Space Suit System Research Articles

Spacesuit contact with wearer: Analysis and visualization

Spacesuits are pressurized garments used in space missions to protect crewmembers from the hazards of space. The wearer moves the suit through contact on the interior of the suit with their body. This contact between the suit and body is a critical factor for the fit, mobility, and comfort of the spacesuit. Part of the utility of spacesuits is providing a pressurized environment needed for astronauts to survive. This pressurization turns the spacesuit into a semi rigid enclosure around the wearer, changing how the suit interacts with the body inside. To better understand the spacesuit-wearer contact, a study was performed wherein test subjects from Johnson Space Center's (JSC) spacesuit test subject pool wore the Extravehicular Mobility Unit (EMU) spacesuit in a variety of configurations, including with and without suit pressurization, and held seven different poses. While holding each pose, the test subject reported the intensity and location of their perceived contact with the suit. This data was converted to a binary contact/no contact variable then analyzed to determine the effect that pressurization and pose had on perceived contact. As a result, overall contact trends can be understood and applied to the design of future spacesuit systems.

Design and development of a space suit mock-up for VR-based EVA research and simulation

Earth-based Extra-Vehicular Activity (EVA) simulation has always been the subject of study by space agencies aimed at reproducing the most accurate experience for astronauts. Challenges and limitations are many and not limited to the natural Laws; the space suit system, an integral part of the successful Extra-Vehicular Activity (EVA), must present the same conditions to the user as it would in the environment of operation. NASA is the most prominent example of a long tradition for a faithful simulation of outer space in which astronauts operate during EVAs: the Neutral Buoyancy Lab at Johnson Space Center in Houston still represents the standard when it comes to providing astronauts with a realistic experience. However, such infrastructures can be difficult to access, considering the renewed interest in space, which is advocated by new private players looking into Low Earth Orbit (LEO) access in the short to medium term. Virtual Reality (VR) provides users with new, flexible, and relatively inexpensive ways of simulating the space environment during an EVA, without the need to build large-scale pools and mock-ups of vehicles. In this paper, it'll be shown how the Sasakawa International Center for Space Architecture (SICSA) at the University of Houston is working to provide students and researchers with a Virtual Reality (VR)-based infrastructure to simulate EVAs and Space Architectures, which are also designed in-situ. An essential component to achieve realism of experience is the design and construction, done entirely in-house, of a mock-up of the latest NASA Artemis Exploration Extra Vehicular Mobility Unit (xEMU) space suit, to recreate the physical constraints that such a garment imposes on astronauts, which cannot be entirely simulated with VR. It'll be shown how this space suit replica substantially enhances the accuracy of the experience, by replicating the mechanisms of the xEMU suit, complementing the virtual experience provided at the same time.

Comparison of air exhausts for surgical body suits (space suits) and the potential for periprosthetic joint infection

Periprosthetic joint infection is a major complication of total joint replacement surgery and is associated with significant morbidity, mortality and financial burden. Surgical body suits (space suits), originally designed to reduce the incidence of infection, have paradoxically been implicated in increased periprosthetic joint infection rates recently. Air exhausted from space suits may contribute to this increased rate of periprosthetic joint infection. To investigate the flow of air exhausted from space suits commonly used in modern operating theatres. The exhaust airflow patterns of four commercially available space suit systems were compared using a fog machine and serial still photographs. The space suit systems tested all air exhausted into the operating room. The single fan systems with a standard surgical gown exhausted air laterally from the posterior gown fold at approximately the level of the surgical field. The single fan system with a dedicated zippered suit exhausted air at a level below the surgical field. The dual fan system exhausted air out of the top of the helmet at a level above the surgical field. Space suit systems currently in use in joint replacement surgery differ significantly from traditional body exhaust systems; rather than removing contaminated air from the operating environment, modern systems exhaust this air into the operating room, in some cases potentially towards the sterile instrument tray and the surgical field.

Proof of concept demonstration of novel technologies for lunar spacesuit dust mitigation

A recent report by NASA identified dust/particulate mitigation techniques as a highly relevant study for future long-term planetary exploration missions (NASA, 2015). The deleterious effects of lunar dust on spacesuits discovered during the Apollo missions has compelled NASA to identify dust mitigation as a critical path for potential future lunar, asteroid and Mars missions. The complexity of spacesuit design has however constrained integrating existing dust cleaning technologies, formerly demonstrated on rigid surfaces, into the spacesuit system. Accordingly, this research is investigating novel methods to integrate dust mitigation technologies for use on spacesuits. We examine utilizing a novel combination of active and passive technologies integrated into the spacesuit outerlayer to alleviate dust contamination. Leveraging two specific technologies, the Electrodynamics Dust Shield (EDS) active technology and Work Function Matching Coating (WFM) passive technology, developed by NASA for rigid surfaces, we apply new high performance materials such as the Carbon Nanotube (CNT) flexible fibers to develop a spacesuit-integrated dust cleaning system. Through experiments conducted using JSC-1A lunar dust simulant on coupons made of spacesuit outerlayer material, feasibility of integrating the proposed dust cleaning system and its performance were assessed. Results from these preliminary experiments show that the integrated dust cleaning system is capable of removing 80–95% of dust from the spacesuit material demonstrating proof of concept. This paper describes the techniques and results from the experiments. Future challenges of implementing the proposed approach into fight suits are identified.

Crew Recovery and Contingency Planning for a Manned Stratospheric Balloon Flight - the StratEx Program.

The StratEx program used a self-contained space suit and balloon system to loft pilot Alan Eustace to a record-breaking altitude and skydive from 135,897 feet (41,422 m). After releasing from the balloon and a stabilized freefall, the pilot safely landed using a parachute system based on a modified tandem parachute rig. A custom spacesuit provided life support using a similar system to NASA's (National Aeronautics and Space Administration; Washington, DC USA) Extravehicular Mobility Unit. It also provided tracking, communications, and connection to the parachute system. A recovery support team, including at least two medical personnel and two spacesuit technicians, was charged with reaching the pilot within five minutes of touchdown to extract him from the suit and provide treatment for any injuries. The team had to track the flight at all times, be prepared to respond in case of premature release, and to operate in any terrain. Crew recovery operations were planned and tailored to anticipate outcomes during this novel event in a systematic fashion, through scenario and risk analysis, in order to minimize the probability and impact of injury. This analysis, detailed here, helped the team configure recovery assets, refine navigation and tracking systems, develop procedures, and conduct training. An extensive period of testing and practice culminated in three manned flights leading to a successful mission and setting the record for exit altitude, distance of fall with stabilizing device, and vertical speed with a stabilizing device. During this mission, recovery teams reached the landing spot within one minute, extracted the pilot, and confirmed that he was not injured. This strategy is presented as an approach to prehospital planning and care for improved safety during crew recovery in novel, extreme events. Menon AS , Jourdan D , Nusbaum DM , Garbino A , Buckland DM , Norton S , Clark JB , Antonsen EL . Crew recovery and contingency planning for a manned stratospheric balloon flight - the StratEx program. Prehosp Disaster Med. 2016;31(5):524-531.

Microgravity Simulator Based on Air Levitation for Astronauts EVA Operation Training

Because of the microgravity environment of the space and mobility restriction by pressurized spacesuit, astronaut extravehicular operation is quite different from that in the ground. For ensuring high reliability of extravehicular operations, the astronauts need to do a great deal of training in simulated environments. A 3-dof of micro-gravity operation training system is designed in the paper, and the kinematics and dynamics of the interaction between the space station system and spacesuit system were simulated. Pressure and flow velocity distributions in the air orifice and air cavity were calculated by FLUENT. Experiments on the bearing capacity characteristic were carried out. The carrying capacities of the air bearing in different air pressures were achieved. Experiments validated the simulation analysis. The research provides the basis for the development of multi-degree of freedom space microgravity ground simulation technology, provides a basis for further development and application of flotation technology as well.

The Soviet/Russian spacesuit history: Part III—The European connection

The European spacesuit system (ESSS) initiated by the European Space Agency (ESA) in the late 1980s had many similarities with the Soviet/Russian ORLAN spacesuit system, due to the Hermes system requirements. First, direct contacts in 1989 permitted closer comparison of the two suit systems, and soon the ORLAN manufacturer Zvezda could be contracted as support to the European spacesuit team. In particular, the suit enclosure design and predevelopment testing and operational analysis were performed in close cooperation between Zvezda and the European team under Dornier. With the changing system requirements and a closer cooperation between ESA and the new Russian Space Agency (RKA) a new joint spaceplane/stations mission scenario came about. This scenario could be served by one spacesuit system, EVA SUIT 2000, which was to be jointly developed by a team headed by Zvezda and Dornier for ESA and RKA. ORLAN-DMA and ESSS experience and hardware were the initial platforms for these activities to create a new generation spacesuits for the Mir 2 and later the ISSs. A suit demonstrator was manufactured and tested by the end of 1994 when ESA stopped its spacesuit development activities and the joint EVA SUIT 2000 project was terminated. However, many of the features designed, manufactured and tested for the EVA SUIT 2000 were then implemented by Zvezda in the new Russian spacesuit system ORLAN-M, now in full operation onboard the ISS.

Spotlight on obstetrics

The European spacesuit system (ESSS) initiated by the European Space Agency (ESA) in the late 1980s had many similarities with the Soviet/Russian ORLAN spacesuit system, due to the Hermes system requirements. First, direct contacts in 1989 permitted closer comparison of the two suit systems, and soon the ORLAN manufacturer Zvezda could be contracted as support to the European spacesuit team. In particular, the suit enclosure design and predevelopment testing and operational analysis were performed in close cooperation between Zvezda and the European team under Dornier.With the changing system requirements and a closer cooperation between ESA and the new Russian Space Agency (RKA) a new joint spaceplane/stations mission scenario came about. This scenario could be served by one spacesuit system, EVA SUIT 2000, which was to be jointly developed by a team headed by Zvezda and Dornier for ESA and RKA. ORLAN-DMA and ESSS experience and hardware were the initial platforms for these activities to create a new generation spacesuits for the Mir 2 and later the ISSs.A suit demonstrator was manufactured and tested by the end of 1994 when ESA stopped its spacesuit development activities and the joint EVA SUIT 2000 project was terminated. However, many of the features designed, manufactured and tested for the EVA SUIT 2000 were then implemented by Zvezda in the new Russian spacesuit system ORLAN-M, now in full operation onboard the ISS.

Extravehicular activity space suit interoperability

The European Agency (ESA) and the Russian Space Agency (RKA) are jointly developing a new space suit system for improved extravehicular activity (EVA) capabilities in support of the MIR Space Station Programme, the EVA Suit 2000. Recent national policy agreements between the U.S. and Russia on planned cooperations in manned space also include joint extravehicular activity (EVA). With an increased number of space suit systems and a higher operational frequency towards the end of this century an improved interoperability for both routine and emergency operations is of eminent importance. It is thus timely to report the current status of ongoing work on international EVA interoperability being conducted by the Committee on EVA Protocols and Operations of the International Academy of Astronautics initialed in 1991. This paper summarises the current EVA interoperability issues to be harmonised and presents quantified vehicle interface requirements for the current U.S. Shuttle EMU and Russian MIR Orlan DMA and the new European/Russian EVA Suit 2000 extravehicular systems. Major critical/incompatible interfaces for suits/mothercraft of different combinations arc discussed, and recommendations for standardisations given.

EVA 2000: A European/Russian space suit concept

For the European manned space activities an EVA space suit system was being developed in the frame of the Hermes Space Vehicle Programme of the European Space Agency (ESA). The space suit was to serve the needs for all relevant extravehicular activities for the Hermes/Columbus operations planned to begin in 2004. For the present Russian manned space programme the relevant EVAs are performed by the Orlan-DMA semi-rigid space suit. The origin of its development reaches back to the 1970s and has since been adapted to cover the needs for extravehicular activities on Salyut and MIR until today. The latest modification of the space suit, which guaranteed its completely self-contained operation, was made in 1988. However, Russian specialists considered it necessary to start developing an EVA space suit of a new generation, which would have improved performance and would cover the needs by the turn of the century and into the beginning of the next century. Potentially these two suit developments could have a lot in common based on similarities in present concepts. As future manned space activities become more and more an international effort, a safe and reliable interoperability of the different space suit systems is required. Based on the results of the Munich Minister Conference in 1991, the European Space Agency and the Russian Space Agency agreed to initiate a requirements analysis and conceptual design study to determine the feasibility of a joint space suit development, EVA 2000. The design philosophy for the EVA 2000 study was oriented on a space suit system design of: • —space suit commonality and interoperability • —increased crew productivity and safety • —increase in useful life and reduced maintainability • —reduced development and production cost. The EVA 2000 feasibility study was performed in 1992, and with the positive conclusions for EVA 2000, this approach became the new joint European/Russian EVA Suit 2000 Development Programme. This paper gives an overview of the results of the feasibility study and presents the joint requirements and the proposed design concept of a jointly developed European/Russian space suit.

EVA suit 2000: A joint European/Russian space suit design

A feasibility study in 1992 showed the benefits of a common European/Russian space suit development, EVA Suit 2000, replacing the Russian space suit Orlan-DMA and the planned European Hermes EVA space suit at the turn of the century. This EVA Suit 2000 is a joint development initiated by the European Space Agency (ESA) and the Russian Space Agency (RKA). The main objectives of this development program are: • • first utilization aboard the Russian Space Station MIR-2 • • performance improvement with respect to current operational suits • • development cost reduction. Russian experience gained with the present extravehicular activity (EVA) suit on the MIR Space Station and extensive application of European Technologies will be needed to achieve these ambitious goals. This paper presents the current status of the development activities, the space suit system design and concentrates in more detail on life support aspects. Specific subjects addressed will include the overall life support conceptual architecture, design features, crew comfort and operational considerations.

The EVA space suit development in Europe

The progress of the European EVA space suit predevelopment activities has resulted in an improved technical reference concept, which will form the basis for a start of the Phase C D development work in 1992. Technology development work over the last 2 years has resulted in a considerable amount of test data and a better understanding of the characteristics and behaviour of individual parts of the space suit system, in particular in the areas of suits' mobility and life support functions. This information has enabled a consolidation of certain design features on the one hand, but also led to the challenging of some of the design solutions on the other hand. While working towards an improved situation with respect to the main design drivers mass and cost, the technical concept has been improved with respect to functional safety and ease of handling, taking the evolving Hermes spaceplane requirements into consideration. Necessary hardware and functional redundancies have been implemented taking the operational scenario with Hermes and Columbus servicing into consideration. This paper presents the latest design status of the European EVA space suit concept, with particular emphasis on crew safety, comfort and productivity, in the frame of the predevelopment work for the European Space Agency.

The European space suit, a design for productivity and crew safety

In order to fulfil the two major mission objectives, i.e. support planned and unplanned external servicing of the COLUMBUS FFL and support the HERMES vehicle for safety critical operations and emergencies, the European Space Suit System baseline configuration incorporates a number of design features, which shall enhance the productivity and the crew safety of EVA astronauts.The work in EVA is today - and will be for several years - a manual work. Consequently, to improve productivity, the first challenge is to design a suit enclosure which minimizes movement restrictions and crew fatigue. It is covered by the “ergonomic” aspect of the suit design.Furthermore, it is also necessary to help the EVA crewmember in his work, by giving him the right information at the right time. Many solutions exist in this field of Man-Machine Interface, from a very simple system, based on cuff check lists, up to advanced systems, including Head-Up Displays.The design concept for improved productivity encompasses following features: •• easy donning/doffing thru rear entry,•• suit ergonomy optimisation,•• display of operational information in alpha-numerical and graphical from, and•• voice processing for operations and safety critical information.Concerning crew safety the major design features are: •• a lower R-factor for emergency EVA operations thru incressed suit pressure,•• zero prebreath conditions for normal operations,•• visual and voice processing of all safety critical functions, and•• an autonomous life support system to permit unrestricted operations around HERMES and the CFFL.The paper analyses crew safety and productivity criteria and describes how these features are being built into the design of the European Space Suit System.

Simulation by personal workstation for man-machine interface design

This paper presents a simulation tool which has been developed for Man-Machine interface (MMI) design study, in the context of the European EVA Space Suit System development, under contract of ESA/ESTEC. The main new point is that this simulation is based on a personal workstation, and not on a heavy real-time computer, as in most simulation centres. It will be used in ESTEC to perform low cost simulations of the front part of a manned system, to improve and develop MMI with efficiency.

Spacesuit systems and penalties for interplanetary missions.

Covers advancements in spacecraft and tactical and strategic missile systems, including subsystem design and application, mission design and analysis, materials and structures, developments in space sciences, space processing and manufacturing, space operations, and applications of space technologies to other fields.