Attachment B2 -Topic 2-Technical Performance Measures.pdf
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- Solicitation number
- 80GRC026R0008
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This is an attachment describing technical performance metrics and desired system characteristics for a NextSTEP-3 Topic 2 oxygen production demonstration project.
The document establishes requirements for offerors to demonstrate a lunar oxygen extraction system capable of producing oxygen from regolith simulant. The primary requirement (1.1.1) mandates that the demonstrated system operate at throughput scalable to 10 metric tons of oxygen per year without significant modifications to the underlying technology. Offerors are encouraged to demonstrate a pilot-scale system producing 1 metric ton of oxygen annually (approximately 0.2 kg O₂/hr) assuming 200 continuous 24-hour operating days per year. The system must feature integrated process flow where product streams transfer directly between components without interruption, with oxygen directly derived from the regolith source. Key performance metrics to be recorded and reported include total oxygen produced (kg), averaged production rate (kg O₂/hr), production efficiency per energy input (kg O₂/kWh), extraction efficiency (kg O₂/kg regolith), output stream composition, and consumables usage excluding regolith simulant.
Additional critical requirements include measuring and quantifying oxygen production and yield at system output, with oxygen purity targets of less than 1% non-condensables and less than 0.5% condensables suitable for downstream liquefaction. The test program must demonstrate minimum 48-hour continuous integrated system operation with all consumables and repairs accounted for in metrics. The system shall include integrated waste handling capability for spent regolith and by-products without disrupting operations. Offerors must identify all modifications required for flight-ready implementation and assess performance impacts, select and procure appropriate lunar highlands regolith simulant representative of lunar south polar conditions, and provide thermal performance data and instrumentation to support future Thermal Vacuum testing. Product stream composition and mass must be measured and quantified at system output, and the system must include regolith feeding capability with a hopper that can be manually replenished.
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Attachment B2: Technical Performance Metrics and Desired System Characteristics Topic 2 NextSTEP-3 Appendix A
Requirements
1.1 Oxygen Production Throughput
1.2 Pilot-Scale Demonstration
1.3 Integrated Process Flow
1.4 System Performance Metrics
1.5 Oxygen Production Measurement
1.6 Flight Demonstration-Forward Readiness
1.7 Continuous Operations Demonstration
1.8 Waste Handling
1.9 Product Stream Characterization
1.10 Regolith Feed System
1.11 Thermal Management
Requirem ent ID
Requiremen t Type
Requirement
1.1.1 Oxygen
Production Throughput
The demonstrated system shall operate at a throughput that is scalable to a production capacity of 10 metric tons (mT) of oxygen per year without requiring significant modifications to the underlying technology architecture or process.
1.2.1 Pilot-Scale
Demonstratio n
Offerors are encouraged to demonstrate a pilot-scale system capable of producing 1 mT of oxygen per year, equivalent to approximately 0.2 kg O₂/hr, assuming 200 continuous 24-hour Earth days of operation per year.
1.3.1 Integrated
Process Flow
The system shall demonstrate an integrated process flow in which the product stream from each component is transferred directly to the next downstream component. The process flow cannot be interrupted to remove or inject any material (solid, gas, or fluid that is not part of the intended lunar system operations and design (any reactant consumable supply and recycling must be integrated). The product from the regolith extraction must flow through the system, where the oxygen must be directly derived from this source.
1.4.1 System
Performance Metrics
The following key system performance metrics shall be recorded and reported: a) total oxygen produced (kg), b) averaged production rate (kg O2/hr), c) averaged production per energy input (e.g. kg O2/KWh), d) extraction efficiency (kg O2/kg regolith), e) and composition of output stream (e.g. molecular abundance of contaminant per molecules of O2),
(f) consumables use (other than regolith simulant) kg consumable/kg O2 produced. Metrics are intended to represent rates that can extrapolated to a year of operation, so must include full extent of system operations.
1.5.1 Oxygen
Production Measurement
The system shall measure and quantify oxygen production and yield (oxygen extracted vs available oxygen in the regolith) at the system output.
1.5.2 Oxygen
Production Measurement
The oxygen product stream shall be characterized to demonstrate compliance with the cleanliness requirements applicable to downstream oxygen liquefaction for propellant production. Offerors are encouraged to explore downstream liquification options that maybe compatible with their system to identify appropriate purity conditions. However, notional targets for the oxygen stream are <1% non-condensables and <0.5% condensables where the following reference summarizes contaminant impacts on liquefaction processes https://cryo.memberclicks.net/assets/cold_facts_issues/cold_facts_vol42 _no2_2026.pdf (pg 24)
1.6.1 Flight
Demonstratio n-Forward Readiness
Offerors shall identify all modifications required to transition the ground demonstrated system to a flight-ready implementation and shall assess the expected impact of those modification to system performance. The modifications required to make the system flight ready must be defined along with any impact on performance. Note: As neither flight qualification nor TRL6 testing is required in the scope of this effort, hardware materials, power draw, etc. do not need to meet flight requirements. However, key Decision Points will consider the viability of a future flight system.
1.7.1 Continuous
Operations Demonstratio n
The test program shall demonstrate full, integrated system operation at a minimum of 48 hours of continuous operations. Any consumables or repairs incurred must be reported and be accounted for in the metrics.
Note: Batch processes are acceptable, but the cycling of the batches must be part of the system operations and design, without taking the system offline.
1.8.1 Waste
Handling
The system shall discharge waste stream (spent regolith simulant or unwanted gaseous by-products) without disrupting system operations.
Waste discharge capability must be integrated into the system as part of the design and operations.
1.8.2 Waste
Handling
The method used to expel processed regolith shall be representative of the intended lunar operating concept.
1.8.3 Waste
Handling
Collection, transport, or disposal of tailings after discharge from the system boundary is not required.
1.9.1 Product
Stream Characterizat ion
The composition and mass of the product stream shall be measured and quantified at the system output. System by-products that are separated to produce the clean, dry O2 stream are encouraged to be measured but not required. Capture and storage of products is not required.
However, proposers are encouraged to address the upstream and downstream systems to the extent possible.
1.10.1 Regolith
Feed System
The system shall include a regolith handling system to feed the regolith simulant into the processing unit. This is assumed to include a regolith hopper in addition to any required feed/metering device. The regolith hopper can be replenished manually. However, Offerors are encouraged to address the upstream and downstream systems to the extent possible.
1.11.1 Regolith
Simulant
The Offeror shall identify within the proposal the regolith simulant to be used in the system test. Offerors shall be responsible for the procurement, acquisition, and associated costs of the selected regolith simulant. The selected simulant shall represent lunar highlands regolith and be relevant to conditions expected in the lunar south polar region.
The selected particle size distribution shall be appropriate for the proposed extraction process. Note: NASA acknowledges that the reaction and products of a regolith simulant may not be fully representative of lunar regolith. Expected limitations of the simulant chosen shall be identified.
https://cryo.memberclicks.net/assets/cold_facts_issues/cold_facts_vol42_no2_2026.pdf https://cryo.memberclicks.net/assets/cold_facts_issues/cold_facts_vol42_no2_2026.pdf
1.12.1 Thermal
Management
The System design and test program shall generate the thermal performance data necessary to support future Thermal Vacuum (TVAC) test planning.
1.12.2 Thermal
Management
The system shall be instrumented to measure temperatures, thermal interfaces, and thermal management performance sufficient to characterize component-level and system-level thermal behavior.
Thermal Management
The test program shall collect and report data necessary to evaluate thermal interactions between major system components and interfaces relevant to future TVAC testing.
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