What is ROLLSROYCE HIGH TEMPERATURE COMPOSITES's OSHA violation history?

Establishment profile

ROLLSROYCE HIGH TEMPERATURE COMPOSITES

CA, 92648

OSHA inspections

Violations

Penalties

Context

No OSHA inspections on record. This does not mean the employer is violation-free — OSHA inspects a small fraction of workplaces annually.

Summary

ROLLSROYCE HIGH TEMPERATURE COMPOSITES has no OSHA inspection history on file. Federal records covering wage, environmental, labor relations, and other agencies are noted below where present.

The most recent federal enforcement activity was recorded 0 days ago.

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

Agency coverage

ROLLSROYCE HIGH TEMPERATURE COMPOSITES appears in UVA Corporate Prosecution Registry record only. No matching records were found in OSHA workplace safety, WHD wage enforcement, MSHA mine safety, EPA environmental compliance, NLRB labor relations, OFLC visa and labor certification, FMCSA motor carrier registration, SAM.gov federal debarment, CMS nursing home enforcement, CPSC product recalls, or NHTSA vehicle recalls. Single-agency enforcement records typically indicate either a discrete incident-based inspection or a low-risk operational profile.

OSHA workplace safety

No OSHA inspections, citations, or accidents on file for ROLLSROYCE HIGH TEMPERATURE COMPOSITES. Verify directly with Occupational Safety and Health Administration →

Safety self-report (OSHA 300A)

No self-reported injury rates filed with OSHA's Injury Tracking Application for ROLLSROYCE HIGH TEMPERATURE COMPOSITES. Verify directly with OSHA Injury Tracking Application →

OSHA severe injury reports

No severe injury reports (hospitalization, amputation, or loss of an eye) on file under 29 CFR 1904.39 for ROLLSROYCE HIGH TEMPERATURE COMPOSITES. Verify directly with Occupational Safety and Health Administration →

Activity timeline

Data refreshed

Weekly

First OSHA inspection

—

Most recent activity

0 days ago

Most recent federal enforcement activity recorded 0 days ago. Data on this page is refreshed weekly.

Wage & Hour Division (WHD)

No WHD wage, overtime, or child-labor enforcement cases on file for ROLLSROYCE HIGH TEMPERATURE COMPOSITES. Verify directly with Wage and Hour Division →

Mine safety (MSHA)

No MSHA mine safety violations on file for ROLLSROYCE HIGH TEMPERATURE COMPOSITES. Verify directly with Mine Safety and Health Administration →

Labor relations (NLRB)

No NLRB unfair labor practice charges or union representation cases on file for ROLLSROYCE HIGH TEMPERATURE COMPOSITES. 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 ROLLSROYCE HIGH TEMPERATURE COMPOSITES. Verify directly with Office of Foreign Labor Certification →

Environmental compliance (EPA)

No EPA inspections or formal enforcement actions on file for ROLLSROYCE HIGH TEMPERATURE COMPOSITES. Verify directly with Environmental Protection Agency →

Federal criminal prosecution record

Prosecutions

Total payments

$169.9M

Disposition

Crime type

FCPA

First case: 2017-01-17. Most recent: 2017-01-17. Source: UVA Corporate Prosecution Registry — federal pleas, DPAs, and NPAs.

Federal contracts

This location

Obligated (5-yr)

Obligated (all-time)

$6.9M

Awards

Top agency

National Aeronautics and Space Administration

$4.0M

Top agencies by obligation (this location)

National Aeronautics and Space Administration$4.0M

Department of Defense$2.9M

Largest awards

Department of Defense
SBIR PHASE II RESEARCH AND DEVELOPMENT.
contract · Last action 2016-05-05
$970,956
Department of Defense
CERAMIC MATRIX COMPOSITE LOW PRESSURE TURBINE BLADE DEVLPMNT
contract · Last action 2017-02-27
$701,609
National Aeronautics and Space Administration
ADVANCED LIQUID ROCKET PROPULSION SYSTEMS MUST ACHIEVE LONGER BURN TIMES WITHOUT PERFORMANCE DEGRADATION TO ALLOW THE LOWEST COST PER KILOGRAM ACCESS TO SPACE. ABLATIVE THRUST CHAMBERS HAVE AN EXTENSIVE HERITAGE AND ARE THE LOW COST APPROACH TO FABRICATING ROCKET THRUST CHAMBERS. HOWEVER, COMPOSITE ABLATIVE CHAMBERS ARE HEAVY AND SUFFER FROM EROSION THAT TYPICALLY LIMITS PERFORMANCE OF THE ENGINE IN TERMS OF BURN TIME AND EFFICIENCY/PERFORMANCE OF THE COMBUSTION. IN THE LAST DECADE, THERE HAS BEEN SIGNIFICANT INTEREST IN UTILIZING FIBER-REINFORCED CERAMIC COMPOSITES SUCH AS CARBON FIBER-REINFORCED SILICON CARBIDE (C/SIC) COMPOSITES. SUCH COMPOSITES HAVE DEMONSTRATED A LOW EROSION RATE IN BI-PROPELLANT LIQUID ROCKET THRUST CHAMBERS AT TEMPERATURES APPROACHING 4000F. HOWEVER INSERTION OF THESE MATERIALS HAVE BEEN LIMITED BY COMPLEXITIES ASSOCIATED WITH REQUIRED SYSTEM REDESIGN TO ACCOMMODATE A RADIATIVELY-COOLED CHAMBER AND UNPROVEN ATTACHMENT METHODS. BY INCORPORATING A CERAMIC COMPOSITE LINER WITHIN AN ABLATIVE THRUST CHAMBER IN CRITICAL AREAS THAT ARE SUBJECTED TO THE HIGHEST TEMPERATURES, A LOW EROSION, HIGH PERFORMANCE CHAMBER IS OBTAINED THAT ELIMINATES COSTS AND COMPLEXITIES THAT HAVE LIMITED THE INSERTION OF CERAMIC COMPOSITE THRUST CHAMBERS. THE PHASE II WILL BUILD ON THE SUCCESSFUL STATIC HOT FIRE TEST OF SUCH A THRUST CHAMBER THAT DEMONSTRATED MINIMAL EROSION TO DEMONSTRATE WEIGHT SAVINGS AND A REDUCTION IN FILM COOLING WITH RESPECT TO A COMPARABLE ABLATIVE ENGINE.
contract · Last action 2012-06-13
$600,000
National Aeronautics and Space Administration
CERAMIC COMPOSITE MECHANICAL FASTENER SYSTEM FOR HIGH-TEMPERATURE STRUCTURAL ASSEMBLIES
contract · Last action 2010-01-13
$598,566
National Aeronautics and Space Administration
DURABLE HIGH TEMPERATURE MATERIALS ARE REQUIRED FOR REUSABLE HYPERSONIC STRUCTURAL THERMAL PROTECTION SYSTEMS. IN PARTICULAR, TEMPERATURES EXCEEDING 2700 F, AND APPROACHING 3000 F, ARE TARGETED FOR CAPABLE STRUCTURAL MATERIALS THAT CAN SURVIVE STRESSES ON THE ORDER OF 10 KSI (70 MPA) FOR AT LEAST 100 HOURS IN AN OXIDIZING ENVIRONMENT. SUCH MATERIALS HAVE BEEN IDENTIFIED AS AN ENABLING MATERIAL FOR FUTURE HYPERSONIC VEHICLES AS THIS APPLICATION IS STRUCTURAL, A STRONG DEGREE OF DAMAGE TOLERANCE IS DESIRED, AND THUS CERAMIC MATRIX COMPOSITES ARE THE PRIMARY CHOICE DUE TO THE DESIRE FOR REDUCED WEIGHT, HIGH TEMPERATURE STRENGTH AND OXIDATION RESISTANCE. SILICON CARBIDE FIBER-REINFORCED SILICON CARBIDE MATRIX (SIC/SIC) COMPOSITES ARE BELIEVED TO BE THE MOST SUITABLE SOLUTION DUE TO MEETING THE REQUIREMENTS WITH THE LIMITATIONS OF CREEP AT THE HIGHEST TEMPERATURES/LOADS, AND OXIDATIVE ATTACK AT STRESSES THAT EXCEED THE MATERIALS PROPORTIONAL LIMIT. THE PROPOSED EFFORT WILL DEFINE THE TEMPERATURE-STRESS LIMIT OF SIC/SIC COMPOSITES, AND EXAMINE METHODS TO FURTHER EXTEND THIS LIMIT.
contract · Last action 2014-02-24
$591,631
Department of Defense
RESEARCH AND DEVELOPMENT SBIR TOPIC N08-154 PHASE II
contract · Last action 2017-02-27
$506,852
National Aeronautics and Space Administration
SIC/SIC COMPOSITE VANES AND PANELS
contract · Last action 2011-03-07
$331,005
National Aeronautics and Space Administration
SILICON CARBON AND GRAPHITE PRODUCTS - IT IS THE GOAL OF NASA S ENVIRONMENTALLY RESPONSIBLE AVIATION PROGRAM (ERA) TO CONTINUE WORK ON THE HIGH PRESSURE TURBINE VANE APPLICATION WITH SIC/SIC COMPOSITES PRODUCED BY THE COMBINED METHODS OF CVI AND SMI. THESE PARTICULAR PROCESSING METHODS YIELD COMPOSITES WITH THE REQUIRED FIBER VOLUME, CREEP RESISTANCE AND HIGH TEMPERATURE STRENGTH NEEDED FOR A HIGH PRESSURE TURBINE VANE APPLICATION.
contract · Last action 2014-03-17
$326,179
Department of Defense
CERAMIC MATRIX COMPOSITE TEST SPECIMENS
contract · Last action 2011-06-03
$242,995
National Aeronautics and Space Administration
THE PRIMARY GOAL OF THIS PROJECT IS FOR THE DESIGN AND DEVELOPMENT OF A CERAMIC MATRIX COMPOSITE HEAT EXCHANGER DESIGN TECHNOLOGY THAT COULD BE UTILIZED FOR ARMD HYPERSONIC PROPULSION SYSTEM EFFORTS PERTAINING TO HIGHLY RELIABLE REUSABLE LAUNCH SYSTEMS (HRRLS). NASA S FUNDAMENTAL AERONAUTICS HYPERSONIC MATERIALS AND STRUCTURES (HYP M&S) DISCIPLINE IS WORKING TO DEVELOP MATERIAL SYSTEMS THAT CAN OPERATE AS THE ENGINE STRUCTURE OF HYPERSONIC PROPULSION CONCEPTS. ONE CANDIDATE METHOD FOR THE SIDE WALLS OF A HYPERSONIC PROPULSION SYSTEM IS TO UTILIZE CERAMIC MATRIX COMPOSITE (CMC) HEAT EXCHANGERS WHICH FORCES HIGH-PRESSURE COOLANT THROUGH COMPOSITE TUBES EMBEDDED IN THE WALLS OF A HIGH-TEMPERATURE COMPOSITE TO MAINTAIN THE WALL TEMPERATURE WITHIN ACCEPTABLE TEMPERATURE LIMITS. THE FOCUS OF THIS EFFORT IS TO DESIGN, MANUFACTURE, AND TEST SEVERAL CANDIDATE CMC HEAT EXCHANGER CONCEPTS TO PROVIDE THE FOUNDATIONAL UNDERSTANDING OF AN ALL CMC HEAT EXCHANGER TO SUPPORT POTENTIAL FUTURE LARGE-SCALE HYPERSONIC PROPULSION DEVELOPMENT EFFORTS. THE SUPPLIER WILL CONSTRUCT SEVERAL ADVANCED CERAMIC COMPOSITE HEAT EXCHANGER TEST PANELS THAT ARE CAPABLE OF MEETING THE REQUIREMENTS OF THE FUNDAMENTAL AERONAUTICS HYPERSONICS PROGRAM. THE HEAT EXCHANGER PANELS CONSIST OF AN ARRAY OF UNIFORMLY DISTRIBUTED COMPOSITE TUBES THAT WILL CARRY COOLANT THAT WILL COOL THE MATERIAL WHEN EXPOSED TO THE THERMAL ENVIRONMENT OF HYPERSONIC PROPULSION. EACH OF THE HEAT EXCHANGER PANELS WILL EXAMINE DIFFERENT TUBE AND MATERIAL COMBINATIONS.
contract · Last action 2010-09-30
$238,542
National Aeronautics and Space Administration
NRA AWARD FOR "DEVELOPMENT OF VALIDATED ANALYTIC MODELS PREDICTING EFFECTS OF DEFECTS ON CERAMIC MATRIX COMPOSITE MATERIAL BEHAVIOR" WITH HYPER-THERM HIGH-TEMPERATURE COMPOSITES
contract · Last action 2009-02-17
$179,487
Department of Defense
SBIR P1
contract · Last action 2009-08-05
$149,981
National Aeronautics and Space Administration
IGF::OT::IGF PARTIALLY RIGIDIZED SIC/SIC COMPOSITE SUPPLIED PANELS
contract · Last action 2015-07-09
$129,047
Department of Defense
HIGH-TEMPERATURE, FULL-FIELD STRAIN MAPPING FO CERAMIC MATIRX COMPOSITES FOR AERO-ENGINE COMPONENTS
contract · Last action 2010-04-26
$100,000
National Aeronautics and Space Administration
DURABLE HIGH TEMPERATURE MATERIALS ARE REQUIRED FOR HYPERSONIC ENGINE AND STRUCTURAL THERMAL PROTECTION SYSTEMS. IN PARTICULAR, 2700 F OR GREATER CAPABLE STRUCTURAL MATERIALS THAT CAN SURVIVE STRESSES ON THE ORDER OF 10 KSI (70 MPA) FOR AT LEAST 100 HOURS IN AN OXIDIZING ENVIRONMENT HAVE BEEN IDENTIFIED AS AN ENABLING MATERIAL FOR FUTURE HYPERSONIC VEHICLES WITH A LONG TERM DESIRED TARGET OF 3000 F. AS THESE APPLICATIONS ARE STRUCTURAL, A STRONG DEGREE OF DAMAGE TOLERANCE IS DESIRED, AND THUS CERAMIC MATRIX COMPOSITES ARE THE PRIMARY CHOICE DUE TO THE DESIRE FOR REDUCED WEIGHT, HIGH TEMPERATURE STRENGTH AND OXIDATION RESISTANCE. SILICON CARBIDE FIBER-REINFORCED SILICON CARBIDE MATRIX (SIC/SIC) COMPOSITES ARE BELIEVED TO BE THE MOST SUITABLE SOLUTION DUE TO MEETING THE REQUIREMENTS WITH THE EXCEPTION OF CREEP AT THE HIGHEST TEMPERATURES/LOADS. THE PROPOSED EFFORT WILL MODIFY THE SIC FIBER PREFORM BY THE ADDITION OF A FRACTION OF MORE CREEP RESISTANT CARBON FIBERS. THE PHASE I WILL ENCOMPASS ENGINEERING THE APPROPRIATE LEVEL OF HYBRIDIZATION IN A C-SIC/SIC COMPOSITE, PRODUCING AND EVALUATING THE CERAMIC COMPOSITE MATERIAL FOR HYPERSONIC VEHICLE APPLICATIONS, INCLUDING STRESS RUPTURE AT TEMPERATURES OF 2700 F OR GREATER.
contract · Last action 2010-01-27
$100,000
Department of Defense
CERAMIC MATRIX COMPOSITE (CMC) LOW PRESSURE TURBINE (LPT) BLADE DEVELOPMENT
contract · Last action 2009-03-24
$100,000
National Aeronautics and Space Administration
ADVANCED LIQUID ROCKET PROPULSION SYSTEMS MUST ACHIEVE LONGER BURN TIMES WITHOUT PERFORMANCE DEGRADATION TO ALLOW THE LOWEST COST PER KILOGRAM ACCESS TO SPACE. ABLATIVE THRUST CHAMBERS HAVE AN EXTENSIVE HERITAGE AND ARE THE LOW COST APPROACH TO FABRICATING ROCKET THRUST CHAMBERS. HOWEVER COMPOSITE ABLATIVE CHAMBERS SUFFER FROM EROSION THAT TYPICALLY LIMITS PERFORMANCE OF THE ENGINE IN TERMS OF BURN TIME AND EFFICIENCY/PERFORMANCE OF THE COMBUSTION. IN THE LAST DECADE THERE HAS BEEN SIGNIFICANT INTEREST IN UTILIZING FIBER-REINFORCED CERAMIC COMPOSITES SUCH AS CARBON FIBER-REINFORCED SILICON CARBIDE (C/SIC) COMPOSITES. SUCH COMPOSITES HAVE DEMONSTRATED A LOW EROSION RATE IN BI-PROPELLANT LIQUID ROCKET THRUST CHAMBERS AT TEMPERATURES APPROACHING 4000F. HOWEVER INSERTION OF THESE MATERIALS HAVE BEEN LIMITED BY COMPLEXITIES ASSOCIATED WITH REQUIRED SYSTEM REDESIGN TO ACCOMMODATE A RADIATIVELY-COOLED CHAMBER ATTACHMENT METHODS AND ADDRESSING CHAMBER PERMEABILITY ISSUES. BY INCORPORATING A CERAMIC COMPOSITE LINER WITHIN AN ABLATIVE THRUST CHAMBER IN CRITICAL AREAS THAT ARE SUBJECTED TO THE HIGHEST TEMPERATURES A LOW EROSION HIGH PERFORMANCE CHAMBER IS OBTAINED THAT ELIMINATES COSTS AND COMPLEXITIES THAT HAVE LIMITED THE INSERTION OF CERAMIC COMPOSITE THRUST CHAMBERS. THE PHASE I EFFORT WILL PRODUCE A CERAMIC COMPOSITE LINED ABLATIVE THRUST CHAMBER IDENTIFY THE DEGREE OF FILM COOLING REQUIRED AND CONDUCT A STATIC HOT FIRE TEST EVALUATION OF THE MATERIAL TO DEMONSTRATE THE PERFROMANCE BENEFIT OF A CMC LINER WITHIN AN ABLATIVE THRUST CHAMBER.
contract · Last action 2008-03-04
$100,000
National Aeronautics and Space Administration
DURABLE, HIGH THERMAL CONDUCTIVITY MELT INFILTRATED CERAMIC COMPOSITES FOR TURBINE ENGINE APPLICATIONS
contract · Last action 2008-02-27
$100,000
Department of Defense
CONTRACT SUMMARY REPORT.
contract · Last action 2008-02-13
$100,000
National Aeronautics and Space Administration
DURABLE HIGH TEMPERATURE MATERIALS ARE REQUIRED FOR STRUCTURAL THERMAL PROTECTION SYSTEMS (TPS) THAT EXHIBIT A STRUCTURAL LOAD CARRYING CAPABILITY AT TEMPERATURES IN EXCESS OF 2700 F. FABRICATION TIMES AND COSTS ARE CHALLENGING FOR HIGH ACREAGE APPLICATIONS SUCH AS A STRUCTURAL TPS SYSTEM. THIS PROPOSED EFFORT OFFERS A NEW APPROACH IN MANUFACTURING OF SIC/SIC CERAMIC MATRIX COMPOSITE COMPONENTS COST EFFECTIVELY WITH SHORT LEAD TIME AND HIGH FLEXIBILITY. THE COMPOSITES WILL BE FABRICATED VIA A POWDER METALLURGY/SINTERING APPROACH USING AN EMERGING FIELD ASSISTED SINTERING TECHNOLOGY (FAST). THE OBJECTIVE IS TO FABRICATE AND DEMONSTRATE MAKING A COST EFFECTIVE CMC COMPOSITE BY FAST. THE SIC/SIC PRODUCED WILL BE PRODUCED FROM SIC CONSTITUENTS SUITABLE FOR TPS APPLICATIONS. BASIC MECHANICAL AND THERMAL PROPERTIES WILL BE MEASURED TO ASSESS THE PROMISE OF THE FAST PROCESS TO RAPIDLY PRODUCING A SIC/SIC COMPOSITE. A TECHNICAL ASSESSMENT OF THE FAST PROCESS TO PRODUCE A 2700 F+ SIC/SIC WILL BE MADE AS WELL.
contract · Last action 2011-07-29
$99,998
National Aeronautics and Space Administration
SCRAMJET PROPULSION SYSTEMS FOR FUTURE HYPERSONIC AEROSPACE VEHICLES WILL BE SUBJECTED TO HEATING RATES FAR GREATER THAN CURRENT MATERIALS CAN MANAGE. IN ORDER TO SUSTAIN HIGH THERMAL LOADING WHILE PREHEATING THE FUEL, REGENERATIVELY COOLED HOT FLOW PATH COMPONENTS FABRICATED FROM CERAMIC MATRIX COMPOSITES ARE BEING CONSIDERED. THE LIMITED AVAILABILITY OF HIGH-TEMPERATURE/ENVIRONMENTALLY DURABLE MATERIALS FOCUSES ATTENTION TO SILICON CARBIDE FIBER-REINFORCED SILICON CARBIDE (SIC/SIC) COMPOSITES. THESE MATERIALS EXHIBIT A UNIQUE COMBINATION OF LOW DENSITY, HIGH THERMAL CONDUCTIVITY AND OUTSTANDING STRENGTH TO NEAR 3000OF. IN ORDER TO EXPLOIT THE BENEFITS OF SIC/SIC COMPOSITES, METHODS ARE NEEDED FOR FABRICATING HIGH DENSITY/HIGH CONDUCTIVITY COMPONENTS INCORPORATING IMPERMEABLE METAL TUBE LINERS. ADDITIONALLY, PRACTICAL METHODS ARE NEEDED FOR UNIFORMLY DISTRIBUTING COOLANT TO THE ARRAY OF TUBES VIA MANIFOLDING ON THE BACKSIDE OF THE HOT FLOW PATH SURFACE. THE OBJECTIVE OF THIS PHASE I PROGRAM IS TO DEMONSTRATE A PROMISING METHOD FOR PRODUCING A HIGH THERMAL EFFICIENCY SIC/SIC COMPOSITE HEAT EXCHANGER WITH LOW RESIDUAL POROSITY AND HIGH INTERLAMINAR STRENGTH WITHOUT HAVING TO RESORT TO EXOTIC AND COSTLY 3D FIBER PREFORMS. A FUNCTIONAL ACTIVELY COOLED COMPOSITE PANEL TEST ARTICLE INCORPORATING REFRACTORY METAL TUBES WILL BE DESIGNED, FABRICATED AND DELIVERED TO NASA FOR BURNER RIG AND/OR THERMAL EVALUATION.
contract · Last action 2010-01-28
$98,187
National Aeronautics and Space Administration
PRODUCTION OF TOOLING
contract · Last action 2012-05-14
$89,800
National Aeronautics and Space Administration
HI-NICALON TYPE-S SIC/MI-SIC COMPOSITE PANELS END USER:DONGMING ZHU 3-5422 BLDG:106 RM:214
contract · Last action 2012-08-01
$72,050
National Aeronautics and Space Administration
FRABICATE AND COAT 5-NASA SUPPLIED SIC PANELS AND MACHINE TENSILE BARS.
contract · Last action 2010-03-04
$53,380
National Aeronautics and Space Administration
SILICON CARBIDE PANELS
contract · Last action 2015-09-10
$36,798
Department of Defense
FABRICATION OF HI-NICALON SMI PANELS
contract · Last action 2015-06-23
$34,220
National Aeronautics and Space Administration
HI-NICALON COMPOSITE PANELS
contract · Last action 2013-03-28
$31,550
National Aeronautics and Space Administration
FABRICATION OF COOLED SOLID VANES
contract · Last action 2010-09-22
$31,050
National Aeronautics and Space Administration
CVI PROCESSING OF SIX PANEL PREFORMS
contract · Last action 2012-11-28
$29,270
National Aeronautics and Space Administration
SIC PANELS WITH CVI
contract · Last action 2010-12-14
$22,850
National Aeronautics and Space Administration
TYPE S FIBER-REINFORCED PANELS
contract · Last action 2011-02-18
$21,700
National Aeronautics and Space Administration
HI NICALON TYPE S COMPOSITE PANELS
contract · Last action 2012-04-13
$18,050
National Aeronautics and Space Administration
HIGH TEMPERATURE CVI-SMI SIC/SIC CMC PANEL
contract · Last action 2017-05-12
$16,462
Department of Defense
HI-NICALON TYPE S SMI SIC PANELS
contract · Last action 2013-04-19
$15,985
National Aeronautics and Space Administration
FIBER REINFORCED PREFORMS - 6" X 9" HI-NICALON TYPE S FIBER-REINFORCED PREFORM PRODUCED FROM 8 PLIES 5HS FABRIC. THE PANEL WILL TARGET 35% FIBER VOLUME AT NOMINALLY 0.08-INCH THICKNESS. THE PREFORM WILL HAVE CVI BN FIBER COATING APPLIED TARGETED AT 0.5 MICRONS THICKNESS FOLLOWED BY CVI SIC DENSIFICATION TO A TARGET POROSITY OF 30-40%.
contract · Last action 2011-08-03
$13,500
National Aeronautics and Space Administration
CVI BN FIBER COAT PREFORMS
contract · Last action 2010-05-26
$11,320
Department of Defense
HI-NICALON TYPE S SMI SIC PANEL
contract · Last action 2014-05-12
$9,604
National Aeronautics and Space Administration
CVI/SIC COAT/DENSIFY NASA PROV FIBERS BN COAT/DENSIFY NASA PROV FIBERS SIBN COAT/DENSIFY NASA PROV FIBERS
contract · Last action 2011-08-05
$6,420
National Aeronautics and Space Administration
CVI BN/CVI SIC FIBER COATING CVI PY/CVI SIC FIBER COATING
contract · Last action 2009-08-18
$5,540
National Aeronautics and Space Administration
BN FIBER COATING AND CVI SIC DENSIFICATION
contract · Last action 2010-03-31
$4,800
National Aeronautics and Space Administration
IGF::OT::IGF APPLICATION OF SIC COATING ON 8 NASA SUPPLIED SIC WAFERS
contract · Last action 2015-05-29
$4,096
National Aeronautics and Space Administration
CVD SIC COATING OF SILICON CARBIDE WAFER
contract · Last action 2011-09-23
$3,180
National Aeronautics and Space Administration
FABRICATE PREFORM
contract · Last action 2008-02-29
$3,000
Department of Defense
200505!000557!5700!FA8650!DET 1 AFRL/PK !FA865005C5201 !A!N! !Y! ! !20050214!20070406!798073391!798073391!798073391!N!HYPER-THERM HIGH-TEMPERATURE C!18411 GOTHARD ST STE B !HUNTINGTON BEA !CA!92648!36000!059!06!HUNTINGTON BEACH !ORANGE !CALIFORNIA!+000000130000!N!N!000000741634!AC13!RDTE/AIRCRAFT-ADV TECH DEV !S1 !SERVICES !000 !* !541710!E! !3! ! ! ! ! !20200930!B! ! !A! !A!U!U!2!002!K! !Z!N!Z! ! !N!B!N!N! ! !A! !B!A!000!C!B!N! ! ! ! ! ! !0001! !
contract · Last action 2010-01-21
$0
Department of Defense
200407!001136!2100!W9113M!USA SPACE AND STRATEGIC DEF CDR !W9113M04C0037 !A!N! !N! ! !20040318!20060317!798073391!798073391!798073391!N!HYPER-THERM HIGH-TEMPERATURE C!18411 GOTHARD ST , #B !HUNTINGTON BEA !CA!92648!36000!059!06!HUNTINGTON BEACH !ORANGE !CALIFORNIA!+000000375000!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! ! !B! !A!N!J!2!002!K! !Z!N!Z! ! !N!B!N!N! ! !Z! !B!A!00 !C!B!N! ! ! ! ! ! !0001! !
contract · Last action 2011-05-03
$-109
Department of Defense
200409!043154!1700!BW10D !NAVAL SURFACE WARFARE CENTER, DA!N0017804C3053 !A!N! !N! ! !20040625!20060625!798073391!798073391!798073391!N!HYPER-THERM HIGH-TEMPERATURE C!18411 GOTHARD ST , #B !HUNTINGTON BEA !CA!92648!36000!059!06!HUNTINGTON BEACH !ORANGE !CALIFORNIA!+000000374839!N!N!000000749676!AJ12!RDTE/PHYSICAL SCIENCES - APPLIED RESEARCH !C9E!ALL OTHER SUPPLIES AND EQUIPMENT !000 !* !541710!E! !3! ! ! ! ! !99990909!B! ! !A! !A!N!U!2!001!K! !Z!Y!Z! ! !N!B!N!N! ! !Z! !B!A!00 !C!B!N! ! ! ! ! !N00024!0001! !
contract · Last action 2011-06-02
$-1,096

Federal contract dollars to this establishment. Primary NAICS: 541712 - RESEARCH AND DEVELOPMENT IN THE PHYSICAL, ENGINEERING, AND LIFE SCIENCES (EXCEPT BIOTECHNOLOGY). Last action: 2017-05-12. Source: USAspending.gov, net obligations. Recipient address is the SAM registration / HQ address, not necessarily the worksite.

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