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GRC Cryogenic & Power Technology FO Cluster

Multiple FO Projects | Lead Org: Glenn Research Center | Last updated: Session 88, 2026-04-07

Summary

Glenn Research Center runs two parallel FO arcs that together form a critical supply chain for NASA's Fission Surface Power (FSP) program and cryogenic propellant management. PI Marc Gibson leads the FSP thermal arc (heat pipes + heat spreader); PI Gregory Zimmerli leads the RF mass gauging arc. These are tightly coupled: FSP needs cryogenic propellant for surface operations, and the RF gauge technology also found its way into the Robotic Refueling Mission-3 (RRM3) ISS demo, into Perseverance CFM analysis, and onto the lunar surface aboard IM-1 Odysseus (Feb 22, 2024).

Session 23 update — RFMG LUNAR MISSION CONFIRMED: RFMG flew as a NASA payload on Intuitive Machines IM-1 "Odysseus" Nova-C lander. It measured propellant levels throughout the mission: tank loading, translunar coast, lunar orbit insertion, powered descent, and post-landing on the Moon. Results published in NTRS 20240014338 ("Results from the Radio Frequency Mass Gauge Technology Demonstration on the Intuitive Machines Nova-C Lunar Lander"). RFMG is one of 7 FO technologies confirmed on the lunar surface — see FO Technologies on the Moon.

Session 40 update — RFMG AIAA PAPER + ARTEMIS II CONTEXT: - AIAA SciTech 2025 paper (DOI: 10.2514/6.2025-0959): "Results From the Radio Frequency Mass Gauge Technology Demonstration on the Intuitive Machines Nova-C Lunar Lander" — first peer-reviewed publication of IM-1 RFMG results, confirming propellant measurements from pad through lunar surface. - Artemis II launched April 1, 2026 from KSC. 10-day crewed lunar flyby mission with SLS/Orion. ICPS (Interim Cryogenic Propulsion Stage) uses helium pressurization of LOX/LH2 — the same physics studied in FO cryogenic cluster projects ([106642], Chung/Darr work). Artemis II splashdown April 10, 2026. - CryoFILL integration (Sep 24, 2025): NASA Glenn integrated a Creare LLC flight-like cryocooler into the CryoFILL (Cryogenic Fluid In-Situ Liquefaction for Landers) test system at Creek Road Cryogenics Complex. CryoFILL demonstrates how lunar water ice oxygen can be condensed into liquid form — a direct path from FO-validated cryo tech to Artemis ISRU. See Creare LAD for Creare's FO connection.

Arc 1: FSP Radiator Thermal Technology (PI Marc A. Gibson)

12184 Heat Pipe Limits in Reduced Gravity

  • TRL: 4→6 | Period: 2011-09-07 to 2015-05-07
  • Views: 915
  • Outcomes: Advanced From 2011-09-01 (Other) → Advanced To 2013-08-01 (Other)
  • TX: TX03.1.4 Dynamic Energy Conversion (confirmed match)

Description: Titanium–water heat pipes for FSP radiators operating as thermosyphons (no wick, gravity-driven). The heat pipes must work vertically on the lunar surface. FO flights provided data on gravity-dependent vapor condensation behavior. The description explicitly names "Fission Power Systems (FPS)" as the target.

Significance: Marc Gibson is the lead GRC engineer for the entire Kilopower → FSP radiator development path. This FO project provided the microgravity and reduced-gravity data needed to qualify the radiator design. Without knowing heat pipe limits at 1/6 g, the FSP radiator cannot be confidently sized.

93976 Radial Core Heat Spreader

  • TRL: 5→6 | Period: 2014-09-01 to 2015-09-30
  • Views: 1,044
  • TX: TX03.1.4 Dynamic Energy Conversion

Description: Heat spreader for free-piston Stirling convertors in FSP. The Stirling convertor converts nuclear heat to electricity; the heat spreader distributes heat uniformly to the hot end. This was a 1-year focused test to advance from TRL 5 to TRL 6.

Significance: Same PI (Marc Gibson), complementary to [12184]. Both projects are directly in the FSP supply chain already documented in kb-techport-only/topics/fission-surface-power.md. Together they show that GRC used FO for two specific thermal subsystems that feed the Kilopower/FSP program timeline.

FSP supply chain link: FSP (105671) is the active TDM program targeting lunar flight demo in 2028. These FO projects fed that development path ~6–10 years earlier.

Arc 2: RF Propellant Mass Gauging (PI Gregory A. Zimmerli)

12177 Radio Frequency Mass Gauge on Parabolic

  • TRL: 4→6 | Period: 2011-08-01 to 2014-08-31
  • Views: 1,111
  • Outcomes: Advanced To 2013-09-01 (Other) + Advanced To 2020-06-29 (Other)
  • TX: TX01.1.3 Cryogenic Propulsion (confirmed match)

Description: RF gauging uses tank resonance modes to measure propellant quantity independent of liquid location. Critical for low-g environments where settled-gauging fails. This was the parabolic flight validation of the technique.

Downstream connections (from library items): 1. Perseverance CFM presentation ("kortes_perseverancecfm_tagged.pdf") — the cryogenic fluid management analysis for Mars 2020 cited this work 2. RRM3 overview presentation — Robotic Refueling Mission-3 (ISS, launched Dec 2018) included an RF mass gauging experiment. The second "Advanced To" outcome in June 2020 (after RRM3 concluded) confirms this connection.

91405 RF Gauging on sRLV (Masten Xaero LOX tank)

  • TRL: 4→6 | Period: 2011-11-04 to 2020-09-30
  • Views: 674
  • TX: TX01.1.3 Cryogenic Propulsion

Description: Evolved test: antenna installed inside the Masten Xaero LOX tank. Instead of parabolic approximation, this gauged an actual cryogenic tank on a flying sRLV. Data compared to Masten's own LOX quantity estimates. This is a direct test-range-to-vehicle integration.

Library: Links to APS March 2020 presentation on "Propellant Quantity Gauging in Microgravity Using Radio Frequency Tank Modes."

Significance: The 9-year span (2011–2020) of this FO project is the longest in the GRC cluster. RF gauging went from parabolic proof-of-concept → ISS RRM3 demonstration → APS publication → cited in Perseverance CFM → lunar surface on IM-1 (Feb 2024). This is one of the most mature FO technologies in the portfolio, with confirmed deployment on ISS, Mars (CFM analysis), and Moon.

Pattern: GRC as FSP/Cryo Supply Chain

GRC uses FO systematically for thermal and propulsion infrastructure that feeds the Kilopower/FSP program and cryogenic propellant management research. Key observations:

  1. Same PIs across multiple FO projects — Gibson and Zimmerli are GRC leads who ran FO projects over 4–10 year spans, not one-off tests
  2. Two "Advanced To" outcomes on RF gauging — rare in the FO portfolio; suggests the technology was explicitly tracked and advanced by program managers twice
  3. Cross-mission utility — RF gauging went to both RRM3 (ISS) and Perseverance CFM analysis — it's a foundational measurement technique
  4. FSP supply chain density — between SBIR suppliers (documented in fission-surface-power.md) and these FO projects, GRC is the nucleus of FSP thermal development

Base rate contribution: 4 GRC FO projects → 4 with confirmed/strong downstream connections = 100% rate for this specific cluster. This is not the norm — GRC FSP/cryo work is specifically well-connected because FSP is an active funded program with a clear 2028 target.

Other GRC FO Projects (Context)

GRC runs several fundamental microgravity fluid/heat research projects that are less directly connected to specific missions:

  • 91346 MFEST multi-phase flow (JSC-led but GRC-adjacent): TRL 5→7, two-phase thermal control; PI Kathryn Hurlbert; Advanced To 2013 → ISS ECLSS active thermal control interest
  • 91381 EHeM Heat Melt Compactor (TRL 4→6): water reclamation from trash, ECLSS connection
  • 106735 ARCTIC cryogenic chilldown (TRL 4→6): cryogenic tank fill/transfer data
  • 91423 In-Flight Lab Analysis (TRL 4→4): biomedical point-of-care, no TRL advance
  • 12250 fNIRS cognitive assessment (TRL 4→6): crew cognitive monitoring
  • 106742 Material Flammability in Lunar Gravity (TRL 4→6): fire safety data for Moon/Mars
  • 155242/158658 Ultrasonic Soil Fluidization (TRL 4→6): extraterrestrial mining/drilling tools

Most of these are research maturation projects: they generate data and publications but don't have clear deployment paths. ARCTIC and MFEST have the strongest downstream connections (Artemis cryogenic propellant management).

Session 58 Update (2026-04-07)

FSP Timeline Slipped: 2028 → 2030

SIGNIFICANT CHANGE: The FSP lunar flight demo target has shifted from 2028 to 2030. A White House Executive Order now calls for a lunar surface reactor "ready for launch by 2030." NASA and DOE signed a renewed MOU advancing nuclear reactors on the Moon. The original 2026 target (first Trump admin) → 2028 (Phase 1 contracts) → 2030 (current EO) reflects a 4-year slip from initial ambition.

Key developments: - Phase 1A Extension (Jan 2025): Added a risk reduction testbed to develop a space nuclear power conversion system - Lockheed Martin FSP: Developing modular reactor systems (5-10 kW single habitat → 100 kW larger ops) using Brayton engine technology - Second Draft AFPP expected on SAM.gov in early 2026 (Final AFPP release anticipated) - 40 kW minimum target — enough for 30 households continuously for 10 years

Impact on GRC FO arc: Gibson's FSP radiator heat pipes ([12184], [93976]) remain in the FSP supply chain, but the delayed timeline means these FO technologies from 2011-2015 are now 15+ years ahead of the flight demo they feed. The physics doesn't change — heat pipe data is still valid — but the program context has shifted significantly.

Session 88 Update (2026-04-07)

FSP Upgraded to 100 kWe — Phase 1 Complete, Competitive Procurement Imminent

SIGNIFICANT CHANGE: FSP has undergone a major power upgrade from 40 kWe to 100 kWe using a closed Brayton cycle power conversion system. Phase 1 studies by all three teams are now complete, and NASA is finalizing the Final RFP (expected early 2026) for competitive procurement of flight-ready hardware.

The three teams and their technical approaches: 1. Lockheed Martin (with BWX Technologies + Creare) — gas-cooled, high-reliability cooling, potential in-situ regolith shielding. NOTE: Creare is an FO company — see creare-lad.md. Their cryogenic expertise (LAD, CryoFILL) now extends to nuclear power cooling. 2. Westinghouse (with Aerojet Rocketdyne) — eVinci heat-pipe-cooled microreactor, very few moving parts. NOTE: Heat-pipe approach connects directly to Gibson's FO projects [12184] and [93976] — the same physics. 3. IX (X-energy + Intuitive Machines, with Maxar + Boeing) — TRISO-X fuel, helium-xenon Brayton cycle

Reactor must be launch-ready by Q1 FY2030 (~late CY2029). Designers can assume a heavy-class lander carrying up to 15 metric tons. The reactor will complete a 1-year demo followed by 9 operational years.

FO connections strengthened: (a) Creare — already tracked as FO company for cryogenic LAD — is now on the Lockheed FSP team. (b) Westinghouse's heat-pipe approach is exactly what Gibson tested in FO projects [12184]/[93976]. The FO data is 10+ years old but directly relevant to the 2030 flight unit.

Artemis II — Day 7 of 10, In-Flight

Artemis II launched April 1, 2026 from KSC. Currently on Flight Day 7 (April 7). Key mission events: - Lunar flyby completed — broke Apollo 13 record for distance from Earth - ICPS manual piloting demonstration: Crew conducted manual piloting using ICPS as a docking target, followed by automated departure burn. ICPS then performed its own disposal burn and re-entered Earth's atmosphere over remote Pacific. - Splashdown targeted April 10 at 8:07 PM PT in Pacific near San Diego - USS John P. Murtha assigned for recovery

The ICPS (Interim Cryogenic Propulsion Stage) used LOX/LH2 — the same cryogenic physics studied in GRC's FO cluster projects ([106642], Chung/Darr work). ICPS has already been disposed, so any cryogenic performance data would come from NASA post-mission reports. No FO technology performance data available yet.

RFMG — No New Publications

No new RFMG publications since the AIAA SciTech 2025 paper (DOI: 10.2514/6.2025-0959). RFMG remains one of the most mature FO technologies: parabolic flights → ISS RRM3 → Mars 2020 CFM → IM-1 lunar surface. NASA's broader CFM portfolio encompasses 24 development activities for Artemis — RFMG is one of the anchors.

Investigated: 2026-04-06, Session 12
Confidence: RF gauging → RRM3 and Perseverance CFM (confirmed, via document links). FSP heat pipes/spreader (confirmed via description + PI identity). ARCTIC → Artemis cryo (suggestive). Other GRC projects: research maturation only.