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FO Technologies and Artemis II

How Flight Opportunities research contributed to humanity's return to the Moon.

Created: Session 41, 2026-04-07
Last updated: Session 68, 2026-04-07

At a Glance

Artemis II launched April 1, 2026 from KSC — the first crewed mission beyond LEO since Apollo 17 (December 1972). Crew: NASA astronauts Reid Wiseman, Victor Glover, Christina Koch, and CSA astronaut Jeremy Hansen. The 10-day lunar flyby mission set the farthest human spaceflight distance record on April 6 (248,655 miles from Earth, eclipsing Apollo 13's 1970 record). Splashdown scheduled April 10, 2026 off San Diego.

FO's contribution to Artemis II spans three tiers:

Tier Category FO Technologies Confidence
1 Hardware on the mission Airborne Systems CPAS parachutes Confirmed
1 Hardware on the mission (probable) ADA Technologies FWM fire extinguisher Suggestive
2 Data informing ICPS cryogenic design Cryo cluster: Aerospace Corp helium, UF Chung boiloff, Mudawar pool boiling, Purdue Collicott slosh Confirmed (data exists); Suggestive (specific design influence)
3 Broader Artemis pipeline RFMG, Carthage MPG, Wyle Mini OCT, Creare CryoFILL Confirmed (funded for Artemis); not on Artemis II specifically

What's next after Artemis II: Artemis III (mid-2027) was restructured in Feb 2026 to a LEO rendezvous/docking test — no lunar landing. First crewed lunar landing is now Artemis IV (early 2028). See Artemis III Restructuring Impact.

Tier 1: Hardware on Artemis II

Airborne Systems — Orion CPAS Parachute Recovery

Field Value
FO Projects 91422 (Guided Parafoil High Altitude Research), 93997 (GPHAR II)
Period 2013–2016
TRL 4 → 6
Artemis II hardware Capsule Parachute Assembly System (CPAS) — 2 drogue + 3 main parachutes
Contract 80LARC22CA008 — $13.57M (NASA LaRC, 2022–2027)
KB page organizations/airborne-systems.md

Airborne Systems North America (Santa Ana, CA) designed and manufactures the CPAS that will bring the Artemis II crew home. The system deploys sequentially: two Kevlar drogue parachutes stabilize the 10-ton Orion capsule, followed by three ringsail main parachutes (10,000 sq ft each) that slow it to ~17 mph for Pacific splashdown.

FO connection: Airborne Systems' FO project [91422] tested guided ram-air parafoils at 35 km altitude (115,000 ft) using Near Space Corporation's balloon platform. The goal was extending military JPADS airdrop capability from ~25,000 ft to 50,000+ ft. While CPAS uses different parachute architectures (ringsail mains, not ram-air parafoils), the FO work advanced Airborne Systems' engineering expertise in high-altitude, thin-atmosphere decelerator aerodynamics — directly relevant to Orion's re-entry profile where parachutes deploy in near-vacuum conditions.

Artemis track record: CPAS deployed flawlessly on Artemis I (December 2022, uncrewed). Testing ran 2011–2018 at Yuma Proving Ground with active-duty Army Airborne Test Force soldiers.

Confidence: Confirmed — Airborne Systems is the documented CPAS manufacturer, and they conducted FO flights. The technology transfer is at the company/expertise level rather than direct hardware lineage.

ADA Technologies — Fine Water Mist Fire Extinguisher (Probable)

Field Value
FO Project 12180
Period 2011–2014
TRL 4 → 7
Artemis II hardware Orion Portable Fire Extinguisher (unconfirmed)
Orion contracts NNJ15HD46P ($120K) + NNJ16HD31P ($406.8K) — Phase III SBIR for Orion adaptation
KB page organizations/ada-technologies.md

ADA Technologies developed the Fine Water Mist (FWM) Portable Fire Extinguisher, which was deployed on ISS in December 2015 (9 units replacing CO2 extinguishers). ADA received two Phase III SBIR contracts (2015–2017) to adapt FWM for the Orion spacecraft, and a 2018 NTRS paper documents "Orion Portable Fire Extinguisher Performance Testing Against Laptop Li-Ion Battery Fires" (NTRS 20180005251).

FO connection: Direct — FO parabolic flights validated FWM performance in microgravity, advancing it from TRL 4 to 7. The gap from FO validation to ISS deployment was only ~1.5 years.

Confidence: Suggestive — ADA was developing the Orion fire extinguisher as recently as 2018. Whether FWM PFE is the selected fire suppression system aboard Orion for Artemis II cannot be confirmed from available sources. FWM was described as "one of two technologies being considered" for Orion.

Tier 2: Cryogenic Data Informing ICPS Design

The Interim Cryogenic Propulsion Stage (ICPS) — built by ULA, derived from the Delta IV upper stage — is the engine that sent Artemis II's Orion to the Moon. It burns liquid hydrogen (LH2) and liquid oxygen (LOX) through an RL10 engine (24,750 lbs thrust). Critically, it uses helium gas for tank pressurization and engine purge — the exact physics studied across the FO cryogenic cluster.

The Helium Anomaly: Why FO Cryo Research Matters

In February 2026, engineers discovered they could not repressurize the ICPS helium system after a successful wet dress rehearsal. The SLS was rolled back to the VAB for troubleshooting — investigation focused on a filter, quick-disconnect umbilical, or check valve in the helium ground system. The anomaly was resolved (Artemis II launched April 1), but it highlighted that helium management in cryogenic stages remains a live, mission-critical engineering challenge.

The FO cryogenic cluster generated the reduced-gravity experimental data that engineers need to understand how helium behaves inside cryogenic tanks — data that cannot be obtained on the ground where buoyancy masks the physics.

Aerospace Corporation — Helium Subsurface Pressurization

Field Value
FO Project 106642
Period 2021–2025
TRL 5 → 6
PI Samuel Darr (co-I: Jason Hartwig, NASA GRC)
Publication npj Microgravity (Nature), July 2025, DOI: 10.1038/s41526-025-00504-w
KB page organizations/aerospace-corp-cryogenics.md

This FO project investigated the exact physics of helium pressurization in cryogenic tanks — 19 experimental cases of helium injection into liquid nitrogen in reduced gravity. The data shows how warm helium causes propellant evaporation, bubble growth, and ullage pressure changes when buoyancy is absent.

Direct Artemis II relevance: ICPS helium pressurization maintains LOX/LH2 tank structural integrity and ensures propellant flow to the RL10 engine during the trans-lunar injection burn. The Aerospace Corp is also an established Artemis technical support contractor providing independent V&V of ICPS flight software and GNC.

Jason Hartwig (NASA GRC), the co-I, is one of NASA's leading cryogenic propellant management experts. His involvement is the direct infusion mechanism: FO data → Hartwig → Glenn cryogenic systems design for Artemis.

UF Chung — Cryogenic Boiloff and Coatings

Field Value
FO Projects 91356, 106581, 106713, 106616, 89415
Period 2011–2026 (5 FO projects, 15 years)
TRL Various, 4 → 6
PI Jacob Chung (NASA Exceptional Public Service Medal, 2024)
KB page organizations/uf-chung-cryogenics.md

Chung's 30-year NASA cryogenics program has produced foundational data on boiloff reduction, tank chilldown, and surface coatings for cryogenic tanks. His May 2025 zero-G flights tested 4 coating materials. This data informs how ICPS LOX/LH2 boiloff behaves during countdown holds and coast phases.

Mudawar/Purdue — Cryogenic Pool Boiling

Field Value
FO Projects 184140 + 3 others
ISS Experiment FBCE (Flow Boiling and Condensation Experiment) — completed Q3 2024
PI Issam Mudawar (Purdue)
Publications 3 new papers in Int'l J. Heat & Mass Transfer 2025–2026
KB page organizations/mudawar-thermal.md

Mudawar's combined FO parabolic + FBCE ISS dataset is the most comprehensive microgravity cryogenic heat transfer dataset ever assembled. Pool boiling behavior (nucleation, critical heat flux, film boiling) changes fundamentally without gravity — this data is essential for predicting thermal behavior in any cryogenic stage, including ICPS.

Purdue Collicott — Propellant Slosh Dynamics

Field Value
FO Projects 106651, 106602, 106630, 106718 + 5 more
Period 2018–2027 (9 FO projects for PI Collicott, 15 total Purdue)
PI Steven Collicott (Purdue)
KB page organizations/purdue-collicott-slosh.md

Collicott's 9 FO projects study propellant sloshing in reduced gravity — how liquid fuel moves inside tanks during maneuvers. Slosh is a direct operational concern for any cryogenic stage performing burns (ICPS trans-lunar injection, Orion service propulsion system). One project (106582) connects to GRC's RFMG Moon mission via Surface Evolver modeling.

Synthesis: The Cryo Cluster as Artemis Data Foundation

The FO cryogenic cluster — 30+ projects across 12+ researchers (see cryogenic-cluster.md) — didn't put specific hardware on Artemis II. Instead, it produced the experimental data that underpins ICPS cryogenic design confidence. Ground testing can't replicate how helium pressurization, boiloff, sloshing, and heat transfer behave in reduced gravity. FO parabolic flights are the only affordable platform for generating this data before committing to orbital-class hardware.

The February 2026 helium anomaly — while ultimately a ground equipment issue — underscored that cryogenic propellant management remains a live, unsolved engineering domain where FO's data contributions have direct mission relevance.

Tier 3: Broader Artemis Pipeline (Not on Artemis II)

These FO technologies are funded for Artemis but target later missions:

Technology FO Project(s) Artemis Target Status KB Page
RFMG (RF Mass Gauge) 12177, 91405 Already flew on IM-1 (Feb 2024); AIAA SciTech 2025 paper published Confirmed lunar deployment grc-cryogenic-power.md
MPG (Modal Propellant Gauging) 94131 + 7 more IM-3 NOVA-C, Orion OMS, Gateway, on-orbit refueling Selected for IM-3; Airbus commercializing carthage-college-mpg.md
Mini OCT (Retinal Imaging) FO precursor 12464 157621: TRL 5→9 for Artemis lunar missions (2022–2029) Active development at JSC wyle-oct-sans.md
CryoFILL (Creare cryocooler) FO 155234 Integrated into CryoFILL lunar ISRU refueling system (Sep 2025) Confirmed integration creare-lad.md
FSP radiator (heat pipes) FO 12184, 93976 Fission Surface Power lunar demo ~2028 Active TDM program grc-cryogenic-power.md

What's NOT on Artemis II from FO

  • Heat shield: Orion uses Avcoat ablative TPS (experienced charring issues on Artemis I; blocks redesigned for Artemis II). No FO connection — HeetShield's FO project is HIAD TPS for Mars entry.
  • NDL: On CLPS lunar landers, not Artemis/SLS/Orion.
  • CDI/DSOC: On Psyche spacecraft, not Artemis.
  • Honeywell GNC: Full navigation and guidance for SLS/Orion, but no FO connection found.

Time Dimension

FO Project FO Flight Test Artemis II Role Gap (years)
Airborne Systems CPAS 2013–2016 Parachute recovery (Apr 10, 2026) 10 years
ADA FWM PFE 2011–2014 Orion fire extinguisher (if confirmed) 12 years
Aerospace Corp He pressurization 2021–2025 ICPS design data 1 year
UF Chung cryo 2011–2026 ICPS boiloff data ongoing
Mudawar/Purdue boiling 2022–2025 Cryo heat transfer data 1 year

The hardware contributions (Tier 1) show the characteristic ~10-year FO maturation gap. The data contributions (Tier 2) are more recent — the cryo cluster is still actively producing data, meaning Artemis II is being supported by concurrent FO research, not just legacy results.

Key Takeaway

FO's Artemis II contribution is primarily a data story, not a hardware story. Unlike the Moon (where 7 specific FO-tested instruments landed) or Mars (where G-FOLD algorithms guided Perseverance), Artemis II's FO connection runs through the cryogenic research cluster that generated the reduced-gravity physics data underpinning ICPS design. The one confirmed hardware element — Airborne Systems CPAS — traces to FO at the company/expertise level rather than direct technology transfer.

This pattern makes sense: Artemis II is a crewed vehicle built by prime contractors (Lockheed, Boeing/ULA, Airbus). FO's role in the crewed architecture is enabling the science that validates the design rather than contributing individual instruments. The 30+ FO cryo projects are the experimental data layer that gives engineers confidence that helium pressurization, propellant boiloff, and sloshing will behave as predicted when four humans are aboard.

Cross-References