Low-power Graphical Processing Unit (LPGPU) are high-performance devices suitable for data parallel workloads, such as image and video processing; they are found in devices we use every day ranging from mobile phones to smart TVs as well as laptops and high-performance computers. Their use in on-board space applications has not yet been investigated in Europe but it could enable missions with extremely high processing requirements, as can be payload processing for scientific or Earth observation missions as well as autonomous closed loop controlled space applications, such as active debris removal, orbital rendezvous and landing.

Additive Manufacturing and more specifically 3D bioprinting of living tissues could have a key role in deep space exploration missions and could be one of the enabling technologies for an inhabited station on a celestial body. A 3D file (based on astronauts Computer Tomography scans) could be sent from Earth and regenerative medicine could be adopted in case of health emergency of one a the crew members. Blood, tissues, but also bones and organs could be printed on planet enabling telemedicine and sustainable life on long term/long distance space and planetary exploration missions.

The first phase of the study shall provide an ex-ante socio-economic assessment of the potential European industry participation toa future global On-Orbit Servicing market. Against this backdrop, the second phase of the study shall assess ex-post the socio-economic impacts of the Clean Space Initiative related to the initiative's first six years (i.e. 2012-2017), and provide an ex-ante assessment of the socio-economic impacts of the realization of the e.Deorbit mission as a technological enabler for a possible future European On-Orbit Servicing capability. This latter assessment shall be complemented by a counter-factual scenario assessment i.e. thepossible consequences that would happen if such a mission would not be accomplished.

The main objective of this study is to perform a comprehensive in-depth assessment and consolidated analysis of socio-economic impacts generated by ESA's technology programmes incl. GSTP, TRP and ITI, on the economies and industries of the ESA Member States participating to the programmes. The analysis shall identify the full range of quantitative and qualitative impacts. In particular, identified cases of technological innovations as well as any intangible (i.e. non-quantifiable) benefits shall be included in the assessment. A representative range of technologies used in space projects, in particular mission-enabling technologies as well as IODs IOVs shall be analysed regarding the various impact categories. The study shall further aim to collect data related to technology research and development activities in the past that provide evidence of impacts in current programmes and activities of the related stakeholders. The analysis should be based mainly on the outcomes of expert interviews and an extensive questionnaire survey with representatives from industry research organisations regarding the follow-on of their current projects in ESA technology programmes, complemented by sensitivity analysis and further validation by expert interviews.

The European Space Agency is interested in the advancement, maturation and demonstration of lunar In-Situ Resource Utilisation (ISRU) technologies. These technologies will eventually be deployed at the lunar surface to provide consumables and materials that will enable the sustainability of future human exploration missions. The goal of this AO is to demonstrate critical technologies in the end-to-end ISRU process chain for production of oxygen at the lunar surface and to characterize the ISRU feedstock at a location which is representative of those which will be visited by future human missions. The objectives of this activity are: (1) to identify a candidate ISRU payload, payload suppliers and partners interested in jointly enabling research and development; (2) to identify commercial providers for Lunar surface delivery and communications services; (3) to study two mission concepts and their implementation feasibility. (4) to select one successful mission concept in a final ESA review.

The European Space Agency is interested in the advancement, maturation and demonstration of lunar In-Situ Resource Utilisation (ISRU) technologies. These technologies will eventually be deployed at the lunar surface to provide consumables and materials that will enable the sustainability of future human exploration missions. The goal of this AO is to demonstrate critical technologies in the end-to-end ISRU process chain for production of oxygen at the lunar surface and to characterize the ISRU feedstock at a location which is representative of those which will be visited by future human missions. The objectives of this activity are: (1) to identify a candidate ISRU payload, payload suppliers and partners interested in jointly enabling research and development; (2) to identify commercial providers for Lunar surface delivery and communications services; (3) to study two mission concepts and their implementation feasibility. (4) to select one successful mission concept in a final ESA review.

The most critical maritime operations requires pilotage, which is compulsory in many ports. A pilot is a mariner who boards a ship entering a harbor or other congested waters. He/she is an expert ship-handler who possess detailed knowledge of local waterways. In harbor navigation, the pilot directly manoeuvres the ship and communicates with the tugs and the shore linesmen to complete the berthing or the un-berthing operations. The objective of the proposed activity is to create a set of reliable safe paths to be used bythe different vessels which navigate in the local waterways environment. These paths are expected to reduce the uncertainty associated with each operation, thus increasing the overall level of safety. Furthermore, they will facilitate the pilots work and reduce their workload. Once certified, these paths will become one of the key enablers for future autonomous vessels traffic operations.In the proposed approach, and for a given port (or a critical inland waterway), a set of certified paths is generated based on GlobalNavigation Satellite Systems (GNSS) position estimations and Big Data techniques. In particular, GNSS Position, Velocity and Timing(PVT) data are available from GNSS receivers, which are widely used in vessels as one of the main sources of navigation information. At the same time, Big Data techniques currently allow for an effective processing of large data sets of GNSS measurements. In this context, a set of certified paths can be created in a four stages approach, i.e.: (1) Path Content Specification; (2) Data Collection; (3) Data Classification; and (4) Data Processing. In the first stage, the content of a certified path is agreed in close collaboration with the maritime community and the receiver manufacturers. Once the content of the path is specified, the next step is the Data Collection stage. Here, a large amount of Global Navigation Satellite Systems (GNSS) PVT data is collected for the ships performing the same type of operation (e.g. berthing) under a pilot control. After that, the collected data is classified based on the ship features (e.g. size, draught or other performance parameters associated with the vessel) and the different operational conditions (e.g. tide levels, sea current or sea state). This is done in the data classification stage. Finally, once classified, the data of a given group is processed to derive all the information which is needed for the generation of a certified path. The processingis done in the last stage of the process and will use suitable techniques such as polynomial regression. Once certified, a path will be fed into the ship navigation system and followed by another pilot in charge of performing the same operation with an identicaltype of ship and under the same environmental conditions. This will reduce the pilots workload and is expected to significantly enhance the safety of critical maritime operations. It is expected that the feasibility of both the concepts and the techniques studied in these activities will pave the way for future ESA missions evolution targeting maritime Safety of Life (SoL) services. In particular, the role of EGNOS, Galileo and, in general, GNSS for critical maritime operations will be clarified. Once feasibility is proven, an objective of this activity is to provide a way forward as a roadmap. This will include a new set of mission requirements forfuture European Satellite Navigation and Communications systems. These new concepts will require not only a change in the approachinrelation to navigation operations but also a need for a two way communication between the vessels and the local waterways authority.

Recent trends show an increased deployment of small satellites, often in massive releases, into Earth orbit. It is expected that this trend will continue and rates will grow. The new small or tiny satellites follow non-classical approaches for the design and for operations. One concern is the dependence from publicly available two-line element (TLE) sets for operations. The timely TLE availability is not guaranteed, and further the assignment of operator identification to TLE sets can be delayed. We propose to study augmenting the observability of small satellites through passive components, such as small laser retro-reflectors or dipoles with minimum design impact at system level. Adding unique patterns to discriminate similar satellites of mass launches or constellations should be investigated, too. This would not only be beneficial for operators of small missions, but also help to improve conjunction predictions, even after mission end, for all satellites. It would also improve assessments of attitude and attitude motion state, e.g. during operations or contingency situations. Finally, the proposed tagging would also help for complying with requirements of spacecraft registration. The study shall collect and synthesise information on available technologies and on-going developments; and shall develop feasible, cost-efficient, and promising concepts for the identification of small satellites with minimal impact on the design. The activity shall address design, operational, and regulatory aspects.

The objective of this activity is to study a concept addressing the need of the climate community of high-resolution and wide-swathcloud profiles by adding active observation capability to future operational cloud observations for synergistic exploitation. Innovative multi-instrument synergistic retrieval algorithms shall be developed to retrieve wide-swath and high vertical resolution products of ice and liquid clouds and precipitation from synergistic exploitation of Metop-SG instruments ICI and MWI and a 94GHz cloud radar flying on an additional satellite in convoy with the Metop-SG satellites. The scientific and operational value of such a convoyshall be assessed.Background:The cloud-radiation feedback is the most significant atmospheric effect in the climate system. Changes in surface and atmospheric temperatures impact directly evaporation/condensation rates and the processes leading to the formationof clouds. In return, clouds directly impact the reflection of incoming solar and outgoing long-wave radiation to space, by this both cooling and heating the Earth. The vertical structure and composition (droplet and ice particle sizes and mass densities) of clouds and their evolution over time are therefore key observables in the climate system in order to understand and monitor climate change. Global observations of clouds are primarily done by space-borne passive imaging instrumentation, which lacks vertical cloud profile information, rendering them basically useless for radiative impact assessments. Cloud profiling radars and lidars in space respond to the need of vertical resolution of cloud observations, but suffer from the lack of (across-track) swath. Future operational meteorological satellite observations are based on passive techniques, which will provide swath, but no or insufficient vertical resolution of clouds. The combination of both passive and active instruments could provide the way forward for the required height resolved and wide-swath observations.

There is a huge potential in the combination of high resolution optical and SAR data in order to generate high level products for land applications. In the verynear future a wealth of data will be made available by the providing high spatial resolution / high temporal resolution multichannel data. However, in order to fullyunderstand the processes and ensure a robust retrieval, a data driven approach has to be complemented by a solid theoretical modelling strategy where it isensured that the modelling inputs and approaches are made consistent between the two wavelength domains.The objective of this activity is to consolidate the theoretical modelling elements and to develop and validate a prototype algorithm exploiting multisource data sets from high resolution imagers (optical and SAR) for a selected land use type (focus will be put on agriculture) with the purpose of demonstrating the added value of thiscombination.

Marine Litter is a global issue, affecting all the major bodies of water on the planet, from the surface to the sea-bottom. It can negatively impact wildlife, habitats, the economic health and burden of coastal communities and maritime activities but also become an issue of public safety, considering the emerging concerns over ingestion of microplastics by marine particle feeders. The objectives of this contract are: - to define the target application(s) and mission objectives (in consultation with scientists) and the corresponding system requirements for the remote sensing of plastic Marine Litter;- to identify by analysis and preliminary lab/in-situ tests which existing or emerging techniques/technologies could be capable to remotely detect plastic Marine Litter and on the base of that to propose a conceptual design of a remote sensing system capable to satisfy the defined requirements.

Marine Litter is a global issue, affecting all the major bodies of water on the planet, from the surface to the sea-bottom. It can negatively impact wildlife, habitats, the economic health and burden of coastal communities and maritime activities but also become an issue of public safety, considering the emerging concerns over ingestion of microplastics by marine particle feeders. The objectives of this contract are: - to define the target application(s) and mission objectives (in consultation with scientists) and the corresponding system requirements for the remote sensing of plastic Marine Litter;- to identify by analysis and preliminary lab/in-situ tests which existing or emerging techniques/technologies could be capable to remotely detect plastic Marine Litter and on the base of that to propose a conceptual design of a remote sensing system capable to satisfy the defined requirements.

This activity aims to combine the work performed so far in REACH and LCA. It will complement the current design models to provide ESA and European industry a process to link chemical risk information and information on the criticality of raw materials with life cycle assessment and proactively address in early stages risks of supply chain disruptions due to environmental legislation. Furthermore it aims to provide a process to assess the lifecycle impact of the substitution of materials due to REACh authorization efforts and compare to alternative scenarios.The objective of the activity is to analyze REACH and LCA processes, identify key synergies, and propose prototype models and processes for reciprocal benefits: 1. REACH â?? LCA· Analyze and trade-off several options to implement the monitoring of REACH and CRM use through the complete lifecycle of space products using LCA methodology.· Develop a prototype full scale LCA model allowing to flag and classify the use of REACH substances and CRMs in different life cycle stages of a spaceproduct.· Validation of the proposed solution through application to a test case.2. LCA â?? REACH· Analyze and trade-off options tosupport REACH authorization efforts (e.g. chemical risk assessment, analysis of alternatives) through complete lifecycle LCA data.

Radio climatological models of the ionosphere are key to the system design and performance assessment of some ESA missions, both for Navigation and Earth Observation. In view of the new missions on the horizon and of the amount of experimental data that has been collected on the ionosphere in the past years, it is a proper time to revisit the performance of these models.The overall objective of this activity is to use the experimental observations of the ionosphere collected in the past years to assess the performance of climatological ionosphere models, to assess their ability to properly support future ESA missions, to identify weak areas if any andto propose recommendations for improvements. Most of the effort is expected to be put on ionosphere scintillation models.

This study will assess how recent advances in the field of quantum metrology and for squeezed light interferometry could be appliedto improve the estimation of parameters in space-based gravitational physics experiments.Based on first analysis, this could be thecase for example for the application of multiple-phase estimation for a space-based gravitational wave detector, such as the evolved Laser Interferometer Space Antenna (eLISA) or the use of light ring gyroscopes for frame dragging experiments similar to Gravity Probe. Universities are encouraged to propose other more suitable or equivalent examples to demonstrate potential improvements of using quantum metrology for space-based experiments.

This study will assess how recent advances in the field of quantum metrology and for squeezed light interferometry could be appliedto improve the estimation of parameters in space-based gravitational physics experiments.Based on first analysis, this could be thecase for example for the application of multiple-phase estimation for a space-based gravitational wave detector, such as the evolved Laser Interferometer Space Antenna (eLISA) or the use of light ring gyroscopes for frame dragging experiments similar to Gravity Probe. Universities are encouraged to propose other more suitable or equivalent examples to demonstrate potential improvements of using quantum metrology for space-based experiments.

This activity will study the effective complexity, resource requirements and overall system-level efficiency of utilizing a High Intensity Laser Power Beaming System (HILPBS) for powering a rover operating in the proximity (<15km) of a lander. The HILPBS would consist of: · a high power laser (and possibly a small telescope) feeding the optical beam to a a high-rise gimbal on the lander. The laser would be powered by solar panels (~3 kW) or nuclear power source and batteries. · a receiver panel (~ 1600 cm2) made of gallium or VMJ photovoltaic cells mounted high on the rover.The HILPB would deliver sufficient watts of power to recharge the relatively small batteries on the rover every time the rover is stationary and has line-of-sight visibility of the lander. This study shall allow to derive sizing formulas for different power cases for the receiver as well as the transmitting side, in order to elaborate on the advantages/disadvantages of a HILPBS solution with respect to a more conventional PV/battery solution.

GNSS-R is a remote sensing technique that relies on the use of navigation signals reflected on the surface of the Earth. Principally devised with ocean applications in mind, the potential of this technique for land applications (soil moisture and vegetation biomass) has been explored through the use theoretical models, and demonstrated thanks to ground-based and airborne experimental measurements.As land surfaces are heterogeneous, it is important to assess the performance of this technique from a spaceborne standpoint, which is now possible thanks tothe availability of spaceborne GNSS-R observations.The objective of this activity is to analyze available spaceborne GNSS-R observations to consolidate the understanding of the GNSS-R technique over land and to assess its performance for soil moisture and vegetation biomass retrieval.

Lunar exploration is likely one of the next steps of human space exploration beyond the International Space Station (ISS). Design reference missions for lunar exploration as well as roadmaps for technologies for space exploration have been established by ESA. Oneof the biggest challenges of the exploration of the Moon is the survival of the crew and the lunar assets during the lunar night, and the provision of energy for such elements. The environmental conditions on the lunar surface and its cycle, with long periods of darkness, make any long mission in need of specific amounts of heat and electricity challenging. This proposal will study the potential of thermal energy storage systems as a means of supporting future lunar exploration scenarios.

There are many places in the solar system where the thermal environment is severely constraining the possibilities for space missions. While major progress has been made in recent years in the development of low temperature electronics, usually it is chemical batteries that are limiting the low temperature survivability of traditional systems. In this study, the feasibility, pros and cons, physical and operational limitations of battery-less avionics systems for spacecraft, with a focus on planetary and lunar landers, are assessed. The state of the art of related key technologies is compiled, and the opportunities offered by battery-less systems are explored.

The advance of numerical atmosphere models to increasingly higher spatial resolutions (sub-km for NWPs, few tens of meters for LES), leads to new grounds being reached for what concerns their potential synergy with spaceborne systems: 1/ in order to feed NWPs, higher resolution input data and boundary conditions are needed that have the potential to be updated on a weekly or semi-weekly basis(e.g. 3-6 days) and which could be provided by recently available spaceborne Earth Observation products and 2/ the ability to modelthe atmosphere physics with high spatio-temporal resolution will allow to provide insight into physical mechanisms such as turbulence that are critical to some spaceborne techniques.The availability of these high-resolution models coincides with the start ofthe era of the Sentinels 1,2 and 3, which are characterized by their ability to provide high spatio-temporal resolution informationover the surface boundary as well as through S1 inSAR - information on the atmospheric water vapour fields.This activity aims atinvestigating new areas of synergy between atmospheric models and data from spaceborne systems such as the use of EO surface informationto constraint high resolution NWPs and to check their output, and the use of LES for a high-resolution description of turbulence insupport of advanced coding techniques for SatCom.

The main purpose of the activity is to develop a new reliability prediction methodology for space systems in an attempt to overcomethe inherent limitations of current prediction practices which are based on out-dated or limited handbooks (e.g. MIL-HDBK-217). Thenew methodology shall turn reliability predictions into more realistic estimations of the inherent reliability of the system design. This will improve the effectiveness of such estimations to support the analysis of alternative design solutions and verification approaches, as well as the evaluation of the conservativeness of design margins with respect to cost savings opportunities.Procurement Policy: C(2) = A relevant participation (in terms of quality and quantity) of non-primes (incl. SMEs) is required. For additional information please go to EMITS news "Industrial Policy measures for non-primes, SMEs and RD entities in ESA programmes".

New technologies available on the market are capable of sampling signal in the microwave range.This kind of technology can make possible the development of microwave sampling front end for space communication applications.This study proposes to analyse the feasibility of the development of a generic microwave sampling front end for multiple frequency bands (S,X and Ka band) and for multiple applications (from near earth to deep space). After requirement analysis the detailed specification of the sampling front end willbe derived and high level architecture defined. Then a technology state of the art analysis will be conducted and the detail designof the front end executed. All the neccessary simulations and models will be developed in order to prove the feasibility of concept.

Satellite nadir observations in the UV, visible, and short-wave infrared wavelength range are currently being used in aerosol monitoring for air quality and climate applications employing data assimilation techniques. The classic approach of assimilating Level-2 Aerosol Optical Depth (AOD) is error prone due to unavoidable inconsistencies in assumed aerosol microphysical parameters. The proposed activity is dedicated to an implementation and testing of an alternative approach based on the assimilation of radiances. This scheme is applied on a dataset from one well-calibrated satellite instrument with good aerosol capabilities. The study concludes withthe assessment of the aerosol monitoring skill of the radiance-based assimilation scheme and comparison with the AOD-based assimilation scheme, using independent aerosol reference data.

Missions requiring magnetically clean spacecraft seem to experience magnetic fields due to thermoelectric currents. At the interface of different electrically conductive materials and due to inhomogenities even inside single materials temperature differences cause differences in electron densities and therefore differences of electric potential. These potential differences drive electric currents, which are sources of magnetic field emissions. The phenomena are known to exist, and need to be studied from a multi-disciplinary perspective encompassing thermal, electric, magnetic and material aspects with special attention to possible mitigations.Understanding the physical roots of the perturbation and modeling the phenomena will improve the data exploitations for the actual and future magnetic missions.

Missions requiring magnetically clean spacecraft seem to experience magnetic fields due to thermoelectric currents. At the interface of different electrically conductive materials and due to inhomogenities even inside single materials temperature differences cause differences in electron densities and therefore differences of electric potential. These potential differences drive electric currents, which are sources of magnetic field emissions. The phenomena are known to exist, and need to be studied from a multi-disciplinary perspective encompassing thermal, electric, magnetic and material aspects with special attention to possible mitigations.Understanding the physical roots of the perturbation and modeling the phenomena will improve the data exploitations for the actual and future magnetic missions.

Lunar observations have been used for decades by EO missions for the in-flight assessment of optical instrument performance. The Moon is being used to assess 1) the image quality (PSF, MTF, straylight) and 2) the radiometric performance (radiometric temporal stability, inter-band calibration) of multispectral imagers. The lunar disk appearance changes continuously as a results of the continuously changing geometrical configurations of the Satellite-Moon-Sun system. The lunar disk spectral irradiance variations in time as measured from satellites orbiting around the Earth can be modelled. However, the absolute accuracy of the state-of-the-art model (the so-called USGS ROLO model) is to estimated to be only about 10%. Such an accuracy is not sufficient to use the Moon as as an absolute calibration target to verify the absolute calibration of EO optical sensors. EO optical sensors generally have more stringent requirements in terms of absolute radiometric accuracy (< 5%). We propose to improve the existing lunar disk irradiance model by developing a practical methodology to measure it from the Earth surface using widely available sun photometers. This would allow improving the modelling of the lunar disk spectral irradiance to a new level of accuracy compatible with the most stringent requirements onabsolute calibration of EO optical missions. The Moon could become a single common reference calibration source radiometrically linking with an unpreceded accuracy past, present and future EO missions having planned lunar observations

Current security architectures employed on most missions rely on a relatively simplecommunications topology (extended space link),consisting of a single spacecraft, multiple ground stations, and a ground segment consisting of a command control centre and a Payload Data Ground Segment (PDGS), and associated communication security mechanism mainly at thedata link layer. Anti-jamming modulation has been researched for enhanced security.Based on that ground/space architecture, a number of security countermeasures like the CCSDS Space Data Link Security protocol have been, and continue to be defined and developed for the benefit of the current and future missions. However, future space missions are anticipated to have a topology consisting of multiple satellites, possibly networked, with evolved application concepts and communication protocols. The simple security architecture previously developed and the corresponding portfolio of security mechanisms may not hold up to the security requirements of these more complex mission topologieswith more sophisticated and evolved protocols. Those mechanisms may not be amenable to evolution to satisfy these new needs.Furthermore, security research continues, attacks evolve, countermeasures and protections become obsolete or stronger and new security countermeasures are required for existing and new applications. In particular enhanced protection for adaptive communication links andsoftware-based processors at nodes performing radio, link, network and security functions are critical. The potential of novel security concepts like physical layer security, homomorphic encryption to respond to some of those requirements need to be investigated.Therefore, the aim of the study is to assess possible security technology candidates and their suitability vis-a-vis realistic future mission architectures.

Space missions are traditionally designed taking into account performances, cost and schedule as the major drivers. To date, possible environmental impacts are not considered within the design process. In 2009, ESA ran an internal study, called ECOSAT, which was the first study of its kind, with the aim to design a satellite taking into consideration the environmental impacts for the design, manufacturing, launch and operations of a satellite. The major outcome of the study was that eco-design is extremely complex and requires an evolution in the design of satellites calling for eco-design tools to be adapted specifically for the space sector, as no methodology, tool or database were existing for space applications. Over the past few years, several studies have looked into the Life Cycle Assessment (LCA) methodology for space missions and currently ESA is finalising design guidelines on LCA for spacecraft in the form of an ESA Handbook. With all this in mind, still no satellite has been designed taking into account the environmental impacts from the beginning. Hence the scope of this activity is to redesign a space mission taking into account eco-design fundamentals inorder to design an environmentally friendly spacecraft. The spacecraft will have of course to comply with all regulations linked debris mitigation and the design should focus on environmental impacts on earth and atmosphere. The design shall be compared with the original conventionally designed space mission so an estimate of the environmental advantages as well as cost and schedule impact at system level can be obtained. Guidelines should be written to allow implementation of ecodesign methods within future space missions. This will be the first time a spacecraft has been designed utilising an environmentally friendly approach.

Space missions are traditionally designed taking into account performances, cost and schedule as the major drivers. To date, possible environmental impacts are not considered within the design process. In 2009, ESA ran an internal study, called ECOSAT, which was the first study of its kind, with the aim to design a satellite taking into consideration the environmental impacts for the design, manufacturing, launch and operations of a satellite. The major outcome of the study was that eco-design is extremely complex and requires an evolution in the design of satellites calling for eco-design tools to be adapted specifically for the space sector, as no methodology, tool or database were existing for space applications. Over the past few years, several studies have looked into the Life Cycle Assessment (LCA) methodology for space missions and currently ESA is finalising design guidelines on LCA for spacecraft in the form of an ESA Handbook. With all this in mind, still no satellite has been designed taking into account the environmental impacts from the beginning. Hence the scope of this activity is to redesign a space mission taking into account eco-design fundamentals inorder to design an environmentally friendly spacecraft. The spacecraft will have of course to comply with all regulations linked debris mitigation and the design should focus on environmental impacts on earth and atmosphere. The design shall be compared with the original conventionally designed space mission so an estimate of the environmental advantages as well as cost and schedule impact at system level can be obtained. Guidelines should be written to allow implementation of ecodesign methods within future space missions. This will be the first time a spacecraft has been designed utilising an environmentally friendly approach.

The Flight Dynamics System (FDS) from ground control centre and the on-board Guidance, Navigation and Control (GNC) sub-system are two critical elements in many new missions demanding fast response in uncertain environment. The early analysis and trade-off of ground and on-board activities is a must in such missions in order to quantify the mission risks and minimize the overall cost. Increased autonomy might reduce the ground operations load but increases the on-board complexity. The proper assessment of the possible operational concepts is a complex task that is currently difficult to perform. It has been shown in some missions that improper assessment and design of FDS and GNC systems has led to significant delays in the mission and increased mission cost.This activity willanalyse the available solutions for the different elements of the FDS (orbit determination, manoeuvre computation, telecommand generation) and of the GNC (attitude guidance and control, image processing, relative navigation, translational guidance and control). The different techniques for each element of both systems will be mathematically defined in order to implement performance models for each solution (e.g. for the image processing function different performance models results for limb fitting, landmark matching, unknown feature tracking â?¦). Each performance model shall consider mission parameters (e.g. measurement frequency and batch duration,ground turn-around time, maximum number of manoeuvres). The interface between the different elements shall be defined in order to specify the flight operations loop (e.g. the manoeuvre execution error depends on the navigation accuracy and attitude control among other parameters).The models shall be implemented in a toolbox that permits fast assessment of different operational concepts and FDS GNC preliminary designs. For instance, defining a certain orbit or trajectory, figures of merit for different strategies are computed (e.g. delta-V, pointing performances, on-board knowledge, position control performance at predefined waypoints). This approachpermits the assessment of expected performances from early phase with poor knowledge (e.g. arrival to a solar system body) up to a later phase with improved knowledge. The mission objectives will be defined for a selection of mission scenarios (e.g. science andexploration missions, telecommunication megaconstellations). The goal of the activity is to produce of new methodology for early assessment of ground and on-board operations that permit substantial cost reductions in future missions (e.g. avoiding delays due tounrealistic assumptions, minimizing operation costs and/or space segment development costs). In addition, it might start a changein the paradigm of designing and operating space missions permitting faster ground and on-board design and implementation by numerical optimization of the performance-driving parameters of the complete system

The objective of this activity is to perform a feasibility study of active debris removal concepts for mega constellations, and trade re-entry, de-orbiting and active orbit cleaning.Not only shall satellites within constellations comply with ESAs Space Debris mitigation rules, it may also be more cost effective for the constellation operator to remove inactive satellites from the constellation to a non-protected LEO zone (or even to re-enter them) than to not remove them and accept occasional collisions, or to maintainconstellation by e.g. increasing reliability on each satellite within the constellation or increasing number of satellites.

This study shall investigate on a few test case the possibility to exploit platform magnetometers onboard spacecraft for the detection and observation of space weather events. One targeted test case is the exploitation of LISA pathfinder magnetometers which should somehow detect some of the solar wind strongest magnetic field signatures. Another one is the exploitation of proba-2 AOCS magnetometers which measures Earth magnetospheric field.

Passive de-orbiting devices (such as drag augmentation, mechanical tethers) are a reliable measure to limit post mission orbital lifetimes, in particular for small missions. However, the increase cross-section also increases the collision risk and (in a worst case) the effect might be neutral. Not all of the cross-section in this case may be sensitive to catastrophic collisions. Flux prediction and vulnerability modelling approaches shall be used to clarify the overall net effect of the passive de-orbiting devices.

This study aims to define the operational strategies, ground and space segment systems and staffing to be used by the megaconstellations to support the implementation of the Space Debris Mitigation measures defining the approach to collision avoidance and end of life disposal.

Delay Tolerant Networking (DTN) is a computer network architecture, seeking to address the technical issues of delayed and disrupted network connectivity. Specifically within the proposal of an Interplanetary Internet, DTN provides networking technologies to copewith the significant delays and packet corruption of deep-space communications. Using DTN, the objective is to achieve successful data delivery, to maximize the link utilization and to address many specific problems of space communication such as high bit error rates, intermittent link connectivity and long transmission delays. This technology enables manifold applications and operations concepts, which are superior to current transmission mechanisms. Focus is put on data delivery and not on timeliness as first criterion.This study aims to identify and proof a suitable scenario to utilise DTN, in particular in the area of LEO and GEO Satellites suchasEarth Observation satellites.The goal is to study how to realise the establishment of the Space Internet around Earth, and to examine and proof the possible benefits thereof. Specifically it should: 1) Examine implementation scenarios for Delay Tolerant Networksfor flexible communication with EO satellites to maximize station utilization and support emergency communication. 2) Proof conceptwith representative simulator and DTN routing configuration generation to devise suitability. 3) Define rollout strategy and roadmap for introduction and Break-even point of investment.

In this study, it is proposed to address the concept of printing lunar habitat and to look at the technology from a broad system perspective. This means not only having a printer to build habitats but to define all the ancillaries equipment required to operate it. This also means establishing other AM technologies that would be required to facilitate the production of the inner equipment required by the crew either to improve the habitability of the base, process food based on a limited number of elements, but also to produce the required spare parts ensuring the safety. This also includes the design and management of the materials from the early design of such mission to ensure a fully waste free cycle; the possible transformation of high-end materials in other with a less critical function down to even organic nutrients. This system approach shall eventually address the possibilities of using the resources available locally to, on the one hand, maintain the equipment brought from Earth to build the settlement and, on the other hand, increase the quality / diversity of resources available for the crew.

The activity aims at assessing the completion of the exploitation of Global Navigation Satellite System in support of weather and space weather nowcasting and forecasting. It addresses several areas not yet covered by current systems and which may be reached via either low-cost systems or the reprocessing of existing datasets:- continuous monitoring over oceans using receivers located in buoys and ships: horizontal gap filler;- monitoring over densely populated areas using cooperative smartphones: quantity over quality;- use of Precise Orbit Determination data: vertical gap filler.In these areas the activity shall assess possible techniques and sensors, investigate and demonstrate the feasibility of most promising techniques, identify the main critical requirements and technological developments (algorithms, communication systems, data rates, data mining, ...), and finally quantify the benefits of such developments.

The objective of the proposed study is to assess where and how Augmented Reality (AR) technology can enhance the performance of Astronauts and Spacecraft Operators during the training and the actual execution phase of operational procedures.The activity aims atremoving the root cause of some of human mistakes, which lie in the discrepancy between the abstract 2D and textual description of operational procedures and their mental transformation to a often substantially diviating 3D reality.The idea is similar to the overlay projection of essential information in aircraft cockpits, which are finding their way into the high end car models, where navigation instructions and speed information are reflected directly in the field of view of the driver on the wind shield. So instead of using an abstracted view in a separate device for navigation, an arrow tells the driver in his "real world" view to turn into an street. This is different than Virtual Reality as the name suggests it works on the concept of enhancing our perception of the reality with essential information.

Management of large constellation is a very effort intensive task. Without a proper automation concept which is developed from the very beginning and incorporated in the system design, effective automation can hardly be added at the later stage.To achieve sufficient level of automation needed for the management of complex constellations, operational services are required at different application domain levels, for example event driven, action/execution, situational awareness based on multicasting of relant information, exchange of orbital and attitude information, and so on. These services shall be distrubuted across the constellation in space and onthe ground.The CCSDS has been working on a set of new standard application level services, the Mission Operations (MO) Services,that could provide the building block for achieveing an advanced automation concept. These, together with other emerging standards more focused on on-board standardisation, such as CCSDS SOIS and SAVOIR may provide the appropriate means to devise a comprehensive andeffictive Constellation Management.The Galileo Second Generation will be used as a use case, however the result of the activity shall be generic and equally interesting for other constellations, including the emerging mega-constellations.

The purpose of this activity is to look at the potential value and feasibility of developing a sensor capable of measuring surface air pressure over the ocean. One technique to be studied is that of measuring differential oxygen absorption in V-band. Other techniques may also warrant further investigation. The study shall look at the existing literature subject of determining atmospheric air pressure, establish the governing equations in error sources, determine realistic sensitivity and accuracy and assess the overall value and feasibility of such an instrument.

The objective of the activity is the development of an operational data assimilation system for space-borne lidar and radar observations of cloud profiles and precipitation. Specifically, the development of assimilation input data handling and pre-processing, including data monitoring, development and testing of assimilation system functionality, experimentation and required development and adaptations of the 4D-VAR assimilation system shall be done. Feasibility shall be demonstrated with CloudSat and CALIPSO data. EarthCARE mission specific aspects shall be implemented so that EarthCARE lidar and radar assimilation will be fully prepared prior to the mission launch.

To avoid the LEO becoming unusable after a chain reaction of space debris collisions, commonly referred to as the Kessler syndrome,spacecrafts and rocket upper stages of ELVs need to be deorbited. This can be accomplished either by active means (i.e. de-orbit boost or active debris removal of a non-cooperative target) or by guaranteeing a sufficient orbit decay rate such that the re-entry event, meaning leaving the LEO Protected Region, will take place within 25 years after S/C demise. During the re-entry of the above mentioned objects, gases and particles are released into the atmosphere. The total mass of the demised spacecraft might seem low compared to the air mass in the atmosphere in a single event, however there might be a local effect around the flightpath of the object(e.g. release of toxic substances), as well as a long-term effect on ozone depletion and possibly even a global warming potential. However, the physical mechanisms behind this are currently completely unknown and are often treated as if they were negligible. Thisstudy aims at providing an analytical background for these assumptions. The major objectives of this study are: 1) To assess theimpact of spacecraft demise on Earth’s atmosphere in terms of short term and long term effects. 2) To understand the long term impact of spacecraft demise of ozone depletion and global warming. 3) To quantify the level of toxic elements released into the atmosphere andto assess the hazard potential. 4) To identify model uncertainties and give recommendations for testing needs to refine the model chemistry.

To avoid the LEO becoming unusable after a chain reaction of space debris collisions, commonly referred to as the Kessler syndrome,spacecrafts and rocket upper stages of ELVs need to be deorbited. This can be accomplished either by active means (i.e. de-orbit boost or active debris removal of a non-cooperative target) or by guaranteeing a sufficient orbit decay rate such that the re-entry event, meaning leaving the LEO Protected Region, will take place within 25 years after S/C demise. During the re-entry of the above mentioned objects, gases and particles are released into the atmosphere. The total mass of the demised spacecraft might seem low compared to the air mass in the atmosphere in a single event, however there might be a local effect around the flightpath of the object(e.g. release of toxic substances), as well as a long-term effect on ozone depletion and possibly even a global warming potential. However, the physical mechanisms behind this are currently completely unknown and are often treated as if they were negligible. Thisstudy aims at providing an analytical background for these assumptions. The major objectives of this study are: 1) To assess theimpact of spacecraft demise on Earth’s atmosphere in terms of short term and long term effects. 2) To understand the long term impact of spacecraft demise of ozone depletion and global warming. 3) To quantify the level of toxic elements released into the atmosphere andto assess the hazard potential. 4) To identify model uncertainties and give recommendations for testing needs to refine the model chemistry.

The World Radiocommunication Conference (WRC) held in 2015 approved a plan for modernization of mobile VHF communications allowing for digital data exchange between ships and shores and among the ships in several VHF channels as well as data collection via satellite in two VHF channels. The WRC also adopted a new agenda Item for the next conference in 2019 to carry out further studies and experiments for data downlink from satellite to ships.This GSP study will evaluate technical challenges and opportunities for Navigation Augmentation using VHF downlink channel particularly in the proposed frequency channels identified in WRC 2015 targeting maritime applications in remote areas such as Arctic region. The study will investigate technical solutions to for maritime communication via satellite and augmentation system for navigation. Compared to the current maritime VHF system such as AIS, the proposed solutions will take advantage of wider spectrum, thus capable of operating at lower power spectral density. The goal is also to assess the use the existing VHF communication infrastructure available on-board of vessels for the new services.

SMILE (Solar wind Magnetosphere Ionosphere Link Explorer) is a joint science mission between ESA and the Chinese Academy of Sciences (CAS) with a planned launch date in 2021. The mission aims at increasing our understanding of the connection between the interaction of the Solar wind with the Earth magnetosphere by looking at the nose and cusps of the magnetosphere and the aurorae at the North pole simultaneously while monitoring the in-situ plasma environment. The mission adoption by the Science Programme Committee is currently planned early 2018. The space segment consists of a Propulsion Module (PM) and Service Module (SVM), both provided by CAS, and a Payload Module (PLM) provided by ESA and including the four science instruments, the PLM Control Unit and the X-band communication system. The launch of the complete space segment will be under ESA responsibility. CAS will be in charge of the MOC, with possible ESA contribution (e.g. for ground stations), and both ESA and CAS will participate to the SOC.The four SMILE instruments are provided by ESA Member or Participating States (UVI and SXI), and CAS (MAG and LIA).The SMILE PLM is the mission element that is the object of this statement of work. Its procurement is divided in two main phases: a) Phase 1, corresponding to a parallel competitive phase A/B that will be concluded with a SRR and the contractor selection for the phase 2. The down-selection process will includethe review of the updated SRR data package which will serve as a PDR data package. The PDR will be concluded at the start of phase 2.b) Phase 2, corresponding to the phase C/D/E1, will be subjected to a CDR and QAR. Following the PLM flight model delivery for S/C AIT, the Contractor shall support the S/C level activities for the aspects related to the PLM. This will include support to S/C AIT, LEOP and in-orbit commissioning.

SMILE (Solar wind Magnetosphere Ionosphere Link Explorer) is a joint science mission between ESA and the Chinese Academy of Sciences (CAS) with a planned launch date in 2021. The mission aims at increasing our understanding of the connection between the interaction of the Solar wind with the Earth magnetosphere by looking at the nose and cusps of the magnetosphere and the aurorae at the North pole simultaneously while monitoring the in-situ plasma environment. The mission adoption by the Science Programme Committee is currently planned early 2018. The space segment consists of a Propulsion Module (PM) and Service Module (SVM), both provided by CAS, and a Payload Module (PLM) provided by ESA and including the four science instruments, the PLM Control Unit and the X-band communication system. The launch of the complete space segment will be under ESA responsibility. CAS will be in charge of the MOC, with possible ESA contribution (e.g. for ground stations), and both ESA and CAS will participate to the SOC.The four SMILE instruments are provided by ESA Member or Participating States (UVI and SXI), and CAS (MAG and LIA).The SMILE PLM is the mission element that is the object of this statement of work. Its procurement is divided in two main phases: a) Phase 1, corresponding to a parallel competitive phase A/B that will be concluded with a SRR and the contractor selection for the phase 2. The down-selection process will includethe review of the updated SRR data package which will serve as a PDR data package. The PDR will be concluded at the start of phase 2.b) Phase 2, corresponding to the phase C/D/E1, will be subjected to a CDR and QAR. Following the PLM flight model delivery for S/C AIT, the Contractor shall support the S/C level activities for the aspects related to the PLM. This will include support to S/C AIT, LEOP and in-orbit commissioning.

The objectives of this study is to numerically characterize the debris cloud distribution that results from orbital hypervelocity collision of a satellite with a secondary object of various sizes up to a complete satellite. The post-collision debris cloud should be characterised in terms of fragment number, mass, area, linear momentum, angular momentum, energy distribution, and directionality. The physical principle of an hypervelocity collision must be simulated and analysed in order to understand the transition between the local damage effect and the catastrophic disruption when varying the energy to mass ratio, the distance between the CoM of thetwo involved objects, the relative-velocity and the type and structure of the intersecting components. The main outcomes shall be (1) on a macroscopic systems level, to understand the propagation of shockwaves throughout a spacecraft due to a hypervelocity collision, (2) to understand the global fragmentation and debris cloud generated due to this collision, and (3) to further understand the catastrophic failure criterion and the energy levels involved.

The objectives of this study is to numerically characterize the debris cloud distribution that results from orbital hypervelocity collision of a satellite with a secondary object of various sizes up to a complete satellite. The post-collision debris cloud should be characterised in terms of fragment number, mass, area, linear momentum, angular momentum, energy distribution, and directionality. The physical principle of an hypervelocity collision must be simulated and analysed in order to understand the transition between the local damage effect and the catastrophic disruption when varying the energy to mass ratio, the distance between the CoM of thetwo involved objects, the relative-velocity and the type and structure of the intersecting components. The main outcomes shall be (1) on a macroscopic systems level, to understand the propagation of shockwaves throughout a spacecraft due to a hypervelocity collision, (2) to understand the global fragmentation and debris cloud generated due to this collision, and (3) to further understand the catastrophic failure criterion and the energy levels involved.

short description will be available soon

Manufacturing high end parts for space is a very complex process where many complementary fields of expertise need to be put together. Various entries such as function of the part, material procurement, heritage, availability of manufacturing equipment, dimensional verification methods are used to, eventually, make the part. ESA through its "Advance Manufacturing" cross cutting initiative hasplaced in perspective the possibilities to improve the manufacturing of parts for space. However, the initiative does not make the link between these technologies and the increase in performances they could induce at part level. This study aims at structuring theapproach to conceive parts taking into consideration all the required fields of expertise to maximise the performances of that part. This approach will be placed in a system perspective i.e. the expected performances will not be evaluated considering the part standing alone but at least within the sub-system it belongs to. Furthermore, the input from other Technical Domains (e.g. thermal, structure, power storage) to assess what additional improvements to the sub-system the part could bring will be addressed.

This activity aims at studying the concepts, trade-offs, preliminary design and technological drivers of Active Optics systems correcting for large deployable optical payloads on-board potential future Earth Observation (GEO 1-m resolution e.g.) and Science (exo-Earth Characterisation e.g.) missions

This ITT addresses the industrial Phase A system studies for LISA (Laser Interferometer Space Antenna), the candidate for third large class mission (L3) in the Science Programme. LISA is a gravitational wave observatory using laser interferometry between three spacecraft in drag-free control with freely falling test masses. The industrial system study will consist of parallel contracts with a duration of 20 months and aim at reaching a preliminary feasible design of the space segment, including: the interfaces to instruments provided by the Member States and potential international partners, to the ground segment, and the launcher; the definition of the metrology telescopes; development planning and programmatic assessments; support to the review activities at the end of Phase A.

This ITT addresses the industrial Phase A system studies for LISA (Laser Interferometer Space Antenna), the candidate for third large class mission (L3) in the Science Programme. LISA is a gravitational wave observatory using laser interferometry between three spacecraft in drag-free control with freely falling test masses. The industrial system study will consist of parallel contracts with a duration of 20 months and aim at reaching a preliminary feasible design of the space segment, including: the interfaces to instruments provided by the Member States and potential international partners, to the ground segment, and the launcher; the definition of the metrology telescopes; development planning and programmatic assessments; support to the review activities at the end of Phase A.

The increase of direct greenhouse gases, such as CH4, are amongst the largest contributors to climate change. The determination of their sources and sinks is hence is a pre-requisite for a reliable prediction of future climate. A recent activity investigating methods for synergetic retrieval of near-surface concentrations of CH4 using passive short-wave infrared (SWIR) and thermal infrared (TIR) observations revealed a fundamental bias problem in the retrieval of CH4 from the TIR (6-10 ìm). In order to further the capabilities of synergetic use of SWIR and TIR observations to obtain CH4 profile information, and thereby improved input to models inferring sources and sinks, this bias problem must be resolved. Also, current and future passive TIR sensors for CH4 will benefit from this investigation. This activity aims at investigating the causes of the bias through investigations of uncertainties in the spectroscopic information, state-of-the-art forward models, and possible instrument biases. Recommendations for further spectroscopic and/or model improvements shall be provided.

Critical transport operations such as landing or port docking among others require safety concepts. For example in the case of aviation, Satellite Based Augmentation Systems (SBAS) provide Safety of Life (SoL) services to pilots using SBAS enabled Global Navigation Satellite Systems (GNSS) receivers. The European Geostationary Navigation Overlay Service (EGNOS) is an SBAS that provides SoL service to Europe. Traditionally the SBAS concept has been built around providing specific safety performances tailored to particular transport operations. The system provides a safety of life service meeting requirements appropriate for each operation: integrity risk (IR), alarm limit (AL) and time to alarm (TTA). The IR can be defined as the probability of providing a positioning signal that is out of tolerance (the AL) without warning the user in a given period of time (TTA). The user GNSS receiver uses data transmitted by the SBAS satellite to improve the accuracy of their position and also compute a bound of the error of said position called protection level (PL). In other words, the protection level provides the user with a limit of the position error to be compared with the maximum tolerable error for that operation, i.e. the alarm limit. If the PL is smaller than the AL, the operation is safe. For the maritime case however ESA missions (namely EGNOS) and the ESA MARitime Safety of Life Working Group (MARSOL) have identified that is extremely difficult to consolidate a set of fixed requirements tailored to specific operations. In the case of harbour operations vessels cannot rely on an guaranteed approach path free of obstacles and traffic as is the case for aviation approach procedures (landing). The maritime case indeed requires a radically new approach. The objective of the activity is to evaluate the feasibility of using adaptive AL by creating a centralised port monitoring and processing of all the vessels in the port waters, instead of using a fixed AL. By collecting the respective positions, headings, velocity and PLs of the vessels in the port it could be possible to derive AL specific to each vessel in a particular instant. Doing this process in a continuous way and at a rate to be analysed within the study will provide an adaptive safety of life service for maritime that neither requires a priori knowledge of the operation AL nor a guaranteed approach path free of obstacles and traffic.

The competitive study implements the phase-A feasibility and requirements study for one of the elements of the Human Lunar Surface Demonstrator Mission. The element to be studied is a lunar ascent vehicle that should act as a demonstrator vehicle in preparation for human missions. It will also carry samples. The mission of the ascent vehicle is to launch from the lunar surface and rendezvous with the Deep Space Gateway in the Moon's orbit, where it will be berthed. In the study, the contractor is to trade various design options based on a consolidated requirements set as approved by the Mission Definition Review. The project management documentation as required by the European Cooperation for Space Standardisation, as well as a phase-A requirements set on system level are requireddeliverables.

The ESA Space Exploration Strategy (http://esamultimedia.esa.int/multimedia/publications/ESA_Space_Exploration_Strategy/) presents the Moon as the next destination for human spaceflight beyond Low Earth orbit. The strategy also identifies the utilisation of local resources a potentially important capability for changing the paradigm of exploration and enabling a sustainable exploration programme. This activity would identify high level In Situ Resource Utilisation (ISRU) system concepts, identify technology and knowledge gaps relating to ISRU and develop a roadmap for the development of ISRU technologies.