Behavior of Lunar Simulants in Reduced Gravity Flights
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1 Robert P. Mueller: Briefing: Feb. 2, 203 Pg. Behavior of Lunar Simulants in Reduced Gravity Flights Effects of Regolith Simulant Properties on an Experiment: ROxygen Phase I Input Hopper Reduced Gravity Flight Houston, Texas, USA Robert P. Mueller, NASA, Kennedy Space Center (KSC), Florida, USA Ivan I. Townsend, QinetiQ North America, KSC, Florida, USA Australian Center for Space Exploration Research (ASCER) Off Earth Mining Forum February 20/2, 203
2 Outline ISRU Oxygen Production ROxygen Phase II System Configuration Regolith Feed System Regolith Input Hopper Design RGF Experiment Configuration RGF Experiment Data JSC-A RGF Experiment Data NU-LHT-2M RGF Experiment Data OB Opportunistic Testing Techniques Flow Effects of Different Simulants Conclusions Q&A Robert P. Mueller: Briefing: Feb. 2, 203 Pg. 2
3 Robert P. Mueller: Briefing: Feb. 2, 203 Pg. 3 ISRU Oxygen Production In-Situ Resource Utilization (ISRU) Mission Consumable Production: Complete Life Support/Extra Vehicular Activity closure for Oxygen (O2) and water (H2O) Regenerate and storage life support and fuel cell power consumables (in conjunction with Life Support and Power) Gases for science and cleaning Propellant production; O2 and methane (CH4) for robotic and human vehicles
4 How Do We Plan To Produce O 2 From Lunar Regolith? Numerous Chemistries Have Been Proposed And Studied Since Apollo. H 2 Reduction of Ilmenite Carbothermal Reduction Hydrogen Extraction Hydrogen Sulfide Reduction Carbochlorination Fluorine Exchange Hydrofluoric Acid Leach Direct Electrolytic Reduction Electrolytic Reduction of Oxide/Caustic Solution Electrolytic Reduction of Oxide/Ionic Liquid Reduction by Lithium or Sodium Reduction by Aluminum Vapor Phase Reduction Ion Separation Source: Eagle Engineering Report: Lunar O2 Pilot Plant Robert P. Mueller: rob.mueller@nasa.gov Briefing: Feb. 2, 203 Pg. 4
5 st Gen ROxygen H 2 Reduction System Field Test Hardware Water Electrolysis Units (2) Two Fluidized H 2 Reduction Reactors - 0 kg/batch each Regolith hopper/auger lift system (2) Water Freezer Hydrogen Tank/Separator Water Tanks (2) Cratos Excavator Gaseous O 2 Storage Ramp to allow Cratos operations (or other small vehicle) Regolith reactor exhaust Water Electrolysis Units (2) Briefing: Feb. 2, 203 Robert P. Mueller: rob.mueller@nasa.gov Pg. 5
6 Robert P. Mueller: Briefing: Feb. 2, 203 Pg. 6 Regolith Feed System Regolith Input Hopper
7 Robert P. Mueller: Briefing: Feb. 2, 203 Pg. 7 Hopper Flow Mock Up: JSC-A The hopper hourglass was constructed from clear acrylic plates and consisted of two inner hopper/outer hopper assemblies mated exit flange to exit flange.
8 RGF REGOLITH FLOW TESTING REDUCED GRAVITY FLIGHT TESTING Robert P. Mueller: Briefing: Feb. 2, 203 Pg. 8 /6G Hopper Flow Testing without flow enhancing assistance
9 RGF REGOLITH FLOW TESTING REDUCED GRAVITY FLIGHT TESTING Hopper Hourglass Assembly Testing on the NASA Reduced Gravity Flight using the hammer flow enhancement method. -Run Video Briefing: Feb. 2, 203 Robert P. Mueller: Pg. 9
10 TIME IN SECONDS RGF REGOLITH FLOW TESTING JSC-A Lunar Simulant JSC-A FLOW CHARACTERISTICS 0 /6 /3 /2 2/3 5/6 /6 /3 /2 GRAVITATIONAL FORCE 2/3 5/6 2 No Assist Side-A No Assistance Side-B Hammer Technique Side-To-Side Shake Technique Side-To-Side & Bounce Techniques Combined Flow characteristics of JSC- A during Earth, Lunar, and Mars gravity force simulations on the C-9 Reduced Gravity Simulator Aircraft October The graph only shows points for the Side-To-Side Shake Technique and the Side-To- Side Shake & Bounce Techniques Combined because there was no data collected at other force levels. Side-B flowed faster than Side-A in each test. The difference in the hoppers is that Side-A has heat conduction fins installed where Side-B does not. Briefing: Feb. 2, 203 Robert P. Mueller: rob.mueller@nasa.gov Pg. 0
11 TIME IN SECONDS RGF REGOLITH FLOW TESTING NULHT-2M Lunar Simulant Robert P. Mueller: Briefing: Feb. 2, 203 Pg / 6 NU-LHT-2M FLOW CHARACTERISTICS / 3 / 2 2/ 3 5/ 6 /6 /3 GRAVITATIONAL FORCE /2 2/3 5/6 2 Hammer Technique Side-To-Side Shake Technique Side-To-Side & Bounce Techniques Combined Bouncing Side A Bouncing Side-B No Assistance Side-A No Assistance Side-B Flow characteristics of NU-LHT-2M lunar simulant during Earth, Lunar, and Mars gravity force simulations on the C- 9 Reduced Gravity Simulator Aircraft October The graph only shows points for the Hammer Technique, Side-To- Side Shake Technique, and the Side-To-Side Shake & Bounce Techniques Combined because there was no data collected at other force levels.
12 TIME IN SECONDS RGF REGOLITH FLOW TESTING OB- Lunar Simulant Robert P. Mueller: Briefing: Feb. 2, 203 Pg / 6 OB- LUNAR SIMULANT FLOW CHARACTERISTICS / 3 / 2 2/ 3 5/ 6 /6 /3 GRAVITATIONAL FORCE /2 2/3 5/6 2 No Assist Side-A No Assistance Side-B Hammer Technique Side- A Side-To-Side Shake Technique Side-A Side-To-Side & Bounce Techniques Combined Hammer Technique Side- B Side-To-Side Shake Technique Side-B Flow characteristics of OB- lunar simulant during Earth, Lunar, and Mars gravity force simulations on the C-9 Reduced Gravity Simulator Aircraft October The graph only shows points for the No Assist Side-A, Hammer Technique Side-A, Hammer Technique Side-B, and the Side-To- Side Shake & Bounce Techniques Combined because there was no data collected at other force levels for that technique
13 Mauna Kea Volcano - Hawaii Robert P. Mueller: rob.mueller@nasa.gov Briefing: Feb. 2, 203 Pg. 3
14 Robert P. Mueller: Briefing: Feb. 2, 203 Pg. 4 Roxygen I at Field Test The NASA ROxygen fluidized bed and auger hydrogen reduction reactor makes oxygen at approximately 660 kg/yr, which is about 2/3 of the scale required for the initial stages of a typical Lunar Outpost to support 4 crew members (000 kg/year).
15 Robert P. Mueller: Briefing: Feb. 2, 203 Pg. 5 Conclusions JSC-A, OB and NU-LHT-2M simulants that flowed through the Roxygen hopper all behaved differently JSC-A flow was intermittent but acceptable (with tapping) at all G levels tested OB and NU-LHT-2M did not flow at reduced gravity and needed flow assistance with a more aggressive bouncing technique (~ 3 Hz) Reduced Gravity Flight was very useful in accelerating development and discovering items needing improvement Opportunistic experiments on board the flight allowed new promising techniques to be developed Availability of various simulants from NASA project collaborations were critical to flying this experiment Thank you! Further analytical techniques are being developed to allow future design methods to evolve
16 Acknowledgements NASA Office of the Chief Technologist (OCT) NASA KSC Surface Systems Office NORCAT OB Simulant Orbitec JSC-A Simulant MSFC / USGS NU-LHT-2M Simulant Kennedy Space Center Prototype Shop JSC Reduced Gravity Flight Office Ellington Field Zero G Corp. KSC Chief Technologist Karen Thompson KSC Leads - Dr. Carlos Calle, Nancy Zeitlin Robert P. Mueller: rob.mueller@nasa.gov Briefing: Feb. 2, 203 Pg. 6
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