Browsing by Author "Quinn, Gregory"
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Item Advanced Space Suit PLSS 2.0 Cooling Loop EValuation and PLSS 2.5 Recommendations(46th International Conference on Environmental Systems, 2016-07-10) Steele, John; Quinn, Gregory; Watts, Carly; Makinen, Janice; Campbell, Colin; Westheimer, DavidFrom 2012 to 2015 The NASA/JSC AdvSS (Advanced Space Suit) PLSS (Primary Life Support Subsystem) team, with support from UTC Aerospace Systems, performed the build-up, packaging and testing of PLSS 2.0. A key aspect of that testing was the evaluation of the long-term health of the water cooling circuit and the interfacing components. Intermittent and end-of-test water, residue and hardware analyses provided valuable information on the status of the water cooling circuit, and the approaches that would be necessary to enhance water cooling circuit health in the future. The evaluated data has been consolidated, interpreted and woven into an action plan for the maintenance of water cooling circuit health for the planned FY (fiscal year) 2016 through FY 2018 PLSS 2.5 testing. This paper provides an overview of the PLSS 2.0 water cooling circuit findings and the associated steps to be taken in that regard for the PLSS 2.5 testing.Item Astronaut Smart Glove: A Human-Machine Interface For the Exploration of the Moon, Mars, and Beyond(2020 International Conference on Environmental Systems, 2020-07-31) Lee, Pascal; McKay, Christopher; Quinn, Gregory; Chase, Tom; Tamuly, Moina; Tagestad, Sondre; Pettersen, Haakon; Arveng, Magnus; Oygard, Frank; Dotson, Brandon; Schutt, John; Rohrig, JakeAstronauts exploring the Moon, Mars and beyond will be assisted by robotic systems to render their work more efficient, productive, and safe. Among these, unmanned aerial vehicles (UAVs) or drones (airplanes, rotorcraft, or gas thrustered flyers), hold great promise, as they may assist astronauts in a wide range of science and exploration activities. UAV operations, however, are presently demanding tasks. Conventional drone interfaces require significant dexterity and situational awareness to enable subtle and rapid real-time control inputs. Such interfacing would be inadequate if the drone operator were wearing a pressurized spacesuit, as the latter fundamentally limits an astronautâs ability to perceive and interact with the extra-vehicular environment. During the 2019 campaign of the NASA Haughton-Mars Project (HMP) on Devon Island, High Arctic, an established Moon and Mars analog field research site, a novel concept for a wireless human-machine interface (HMI) called âAstronaut Smart Gloveâ(ASG) was field-tested in partially simulated, unpressurized astronaut extra-vehicular activity (EVA). The ASG, along with its compact in-suit augmented reality (AR) head-mounted display (HMD), were evaluated for their potential adequacy in allowing UAVs to be operated by a suited astronaut. The ASG showed promise in being able to address both the dexterity and situational awareness limitations of spacesuits by allowing an astronaut to operate single-handedly, within conservative work envelopes for EVA hand operations, a UAV via low amplitude, intuitive gestures of one hand, and in head-up mode via direct visual contact with the UAV and/or in First Person View (FPV) using the AR display. While the ASG offers the prospect of enabling a wide range of robotic operations in future human exploration, further studies are needed to understand better the systemâs potential limitations, in particular higher fidelity tests using a pressurized suit, and field demonstrations of end-to-end EVA surface science and exploration operations.Item Continued Development of Compact Multi-gas Monitor for Life Support Systems Control in Space(46th International Conference on Environmental Systems, 2016-07-10) Alonso, Jesus Delgado; Chullen, Cinda; Quinn, Gregory; Berry, David; Dicarmine, PaulMiniature optical gas sensors based on luminescent materials have shown great potential as alternatives to NIR-based gas sensor systems for the Portable Life Support System (PLSS). The unique capability of luminescent sensors for carbon dioxide and oxygen monitoring under wet conditions has been reported, as has the fast recovery of humidity sensors after long periods of being wet. Lower volume and power requirements are also potential advantages over both traditional and advanced non-dispersive infrared (NDIR) gas sensors, which have so far shown longer life than luminescent sensors. In this paper we present the most recent results in the development and analytical validation of a compact multi-gas sensor unit based on luminescent sensors for the PLSS. Results of extensive testing are presented, including studies conducted in Intelligent Optical Systems laboratories, and a United Technologies Corporation Aerospace Systems (UTC) laboratory. The potential of this sensor technology for gas monitoring in PLSSs and other life support systems, and the advantages and limitations found through detailed sensor validation are discussed.Item Design of a Lithium Chloride Absorber Radiator for Flight Testing on an Extravehicular Mobility Unit(46th International Conference on Environmental Systems, 2016-07-10) Izenson, Michael; Phillips, Scott; Chepko, Ariane; Quinn, Gregory; Steele, John; Bue, GrantThermal control systems for exploration space suits and spacecraft will need to meet critical requirements for water conservation and durability. Spacesuit Evaporator Absorber Radiator (SEAR) technology offers a non-venting thermal control approach. A SEAR system combines a lithium chloride absorber radiator (LCAR) with a spacesuit water membrane evaporator (SWME). To prove operation of a SEAR system in a space environment, we are currently designing and demonstrating a subscale SEAR system that is designed to meet requirements for a flight test as part of an EMU on the International Space Station. The flight-test system must meet critical requirements for safety, impact resistance, ease of use, durability/lifetime, and simplicity of operation. To meet these requirements, we have developed and demonstrated a new design for the LCAR housing that increases durability dramatically compared to prior prototypes. We have also developed new concepts for integrating the LCAR with the EMU that use existing spacesuit interface components. The overall SEAR system includes controls that will enable operation during EVA with minimal direct intervention by the crew. We have formulated plans for controlling water chemistry to prevent corrosion and growth of microbes in the system. Finally, we have developed a concept for regenerating the LCAR on orbit using existing ISS experimental accommodations. The regeneration system will enable multiple absorption/regeneration cycles while on orbit while also demonstrating critical features of SEAR operation in microgravity.Item Development and Test of a Spacesuit Informatics System for Moon, Mars, and Further Deep-Space Exploration(51st International Conference on Environmental Systems, 7/10/2022) Rohrig, Jake; Himmelmann, Ashley; Torralba, Monica; Quinn, Gregory; Lee, Pascal; Dalal, Sawan; Arveng, Magnus; Tamuly, Moina; Lysberg, JosteinToday, crewmembers use paper cuff checklists, a 12-digit LED display, and oversight from Mission Control to attain mission situational awareness. As humans explore deeper into space and expand our presence outside of low Earth orbit, the demand for on-location situational awareness independent of Earth operations grows substantially. In the case of Mars exploration, real-time oversight and communication from Mission Control are not possible. These future crews will need to have cognizance of suit and consumable status; location, terrain, and heading for navigation; personal and team biometric information; access to procedures, checklists, and data; and the ability to review and record field notes, among other capabilities. Collins Aerospace is developing an Information Technologies and Informatics Subsystem (IT IS) that includes these features to provide intuitive, Earth-independent situational awareness to astronauts. The IT IS uses an in-helmet head-up display (HUD) and a natural language interface (NLI) for instinctive, convenient interaction between the crewmember and the spacesuit. Human-robotic collaboration capabilities were also added to aid in exploration and sample collection. By combining Ntentionďż˝s Interaction Framework and associated Astronaut Smart Glove (ASG) with the Collinsďż˝ IT IS, a new multi-modal Astronaut Interaction System (AIS) was generated that allows crewmembers to use robotic assets through verbal commands and physical gestures. During the 2021 Haughton Mars Project (HMP) field campaign, these systems were integrated into an analog spacesuit and tested in a relevant environment. This paper reports on the need for an informatics suite and interaction system, providing a brief review of informatics testing at HMP that preceded the 2021 field tests, a statement of the 2021 HMP test objectives, a description of the technologies enabling the fielded solution, and the results of the field tests.Item Development of Lithium Chloride Absorber Radiator for Flight Demonstration(47th International Conference on Environmental Systems, 2017-07-16) Izenson, Michael; Phillips, Scott; Chepko, Ariane; Daines, Gregory; Quinn, Gregory; Steele, JohnWater conservation is an essential requirement for future exploration space suits. Lithium Chloride Absorber Radiator (LCAR) technology has been developed to meet this requirement by rejecting heat without venting water from a Spacesuit Evaporator Absorber Radiator (SEAR) subsystem. Prototype LCARs have been developed and optimized through numerous thermal vacuum tests that simulate operation in space. An actual flight demonstration is a key next step needed to advance the technology readiness level of the LCAR and make it available for future exploration missions. This paper describes on-going work to enable a flight test of an LCAR as part of a subscale SEAR system that uses a space station EMU as a test bed. The twin goals of this program are to develop a prototype LCAR design that can integrate with an EMU using existing flight-qualified hardware, and to develop and demonstrate a regeneration system that is suitable for use on the space station. Significant advances in LCAR technology include: (1) an optimized design of the absorber bed enables heat rejection at higher temperature and higher rates than prior LCAR designs; (2) measurement of improved heat rejection performance of the optimized LCAR panel through several absorption/regeneration cycles; (3) demonstration of a suitable coolant/refrigerant for use in the SEAR system; (4) demonstration that the prototype panel survives impact loads required for operation on the space station without compromising containment of LiCl / water solution; and (5) demonstration that the LCARâs thermal performance is essentially unaffected after suffering a design-basis impact.Item Evolution of an Additive Manufactured Heat Exchanger for PLSS 2.5(48th International Conference on Environmental Systems, 2018-07-08) Quinn, Gregory; Strange, Jeremy; Zaffetti, MarkThe next generation of extravehicular mobility unit (EMU) will require lightweight, high performance components in order to minimize the mass, volume and power of its portable life support system (PLSS). One component under development for this application is a gas / liquid heat exchanger that will cool the breathing gas delivered to the crewmemberâs helmet. This technology has been gradually matured over the past several years. It started with a vacuum brazed compact heat exchanger used in NASAâs PLSS 2.0 and continued with two selective laser sintered heat exchangers, which were built using Inconel and titanium. This paper describes how the use of additive manufacturing has reduced weight, volume, cost, and manufacturing lead time of this line of heat exchangers. It also shows how performance test results have good agreement with the computational models.Item High-Capacity Spacesuit Evaporator Absorber Radiator (SEAR)(45th International Conference on Environmental Systems, 2015-07-12) Izenson, Michael G.; Chen, Weibo; Phillips, Scott; Chepko, Ariane; Bue, Grant; Quinn, GregoryFuture human space exploration missions will require advanced life support technology that can operate across a wide range of applications and environments. Thermal control systems for space suits and spacecraft will need to meet critical requirements for water conservation and multifunctional operation. This paper describes a Spacesuit Evaporator Absorber Radiator (SEAR) that has been designed to meet performance requirements for future life support systems. A SEAR system comprises a lithium chloride absorber radiator (LCAR) for heat rejection coupled with a space water membrane evaporator (SWME) for heat acquisition. SEAR systems provide heat pumping to minimize radiator size, thermal storage to accommodate variable environmental conditions, and water absorption to minimize use of expendables. We have built and tested a flight-like, high-capacity LCAR, demonstrated its performance in thermal vacuum tests, and explored the feasibility of an ISS demonstration test of a SEAR system. The new LCAR design provides the same cooling capability as prior LCAR prototypes while enabling over 30% more heat absorbing capacity and regeneration in only half the time. Studies show that it should be feasible to demonstrate SEAR operation in flight by coupling with an existing EMU on the Space Station.Item Nitrous Oxide Boiler Development for the Dream ChaserÂŽ Spacecraft Thermal Control System(44th International Conference on Environmental Systems, 2014-07-13) Metts, Jonathan G.; Miller, Stephen W.; Johnson, Jeff; Quinn, GregoryThe Dream ChaserÂŽ human spacecraft utilizes excess nitrous oxide propulsion oxidizer as an evaporant to provide heat rejection for the vehicleâs Active Thermal Control System. This capability is provided by a nitrous oxide boiler, currently in development. Performance analysis and test results indicate that a heat exchanger boiling nitrous oxide with a propylene glycol/water coolant fluid can provide the required heat rejection for Dream Chaser while preventing freezing or incomplete phase transition in the boiler unit. Integration of nitrous oxide boiler technology will result in a net system mass savings.Item Performance of a Multifunctional Space Evaporator- Absorber-Radiator (SEAR)(44th International Conference on Environmental Systems, 2014-07-13) Izenson, Michael G.; Chen, Weibo; Phillips, Scott; Chepko, Ariane; Bue, Grant; Quinn, GregoryThe Space Evaporator-Absorber-Radiator (SEAR) is a nonventing thermal control subsystem that combines a Space Water Membrane Evaporator (SWME) with a Lithium Chloride Absorber Radiator (LCAR). The LCAR is a heat pump radiator that absorbs water vapor produced in the SWME. Because of the very low water vapor pressure at equilibrium with lithium chloride solution, the LCAR can absorb water vapor at a temperature considerably higher than the SWME, enabling heat rejection sufficient for most EVA activities by thermal radiation from a relatively small area radiator. Prior SEAR prototypes used a flexible LCAR that was designed to be installed on the outer surface of a portable life support system (PLSS) backpack. This paper describes a SEAR subsystem that incorporates a very compact LCAR. The compact, multifunctional LCAR is built in the form of thin panels that can also serve as the PLSS structural shell. We designed and assembled a 2 ft2 prototype LCAR based on this design and measured its performance in thermal vacuum tests when supplied with water vapor by a SWME. These tests validated our models for SEAR performance and showed that there is enough area available on the PLSS backpack shell to enable rejection of metabolic heat from the LCAR. We used results of these tests to assess future performance potential and suggest approaches for integrating the SEAR system with future space suits.Item Performance of a Nafion Water Vapor Exchanger in an Amine Bed Test Loop(46th International Conference on Environmental Systems, 2016-07-10) Izenson, Michael; Micka, Danny; Quinn, Gregory; Papale, WilliamThermal and environmental control systems for future exploration spacecraft must meet challenging requirements for efficient operation and conservation of resources. Maximizing the use of regenerative systems and conserving water are critical design considerations. This paper presents the results of testing a Nafion-based water vapor exchanger (WVX) in an amine bed test loop under conditions that simulate operation in a spacecraft life support system with a regenerative CO2 removal system. The WVX comprises an innovative assembly of Nafion tubes that achieves high water recovery (80-90%) with very low pressure losses (< 0.5 in. H2O). Nafion is an attractive material for this application because of its very high permeability for water vapor. However, Nafion is sensitive to poisoning by ammonia which is present in trace quantities in the outflow from amine-based CO2 removal beds. We measured the performance of a prototype WVX built by Creare in an amine-bed test loop at UTC Aerospace Systems. We found that water recovery efficiencies for short-duration tests were in the range 80-90%. These data come from tests run with flow rates and humidity levels that simulate the range of possible cabin conditions in future exploration spacecraft. These data are very consistent with the water recovery efficiencies measured in Creareâs laboratories without the amine beds. Pressure drop measurements by UTAS are also consistent with pressure drop data from Creare. These data are also consistent with separate effects tests in which we measured the water permeability of an unstructured Nafion tube bundle exposed to ammonia under accelerated test conditions. The accelerated tests can be used to extrapolate the lifetime of a Nafion WVX when used in conjunction with an amine bed.Item Phase Change Material Heat Sink Flight Experiment Results(47th International Conference on Environmental Systems, 2017-07-16) Quinn, Gregory; Le, Hung; Ahlstrom, Thomas; Sheth, RubikA flight experiment was conducted on the International Space Station (ISS) to prove out operation of a microgravity compatible paraffin wax phase change material (PCM) heat sink. A PCM heat sink can help to reduce the overall mass and volume of future exploration spacecraft thermal control systems (TCS). Vehicles such as the Orion Multipurpose Crew Vehicle can use PCM heat sinks to temporarily store thermal energy during mission phases where the radiators are unavailable or too warm to reject the heat as itâs generated, or sublimating water would require significant expendable mass. The experiment was conducted specifically to prove out a heat sink design that incorporates a novel phase management approach to prevent high pressures and structural deformation that often occur with PCM heat sinks undergoing cyclic operation. The PCM heat sink test article was incorporated into an ISS double EXPRESS rack, where it underwent performance testing and acceptance testing at NASA Johnson Space Center. The experiment was delivered to the ISS on the SpaceX 9 mission in the summer of 2016. It was successfully installed into the ISS and run remotely for several months to exercise the PCM heat sink. Freeze and thaw cycles were conducted with a range of coolant flow rates and heater powers to characterize the performance of the technology with regard to heat storage and wax pressure management. Heat storage performance met the objectives of the tests, but the novel phase management approach had mixed results. Wax cavity pressures remained low in some tests, but not others.Item Phase Change Material Heat Sink for an International Space Station Flight Experiment(45th International Conference on Environmental Systems, 2015-07-12) Quinn, Gregory; Stieber, Jesse; Sheth, Rubik; Ahlstrom, ThomasA flight experiment is being constructed to utilize the persistent microgravity environment of the International Space Station (ISS) to prove out operation of a microgravity compatible phase change material (PCM) heat sink. A PCM heat sink can help to reduce the overall mass and volume of future exploration spacecraft Thermal Control Systems. The program is characterizing a new PCM heat sink that incorporates a novel phase management approach to prevent high pressures and structural deformation that often occur with PCM heat sinks undergoing cyclic operation in microgravity. The PCM unit was made using brazed aluminum construction and will be filled with paraffin wax as the fusible material. It is designed to be installed into a propylene glycol and water cooling loop, with scaling consistent with the conceptual designs for the Orion Multipurpose Crew Vehicle. This paper reports on the construction of the PCM heat sink. The prototype will be tested later on the ground and on orbit via a selfâcontained experiment package developed by NASA Johnson Space Center to operate in an ISS Expedite the Processing of Experiments to the Space Station rack.Item PLSS 2.5 Fan Design and Development(46th International Conference on Environmental Systems, 2016-07-10) Quinn, Gregory; Converse, David; Carra, Michael; Chullen, CindaNASA is building a high-fidelity prototype of an advanced Portable Life Support System (PLSS) as part of the Advanced Exploration Systems Program. This new PLSS, designated as PLSS 2.5, will advance component technologies and systems knowledge to inform a future flight program. The oxygen ventilation loop of its predecessor, PLSS 2.0, is driven by a centrifugal fan developed using specifications from the Constellation Program. PLSS technology and system parameters have matured to the point where the existing fan will not perform adequately for the new prototype. In addition, areas of potential improvement were been identified with the existing fan that could be addressed in a new design. As a result, a new fan was designed and tested for the PLSS 2.5. The PLSS 2.5 fan is a derivative of the one used in PLSS 2.0. It uses the same nonmetallic, canned motor, with a larger volute and impeller to meet the higher pressure drop requirements of the PLSS 2.5 ventilation loop. The larger impeller allows it to operate at rotational speeds that are matched to rolling element bearings, and which create reasonably low impeller tip speeds consistent with prior, oxygen-rated fans. Development of the fan also considered a shrouded impeller design that allows larger clearances for greater oxygen safety, assembly tolerances, particle ingestion, and improved performance. This paper discusses the design, manufacturing and performance testing of the new fans.Item Space Evaporator Absorber Radiator (SEAR) for Thermal Storage on Manned Spacecraft(45th International Conference on Environmental Systems, 2015-07-12) Izenson, Michael G.; Chen, Weibo; Chepko, Ariane; Bue, Grant; Quinn, GregoryFuture manned exploration spacecraft will need to operate in challenging thermal environments. State-of-the-art technology for active thermal control relies on sublimating water ice and venting the vapor overboard in very hot environments, and or heavy phase change material heat exchangers for thermal storage. These approaches can lead to large loss of water and significant mass penalties for the spacecraft. This paper describes an innovative thermal control system that uses a Space Evaporator Absorber Radiator (SEAR) to control spacecraft temperatures in highly variable environments without venting water. SEAR uses heat pumping and energy storage by LiCl/water absorption to enable effective cooling during hot periods and regeneration during cool periods. The LiCl absorber module has the potential to absorb over 500 kJ, compared to phase change heat sink systems that typically achieve ~50 kJ/kg. This paper describes analysis models to predict performance and optimize the size of the SEAR system, estimated size and mass of key components, and an assessment of potential mass savings compared with alternative thermal management approaches. We also describe a concept design for an ISS test package to demonstrate operation of a subscale system in zero gravity.Item Suitport and Tether Operational Simulations for the 2013 Haughton Mars Project(44th International Conference on Environmental Systems, 2014-07-13) Fort, James; Greene, Marc; Quinn, Gregory; Lee, PascalUTC Aerospace Systems participated in the 2013 Haughton Mars Project field studies on Devon Island, Canada by testing a new version of their suitport concept and a novel suit tether system. The suitport concept integrated lessons learned from prior studies and upgraded the user interface to use pneumatic actuation. Pneumatic actuation of the suitport and other minor upgrades were successful in improving the donning and doffing process for most users. The tether system used an external waist bearing hooked to four retractable cables that were anchored in a square pattern to form a work area. These features allowed the test subject to conduct geological work without frequent re-clipping, nor unintended entanglement in the tethers.