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Psychological support to the crew is crucial for space mission accomplishment and cosmonauts' professional longevity. In advance of remote space exploration missions we need to sum up and organize the accumulated experience of psychological support at the current stage of astronautic development. The paper gives a retrospect of the psychological support to space crews of piloted space systems/vehicles and highlights its basic goals and methods. [ABSTRACT FROM AUTHOR]

This paper examines the development of the ‘space tourism’ industry, a concept which primarily denotes the development of space technology for recreational or leisure purposes. It will first theoretically locate space tourism with relevant streams of the mobilities literature, primarily research on aeromobilities and tourism mobilities. It will then summarise existing literature on space tourism, focusing especially on the different models of space tourism that have been proposed and the subtle but important differences between them. The analysis then explores the perceptions of feasibility of space tourism from those within the space sector, the anticipated changes to living these forms of space tourism would bring with them, and the comparisons with existing forms of mobility that are drawn by many in the space sector when attempting to ‘sell’ the value and potential of space tourism. In the final part of the paper, we explore many of the implicit assumptions held by this nascent industry, the uncertain position of the passenger within these conceptions of future space tourism, and identify avenues for future research into this emerging form of mobility. [ABSTRACT FROM AUTHOR]

The Space Race between the Soviet Union and the United States back in 1960s had propelled vast development of space technology. Although it was still nascent during that time, space technology had spurred the launch of the first human to outer space and eventually the first human to step on the Moon. Nevertheless, the much celebrated technology breakthrough in human spaceflight could not expand its benefit to society due to the dual nature of space projects. Unlike other forms of technology, spacecraft and rocketry remain to be highly confidential and special privilege of space faring nations particularly their space agencies. With receding funding growth to these space agencies especially after the end of the Space Race, this paper aims to explore the potential of commercial human spaceflight in modern days to rejuvenate the development of space technology and its challenges. The scope of this paper is limited to commercial and private initiatives of human spaceflight, but not government or space agency. Towards the end, this paper concludes that commercial human spaceflight particularly the suborbital spaceflight has the potential to develop space tourism, point-to-point transportation, science research, satellite deployment, remote sensing, education, technology demonstration and media promotion. [ABSTRACT FROM AUTHOR]

The paper analyzes the utopian science fiction novel Red Star by A. Bogdanov (1908). The study focuses on the description of a fictional interplanetary travel analyzed in the context of scientific knowledge in the field of theoretical physics and astrophysics in the beginning of the twentieth century, and compares it with modern scientific concepts. A comparison of Bogdanov's technological imagery with the existing technologies of space travel is also presented. The study considers such concepts as antigravity, the theory of matter and 'minus-matter', ideas related to radioactivity and the possibilities of its use, the characteristics of the fictional interplanetary spacecraft etheroneph, the idea of the parameters of an interplanetary flight, including a description of weightlessness and its effects on a human body, space flight trajectory, the importance of using computer technologies, presented in the novel. While certain concepts had obviously been borrowed from the already existing sci-fi narrative, other details in the Red Star can be regarded as a novelty and original solutions predicting the later technological advances. They reveal the breadth of Bogdanov's background, almost unique in science fiction writers of the beginning of the twentieth century. [ABSTRACT FROM AUTHOR]

Indian Prime Minister Narendra Modi announced support for a human spaceflight program during his 2018 Independence Day speech. The target year of 2022 is when India plans to realize its first indigenous human space mission. Human spaceflight is a high risk activity and in many ways unaffordable for a developing country. Moreover, India professes that space technology is best utilized for aiding socioeconomic development and not as a tool in geopolitical competition and prestige. By assessing relevant developments, this paper argues that a variety of concerns and ambitions compelled India to consider a human space mission. The main actors are India's political and scientific leaders who found support for such a mission in response to China and international prestige factors. Indian political leaders also saw an opportunity for improving their domestic political image. Further, the Indian Space Research Organization views human space missions as providing a new raison d'etre to the organization and helping it retain a skilled workforce amidst industrialization of satellite and launch vehicle development. [ABSTRACT FROM AUTHOR]

Abstract Italy, as well as many other countries, has increasing interest in Commercial Space Transportation and in particular, in suborbital flights. A suborbital space transportation system is an opportunity to involve the Italian industry in the development of new technologies, exploit opportunities of microgravity experimentation and pilots/astronauts training, as well as catalyse the national industry. The central position of Italy in the Mediterranean basin, the generically favourable climate condition, the touristic vocation resulting in hospitality at the highest level, pretty much allow year round suborbital operations and unique customer experience. Consequently, Italy appears to be a suitable location to host a Spaceport, even though the density of population has to be factored in as a key aspect, together with a proper environmental assessment. This paper outlines the current Italian approach that, instead of focusing on the development of new Spaceport from scratch, evaluates the capabilities of existing airports and their possible upgrades to achieve the Spaceport license, when a proper regulatory frame is established. Advances in the technical activities that are being conducted to assess various Italian sites of interest are described, including trade off methodologies and ranking criteria. Different aspects are considered, from the availability of civil and military airports, to the identification of the best location between coastline or inland sites but, first of all, in compliance to the safety requirements. Some specific Spaceport infrastructure and operational aspects are described, along with their integration with the already existing ones. These include hangars, propellant storage facilities, ground support equipment, high and low airspace surrounding the airport area, ascent and descent corridors, as well as tracking telemetry station to support specific mission profiles in integrated fashion with the existing airport infrastructure and air traffic. The paper will also describe the approach to the definition of a harmonized cooperative regulatory framework, according to the Aviation Authority, that represents the basis to assess suborbital operations and allows the relevant missions execution. In this activity, basing upon an established Memorandum of Cooperation between FAA, ENAC and the Italian Space Agency, the existing FAA/AST regulatory work frame is considered as reference benchmark and further tailored to the Italian case. Some considerations will also be developed relevant to initial challenges to be faced, by interested stakeholders, in starting commercial spaceflight initiatives as a new ground and emerging business opportunity. Highlights • Spaceport and Ground Segment assessment for future suborbital transportation system. • Market opportunities and benefits for the Italian economy. • Spaceport requirements identification for the Italian case. • Spaceport operations business strategy considerations for the Italian case. [ABSTRACT FROM AUTHOR]

The zero-propellant maneuver is an advanced concept of the spacecraft attitude control. The problem of zero-propellant maneuver using single gimbal control moment gyroscopes is researched in this paper. The saturation and singularity problems of single gimbal control moment gyroscopes are analyzed, and the performance indexes to measure saturation and singularity are proposed. The path planning model considering the gimbal steering law is established using modified rodrigues parameter. Then, a hybrid approach combining the pseudospectral method and direct shooting method is proposed to solve the nonlinear path planning problem with complicated constraints. Finally, the numerical simulation is executed to validate the effectiveness of the proposed method. It is shown that an optimized attitude maneuver path satisfying the saturation and singularity constraints can be obtained and the zero-propellant maneuver using single gimbal control moment gyroscopes can be successfully achieved. [ABSTRACT FROM AUTHOR]

This paper illustrates an indirect method to optimize multiple-impulse trajectories from circular lunar orbit to Earth. Optimization is performed in the circular restricted three-body problem, and the necessary optimality conditions are found through optimal control theory. In order to overcome the difficulty of initial adjoints estimation, a homotopic approach, which is based on an auxiliary optimization problem with known solution, is developed; this approach proves to be robust and efficient. Examples are presented for a range of lunar orbit orientations to assess the impact on velocity impulse requirements. Optimization results for trajectories with different number of impulses are also compared. The developed procedure can support fast and accurate evaluation of the transfer costs for Moon-to-Earth trajectories both in nominal conditions and for contingency plans. [ABSTRACT FROM AUTHOR]

The Floating Potential Measurement Unit (FPMU) is a multiprobe package designed to measure the floating potential of the International Space Station (ISS) as well as the density and temperature of the local ionospheric plasma environment. The purpose of the FPMU is to provide direct measurements of ISS spacecraft charging as continuing construction leads to dramatic changes in ISS size and configuration. FPMU data are used for refinement and validation of the ISS spacecraft charging models used to evaluate the severity and frequency of occurrence of ISS charging hazards. The FPMU data and the models are also used to evaluate the effectiveness of proposed hazard controls. The FPMU consists of four probes: a floating potential probe, two Langmuir probes, and a plasma impedance probe. These probes measure the floating potential of the ISS, plasma density, and electron temperature. Redundant measurements using different probes support data validation by interprobe comparisons. The FPMU was installed by ISS crew members during an extra-vehicular activity on the starboard (S1) truss of the ISS in early August 2006 when the ISS configuration included only one 160-V U.S. photovoltaic (PV) array module. The first data campaign began a few hours after installation and continued for over five days. Additional data campaigns were completed in 2007 after a second 160-V U.S. PV array module was added to the ISS. This paper discusses the general operational characteristics of the FPMU as integrated on ISS, the functional performance of each probe, the charging behavior of the ISS before and after the addition of a second 160-V U.S. PV array module, and initial results from model comparisons. [ABSTRACT FROM AUTHOR]

Once considered intractable, the problem of interstellar flight is slowly yielding to analysis. Although manned missions to the stars are exceedingly improbable in this century, the possibility of interstellar robotic probes should not be ruled out. Recent laboratory work and theoretical analysis suggest several near-term technologies that could, given the development of an adequate space-based infrastructure, provide the needed propulsion. Laserdriven lightsails offer the key advantage of leaving the fuel behind, with the laser beam focused by a large Fresnel lens in the outer Solar System. Perhaps more efficient is the use of a particle beam to boost a spacecraft by interacting with its magnetic sail, the latter a system already under intense scrutiny. Variations on "pellet" propulsion using macroscopic objects continue to surface, their mass converted to energy as they arrive at the departing starship. Interstellar flight will be both difficult and expensive, although it can no longer be considered an impossibility. This paper examines the above concepts and relates them to older ideas, such as the Bussard ramjet, that are currently out of favor. The vibrancy of interstellar flight studies is its syncretism—it was through analysis of the drag problem in fusion ramjet designs that a practical means of decelerating an interstellar probe by deployment of a magnetic sail emerged. The intermingling of such ideas offers the hope of robust hybrid concepts that may make interstellar flight a reality. [ABSTRACT FROM AUTHOR]

In recent years, formation flying has been recognized as an enabling technology for a variety of mission concepts in both the scientific and defense arenas. Examples of developing missions at NASA include magnetospheric multiscale (MMS), solar imaging radio array (SIRA), and terrestrial planet finder (TPF). For each of these missions, a multiple satellite approach is required in order to accomplish the large-scale geometries imposed by the science objectives. In addition, the paradigm shift of using a multiple satellite cluster rather than a large, monolithic spacecraft has also been motivated by the expected benefits of increased robustness, greater flexibility, and reduced cost. However, the operational costs of monitoring and commanding a fleet of close-orbiting satellites is likely to be unreasonable unless the onboard software is sufficiently autonomous, robust, and scalable to large clusters. This paper presents the prototype of a system that addresses these objectives—a decentralized guidance and control system that is distributed across spacecraft using a multiple team framework. The objective is to divide large clusters into teams of "manageable" size, so that the communication and computation demands driven by N decentralized units are related to the number of satellites in a team rather than the entire cluster. The system is designed to provide a high level of autonomy, to support clusters with large numbers of satellites, to enable the number of spacecraft in the cluster to change post-launch, and to provide for on-orbit software modification. The distributed guidance and control system will be implemented in an object-oriented style using a messaging architecture for networking and threaded applications (MANTA). In this architecture, tasks may be remotely added, removed, or replaced post launch to increase mission flexibility and robustness. This built-in adaptability will allow software modifications to be made on-orbit in a robust manner. The prototype system, which is implemented in Matlab, emulates the object-oriented and message-passing features of the MANTA software. In this paper, the multiple team organization of the cluster is described, and the modular software architecture is presented. The relative dynamics in eccentric reference orbits is reviewed, and families of periodic, relative trajectories are identified, expressed as sets of static geometric parameters. The guidance law design is presented, and an example reconfiguration scenario is used to illustrate the distributed process of assigning geometric goals to the cluster. Next, a decentralized maneuver planning approach is presented that utilizes linearprogramming methods to enact reconfiguration and coarse formation keeping maneuvers. Finally, a method for performing online collision avoidance is discussed, and an example is provided to gauge its performance. [ABSTRACT FROM AUTHOR]

Using newly available information from Russian archives, this paper explores American rocketry pioneer Robert Goddard's relationship to the Soviet space-flight advocacy community in the 1920s. In post-Revolutionary Russia, Goddard enjoyed a curious kind of fame. News of his alleged plan to launch a rocket to the Moon permeated widely through a Soviet audience interested in the possibility of space exploration. Goddard's practical work in developing rockets became a metaphor for the aspirations of the many in Soviet Russia who were unwilling to limit their horizons to theory and prognostication. The new research into Goddard's relationship to the Soviet space-flight enthusiast community underscores how international contacts shaped the space advocacy movements of the early twentieth century. The new evidence prompts us to consider an alternative approach to the 'foundation myth' of space history involving Tsiolkovskii, Goddard and Oberth, one that privileges an international context instead of the usual multiple national contexts. [ABSTRACT FROM AUTHOR]

In this paper, we consider minimizing the action functional as a method for numerically discovering periodic solutions to the n-body problem. With this method, we can find a large number of choreographies and other more general solutions. We show that most of the solutions found, including all but one of the choreographies, are unstable. It appears to be much easier to find unstable solutions to the n-body problem than stable ones. Simpler solutions are more likely to be stable than exotic ones. [ABSTRACT FROM AUTHOR]

The International Academy of Astronautics (IAA) Symposia on the History of Rocketry and Astronautics have been held annually at the International Astronautical Congresses since 1967. During these past 50 years nearly 800 papers have been presented and subsequently published in the proceedings. With a 20-year rule imposed for historical presentations, the first 10 symposia concentrated on pre-World War II and early 1950s activities. A surprisingly large number of papers on early, less well-known Soviet-Russian contributions to rocketry and astronautics were presented in the first symposia, despite the ongoing Space Race between the U.S and USSR. Another important element in these symposia involved memoir papers offered by pre- and post-war rocket and astronautics pioneers from many countries, and the participation of many of these pioneers in person. In sum, the history of national space and rocket projects from some 40 countries were presented over the years in IAA History Symposia. These 50 symposia have provided a platform for scholars and professional and non-professional historians to meet and discuss the history of rocketry and astronautics, and to personally interview many space pioneers, most of whom today are deceased. Their personal recollections have since been shared with a large audience. Over time, IAA history papers divided into recognizable periods: ancient times through the 19th century, and the 20th and 21st centuries, which separate among actions and events that took place before 1945, in 1945 to 1957, and after 1957 (which marked the beginning of the space age). Proceedings of the IAA History Symposia have been published in English, ultimately in the History Series of the American Astronautical Society (AAS) and its publishing arm, Univelt Inc., under an agreement secured with the IAA. This paper presents an overview of the IAA History Symposia. It examines the early years of the history committee and its first symposium, the evolution of subsequent symposia, and it recognizes those individuals who shaped these symposia and the publication of its proceedings. [ABSTRACT FROM AUTHOR]

The aim of this paper is to optimize reliability and mass of three CO 2 extraction technologies/components: the 4-Bed Molecular Sieve, the Electrochemical Depolarized Concentrator and the Solid Amine Water Desorption. The first one is currently used in the International Space Station and the last two are being developed, and could be used for future long duration missions. This work is part of a complex study of the Environmental Control and Life Support System (ECLSS) reliability. The result of this paper is a methodology to analyze the reliability and mass at a component level, which is used in this paper for the CO 2 extraction technologies, but that can be applied to the ECLSS technologies that perform other tasks, such as oxygen generation or water recycling, which will be a required input for the analysis of an entire ECLSS. The key parameter to evaluate any system to be used in space is mass, as it is directly related to the launch cost. Moreover, for long duration missions, reliability will play an even more important role, as no resupply or rescue mission is taken into consideration. Each technology is studied as a reparable system, where the number of spare parts to be taken for a specific mission will need to be selected, to maximize the reliability and minimize the mass of the system. The problem faced is a Multi-Objective Optimization Problem (MOOP), which does not have a single solution. Thus, optimum solutions of MOOP, the ones that cannot be improved in one of the two objectives, without degrading the other one, are found for each selected technology. The solutions of the MOOP for the three technologies are analyzed and compared, considering other parameters such as the type of mission, the maturity of the technology and potential interactions/synergies with other technologies of the ECLSS. [ABSTRACT FROM AUTHOR]

The Arctic has become an area of particular relevance, where manifold interests meet with particular challenges, such as the harsh environment, a limited infrastructure and a low population density. Since many years, the European Space Agency (ESA) supports its Member States with interests in the Arctic. A variety of ESA programmes are directly or indirectly targeting the Arctic area for scientific purposes, for a better understanding of the Arctic environment or to support other activities in the Arctic region, since many of the specific challenges of the Arctic can be addressed by space technology. Monitoring and assessing the Arctic environment are tasks best met with space systems. Satellite technology facilitates navigation and communication and improves marine safety, and it enables the comprehension of climate change impacts, which are particularly evident and dramatic in the Arctic. While the Sustainable Development Goals (SGDs), which were adopted by UN Member States in 2015, apply globally, the Arctic is especially affected by the changing climate and thus considered to be of great interest to the European and international community. ESA fully supports and works towards attaining the SGDs, and has to this end created a toolbox to target each of the 17 goals. Given the technological capabilities of ESA as well as the Agency's commitment to the SDGs, ESA continues to strengthen its contributions towards a sustainable economic development in the Arctic. After providing a general introduction to the Arctic and its legal status, as well as an overview over different interests in the region, this paper details the numerous ways, in which space activities can contribute to the sustainable development and life in the Arctic. It then turns to retracing the specific steps taken in the European Space Agency, including the work of specific Arctic Task Forces, and gives an outlook on future projects in support of a sustainable Arctic. • The Arctic, heavily affected by climate change, is vital for the global community. • Monitoring and assessing Arctic environment are tasks best met with space systems. • ESA, working on attaining the 17 SGDs, has created a toolbox to target each of them. [ABSTRACT FROM AUTHOR]

Availability of higher capacity for both uplinks and downlinks is expected in the future deep-space missions on Mars, thus enabling a large range of services that could eventually support human remote operations. The provisioning for deep-space links offering data rate up to several megabits per second will be a crucial element to allow new services for the space domain along with the common telecommand and telemetry services with enhanced communication capabilities. On the other hand, also the geometry proper of this scenario with orbiting and landed elements sharing only partial visibility among them and towards Earth provides another challenge. This paper surveys the reliability options that are available in the Consultative Committee for Space Data Systems (CCSDS) Protocol Stack for application in the deep-space missions. In particular, the solutions implemented from the physical up to the application layer are illustrated in terms of channel coding and Automatic Retransmission reQuest (ARQ) schemes. Finally, advanced reliability strategies possibly applicable in next-generation deep-space missions are explored as well. [ABSTRACT FROM PUBLISHER]

Abstract: Korea has a short history in space development compared to neighboring countries like Japan, China, India and Russia. During the past 20 years, Korea has focused on developing satellite and rocket space technology under the national space development plan. KOMPSAT-1 and 2, and KSLV-1 are the results of the selection and concentration policy of the Korean government. Due to the arduous mission of developing hardware oriented space technology, the topic of space education and outreach for the general public has not received much in the national space program. But recently, the Korean government has begun planning a space science outreach program in the detailed action plan of the mid-long term national space development plan. This paper introduces and analyzes the organizations performing space education and outreach programs for primary and secondary schools in the Republic of Korea. “Young Astronaut Korea (YAK)” is one such program. This is a non-profit organization established to provide space education for students in 1989 when Korea just started its space development program. “YAK” is a unique group in Korea for space education and outreach activities because it is organized by branches at each school in the nation and it is much like the Boy Scout and Girl Scout programs. Space Science Museum and National Youth Space Center (NYSC), which are located near NARO space center in the southernmost part of the Korean peninsula are other examples of space education and outreach programs. NARO space center, which is the only launch site in Korea became the center of public interest by showing the KSLV-1 launch in 2009 and will be expected to play a key role for the space education of students in the Republic of Korea. The NYSC will perform many mission oriented space education programs for students as Space Camp in the USA does. This paper introduces the status of the space education and outreach programs of each organization and presents the future direction of space education and outreach for the Korean public and students. If these three organizations cooperate with each other and develop systematic programs of space education and outreach for the people, they will prepare a base for growth and progress in future space science and technology in Korea. [Copyright &y& Elsevier]

Abstract: The current emphasis in the US and internationally on lunar robotic missions is generally viewed as a precursor to possible future human missions to the Moon. As initially framed, the implementation of high level policies such as the US Vision for Space Exploration (VSE) might have been limited to either human lunar sortie missions, or to the testing at the Moon of concepts-of-operations and systems for eventual human missions to Mars [White House, Vision for Space Exploration, Washington, DC, 14 January, 2004. ]. However, recently announced (December 2006) US goals go much further: these plans now place at the center of future US—and perhaps international—human spaceflight activities a long-term commitment to an outpost on the Moon. Based on available documents, a human lunar outpost could be emplaced as early as the 2020–2025 timeframe, and would involve numerous novel systems, new technologies and unique operations requirements. As such, substantial investments in research and development (R&D) will be necessary prior to, during, and following the deployment of such an outpost. It seems possible that such an outpost will be an international endeavor, not just the undertaking of a single country—and the US has actively courted partners in the VSE. However, critical questions remain concerning an international lunar outpost. What might such an outpost accomplish? To what extent will “sustainability” be built into the outpost? And, most importantly, what will be the outpost''s life cycle cost (LCC)? This paper will explore these issues with a view toward informing key policy and program decisions that must be made during the next several years. The paper will (1) describe a high-level analytical model of a modest lunar outpost, (2) examine (using this model) the parametric characteristics of the outpost in terms of the three critical questions indicated above, and (3) present rough estimates of the relationships of outpost goals and “sustainability” to LCC. The paper will also consider possible outpost requirements for near-term investments in enabling research in light of experiences in past advanced technology programs. [Copyright &y& Elsevier]

The SMART-i mission was successfully completed on September 3, 2006, with a controlled crash on the visible side of the Moon. The primary electric-propulsion (EP) system included a nonredundant SNECMA PPS-i350-G Hall effect thruster. The thruster discharge was electrically floating with respect to the spacecraft ground. The cathode floating potential (UCRP) is an important thruster parameter, giving information on cathode performance and life expectancy. During ground testing and steady-state operation, UCRP was approximately constant and negative. However, in space, it was observed that the UCRP was slightly positive and was periodically varying in time by a few volts. The capability to compare to ground-test data and check the cathode good health and life potential was largely impaired. Fortunately, SMART-i included a plasma diagnostic package (electric-propulsion diagnostic package) with a Langmuir probe and a retarding-potential analyzer, both positioned on the same plane as the plasma thruster and provided data on the plasma potential as well as the energy of the charge-exchange ions. The short- and long-term correlations of these data with the cathode reference potential (CRP) were performed. It was concluded that the UCRP is evolving with respect to the plume potential near the cathode, and this potential difference is shown to be constant over the mission. Plume-potential distribution is adapting itself relative to the local plasma potential. The spacecraft potential with respect to the plasma potential is defined in steady state when the electron and ion currents entering and leaving the spacecraft are balanced. This balance depends primarily on the solar-array electrical configuration and orientation and thruster operating conditions. When the local plasma is chosen as a reference, the absolute cathode potential is found to be the same as the one on the ground. This paper confirms the good health of the cathodes. Contrary to a spacecraft without EP, the SMART-i spacecraft potential varies within a limited range and is comparatively close to zero during electric-thruster operation. In addition, UCRP can be used to derive the spacecraft potential throughout the mission. All the various cyclic and long-term effects influencing the spacecraft potential on SMART-i have been identified and characterized across the mission lifetime. In particular, a strong correlation between the solar-array rotation and the variation of the spacecraft potential has been established. [ABSTRACT FROM AUTHOR]

Abstract: The International Space Station (ISS) is a multifaceted international project. Several space agencies from different countries work together in the Outer Space. This paper will illustrate the exciting questions arising from such a venture and therefore the challenge to incorporate a variety of issues into a legal order. The Paper is addressed to lawyers who need not necessarily be experts in space law, and also to space experts who have no legal background. It demonstrates the three layers of the ISS regime—from the “Intergovernmental Agreement” (IGA) as a “frame” with pillars and boundaries, over the “Memoranda of Understanding” (MOU) which rules in a more specific way, to the so-called “Implementing Arrangements” regulating the overall and single aspects of ISS in detail. The paper underlines questions of applicable jurisdiction, utilization rights and the rights on intellectual property onboard of the ISS. Furthermore the problem of liability in space flight is highlighted, also with a view to the different aspects of the liability issue, for example (internal) liability caused by programme delays (e.g. US Space Shuttle delays). In conclusion, the paper illustrates the situation of astronauts by the “Code of Conduct for the International Space Station Crew” and provides an example for the actual ISS Programme—an international cooperation in a highly demanding environment which will be a basis for future space ventures in many ways. [Copyright &y& Elsevier]

Problems of obtaining of robust estimates of the state of space vehicles with flexible dynamics are considered in the paper. It is shown, that for improvement of the quality of flexible spacecraft handeling at presence of parametric indeterminacy of its model it is necessary to use approaches of synthesis of parametric robust adjusters. Algorithmus of neural control are also considered in the paper, and it is marked, that on the basis of these algorithms it is possible to decide problems of steering flexible spacecraft handling in the case of complicate parameterization of indeterminacy of its model. [ABSTRACT FROM AUTHOR]

In this paper, the preliminary design of a space mission is approached by introducing uncertainties on the design parameters and formulating the resulting reliable design problem as a multiobjective optimization problem. Uncertainties are modelled through evidence theory and the belief, or credibility, that the successful achievement of mission goals is maximized along with the reliability of constraint satisfaction. The multiobjective optimization problem is solved through a novel algorithm based on the collaboration of a population of agents in search for the set of highly reliable solutions. Two typical problems in mission analysis are used to illustrate the proposed methodology. [ABSTRACT FROM AUTHOR]

This paper establishes a methodology for obtaining the general solution to the spacecraft relative motion problem by utilizing Cartesian configuration space in conjunction with classical orbital elements. The geometry of the relative motion configuration space is analyzed, and the relative motion invariant manifold is determined. Most importantly, the geometric structure of the relative motion problem is used to derive useful metrics for quantification of the minimum, maximum, and mean distance between spacecraft for commensurable and non-commensurable mean motions. A number of analytic solutions, as well as useful examples, are provided, illustrating the calculated bounds. A few particular cases are given that yield simple solutions. [ABSTRACT FROM AUTHOR]

The engineering goal of the Deep Impact mission is to impact comet Tempel 1 on July 4, 2005, with a 370 kg active Impactor spacecraft (s/c). The impact velocity will be just over 10 km/s and is expected to excavate a crater approximately 20 m deep and 100 m wide. The Impactor s/c will be delivered to the vicinity of Tempel 1 by the Flyby s/c, which is also the key observing platform for the event. Following Impactor release, the Flyby will change course to pass the nucleus at an altitude of 500 km and at the same time slow down in order to allow approximately 800 s of observation of the impact event, ejecta plume expansion, and crater formation. Deep Impact will use the autonomous optical navigation (AutoNav) software system to guide the Impactor s/c to intercept the nucleus of Tempel 1 at a location that is illuminated and viewable from the Flyby. The Flyby s/c uses identical software to determine its comet-relative trajectory and provide the attitude determination and control system (ADCS) with the relative position information necessary to point the High Resolution Imager (HRI) and Medium Resolution Imager (MRI) instruments at the impact site during the encounter. This paper describes the Impactor s/c autonomous targeting design and the Flyby s/c autonomous tracking design, including image processing and navigation (trajectory estimation and maneuver computation). We also discuss the analysis that led to the current design, the expected system performance as compared to the key mission requirements and the sensitivity to various s/c subsystems and Tempel 1 environmental factors. [ABSTRACT FROM AUTHOR]

The primary objective of the International Space Station (ISS) is to provide a long-term quiescent environment for the conduct of scientific research for a variety of microgravity science disciplines.This paper reports to the microgravity scientific community the results of an initial characterization of the microgravity environment on the International Space Station for increments 2 through 4. During that period almost 70,000 hours of station operations and scientific experiments were conducted. 720 hours of crew research time were logged aboard the orbiting laboratory and over half a terabyte of acceleration data were recorded and much of that was analyzed. The results discussed in this paper cover both the quasi-steady and vibratory acceleration environment of the station during its first year of scientific operation.For the quasi-steady environment, results are presented and discussed for the following: the space station attitudes Torque Equilibrium Attitude and the X-Axis Perpendicular to the Orbital Plane; station docking attitude maneuvers; Space Shuttle joint operation with the station; cabin de-pressurizations and the station water dumps.For the vibratory environment, results are presented for the following: crew exercise, docking events, and the activation/de-activation of both station life support system hardware and experiment hardware. Finally, a grand summary of all the data collected aboard the station during the 1-year period is presented showing where the overall quasi-steady and vibratory acceleration magnitude levels fall over that period of time using a 95th percentile benchmark. [Copyright &y& Elsevier]

This paper focuses on the technical challenges that arise when electric propulsion is used on a small spacecraft such as SMART-1. The choice of electric propulsion influences not only the attitude control system and the power system, but also the thermal control as well as the spacecraft structure. A description is given on how the design of the attitude control system uses the possibility to control the alignment of the thrust vector in order to reduce the momentum build-up. An outline is made of the philosophy of power generation and distribution and shows how the thermal interfaces to highly dissipating units have been solved.Areas unique for electric propulsion are the added value of a thrust vector orientation mechanism and the special consideration given to the electromagnetic compatibility. SMART-1 is equipped with a thruster gimbal mechanism providing a 10° cone in which the thrust vector can be pointed. Concerning the electromagnetic compatibility, a discussion on how to evaluate the available test results is given keeping in mind that one of the main objectives of the SMART-1 mission is to assess the impact of electric propulsion on the scientific instruments and on other spacecraft systems.Finally, the assembly, integration and test of the spacecraft is described. Compared to traditional propulsion systems, electric propulsion puts different requirements on the integration sequence and limits the possibilities to verify the correct function of the thruster since it needs high quality vacuum in order to operate.Prime contractor for SMART-1 is the Swedish Space Corporation (SSC). The electric propulsion subsystem is procured directly by ESA from SNECMA, France and is delivered to SSC as a customer furnished item.The conclusion of this paper is that electric propulsion is possible on a small spacecraft, which opens up possibilities for a new range of missions for which a large velocity increment is needed. The paper will also present SMART-1 and show how the problems related to the accommodation of electric propulsion have been solved during design and planning of the project. [Copyright &y& Elsevier]

The problems of investigation and optimization of the motion of spacecraft are extensively discussed in the literature. Nevertheless, in many cases a large variety of qualitative characteristics of their motion and of the form of their trajectories are still unclear. In this paper we consider a plane equiangular acceleration of a spacecraft both in a Newtonian field and in its absence (at a large distance from the center of attraction). The general equation of a trajectory of plane acceleration is presented with the introduction of a new variable, an index of an exponent, which allows one to obtain convenient solutions at different values of the time-independent angle of inclination of the vector of thrust to the spacecraft's radius vector (i.e., when equiangular acceleration takes place). Asymptotic solutions are constructed and an interesting fact is revealed. Namely, it is shown that when the center of attraction exists or is absent, for all initial conditions the trajectories appearing at the above equiangular acceleration of a material point tend to the standard logarithmic spirals at a large distance from the center. Specifically, when the value of transverse (perpendicular to the radius vector) thrust is constant, there appears a logarithmic spiral with an angle of inclination to the radius vector equal to 35.264°. Different forms of the trajectory of equiangular acceleration of spacecraft at a low thrust are also studied. The results obtained can be useful for the investigation and choice of optimum space trajectories. [ABSTRACT FROM AUTHOR]

Weak stability regions serve as superior locations for interferomertric scientific investigations. These regions are often selected to minimize environmental disturbances and maximize observation efficiency. Designs of formations in these regions are becoming ever more challenging as more complex missions are envisioned. The development of algorithms to enable the capability for formation design must be further enabled to incorporate better understanding of weak stability boundary solution space. This development will improve the efficiency and expand the capabilities of current approaches. The Goddard Space Flight Center (GSFC) is currently supporting multiple formation missions in weak stability boundary regions. This end-to-end support consists of mission operations, trajectory design, and control. It also includes both algorithm and software development. The Constellation-X, Maxim, and Stellar Imager missions are examples of the use of improved numeric methods to attain constrained formation geometries and control their dynamical evolution. This paper presents a survey of formation missions in the weak stability boundary regions and a brief description of formation design using numerical and dynamical techniques. [ABSTRACT FROM AUTHOR]

Abstract In traditional form-finding of a deployable mesh reflector (DMR), the nodes of the DMR mesh are placed on the desired working surface and the surface accuracy of the DMR is measured either by the deviation of the nodes from the desired working surface or by the deviation of the mesh from its best-fit surface. Placement of nodes on working surface and inaccurate measures of surface accuracy cause non-negligible surface errors that cannot be further reduced. To deal with these issues and to further improve surface accuracy of DMRs, a new mesh geometry design method, called the Projecting Surface Method (PSM), is presented in this paper. The highlight of the PSM is that it purposely places the nodes of a DMR off its working surface, to achieve higher surface accuracy. To this end, a direct RMS error measuring the deviation of a DMR mesh from its desired working surface is introduced and a projecting surface for hosting the nodes of the DMR mesh is defined. By the direct RMS error and projecting surface, an optimization process produces a mesh geometry with its best-fit surface closest to the desired working surface, leading to significant surface error reduction. As shown in numerical examples of DMRs with 37, 271 and 817 nodes, the PSM can reduce surface errors by 50% or more. The proposed method is usable with existing form-finding methods for further improvement of surface accuracy of DMRs. Highlights • A newly defined RMS error for precise measurement of surface accuracy. • Establishment of a projecting surface for form-finding of mesh reflectors. • Purposely placing mesh nodes off the working surface of a reflector in design. • Significant reduction of surface errors (by 50–97%). • Usable with any existing form-finding method for further surface error reduction. [ABSTRACT FROM AUTHOR]

Abstract In this paper I revisit proposed definitions of the boundary between the Earth's atmosphere and outer space, considering orbital and suborbital trajectories used by space vehicles. In particular, I investigate the inner edge of outer space from historical, physical and technological viewpoints and propose 80 km as a more appropriate boundary than the currently popular 100 km Von Kármán line. Highlights • Historically, the lowest satellite orbits have had perigees as low as 80-90 km. • The Karman Line as originally defined lies between 70 and 90 km, not at 100 km. • This result is not sensitive to solar activity or other atmospheric variations. [ABSTRACT FROM AUTHOR]

Public support and interest are needed to design an ambitious human spaceflight program. However, it is difficult to understand what the public values and would support. And it is even more challenging and rare to consider public views prior to actually developing a mission. Participatory technology assessment (pTA) is a method that aims to understand public preferences and values in order to inform upstream government decision-making. We assess a recently completed experiment in pTA, the “Informing NASA's Asteroid Initiative” project. Through a cooperative agreement with NASA, the Expert and Citizen Assessment of Science and Technology (ECAST) network conducted a pTA-based forum on NASA's Asteroid Initiative and the Journey to Mars. ECAST organized two citizen forums in Phoenix, Arizona and Boston, Massachusetts in November 2014, with a total of 183 citizens selected so as to minimize self-selection biases. This paper focuses on the “Journey to Mars” session, which had the primary goal of soliciting citizen perceptions about different Mars exploration scenarios and mission planning approaches. Citizens were given background information about three potential Mars exploration scenarios that NASA could carry out: 1) Crewed orbital mission to direct robots on the surface of Mars; 2) Short exploratory crewed mission to the surface of Mars; and 3) establishing a permanent settlement. Citizens then engaged in structured facilitated discussions about their preferences among the scenarios and NASA's mission planning approach. Using a grounded theory coding approach, we analyzed participants' written rationales and dialogue about Mars exploration. In general, participants did not show a strong preference for any particular mission profile, but there was a slight preference for the crewed orbital robotics scenario. Participants who supported this approach saw it as the quickest, safest, and least costly road to a successful mission. However, many participants were interested in seeing “boots on the ground,” as they believed this would propel scientific advancement, increase excitement about space exploration, and make humans a “two-planet species.” [ABSTRACT FROM AUTHOR]

In examining alternative space-development models, one observes that Heinlein postulated the first Moon flight as the outcome of the focused action of an individual – building upon an ample commercial aerospace transportation infrastructure. The same technological basis and entrepreneurial drive would then sustain a fast human and economic expansion on three new planets. Instead, historically, humans reached the Moon thanks to a “Faustian bargain” between astronautical developers and governments. This approach brought the early Apollo triumphs, but it also created the presumption of this method as the sole one for enabling space development. Eventually, the application of this paradigm caused the decline of the astronautical endeavor. Thus, just as conventional methods became unable to sustain the astronautical endeavor, space development appeared as vital, e.g., to satisfy the people׳s basic needs (metabolic resources, energy, materials, and space), as shown elsewhere. Such an endeavor must grow from actions generating new wealth through commercial activities to become self-supporting. Acquisition and distribution of multiform space resources call, however, for a sound ethical environment, as predatory governments can easily forfeit those resources. The paper begins the search for means apt to maintain a societal environment suited for this purpose. Among numerous initiatives needed, dissemination of factual information and moral-right education support take a central position: In fact, the vital condition for true Astronautics – a vast increase in actual respect of moral rights – can also become its best consequence, as the prosperity from the space arena empowers the people, making them materially safer and more secure in their fundamental moral rights. [ABSTRACT FROM AUTHOR]

Abstract: Space science missions are increasingly challenged today: in ambition, by increasingly sophisticated hypotheses tested; in development, by the increasing complexity of advanced technologies; in budgeting, by the decline of flagship-class mission opportunities; in management, by expectations for breakthrough science despite a risk-averse programmatic climate; and in planning, by increasing competition for scarce resources. How are the space-science missions of tomorrow being formulated? The paper describes the JPL Innovation Foundry, created in 2011, to respond to this evolving context. The Foundry integrates methods, tools, and experts that span the mission concept lifecycle. Grounded in JPL's heritage of missions, flight instruments, mission proposals, and concept innovation, the Foundry seeks to provide continuity of support and cost-effective, on-call access to the right domain experts at the right time, as science definition teams and Principal Investigators mature mission ideas from “cocktail napkin” to PDR. The Foundry blends JPL capabilities in proposal development and concurrent engineering, including Team X, with new approaches for open-ended concept exploration in earlier, cost-constrained phases, and with ongoing research and technology projects. It applies complexity and cost models, project-formulation lessons learned, and strategy analyses appropriate to each level of concept maturity. The Foundry is organizationally integrated with JPL formulation program offices; staffed by JPL's line organizations for engineering, science, and costing; and overseen by senior Laboratory leaders to assure experienced coordination and review. Incubation of each concept is tailored depending on its maturity and proposal history, and its highest-leverage modeling and analysis needs. [Copyright &y& Elsevier]

Abstract: This paper presents the development of solar arrays for Argentine satellite missions performed within the frame of cooperation agreements between the Argentine National Atomic Energy Commission (CNEA) and the Argentine National Commission for Space Activities (CONAE). Relevant issues such as simulation and design, solar cells characterisation, set up of soldering and bonding processes, radiation damage and development of testing techniques, are reviewed. A chamber for testing solar cells and other devices in a simulated space environment, and the integration and tests of two engineering models for qualification of space technology processes are described. The requirements and solar array design for 3 missions, Aquarius/SAC-D and SAOCOM 1A and 1B, are presented. Finally, the flight model for the SAC-D mission, which was launched on 10 June 2011, is outlined, and telemetry data analysis from the first stages of the mission is presented. [Copyright &y& Elsevier]

Abstract: The paper analyzes the “value proposition” for government-funded human space flight, a vexing question that persistently dogs efforts to justify its $1010/year expense in the US. The original Mercury/Gemini/Apollo value proposition is not valid today. Neither was it the value proposition actually promoted by von Braun, which the post-Apollo 80% of human space flight history has persistently attempted to fulfill. Divergent potential objectives for human space flight are captured in four strategic options—Explore Mars; accelerate Space Passenger Travel; enable Space Power for Earth; and Settle the Moon—which are then analyzed for their purpose, societal myth, legacy benefits, core needs, and result as measured by the number and type of humans they would fly in space. This simple framework is proposed as a way to support productive dialog with public and other stakeholders, to determine a sustainable value proposition for human space flight. [Copyright &y& Elsevier]

Abstract: After a gap of 40 years, the Moon is again the focus of several countries’ space ambitions. Japan, China and India have already launched their first Moon missions and are expected to send humans moonwards within the next 10–15 years. This revival of lunar programmes in the post-cold war era goes beyond symbolism and is also about the race to grab the natural resources of the Moon. Such ambitious missions by these states imply that they intend to change the unipolar world into one with multiple power centres, and would use space technology as one of the components to do so. This paper examines the first phase Moon missions of the Asian states and argues that their overall deep space mission aspirations have strategic ambitions attached. [ABSTRACT FROM AUTHOR]

Abstract: The word “exploration” threads its way through every discussion of human space flight and often headlines national policy statements about the US space agency. Yet this concept, so rooted in our culture, remains remarkably ill-defined. In this paper, we examine various presumptions implicit in the term and its ramifications for federally supported space endeavors. We argue that historical examples of exploration, widely used by policy makers, often make poor models for contemporary space travel. In particular, historical precedents of exploration set up a land-biased view of discovery, a restriction which impedes full expression of the Vision for Space Exploration and its possible scientific returns. These same precedents also set up a view of discovery that is biased toward in situ human presence, a view that modern technology is rendering increasingly absurd. [Copyright &y& Elsevier]

We examine photoelectron distributions detected by the low-energy-particle (LEP) instrument onboard the GEOTALL spacecraft by means of both data analysis and numerical simulations. Statistical data analysis shows asymmetries in the photoelectron distributions. For photoelectrons incident normal to the spacecraft spin axis, a higher flux is observed in the dawnward than in the duskward sector of the LEP. The distribution significantly depends on the ratio of the photoelectron energy to the spacecraft potential. Our numerical simulations reveal that the asymmetry is caused by the electrostatic potential around the thin antenna located at +18° anticlockwise (viewed from the top) relative to the LEP. Photoelectrons in the dawnward sector are preferentially carried from the sunlit surface by this potential. For upward/downward incident photoelectrons, a higher flux of upward photoelectrons is observed in the antisunward than in the sunward sector, whereas downward photoelectrons show a weak asymmetry. Our numerical simulations demonstrate that the greater flux of upward photoelectrons is caused by the electrons emitted from the sunlit surface; they are attracted to the antisunward sector. Based on these results, the asymmetries in the photoelectron distribution measured around GEOTAIL are found to be caused by the asymmetric positioning of the thin antennas relative to the LEP. [ABSTRACT FROM AUTHOR]

In this paper a solar sail magnetotail mission concept was examined. The 43-m square solar sail is used to provide the required propulsion for continuous sun-synchronous apse-line precession. The main driver in this mission was found to be the reduction of launch mass and mission cost while enabling a nominal duration of 2 years within the framework of a demonstration mission. It was found that the mission concept provided an excellent solar sail technology demonstration option. The baseline science objectives and engineering goals were addressed, and mission analysis for solar sail, electric, and chemical propulsion performed. Detailed subsystems were defined for each propulsion system and it was found that the optimum propulsion system is solar sailing. A detailed tradeoffas to the effect of spacecraft and sail technology levels, and requirements, on sail size is presented for the first time. The effect of, for example, data acquisition rate and RF output power on sail size is presented, in which it is found that neither have a significant effect. The key sail technology requirements have been identified through a parametric analysis. [ABSTRACT FROM AUTHOR]

Abstract: The application of SCARAB (spacecraft atmospheric re-entry and aerothermal break-up) to several re-entry objects within the last years has shown the need of fast methods and easy-to use guidelines for a first assessment of the survival probability for these objects or parts of them. Such methods and guidelines will be also very helpful during the design process of a satellite in order to decide, whether a controlled re-entry had to be foreseen at the end of the lifetime, or an uncontrolled re-entry would be acceptable. Within current studies HTG has developed analytical and numerical methods to analyze the demise of simple-shaped objects like spheres, boxes, and cylinders. In addition, the SCARAB software system has been used to evaluate the shielding effects of concentric shells. This paper presents the analytical and numerical models used within the study and the results which have been achieved, including demise ranges for several object/material combinations. The SCARAB results for shielding effects are presented as well. [Copyright &y& Elsevier]

Abstract: The optimal attitude control problem of spacecraft during the stretching process of solar wings is investigated in this paper. The dynamical equations of the nonholonomic system are derived from the conservation principle of the angular momentum of the multibody system. Attitude control of the spacecraft with internal motion is reduced to a nonholonomic motion planning problem. The spacecraft attitude control is transformed into the steering problem for a drift free control system. The optimal solution for steering a spacecraft with solar wings is presented. The controlled motion of spacecraft is simulated for two cases. The numerical results demonstrate the effectiveness of the optimal control approach. [Copyright &y& Elsevier]

Abstract: This paper discusses the findings for [Interior] configuration options, habitability and architectural aspects of a first human spacecraft to Mars. In 2003 the space architecture office LIQUIFER was invited by the European Space Agency''s (ESA) AURORA Program committee to consult the scientists and engineers from the European Space and Technology Center (ESTEC) and other European industrial communities with developing the first human mission to Mars, which will take place in 2030, regarding the architectural issues of crewed habitats. The task was to develop an interior configuration for a transfer vehicle (TV) to Mars, especially a transfer habitation module (THM) and a surface habitat module (SHM) on Mars. The total travel time Earth—Mars and back for a crew of six amounts to approximately 900 days. After a 200-day-flight three crewmembers will land on Mars in the Mars excursion vehicle (MEV) and will live and work in the SHM for 30 days. For 500 days before the 200-day journey back the spacecraft continues to circle the Martian orbit for further exploration. The entire mission program is based on our present knowledge of technology. The project was compiled during a constant feedback-design process and trans-disciplinary collaboration sessions in the ESA-ESTEC concurrent design facility. Long-term human space flight sets new spatial conditions and requirements to the design concept. The guidelines were developed from relevant numbers and facts of recognized standards, interviews with astronauts/cosmonauts and from analyses about habitability, sociology, psychology and configuration concepts of earlier space stations in combination with the topics of the individual''s perception and relation of space. Result of this study is the development of a prototype concept for the THM and SHM with detailed information and complete plans of the interior configuration, including mass calculations. In addition the study contains a detailed explanation of the development of the Design process including all suggested design and configuration options. [Copyright &y& Elsevier]

Abstract: The paper discusses concepts about the role of architecture in the design of space habitats and the development of a general evaluation criteria of architectural design contribution. Besides the existing feasibility studies, the general requisites, the development studies, and the critical design review which are mainly based on the experience of human space missions and the standards of the NASA-STD-3000 manual and which analyze and evaluate the relation between man and environment and between man and machine mainly in its functionality, there is very few material about design of comfort and wellbeing of man in space habitat. Architecture for space habitat means the design of an artificial environment with much comfort in an “atmosphere” of wellbeing. These are mainly psychological effects of human factors which are very important in the case of a long time space mission. How can the degree of comfort and “wellbeing atmosphere” in an artificial environment be measured? How can the quality of the architectural contribution in space design be quantified? Definition of a criteria catalogue to reach a larger objectivity in architectural design evaluation. Definition of constant parameters as a result of project necessities to quantify the quality of the design. Architectural design analysis due the application and verification within the parameters and consequently overlapping and evaluating results. Interdisciplinary work between architects, astronautics, engineers, psychologists, etc. All the disciplines needed for planning a high quality habitat for humans in space. Analysis of the principles of well designed artificial environment. Good quality design for space architecture is the result of the interaction and interrelation between many different project necessities (technological, environmental, human factors, transportation, costs, etc.). Each of this necessities is interrelated in the design project and cannot be evaluated on its own. Therefore, the design process needs constant check ups to choose each time the best solution in relation to the whole. As well as for the main disciplines around human factors, architectural design for space has to be largely tested to produce scientific improvement. [Copyright &y& Elsevier]

Abstract: This paper discusses the development of a full-pressure space suit to be used in the Argentine Gauchito suborbital space vehicle. Rationales for providing full-pressure suits with bailout capabilities for both crew and passengers are first discussed. Mishaps during past US and Russian space missions are also presented to show how the hazards of reentry and landing can be mitigated by a robust space suit with bailout capabilities. Results from the testing of the suit''s helmet, enclosure mechanisms, gloves, cooling system, thermal garment, and mobility range are presented followed by a description of the suit''s emergency operating procedures. Testing of the suit culminated in an altitude chamber and a high-altitude glider flight. [Copyright &y& Elsevier]

Abstract: The “Pille-MKS” thermoluminescent (TL) dosimeter system developed by the KFKI Atomic Energy Research Institute (KFKI AEKI) and BL-Electronics, consisting of 10 :Dy bulb dosimeters and a compact reader, has been continuously operating on board the International Space Station (ISS) since October 2003. The dosimeter system is utilized for routine and extravehicular activity (EVA) individual dosimetry of astronauts/cosmonauts as part of the service system as well as for on board experiments, and is operated by the Institute for Biomedical Problems (IBMP). The system is unique in that it regularly provides accurate dose data right on board the space station, a feature that became increasingly important during the suspension of the Space Shuttle flights. Seven dosimeters are located at different places of the Russian segment of the ISS and are read out once a month. Two of these dosimeters are dedicated to EVAs and one is kept in the reader and will be read out automatically every 90min. During coronal mass ejections impacting Earth some of the dosimeters serve for individual monitoring of the astronauts with readouts once or twice every day. In this paper we report the results of dosimetric measurements made on board the ISS during Expedition-8, -9 and -10 using the “Pille” portable thermoluminescent detector (TLD) system and we compare them with our previous measurements on different space stations. [Copyright &y& Elsevier]

Main directions of space activities of Ukrainian enterprises and organizations for 2007-2011 years as an important direction of the state development have been analyzed in this paper. The achievements or previous years are shown. They have shown a high space status of the state. Main tasks of the new Ukrainian Space Program and the ways to fulfill them have been described. The place and importance of the scientific, educational and youth programs, and significance of the universities for creating small satellites and for carrying out the space projects have been determined. [ABSTRACT FROM AUTHOR]

Abstract: This paper provides a classification of robotics means for planetary missions with a description of their characteristic, benefits and current and future applications in low cost planetary missions. [Copyright &y& Elsevier]

Abstract: This paper presents an extension to the classical cones intersection technique, which was, and is, exhaustively used to estimate the spin axis direction of spin stabilized spacecraft. The resulting optimal cones intersection technique is derived from a demonstrated co-planarity condition and does not present ambiguities or singularities. The proposed method allows an optimal estimation of any on-board direction in a closed-form by fully complying with Wahba''s optimality criterion of spacecraft attitude. Numerical tests show that the optimal cones intersection technique is faster than ESOQ-2, the presently fastest optimal attitude estimator, for two vector observation case. [Copyright &y& Elsevier]

Abstract: Korea has participated in space development only since the 1990s. Despite its short history, Korea has been increasing its technological capabilities with the successful experience of several national projects. The Korean government established a long-term space development plan in 1996, which suggests a clear way forward for space development up to 2015. Space activities in Korea will grow continuously. The direction of future space activities will be decided by the national space development plan. This paper discusses Korea''s past and present space activities and future development projects. [Copyright &y& Elsevier]