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Exploration and Sciences Technologies in Thales Alenia Space towards Horizone 2020
 

Exploration and Sciences Technologies in Thales Alenia Space towards Horizone 2020

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Strategic Road maps for Exploration and Sciences Technologies in Thales Alenia Space in view of Horizone 2020-Thales Alenia Space ad Aerospace and Defence Meetings 2013-Turin

Strategic Road maps for Exploration and Sciences Technologies in Thales Alenia Space in view of Horizone 2020-Thales Alenia Space ad Aerospace and Defence Meetings 2013-Turin

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    Exploration and Sciences Technologies in Thales Alenia Space towards Horizone 2020 Exploration and Sciences Technologies in Thales Alenia Space towards Horizone 2020 Presentation Transcript

    • TAS-I - Domain Exploration and Science Technological road maps based on STEPS and STEPS 2 developments May 2013
    • International Scenario (GER 2.0) This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space
    • International Scenario (GER 2.0) This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space
    • Aerospace Platform and STEPS Project Synergies between the Piedmont Aerospace District and the European Regional Development Fund (ERDF) 2007-2013 enabled Regione Piemonte to design and fund the initiative “Piattaforma Aerospazio” for accelerating the innovation of aerospace technology within the Region and reassuring its worldwide excellence European Regional Development Funds Macro-projects UAV Systems for civil land monitoring (SMAT F1) Green Aeronautical Engine technologies (GREAT 2020) Systems & technologies for Space Exploration (STEPS) market opportunity 4 System Primes, SMEs, Academies and Research Centers This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space
    • STEPS Conceptual Approach Infrastructures Fault Diagnostics Concurrent/Collaborative Design Virtual Reality Multidisciplinary Optimization Man-machine Interfaces Vision and Terrain Reconnaissance Navigation and Guidance Aerothermodynamics Rigid and Inflatable Structures Energy Management Landing/Ascent Vehicles Pressurized Structures Environmental Control Locomotion and Mechanisms This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space
    • STEPS Technology Domains Thales Alenia Space coordinated the overall project that involved Politecnico di Torino, Università di Torino, Università del Piemonte Orientale, ALTEC and 22 SMEs based in the region. The 3-year reaserch activities focus on the following space exploration enabling technologies: • Entry Descent & Landing and Surface Navigation • Surface Mobility, Rendez-vous & Docking (RVD) • Protection from Planetary Environment • Inflatable Structures and Multifunctional Smart Skin • Landing Legs and Shock Absorbers • Thermal Protection and Aerothermodynamics • Energy Management and Regenerative Fuel Cells • Health Management System (HMS) and Composite Structures Modelling • Human Machine Interfaces (HMI) • Virtual Reality and Collaborative Engineering 6 This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space
    • Rover and Lander Demonstrators on MMTS PRODE (Pressurized ROver Demonstrator) Scale 1:2 vs Flight Model Mass 1.5 vs 8 Tons Speed 5 vs 15 Km/hr PLADE (Planetary LAnder Demonstrator) Scale 1:1 vs Flight Model Mass 0.5 vs 3 Tons This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space
    • STEPS 2 The idea is to continue the technological development in selected areas with the objective to pass from a TRL 3 to 5/6 in order to be ready for possible in-orbit validations in the short-medium term In particular the technologies of STEPS have been screened using the following criteria: quality of the results, effectiveness of the involved partnerships, opportunities to have in-orbit validation in short/medium time frame, strategic values for their application in future space projects and maximum utilization of the infrastructures and laboratories developed in STEPS STEPS 2 started in January 2013 and will last two years including design of target flight hardware, development of a ground prototype and functional testing In the next days a DRR will approve the design and authorize the development of the test article for the validation of the technological solutions This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space
    • STEPS 2 Technologies Precision Landing Surface Navigation Smart Skin Landing Legs Regenerative Fuel Cells RVD & Mechanisms Inflatable and Environmental Protection Ablative/aerothermodynamics Health Management Systems/ Ultralight Structures STRUCTURAL HEALTH MONITORING DEMO (BS SIT R&D 2010) EARLY WARNING FAILURE ‘Health’ Evolution CRACK GROWTH MONITORING UNDER FATIGUE This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor LOADING disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space
    • Roadmap Legend Activities performed in the past Activities currently funded Future activites with funds to be allocated 1, 3 10 Indicates who was/is the contributor (refer to “past and ongoing project and budget”) This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space
    • Descent & Landing Technologies Roadmap Technical and business motivation: Objective: Guidance, navigation and control for trajectory and attitude management for a precision landing on a celestial body (i.e. Mars, asteroids, Moon). Navigation supported by Vision and Image processing to improve the precision in identifying and tracking specific targets on the terrain. Algorithms developed and validated in an EDL E2E simulator (model of the system and the units, model of the environment) and in a representative terrain facility (VNTF). Advanced navigation sensors are required to achieve the performance and precision required: e.g. Cameras, LIDAR, RadarAltimeter… Specific Guidance and control techniques are required to take under control and steer the trajectory during the entry phase in order to improve the position of the spacecraft at the beginning of the parachute phase. An active control is also required to minimize the dispersion effects on the trajectory during the parachute phase by means of a steerable parachute Team & State-of-the-art: Capability Proposal/ Mission Exomars 2016, 2018 Post EXOMARS prep.: Phobos Sample Return / Mars Network / Mars Precision Lander Future Robotic Exploration Missions: MARS Sample Return Entry, Deceleration and Descent TAS-I: EDL algorithms for Exomars, Vision based navigation developed in STEPS (TRL 3), simulation environment and testing area Academy and SMEs: PoliTO, PoliMI, … End-user and other stakeholders: ESA, ASI, EC Precision Landing Past and On-going projects and budget (concluded projects in brackets) Technology 1,2,3 Algorithms 2 and Sim. Dev. 3 Validation ESA : SAGE, VISNAV, CAIMAN => 1710 K€ PAD : (STEPS), STEPS2 =>1315 K€ TAS-I Int R&D => Included in 2 Set-up for Exploitation TRL 3/4 1,2,3 verification & validation facilities Development Upgrading Demonstration Validation 2013 11 1 Technologies for precision Landing (GNC data fusion and hazard avoidance+ Vision) 2014 2015 2016 Following proposed steps: Tayloring to specific mission needs 2017 2018 2019 2020 2021 2022 • Enhanced Test Facility (MREP) 400 K€ • Vision based Navigation, Guidance and Control validation (MREP-TRP) 2.5 M€ This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space
    • Surface Navigation Roadmap synthesis Future Robotic Exploration Missions Manned Surface Operations 1,2,3 1,2,3 characterizati on Test 2,3 Rover Expl Facil 1,2,3 Past and On-going projects and budget (concluded projects in brackets) 1 2 Autonomous GNC TRL 3/4 Technology TAS-I: Rover GMC, Advanced SW framework, Localization and path planning algorithms, Robotic Test Bench, Rover simulator (ROSEX for Exomars), STEPS Press. Rover (TRL 2-4) Academy and SMEs: PoliTO, UnivGenova, Zona, End-user and other stakeholders: ESA, EC Post EXOMARS prep.: Phobos Sample Return / Mars Network / Mars Precision Lander Rob/telerob. Surface Operations Integration in ATB… Test in closed loop Facility upgrading/adaptation 3 2 2013 ESA : (Sample Fetching Rover), (XROB), (EUROBOT),VISNAV => 435K€ PAD : (STEPS), STEPS2 =>1090K€ TAS-I Int R&D => Included in Following proposed steps: Autonomous . GNC :(GSTP-TRP 1-2M€ each): GNC based on innovative Sensors; Simultaneous specific characterization Localization And Mapping (SLAM);Continuous Navigation; Test features Integration in ATB… Test in closed loop Robot Cooperation;Mission and Action Planning; Object Recognition / Target Tracking Pressurised rovers ADV Mobility: studies on specific features (TRP) Test in Future Human surface Pressurised Rover: Assesement of requirements from future characterization Integration in Test closed mission studies Human surface missions (TRP) ATB… loop H2020 complement for specific area (e.g. collaborative rover 2014 2015 2016 2017 2018 2019 2020 2021 2022 This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor and mechanism, andvanced SLAM techniques, etc) Advanced Mobility 2,3 12 Team & State-of-the-art: Exomars 2018 Mission Capability Proposal/ Technical and business motivation: Robotics Surface exploration and Multi-rover formation control requires a great deal of autonomy for environment interaction: Hazard detection, viable path identification and planning, optimization of on-board and fleet resources Autonomous Rover Localization & Navigation: to determine the terrain morphology and identify the on-ground position Hazard mapping & guidance functions: to identify the critical situations and harazdous conditions and to generate the path for the rover motion Test Benchfor Robotic Autonomy platform implemented including new sensors (LIDAR, OmniCamera, Time of flight Camera) to enhance navigation performance development and test of innovative GNC systems tailored for mobile robots Navigation, based on stereo vision (developed in the internal R&D and STEPS) Visual odometry, to improve the localization accuracy SLAM Module: Estimation of 6D rover pose with pose correction based on landmarks ROver eXploration facilitY (ROXY) disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space
    • Multifunctional advanced thermal control Roadmap Capabil Proposa l/ ity Mission Technical and business motivation: Active thermal control is a key element in spacecrafts design which can significantly impact the architecture and performances of the system. The aim to optimize the system design it is essential to define new thermal control architectures and technologies capable of integration several functions maintaining the highest level of flexibility. This would have direct impacts on weights volumes, design constrain and consequently costs reductions. The proposed approach intends to develop modular multifunctional panels composed by a thermo-structural component (i.e. the multifunctional panel) and a flexible electronic layer (i.e the smart skin). The multifunctional panel will include not only mechanical and thermal passive functions but also energy production and storage capability, electromechanical elements e.g. for AOCS, etc. Thermo-mechanical aspects were already investigated in past R&D projects (MULFUN, Advanced BreadBoard, STEPS, ROV-E). The flexible electronic layer (i.e. smart skin) will embed thermal monitoring and heating capabilities, health monitoring functions and control electronics with integrated power control and harness routing. Transportation Service and Orbiting Infrastructures Enabling Technologies for Exploration Missions (post Exomars, MSR preparation,…) Science, Earth Observation, Telecommunication, Navigation Advanced Thermal Control Integrated Multifunctional System management Team & State-of-the-art: TAS-I: TCS Smart Skin (TRL5); Multifunctional Panel Breadboards (TRL3-4); Technological Engineering Area for experiments and equipment development and testing is available Academy and SMEs: various SME, IIT@PoliTo, Tecnalia (E), VTT (FI) End-user and other stakeholders: Any new spacecraft development (either scientific or commercial) can use this development ( Satellites & Infrastructure) Smart Skin TRL 5 Technology TCS Smart skin validation 2, 3 1, 2, 3 Product implementation Past and On-going projects and budget (concluded projects in brackets) Electronic tech. enhancement 1 Advanced functionalities Smart-skin validation (HMS and P/L control) Modular Multifunctional Panel 1,3 Advanced ThermoStructural Panel 3 2013 13 Development of a Modular Thermo-Structural Panel with Integrated Smart Skin 2014 2015 Product implementation EC : (MULFUN), ROV-E =>405 K€ 2 PAD : (STEPS), STEPS2 =>393K€ 3 TAS-I Int R&D => Included in 1, 2 Following proposed steps: • AMALIA for the on-orbit Smart Skin validation • GSTP - Development of Modular Multifunctional Structural 2016 2017 2018 2019 2020 2021 2022 Panel Prototype (450 k€) • H2020 c0mplementary activities for specific development of This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor TM panels and advanced functionalities modular disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space
    • Landing Leg Roadmap Technology Capability Proposal/ Mission Technical and business motivation: The spacecraft landing, ground to deliver a rover and crew safety/egress bring to a need of a soft landing. Landing Legs assure the conditions for a controlled landing for manned or unmanned spacecraft mission. Landing Legs are tailored to a soft landing and can act in a passive or active mode. The objective of development of an active leg system for impact absorption is based on the purpose of being the system adjustable after landing. Active system can lead to the possibility of copying with terrain roughness and slopes. TAS-I active system is identified as Active Shock Absorber (ASA), a key technology for enabling future missions on-soil explorations. ASA is a leading technology for Lander and Rover missions (i.e. landing gear reutilization, hopping mobility exploitation, reduction of terrain roughness induced vibrations, motion energy reduction, realignment of spacecraft e.g. for return capsule launch, etc). ASA shock absorbers technologies is based on electromagnetic actuators. ASA: works in a bidirectional way; acts as a damper, assuring a safe mode landing; is utilized as attitude adjuster , after landing; provides walking capability (if needed being a feature considered in the definition of leg kinematics). Potential ASA advantage is harvesting of energy in the process of vibration reduction. Enabling Technologies for Exploration Missions Team & State-of-the-art: Lunar Lander, Lunar Polar Sample Return and Mars Missions TAS-I: Active Shock absorber breadboard and test bench (TRL3) Academy and SMEs: PoliTo - LIM Safe and Precision Soft Landing Robotic surface operations and Human Surface Habitability and Operations Past and On-going projects and budget Active Shock Absorber Dev. Validation 2, 3 (concluded projects in brackets) TRL 5-6 1 2, 3 2 Deploying mechanisms Dev. Validation 3 Landing Leg Following proposed steps: • the target demonstration mission is AMALIA. The mission would represent the on-orbit demonstration case to reach a technology qualification for implementation on future Exploration Missions Prototype Design Validation 2, 3 Test bench devel. 2013 14 2014 Exploitation on Exploration Missions 2, 3 2015 2016 ASI : (AMALIA) PAD : (STEPS), STEPS2 => 740 K€ 2 TAS-I Int R&D => Included in 2017 2018 2019 2020 2021 2022 This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space
    • Energy Management Roadmap Technical and business motivation: Objective: Future planetary exploration will require advanced energy storage technologies in order to provide higher power and higher storage densities than secondary chemical batteries. The Energy density for the current batteries is in the order of 150/180 Whr/Kg and with the next battery technology could increase up to 250 Whr/Kg. Innovative energy storage technologies and systems should provide energy densities above 400 Wh/kg for target power systems of up to 8 kW (required for a Pressurized Lunar Rover application). The Reversible solution under development is based on the Alkaline technology. Interest: Enables the management of energy for surface planetary exploration that today cannot be satisfied by Secondary batteries Capability Proposal/ Mission ISS for Techno Demos and European Contribution to Human Explor Lunar lander & Lunar Polar S. Return ISS Exploitation Enabling Technologies for Exploration Missions (post Exomars, MSR preparation,…) High density energy storage High efficiency Micro-g fluid management Technology TRL 4 1, 2 Test bench Recirculation Enhancement 1, 2 test to 0g Environmental test TRL 6 System design and TRL 5 AIT Environmental test 1, 2 2014 2015 TAS-I: TRL 4 Technological Engineering Area for experiments and equipment development and testing is available. A demonstrator is available and under testing (a preliminary test with 2 kW of output was performed with success) Academy and SMEs: H2-Nitidor, Hysytech, Politecnico di Torino. End-user and other stakeholders: Primary use for Space Exploration but future applications on scientific or even commercial satellites possible Past and On-going projects and budget (concluded projects in brackets) Flight model for OnOrbit demo Set-up for to Expl. mission TRL 6 Flight model for OnOrbit demo 1 PAD : (STEPS), STEPS2 => 1 M€ 2 Reversible fuel cell system (1 stack) 2013 15 Regenerative fuel cell (2 stack) Team & State-of-the-art: TAS-I Int R&D => Included in 1 Following proposed steps: Set-up for to Expl. mission • Proposed at ESA call for ideas for IOD of a single stack reversible fuel cell with a budget of 15 M€ and 2016 2017 2018 2019 2020 2021 2022 3 year development schedule • Dedicated GSTP This document is not to be reproduced, modified, adapted, published, translated in any material form in whole•orH2020 complement for specific development in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space
    • Inflatable Structures Roadmap Technical and business motivation: Objectives (manned): increase the on-orbit habitable volumes (up to 5 times increase wrt current metallic modules) in spite of a launch highly packaged & mass effective configuration exploiting existing or next generation launchers. Application envisaged for Orbiting Infrastructures, Planetary Transfer, Surface Habitats on Moon & Mars (including pressurized cabin for manned rovers). The safety standard & functionality of rigid modules are maintained through a multi-layering solution for the inflatable shell including: sensorized internal barrier, air containment bladder, pressure containment restraint, MMOD (micro-meteoroids & orbital debris) & MLI (multi-layer insulation). Objectives (unmanned): increase the capability to deploy on-orbit extremely large structures in spite of a high packaging and lightness at launch. The typical application is envisaged for inflatable radiators (huge surface available to reject heat in space), solar arrays equipped with flexible solar cells, inflatable booms for solar sails and SAR antenna deployment, inflatable heat shields and airbags in EDLS, capture mechanisms for retrieval of sample containers, orbiting debris, etc. Capability Proposal/ Mission Team & State-of-the-art: Human Exploration Enabling Technologies Preparation for Future Robotics Exploration Missions Option for 2022 Mission: Mars Sample Return CAB & Inflatable Greenhouse Sustainable Human Orbiting, Cruise & Surface Habitability/Ops Entry Deceleration & Descent (Aero-braking, Heat Shielding) Soft Landing (Airbags) Large Orbital Deployable/Inflatable/Rigidizable Structures (e.g. radiators, solar arrays, booms) 3,4 1, 2, 3,4 TAS-I: Design, Mfg & Testing of scaled breadboard for manned inflatable modules and unmanned capture mechanisms (TRL 2-4) Academy and SMEs: PoliTO; Sistemi Compositi; CISAS; ALTA; Aerosekur End-user and other stakeholders: Bigelow major competitor in US for manned modules Past and On-going projects and budget (concluded projects in brackets) Inflatable Habitable Modules Technology TRL 4-5 Scaled Module Prototype Development TRL 2-3 On-orbit Rigidization by UV curing TRL 4 Inf Capture Mech Full Scale Module Prototype On-orbit Demo ESA : ( IMOD, IHAB, FLEXWIN, ICM) 2 ASI : (FLECS) 3 TAS-I Int R&D => Included in 4 Full Scale Adaptation for Exploration Missions Unmanned Inflatable Applications PAD : (STEPS), STEPS2 =>1475K€ 4 3 Full scale development of Inflatable Structures for Aerobraking, Heat Shielding, Airbags, Large Deployable Structures Following proposed steps: 1 2013 16 1 TRL 6-7 • On orbit demostration (IOD proposal issued 50 M) of inflatable manned module at ISS 2016 2017 2018 2019 2020 2021 2022 • Techno studies for Inflatable elements development (GSTP, TRP, etc) This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor TRL 6 2014 2015 disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space
    • RVD & Capture Roadmap Capability Proposal/ Mission Technical and business motivation: The creation of space infrastructure (e.g. for planetary exploration or debris removal) requires the capability of performing complex operations interfacing with other spacecrafts. The control of such operations is implemented by means of mechanisms and robots wich require both system capabilities and new sensors and actuators technologies. Rendezvous and Docking capability is extremely important for planets exploration missions, orbital RVD connections (e.g. satellite-to-satellite or spacecrafts to the International Space Station) and payload handling capability and ADR. Team & State-of-the-art: TAS-I: Engineering Technological Area for experiments and equipment development and testing TASI: algorithms for RVD model predictive control and optimizations (TRL 2-3) Academy and SMEs: PoliTO, various local SME Enabling Technologies for Exploration Missions (post Exomars, MSR preparation,…) Space Tugs RdV and Docking with collaborative target Past and On-going projects and budget RvD engineering Technological area (concluded projects in brackets) MIUR : SAPERE - STRONG=> 200 K€ 2 PAD : (STEPS), STEPS2 => 1040 K€ 1,2 3 TAS-I Int R&D => Included in ESA : DELIAN => 30 K€ 4 1 Technology GNC for RVD-capture on Space Tug/ADR 2, 3, 4 Algorithms for GNC prototype 2,3 GNC upgrade & Software GNC Validation Tailoring for specific mission Following proposed steps: Mechanism for RVD/ADR on Space Tug 4 2013 17 TRL 5 Qualification Mechanism Breadboard 1,3 2014 2015 RVD development for Post-EXM Exploration missions 2016 2017 2018 2019 2020 2021 2022 • GNC dev. & validation: 2 M€ (GSTP, H2020 , Clean Space,ADR,SSA) • Mechanism: 3 M€ (GSTP, H2020, Clean Space,ADR, SSA) This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space
    • Atmosphere Entry technologies Roadmap CapabilityProposal/ Mission Technical and business motivation: A critical element of entry vehicles is the selection of high performance and cost effective solutions for Thermal protection of the external layer of the structure. Ablative materials allows the thermal insulation by phase change and mass loss. Specific materials exists for low energy applications or medium-high energy application. The multi-physics behavior of a vehicle body with a thermal shield and complex flightdynamics requires the development of sophisticated analysis and simulation tools which can be combined with algorithms for the multi-disciplinary optimization of the system architecture. Enabling Technologies for Exploration Missions (Marco Polo - R, post Exomars, MSR preparation,…) Entry demos and pre-operational (IXV Evo – PRIDE) Team & State-of-the-art: Hypersonic Transportation & Crew Commercial Vehicles Entry, Deceleration and Descent (Earth, targets) Surface Ascent and Return (Robotic / Human) Tile Manufacturing & Verification 1 1 Ablative Material for Medium-High Heat fluxes Heat shield Integration Exploitation & Test Past and On-going projects and budget (concluded projects in brackets) Lightweight Ablative Material for Low Heat fluxes Material Charact. 3, 4 Tile Manufacturing & PWT test 3, 4 TRL 4 Tile array verification TRL 4 Heat shield Integration for inorbit demonstration Technology 2 In-orbit demonstration 3 Exploitation Multi-physics Optimization methodologies for Aerothermodynamics 4 ESA : Expert and IXV, (CSTS, Medium-High Flux Ablative material) EC : (Sacomar: EC, thermo-chemical models for Mars Expl.); Aersus (EC, Aerogel Insulation, 132 K€) PAD : (STEPS), STEPS2 =>1015 K€ (Low-Heat Flux Ablative material and Multi-physics Aerothermodynamics) TAS-I Int R&D => Included in 2, 3 Following proposed steps: for both High and Low Energy ablative TPS solutions: • Completion of Material Qualification in a Relevant Environment (e.g. thermal-vacuum, Off-gassing) and Tile array/Heat shield subassy PWT validation (about 700-1000 k€) Aeroshape optimization • Multi-physics Optimization for Aerothermodynamics Integrated Engineering Simulation Environments Design/Simulation Tools validation (e.g. Expert and IXV Post-flight Analysis Level2, about 500k€) Entry Vehicles Flight Dynamics Simulator • Atmosphere Entry Technologies in-orbit demonstration in relevant Airframe/Propulsion System Simulator 4 operational environment (Marco Polo and PRIDE mission) (about 2,5 M€ for HW design/MAIT/Post-flight Analysis) This document is not to 2018 be reproduced,2019 adapted, published, 2021 in any material form in whole or in part nor modified, translated 2013 2014 2015 2016 2017 2020 2022 disclosed • IOD/GSTP/H2020 Full N-S CFD code High Performance Computing Therm.Fluid.Chem. Modeling 1, 3, 4 High altitude DSMC aerotd. 1, 2, 3, 4 4 18 1 Exploitation Aerogel Insulation Performance Evaluation and Manufacturing Validation 2, 4 Processes Qualif. TAS-I: TRL4 Medium-High Heat fluxes Ablative material (6 MW/m2 test performed with success); TRL3 Low Heat fluxes Ablative material (thermal ablative characerization) Academy and Industrial Partners: Uni La Sapienza, CIRA and DLR (High Heat Flux Ablative material); PoliTO, UniTO -NIS, FN S.p.A. (Low Heat Fluxes Ablative; Exemplar and Optimad (SMEs) End-user and other stakeholders: ESA, ASI, MoD to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space
    • Advanced structures and Health Management Roadmap Technical and business motivation: HMS technology is aimed at embedding, into space infrastructures and reusable vehicles, ‘self inspection’ functions for generating real time health diagnostics (anomalies, ageing, integrity) and raising early prognosis about actual residual strength and/or lifetime capability of fulfilling the mission without replacement ad/or maintenance servicing. The objective is to develop a structure embedded Health Monitoring System which is based on ultrasound piezo polymeric sensors/actuators technology and which integrates both passive detection of impacts and automatic integrity inspection functions Capability Proposal/ Mission Post Exomars Prepar.: Options for 2022 Mission & Enabling Technologies preparation for future Robotic Exploration Missions Team & State-of-the-art: TAS-I: Design and Integration of HMS proprietary breadboard is in progress. TRL 4 has been achieved on specific components (sensors and algorithms) for composite structures HMS Academy and industrial partners: UniRoma (reusable TPS); AAC (Impact detection Diagnostics); UniFirenze (Diagnostics SW); CIRA (HMS Lab); CNR (Ultrasound Comformable Sensors); IIT@PoliTo (Piezo-polymeric Sensors) End-user and other stakeholders: Boeing has been developing HMS for aeronautics and space applications since late 90s. TAS-I and Boeing collaborated in the frame of OFFSET programme. Launchers and Transportation services (including services to orbiting infrastructures and Human Transportation for Exploration, e.g. MPCV) PRIDE and IXV operational evolution Entry, deceleration and descent Human Cruise Sustainable Surface Habitability Technology Health management system for composite tanks and structures 1, 2, 5, 6 TRL 5 Breadboard development TRL 7 5, 6 Flight Demonstration Set-up for Exploitation Past and On-going projects and budget HMS for Reusable Hot structures and TPS (< 1 MW/m2) 3 Reusable TPS impact detection sensors On-board NDI techniques 4, 6 TRL 4 (concluded projects in brackets) 1 TRL 5 TRL 7 2 3 4 5, 6 Flight Demonstration HMS Breadboard for reusable TPS Exploitation 5 6 2013 19 2014 2015 2016 2017 2018 2019 2020 2021 2022 MoD: (OFFSET) ESA: (FLPP1 HMS study) ASI : ASA2 => 1300K€ EC: THOR => 500K€ PAD : (STEPS), STEPS2 => 912 K€ TAS-I Int R&D => Included in 4 5 Following proposed steps: Two IOD proposals for PRIDE (reusable TPS) and ISS exploitation (impact detection on modules) are identified and This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor submitted to ESA disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space •H2020 complement for specific development
    • DEVICE Roadmap Capability Proposal/ Mission Technical and business motivation: Objective: Study, Prototype and Validate a so called DEVICE architecture of infrastructure and related process, able to support design activities during project phases A-B-C/D, so to: Improve Online/Offline Collaboration; Enable MBSE: have more models, less documents; Have a common baseline, machine-interpretable; Have more time for engineering, less time for searching; Enable the SE Vision 2020 of INCOSE. Obtain a stable DEVICE versions increments trough a Spiral life cycle allowing: System Model definition (driven by ESA); Functional and Physical Design integration; Simulation integration and MDO; Asynchronous and distributed support process; Correlated 2D formal notation and 3D hifidelity visualization; 4D (3D + t) manual procedures execution support in a hi-fidelity Synthetic Environment in both VR and AR; Be as much as possible COTS independent; No changes in current tools and methods for the single discipline, but “adapters” of tools to the centralized data and improvement in the process; Historical data capture/retrieval. Team & State-of-the-art: All projects & studies VR & AR TAS-I: DESI/ENG Disciplines, CC-AIT, IS TAS, THALES Academy and SMEs: PoliTO, UniTO, Blue Eng… End-user and other stakeholders: Space Agencies, EC Yearly increments/ Interaction trough innovative devices MBSE & SYSTEM DATA MODEL Yearly increments/ Updating-optimising Collaborative working with other entities Yearly increments/ Updating-optimising Past and On-going projects and budget (concluded projects in brackets) Technology 1,5,6,7 1 VERITAS Developments 2 Validation Demonstration 3 4 Spiral life-cycle Increments Developments TRL 4/5 5 2,3,5,6,7 DEVICE & SYSTEM DATA MODEL 6 TRL 4/5 Validation Developments Demonstration 7 8 EU/VR: (VIEW, MANUVAR), CROSSDRIVE: ~2 M € EU/CE: USE-IT-WISELY: ~0.9 M € ESA : MATED, (CEMAT, VSD): ~2 M € ASI: (CEF&DBTE): 1.2 M € PAD : (STEPS), STEPS2: ~2 M€ MIUR: STRONG: ~0,3 M€ IDoD: MASTER: ~0,3 M€ TAS-I Int R&D => Included in 1,2,4,5,6 TRL 3/4 Following proposed steps: 2013 20 2014 2015 2016 2017 2018 2019 2020 2021 2022 • Enhanced Tools (SW, AR device: Investment) 0,4 M€ • Demonstration on real project (GSTP6) 2.0 M€ This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space
    • Conclusions & Perspectives • The Space Exploration global road maps are asking for enabling capabilities based on advanced technologies • STEPS projects has been carried-out to start the development of a group of these technologies considered strategic for TAS and the other Piedmont Aerospace District actors • Now a second phase called STEPS 2 is in progress with promising results in order to reach a TRL 5/6 for a selected number of technologies having possible application in short-medium term • For these technologies the next logical step would be an in-orbit (or on-planet) demonstration through the Space Agencies, National and European research projects or other commercial initiatives • National and European support is essential to reach this objective 21 This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space