Browse Topic: Spacesuits

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Inductive Power Transfer for Spaceflight SystemsTBMG-349138/1/2019
NASA Goddard Space Flight Center has developed technology that uses inductive power transfer (IPT) for wireless power interfaces between spaceflight elements (such as the payload, vehicle, and pad). Current spaceflight systems require traditional hardwire connections for power interfaces. This introduces risk of failure due to such factors as bent pins and contact contamination, as well as other disadvantages.
Bringing a Human Touch to Modern ProstheticsTBMG-324588/1/2018
Amputees often experience the sensation of a “phantom limb”—a feeling that a missing body part is still there. That sensory illusion is closer to becoming a reality thanks to a team of engineers at Johns Hopkins University that have created an electronic skin. When layered on top of prosthetic hands, this e-dermis brings back a real sense of touch through the fingertips.
Polyimide Aerogels with Three-Dimensional Cross-Linked StructureTBMG-251708/1/2016
NASA-developed polyimide aerogels are 500 times stronger than conventional silica aerogels. The innovative aerogels represent a revolutionary advance over fragile silica aerogels because they are highly flexible and foldable in thin film form. As a thin film, they can be used to insulate industrial pipelines, automotive shields, and temporary housing structures, and can be used within protective clothing such as firefighting jackets, space suits, and parkas. As a thicker part, they can be easily molded to a shape, or sanded and machined to provide insulation as well as mechanical support. No other aerogel possesses the compressive and tensile strength of the NASA innovation while still retaining its ability to be flexibly folded to contour to whatever shape is needed.
Suiting Up for the FutureTBMG-252328/1/2016
NASA is developing the next generation of suit technologies that will enable deep-space exploration by incorporating advancements such as regenerable carbon dioxide removal systems and water evaporation systems that more efficiently provide crewmembers with core necessities such as breathing air and temperature regulation. Mobility and fit of a pressurized suit are extremely important in keeping astronauts productive, so NASA is focusing on spacesuit designs to help crews work more efficiently and safely during spacewalks.
Spacesuit Glove Cut/Damage Warning SystemTBMG-2328211/1/2015
Current spacesuit gloves used by astronauts on the International Space Station (ISS) have sustained cuts during extravehicular activities (EVAs) due to sharp edges and burrs, possibly on damaged ISS handrails. A warning system in the glove would aid in identifying the location of sharp objects and the extent of damage to the glove. This work investigated various e-textile and flexible circuit technologies to determine the best ones for creating a glove cut/damage warning system for integration into a spacesuit glove.
Lightweight, Flexible, Freezable Heat Pump/Radiator for EVA SuitsTBMG-203058/1/2014
For space exploration missions that may require extended stays and extensive extra-vehicular activity (EVA) operations, the temperature control system must be lightweight, rugged, non-venting, and repairable in space.
Advanced Hybrid Spacesuit Concept Featuring Integrated Open Loop and Closed Loop Ventilation SystemsTBMG-1875412/1/2013
A document discusses the design and prototype of an advanced spacesuit concept that integrates the capability to function seamlessly with multiple ventilation system approaches. Traditionally, spacesuits are designed to operate both dependently and independently of a host vehicle environment control and life support system (ECLSS). Spacesuits that operate independent of vehicle-provided ECLSS services must do so with equipment selfcontained within or on the spacesuit. Suits that are dependent on vehicle-provided consumables must remain physically connected to and integrated with the vehicle to operate properly.
Video Wall Improves CollaborationTBMG-1755710/1/2013
The renovated Payload Operations Integration Center, part of the Huntsville, AL-based Marshall Space Flight Center, features a new video wall. The wall includes a 2 × 12 array of monitors that uses RGB Spectrum’s OmniWall 32 Display Processor to route and display up to 32 input signals. The processor expands the ability of operators to share information in real time, such as live video feeds, diagrams, photographs, results of experiments, and information on power usage.
Spacesuit Simulator Meets NASA Training NeedsTBMG-1755610/1/2013
Aurora Flight Sciences delivered a completed Space Suit Simulator (S3) to NASA following the successful completion of a Phase II Small Business Innovation Research (SBIR) effort.
Li-Ion Battery and Supercapacitor Hybrid Design for Long Extravehicular ActivitiesTBMG-171829/1/2013
With the need for long periods of extravehicular activities (EVAs) on the Moon or Mars or a near-asteroid, the need for long-performance batteries has increased significantly. The energy requirements for the EVA suit, as well as surface systems such as rovers, have increased significantly due to the number of applications they need to power at the same time. However, even with the best state-of-the-art Li-ion batteries, it is not possible to power the suit or the rovers for the extended period of performance. Carrying a charging system along with the batteries makes it cumbersome and requires a self-contained power source for the charging system that is usually not possible. An innovative method to charge and use the Li-ion batteries for long periods seems to be necessary and hence, with the advent of the Li-ion supercapacitors, a method has been developed to extend the performance period of the Li-ion power system for future exploration applications.
Spectroscopic Determination of Trace Contaminants in High-Purity OxygenTBMG-169748/1/2013
Oxygen used for extravehicular activities (EVAs) must be free of contaminants because a difference in a few tenths of a percent of argon or nitrogen content can mean significant reduction in available EVA time. These inert gases build up in the extravehicular mobility unit because they are not metabolized or scrubbed from the atmosphere. A prototype optical emission technique capable of detecting argon and nitrogen below 0.1% in oxygen has been developed. This instrument uses a glow discharge in reduced-pressure gas to produce atomic emission from the species present. Because the atomic emission lines from oxygen, nitrogen, and argon are discrete, and in many cases well-separated, trace amounts of argon and nitrogen can be detected in the ultraviolet and visible spectrum. This is a straightforward, direct measurement of the target contaminants, and may lend itself to a device capable of on-orbit verification of oxygen purity.
Hollow-Fiber Spacesuit Water Membrane EvaporatorTBMG-167897/1/2013
The hollow-fiber spacesuit water membrane evaporator (HoFi SWME) is being developed to perform the thermal control function for advanced spacesuits and spacecraft to take advantage of recent advances in micropore membrane technology in providing a robust, heat-rejection device that is less sensitive to contamination than is the sublimator. After recent contamination tests, a commercial-off- the-shelf (COTS) micro porous hollow-fiber membrane was selected for prototype development as the most suitable candidate among commercial hollow-fiber evaporator alternatives. An innovative design that grouped the fiber layers into stacks, which were separated by small spaces and packaged into a cylindrical shape, was developed into a full-scale prototype for the spacesuit application.
Sheet Membrane Spacesuit Water Membrane EvaporatorTBMG-154971/1/2013
A document describes a sheet membrane spacesuit water membrane evaporator (SWME), which allows for the use of one common water tank that can supply cooling water to the astronaut and to the evaporator. Test data showed that heat rejection performance dropped only 6 percent after being subjected to highly contaminated water. It also exhibited robustness with respect to freezing and Martian atmospheric simulation testing. Water was allowed to freeze in the water channels during testing that simulated a water loop failure and vapor backpressure valve failure. Upon closing the backpressure valve and energizing the pump, the ice eventually thawed and water began to flow with no apparent damage to the sheet membrane.
RAPID: Collaborative Commanding and Monitoring of Lunar AssetsTBMG-98745/1/2011
RAPID (Robot Application Programming Interface Delegate) software utilizes highly robust technology to facilitate command-ing and monitoring of lunar assets. RAPID provides the ability for intercenter communication, since these assets are developed in multiple NASA centers.
Space Suit Simulator Aids Astronaut Training ProceduresTBMG-90381/1/2011
Extra-Vehicular Activity Space Suit Simulator (S3) Aurora Flight Sciences Cambridge, MA 703-396-6304 www.aurora.aero
Fully Printed High-Frequency Phased-Array Antenna on Flexible SubstrateTBMG-80706/1/2010
To address the issues of flexible electronics needed for surface-to-surface, surface-to-orbit, and back-to-Earth communications necessary for manned exploration of the Moon, Mars, and beyond, a room-temperature printing process has been developed to create active, phased-array antennas (PAAs) on a flexible Kapton substrate.
Advanced Liquid-Cooling Garment Using Highly Thermally Conductive SheetsTBMG-66041/1/2010
This design of the liquid-cooling garment for NASA spacesuits allows the suit to remove metabolic heat from the human body more effectively, thereby increasing comfort and performance while reducing system mass. The garment is also more flexible, with fewer restrictions on body motion, and more effectively transfers thermal energy from the crewmember’s body to the external cooling unit. This improves the garment’s performance in terms of the maximum environment temperature in which it can keep a crewmember comfortable.
Integrated Spacesuit Audio System Enhances Speech Quality and Reduces NoiseTBMG-586711/1/2009
A new approach has been proposed for increasing astronaut comfort and speech capture. Currently, the special design of a spacesuit forms an extreme acoustic environment making it difficult to capture clear speech without compromising comfort. The current system, called Communication-Cap-based Audio (CCA), relies on a single microphone placed close to the subject’s mouth. While this results in clear audio, it also has problems: wire fatigue, blind mating, interference with food/drink, need for custom communication caps, and not being able to adjust the microphone during extravehicular activities.
Testing and Model Correlation of Sublimator Driven Coldplate Coupons and EDU2009-01-24797/12/2009
The Sublimator Driven Coldplate (SDC) is a unique piece of thermal control hardware that has several advantages over a more traditional thermal control system. The principal advantage is the possible elimination of a pumped fluid loop, potentially saving mass, power, and complexity. Because this concept relies on evaporative heat rejection techniques, it is primarily useful for short mission durations. Additionally, the concept requires a conductive path between the heat-generating component and the heat rejection device. Therefore, it is mostly a relevant solution for a vehicle with a relatively low heat rejection requirement and/or short transport distances. Tests were performed on coupons and an Engineering Development Unit (EDU) at NASA's Johnson Space Center to better understand the basic operational principles and to validate the analytical methods being used for the SDC development. This paper outlines the results of the SDC tests, the subsequent thermal model correlation, and a description of the SDC Engineering Development Unit test results.
Sheth, Rubik B., Stephan, Ryan A., Leimkuehler, Thomas O.
Proposed Androgynous Docking Airlock/Utility Module2009-01-25857/12/2009
The objective of this paper is to detail a proposal for an Androgynous Docking Airlock/Utility Module (ADAM) that would allow extravehicular (EVA) crews, working from the Orion spacecraft, to avoid depressurizing the command module of the Orion vehicle for planned EVA repair, maintenance and interdiction of orbital structures. Unlike the Space Shuttle, Russian Soyuz vehicle or the Chinese Shenzhou manned spacecraft, the proposed Orion space vehicle has no airlock. This necessitates the depressurizing of the entire Command Module cabin during EVA activity. It also means that all crewmembers will have to wear space suits during contingency and planned EVAs. This inordinately dangerous situation will require all crewmembers to be exposed to the space vacuum for as much as seven hours or more if a working EVA becomes necessary. It also means that if an airlock is not employed on Orion, as indeed none is presently envisioned, the space suits the crew wears will be severely compromised in design as they will have to be employed as EVA suits and emergency launch/escape suits as well, a function that is preclusive on design, engineering and optimization levels. The ADAM module, which is a lightweight, disposable, inflatable airlock/utility carrier, could be launch separately by SpaceX Corporation from launch Complex 40 at Cape Canaveral Air Force Station. Following the successful launch and orbit of the manned Orion spacecraft, ADAM would be launched into a similar orbit. Upon reaching orbit ADAM would automatically inflate, initiate its beacon and radar transponder. With the Orion orbiter acting as the active vehicle, the two spacecraft would rendezvous and dock in a manner not unlike that of the old Gemini/Agena docking system of the 1960s. The ADAM module is deflated and tightly packed during the launch phase. This allows the module to impose the least stowage penalty within the launch shroud and also the least mass, thus, it can be launched by a relatively small booster utilizing the smallest payload fairing dimensions. On the forward and aft ends of the inflatable, cylindrical ADAM module are rigid structural hemispheres with a docking adaptor on the side interfacing to the Orion Vehicle. On the opposite end is an airlock hatch/docking adaptor. Between the two hemispherical ends the ADAM module is composed of a rugged fabric outer restraint layer (to hold the module into a cylindrical shape) and underneath is a polyurethane/Nylon bladder to hold in airlock life support gasses/pressure. Covering both is a thermal-micrometeoroid layer. When the ADAM module is sealed off from the Orion Command Module and deflated during EVA activity, aerobeams running longitudinally (as part of the inner bladder) along the modules fore-aft length, would maintain the shape/geometry of the inflatable structure. Stowed inside the ADAM module hemispherical ends are two EVA space suits, and their supporting equipment and tools, etc. Also stowed in the ADAM module would be a lightweight fan and carbon dioxide scrubber to enhance and work with the Orion's life support system. When the planned EVA activity is completed at mission termination, tools, etc. are stowed inside the upper torsos of the EVA space suits and they are then transferred into the Orion Command Module, strapped into two unused seats, and are deorbited, along with the Orion vehicle, to be used again for future missions. The ADAM module is undocked from the Orion vehicle and allowed to deorbit and burn up upon eventual atmospheric reentry.
Harris, Gary L., de León, Pablo
Tactile Sensing Gloves for Extravehicular Activity2009-01-24987/12/2009
Gloves are a critical element of the space suit used for extra-vehicular activity (EVA) since most work is done with the hands. The stiffness of the pressurized space suit limits the dexterity and flexibility of the astronauts' fingers, considerably depriving the fingertips of tactile sense of objects external to the glove. Providing tactile feedback to the fingertips may potentially improve the dexterity of the astronauts' gloves to better handle EVA tools. A complete glove-based tactile feedback system was developed to translate the sense of touch from the external fingertips of the glove to the fingertips within the glove.
Son, Ji, Fan, Richard, Wottawa, Christopher, Grundfest, Warren, Dutson, Erik, Culjat, Martin
Sub-Critical Liquid Oxygen (Lox) Storage for Exploration Life Support Systems2009-01-24177/12/2009
Oxygen storage and delivery systems for advanced Lunar Exploration Missions are substantially different than those of the International Space Station (ISS) or Apollo missions. The oxygen must be stored without venting for durations of 180 to 210 days prior to use and then used to supply both the steady, low pressure oxygen for the crew, and the higher-pressure oxygen for the extra-vehicular mobility unit. The baseline design is a high pressure gaseous oxygen storage system. Alternate technologies that may offer substantial advantages in terms of the equivalent system mass over the baseline design are being currently evaluated. This study examines both the supercritical and subcritical liquid oxygen storage options, including one with active cooling using a cryocooler. It is found that an actively cooled sub-critical storage system offered the lowest mass system that could satisfy the requirements. A well insulated passive sub-critical storage system could also satisfy the requirements, provided the thermal environment is less than 237K.
Plachta, David W., Hasan, Mohammad M.
Radiator Heat Pump Subsystem for the Space Suit Portable Life Support2009-01-24077/12/2009
The study of conceptual designs for a space suit Personal Life Support Subsystem (PLSS) at the Texas Engineering Experiment Station resulted in the recommendation to NASA of an evolution path from the existing PLSS to a long duration, low mass PLSS suitable for Martian missions. The replacement of the water sublimator cooling unit by a radiator-mechanical heat pump subsystem was one of the key technology upgrades for this evolution. The assessment was based on using a carbon radiator and mechanical heat pump. The “Lunar Noon” environment was used for sizing the system. The effect of lunar dust on the radiator and choice of refrigerant fluid were considered. A survey of previous work on high temperature heat pumps was made in order to estimate the maturation time for the heat pump technology. We concluded that a heat pump radiator using water as its cooling fluid was the best alternative.
Silva, C., Schuller, M., Marotta, E.
Investigation of Transient Sublimator Performance2009-01-24807/12/2009
Sublimators have been used for heat rejection in a variety of space applications including the Apollo Lunar Module and the Extravehicular Mobility Unit (EMU). Sublimators typically operate with steady-state feedwater utilization at or near 100%. However, sublimators are currently being considered to operate in a cyclical topping mode during low lunar orbit for Altair and possibly Orion, which represents a new mode of operation. This paper will investigate the feedwater utilization when a sublimator is used in this nontraditional manner. This paper includes testing efforts to date to investigate the Orbit-Averaged Feedwater Utilization (OAFU) for a sublimator.
Leimkuehler, Thomas O., Sheth, Rubik, Stephan, Ryan A.
Development and Testing of the First Full Pressure Suit for Non-Governmental Commercial Spaceflight2009-01-24977/12/2009
The objective of this paper is to detail the development of the DL/H-1 full pressure suit, which was developed by De Leon Technologies LLC, with the assistance of the University of North Dakota. The DL/H-1 was specifically developed to fulfill the needs for a full pressure suit for private spaceflight in case of decompression or in the need of bailout of the spacecraft. This work also details the objectives, basis for design, problems encountered by the designers, final development of the DL/H-1 full pressure suit and testing in the high altitude chamber at the School of Aerospace Sciences at the University of North Dakota. The authors believe that during experimental flights of private spaceflight, orbital or suborbital a full pressure suit will be required to augment safety during all flight phases where in the case of cabin pressure loss, without personal protection, the loss of crew and vehicle could result. This paper explains the different steps being performed by the authors, who designed and built a flight hardware pressure suit that can meet the physiological and comfort requirements of the tourist suborbital industry and the early commercial private spaceflight community. The suborbital tourist and commercial spaceflight industry have unique problems confronting the pressure suit builder, such as unpressurized comfort, reasonable expense, unique sizing of the general population, decompression complications of persons not fitting a military physiology profile and equipment weight issues.
de León, Pablo, Harris, Gary L.
A Method for and Issues Associated with the Determination of Space Suit Joint Requirements2009-01-25377/12/2009
In the design of a new space suit it is necessary to have requirements that define what mobility space suit joints should be capable of achieving in both a system and at the component level. NASA elected to divide mobility into its constituent parts -- range of motion (ROM) and torque -- in an effort to develop clean design requirements that limit subject performance bias and are easily verified. Unfortunately, the measurement of mobility can be difficult to obtain. Current technologies, such as the Vicon motion capture system, allow for the relatively easy benchmarking of range of motion (ROM) for a wide array of space suit systems. The ROM evaluations require subjects in the suit to accurately evaluate the ranges humans can achieve in the suit. However, when it comes to torque, there are significant challenges for both benchmarking current performance and writing requirements for future suits. This is reflected in the fact that torque definitions have been applied to very few types of space suits and with limited success in defining all the joints accurately. This paper discusses the advantages and disadvantages to historical joint torque evaluation methods, describes more recent efforts directed at benchmarking joint torques of prototype space suits, and provides an outline for how NASA intends to address joint torque in design requirements for the Constellation Space Suit System (CSSS).
Matty, Jennifer E., Aitchison, Lindsay
Evaluation of Carbon Dioxide Sensors for the Constellation Space Suit Life Support System for Surface Exploration2009-01-23727/12/2009
This paper presents the findings of the trade study to evaluate carbon dioxide (CO2) sensing technologies for the Constellation (Cx) space suit life support system for surface exploration. The trade study found that non-dispersive infrared absorption (NDIR) is the most appropriate high Technology Readiness Level (TRL) technology for the CO2 sensor for the Cx space suit. The maturity of the technology is high, as it is the basis for the CO2 sensor in the Extravehicular Mobility Unit (EMU). The study further determined that while there is a range of commercial sensors available, the Cx CO2 sensor should be a new design. Specifically, there are light sources (e.g., infrared light emitting diodes) and detectors (e.g., cooled detectors) that are not in typical commercial sensors due to cost. These advanced technology components offer significant advantages in performance (weight, volume, power, accuracy) to be implemented in the new sensor. The exact sensor design (light source, transmitting optics, path length, receiving optics and detector) will be specific for the Cx space suit and will be determined by the performance requirements of the Cx space suit. The paper further identifies specifications for some of the critical performance parameters as well as discussing the engineering aspects of implementing the sensor into the Portable Life Support System (PLSS). The paper then presents testing results from three CO2 sensors with respect to issues important to Extravehicular Activity (EVA) applications; stability, humidity dependence and low pressure compatibility. The three sensors include two NDIR sensors, one commercial and one custom-developed by NASA (for a different purpose), and one commercial electrochemical sensor. The results show that both NDIR sensors have excellent stability, no dependence on ambient humidity (when the ambient temperature is above the dew point) and operate in low pressure conditions and after being exposed to a full vacuum. The commercial electrochemical sensor was not suitable for the Cx space suit for surface exploration. Finally, the paper identifies a number of techniques currently under development that offer significant advantages for EVA applications. These include miniaturized, room temperature, solid electrolyte systems and advanced optical detectors.
Dietrich, D.L., Paul, H.L., Conger, B.C.
Results of the Particulate Contamination Control Trade Study for Space Suit Life Support Development2009-01-23737/12/2009
As the United States makes plans to return astronauts to the moon and eventually send them on to Mars, designing the most effective, efficient, and robust spacesuit life support system that will operate successfully in dusty environments is vital. Some knowledge has been acquired regarding the contaminants and level of infiltration that can be expected from lunar and Mars dust, however, risk mitigation strategies and filtration designs that will prevent contamination within a spacesuit life support system are yet undefined. A trade study was therefore initiated to identify and address these concerns, and to develop new requirements for the Constellation spacesuit element Portable Life Support System. This trade study investigated historical methods of controlling particulate contamination in spacesuits and space vehicles, and evaluated the possibility of using commercial technologies for this application. The trade study also examined potential filtration designs. This paper summarizes the results of this trade study.
Cognata, Thomas J., Conger, Bruce, Paul, Heather L.
Philosophies Applied in the Selection of Spacesuit Joint Range-of-Motion Requirements2009-01-25387/12/2009
Space suits are the most important tool for astronauts working in harsh space and planetary environments; suits keep crewmembers alive and allow them to perform exploration, construction, and scientific tasks on a routine basis over a period of several months. The efficiency with which the tasks are performed is largely dictated by the mobility features of the space suit. For previous space suit development programs, the mobility requirements were written as pure functional mobility requirements that did not separate joint ranges of motion from joint torques. The Constellation Space Suit Element has the goal to make more quantitative mobility requirements that focused on the individual components of ‘mobility’ to enable future suit designers to build and test systems more effectively. This paper details the test planning and selection process for the Constellation space suit pressure garment range of motion requirements.
Aitchison, Lindsay
Performance of the Extravehicular Mobility Unit (EMU) Airlock Coolant Loop Remediation (A/L CLR) Hardware Phase II2009-01-25417/12/2009
An EMU water processing kit (Airlock Coolant Loop Recovery – A/L CLR) was developed as a corrective action to Extravehicular Mobility Unit (EMU) coolant flow disruptions experienced on the International Space Station (ISS) in May of 2004 and thereafter. Conservative schedules for A/L CLR use and component life were initially developed and implemented based on prior analysis results and analytical modeling. The examination of post-flight samples and EMU hardware in November of 2006 indicated that the A/L CLR kits were functioning well and had excess capacity that would allow a relaxation of the initially conservative schedules of use and component life. A relaxed use schedule and list of component lives were implemented thereafter. Since the adoption of the relaxed A/L CLR schedules of use and component lives, several A/L CLR kit items, transport loop water samples and sensitive EMU transport loop components have been examined to gage the impact of the relaxed requirements. The intent of this paper is to summarize the findings of that evaluation, and to outline updated schedules for A/L CLR use and component life.
Steele, John W., Rector, Tony, Gazda, Daniel B., Lewis, John
Incorporating Advanced Controls, Displays and other Smart Elements into Space Suit Design2009-01-24727/12/2009
The MX-2 neutral buoyancy space suit analogue has been designed and developed at the University of Maryland to facilitate analysis of space suit components and assessment of the benefits of advanced space suit technologies, The MX-2 replicates the salient features of microgravity pressure suits, including the induced joint torques, visual, auditory and thermal environments, and microgravity through the use of neutral buoyancy simulation. In this paper, design upgrades and recent operations of the suit are outlined, including many experiments and tests of advanced space suit technologies, This paper focuses on the work done using the MX-2 to implement and investigate various advanced controls and displays within the suit, to enhance crewmember situational awareness and effectiveness, and enable human-robotic interaction. An advanced interface has been built into the suit which includes a speech recognition system, augmented reality and several different displays, which provide information to the crewmembers through images which incorporate status updates, electronic checklists, diagrams, camera feeds, video, etc. This system allows the suit subject to choose the information on the displays using voice, as well as to control various robotic systems with voice commands. The system also provides auditory feedback. This hands-off, eyes-off interface could make future servicing tasks, such as satellite repairs or construction of structures in space or on the moon, simpler and more time-effective, reducing the demands on the EVA astronaut while taking advantage of the extensive benefits of human-robot teams. By significantly enhancing the capabilities of a suited astronaut, this system will enable astronauts on the surface of the Moon or Mars to explore more effectively, safely, efficiently, and autonomously. The system reduces reliance on external communications, which has the potential to reduce operational costs and crewmember workload.
Jacobs, Shane E., Di Capua, Massimiliano, Husain, Syed-Ali A., Mirvis, Adam, Akin, David L.
Hollow Fiber Space Suit Water Membrane Evaporator Development for Lunar Missions2009-01-23717/12/2009
The Space Suit Water Membrane Evaporator (SWME) is a baseline heat rejection technology that was selected to develop the Constellation Program lunar suit. The Hollow Fiber (HoFi) SWME is being considered for service in the Constellation Space Suit Element Portable Life Support Subsystem to provide cooling to the thermal loop via water evaporation to the vacuum of space. Previous work [1] described the test methodology and planning that are entailed in comparing the test performance of three commercially available HoFi materials as alternatives to the sheet membrane prototype for SWME: (1) porous hydrophobic polypropylene, (2) porous hydrophobic polysulfone, and (3) ion exchange through nonporous hydrophilic-modified Nafion®. Contamination tests were performed to probe for sensitivities of the candidate SWME elements to the organic and non-volatile inorganic constituents that are expected to be found in the target feedwater source, i.e., the potable water that is provided by the vehicle. The resulting presence of precipitate in the coolant water could plug the pores and tube channels, thus affecting SWME performance. From this prior work, a commercial porous hydrophobic HoFi was selected that will satisfy both the sensitivity question and the need to provide 800 W of heat rejection. This paper describes the trade studies, design method ology, and HoFi test data that are used to design a full-size HoFi test article for future testing in the summer of 2009.
Bue, Grant C., Trevino, Luis A., Hanford, Anthony J., Mitchell, Keith
NASA’s Next-Generation Space Suit Built for Orion SpacecraftTBMG-330310/1/2008
Constellation Space Suit Station (CSSS) Oceaneering International Houston, TX 281-228-5300 www.oceaneering.com
A Freezable Heat Exchanger for Space Suit Radiator Systems2008-01-21116/29/2008
During an ExtraVehicular Activity (EVA), both the heat generated by the astronaut's metabolism and that produced by the Portable Life Support System (PLSS) must be rejected to space. The heat sources include the heat of adsorption of metabolic CO2, the heat of condensation of water, the heat removed from the body by the liquid cooling garment, the load from the electrical components and incident radiation. Although the sublimator hardware to reject this load weighs only 1.58 kg (3.48 lbm), an additional 3.6 kg (8 lbm) of water are loaded into the unit, most of which is sublimated and lost to space, thus becoming the single largest expendable during an eight-hour EVA. Using a radiator to reject heat from the astronaut during an EVA can reduce the amount of expendable water consumed in the sublimator. Radiators have no moving parts and are thus simple and highly reliable. However, past freezable radiators have been too heavy. The weight can be greatly reduced by placing a small and freeze tolerant heat exchanger between the astronaut and radiator, instead of making the very large radiator freeze tolerant. Therefore, the key technological innovation to improve space suit radiator performance was the development of a lightweight and freezable heat exchanger that accommodates the variable heat load generated by the astronaut. Herein, we present the heat transfer performance of a newly designed heat exchanger that endured several freeze / thaw cycles without any apparent damage. The heat exchanger was also able to continuously turn down or turn up the heat rejection to follow the variable load.
Nabity, James A., Mason, Georgia R., Copeland, Robert J., Trevino, Luis A.
Performance of the Extravehicular Mobility Unit (EMU) Airlock Coolant Loop Remediation (A/L CLR) Hardware2008-01-20606/29/2008
Following the Columbia accident, the EMUs (Extravehicular Mobility Units) onboard the ISS (International Space Station) went unused for an extended period of time. Upon startup, the units experienced a failure in the coolant systems. The failure resulted in a loss of EVA (Extravehicular Activity) capability from the US segment of the ISS. A failure investigation determined that chemical and biological contaminants and byproducts from the ISS Airlock Heat Exchanger, and the EMU itself, fouled the magnetically coupled pump in the EMU Transport Loop Fan/Pump Separator leading to a lack of coolant flow. Remediation hardware (the Airlock Coolant Loop Remediation water processing kit) and a process to periodically clean the EMU coolant loops on orbit were devised and implemented. The intent of this paper is to report on the successful implementation of the resultant hardware and process, and to highlight the go-forward plan.
Steele, John W., Rector, Tony, Gazda, Daniel B., Lewis, John
Functional Mobility Testing: A Novel Method to Create Suit Design Requirements2008-01-18576/17/2008
This study was performed to aide in the creation of design requirements for the next generation of space suits that more accurately describe the level of mobility necessary for a suited crewmember through the use of an innovative methodology utilizing functional mobility. A novel method was utilized involving the collection of kinematic data while 20 subjects (10 male, 10 female) performed pertinent functional tasks that will be required of a suited crewmember during various phases of a lunar mission. These tasks were selected based on relevance and criticality from a larger list of tasks that may be carried out by the crew. Kinematic data was processed through Vicon BodyBuilder software to calculate joint angles for the ankle, knee, hip, torso, shoulder, elbow, and wrist. Maximum functional mobility was consistently lower than maximum isolated mobility. This study suggests that conventional methods for establishing design requirements for human-systems interfaces based on maximal isolated joint capabilities may overestimate the required mobility. Additionally, this method provides a valuable means of evaluating systems created from these requirements by comparing the mobility available in a new spacesuit, or the mobility required to use a new piece of hardware, to this newly established database of functional mobility.
England, Scott A., Benson, Elizabeth A., Rajulu, Sudhakar L.
Derivation of Boundary Manikins: A Principal Component Analysis2008-01-18796/17/2008
When designing any human-system interface, it is critical to provide realistic anthropometry to properly represent how a person fits within a given space. This study aimed to identify a minimum number of ‘boundary manikins’ or representative models of subjects' anthropometry from a target population, which would realistically represent the population. The boundary manikin anthropometry was derived using, Principal Component Analysis (PCA). PCA is a statistical approach to reduce a multi-dimensional dataset using eigenvectors and eigenvalues. The measurements used in the PCA were identified as those measurements critical for space suit and cockpit design. The PCA yielded a total of 26 manikins per gender, as well as their anthropometry from the target population. Reduction techniques were implemented to reduce this number further with a final result of 20 female and 22 male subjects. The anthropometry of the ‘boundary manikins’ was then be used to create 3D digital models (to be discussed in subsequent papers) intended for use by designers to test components of their space suit design, to verify that the requirements specified in the Human Systems Integration Requirements (HSIR) document are met. The end-goal is to allow for designers to generate suits which accommodate the diverse anthropometry of the user population.
Young, Karen, Margerum, Sarah, Barr, Abbe, Ferrer, Mike A., Rajulu, Sudhakar
Development and Testing of the Contaminant Insensitive Sublimator2007-01-32037/9/2007
Sublimators have been used for heat rejection for a variety of space applications including the Apollo Lunar Module and the Extravehicular Mobility Unit (EMU). Some of the attractive features of sublimators are that they are compact, lightweight, and self-regulating. One of the drawbacks of previous designs has been sensitivity to non-volatile contamination in the feedwater, which can clog relatively small pores (~3-6 pm) in the porous plates where ice forms and sublimates. A new design that is less sensitive to contaminants is being developed at the Johnson Space Center (JSC). This paper describes the design, fabrication, and testing of the Contaminant Insensitive Sublimator (CIS) Engineering Development Unit (EDU).
Leimkuehler, Thomas O., Stephan, Ryan A.
Inhibition of Biofilm Formation on the Service and Performance Heat Exchanger by Quorum Sensing Inhibition2007-01-31437/9/2007
Shortly after installation of the service and performance heat exchanger (SPCU HX) in 2001, samples collected from the coolant fluid indicated the presence of nickel accompanied by a subsequent decrease in phosphate concentration along with a high microbial load. When the SPCU HX was replaced and evaluated post-flight, it was expected that the heat exchanger would have significant biofilm and corrosion present given the composition of the coolant fluid; however, there was no evidence of either. Early results from two experiments imply that the heat exchanger materials themselves are inhibiting biofilm formation. This paper discusses the results of one set of experiments and puts forward the inhibition of quorum sensing as a possible mechanism for the lack of biofilm formation.
Vega, Leticia M., Pyle, Barry H., Roman, Monserrate C., Alvarez, Pedro J. J., Pickering, Karen D.
Loping: A Strategy for Reduced Gravity Human Locomotion?2007-01-31347/9/2007
Loping, defined here as skipping without a foot exchange, is a gait uncommonly used by humans on Earth, but favored by Apollo astronauts during lunar surface excursions. Astronauts may have adopted loping due to space suit-imposed mobility restrictions or because of a possible stability advantage conferred by a relatively constant and wide support base. To evaluate whether loping confers metabolic advantages we monitored ten subjects during loping and running, simulating reduced gravity via partial body suspension, and simulating suited conditions using a lower body exoskeleton. In lunar gravity, loping incurred lower metabolic costs than running for every subject; loping, while efficient at low gravity levels, was less efficient than running in Earth gravity. Loping combines the energy conversion characteristics of walking and running; loping may confer an even larger metabolic advantage during lunar space-suited locomotion due to mobility limitations not associated with the exoskeleton.
Rader, Andrew A., Newman, Dava J., Carr, Christopher E.
Digital Learning Network Education Events for the Desert Research and Technology Studies2007-01-30637/9/2007
NASA's Digital Learning Network (DLN) reaches out to thousands of students each year through video conferencing and webcasting. As part of NASA's Strategic Plan to reach the next generation of space explorers, the DLN develops and delivers educational programs that reinforce principles in the areas of science, technology, engineering and mathematics. The DLN has created a series of live education videoconferences connecting the Desert Research and Technology Studies (RATS) field test to students across the United States. The programs are also extended to students around the world via live webcasting. The primary focus of the events is the Vision for Space Exploration. During the programs, Desert RATS engineers and scientists inform and inspire students about the importance of exploration and share the importance of the field test as it correlates with plans to return to the Moon and explore Mars. This paper describes the events that took place in September 2006.
Paul, Heather L., Guillory, Erika R.
Dust Mitigation Solutions for Lunar and Mars Surface Systems2007-01-32137/9/2007
Dust mitigation has been identified as a major obstacle to lunar and Mars surface operations for space suits, robotics, and vehicle systems. Experience from the Apollo program has demonstrated that lunar stays of limited duration will be difficult and dangerous if dramatic measures are not taken to mitigate the impacts of dust contamination. Numerous mitigation approaches have been studied in the past including electrostatic materials, cleaning techniques, and suit-locks. Many of these approaches are effective in operation but are challenged by the trend of returning to a single space suit system, similar to Apollo, which is used for launch/entry as well as surface and contingency extra-vehicular activity (EVA) operations. Bringing the surface suit inside the vehicle after surface EVA will transfer surface material in the vehicle. Studies are currently ongoing to identify containment methods of isolating the space suit or robotics elements from the surface dust during EVA operations through the use of removable covers. This approach not only protects the underlying components from dust contamination but also precludes the transfer of dust into the vehicle or habitat. Similar containment analogs are employed everyday throughout the world when using chemical, biological, or radiological protective equipment in the military and various industries. Prototype covers for the space suit have been designed and tested to create robust durable covers that protect the suit from degradation without encumbering mobility, while also being simple to don & doff. Accompanying procedures, such as removing the covers just outside the airlock, will keep the dust off the underlying space suit and therefore prevent it from entering the vehicle. The covers may also include any dust mitigating materials advances such as lotus-effect coatings as they evolve, simplifying certification and life-cycle impacts of the underlying space suit. First order system level trades have been conducted on various technical approaches. Results of the trade studies, discussion of the analogs that are in existence and prototype testing will be presented in the paper.
Cadogan, Dave, Ferl, Janet
Minimizing the Effects of Material Obsolescence on Constellation Space Suit System Design2007-01-30347/9/2007
Materials used for manned space flight are tightly controlled to ensure the safety of the crewmembers. Significant changes to the economic environment as well as impact from environmental restrictions have resulted in material obsolescence that requires recertification or revalidation, increasing cost and risk to the program. This paper will review the impact this issue has had on the Shuttle Extravehicular Mobility Unit (EMU) Space Suit Assembly (SSA) and will provide insight into challenges expected for the Constellation Space Suit System (CSSS) program. Factors that affect availability, the impacts of material obsolescence, identification processes and risk reduction and management are described.
Hewes, Linda, Marini, Brian, Dasgupta, Rajib
A Semi-Continuous, Regenerable System for Trace Contaminant Control in Closed Atmospheres2007-01-31557/9/2007
Long term space exploration poses considerable challenges in logistics since launch costs, weight, and volume are all limited. In space life support systems contaminants are generated due to the off-gassing of materials of construction and are also a by-product of crew metabolism. While carbon dioxide is a metabolic contaminant, its control is typically accomplished by a dedicated system, whereas the rest of the contaminants are controlled using a trace contaminant control system (TCCS). Currently, NASA employs various TCCS approaches depending on the mission type and duration. In the Extravehicular Mobility Unit (EMU) this is accomplished with activated carbon as well as strict control on materials of construction. The activated carbon is thermally regenerated in some EMU applications and the adsorbed contaminants are purged to the International Space Station (ISS) where they are subsequently removed. The ISS combines phosphoric impregnated charcoal, high temperature catalysis, and lithium carbonate, along with similar control of materials of construction for the control of trace contaminants. However, in the ISS, or any vehicle such as the Shuttle or Crew Exploration Vehicle, there are significant quantities of non-metallics, in addition to other crew activities such as hygiene and experimentation, which can significantly impact the trace contaminant load. This paper presents an approach to contaminant control which combines electrically regenerable carbon structures, periodically desorbing contaminants to space vacuum, with a photocatalytic oxidation system. This approach uses existing, proven technologies, which require minimal logistics offering significant savings over currently employed systems. The regenerable sorbents eliminate the need to carry non-regenerable sorbent beds, while photocatalytic oxidation uses less power than conventional high temperature oxidation processes.
Nalette, Tim, Obee, Tim
A New Method for Breath Capture Inside a Space Suit Helmet2007-01-32487/9/2007
This project investigates methods to capture an astronaut's exhaled carbon dioxide (CO2) before it becomes diluted with the high volumetric oxygen flow present within a space suit. Typical expired breath contains CO2 partial pressures (pCO2) in the range of 20-35 mm Hg (.0226-.046 atm). This research investigates methods to capture the concentrated CO2 gas stream prior to its dilution with the low pCO2 ventilation flow. Specifically this research is looking at potential designs for a collection cup for use inside the space suit helmet. The collection cup concept is not the same as a breathing mask typical of that worn by firefighters and pilots. It is well known that most members of the astronaut corps view a mask as a serious deficiency in any space suit helmet design. Instead, the collection cup is a non-contact device that will be designed using a detailed Computational Fluid Dynamic (CFD) analysis of the ventilation flow environment within the helmet. The CFD code, Fluent, provides modeling of the various gas species (CO2, water vapor, and oxygen (O2)) as they pass through a helmet. This same model will be used to numerically evaluate several different collection cup designs for this same CO2 segregation effort. A new test rig will be built to test the results of the CFD analyses and validate the collection cup designs. This paper outlines the initial results and future plans of this work.
Filburn, Tom, Dolder, Craig, Tufano, Brett, Paul, Heather L.
Mark III Space Suit Mobility: A Reach Evaluation Case Study2007-01-24736/12/2007
A preliminary assessment of the reach envelope and field of vision (FOV) for a subject wearing a Mark III space suit was requested for use in human-machine interface design of the Science Crew Operations and Utility Testbed (SCOUT) vehicle. The reach and view of two suited and unsuited subjects were evaluated while seated in the vehicle using 3-dimensional position data collected during a series of reaching motions. Data was interpolated and displayed in orthogonal views and cross-sections. Compared with unsuited conditions, medio-lateral reach was not strongly affected by the Mark III suit, whereas vertical and antero-posterior reach were inhibited by the suit. Lateral FOV was reduced by approximately 40° in the suit. The techniques used in this case study may prove useful in human-machine interface design by providing a new means of developing and displaying reach envelopes.
Thaxton, Sherry S., Abercromby, Andrew F. J., Onady, Elizabeth A., Rajulu, Sudhakar L.
Noise-Canceling Helmet Audio SystemTBMG-19125/1/2007
A prototype helmet audio system has been developed to improve voice communication for the wearer in a noisy environment. The system was originally intended to be used in a space suit, wherein noise generated by airflow of the spacesuit life-support system can make it difficult for remote listeners to understand the astronaut’s speech and can interfere with the astronaut’s attempt to issue vocal commands to a voice-controlled robot. The system could be adapted to terrestrial use in helmets of protective suits that are typically worn in noisy settings: examples include biohazard, fire, rescue, and diving suits.
A Comparison of Pressure Suit Systems Architectures for the Space Exploration Enterprise2006-01-21357/17/2006
The space exploration enterprise that will lead to human exploration on Mars requires pressure suit system capabilities and characteristics that change significantly over time and between different missions and mission phases. These capabilities must be provided within tight budget constraints and severely limited launch mass and volume, and at a pace that supports NASA's over-all exploration timeline. As a result, it has not been obvious whether the use of a single pressure suit system (like Apollo) or combinations of multiple pressure suit designs (like Shuttle) will offer the best balance among life cycle cost, risk, and performance. Because the answer to this question is pivotal for the effective development of pressure suit system technologies that will met NASA's needs, ILC and Hamilton Sundstrand engineers have collaborated in an independent study to identify and evaluate the alternatives. Our study has included consideration of pressure suit system design requirements, trade criteria and their relative importance, architectural alternatives, and potential design solutions for their implementation. Requirements were analyzed for key missions and mission phases from initial CEV flights to Mars surface exploration, and nine different architectural approaches to meeting those requirements through the life of the enterprise were developed. Implementation possibilities were defined based on a review of both historical design precedents (e.g. Gemini, Apollo, MOL, EMU, Orlan) and emerging technologies and design concepts and used as a realistic basis for evaluating each architectural option. This paper discusses the execution and results of our study and potential implications for subsequent pressure suit system designs and technology development needs.
Dionne, Steven, Hodgson, Edward, Howe, Robert, Margiott, Victoria, Murray, Sean, Quinn, Gregory, Thomas, Kenneth, Valk, Mary Ann, Ferl, Janet, Splawn, Keith
Defining Space Suit Operational Requirements for Lunar and Mars Missions and Assessing Alternative Architectures2006-01-22907/17/2006
Sending humans to the moon and Mars in support of NASA’s Vision for Space Exploration (VSE) presents a variety of operational environments in which astronauts will need to wear a space suit, both inside the vehicle and during Extravehicular Activity (EVA). Four feasible suit architectures were proposed by NASA in terms of the number and type of suits needed to enable task performance in scenarios ranging from launch and entry operations to conducting EVA’s in microgravity and on planetary surfaces. This study was aimed at defining space suit operational and functional needs across the spectrum of mission elements called out in the VSE, identifying temporal and technical design drivers, and establishing appropriate trade variables with associated weighting factors for analyzing the proposed architecture options. Recommendations from the analysis are offered for consideration in selecting from the four options.
Klaus, D., Bamsey, M., Schuller, M., Godard, O., Little, F., Askew, R.
Micrometeoroid and Orbital Debris Enhancements of Shuttle Extravehicular Mobility Unit Thermal Micrometeoroid Garment2006-01-22857/17/2006
As NASA is preparing to extend man's reach into space, it is expected that astronauts will be required to spend more and more time exposed to the hazards of performing Extra-Vehicular Activity (EVA). One of these hazards includes the risk of the space suit bladder being penetrated by hypervelocity micrometeoroid and orbital debris (MMOD) particles. Therefore, it has become increasingly important to investigate new ways to improve the protectiveness of the current Extravehicular Mobility Unit (EMU) against MMOD penetration. ILC Dover conducted a NASA funded study into identifying methods of improving the current EMU protection. The first part of this evaluation focused on identifying how to increase the EMU shielding, selecting materials to accomplish this, and testing these materials to determine the best lay-up combinations to integrate into the current thermal micrometeoroid garment (TMG) design. Part of this study included using extensive hypervelocity testing to identify potential candidate materials. The last part of this study expanded on the previous results by conducting a more thorough investigation into the performance of the top three candidate lay-ups for micrometeor protection. The ability to manufacture the candidates into the current TMG and their effects on the torque of a mobility joint were the main focus points. This paper summarizes the findings of this study.
Jones, Robert, Graziosi, David, Ferl, Jinny, Splawn, Keith, Zetune, David, Cadogan, David, Christiansen, Eric L.
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