What is VANGUARD SPACE TECHNOLOGIES, INC's OSHA violation history?

VANGUARD SPACE TECHNOLOGIES, INC has 1 OSHA inspection on record with 3 violations and $1,120 in total penalties.

Establishment profile

VANGUARD SPACE TECHNOLOGIES, INC

9431 DOWDY DR, SAN DIEGO, CA, 92126
334220 — Radio and Television Broadcasting and Wireless Communications Equipment Manufacturing

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OSHA inspections

over 13 years

Violations

$1,120 in penalties

Penalties

$1,120

$373 avg

Summary

VANGUARD SPACE TECHNOLOGIES, INC has accumulated 3 OSHA violations across 1 inspection over 13 years of recorded history, with $1,120 in total assessed penalties.

The establishment sits in the 65th percentile for violations within its industry-state peer group of 75 employers. The most recent enforcement activity was recorded 13 years ago.

Federal records were found in 1 of 15 sources. Sources without matching records returned empty for this establishment.

Agency coverage

VANGUARD SPACE TECHNOLOGIES, INC appears in OSHA workplace safety and FMCSA motor carrier registration records only. No matching records were found in WHD wage enforcement, MSHA mine safety, EPA environmental compliance, NLRB labor relations, OFLC visa and labor certification, SAM.gov federal debarment, CMS nursing home enforcement, UVA Corporate Prosecution Registry, CPSC product recalls, or NHTSA vehicle recalls.

OSHA workplace safety

Inspections

0.1 / yr · last 13 yrs

Violations

0.2 / yr

Penalties

$1,120

$373 avg / violation

Inspection trigger · complaint

1 of 1

100% of inspections at this establishment produced violations,

Peer comparison

65th

Above average violations in NAICS 3342 within CA. Peer group: 75 employers. This establishment has 3 OSHA violations; peer median is 1.

Fewer violationsMore violations

Penalty percentile

62nd

peer median: $465

Inspection frequency

0th

peer median: 1

Safety self-report (OSHA 300A)

No self-reported injury rates filed with OSHA's Injury Tracking Application for VANGUARD SPACE TECHNOLOGIES, INC. Verify directly with OSHA Injury Tracking Application →

Industry benchmark

Industry avg TRIR

0.4

BLS SOII 2024

Industry avg DART

0.2

BLS SOII 2024

Self-reported TRIR

—

Not in OSHA ITA

BLS rates reflect industry-wide averages. Self-reported figures come from OSHA’s Injury Tracking Application; absence of self-reported data does not necessarily indicate non-compliance — many establishments fall below the ITA reporting threshold.

Inspection breakdown

Complaint

Complaint- and accident-triggered inspections are stronger risk signals than routine planned inspections.

OSHA severe injury reports

No severe injury reports (hospitalization, amputation, or loss of an eye) on file under 29 CFR 1904.39 for VANGUARD SPACE TECHNOLOGIES, INC. Verify directly with Occupational Safety and Health Administration →

Activity timeline

Data refreshed

Weekly

First OSHA inspection

—

Most recent activity

13 years ago

No federal enforcement activity has been recorded against this establishment in 13+ years. Most recent activity: 13 years ago. Data on this page is refreshed weekly.

Wage & Hour Division (WHD)

No WHD wage, overtime, or child-labor enforcement cases on file for VANGUARD SPACE TECHNOLOGIES, INC. Verify directly with Wage and Hour Division →

Mine safety (MSHA)

No MSHA mine safety violations on file for VANGUARD SPACE TECHNOLOGIES, INC. Verify directly with Mine Safety and Health Administration →

Labor relations (NLRB)

No NLRB unfair labor practice charges or union representation cases on file for VANGUARD SPACE TECHNOLOGIES, INC. Verify directly with National Labor Relations Board →

Visa & labor certification (OFLC)

No H-1B, H-2A, or H-2B labor condition applications on file for VANGUARD SPACE TECHNOLOGIES, INC. Verify directly with Office of Foreign Labor Certification →

Environmental compliance (EPA)

No EPA inspections or formal enforcement actions on file for VANGUARD SPACE TECHNOLOGIES, INC. Verify directly with Environmental Protection Agency →

Motor carrier safety (FMCSA)

DOT number

2691086

Operation

Federal Motor Carrier Safety Administration — DOT-regulated carrier registration and fleet data.

Federal criminal prosecution record

No federal criminal prosecutions, plea agreements, or deferred-prosecution agreements on file for VANGUARD SPACE TECHNOLOGIES, INC. Verify directly with UVA Corporate Prosecution Registry →

Federal contracts

This location

Obligated (5-yr)

$3K

Obligated (all-time)

$12.7M

Awards

Top agency

Department of Defense

$7.7M

Company-wide — VANGUARD SPACE TECHNOLOGIES, INC. (across 6 entities)

Obligated (5-yr)

$3K

Obligated (all-time)

$23.6M

Awards (all-time)

Consolidated across all USAspending recipient entities under this corporate parent — not attributable to this single location.

Top agencies by obligation (this location)

Department of Defense$7.7M

National Aeronautics and Space Administration$5.0M

Largest awards

Department of Defense
HIGH EFFICIENCY MODULAR SOLAR ARRAY
contract · Last action 2018-02-27
$1,432,145
National Aeronautics and Space Administration
IGF::OT::IGF EXISTING AND PROPOSED MISSIONS WITH AMBITIOUS SCIENCE GOALS DEMAND EVER LARGER PRIMARY MIRRORS WHICH, IN TURN, REQUIRE THE DEVELOPMENT OF NEW LIGHT-WEIGHT, LOW-COST MIRROR TECHNOLOGIES. FOR PHASE 2, VANGUARD SPACE TECHNOLOGIES (VST) PROPOSES TO DELIVER A 2.5 METER, COMPOSITE, ON-AXIS, TELESCOPE BY BUILDING UPON THE SUCCESS OF THE PHASE I EFFORT. THE TELESCOPE WIL BE SUITABLE FOR USE ON THE SUPER BLAST-POL MISSION. VST PROPOSES BUILDING UPON THE SUCCESS AND LEVERAGING THE LESSONS LEARNED FROM PREVIOUS TECHNOLOGY DEMONSTRATION PROGRAMS, LEADING TO A SUCCESSFUL CDR THAT INCLUDES A FINAL DESIGN WITH BUDGETED ERRORS, A DETAILED MANUFACTURING PLAN, AND A MATURE RECURRING COST MODEL AND ESTIMATE. A CDR PACKAGE AND ONE HIGH EFFICIENCY TELESCOPE SYSTEM WIL BE PROVIDED DURING PHASE II. THE ENVISIONED TELESCOPE SYSTEM WIL FEATURE 2X LOWER AREAL MASS AND COMPARABLE AREAL COST FOR UNIT TWO+ THAN BLAST. THE SUPER BLAST-POL TEAM AT UPENN IS COMMITTED TO FLIGHT TEST THIS NEW TECHNOLOGY ON THE MAIDEN FLIGHT IN 2016.
contract · Last action 2016-10-18
$1,419,345
Department of Defense
3-D X-RAY STUDY
contract · Last action 2018-02-27
$799,965
Department of Defense
FLEXIBLE COVERSHIELD FOR THIN FILM SOLAR ARRAYS
contract · Last action 2018-02-27
$750,000
Department of Defense
IGF::OT::IGF ALD-ENHANCED DURABILITY OF LIGHTWEIGHT CO-CURED SOLAR ARRAY PANELS, PHASE II
contract · Last action 2018-02-27
$749,999
National Aeronautics and Space Administration
IGF::OT::IGF OTHER FUNCTION - THIN, FLEXIBLE, AND HIGHLY EFFICIENT SOLAR ARRAYS ARE NEEDED THAT PACKAGE COMPACTLY FOR LAUNCH AND DEPLOY INTO LARGE, STRUCTURALLY STABLE HIGH POWER GENERATORS. INVERTED METAMORPHIC MULTI-JUNCTION (IMM) SOLAR CELLS CAN ENABLE THESE ARRAYS, OFFERING HIGHER EFFICIENCIES OF>33% AND LOWER MASS AND FLEXIBILITY, BUT INTEGRATION CHALLENGES OF THIS THIN CRYSTALLINE CELL TECHNOLOGY NEED SOLUTION. THE THIN HYBRID INTERCONNECTED SOLAR-ARRAY (THINS) TECHNOLOGY ALLOWS ROBUST AND RELIABLE INTEGRATION OF IMM CELLS INTO A FLEXIBLE BLANKET COMPRISING STANDARDIZED MODULES ENGINEERED FOR PRODUCIBILITY. THE MODULES SUPPORT THE IMM CELL BY USING MULTI-FUNCTIONAL MATERIALS FOR STRUCTURAL STABILITY, SHIELDING, CTE STRESS RELIEF, AND INTEGRATED THERMAL AND ELECTRICAL FUNCTIONS. THE PHASE I EFFORT DEMONSTRATED THE FEASIBILITY OF KEY THINS COMPONENT, INCLUDING THE STRUCTURALLY STABILIZED IMM CELL, AND INTEGRATION WITH ADVANCED MULTI-FUNCTIONAL SUBSTRATE AND SUPERSTRATE COMPONENTS, AND COMPLETED THE MODULARITY APPROACH FOR INTERFACING INTO THE ROLL OUT SOLAR ARRAY (ROSA) DEPLOYABLE STRUCTURE, WHILE IMPROVING STANDARDIZATION AND MANUFACTURABILITY. DESIGN EVALUATION SHOWS FIGURES OF MERIT FOR ARRAY LEVEL SPECIFIC POWER, INCLUDING DEPLOYABLE STRUCTURE, GREATER THAN 400W/KG AND VOLUMETRIC EFFICIENCY GREATER THAN15KW/M^3, SIGNIFICANTLY HIGHER THAN CURRENT APPROACHES. THE LOW MASS AND LOW STOWED VOLUME PROVIDES A PATH TO PACKAGE 300KW IN A SINGLE LAUNCH WITH A DEPLOYMENT APPROACH THAT USES SIMPLE, ROBUST MECHANISMS. PHASE II ADVANCES THE THINS/ROSA TECHNOLOGY, INCORPORATING ADVANCED 4 -JUNCTION IMM SOLAR CELLS INTO THINS MODULES USING DEMONSTRATED SPACEFLIGHT QUALIFIED MATERIALS, TESTING MODULE COUPONS IN THERMAL CYCLING AND PLASMA ENVIRONMENTS, FABRICATING A FULL-SCALE MODULE TO DEMONSTRATE AUTOMATABLE MANUFACTURING PROCESSES, INTEGRATING THAT MODULE AND INACTIVE MODULES (WITH CELL SIMULATORS) INTO THE ROSA DEPLOYABLE STRUCTURE, AND CULMINATING IN A FULL-SCALE DEPLOYMENT DEMONSTRATION.
contract · Last action 2013-04-02
$749,965
Department of Defense
SBIR II- FLEXIBLE SOLAR ARRAY BLANKET TECHNOLOG
contract · Last action 2021-10-07
$749,000
Department of Defense
IGF::OT::IGF "SYNCHRONIZED MODULAR INTEGRATED DEPLOYABLE ARRAY (P-DOD12-003)"
contract · Last action 2018-02-27
$740,050
Department of Defense
ARMY SBIR PH II CONTRACT
contract · Last action 2020-09-21
$729,890
Department of Defense
SBIR PHASE II RESEARCH AND DEVELOPMENT.
contract · Last action 2020-07-13
$728,756
National Aeronautics and Space Administration
IGF::OT::IGF SPACECRAFT FOR NASA, DOD AND COMMERCIAL MISSIONS NEED HIGHER POWER THAN EVER BEFORE, WITH LOWER MASS, COMPACT STOWAGE, AND LOWER COST. WHILE HIGH EFFICIENCY, SPACE-QUALIFIED SOLAR CELLS ARE IN THEMSELVES COSTLY, INTEGRATING THEM INTO A HIGH PERFORMANCE PHOTOVOLTAIC ASSEMBLY (PVA) USING CONVENTIONAL GLASSING, INTERCONNECTING, STRINGING, TILING AND LAYDOWN TECHNIQUES CAN DOUBLE THEIR COST IN $/WATT. THE COST OF SOLAR POWER COULD BE SIGNIFICANTLY REDUCED IF THE DESIGN OF THE PHOTOVOLTAIC ASSEMBLY COULD BE MODIFIED, MODULARIZED AND STANDARDIZED TO BE COMPATIBLE WITH AUTOMATED ELECTRONIC ASSEMBLY AND TERRESTRIAL SOLAR PANEL MANUFACTURING METHODS. ADDITIONAL BENEFITS OF SUCH AN APPROACH INCLUDE HIGHER QUALITY AND CONSISTENCY, IMPROVED QUALIFICATION TRACEABILITY, AND ROBUSTNESS ON THIN FLEXIBLE AS WELL AS RIGID ARRAYS. DURING THE PHASE I EFFORT VANGUARD SUCCESSFULLY DEMONSTRATED AUTOMATED PICK-AND-PLACE, ELECTRICAL INTERCONNECTION, AND ADHESIVE DISPENSING ADAPTED TO OUR LIGHTWEIGHT FLEXIBLE THIN INTEGRATED SOLAR (THINS) PVA. THINS USES MULTI-CELL COVERS AND ADVANCED INTERCONNECTION AND ENCAPSULATION TECHNOLOGY, WHICH ENABLES AUTOMATED INTEGRATION OF TRADITIONAL AND ADVANCED SPACE QUALIFIED SOLAR CELLS. ENGINEERING ECONOMIC ANALYSIS SHOWED THE POTENTIAL FOR>30% PVA $/WATT COST REDUCTION, WHILE THE ENCAPSULATION APPROACH ASSOCIATED WITH THINS SHOWED ENHANCED DURABILITY IN SPACE ENVIRONMENTS, EVEN AT HIGH VOLTAGES AND EXTREME THERMAL CYCLE ENVIRONMENTS. DURING THE PHASE II PROGRAM WE WILL FURTHER ENHANCE OUR AUTOMATED SUB-MODULE MANUFACTURING, AND SCALE THE APPROACH TO THE MODULE LEVEL. AUTOMATED ASSEMBLY SCALE UP WILL BE PERFORMED WHILE INTEGRATING INTO AN EXISTING DEPLOYABLE SPACE STRUCTURE PLATFORM, ENHANCING THE TRL OF A HIGH PERFORMANCE HIGH POWER APPLICATION OF AUTOMATED CELL INTEGRATION SCALABLE FROM TENS TO HUNDREDS OF KILOWATTS, AND PROVIDING A CREDIBLE COMMERCIALIZATION PATH, ALL WHILE REDUCING SOLAR ARRAY COSTS BY MORE THAN $150/W.
contract · Last action 2016-09-02
$720,748
National Aeronautics and Space Administration
FUTURE NASA MISSIONS INCLUDING THE CORNELL CALTECH ATACAMA TELESCOPE (CCAT) AND GLOBAL ATMOSPHERIC COMPOSITION MISSION (GACM), REQUIRE 1 TO 4 METER APERTURE, SUBMILLIMETER-WAVELENGTH, PRIMARY REFLECTOR (MIRROR) SEGMENTS. ASTIGMATIC SURFACE ERRORS IN A COMPOSITE PRIMARY REFLECTOR AND INCONSISTENT RADIUS OF CURVATURE IN COMPOSITE REFLECTOR SEGMENTS LIMIT APPLICATION OF COMPOSITES TO INSTRUMENTS. THIS PROJECT PROPOSES TO IMPROVE UPON STATE-OF-THE-ART PASSIVE REFLECTOR SURFACE ACCURACY BY CHARACTERIZING THE BEHAVIOR AND PROPERTIES OF ACTUATED, GRAPHITE COMPOSITE REFLECTOR LAMINATES AND PANELS THAT ARE SUITABLE FOR SPACE AND EARTH SCIENCE INSTRUMENTS. SURFACE ERROR IN COMPOSITE PRIMARY REFLECTORS AND INCONSISTENT RADIUS OF CURVATURE IN COMPOSITE REFLECTOR SEGMENTS CURRENTLY LIMIT APPLICATION OF COMPOSITES TO SUBMILLIMETER WAVELENGTH PRIMARY MIRRORS. THE GOAL IS TO MINIMIZE SURFACE ERROR INCLUDING ROC ERROR.
contract · Last action 2012-02-28
$599,999
National Aeronautics and Space Administration
IGF::OT::IGF PHASE III SBIR CONTRACT FOR 25 CM COMPOSITE OPTICAL REFLECTOR CENTERED ON THE VERTEX OF THE PRIMARY PARABOLIC REFLECTOR. THIS IROC MIRROR WILL BE FABRICATED BY PRECISION OPTICAL REPLICATION USING HIGH-MODULUS GRAPHITE-FIBER-REINFORCED COMPOSITE MATERIALS OR EQUIVALENT TECHNOLOGY. SPECIFIC PHASE 1 TASKS INCLUDE: 1. PERFORM AN ENGINEERING STUDY TO MINIMIZE SUBSTRATE AERIAL DENSITY AND OPTIMIZE STIFFNESS. 2. REPLICATE A MINIMUM OF FOUR FLAT SANDWICH COUPONS. THE RESULTS OF THE FLAT COUPON EVALUATION SHALL BE REVIEWED WITH NASA PRIOR TO FABRICATION OF DOUBLY-CURVED (ON-AXIS) COUPONS. THE COUPON FORMAT SHALL BE LARGE ENOUGH TO RETIRE RISK ASSOCIATED WITH THE 25 CM COMPOSITE MIRROR TO BE FABRICATED IN PHASE 2. COUPONS ARE TO BE TESTED VIA INTERFEROMETRY TO DETERMINE OPTICAL FIGURE/ESTABLISH SURFACE RMS ERROR. A MANUFACTURING READINESS REVIEW WITH NASA IS REQUIRED PRIOR TO PROCEEDING TO PHASE 2. SPECIFIC PHASE 2 TASKS INCLUDE: 1. DESIGN AND FABRICATE THE 25 CM DIAMOND TURNED OPTICAL MASTER. THE BASELINE MASTER MATERIAL IS ALUMINUM WITH AN ELECTROLESS NICKEL LAYER AS THE OPTICAL SURFACE. 2. FABRICATE (REPLICATE) THE 25 CM COMPOSITE MIRROR SUITABLE FOR OPERATION AT 1550 NM. TESTING SHALL INCLUDE SURFACE QUALITY MEASUREMENTS AND WEIGHT MEASUREMENT.
contract · Last action 2016-11-29
$256,899
National Aeronautics and Space Administration
IGF::OT::IGF THE PHASE I OBJECTIVE IS TO DEVELOP A PRELIMINARY DESIGN AND MANUFACTURING PLAN FOR CARBON FIBER COMPOSITE REFLECTORS AND/OR A CARBON FIBER TELESCOPE THAT ARE TRACEABLE TO THE REQUIREMENTS OF CURRENT AND FUTURE CMB MISSIONS. THE PHASE II OBJECTIVES ARE TO COMPLETE THE DESIGN AND MANUFACTURING PLANNING, FABRICATE NECESSARY TOOLING, MANUFACTURE HARDWARE COMPONENTS THAT INCLUDE TWO REFLECTOR SUPPORT STRUCTURES, INTEGRATE AND ALIGN THE REFLECTORS AND CONFIRM TELESCOPE OPTICAL PERFORMANCE VIA ANALYSIS OF AS-BUILT MECHANICAL ALIGNMENT AND SURFACE ACCURACY DATA. TO PREPARE FOR AND CONDUCT THE PDR WITHIN SIX MONTHS, THE PROPOSED PHASE I TASKS WILL INCLUDE: 1) DEVELOP TELESCOPE REQUIREMENTS IN CONJUNCTION WITH CMB RESEARCHERS AND/OR NASA WITH THE GOAL OF RESOLVING SUFFICIENT DETAIL TO EVALUATE CFRP TECHNOLOGY FOR CMB MISSIONS, 2) COMPARE THE REQUIREMENTS TO CFRP HERITAGE, AS-BUILT RESULTS, AND EXPERIENCE, 3) DEVELOP A CONCEPT BASED UPON HIGH (CURRENTLY 4-9) TRL CFRP COMPONENT TECHNOLOGIES, 4) PREDICT THE PERFORMANCE OF THE CONCEPT, 5) DEVELOP A PRICING MODEL TO PREDICT RECURRING COST, 6) DEFINE A PRELIMINARY MANUFACTURING PLAN THAT INCLUDES PREDICTED VERSUS BUDGETED ERRORS, 7) DEVELOP A SUMMARY TECHNICAL/COST COMPLIANCE MATRIX THAT SUMMARIZES ALL TECHNICAL AND COST PREDICTIONS VERSUS REQUIREMENTS, 8) SUMMARIZE ALL ENGINEERING, MANUFACTURING, AND COST INFORMATION IN PREPARATION FOR PDR INCLUDING THE ENVISIONED PATH TO TELESCOPE TRL6 DURING PHASE II, AND 9) CONDUCT A PDR WITH SUPPORT FROM MECHANICAL, OPTICAL, STRUCTURAL, THERMAL, MATERIALS, AND MANUFACTURING ENGINEERS.
contract · Last action 2013-07-17
$199,898
Department of Defense
SOLAR PANEL
contract · Last action 2012-09-26
$181,343
Department of Defense
SYNCHRONIZED MODULAR INTEGRATED DEPLOYABLES ARRAY
contract · Last action 2012-07-31
$150,000
Department of Defense
IGF::OT::IGF ALD-ENHANCED DURABILITY OF LIGHTWEIGHT CO-CURED SOLAR ARRAY PANELS
contract · Last action 2013-05-20
$149,999
Department of Defense
IGF::OT::IGF "ADVANCED SOLAR ARRAY FOR DUAL LAUNCH GPS"
contract · Last action 2015-12-24
$149,579
Department of Defense
SBIRSOL2013.3
contract · Last action 2014-01-17
$149,491
National Aeronautics and Space Administration
IGF::OT::IGF THIS PROJECT PROPOSES TO DEVELOP/DEMONSTRATE HIGHER STRENGTH, LOW PRINT-THROUGH, LOW MASS, DISCRETE CORE JOINT DESIGN AND ANALYSIS METHOD FOR LARGE, LIGHTWEIGHT, THERMALLY-STABLE, COMPOSITE SUB-MM REFLECTORS. TWO SMLS REFLECTOR DEMONSTRATORS DELIVERED BY VANGUARD TO JPL WERE OPTIMIZED FOR THERMAL STABILITY AND SPECIFIC STIFFNESS. THE FULL APERTURE WAS DIVIDED INTO THREE ZONES WHERE CORE SLOTS ARE ALIGNED APPROXIMATELY PERPENDICULAR TO THE REFLECTOR SKIN. THIS APPROACH WAS DEFINED AND SELECTED BASED ON: 1) A BASELINE CORE MODULE; 2) CTE TEST DATA INDICATES THE CORE LAMINATE IS ANISOTROPIC; AND 3) THE DESIRE TO REDUCE TEMPERATURE INDUCED ASTIGMATISM BY USE OF ALTERNATING CORE SLOTS. DISCRETE RIBS WERE BONDED UP TO +/-30 FROM THE FRONT FACESHEET. THE PROJECT WILL EVALUATE AND MATURE THE SMLS DESIGN FOR NASA AND JPL. DESIGN MODIFICATIONS WILL BE IDENTIFIED AND DEMONSTRATED TO PRESERVE/IMPROVE THE PREVIOUSLY DEMONSTRATED THERMAL STABILITY AND STIFFNESS. LIGHTWEIGHT, THERMALLY STABLE, LOW-COST LAMINATE DESIGNS, ADHESIVE MATERIALS, AND MANUFACTURING METHODS ARE REQUIRED TO ADEQUATELY STRENGTHEN RIB-TO-FACESHEET BUTT JOINTS AND REDISTRIBUTE LOCAL RIB-TO-FACESHEET LOADS. TO MINIMIZE IMPACT TO EXISTING SMLS' DEMONSTRATION REFLECTOR MASS AND THERMAL STABILITY, DEVELOPMENT OF A NOVEL, SUPPLEMENTARY MODULAR RIB/CLIP AND JOINING METHOD IS ENVISIONED. THE PROPOSED APPROACH WILL REQUIRE FINITE ELEMENT ANALYSES, DESIGN ACTIVITIES, COUPON TESTS, AND MODEL-TO-TEST DATA CORRELATION. ANALYSES WILL INCLUDE MODAL, ACOUSTIC RESPONSE, AND STRENGTH EVALUATION. POTENTIAL MASS REDUCTION OPPORTUNITIES WILL BE IDENTIFIED. EXISTING COUPON FAILURE MODES WILL BE EVALUATED AND LESSONS LEARNED APPLIED TO ENHANCED STRENGTH JOINT CONCEPTS. PREVIOUS DEMONSTRATION REFLECTOR THERMAL DISTORTION TEST RESULTS AND CORRELATION ACTIVITIES WILL BE REVIEWED TO REDUCE MODEL UNCERTAINTY AND EVALUATE THE INFLUENCE OF THE SEVERAL TYPES OF RIB/CLIP JOINTS ON FIGURE CHANGE DUE TO TEMPERATURE SOAK.
contract · Last action 2014-11-25
$125,000
National Aeronautics and Space Administration
IGF::OT::IGF SPACECRAFT FOR NASA, DOD AND COMMERCIAL MISSIONS NEED HIGHER POWER, HIGHER VOLTAGE, AND MUCH LOWER COST SOLAR ARRAYS TO ENABLE A VARIETY OF VERY HIGH POWER MISSIONS. POWER FOR THESE MISSIONS IS ENVISIONED TO REACH FROM 30KW-300KW IN THE NEAR TERM AND TO 1MW IN THE FUTURE. CONVENTIONAL SOLAR ARRAYS ARE SIMPLY NOT UP TO THE CHALLENGE FOR MANY REASONS. HIGH EFFICIENCY, SPACE-QUALIFIED SOLAR CELLS ARE IN THEMSELVES COSTLY,>$250/WATT, AND THERE IS CONSIDERABLE ADDITIONAL COST ASSOCIATED WITH THE LARGE NUMBER OF PIECE-PARTS AND LABOR NEEDED TO ASSEMBLE THE CELLS INTO THE PHOTOVOLTAIC ASSEMBLY. THE CURRENT APPROACH HAS MANY ASSEMBLY STEPS, AND HAS EVOLVED WITH ONLY MINOR CHANGES FROM SOLAR ARRAYS FABRICATED IN THE 1970S, SACRIFICING COST BECAUSE OF RISK ADVERSE INCREMENTAL DEVELOPMENT. IF A VERY LOW COST SOLAR CELL COULD BE IMPLEMENTED, WHILE BEING COMPLEMENTED BY ECONOMICAL AUTOMATED SOLAR ARRAY INTEGRATION PROCESSES, AND HAVING ENVIRONMENTAL DURABILITY, THEN EXTENSIVE COST SAVINGS COULD BE REALIZED, THUS ENABLING ENERGY INTENSIVE NEXT GENERATION MISSIONS. THE PROPOSED INNOVATION IS A VERY LOW COST DURABLE PVA WHICH HAS INTEGRATED CONSTRUCTION DESIGNED FOR MANUFACTURABILITY, AND ACTIVE ARRAY MANAGEMENT FOR VOLTAGE AND CURRENT REGULATION. BY UTILIZING MATURE THIN FILM CIGS TECHNOLOGY, ALONG WITH VANGUARD PROPRIETARY COVERGLASS REPLACEMENT TECHNOLOGY (CGR), AND AUTOMATED INTEGRATION AND LAMINATION PROCESSES, AN EXTREMELY THIN FLEXIBLE LIGHTWEIGHT AND LOW COST SOLAR ARRAY CAN BE REALIZED.
contract · Last action 2014-11-25
$125,000
National Aeronautics and Space Administration
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.
contract · Last action 2012-02-23
$124,986
National Aeronautics and Space Administration
IGF::OT::IGF FLEXIBLE PHOTOVOLTAIC ARRAY TECHNOLOGIES REQUIRE VERY THIN AND PRECISELY CONTROLLED DEPOSITION OF THE POLYMERIC FILMS USED TO FABRICATE THEM. IN MOST FLEXIBLE BLANKET ARCHITECTURES, OPTICALLY TRANSPARENT SILICONES ARE UTILIZED IN THE FABRICATION OF THE ARRAYS, HOWEVER DUE TO THEIR RHEOLOGY AND PROCESSING CONDITIONS THERE ARE LIMITATIONS TO HOW THIN THEY CAN BE APPLIED. IN THIS PROPOSAL, VANGUARD PROPOSES THIN AND AUTOMATED BLANKET LAMINATION AND ENCAPSULATION SYSTEMS (TABLES) THAT UTILIZE AUTOMATED DRAWDOWN METHODS AND RHEOLOGY CONTROL TO RENDER FLEXIBLE BLANKETS APPROACHING 700 W/KG AND ONLY 13 MILS THICK (INCLUDING CELLS). FURTHER, THE TABLES CONCEPT IS EASILY ADAPTED TO A NUMBER OF SUBSTRATES AND SUPERSTRATES, RENDERING "LEO TO GEO" PACKAGING AND AUTOMATION SIMPLY THROUGH APPROPRIATE SUBSTRATE CHOICE.
contract · Last action 2014-11-25
$124,778
National Aeronautics and Space Administration
IGF::OT::IGF NASA NEEDS LOWER COST SOLAR ARRAYS WITH HIGH PERFORMANCE FOR A VARIETY OF MISSIONS. WHILE HIGH EFFICIENCY, SPACE-QUALIFIED SOLAR CELLS ARE IN THEMSELVES COSTLY,>$250/WATT, THERE IS CONSIDERABLE ADDITIONAL COST ASSOCIATED WITH THE PARTS AND LABOR NEEDED TO INTEGRATE THE PHOTOVOLTAIC ASSEMBLY. THE STANDARD APPROACH HAS EVOLVED WITH ONLY MINOR CHANGES, SACRIFICING COST BECAUSE OF RISK AVERSION. INTEGRATION COST CAN BE AS MUCH AS DOUBLE THE BARE CELL COST I.E.>$500/WATT. DRAMATIC COST SAVINGS CAN BE REALIZED THROUGH MANUFACTURING ENGINEERING OF MORE EFFICIENT AUTOMATED ASSEMBLY PROCESSES. IF THE DESIGN OF THE PHOTOVOLTAIC ASSEMBLY COULD BE MODIFIED TO BE COMPATIBLE WITH CONVENTIONAL AND AUTOMATABLE ELECTRONIC ASSEMBLY AND TERRESTRIAL SOLAR PANEL ASSEMBLY APPROACHES, THERE COULD BE CONSIDERABLE COST SAVINGS. THERE ARE MANY ADDITIONAL BENEFITS WITH AUTOMATION WHICH INCLUDE HIGHER QUALITY AND CONSISTENCY. THIS CAN REDUCE FAILURES, INCREASE PRODUCTION THROUGHPUT, SPEED TURNAROUND, AND IMPROVE OVERALL RELIABILITY. COST AND QUALITY IMPROVEMENTS CAN BE REALIZED ON BOTH THIN AND RIGID ARRAYS, INCREASING CURRENT CAPABILITIES, AND ENABLING FUTURE HIGH POWER MISSIONS. THE BENEFITS OF AUTOMATION ARE ENHANCED BY THE NEED FOR HIGH POWER GENERATION IN SUPPORT OF ENERGY INTENSIVE SPACE MISSIONS. A 300KW ARRAY AT $500/W WOULD COST $150M JUST FOR THE SOLAR CELL INTEGRATED ARRAY PANELS. A $150/W CELL INTEGRATION COST REDUCTION WOULD TRANSLATE INTO SAVINGS OF $45M, BEFORE CONSIDERING THE IMMEDIATE AND SUBSTANTIAL BENEFITS IN CONSISTENCY, RELIABILITY, AND SCHEDULE. THE PHASE I EFFORT DEMONSTRATES FEASIBILITY OF A LOW COST ARRAY USING AN AUTOMATED AND INTEGRATED MANUFACTURING APPROACH, PERFORMED ON AN AUTOMATION FRIENDLY SOLAR CELL, VERIFIED WITH ENVIRONMENTAL TESTING, AND IS USED TO PREDICT ARRAY COST FOR A HIGH POWER MISSION. MEETING THESE TECHNICAL OBJECTIVES WILL DEMONSTRATE REDUCED COST AND JUSTIFY A PHASE II SBIR PROGRAM PREPARING FOR A FLIGHT EXPERIMENT.
contract · Last action 2013-05-23
$124,311
National Aeronautics and Space Administration
IGF::OT::IGF HIGH POWER SOLAR ARRAYS WITH CAPABILITIES OF>100KW ARE NEEDED FOR PROJECTED NASA MISSIONS. PHOTOVOLTAIC ARRAYS USING DEPLOYABLE MEMBRANES WITH THIN CELLS HAVE TRENDED TO HIGHER EFFICIENCY CELLS TO MINIMIZE DEPLOYED AREA AND DEPLOYMENT STRUCTURE MASS AND COMPLEXITY, HOWEVER, THE COST OF HIGH EFFICIENCY CELLS MAKE THESE ARRAYS PROHIBITIVELY EXPENSIVE. AMORPHOUS CELLS THAT ARE IN PRODUCTION FOR TERRESTRIAL APPLICATION HAVE $/WATT COST LESS THAN 10% OF SPACE CELLS, AT ABOUT THE HALF THE EFFICIENCY. THIS SBIR DEVELOPS THE PHOTOVOLTAIC ASSEMBLY WITH RECONFIGURABLE ARRAY STRUCTURE - PARASOL - A CENTRIPETAL FORCE DEPLOYMENT AND TENSIONING APPROACH THAT ENABLES AFFORDABILITY OF MULTI-100KW ARRAYS WITH COMMERCIALLY AVAILABLE THIN FILM CIGS CELLS, WHICH CAN BE ADAPTED FOR SPACE ENVIRONMENT COMPATIBILITY. PARASOL IMPLEMENTS CIGS CELL MODULES USING VANGUARD'S THINS SOLAR CELL ENCAPSULATION TECHNOLOGY TO ACHIEVE HIGH MASS AND STOWED VOLUME METRICS (>500W/KG,>200KW/M3), AND MOUNT THE CIGS-THINS MODULES ONTO A MEMBRANE SOLAR ARRAY (MSA) THAT CAN BE ROLLED AND FOLDED INTO A COMPACT ENVELOPE AND DEPLOYED WITHOUT CUMBERSOME EXTERNAL DEPLOYMENT STRUCTURE. IN PHASE I WE WILL DEVELOP THE DESIGN AND STRUCTURAL ANALYSIS OF A 250KW PARASOL MSA, SELECTING FROM FLOWER-, UMBRELLA-, OR ORIGAMI-LIKE DEPLOYMENTS, AND EVALUATE FIGURES OF MERIT FOR THE ARRAY WHEN IMPLEMENTED WITH A COMBINATION OF CENTRIPETAL FORCE AND ELASTIC OR SHAPE-MEMORY INTEGRAL RIBS TO DEPLOY AND TENSION THE ARRAY. WE WILL EVALUATE THE ALTERNATIVE GORE SIZES AND SHAPES TO DETERMINE THE MAXIMUM PV PACKING FACTOR WE CAN ACHIEVE. WE WILL DEVELOP A PLAN FOR SCALING UP THE TECHNOLOGY AND QUALIFYING FOR SPACE, ADDRESSING THE KEY CHALLENGE OF DEMONSTRATING AND CHARACTERIZING SUCH A LARGE ARRAY IN GROUND-TEST WITH GRAVITY OFF-LOADER. THE PHASE I COMPLETES WITH A SUBSCALE DEMONSTRATION USING A SCALABLE VERSION OF THE TEST FIXTURE, LEADING TO A PLAN FORWARD TOWARDS FLIGHT EXPERIMENT IN PHASE II.
contract · Last action 2014-11-25
$124,309
National Aeronautics and Space Administration
INVERTED METAMORPHIC (IMM) SOLAR CELLS HAVE ACHIEVED HIGH EFFICIENCY AT VERY LOW MASS, BUT INTEGRATION OF THE THIN CRYSTALLINE PHOTOVOLTAIC DEVICE INTO A FLEXIBLE PANEL HAS BEEN A CHALLENGE. THE OBJECTIVES OF THIS SBIR ARE TO MECHANICALLY PACKAGE THE IMM CELL INTO A FLEXIBLE LAMINATED PANEL, AND TO ASSEMBLE MODULAR BUILDING BLOCKS OF THESE PANELS INTO A DEPLOYABLE ARRAY STRUCTURE. THE THIN MODULE DEVELOPMENT INCLUDES OPTIMIZING MULTIFUNCTIONAL MATERIALS FOR THE SUBSTRATE AND SUPERSTRATE TO PROVIDE APPROPRIATE STRUCTURAL SUPPORT AS WELL AS PROPERTIES FOR INSULATION, TRANSPARENCY, SURFACE CONDUCTIVITY, EMISSIVITY AND ENVIRONMENTAL DURABILITY. THE LAMINATED IMM PANELS BUILD ON ELECTRICAL INTERCONNECTION DEVELOPMENT FROM PARALLEL PROGRAMS TO ASSEMBLE BODY-MOUNTED OR DEPLOYABLE ARRAYS USING A MODULAR CONCEPT. THE EMPHASIS ON MODULARITY AND LAMINATION OBJECTIVES WILL PROVIDE ENHANCED CONSISTENCY, QUALIFICATION TRACEABILITY, AND MANUFACTURING TECHNOLOGY THAT IS AMENABLE TO PROCESS CONTROL AND LOWERED COST. IN THE PHASE 1 EFFORT SELECTS THE OPTIMIZED MATERIAL FOR EACH LAYER OF THE SUBSTRATE AND SUPERSTRATE, VALIDATES THE MATERIALS' PREDICTED PERFORMANCE, LAMINATES IMM COUPONS AND SUBMODULES, AND TESTS THEM IN BASIC ENVIRONMENTS, SUCH AS THERMAL CYCLING AND BEND RADIUS. PHASE 1 ALSO PERFORMS THE CONCEPTUAL DESIGN OF THE ROLL-OUT ARRAY USING STATE-OF-THE-ART DEPLOYABLE ARRAY STRUCTURE SUCH AS THOSE FROM THE SELECTED PHASE 1 SUBCONTRACTOR, DEPLOYABLE SPACE SYSTEMS OF GOLETA, CA. THE PHASE 2 EFFORT WILL PERFORM A FULL-SCALE ARRAY DESIGN, INCLUDING DEPLOYABLE STRUCTURE, AND BUILD A DEPLOYABLE ENGINEERING GROUND DEMONSTRATION MODEL, INCLUDING FLIGHT QUALIFIABLE MATERIALS AND SOME ACTIVE IMM THIN MODULES. PHASE 2 ALSO INCLUDES A SET OF GROUND VERIFICATION TESTING ON COUPONS, SUBMODULES AND MODULES TO SHOW DURABILITY IN OTHER HARSH SPACE ENVIRONMENTS, SUCH AS VUV, PROTONS, PLASMA, ATOMIC OXYGEN, AND LIFE THERMAL CYCLING.
contract · Last action 2011-09-14
$100,000
Department of Defense
SBIR I
contract · Last action 2010-05-04
$100,000
Department of Defense
DR TECH SBIR I
contract · Last action 2009-03-02
$100,000
National Aeronautics and Space Administration
AFFORDABLE, PRECISION REFLECTOR MOLD TECHNOLOGY (PDRT08-029) ADVANCES IN REPLICATION MOLD TECHNOLOGY THAT REDUCE MATERIAL COSTS, GRINDING TIME, AND POLISHING TIME WOULD ENABLE FABRICATION OF LARGE, PRECISION MOLDS AND POSSIBLY OPTICS AT 50-75% LOWER COST. MOLD COST SAVINGS COULD BE APPLIED TO OTHER ASPECTS OF A TELESCOPE MISSION'S TECHNOLOGY DEVELOPMENT AND DEMONSTRATION EFFORTS TO REDUCE LARGE APERTURE FAR INFRARED TELESCOPE AREAL DENSITY AND IMPROVE OPTICAL TECHNICAL PERFORMANCE.
contract · Last action 2009-01-20
$100,000
Department of Defense
RESEARCH AND DEVELOPMENT IN THE PHYSICAL, ENGINEERING, AND LIFE SCIENCES (EXCEPT BIOTECHNOLOGY)
contract · Last action 2010-12-20
$99,999
National Aeronautics and Space Administration
THIS SBIR PROGRAM WILL IDENTIFY AND ADDRESS THE PRIMARY TECHNICAL ISSUES THAT LIMIT THE CURRENT PRECISION OF REPLICATED CFRP OPTICS. THESE ISSUES MUST BE RESOLVED TO BRING THIS CAPABILITY TO THE SUB-MICRON RANGE OF PRECISION REQUIRED BY THE NEXT GENERATION OF FLIGHT AND GROUND SUBMILLIMETER AND FAR INFRARED PROJECTS. WERE THESE ISSUES RESOLVED, THIS CAPABILITY WOULD PROVIDE REDUCED COST AND RISK AND IMPROVED AREAL DENSITY, THERMAL STABILITY, AND STIFFNESS TO THE LARGE SUB-MICRON OPTICS REQUIRED BY THE NEXT GENERATION OF FLIGHT AND GROUND SUBMILLIMETER AND FAR INFRARED PROJECTS.
contract · Last action 2009-01-13
$99,999
Department of Defense
ARMY SBIR PHASE I
contract · Last action 2008-12-04
$70,000
Department of Defense
INTERIOR DESIGN SERVICES
contract · Last action 2010-06-22
$70,000
Department of Defense
ARMY SBIR PH I OPTIO
contract · Last action 2010-02-24
$40,000
National Aeronautics and Space Administration
IGF::OT::IGF THE SHIELDS 1 CUBESAT MISSIONS ARE SPONSORED NASA LANGLEY RESEARCH CENTER, RESEARCH DIRECTORATE, ADVANCED MATERIALS AND PROCESSING BRANCH TECHNOLOGY DEVELOPMENT EFFORTS TO INCREASE THE TECHNOLOGY READINESS LEVELS TRL OF RADIATION SHIELDING, CHARGE DISSIPATION COATINGS, AND ELECTRONICS THROUGH SPACEFLIGHT HERITAGE. THE RECIPIENTS ELECTROSTATIC DISCHARGE ESD CLEAN SOLAR PANELS ESDCPS WILL POWER THESE TWO PLANNED MISSIONS FOR POLAR LOW EARTH ORBIT LEO FOURTH QUARTER FISCAL 2015 OR 1ST QUARTER FISCAL 2016 AND GEOTRANSFER ORBIT GTO LATE FISCAL 2016 2017.
contract · Last action 2016-09-07
$26,500
National Aeronautics and Space Administration
IGF::CL::IGF SMALL BUSINESS SET-ASIDE, 60 OFFERS 52.223-15 FABRICATION OF COMMERCIAL SERVICES AND SUPPLIES FOR GODDARD SPACE FLIGHT CENTER II THE ADVANCED MANUFACTURING BRANCH (AMB) IS RESPONSIBLE FOR MAINTAINING A COMPLETE MANUFACTURING FACILITY TO MEET THE CENTER'S RESEARCH AND DEVELOPMENT REQUIREMENTS AND ASSIST IN THE FABRICATION OF HARDWARE REQUIREMENTS FROM MULTIPLE NASA PROJECT MISSIONS. THIS FACILITY INCLUDES CONVENTIONAL MACHINING EQUIPMENT, NUMERICALLY CONTROLLED (NC) MACHINING CENTERS, SHEET METAL AND WELDING FABRICATION EQUIPMENT AND REMOTELY LOCATED STAFF SHOPS. VENDORS SHALL PROVIDE FABRICATION SERVICES AND SUPPLIES TO THE MANUFACTURING ENGINEERING GROUP IN THEIR RESPECTIVE AREAS OF EXPERTISE FOR THE DEVELOPMENT OF INSTRUMENTS AND SPACE FLIGHT AND NON-SPACEFLIGHT HARDWARE INTERCHANGEABLE PIECE PARTS. VENDORS WILL MANUFACTURE PER ENGINEERING DRAWINGS WITH AEROSPACE INDUSTRY TOLERANCES AND PROVIDE FABRICATION CAPABILITIES IN ACCORDANCE WITH THE STATEMENT OF WORK. TO FABRICATE CLOSE TOLERANCE AEROSPACE INSTRUMENTS AND SPACE FLIGHT GRADE PARTS, IN VARIOUS MATERIALS SUCH AS (BUT NOT LIMITED TO) ALUMINUM, TITANIUM, HIGH STRENGTH STEEL AND NICKEL ALLOY, ENGINEERING PLASTICS, AND COMPOSITES BASED ON INDUSTRY ENGINEERING DRAWINGS, PROVIDED IN ELECTRONIC FORMAT, TO INDUSTRY STANDARD TOLERANCES AND SPECIFICATIONS. PARTS MAY RANGE IN COMPLEXITY FROM VERY SIMPLE TO VERY COMPLEX, WITH QUANTITIES. EACH DISCIPLINE IS FURTHER DIVIDED INTO SUBCATEGORIES BASED ON THE EXPECTED SIZE OF FABRICATED PARTS. THE FABRICATIONS OF PRODUCTS OR SERVICES PROPOSED AS "SPACEFLIGHT" ARE REQUIRED TO BE, ISO 900I OR AS9100 COMPLAINT, ITEMS PROPOSED AS "NON-FLIGHT" WILL NOT REQUIRE RESPONDENTS TO BE ISO 9001 OR AS9100 COMPLIANT. OFFERS SHALL INDICATE IF THEY ARE ISO 9001 OR AS9100 COMPLAINT AND PROVIDE SUPPORTING DOCUMENTATION.
contract · Last action 2014-08-21
$0
National Aeronautics and Space Administration
IGF::OT::IGF SMALL BUSINESS SET-ASIDE, 63 OFFERS PLACE OF PERFORMANCE: VENDOR SITE FABRICATION OF COMMERCIAL SERVICES AND SUPPLIES FOR GODDARD SPACE FLIGHT CENTER THE ADVANCED MANUFACTURING BRANCH (AMB) IS RESPONSIBLE FOR MAINTAINING A COMPLETE MANUFACTURING FACILITY TO MEET THE CENTER'S RESEARCH AND DEVELOPMENT REQUIREMENTS AND ASSIST IN THE FABRICATION OF HARDWARE REQUIREMENTS FROM MULTIPLE NASA PROJECT MISSIONS. THIS FACILITY INCLUDES CONVENTIONAL MACHINING EQUIPMENT, NUMERICALLY CONTROLLED (NC) MACHINING CENTERS, SHEET METAL AND WELDING FABRICATION EQUIPMENT AND REMOTELY LOCATED STAFF SHOPS. VENDORS SHALL PROVIDE FABRICATION SERVICES AND SUPPLIES TO THE MANUFACTURING ENGINEERING GROUP IN THEIR RESPECTIVE AREAS OF EXPERTISE FOR THE DEVELOPMENT OF INSTRUMENTS AND SPACE FLIGHT AND NON-SPACEFLIGHT HARDWARE INTERCHANGEABLE PIECE PARTS. VENDORS WILL MANUFACTURE PER ENGINEERING DRAWINGS WITH AEROSPACE INDUSTRY TOLERANCES AND PROVIDE FABRICATION CAPABILITIES IN ACCORDANCE WITH THE STATEMENT OF WORK. TO FABRICATE CLOSE TOLERANCE AEROSPACE INSTRUMENTS AND SPACE FLIGHT GRADE PARTS, IN VARIOUS MATERIALS SUCH AS (BUT NOT LIMITED TO) ALUMINUM, TITANIUM, HIGH STRENGTH STEEL AND NICKEL ALLOY, ENGINEERING PLASTICS, AND COMPOSITES BASED ON INDUSTRY ENGINEERING DRAWINGS, PROVIDED IN ELECTRONIC FORMAT, TO INDUSTRY STANDARD TOLERANCES AND SPECIFICATIONS. PARTS MAY RANGE IN COMPLEXITY FROM VERY SIMPLE TO VERY COMPLEX, WITH QUANTITIES. EACH DISCIPLINE IS FURTHER DIVIDED INTO SUBCATEGORIES BASED ON THE EXPECTED SIZE OF FABRICATED PARTS. THE FABRICATIONS OF PRODUCTS OR SERVICES PROPOSED AS "SPACEFLIGHT" ARE REQUIRED TO BE, ISO 900I OR AS9100 COMPLAINT, ITEMS PROPOSED AS "NON-FLIGHT" WILL NOT REQUIRE RESPONDENTS TO BE ISO 9001 OR AS9100 COMPLIANT. OFFERS SHALL INDICATE IF THEY ARE ISO 9001 OR AS9100 COMPLAINT AND PROVIDE SUPPORTING DOCUMENTATION.
contract · Last action 2018-05-23
$0
Department of Defense
INNOVATIVE COMPOSITE STRUCTURAL CONCEPTS FOR DEEP-WINGED LARGE TRANSPORTS (PVSC08-068)
contract · Last action 2018-02-27
$0
Department of Defense
SBIR PHASE III
contract · Last action 2018-02-27
$0
Department of Defense
SBIR PHASE III -TASK ORDER 0004
contract · Last action 2017-11-07
$0
Department of Defense
200411!000671!5700!GS05 !DET 8 AFRL/PK (SUPPORTS VS) !FA945304C0021 !A!N! !Y! ! !20040729!20061010!928223494!928223494!838266369!N!VANGUARD COMPOSITES GROUP INC !5550 OBERLIN DRIVE, SUITE !SAN DIEGO !CA!92121!66000!073!06!SAN DIEGO !SAN DIEGO !CALIFORNIA!+000000375000!N!N!000000743249!AC25!RDTE/MISSILE AND SPACE SYSTEMS-ENG/MANUF DEVEL !A2 !MISSILE AND SPACE SYSTEMS !CAA !MDA SUPPORT !541710!E! !3! ! ! ! ! !99990909!B! ! !B! !A!N!U!2!003!K! !Z!Y!Z! ! !N!B!N!N! ! !Z! !B!A!00 !C!B!N! ! ! ! ! ! !0001! !
contract · Last action 2016-01-16
$0
Department of Defense
200412!000824!5700!GS05 !DET 8 AFRL/PK (SUPPORTS VS) !FA945304C0313 !A!N! !Y! ! !20040915!20061211!928223494!928223494!838266369!N!VANGUARD COMPOSITES GROUP INC !5550 OBERLIN DRIVE, SUITE !SAN DIEGO !CA!92121!66000!073!06!SAN DIEGO !SAN DIEGO !CALIFORNIA!+000000748496!N!N!000000748496!AC25!RDTE/MISSILE AND SPACE SYSTEMS-ENG/MANUF DEVEL !A2 !MISSILE AND SPACE SYSTEMS !CAA !MDA SUPPORT !541710!E! !3! ! ! ! ! !99990909!B! ! !B! !A!N!U!2!014!K! !Z!Y!Z! ! !N!B!N!N! ! !Z! !B!A!00 !C!B!N! ! ! ! ! ! !0001! !
contract · Last action 2016-01-16
$0
Department of Defense
SBIR PHASE II
contract · Last action 2015-12-24
$0
Department of Defense
200412!002495!2100!W9113M!USA SPACE AND STRATEGIC DEF CDR !W9113M04C0068 !A!N! !N! ! !20040902!20050301!928223494!928223494!838266369!N!VANGUARD COMPOSITES GROUP INC !5550 OBERLIN DRIVE, SUITE !SAN DIEGO !CA!92121!21082!073!06!EAST SAN DIEGO !SAN DIEGO !CALIFORNIA!+000000045000!N!N!000000000000!AC23!RDTE/MISSILE AND SPACE SYSTEMS-ADV TECH DEV !A2 !MISSILE AND SPACE SYSTEMS !CAA !MDA SUPPORT !541710!E! !3! ! ! ! ! !99990909!B! ! !A! !A!U!J!2!002!K! !Z!N!Z! ! !N!B!N!N! ! !A! !B!A!00 !D!B!N! ! ! ! ! ! !0001! !
contract · Last action 2015-12-24
$0
Department of Defense
SBIR PHASE III (TASK ORDER 0003)
contract · Last action 2020-10-20
$-288,609

Federal contract dollars to this establishment. Primary NAICS: 541712 - RESEARCH AND DEVELOPMENT IN THE PHYSICAL, ENGINEERING, AND LIFE SCIENCES (EXCEPT BIOTECHNOLOGY). Last action: 2021-10-07. Source: USAspending.gov, net obligations. Recipient address is the SAM registration / HQ address, not necessarily the worksite.

Inspection history

Date	Trigger	Violations	Serious	Penalty
2012-12-11	Complaint	3	—	$1,120

Source: OSHA IMIS. Citation amounts reflect initially assessed penalties; final amounts after appeal may differ.

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