLOW A DRAMATIC DECREASE IN SYSTEM MASS AND INCREASE IN THRUST EFFICIENCY OVER TRADITIONAL 500-3000 W PROPULSION SYSTEMS. THE HIGH SPECIFIC POWER (>700 W/KG) AND HIGH EFFICIENCY OF EMPT WILL ENABLE A WIDE RANGE OF DEEP SPACE MISSIONS SUCH AS NEPTUNE, PLUTO AND OORT CLOUD ORBITAL INSERTION. ADDITIONALLY, A SOLAR ELECTRIC EMPT SYSTEM WOULD DRAMATICALLY INCREASE THE CAPABILITY AND REDUCE THE TRAVEL TIME OF AN ASTEROID OR MARTIAN MOON SAMPLE AND RETURN MISSION DUE TO THE VARIABLE-POWER, LOW-MASS PROPULSION SYSTEM. THE EMPT EMPLOYS A ROTATING MAGNETIC FIELD (RMF) TO PRODUCE LARGE PLASMA CURRENTS INSIDE A CONICAL THRUSTER CREATING A PLASMOID THAT IS MAGNETICALLY ISOLATED FROM THE THRUSTER WALLS. THE INTENSIFIED GRADIENT MAGNETIC FIELD FROM THE PLASMOID TOGETHER WITH THE LARGE PLASMA CURRENTS RESULT IN AN ENORMOUS BODY FORCE THAT EXPELS THE PLASMOID AT HIGH VELOCITY. THE EMPT IS A PULSED DEVICE, NOMINALLY OPERATING AT 1 KWE WITH 0.5-1 JOULE DISCHARGES AT 1-2 KHZ. PRESENTED IS A FULL DESCRIPTION OF THE RELEVANT PLASMA PHYSICS AS WELL AS THE THRUSTER AND PPU DESIGN. THE PHASE I EMPT DEMONSTRATED THE MULTI-PULSE FORMATION AND EJECTION OF PLASMOIDS AT 0.1-3 JOULES AND 500-6,000 S ISP ON BOTH XENON AND ARGON. ADDITIONALLY, IT DEMONSTRATED ZERO EROSION OR LIFE LIMITING PHENOMENA. THE FOCUS OF THE PROPOSAL IS THE EXPERIMENTAL VALIDATION OF AN INTEGRATED THRUSTER AND PPU OPERATING IN A STEADY-STATE MODE. THE EMPT WILL BE CHARACTERIZED OVER A RANGE OF PARAMETERS: INPUT POWER FROM 200-3000 WATTS, AND 1,500-4,000 SECONDS SPECIFIC IMPULSE. THE INTEGRATED THRUSTER AND PPU TO BE BUILT AND TESTED WILL HAVE A TOTAL SYSTEM MASS OF LESS THAN 1.5 KG. SUCCESSFUL COMPLETION OF PHASE II WILL BE A FULLY INTEGRATED, STEADY-STATE DEMONSTRATION OF THRUSTER AND INTEGRATED POWER PROCESSING. PHASE II WILL MATURE THE TECHNOLOGY FROM A TRL LEVEL 4 TO 6.
Definitive Contract - 541712 Research and Development in the Physical, Engineering, and Life Sciences (except Biotechnology)
Contractor
M S N W LLC
Contracting Agency/Office
National Aeronautics and Space Administration»Mission Support Directorate»NASA Shared Services Center
Effective date
06/01/2011
Obligated Amount
$600k
NNX11CB09C - AMPLIFICATION TECHNOLOGIES INC ("ATI") PROPOSES TO DEVELOP THE ENABLING MATERIAL AND DEVICE TECHNOLOGY FOR THE DESIGN OF ULTRA LOW NOISE, HIGH GAIN AND HIGH SPEED NEAR-INFRARED SINGLE PHOTON COUNTING PHOTODETECTORS AND ARRAYS SENSITIVE IN THE 1000 NM TO 1600 NM SPECTRAL REGION FOR LONG RANGE SPACE COMMUNICATION APPLICATIONS, BASED ON THE ALREADY PROVEN MECHANISM OF INTERNAL DISCRETE AMPLIFICATION TECHNOLOGY IN INGAAS/INP MATERIAL SYSTEM. WE PLAN TO ACHIEVE THIS BY USING THE CONCEPT OF INTERNAL DISCRETE AMPLIFICATION MECHANISM IN THE INP MATERIAL SYSTEM THAT GAVE STATE OF THE ART PERFORMANCE PARAMETERS IN THE 1000 TO 1600NM WAVELENGTH RANGE AND THE DEVELOPED DEVICE DESIGN AS PART OF THE PHASE I PROGRAM THAT SHOWS HIGHER DETECTION EFFICIENCY AND LOWER JITTER PERFORMANCE. THE PRIMARY ACCOMPLISHMENTS FROM THE PHASE II EFFORT WOULD BE THE DEVELOPMENT OF ULTRA LOW NOISE (LOW JITTER), HIGH DETECTION EFFICIENCY, VERY HIGH GAIN AND HIGH SPEED NEAR-INFRARED PHOTODETECTORS AND ARRAYS SENSITIVE IN THE 1000 NM TO1600 NM SPECTRAL REGION. THE TECHNOLOGY OF INTERNAL DISCRETE AMPLIFICATION ENABLES THE COMBINATION OF HIGH SPEED, VERY HIGH GAIN AND ULTRA LOW NOISE BECAUSE THE INTERNAL DISCRETE AMPLIFICATION NULLIFIES THE EFFECT OF IMPACT IONIZATION COEFFICIENTS AND PREVENTS THE EDGE BREAK DOWN, WITH HIGH DETECTION EFFICIENCY AND HIGH SPEED OF OPERATION. THESE PHOTODETECTORS MIGHT ALSO BE USED IN MISSILE SEEKERS, BATTLEFIELD TARGET IDENTIFICATION AND RECOGNITION SYSTEMS, AND EYE-SAFE LADAR. POTENTIAL CIVILIAN APPLICATIONS INCLUDE FIBER-OPTIC TELECOMMUNICATIONS, REMOTE SENSING AND LASER SPECTROSCOPY.
Definitive Contract - 541712 Research and Development in the Physical, Engineering, and Life Sciences (except Biotechnology)
Contractor
AMPLIFICATION TECHNOLOGIES, INC.
Contracting Agency/Office
National Aeronautics and Space Administration»Mission Support Directorate»NASA Shared Services Center
Effective date
06/01/2011
Obligated Amount
$599.9k
NNX11CB07C - THE DEVELOPMENT OF MULTI-METER DIAMETER RADIOFREQUENCY (RF) ANTENNAS FOR NASA AND DOD WILL HAVE A SIGNIFICANT IMPACT OF FUTURE SPACE PROGRAMS. POLYMER MEMBRANE TECHNOLOGIES ARE WELL SUITED FOR LARGE AREA DEPLOYABLE SPACE ANTENNAS BY SIGNIFICANTLY REDUCING THE MASS AND VOLUME OF THE LAUNCH VEHICLE. LOW CTE POLYMER PIEZOELECTRIC MEMBRANE TECHNOLOGY IS NOW AT A MATURITY LEVEL TO ENABLE THE DEVELOPMENT OF HIGH PERFORMANCE LARGE AREA ELECTRICALLY FORMAL MEMBRANE REFLECTORS. ADVANCED COATING TECHNOLOGY IS CRUCIAL TO ENABLING TECHNOLOGICAL DEVELOPMENTAL OF HIGH PERFORMANCE RF ANTENNAS. THE PRODUCTION OF A CONDUCTIVE AND HIGHLY REFLECTIVE THERMAL CONTROL COATING THAT MATCHES THE CTE OF THE POLYMER MEMBRANE IS AT THE CENTER OF THIS DEVELOPMENT PROGRAM. IN ADDITION, IN PHASE I, THE PIEZOELECTRIC POLYMERIC MEMBRANE HAD A SIGNIFICANT DEFORMATION AT THE APPLICATION OF THE ELECTRICAL POTENTIAL - THIS MANIFESTED THE NEED FOR STRESS BALANCING THE COATING. SPECIFICALLY, THE OBJECTIVE IS TO DEVELOP THE THIN-FILM STRESS-BALANCED COATING THAT WILL PRECISELY MATCH THE CTE OF THE POLYMER TO THE COATING MATERIAL ITSELF, RESULTING IN A ZERO CTE MEMBRANE/COATING COMPOSITE STRUCTURE. IN ADDITION, THE COATED MEMBRANE WILL EXHIBIT THE REQUIRED RF PERFORMANCE, THERMAL CHARACTERISTICS, AND ENVIRONMENTAL ENDURANCE, SUCH AS: ATOMIC OXYGEN (AO) RESISTANCE; VISIBLE AND ULTRA-VIOLET (VUV) RADIATION REJECTION; AND SPACE TEMPERATURE EXTREMES. SURFACE OPTICS CORPORATION (SOC) HAS CONSIDERABLE EXPERIENCE IN PRODUCING RF/THERMAL COATINGS AND PRECISELY CONTROLLED INTRINSIC STRESS THIN-FILMS; BOTH ARE NECESSARY TO THE SUCCESS OF THIS PROGRAM. NEXOLVE IS THE PARTNERING ORGANIZATION WITH SOC, PROVIDING THE POLYMER MEMBRANES THAT HAVE THE APPROPRIATE PIEZOELECTRIC FORMULATION, SURFACE PROPERTIES, AND ZERO CTE.
Definitive Contract - 541712 Research and Development in the Physical, Engineering, and Life Sciences (except Biotechnology)
Contractor
SURFACE OPTICS CORP.
Contracting Agency/Office
National Aeronautics and Space Administration»Mission Support Directorate»NASA Shared Services Center
Effective date
06/01/2011
Obligated Amount
$579.8k
NNX11CB27C - THE CONTINUED DEVELOPMENT OF AUTOMATED SAMPLE ACQUISITION AND HANDLING TOOLS IS OF CRITICAL IMPORTANCE TO FUTURE ROBOTIC MISSIONS ON MARS, THE MOON, VENUS, AND OTHER PLANETARY BODIES. IN RESPONSE TO THE NEED FOR A COMPACT, LOW MASS, LOW POWER, AND LOW WEIGHT-ON-BIT CORING DEVICE, WE PROPOSE TO CONTINUE DEVELOPMENT OF AN ARM-DEPLOYED AND ARM-STABILIZED ROTARY-PERCUSSIVE CORING TOOL. BY USING A ROBOTIC ARM TO DEPLOY THE CORING TOOL INTO ROCK OR SOIL TARGETS AND STABILIZE THE TOOL WHILE OPERATING, THE CORING TOOL'S INTERNAL DEPLOYMENT (OR "Z") AXIS AND EXTERNAL STABILIZATION DEVICES CAN BE REMOVED, RESULTING IN A MORE COMPACT, LOWER MASS DEVICE. ALSO, ADDING PERCUSSION TO THE CORING TOOL WILL REDUCE AVERAGE WEIGHT-ON-BIT AND ENERGY CONSUMPTION OVER THE DURATION OF THE CORING OPERATION. THE FLEXIBILITY AFFORDED FROM A ROVER OR LANDER ARM TO TARGET OUTCROPPINGS, AND THE RELATIVELY HIGHER TRL OF SURFACE CORING TOOLS (VS. DEEPER SUBSURFACE DRILLS), MAKE SURFACE CORING, ESPECIALLY WITH AN ARM-DEPLOYED CORING TOOL, A PARTICULARLY ATTRACTIVE OPTION FOR NEAR TERM PLANETARY EXPLORATION. DURING PHASE I, A PRELIMINARY CORING TOOL DESIGN WAS DEVELOPED THAT WEIGHS LESS THAN 5 KG AND MEETS ALL OF THE CURRENT MSR REQUIREMENTS. BREADBOARD TESTING ALSO DEMONSTRATED THE FEASIBILITY OF ARM-DEPLOYED AND STABILIZED CORING. THE OBJECTIVES OF PHASE II ARE TO FURTHER DEVELOP, DEMONSTRATE AND CHARACTERIZE A TRL 5/6 MSR-COMPATIBLE CORING TOOL. THE ROTARY-PERCUSSIVE CORING TOOL WILL WEIGH LESS THAN 5 KG, BE ARM-DEPLOYED AND STABILIZED, INCLUDE A PASSIVE LINEAR FEED DEVICE, REQUIRE LESS THAN 50 N WEIGHT-ON-BIT, PRODUCE AND CAPTURE 1 CM DIAMETER BY 5 CM LONG CORES, ACCOMMODATE ACTIVE BIT CHANGE-OUT AND PASSIVE BIT RELEASE, AND POSITIVELY RETAIN CORES IN CORE TUBES WHEN REMOVED FROM THE BIT. THE CORING TOOL WILL BE FULLY DEMONSTRATED AND CHARACTERIZED AT AMBIENT AND MARS CONDITIONS.
Definitive Contract - 541712 Research and Development in the Physical, Engineering, and Life Sciences (except Biotechnology)
Contractor
HONEYBEE ROBOTICS, LTD. (HONEYBEE ROBOTICS LTD)
Contracting Agency/Office
National Aeronautics and Space Administration»Mission Support Directorate»NASA Shared Services Center
Effective date
06/01/2011
Obligated Amount
$324.4k
NNX11CB13C - NUVOTRONICS HAS DEVELOPED AND OPTIMIZED THE POLYSTRATATM PROCESS FOR THE FABRICATION OF INTRICATE MICROWAVE AND MILLIMETER-WAVE DEVICES. THESE DEVICES HAVE PRIMARILY BEEN RECTANGULAR COAXIAL TRANSMISSION LINES, ALTHOUGH RECTANGULAR WAVEGUIDE AND OTHER STRUCTURES HAVE ALSO BEEN DEMONSTRATED. INTRICATE DEVICES HAVE BEEN DEMONSTRATED WITH INSERTION LOSS 5 TO 10 TIMES LOWER THAN TRADITIONAL PLANAR CIRCUITS; ISOLATION BETTER THAN 60DB FOR LINES THAT SHARE SEPARATING WALLS; MULTIPLE LEVELS OF DENSELY-PACKED COAXIAL CIRCUITS; AND LOW-PARASITIC ATTACHMENT TO ACTIVE DEVICES AND TRADITIONAL CIRCUIT BOARDS. IN THIS PHASE II PROJECT, NUVOTRONICS WILL OPTIMIZE AND FABRICATE HIGH DENSITY LOW-LOSS MILLIMETER BACKPLANE CIRCUITS TO PACKAGE AND INTERCONNECT COMPONENTS OF FUTURE NASA MILLIMETER WAVE (MMW) RADARS. THE SIGNIFICANCE OF THE INNOVATION PRIMARILY LIES IN THREE AREAS: REDUCTION OF SYSTEM SIZE, WEIGHT AND LOSS IN MMW RADARS. THE POLYSTRATA TECHNOLOGY IS A BATCH MANUFACTURING PROCESS, PROVIDING ECONOMIES OF SCALE AND COST REDUCTION FOR HIGHER VOLUMES, IN ADDITION TO FLEXIBILITY IN DESIGN FOR VARIOUS FREQUENCIES OF INTEREST.
Definitive Contract - 541712 Research and Development in the Physical, Engineering, and Life Sciences (except Biotechnology)
Contractor
Cubic Corporation (NUVOTRONICS, LLC)
Contracting Agency/Office
National Aeronautics and Space Administration»Mission Support Directorate»NASA Shared Services Center
Effective date
06/01/2011
Obligated Amount
$685.5k
NNX11CB17C - THE INNOVATIVE, HIGH TRANSMISSION BAND-PASS FILTER TECHNOLOGY PROPOSED HERE IS AN IMPROVEMENT IN MULTILAYER METAL-MESH FILTER DESIGN AND MANUFACTURE FOR THE FAR IR TO SUBMILLIMETER RANGES. THE PROPOSED METAL-MESH FILTERS CAN TOLERATE CRYOGENIC TEMPERATURES (DOWN TO 4K AND BELOW) AND A WIDE VIBRATION/SHOCK SPECTRUM, MAKING THEM LAUNCH-CAPABLE AND DURABLE FOR LONG PERIODS IN SPACE. IN ADDITION, THE PROPOSED BAND-PASS FILTERS ARE LIGHT WEIGHT, AS THEY EMPLOY NO HEAVY SUBSTRATES. THE PROPOSED 2 5 MM THICKNESS (MOSTLY THE MOUNTING FRAME) ALLOWS INSERTION INTO TIGHT SPACES AND STANDARD FILTER WHEELS. THE THIN, LIGHT WEIGHT, VACUUM COMPATIBLE DESIGN CAN BE INCORPORATED INTO ALMOST ANY DETECTOR SETUP. LARGE SIZES CAN BE MANUFACTURED FOR NEWER INSTRUMENTS WITH LARGER DIAMETER BEAMS.
Definitive Contract - 541712 Research and Development in the Physical, Engineering, and Life Sciences (except Biotechnology)
Contractor
LAKE SHORE CRYOTRONICS, INC.
Contracting Agency/Office
National Aeronautics and Space Administration»Mission Support Directorate»NASA Shared Services Center
Effective date
06/01/2011
Obligated Amount
$599.8k
NNX11CB22C - THIS PROPOSAL DESCRIBES A NEW CONCEPT TO DRIVE MEMS DMS USING LOW-POWER, HIGH-VOLTAGE MULTIPLEXING. COMPARED TO OTHER REPORTED APPROACHES, THE PROPOSED ARCHITECTURE WILL REDUCE POWER CONSUMPTION BY A FACTOR OF ONE HUNDRED, TO A LEVEL OF A FEW HUNDRED MILLIWATTS. THIS ESTIMATE IS SUPPORTED BY DIRECT MEASUREMENTS OBTAINED FROM PROTOTYPE MODULES THAT WERE DEMONSTRATED IN PHASE I RESEARCH. IN THE PHASE II PROJECT WE WILL SCALE UP THIS INNOVATIVE CIRCUIT DMS THAT BOSTON MICROMACHINES CORPORATION (BMC) DEVELOPED FOR NASA IN SUPPORT OF THE TERRESTRIAL PLANET FINDING PROGRAM. AT THE SAME TIME, WE WILL REDUCE THE DRIVER'S SIZE IN TWO SUCCESSIVE STAGES OF INTEGRATION. IN THE FIRST STAGE, WE WILL IMPLEMENT A HYBRID PACKAGING APPROACH IN WHICH A 993-ACTUATOR DM, HV AMPLIFIER, MULTIPLEXER COMPONENTS, AND POWER SUPPLIES WILL ALL BE CO-LOCATED ON A COMMON MULTI-LAYERED CIRCUIT BOARD. WITH THIS DRIVER WE WILL DEMONSTRATE BOTH LOW POWER CONSUMPTION (~300MW) AND HIGH PRECISION (~10PM). IN THE SECOND STAGE OF INTEGRATION, WE WILL DESIGN, FABRICATE, AND TEST A HIGH VOLTAGE APPLICATION-SPECIFIC INTEGRATED CIRCUIT (HV-ASIC) VERSION OF THE MULTIPLEXING ARCHITECTURE USING A COMMERCIAL FOUNDRY. WE WILL COMBINE A NUMBER OF THESE 256 CHANNEL HV-ASIC MODULES INTO A DRIVER FOR A 3063 ACTUATOR DM THAT IS CURRENTLY BEING DEVELOPED BY BMC TO SUPPORT NASA'S CORONOGRAPHY GOALS.
Definitive Contract - 541712 Research and Development in the Physical, Engineering, and Life Sciences (except Biotechnology)
Contractor
BOSTON MICROMACHINES CORPORATION
Contracting Agency/Office
National Aeronautics and Space Administration»Mission Support Directorate»NASA Shared Services Center
Effective date
06/01/2011
Obligated Amount
$599.8k
NNX11CB08C - CRITICAL TO THE SUCCESS OF DELIVERING ON THE PROMISE OF DEEP SPACE OPTICAL COMMUNICATIONS IS THE CREATION OF A STABLE AND RELIABLE HIGH POWER MULTICHANNEL OPTICAL UPLINK/BEACON. OPTICAL ENGINES PROPOSES TO DELIVER IN PHASE 2 2 COMPACT AND LOW COST FIBER AMPLIFIERS SUITED TO THE UPLINK APPLICATION. THIS WILL BE ACCOMPLISHED THROUGH THE USE OF OPTICAL ENGINES PROPRIETARY MULTI-FIBER COUPLED 2.5KW LASER DIODE STACKS, ITS ETCHED TAPER ALL FIBER COMBINER TECHNOLOGY AND A CUSTOM DESIGNED PHOTONIC CRYSTAL FIBER. ONE OF THESE AMPLIFIERS WILL BE OF THE COILED PCF TYPE AND ONE OF THE ROD TYPE AND WILL BE INTEGRATED INTO EXISTING NASA DEEP SPACE COMMUNICATIONS UP LINK INFRASTRUCTURE.
Definitive Contract - 541712 Research and Development in the Physical, Engineering, and Life Sciences (except Biotechnology)
Contractor
OPTICAL ENGINES, INC
Contracting Agency/Office
National Aeronautics and Space Administration»Mission Support Directorate»NASA Shared Services Center
Effective date
06/01/2011
Obligated Amount
$600k
NNX11CB23C - WE PROPOSE TO DESIGN AND FABRICATE A MEMS MICROMIRROR ARRAY CONSISTING OF 1021 ULTRA-FLAT, CLOSE-PACKED HEXAGONAL MIRROR ELEMENTS, EACH CAPABLE OF 6MRAD OF TIP AND TILT, AND 1.7UM OF PISTON (TTP) MOTION WITH SUB-NANOMETER PRECISION AS REQUIRED FOR A SPACE-BASED TELESCOPE USING A HYPER-CONTRAST CORONAGRAPH FOR TERRESTRIAL PLANET FINDING. FABRICATION PROCESS ENHANCEMENTS DEVELOPED IN THE PHASE I EFFORT TO INCREASE DEVICE YIELD BY SIGNIFICANTLY REDUCING THE DEFECT DENSITY IN POLYSILICON FILMS AND REDUCE WAFER BOW BY MODIFYING THIN FILM DEPOSITION PROCESSES, WILL BE INTEGRATED IN TO THE DM FABRICATION PROCESS TO PRODUCE A DEVICE WITH 100% ACTUATOR YIELD AND AN UNPOWERED PEAK-TO-VALLEY SURFACE FIGURE ERROR OF<500NM - WELL WITHIN THE DYNAMIC RANGE OF THE DM ACTUATORS. THIS LARGE ARRAY OF MIRROR SEGMENTS WITH TIP-TILT-PISTON DEGREES OF FREEDOM AND /100 OPTICAL QUALITY WOULD CONSTITUTE A SIGNIFICANT TECHNOLOGICAL ADVANCE AND WOULD BECOME AN ENABLING COMPONENT FOR THE HIGH CONTRAST VISIBLE NULLING CORONAGRAPH INSTRUMENTS PLANNED FOR EXOPLANET IMAGING MISSIONS.
Definitive Contract - 541712 Research and Development in the Physical, Engineering, and Life Sciences (except Biotechnology)
Contractor
BOSTON MICROMACHINES CORPORATION
Contracting Agency/Office
National Aeronautics and Space Administration»Mission Support Directorate»NASA Shared Services Center
Effective date
06/01/2011
Obligated Amount
$599.6k
NNX11CB29C - MARS SAMPLE RETURN POSES SOME OF THE MOST CHALLENGING OPERATIONAL ACTIVITIES OF ANY NASA DEEP SPACE MISSION. RENDEZVOUS OF A VEHICLE WITH A SAMPLE CANISTER IN ORDER TO RETURN THE CANISTER TO EARTH REQUIRES A VARIETY OF COMPLEX MATHEMATICAL PROCESSING ON A CHANGING DATA SET, COUPLED WITH THE NEED TO SAFELY AND EFFECTIVELY HANDLE A LARGE RANGE OF OFF-NOMINAL CONDITIONS AND SPACECRAFT FAULTS. LIGHT SPEED DELAY ISOLATES THE SPACECRAFT FROM REAL-TIME OPERATOR INTERVENTION, WHILE INERTIAL AND SITUATIONAL UNCERTAINTIES DEMAND REACTIVITY NOT REQUIRED OF TYPICAL SPACECRAFT SEQUENCING SYSTEMS. THESE MISSION FEATURES CALL FOR A NEW CLASS OF SEQUENCE CAPABILITY: REACTIVE RENDEZVOUS AND DOCKING SEQUENCER (RRDS). RRDS MELDS THE RULE-BASED REACTIVITY NEEDED FOR RENDEZVOUS AND DOCKING WITH SEQUENCE CHARACTERISTICS COMMON TO MORE TRADITIONAL MISSIONS. RULES WATCH FOR CONDITIONS IN ORDER TO REACT TO THE CURRENT SITUATION, ALLOWING A WIDE RANGE OF COMPLEX ACTIVITIES AND SAFETY-RELATED RESPONSES TO BE CONCISELY REPRESENTED WITHOUT COMPLEX PROCEDURAL PROGRAMMING. RESPONSIBILITY FOR COMMANDING ELEMENTS ABOARD THE SPACECRAFT IS DIVIDED AMONG SEQUENCED STATE MACHINES CALLED MANAGERS, COORDINATED TOGETHER BY A FLIGHT DIRECTOR WHICH THE GROUND COMMANDS. UNDERLYING FLIGHT SOFTWARE FOR NAVIGATION, THRUSTER ALLOCATION, INERTIAL CHECKING, ATTITUDE ESTIMATION AND CONTROL, CONTACT DETECTION, DOCKING MECHANISMS, AND THE LIKE RECEIVE DIRECTION FROM THE MANAGERS. THIS MEDIATED CONTROL CAUSES THE SYSTEM TO REACTIVELY OPERATE IN MODES WITH PROPER ORDERING OF ACTIVITIES. REACTIVE OPERATIONS ARE REPRESENTED EXPLICITLY BY STATES AND TRANSITIONS DEFINING THE MANAGERS, AND DO NOT REQUIRE USE OF EXPLICITLY TIMED ACTIVITIES. PHASE II OF THIS SBIR WILL PRODUCE A CLASS B VERSION OF THE UNDERLAYING VML 2.2 FLIGHT SOFTWARE CAPABLE OF EXECUTING THE RRDS STATE MACHINES. IT WILL ALSO PRODUCE CLASS C VERSIONS OF THE ASSOCIATED VML COMPILER AND OFFLINE VM EXECUTION SYSTEM FOR DEPLOYMENT ONTO FLIGHT PROJECTS.
Definitive Contract - 541712 Research and Development in the Physical, Engineering, and Life Sciences (except Biotechnology)
Contractor
BLUE SUN ENTERPRISES, INC
Contracting Agency/Office
National Aeronautics and Space Administration»Mission Support Directorate»NASA Shared Services Center
Effective date
06/01/2011
Obligated Amount
$599.8k
NNX11CB28C - BEAR ENGINEERING PROPOSES TO ADVANCE THE DEVELOPMENT OF AN INNOVATIVE HIGH TORQUE, LOW SPEED, DIRECT DRIVE MOTOR IN ORDER TO MEET NASA'S REQUIREMENTS FOR SUCH DEVICES. FUNDAMENTALLY, ALL ELECTRIC MOTORS BASICALLY WORK ON THE SAME ELECTROMAGNETIC PRINCIPLE: A TANGENTIAL ELECTROMAGNETIC FORCE ATTRACTS THE ROTOR TO THE STATOR. JUST WHEN THE ROTOR FIELD IS CLOSEST TO THE STATOR FIELD AND THE ELECTROMAGNETIC ATTRACTION IS GREATEST, THE POWER IS INTERRUPTED AND ANOTHER SET OF MAGNETIC POLES REPEATS THE CYCLE. FURTHERMORE, THE TWO MAGNETICALLY ATTRACTED ELEMENTS NEVER MAKE CONTACT, WHICH WOULD OTHERWISE OFFER THE HIGHEST FORCE OF ATTRACTION. THE PROPOSED NOVEL MOTOR DESIGN, SUCCESSFULLY DEMONSTRATED AT TRL 4 IN PHASE 1, OPERATES AND BEHAVES ENTIRELY DIFFERENTLY FROM ALL OTHER KNOWN ELECTRIC MOTOR DESIGNS AND IS CAPABLE OF PRODUCING INCREDIBLY HIGH, DIRECT DRIVE TORQUES AT LOW ROTATIONAL SPEEDS. ITS OPERATIONAL PERFORMANCE IS SIMILAR TO THAT OF A STEPPER MOTOR WITH A 1000:1 GEARHEAD ATTACHED, BUT THE SIMILARITY ENDS THERE. THE MOTOR IS CONFIGURED SUCH THAT ITS LENGTH TO DIAMETER ASPECT RATIO IS OPPOSITE THAT OF TRADITIONAL MOTORS AS IT HAS A RELATIVELY LARGE DIAMETER AND SHORT AXIAL LENGTH; THIS OFFERS ALL NEW PACKAGING OPPORTUNITIES. THE DESIGN ALSO ALLOWS FOR A SINGLE, LARGE DIAMETER BEARING PAIR TO BE USED FOR THE MOTOR'S OUTPUT SHAFT WHICH RENDERS IT STIFF ENOUGH TO DIRECTLY MOUNT THE DRIVEN ELEMENTS. THE NEED FOR ADDITIONAL BEARING SUPPORTS AND BEARING MOUNTING STRUCTURE IS THUS ELIMINATED. BY THE END OF PHASE 2, THE SYSTEM WILL BE DESIGNED, DEVELOPED AND TESTED AT TRL 6 WITH MARS ENVIRONMENTAL CONDITIONS.
Definitive Contract - 541712 Research and Development in the Physical, Engineering, and Life Sciences (except Biotechnology)
Contractor
BEAR TECHNOLOGIES, LLC
Contracting Agency/Office
National Aeronautics and Space Administration»Mission Support Directorate»NASA Shared Services Center
Effective date
06/01/2011
Obligated Amount
$597.4k
NNX11CB16C - THE MOTIVATION OF THE PROPOSED SBIR IS TO DEVELOP, DEMONSTRATE AND COMMERCIALIZE A COMPACT, LOW-MASS, HIGH OUTPUT POWER (1-10 MILLIWATT), TUNABLE SOURCE OF CW THZ RADIATION OPERATING AT ROOM TEMPERATURE. THE SOURCE WILL BE USEFUL BOTH AS A NARROW BAND FREQUENCY STABLE SOURCES FOR DRIVING HETERODYNE RECEIVERS AT KEY FREQUENCIES BETWEEN 1 AND 5 THZ (1.4, 1.9, 2.7, 4.7 ETC..) OR FOR LABORATORY SOURCES TO CHARACTERIZE THZ COMPONENTS, INCLUDING MMIC'S, OR POSSIBLY FOR ACTIVE SPECTROMETERS IN AN IN-SITU ENVIRONMENT THE PROPOSED SOURCE WOULD ENABLE THE DEVELOPMENT OF THZ ARRAY RECEIVERS FOR USE IN SPACE AND SUBORBITAL MISSIONS, OR FOR ATMOSPHERIC SOUNDERS AND PLANETARY LANDERS. IN PHASE 1 OUR VECSEL THZ SOURCE, BASED ON INTRA-CAVITY DIFFERENCE FREQUENCY GENERATION, DEMONSTRATED 2MW AT 1.9THZ RUNNING ON A FINITE NUMBER OF CAVITY MODES WITH A LINEWIDTH PER MODE OF AROUND 1MHZ. DESERT BEAM TECHNOLOGIES WILL TEAM UP TERAVISION (TUCSON) AND WITH RESEARCHERS AT THE STEWARD OBSERVATORY RADIO ASTRONOMY LABORATORY (SORAL), UNIVERSITY OF ARIZONA IN PHASE 2 TO FURTHER CHARACTERIZE A BREADBOARD VECSEL 1.9THZ SYSTEM, MEASURE Y-FACTOR AND I-V CURVES, REDESIGN THE VECSEL CAVITY TO REDUCE IT TO SINGLE MODE OPERATION AND TEST IT AS A LOCAL OSCILLATOR FOR SORAL'S 1.9THZ RECEIVER.
Definitive Contract - 541712 Research and Development in the Physical, Engineering, and Life Sciences (except Biotechnology)
Contractor
DESERT BEAM TECHNOLOGIES, L.L.C.
Contracting Agency/Office
National Aeronautics and Space Administration»Mission Support Directorate»NASA Shared Services Center
Effective date
06/01/2011
Obligated Amount
$600k
NNX11CB06C - WITH MORE MISSIONS AT HIGH DATA RATES DEMANDING USE OF LIMITED SPECTRAL RESOURCES, NASA'S SCAN OFFICE RECENTLY COORDINATED A STUDY TO IDENTIFY A SPACE COMMUNICATIONS ARCHITECTURE TO SUPPORT FUTURE MISSIONS. THE STUDY RECOMMENDS PRECODED GMSK AND AR4JA LDPC CODES AS PREFERRED OPTIONS IN MOST SPACE NETWORK AND GROUND NETWORK FORWARD AND RETURN LINKS AND DEEP SPACE NETWORK RETURN LINKS. THIS MODULATION AND CODING PAIR PROVIDES EXCELLENT BANDWIDTH-EFFICIENCY AND GREATLY REDUCED TRANSMITTER SWAP. UNFORTUNATELY, THERE ARE NO HIGH-DATA-RATE AR4JA LDPC DEVICES CURRENTLY AVAILABLE AND EXISTING GMSK RECEIVERS OPERATE FAR FROM THE PERFORMANCE PREDICTED BY THEORY, ESPECIALLY IN THE PRESENCE OF SEVERE CHANNEL AND EQUIPMENT IMPAIRMENTS. PHASE I PROVIDED A DESIGN OF A SOFT-DECISION GENERATING GMSK DEMODULATOR INTEGRATED WITH AN AR4JA LDPC DECODER AND WITH ESTIMATION AND COMPENSATION OF A COMPREHENSIVE SET OF SEVERE IMPAIRMENTS. FIXED-POINT SIMULATIONS SHOW PERFORMANCE WITHIN A SMALL FRACTION OF A DB OF THE PERFORMANCE WITH FAR LESS BANDWIDTH-EFFICIENT MODULATIONS SUCH AS BPSK. THE RESULTS OF THIS EFFORT SHOW THE TECHNICAL AND COMMERCIAL VIABILITY OF AN INTEGRATED GMSK/AR4JA LDPC DESIGN. THE PROPOSED PHASE 2 EFFORT INVOLVES THE DEVELOPMENT AND DELIVERY OF A PROTOTYPE TRANSMITTER AND RECEIVER TO DEMONSTRATE THE SUPERIOR CAPABILITIES OFFERED BY THIS INNOVATION AND ENABLE SUBSEQUENT COMMERCIALIZATION. A SIMPLE AND HIGHLY FLEXIBLE GUI SYSTEM FOR PROTOTYPE CONFIGURATION AND CONTROL AND MODULAR API DESIGN WILL ALLOW PHASE II REFINEMENT OF THE DESIGN AND FACILITATE INTEGRATION IN FUTURE COMMERCIAL PRODUCTS.
Definitive Contract - 541712 Research and Development in the Physical, Engineering, and Life Sciences (except Biotechnology)
Contractor
ORB ANALYTICS
Contracting Agency/Office
National Aeronautics and Space Administration»Mission Support Directorate»NASA Shared Services Center
Effective date
06/01/2011
Obligated Amount
$600k
NNX11CB31C - CHRONOS TECHNOLOGY (DIV. OF FMI, INC.) PROPOSES TO DESIGN, FABRICATE AND DELIVER A CONCEPTUALLY PROVEN, PRACTICAL, AND COMMERCIALLY AVAILABLE SOLUTION FOR A NOVEL COMPACT, RADIATION HARDENED, STABLE, LOW POWER, PROGRAMMABLE CRYSTAL OSCILLATOR (RPXO), FOR HIGH RELIABILITY SPACE&EXTREME TEMPERATURE APPLICATIONS. OUR PROPOSED DEVICE WILL BE OFFERED IN A ROBUST MINIATURE 5X7MM INDUSTRY STANDARD SURFACE MOUNT PACKAGE (0.24 GRAMS ONLY). WE HAVE ENGAGED IN THE PHASE I STUDY TO FURTHER REFINE THE APPROACH WITH MORE CONFIDENCE WHICH CONCLUDES THAT THE PROPOSED SOLUTION WOULD ALSO OFFER COMPELLING FEATURES SUCH AS SCALABLE (WIDE) FREQUENCY RANGE (100KHZ TO 250MHZ), AND DUAL OUTPUT LOGIC COMPATIBILITY (CMOS&LVDS). THE COMPELLING FEATURES OF OUR DEVICE FEATURES INCLUDE DRASTICALLY IMPROVED RELIABILITY AND QUICKER AVAILABILITY. THE OVERALL DESIGN OF THE RPXO INCLUDES A RADIATION HARDENED SIGE ASIC THAT OPERATES OVER THE EXTREME TEMPERATURE RANGE OF -230C TO +150C AND HOLDS ALL THE NECESSARY FUNCTIONS OF A CRYSTAL DRIVER CIRCUIT, SYNTHESIZER, AND OUTPUT BUFFERS. THE ASIC UNIQUELY PROVIDES DUAL OUTPUT LOGIC COMPATIBILITY (CMOS AND LVDS). ALL ASPECTS OF RADIATION HARDNESS SUCH AS TID, ELDERS AND SEU HAVE BEEN RESEARCHED AND ADDRESSED IN THE PHASE 1 STUDY. THE SIGE ASIC IS INTEGRATED WITH A HIGH RELIABILITY AND RADIATION HARDENED CRYSTAL RESONATOR IN A HIGHLY COMPLIANT YET ROBUST MINIATURE PACKAGE.
Definitive Contract - 541712 Research and Development in the Physical, Engineering, and Life Sciences (except Biotechnology)
Contractor
FREQUENCY MANAGEMENT INTERNATIONAL INC
Contracting Agency/Office
National Aeronautics and Space Administration»Mission Support Directorate»NASA Shared Services Center
Effective date
06/01/2011
Obligated Amount
$599.9k

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