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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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All sourcesNASA NTRSDOE OSTI
NASA NTRSDate not supplied

Liquefaction of Cryogenic Fluids for Production and Storage of Commodities on Extra-Terrestrial Surfaces

The Cryogenic Fluid In-situ Liquefaction for Landers (CryoFILL) activity has been investigating concepts for the liquefaction of cryogenic fluids produced on the surface of the Moon and Mars. CryoFILL consists of four activities: liquid nitrogen liquefaction testing that was completed in 2019, liquid oxygen liquefaction testing planned to begin in early 2022, fiber-optic sensor temperature measurement system development, and lightweight vacuum jacketed systems designed for the atmosphere of Mars. Additional activities include the development and validation of numerical modeling systems at three stages: thermodynamic models of the liquefaction process for basic energy/mass estimates, nodal models to predict liquefaction tank system level performance, and computational fluid dynamics to assess fluid phenomena occurring within the tank, specifically condensation and stratification within the ullage. These developments form a combined liquefaction and storage solution to support Lunar and Martian exploration. Key testing results from liquid nitrogen testing as well as plans for liquid oxygen testing will be discussed including key sensitivities from analytical evaluation of completed test results. Progress on the development and improvements on fiber optic sensor testing and developments will also be provided. Finally, work on the progress of the lightweight vacuum jacketed systems being co-developed by NASA and industry will be summarized.

Liquefaction↗
NASA NTRSDate not supplied

Comparison of Oxygen Liquefaction Gaseous Oxygen Injection via Ullage and Dip Tube

The Cryogenic Fluid In-situ Liquefaction for Landers (CryoFILL) testing demonstrated constant and transient oxygen liquefaction in a scaled lander tank integrated with an industrial cryocooler. Early in the test series, two methods for injecting gaseous oxygen into the test tank were ran under similar constant liquefaction conditions for comparison. Gaseous oxygen was either injected directly from the lid into the ullage or bubbled up through the liquid using a dip tube that extends to the bottom of the test tank. The direct comparison of these gaseous oxygen injection methods for constant liquefaction indicated ullage injection provided a greater liquefaction rate than injection via a dip tube. Injection through the ullage was subsequently selected as the nominal injection method for the CryoFILL test series. The comparison of the two injection methods will be highlighted with a discussion of what may cause the variation in liquefaction rate.

Cryogenic Fluid Management↗
NASA NTRS2019

Liquid Nitrogen Testing of ISRU Liquefaction Methods in Unsteady Applications

To enable NASA’s planned long duration missions, the agency is putting emphasis on reusable cryogenic systems. Such systems will require replenishing of cryogens on-orbit via a cryogenic tanker or refueling depot, and potentially on the lunar or Martian surfaces with the utilization of in-situ resources. Surface replenishing requires the in-situ production of gaseous oxygen (and hydrogen if on the lunar surface), followed by liquefaction and storage. Funded by NASA’s Advanced Exploration Systems, and managed under the Advanced Cis-Lunar Space Capability Project, the Cryogenic Fluid In-Situ Liquefaction for Landers (CryoFILL) multi center team was formed to develop a liquefaction and storage system that is efficient, reliable and scalable. This presentation will demonstrate the liquefaction and storage of “In-Situ like” propellant via a Tube-On-Tank Heat Exchanger integrated with Active Cooling (cryocooler) (verify proof of concept and obtain relevant data for model validation) and gather lessons learned from “brassboard” testing which will be applied to future liquefaction system prototype testing, then eventually to an end-to-end demonstration.

Stephens, J. R.↗
NASA NTRSDate not supplied

Transient Liquefaction on the Lunar or Martian Surface Operational Demonstration

As developments of local production of cryogenic fluids on the Lunar or Martian Surface progress, it is important to understand transient system responses to help with the balancing of process plant power and understanding system level operations. During the Cryogenic Fluid In-situ Liquefaction for Landers (CryoFILL) testing, a series of transient oxygen liquefaction tests were completed. These tests included varying liquefaction flow rate, environmental temperature, tank fill level, and effective cryocooler lift while allowing the tank pressure to respond to the input controls. An additional transient test was run at the 90% fill level to determine the impact of injecting the gaseous oxygen at the bottom of the tank, allowing the vapor to bubble up through the liquid. Tests were run in a cyclical nature varying one variable at a time. The control variable was set in a manner to increase tank pressure for a period of time and then subsequently changed in a manner to decrease the tank pressure back to its original value with multiple cycles run for all tests. Tank pressure and system temperature responses were tracked as a function of time with an emphasis on repeatability. Results indicate that of the four variables tested, the environmental temperature is the least important. As expected, the bubbling of the liquefaction gas significantly decreased the pressurization and depressurization rates in the tank at the 90% full level.

Liquefaction↗
NASA NTRS2023

Transient Liquefaction on the Lunar or Martian Surface Operational Demonstration

The Cryogenic Fluid In-situ Liquefaction for Landers (CryoFILL) activity has been investigating concepts for the liquefaction of cryogenic fluids produced on the surface of the Moon and Mars. Liquefaction testing of oxygen in a scaled lander tank using an integrated, industrial cryocooler system was completed. The testing covered the determination of the nominal performance operation of the system, constant liquefaction performance, and transient liquefaction performance. The goal of the testing was to demonstrate cryogenic liquefaction operational capabilities on the Lunar and Martian surfaces for landers and In Situ Resource Utilization. The testing met all key performance parameter threshold values including liquefaction rate (demonstrated 1.6 kg/hr compared to threshold of 1.1 kg/hr), number of variables as transient (goal of 3: liquefaction flow, environmental temperature, and cryocooler input power – all demonstrated), and number of fill levels (goal of 3: < 5%, 50%, and 90% - all demonstrated). Key testing results from oxygen liquefaction testing will be discussed including sensitivities provided by the analysis team.

Liquefaction↗
NASA NTRS2023

Comparison of Liquefaction Testing with Liquid Nitrogen and Liquid Oxygen

Liquid nitrogen is often used as a substitute for oxygen testing due to safety concerns, and the general similarity between their fluid properties. During the Cryogenic Fluid In-situ Liquefaction for Landers (CryoFILL) testing, an opportunity arose to compare liquid nitrogen and liquid oxygen behavior using the same test hardware in similar test conditions. Comparative testing would verify whether the system response to nitrogen and oxygen would behave in a similar manner. Tests that were investigated include system boil-off heat load determination, autogenous pressurization, cryocooler loop initiation, and cryocooler loop operations. Results from testing are shown and compared to verify that liquid nitrogen and liquid oxygen tests yield similar system responses, and that nitrogen can be used as a substitute for oxygen in developmental tests at cryogenic temperatures.

Cryogenic Fluid Management↗
NASA NTRSDate not supplied

Cryogenic Fluid Management for the Artemis Program and Beyond

NASA is endeavoring on an ambitious return to the Moon and eventually on to Mars through the Artemis Program leveraging innovative technologies to establish sustainable exploration architectures collaborating with US commercial and international partners [1]. Future NASA architectures have baselined cryogenic propulsion systems to support lunar missions and ultimately future missions to Mars. NASA has been investing in maturing CFM active and passive storage, transfer, and gauging technologies over the last decade plus primarily focused on ground development with a few small-scale microgravity fluid experiments. Recently, NASA created a Cryogenic Fluid Management (CFM) Technology Roadmap identifying the critical gaps requiring further development to reach a technology readiness level (TRL) of 6 prior to infusion to flight applications. To address the technology gaps the Space Technology Mission Directorate (STMD) strategically plans to invest in a diversified CFM portfolio approach through ground and flight demonstrations, collaborating with international partners, and leveraging Public Private Partnerships (PPPs) opportunities with US industry through the Tipping Point and Announcement of Collaborative Opportunities (ACO) solicitations. Once proven, these system capabilities will enable the high performing cryogenic propellant systems needed for the Artemis Program and beyond.

Cryogenic Fluid Management↗