Amplitude, Inc.

RESEARCH AND DEVELOPMENT LOW-LATENCY, HIGH-AMPLITUDE TVC

MULTI-FUNCTION LASER 4023 AGREEMENT

PHASE II SBIR - ULTRA-HIGH TEMPORAL RESOLUTION LASER RADAR (LADAR) RECEIVER - THE ARMY IS IN NEED OF AN ULTRA-HIGH TEMPORAL RESOLUTION LADAR RECEIVER FOR DIRECT DETECTION OF DIFFICULT TARGETS ON UAV AND UGV SENSOR PLATFORMS. CURRENT DESIGNS EMPLOY 1.5-MICRON FIBER LASERS THAT CAN EMIT SUB-NANOSECOND PULSES AT REPETITION RATES FROM 50 KHZ TO 1.63 MHZ. THE GOAL OF THIS PROGRAM IS TO DEVELOP A LADAR RECEIVER WITH THE FOLLOWING REQUIREMENTS: SUB-NANOSECOND LASER PULSE RESPONSE, A 1.5-MICRON RESPONSE, 75-100 MICRON DIAMETER FIBER COUPLED APD WITH THE BEST POSSIBLE EXCESS NOISE PERFORMANCE,<500-PSEC PULSE TIME-OF-FLIGHT (TOF) RESPONSE AND THE ABILITY TO CAPTURE MULTIPLE TOF AND SAMPLE 50-PSEC PULSE AMPLITUDES AT KHZ PULSE-REPETITION RATES.

IGF::OT::IGF "RISK REDUCTION FOR FUTURE COMMUNITY RESPONSE TESTING WITH A LOW-BOOM FLIGHT DEMONSTRATION VEHICLE." THE CONTRACT SHALL CONSIST OF TWO PHASES. THE FIRST PHASE SHALL ADDRESS THE CREATION OF A CONCEPTUAL PLAN FOR COMMUNITY RESPONSE TESTING USING AN EXPERIMENTAL LOW-BOOM AIRCRAFT, AND THE IDENTIFICATION OF RISK AND DEVELOPMENT AREAS ASSOCIATED WITH THE PLANNING, EXECUTION, AND DATA ANALYSES OF SUCH TESTING. THE SECOND PHASE SHALL ADDRESS THE HIGH PRIORITY RISK AREAS THROUGH ADDITIONAL RESEARCH OR EXPERIMENTATION.THE CONCEPTUAL TEST PLAN SHALL ADDRESS A BROAD SCOPE OF TEST ELEMENTS. THE ELEMENTS THAT SHALL BE CONSIDERED AND ASSESSED INCLUDE, BUT ARE NOT LIMITED TO:LESSONS LEARNED FROM A PREVIOUS NASA PILOT COMMUNITY STUDY CONDUCTED IN 2011 AT EDWARDS AIR FORCE BASE, AS DOCUMENTED IN:J. PAGE ET AL., WAVEFORMS AND SONIC BOOM PERCEPTION AND RESPONSE (WSPR): LOW-BOOM COMMUNITY RESPONSE PROGRAM PILOT TEST DESIGN, EXECUTION, AND ANALYSIS, NASA CR-2014-218180.S. FIDELL ET AL., PILOT TEST OF A NOVEL METHOD FOR ASSESSING COMMUNITY RESPONSE TO LOW-AMPLITUDE SONIC BOOMS, NASA CR-2012-217767.SELECTION OF COMMUNITIES TO PARTICIPATE IN THE FUTURE STUDIES (E.G. NUMBER OF COMMUNITIES AND THE CRITERIA AND METHODOLOGY FOR THEIR SELECTION)STRATEGIES TO INTRODUCE A NEW NOISE SOURCE TO A COMMUNITY AIMED AT ELICITING COOPERATION AND MINIMIZING BIAS IN ACQUIRED DATA SELECTION OF STUDY PARTICIPANTS WITHIN THE COMMUNITIES (E.G. NUMBER OF PARTICIPANTS AND METHOD/CRITERIA FOR THEIR SELECTION) ANNOYANCE DATA REQUIRED AND ACQUISITION METHODS ACOUSTICAL DATA REQUIRED AND PREDICTION/ACQUISITION METHODS ANALYSIS METHODS TO OBTAIN USEFUL NOISE-ANNOYANCE DOSE-RESPONSE RELATIONSHIP(S) SONIC BOOM EXPOSURE (SINGLE EVENT LEVELS, NUMBER OF BOOMS PER DAY, TIME OF DAY) APPROACHES FOR IMPROVING TEST EFFICIENCY AND AFFORDABILITY COST, TIMING, AND TEST DURATION CAPABILITIES AND PERFORMANCE OF THE LOW-BOOM RESEARCH AIRCRAFT AND ITS IMPACT ON TEST EXECUTION

SBIR PHASE II - VISIBLE LIGHT PHASE AND AMPLITUDE MODULATORS FOR QUANTUM SENSORS AND CLOCKS

IGF::OT::IGF OTHER FUNCTION - LARGE AMPLITUDE, UNSTEADY HEATING LOADS AND STEEP FLOW GRADIENTS PRODUCED IN REGIONS OF SHOCK-WAVE/TURBULENT BOUNDARY-LAYER INTERACTION (SWTBLI) POSE A SERIOUS AND CHALLENGING PROBLEM FOR DESIGNERS OF HYPERSONIC VEHICLES. CHARACTERIZING SWTBLI FLOW FEATURES, SUCH AS THE SIZE OF FLOW SEPARATION, IS IMPORTANT FOR DESIGN EVALUATION AND CFD VALIDATION. TAO SYSTEMS AND CUBRC PROPOSE TO DEVELOP A WIDE-BANDWIDTH, THIN-FILM HEAT TRANSFER SENSOR SYSTEM THAT QUANTIFIES THE HIGH FREQUENCY SWTBLI AT DUPLICATED FLIGHT CONDITIONS. THIS EFFORT COMBINES TAO SYSTEMS' HIGH FREQUENCY-RESPONSE/HIGH-SENSITIVITY ELECTRONICS AND SIGNAL PROCESSING TECHNIQUES WITH THE UNIQUE EXPERTISE OF CUBRC IN HIGH-SPEED, HIGH-ENTHALPY FLOWS TO OBTAIN SPATIOTEMPORAL INFORMATION FOR THE DEVELOPMENT OF PHYSICS-BASED TURBULENCE MODELS.

IGF::OT::IGF WE PROPOSE TO DEVELOP A SENSITIVE PM MEASUREMENT INSTRUMENT TO DETERMINE SOOT PARTICLE MASS DISTRIBUTION FROM AIRCRAFT ENGINE EXHAUSTS AS WELL AS FROM OTHER IC ENGINE EMISSIONS. FUNDAMENTAL OF THE PROPOSED TECHNIQUE IS TO MEASURE PARTICLE CHARGE UNDER AN ELECTRIC FIELD. THROUGH EXTENSIVE EXPERIMENTAL AND THEORETICAL INVESTIGATION ON SOOT EMISSIONS FROM IC ENGINES OVER THE PAST FOUR DECADES, IT HAS BEEN WELL-KNOWN THAT ENGINE SOOT PARTICLES ARE USUALLY CHARGED. COUNTING PARTICLE CHARGE AT SPECIFIC MASS COULD LEAD TO THE DETERMINATION OF BOTH TOTAL PARTICLE COUNT AND MASS. CURRENTLY COMMERCIALLY AVAILABLE ELECTROMETRIC MEASUREMENTS ON CHARGED PARTICLES SUFFER FROM RAPID SIGNAL DRIFT, WHICH LIMITS ITS APPLICATIONS ON SOOT EMISSION MEASUREMENTS. IN OUR PROPOSED DESIGN, AN AMPLITUDE MODULATION SCHEME IS INCLUDED TO ELIMINATE THE BACKGROUND SIGNAL DRIFT AND ALSO IMPROVE DETECTION SENSITIVITY. THE PROPOSED SOOT MASS DISTRIBUTION MONITOR WILL BE APPROXIMATELY 50 POUNDS IN WEIGHT AND CONSUME APPROXIMATELY 300W ELECTRICAL POWER. IT WILL ALSO BE CAPABLE OF BEING REMOTELY CONTROLLED AND OPERATING UNDER VACUUM CONDITION. TOTAL COST OF THE PROPOSED DEVICE COULD BE LESS THAN $30,000.

IGF::OT::IGF THE HIGH-EFFICIENCY AND LINEAR UPEND RF C-BAND POWER A MPLIFIER WAS DESIGNED, SIMULATED AND PARTIALLY PROTOTYPED IN PHASE I TO PROVIDE RANGE EXTENSION FOR THE NASA/ROCKWELL COLLINS CONTROL AND NON-PAYLOAD COMMUNICATION (CNPC) PROGRAM'S TRANSCEIVER IN SUPPORT OF NAS INTEGRATION OF UAS. UPEND LEVERAGES STATE-OF-THE-ART ANALOG PRE-DISTORTION LINEARIZATION AND DOHERTY POWER AMPLIFIER CIRCUITS, MMIC TECHNOLOGY, AND MODULE-LEVEL POWER EFFICIENCY AND THERMAL DESIGN, TO MINIMIZE SIZE, WEIGHT, AND POWER CONSUMPTION (SWAP) OF THE CONNECTORIZED PA MODULE, WHILE MAINTAINING THE LINEAR OUTPUT REQUIRED BY AMPLITUDE MODULATION. THE UPEND MODEL ACHIEVED SIGNIFICANT IMPROVEMENT IN ERROR VECTOR MAGNITUDE (EVM) AND POWER EFFICIENCY, WHILE THE PROOF-OF-CONCEPT PROTOTYPE PROVIDED VALIDATION FOR THE MODEL WITH RESPECT TO EVM PERFORMANCE IMPROVEMENT WITH LINEARIZATION. IN PHASE II NUWAVES WILL ADDRESS THE NEEDS OF BOTH AMPLITUDE-MODULATED AND CONSTANT-ENVELOPE WAVEFORMS BY DEVELOPING MULTIPLE MMICS AND PACKAGING THEM TOGETHER AS NEEDED. SEPARATE DIE WILL BE FABRICATED FOR THE DOHERTY AMPLIFIER AND THE LINEARIZER CIRCUITS, WIRE BONDED AND PACKAGED INTO TWO DIFFERENT COMPONENT-LEVEL INTEGRATED CIRCUITS ONE WITH AND ONE WITHOUT THE LINEARIZER. TWO DIFFERENT CONNECTORIZED PA MODULE VARIANTS WILL BE DEVELOPED USING THESE TWO COMPONENT-LEVEL ICS, ADDING THE NECESSARY POWER SUPPLY CIRCUITRY, SUPPORTING CIRCUITRY, AND MECHANICAL AND THERMAL DESIGN TO ADDRESS DIFFERENT NASA AND COMMERCIAL MARKET NEEDS.

IGF::OT::IGF THE LCCE-2 PROGRAM BUILDS OFF THE SUCCESSES OF THE SAF "LOW COST CRYOCOOLER ELECTRONICS FOR SPACE MISSIONS" PROGRAM, EXTENDING THE PERFORMANCE OF THE DEVELOPED LCCE TO INCLUDE ACTIVE VIBRATION CANCELLATION AND ADVANCED INPUT POWER BUS CIRCUITRY. THE FORMER IS IMPORTANT FOR IMAGING PAYLOADS BECAUSE THE EXPORTED VIBRATION FROM THE CRYOCOOLER CAN BE A MAJOR CONTRIBUTOR TO THE OVERALL IMAGE JITTER. THE LATTER WILL PROVIDE THE ABILITY TO SAFELY OPERATE THE CRYOCOOLER SYSTEM OFF OF VIRTUALLY ANY SPACECRAFT POWER BUS FROM ALL PERSPECTIVES, MEANING THAT THE CRYOCOOLER SYSTEM WILL BE PROTECTED FROM TRANSIENT EFFECTS FROM A "DIRTY BUS," AND THE CRYOCOOLER WILL NOT IMPART BACK ONTO THE POWER BUS LARGE AMPLITUDE CURRENT RIPPLE THAT WOULD OTHERWISE AFFECT THE PERFORMANCE OF OTHER DEVICES ON THE BUS.

SIBR PHASE II - MICRODENSITY OF HIGH AMPLITUDE ULTRASHORT RF AND ELECTRIC FIELDS