Space Suit

Pressurized garments for space exploration training require design for ease-of-maintenance and repair, and toolkits, manuals and procedures for such. Consideration for these is required in pressurized garment design and hardware integration.

In the quest for a viable non-gravity dependent method to "lift weights" in space, our laboratory introduced iso-inertial resistance (YoYo TM ) exercise using spinning flywheel(s), more than 25 years ago. After being thoroughly tested in individuals subjected to various established spaceflight analogs, a multi-mode YoYo TM exercise apparatus was eventually installed on the International Space Station in 2009. The method, applicable to any muscle group, provides accommodated resistance and optimal muscle loading through the full range of motion of concentric actions, and brief episodes of eccentric overload. This exercise intervention has found terrestrial applications and shown success in enhancing sports performance and preventing injury and aiding neurological or orthopedic rehabilitation. Research has proven that this technique offers unique physiological responses not possible with other exercise hardware solutions. This paper provides a brief overview of research that has made use, and explored the efficacy, of this method in healthy sedentary or physically active individuals and populations suffering from muscle wasting, disease or injury. While the collective evidence to date suggests YoYo TM offers a potent stimulus to optimize the benefits of resistance exercise, systematic research to support clinical use of this method has only begun to emerge. Thus, we also offer perspectives on unresolved issues, unexplored applications for clinical conditions, and how this particular exercise paradigm could be implemented in future clinical research and eventually being prescribed. Fields of particular interest are those aimed at promoting muscle health by preventing injury or combating muscle wasting and neurological or metabolic dysfunction due to aging or illness, or those serving in rehabilitation following trauma and/or surgery.

The International Space Station (ISS) provides significant challenges for radiation protection of the crew due to a combination of circumstances including: the extended duration of missions for many crewmembers, the exceptionally dynamic nature of the radiation environment in ISS orbit, and the necessity for numerous planned extravehicular activities (EVA) for station construction and maintenance. Radiation protection requires accurate radiation dose measurements and precise risk modeling of the transmission of high fluxes of energetic electrons and protons through the relatively thin shielding provided by the space suits worn during EVA. Experiments and analyses have been performed due to the necessity to assure complete radiation safety for the EVA crew and thereby ensure mission success. The detailed characterization described of the material and topological properties of the ISS space suits can be used as a basis for design of space suits used in future exploration missions. In ...

Negative or disturbed body perceptions are often interwoven with people's physical inactivity. While wearables can support body perception changes (body transformation), the design space of body transformation wearables supporting physical activity remains narrow. To expand this design space, we conducted an embodied co-design workshop with users. Using conceptual and tangible sensitizing tools, we explored/reflected on bodily sensations at three moments of movement execution (before/during/after). Conceptual tools were used to evoke/reflect/capture past lived experiences, while tangible tools were used as ideation probes for sensory bodystorming. Two design concepts emerged, reflecting diverging approaches to body transformation wearables: one focused on reminders and movement correction; the other on sensory augmentation and facilitation. We reflect on how each facilitates useful representations of body sensations during movement, and present methodological recommendations for designing technology for sensory augmentation in this area. Finally, we propose a preliminary prototype based on our design concepts and discuss future steps.

The International Space Station (ISS) is the greatest endeavour in low Earth orbit since the beginning of the space age and the culmination of human outposts like Skylab and Mir. While a clear schedule has yet to be drafted, it is expected that ISS will cease operation in the 2020s. What could be the layout for a human outpost in LEO with lessons learnt from ISS? What are the use cases and applications of such an outpost in the future? The System Analysis Space Segment (SARA) group of the German Aerospace Center (DLR) investigated these and other questions and developed the Orbital Hub concept. In this paper an overview is presented of how the overall concept has been derived and its properties and layout are described. Starting with a workshop involving the science community, the scientific requirements have been derived and strawman payloads have been defined for use in further design activities. These design activities focused on Concurrent Engineering studies, where besides DLR employees also participants from industry and astronauts were involved. The result is an expandable concept that is composed of two main parts, the Base Platform, home for a permanent crew of up to 3 astronauts, and the Free Flyer, an uncrewed autonomous research platform. This modular approach provides one major advantage: the decoupling of the habitat and payload leading to increased quality of the micro gravity environment. The former provides an environment for human physiology experiments, while the latter allows science without the perturbations caused by a crew, e.g. material experiments or Earth observation. The Free Flyer is designed to operate for up to 3 months on its own, but can dock with the space station for maintenance and experiment servicing. It also has a hybrid propulsions system, chemical and electrical, for different applications. The hub's design allows launch with just three launches, as the total mass of all hub parts is about 60,000 kg. The main focus of the design is on autonomy and reducing crew maintenance and repair efforts, and reducing the need for extravehicular activities. Following a description of the design approach and technical details, a cost estimation and a detailed discussion of the use cases for such a station concept, along with the possible scenarios of international cooperation, are also presented in this paper.

The Advanced Inflatable Airlock (AIA) System is currently being developed for the Space Launch Initiative (SLI). The objective of the AIA System is to greatly reduce the cost associated with performing extravehicular activity (EVA) from manned launch vehicles by reducing launch weight and volume from previous hard airlock systems such as the Space Shuttle and Space Station airlocks. The AIA System builds upon previous technology from the TransHab inflatable structures project, from Space Shuttle and Space Station Airlock systems, and from terrestrial flexible structures projects. The AIA system design is required to be versatile and capable of modification to fit any platform or vehicle needing EVA capability. During the basic phase of the program the AIA conceptual design and key features were developed to help meet the SLI program goals of reduced cost and program risk. Option 1 focused on development of key design features and testing of breadboard units to demonstrate effectiveness of the design solutions. This paper discusses the progress made during option 1 of the AIA program. The basic phase of the program focused on requirements definition, material selection and conceptual design definition (See Reference). Key requirements were identified to set the boundary conditions for the materials research and final selection. Requirements focused on pressure containment, minimizing leakage, allowing multiple folding cycles, ability to withstand the environments of low earth orbit (LEO), and provide micrometeoroid and orbital debris (MMOD) protection. Figure shows the Mock-up/test article fabricated for the basic phase.

The extravehicular mobility unit (EMU), commonly known as the astronaut space suit assembly (SSA) and primary life support system (PLSS), has evolved through the years to incorporate new and innovative materials in order to meet the demands of the space environment. The space shuttle program which is seeing an increasing level of extravehicular activity (EVA), also called space walks, along with interest in an EMU for Lunar-Mars missions means even more demanding conditions are being placed on the suit and PLSS. The project for this NASA-ASEE Summer Program was to investigate new materials for these applications. The focus was to emphasis the use of composite materials for every component of the EMU to enhance the properties while reducing the total weight of the EMU. To accomplish this, development of new materials called fuUerene reinforced materials (FRM's) was initiated. Fullerenes are carbon molecules which when added to a material significantly reduce the weight of that material. The Faculty Fellow worked directly on the development of the fullerene reinforced materials. A chamber for fullerene production was designed and assembled and first generation samples were processed. He also supervised with the JSC Colleague, a study of composite materials for the EMU conducted by the student participant in the NASA-ASEE Program, Hector Tello a Rice University graduate student, and by a NASA Aerospace Technologist (Materials Engineer) Evelyne Omdoff, in the Systems Engineering Analysis Office (EC7), also a Rice University graduate student. Hector Tello conducted a study on beryllium and Be alloys and initiated a study of carbon and glass reinforced composites for space applications. Evelyne Orndoff complied an inventory of the materials on the SSA. Ms. Orndoff also reviewed SSA material requirements and cited aspects of the SSA design where composite materials might be further considered. Hector Tello spend part of his time investigating the solar radiation sensitivity of anodic coatings. This project was directed toward the effects of ultra-violet radiation on high emissivity anodic coatings. The work of both Evelyne Orndoff and Hector Tello is of interest to the Engineering Directorate at NASA/JSC and is also directed toward their research as Rice University graduate students.

NASA's Z-2 prototype space suit is the highest fidelity pressure garment from both hardware and systems design perspectives since the Space Shuttle Extravehicular Mobility Unit (EMU) was developed in the late 1970's. Upon completion the Z-2 will be tested in the 11 foot human-rated vacuum chamber and the Neutral Buoyancy Laboratory (NBL) at the NASA Johnson Space Center to assess the design and to determine applicability of the configuration to micro-, low-(asteroid), and planetary-(surface) gravity missions. This paper discusses the 'firsts' that the Z-2 represents. For example, the Z-2 sizes to the smallest suit scye bearing plane distance for at least the last 25 years and is being designed with the most intensive use of human models with the suit model. NASA's Advanced Exploration Systems (AES) Advanced Extra-Vehicular Activity (EVA) project is working toward a Chamber B human-rated thermal, vacuum chamber demonstration of a complete advanced Extravehicular Mobility Unit (EMU), consisting of a planetary surface walking pressure garment configuration and a portable life support system (PLSS) that utilizes new technology components. The Z-2 prototype pressure garment addresses two major steps in pressure garment maturation that are required to meet this goal: hardware fidelity and systemlevel interfaces. Previous pressure garment prototypes have primarily served as mobility joint system test beds. The prototypes were tested in ambient atmosphere, meaning the suits were tested using breathing air and at a delta pressure above 14.7 psia. Life support was provided by ground support equipment via an umbilical interface or by a portable backpack. The Z-2 will be tested in Johnson Space Center's 11 foot chamber, which is an 11.0 foot by19.0 foot chamber with dual airlock compartments of 9.0 foot and 10.0 foot lengths used for human testing in a vacuum environment, and for space suit development. It features a treadmill, fall protection and the necessary support systems for reduced pressure crew operations. Test of the Z-2 in the 11 foot human-rated vacuum chamber at the Johnson Space Center requires that the suit be compatible with 100% oxygen and a hard vacuum (1x10 -2 Torr). Although most prototype pressure garments are fabricated with materials that are oxygen and vacuum compatible, the compatibility is not documented and certified. The Z-2 design and hardware will be approved for chamber use. Additionally, the Z-2 takes steps toward incorporating EMU system-level interfaces and components. Interfaces such as integrated ventilation lines, integrated audio, purge and relief valves, and volumes reserved for the PLSS feedwater supplies are examples of interfaces that are included. However, the PLSS and display and control interfaces have not been fully defined, thereby requiring additional maturation and design changes for the Z-3 prototype that will be used in the Chamber B human-rated thermal, vacuum advanced EMU demonstration. As a clarification, the Z-2 is not a follow-on to the Z-1. The Z-1 prototype was one of several pressure garment mobility demonstrators that contributed to the decisions NASA made regarding which mobility joints were specified in the Z-2 contract. However, the Z-3 pressure garment will be a further maturation of Z-2. Z-2 is new technology and is still in the development stage. This paper is sometimes limited in the detail it provides because of this.

A research program was funded by the European space agency (ESA) to improve and optimize the shields used to protect the manned elements of the international space station (ISS) against impacts of micro-meteoroids and orbital debris. After a review of existing shielding systems and after a series of light gas gun (LGG) experiments to screen interesting new materials and configurations, the research focused on shields with a metallic outer bumper, an intermediate stuffing and an inner metallic wall (representing the pressure shell of a manned spacecraft). Additional LGG experiments were performed on several configurations, with bumpers containing aluminum foam or made from titanium and aluminum super-alloys and with several combinations of stuffing materials. The comparison of the test results showed that ceramic cloth (Nextel) plus aramid fabric (both 2D and 2.5D Kevlar weaving) used as intermediate bumper gave a good protection compared to the overall area density requested. Configurations with by-layered aluminum foam bumpers (sandwich panels with asymmetric Al face sheets and a core made from Al foam) and Kevlar stuffing showed excellent resistance to normal impacts at about 6.5 km/s. However, the influence of material properties varying from batch to batch and threshold phenomena made ranking among the tested options rather difficult. The test campaign showed that it was rather difficult to improve over the already good ballistic performances of the debris shields developed by Alenia Spazio for the ISS manned elements. The by-layered Al-foam bumper and Kevlar stuffing configuration was selected for additional tests, including low velocity and oblique impacts, to develop ballistic limit curves.

The normal working and living areas of the astronauts are designed to provide an acceptable level of protection against the hazards of ionizing radiation of the space environment. Still there are occasions when they must don a spacesuit designed mainly for environmental control and mobility and leave the confines of their better-protected domain. This is especially true for deep space exploration. The impact of spacesuit construction on the exposure of critical astronaut organs will be examined in the ionizing radiation environments of free space, the lunar surface and the Martian surface. The computerized anatomical male model is used to evaluate astronaut self-shielding factors and to determine space radiation exposures to critical radiosensitive human organs.

The structural efficiency of carbon-epoxy tapered struts is considered through trade studies, detailed analysis, manufacturing and experimentation. Since some of the lunar lander struts are more highly loaded than struts used in applications such as satellites and telescopes, the primary focus of the effort is on these highly loaded struts. Lunar lander requirements include that the strut has to be tapered on both ends, complicating the design and limiting the manufacturing process. Optimal stacking sequences, geometries, and materials are determined and the sensitivity of the strut weight to each parameter is evaluated. The trade study results indicate that the most efficient carbon-epoxy struts are 30 percent lighter than the most efficient aluminum-lithium struts. Structurally efficient, highly loaded struts were fabricated and loaded in tension and compression to determine if they met the design requirements and to verify the accuracy of the analyses. Experimental evaluation of some of these struts demonstrated that they could meet the greatest Altair loading requirements in both tension and compression. These results could be applied to other vehicles requiring struts with high loading and light weight.

One of the main challenges to be faced in deep space missions is to protect the health and ensure the maximum efficiency of the crew by preparing methods of prevention and in situ diagnosis. Indeed, the hostile environment causes important health problems, ranging from muscle atrophy, osteopenia, and immunological and metabolic alterations due to microgravity, to an increased risk of cancer caused by exposure to radiation. It is, therefore, necessary to provide new methods for the real-time measurement of biomarkers suitable for deepening our knowledge of the effects of space flight on the balance of the immune system and for allowing the monitoring of the astronaut's health during long-term missions. APHRODITE will enable human space exploration because it fills this void that affects both missions in LEO and future missions to the Moon and Mars. Its scientific objectives are the design, production, testing, and in-orbit demonstration of a compact, reusable, and reconfigurable system for performing the real-time analysis of oral fluid samples in manned space missions. In the frame of this project, a crew member onboard the ISS will employ APHRODITE to measure the selected target analytes, cortisol, and dehydroepiandrosterone sulfate (DHEA-S), in oral fluid, in four (plus one additional desired session) separate experiment sessions. The paper addresses the design of the main subsystems of the analytical device and the preliminary results obtained during the first implementations of the device subsystems and testing measurements on Earth. In particular, the system design and the experiment data output of the lab-on-chip photosensors and of the front-end readout electronics are reported in detail along with preliminary chemical tests for

NASA's next generation space suit system will place new demands on the fan used to circulate breathing gas through the ventilation loop of the portable life support system. Long duration missions with frequent extravehicular activities (EVAs), the requirement for significant increases in reliability and durability, and a mission profile that imposes strict limits on weight, volume and power create the basis for a set of requirements that demand more performance than is available from existing fan designs. This paper describes the development of a new fan to meet these needs. A centrifugal fan was designed with a normal operating speed of approximately 39,400 rpm to meet the ventilation flow requirements while also meeting the aggressive minimal packaging, weight and power requirements. The prototype fan also operates at 56,000 rpm to satisfy a second operating condition associated with a single fan providing ventilation flow to two spacesuits connected in series. This fan incorp...

NASA's next generation space suit system will place new demands on the fan used to circulate breathing gas through the ventilation loop of the portable life support system. Long duration missions with frequent extravehicular activities (EVAs), the requirement for significant increases in reliability and durability, and a mission profile that imposes strict limits on weight, volume and power create the basis for a set of requirements that demand more performance than is available from existing fan designs. This paper describes the development of a new fan to meet these needs. A centrifugal fan was designed with a normal operating speed of approximately 39,400 rpm to meet the ventilation flow requirements while also meeting the aggressive minimal packaging, weight and power requirements. The prototype fan also operates at 56,000 rpm to satisfy a second operating condition associated with a single fan providing ventilation flow to two spacesuits connected in series. This fan incorp...

The purpose of this study was to characterize hand strength, while wearing a Phase VI Extravehicular Activity (EVA) glove in an Extravehicular Mobility Unit (EMU) suit. Three types of data were collected: hand grip, lateral pinch, and pulp-2 pinch, wider three different conditions: bare-handed, gloved with no Thermal Micrometeoroid Garment (TMG), and glove with TMG. In addition, during the gloved conditions, subjects were tested when unpressurized and pressurized (43 psi). As a percentage of bare-hand strength, the TMG condition showed reduction in grip strength to 55% unpressurized and 46% pressurized. Without the TMG, grip strength increased to 66% unpressurized and 58% pressurized of barehand strength. For lateral pinch strength, the reduction in strength was the same for both pressure conditions and with and without the TMG, about 8.5% of bare-hand-Pulp-2 pinch strength with no TMG showed an increase to 122% unpressurized and 115% pressurized ofbare-hand strength. While wearing the TMG, pulp-2 pinch strength was 115% of bare-hand strength for both pressure conditions.

The gloved hand is one of an astronaut's primary means of interacting with the environment, and any restrictions imposed by the glove can strongly affect performance during extravehicular activity (EVA). Glove restrictions have been the subject of study for decades, yet previous studies have generally been unsuccessful in quantifying glove mobility and tactility. Past studies have tended to focus on the dexterity, strength, and functional performance of the gloved hand; this provides only a circumspect analysis of the impact of each type of restriction on the glove's overall capability. The aim of this study was to develop novel capabilities to provide metrics for mobility and tactility that can be used to assess the performance of a glove in a way that could enable designers and engineers to improve their current designs. A series of evaluations were performed to compare unpressurized and pressurized (4.3 psi) gloved conditions with the ungloved condition. A second series of evaluations were performed with the Thermal Micrometeoroid Garment (TMG) removed. This series of tests provided interesting insight into how much of an effect the TMG has on gloved mobility-in some cases, the presence of the TMG restricted glove mobility as much as pressurization did. Previous hypotheses had assumed that the TMG would have a much lower impact on mobility, but these results suggest that an improvement in the design of the TMG could have a significant impact on glove performance. Tactility testing illustrated the effect of glove pressurization, provided insight into the design of hardware that interfaces with the glove, and highlighted areas of concern. The metrics developed in this study served to benchmark the Phase VI EVA glove and to develop requirements for the next-generation glove for the Constellation program.

The purpose of the current study was to quantify finger tactility, while wearing a Phase VI Extravehicular Activity (EVA) glove. Subjects were fully suited in an Extravehicular Mobility Unit (EMU) suit. Data was collected under three conditions: bare-handed, gloved at 0 psi, and gloved at 4.3 psi. In order to test tactility, a series of 30 tactile stimuli (bumps) were created that varied in both height and width. With the hand obscured, subjects applied pressure to each bump until detected tactilely. The amount of force needed to detect each bump was recorded using load cells located under a force-plate. The amount of force needed to detect a bump was positively related to width, but inversely related to height. In addition, as the psi of the glove increased, more force was needed to detect the bump. In terms of application, it was possible to determine the optimal width and height a bump needs to be for a specific amount of force applied for tactility.

Extravehicular activity (EVA) is one of the most critical enabling capabilities for human spaceflight. Performing EVA is both technically challenging and physically demanding, requiring many hours of training and detailed preparation. As a result of working and training in the extravehicular mobility unit (EMU) spacesuit, many astronauts sustain musculoskeletal and minor injuries. Although injuries are typically minor and self-limited, they have the potential to impact mission success. We outline our research methodology to investigate EVA injury ultimately providing solutions that can be implemented both in the EMU and in future spacesuit designs. We review the issues and mechanisms causing injury as documented in the literature. The result of this work will be an injury database with input from many NASA stakeholders. We also highlight our work to model the astronaut performing realistic EVA motions to study the interaction between the person and the suit. Spacesuit models of the EMU and Mark III spacesuits will be used in combination with a human body model driven by the biomechanics of EVA motions. We will investigate joint torque, muscle activation, and contact pressure between the body and suit. This modeling effort informs our spacesuit injury countermeasure designs and recommendations. We present our design process for protection devices that ameliorate current astronaut suitinduced injuries.

Earth entry system options for human return missions from the Moon and Mars were analyzed and compared to identify trends among the configurations and trajectory options and to facilitate informed decision making at the exploration architecture level. Entry system options included ballistic, lifting capsule, biconic, and lifting body configurations with direct entry and aerocapture trajectories. For each configuration and trajectory option, the thermal environment, deceleration environment, crossrange and downrange performance, and entry corridor were assessed. In addition, the feasibility of a common vehicle for lunar and Mars return was investigated. The results show that a low lift-to-drag ratio (L/D = 0.3) vehicle provides sufficient performance for both lunar and Mars return missions while providing the following benefits: excellent packaging efficiency, low structural and TPS mass fraction, ease of launch vehicle integration, and system elegance and simplicity. Numerous configuration options exist that achieve this L/D.

Objective To better study human motion inside the space suit and suit-related contact, a multifactor statistical model was developed to predict torso body shape changes and lumbar motion during suited movement by using fabric strain sensors that are placed on the body. Background Physical interactions within pressurized space suits can pose an injury risk for astronauts during extravehicular activity (EVA). In particular, poor suit fit can result in an injury due to reduced performance capabilities and excessive body contact within the suit during movement. A wearable solution is needed to measure body motion inside the space suit. Methods An array of flexible strain sensors was attached to the body of 12 male study participants. The participants performed specific static lumbar postures while 3D body scans and sensor measurements were collected. A model was created to predict the body shape as a function of sensor signal and the accuracy was evaluated using holdout cross-validation...

A detailed space suit computational model is being developed at the Langley Research Center for radiation exposure evaluation studies. The details of the construction of the space suit are critical to estimation of exposures and assessing the risk to the astronaut on EVA. Past evaluations of space suit shielding properties assumed the basic fabric layup (Thermal Micrometeoroid Garment, fabric restraints, and pressure envelope) and LCVG could be homogenized as a single layer overestimating the protective properties over 60 percent of the fabric area. The present space suit model represents the inhomogeneous distributions of LCVG materials (mainly the water filled cooling tubes). An experimental test is performed using a 34-MeV proton beam and high-resolution detectors to compare with model-predicted transmission factors. Some suggestions are made on possible improved construction methods to improve the space suit's protection properties.

Introduction Scarcity of operating rooms and personal protective equipment in far-forward field settings make surgical infections a potential concern for combat mortality and morbidity. Surgical and transport personnel also face infectious risks from bodily fluid exposures. Our study aimed to describe the serial, proof-of-concept testing of the SurgiBox technology: an inflatable sterile environment that addresses the aforementioned problems, fits on gurneys and backpacks, and drapes over incisions. Materials and Methods The SurgiBox environmental control unit and inflatable enclosure were optimized over five generations based on iterative feedback from stakeholders experienced in surgery in austere settings. The airflow system was developed by analytic modeling, verified through in silico modeling in SOLIDWORKS, and confirmed with prototype smoke-trail checking. Particulate counts evaluated the enclosure’s ability to control and mitigate users’ exposures to potentially infectious co...

This study aimed to develop and deploy a novel motion capture system capable of measuring space suit kinematics in an underwater test environment. The system was built using off-the-shelf, dive-rated hardware and open source software tools. The new system performance was validated by comparing the measurement outcome to a reference motion capture system in a dry-land condition. Measurement errors, defined as the linear distances of the marker position measurements between the developed and reference system, were 1.9 cm root-meansquare error (RMSE) with a 50-percentile error of 1.3 cm and a 95-percentile error of 3.6 cm. Measurement error tended to increase with motion speed. Similarly, the error showed a slight tendency of increasing with the distance from the center of the calibrated capture volume. However, the trend was not clearly identifiable. A second metric of system accuracy performance was calculated by assessing the wand length. The system was deployed underwater and tested for space suit kinematic assessments. Given the speed and range of space suit motions underwater, the measurement error of the developed system underwater was estimated to be approximately 1.39 cm and the wand length estimation error had a RMSE of 0.67 cm with a 50-percentile error of 0.51 cm and a 95-percentile error of 0.92 cm. Overall, the new system showed reliable and acceptably accurate kinematic measurements comparable to a common dry land motion capture system and can provide usable suit performance metrics in a simulated microgravity environment. Relevance to industry: An underwater motion capture system was developed using off-the-shelf equipment. The new system was deployed to assess the kinematic mobility of space suits. The system can offer an inexpensive solution where traditional motion capture system may not be applicable.

Extravehicular activity (EVA) spacesuits frequently remain bulky and pressurized, which impedes astronauts' ability to engage with the proximate environment and with fellow astronauts. In this project, a concept prototype for a sensate skin intended for the exterior of an EVA suit is manufactured using commercially available electronic fabric sensors. This prototype is then shown to discriminate between surfaces relevant to space explorers (metallic objects, rocky surfaces, and spacesuit gloves), implying that each surface can be translated into a unique sensory experience. Specifically, haptic actuators flush against the astronaut's biological skin can transduce sensory data from the external environment through the pressurized suit, allowing the astronaut to feel touch input right through the spacesuit. The key contribution of this work is to introduce a plausible application area for space-resilient electronic textiles using commercial off-the-shelf fabric sensors for demonstration.

Planning for long-duration lunar and Mars exploration missions must provide appropriate human support accommodations to optimize crew comfort, health, morale, performance and safety. This paper presents considerations and concepts for the exterior and interior architectures for lunar and Mars surface habitat modules. The paper addresses two general types of habitat structures: vertical and horizontal. Both types have strictly constrained diameter and length dimensions which must comply with Earth launch vehicles, landing limitations and surface mobility restrictions. Interior configurations discussed in the paper are based upon a design approach utilizing "inflatable" soft pliable laminated wall structures that can provide large multi-functional interior spaces. A special "pop-out" design concept enables floors and utility interfaces to be pre-integrated in a manner that avoids complex and time-consuming construction on the lunar/planetary surface. Both of these construction types offer special advantages, and also impose special planning considerations to optimize benefits. Goals are to maximize habitability, crew safety, spatial efficiency, functional versatility and EVA access/egress from the surface. Illustrative concepts are presented showing examples of interior layouts, functional areas and equipment systems.

The Porous Tube Plant Nutrient Delivery System or PTPNDS (U. S. Patent #4,926,585) has been under development for the past six years with the goal of providing a means for culturing plants in microgravity, specifically providing water and nutrients to the roots. Direct applications of the PTPNDS include plant space biology investigations on the Space Shuttle and plant research for life support in Space Station Freedom. In the past, we investigated various configurations, the suitability of different porous materials, and the effects of pressure and pore size on plant growth. Current work is focused on characterizing the physical operation of the system, examining the effects of solution aeration, and developing prototype configuratmns for the Plant Growth Unit (PGU), the flight system for the Shuttle mid-deck. Future developments will involve testing on KC-135 parabolic flights, the design of flight hardware and testing aboard the Space Shuttle.

Investigative procedures were approved by Henry Ford Human Investigation Committee and NASA Johnson Space Center Committee for Protection of Human Subjects. Informed consent was obtained. Authors evaluated ability of nonphysician crewmember to obtain diagnostic-quality musculoskeletal ultrasonographic (US) data of the shoulder by following a just-in-time training algorithm and using real-time remote guidance aboard the International Space Station (ISS). ISS Expedition-9 crewmembers attended a 2.5-hour didactic and hands-on US training session 4 months before launch. Aboard the ISS, they completed a 1-hour computer-based Onboard Proficiency Enhancement program 7 days before examination. Crewmembers did not receive specific training in shoulder anatomy or shoulder US techniques. Evaluation of astronaut shoulder integrity was done by using a Human Research Facility US system. Crew used special positioning techniques for subject and operator to facilitate US in microgravity environment. Common anatomic reference points aided initial probe placement. Real-time US video of shoulder was transmitted to remote experienced sonologists in Telescience Center at Johnson Space Center. Probe manipulation and equipment adjustments were guided with verbal commands from remote sonologists to astronaut operators to complete rotator cuff evaluation. Comprehensive US of crewmember's shoulder included transverse and longitudinal images of biceps and supraspinatus tendons and articular cartilage surface. Total examination time required to guide astronaut operator to acquire necessary images was approximately 15 minutes. Multiple arm and probe positions were used to acquire dynamic video images that were of excellent quality to allow evaluation of shoulder integrity. Postsession download and analysis of high-fidelity US images collected onboard demonstrated additional anatomic detail that could be used to exclude subtle injury. Musculoskeletal US can be performed in space by minimally trained operators by using remote guidance. This technique can be used to evaluate shoulder integrity in symptomatic crewmembers after strenuous extravehicular activities or to monitor microgravity-associated changes in musculoskeletal anatomy. Just-in-time training, combined with remote experienced physician guidance, may provide a useful approach to complex medical tasks performed by nonexperienced personnel in a variety of remote settings, including current and future space programs.

The fit of a spacesuit has been identified as a crucial factor that will determine its usability. Therefore, because one-size-fits-all spacesuits seldom fit any wearer well, and because individually tailored spacesuits are costly, the University of Maryland has conducted research into a resizable Extravehicular Activity (EVA) suit. This resizing is accomplished through a series of cable-driven parallel manipulators, which are used to adjust the distance between plates and rings built into a soft space suit. These actuators, as well as enabling passive suit resizing, could be used to actively assist the astronaut's motion, decreasing the torques that must be applied for movement in a pressurized suit. This thesis details the development and testing of an arm test section, which is used to better understand the dynamics of a more complex torso-limb system.

A NASA-funded study of astronauts freshly returned from six-month stays aboard the International Space Station found that their muscle volume was about 15 percent smaller and 25 percent weaker than when they left. The main cause being the long-term exposition to low-gravity environments; while other studies found similar degenerative effects over their cardiovascular system.

On Earth, this approaches what we see in aging populations in comparisons of a 20-year-old versus an 80-year-old. In line with this, similar effects can be caused by over 30 different types of muscle-weakening hereditary diseases, medically diagnosed as ‘muscular dystrophy’; while, according to the WHO, about 32% of all human global deaths in 2019 were caused by cardiovascular diseases, making it the single leading cause of human death on Earth.

Thus, the impact of this project is two-folded, aiming to tackle main degenerative affections, both inside planet Earth, as well as out in space.

The ‘Bio-Soft Space Suit’ is an indoors space suit for long-term human-led missions which uses Soft Pneumatic Actuators (SPA) to apply rhythmic pressure in strategic points of the human body in order to stimulate muscle activity and cardiovascular flow. The system of actuators used in the space suit, which we call ‘Bio-Soft Actuator System’ can be used independently, as a medical device, for the treatment of muscular and cardiovascular diseases in medical centers on Earth.

Furthermore, the Bio-Soft Space Suit seeks to critically address diverse human matters of life in space which go beyond medical implications. Such considerations include reflections over gender diversity and women participation in the space sector, thus, the development of a version tailored for female astronauts, considering their particular characteristics and needs; as well as reflections over cultural diversity in space, as this project seeks to question the idea of a single space design canon for everyone. Therefore, the patterns of the suit in this case are referenced in the clothing, accessories and patterns of two pre-Incan important figures: the Lord of Sipan, and the Dame of Cao, as an appreciation of Peruvians’ ancestral legacy in the study of astronomy as a fundamental part of their worldview.