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Prepared by X. Barbier Reference TEC-SGT/2013-006/XB Issue 1 Revision 1 Date of Issue 26/02/2013 Status Document Type Distribution ESA UNCLASSIFIED – For Official Use estec European Space Research and Technology Centre Keplerlaan 1 2201 AZ Noordwijk The Netherlands T +31 (0)71 565 6565 F +31 (0)71 565 6040 www.esa.int Clean Space Compendium of Potential Activities for 2013 & 2014 GSTP-6 Element 1

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Prepared by X. Barbier Reference TEC-SGT/2013-006/XB Issue 1 Revision 1 Date of Issue 26/02/2013 Status Document Type Distribution

ESA UNCLASSIFIED – For Official Use

estec

European Space Researchand Technology Centre

Keplerlaan 12201 AZ Noordwijk

The Netherlands T +31 (0)71 565 6565F +31 (0)71 565 6040

www.esa.int

Clean Space – Compendium of Potential Activities for 2013 & 2014 GSTP-6 Element 1

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T Title

T Issue T1 T Revision T1

T Author T Date T26/02/2013

T Approved by T Date

T Reason for change T IssueT T RevisionT Date

T Issue T1 T Revision T1

Reason for change Date Pages Paragraph(s)

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Table of contents:

T1T TINTRODUCTION TO THE COMPENDIUMT .........................................................................................4 T2T TINTRODUCING CLEAN SPACET..........................................................................................................6 T3T TCLEAN TECHNOLOGIEST ...................................................................................................................7 T3.1T TDefinitionT ...........................................................................................................................................................................7 T3.2T TProposed Approach and Related ActivitiesT ......................................................................................................................7 T3.3T TBranch 1 – Eco-designT .......................................................................................................................................................8 T3.4T TBranch 2 – Green TechnologiesT .......................................................................................................................................11 T3.5T TBranch 3 – Debris MitigationT ......................................................................................................................................... 15 T3.6T TBranch 4 – Technologies for Space Debris RemediationT............................................................................................... 19 T4T TORGANIZATIONAL AND FINANCIAL ASPECTST .............................................................................23 T4.1T TGSTP Specific Working AreaT...........................................................................................................................................23 T5T TCONCLUSIONST................................................................................................................................24 T6 TLIST OF ACTIVITIES FOR 2013T .......................................................................................................25 T

T7T TDESCRIPTION OF ACTIVITIES FOR 2013T .......................................................................................26 T7.1T TBranch 1 (Eco-design) Activities for 2013T ......................................................................................................................26 T7.2 TBranch 2 (Green Technologies) Activities for 2013T .......................................................................................................29 T

T7.3 TBranch 3 (Space Debris Mitigation) Activities for 2013 T ................................................................................................33 T

T7.4T TBranch 4 (Technologies for Space Debris Remediation) Activities for 2013T ................................................................43 T8 TLIST OF ACTIVITIES FOR 2014T .......................................................................................................49 T

T9T TDESCRIPTION OF ACTIVITIES FOR 2014T .......................................................................................50 T9.1T TBranch 1 (Eco-design) Activities for 2014T ..................................................................................................................... 50 T9.2T TBranch 2 (Green Technologies) Activities for 2014T ....................................................................................................... 51 T9.3T TBranch 3 (Space Debris Mitigation) Activities for 2014T ................................................................................................62 T9.4T TBranch 4 Description of Activities for 2014T................................................................................................................... 68

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1 0BINTRODUCTION TO THE COMPENDIUM

During the Council meeting at Ministerial level held in November 2012, the sixth Period of the GSTP (ESA/C(2012)199) was presented and extensively subscribed by the GSTP Participating States with the following framework: GSTP-6 Element 1 – Support Technology Activities for Projects and Industry GSTP-6 Element 2 – Competitiveness GSTP-6 Element 3 – Technology Flight Opportunities GSTP-6 Element 4 – Precise Formation Flying Demonstration Following the approval of this new GSTP Period, this document provides the first list of candidate activities to the Initial Specific Area work Plan for Clean Space, within the frame of GSTP-6 Element 1. Roadmaps covering the four Branches of Clean Space– presented in this document – were defined throughout 2012. They amount to about 130 M€. A significant prioritization exercise was then undertaken, in line with the process and timeline described in the information note to the September 2012 (IPC ESA/IPC(2012)98, “Preparing the work plans for the GSTP-6 Element 1”). As indicated in this referenced document, Technology development activities in ESA are organised in 9 Service Domains (SD) and 25 Technology Domains (TD). This first pre-selection corresponds to activities belonging to the Generic Domain, SD7, devoted to transversal technologies common to several other SD, and to exploitation of technology (r)- evolution. According to the ESA-wide technology E2E process described in ESA/IPC(2008)61 rev 1, the activities which are part of this compendium have been pre-selected following an intensive internal exercise started in October 2012 and which included programmatic screening, technical evaluation and consistency checking with technology strategy and THAG Roadmaps. Apart from the current Clean Space document, two compendiums are issued for activities intended to be started in 2013 and 2014. These documents cover the core activities which are dedicated to the development of technologies, building blocks and components for future space missions, as well as three special areas (EGS-CC, SAVOIR and Space & Energy).

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The current compendium on Clean Space is divided in three parts

• An overall description of Clean Space and its four Branches, including the roadmaps of each Branch,

• A list and description of 18 activities which are intended to be initiated in 2013,

• A list and description of 17 activities which are intended to be initiated in 2014.

This compendium is issued to Delegations of GSTP-6 Participating States and their industries for comments. Such comments will be considered in establishing the initial Specific Area work plan for this part of GSTP-6 Element 1. The objective is to have a good indication of the developments GSTP Participating States may consider to support in order to present the GSTP-6 Element 1’s Clean Space Initial Specific Area Work Plan with a consolidated set of activities to the IPC in May 2013 and the corresponding Procurement Plan to the IPC in June 2013 for approval.

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2 1BINTRODUCING CLEAN SPACE

ESA is strongly committed to maintain the highest environmental standard for European citizens. This goal shall be accomplished through a coherent approach that encompasses not only the services provided by ESA satellites to the scientific community but also the preservation of Earth’s environment by mitigating the environmental impact of space activities both on ground and in space. Environmental laws and regulations are among the fastest evolving areas of law, particularly within the EU. As prime examples, the EU directives and regulations RoHS FP

1PF and REAChFP

2PF have

considerable implications for European space activities. Recently updated regulations such as ESA’s own “Requirements on Space Debris Mitigation for Agency Projects” and France’s “Space Operations Act” also impose regulations on environmental impact of space activities. It is important that actions are taken to transform these regulations into an opportunity for European space industry. Quickly mapping the road ahead will save crucial time, will foster innovation, and will yield substantial first mover advantage for Europe. ESA must continue to work with European industry and National Space Agencies to develop new processes and technologies and be well-positioned to shape and comply with future regulations in these areas, while, at the same time, minimising possible disruption of qualified materials and processes in the European supply chains. By being a pioneer in adopting eco-friendly approaches (e.g. eco-design) and technologies (e.g. green propellants), European industry will be ensured a competitive advantage. In that respect, resource efficient technologies also contribute to reduce costs by decreasing material inputs, energy consumption and waste. A safe and secure space environment is a requirement for all current and future space activities. Analyses performed by ESA and NASA indicate that the only means of sustaining the orbital environment at a safe level for space operations will be by carrying out both active debris removal and end-of-life de-orbiting or re-orbiting of future space assets. Already in the past, ESA has taken the initiative to remove its satellites from crowded orbits (e.g. ERS-2) when technically feasible by managing the end of their missions rather than waiting for a failure to declare the end of a mission. Today, ESA missions take into consideration space debris mitigation requirements during the development of future satellites and, when technically feasible, during the operations of current satellites. ESA, with its Clean Space initiative, will devote increasing attention to the environmental impact of its activities, including its own operations as well as operations performed by European industry in the frame of ESA programmes, through the implementation of specific technology roadmaps.

P

1P EU Directive (2002/95/EC) pertaining to the Restriction of Hazardous Substances in Electrical and Electronic Equipment (EEE). It was adopted by the EU in February 2003 and brought into force 1st of July 2006

P

2P European Community Regulation (EC 1907/2006), Registration, Evaluation, Authorisation and Restriction of Chemical substances. The law entered into force on 1 June 2007.

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3 2BCLEAN TECHNOLOGIES

3.1 9BDefinition Clean Space is introduced as a cross-cutting theme within ESA's Technology programmes. ESA defines “Clean technologies” as those that contribute to the reduction of the environmental impact of space programmes, taking into account the overall life-cycle and the management of residual waste and pollution resulting from space activities.

3.2 10BProposed Approach and Related Activities The approach proposed by the Clean Space initiative takes into consideration studies and technical activities that have been carried out over the past years by ESA, Member States, the EU and more generally world-wide. The General Study Programme (GSP) has played a key role in the preparation of the Clean Space initiative by conducting technical analyses to identify knowledge-gaps, which have been individually addressed through specific technical and scientific studies. Subsequently, the related recommendations have been addressed through a number of GSP activities in the fields of: • Spacecraft and Launchers life cycle assessments at system level. • Orbital debris, from the understanding of the current situation to the assessment of mitigation

solutions. • System studies on active debris removal, etc. The Clean Space initiative, organizes the implementation around four distinct branches: 1. Eco-design: the development of tools to monitor and evaluate the environmental impact and

legislation compliance of programmes. 2. Green technologies: the development and qualification of new technologies and processes

to mitigate the environmental impacts of space activities. 3. Space debris mitigation: the study and development of affordable technologies required for

managing the end-of-life of space assets. 4. Technologies for space debris remediation: the study and development of the key

technologies for active debris removal. Because of the different characteristics of those branches, the related context is hereafter addressed individually. UTechnology development roadmaps have been developed and discussed with industry and delegations. Technology activities will be implemented through different ESA technology programmes such as TRP and GSTP. In particular, concerning GSTP, a specific Clean Space working area will be created within Element1.

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3.3 11BBranch 1 – Eco-design A broad understanding of the environmental footprint of space activities is paramount to be able to mitigate the risks of supply chain disruption from the early stages of the design. Industries must be provided with a harmonised framework of tools to consider environmental issues during the design phase. The preceding activities in the field show that ESA has the right background to coordinate this European effort. XFigure 1X describes the implementation of the set of activities that are proposed within the programmatic frame of Clean Space – Branch 1.

3.3.1 Monitor and Evaluate Legislation Compliance

Environmental legislation, such as REACh regulation, has considerable impact on all European industry. While some actions are already being taken at national institutional level and by industry, ESA is currently pursuing a strong endeavour to actively monitor evolutions in the area of environmental law and to anticipate possible disruptions to the supply chain of qualified materials and processes. ESA has also played a key role in the preparation of the dossier for the exception for the use of hydrazine in space. This dossier, has been presented by Eurospace on behalf of European industry to the European Commission in October 2012. The information gathered from the monitoring and evaluation of legislation compliance will be taken into account in the assessment of Green Technologies and in space systems Life Cycle Assessment, in its aim of minimizing supply chain disruptions.

3.3.2 Life Cycle Assessment

An environmental impact assessment deals with the possible positive or negative impacts that a project may have on the environment, including issues such as: climate change, ozone depletion, resource depletion, toxicity, etc. The European Commission, thanks to the work performed by the Joint Research Centre, is at the forefront on this topic and has recently issued the leading guide on environmental assessmentFP

3PF.

Currently the most appropriate tool to evaluate environmental impact of industrial activities is the Life Cycle Assessment (LCA), a structured, internationally standardized method and management tool (ISO 14040 and 14044). LCA has been used by industry for over 30 years, for quantifying resources consumption and environmental impacts associated with goods and services throughout the entire life cycle, from the resource mining to its disposal/recycle. Life Cycle-based approaches are used for all environmental regulations on products (e.g. PAS 2050, GHG Protocol scope 3, French standard X30-323). ESA has been a pioneer in applying the LCA methodology in the space sector, starting in 2009 with a preliminary CDF study called ECOSAT. Later, a complete LCA of the current European family of launchers was carried out, with the contribution of most of the main industrials in the European launchers production chain. This endeavour is being expanded to the whole life-cycle of a space mission through a GSP activity, started in January 2012, to which European primes are actively

P

3P ILCD Handbook – Analysis of existing Environmental Impact Assessment methodologies for use in Life Cycle Assessment, IES – JRC – EC, 2010, http://lct.jrc.ec.europa.eu/

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contributing in the data collection. In parallel, LCA is being gradually tested in design studies with the aim of adapting this framework to be used in the design process. These recent efforts have placed ESA at the forefront of the development of environmental impact assessment methods for space projects. However, a lot of work is still required to adapt these methods to take into account the specificities of space materials and processes. The goal is to establish a common eco-design framework available for European space agencies and industry. This framework shall include dedicated databases and tools for space activities LCA and allow assessing the risk of supply chain disruptions due to environmental legislation already in the early phases of the design.

3.3.3 Combustion and Plumes

LCA methodology needs to be complemented by scientific studies covering the areas where there is a lack of understanding on related environmental impacts. One important example is the atmospheric impact of launcher plumes, for which a GSP study has been started in 2012. This study will provide a state of the art model based evaluation of the atmospheric impact of the European launchers plumes. However, the developed models need to be validated and further understanding of the physical and chemical processes occurring during a launch are required in order to properly quantify the impact on the atmosphere (e.g. characterisation of Alumina distribution in the plume and respective sticking and catalytic effects).

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App

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3.4 12BBranch 2 – Green Technologies Recent EU legislative restrictions enforced strong limitations on the use of many materials, manufacturing processes, and technologies. The most imminent implication is their possible obsolescence, as manufacturers are forced to change materials compositions, alter manufacturing processes or take the decision to remove materials from the European market. Space systems rely on basic technologies which are sometimes not primarily driven by the needs of space but mostly by the evolution of terrestrial sectors (e.g. microelectronics and materials). New material/coating concepts in combination with advanced “greener” manufacturing processes and innovative design principles are already available in the industrial portfolio and could be implemented in space applications.

3.4.1 Definition

ESA is considering Green Technologies as contributors to: • Reducing the energy consumption during the life-cycle of a space mission, • Using resources in a more sustainable way, • Limiting and controlling the use of substances harmful to human health and bio-diversity, • Managing the residual waste and polluting substances resulting from space activities. XFigure 2X and XFigure 3X describe the implementation of the complete set of activities that are proposed within the programmatic frame of Clean Space – Branch 2.

3.4.2 Green propulsion

International research on green technologies has been on-going for some time, most notably on green propellants. A driver for green propulsion development has been the inclusion of hydrazine on REACh’s candidate list of Substances of Very High Concern (SVHCs). Green propellant is defined as propellant with reduced toxicity for the environment or the personnel that may come in contact with the propellant. Green Propulsion addresses the green propellant compounds, their performance and operational aspects and the hardware technologies needed specifically for use of these propellants. Green propellants and associated hardware must however be qualified to allow access to the space market. ESA has played a key role in the preparation of the dossier for the exception for the use of hydrazine in space, which has been presented to European Commission mid October 2012. In parallel, ESA is actively developing green propulsion, which has been a subject of the Technology Harmonisation process since 2002, with the most recent revisit being in 2012. The harmonisation process for green propulsion took place in 2012 and the THAG agreed Roadmap (CPGP issue 3, rev 2 on HDMS, http://harmostrat.esa.int) focuses its priority on rapidly maturing key technologies that will help such access as quickly as possible.

3.4.3 New materials and processes

New materials and processes will be considered to limit the human and environmental exposure to harmful substances, to reduce waste, and to reduce energy consumption.

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Additive Manufacturing (AM) offers significant reduction of waste material compared to classical subtractive manufacturing. The flexibility of the AM process will allow for the introduction of more efficient manufacturing practices, by reducing the production and inspection steps and thus simplifying the production chain. The dramatic decrease in the amount of raw materials combined with the design optimisation and possible reduction of life-cycle steps, enables to decrease energy consumption and to reduce CO2 footprint. Solid state welding processes such as Friction Stir Welding (FSW) allows energy efficient production, while also providing excellent mechanical and fatigue properties. In addition it has demonstrated exceptional environmental friendliness. Compared to conventional fusion welding processes, FSW consumes considerably less energy, no consumables such as a cover gas or flux are used, and no harmful emissions are created during welding. Other activities cover issues such as replacement of chromates, tartaric sulphuring anodising, lead-free assembly, use of thermoplastic vs. thermo-set materials, solvent cleaning, reduction of volatile organic compounds of paint systems and alternatives for polyurethanes.

3.4.4 Green electronics

Green electronics and components are covered by the European Component Initiative (ECI) (ESA/IPC(2006)57 and ESA/IPC(2007)21).

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ALM Green surfaces

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3.5 13BBranch 3 – Debris Mitigation This branch will be devoted to the development of the technologies that will allow the management of the end-of-life of space assets, such as design for demise, inflatable structures, propulsive de-/re-orbit, while imposing as few constraints as possible on the respective mission. XFigure 4X describes the implementation of the complete set of activities that are proposed within the programmatic frame of Clean Space – Branch 3.

3.5.1 First level counter measures

The current space debris environment poses a safety hazard to operational spacecraft as well as a hazard to public safety and property in cases of uncontrolled re-entry events. Europe is playing a leading role in the establishment of space debris mitigation requirements, which include: • Preventing fragmentation by carrying out the power and propulsion system passivation of all

space assets in-orbit after the end-of-mission, • In the densely populated LEO environment, limiting the residence time of space objects in

altitudes below 2000 km to 25 years after the end-of-mission. Furthermore, for those space objects whose on-ground casualty expectancy in the event of an uncontrolled re-entry exceeds 10-4 a controlled re-entry over an un-populated area is mandatory.

• For GEO, a post mission disposal by re-orbiting to a graveyard orbit above the geostationary ring.

3.5.2 Major technological gaps in the area of mitigation

Preliminary analyses have shown that space objects in LEO with masses above 500 kg might already imply an on-ground casualty risk higher than 10-4 and require detailed analysis to determine the need to perform a controlled re-entry. Compact, robust and autonomous systems for direct and controlled re-entry of spacecraft are needed. Furthermore, design for demise of the satellite in the atmosphere during re-entry may contribute to minimising the risk on-ground. For smaller satellites that do not require a controlled re-entry, the risk of in-orbit collision can be mitigated through disposal options that guarantee the decay in less than 25 years. De-orbiting systems that provide passive or active means to lower the spacecraft altitude are needed. Reliable measurement of the propellant on-board will also enable successful disposal of spacecraft, optimising the operational life-time. Thus, the development of accurate propellant gauging devices is key to perform the end-of-life operations efficiently. Robust and reliable passivation concepts must be developed that guarantee the proper passivation at end-of-life without increasing the risk during the operational lifetime. The procedures to passivate (as much as possible) the currently operated spacecraft and upper-stages need also to be improved. Finally, our knowledge on the current space debris environment and its evolution needs to be improved in order to enable the evaluation of the non-compliances to mitigation efforts and the effectiveness of the different mitigation measures.

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3.5.3 End-of-life de-orbiting / graveyarding systems

While a number of candidate technologies can be applied to accelerate orbit decay, de-orbiting of spacecraft in LEO and re-orbiting spacecraft in GEO, the integration of de-/re-orbiting devices, passive or active, must have a limited impact at system level.

3.5.3.1 Passive de-orbiting systems

UDrag augmentation devices

De-orbiting and (uncontrolled) re-entry of small satellites in LEO (below 800 km altitude) can be achieved in a passive way by means of drag augmentation devices. ESA has been supporting technology developments for inflatable and deployable structures, which have reached TRL of 4 to 5 and are now ready for integration into a de-orbiting subsystem, thus bringing their TRL to 6 to 7. The proposed approach is to develop and validate a de-orbiting passive subsystem. The de-orbiting device shall be modular (i.e. adaptable for multiple types of missions) and generic (i.e. scalable for different missions with a different mass). Spacecraft control concepts to optimize the dragging area have to be studied also. UTethers

Allowing for fast de-orbiting (e.g. several months), conductive tethers are a promising technology for de-orbiting small satellites in LEO (typically within 700-1500 km altitude). The current maturity in Europe of these systems, which use the electromagnetic force created by an electro-dynamics tether, relevant sub-systems is currently being raised to TRL 4 through a FP7 sponsored study. It is therefore proposed to take advantage of this European know-how and address the system level requirements in order to pave the way to further qualify this technology and promote its in-orbit demonstration.

3.5.3.2 Active de-orbiting and re-orbiting systems

The development of a modular and reliable active de-orbiting system, capable of performing the controlled de-orbit of spacecraft autonomously and applicable to a high number of missions, brings important programmatic and cost benefits. ESA’s CDF has performed a system level trade-off study among the different propulsive technologies and has identified aluminium-free solid propulsion systems as a promising option. In addition to the high-density impulse and high thrust, those systems are reliable and robust, have low power requirements and, with Thrust Vector Control (TVC) technologies, have the potential of being autonomous. A solution based on the use of clusters of small standard motors could perform controlled de-orbit at the end-of-life (LEO) and the re-orbit (e.g. GEO satellites graveyarding) of spacecraft with different sizes, while allowing to reduce the unit cost. Activities for the qualification of the propellant and motors and for the design and test of an autonomous de-/re-orbiting system, including the design of a GNC architecture and the design of the FDIR concept, are proposed.

3.5.4 Design for Demise

Design for demise (D4D) is the engineering process established for the intentional design, assembly, integration and testing of spacecraft such that it will demise upon atmospheric re-entry to a degree that is no longer considered a threat for people or properties on Earth. The proposed activities on this domain encompass: 1) the acquisition of re-entry data through observation campaigns, building upon the lessons learnt of ATV-1 re-entry airborne observation and testing data with emphasis on fragmentation, surface catalysis, ablation and melting to develop

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and refine models in support of design for demise strategies, 2) the development of rapid design for demise analysis capabilities for assessing public safety (considering also aviation and maritime traffic flows) as a design trade-off in the selection of materials, structures and configuration aspects, 3) the pre-selection and characterisation of demisable materials, 4) prediction of battery behaviour (e.g.: risk of exposition) and subsequent impact on re-entry events, and finally, 5) validation activities in relevant platforms (e.g. CubeSats).

3.5.5 Passivation

3.5.5.1 Propulsive systems

A study shall be initiated to assess the different passivation methods and architectural options for propulsion systems and identify additional technology developments. It is paramount to develop robust and reversible passivation valves that allow developing safe architectures for passivation.

3.5.5.2 Power Systems

The passivation of electrical systems will involve the discharge and disconnection of the batteries and the disconnection of the solar arrays. This passivation needs to be reliable enough to avoid deactivating the power system before the end of the mission. It is proposed to study the various passivation methods for electrical systems and define the specifications of the most adequate solution that could be transversally applicable to most of the space applications. The design shall then be prototyped and validated in the relevant environment.

3.5.6 Operations

3.5.6.1 Propellant gauging devices

Activities are proposed which are aimed at improving the accuracy of propellant gauging devices; this being crucial for performing end-of-life operations. Solutions based on ultra-sonic gauging are promising and will increase the precision of determination of the amount of propellant in the tanks. Other solutions such as mass-flow-meters will also be further analysed.

3.5.6.2 Managing the End-of-Life of running missions

Missions that are currently under operation are not fully prepared to conduct the operational measures mandated by the mitigation requirements. Conducting reliable passivation of remnant energy sources of running ESA missions requires stable criteria and procedures. Hence tank depletion burns, battery disconnection, transmitter shut-off processes need to be specified and qualified with the help of the equipment manufacturer.

3.5.7 Debris risk modelling and measurements

Space debris environment models are by no means static and require continuous improvements to keep pace with an ever-changing highly dynamic space debris environment. They also constitute the baseline for environment prediction models (as DELTA, Damage, SDM,…) that allow to simulate the application of mitigation measures. Such models also allow to evaluate the potential impact of missions on the space debris environment and to quantify the risk that missions are exposed to. Clean Space also proposes the development and breadboarding of an optical in-situ debris monitor to detect small debris and analyse the space debris environment, filling the current technology gap. This payload shall be flown as a piggy-bag payload on an Earth-oriented platform (e.g. from Sentinel series) in sun-synchronous orbit.

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Them

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Figure 4. Clean Space Roadmap - Branch 3

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3.6 14BBranch 4 – Technologies for Space Debris Remediation A 2009 joint study of the current space debris environment performed by all major space agencies (with NASA and ESA among them) showed that even if no further space launches took place the space debris population would continue to increase, resulting in a continuously growing collision rate unless something is done to interrupt that pattern. Active removal efficiency is increased when applied to objects with a high mass, high collision probabilities and at high altitudes, and applied early enough so as to prevent the further degradation of the environment. The main objective of Branch 4 is to start the development and demonstration of the key technologies required for the capture and controlled atmospheric re-entry of an uncooperative target orbiting in the LEO protected region. The technology developments shall be streamlined with a system oriented approach. This will place European industry at the forefront in the worldwide active removal efforts, providing a competitive advantage. ESA has performed several system studies for orbital servicing, such as ROGER, Conexpress, or SMART-OLEV for servicing GEO satellites, as well as CDF studies on active debris removal of large objects. European National Agencies are also addressing active debris removal. An important example is the DLR’s Deutsche Orbitale Servicing Mission (DEOS), a demonstrator for in-orbit servicing and active debris removal in LEO that entered in phase-B2 in 2012. XFigure 5X describes the implementation of the complete set of activities that are proposed within the programmatic frame of Clean Space’s Branch 4.

3.6.1 System activities

An assessment study for a de-orbiting mission carried out by ESA’s CDF highlighted the major technology and system level trade-offs and identified feasibility analyses to be performed. It is proposed to continue these system studies with the objective of streamlining the mission design. A mission design study (phase A/B1) and technology development activities are proposed to be undertaken in parallel, thus allowing for coordination of the technology activities in a mission driven roadmap. At the end of 2012, the ITT for a GSP study on “Service Oriented approach for Active Debris removal” was issued. Industrial recommendations issued from this study will be taken into account in the phase A and B1 studies.

3.6.2 GNC sensing suite and advanced GNC techniques

Unlike cooperative targets, rendezvous with non-cooperative targets (i.e. complex objects that have not been designed to cooperate with servicing) have to rely on a different sensing suite. The objective is the adaptation and upgrade of the existing sensing suite for co-operative targets to be used for uncooperative targets. The proposed development plan will bring the GNC technologies for ADR up to TRL 5 to 6. The proposed approach includes the development of vision-based sensors and LIDAR systems adapted to the ADR mission requirements and the enhancement, testing and validation of image recognition and processing algorithms.

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Finally, advanced guidance and control algorithms to comply with the specific requirements for phasing, fly around, and mating phases will be developed as well as the algorithms to control the capture mechanism and the relative position of the captured target.

3.6.3 Capture mechanisms

Out of all the mechanisms studied to capture non-cooperative targets, the most promising ones are: throw-net, enclosing tentacles, harpoon and robotic arms. Clean Space proposes that several capturing mechanisms are developed in parallel so as to limit the associated programmatic risk, bringing these mechanisms up to TRL 5 to 6: • Throw-nets appear to have a very large applicability to debris, because of the associated

scalability and low sensitivity to the target attitude. A thorough programme for characterisation, development and testing of throw-net systems is therefore proposed,

• Tentacles, a clamping mechanism for which the development can build upon heritage from current berthing and docking mechanisms. It allows capturing different targets as it can be easily adapted to capture the launch adapter ring of a satellite. This mechanism requires more accurate rendezvous manoeuvres but simplifies the operations after capture,

• Harpoons are rather insensitive to the target attitude and shape and do not require very close proximity operations. Recent research has shown that adapting the shape of the harpoon also allows to avoid the formation of new debris,

• Concerning robotic arms, synergies with the results from DLR’s DEOS demonstration mission shall be considered.

3.6.4 Validation and Verification framework

The validation and verification of the different technologies on representative environments will also require the development of a GNC test bench adapted to the relevant development and testing requirements and allowing the simulation of the physical rendezvous sequence. In-orbit demonstration opportunities to improve the maturity will also be taken into consideration.

3.6.5 Debris attitude motion measurements and modelling

Today, there is little knowledge on the attitude state of decommissioned objects. However, this is an essential element for the preparation of a removal mission, since the selection of the appropriate capture method strongly depends on the attitude motion of the target. Algorithms for the fitting of space objects geometry and attitude in dedicated observation data need to be developed. This will allow exploiting the measurement results and determining the attitude motion vector in an unequivocal way. In parallel, the currently available multi-body (6 degrees-of-freedom) simulators and propagators enhancement must also be enhanced, allowing to determine the attitude motion vector and to understand its evolution.

3.6.6 Other technologies

3.6.6.1 Investigation of de-tumbling solutions

Unlike cooperative rendezvous, where the attitude of the target is controlled or stable by design, uncooperative targets can have any rotational state. Any envisaged capture technique (throw-nets, robotic arm, and tentacles) has a natural physical limit in the angular momentum it can absorb. It

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is proposed to study the most promising generic de-tumbling techniques, such as, but not limited to, magnetic induction or the use of plume effect.

3.6.6.2 Ion Beam Shepherd (IBS)

The use of the ion beam from electric propulsion thrusters to induce a force on a space object without requiring physical contact between the chaser and the target is a very promising option. It could be used to de-orbit or re-orbit debris without requiring close proximity operations and due to the high mass efficiency of electric propulsion, be used for multi-target active debris removal. Even though, it cannot carry out the controlled re-entry of an object, the IBS could be used in re-orbit strategies or applied to several smaller targets. Following an exploratory study performed by ESA’s Advanced Concepts Team, it is proposed to mature this technology by carrying out concept validation activities on specific potentially critical issues. A concrete example is the test of the sputtering of the surface hit by the ion beam. It has to be proven that it will not generate numerous small debris that would pollute the orbital environment.

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4 3BORGANIZATIONAL AND FINANCIAL ASPECTS

Clean Space is introduced as a cross-cutting theme within ESA's Technology programmes. It is worth noting that the complete set of activities proposed within the programmatic frame of Clean Space add up to about 130 M€ at 2012 e.c. An important prioritization effort has resulted in the identification of priority activities, over the period 2013 to 2016, amounting to about 60 M€ at 2012 e.c. to be covered by various programmes:

• Branch 1 – ECO Design: 4-6 Meuro • Branch 2 – Green Technologies: 10-15 Meuro • Branch 3 – Debris Mitigation: 15-20 Meuro • Branch 4 – Debris Remediation: 15-20 Meuro

The proposed activities include studies for the definition of the actions and monitoring of environmental legislation (5-10% of the total cost), technology studies covering TRL up to 3 (20-30% of the total cost), technology studies covering TRL 4 to 7 (50-70% of the total cost), and a phase A/B1 study for mission de-orbiting (5-10% of the total cost). With regard to the synergies between the Clean Space initiative and SSA, it is worth noting that the main objectives of the future European SSA system, established in the corresponding Programme Declaration, are purely observational and do address any interaction with space debris environment (e.g. through design measures on satellites or actively influencing objects in space). For its part, Clean Space aims at providing the technical solutions to promote the compliance of ESA’s future missions with the debris mitigation guidelines as well as to actively remove space debris from critical regions. Therefore SSA and Clean Space are complementary.

4.1 15BGSTP Specific Working Area As indicated in ESA/IPC(2012)98, Clean Space, technologies identified in the CleanSpace roadmaps will be addressed under a specific area work plan within GSTP-6 Element 1. This Clean Space specific working area will allow an easier tracking of all activities both for the executive and delegations which will allow a more efficient management by executive and monitoring by delegations. By bundling the activities in a GSTP working area there is no extra cost, the member states still have budget flexibility within GSTP and Clean Space can more easily be understood as the European effort of space sustainability. The compendium of the activities presented covers Clean Space GSTP-6 work-plan for Element 1 SD7.

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5 4BCONCLUSIONS

In the past few decades, the environmental protection has come to the forefront of international attention and regulation. ESA is committed to maintain the highest environmental standard for European citizens. In particular ESA aims at ensuring that space activities comply with environmental legislation and space remains a safe, secure and sustainable environment. In this respect, ESA is working together with other stakeholders to reinforce international cooperation measures that will ensure the future of space endeavours. The Clean Space initiative is introduced as a cross-cutting theme within ESA's Technology programmes and it aims to make ESA an exemplary space agency in the area of terrestrial and space environmental protection. This will provide the European industry a competitive advantage thanks to an early introduction of technologies to face new legislation and more efficient “clean” technologies. It is organised through the following 4 branches: 1. Eco-design: the development of tools to monitor and evaluate the environmental impact

and legislation compliance of space projects. 2. Green technologies: the development and qualification of new technologies and processes

to mitigate the environmental impacts of space activities. 3. Space debris mitigation: the study and development of affordable technologies required

for managing the end-of-life of space assets. 4. Technologies for space debris remediation: the study and development of the key

technologies for active debris removal. The present paper serves as an introduction of the GSTP Clean Space Specific Working area within GSTP-6 Element 1, SD7 (Generic Domain) work plan for 2013 and 2014.

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6 5BLIST OF ACTIVITIES FOR 2013

GSTP-6

Reference Title Budget(k€)

Branch 1: Eco-design

G61C-001SY Space propellants Life Cycle Assessment (LCA) 300

G61C-002SY Life Cycle Assessment (LCA) of manufacturing processes and space materials

400

Branch 1 total 700 Branch 2: Green Technologies

G61C-005MP Hydrogen Peroxide Storability/Compatibility Verification 1,000

G61C-007QT Surface Engineering for parts made by Additive Manufacturing (Step 1) 600

G61C-010QT Sustainable, green ancillary materials for structure manufacturing 200

G61C-011QT Development of Green Polyurethane Materials for Use in Space Applications

300

Branch 2 total 2,100 Branch 3: Space Debris Mitigation

G61C-014MS Deployable Membrane 400

G61C-015MS Architectural design and testing of the Sub-system boom-sails 600

G61C-016EC GNC for drag augmentation devices 450

G61C-017MP De-orbit motor Engineering Model Manufacturing and Testing 1,300

G61C-018EC Rapid Assessment of Design Impact on Debris Generation 500

G61C-021EP Spacecraft power system passivation at end of mission 400

G61C-022MP Characterization of Ultrasonic Gauging Sensor for membrane tanks 300

G61C-024GR Optical In-Situ Monitor 1,200

Branch 3 total 5,150 Branch 4: Technologies for Space Debris Remediation

G61C-028MM Miniaturized Imaging LIDAR System (MILS) for Rendezvous & Docking operations between spacecrafts 1,200

G61C-029EC Image Recognition and Processing for Navigation 600

G61C-032MM Harpoon characterisation, breadboarding and testing for Active Debris Removal (ADR)

700

G61C-034GR Debris Attitude Motion Measurements and Modelling 600

Branch 4 total 3,100

Total 11,050

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7 6BDESCRIPTION OF ACTIVITIES FOR 2013

7.1 16BBranch 1 (Eco-design) Activities for 2013

Clean Space Branch Branch 1 - Eco-design

Technology Domain 26 Others

Ref. Number: G61C-001SY Budget (k€): 300 Title: Space propellants Life Cycle Assessment (LCA)

Objectives:

Carry out the Life Cycle Assessment of current and more mature alternative propellants proposed as alternatives with the following main objectives: – Evaluate the environmental impacts at all stages of the production and use of

space propellants, – Assess the risks of supply chain disruption due to environmental legislation, – Provision of an ILCD-compliant life cycle inventory databases of space

propellants, – Perform a preliminary comparison of the different propellants' environmental

impact.

Description:

This activity in part of the overall road-map for the development of a Environmental impact assessment framework for space systems. LCA is a standardised method and management tool (ISO 14040 and ISO 14044). The propellants are a critical element of space systems design and have an important impact on the missions life-cycle. However, most of them are very specific substances which life-cycle is not modeled in the current LCA databases and the environmental impact is not well understood. A very preliminary assessment of some space propellants is being done in the frame of the GSP activity on Environmental impact assessment of space missions for which 4 Spacecraft life-cycles are being modeled. The hereby proposed activity will complement the past studies in one area where more specific processes and materials/substances have been identified, i.e. propulsion. The fast evolving environmental regulation (e.g. REACh) also has lately raised the risk of supply chain disruptions (e.g. Hydrazine has been identified as a substance of very high concern for REACh). Nowadays several alternative less toxic propellants are being studied and developed in Europe. Nevertheless the environmental impact as well as the risk of supply chain disruptions due to environmental legislation is not being addressed throughout the whole propellant life-cycle. This activity should carry out: 1. An analysis of the different steps of the life-cycle of the indicated propellants, 2. An assessment of the risk of supply chain disruption for the different propellants, 3. A LCA model of the environmental impact of the different propellants assessed, 4. The provision of an ILCD-compliant life cycle inventory databases to be included

in the overall space Environmental impact assessment framework,

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5. A preliminary comparison of the propellants LCA results by looking at the overall impact on a space system life-cycle.

Deliverables: Study Report

Current TRL: Not Specified Target TRL: Not Specified Duration (months) 12

Applicable THAG Roadmap:

N/A

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Clean Space Branch Branch 1 - Eco-design

Technology Domain 26 Others

Ref. Number: G61C-002SY Budget (k€): 400 Title: Life Cycle Assessment (LCA) of manufacturing processes and space materials

Objectives:

Identification of manufacturing processes and materials specific to space applications with major differences to non-space processes and materials available in environmental databases; Assessment of the environmental impact of the identified processes and materials by means of LCAs; Assessment and comparison of the environmental impact of alternative manufacturing processes; Elaboration of specific ILCD-compliant inventory data.

Description:

This activity is part of the overall road-map for the development of an environmental impact assessment framework for space systems. Manufacturing processes and materials used specifically for space applications can differ gravely from non-space specific materials and processes. But due to their - comparably - seldom application, the impact of these differences is not well understood, especially from an environmental point of view. The assessment of environmental impacts relies on generic inputs based on existing databases for e.g. electricity, material and other resource usage for specific processes or given equipment employed or integrated. In former LCA studies the data availability on these space specific processes and materials were identified as one major gap in knowledge resulting in uncertainties and negatively affecting the informative value of the studies. This study therefore aims at closing this gap in knowledge, complementing the analysis performed in previous studies and identifying the environmental impact of space-specific manufacturing processes and materials. This will provide life cycle inventory data on space specific processes and materials for use in further environmental impact assessment studies. The activity should include: 1. The identification of space specific manufacturing processes and materials with major

differences to non-space related ones available in existing databases and manufacturing processes and materials not at all available in existing databases,

2. Carrying out of a life cycle assessment (LCA) of the identified processes and materials,

3. LCA of alternative manufacturing processes such as Additive Manufacturing technologies for specific parts,

4. Assessment of risks of supply chain disruption due to the use of hazardous substances in the manufacturing processes,

5. Provision of an ILCD-compliant life cycle inventory database on the identified processes and materials for further use.

Deliverables: Study Report

Current TRL: Not Specified Target TRL: Not Specified Duration (months) 12

Applicable THAG Roadmap:

N/A

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7.2 17BBranch 2 (Green Technologies) Activities for 2013

Clean Space Branch Branch 2 - Green Technologies

Technology Domain 19 Propulsion

Ref. Number: G61C-005MP Budget (k€): 1,000 Title: Hydrogen Peroxide Storability/Compatibility Verification

Objectives: Characterise the Storability/Compatibility and Safety of Hydrogen Peroxide for use in space propulsion applications and resolve disputes over the suitability of its use for these applications.

Description:

Hydrogen Peroxide has been investigated and used as a propellant since the 40's. However, since the 70's there has been significant controversy regarding the storability, long term chemical compatibility and handling of the high purity grades required for the use as a propellant. In the past decade, extensive research has been devoted to hydrogen peroxide including major efforts in Europe (e.g. EU FP7 GRASP). This includes a better understanding of the hydrogen peroxide chemistry but is not yet conclusive. Therefore there is a need to provide a definitive status on the storability / compatibility and safety characteristics of this propellant. The goal is to have a neutral entity perform analysis & testing via a meticulous experimental approach to provide definitive, credible conclusions on storability and material compatibilityand identify space propulsion applications for which hydrogen peroxide is appropriate. The activity should include: – Propellant Safety characterisation (e.g. resistance to radiation, adiabatic

compressibility), – Material compatibility (e.g. long term storage, material surface treatment

investigation), – Long term storability (e.g. influence of the impurities on the hydrogen peroxide

chemistry). An outcome of this activity will be a better understanding of the impacts of hydrogen peroxide on current and foreseen space propulsion systems (e.g. material selection, architecture impacts, etc).

Deliverables: Study Report

Current TRL: 2 Target TRL: 4 Duration (months) 12

Applicable THAG Roadmap:

Chemical Propulsion - Green Propulsion (2012)

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Clean Space Branch Branch 2 - Green Technologies

Technology Domain 24 Materials and Processes

Ref. Number: G61C-007QT Budget (k€): 600 Title: Surface Engineering for parts made by Additive Manufacturing (Step 1)

Objectives: To evaluate the surface finishing technique for AM parts in order to derive guidelines for future applications.

Description:

Within this study, the surface finish techniques that can be applied to AM build hardware will evaluated. The surface coating techniques will be evaluated, including electro and electroless depositions, surface conversion, anodising and paint for few widely used space materials (e.g. Ti6Al4V, AA316L, A357.0). The surface finishing techniques will also be evaluated including chemical milling, shot pinning, honing and electrochemical polishing. The combination of the two methods will also be investigated. Guideline on surface treatments for AM made parts will be established. Firstly the main surface finish used in space will be applied on flat samples of materials made using AM and the impact of the AM process on surface properties will be measured. In a second step, more complex geometries and requirements, derived from space hardware that could be manufactured in the future using AM technologies, will be made to establish the limitations in applying the selected surface treatments. Alternative finishing techniques will be evaluated and guidelines will be proposed.

Deliverables: Study Report

Current TRL: 2 Target TRL: 4 Duration (months) 24

Applicable THAG Roadmap:

N/A

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Clean Space Branch Branch 2 - Green Technologies

Technology Domain 24 Materials and Processes

Ref. Number: G61C-010QT Budget (k€): 200 Title: Sustainable, green ancillary materials for structure manufacturing

Objectives: Reduction of waste thanks to replacement of ancillary materials used for composite structures manufacturing with more sustainable, environmental friendly alternatives.

Description:

Manufacturing of space composite structures made of Carbon Fibre Reinforced Polymer (CFRP) require the use of different bagging materials during cure taking place most often at 180°. CFRP materials used for space application are usually based on epoxy or cyanate-ester resins. Bagging materials used for such materials consist in breather fabrics or peel plies for flow control or surface finish for bonding. Most of these ancillary materials are historical ones, without any improvement since many years. Even for cyanate-ester CFRP parts, more recent than epoxies and also more sensitive to bagging chemical composition, there has not been any assessment of innovative ancillary materials. It is proposed to study the use of biosourced or biodegradable bagging materials, new concepts enabling to reduce waste (reusable concept). Special care should be taken to check compatibility with cyanate-ester resins as the metallic catalyse system can be affected. The following tasks should be accomplished: 1. Revision of commercially available bagging materials that are biosourced or

biodegradable, 2. Manufacturing of CFRP skins with selected bagging materials as well as

conventional bagging for reference, 3. Compatibility testing of the bagging material with the skin production process

and performance evaluation of the CFRP skin in comparison with a manufacturing process using conventional bagging. Testing should include as minimum: (i) for the bagging material the thermal properties and contamination transfer potential and (ii) for the CFRP skin the surface quality and contamination, a subsequent coating application as well as mechanical properties.

Deliverables: Study Report

Current TRL: 4 Target TRL: 6 Duration (months) 18

Applicable THAG Roadmap:

N/A

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Clean Space Branch Branch 2 - Green Technologies

Technology Domain 24 Materials and Processes

Ref. Number: G61C-011QT Budget (k€): 300 Title: Development of Green Polyurethane Materials for Use in Space Applications

Objectives:

The objective of this study is to develop one or more “green” polyurethane synthesis routes which can be upscaled towards development and use for space applications such as coatings or paints, conformal coatings for electronics and foams. In particular development of alternatives to toluene diisocyanate (TDI) based systems are sought. The technologies for consideration are aimed at developing polyurethane systems which do not utilize the diisocyanate molecules as part of the production path. These materials are often extremely toxic to both humans and the environment.

Description:

Polyurethanes are traditionally manufactured from TDI or MDI (methylene diphenyl diisocyanate) based precursorsors. Both materials are harmful to human health, in particular TDI is considered Toxic by inhalation and should be carefully controlled in the production environment. TDI whilst not presently impacted by REACH is already controlled by other national and international legislation and is therefore likely to be subject to increasingly proscriptive restrictions. Despite its toxic nature, TDI (and to a lesser extent MDI) based polyurethanes display excellent properties for certain space applications with good flexibility, light and radiation stability as well good adhesion and foaming capabilities. This usefulness has meant it is used in a number of products for space including paints, conformal coatings and foams. In recent years various researchers have successfully developed polyurethane chemistries which do not involve diisocyanates in their formation. This activity is proposed to investigate and develop some of these alternative chemistries further towards a “green” polyurethane synthesis route which can be demonstrated to be upscaled towards manufacturing of useful quantities for production of space hardware. As a first target any chemistry developed would need to demonstrate that two technical systems could be addressed; paints and conformal coating. The activity would demonstrate that suitable materials could be manufactured for production of diisocyanate free paints and conformal coatings with properties equivalent to or better than their TDI/MDI counterparts. In particular emphasis would be given to any proposal for paint which also considered a VOC free green polyurethane system.

Deliverables: Study Report

Current TRL: 3 Target TRL: 4 Duration (months) 18

Applicable THAG Roadmap:

N/A

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7.3 18BBranch 3 (Space Debris Mitigation) Activities for 2013

Clean Space Branch Branch 3 - Space Debris Mitigation

Technology Domain 20 Structures & Pyrotechnics

Ref. Number: G61C-014MS Budget (k€): 400 Title: Deployable Membrane

Objectives: The objective of this activity is to perform a prototype demonstration of a deployable sail to be used in LEO for passive de-orbiting of satellites (maximum 1000kg).

Description:

De-orbiting of satellites in Low Earth Orbit (LEO) can be achieved in a passive way by means of inflatable and deployable structures. By deploying ultra-light sails, the atmospheric drag on the satellite will be increased and its natural decay will be accelerated. In order to further mature the sails for a passive de-orbiting system, a number of significant technological steps need to be performed: • Definition of the sail material to be used.

The material of the sail has to be selected and shall be compatible with the Space requirements: AtOx and UV resistant, compatible with radiation, charging, temperature environment and with vacuum. The probability of collisions with meteoroids shall be addressed vis a vis the remaining dragging area and the de-orbiting performance.

• Definition of the deployment system. The sails design shall be defined including dimensions (sail 2x5m2).

• Manufacturing of breadboards. Breadboards have to be manufactured in order to: assess the possibilities of joining parts, develop the interfaces to the deployment device, execute material characterization tests (but not limited to tension tests and tear tests)and aging tests. To these purposes the breadboards do not have to be full scale.

• Compatibility with folding and packaging. The material shall be characterised and properties related to packaging and folding shall be identified, i.e. minimum radius of curvature, packaging technique ensuring no damage to the sail when it is deployed afterwards (life test), etc.

UNoteU: this activity presents synergies with G61C-015MS “Architectural design and testing of the Sub-system boom-sails” and it would be beneficial to run both activities mostly in parallel. The architecture study would support the definition of the membrane requirements, hence allowing an optimal outcome for this activity.

Deliverables: Breadboard

Current TRL: 3 Target TRL: 5 Duration (months) 12

Applicable THAG Roadmap:

Deployable Booms & Inflatable Structures (2010)

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Clean Space Branch Branch 3 - Space Debris Mitigation

Technology Domain 20 Structures & Pyrotechnics

Ref. Number: G61C-015MS Budget (k€): 600 Title: Architectural design and testing of the Sub-system boom-sails

Objectives: The objective of this activity is to design, manufacture and test a sub-system constituted by a boom and a membrane to be used in LEO to augment the drag of small satellites (1000 Kg).

Description:

The already developed inflatable/deployable boom and the innovative deployable sails technologies can be now merged together to develop a subsystem boom+sails to augment the drag of small satellites (maximum 1000Kg) in LEO and make possible a faster de-orbiting. Thanks to the packaging density and the low mass ratio, the objective of such a subsystem shall be to allow a de-orbit to occur well within the 25 years requirement. The following steps need to be performed in this activity: • State of the art of subsystem architectures and trade-offs taking into

consideration system aspects. A state of the art review shall be performed in order to analyse the different boom+sails architecture and execute a trade-off exercise among 5 concepts (2 of which shall be new) and come up with a final concept selection.

• Definition of the subsystem design. The boom+sails de-orbiting subsystem shall be designed. The interfaces sails/boom shall be defined, taking into account load transfer paths and strength and stiffness issues, and the sails deployment mechanism shall be developed.

• A numerical model shall be developed. • Thermo-mechanical analyses of the subsystem boom+sails shall be performed. • Manufacturing of one breadboard. • Deployment of the subsystem boom+sails.

The deployment of the subsystem shall be successfully demonstrated on ground. Together with this, the packaging performances shall also be assessed.

• Validation of the subsystem deployment in thermal vacuum environment. • Exposure of the subsystem to the vibration environment and subsequent model

validation. UNoteU: this activity presents synergies with G61C-014MS “Deployable Membrane” and it would be beneficial to run both activities mostly in parallel. The architecture study would support the definition of the membrane requirements, hence allowing an optimal outcome for G601-014MS.

Deliverables: Breadboard

Current TRL: 3 Target TRL: 5 Duration (months) 18

Applicable THAG Roadmap:

Deployable Booms & Inflatable Structures (2010)

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Clean Space Branch Branch 3 - Space Debris Mitigation

Technology Domain 5 Space System Control

Ref. Number: G61C-016EC Budget (k€): 450 Title: GNC for deployable sail de-orbit devices

Objectives: Development of a GNC functional model for active as well as passive attitude stabilization of drag augmentation devices in drag as well as solar sailing mode. Provision of a software framework for verification of the GNC functional model.

Description:

While the concept of drag augmentation devices, such as deployable sails, as facilitator of end-of-life accelerated spacecraft deorbitation is attracting more and more interest, analysis has shown that drag sail effectiveness severely deteriorates in altitudes of 750km and above due to the extremely low atmospheric density. Also, as the NASA Nanosail-D mission illustrated, it is not trivial to avoid flat-spin of a sail. It is therefore instrumental for the attractiveness of drag augmentation devices to achieve attitude stabilization and in case of higher altitude orbits to operate the device as solar sail rather than drag sail, which requires active attitude control. The output of this activity shall allow to: • Evaluate technologies for attitude control by conventional means (e.g. magneto

torque generation) and unconventional means, such as sail charging for attitude control. Analysis software will be developed to assess controllability and effectiveness of sails in various AOCS modes.

• To carry out system design analysis performing a benefits trade-off for sail enlargement, geometric attitude stabilization, or integration of an active attitude control device to achieve satisfactory end-of-life deorbitation effectiveness of a drag augmentation device for different target spacecraft conditions.

• Design an AOCS architecture for attitude control in solar sailing and/or drag mode that improves system performance under consideration of CoG and CoP dependency and system impact (power, thermal and TMTC needs).

• Develop a GNC functional model that includes a Failure Detection, Insulation and Recovery (FDIR) as well as sail activation logic,

• Perform verification in a software environment, extending the capabilities of the analysis framework.

Deliverables: GNC functional model, software

Current TRL: 3 Target TRL: 5 Duration (months) 18

Applicable THAG Roadmap:

N/A

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Clean Space Branch Branch 3 - Space Debris Mitigation

Technology Domain 19 Propulsion

Ref. Number: G61C-017MP Budget (k€): 1,300 Title: De-orbit motor Engineering Model Manufacturing and Testing

Objectives:

To design and test 3 Engineering models of a de-orbit solid propellant rocket motor, based on propellant formulation from preceding activity. Note: the activity is also applicable to the space transportation domain for (autonomous) de-orbiting of upper stages.

Description:

Within the frame of Clean Space’s Branch 3 and in line with the requirements applicable to ESA Projects (formulated in ESA/ADMINIPOL(2008)2), controlled de-orbiting has been identified as an appropriate strategy to prevent the uncontrolled formation of debris. Current on-board propulsion systems in EO satellites do not have high enough thrust to de-orbit spacecraft swiftly and in a controlled manner. To this purpose, solid propellant motors meet the need for controlled de-orbiting of satellites to a pre-designated uninhabited area of the planet, such as e.g. south Pacific Ocean. Several studies (e.g. CDF) have been performed already regarding this topic and large experience exists in Europe already with solid propellants. Solid propellant motors have high impulse density and high thrust at low cost and have the possibility to be produced in series and assembled in clusters depending on the satellite mass. Moreover innovative TVC technologies can also be used for autonomous de-orbit systems in the future. The proposed activity is a follow-up of the activities for aluminium free propellants development and testing carried out within TRP and system studies for trading-off technologic solutions and designing a de-orbit system carried out in ESA’s CDF. The proposed work is therefore a Phase B of the de-orbit motors activity supported by the development of 3 Engineering Models and will include: 1. Consolidation of the (mission) requirements and product functional specification

(in close consultation with ESTEC), 2. Design of SRM based on the from previous activity determined Propellant

formulation and burn characteristics, 3. Testing of the SRMs (e.g. delivered thrust, specific impulse, regression rate,

chamber pressure, ignition train, thermal cycling, radiation exposure, ageing, etc.),

4. Design iterations, reporting and recommendations for following phases. The complete development roadmap including activities in TRP (400k€) and GSTP(~2,200k€) targeting a potential flight model will include: A) Testing and performance assessment of aluminium free solid propellant

(preceding activity), B) CDF study for system requirements definition, C) Design and 3 x Engineering Model motor manufacturing and testing to bring the

motor up to CDR level, D) Design iteration and 3 x Qualification Model motor manufacturing and testing to

achieve qualification level, E) Flight Model motor manufacturing and Implementation in spacecraft.

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Deliverables: Engineering Model

Current TRL: 5 Target TRL: 7 Duration (months) 15

Applicable THAG Roadmap:

Chemical Propulsion - Components (2012)

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Clean Space Branch Branch 3 - Space Debris Mitigation

Technology Domain 5 Space System Control

Ref. Number: G61C-018EC Budget (k€): 500 Title: Rapid Assessment of Design Impact on Debris Generation

Objectives:

Model enhancement and upgrade of a software framework for the early and rapid assessment of the impact that spacecraft design choices would have on the amount and characteristics of debris that is generated during spacecraft orbit decay for controlled as well as un-controlled reentry.

Description:

Successful design for debris mitigation (Design for Demise – D4D) heavily relies on the ability to analyse any spacecraft mission as well as the system design to high fidelity. The systems engineer needs to have the ability to rapidly analyse the impact that certain design choices will have on the risk to humans or assets on ground during spacecraft end-of-life reentry in the atmosphere. Thereto, it is imperative to have reliable, validated modelling capabilities for fragmentation and explosion events during atmospheric reentry and also for ablation effects. Such functions need to interface with an analysis environment, where robustness of the results can be assessed by means of, for instance, worst case identification or Monte Carlo simulation, which requires efficient algorithms that can rapidly be executed. Several software packages (e.g. SESAM, DRAMA, DARS, ASTOS) have been developed in the past for reentry simulation under consideration of ablation effects and present a suitable starting point for consecutive upgrade. In order to make them fit for rapid D4D assessment, the following work is required to arrive at a software framework for rapid assessment of design impact on debris generation: • Upgrade of explosion, fragmentation and ablation modelling algorithms where

needed, • Compilation and integration of Geographic Information System (GIS) data, air

and ship traffic models and human population models, • Interfacing with the dynamics analysis software ASTOS, • Augmentation of ASTOS functionality for assessment of mission or system

design impacts on risk to humans, ground infrastructure and assets, • Maturation of optimization techniques for D4D Worst Case Identification as well

as efficient Monte Carlo simulation within the software framework.

Deliverables: Software

Current TRL: 4 Target TRL: 5 Duration (months) 18

Applicable THAG Roadmap:

N/A

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Clean Space Branch Branch 3 - Space Debris Mitigation

Technology Domain 3 Spacecraft Electrical Power

Ref. Number: G61C-021EP Budget (k€): 400 Title: Spacecraft power system passivation at end of mission

Objectives: Study and implementation of the most adequate means to ensure a proper and reliable spacecraft power system passivation at end of mission.

Description:

The ESA Clean Space initiative is organised around four branches, one of them being the space debris mitigation branch, which includes the passivation of power systems. ESA/ADMIN-IPOL(2008)2, “Requirements on Space Debris Mitigation for Agency Projects” and France’s Space Operations Act&, affecting all the spacecraft launched from CSG, impose the elimination of all stored energy on board of a space system within two months after the end of the operational phase. Nowadays most spacecraft power systems cannot be completely passivated at EoL and this may cause unexpected spacecraft behaviours or even break-up, which can create debris in the space environment. The goal of the activity is to study and implement the most adequate means to achieve this power system passivation. This may involve the discharge and disconnection of the batteries and the disconnection of the solar arrays. This passivation needs to be reliable enough to avoid to deactivate the power system before the end of the mission. The proposed concept should be universal enough to be compatible with most space applications (but in priority European institutional market). This includes compatibility with requirements of most launch site authorities (e.g. for battery switch). The need of European standardisation of power system interfaces should also be considered. This 18-month activity will be organised as follows: 1. Study of the different possibilities and definition of a detailed specification. This

part requires a system level background. Deliverables: study report and specification (T0 + 4 months).

2. Implementation preliminary design. Deliverable: PDR data package (T0 + 8 months).

3. Implementation detailed design. Deliverable: CDR data package including detailed schematics and analyses (T0 + 12 months).

4. Realization and test of a breadboard or prototype validated in the relevant environment. Deliverables: breadboard/prototype and test report (T0 + 17 months).

5. Final conclusions. Deliverable: final report (T0 + 18 months).

Deliverables: Breadboard

Current TRL: 2 Target TRL: 5 Duration (months) 18

Applicable THAG Roadmap:

Power Management and Distribution (2008)

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Clean Space Branch Branch 3 - Space Debris Mitigation

Technology Domain 19 Propulsion

Ref. Number: G61C-022MP Budget (k€): 300 Title: Characterization of Ultrasonic Gauging Sensor for membrane tanks

Objectives:

The objective of this activity is to characterize the ultrasonic sensor, developed for Meteosat Second Generation, for propellant gauging in membrane tanks with main goal to improve the accuracy at End of Life when other gauging methods (bookeeping, PVT) typically exhibit large errors.

Description:

The accurate determination of the propellant residuals in the tank is of major importance for the nominal mission and completion of the EoL disposal manouvres for satellites. Presently the majority of the satellites uses the bookeeping and/or combination with PVT method to determine the propellant residuals. Anyway these methods are quite inaccurate close to the EoL because they are based on performance prediction models and indirect measurements. An alternative technique, recently applied on MSG, consists on the direct detection of the propellant liquid surface by use of ultrasonic sensors. Unfortunately, this technique is valid only when the liquid surface is well defined like the case of spinning spacecraft or membrane tanks. This activity proposes to extend the use of this type of sensors (successfully developed on the spinning spacecraft MSG) to membrane tanks, largely used for LEO/MEO applications. The motivation for this activity is driven by the fact that close to EOL the membrane exhibit a stable configuration making possible to determine its position/shape with the use of ultrasonic sensors and therefore compute the volume fraction occupied by the liquid propellant. The activity shall therefore be phased in the following steps: • Definition of reference application (tank size, configuration, EOL conditions,..), • Definition of gauging architecture (position, number of sensors, sensitivity,..), • Identification of a test tank, • Characterization test campaign with simulant, • Final reporting and recommendations.

Deliverables: Study Report

Current TRL: 2 Target TRL: 4 Duration (months) 15

Applicable THAG Roadmap:

Chemical Propulsion - Components (2012)

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Clean Space Branch Branch 3 - Space Debris Mitigation

Technology Domain 11 Space Debris

Ref. Number: G61C-024GR Budget (k€): 1,200 Title: Optical In-Situ Monitor

Objectives:

This activity aims at the design, development, breadboarding and laboratory testing of an optical in-situ debris monitor, to be flown on an (to-be-selected) Earth-oriented platform in sun-synchronous orbit. The goal is to achieve technological readiness of the instrument such, that engineering and flight models can be initialised as soon as a target platform is selected.

Description:

Today, there exist no technical means to collect measurements on man-made objects between 1mm and a few centimetres in the most critical altitudes around 800 and 1000km. In-situ impact detectors are too small to collect meaningful samples and terrestrial radars cannot detect objects of such size. The threat of objects in this size regime is, however, found critical for spacecraft, as impacts may cause critical damage to payloads or vital satellite components. Space debris models, which are used to estimate the vulnerability and survivability of spacecraft and protection shields, urgently require data for calibration in this regime. Optical sensors in the visible wavelengths on Earth-oriented platforms in sun-synchronous orbits are understood as best suited means to close this knowledge gap. A possible and promising mission concept would be to continuously observe in anti-sun direction, which ensures best illumination conditions. As past studies have shown, a large field-of-view of about 10deg diameter would allow collecting sufficiently large observation samples of objects > 1mm. A modest aperture of 10cm and above is required to meet the radiometric requirements. As a secondary payload such a fully passive and fix-mounted sensor would be fully compatible with the requirements of, e.g., an Earth-observation mission as primary payload. The major technological achievements to be reached in this area are: • Breadboarding of an optical instrument with an aperture >10cm and a FoV

about 10deg • Development of algorithms for on-board pre-processing for data reduction,

covering data handling, autonomous image segmentation and object detection, and, possibly, astrometric reduction

• Trade-off with accompanying active technologies like LIDAR for additional ranging information

• Trade-off with accompanying measurements in other wavelengths than visible, as, e.g., in the infrared domain, which could allow estimating the size of the particles via temperature equilibrium models

• Ground-testing and validation of such a sensor and the developed algorithms in a suitable test environment

Detailed break-down of the activity and associated TRLs: 1.) Sensor hardware (200 k€):

Optical design, optical bench, camera development, environmental tests; TRL: 3 Pre-cursor design studies carried out notably through ESA’s Space Debris

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Activities Activities during 2001-2003 and the General Studies Programme: “Space-Based Optical observation of space debris” (SBO), “Sensor Simulation for debris Detection” (PROOF) and “RObotic GEostationary orbit Restorer” (ROGER).

2.) Software (700 k€):

– Autonomous data processing system and software architectural design streak detection (can make use of experiments performed in a running TRP study entitled "streak detection"): TRL 2,

– Size/range/angular velocity processing: TRL 3, – Astrometric reduction: TRL 7, – False event detection and robustness: TRL 2, – Data reduction: TRL 3.

3.) Test environment and verification (300 k€):

– Generation of light streaks under pre-defined emulation of range, size and angular velocity,

– Emulation of continuous and discrete background sources, – Emulation of unwanted events (cosmics, pixel failures), – Tests and software hardening.

Deliverables: Breadboard

Current TRL: 2 Target TRL: 4 Duration (months) 24

Applicable THAG Roadmap:

On-Board Payload Data Processing (2011)

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7.4 19BBranch 4 (Technologies for Space Debris Remediation) Activities for 2013

Clean Space Branch Branch 4 - Technologies for Space Debris Remediation

Technology Domain 16 Optics

Ref. Number: G61C-028MM Budget (k€): 1,200

Title: Miniaturized Imaging LIDAR System (MILS) for Rendezvous & Docking operations between spacecrafts

Objectives:

Design, manufacture and test of a Miniaturized Imaging LIDAR System (MILS) elegant breadboard targeting the rendezvous & docking operation between two spacecrafts (like the ones foreseen in the CleanSpace cross-cutting initiative). The MILS elegant breadboard shall implement novel technologies, like for example CMOS detector arrays, in order to achieve a high level of compactness and low risk (preferably a flash-type LIDAR system without moving parts) while reducing substantially the mass and power consumption, when compared with traditional Imaging LIDAR systems. The test logic shall include the demonstration of the elegant breadboard operation and performance in a representative rendezvous & docking scenario, with cooperative as well as uncooperative targets, and under dynamic test conditions.

Description:

Imaging LIDARs (LIght Detection And Ranging) are considered a key enabling technology for future exploration missions and for operations involving the rendezvous between two spacecrafts in orbit (like the ones foreseen in the CleanSpace cross-cutting initiative). These missions include the need to perform autonomous guidance and navigation operations that require the use of very accurate and high resolution distance measurement systems. The Imaging LIDAR can provide to the chaser spacecraft the absolute distance and position of the target spacecraft, as well as its relative attitude during the final terminal phase of the rendezvous sequence. Typically the Imaging LDAR is designed to acquire the target spacecraft from ranges between 5km to 3km, inside a defined field of view, and it is able to track the target down to less than 1m, when the docking or capture of the target spacecraft takes place. Imaging LIDARs can be designed to operate with spacecrafts with or without cooperative targets. In the case of acquiring and tracking objects without cooperative targets the challenge is to maintain the Imaging LIDAR system mass and power consumption budgets within the acceptable levels for its use in a space-based platform, while maintaining the required operational range and accuracy performances. The background illumination, the target resolution and time operational constraints are no longer limiting factors as in the landing applications, so a full-flash system could be envisaged. Novel CMOS detectors, with high resolution pixel arrays, can be implemented using for example advanced photon counting techniques. The objective of the proposed activity is to design, test and manufacture a Miniaturized Imaging LIDAR System elegant breadboard implementing novel technologies, and focusing on the rendezvous & docking operation with

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cooperative as well as uncooperative targets. During this activity the following tasks shall be executed: • Design of a MILS (Miniaturized Imaging LIDAR System) elegant breadboard

implementing novel technologies in order to reduce mass and power consumption as much as possible,

• Manufacture the MILS elegant breadboard, • Test the MILS elegant breadboard taking into consideration the dynamic

conditions of the rendezvous operation.

Deliverables: Breadboard

Current TRL: 3 Target TRL: 5 Duration (months) 24

Applicable THAG Roadmap:

AOCS Sensors and Actuators (2009)

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Clean Space Branch Branch 4 - Technologies for Space Debris Remediation

Technology Domain 5 Space System Control

Ref. Number: G61C-029EC Budget (k€): 600 Title: Image Recognition and Processing for Navigation

Objectives: This activity will design, develop and verify the necessary capabilities in image processing for position, pose and angular motion detection on uncooperative targets in an Active Debris Removal scenario.

Description:

This activity comprises the development of image processing algorithms and their corresponding testing in open and closed loop inside a Simulator In the Loop (SIL). The activity includes image processing of the target satellite using photos and videos of a mock-up of the target is realistic conditions for all phases. The activity shall deliver the algorithm and software in a suitable form to be included in the simulator to be developed in the TRP activity "Advanced GNC for ADR" The image processing algorithms will be tested in the Processor In the Loop (PIL) environment and with Hardware in the Loop (HIL) in the rendezvous test facility. Hardware/Software co-design is required to optimise the overall design, since the algorithms to be developed are expected to be demanding in terms of RAM memory, CPU and data rates, calling for specific avionics architectures. In parallel to the sensors building blocks development, image processing algorithms relying on 2D, 3D or both information (hybrid mode) need to be developed. The development should also consider Image Processing techniques allowing to estimate relative pose and rotational state of uncooperative targets, with or without a priori 3D knowledge of the targeted debris, in complement or not of a 3D sensor. This activity also comprises the maturation of on board navigation processing technologies (SW, detector, etc;) based on lessons learned from past flight experience (ATV, PRISMA), and derived from latest technological improvements of STR technology (e.g. APS detectors). Another starting point could be the recent ITI "Multi-view 3D Reconstruction of Asteroid". The resulting software which, starting from a spherical model, uses multiple inputs from an orbiting 2D camera to reconstruct the actual model of an asteroid could be adapted to identified the shape of an unknown piece of debris when approached by the servicing spacecraft.

Deliverables: Software

Current TRL: 3 Target TRL: 6 Duration (months) 18

Applicable THAG Roadmap:

N/A

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Clean Space Branch Branch 4 - Technologies for Space Debris Remediation

Technology Domain 13 Automation, Telepresence & Robotics

Ref. Number: G61C-032MM Budget (k€): 700

Title: Harpoon characterisation, breadboarding and testing for Active Debris Removal (ADR)

Objectives:

Parametric characterisation of harpoon designs and harpoon launch strategies. The activity shall focus on the harpoon design implications of: 1) Capturing an uncooperative target without generating additional debris, 2) Guaranteeing that the attachment point can carry adequate dynamic load during

deorbitation.

Description:

Harpoons are a potential means for capturing large space debris. They intrinsically rely on 3 physical actions that are a concern for the conduct of a safe and clean grasping operation: 1) high energy impact on the debris, 2) piercing of structural elements of the debris and 3) pulling of debris on a single point. The first action can lead to high momentum exchange which can generate tumbling of the debris, the second action may lead to catastrophic damage of the structure of the debris or generation of secondary debris, the third action can lead to loss of the debris during towing. The subject activity addresses all these concerns through a programme of modeling, testing and analysis of the actions. Programme of work: 1) Elaborate detailed system requirements for the harpoon system with a focus on

the system being able to capture a range of uncooperative targets without generating additional debris (up to 1 millimetre size),

2) Development of a mathematical model of the harpoon-target interaction, accounting for all the various design parameters and environmental parameters affecting the system. The model shall include both the capture phase and the deorbitation phase, and shall model the amount and size of debris generated in both phases as a function of all the parameters,

3) Design of a test-campaign for harpooning a large and representative selection of debris types and materials, as well as a representative selection of harpoon designs to cover the necessary design space. The test campaign may include low-friction and/or parabolic flight testing,

4) Development of harpoon breadboards and test support equipment, 5) Carry out the test campaign and validate the mathematical model.

Deliverables: Breadboard

Current TRL: 2 Target TRL: 5 Duration (months) 24

Applicable THAG Roadmap:

Automation & Robotics (2012)

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Clean Space Branch Branch 4 - Technologies for Space Debris Remediation

Technology Domain 11 Space Debris

Ref. Number: G61C-034GR Budget (k€): 600 Title: Debris Attitude Motion Measurements and Modelling

Objectives:

This activity aims at the development of algorithms for the assessment of attitude states from terrestrial radar and optical data, the advancement of measurement techniques and the parallel development of 6 degree-of-freedom simulation of the attitude behaviour of complex bodies. The goal is to arrive at a setup that allows to predict (by simulation models), analyse and verify (by measurements) the attitude motion of uncontrolled, large complex bodies.

Description:

Today, there is little knowledge on the attitude state of decommissioned objects. Observational means have advance in the past years, but are still limited w.r.t. to an accurate estimate of motion vector orientations and magnitude. Such knowledge is absolute essential for the preparation of a removal mission, since attitude motions above a few degree per second will not allow to use classical robotic capture mechanisms anymore. Hence, the attitude state of the target is a significant criterion for the selection of removal techniques. The reason for tumbling motions of uncontrolled objects are twofold: firstly, a mismatch between the barycentre of the projected surface in flight direction (relevant for drag) from the centre of mass will cause a momentum. Secondly, internal components like reaction wheels and gyros or rotating disks might transfer momentum to the satellite body. Observations in the past (e.g. with the FHR TIRA radar applying SAR techniques) have mainly concentrated on objects which were about to undergo an uncontrolled re-entry in the following days (UARS, Phobos-Grunt). In a few cases attitude rates of about 10 deg/s have been estimated. The altitudes observed and geometries of the bodies are, however, not representative for the envisaged removal targets. Generation of so-called light curves (i.e. evolution of the brightness of space objects in the visible region) with the help of optical telescopes (ZIMLAT, OGS) is a second promising measure to estimate attitude rates of targets in higher altitudes. Further laser ranging could be a promising means to identify varying offset of a reflective surface from the centre of mass of the parent body. In all cases, techniques need to be required to improve the resolution of the data and to fit geometric models into the measurements for an estimation of the attitude and to compensate aspect angle motions. In order to understand the effects that cause the attitude motion, simulation models are required. These models will have to accurately represent the spacecrafts geometry and moments of inertia as well as internal moving parts for a 6 degree of freedom numerical propagation to analyse the expected attitude evolution in preparation and in comparison to observational results. The ultimate goal of this activity is accomplish the above mentioned technology and to apply it on selected candidate targets to provide a representative data set as input for the selection of removal technologies. The technology will also be a valuable help for the analysis of spacecraft contingency where the identifaction of the attitude motion is key element in the process. The major technological achievements to be reached are: • Advancement of radar and optical measurements (including Laser Ranging) for

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the sensing of spacecraft attitude states (SAR and light curves) in terms of temporal and geometric resolution as well as noise reduction,

• Advancement of algorithms and techniques to fit geometric models into the data to result at an increased accuracy in the domain of <1deg/s in estimating the attitude rate and <1deg in estimating the orientation of the motion vector,

• Development of 6 degree of freedom simulators and spacecraft geometry models also reflecting internal moving parts to predict attitude state evolution by building on existing technologies (ANGARA, Scarab),

• Application of the techniques to provide a first representative screening of the attitude motion of selected removal targets in the respective altitudes.

Detailed break-down of the activity and associated TRLs: 1.) Measurements 250 k€

SLR measurements and processing: TRL 5, 50 k€, Optical measurements (light-curve, imaging) and processing: TRL 6, 100 k€, Radar imaging measurements and processing: TRL 7, 100 k€.

2.) Modelling (ca. 300 k€, to be carried out by the entity that performed

measurements) Attitude modelling (Angara): TRL 8, Modelling light curve measurement: TRL 4, Modelling SLR returns: TRL 4, Modelling synthetic radar images: TRL 4.

3.) Pattern matching algorithms 50 k€, TRL 2-3.

Deliverables: Other: Measurements, Survey data, motion results, softwar

Current TRL: 6 Target TRL: 8 Duration (months) 24

Applicable THAG Roadmap:

N/A

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8 7BLIST OF ACTIVITIES FOR 2014

GSTP-6

Reference Title Budget(k€)

Branch 1: Eco-design

G61C-003MP Hot gas plume characterisation in vacuum 500

Branch 1 total 500 Branch 2: Green Technologies

G61C-004MP MON/MMH replacement with green bi-propellant - Phase 1 750

G61C-006MP Key propulsion system hardware development/requal - Phase 1 500

G61C-008QT Verification methodology for parts made by Additive Manufacturing 500

G61C-036QT Development and test of Additive Manufactured space hardware 1,300

G61C-009QT Qualification of green cleaning processes 300

G61C-012MS Bio-composite structure in space applications 500

G61C-013QT Novel energy efficient processes for thermoplastic composite manufacturing 500

G61C-035QT Alodine 1200 replacement testing and qualification 400

Branch 2 total 4,750 Branch 3: Space Debris Mitigation

G61C-020MP Development of a non-pyrotechnic passivation valve 600

G61C-023MP Enhancement of Passivation Techniques for Current and Future Missions 800

G61C-025GR Enhancement of S/C Fragmentation and Environmental Evolution Models 300

Branch 3 total 1,700 Branch 4: Technologies for Space Debris Remediation

G61C-026SY Phase B1 of an Active Debris Removal mission (2 parallel studies) 1,600

G61C-027EC Infrared Camera BreadBoard for Rendezvous with Non-cooperative Target

800

G61C-030MM Net-Winch-Tether design and breadboard development 450

G61C-031MS Breadboard development of the throw-net ejector mechanism 400

G61C-033MS Breadboard of a clamping based capture mechanism 450

Branch 4 total 3,700

Total 10,650

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9 8BDESCRIPTION OF ACTIVITIES FOR 2014

9.1 20BBranch 1 (Eco-design) Activities for 2014

Clean Space Branch Branch 1 - Eco-design

Technology Domain 18 Aerothermodynamics

Ref. Number: G61C-003MP Budget (k€): 500 Title: Hot gas plume characterisation in vacuum

Objectives: The objective of the present study is a detailed experimental characterisation of mono- and bi-propellant hot gas plumes in low density and near vacuum conditions.

Description:

Existing data for low-Newton thrusters typically associated with low-density applications has been collected for cold gas thrusters, however, since in this case the plume is single species, the important features associated with multiple gas interactions in expanding rarefied plumes has not yet been measured (the expansion angle of low density gases exceeds that of high density gases). Current numerical tools such as DSMC (Direct Simulation Monte Carlo) urgently require validation if they are to be used to predict performance and mission requirements for ESA missions. Experimental characterisation of plumes is required for determination of: a) Contamination of solar panels, optical sensors etc. (satellite), b) Parasitic force and torque measurements (all satellite and craft).

Deliverables: Study Report

Current TRL: 3 Target TRL: 6 Duration (months) 12

Applicable THAG Roadmap:

Aerothermodynamic Tools (2012)

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9.2 21BBranch 2 (Green Technologies) Activities for 2014

Clean Space Branch Branch 2 - Green Technologies

Technology Domain 19 Propulsion

Ref. Number: G61C-004MP Budget (k€): 750 Title: MON/MMH replacement with green bi-propellant – Phase 1

Objectives: The primary objective is to identify a low toxicity (green) bipropellant fuel/oxidiser pair able to demonstrate comparable performance to the currently used MON/MMH.

Description:

Since the 1960s the large majority of space bi-propellant systems have used MON/NTO as an oxidiser and MMH/UDMH as a fuel. The toxicity level of these propellants has demanded special measures to reduce safety risks (e.g. SCAPE suits, limited testing with propellants, extra mechanical barriers, restriction on air transport, etc.). These measures can have significant impact to cost and schedule for ground operations. The propulsion industry has been investigating lower toxicity (green) propellant options to address this problem. In 2011, Europe's Registration Evaluation Authorisation and Restriction of Chemicals (REACH) added hydrazine to their candidate list of substances of very high concern (SVHC), due to its toxicity. With this step, there is an associated risk that REACH will make hydrazine obsolescent (restrict or prohibit its use) in the near to mid-term. This risk also exists for hydrazine derivatives like MMH or UDMH and, to a lesser extent, Nitrogen Tetroxide (or MON). The SVHC list is updated on a regular basis (i.e. two times per year). This risk places further and more immediate emphasis on the need for green bi-propellant alternatives. Currently in Europe, several entities have initiated activities to develop green bipropellant combinations to replace MON/MMH. However, the level of maturity is lower when compared to green monopropellant technologies. The 2012 European Technology Harmonisation Chemical Propulsion - Green Propulsion roadmap includes activity B1 - MON/MMH Replacement with Green Bi-propellant. This activity extends to TRL 6 with a total budget of 4 M Euros. This proposal addresses phase 1 of this activity. Phase 1 will evaluate green bipropellant combination concepts for space applications which are able to operate in pulse and steady-state mode with performances comparable to MON/MMH. More specifically, the activity shall include: – Identification of green bi-propellants, – Proof of concept of the working principle with chemical lab scale testing, – A preliminary material compatibility screening, – Propellant characterisation (e.g. physical properties, toxicity, safety).

Deliverables: Study Report

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Current TRL: 1 Target TRL: 3 Duration (months) 24

Applicable THAG Roadmap:

Chemical Propulsion - Green Propulsion (2012)

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Clean Space Branch Branch 2 - Green Technologies

Technology Domain 19 Propulsion

Ref. Number: G61C-006MP Budget (k€): 500 Title: Key propulsion system hardware development/requal – Phase 1

Objectives:

The primary objective is to achieve qualification of key propulsion system equipment for use with green mono-propellants. Phase 1 of this activity addresses the propulsion system equipment that does not require further design modification/development for use with LMP-103S.

Description:

In 2011, Europe's Registration Evaluation Authorisation and Restriction of Chemicals (REACH) added hydrazine to their candidate list of substances of very high concern. With this step, there is an associated risk that REACH will make hydrazine obsolescent (restrict or prohibit its use) in the near to mid term. While ESA is pursuing possible exemptions for hydrazine for space applications, additional risk mitigation is necessary. This additional mitigation includes development of green propulsion as a replacement for hydrazine and other high toxicity propellants along with the associated hardware. Currently in Europe, the most mature propellant option as a hydrazine replacement is ECAPS' LMP-103S (ammonium dinitramide based monopropellant). Under the GSTP 3/4 Development of Green Propulsion for Spacecraft activity, a 1N thruster for use with LMP-103S has been developed to CDR. Funding for follow on development of the 1N thruster into the qualification phase has been approved. Also, an activity proposal for qualification of LMP-103S propellant has been submitted. There are currently programs interested in this propellant and associated hardware (e.g. Myriad Evolution). One of the next steps is to ensure that propulsion system hardware is qualified for use with LMP-103S. This is a requisite step to allow use of this green propellant for space applications. The 2012 European Technology Harmonisation Chemical Propulsion - Green Propulsion roadmap includes activity E3 - Key Propulsion System Hardware Development/requal. This activity extends to TRL 6 with a total budget of 5 M Euros. The current proposal addresses phase 1 of this activity. The intent of harmonisation activity E3 is to ensure that propulsion system hardware (in addition to the thruster) is qualified for use with LMP-103S. The proposed phase 1 targets only the propulsion system hardware (equipment) that does not require design modification/development and is foreseen to be used with LMP-103S in the near to mid term. A separate roadmap activity, E2 - LMP-103S System/Component Qualification Needs Evaluation, will determine which hardware requires design modification/development. The design modification/development tasks would then be performed in phase 2 of activity E3. UNoteU: based on development activity to date, it is expected that LMP-103S is materially and functionally compatible with most propulsion equipment. Thus, the development needs are thought to be minimal; which must however be verified in roadmap activity E2. It is foreseen that the currently proposed phase 1 activity would overlap the E2 activity. As modifications are deemed unnecessary on particular equipment, this equipment's qualification for use with LMP-103S can be addressed.

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Primary tasks of the phase 1 activity include the following: – Contractor to review results of activity E2 tasks and provide results to equipment

suppliers, – Equipment suppliers to evaluate results, – Perform EQSR for each piece of equipment regarding its use with LMP-103S, – Any Hardware that does not pass the equipment supplier's review or the EQSR

would be deferred to phase 2.

Deliverables: Equipment qualification documentation

Current TRL: 4 Target TRL: 6 Duration (months) 8

Applicable THAG Roadmap:

Chemical Propulsion - Green Propulsion (2012)

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Clean Space Branch Branch 2 - Green Technologies

Technology Domain 24 Materials and Processes

Ref. Number: G61C-008QT Budget (k€): 500 Title: Verification methodology for parts made by Additive Manufacturing.

Objectives:

The objective of the study is to establish a mapping of the most relevant methods to ensure that a part made by AM can be used for the intended application. As AM technologies produce parts having local properties variation, the verification shall combine local and global verification approaches.

Description:

Items with several different geometrical features will be produced e.g. thin and thick sections, buried cavities, trabecular structures; including items containing defects generated on purpose. The capability to detect defaults using conventional NDI techniques will be investigated on as processed items and, when feasible, repeated on the same items after surface finishing. In addition, mechanical tests will be performed on samples containing defects to quantify knock-down factors and physical destructive analysis will be performed to correlate the population of defects detected on as processed and on finished items with the mechanical characteristics. Guidelines will be proposed for verification methods of ALM manufactured items.

Deliverables: Study Report

Current TRL: 3 Target TRL: 5 Duration (months) 24

Applicable THAG Roadmap:

N/A

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Clean Space Branch Branch 2 - Green Technologies

Technology Domain 24 Materials and Processes

Ref. Number: G61C-036QT Budget (k€): 1,300 Title: Development and test of Additive Manufactured space hardware

Objectives:

This activity aims to demonstrate the gain in performances brought by using the geometrical freedom of Additive Manufacturing and increase the maturity of S/C hardware produced with AM. The main objectives of the activity are: • Re-assess and optimise the design S/C hardware (e.g. antenna, thrusters, etc.)

making use to the full extent of the design freedom provided by AM. The designs should be evaluated in terms of mass, interfaces, environmental impact and cost.

• Manufacture and test at least 2 of these parts. The requirements driving the application shall be critically reviewed and elegant breadboards answering these needs will be manufactured, controlled and tested.

Description:

The limits of the design freedom brought by the use of additive manufacturing (AM) technologies is today not established, even if it is considered tremendous; The benefit brought by using different features shall be better estimated to help the designers. Among the possibilities, topographic optimisation can significantly reduce the mass of hardware (many tens%), suppressing interfaces leads to significant mass savings, integrating several functions can allow new applications and limit controls and verifications. The benefits brought by any of the above (including environmental related) is today not quantified and the overall impact on cost is to be established. A design approach addressing to the full extent the features that allowed by AM from manufacturing viewpoint is paramount. This can be initiated by using a number of selected study cases. This activity will: 1. Based on a preliminary redesign and system level impact assessment

spacecraft parts will be ranked with respect to the potential benefits brought by using Additive manufacturing technologies.

2. At least two of these parts will selected based on this ranking and “end to end manufacturing strategies" for the development of the respective elegant breadboards up to BDR. The manufacturing strategy shall include at least the means to test the materials, verify the soundness of the process, define ancillary processes and NDI methods for the part.

3. Evaluate the validity of the concepts presented at BDR and assess design variations will be implemented to increase their specific performances The detailed design of at least two elegant breadboards will be matured up to CDR.

4. Manufacture of the elegant breadboards, implementation of the in-process verification methodology characterisations. The performances of the breadboards will be compared to the expected performances. An environmental and economic evaluation will be conducted and AM design guidelines will be derived.

UNoteU: tests will depend on selected parts. e.g. for antenna component AM process verification could include: mechanical test, validation of thermal treatment, assessment of surface finish, verification of coating process, NDI and metrology,

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destructive analysis, validation of assembly, thermal vacuum tests, vibration.

Deliverables: Technical Notes, Test plans & Test reports. Design, manufacturing and testing of breadboards.

Current TRL: 3 Target TRL: 5 Duration (months) 30

Applicable THAG Roadmap:

N/A

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Clean Space Branch Branch 2 - Green Technologies

Technology Domain 24 Materials and Processes

Ref. Number: G61C-009QT Budget (k€): 300 Title: Qualification of green cleaning processes

Objectives:

The objective of this activity is the validation of green cleaning processes to replace solvents that have ozone depleting potential or are facing obsolescence by national or international environmental legislation.

Description:

Task 1: Target selection of the cleaning process and requirement definition. Task 2: Revision of alternative cleaning processes including the use of alternative

organic solvents, aqueous solvents, and solvent less processes such as hot purge, plasma, blasting, etc.

Task 3: Trade-off, and preliminary performance testing of short-listed cleaning processes.

Task 4: Full validation/qualification of best performing cleaning process.

Deliverables: Study Report

Current TRL: 4 Target TRL: 5 Duration (months) 18

Applicable THAG Roadmap:

N/A

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Clean Space Branch Branch 2 - Green Technologies

Technology Domain 20 Structures & Pyrotechnics

Ref. Number: G61C-012MS Budget (k€): 500 Title: Bio-composite structure in space applications

Objectives:

In the last years, the development of bio-composite materials has increased and many application consider these environment friendly composite materials. However, there is no development at the moment in the space domain. Since it is explicitly in the interest of ESA to limit the environmental footprint, this family of materials should be investigated and a range of potential applications should be established

Description:

The following tasks shall be performed: • State-of-the-art review. • Investigation of application range with selection of demonstrator space structure

application. The investigation shall cover launch and space environment requirements including temperatures, radiation and mechanical loads for different types of space structure applications. A screening of typical space structures and their typical features (interfaces, load levels) shall be presented.

• Material trade-off shall be performed supported by material test programme where candidate material systems are screened. The results shall be presented as direct comparisons to existing composite materials.

• Manufacturing trials shall be performed and prototypes shall be subjected to breadboard tests for mechanical loads and/or environment.

• A demonstrator structure shall be designed and manufactured targeting a specific space structure application. The demonstrator structure can be a sub-scale model or a part of a larger structure. Demonstration test campaign shall be performed on the demonstrator structure and test evaluation shall be presented with compliance status to the requirements of the target application.

• A development plan shall be established covering foreseen efforts to achieve TRL 6 in potential future ESA studies for bio-composites. The development plan shall also describe the possible application range for current state-of-the-art bio-composites in space structures applications.

• An evaluation of the environmental benefits for bio-composites for the selected space structure application shall be performed and reported.

Deliverables: Breadboard

Current TRL: 2 Target TRL: 4 Duration (months) 24

Applicable THAG Roadmap:

Composite Materials (2005)

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Clean Space Branch Branch 2 - Green Technologies

Technology Domain 24 Materials and Processes

Ref. Number: G61C-013QT Budget (k€): 500 Title: Novel energy efficient processes for thermoplastic composite manufacturing

Objectives: The objective of the activity is to develop processes for manufacturing thermoplastic composite parts for satellites with a greener technology and associated cost saving.

Description:

The aim is to investigate and develop the use of thermoplastic composites and processing techniques towards demonstrating a significant reduction in the productions environmental footprint for composite parts. The principle is to design and manufacture a standard structural element for use in a typical space application whilst considering the impact of the entire end-to-end lifetime and process for production of the composite part. Analysis is to specifically include a comparison with conventional techniques (i.e. thermosetting composites) with an evaluation of the mechanical performances which can be achieved, the use or non-use of VOCs or other hazardous materials, the energy inputs required to manufacture and the capability for recycling of scrap materials. All of this data is to be used to derive a trade-off analysis of compromises in performance (if applicable) compared to an improved green rating for the end-to-end process. Thermoplastic Composites Manufacturing has an existing application potential in manufacturing structural elements (panels, frame), complex shapes and tanks. In addition the use of thermoplastic composites has found increasing popularity in non-space applications (especially automotive, aerospace and power generation). Their attraction arises due to the easier (and potentially lower cost) manufacturing processes, capability to obtain complex shapes, the materials weldability, improved material toughness (wrt thermoset materials), essential absence of shelf life of the resin and the greener nature of the processes (Low VOC release, recyclability etc.). This activity is to establish the feasibility of manufacturing a standard structural element and, from this production quantitatively assess the relative merits in terms of greener production. The greener benefits are to be evaluated and traded-off against any performance limitations. As part of this activity the investigation should consider improvements, adoption and development of existing thermoplastic technology for use in production of space hardware. Besides, the developed part should be assigned a green rating, based upon a scale developed within the activity and applicable to the manufacture of other hardware.

Deliverables: Breadboard

Current TRL: 3 Target TRL: 5 Duration (months) 24

Applicable THAG Roadmap:

N/A

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Clean Space Branch Branch 2 - Green Technologies

Technology Domain 24 Materials and Processes

Ref. Number: G61C-035QT Budget (k€): 400 Title: Alodine 1200 replacement testing and qualification

Objectives: Find alternatives and qualify replacements for chromates covering future obsolescence by REACH

Description:

The objective of the present study is to identify and qualify surface treatments exempt of hexavalent chromium to specific requirements of space applications. Space industrials are actually under derogation for using Cr VI processes. In order to be compliant with REACH and RoHS directives, as well as requirements for future projects, there is a need to qualify new processes for space applications. Some development work has already been done, especially for aeronautic applications, where preliminary evaluations have been performed. The acquired experience of these working groups can allow identifying promising candidates for space industries. The present study consists in identifying available processes with a level of maturity that allows reproducibility of the process and to qualify these surface treatments to space industry specific constraints. The activity will consist in characterizing candidate materials to the specific constraints of space applications (vacuum, thermal cycling): • Manage the procurement of samples and BOL characterisations, • Manage test campaign (ground and flight simulation): this activity will include

UV, radiation and ATOX testing in order to qualify a use of these materials on external surfaces for both GEO and LEO applications,

• Characterize EOL properties (adherence, electrical properties, thermo-optical), • Perform the synthesis of results and conclusion on qualification status.

Deliverables: Study Report

Current TRL: 3 Target TRL: 6 Duration (months) 18

Applicable THAG Roadmap:

N/A

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9.3 22BBranch 3 (Space Debris Mitigation) Activities for 2014

Clean Space Branch Branch 3 - Space Debris Mitigation

Technology Domain 19 Propulsion

Ref. Number: G61C-020MP Budget (k€): 600 Title: Development of a non-pyrotechnic passivation valve

Objectives:

The objective of this activity is to develop a non-pyrotechnic valve to be used for passivation of propulsion sub-systems at End Of Life and compatible with a long term exposure to Space Environment.

Description:

The passivation of propulsion sub-systems including the pressurant and propellant compartment is required by the ESA ADMIN/IPOL(2008)2 and France’s Space Operations Act, applicable to all spacecrafts launched from CSG. This is considered to be a major requirement for Space Debris Mitigation. Several ESA programmes are presently taking into account this requirement in the definition of the propulsion sub-systems for LEO, MEO and GEO missions. For LEO/MEO applications, using typically blow-down systems with membrane tanks, the passivation of the propellant is performed by EOL manouvres trying to minimize the residuals and leaving a final pressure on the order of 5 bar. For GEO missions using pressure regulated systems, the pressurant compartment is vented just after the GTO transfer by a pyrovalve and the propellant at End Of Life after graveyarding by dedicated thruster firing. Anyway for all these cases, the final results is not completely satisfactory because residual energy is still left in the systems and for the GEO case the passivation of the gas side is conducted after LEOP (Launch and Early Operations), introducing an additional risk for the operational life of the Spacecraft. The development of a device overcoming the life limitations of the pyrotechnic devices would therefore guarantee a safer and better passivation of the propulsion sub-systems significantly reducing the risk of explosions due to collisions. The non-pyrotechnic passivation valve shall therefore be designed with the following drivers: – Use of a non-pyrotechnic actuator, – Presence of sufficient barriers in non-activated mode, – Compatibility with propellants and pressurant on board of the Spacecraft, – Compatibility with long term exposure to the Space Environment (>20 years,

GEO missions worst case), – Reversibility of its state after actuation. The proposed activity shall comprise the following steps: • Definition of the concept and requirements (SRR), • Breadboards/Proof of concept tests, • Preliminary Design (PDR), • Development and Testing of a Engineering Model, • Critical Design Review (CDR).

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Deliverables: Engineering Model

Current TRL: 1 Target TRL: 5 Duration (months) 15

Applicable THAG Roadmap:

Chemical Propulsion - Components (2012)

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Clean Space Branch Branch 3 - Space Debris Mitigation

Technology Domain 19 Propulsion

Ref. Number: G61C-023MP Budget (k€): 800 Title: Enhancement of Passivation Techniques for Current and Future Missions

Objectives:

This activity aims at the establishment of the key technical figures and processes required to conduct in a reliable way passivation of the propulsion system of running and future ESA missions. The goal is to have implemented, tested, validated, and operated concepts for these ESA missions (not having been designed for all passivation measures) to allow for the best possible degree of passivation, as well as to set-up recommendations for future ones.

Description:

Current debris mitigation requirements specify the need to passivate the spacecraft at the end-of mission, see ADMIN/IPOL/(2008)2. Missions that are currently under operation are not designed to fulfil these requirements, but the operation teams should strive to do its best to comply to the maximum degree. It implies many difficulties on the operation which typically are solved by the operation team on a case by case basis. The only design measure for passivation of the spacecraft residual propellant is currently to conduct depletion burns. This phase is particularly critical for bi-propellant sub-systems. Indeed close to the tank depletion, the thrusters may start to operate, at very low pressure, with highly deviated mixture ratio and helium bubbles in the feeding lines with resulting unstable thrust and unbalanced conditions in the different branches. As a consequence, the spacecraft attitude might be lost and the remaining passivation measures, such as battery disconnection, transmitter shut-off, etc., cannot be completed. Finally, stable criteria to judge on achieving sufficient depletion are lacking today. This activity’s major goal is consequently to deliver methods and concepts that solve these problems through dedicated studies at system level and on-ground testing of thrusters. The activity shall comprise the following steps: • Analysis and evaluation of criteria for the successful and operationally safe

depletion of propellant tanks by performing depletion burning,, • Definition of operating requirement of thrusters during passivation both mono

and bi-propellant, • Definition of gaps in thrusters test heritage and new test requirements, • Test characterization of thrusters in passivation modes, • Synthesis of test results and review of strategies for propellant passivation, • Identification of remnant energy sources on-board of running missions and

procedures for their passivation and quantification of the remaining break-up probability.

Deliverables: Study Report

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Current TRL: 3 Target TRL: 6 Duration (months) 18

Applicable THAG Roadmap:

Chemical Propulsion - Components (2012)

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Clean Space Branch Branch 3 - Space Debris Mitigation

Technology Domain 11 Space Debris

Ref. Number: G61C-025GR Budget (k€): 300 Title: Enhancement of S/C Fragmentation and Environmental Evolution Models

Objectives:

This activity aims at the advancement of environment status and prediction models, to be used for the impact risk assessment in spacecraft design and for the analysis of the efficiency of mitigation and remediation measures. The goal is to arrive at operational implementations that incorporate the latest and best knowledge on the environment, highest accuracy long-term propagation in order to assist spacecraft developers in their risk assessment, as well as stakeholders in identifying and negotiating mitigation and remediation measures on multinational level.

Description:

Environment prediction models (like MASTER) are by no means static and require continuous improvements to keep the pace with an ever-changing highly dynamic space debris environment. New types of measurements (as, e.g., from potential in-situ sensors), newly discovered debris sources (as the release of MLI foils), and additional severe debris generating events (like the Chinese ASAT test of January 2007 and the Iridium-33/Cosmos-2251 collision in 2009) need to be reflected. These models are essential for the analysis of the impact risk on spacecraft, design of shields and vulnerability assessments. They also form the baseline for environment prediction models (like DELTA, Damage, SDM, LUCA), which make use of launch traffic models and collision risk assessment to predict long-term trends and collision rates in the environment. Such tools allow to simulate the application of various mitigation measures and the level of fulfilment of such measures. They will return the environmental trend in response to the measures applied. Such models also allow to simulate various active removal scenarios and allow to identify the most efficient approaches. These models heavily rely on assumptions for the energy levels required to break-up spacecraft, fragmentation models and accurate long-term simulators. The major technological achievements to be reached in this area are: • Refinement of existing models for lately discovered events and sources

(collisions and MLI release) on the basis of measurement data from in-situ sensors and terrestrial sensors (OGS, TIRA, EISCAT),

• Research and development in the area of collisional break-up monitoring oriented towards the Iridium/Cosmos and Fengyun-1C examples,

• Accompanying hypervelocity impacts experiments near the critical energy-to-mass ration, shallow impact angles,

• Improvement of semi-analytical, fast and accurate long-term propagators along with a reasonable handling of non-conservative perturbations, such as atmospheric drag and solar pressure for a wide range of area-to-mass ratios,

• Establishment of traceable criteria for the initiation of catastrophic collisions.

Deliverables: Software

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Current TRL: 6 Target TRL: 9 Duration (months) 15

Applicable THAG Roadmap:

Thermal & Space Environment S/W Tools (2002)

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9.4 23BBranch 4 Description of Activities for 2014

Clean Space Branch Branch 4 - Technologies for Space Debris Remediation

Technology Domain 11 Space Debris

Ref. Number: G61C-026SY Budget (k€): 1,600 Title: Phase B1 of an Active Debris Removal mission (2 parallel studies)

Objectives: Mature the design of an Active Debris Removal mission to B1 level and obtain a successful System Requirements Review.

Description:

Following the assessment study of the "Service Oriented aproach to the procurement/development of an Active Debris Removal mission" in early 2013, and the phase A study of the Active Debris Removal mission in end 2013, the phase B1 of this mission shall start at end 2014. The mission targets removing a high-mass ESA owned debris object from space by performing a controlled re-entry complying to the ECSS-U-AS-10 standards on space sustainability. The budget should allow for two parallel B1 studies.

Deliverables: Study Report

Current TRL: 2 Target TRL: 6 Duration (months) 5

Applicable THAG Roadmap:

N/A

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Clean Space Branch Branch 4 - Technologies for Space Debris Remediation

Technology Domain 5 Space System Control

Ref. Number: G61C-027EC Budget (k€): 800 Title: Infrared Camera BreadBoard for Rendezvous with Non-cooperative Target

Objectives: The objective of this activity is to develop an Engineering Model (EM) of an Infrared (IR) camera for relative navigation.

Description:

Active satellite removal needs accurate relative navigation that can be provided using vision-based (far range) or LIDAR-based (short range) sensors. The drawback of this approach is that a vision-based sensor is dependent on good lightning conditions (for example, rendezvous in eclipse is not possible). LIDAR-based navigation is only possible at short distances due to power limitations and for limited periods of time. Infrared-based relative navigation is less dependent on illumination conditions and power limitation. An IR-based system can be active during the complete rendezvous sequence, including fly-around, close approach and mating with the target. The activity shall develop an IR camera breadboard to cover the relative navigation during the complete rendezvous sequence, from early detection on very long range until capture and mating. The main objectives shall be: • To gather mission requirements from the approved TRP activity "Advanced

GNC for ARD" and derive from these the GNC and camera requirements, • To derive both the characteristics and specifications of the IR camera, • To create a software model of the camera and integrate it in a close-loop

simulation of the rendezvous, with high-fidelity models of the environment, • To run simulation campaigns and use the results to evaluate the performance

specifications of the IR camera, • To provide inputs to the image processing part of the proposed GSTP activity

G61C-029EC " Image Recognition and Processing for Navigation", • To develop a breadboard up to the level of engineering model of the camera.

The camera shall be composed at least of the optics, the thermal imager and detector, and the IPB (Image Processing Board) with the corresponding I/O interfaces.

The IR breadboard is intended to allow for field tests (either on static benches or dynamic tests on-board helicopters or dedicated demonstrators). The IR Breadboard will have representative SpaceWire, ethernet interfaces to from the IPB, and will be built as a stand-alone experiment (including: self-synchronisation of acquired images, robust data storage capacity, ruggedized experiment computer which can be embarked for field tests, and which can interface with external sensors). Specific tasks shall include: • Image Processing Board refined specification for the needs of rendezvous with

Non-cooperative Target, • VHDL code development (in line with selected FPGA) / co-processor code

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development (DSP, powerPC), • VHDL/co-processor code integration on IPB and integration tests, • IR breadboard design, manufacturing, and validation on representative

environment (e.g. TEC EC lab), • IPB development (detailed design, PCB realization and unit testing), • Performance assessment of selected detector.

Deliverables: Engineering Model

Current TRL: 2 Target TRL: 4 Duration (months) 24

Applicable THAG Roadmap:

N/A

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Clean Space Branch Branch 4 - Technologies for Space Debris Remediation

Technology Domain 13 Automation, Telepresence & Robotics

Ref. Number: G61C-030MM Budget (k€): 450 Title: Net-Winch-Tether design and breadboard development

Objectives:

This activity aims at bringing together the knowledge acquired in modelling net and winch into one single system in which all subsystem and phases of the net system can be tested.

Description:

The whole net system shall be designed and modelled into a software simulator covering the complete operation of the net. Following the confirmation of the design, breadboards of the net, of the net ejection system, of the winch and possibly net closure, shall be realised according to the design. These shall be tested in order to confirm their performance in the most appropriate environment

Deliverables: Breadboard

Current TRL: 3 Target TRL: 5 Duration (months) 12

Applicable THAG Roadmap:

Automation & Robotics (2012)

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Clean Space Branch Branch 4 - Technologies for Space Debris Remediation

Technology Domain 15 Mechanisms & Tribology

Ref. Number: G61C-031MS Budget (k€): 400 Title: Breadboard development of the throw-net ejector mechanism

Objectives: The objective of this activity is to develop, manufacture and test an Engineering Breadboard model (TRL4-5) of a Net Ejection Mechanism, for capturing space debris.

Description:

The activity main tasks will consist in: • Based on the output of the Parabolic Flight Net deployment characterisation

testing activity, a set of requirements will be established for the net ejection mechanism,

• The contractor will then perform a concept trade-off leading to a preferred preliminary design,

• Simplified BB models shall be manufactured to provide an initial justification of the preliminary design. The design will then be consolidated based on these initial tests,

• An engineering breadboard model will then be manufactured and functionally tested using representative dummy masses to simulate the net. Environmental tests (vibration, temperature, vacuum) will also be performed to verify the design,

• The EBB will then be delivered to the contractors undertaking a Detailed design of net and winch activity, whereby the mechanism shall be tested with a representative net and tether, in a representative environment,

• The output of this activity would be used as input to a Detailed net ejector design and qualification activity aimed at developing, manufacturing and testing a Qualification model (TRL6) of a Net Ejection Mechanism.

Deliverables: Breadboard

Current TRL: 3 Target TRL: 5 Duration (months) 14

Applicable THAG Roadmap:

N/A

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Clean Space Branch Branch 4 - Technologies for Space Debris Remediation

Technology Domain 15 Mechanisms & Tribology

Ref. Number: G61C-033MS Budget (k€): 450 Title: Breadboard of a clamping based capture mechanism

Objectives: The objective is to produce the breadboard of a clamping based capture mechanism (starting from a PDR definition), with the aim to perform its functional test.

Description:

The clamping based capture mechanism will be breadboarded (starting from a PDR definition) with the aim to functionally test the following aspects: • Vibration tests in the stowed configuration, • Deployment of the capture mechanism, • Capture scenario in a set of predefined relative positions between the chaser

and the target, • Assessment of the capture scenario to become autonomous. The activity also includes the correlation between the functional tests and a multi-body model.

Deliverables: Breadboard

Current TRL: 3 Target TRL: 5 Duration (months) 24

Applicable THAG Roadmap:

N/A