What is PIONEER INVENTION, INC.'s OSHA violation history?

PIONEER INVENTION, INC. has 1 OSHA inspection on record with 5 violations and $8,928 in total penalties.

How does PIONEER INVENTION, INC.'s safety record compare to its industry?

PIONEER INVENTION, INC. operates in the hardware manufacturing industry. The industry average Total Recordable Incident Rate (TRIR) is 2.9.

Establishment profile

PIONEER INVENTION, INC.

11111 W 8TH AVE UNIT A, LAKEWOOD, CO, 80215
Operated by Voyager Technologies, Inc · 1 of 2 establishments
332510 — Hardware Manufacturing

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OSHA inspections

over 3 years

Violations

$8,928 in penalties

Penalties

$8,928

$1,786 avg

Summary

PIONEER INVENTION, INC. has accumulated 5 OSHA violations across 1 inspection over 3 years of recorded history, with $8,928 in total assessed penalties.

The establishment sits in the 56th percentile for violations within its industry-state peer group of 10 employers. The most recent enforcement activity was recorded 3 years ago.

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

Agency coverage

PIONEER INVENTION, INC. appears in OSHA workplace safety record only. No matching records were found in WHD wage enforcement, MSHA mine safety, EPA environmental compliance, NLRB labor relations, OFLC visa and labor certification (historical), FMCSA motor carrier registration, SAM.gov federal debarment, CMS nursing home enforcement, UVA Corporate Prosecution Registry, 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

Inspections

0.3 / yr · last 3 yrs

Violations

1.7 / yr

Penalties

$8,928

$1,786 avg / violation

Inspection trigger · complaint

1 of 1

100% of inspections at this establishment produced violations,

Most-cited OSHA standards

Top OSHA standards cited at this employer, ranked by citation count. Standards (CFR sections) cluster citations into safety themes -- machine guarding, lockout-tagout, hazard communication, fall protection, process safety, etc. A concentration on one or two sections reveals a pattern that individual citations don’t. 5 distinct standards shown · 5 citations in this view · $8,928 in penalties.

CFR section	Citations	Inspections	Total penalty	First cited	Last cited
29 CFR 1910.0132 D01 I	1	1	$3,572	Jul 2023	Jul 2023
29 CFR 1910.0151 C	1	1	$2,678	Jul 2023	Jul 2023
29 CFR 1910.1450 E01	1	1	$2,678	Jul 2023	Jul 2023
29 CFR 1910.1450 F01	1	1	—	Jul 2023	Jul 2023
29 CFR 1910.1450 F03 V	1	1	—	Jul 2023	Jul 2023

Source: OSHA inspection citations (violation_detail). CFR section codes can be looked up at osha.gov/laws-regs for the formal standard text. Per-inspection detail and the specific violation descriptions are available by expanding individual inspections below.

Peer comparison

56th

Above average violations in NAICS 3325 within CO. Peer group: 10 employers. This establishment has 5 OSHA violations; peer median is 5.

Fewer violationsMore violations

Penalty percentile

67th

peer median: $3,510

Inspection frequency

0th

peer median: 1

Safety self-report (OSHA 300A)

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

Industry benchmark

Industry avg TRIR

2.9

BLS SOII 2024

Industry avg DART

1.5

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 PIONEER INVENTION, INC.. Verify directly with Occupational Safety and Health Administration →

Activity timeline

Data refreshed

Weekly

First OSHA inspection

—

Most recent activity

3 years ago

No federal enforcement activity has been recorded against this establishment in 3+ years. Most recent activity: 3 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 PIONEER INVENTION, INC.. Verify directly with Wage and Hour Division →

Mine safety (MSHA)

No MSHA mine safety violations on file for PIONEER INVENTION, 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 PIONEER INVENTION, INC.. Verify directly with National Labor Relations Board →

Visa & labor certification (OFLC) — historical

No H-1B, H-2A, or H-2B labor condition applications on file (historical data only — DOL ended OFLC publication) for PIONEER INVENTION, INC.. Verify directly with Office of Foreign Labor Certification →

Environmental compliance (EPA)

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

Federal criminal prosecution record

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

Federal contracts

This location

Obligated (5-yr)

$722K

Obligated (all-time)

$14.2M

Awards

Top agency

National Aeronautics and Space Administration

$13.8M

Top agencies by obligation (this location)

National Aeronautics and Space Administration$13.8M

Department of Defense$424K

Largest awards

National Aeronautics and Space Administration
MOON TO MARS OXYGEN AND STEEL TECHNOLOGY (MMOST)
contract · Last action 2022-09-09
$3,999,973
National Aeronautics and Space Administration
THE ADVANCED ORGANIC WASTE GASIFIER (AOWG) IS A TECHNOLOGY DESIGNED TO CONVERT ORGANIC WASTES GENERATED DURING HUMAN SPACEFLIGHT INTO CLEAN WATER FOR MISSION CONSUMABLES AND GASES SUITABLE FOR VENTING TO MINIMIZE VEHICLE MASS FOR MARS TRANSIT AND RETURN MISSIONS. THE AOWG INTEGRATES STEAM REFORMATION, METHANATION, AND ELECTROLYSIS TO CONVERT ORGANIC WASTE INTO WATER, DRY VENT GAS, AND A SMALL AMOUNT OF INORGANIC RESIDUE, THEREBY REDUCING TRANSIT PROPELLANT AND TANKAGE MASS. THE AOWG REDUCES RISKS ASSOCIATED WITH STORING, HANDLING, AND DISPOSING FOOD WASTE AND PACKAGING, WASTE PAPER, WIPES AND TOWELS, GLOVES, FECAL MATTER, URINE BRINE, AND MAXIMUM ABSORBENCY GARMENTS IN MICROGRAVITY ENVIRONMENTS. THE REFORMER PROVIDES NEARLY COMPLETE CONVERSION OF FEEDS TO VALUABLE WATER AND JETTISONED GAS WITH MINIMAL LOSSES AND CONSUMABLES REQUIREMENTS WHILE OPERATING AT PRESSURES JUST ABOVE THE AMBIENT ENVIRONMENT. THE BASELINE AOWG PHASE II DESIGN INCORPORATES SIGNIFICANT NOVEL ENHANCEMENTS TO PREVIOUS STATE-OF-THE-ART TRASH TO GAS (TTG) STEAM REFORMING TECHNOLOGY INCLUDING A FEED SHREDDER, FEED DRYER, CONTINUOUS FEEDER, TAR DESTRUCTION REACTOR, AND WATER PURIFICATION. THE LARGELY AUTOMATED AOWG LIMITS CREW OPERATION REQUIREMENTS PRIMARILY TO LOADING PACKAGED WASTES INTO THE FEED HOPPER AND OCCASIONAL DISCHARGE AND COMPACTION OF ASH RESIDUE. THE PROPOSED PHASE II AOWG WILL BE DEVELOPED WITH A FOCUS ON ACHIEVING COMPLETE ORGANIC WASTE GASIFICATION SIMULTANEOUS WITH MAXIMUM WATER PRODUCTION USING FEEDING, MATERIALS HANDLING, AND ANCILLARY SYSTEMS GEARED TO MICROGRAVITY OPERATIONS. THESE CONCEPTS WILL BE INTEGRATED INTO A PROTOFLIGHT PHASE II DESIGN, WHICH WILL CONSIDER AND ACCOMMODATE THE MICROGRAVITY ENVIRONMENT NECESSARY TO OPERATE THE AOWG THROUGH STARTUP, STEADY OPERATION, AND SHUTDOWN. THIS PROGRESSION OF DEVELOPMENT WILL LEAD TO IMPLEMENTATION IN ADVANCED HUMAN SPACE MISSIONS.
contract · Last action 2022-01-20
$779,964
National Aeronautics and Space Administration
THE LIQUID SORPTION PUMP (LSP) IS A NEW TECHNOLOGY FOR ACQUIRING CO2 FROM THE MARTIAN ATMOSPHERE FOR USE IN IN SITU RESOURCE UTILIZATION (ISRU) SYSTEMS. IN THE LSP, A SOLVENT, SUCH AS AN ALCOHOL, KETONE, OR ACETATE IS COOLED TO TEMPERATURES BELOW -100 C, WHERE IT BECOMES AN EFFECTIVE SOLVENT FOR MARS ATMOSPHERIC CO2. AFTER ABSORBING 5 PERCENT OR MORE BY MOLE CO2, THE SOLVENT IS PUMPED TO ANOTHER VESSEL WHERE IT IS HEATED TO 30 C, RELEASING THE CO2 AT PRESSURES OF MORE THAN 1 BAR. THE CLEAN WARM SOLVENT IS THEN SENT BACK TO THE ABSORPTION VESSEL, EXCHANGING HEAT WITH THE COLD ABSORPTION COLUMN EFFLUENT AS IT GOES. AFTER THE CLEAN SOLVENT IS COOLED TO NEAR THE DESIGN ABSORPTION TEMPERATURE IN THIS WAY, A MECHANICAL REFRIGERATOR IS USED TO ACHIEVE THE FINAL TEMPERATURE REDUCTION. ADVANTAGES OF THE LSP ARE THAT IT CAN OPERATE CONTINUOUSLY DAY OR NIGHT WITHOUT THE NEED FOR MECHANICAL VACUUM ROUGHING PUMPS, SOLID FREEZERS, OR LARGE SORPTION BEDS, REQUIRES LESS POWER THAN OTHER OPTIONS, IS READILY SCALABLE TO HIGH OUTPUTS, AND THAT IT STOPS ALL SULFUR, DUST, OR NON-CONDENSABLE GASES FROM REACHING THE ISRU REACTOR SYSTEM. IN THE PROPOSED SBIR PHASE 2, AN OPERATING PROTOFLIGHT LSP UNIT MEETING THE FULL-SCALE NASA CO2 ACQUISITION REQUIREMENT NEEDED TO SUPPORT WILL BE DEMONSTRATED AND ITS PERFORMANCE ASSESSED.
contract · Last action 2021-07-01
$754,948
National Aeronautics and Space Administration
IGF::OT::IGF THE EXTRATERRESTRIAL METALS PROCESSING (EMP) SYSTEM PRODUCES IRON, SILICON, AND LIGHT METALS FROM MARS, MOON, OR ASTEROID RESOURCES IN SUPPORT OF ADVANCED HUMAN SPACE EXPLORATION. REFRACTORY OXIDES AND MINOR CONSTITUENTS SUCH AS SULFUR, PHOSPHORUS, AND ALKALINE EARTH OXIDES ARE ALSO GENERATED AS BYPRODUCTS AND CAN BE USED FOR THE REFINING OF FINISHED GOODS, THEREBY FURTHER REDUCING DEPENDENCE ON EARTH-BASED CONSUMABLES. IRON IS PRODUCED VIA REDUCTION OF OXIDES BY HYDROGEN OR CARBON MONOXIDE. SILICON, FERROSILICON, AND HIGH-PURITY FUMED SILICON MONOXIDE ARE GENERATED VIA CARBOTHERMAL REDUCTION OF SILICA-CONTAINING RESOURCES. REDUCTANTS ARE GENERATED USING ESTABLISHED ISRU-RELATED TECHNOLOGIES INCLUDING ELECTROLYSIS, THE REVERSE WATER GAS SHIFT REACTION, THE BOUDOUARD CARBON DEPOSITION REACTION, AND COMBINATIONS THEREOF. DURING PHASE I, MAGNESIUM METAL WAS SUCCESSFULLY PRODUCED VIA SILICOTHERMIC REDUCTION. ALTERNATIVE LIGHT METAL REDUCTION METHODS WILL BE EVALUATED AND COMPARED TO THE BASELINE SILICOTHERMIC REDUCTION OF MAGNESIUM OXIDE FOR STRUCTURAL APPLICATIONS, REPLACEMENT PARTS, AND MANUFACTURING HARDWARE ON MARS. A HIGH-QUALITY FUMED SILICON MONOXIDE PRODUCT CAN BE FURTHER OXIDIZED AND USED FOR PRODUCTION OF CLEAR GLASS. UPON REDUCTION WITH CARBON, SIO CAN ALSO BE USED TO MAKE HIGH PURITY SILICON FOR THE PRODUCTION OF SEMICONDUCTOR MATERIALS USING DOPING AGENTS SUCH AS PHOSPHORUS. THE PHASE II EFFORT WILL EXPAND ON THE FINDINGS OF THE PHASE I WORK WITH DEMONSTRATION OF AN END-TO-END SYSTEM TO PRODUCE IRON AND STEEL AT A RATE ON THE ORDER OF ONE KILOGRAM PER DAY. EXAMPLE PARTS WILL BE MADE USING CASTING, SINTERING, OR ADVANCED MANUFACTURING METHODS. IN PARALLEL WITH THE DEMONSTRATION OF END-TO-END IRON PRODUCTION DURING PHASE II, LIGHT METALS MANUFACTURING METHODS EVALUATED DURING PHASE I WILL BE FURTHER REFINED. SMALL-SCALE PRODUCTION OF LIGHT METALS WILL BE DEMONSTRATED DURING PHASE II.
contract · Last action 2018-06-03
$754,637
National Aeronautics and Space Administration
IGF::OT::IGF THE NITROUS ETHANE-ETHYLENE ROCKET WITH HYPERGOLIC IGNITION (NEERHI) ENGINE IS A PROPOSED TECHNOLOGY DESIGNED TO PROVIDE SMALL SPACECRAFT WITH NON-TOXIC, NON-CRYOGENIC, HIGH PERFORMANCE, HYPERGOLIC PROPULSION. WHEN PASSED OVER A WARM CATALYST BED, GASEOUS NITROUS OXIDE AND AN ETHYLENE-ETHANE GASEOUS BLEND COMBUST INSTANTLY. A SMALL 1 N THRUSTER CAN BE DESIGNED TO PROVIDE SMALL SATELLITE PROPULSION SYSTEMS WITH A SPECIFIC IMPULSE OF APPROXIMATELY 300 SECONDS. BOTH PROPELLANTS ARE SELF-PRESSURIZING, CAPABLE OF DELIVERING FEED LINE PRESSURES IN EXCESS OF 800 PSI AT ROOM TEMPERATURE, AND 400 PSI IF COOLED TO 0?C. FOR LONGER DURATION MISSIONS, BOTH NITROUS OXIDE AND AN ETHANE-ETHYLENE FUEL BLEND DO NOT REQUIRE THERMAL HEATING TO MAINTAIN A LIQUID STATE, AND AS SUCH, CAN BE STORED ON EARTH OR IN SPACE FOR IN-DEFINITE PERIODS OF TIME WITH NO PARASITIC POWER DRAIN REQUIRED TO MAINTAIN A LIQUID PROPELLANT. COMPARED TO OTHER AVAILABLE CHEMICAL PROPULSION SYSTEMS, A NEERHI SYSTEM OFFERS A COST EFFECTIVE SOLUTION AS OTHER HYPERGOLIC ENGINES USE HYDRAZINE AND NITROGEN TETROXIDE WHICH ARE TOXIC AND DANGEROUS TO HANDLE, INCREASING GROUND COSTS. AS AN ADDED CAPABILITY, THE NEERHI ENGINE HAS THE ABILITY TO OPERATE AS A MONOPROPELLANT ENGINE IF THE CATALYST BE IS HEATED WITH A BIPROPELLANT REACTION, INCREASING THE LIFETIME OF THE CATALYST BED AND REDUCING HEATING LOADS ON THE ENGINE. THE FUEL AND OXIDIZER HAVE NEARLY IDENTICAL VAPOR PRESSURE CURVES, ALLOWING THEM TO BE STORED IN COMPACT COMMON-BULKHEAD TANKS.
contract · Last action 2018-06-03
$754,607
National Aeronautics and Space Administration
IGF::OT::IGF THE CARBONACEOUS ASTEROID VOLATILE RECOVERY (CAVOR) SYSTEM PRODUCES WATER AND HYDROGEN-RICH SYNGAS FOR PROPELLANT PRODUCTION, LIFE SUPPORT CONSUMABLES, AND MANUFACTURING FROM IN-SITU RESOURCES IN SUPPORT OF ADVANCED SPACE EXPLORATION. THE CAVOR THERMALLY EXTRACTS ICE AND WATER BOUND TO CLAY MINERALS, WHICH IS THEN COMBINED WITH SMALL AMOUNTS OF OXYGEN TO GASIFY ORGANIC MATTER CONTAINED IN CARBONACEOUS CHONDRITE ASTEROIDS. IN ADDITION TO WATER, CAVOR PRODUCES HYDROGEN, CARBON MONOXIDE, AND CARBON DIOXIDE THAT COMPRISE PRECURSORS TO PRODUCE OXYGEN FOR PROPELLANT AND BREATHING GAS AND TO PRODUCE ORGANIC COMPOUNDS INCLUDING FUELS SUCH AS METHANE WHEN INTEGRATED WITH A DOWNSTREAM METHANATION-ELECTROLYSIS. THERMOCHEMICAL PRODUCTION OF HYDROGEN BY CAVOR RESULTS IN SUBSTANTIAL REDUCTIONS IN ELECTROLYSIS MASS AND POWER REQUIREMENTS COMPARED TO COMBUSTION-BASED VOLATILE RECOVERY METHODS. A CONCEPTUAL PHASE II CONTINUOUS FLOW AUGER REACTOR DESIGN WAS BASED ON SUCCESSFUL PHASE I BATCH REACTOR OPERATIONS. PHASE II ADVANCEMENTS WILL INCLUDE REACTOR SEAL DESIGNS TO ACCOMMODATE REGOLITH SIMULANT FEEDING AND DISCHARGING WHILE COLLABORATIONS WILL BE DEVELOPED TO AID THE INFUSION OF THE CAVOR SYSTEM INTO A CONCEPTUAL ASTEROID RESOURCE UTILIZATION MISSION PLAN
contract · Last action 2018-05-31
$754,567
National Aeronautics and Space Administration
TAS::80 0123::TAS THE MULTI-CELL THERMAL BATTERY (MCTB) IS A DEVICE THAT CAN RECOVER A LARGE FRACTION OF THE THERMAL ENERGY FROM HEATED REGOLITH AND SUBSEQUENTLY APPLY THIS ENERGY TO HEAT UP COOL REGOLITH. THE INDIVIDUAL CELLS OF THE MCTB CONTAIN A THERMAL STORAGE MEDIA THAT IS SPECIFICALLY DESIGNED FOR OPTIMAL PERFORMANCE AT A GIVEN TEMPERATURE RANGE. EACH OF THESE CELLS IS CHARGED WITH THERMAL ENERGY FROM HOT REGOLITH THAT HAS BEEN USED IN A LUNAR ISRU APPLICATION. ONCE THE MCTB IS CHARGED, THE HEAT IS TRANSFERRED FROM THE BATTERY TO NEWLY HARVESTED REGOLITH. IN THIS MANNER OVER 85% OF THE HEAT CAN BE TRANSFERRED FROM THE EXPENDED TO THE NEW REGOLITH. THIS IS A LARGE IMPROVEMENT ESPECIALLY CONSIDERING THAT THIS REDUCES THE HEATING REQUIREMENT TO PRODUCE 1000 KG OF O2 FROM LUNAR REGOLITH FROM AN AVERAGE OF 1 KW TO ONLY 0.15 KW (ASSUMING 3% O2 RECOVERY BY WEIGHT). THE OTHER IRREDUCIBLE POWER CONSUMPTION OF LUNAR ISRU O2 PRODUCTION IS ELECTROLYSIS WHICH CONSUMES AT LEAST 0.3 KW. HENCE, USING THE MCTB DECREASES THE IRREDUCIBLE POWER CONSUMPTION OF LUNAR ISRU BY 65 %.
contract · Last action 2009-10-13
$599,990
National Aeronautics and Space Administration
THE LUNAR ORGANIC WASTE REFORMER (LOWR) UTILIZES HIGH TEMPERATURE STEAM REFORMATION TO CONVERT ALL PLASTIC, PAPER, AND HUMAN WASTE MATERIALS INTO USEFUL GASES. IN THE LOWR, SOLAR THERMAL CONCENTRATORS ARE USED TO HEAT STEAM DIRECTLY TO 600 C, AFTER WHICH THE STEAM IS MIXED WITH A SMALL AMOUNT OF OXYGEN AND INJECTED INTO A REACTOR WHICH IS BEING FED WITH WASTE MATERIALS VIA A LOCK HOPPER. AT THE HIGH TEMPERATURES, THE OXYGENATED STEAM WILL REACT WITH ALL ORGANIC MATERIALS TO PRODUCE A GAS MIXTURE LARGELY COMPOSED OF HYDROGEN, CO AND CARBON DIOXIDE. AFTER REMOVING THE REMAINING STEAM FROM THE PRODUCT STREAM VIA CONDENSATION, THE GASES ARE DUSULFURIZED AND THEN FED TO A CATALYTIC REACTOR WHERE THEY CAN BE COMBINED WITH HYDROGEN TO PRODUCE METHANE, METHANOL, OR OTHER FUELS. BOTH THE NECESSARY HYDROGEN AND OXYGEN FOR THE PROCESS CAN BE PRODUCED BY ELECTROLYSIS OF PART OF THE WATER CONTENT OF THE WASTE MATERIAL, WHICH IS EXTRACTED FROM THE WASTES DIRECTLY BY THE REFORMER ITSELF. WITH EFFECTIVE RECYCLING OF THE STEAM, NO CONSUMABLES ARE LOST IN THE PROCESS. ALL PRODUCTS ARE LIQUIDS OR GASES, MAKING THE SYSTEM HIGHLY RELIABLE AND SUBJECT TO AUTOMATION. IN THE PROPOSED PHASE 2 PROGRAM, PIONEER ASTRONAUTICS WILL BUILD A FULL-SCALE END-TO-END LOWR SYSTEM CAPABLE OF TURNING 10 KG OF WASTE PER DAY INTO METHANE AND OXYGEN.
contract · Last action 2013-06-21
$599,931
National Aeronautics and Space Administration
THE LUNAR SOIL PARTICLE SEPARATOR (LSPS) IS AN INNOVATIVE METHOD TO BENEFICIATE SOIL PRIOR TO IN-SITU RESOURCE UTILIZATION (ISRU). THE LSPS CAN IMPROVE ISRU OXYGEN YIELD BY BOOSTING THE CONCENTRATION OF ILMENITE OR OTHER IRON-OXIDE BEARING MATERIALS FOUND IN LUNAR SOILS. THIS CAN SUBSTANTIALLY REDUCE HYDROGEN REDUCTION REACTOR SIZE AND DRASTICALLY DECREASE THE POWER INPUT REQUIRED FOR SOIL HEATING. LSPS PARTICLE SIZE SEPARATIONS CAN BE PERFORMED TO DE-DUST REGOLITH AND TO IMPROVE ISRU REACTOR FLOW DYNAMICS. LSPS MINERAL SEPARATIONS CAN BE USED TO ALTER THE SINTERING CHARACTERISTICS OF LUNAR SOIL. THE LSPS CAN ALSO BE USED TO SEPARATE AND CONCENTRATE LUNAR MINERALS USEFUL FOR MANUFACTURE OF STRUCTURAL MATERIALS, GLASS, AND CHEMICALS. THE LSPS INTEGRATES AN INITIAL CENTRIFUGAL PARTICLE SIZE SEPARATION WITH MAGNETIC, GRAVITY, AND ELECTROSTATIC SEPARATIONS. THE LSPS CENTRIFUGAL SEPARATION METHOD OVERCOMES THE REDUCED EFFICIENCY OF CONVENTIONAL PARTICLE SIEVING IN REDUCED GRAVITY. THE LSPS HARDWARE DESIGN INTEGRATES MANY INDIVIDUAL UNIT OPERATIONS TO REDUCE SYSTEM MASS AND POWER REQUIREMENTS. THE LSPS IS APPLICABLE TO ISRU FEED PROCESSING AS WELL AS ROBOTIC PROSPECTING TO CHARACTERIZE SOILS OVER WIDE REGIONS ON THE MOON. THE LSPS IS SCALABLE AND IS AMENABLE TO TESTING AND DEVELOPMENT IN VACUUM AND REDUCED GRAVITY.
contract · Last action 2011-08-04
$599,827
National Aeronautics and Space Administration
LUNAR SULFUR CAPTURE SYSTEM THE LUNAR SULFUR CAPTURE SYSTEM (LSCS) IS AN INNOVATIVE METHOD TO CAPTURE GREATER THAN 90 PERCENT OF SULFUR GASES EVOLVED DURING THERMAL TREATMENT OF LUNAR SOILS. LSCS SORBENTS ARE BASED ON LUNAR SOIL IRON COMPOUNDS THAT TRAP SULFUR CONTAINED IN HOT IN-SITU RESOURCE UTILIZATION (ISRU) PRODUCT GASES. SMALL AMOUNTS OF POLISHING SORBENTS ARE USED AS NEEDED TO REDUCE EQUILIBRIUM SULFUR CONCENTRATIONS TO THE PPM OR SUB-PPM LEVEL. THE LSCS IS AN EFFECTIVE TECHNOLOGY FOR PROTECTING IN-SITU RESOURCE UTILIZATION (ISRU) HARDWARE FROM DAMAGE CAUSED BY THE CORROSIVE EFFECTS OF HYDROGEN SULFIDE (H2S) AND OTHER SULFUR-CONTAINING GASES. SATURATED SORBENTS CAN BE REGENERATED FOR REUSE, AND DESORBED SULFUR CAN BE CONVERTED TO ELEMENTAL SULFUR. KEY PROCESS STEPS INCLUDE BULK H2S CAPTURE ON LUNAR SOIL, FURTHER CAPTURE OF H2S ON POLISHING SORBENT, REGENERATION OF SOIL SORBENT FOR RE-USE, RECOVERY OF HIGH-PURITY H2S, AND CONVERSION OF H2S TO ELEMENTAL SULFUR. THE LSCS REDUCES THE RISK OF USING EARTH-BASED SORBENTS FOR PRIMARY SULFUR CAPTURE BY ENSURING A READY SUPPLY OF SORBENT IN THE EVENT OF POOR REGENERATION PERFORMANCE OR PROCESS UPSET. THE LSCS PRIMARY SULFUR SORBENT CAN BE USED AS A NON-REGENERABLE SORBENT IF NECESSARY WITHOUT SIGNIFICANT CONSEQUENCE TO THE ISRU PROCESS.
contract · Last action 2011-03-18
$599,764
National Aeronautics and Space Administration
LUNAR MATERIALS HANDLING SYSTEM SMALL BUSINESS INNOVATIVE RESEARCH (SBIR) PROGRAM 2005 PHASE II RESEARCH PROJECT INDENTIFIED IN B.1
contract · Last action 2009-01-05
$273,000
Department of Defense
SBIR/STTR PHASE II R&D - ENABLING SMALLSAT PROPULSION FOR ORBITAL MANEUVERABILITY
contract · Last action 2024-03-04
$172,366
National Aeronautics and Space Administration
E014042 SBIR PHASE I MAGNETIC DUST FILTRATION SYSTEM.
contract · Last action 2022-07-20
$156,498
National Aeronautics and Space Administration
E014042 SBIR PHASE I NOVEL DURABLE SILICA-BASED TRANSPARENT COATINGS.
contract · Last action 2022-07-20
$156,493
National Aeronautics and Space Administration
EO14042 SBIR PHASE 1
contract · Last action 2022-07-21
$156,491
National Aeronautics and Space Administration
RADIATOR FREE ENGINE
contract · Last action 2021-06-08
$131,478
National Aeronautics and Space Administration
THE LIQUID SORPTION PUMP (LSP) IS A NEW TECHNOLOGY FOR ACQUIRING CO2 FROM THE MARTIAN ATMOSPHERE FOR USE IN IN SITU RESOURCE UTILIZATION (ISRU) SYSTEMS. IN THE LSP, PROPANOL IS COOLED TO TEMPERATURES BELOW -100 C, WHERE IT BECOMES AN EFFECTIVE SOLVENT FOR MARS ATMOSPHERIC CO2. AFTER ABSORBING 5 PERCENT OR MORE BY MOLE CO2, THE PROPANOL IS PUMPED TO ANOTHER VESSEL WHERE IT IS HEATED TO 30 C, RELEASING THE CO2 AT PRESSURES OF MORE THAN 1 BAR. THE CLEAN WARM PROPANOL IS THEN SENT BACK TO THE ABSORPTION VESSEL, EXCHANGING HEAT WITH THE COLD ABSORPTION COLUMN EFFLUENT AS IT GOES. AFTER THE CLEAN PROPANOL IS COOLED TO NEAR THE DESIGN ABSORPTION TEMPERATURE IN THIS WAY, A MECHANICAL REFRIGERATOR IS USED TO ACHIEVE THE FINAL TEMPERATURE REDUCTION. ADVANTAGES OF THE LSP ARE THAT IT CAN OPERATE CONTINUOUSLY DAY OR NIGHT WITHOUT THE NEED FOR MECHANICAL VACUUM ROUGHING PUMPS, SOLID FREEZERS, OR LARGE SORPTION BEDS, REQUIRES LESS POWER THAN OTHER OPTIONS, IS READILY SCALABLE TO HIGH OUTPUTS, AND THAT IT STOPS ALL SULFUR, DUST, OR NON-CONDENSABLE GASES FROM REACHING THE ISRU REACTOR SYSTEM. IN THE PROPOSED SBIR PHASE 1, AN OPERATING LSP WILL BE DEMONSTRATED AND ITS PERFORMANCE ASSESSED.
contract · Last action 2019-02-11
$124,995
National Aeronautics and Space Administration
IGF::OT::IGF THE ADVANCED MARS WATER ACQUISITION SYSTEM (AMWAS) RECOVERS AND PURIFIES WATER FROM MARS SOILS FOR OXYGEN AND FUEL PRODUCTION, LIFE SUPPORT, FOOD PRODUCTION, AND RADIATION SHIELDING IN SUPPORT OF HUMAN EXPLORATION MISSIONS. THE AMWAS REMOVES WATER FROM MARS SOILS USING HOT, RECIRCULATING CARBON DIOXIDE GAS TO PROVIDE RAPID HEAT TRANSFER. THE AMWAS EVAPORATES WATER FROM ICE AND SALT HYDRATES, LEAVING DISSOLVED CONTAMINANTS IN THE SOIL RESIDUE. THE WATER DISTILLED FROM THE EXTRACTION VESSEL IS CONDENSED, TREATED WITH ACTIVATED CARBON TO REMOVE RESIDUAL VOLATILES AND ORGANIC MATERIAL, FILTERED TO REMOVE SUSPENDED SOLIDS, AND SUBJECTED TO DEIONIZATION IN PREPARATION FOR PROTON EXCHANGE MEMBRANE ELECTROLYSIS. RECUPERATIVE HEAT EXCHANGE IS EMPLOYED TO MINIMIZE HEAT LOSSES FROM RECIRCULATING CARBON DIOXIDE GAS. COLD TEMPERATURES OF THE MARS ATMOSPHERE ARE USED TO FACILITATE CONDENSATION AND SEPARATION OF WATER FROM RECYCLED CARBON DIOXIDE GAS. A VACUUM JACKET IS USED TO MINIMIZE HEAT LOSSES FROM THE EXTRACTION VESSEL. MUCH OF THE NET HEAT INPUT TO THE AMWAS CAN BE SUPPLIED BY SOLAR CONCENTRATORS OR WASTE HEAT FROM RADIOISOTOPE THERMOELECTRIC GENERATORS. THE AMWAS VESSEL IS EQUIPPED WITH A SINGLE, STATIONARY SEAL THAT FACILITATES MATERIALS HANDLING AUTOMATION AND MINIMIZES POTENTIAL LEAKAGE OVER THE NOMINAL OPERATING PERIOD OF UP TO 480 DAYS.
contract · Last action 2017-06-07
$124,990
National Aeronautics and Space Administration
THE ADVANCED ORGANIC WASTE GASIFIER (AOWG) IS A NOVEL TECHNOLOGY TO CONVERT ORGANIC WASTES FROM SPACE EXPLORATION OUTPOSTS INTO CLEAN WATER AND GASES SUITABLE FOR VENTING WITH THE OVERALL GOAL OF MINIMIZING VEHICLE MASS FOR MARS TRANSIT AND RETURN MISSIONS. THE AOWG INTEGRATES STEAM REFORMATION, AND ELECTROLYSIS TO CONVERT ORGANIC WASTE INTO WATER AND A SMALL AMOUNT OF INORGANIC MATTER AND OXYGEN PRODUCTS, THEREBY REDUCING TRANSIT FUEL AND TANKAGE MASS. THE AOWG REDUCES RISKS ASSOCIATED WITH STORING, HANDLING, AND DISPOSING FOOD WASTE AND PACKAGING, WASTE PAPER, WIPES AND TOWELS, GLOVES, FECAL MATTER, URINE BRINE, AND MAXIMUM ABSORBENCY GARMENTS IN MICROGRAVITY ENVIRONMENTS. THE GASIFIER PROVIDES NEARLY COMPLETE CONVERSION OF FEEDS TO VALUABLE WATER AND JETTISONED GAS WITH MINIMAL LOSSES AND CONSUMABLES REQUIREMENTS. THE AOWG INCORPORATES SIGNIFICANT NOVEL ENHANCEMENTS TO PREVIOUS STATE-OF-THEART TRASH TO GAS (TTG) STEAM REFORMING TECHNOLOGY INCLUDING A FEED PREPARATION SYSTEM, CONTINUOUS FEEDER, AND TAR DESTRUCTION REACTOR TO PRODUCE CLEAN WATER. THE AOWG CREW OPERATION REQUIREMENTS CONSIST OF PACKAGING WASTES IN A MANNER SIMILAR TO THE FOOTBALL PREPARATION METHODS CURRENTLY USED IN STATE-OF-THE ART TTG SYSTEMS BUT ARE NOT LIMITED TO THIS PREPARATION METHOD. THE ACTUAL OPERATION OF THE AOWG IS LARGELY AUTOMATED AND REQUIRES MINIMAL CREW INTERVENTION. THE PROPOSED PHASE I AOWG WILL BE DEVELOPED WITH A FOCUS ON ACHIEVING THE MAXIMUM WASTE MASS REDUCTION SIMULTANEOUS WITH WATER PRODUCTION USING FEEDING, MATERIALS HANDLING, AND ANCILLARY SYSTEMS GEARED TO MICROGRAVITY OPERATIONS. THESE CONCEPTS WILL BE INTEGRATED INTO A FLIGHT READY PHASE II DESIGN, WHICH WILL SIMULATE A MICROGRAVITY ENVIRONMENT NECESSARY TO OPERATE THE AOWG THROUGH STARTUP, STEADY OPERATION, AND SHUTDOWN. THIS PROGRESSION OF DEVELOPMENT WILL LEAD TO IMPLEMENTATION IN ADVANCED HUMAN SPACE MISSIONS.
contract · Last action 2019-02-11
$124,989
National Aeronautics and Space Administration
LUNAR EXPLORATION GAS SPECTROMETER
contract · Last action 2019-08-05
$124,988
National Aeronautics and Space Administration
THE LUNAR FLOW BATTERY (LFB) IS A SCALABLE, LONG-DURATION ENERGY STORAGE SOLUTION FEATURING MINIMUM CAPACITY FADE OVER MANY CYCLES THAT USES ELECTROLYTES DERIVED FROM LUNAR REGOLITH TO MINIMIZE LAUNCH MASS.
contract · Last action 2019-07-12
$124,976
National Aeronautics and Space Administration
GAS REPLACEMENT SYSTEM
contract · Last action 2020-08-07
$124,970
National Aeronautics and Space Administration
PIONEER ASTRONAUTICS MAGSAIL FOR SPACECRAFT DEORDBIT
contract · Last action 2020-08-12
$124,949
National Aeronautics and Space Administration
IGF::OT::IGF PIONEER ASTRONAUTICS PROPOSES AN ADVANCED PHOTOCATALYTIC OXIDATION REACTOR FOR ENHANCING THE RELIABILITY AND PERFORMANCE OF WATER RECOVERY POST PROCESSING SYSTEMS ABOARD CREWED SPACECRAFT. THIS NOVEL TECHNOLOGY, CALLED THE ADVANCED WASTEWATER PHOTOOXIDATION SYSTEM (AWPS) IS DESIGNED TO OXIDIZE AND REMOVE RECALCITRANT AQUEOUS ORGANIC CONSTITUENTS IN THE WATER RECOVERY POST PROCESSING SYSTEM UNDER AMBIENT TEMPERATURE AND PRESSURE CONDITIONS. THE BASIS OF THE INNOVATION IS THE COMBINATION OF HIGH BRIGHTNESS AND LONG LIFETIME UV LED LIGHT SOURCES WITH EFFICIENT GEOMETRICILLUMINATION OF A HIGHLY ACTIVE PHOTOCATALYST IMMOBILIZED ON A HIGH SURFACE AREA SUPPORT. THIS COMBINED APPROACH LEADS TO NUMEROUS PERFORMANCE BENEFITS INCLUDING HIGH CONVERSION EFFICIENCY, LOW TEMPERATURE AND PRESSURE OPERATION, COMPACT FOOTPRINT, HIGH RELIABILITY AND LOW CREW MAINTENANCE, AND DECREASED EQUIVALENT SYSTEM MASS (ESM). THE PHASE I EFFORT WILL CLEARLY DEMONSTRATE THE FEASIBILITY OF THESE CONCEPTS BY MINERALIZATION OF POLAR WATER SOLUBLE ORGANICS AND ORGANOSILANOL CONSTITUENTS UNDER LONG DURATION TESTING. DATA FROM THE PHASE I WILL LEAD TO A PROTOTYPE SCALE-UP OF THE DEVICE IN PHASE II. DEVELOPMENT STRATEGIES FOR THE PHASE II DEVICE INCLUDE COMPONENT DESIGN VERIFICATION TESTING AND DETERMINING OPTIMUM REACTION CONDITIONS. LONG DURATION PERFORMANCE TESTS WILL VALIDATE THE REACTOR DESIGN, AND ESTABLISH THE TECHNOLOGY APPLICATIONS IN SPACE AND COMMERCIAL MARKETS.
contract · Last action 2014-06-06
$124,946
National Aeronautics and Space Administration
IGF::OT::IGF THE CARBONACEOUS ASTEROID VOLATILE RECOVERY (CAVOR) SYSTEM EXTRACTS WATER AND VOLATILE ORGANIC COMPOUNDS FOR PROPELLANT PRODUCTION, LIFE SUPPORT CONSUMABLES, AND MANUFACTURING FROM IN-SITU RESOURCES IN SUPPORT OF ADVANCED SPACE EXPLORATION. THE CAVOR THERMALLY EXTRACTS ICE AND WATER BOUND TO CLAYS MINERALS, WHICH IS THEN COMBINED WITH SMALL AMOUNTS OF OXYGEN TO GASIFY ORGANIC MATTER CONTAINED IN CARBONACEOUS CHONDRITE ASTEROIDS. IN ADDITION TO WATER, CAVOR PRODUCES HYDROGEN, CARBON MONOXIDE, AND CARBON DIOXIDE THAT COMPRISE PRECURSORS TO PRODUCE OXYGEN FOR PROPELLANT AND BREATHING GAS AND TO PRODUCE ORGANIC COMPOUNDS INCLUDING FUELS AND PLASTICS. ADDITIONAL CAVOR BYPRODUCTS INCLUDE NITROGEN, SULFUR, AND PHOSPHORUS COMPOUNDS THAT HAVE POTENTIAL USES AS BUFFER GAS FOR LIFE SUPPORT AND REAGENTS FOR MORE-ADVANCED ASTEROID MATERIALS PROCESSING. PROCESS RESIDUES ARE THERMALLY STABILIZED BY THE CAVOR SYSTEM, WHICH RENDERS THEM SUITABLE AS BULK SHIELDING, AS FEED TO MINERAL SEPARATION AND CONCENTRATION, OR AS RAW MATERIAL FOR MANUFACTURE OF STRUCTURAL COMPONENTS. THE CAVOR IS A LOW-PRESSURE, NON-CATALYTIC, BATCH PROCESS AIMED TOWARD MAXIMUM RECOVERY OF VALUABLE CONSTITUENTS IN A DIFFICULT OPERATING ENVIRONMENT USING STEEL OR OTHER LIGHT-WEIGHT REACTOR ALLOYS. KEY ELEMENTS OF THE CAVOR WILL BE SYSTEMATICALLY DEVELOPED AND DEMONSTRATED THROUGH A PROGRESSION FROM AN EARTH LABORATORY ENVIRONMENT TO EXPERIMENTS IN ZERO-G FLIGHTS AND ISS WITH APPROPRIATE SCALE UP AND PERFORMANCE VALIDATIONS LEADING TO IMPLEMENTATION ON A NEAR EARTH ASTEROID (NEA). HARDWARE DESIGNS TO ACHIEVE REQUIRED SEALING AND OPERATING PERFORMANCE OVER LONG DURATIONS IN MICROGRAVITY WILL BE DERIVED IN PART FROM PIONEER'S HERITAGE IN LUNAR AND MARS ISRU. A COMBINATION OF MODELING AND EXPERIMENTATION WILL BE USED TO OVERCOME THE LACK OF CURRENT WELLESTABLISHED STATE-OF-THE-ART PROCESS METHODS AND CONDITIONS FOR RESOURCE RECOVERY FROM NEAR EARTH ASTEROIDS.
contract · Last action 2015-06-03
$124,911
National Aeronautics and Space Administration
IGF::OT::IGF THE NITROUS ETHANE-ETHYLENE ROCKET WITH HYPERGOLIC IGNITION (NEERHI) ENGINE IS A PROPOSED TECHNOLOGY DESIGNED TO PROVIDE SMALL SPACECRAFT WITH NON-TOXIC, NON-CRYOGENIC, HIGH PERFORMANCE, HYPERGOLIC PROPULSION. WHEN PASSED OVER A WARM RUTHENIUM CATALYST BED, GASEOUS NITROUS OXIDE AND AN ETHYLENE-ETHANE GASEOUS BLEND COMBUST INSTANTLY. A SMALL 1 N THRUSTER CAN BE DESIGNED TO PROVIDE SMALL SATELLITE PROPULSION SYSTEMS WITH A SPECIFIC IMPULSE OF APPROXIMATELY 300 SECONDS. BOTH PROPELLANTS ARE SELF-PRESSURIZING, CAPABLE OF DELIVERING FEED LINE PRESSURES IN EXCESS OF 800 PSI AT ROOM TEMPERATURE, AND 400 PSI IF COOLED TO 0?C. FOR LONGER DURATION MISSIONS, BOTH NITROUS OXIDE AND AN ETHANE-ETHYLENE FUEL BLEND DO NOT REQUIRE THERMAL HEATING TO MAINTAIN A LIQUID STATE, AND AS SUCH, CAN BE STORED ON EARTH OR IN SPACE FOR IN-DEFINITE PERIODS OF TIME WITH NO PARASITIC POWER DRAIN REQUIRED TO MAINTAIN A LIQUID PROPELLANT. COMPARED TO OTHER AVAILABLE CHEMICAL PROPULSION SYSTEMS, A NEERHI SYSTEM OFFERS A COST EFFECTIVE SOLUTION AS OTHER HYPERGOLIC ENGINES USE HYDRAZINE AND NITROGEN TETROXIDE WHICH ARE TOXIC AND DANGEROUS TO HANDLE, INCREASING GROUND COSTS. AS AN ADDED CAPABILITY, THE NEERHI ENGINE HAS THE ABILITY TO OPERATE AS A MONOPROPELLANT ENGINE IF THE RUTHENIUM CATALYST BE IS HEATED WITH A BIPROPELLANT REACTION, INCREASING THE LIFETIME OF THE CATALYST BED AND REDUCING HEATING LOADS ON THE ENGINE.
contract · Last action 2015-06-01
$124,881
National Aeronautics and Space Administration
IGF::OT::IGF PIONEER ASTRONAUTICS PROPOSES A TECHNOLOGY PROGRAM FOR THE DEVELOPMENT OF AN INNOVATIVE PHOTOCATALYTIC OXIDATION REACTOR FOR THE REMOVAL AND MINERALIZATION OF VOLATILE ORGANIC COMPOUNDS TO EXTEND CREWED SPACE EXPLORATION BEYOND LOW EARTH ORBIT. THIS NOVEL TECHNOLOGY, CALLED THE HIGH PERFORMANCE PHOTOCATALYTIC OXIDATION REACTOR SYSTEM (HPPORS) LEVERAGES RECENT PROGRESS IN HIGH POWER LIGHT EMITTING DIODES (LED) AND EFFICIENT, VISIBLE WAVELENGTH PHOTOOXIDATION (PO) CATALYSTS TO COMPLETELY OXIDIZE VOLATILE ORGANIC COMPOUNDS (VOCS) TO CARBON DIOXIDE AND WATER. THE BASIS OF THE INNOVATION IS THE SYNTHESIS OF COMMERCIAL HIGH POWER, HIGH BRIGHTNESS LEDS WITH EFFICIENT GEOMETRIC ILLUMINATION OF ACTIVE VISIBLE-LIGHT ACTIVATED PO CATALYST IN A HIGH SURFACE AREA TO VOLUME FIBER OPTIC REACTOR. THIS COMBINED APPROACH LEADS TO NUMEROUS PERFORMANCE BENEFITS INCLUDING HIGH VOC CONVERSION EFFICIENCY, COMPACT REACTOR VOLUME, AND LOW PRESSURE DROP. THE DEVELOPMENT OF THE HPPORS TECHNOLOGY WILL LEAD TO A PHOTOCATALYTIC REACTOR THAT MEETS THE RIGOROUS COMPLIANCE REQUIREMENTS OF COMPLETE VOC MINERALIZATION TO CO2 AND H2O, WHILE UTILIZING EFFICIENT VISIBLE LEDS OR SOLAR ENERGY IN A COMPACT, SCALABLE PACKAGE.
contract · Last action 2013-05-21
$124,880
National Aeronautics and Space Administration
IGF::OT::IGF THE EXTRATERRESTRIAL METALS PROCESSING (EMP) SYSTEM PRODUCES FERROSILICON, SILICON MONOXIDE, A GLASSY MIXED OXIDE SLAG, AND SMALLER AMOUNTS OF ALKALI EARTH COMPOUNDS, PHOSPHORUS, SULFUR, AND HALOGENS FROM MARS, MOON, AND ASTEROID REGOLITH BY CARBOTHERMAL REDUCTION. THESE MATERIALS, IN SOME CASES AFTER FURTHER PROCESSING WITH OTHER IN-SITU RESOURCES, ARE USED FOR PRODUCTION OF HIGH-PURITY IRON AND MAGNESIUM METALS (FOR STRUCTURAL APPLICATIONS), HIGH PURITY SILICON (FOR PHOTOVOLTAICS AND SEMICONDUCTORS), HIGH PURITY SILICA (FOR CLEAR GLASS), REFRACTORY CERAMICS (FOR INSULATION, THERMAL PROCESSING CONSUMABLES, AND CONSTRUCTION MATERIALS), AND FERTILIZER (FROM PHOSPHORUS RECOVERED FROM CARBOTHERMAL REDUCTION EXHAUST GASES). CARBOTHERMAL REDUCTION ALSO CO-PRODUCES OXYGEN AT YIELDS ON THE ORDER OF 20 PERCENT OF REGOLITH FEED MASS WHEN INTEGRATING DOWNSTREAM PROCESSES TO RECOVER AND RECYCLE CARBON. MANY OF THE EMP PRODUCTS CAN BE PREPARED IN A FASHION SUITABLE FOR CASTING OR ADDITIVE MANUFACTURE METHODS AND HAVE BROAD APPLICATION IN SUPPORT OF ADVANCED HUMAN SPACE EXPLORATION. THE EMP METHODS ARE BASED ON MINIMAL RELIANCE ON EARTH-BASED CONSUMABLES; NEARLY ALL OF THE GASES AND REAGENTS REQUIRED FOR PROCESSING CAN BE MANUFACTURED FROM MARS IN-SITU RESOURCES OR CAN BE RECOVERED AND RECYCLED FOR APPLICATIONS USING MOON OR ASTEROID RESOURCES.
contract · Last action 2016-05-23
$124,849
National Aeronautics and Space Administration
MAGNETIC PHASE SEPERATOR
contract · Last action 2021-02-12
$124,804
National Aeronautics and Space Administration
IGF::OT::IGF THE NITROUS OXIDE ETHANE-ETHYLENE (NEE) ENGINE IS A PROPOSED TECHNOLOGY DESIGNED TO PROVIDE SPACECRAFT WITH NON-TOXIC NON-CRYOGENIC HIGH-PERFORMANCE PROPULSION. WITH THE NEE ENGINE, NITROUS OXIDE IS USED AS AN AUTOGENOUSLY PRESSURIZING OXIDIZER, AND A MIXTURE OF ETHANE AND ETHYLENE IS USED IN THE SAME MANNER AS FUEL. INITIALLY, THE ETHANE AND ETHYLENE MIXTURE HAVE THE SAME VAPOR PRESSURE AS THE NITROUS OXIDE. BY UTILIZING THE AUTOGENOUS PRESSURIZATION CAPABILITIES OF THESE PROPELLANTS INSTEAD OF AN ADDITIONAL PRESSURIZATION SYSTEM GREATER SYSTEM SIMPLICITY AND RELIABILITY CAN BE ATTAINED. ACHIEVABLE SPECIFIC IMPULSE WITH PURE N2O IS ABOUT 315 S, WHICH CAN BE RAISED ABOVE 325 S BY DISSOLVING SOME O2 IN THE N2O. CATALYTIC IGNITION CAN BE ACHIEVED BY USING A RUTHENIUM REACTOR TO EXOTHERMICALLY DISSOCIATE N2O. SINCE BOTH PROPELLANTS CAN EXIST AS A LIQUID IN THE SAME TEMPERATURE RANGE, NO THERMAL SEPARATION IS REQUIRED, AND THE TWO PROPELLANTS CAN BE STORED TOGETHER IN COMPACT COMMON BULKHEAD TANKS, AND FREEZING IS NOT AN ISSUE DOWN TO -90C. PIONEER ASTRONAUTICS HAS DEMONSTRATED MONOPROPELLANT NITROUS OXIDE THRUSTERS WITH A SPECIFIC IMPULSE OF 190 S. USING SUCH NITROUS OXIDE MONOPROPELLANT ENGINES FOR LOW THRUST RCS TOGETHER WITH THE NEE FOR ??V AND LARGER THRUST REACTION CONTROL PROPULSION, IT WILL BE POSSIBLE TO BUILD SPACECRAFT PROPULSION SYSTEMS THAT ARE COMPLETELY STORABLE AND NON-TOXIC, WITH ONLY TWO PROPELLANT FLUIDS REQUIRED. IN THE PROPOSED PROGRAM, WE WILL DEMONSTRATE A NEE ENGINE.
contract · Last action 2013-05-21
$124,660
Department of Defense
IGF::OT::IGF!8503391079!SERVICES - MANAG
contract · Last action 2016-07-05
$102,926
National Aeronautics and Space Administration
LUNAR SOIL PARTICLE SEPARATOR THE LUNAR SOIL PARTICLE SEPARATOR (LSPS) IS AN INNOVATIVE METHOD TO BENEFICIATE SOIL PRIOR TO IN-SITU RESOURCE UTILIZATION (ISRU). THE LSPS IMPROVES ISRU OXYGEN YIELD BY BOOSTING THE CONCENTRATION OF ILMENITE OR OTHER IRON-OXIDE BEARING MATERIALS FOUND IN LUNAR SOILS. LSPS PARTICLE SIZE SEPARATIONS CAN BE PERFORMED TO IMPROVE GAS-SOLID INTERACTIONS AND REACTOR FLOW DYNAMICS. LSPS MINERAL SEPARATIONS CAN BE USED TO ALTER THE SINTERING CHARACTERISTICS OF LUNAR SOIL. THE LSPS CAN EVENTUALLY BE USED TO SEPARATE AND CONCENTRATE LUNAR MINERALS USEFUL FOR MANUFACTURE OF STRUCTURAL MATERIALS, GLASS, AND CHEMICALS. THE LSPS INTEGRATES AN INITIAL CENTRIFUGAL PARTICLE SIZE SEPARATION WITH MAGNETIC, GRAVITY, AND/OR ELECTROSTATIC SEPARATIONS. THE LSPS CENTRIFUGAL SEPARATION METHOD OVERCOMES THE REDUCED EFFICIENCY OF CONVENTIONAL PARTICLE SIEVING IN REDUCED GRAVITY. FEED CONDITIONING, SUCH AS CHARGE NEUTRALIZATION, CAN BE INCORPORATED INTO THE LSPS TO RELEASE AND DISPERSE SURFACE FINES PRIOR TO PARTICLE SEPARATIONS. THE CONCEPTUAL LSPS HARDWARE DESIGN INTEGRATES MANY INDIVIDUAL UNIT OPERATIONS TO REDUCE SYSTEM MASS AND POWER REQUIREMENTS. THE LSPS IS APPLICABLE TO ISRU FEED PROCESSING AS WELL AS ROBOTIC PROSPECTING TO CHARACTERIZE SOILS OVER A WIDE REGION ON THE MOON. THE LSPS IS SCALABLE AND IS AMENABLE TO TESTING AND DEVELOPMENT UNDER SIMULATED LUNAR ENVIRONMENTAL CONDITIONS.
contract · Last action 2009-01-09
$100,000
National Aeronautics and Space Administration
NITROUS OXIDE MICRO ENGINES (NOME) ARE A NEW TYPE OF NITROUS OXIDE DISSOCIATION THRUSTER DESIGNED TO GENERATE LOW LEVELS OF THRUST THAT CAN BE USED FOR RCS CONTROL IN LARGE SATELLITES OR AS MAIN PROPULSION IN MICRO-SATELLITES. NITROUS IS THE IDEAL PROPELLANT CHOICE FOR RCS CONTROL IN SATELLITES DUE TO THE FACT THAT IT IS NON-TOXIC, NON-CRYOGENIC, EASILY STORABLE, SELF-PRESSURIZING, AND COST EFFECTIVE (UNLIKE MONOPROPELLANT ENGINES THAT USE HYDRAZINE OR HYDROGEN PEROXIDE WHICH ARE TOXIC AND/OR DANGEROUS, INCREASING GROUND COSTS). NOME ENGINES WILL HAVE ALL THE DESIRABLE FEATURES OF OTHER MONOPROPELLANT ENGINES (I.E. SIMPLICITY OF DESIGN, RESTARTABLE/CONTROL ON DEMAND, AND REPEATABILITY) NOME ENGINES WILL ALSO HAVE A COMPARABLE ISP TO CURRENT MONOPROPELLANT ENGINES (NEAR 190S) BUT WILL BE MADE TO ACHIEVE GREATER SIMPLICITY AND LOWER HANDLING COSTS THAN CURRENT SYSTEMS. NOMES WILL HAVE OVER DOUBLE THE ISP OF COLD GAS REACTION CONTROL SYSTEMS.
contract · Last action 2011-07-26
$99,999
National Aeronautics and Space Administration
THE MARS REGOLITH WATER EXTRACTOR (MRWE) IS A SYSTEM FOR ACQUIRING WATER FROM THE MARTIAN SOIL. IN THE MRWE, A STREAM OF CO2 IS HEATED BY SOLAR ENERGY OR WASTE HEAT FROM A NUCLEAR REACTOR AND THEN PASSED THROUGH A VESSEL CONTAINING MARTIAN SOIL FRESHLY REMOVED FROM THE GROUND. THE HOT CO2 WILL CAUSE WATER ABSORBED IN THE MARTIAN SOIL TO OUTGAS, WHEREUPON IT WILL BE SWEPT ALONG BY THE CO2 TO A CONDENSER CHAMBER WHERE AMBIENT MARTIAN COLD TEMPERATURES WILL BE USED TO CONDENSE THE WATER FROM THE CO2. THE CO2 IS THEN PUMPED BACK TO THE HEATER WHERE IT IS REHEATED AND RECIRCULATED BACK TO THE SOIL VESSEL TO REMOVE MORE WATER. MEASUREMENTS TAKEN BY THE VIKING MISSION SHOWED THAT RANDOMLY GATHERED MARTIAN SOIL CONTAINS AT LEAST 1% WATER BY WEIGHT, AND PROBABLY MORE THAN 3%. THIS BEING THE CASE, THE MWRE SHOULD PROVE TO BE A HIGHLY EFFECTIVE WAY OF ACQUIRING WATER ON MARS. BY DOING SO, IT WILL ELIMINATE THE REQUIREMENT TO TRANSPORT HYDROGEN TO MARS IN ORDER TO MAKE METHANE FUEL, AND ALLOW ALL THE PROPELLANT NEEDED FOR A MARS TO EARTH RETURN FLIGHT TO BE MANUFACTURED ON MARS USING A SABATIER/ELECTROLYSIS (S/E) CYCLE, WITHOUT ANY NEED FOR AUXILIARY OXYGEN PRODUCTION THROUGH ZIRCONIA CELLS, REVERSE WATER GAS SHIFT CYCLES, OR OTHER SYSTEMS. THIS IS HIGHLY ADVANTAGEOUS SINCE THE S/E CYCLE IS THE SIMPLEST AND EASIEST TO IMPLEMENT OF ALL MARS IN-SITU PROPELLANT PRODUCTION METHODS. THE ABILITY TO EXTRACT WATER FROM MARS WILL ALSO SERVE TO SUPPLY THE CREW OF A MARS MISSIONS WITH COPIOUS SUPPLIES OF WATER ITSELF, WHICH AFTER PROPELLANT, IS THE MOST MASSIVE LOGISTIC COMPONENT OF A MARS MISSION. BY ELIMINATING THE NEED TO TRANSPORT FUEL, OXYGEN, AND WATER TO MARS, THE MWRE WILL HAVE A MAJOR EFFECT IN REDUCING THE MASS, COST, AND RISK OR HUMAN MARS EXPLORATION.
contract · Last action 2011-07-22
$99,999
National Aeronautics and Space Administration
THE REGENERABLE CONTAMINANT REMOVAL SYSTEM (RCRS) IS AN INNOVATIVE METHOD TO REMOVE SULFUR AND HALIDE COMPOUNDS FROM CONTAMINATED GAS STREAMS TO PART-PER-BILLION LEVELS IN SUPPORT OF LUNAR OXYGEN PRODUCTION. A SERIES OF HIGH EFFICIENCY SORBENTS SEQUENTIALLY REMOVES CONTAMINANTS AT TEMPERATURES ABOVE DEW POINT. SORBENTS ARE REGENERATED, AND CONTAMINANTS ARE RECOVERED IN CONCENTRATED FORM. THE RCRS IS INSTALLED DOWNSTREAM FROM LUNAR SOIL REDUCTION REACTORS TO PROTECT HARDWARE FROM CORROSION, TO PROTECT CATALYSTS FROM POISONING, AND TO REDUCE THE LOAD ON AQUEOUS CONTAMINANT REMOVAL PROCESSES USED IN ADVANCE OF ELECTROLYSIS. CUSTOM, HIGH-POROSITY, HIGH-CAPACITY SORBENTS ARE USED TO MINIMIZE SORBENT MASS AND SORPTION REACTOR VOLUME WHILE ALSO MINIMIZING PROCESS PRESSURE DROP. SORPTION REACTOR VOLUMES ARE SMALL COMPARED TO THE VOLUME OF SOIL REDUCTION REACTORS. HIGH POROSITY AND SORBENT DURABILITY ARE IMPARTED THROUGH THE USE OF ORGANIC AND INORGANIC FILLERS AND BINDERS DURING MANUFACTURE OF THE SORBENTS. THE RCRS IMPOSES VERY LITTLE PARASITIC LOAD ON ISRU OXYGEN RECOVERY SYSTEMS DURING THE COURSE OF SORBENT REGENERATION AND RECOVERY OF CONTAMINANT BYPRODUCTS. THE BASIC RCRS PROCESS CAN BE TAILORED TO PROVIDE CONTAMINANT REMOVAL FOR A WIDE RANGE OF REDUCING GAS COMPOSITIONS.
contract · Last action 2011-07-22
$99,984
National Aeronautics and Space Administration
COUNTERFLOW REGOLITH HEAT EXCHANGER THE COUNTERFLOW REGOLITH HEAT EXCHANGER (CORHE) IS A DEVICE THAT TRANSFERS HEAT FROM HOT REGOLITH TO COLD REGOLITH. THE CORHE IS ESSENTIALLY A TUBE-IN-TUBE HEAT EXCHANGER WITH INTERNAL AND EXTERNAL AUGERS ATTACHED TO THE INNER, ROTATING TUBE TO MOVE THE REGOLITH. HOT REGOLITH IN THE OUTER TUBE IS MOVED IN ONE DIRECTION BY A RIGHT-HANDED AUGER AND THE COOL REGOLITH IN THE INNER TUBE IS MOVED IN THE OPPOSITE BY A LEFT-HANDED AUGER ATTACHED TO THE INSIDE OF THE ROTATING TUBE. IN THIS COUNTERFLOW ARRANGEMENT A LARGE FRACTION OF THE HEAT FROM THE EXPENDED REGOLITH IS TRANSFERRED TO THE NEW REGOLITH. THE SPENT REGOLITH LEAVES THE HEAT EXCHANGER CLOSE TO THE TEMPERATURE OF THE COLD NEW REGOLITH AND THE NEW REGOLITH IS PRE-HEATED CLOSE TO THE INITIAL TEMPERATURE OF THE SPENT REGOLITH. USING THE CORHE CAN REDUCE THE HEATING REQUIREMENT OF A LUNAR ISRU SYSTEM BY 80%, REDUCING THE TOTAL POWER CONSUMPTION BY A FACTOR OF TWO.
contract · Last action 2009-01-09
$99,980
National Aeronautics and Space Administration
THE LUNAR ORGANIC WASTE REFORMER (LOWR) UTILIZES HIGH TEMPERATURE STEAM REFORMATION TO CONVERT ALL PLASTIC, PAPER, AND HUMAN WASTE MATERIALS INTO USEFUL GASES. IN THE LOWR, SOLAR THERMAL CONCENTRATORS ARE USED TO HEAT STEAM DIRECTLY TO 900 C, AFTER WHICH THE STEAM IS INJECTED INTO A REACTOR WHICH IS BEING FED WITH WASTE MATERIALS VIA A LOCK HOPPER. AT THE HIGH TEMPERATURES, THE STEAM WILL REACT WITH ALL ORGANIC MATERIALS TO PRODUCE A GAS MIXTURE LARGELY COMPOSED OF HYDROGEN AND CARBON DIOXIDE, WITH SMALL FRACTIONS OF METHANE AND CO. AFTER REMOVING THE REMAINING STEAM FROM THE PRODUCT STREAM VIA CONDENSATION, THE GASES ARE DUSULFURIZED AND THEN FED THROUGH A POLYSULFONE MEMBRANE WHICH SEPARATES CO AND CH4 IN THE RETENTATE FROM CO2 AND H2 IN THE PERMEATE. THE RETENTATE CO/CH4 GAS STREAM CAN BE USED TO REDUCE REGOLITH, WHILE THE CO2/H2 PERMEATE STREAM IS SENT TO A REVERSE WATER GAS SHIFT (RWGS) REACTOR WHICH TRANSFORMS THE CO2/H2 GAS INTO CO AND H2O. THE CO CAN THEN BE USED FOR REGOLITH REDUCTION, WHILE THE H2O CAN BE USED AS IS, OR ELECTROLYZED TO MAKE OXYGEN AND HYDROGEN. WITH EFFECTIVE RECYCLING OF THE STEAM, NO CONSUMABLES ARE LOST IN THE PROCESS. ALL PRODUCTS ARE LIQUIDS OR GASES, MAKING THE SYSTEM HIGHLY RELIABLE AND SUBJECT TO AUTOMATION. IN THE PROPOSED PHASE 1 PROGRAM, PIONEER ASTRONAUTICS WILL BUILD ON ITS EXTENSIVE HERITAGE WITH DEVELOPMENT OF RWGS AND REGOLITH REDUCTION SYSTEMS DEVELOPED FOR LUNAR AND MARS IN-SITU PROPELLANT PRODUCTION TO BUILD AND DEMONSTRATE A LOWR UNIT.
contract · Last action 2010-01-26
$99,964
National Aeronautics and Space Administration
LUNAR SULFUR CAPTURE SYSTEM
contract · Last action 2008-02-27
$99,962
National Aeronautics and Space Administration
DURABLE DUST REPELLENT COATING FOR METALS THE DURABLE DUST REPELLENT COATING (DDRC) CONSISTS OF NANO-PHASE SILICA, TITANIA, OR OTHER OXIDE COATINGS TO REPEL DUST IN A VACUUM ENVIRONMENT OVER A WIDE RANGE OF TEMPERATURES. THE COATINGS ARE ENGINEERED WITH DIELECTRIC PROPERTIES TO STRONGLY REPEL PARTICLES FROM SURFACES. DURABILITY IS ATTAINED BY APPLICATION METHODS SUCH AS SOL-GEL COATING OR PHYSICAL VAPOR DEPOSITION ONTO STATIONARY AND ROTATING SURFACES OF EVA EQUIPMENT, HATCHES AND SEALS, LUNAR MODULES, ISRU HARDWARE, AND HABITATS PRIOR TO ASSEMBLY. THE APPLICATION OF THE COATING IS FOLLOWED BY ANNEALING AT ELEVATED TEMPERATURES. INITIAL DEVELOPMENT IS PLANNED FOR STAINLESS STEEL, FOLLOWED LATER BY OTHER METALS AND PLASTICS. IN ADDITION TO DUST REPELLENCY, THE DDRC PROVIDES ABRASION RESISTANCE TO LUNAR HARDWARE. SOME OF THE DDRC COATINGS ALSO IMPART UV RESISTANCE TO THE SUBSTRATE. UNLIKE CONVENTIAL DUST REMOVAL METHODS SUCH AS BRUSHING OR BLOWING THAT MAY RESULT IN DEEP INFILTRATION OF PARTICLES, DUST CAN BE READILY REMOVED FROM DDRC SURFACES BY TILTING OR MILD VIBRATION.
contract · Last action 2009-01-09
$99,941
National Aeronautics and Space Administration
MULTI CELL THERMAL BATTERY.
contract · Last action 2008-02-01
$99,932
Department of Defense
SBIR/STTR PHASE I RESEARCH&DEVELOPMENT - STORABLE CLEAN ETHANE/ETHYLENE NITROUS ENGINE (SCENE)
contract · Last action 2019-03-25
$99,652
National Aeronautics and Space Administration
ADVANCED ORGANIC WASTE GASIFIER
contract · Last action 2022-09-09
$55,000
Department of Defense
STRATOSPHERIC FLIGHT GAS SYSTEM
contract · Last action 2021-10-29
$49,968
National Aeronautics and Space Administration
SBIR II/CARBON MONOXIDE SILICATE REDUCTION SYSTEM
contract · Last action 2008-03-18
$0
National Aeronautics and Space Administration
MARS INTEGRATED PROPELLANT PRODUCTION SYSTEM
contract · Last action 2008-01-28
$0
National Aeronautics and Space Administration
SBIR II/MARS AQUEOUS PROCESSING SYSTEM
contract · Last action 2008-03-28
$-5
Department of Defense
200411!004936!2100!W31P4Q!USA AVIATION AND MISSILE COMMAND!W31P4Q04CR322 !A!N! !N! ! !20040824!20061126!120561456!120561456!120561456!N!PIONEER INVENTION, INC !11111 W 8TH AVE , UNIT A !LAKEWOOD !CO!80215!43000!059!08!LAKEWOOD !JEFFERSON !COLORADO !+000000375000!N!N!000000000000!AD92!RDTE/OTHER DEFENSE-APPLIED RESEARCH !A2 !MISSILE AND SPACE SYSTEMS !000 !* !541710!E! !3! ! ! ! ! !99990909!B! ! !N!Z!A!N!U!2!002!K! !Z!Y!Z! ! !N!B!N!N! ! !A! !B!A!00 !C!B!N! ! ! ! ! ! !0001! !
contract · Last action 2012-09-10
$-880

Federal contract dollars to this establishment. Primary NAICS: 541715 - RESEARCH AND DEVELOPMENT IN THE PHYSICAL, ENGINEERING, AND LIFE SCIENCES (EXCEPT NANOTECHNOLOGY AND BIOTECHNOLOGY). Last action: 2024-03-04. Source: USAspending.gov, net obligations. Recipient address is the SAM registration / HQ address, not necessarily the worksite.

Inspection history

Date	Trigger	Violations	Serious	Penalty
2023-04-11	Complaint	5	—	$8,928

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

In the news

Part of a larger organization

PIONEER INVENTION, INC. is one of 2 establishments rolled up under the parent organization Voyager Technologies, Inc.

Federal enforcement records on this page represent activity at this specific establishment only. The full enforcement footprint of Voyager Technologies, Inc across all 2 of its tracked locations is viewable on the parent profile.

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MASTER MANUFACTURERS, INC.DENVER — 1 federal enforcement record
ACME MANUFACTURING COMPANY, INC.DENVER — 1 federal enforcement record