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The series of celebrated and grand accomplishments and progress of mankind in space exploration make people more intelligent, quixotic, imaginative, creative and realistic. Also, these imply vision for the future, further exploration and taking advantage of the Universe, for human benefits and sustainability, gaining scientific knowledge and developing engineering structures to that end. The most modern Earth and Universe observation spacecraft to date are now equipped with large lightweight and flexible structures, such as antennas, telescopes, and extendable elements, including the incorporation of more complex and larger appendages with high precision for scientific applications. These demand more stringent structural integrity requirements to minimize performance degradation due to structural damages. In addition, spacecraft structures weight and their associated manufacturing costs should be minimized, most appropriate materials should be utilized, assembly costs should be reduced and fewer parts should be opted, or one-piece more complex configuration parts should be produced. Various sensors, actuators and control technology could be employed to reduce structural damage. Associated with these, appropriate sensors configuration and strategies for their deployment are required to accurately detect failures in the most critical areas of the structure. Spacecraft structural integrity is subject to a series of prevailing loading due to thermo-structural dynamics and environmental effects from design, manufacturing, launching and operation during their pathways to meet a multitude of objectives under a myriad of requirements and constraints. To that end, the objective of the present paper is to provide an overview on spacecraft structural integrity covering a host of selected concepts, design, methods and engineering to maintain structural integrity of space vehicles and associated sub-structures. In spite of citing examples drawn from small satellite situations under vibro-acoustic and environmental thermal loading, the overriding issues addressed could be extended to more general situations. An infographic is presented to map out the state of affairs to be addressed for structural integrity considerations. [Display omitted] The present paper is to provide an overview on spacecraft structural integrity covering a host of selected concepts, design, methods and engineering to maintain structural integrity of space vehicles and associated sub-structures, subject to a series of prevailing loading due to thermo-structural dynamics and environmental effects from design, manufacturing, launching and operation during their pathways to meet a multitude of objectives under a myriad of requirements and constraints, such as various loading and environmental effects. The Rationale and Key Technical Structural Integrity Challenge are first identified. In spite of citing examples drawn from small satellite situations under vibro-acoustic and environmental thermal loading, the overriding issues addressed could be extended to more general situations. An infographic is presented to map out the state of affairs to be addressed for structural integrity considerations. [ABSTRACT FROM AUTHOR]

NASA HRP considers developing radiation protection for human space flight and surface habitation as one of the critical technologies for successful deep space exploration. Although the danger of radiation exposure is recognized as a potential show-stopper for deep space exploration, and radiation effects on humans are now understood better than before, shielding strategies for different stages of space flight and habitation are still not addressed in a fully comprehensive manner. Habitats and all space structures planning and design are guided by essential requirements and constraints associated with safety, manufacturing and assembly procedures, propellant and construction costs, maintenance, crew and/or passenger satisfaction. This paper reviews radiation shielding options for space habitats and discusses their feasibility in relation to habitability needs, including the potential for outside viewing in distinct types of space habitats. Typically, radiation protection depends on the thickness of the exterior structure that consists of a pressurized shell, multilayer insulation (MLI) and any applied radiation shielding material. The mass of the external protection shell is the primary factor of radiation shielding effectiveness. Nevertheless, using materials with low atomic numbers (e.g., Boron (5), Carbon (6), and H 2 O) helps to lower secondary radiation hazards. Water, which is rich in hydrogen and has the lowest atomic number, can also be used for other mission needs. Other materials, including biomaterials, can be considered when their inclusion in the structure is possible and appropriate. The paper presents a comprehensive strategy for radiation shielding selection that includes investigation of complications associated with a type of space habitat structure, mission needs, duration, destination, and crew requirements. The approach presented in the paper aims to establish an evaluation methodology for defining the feasibility of the integration of diverse radiation shielding types into habitat structures. The paper summarizes by reviewing radiation shielding proposals with selected case studies including water, regolith, hydrogen-rich polymers, biotechnology, polyethylene/boron nitride composites, and active strategies. • Case studies of different materials and methods used for radiation shielding purposes, • Pros and cons of using referenced materials and methods in habitat architectures • Criteria for evaluation and selection of appropriate radiation protection strategy • Comparisons of radiation shielding methods by space architecture categories • Comparisons of radiation shielding methods by structural integration options [ABSTRACT FROM AUTHOR]

Leveraging advancements in micro-scale technology, we propose a fleet of autonomous, low-cost, small solar sails for interplanetary exploration. The Berkeley Low-cost Interplanetary Solar Sail (BLISS) project aims to utilize small-scale technologies to create a fleet of tiny interplanetary spacecraft for rapid, low-cost exploration of the inner solar system. This paper describes the hardware required to build a ∼10 g spacecraft using a 1 m2 solar sail steered by micro-electromechanical systems (MEMS) inchworm actuators. The trajectory control to a NEO, here 101955 Bennu, is detailed along with the low-level actuation control of the solar sail and the specifications of proposed onboard communication and computation. Two other applications are also shortly considered: sample return from dozens of Jupiter-family comets and cometary nuclei imaging. The paper concludes by discussing the fundamental scaling limits and future directions for steerable autonomous miniature solar sails with onboard custom computers and sensors. • An autonomous 10−2 kg spacecraft to navigate the solar system is proposed. • Low-cost spacecraft composed of mostly off-the-shelf parts to return images of NEOs. • Propelled by a 1 m2 solar sail controlled by micro-electromechanical systems motors. • Autonomous trajectory control to a NEO, communication, and computation is detailed. [ABSTRACT FROM AUTHOR]

Virtual reality (VR) and augmented reality (AR) are rapidly developing technologies that may have important healthcare-related applications, including the possible evaluation of the health and performance of astronauts. Advances in the fields of VR/AR and space exploration have independently progressed; however, over the last decade synergies and overlapping applications have emerged between spaceflight and extended reality. This paper is intended to be a resource to update the medical community on the current and future integration of VR and AR into space exploration, particularly as this integration relates to astronaut health. We highlight how these technologies are used in terrestrial healthcare with specific attention to visual function. Furthermore, we elaborate on emerging VR applications being developed for future spaceflight. The paper discusses the current state of the art, such as the Apple Vision Pro headset, and outlines key challenges like mass and volume constraints, power limitations, and the heightened cognitive and physical demands of space travel. It also addresses the potential of VR/AR technologies to mitigate these issues through efficiency, stress reduction, and exercise motivation. Finally, we emphasize the benefits that these technologies provide to overcome possible barriers to long duration spaceflight and manned exploration missions, including spaceflight associated neuro-ocular syndrome (SANS). • Virtual reality (VR) and augmented reality (AR) are rapidly developing technologies that may have important healthcare-related applications, including the possible evaluation of the health and performance of astronauts. • This paper is intended to be a resource to update the medical community on the current and future integration of VR and AR into space exploration, particularly as this integration relates to astronaut health. • We highlight how these technologies are used in terrestrial healthcare with specific attention to visual function. Furthermore, we elaborate on emerging VR applications being developed for future spaceflight. [ABSTRACT FROM AUTHOR]

The Korea Pathfinder Lunar Orbiter (KPLO), officially named as Danuri, is the Republic of Korea's first spacecraft to orbit the Moon. The goal of KPLO is to secure core deep space technology for future space exploration in Korea and contribute to lunar science by gathering data from the lunar orbit for one year. This paper presents the results of KPLO's Lunar Orbit Acquisition (LOA) phase in detail, with a particular focus on the operational results of Flight Dynamics (FD). During the LOA phase, the KPLO FD team experienced many expected and unexpected issues. These issues were mitigated by making real-time updates to the LOA phase Design Reference Mission (DRM). The paper also presents the results of the Orbit Determination (OD) and performance of each Lunar Orbit Insertion (LOI) maneuver conducted during the actual flight operation. The importance of considering operational constraints when designing the DRM is emphasized by presenting lessons learned based on actual flight experiences. Unlike the original KPLO LOA phase DRM, KPLO successfully achieved the final mission orbit using only three LOI burns, instead of the planned five LOI burns and an Orbit Trim Maneuver (OTM). Despite the extensive revisions made to the DRM, all mission requirements were still fulfilled during the final lunar orbit insertion, taking into account the significant operational constraints. • Real flight operation results of the Korea Pathfinder Lunar Orbiter's lunar orbit acquisition phase are presented. • Orbit determination and lunar orbit insertion maneuver performance are analyzed based on actual flight data. • Unexpected issues during the actual flight operation were mitigated through real-time updates on the design reference mission. • Considering real-world operational constraints while designing the design reference mission is very critical. [ABSTRACT FROM AUTHOR]

The Mars Sample Return (MSR) campaign is one of the most ambitious and complex planetary science exploration missions ever pursued. With the participation of NASA, ESA, and many industry partners, MSR aims to bring Martian rock and atmosphere samples to Earth with the goal of answering key questions about Mars' geological, climatological and, potentially, biological evolution. To accomplish this ambitious goal, the MSR campaign relies on three distinct flight elements and a ground element. The Earth Return Orbiter mission that would host the Capture, Containment, and Return System (CCRS) is the last flight element of the trio. The mission would capture the orbiting sample in low Mars orbit (launched into orbit by another mission), contain it, and return it to Earth, landing at the Utah Test and Training Range. Since its early architecture, several changes were adopted by CCRS to improve overall payload efficiency and reduce mass. This paper will discuss the CCRS design, how the current CCRS architecture contributes to an improved mission concept, and the next critical steps of the mission toward its launch. • MSR is one of the most ambitious and complex exploration missions ever pursued. • CCRS is the last flight element of MSR bringing the Mars samples to Earth. • Detailed examination of the NASA CCRS payload is presented. • Insight into the operational plans of CCRS that enables a successful sample return. • Contributes to the broader body of knowledge in space exploration. [ABSTRACT FROM AUTHOR]

The purpose of this paper is to study the development of space-age aesthetics culture and arts in seven decades since 1950s. The first known use of "space-age" was in 1946, and was defined as "of, relating to, or befitting the age of space exploration." A more popular definition for the "space age" is "The space age is the time period in human history related to the space race, space exploration, and space technology. Most people say this started when Sputnik 1 was launched in 1957, and continues to today. This has influenced culture such as in movies, television, music, art, and architecture." Culture, in the anthropology, is the patterns of behaviour and thinking that people living in social groups learn, create, and share. Culture distinguishes one human group from others. It also distinguishes humans from other animals. A people's culture includes their beliefs, rules of behaviour, language, rituals, art, technology, styles of dress, ways of producing and cooking food, religion, and political and economic systems. Therefore, the space-age art is one of the major elements of the space-age culture of human beings. On the other hand, the space exploration has significant inspiration and influence on the aesthetics art. In particular, the following aspects shall be studied in this paper: architecture and exhibition craftworks. • The space-age architecture and exhibition craftworks were investigated. • Five space-age architecture shapes investigated are disc, rocket, tower, spherical and combined. • Three space-age installation craftworks studied are sky waves, embroidery, planet models, etc. • Many space-age architectures are destroyed due to many reasons. • Hopefully the young generations can be inspired to carry forward these precious heritages. [ABSTRACT FROM AUTHOR]

A long-duration microgravity environment has numerous detrimental effects on the human physiology. The most obvious solution for this problem related to long duration space exploration missions is to remedy the lack of gravity. This could be done using short arm human centrifuges but they do not seem to be sufficiently effective, perhaps because of the short duration exposure of this countermeasure and/or the huge body gravity gradient. New views have to be investigated, such as to see if a (very) long-arm rotating system generating a continuous 1 g or partial gravity field might resolve this issue. Besides the expected benefits regarding astronauts' microgravity pathologies, additionally the spacecraft itself, its on-board (sub-)systems and procedures might benefit from a rotating configuration. In this paper we address very briefly the medical issues, but the work is mainly focused on the advantages regarding engineering, operations, life support, safety and budget of having a constantly rotating spacecraft first in Low Earth Orbit and later for long duration missions to Mars. A large rotating spacecraft is feasible and affordable to build, operate and maintain. It has advantages for governmental and commercial use but also in light of the expected increase in space tourism. It will also save crew time and billions of dollars now being spent to counteract the effects of microgravity. A continuous rotating spacecraft providing Artificial Gravity will: • Improve crew health and wellbeing. • Improve mission safety and success. • Reduce costs significantly. • Simplify numerous operations in flight. • Provides the use of 1 g verified systems. [ABSTRACT FROM AUTHOR]

The major purpose of this paper is to study the important role of historical painting art on the creation of space-age era eight decades ago in 1950s. According to the Merriam-Webster Dictionary , the first known use of "space age" was in 1946. In the Collins Dictionary , the space age is the present period in the history of the world when travel in space has become possible, and people use "space-age" to describe something that is very modern and makes you think of the technology of the space age. In American English, space age is the period in modern history characterized by space exploration, usually considered as beginning on October 4, 1957, when the Soviet Union launched the first artificial satellite, Sputnik I, into orbit around the Earth. In the ancient time, many artists including Giovanni di Paolo, Albrecht Dürer, Étienne Léopold Trouvelot and Vincent van Gogh created masterpieces of space related paintings. Even in the extreme ancient era, the cave art already evidenced humans' astronomical knowledge. Besides the technological research and development for space explorations, groups of workers and artists in the areas of culture, painting, architects, installation artwork, etc. had done many contributions in the development of space-age cultural and aesthetic art before 1950s. They not only created so many masterpieces with plenty of space-age aesthetics, but witnessed and recorded the development history of the space age. It goes without doubt that historical space painting art played an important role on the creation of space-age era in 1950s. Therefore, it is mandatory to investigate and reveal the fact. • To study the important role of historical painting art on the creation of space-age era eight decades ago in 1950s. • The first known use of "space age" was in 1946, considered as beginning on October 4, 1957 when Sputnik I launched. • Giovanni di Paolo, Albrecht Dürer, Étienne Léopold Trouvelot and Vincent van Gogh created masterpieces of space related paintings. • In the extreme ancient era, the cave art already evidenced humans' astronomical knowledge. • Groups of artists in the areas of culture, painting, architects, etc. contributed space-age cultural and aesthetic art before 1950s. • Historical space painting art played an important role on the creation of space-age era in 1950s. [ABSTRACT FROM AUTHOR]

A comprehensive approach to creating a control system for the shape of the radio-reflecting surface of a large-size space reflector is considered. Large-aperture space antennas are used for satellite communications and space exploration. The design of these structures is one of the most promising areas. Ensuring the specified characteristics of the reflector is directly related to maintaining the specified shape of the radio-reflective netting. Developing a control system for the shape of the active antenna surface is an urgent task. Optimizing this process makes it possible to accomplish the mission during the operational period effectively. The paper evaluates the effects of perturbations on a large-scale structure operating in outer space. A method for adjusting the geometry of the frontal network is proposed. This allows for improved communication between spacecraft and ground stations, which is very important for the safety of space flights. The conductive parts of the reflector are considered to transmit energy and control signals to the actuators. The application results of various control algorithms of the executive device making it possible to correct the netting considering the minimization of energy costs and oscillations of the structure are shown. According to the simulation results, the optimal algorithm of the target criteria hierarchy showed greater stability in terms of convergence in the presence of measurement noise and disturbances, which allows it to be applied in real time. This algorithm is supposed to be used in the future when creating a prototype of the system for controlling the shape of the radio-reflective surface of a large-size space reflector using its current-conducting structural parts. • The design of a system for setting up and maintaining a radio-reflective network fabric has been developed. • Algorithms are developed to minimize energy when setting up a radio-reflective mesh. • The optimal algorithm of the control allows solving the problem in real time. • The method for transmitting energy and control signals through the use of conductive structural parts of the reflector is proposed. [ABSTRACT FROM AUTHOR]

With the deepening of space exploration, the moon has significant value for scientific research. However, because of such research's costs and risks, international cooperation will be critical for the future lunar exploration. In 2021, China and Russia jointly initiated the International Lunar Research Station (ILRS) project and released the Guide for Partnership (V1.0). However, the basic regulatory framework for creating the ILRS project is not yet in place, posing a challenge to pursuing this complex and technically ambitious endeavor. The paradigm of international cooperation that was the International Thermonuclear Experimental Reactor (ITER) project set a good example of how scientific research could transcend geographic boundaries. This paper examines the ITER Agreement, the constitutive agreement of the ITER, and analyzes the successful experience of large-scale international cooperation on a complex scientific project. Then, in view of the characteristics of the ILRS project and the existing space law, the main elements of a regulatory framework for international cooperation on this project are proposed, which follows the ITER Agreement closely. The paper concludes that such a regulatory framework for international cooperation on the ILRS project may contribute to the peaceful exploration and use of the moon, thus promoting the well-being and interests of humankind. • The moon has significant value for scientific research. • International cooperation will be critical for the future lunar exploration. • A regulatory framework for the International Lunar Research Station (ILRS) is not in place. • The paradigm of international cooperation on the ITER set a good example. • The main elements of a regulatory framework for the ILRS are proposed. [ABSTRACT FROM AUTHOR]

Martian Moons eXploration (MMX) is a mission under development in JAXA in cooperation with NASA, CNES, ESA, DLR to be launched in 2024. This paper introduces the result of its preliminary design and the latest status of the MMX program, putting more weight on the novel part of the mission. The goal of MMX is to reveal the origin of the Martian moons and then to make progress in our understanding of planetary system formation and of primordial material transport around the border between the inner- and the outer part of the early solar system. Additionally, the mission is to survey two Martian moons and return samples from Phobos. Add to those MMX's contribution to the planetary science field, on the growing discussion on the International Space Exploration activities, MMX's contribution to future human Mars exploration is also considered as an essential aspect of the program. Following the system definition study results presented in the previous conference, the following items will be reported in this paper. First, as a result of the comprehensive completion of the Phase-B activities, the preliminary design is completed in coordination with the design of the spacecraft system, mission instruments, and operation plans. This paper describes the proximity and surface operations around Phobos in detail. Second, Phase-C activities have started, incorporating engineering models manufacturing and tests. Those of critical technologies for surface exploration are described in detail. Moreover third, the programmatic aspects, including international cooperation frameworks and the program schedule, are presented. • Martian Moons eXploration (MMX) is a JAXA's mission to be launched in 2024. • MMX achieves the world's first sample return from a Martian moon, Phobos, in 2029. • MMX investigates the origin of Martian moons and the planetary formation process. • Sample of Phobos contains the ejecta derived from Mars by meteorite impacts. • MMX acquires data that contributes to future human Mars exploration. [ABSTRACT FROM AUTHOR]

Launch date of the first artificial satellite Sputnik 1 was on October 4, 1957, therefore it was commonly considered to be the starting year of the space age. Being inspired by the rapid developments in space and universe explorations, André Courrèges, Pierre Cardin and many other designers opened the frontier territory of the space-age era in the fashion community. From 1964, André Courrèges extensively used the white and silver metallic colours which soon became the definition of aesthetics at that time and was named Godfather of the space-age designer. On the other hand, Pierre Cardin demonstrated his early space-age work at the Paris Fashion Week in 1968 and was called the pioneer of the space-age fashion designer. For the six decades up to now, at least 15 fashion designers launched the so-called "Fashion communities' interplanetary mission" in different years: André Courrèges (1964), Mary Quant (1965), Reed Crawford (1966, specialized in hat design), Pierre Cardin (1968), Paco Rabanne (1968), Thierry Mugler (1979), Issey Miyake (1995), Alexander McQueen (1995), Nicolas Ghesquière (2007), Hussein Chalayan (2007), Christopher Kane (2011), Raf Simons (2014), Donatella Versace (2016), Karl Lagerfeld (2017), Nicolas Ghesquière (second time in 2019, as the artistic director of Louis Vuitton) and Iris Van Herpen (2019). The purpose of this paper is to systematically and methodically review the inspiration and significant influence of space exploration and universe discovery on the fashion aesthetics, styling and design in six decades from 1960 to the current year. Major creative ideas included new colours such as silver, new materials such as metallic, new styling such as flying saucer, new patterns such as totems, and the use of new technologies such as 3-dimensional (3D) printing, with the most important considerations of noble, elegancy and aesthetics. Also, the feedback influence of the space-age fashion on the new generation SpaceX and Boeing suits is discussed. • The starting year of the space age was on October 4, 1957. • Inspired by the space age, André Courrèges, Pierre Cardin, etc. opened the frontier in fashion community. • For six decades from 1960, fashion designers launched the "Fashion communities' interplanetary mission". • This paper reviews the inspiration and significant influence of space exploration on the fashion aesthetics. • Major creative ideas included new colours, new materials, new styling, new patterns and new technologies. [ABSTRACT FROM AUTHOR]

The Moon is a highly valued destination for human space exploration because it is close and it contains a wide array of lunar and Solar System science targets, which include resources that could be used to sustain humans on the lunar surface. These resources have the potential to enable sustainable human space exploration, develop a vibrant cislunar economy, and directly benefit society here on Earth. However, recent rhetoric about the importance and value of these resources has used the term as if we know they are reserves. An immediate and vital next step has not yet been realized to define the reserve potential of such resources, and that is designing and implementing a coordinated international lunar resource evaluation (prospecting) campaign. This paper outlines the issues that need to be addressed by such a campaign, including why it needs to be international in nature and how the coordination can be started and evolved, as well as exploring the benefits that would come from prospecting on the Moon. • A distinction between lunar resources and lunar reserves is defined. • Roadblocks in the in-situ resource value chain are highlighted. • Reserve potential of lunar resources requires a coordinated prospecting campaign. • The prospecting campaign must be international due to the scale of the task. • Coordination can start at the grassroots level with current and scheduled missions. [ABSTRACT FROM AUTHOR]

The Moon has returned into the focus of human endeavors regarding human spaceflight, e.g., with NASA's Artemis program, ESA's Moon Village, and the Russian/Chinese International Lunar Research Station. In difference to the pathfinding missions of the Apollo -era, the goal for these future missions is to stay on the lunar surface for longer durations and inhabit the lunar environment (near-)permanently. This requires a different approach to be affordable, i.e., instead of resupply as mostly used on e.g., the International Space Station, resource management has to include recycling and in-situ utilization. The former especially calls for the application of so-called BLSS to allow providing essential life-support services to the crew without prohibitive resource consumption, which is economically not feasible to achieve with resupplies. Bio-regenerative-life-support systems have been researched for decades, yet the system complexity, technology advancements, and singular aspects as e.g., plant biology require more research, especially if combined as in a greenhouse. For instance, the understanding of how a microbiome develops in a closed environment and what implications the microbiome has on plant growth is still insufficient. Within the EDEN project, the German Aerospace Center built a lunar analogue greenhouse and operated it at the Neumayer-III research station in Antarctica for four years, testing the technology – which was not space hardware – and operations. Derived from this experience the next step in the project is to design and subsequently operate a ground test demonstrator for a lunar greenhouse, as close as possible to the actual space hardware and operations. This paper explains the current design and trade-offs that led to it. Furthermore, the concept of operations is shown to illustrate the demonstrator's utility for researching bioregenerative-life-support. Overall, the system presented is feasible and useful to close the gaps, currently still existing in this field of research, and thus a mission enabler for future long-duration human space exploration missions. • Design of an integrated greenhouse module test demonstrator. • Extensive science program definition. • Mission scenario definition for lunar greenhouse. • Discussion of benefits and open issues. [ABSTRACT FROM AUTHOR]

Exploring farther into our solar system for planetary exploration will require the human crews to reside in their space transfer habitats for a long period of time. These explorers will also face isolation, owing to the sheer physical distance from the Earth, which may eventually affect their health and well-being. Furthermore, looking at a trip to Mars, astronauts may need to wait for as long as 40 min before receiving updated round communications from Earth, due to the time it takes for the signal to travel the separation distance at the speed of light. Thus, when it comes to long-duration crewed space missions, communication and the feeling of connection with their loved ones—friends and family—on Earth is crucial for the astronauts' well-being. In this context, exploring a new communication approach for long-duration spaceflight seems necessary for our missions to Mars. This paper attempts to introduce a new way of decoupled communication that enables astronauts to connect with their feelings towards their loved ones on Earth via embedded interactions, focusing on the idea of "qualitative contact". The idea of qualitative contact was inspired by one of our previous studies on the concept of "qualitative interface" in relation to HCI (Human-Computer Interaction), then extended to our case study for human-object interactions. Much of how we construct meaning in the real world tends to be qualitative rather than quantitative. Yet quantification has become a default method for displaying, presenting and communicating information. In this paper, we explore beyond the idea of ordinary distance communication and information exchange during deep space exploration in particular during long-duration interplanetary spaceflight. We introduce how human explorers in a space transfer habitat can qualitatively contact their loved ones on Earth during their long-duration space missions. We discuss our design processes, which includes the study of human-centredness, communication barriers, the ideation process, and prototype development with a boundary-object based demonstration. We believe that our communication method or tool can stimulate ideas for space habitat designs beyond today's technological solutions for long-duration and long-distance space missions. By advancing the astronauts' physiological and psychological well-being, human explorers could venture to expand our civilisation deeper into the solar system. What are the ways to make astronauts feel connected with their family and friends back on Earth during their long-duration space missions? Here we share the idea of qualitative contact through a device we call Martian Delight—a device intended to advance the astronauts' well-being. • Decoupled communication methods could be helpful for improving astronauts' well-being during deep space missions. • Reward systems could encourage astronauts' well-being and a healthy lifestyle during long duration space missions. • Focusing on human-interaction is one of the key factors of advancing habitat design for deep space explorations. [ABSTRACT FROM AUTHOR]

Deep space exploration technology is an important development direction for scientific exploration. The penetrator method has been proposed as an inexpensive method of studying planetary bodies. The basic principle of this method is that the detection equipment carried by the high-speed penetrator hits a planetary body at a high speed and is buried up to several meters below the surface to carry out detection work. During the frictional collision process with the planets crust, the instantaneous acceleration peaks of the scientific payload (electronic instrumentation) are large. Shock protection of these payloads is necessary to improve their survival and mission success. In this paper, with the goal of improving the survival rate of scientific loads inside a penetrator, a penetrator with a multilayer energy-absorbing structure is developed, in which cushioning protection measures, such as an aluminum foam-filled corrugated tube(AFFT) structure, polyurethane rubber, and epoxy resin potting, are applied to the penetrator. Since the analysis of this process is a highly nonlinear problem, a numerical modeling method is the main approach in this paper. The LS-DYNA software platform was used to simulate the penetrators penetration process on a moon soil medium. The results obtained using empirical formulas and theoretical derivations were compared with the results of numerical analysis to ensure the accuracy of the penetration simulation model. The finite element model of the penetrator was then verified and modified by conducting shock response spectral experiments and shock simulations. The results showed that the spacer scheme had a positive effect on the impact isolation and energy absorption. In addition, this scheme provides an important reference for the design of the penetrator prototype to guarantee the success of subsequent ground rocket sled experiments. • The buffering and energy absorption characteristics of the proposed AFFT structure are analyzed applied to the penetrator. • Through numerical simulation of the penetration process, the initial velocity satisfying the penetration depth was obtained. • The impact response spectrum test and simulation analysis of the penetrator prototype have verified the numerical model. [ABSTRACT FROM AUTHOR]

The development of deep space exploration has led to new exploration demands that cannot be met by traditional planetary rovers. This paper proposes a new wheeled rover that combines the advantages of passive all-wheel attachment and vibration reduction at high speeds. This rover can achieve vibration reduction in the vertical direction from ground excitation, preventing the instability of pitch and roll. Flexible wheels were used to reduce the high-frequency excitation of the ground on the rover. The design concept and mechanical principle of the proposed rover were comprehensively analyzed. A quasi-static kinematic model was developed to analyze the overstepping performance of the rover with this new design. Further, the response characteristics of the system to the ground excitation were investigated by vibration equations established using the Lagrangian method. The optimal parameters were obtained using a genetic algorithm to optimize the system with multiple objectives. Furthermore, the overstepping performance, all-wheel attachment, and vibration reduction of the planetary rover were verified through multi-body simulation. The proposed rover has considerable potential for missions such as the Mars sample return and planetary station construction. • A planetary rover with adaptive suspension for high-speed driving is proposed. • The theoretical analysis of the climbing ability of a planetary rover is provided. • A vibration modeling and evaluation method for proposed rover is established. • A variety of objective functions are proposed and optimized accordingly. [ABSTRACT FROM AUTHOR]

This publication examines the history of Project Orion and NERVA nuclear engine program within the Integrated Program Plan, the technical reasons for their study, their progress, and the political reasons for their cancellation. Whether pulsed or thermal, nuclear propulsion offers the best compromise in efficiency and thrust for the propulsion of future manned missions. Project Orion was born in the mind of Stanislaw Ulam, an atomic physicist who had worked on the Manhattan project. Despite theoretical performances superior to anything conceivable even with current technologies, and despite the mobilisation of some of the most brilliant physicists of the time (Freeman Dyson), the project was killed by the Treaty banning nuclear weapon tests in the atmosphere, in outer space and under water (Moscow, 5 August 1963). The Integrated Program Plan was Wernher von Braun's proposal to the Space Task Group (STG), chaired by Vice President Spiro Agnew, for the continuation of the Apollo program. This plan envisaged a lunar base in the 1970s, and a first manned mission to Mars in the early 1980s. All of this would have been powered by nuclear-powered orbital shuttles, using NERVA, a nuclear engine tested and operational since 1968. Here again, even though it performed better than anything else in the world, even today, the project failed politically. This retrospective publication therefore aims to answer the following question: How can nuclear space programs of today and tomorrow be protected from the uncertainties of this influence? The study of propulsion systems is very often left to engineers, and political and public relations issues to politicians. However, every technology is the result of a political system, and has a strategic impact, which is a subject for social and political sciences. That's why this paper adopts an original approach crossing social sciences through the historical study of decision-making dynamics, and engineering through the study of the technical characteristics of the projects involved. This publication is based on declassified technical reports, testimonies of the personalities of the time, and a document from the archives of the John F. Kennedy Presidential Library. History can be the academic bridge between political and technical studies. In a context of resurgence of nuclear propulsion projects throughout the world, such an approach is now necessary both at the historical level and in terms of political decisions making. Indeed, space programs involving nuclear energy are, by nature, at the crossroads of public relations issues very specific to both space and atomic subjects. [ABSTRACT FROM AUTHOR]

This paper proposes a robust finite element Kalman filter for the state estimation of flexible space tether systems, which are critical for space exploration and satellite missions. Due to the limited access to placing sensors along the flexible tether to measure them directly, the measurement of the state of these systems is challenging. To address this, a fully expandable, scalable, and robust approach is developed that fuses position/velocity sensors at tether ends, distributed fiber optic strain measurement along the tether, and a position/velocity estimation by a finite element-based Kalman filter to estimate the state of the tether system. The proposed estimator is mathematically proven to be observable, stable, and robust. The effectiveness of the estimator is demonstrated through numerical simulations of a space tether system in orbit, and the method can be extended to any flexible body system. The results of the simulations show that the proposed approach can accurately estimate the state of the tether system, even in the presence of disturbances and noise. • Expandable, scalable FE-Kalman state estimator for flexible space tether systems. • Data fusion with tether end position/velocity, distributed fiber optic strain measure, and estimated internal position/velocity. • Mathematically proven observability, stability, and robustness to noise of the estimator. [ABSTRACT FROM AUTHOR]

NASA's Deep Space Network (DSN) serves as a critical element in the exploration of deep space, providing telecommunication services such as tracking, telemetry, command, and delivery of science data to its customers around the globe. In addition to supporting robotic spacecraft for scientific missions, the DSN also supports human spaceflight (HSF) endeavors, including NASA's flagship Artemis missions to the Moon. This paper describes DSN lessons learned during preparations for the first Artemis mission, Artemis I. Topics covered include DSN performance and reliability, network loading, interface management, international collaboration and the role of international partners. Lessons learned will be applied to future missions, including Artemis II and beyond. • NASA is managing projected growth in antenna demand and improving supportability to customers. • NASA is working on mission support enhancements to enable a sustained human presence on the Moon. • DSN antenna scheduling processes and downtime planning are designed to meet mission needs. • DSN support for human spaceflight necessitates years of coordination across many entities. • DSN coordination with international partners provides support for human spaceflight endeavors. [ABSTRACT FROM AUTHOR]

The purpose of this paper is to study the birth of space age and the distinguished achievements in the space-age painting aesthetics inspired by space exploration. It has been 66 years ever since the first successfully launch of the artificial satellite Sputnik 1 on October 4, 1957, generally recognized as the first year of space age. Exemplified by the best and most well-known "NASA Art Program", many major space agencies have sponsored the art program. In Japan, the Japanese Aerospace Exploration Agency (JAXA) supports the art program through its Public Affairs Department. In the European Space Agency (ESA), one of its well-known residence artists is Aoife van Linden Tol. For 66 years of the space age, there are many outstanding painters with many distinguished achievements and heritage of aesthetic paintings created. In particular, Robert Rauschenberg's work " Buffalo II " painted in 1964 has become a classic masterpiece that realized the price of $ 88 million at Christie's auction in 2019. • It has been 65 years since the launch of Sputnik 1 in 1957 generally recognized as the first year of space age. • After the well-known "NASA Art Program", many major space agencies have sponsored the art program. • In Japan, the Japanese Aerospace Exploration Agency (JAXA) supports the art program through its Public Affairs Department. • In the European Space Agency (ESA), one of its well-known residence artists is Aoife van Linden Tol. • Robert Rauschenberg's work " Buffalo II " painted in 1964 priced $88 million at Christie's auction in 2019. [ABSTRACT FROM AUTHOR]

As small satellites are finding increased applicability in a number of space missions, the community is actively exploring the feasibility of missions employing active instruments on small spacecraft. In particular, synthetic aperture radars are of interest as they prove to be versatile tools for Earth Observation purposes. This paper proposes a trade space exploration model to identify designs for space-borne satellite synthetic aperture radars that address the desired instrument requirements. Two trade space analysis approaches are proposed, based on a multivariate analysis with two evaluation metrics and using parallel coordinate plots. The paper demonstrates the utility of the trade space model by considering two case studies. The first study looks at radar instruments on a broad range of small satellite platforms. This study narrows down a trade space of 1265 feasible radar designs to less than 44 Pareto optimal designs at different center frequencies (C- and X-band), elicits conditions for L-band SARs feasibility, and discusses the feasibility bounds and technical constraints on associated instrument and spacecraft requirements. The second study considers radars for 3U CubeSat platforms. The study identifies 44 Pareto optimal designs within 12,928 feasible designs and sheds light on the operational constraints required for the development of such innovative miniaturized radars. • SAR design model for trade space exploration at early design stages is proposed. • 30 (X), 14 (C) and 14 (L-band) Pareto optimal SARs are obtained for small satellites. • X-band and C-band SAR instruments are feasible for use with 3U CubeSat platforms. • L-band SARs require larger antenna width in comparison with X and C-band SARs. • PRF boundaries is the most powerful limiting constraint on SARs trade space (>90%). [ABSTRACT FROM AUTHOR]

The importance of interdisciplinary approaches through collaborative mindset, cross-field knowledge, and co-creative team actions is integral for continuing space exploration success as evidenced by past and ongoing terrestrial space habitat analog missions and extraordinary International Space Station (ISS) achievements. This paper presents the third annual iterative outcomes of an innovative university-based space program using Project Based Learning (PBL) methodology in creating design ideas for astronaut health support and wellbeing during a long duration mission (LDM) for a future inhabited lunar moon base or Mars Mission astronaut transit. University faculties including Built Environment, Industrial Design, Engineering, Science, and Health, at Western Sydney University Australia and supported by University of Houston USA are brought together to develop a new understanding of discipline capabilities with the prospect to co-creatively provide new opportunities and inspiration for teamwork across fields. This is of key interest to employers of new graduates in space or innovation-based industries where human factors and designing for high quality human-centered outcomes supports career resilience through currency, agility, and focus. The altruistic nature of interactions that make the ISS a success on multiple levels across cultural, scientific and humanitarian foundations provide the template for cross-disciplinary inspiration, that leverage synergies, and shared goals unattainable by single fields alone. It is not common for disciplines to work so closely together though industry has an expectation for this knowledge. Previously teams of three (2018); five (2019), and now ten undergraduates in 2020 represent team formation. Student numbers across the design for space theme have grown annually from fifteen, to twenty-five, to forty students in 2020. Now opportunities to respond to the complexities of the project in more detail are presented in addressing the overarching research domains in spatial design, human factors and design for health for LDMs. Team supervisory academic staff grew from 1-to-3 and provided further team guidance and discipline specialisations to inform three iterative project phases across the twelve activity weeks for four teams focusing on human spaceflight, exercise, related design performance and materials, and selected UNSDGs principles. The paper outlines the methodological approach, assessment methods, acculturation to working in teams and immersion in space knowledge for newcomers, and a review of forty collaborative outcomes all conducted by migrating Online during the COVID19 pandemic of 2020 by necessity. Periodic project collaborations with sports and health science, engineering, health informatics, space architects, a former astronaut, a representative from NASA Johnson Space Center (JSC) Flight Control, and industrial design academics (project host discipline and non-traditional space area) provided an environment for discussion, development, and co-creative processes that have led to new discoveries and stimuli for new collaboration, international understanding and advancing humankind in space and on earth. • University space curriculum in design for Astronaut health and wellbeing • Space Habitat Design • Interdisciplinary Project Based Learning • Astronaut Health on Long Duration Missions • Space Architecture [ABSTRACT FROM AUTHOR]

Private commercial space tourism carrying passengers to outer space is no longer a distant or far-fetched fantasy, rather it is at verge of becoming an affordable reality with exponential development in space technology including development of Reusable Launch Vehicle (RLV), increasing involvement of private companies like Virgin Galactic, SpaceX, Blue Origin etc. into research and funding of space tourism explorations and applications. It is also receiving huge attention from the public. These developments reflect the infinite possibilities and inevitability of space tourism in near future. However, space tourism may also pose many critical legal issues which must be addressed to ensure the consistent and sustainable development of space tourism, and to secure the rights of all stakeholders involved including operators, passengers, launching State etc. The research paper would highlight the crucial legal issues associated with the space tourism. The paper would critically analyze the efficiency of the present international space treaties in dealing with these issues. At the end, the paper would also attempt to provide few suggestions and solutions to these legal conundrums relating to space tourism. • Commercial space tourism • Legal framework governing space tourism • Sustainable development of outer space • Space tourism and international law [ABSTRACT FROM AUTHOR]

As one of the most important parts of deep space exploration missions, the sampling technologies of extraterrestrial celestial bodies (ECBs) have attracted the attention and interest of many researchers. As a relatively efficient and convenient sampling technique, drill samplers have been applied in different ECBs exploration missions. Different from the previous drill apparatus, this paper introduces a novel automatic assisted drill system (AADS), which is used to sample the deep layer regolith of ECBs. This drilling system can sample the deep regolith layer under manual assistance or unmanned automatic operation mode. The sampler has improved and designed a segmented detachable coring pipe, drilling pipe and casing pipe. It can largely maintain the layer information in the depth direction of the ECBs regolith and can also automatically change the drill sampling process through the driller change system to improve the sampling efficiency. Finally, an automatic test apparatus was designed, and an experimental platform was established to conduct a drill sampling test for the AADS sampler. The experimental results show that the AADS sampling system can successfully obtain at least 2.4 m depth and 1.1 kg weight simulated regolith samples. • The AADS design details are provided. • The AADS sampling strategy are analyzed. • An automatic test apparatus and experimental platform are introduced. • Preliminary filed test results are presented. [ABSTRACT FROM AUTHOR]

This paper describes a solution for procuring propellent needed for future space exploration missions based on the Lunar Electromagnetic Mass Accelerator (LEMMA) concept analyzed by McNab and McGlasson. This study examined the feasibility of using an electromagnetic launcher (EML) to transport raw materials used in propellent production from the lunar south pole to the National Aeronautics and Space Administration's (NASA) Lunar Gateway. The proposed Gateway space station, to be located in a lunar near-rectilinear halo orbit (NRHO), is a critical part of NASA's Artemis program. Cheaply and efficiently sourcing lunar hydrogen from surface ice to the Gateway would benefit the program's success and future exploration of the solar system. Our study of the launch requirements for a lunar EML payload are described here. AGI Inc's Systems Tool Kit (STK) was used to calculate the required launch azimuth, elevation, magnitude, epoch, and trip duration for a payload launched from the Moon to rendezvous with Gateway. The study shows that it is feasible to conduct a single launch from the lunar south pole that can intercept any point along the Gateway's orbit with variable launch conditions. • Electromagnetic Launchers could transport raw materials from the lunar surface to rendezvous with lunar space station. • Study created a model to determine launch parameters for EML launch. • Launch parameters within the specification of current rail gun technology. • Further research into additional payload thrusters required. [ABSTRACT FROM AUTHOR]

In deep space exploration, the application of low-thrust propulsion technology and multiple gravity-assist technology will greatly improve the scope of spacecraft exploration but will significantly increase the difficulty of trajectory design. This study proposes a fast initial design method of low-thrust trajectories, which reasonably combines low-thrust propulsion and multiple gravity-assist technology. In this paper, the Bezier shape-based method is combined with the gravity-assist algorithm to obtain a fast algorithm for calculating the low-thrust multiple gravity-assist transfer trajectories. For the design of the Jupiter rendezvous trajectories, the feasibility of the proposed method is proved by comparing several calculation examples with and without gravity assistance. In order to prove the effectiveness of the proposed method, it is compared with the finite Fourier series (FFS) shape-based method. The simulation results show that the proposed method can use shorter computation time to obtain transfer trajectories with smaller velocity increments than the FFS shape-based method. In order to prove the superiority of the proposed method, the results obtained by the proposed method are used as initial values for further optimization of the Gauss pseudospectral method (GPM). The simulation results show that the difference between the performance indexes of the Bezier method and the GPM is only about 2%, while the Bezier method only uses approximately 2% of the computation time of the GPM. The method described in this paper is significant for obtaining a feasible initial solution quickly for a large number of design cases. • A fast algorithm for calculating the low-thrust multiple gravity-assist transfer trajectories is proposed. • Low-thrust Earth–Jupiter transfer using multiple gravity-assist scheme is studied. • Four sets of trajectories are designed, and the influence of launch window on transfer fuel consumption is analyzed. • The feasibility of using the results obtained from the fast trajectory calculation method for the direct optimization algorithm is evaluated. [ABSTRACT FROM AUTHOR]

This paper investigates the future U.S. demand for streamlined space tourism by showing the missions and factors impacting traveler choices with machine learning. Space tourism is growing and is expected to become available to the masses soon. While private companies need to better understand the demand for space tourism to customize their services, transportation agencies require guidance to support fund management related to commercial space exploration. This work analyzes the three most prominent missions for streamlined space tourism (i.e., suborbital, orbital, and space tourism around the moon) and their selection determinants (i.e., price, safety, training, number of passengers, take-off locations, among other decision-maker factors). A stated preference experiment is constructed to collect data that is analyzed using machine learning. Results provide valuable insights into the mixed opinions of Americans with respect to space tourism, their mission preferences, and risk considerations. • Space tourism serves a niche of high-income travelers. • We investigate the future U.S. demand if space tourism is available to the masses. • A stated preference experiment is constructed to collect data from Americans. • The collected dataset is analyzed using machine learning paradigms. • Results unveil the mission and traveler factors impacting space tourism choices. [ABSTRACT FROM AUTHOR]

The electric solar wind sail is a propulsion system that extracts the solar wind momentum for the thrust force of a spacecraft by using an interaction between solar wind protons and the electric potential structure around charged long thin conducting tethers. The system enables a spacecraft to generate a thrust force without consuming reaction mass. This paper investigates the capability of the electric solar wind sail as a propulsion system for deep space exploration missions. The shape of the conducting tether that is determined by the equilibrium of the solar wind force and centrifugal force is numerically calculated for formulating an advanced solar wind force model. The conducting tethers deviate from the ideal sail spin plane, and the maximum value of the thrust direction varies from 13 ∘ to 19 ∘ . To estimate the spacecraft thrust vector, which is calculated as the sum of solar wind force vectors exerted on each tether, best-fit polynomial equations are proposed. We performed numerical simulations for a two-dimensional orbital transfer mission to investigate the capability of the electric solar wind sail. Results of numerical simulations show that the electric solar wind sail enables spacecraft to perform Earth–Venus, Earth–Mars, and Earth–Itokawa transfer missions. Additionally, this paper performs three-dimensional simulations for an Earth–Ryugu transfer mission. The electric solar wind sail achieves a more complicated orbital transfer in a reasonable mission time. • Electric solar wind sail generates thrust by solar wind and tether interaction. • By investigating the change in the tether shape, advanced force model is developed. • Orbital maneuvering technique that doesn't change the spacecraft attitude is proposed. • Earth-Mars, Venus, and asteroids missions are numerically demonstrated. • Results show that the system can complete the missions in reasonable flight times. [ABSTRACT FROM AUTHOR]

Space operations in the United States has required the skills of aerospace medicine specialists since the before the inception of human spaceflight in 1958. The literature extensively covers physiology, clinical science, and conjectures on the nature and future of space medicine. The goals of this project were to examine the evolution of the operational spaceflight surgeon, define the role today, and explore the future of operational space medicine. The data gathered for this project were obtained from several sources including personal interviews with actively serving NASA personnel, a literature review identified by searches of MEDLINE, Current Contents, PubMed, Google Scholar, internal NASA records and databases, and references from relevant articles. Only articles published in English between 1961 and 2019 were included. Finally, to provide a primary account to compliment the findings from above eight oral histories were examined from leaders in this field. This paper reviews the evolution of operational spaceflight medicine from the NASA perspective, offers a modern definition by those who practice it on a daily basis and explores its future development as a profession. While this work is inherently limited as defined by the experiences of select individuals; the 336 combined years-of-service of the sources, personal interviews, and command perspectives of the authors attempt to lay a foundation for such a definition. Understanding and appreciating this history is key to the successful future development of operational spaceflight medicine as a specialty, and by extension to manned space exploration as a whole. • History of the operational flight surgeon from the NASA perspective. • Period - 1958 through the current time period. • The knowledge shared here has been collected from the historical record, first hand accounts. [ABSTRACT FROM AUTHOR]

This paper presents a new multiple spacecraft full-coverage inspection path-planning scheme to closely observe any large complex space structure hovering in space. For this purpose, a decentralized multi-spacecraft methodology is proposed, extending our previous work on the inspection of structures using a single inspector spacecraft for a cooperative collection of small spacecraft. Multi-robot systems are more reliable, flexible, and scalable and can accomplish complex missions, which might be impossible or significantly time-consuming for a single robot. To this end, our previously developed asymptotically optimal sampling-based path planner, called the Rapidly Exploring Random Tree, is combined with a multi-spacecraft coordination methodology. The resulting kinodynamic inspection path planner generates 3-dimensional inspection trajectories for each spacecraft to fully observe any points on the boundary of a complex space structure in close proximity while satisfying the kinematic and dynamic constraints. Spacecraft coordination, communication, and task allocations are developed to reduce the total inspection time, crucial during servicing and proximity operations. Simulation results are presented to demonstrate the ability and effectiveness of our planner. • Multi-spacecraft coordination and motion planning for inspection of large space structures. • Decentralized coordination for cooperative and homogeneous collection of small spacecraft. • Full sensor coverage inspection trajectories for complete inspection of the space structure. • Contributing to the technologies required for space exploration and proximity operations. [ABSTRACT FROM AUTHOR]

Space exploration is a topic of great interest in the space community and worldwide. For instance, the race to the Lunar surface now includes not only government agencies, but also commercial entities and organizations. Such missions will require robotic spacecraft to perform formation flying, rendezvous and docking to reduce costs of the overall mission and establish space stations within Lunar orbits. Therefore, an accurate and computationally efficient dynamics model, to be used within a spacecraft's guidance, navigation and control system, to calculate and control the desired relative motion will be required. This paper presents a new, linear time-varying, solution to spacecraft relative motion on Lunar orbits that includes solar radiation pressure, third-body, and J 2 perturbations. The solution is obtained by using Hamiltonian dynamics in combination with the Peano–Baker solution for linear time-varying systems, which allows for the inclusion of short and long periodic variations of each perturbation within the dynamical model. The solution resulted in a 75% decrease in computational time when compared to a numerical simulator with the same perturbing effects. • Spacecraft relative dynamics with gravitational, third-body and SRP perturbations based on LTV state transition matrix. • Simulations of proposed model in a perturbed lunar environment. • Comparison of the effects of perturbations on the proposed solution in highly elliptical and low earth orbits. [ABSTRACT FROM AUTHOR]

Outer space exploration has been an area where the international community demonstrated a significant level of co-operation, successfully transcending geographical, national and cultural boundaries. In the age of global governance, international co-operation has never been more important in resolving today's global challenges. One of such challenges is the growing amount of space debris in orbits, which, if unresolved, will not only undermine global information and communications technology (ICT) system, but will also hinder areas of sustainable development where outer space activities contribute to. (e.g. satellite imaging for disaster warning and management, satellite imaging for agricultural purpose) This paper proposes to conceptualize space orbit and radio frequency as essential global commons, whose governance requires international co-operation. In examining potentials and challenges in moving forward space orbit governance, the paper pays particular focus on ensuring space safety and sustainability through the introduction of on-orbit servicing (OOS) operations. The paper will identify aspects of OOS that warrant further collaborations, specifically, the standardization of docking and rendez-vous practices that could facilitate future space activities. Recognizing the potential of future commercialization of refueling, repairing and debris removal operations in orbits, this paper argues that standardization practices would be the first step towards enhancing international co-operation, as well as in strengthening the existing regime of peaceful use of outer space. Ultimately, it could play a role in addressing one of today's most imminent challenges – ensuring sustainable use of global commons. • Space technologies are critical to daily socio-economic activities. • Immaterial space resources (e.g. orbital slots) are limited, finite resources. • Space resources are susceptible to depletion if their use is not co-ordinated. • On-Orbit Servicing (OOS) can ensure sustainable use of resources in outer space. • International docking and rendez-vous standards could enable OOS to take-off. [ABSTRACT FROM AUTHOR]

STEM stands for Science, Technology, Engineering and Mathematics. This paper discusses the importance of delivering STEM education as an integrated applied interdisciplinary approach to learning. Such a holistic interactive experience can inspire the younger generation to get interested in STEM. This learning approach can be greatly enhanced through being exposed to real life experiences, projects and activities, where STEM plays a pivotal role. Many astronauts, scientists, and engineers working in aerospace and the space industry were inspired to follow such careers because at some early stage of their lives they witnessed a pivotal life changing event which could have only been possible to comprehend or realise through the integrated utilization of STEM. This may have been a natural phenomenon, such as witnessing a solar eclipse or a meteor shower, while some are man-made, such as the first man in space orbiting the Earth or the first humans to land on the Moon. All of these experiences would have had a powerful effect in igniting the imagination of a young child or student. For example, Neil Alden Armstrong at the age of six took his first airplane ride. He was so intrigued by this experience on this marvel of an invention that it made him determined to become a pilot. In an indirect way it drove him to want to learn STEM, which are essential if you want to become a proficient aviator. Of course we all know now that if it wasn't for that inspiration, Armstrong may have never set his foot on the Moon to become the first human to do so. The United Arab Emirates Space Agency (UAE SA) endeavours to play a big part in building a bright and exciting future for the UAE nation. This it has already started to do by focusing on the UAE younger generation which it considers as the most valuable resources. The aim is to set the sound foundation for a knowledge and technology based society. The approach is to set up a variety of Space related programs that inspire the students from an early age and motivate them to study STEM. Most importantly these programs are designed to empower them with knowledge, teaching them creative and innovative ways of thinking. These its space exploration and space based experimentation programs as platform in which students can get involved through holistic interactive hands on experiences covering all the fields of STEM. It is a well-known fact that involving all your senses in an activity enhances your experience and knowledge. In this way knowledge is retained, providing an extended background to solving problems and the insight towards future discoveries and developments. Examples of the UAE Space Agency Space related activities designed to encourage the engagement of student in STEM are: This paper will explain the objectives, phases, and the outcomes of running these types of activities and how they inspire the younger generation through exposure to these real life examples where STEM plays an essential role. • Promoting the integrated STEM education approach within UAE schools. • Training and equipping teachers to deliver integrated STEM education. • Ensuring access to practical learning experiences to students from an early age. • Engaging students in collaborative research and development activities. [ABSTRACT FROM AUTHOR]

Abstract A Smart Dust is a femto-spacecraft with an external surface coated with electrochromic material, which exploits the solar radiation pressure to produce a propulsive acceleration. As the optical properties of the electrochromic material change upon application of a suitable electric voltage, its propulsive acceleration may be modulated, within some limits, without the use of any propellant. This paper analyzes the optimal trajectories of a Sun-pointing Smart Dust, which provides a propulsive acceleration aligned with the Sun-spacecraft direction. In particular, the paper describes the relative motion of a Smart Dust with respect to a conventional spacecraft (the Mother Ship) that covers a heliocentric circular orbit of given radius. The Smart Dust is required to vary periodically its angular position with respect to the Mother Ship using an optimal (minimum time) strategy. This problem is addressed using an indirect approach and the optimal control law is obtained in a closed-form solution. The results discussed in this paper ensure interesting improvements over existing models from the recent literature, including the possibility of obtaining a generic phasing angle of the Smart Dust and to take into account an optimal number of on-off switchings of the electrochromic control system. Highlights • The paper analyzes the phasing maneuver of a Smart Dust in a circular heliocentric orbit. • The phasing maneuver is studied by evaluating the optimal (minimum) flight time. • The optimization problem is solved using an indirect approach. • The optimal control law is obtained in an analytical form using a lin-earized dynamics. [ABSTRACT FROM AUTHOR]

Abstract This paper aims to assess the feasibility of an interstellar mission to reach the Alpha Centauri star system and delivering scientific data, using current and near-future technology. The mission baseline uses 100 GW of laser power to accelerate a spacecraft of 2750 kg to 5% the speed of light with light sail technology, resulting in a travel time of about a century. This paper explores several aspects of the mission: Possible locations of the laser infrastructure and different sail materials to achieve the required acceleration are discussed. Deceleration using a magnetic sail in the interstellar medium and in the heliosphere of the target star, taking into account mathematical models from Zubrin [6], Freeman [22] and Gros [21], is studied. Potential orbits in the star system are considered for observation and data collection. Finally, a multi-spacecraft mission architecture is presented, as it would allow for the spacecraft to be launched sequentially, thus exploiting the possibility of continuously operating the laser infrastructure. Highlights • Mission architecture to send multiple spacecrafts to Alpha Centauri star system. • Laser sail acceleration and magnetic sail deceleration. • Performance comparison of different light sail materials, on a spacecraft level. • Dependencies between light sail, laser and mission parameters. • Performance analysis of magnetic sails considering different mathematical models. [ABSTRACT FROM AUTHOR]

Abstract It is inevitable that individuals and groups will experience stress and distress in the harsh and extreme environment of deep space. When these occur, we now have a mission in jeopardy -- not due to hardware failure, but because a psychological breaking point has been reached. It will happen. The question is when. This paper seeks to identify signs of impending breakdowns and suggests strategies for a crew to minimize its impact when it does. This paper begins to create definitions and qualities of breaking points, define the impact on group dynamics, and identify post-breakdown recovery strategies that will be used as a foundation for predictive model development. Highlights • An individual's psychological is vital to the success of the mission itself. • Mission cycle type influences the required skill set for individual success. • Group maturity is as important as the individual's ability to cope with the environment. • An individual's psychological health relative to the group dynamics is key. • Other impacting factors are physical health, culture, grief, and gender relationships. [ABSTRACT FROM AUTHOR]

Abstract At present, the moon is still an important and preferred destination for human beings to visit due to the abundant resources and its potential to be the stepping-stone and platform of deep space exploration in the future. The manned lunar exploration has very important and profound meaning for leading technology innovation and manifesting comprehensive power of a country. Mission scale analysis and flight scheme selection are key problems for top-level projection and are still remaining to be researched systematically and deeply. This paper focus on the scale analysis of manned lunar landing mission and the optimal selection of flight schemes. At first, the basic configurations and the overall technical specifications of flight vehicle system were presented based on the investigation of traditional vehicles and developing trend of new vehicles. Afterwards, the fundamental elements of flight scheme were defined and the Mission Architecture Matrix was constructed. Based on Mission Architecture Matrix, the scale evaluation method was demonstrated. Finally, the qualitative selection model based on Analytic Hierarchy Process and Gray comprehensive evaluation method were established, the optimal scheme with economic and technical feasibility was given based on these two models. The validity of all models in this paper was tested and verified by different testing examples. The results show that EOR-LOR architecture is the best flight scheme for a short-period manned lunar exploration mission. To the best of our knowledge, it is the very first time that the concept of Mission Architecture Matrix was proposed. The reverse calculating algorithm based on Mission Architecture Matrix could improve the efficiency of mission scale analysis and the presented comprehensive evaluation model could make the selection of flight scheme more objective. These models and methods in this paper could be technical references for preliminary design of manned lunar landing mission. Highlights • Proposed convenient Mission Matrix for manned lunar mission scale estimation. • Built up a quantitative comprehensive evaluation model for mission architecture. • TRL was considered in the evaluation, reflecting engineering realizability. [ABSTRACT FROM AUTHOR]

Abstract The Space Rider Programme, previously named Pride, is an ESA programme whose objective is to define and develop an affordable reusable European space transportation system to be launched by VEGA-C, to be used as a platform for several types of payload applications. Payloads and related applications strongly drive the definition of Space Rider mission and system, then an analysis of end user's needs has been necessary to adequately feed the design process. This paper reports a survey and an analysis with respect to the following payloads classes: 1- Free-Flyer (Micro-gravity experimentation and Radiation exposure); 2- In-Orbit Demonstrations and Validation for several technologies (Exploration, Orbital infrastructures servicing, Earth observation, Earth science, Telecommunication, Reentry); 3- In-Orbit applications (Earth monitoring and Satellites inspection). In particular, the analysis has been carried out with investigation of the current microgravity platforms and payloads needs, In-Orbit Demonstrations (IOD) flight opportunities status and demand from different stakeholders both on scientific and industrial side. Key assets of the Space Rider platform with respect to payload have been defined and the results of the work has been flow down into the identification of a set of requirements for the Space Rider mission and system focusing on main aspects as operations, mass, power, volume and interfaces. Highlights • The Space Rider Programme objective is to define and develop an affordable reusable European space transportation system. • Payloads and related applications strongly drive the definition of Space Rider mission and system. • An analysis of end user's needs has been necessary to adequately feed the design process. • This paper reports a survey and an analysis with respect to several payloads classes. • The results of the work have been translated in a set of mission and system requirements. [ABSTRACT FROM AUTHOR]

Abstract The Asteroid Impact Mission (AIM) is an ESA small mission of opportunity that intends to travel to the binary asteroid Didymos to assess planetary defence capabilities in the context of the AIDA program, in collaboration with NASA, to demonstrate new technologies for future exploration missions to asteroids and to perform scientific observations. The AIM spacecraft is described in the paper, focusing on the vision-based GNC strategy that reached a high level of maturity at the end of the Consolidation Phase (post B1). Ground navigation analyses pointed out that for close proximity operations (distances under 20 km) a certain degree of autonomy is required. A semi-autonomous attitude guidance has been developed to guarantee that the asteroid will always be kept in the camera Field of View. This algorithm will apply a delta quaternion to the reference attitude profile provided by ground control in order to correct the pointing to the body. This technology has been designed to be easily validated and, at the same time, constrained: the delta quaternion can be limited and in case the thresholds are crossed or any failure occurs, the ground-based reference attitude profile will be used. The AIM GNC prototype was updated to use Line of Sight measurements provided by a centroiding algorithm designed and autocoded in Matlab/Simulink, then validated up to Processor-in-the-loop tests using a flight-representative processor (AT697E LEON2-FT @ 80 MHz). The algorithm is based on the correlation of the image with a Lambertian sphere, taking advantage of the almost spherical shape of Didymain. When relative distance to the binary system is below 8 km, the feature tracking algorithm is used. In this paper a specific case is assessed: the close fly-by for MASCOT-2 delivery (lander included in the payload for AIM's phase B1), tested up to Hardware-in-the-loop with the AIM Framing Camera. Highlights • Design of a semi-autonomous attitude guidance to correct pointing to asteroid. • The attitude correction is limited and controllable for a fail-safe approach. • A Centroiding Image Processing and the GNC prototype guarantee the required pointing. • Processor-in-the-Loop tests demonstrated the feasibility of the described strategy. [ABSTRACT FROM AUTHOR]

The next step for the exploration of space seems to require the human participation by means of a long-lasting lunar outpost. Therefore, this paper attempts to review the up-to-date knowledge regarding prominent issues surrounding the construction stage of a permanent base on the Moon in the light of the 3D printing process. In this context, a number of significant and specific issues are presented and discussed in a detailed manner to determine both the state-of-the-art position of the related literature and the relevant fields for improvement and implications. As a result, the use of heterogeneous and collective swarms of ground robots through a decentralized approach seems reasonable for the 3D printing tasks. However, as it is an emerging technology, it has to be improved further and tested in a terrestrial context as well as on the Moon. In this regard, it is a must to investigate precisely if the solar energy will be adequate for the operation of robots during preparation, transportation, and printing processes of local and Earth-based construction materials. In terms of structural needs, a composite shelter, including (i) an inner inflatable shell with a three-layer membrane, (ii) an outer concrete layer with regolith, polymer, and reinforcing fibers, and (iii) an outermost shield with raw regolith, will likely be viable. However, sieving and binding issues during the preparation phase of concrete under vacuum and microgravity conditions must be solved efficiently. • Lunar shelter construction issues were reviewed through 3D printing. • Heterogeneous and decentralized swarms of ground robots can be used. • Adequacy of solar energy must be found for the entire operation of robots. • A shelter can include an inflatable shell, a concrete layer, and a regolith shield. • Sieving and binding issues during concrete preparation on the Moon must be solved. [ABSTRACT FROM AUTHOR]

Abstract In 2018, the Congress of the Philippines is expected to pass the Philippine Space Development Act , leading to the adoption of the first national space policy in the country and the establishment of the Philippine Space Agency (or PhilSA). This historic event is the final outcome of a long process involving various stakeholders in the Philippines from government, academia and industry. This article provides the first comprehensive history of this process from its inception in the late 20th century until now, with a specific focus on its acceleration since 2013. It also investigates the future expectations of the national space development program, in particular regarding the development of a local space industry. Apart from solely describing the history of the Philippines, this paper presents more generally the case of a developing country willing to gain a foothold in space. In comparison with existing literature on space development programs focusing exclusively on rich western countries or powerful emerging nations, this paper provides other developing countries with highly valuable information by describing such a transparent, balanced and promising initiative as the Philippine space development program. Highlights • The Philippine Space Policy is balanced and perfectly fits the needs of the country. • The process of developing the Philippine space policy can inspire other countries. • Private sector's involvement is crucial for the success of the future space program. • The Filipino space policy's parliamentary approval is expected for late 2018. • Initiating a space program is feasible and recommended for developing countries. [ABSTRACT FROM AUTHOR]

Abstract This paper focuses on the trajectory design for missions destined to explore Mars and/or Phobos departing from Low Earth Orbit (LEO) and arriving into a Mars-Phobos Distant Retrograde Orbit (DRO). Lunar DROs are also briefly explored as an alternative departure location. A Mars-Phobos DRO is a relatively stable environment which would make both the surfaces of Mars and Phobos available for a reasonable propellant expenditure. This paper presents the methodology used to compute LEO to Mars-Phobos DRO trajectories and results regarding required C 3 at launch, v ∞ at arrival, Time-of-Flight (T O F), and total Δ V for various Mars-Phobos DROs using full ephemeris planetary data. The results show that propellant-optimal trajectories from LEO to a specified Mars-Phobos DRO could be used as a staging location between Mars and Phobos. Assuming that refueling is available at the targeted DRO, LEO to Low Mars Orbits (LMO) trajectories would have higher total Δ V due to the additional stop at the Mars-Phobos DRO. However, the aformentioned trajectories would have lower Initial Mass in LEO (IMLEO) and thus a lower gear ratio thanks to the added "pit stop" located at the given DRO. This results in a lower overall spacecraft dry mass that needs to be launched into space from Earth's surface. Highlights • Mars-Phobos DROs are explored as arrival destinations in cis-martian space. • Trajectory design for Earth to Mars-Phobos DROs are presented. • The design methodology is detailed in the paper and numerical examples are provided. • Lunar DROs are also explored as possible departure locations. • Propellant-optimal solutions for lunar DROs to Mars-Phobos DROs transfers are given. [ABSTRACT FROM AUTHOR]

This paper focuses on the trajectory design which is relevant for missions that would exploit the use of asteroid mining in stable cis-lunar orbits to facilitate deep space missions, specifically human Mars exploration. Assuming that a refueling “gas station” is present at a given lunar Distant Retrograde Orbit (DRO), ways of departing from the Earth to Mars via that DRO are analyzed. Thus, the analysis and results presented in this paper add a new cis-lunar departure orbit for Earth-Mars missions. Porkchop plots depicting the required C 3 at launch, v ∞ at arrival, Time of Flight (TOF), and total Δ V for various DRO departure and Mars arrival dates are created and compared with results obtained for low Δ V Low Earth Orbit (LEO) to Mars trajectories. The results show that propellant-optimal trajectories from LEO to Mars through a DRO have higher overall mission Δ V due to the additional stop at the DRO. However, they have lower Initial Mass in LEO (IMLEO) and thus lower gear ratio as well as lower TOF than direct LEO to Mars transfers. This results in a lower overall spacecraft dry mass that needs to be launched into space from Earth's surface. [ABSTRACT FROM AUTHOR]

The main purpose of the 1975 Registration Convention is to achieve transparency in space activities and this objective is motivated by the belief that a mandatory registration system would assist in the identification of space objects launched into outer space. This would also consequently contribute to the application and development of international law governing the exploration and use of outer space. States Parties to the Convention furnish the required information to the United Nations' Register of Space Objects. However, the furnished information is often so general that it may not be as helpful in creating transparency as had been hoped by the drafters of the Convention. While registration of civil satellites has been furnished with some general details, till today, none of the Parties have described the objects as having military functions despite the fact that a large number of such objects do perform military functions as well. In some cases, the best they have done is to indicate that the space objects are for their defense establishments. Moreover, the number of registrations of space objects is declining. This paper addresses the challenges posed by the non-registration of space objects. Particularly, the paper provides some data about the registration and non-registration of satellites and the States that have and have not complied with their legal obligations. It also analyses the specific requirements of the Convention, the reasons for non-registration, new challenges posed by the registration of small satellites and the on-orbit transfer of satellites. Finally, the paper provides some recommendations on how to enhance the registration of space objects, on the monitoring of the implementation of the Registration Convention and consequently how to achieve maximum transparency in space activities. [ABSTRACT FROM AUTHOR]

Human space exploration (HSE) is an interdisciplinary field composed of a range of subjects that have developed dramatically over the last few decades. This paper investigates the intellectual structure of HSE research with a focus on human related factors. A bibliometric approach with quantitative analytical techniques is applied to study the development and growth of the research. This study retrieves 1921 papers on HSE related to human factors from the year 1990 to the year 2016 from Web of Science and constructs a critical citation network composed of 336 papers. Edge-betweenness-based clustering is used to classify the citation network into twelve distinct research clusters based on four research themes: “biological risks from space radiation,” “health and performance during long-duration spaceflight,” “program and in-situ resources for HSE missions,” and “habitat and life support systems in the space environment.” These research themes are also similar to the classification results of a co-occurrence analysis on keywords for a total of 1921 papers. Papers with high centrality scores are identified as important papers in terms of knowledge flow. Moreover, the intermediary role of papers in exchanging knowledge between HSE sub-areas is identified using brokerage analysis. The key-route main path highlights the theoretical development trajectories. Due to the recent dramatic increase in investment by international governments and the private sector, the theoretical development trajectories of key research themes have been expanding from furthering scientific and technical knowledge to include various social and economic issues, thus encouraging massive public participation. This study contributes to an understanding of research trends and popular issues in the field of HSE by introducing a powerful way of determining major research themes and development trajectories. This study will help researchers seek the underlying knowledge diffusion flow from multifaceted aspects to establish future research directions. [ABSTRACT FROM AUTHOR]

This paper discusses the National Aeronautics and Space Administration's (NASA) work to support ethics and public integrity in human space exploration. Enterprise Risk Management (ERM) to protect an organization's reputation has become widespread in the private sector. Government ethics law and practice is integral to a government entity's ERM by managing public sector reputational risk. This activity has also increased on the international plane, as seen by the growth of ethics offices in UN organizations and public international financial institutions. Included in this area are assessments to ensure that public office is not used for private gain, and that external entities are not given inappropriate preferential treatment. NASA has applied rules supporting these precepts to its crew since NASA's inception. The increased focus on public sector ethics principles for human activity in space is important because of the international character of contemporary space exploration. This was anticipated by the 1998 Intergovernmental Agreement for the International Space Station (ISS), which requires a Code of Conduct for the Space Station Crew. Negotiations among the ISS Partners established agreed-upon ethics principles, now codified for the United States in regulations at 14 C.F.R. § 1214.403. Understanding these ethics precepts in an international context requires cross-cultural dialogue. Given NASA's long spaceflight experience, a valuable part of this dialogue is understanding NASA's implementation of these requirements. Accordingly, this paper will explain how NASA addresses these and related issues, including for human spaceflight and crew, as well as the development of U.S. Government ethics law which NASA follows as a U.S. federal agency. Interpreting how the U.S. experience relates constructively to international application involves parsing out which dimensions relate to government ethics requirements that the international partners have integrated into the ISS Crew Code of Conduct, and which relate to other areas of U.S. administrative law. It is also constructive to identify areas where national and/or cultural perspectives may differ. Another reason for heightened focus on ethics is the increasing regularity of long duration human spaceflight. In earlier days of spaceflight astronauts had little time for anything other than mission operations. The increase in inflight personal time and opportunity for personal communications heightens the importance to spacefaring nations of advising on ethics obligations in real time. Through individual and collective action, stakeholders in evolving and future government space exploration will be able to effectively address ethics compliance and reputational risk. [ABSTRACT FROM AUTHOR]

Human space exploration requires massive budgets every fiscal year. Especially under severe financial constraint conditions, governments are forced to justify to society why spending so much tax revenue for human space exploration is worth the cost. The value of human space exploration might be estimated in many ways, but its social significance and cost-effectiveness are two key ways to gauge that worth. Since these measures should be applied country by country because sociopolitical conditions differ in each country and must be taken into consideration, the study on the social significance of human space exploration must take the coloration of a case-study. This paper, focusing on the case of Japan with surveying Japanese literary and national documents as well as taking its sociopolitical conditions into account, examines the social significance of human space exploration. First, we give an overview of the circumstances surrounding Japan's human space exploration program. Derived from the statements of such relevant parties as scholars, journalists, policy makers, and astronauts, this overview indicates that the main concerns about human space exploration in Japan are its social significance and cost-effectiveness (Section 1). Next, an overview of behavioral science—an essential field for human space exploration (referred to in this paper as space behavioral science) that provides support for astronauts—is presented from the perspective of stress research in isolated and confined environments (Section 2). We then give two examples of where such knowledge from space behavioral science research has been applied to terrestrial isolated and confined environments. One is JAXA’s support in 2009 for people who were vulnerable to infection by a new strain of flu and accordingly placed in an isolated and confined facility under the Infectious Disease Law and the Quarantine Law. The other is NASA's support in 2010 for Chilean mine workers who were trapped 700 m underground after a mining accident (Section 3). Based on these case studies, we illustrate the further social utility of such knowledge through a discussion of potential applications in other situations in Japan. Focusing on Japan for its geographical and social features in being an earthquake-prone archipelago and having the world's preeminent aging society, we show that refugees living in evacuation centers and people in an elderly-elderly homecare situation pose socially problematic situations specific to Japan. We then argue that space behavioral scientific knowledge can be applied to support people under these and other isolated and confined environments in various ways (Section 4). Finally, we demonstrate that such an application can be understood as an ethical contribution to Japanese society and that this contribution can be embedded in Japan's space policy (Section 5). We conclude that human space exploration can be a socially significant and cost-effective endeavor that is worthy of tax revenue expenditures because space behavioral science is highly likely to provide unique and useful knowledge to help address various social problems concerning terrestrial isolated and confined environments and support people in sufferings there. [ABSTRACT FROM AUTHOR]

Collecting samples from extraterrestrial body is of great significance for deep space scientific exploration. This paper proposes an autonomous grasping method to collect unknown natural samples from unstructured extraterrestrial surface in a safe, gentle and robust way. A deep reinforcement learning based end-to-end grasping pose estimation framework is designed. The proposed framework takes visual information as input and learns an appropriate grasping strategy. A feature extraction deep neural network and a reinforcement learning policy network are trained simultaneously so as to obtain light-weight networks for extraterrestrial detector. Meanwhile, in order to protect the sample from being damaged during grasping, collision detection is incorporated into the closed-loop during training. The grasping strategy is trained in simulation and is then transferred to real-world. Simulation and real-world experiments show that the learned policy can adapt to unseen irregular stones with less times of collision and at a high grasp success rate under single, scattered, and cluttered scenes. • Autonomous grasping method is proposed to collect unknown natural samples. • Deep reinforcement learning based end-to-end grasping pose estimation framework is designed.. • Light-weight networks is built for extraterrestrial detector. • Gentle grasping behavior is achieved for safety and reliability concern. • The learned policy is verified by simulation and real-world experiments. [ABSTRACT FROM AUTHOR]