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The detection of gravitational waves (GWs) from space is a hot topic in astronomy and space science, as the Space Gravitational Wave Observatory can detect low-frequency GWs from various sources. The long-term stability of the configuration of GW observatories is the key to the success of GWs detection, which challenges the configuration design and optimization. This paper innovatively proposes an semi-analytical double-layer iterative optimization algorithm (DLI) to solve the geocentric configuration optimization problem. First, an iterative method with gradient information of breathing angle, which is compensated by its standard deviation, is introduced as the inner iteration layer. Then, the outer iterative layer executes the initial value update process via the selection of the constructed candidates with smallest arm length variation rate, until the maximum breathing angle variation converges to the preset accuracy. The proposed method is applied to optimize the nominal configuration of TianQin mission. The results shows that DLI can reduce about 99% computation duration compared with the numerical optimization method. Furthermore, the influence of initial configuration elements on stability parameters are analyzed, providing better alternation for geocentric GWs detection missions. • A semi-analytical configuration optimization of the GWs observatory is proposed. The efficiency is improved more than 100 times. • The inner iteration is realized with the compensated breathing angles as the gradient. • The effects of orbital elements on the configuration performance are analyzed. [ABSTRACT FROM AUTHOR]

This paper presents a proof-of-concept investigation for demonstrating the feasibility of robotically assembling a space structure from cooperative modular components. The work is motivated by the requirement of in-orbit assembly of large space structures which play an increasingly important role in space engineering and science. The main goal of this paper is three-fold. The first is to design and develop a series of cooperative modular components. The second is to develop an automated assembly strategy to fulfill the assembly task based on visual measurement using an economic camera. The third is to experimentally demonstrate the automated assembly of the modular components into a much larger structure using the proposed assembly strategy and the developed hardware platform. In the demonstration, the robot grasps modular components, manipulates them to target positions with Iterative Learning Control and then assembles them to a central modular component fixed on a rotating platform to form a full structure. The whole assembly process takes about 4 mins and the video showcasing the experiment can be seen at https://youtu.be/OI7aaPwY_qQ. • A series of simplified cooperative modular components are developed. • An automated assembly strategy to fulfill the assembly task is proposed. • An experimental demonstration of the automated assembly strategy is achieved. [ABSTRACT FROM AUTHOR]

There has been a growing interest in spacecraft formation flying for space science applications. Such missions will require an accurate and efficient dynamics model, on-board the flight computer, to calculate and control the desired relative motion. Hence, an analytical dynamics model which can be applied to eccentric orbits and includes perturbations can provide an increase in accuracy and efficiency. This paper develops an accurate analytical solution of relative motion between two spacecraft using classical orbital elements. The analytical solution is obtained by propagating the orbital elements forward in time, while taking into account gravitational field up to the fifth harmonic, third-body and drag secular and periodic perturbations, and calculating the relative motion in the local-vertical–local-horizontal reference frame at each time-step. The analytical solution was observed to accurately describe the relative motion when compared with a numerical simulator, yielding errors on the order of meters for separation distances on the order of hundreds of meters. • Analytical spacecraft relative dynamics • Gravitational, drag, and third-body LuniSolar perturbations • Effects of perturbations on spacecraft relative motion in LEO and HEO • Effects of Long and short periodic variations due to J 2 on spacecraft relative motion [ABSTRACT FROM AUTHOR]

The European Space Agency (ESA) has twenty-two Member States with a variety of governance structures and strategic priorities regarding their space activities. The objective of this paper is to provide an up-to date overview and a holistic assessment of the national space governance structures and strategic priorities of the eleven smaller Member States (based on annual ESA contributions). A link is made between the governance structure and the main strategic objectives. The specific needs and interests of small and new Member States in the frame of European Space Integration are addressed. The first part of the paper focuses on the national space governance structures in the eleven smaller ESA Member States. The governance models of these Member States are identified including the responsible ministries and the entities entrusted with the implementation of space strategy/policy and programmes of the country. The second part of this paper focuses on the content and analysis of the national space strategies and indicates the main priorities and trends in the eleven smaller ESA Member States. The priorities are categorised with regards to technology domains, the role of space in the areas of sustainability and the motivators for space investments. In a third and final part, attention is given to the specific needs and interests of the smaller Member States in the frame of European space integration. ESA instruments are tailored to facilitate the needs and interests of the eleven smaller and/or new Member States. [ABSTRACT FROM AUTHOR]

The field of Space has become very important in the wake of opportunities and strategic advantages accrued from it. It has become increasingly evident that space science education is beginning to gain grounds in the 21st century and it is perceived to bring about Science, Technology, Engineering, Mathematics (STEM) awareness providing a context for teaching and learning of the subject. The competitive nature of Space means developing nations will need to invest in the skills that the industry needs by way of sustained pathways, incentivised research and development, and assured a favourable prevailing business environment by way of creating capacities and capabilities in space sciences. Through an explanatory study, we draw on students' responses (N = 504, interviews = 20) to investigate the educational need of a space science program. Findings revealed implications for the quality and function of a space science program which provide a platform for engagement in space related research and development. Data also demonstrated key facts with the potential of increasing the future of space science instruction which will necessitate a paradigm shift towards the value of space education in the phase of integrating a space science program in the curriculum. The paper concludes with recommendations for practitioners responsible for integration of new curriculum in science education in higher education sectors. • Positive student perceptions towards a space science program. • Space science education influences learners' decision in STEM studies. • Overwhelming student interest for space science curriculum integration. • Space science provides an interdisciplinary avenue for engagement and participation. • Positive mindset breeds right mentality to teaching and learning of the space science. [ABSTRACT FROM AUTHOR]

This paper presents the results of analyses and simulations for the design of a small sounding platform, dedicated to conducting scientific atmospheric research and capable of reaching the von Kármán line by means of a rocket launched from it. While recent private initiatives have opted for the air launch concept to send small payloads to Low Earth Orbit, several historical projects considered the use of balloons as the first stage of orbital and suborbital platforms, known as rockoons. Both of these approaches enable the minimization of drag losses. This paper addresses the issue of utilizing stratospheric balloons as launch platforms to conduct sub-orbital rocket flights. Research and simulations have been conducted to demonstrate these capabilities and feasibility. A small sounding solid propulsion rocket using commercially-off-the-shelf hardware is proposed. Its configuration and design are analyzed with special attention given to the propulsion system and its possible mission-orientated optimization. The cost effectiveness of this approach is discussed. Performance calculation outcomes are shown. Additionally, sensitivity study results for different design parameters are given. Minimum mass rocket configurations for various payload requirements are presented. The ultimate aim is to enhance low-cost experimentation maintaining high mobility of the system and simplicity of operations. An easier and more affordable access to a space-like environment can be achieved with this system, thus allowing for widespread outreach of space science and technology knowledge. This project is based on earlier experience of the authors in LEEM Association of the Technical University of Madrid and the Polish Small Sounding Rocket Program developed at the Institute of Aviation and Warsaw University of Technology in Poland. [ABSTRACT FROM AUTHOR]

The use of Electric Propulsion (EP) on satellites for commercial, defense, and space science missions has been increasing in recent decades, from the first successful operation in 1964 aboard the Zond-2 spacecraft to the present day. This paper provides an overview of the technological and commercial development of EP systems that have been deployed. A review of the early years of EP application ends in 1980, when the first geostationary commercial satellite using EP, Intelsat-V, was launched. Beyond 1980, all EP-based spacecraft deployment data through 2018 are presented, divided by spacecraft type: GEO-synchronous satellite, LEO satellites, deep-space missions and small satellites. To date, a total of 587 spacecraft have been launched with some variant of electric propulsion. During the 1960s and 1970s, all 48 spacecraft using EP were government missions, with the US and USSR leading in the development, production, and flight of these systems. These first platforms included a variety of pulsed plasma thrusters, resistojets, arcjets, ion thrusters and Hall thrusters. The number of GEO satellites with electric propulsion systems has increased significantly since 1981, from an average of less than 5 satellites per year during the 1980s to over 15 in recent years. The corresponding annual fraction of EP based GEO satellite launches, compared to all GEO satellite launches, has increased from 20% during the 1980s to over 40% in recent years. For LEO applications, a gradual increase in the utilization of EP has been realized. Of the 167 EP-based LEO platforms deployed, resistojets were the most prolific legacy thruster type (124 S/C) with Hall thrusters gaining traction in recent years (25 S/C), appearing on 19 of 45 satellite missions in the past decade. Of all EP-based LEO missions, approximately half served as testbeds for new technologies. Through 2018, eight deep space spacecraft with EP have been launched, with the US, Japan, and the European Union leading these efforts. Small satellites are also benefiting from this technology, with 24 EP-based small satellites launched to date. Nearly half of these were launched between 2016 and 2018, demonstrating accelerated growth and a large potential for the future of this spacecraft class. • Overview of all electric propulsion missions, divided into mission classes. • For each mission type statistics are presented on the different thruster subclasses. • Arguments are given for the historical trends of the use of electric propulsion subclasses. • Current trends, for the growth/use of classes of electric propulsion, are analyzed. [ABSTRACT FROM AUTHOR]

Abstract The international Rosetta mission was launched on 2nd March 2004 for a ten year journey to its target destination, comet 67P/Churyumov-Gerasimenko. Following the January 2014 exit from a 31 month hibernation period, Rosetta approached and rendezvoused with the comet in August 2014. On 12th November 2014, the Philae lander was deployed from Rosetta onto the comet's surface after which the Orbiter continued its comet escort phase. The Rosetta Science Ground Segment supports the Project Scientist and the Science Working Team, in order to ensure the coordination, development, validation and delivery of the desired science operations plans and their associated operational products throughout the mission, and to ensure the preservation of adequate data to the Planetary Science Archive. Within the Science Ground Segment, the Operations and Planning Group is responsible for the medium, short and very short term cycles, a stepped sequential process that implements the higher level science long term plan into the final science pointing requests and the command sequences to be executed on board the spacecraft. In this paper we will present the Operations and Planning group and its science planning activities, focusing on the evolution of the Science Operations implementation through the Rosetta mission phases. We will describe the day-to-day work needed to achieve science operations around the challenging and previously unknown cometary environment, and the software tools that support the planning process. We will finally outline several conclusions after the experience gained in the ∼2 years of operations at the comet. Highlights • Space science operations discipline combines scientific and engineering knowledge. • Rosetta successfully returned unique science results in its two years at comet 67P. • Rosetta changed from a rigid long-lead concept to a close-to-execution agile planning. • Rosetta integrated new planning rules in the harsh fickle comet environment. • It is remarkable how fast planning was adapted while performing comet observations. [ABSTRACT FROM AUTHOR]

This paper reports findings of the International Academy of Astronautics (IAA) Study Group (SG), International Cooperation for Space Life Sciences Knowledge Sharing and Development in Africa, (2013). The SG, established in 2010, is comprised of space life sciences experts from across the globe. It charged with developing a cooperative global strategy to generate partnerships for space workforce development and life sciences knowledge sharing among space-faring and space-aspiring African nations. The study group׳s findings emphasize the need for cultural competencies and cooperation. In recent years, Africa׳s spending on space science has increased as national governments have defined their space aspirations and goals within the context of “space for humanity” and global workforce development. Some African countries have developed their own space agencies with well-defined policies and objectives. Space workforce development efforts among these countries focus on satellite technology and ground station operation, astronomy/space science and investment in related activities that advance their specific space exploration/utilization aspirations (e.g., communication services; satellite data collection and processing, with applications in areas such as food security, health and education, crime control, environmental and disaster management, and urban sprawl; radio telescope technology; and space science education outreach and awareness). The IAA study also examines the implications of increased international governmental/non-governmental educational partnerships for workforce development and proposes a roadmap for Africa׳s space-emerging countries seeking to establish global partnerships to develop indigenous space workforces. The study concludes that there are many platforms available to promote inter-regional cooperation on space workforce development, particularly in the areas of space science and technology. This paper calibrates the IAA study group׳s report with the IAA׳s report, Future Human Spaceflight: the Need for International Cooperation (2010), which outlines common global interests for human space exploration and supports the outcomes of three African IAA regional conferences on “Space for Africa.” [ABSTRACT FROM AUTHOR]

Celestial bodies like the Moon and asteroids contain materials and precious metals, which are valuable for human activity on Earth and beyond. Space mining has been mainly relegated to the realm of science fiction, and was not treated seriously by the international community. The private industry is starting to assemble towards space mining, and success on this front would have major impact on all nations. We present in this paper a review of current space mining ventures, and the international legislation, which could stand in their way - or aid them in their mission. Following that, we present the results of a role-playing simulation in which the role of several important nations was played by students of international relations. The results of the simulation are used as a basis for forecasting the potential initial responses of the nations of the world to a successful space mining operation in the future. [ABSTRACT FROM AUTHOR]

The United Nations Office for Outer Space Affairs (UNOOSA) has the mandate to assist Member States with building capacity in using space science, technology and their applications in support of sustainable economic, social and environmental development. From 20 to 21 June 2018 the international community will gather in Vienna for UNISPACE + 50, a special segment of the 61st session of the Committee on the Peaceful Uses of Outer Space (COPUOS), to celebrate the 50th anniversary of the first UNISPACE conference and to reach consensus on a global space agenda for the next two decades. “Capacity-building for the twenty-first century” is one of the seven thematic priorities of UNISPACE + 50, identified and agreed upon by COPUOS. The Committee has tasked UNOOSA with undertaking the work under this thematic priority and with reporting regularly to the Committee and its Subcommittees on the progress of its work. It is therefore appropriate, in this context, to take stock of the achievements of the capacity-building activities of the Office, to review the relevant mandates and activities and to consider the necessity to strengthen and better align them with the future needs of the World and in particular with the 2030 Agenda for Sustainable Development. This paper describes the efforts on-going at UNOOSA, building on its experiences with implementing the United Nations Programme on Space Applications and the United Nations Platform for Space-based Information for Disaster Management and Emergency Response (UN-SPIDER) and working with Member States and other United Nations entities, to develop a results-based management approach, based on an indicator framework and a database with space solutions, for promoting the use of space-based solutions to help Member States achieve the Sustainable Development Goals (SDGs) and successfully implement the 2030 Agenda for Sustainable Development. [ABSTRACT FROM AUTHOR]

A comprehensive tour of the complex outer planet systems is a central goal in space science. However, orbiting multiple moons of the same planet would be extremely prohibitive using traditional propulsion and power technologies. In this paper, a new mission concept, named Magnetour, is presented to facilitate the exploration of outer planet systems and address both power and propulsion challenges. This approach would enable a single spacecraft to orbit and travel between multiple moons of an outer planet, without significant propellant or onboard power source. To achieve this free-lunch ‘Grand Tour’, Magnetour exploits the unexplored combination of magnetic and multi-body gravitational fields of planetary systems, with a unique focus on using a bare electrodynamic tether for power and propulsion. Preliminary results indicate that the Magnetour concept is sound and is potentially highly promising at Jupiter. [ABSTRACT FROM AUTHOR]

Abstract: As part of the European Space Situational Awareness programme, ESA uses its 1-m telescope on Tenerife regularly for asteroid observations since 2009. The focus of the work is follow-up observations. In addition, dedicated timeslots are used for survey observations. This paper summarizes the results of the asteroid observations in the year 2010 and provides detailed information on the methodology used for follow-up and survey. In the main part of the paper, lessons-learnt are presented. [Copyright &y& Elsevier]

Drag-free flight has played a more and more important role in many space missions. The thrust control system is the key unit to achieve drag-free flight by providing a precise compensation for the disturbing force except gravity. The cusped field thruster has shown a significant potential to be capable of the function due to its long life, high efficiency, and simplicity. This paper demonstrates a cusped field thruster's feasibility in drag-free flight based on its instinctive characteristics and describes a detailed design of a cusped field thruster made by Harbin Institute of Technology (HIT). Furthermore, the performance test is conducted, which shows that the cusped field thruster can achieve a continuously variable thrust from 1 to 20 mN with a low noise and high resolution below 650 W, and the specific impulse can achieve 1800 s under a thrust of 18 mN and discharge voltage of 1000 V. The thruster's overall performance indicates that the cusped field thruster is quite capable of achieving drag-free flight. With the further optimization, the cusped field thruster will exhibit a more extensive application value. [ABSTRACT FROM AUTHOR]

Abstract: In less than a decade, Cubesats have evolved from purely educational tools to a standard platform for technology demonstration and scientific instrumentation. The use of COTS (Commercial-Off-The-Shelf) components and the ongoing miniaturization of several technologies have already led to scattered instances of missions with promising scientific value. Furthermore, advantages in terms of development cost and development time with respect to larger satellites, as well as the possibility of launching several dozens of Cubesats with a single rocket launch, have brought forth the potential for radically new mission architectures consisting of very large constellations or clusters of Cubesats. These architectures promise to combine the temporal resolution of GEO missions with the spatial resolution of LEO missions, thus breaking a traditional trade-off in Earth observation mission design. This paper assesses the current capabilities of Cubesats with respect to potential employment in Earth observation missions. A thorough review of Cubesat bus technology capabilities is performed, identifying potential limitations and their implications on 17 different Earth observation payload technologies. These results are matched to an exhaustive review of scientific requirements in the field of Earth observation, assessing the possibilities of Cubesats to cope with the requirements set for each one of 21 measurement categories. Based on this review, several Earth observation measurements are identified that can potentially be compatible with the current state-of-the-art of Cubesat technology although some of them have actually never been addressed by any Cubesat mission. Simultaneously, other measurements are identified which are unlikely to be performed by Cubesats in the next few years due to insuperable constraints. Ultimately, this paper is intended to supply a box of ideas for universities to design future Cubesat missions with high scientific payoff. [Copyright &y& Elsevier]

Abstract: At the 59th IAC in Glasgow, a paper was presented describing two studies being carried out by Commission VI of the International Academy of Astronautics on the impact of space activities upon society. One of these studies sought to discover the hopes, aspirations and expectations of those outside the space field – the person in the street – regarding space activities. The paper reviewed the thought processes and decisions leading up to the commencement of the survey, documented the reasoning behind the questions which the public were; described the efforts to translate the questionnaire into the six Unesco languages to achieve wider participation, and provided an overview of results to date. This present paper provides an update on this Space Expectations survey as the study comes to a close. The paper briefly discusses the addition of new languages for the questionnaire and the drive to make the survey better known and encourage participation worldwide, before going on to provide a detailed analysis of the latest results of opinions. Insights include respondent’s thoughts regarding the visions and costs of space activities, how much people feel part of them and whether and how they would like to be more involved. [ABSTRACT FROM AUTHOR]

Abstract: This paper describes results of the calibration of the miniature thermal emission spectrometer (Mini-TES) being built by Raytheon Santa Barbara Remote Sensing (SBRS) under contract to Arizona State University (ASU). This paper also serves as an update to an earlier paper [R.J. Peralta, S. Silverman, D. Bates, Raytheon/Santa Barbara Remote Sensing, P. Christensen, G. Mehall, T. Tourville, R. Keehn, G. Cannon, Arizona State University, Miniature thermal emission spectrometer for the Mars Exploration Rover, Proceedings of the SPIE, vol. 4485-09, August 2001] for mission description and instrument design. Mini-TES is a single detector Fourier transform spectrometer (FTS), covering the spectral range at spectral resolution. Launched in June 2003, one Mini-TES instrument will fly to Mars aboard each of the two missions of NASA''s Mars Exploration Rover Project (MER), named Spirit and Opportunity. Mini-TES is designed to provide a key minerological remote sensing component of the MER mission, which includes several other science instruments. The first Mini-TES unit was required to meet a two-year development schedule with proven, flight-tested instrumentation. Therefore, SBRS designed Mini-TES based on proven heritage from the successful Mars Global Surveyor (MGS) thermal emission spectrometer (TES), which was launched in 1996 and is still operational with over 500 million spectra collected to date. Mini-TES design, performance, integration onto the rovers, as well as details of the calibration are discussed. Full instrument and calibration details are the subject of an upcoming Journal of Geophysical Research Mini-TES paper by Christensen, et al. [Copyright &y& Elsevier]

Abstract: This paper presents several analog and mixed signal VLSI chips that have been successfully developed over the past several years at JHU/APL for space science missions. The chips have applications for spacecraft avionics and several types of instrumentation. The family of the chips include: the TRIO smart sensor multiplexed ADC chip for spacecraft/instrument avionics, the time-of-flight (TOF) chip for precise time interval measurement, the CFD chip for time discrimination, the energy chip for low-noise particle/photon measurement, a commandable discriminator pulse high analyzer, event accumulator, a radiation hardened voltage reference, an ADC and other. This paper addresses some design, radiation hard by design, design for testability, testing, and space qualification issues. The paper also briefly describes the spacecraft and instrument applications of these chips including: the NASA missions CASSINI, IMAGE, CONTOUR, MESSENGER, STEREO, PLUTO, oncoming funded missions MMS, JUNO, RBSP, as well as planned planetary and moon missions. [Copyright &y& Elsevier]

Abstract: The purpose of this paper is to present an engineering assessment of a proposal for a deployment brake for a momentum exchange tether. Tethers have attracted considerable interest amongst the propulsion community for many years for orbit raising, energy conversion, de-orbiting, and injection into interplanetary transfers, and the motivation for the work described in the paper is directly mission-oriented. The YES2 SpaceMail mission has been planned as a low-cost international effort to provide a facility for the return of small samples from the ISS back to Earth, based on an inflatable re-entry capsule and a mechanical tether system. The system will be lofted into orbit as part of a payload on a Foton/Bion rocket launcher. The brake design concept is based on the use of friction between the deploying tether and a short pole onto which several turns are wound, and the paper summarises the modelling work that has been done, and then discusses an experiment in which the premise was tested in the laboratory. The paper concludes with certain practical proposals for implementation. [Copyright &y& Elsevier]

Abstract: This paper presents the experience gained at the Integration and Tests Laboratory—LIT, National Institute for Space Research—INPE, in São José dos Campos, SP, from the thermal vacuum tests campaign of the SATEC protoflight spacecraft, held from February 6th to 12th, 2003. The Satélite Tecnológico (SATEC) is a micro-satellite made in Brazil, as a payload for the Brazilian launching vehicle VLS-1.3, scheduled to be launched in the year of 2003. 1 [1] SATEC was lost when the VLS-1 pre-ignited on pad during final launching procedures on 2003 August 22nd. Considering the small size, relatively small cost and limited responsibility of this particular micro-satellite, the environmental tests should be performed in a short period of time requiring as low cost as possible, albeit being reliable, comprehensive and representative. For the thermal vacuum tests basically it was used a medium-size space simulation chamber, complemented by the use of the technique of thermal radiant heat plates for simulation of the heat input from the orbital thermal conditioning. This paper details the infrared testing technique applied to the acceptance tests of the Brazilian micro-satellite, including the adopted test setup, the thermal vacuum chamber mode-of-operation and performance, the precise thermal conditioning and controlling of the radiative heat plates, and the results obtained in terms of spacecraft temperatures. [Copyright &y& Elsevier]

Abstract: NASA is currently studying the possibility of establishing future space bases at either of the libration points (also called Lagrangian points) L1 and L2 of the Earth–Moon system. Two more similar points L1 and L2 of the Sun–Earth system are also under consideration. Such possible future space bases are called Gateways in the NASA jargon. Each Gateway has its own pros and cons in terms of gravitational pull, distance from the Earth, and targets attainable by future spacecraft departing from the Gateway. A preliminary, concise review of these alternative possibilities is presented in this paper. We claim, however, that an extra factor has to be included in the NASA scenario also. This is the Radio-Quiet Moon Farside Imperative, called simply the Farside Imperative hereafter. This imperative is the need to keep at least the central part of the Farside of the Moon free from Radio Frequency Interference (RFI) coming from the Earth and shielded by the Moon''s spherical body. In fact, the Farside of the Moon, and the Quiet Cone that extends into space above it for a few thousands of kilometers, represent a unique outpost for humankind: they are the only place close to the Earth where all radio-garbage produced by modern human civilization cannot reach. Thus, an array of radio antennas located there would sense the rest of the universe to an unprecedented degree of radio cleanliness, and, hence, of radio details. Not only would astrophysics and radio astronomy in general greatly benefit from this radio-quiet environment, but we would possibly achieve there for the first time a neat radio contact with an extraterrestrial civilization harboring somewhere else in the Galaxy (SETI) that could be too noisy to be detected on Earth. It is thus felt that a fair balance has to be reached between the astronautical drive to enlarge the exploration of the solar system and the imperative to keep the Farside of the Moon radio-clean. This paper puts forward a set of constructing proposals in this direction. [Copyright &y& Elsevier]

This paper proposes an approach for a complex and innovative project requiring international contributions from different communities of knowledge and expertise. Designing a safe and reliable architecture for a manned mission to Mars or the Asteroids necessitates strong cooperation during the early stages of design to prevent and reduce risks for the astronauts at each step of the mission. The stake during design is to deal with the contradictions, antagonisms and paradoxes of the involved partners for the definition and modeling of a shared project of reference. As we see in our research which analyses the cognitive and social aspects of technological risks in major accidents, in such a project, the complexity of the global organization (during design and use) and the integration of a wide and varie d range of sciences and innovative technologies is likely to increase systemic risks as follows: human and cultural mistakes, potential defaults, failures and accidents. We identify as the main danger antiquated centralized models of organization and the operational limits of interdisciplinarity in the sciences. Beyond this, we can see that we need to take carefully into account human cooperation and the quality of relations between heterogeneous partners. Designing an open, self-learning and reliable exploration system able to self-adapt in dangerous and unforeseen situations implies a collective networked intelligence led by a safe process that organizes interaction between the actors and the aims of the project. Our work, supported by the CNES (French Space Agency), proposes an innovative approach to the coordination of a complex project. [ABSTRACT FROM AUTHOR]

Europe is present in robotic exploration though the European Space Agency׳s mandatory space science program and the optional Aurora program. In addition some member states are also involved in projects of non-European space faring countries through bilateral co-operations. Europe is also present in human exploration through the ISS utilization program. ESA and some of its member states participate in the activities of the International Space Exploration Coordination Group (ISECG), a club of 14 space agencies working for the elaboration of a global exploration roadmap. Finally, ESA and the European Union have initiated a political approach with the setting up of an international forum so as to elaborate a commonly agreed vision on space exploration at political level. However the role of Europe in such a global strategy is not well defined yet; Europe has to build its own vision and to precise the role it intends to play in a future global space exploration venture. We try in this paper to sketch what could be such a European vision, taking into account the European capabilities and priorities, and also the foreseeable economic situation. With limited resources, Europe cannot be present everywhere. In the field of robotic exploration Europe has the capabilities to implement first class projects where it is the major partner. In the field of human exploration, Europe needs to join a co-operation where it has to accept to be a minor partner while its contributions should benefit from the legacy of the previous European achievements The role of the EU, as a political entity, can be determinant; the high level political forum initiated by ESA and EU can be the nucleus of a global strategy. Also the space part of the new UE R&D program Horizon 2020 can support the European effort by focusing on the technological activities which have been highlighted as key areas for exploration and which may yield applications for the citizen. A key role for EU could be to foster the technology transfers in either way between space and non-space utilizations. [ABSTRACT FROM AUTHOR]

The present paper is concerned with the search for orbits that have potential to require low fuel consumption for station-keeping maneuvers for constellations of satellites. The method used to study this problem is based on the integral over the time of the undesired perturbing forces. This integral measures the change of velocity caused by the perturbation forces acting on the satellite, so mapping orbits that are less perturbed, which generates good candidates for orbits that requires low fuel consumption for station-keeping maneuvers. The integral over the time depends only on the orbit of the spacecraft and the dynamical system considered. The type of engine and the control technique applied to the spacecraft are not considered to search for those orbits. It can be a good strategy to be applied for a first mapping of orbits. For this search, it is analyzed the integral of orbits with different values of the Keplerian elements in order to find the best ones with respect to this criterion. The perturbations considered are the ones caused by the third body, which includes the Sun and the Moon, and the J 2 term of the geopotential. The results presented here show numerical simulations to obtain the integral of those perturbing forces for different orbits. The GPS and the Molniya constellations are used as examples for those calculations. [ABSTRACT FROM AUTHOR]

Underactuated attitude control is supposed to be used on spacecraft when failure happens with onboard actuators. One main problem with existing underactuated attitude control designs is their limited capabilities against disturbances. In order to solve this problem, an approach based on the theory of H ∞ is proposed in this paper. Two propositions are derived from the H ∞ theory to improve the robustness of one popular underactuated attitude control design, which was presented by Tsiotras et al. It is proved mathematically that the controller satisfying these two propositions respectively can stabilize the underactuated attitude system locally or globally. The numerical simulations show that the improved controllers based on the H ∞ theory could provide higher pointing accuracy for small satellites against disturbances. This validates the effectiveness of the proposed H ∞ based approach to improve existing underactuated attitude control designs. [ABSTRACT FROM AUTHOR]

In May 2007, what was then the Space Life Sciences Directorate published the 2007 Space Life Sciences Strategy for Human Space Exploration, setting the course for development and implementation of new business models and significant advances in external collaboration over the next five years. The strategy was updated on the basis of these accomplishments and reissued as the NASA Human Health and Performance Strategy in 2012, and continues to drive new approaches to innovation for the directorate. This short paper describes the successful execution of the strategy, driving organizational change through open innovation efforts and collaborative projects, including efforts of the NASA Human Health and Performance Center (NHHPC). [ABSTRACT FROM AUTHOR]

Abstract: This paper presents a new method for rapid transfer alignment of strapdown inertial navigation system (SINS) by combining the local observability concept with robust adaptive filtering. The system state and observation models are simplified to analyze the observability of the SINS attitude error. Based on the simplified models, the observability matrix and its condition number are constructed to determine the observability degree of SINS during the process of rapid transfer alignment. On the basis of the local obsersability analysis, a robust adaptive filter is developed to estimate the attitude angle error for SINS rapid transfer alignment. Simulation experiments and comparison analysis have been conducted, demonstrating that the proposed method cannot only effectively measure the local observability of SINS, but it can also enhance the performance of SINS rapid transfer alignment and reduce the alignment time. [Copyright &y& Elsevier]

Abstract: Recent studies by the US National Research Council identify nuclear explosives as the only current technology able to deflect large asteroids (those exceeding 500m in diameter) or to mitigate impacts of smaller bodies when the warning time is short. Previous work predicts that either a standoff burst or a very low-yield surface burst is easily capable of deflecting a large (1km) asteroid without fragmentation. Alternatively, large near-surface or just sub-surface bursts can sufficiently disrupt and disperse smaller bodies (300m) to ensure that large fractions (in excess of 99.99%) miss the Earth entirely. Even for very short warning times (less than a month), more than 99.5% of a body′s mass can be deflected off of an Earth-bound trajectory. However, successfully deflecting a small body, while avoiding fragmentation, becomes a challenging problem when the required kinetic energy increment is a substantial fraction of the body′s potential. This paper addresses the challenge of preventing the production of substantial low-speed debris while deflecting small bodies with an impulsive method. [Copyright &y& Elsevier]

Abstract: Although discussions are underway within the Action Team 14 of the United Nations COPUOS, there is currently no concerted international plan addressing the impact threat from near-Earth objects (NEOs) and how to organize, prepare and implement mitigation measures. We report on a new international project to address impact hazard mitigation issues, being the subject of a proposal submitted to the European Commission in response to the 2011 FP7 Call “Prevention of impacts from near-Earth objects on our planet”. Our consortium consists of 13 research institutes, universities, and industrial partners from 6 countries and includes leading US and Russian space organizations. The primary aim of the project, NEOShield, is to investigate in detail the three most promising mitigation techniques: the kinetic impactor, blast deflection, and the gravity tractor, and devise feasible demonstration missions. Furthermore, we will investigate options for an international strategy for implementation when an actual impact threat arises. The NEOShield project was formally accepted by the European Commission on 17 November 2011 and funded with a total of 5.8 million Euros for a period of 3.5 years. The kick-off meeting took place at the DLR Institute of Planetary Research, Berlin, in January 2012. In this paper we present a brief overview of the planned scope of the project. [Copyright &y& Elsevier]

Abstract: Design and analysis of a 2028–2029 human-piloted exploration mission to asteroid 99942 Apophis is studied in this paper. A fictional scenario is also examined in which Apophis is assumed to have passed through a keyhole in 2029, resulting in an Earth impact in 2036, is also examined. Several mission architectures are developed and analyzed for such a fictional scenario. Although Apophis currently has a very low impact probability estimated of approximately four-in-a-million, it is one of the most likely to impact the Earth, warranting further examination. Both human-piloted and robotic exploration missions are designed for missions prior to and after the April 13, 2029 Earth-Apophis close encounter. [Copyright &y& Elsevier]

Abstract: The Search for Extraterrestrial Intelligence (SETI) has a low probability of success, but it would have a high impact if successful. Therefore it makes sense to widen the search as much as possible within the confines of the modest budget and limited resources currently available. To date, SETI has been dominated by the paradigm of seeking deliberately beamed radio messages. However, indirect evidence for extraterrestrial intelligence could come from any incontrovertible signatures of non-human technology. Existing searchable databases from astronomy, biology, earth and planetary sciences all offer low-cost opportunities to seek a footprint of extraterrestrial technology. In this paper we take as a case study one particular new and rapidly-expanding database: the photographic mapping of the Moon's surface by the Lunar Reconnaissance Orbiter (LRO) to 0.5m resolution. Although there is only a tiny probability that alien technology would have left traces on the moon in the form of an artifact or surface modification of lunar features, this location has the virtue of being close, and of preserving traces for an immense duration. Systematic scrutiny of the LRO photographic images is being routinely conducted anyway for planetary science purposes, and this program could readily be expanded and outsourced at little extra cost to accommodate SETI goals, after the fashion of the SETI@home and Galaxy Zoo projects. [Copyright &y& Elsevier]

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 describes the design and the manufacturing of a Cubesat platform based on a plastic structure. The Cubesat structure has been realized in plastic material (ABS) using a “rapid prototyping” technique. The “rapid prototyping” technique has several advantages including fast implementation, accuracy in manufacturing small parts and low cost. Moreover, concerning the construction of a small satellite, this technique is very useful thanks to the accuracy achievable in details, which are sometimes difficult and expensive to realize with the use of tools machine. The structure must be able to withstand the launch loads. For this reason, several simulations using an FEM simulation and an intensive vibration test campaign have been performed in the system development and test phase. To demonstrate that this structure is suitable for hosting a complete satellite system, offering innovative integrated solutions, other subsystems have been developed and assembled. Despite its small size, this single unit (1U) Cubesat has a system for active attitude control, a redundant telecommunication system, a payload camera and a photovoltaic system based on high efficiency solar cells. The developed communication subsystem has small dimensions, low power consumption and low cost. An example of the innovations introduced is the antenna system, which has been manufactured inside the ABS structure. The communication protocol which has been implemented, the AX.25 protocol, is mainly used by radio amateurs. The communication system has the capability to transmit both telemetry and data from the payload, in this case a microcamera. The attitude control subsystem is based on an active magnetic system with magnetorquers for detumbling and momentum dumping and three reaction wheels for fine control. It has a total dimension of about 50×50×50mm. A microcontroller implements the detumbling control law autonomously taking data from integrated magnetometers and executes pointing maneuvers on the basis of commands received in real time from ground. The subsystems developed for this Cubesat have also been designed to be scaled up for larger satellites such as 2U or 3U Cubesats. The additional volume can be used for more complex payloads. Thus the satellite can be used as a low cost platform for companies, institutions or universities to test components in space. [Copyright &y& Elsevier]

Abstract: Bi-directional ground-to-satellite laser communication experiments were successfully performed between the optical ground station developed by the National Institute of Information and Communications Technology (NICT), located in Koganei City in suburban Tokyo, and a low earth orbit (LEO) satellite, the “Kirari” Optical Inter-orbit Communications Engineering Test Satellite (OICETS). The experiments were conducted in cooperation with the Japan Aerospace Exploration Agency (JAXA), and called the Kirari Optical communication Demonstration Experiments with the NICT optical ground station (or KODEN). The ground-to-OICETS laser communication experiment was the first in-orbit demonstration involving the LEO satellite. The laser communication experiment was conducted since March 2006. The polarization characteristics of an artificial laser source in space, such as Stokes parameters, and the degree of polarization were measured through space-to-ground atmospheric transmission paths, which results contribute to the link estimation for quantum key distribution via space and provide the potential for enhancements in quantum cryptography on a global scale in the future. The Phase-5 experiment, international laser communications experiments were also successfully conducted with four optical ground stations located in the United States, Spain, Germany, and Japan from April 2009 to September 2009. The purpose of the Phase-5 experiment was to establish OICETS-to-ground laser communication links from the different optical ground stations and the statistical analyses such as the normalized power, scintillation index, probability density function, auto-covariance function, and power spectral density were performed. Thus the applicability of the satellite laser communications was demonstrated, aiming not only for geostationary earth orbit-LEO links but also for ground-to-LEO optical links. This paper presents the results of the KODEN experiments and mainly introduces the common analyses among the different optical ground stations. [Copyright &y& Elsevier]

Abstract: The global financial crisis of 2008 has created an economic environment unfavourable to public and corporate economic activity alike, which could not have left space activities unaffected. However, the effects of the crisis upon the space sector have been so far less damaging than anticipated. The following paper presents recent developments in the field of space policies, institutional budgets and commercial activity worldwide, in an effort to improve the understanding of the new trends in commercial and public space activities. It particularly explores the strategies followed by space stakeholders in different countries and regions in order to pursue their planned space programmes in view of difficult financial conditions. Finally, it highlights the differences in the outlook of space activities between established and emerging space-faring nations and attempts to explore their medium-term consequences on an international level. For this purpose, it was based on research conducted in the framework of a recent ESPI report on “Space Policies, Issues and trends in 2009/2010”. [Copyright &y& Elsevier]

Abstract: With a growing interest for rocket technology and space travel after WW II a number of new “space societies” were formed in the period 1948–1951 in addition to the ones already existing in Germany, the UK and the US since before WW II. Soon came the need for a common international platform for exchange of information and experience, and the concept of an international federation of astronautical societies emerged. Sweden was one of the 8 countries to sign the original declaration to create an International Astronautical Federation on October 2, 1950 in Paris at the 1st International Astronautical Congress. The Swedish Society for Space Research (Svenska Sällskapet för Rymdforskning) was formed a few days after the historical event in Paris. The name was soon to be changed to the Swedish Interplanetary Society (Svenska Interplanetariska Sällskapet, SIS). Sweden was one of the 10 countries to sign the IAF foundation in 1951 in London and in the following year the first Constitution of IAF in Stuttgart. The SIS quickly grow to a membership of several hundred persons and its membership in IAF promoted an intensive exchange of journals, and the annual participation at the IAC gave growth to start study projects on spacecraft and sounding rockets, and the publication of astronautical journals in Swedish. In 1957 the first Swede was elected vice-president of IAF. Not too long after the IAF foundation the idea of an international body of distinguished individuals emerged, in addition to the body of "member societies" (IAF). Upon the initiative of Theodor von Karman, Eugen Sänger and Andrew Haley the IAF council approval of an International Academy of Astronautical was given on August 15, 1960 during the 11th IAC in Stockholm. This IAC in Stockholm gave a large publicity to space research and astronautics in Sweden, and put the activities of the SIS in the focus of the general public. This paper presents the Swedish involvement in the foundation of IAF and IAA. It also gives an overview on the positive influence of these two organisations on the work and progress of the Swedish Interplanetary Society and the diffusion of astronautics to the general public in Sweden. [Copyright &y& Elsevier]

Abstract: While humanity has not yet observed any extraterrestrial intelligence (ETI), contact with ETI remains possible. Contact could occur through a broad range of scenarios that have varying consequences for humanity. However, many discussions of this question assume that contact will follow a particular scenario that derives from the hopes and fears of the author. In this paper, we analyze a broad range of contact scenarios in terms of whether contact with ETI would benefit or harm humanity. This type of broad analysis can help us prepare for actual contact with ETI even if the details of contact do not fully resemble any specific scenario. [Copyright &y& Elsevier]

Abstract: Tethered Satellite System has turned into a reality from theory, and has become a new research focus in the field of space science. However, the system’s stability will directly affect the success of the mission. In this paper, the system''s stability is deeply studied. First, the system’s equilibrium conditions are derived according to the system''s dynamics model, and the maximum extent that these conditions can be reached is determined. Second, the stability of the system equilibrium state is analyzed by utilizing Taylor expansion formula and stability criterion, and the required conditions that the tether parameters should be satisfied during a stable equilibrium state are also deduced. Finally, based on the stability of studied above, a range-rate control algorithm is developed to achieve the stable control of tether''s deploying, keeping, and retrieving. Simulation results verify the validity of these conclusions, which provide a good reference for future experiments of Tethered Satellite System. [Copyright &y& Elsevier]

Abstract: A prerequisite to accomplish a system simulation is to have a system model holding all necessary project information in a centralized repository that can be accessed and edited by all parties involved. At the Institute of Astronautics of the Technische Universitaet Muenchen a modular approach for modeling and dynamic simulation of satellite systems has been developed called dynamic system simulation (DySyS). DySyS is based on the platform independent description language SysML to model a small satellite project with respect to the system composition and dynamic behavior. A library of specific building blocks and possible relations between these blocks have been developed. From this library a system model of the satellite of interest can be created. A mapping into a C++ simulation allows the creation of an executable system model with which simulations are performed to observe the dynamic behavior of the satellite. In this paper DySyS is used to model and simulate the dynamic behavior of small satellites, because small satellite projects can act as a precursor to demonstrate the feasibility of a system model since they are less complex compared to a large scale satellite project. [ABSTRACT FROM AUTHOR]

Abstract: Space agencies such as NASA and ESA have ambitious long-term programmes that mark the beginning of a new era in space exploration where humans will land on Mars; an era requiring public support and, therefore, more consideration for public opinion. Empirical research shows that there are substantial differences in the level of understanding of space exploration among the general public. Studying audiences appears to be crucial to inform public engagement and communication strategies as well as policy debate. This paper presents the results of a survey conducted in the UK in 2008 at two science outreach events, the Royal Society Exhibition in London and the National Space Centre in Leicester, to investigate the motivations, beliefs, political preferences and attitudes towards space exploration of this audience. A sample of 744 respondents was collected. The analysis shows that the British public who come to outreach and engagement activities support space exploration but have some reservations about considering the advancement of UK space activities to be of national interest. Yet, when asked about means of exploring space, the majority agrees that space should be explored using both mankind and machines, ranking “generating new scientific knowledge and advancing human culture” as the most important reason for continuing investment in space research. Although the greater number of supporters says that more than the current government funding should be allocated to civil space activities, concerns about risk and value appear to influence this view. [ABSTRACT FROM AUTHOR]

Abstract: In over 50 years the United Kingdom has designed, built, launched, operated or otherwise contributed to hundreds of spacecraft and space missions. Its scientists, engineers and officials have carved centres of astronautical excellence around the country, participated in a great number of international space programmes and missions and played a leading role in the establishment of the world''s main pan-national space agency (ESA) and its two precursors, the European Launcher Development Organisation (ELDO) and the European Space Research Organization (ESRO). With its Skylark sounding rocket launch of November 1957 the UK was one of the first nations to gather new scientific data as part of the International Geophysical Year. Fifty years on, the UK is an enthusiastic supporter of the Global Exploration Strategy with major commitments to future missions to the moon and to the Mars that exploit the nation''s expertise in small satellite and planetary robot technology. And while such mission involvement takes UK space technologies out into the solar system as never before the nation continues to excel in Earth orbit with its development and manufacture of large, increasingly powerful telecommunications satellites. The UK''s space heritage and its ongoing and directed activities are rich and productive. And yet—the representation of UK space endeavour is all too often skewed—misleading and unduly pejorative: ‘…British space…more romance than reality.’ 1 [1] In Praise of…the British Space Programme, The Guardian Newspaper, March 4th, 2008. Why does such partisan commentary occur and why has such an attitude prevailed for so long? This paper seeks some answers by reviewing UK space activity and its historiography in the wider and global context of astronautics between 1957 and 2007. [Copyright &y& Elsevier]

Abstract: Introduction: NASA has played an influential role in bringing the enthusiasm of space science to schools across the United States since the 1980s. The evolution of this public outreach has led to a variety of NASA funded education programs designed to promote student interest in science, technology, engineering, math, and geography (STEM-G) careers. Purpose: This paper investigates the educational outreach initiatives, structure, and impact of two of NASA''s largest educational programs: the NASA Explorer School (NES) and NASA Spaceward Bound programs. Results: Since its induction in 2003 the NES program has networked and provided resources to over 300 schools across the United States. Future directions include further development of mentor schools for each new NES school selected, while also developing a longitudinal student tracking system for NES students to monitor their future involvement in STEM-G careers. The Spaceward Bound program, now in its third year of teacher outreach, is looking to further expand its teacher network and scientific collaboration efforts, while building on its teacher mentorship framework. [Copyright &y& Elsevier]

Abstract: Russia is a strategic partner for Europe, in particular in its space endeavour. However, in the past decade the Russian partner has significantly changed. Strengthened by a better economic situation, Russia is now reasserting strong ambitions, and its leadership aims to reaffirm the country''s position on the international scene. As a result, Russia''s international partnerships in the space field have evolved and the country has recently intensified relationships with China and India. This development has the potential to strongly impact Europe, its space activities and the relations between all those actors. This paper investigates the relations between Russia, India and China, their possible evolution and the consequences for Europe. It evaluates the potential impact on Europe''s space activities and on its cooperation with the Russian partner. It concludes with recommended actions to be taken by European decision-makers in order to maximise opportunities and minimise risks in this changing environment. [Copyright &y& Elsevier]

Abstract: The paper presents analysis of usefulness of space applications in crisis management activities carried out on the national level. Analytical approach has been based upon development of realistic disaster scenarios and their evaluation with assumption of existence of space-related capabilities available to rescue forces. Building upon analysis''s results, the experimental information environment has been developed and it successfully supported commanding of a large-scale crisis management field training. The results prove that many crisis management needs can be served with existing, commercially available products. The key to success lays in understanding operational needs; integration into common information environment; and standardisation of information exchange. [Copyright &y& Elsevier]

Abstract: Several on-going studies indicate the interest for large, light orbiting structures, shaped as fish nets or webs: along the ropes of the web small spacecraft can move like spiders to position and re-locate, at will, pieces of hardware devoted to specific missions. The concept could be considered as an intermediate solution between the large monolithic structure, heavy and expensive to realize, but easy to control, and the formations of satellites, where all system members are completely free and should manoeuvre in order to acquire a desired configuration. Instead, the advantage of having a “hard-but-light” link among the different grids lays in the partition of the tasks among system components and in a possible overall reduction of the control system complexity and cost. Unfortunately, there is no stable configuration for an orbiting, two-dimensional web made by light, flexible tethers which cannot support compression forces. A possible solution is to make use of centrifugal forces to pull the net, with a reduced number of simple thrusters located at the tips of the tethers to initially acquire the required spin. In this paper a dynamic analysis of a simplified rotating web is performed, in order to evaluate the spinning velocity able to satisfy the requirement for the stability of the system. The model adopted overlaps simpler elements, each of them given by a tether (made up of a number of linear finite elements) connecting two extreme bodies accommodating the spinning thrusters. The combination of these “diameter-like” elements provides the web, shaped according to the specific requirements. The net is primarily considered as subjected to Keplerian attraction and J2 and drag perturbations only, but its behaviour under thermal inputs is also investigated. [Copyright &y& Elsevier]

Abstract: Since the number of satellites in Earth orbit is steadily increasing, space debris will eventually pose a serious problem to near-Earth space activities if left unchecked, and so effective measures to mitigate it are becoming urgent. Equipping new satellites with an end-of-life de-orbit or orbital lifetime reduction capability could be an effective means of reducing the amount of debris by reducing the probability of the collisions between objects. On the other hand, the active removal of space debris and the retrieval of failed satellites by spacecraft are other possible measures. The Institute of Aerospace Technology, Japan Aerospace Exploration Agency (JAXA), is studying a micro-satellite system for active space debris removal, and is examining the applicability of electro-dynamic tether (EDT) technology as its high efficiency orbital transfer system. A small EDT package provides a possible means for lowering the orbits of objects without the need for propellant. Capture is indispensable for the retrieval of large space debris objects, and we propose a flexible robot arm for this purpose. This paper discusses a space debris removal satellite system and describes the development status of prototypes of the EDT package and a new robot arm for capturing non-cooperative targets. [Copyright &y& Elsevier]

Abstract: NASA''s planned Ares V cargo launch vehicle offers the potential to completely change the paradigm of future space science mission architectures. Future space science telescopes desire increasingly larger telescope collecting aperture. But, current launch vehicle mass and volume constraints are a severe limit. The Ares V greatly relaxes these constraints. For example, while current launch vehicles have the ability to place a 4.5m diameter payload with a mass of 9400kg on to a Sun-Earth L2 transfer trajectory, the Ares V is projected to have the ability to place an 8.8m diameter payload with a mass of approximately 60,000kg on to the same trajectory, or 180,000kg into Low Earth Orbit. Also the Ares V could place approximately 3000kg (13,000kg with a Centaur upper stage) on to a trajectory with a C3 of 106km2/s2, arriving at Saturn in 6.1 years without the use of gravity assists. This paper summarizes the current planned Ares V payload launch capability. [Copyright &y& Elsevier]

Abstract: We introduce a more advanced analysis than that of Roth concerning the following two points of view: (1) We attempt to find an analytical solution of the optimization problem instead of Roth''s iterative solution. That means a stress is operated on the analytical approach. (2) We consider the terminal orbits to be elliptic and not circular as Roth assumed. This is a generalization of the problem. We shall complete the solution of this Bi-Elliptic transfer with plane change problem in the second part of the present research paper (I). [Copyright &y& Elsevier]

Abstract: The international scientific community, and especially the IAA (International Academy of Astronautics) have long been discussing the need to keep the Farside of the Moon free from man-made RFI (radio frequency interference). In fact, the center of the Farside, specifically crater Daedalus, is ideal to set up a future radiotelescope (or phased array) to detect radio waves of all kinds that are impossible to detect on Earth because of the ever-growing RFI. Nobody, however, seems to have established a precise border for the circular region around the antipode of the Earth (i.e. zero latitude and 180° longitude both East and West) that should be Protected from wild human exploitation when several nations will have reached the capability of easy travel to the Moon. In this paper we propose the creation of PAC, the Protected Antipode Circle, centered around the antipode on the Farside and spanning an angle of 30° in longitude, in latitude and in all radial directions from the antipode. There are sound scientific reasons for this: [(1)] PAC is the only area of the Farside that will never be reached by the radiation emitted by future human space bases located at the L4 and L5 Lagrangian points of the Earth–Moon system; [(2)] PAC is the most shielded area of the Farside, with an expected attenuation of man-made RFI of 100dB or higher; [(3)] PAC does not overlap with other areas of interest to human activity except for a minor common area with the Aitken Basin, the southern depression supposed to have been created 3.8 billion years ago during the “big wham” between the Earth and the Moon. In view of these unique features, we propose PAC to be officially recognized by the United Nations as an International Protected Area, where no radio contamination by humans will possibly take place now and in the future for the benefit of all humankind. [Copyright &y& Elsevier]

Abstract: In the 14th and 15th centuries, Portugal went discovering and conquering sea and land all over the world. History was forever changed by the courage and bravery of one people. The Portuguese navy introduced new techniques of navigation, using astronomical instruments like the astrolabe. In this paper, some episodes of the Portuguese relation with astronomy and space will be highlighted. These refer not only to governmental measures and decisions, but also to initiatives of the society at large, telling of the important role that this subject has played in the Portuguese society throughout the years. [Copyright &y& Elsevier]