Latch, Inc.

TELEDYNE SHALL PROVIDE FORTY TWO (42) FUNCTIONAL H4RG-10 SCA UNITS, AS DESCRIBED BELOW. THE CONTRACTOR SHALL PROVIDE, ACCORDING TO THE NOTIONAL SCHEDULE BELOW, THE FACILITIES, PERSONNEL, SERVICES, TOOLS, EQUIPMENT, AND MATERIALS NECESSARY TO: A) JUNE 2014 - JAN 2015, FABRICATE TWELVE (12) SCA UNITS FOR FULL ARRAY DEMONSTRATION LOT A. IN RECOGNITION THAT THE DCL WILL BE UTILIZED FOR TEST AND EVALUATION, THEY SHALL BE FUNCTIONAL. THE GOVERNMENT, AT ITS DISCRETION, MAY ALLOW SOME NUMBER OF NON-FUNCTIONAL SCA'S TO BE DELIVERED DEPENDING UPON YIELD AND ESTIMATES OF OVERALL COST. B) SCREEN AND TEST TWELVE (12) SCAS. THE SCOPE OF THE SCREEN TEST SHALL BE SUFFICIENT TO DIFFERENTIATE BETWEEN GENERALLY FUNCTIONAL AND NON-FUNCTIONAL SCAS AT OPERATING TEMPERATURE. C) NOV 2014 - JUN 2015, FABRICATE TWELVE (12) SCA UNITS FOR FULL ARRAY DEMONSTRATION LOT B. IN RECOGNITION THAT THE DCL WILL BE UTILIZED FOR TEST AND EVALUATION, THEY SHALL BE FUNCTIONAL. THE GOVERNMENT, AT ITS DISCRETION, MAY ALLOW SOME NUMBER OF NON-FUNCTIONAL SCA'S TO BE DELIVERED DEPENDING UPON YIELD AND ESTIMATES OF OVERALL COST. D) SCREEN AND TEST TWELVE (12) SCAS. THE SCOPE OF THE SCREEN TEST SHALL BE SUFFICIENT TO DIFFERENTIATE BETWEEN GENERALLY FUNCTIONAL AND NON-FUNCTIONAL SCAS AT OPERATING TEMPERATURE. E) OCT 2015 - MAY 2016, FABRICATE EIGHTEEN (18) SCA UNITS FOR THE YIELD DEMONSTRATION LOT. IN RECOGNITION THAT THE DCL WILL BE UTILIZED FOR TEST AND EVALUATION, THEY SHALL BE FUNCTIONAL. THE GOVERNMENT, AT ITS DISCRETION, MAY ALLOW SOME NUMBER OF NON-FUNCTIONAL SCA'S TO BE DELIVERED DEPENDING UPON YIELD AND ESTIMATES OF OVERALL COST. F) SCREEN AND TEST TWELVE (18) SCAS. THE SCOPE OF THE SCREEN TEST SHALL BE SUFFICIENT TO DIFFERENTIATE BETWEEN GENERALLY FUNCTIONAL AND NON-FUNCTIONAL SCAS AT OPERATING TEMPERATURE. G) PROVIDE DOCUMENTATION AND DELIVERABLE DATA PER CONTRACT. H) FLIGHT QUALIFICATION OF A FLIGHT REPRESENTATIVE DESIGN, INCLUDING BUT NOT LIMITED TO RADIATION TESTING (LIFETIME AND LATCHUP, PROTONS, ELECTRONS, AND HEAVY IONS), VIBRATION, THERMAL (EXTREMES AND CYCLING), POWER CYCLING, AND MATE/DEMATE CYCLES. A MINIMUM OF 3 PARTS SHALL BE TESTED.

NASA'S GODDARD SPACE FLIGHT CENTER (GSFC) IS ACQUIRING A SPACE-QUALIFIED GIMBAL AND LATCH ASSEMBLY FOR USE WITH AN OPTICAL SYSTEM. THE GIMBAL AND LATCH ASSEMBLY INCORPORATES A GIMBAL ASSEMBLY, LATCH ASSEMBLY, AND INSTRUMENT PANEL ASSEMBLY. THE OPTICAL SYSTEM INTENDED FOR USE WITH THE GIMBAL AND LATCH ASSEMBLY IS OUTSIDE THE SCOPE OF THIS CONTRACT. THEREFORE, FOR TESTING PURPOSES, THE GIMBAL AND LATCH ASSEMBLY INCLUDES A BRIDGE MASS ASSEMBLY IN PLACE OF THE OPTICAL SYSTEM. THE GIMBAL ASSEMBLY AND LATCH ASSEMBLY ARE BOTH TO BE MOUNTED TO THE INSTRUMENT PANEL ASSEMBLY. THE INSTRUMENT PANEL ASSEMBLY PROVIDES ELECTRICAL AND MECHANICAL FEATURES FOR THE INTEGRATION OF GIMBAL AND LATCH ASSEMBLY TO ANY HIGHER LEVEL ASSEMBLIES. THE BRIDGE MASS ASSEMBLY MOUNTS TO THE GIMBAL ASSEMBLY. THE GIMBAL ASSEMBLY PRO-VIDES PRECISION MOTION AND ACCURATE POINTING OF THE BRIDGE MASS ASSEMBLY. THE LATCH PRO-VIDES PROTECTION AND RESTRAINT FOR THE BRIDGE MASS ASSEMBLY AGAINST ENVIRONMENTAL HAZARDS. FOR THIS CONTRACT, THE VENDOR SHALL CONSTRUCT TWO GIMBAL AND LATCH ASSEMBLIES (GLAS).

PURCHASE 4 EA. NSN 5960-01-460-0115AY CRT ASSY; 4 EA NSN 5305-01-520-9469AY CRT ASSY; 6 EA NSN 8475-01-475-4702, ANTI SCRATCH DAY VISOR; 5 EA NSN 8475-01-475-4626TG, VISOR LATCH KIT; 5 EA NSN 8475-01-475-4741MH, VISOR KNOB KIT; 1 EA NSN 8475-01-475-6577TG, HELMET (XL); 3 EA NSN 8475-01-475-6575TG, HELMET (L); 2 EA NSN 8475-01-520-9474, HELMET RECEPTACLE KIT; 37 EA NSN 6150-01-469-7865AY, CABLE ASSY, (XL); 2 EA NSN 6150-01-469-7865AY, CABLE ASSY, (XL); 98 EA NSN 6150-01-479-7863AY, CABLE ASSY, (L); 34 EA NSN 6150-01-469-7862AY, CABLE ASSY, (M); 39 EA NSN 1280-01-470-1435, MTU, 12 EA NSN 1280-01-506-689, MTU; 2 EA NSN 8475-01-504-9331AY, UHVI HELMET, (XL); 1 EA NSN 8475-01-504-9332AY, UHVI HELMET, (M); 1 EA NSN 8475-01-504-9330AY, UHVI HELMET, (L); 5 EA NSN 8415-01-0520-8958, VISOR.

IGF::OT::IGF NASA/GSFC REQUIRES A SPACE-QUALIFIED GIMBAL AND LATCH ASSEMBLY FOR USE WITH AN OPTICAL SYSTEM. THE GIMBAL AND LATCH ASSEMBLY INCORPO RATES A GIMBAL ASSEMBLY, LATCH ASSEMBLY, AND INSTRUMENT PANEL ASSEMBLY. THE OPTICAL SYS TEM INTENDED FOR USE WITH THE GIMBAL AND LATCH ASSEMBLY IS OUTSIDE THE SCOPE OF THIS PROCUREMENT. FOR TESTING PURPOSES, THE GIMBAL AND LATCH ASSEMBLY WILL INCLUDE A BRIDGE MASS ASSEMBLY IN PLACE OF THE OPTICAL SYSTEM. THE OPTICAL SYSTEM WILL BE INTEGRATED AT A LATER DATE AND IS OUTSIDE THE SCOPE OF THIS CONTRACT.

THE PURPOSE OF THIS DELIVERY ORDER IS TO INCORPORATE ECP-0917 FOR NRE AND RETROFIT KITS FOR NACELLE DOOR AND HOOK LATCH PINS.

HST LATCHES - REFURBISHMENT

8504856819!15-TON LATCH-HEAD CRIMPER, 5.

THIS PROCUREMENT IS FOR A SPACE FLIGHT PROPELLANT TANK FOR THE PLANKTON, AEROSOL, CLOUD, OCEAN ECOSYSTEM (PACE) SPACECRAFT. THIS CONTRACT INCLUDES THE FABRICATING, TEST, INSPECT, AND DELIVER OF ONE (1) DIAPHRAGM PROPELLANT TANK, UTILIZE AN EXISTING PROPELLANT TANK SIMULATOR TO PERFORM DIAPHRAGM AND SLOSH TESTING, AND PERFORM PROPELLANT TANK VIBRATION TESTING. THE CONTRACTOR WILL ALSO PROVIDE GSFC NO-COST USE OF THEIR PROPELLANT TANK SIMULATOR FOR SUPPORTING PROPELLANT TANK CLOSE OUT WELDING. THIS SIMULATOR WILL BE SHIPPED TO GSFC UPON COMPLETION OF SLOSH TESTING. PACE IS COMPRISED OF THREE INSTRUMENTS, AN OCEAN COLOR INSTRUMENT (OCI) AND TWO POLARIMETERS (HARP2 AND SPEXONE). THE OCI IS THE PRIMARY INSTRUMENT ON THE OBSERVATORY AND IS BEING DEVELOPED AT GSFC. THE OCI IS A HYPER-SPECTRAL SCANNING (HSS) RADIOMETER DESIGNED TO MEASURE SPECTRAL RADIANCES FROM THE ULTRAVIOLET TO SHORTWAVE INFRARED (SWIR) TO ENABLE ADVANCED OCEAN COLOR AND HERITAGE CLOUD AND AEROSOL PARTICLE SCIENCE. THE POLARIMETERS ARE SECONDARY INSTRUMENTS ON THE PACE OBSERVATORY, DEVELOPED OUTSIDE OF GSFC. BOTH POLARIMETERS ARE MULTI-BAND, MULTI-ANGLE POLARIMETERS PLANNED TO MEASURE SPECTRAL POLARIZED AND UNPOLARIZED RADIANCES TO ENABLE ADVANCED CLOUD AND AEROSOL PARTICLE SCIENCE, AS WELL AS IMPROVED ATMOSPHERIC CORRECTION FOR OCEAN COLOR ACTIVITIES. THE PACE MISSION REQUIRES AN INTEGRATED PROPULSION SYSTEM. THE PACE PROPULSION SUBSYSTEM CONSISTS OF THE COMPONENTS REQUIRED TO CONTAIN, CONTROL, MONITOR, AND UTILIZE HYDRAZINE PROPELLANT TO ACCOMPLISH ORBIT MANEUVERING AND MOMENTUM MANAGEMENT REQUIREMENTS. THE PROPULSION SUBSYSTEM INCLUDES A PROPELLANT TANK, PROPELLANT FILTER, PRESSURE TRANSDUCERS, SURGE SUPPRESSION DEVICES, LATCHING ISOLATION VALVES, FILL AND DRAIN VALVES, THRUSTERS, AND INTERCONNECTING TUBING. THE PROPULSION SUBSYSTEM ALSO INCLUDES ELECTRICAL HARDWARE CONNECTING COMPONENTS TO AVIONICS AND TEST CONNECTORS, AS WELL AS HEATERS, THERMOSTATS, AND SENSORS ON THE PROPELLANT LINES AND COMPONENTS. THE SYSTEM IS AN ALL WELDED SYSTEM USING STAINLESS STEEL TUBING; ALL WELDS ARE RADIOGRAPHICALLY INSPECTED PRIOR TO THE SYSTEM PROOF PRESSURE TEST AND CHECKED FOR LEAKAGE AFTER THE SYSTEM PROOF PRESSURE TEST. THE PROPULSION SUBSYSTEM IS A MONOPROPELLANT HYDRAZINE SYSTEM USING UNREGULATED (BLOWDOWN) GASEOUS HELIUM PRESSURIZATION

THE EUROPA MISSION IS BEING FORMULATED AND IMPLEMENTED BY A JOINT PARTNERSHIP BETWEEN THE JET PROPULSION LABORATORY AND THE APPLIED PHYSICS LABORATORY, WITH NASA GSFC BUILDING THE PROPULSION SYSTEM FOR THE APPLIED PHYSICS LABORATORY. THIS DOCUMENT DEFINES THE WORK TO BE PERFORMED BY THE SUPPLIER FOR THE DESIGN, DEVELOPMENT, FABRICATION, AND DELIVERY OF THE EUROPA PROJECT HIGH PRESSURE LATCH VALVE (HPLV), FROM HERE ON REFERRED TO AS THE LATCH VALVE. THE HPLV DESIGN SHALL HAVE BEEN QUALIFIED TO THE LEVELS IN EUROPA PROJECT HPLV SPECIFICATION EUROPA-PROP-SPEC-0009 OR THE SUPPLIER SHALL DESIGNATE ONE (1) NON-FLIGHT UNIT AS A QUALIFICATION TEST UNIT TO TEST AT THE QUALIFICATION LEVELS LISTED IN THIS DOCUMENT. ANY PROTOFLIGHT VERIFICATIONS SHALL BE SUBJECT TO APPROVAL BY THE CONTRACTING OFFICER'S REPRESENTATIVE (COR). THE SUPPLIER SHALL GENERATE A SPECIFICATION VERIFICATION MATRIX LISTING EACH SECTION IN EUROPA PROJECT HPLV SPECIFICATION EUROPA-PROP-SPEC-0009 AND DESCRIBING THE VERIFICATION METHOD (INSPECTION, ANALYSIS, DEMONSTRATION, OR TEST), DETAILS OF THE VERIFICATION PLAN, AND SPECIFIC DOCUMENT(S) SHOWING VERIFICATION EVIDENCE FOR EACH REQUIREMENT.

IGF::OT::IGF RADIATION HARDENED APPLICATION SPECIFIC INTEGRATED CIRCUITS (ASICS) PROVIDE THE HIGHEST PERFORMANCE, LOWEST POWER AND SMALLEST SIZE ICS FOR SPACE MISSIONS. TO DRAMATICALLY REDUCE THE DEVELOPMENT CYCLE, AND REDUCE COST TO TAPE OUT, MICRO-RDC PROPOSES A STRUCTURED ASIC APPROACH. IN THIS METHODOLOGY, WE FIX AN ARRAY OF COMPLEX LOGIC CELLS AND PROVIDE A FIXED AREA ARRAY FOR I/O PADS SUPPORTING IN EXCESS OF 400 COMPLEMENTARY METAL-OXIDE SEMICONDUCTOR (CMOS) GENERAL PURPOSES INPUT/OUTPUT (GPIO) PINS. IN ADDITION, WE FIX THE POWER GRID AND THE PINS ASSOCIATED WITH POWER (CORE AND I/O) AND GROUND. THUS, WE REQUIRE ONLY ROUTING IN A SUBSET OF THE METAL LAYERS TO CONFIGURE THE STRUCTURED ASIC FOR A SPECIFIC DESIGN. THIS LEADS TO SUBSTANTIAL REDUCTION IN DESIGN AND VERIFICATION TIME TO TAPE OUT. COSTS ARE REDUCED BY REQUIRING A SUBSET OF MASK CHANGES PER DESIGN. IN THIS WORK, WE WILL BUILD ON MICRO-RDC'S EXISTING 90NM SILICON-PROVEN RADIATION HARDENED STRUCTURED ASIC PLATFORM. WE WILL DEVELOP A STRUCTURED ASIC PLATFORM AT THE 45NM SOI TECHNOLOGY NODE. THE OBJECTIVE IS TO INCREASE CLOCK SPEEDS TO HUNDREDS OF MHZ. SINGLE EVENT UPSET (SEU) IMMUNITY IS ACHIEVED IN THE SEQUENTIAL LOGIC USING TEMPORAL LATCH TECHNOLOGY. WE WILL PROVIDE TURNKEY REGISTER TRANSFER LANGUAGE (RTL) TO GDSII CAPABILITY FOR RADIATION HARDENED ASICS.