exploration and sciences technologies in thales alenia space towards horizone 2020

TAS-I - Domain Exploration and Science

Technological road maps

May 2013

Technological road maps based on STEPS and STEPS 2

developments

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

UAV Systems for civil land monitoring (SMAT F1)

European Regional Development Funds

Synergies between the Piedmont Aerospace District andthe European Regional Development Fund (ERDF)2007-2013 enabled Regione Piemonte to design andfund the initiative “Piattaforma Aerospazio”for accelerating the innovation of aerospace technologywithin the Region and reassuring its worldwideexcellence



4 System Primes, SMEs, Academies and Research Centers

market opportunity

monitoring (SMAT F1)

Mac

ro-p

roje

cts

Systems & technologies for Space Exploration (STEPS)

Green Aeronautical Engine technologies (GREAT 2020)

STEPS Conceptual Approach

Fault DiagnosticsInfrastructures

Vision and Terrain Reconnaissance

Navigation andGuidance

Man-machine Interfaces

Virtual RealityConcurrent/Collaborative

Design

Multidisciplinary Optimization



Environmental Control

Pressurized Structures

Rigid and Inflatable

Structures Energy Management

Landing/Ascent Vehicles

Aerothermodynamics

Locomotion and Mechanisms

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)



6

• 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

PRODE (Pressurized ROver Demonstrator)�Scale 1:2 vs Flight Model�Mass 1.5 vs 8 Tons�Speed 5 vs 15 Km/hr

Rover and Lander Demonstrators on MMTS



PLADE (Planetary LAnder Demonstrator)�Scale 1:1 vs Flight Model�Mass 0.5 vs 3 Tons

STEPS 2The 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 termIn 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 andlaboratories developed in STEPS



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 testingIn the next days a DRR will approve the design and authorize the development of the test article for the validation of the technological solutions

STEPS 2 Technologies

� Precision Landing� Surface Navigation� Smart Skin� Landing Legs� Regenerative Fuel Cells� RVD & Mechanisms� Inflatable and Environmental Protection� Ablative/aerothermodynamics



� Ablative/aerothermodynamics� Health Management Systems/ Ultralight

Structures

‘Health’ Evolution

CRACK GROWTH MONITORING

UNDER FATIGUE LOADING

FAILUREEARLY WARNING

STRUCTURAL HEALTH MONITORING DEMO (BS SIT R&D 2010)

Roadmap Legend

Activities performed in the past

Activities currently funded

Future activites with funds to be allocated


to any third party without the prior written permission of Thales Alenia Space - 2012, Thales Alenia Space10

Future activites with funds to be allocated

1, 3 Indicates who was/is the contributor (refer to “past and ongoing project and budget”)

Descent & Landing Technologies RoadmapTechnical and business motivation:

Objective: Guidance, navigation and control for trajector y and attitude management for a precisionlanding on a celestial body (i.e. Mars, asteroids, Moon). Na vigation supported by Vision and Imageprocessing to improve the precision in identifying and trac king 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 fa cility (VNTF).Advanced navigation sensors are required to achieve the per formance and precision required: e.g.Cameras, LIDAR, RadarAltimeter…Specific Guidance and control techniques are required to ta ke under control and steer thetrajectory during the entry phase in order to improve the pos ition of the spacecraft at thebeginning of the parachute phase. An active control is also r equired to minimize the dispersioneffects on the trajectory during the parachute phase by mean s of a steerable parachute

Team & State-of-the-art:TAS-I: EDL algorithms for Exomars, Vision based navigation developed in STEPS (TRL 3), simulation environment and testing area Academy and SMEs: PoliTO, PoliMI, …P

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sion Post EXOMARS prep.: Phobos Sample Return / Mars Net work / Mars Precision Lander

Future Robotic Exploration Missions: MARS Sample Re turn

Exomars 2016, 2018



Academy and SMEs: PoliTO, PoliMI, …End-user and other stakeholders: ESA, ASI, EC

ValidationSet-up for Exploitation

DemonstrationValidation

verification & validation facilities

Past and On-going projects and budget(concluded projects in brackets)

ESA : SAGE, VISNAV, CAIMAN => 1710 K€PAD : (STEPS), STEPS2 =>1315 K€TAS-I Int R&D => Included in

Technologies for precision Landing (GNC data fusion and hazard avoidance+ Vision)

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Precision Landing

2013 2014 2015 2016 2017 2018 2019 2020 2021 2022

Following proposed steps:• Enhanced Test Facility (MREP) 400 K€• Vision based Navigation, Guidance and Control

validation (MREP-TRP) 2.5 M€

1

2

3Algorithms

Development

1,2,3

1,2,3

2and Sim. Dev.

UpgradingTayloring to specificmission needs

TRL 3/4

Surface Navigation Roadmap synthesisTechnical and business motivation:

Robotics Surface exploration and Multi-rover formation co ntrol requires a great deal of autonomyfor environment interaction: Hazard detection, viable pat h identification and planning, optimizationof on-board and fleet resourcesAutonomous Rover Localization & Navigation: to determine t he terrain morphology and identify theon-ground positionHazard mapping & guidance functions: to identify the critic al situations and harazdous conditionsand to generate the path for the rover motionTest Benchfor Robotic Autonomy platform implemented inclu ding new sensors (LIDAR,OmniCamera, Time of flight Camera) to enhance navigation pe rformance

development and test of innovative GNC systems tail ored for mobile robots Navigation, based on stereo vision (developed in th e internal R&D and STEPS)Visual odometry, to improve the localization accura cySLAM Module: Estimation of 6D rover pose with pose correction based on landmarks

ROver eXploration facilitY (ROXY)

Team & State-of-the-art: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)

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Exomars 2018

Post EXOMARS prep.: Phobos Sample Return / Mars Net work / Mars Precision Lander



Academy and SMEs: PoliTO, UnivGenova, Zona, End-user and other stakeholders: ESA, EC

Advanced Mobility


ESA : (Sample Fetching Rover), (XROB), (EUROBOT),VISNAV => 435K€PAD : (STEPS), STEPS2 =>1090K€

TAS-I Int R&D => Included in

Autonomous GNC

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Future Robotic Exploration Missions

Cap

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ty Rob/telerob. Surface Operations

Integration in ATB…

Test in closed loop

Test Integration in ATB… Test in closed loop

2013 2014 2015 2016 2017 2018 2019 2020 2021 2022

Manned Surface Operations

Pressurised rovers

Test Integration in ATB…

Test in closed loop

Following proposed steps:Autonomous . GNC :(GSTP-TRP 1-2M€ each):GNC based on innovative Sensors; Simultaneous Localization And Mapping (SLAM);Continuous Navigation;Robot Cooperation;Mission and Action Planning;Object Recognition / Target TrackingADV Mobility: studies on specific features (TRP)Pressurised Rover: Assesement of requirements from future Human surface missions (TRP)H2020 complement for specific area (e.g. collaborative rover and mechanism, andvanced SLAM techniques, etc)

1

2

3characterizati

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characterization

characterization

1,2,3

1,2,3

2

Rover Expl Facil

Test2,3

1,2,3

2,3

Facility upgrading/adaptation

Future Human surface mission studies

specific features

TRL 3/4

Multifunctional advanced thermal control RoadmapTechnical and business motivation:

Active thermal control is a key element in spacecra fts design which can significantly impact the architecture and performances of the system. Th e aim to optimize the system design it is essential to define new thermal control architectur es 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 mu ltifunctional panels composed by a thermo-structural component (i.e. the multifunction al panel) and a flexible electronic layer (i.e the smart skin). The multifunctional panel will inc lude not only mechanical and thermal passive functions but also energy production and storage ca pability, electromechanical elements e.g. for AOCS, etc. Thermo-mechanical aspects were alrea dy investigated in past R&D projects (MULFUN, Advanced BreadBoard, STEPS, ROV-E).The flexible electronic layer (i.e. smart skin) wil l embed thermal monitoring and heating capabilities, health monitoring functions and contr ol electronics with integrated power control and harness routing. 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

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Enabling Technologies for Exploration Missions (pos t Exomars, MSR preparation,…)

Transportation Service and Orbiting Infrastructures

Science, Earth Observation, Telecommunication, Navi gation



1,3

testing is availableAcademy 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)

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2013 2014 2015 2016 2017 2018 2019 2020 2021 2022

TCS Smart skin validation

Smart Skin

Advanced Thermal Control

Electronic tech. enhancement

Advanced functionalities Smart-skin validation (HMS and P/L control)

Product implementation

Science, Earth Observation, Telecommunication, Navi gation

Modular Multifunctional Panel

Advanced Thermo-Structural Panel

Development of a Modular Thermo-Structural Panel

with Integrated Smart Skin

Integrated Multifunctional System management

Product implementation

TRL 5


EC : (MULFUN), ROV-E =>405 K€

PAD : (STEPS), STEPS2 =>393K€


1

2

3

Following proposed steps:• AMALIA for the on-orbit Smart Skin validation• GSTP - Development of Modular Multifunctional Structural

Panel Prototype (450 k€)• H2020 c0mplementary activities for specific development of

modular TM panels and advanced functionalities

1, 2

2, 3 1, 2, 3

3

Landing Leg RoadmapTechnical 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 c ontrolled 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 abso rption 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 A bsorber (ASA), a key technology for enabling future missions on-soil explorations.ASA is a leading technology for Lander and Rover mi ssions (i.e. landing gear reutilization, hopping mobility exploitation, reduction of terrain roughne ss induced vibrations, motion energy reduction, re-alignment of spacecraft e.g. for return capsule lau nch, etc). ASA shock absorbers technologies is based on electr omagnetic 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 i n the definition of leg kinematics).Potential ASA advantage is harvesting of energy in the process of vibration reduction.

Team & State -of -the-art:

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2, 3

Team & State -of -the-art:TAS-I: Active Shock absorber breadboard and test bench (TRL3)Academy and SMEs: PoliTo - LIM

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Lunar Lander, Lunar Polar Sample Return and Mars Mi ssions

Cap

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2013 2014 2015 2016 2017 2018 2019 2020 2021 2022

Safe and Precision Soft Landing

Robotic surface operations and Human Surface Habita bility and Operations

ValidationActive Shock Absorber

Landing Leg

Prototype DesignValidation Exploitation on Exploration Missions

Test bench devel.

Deploying mechanismsValidation

Dev.

Dev.

TRL 5-6Past and On-going projects and budget(concluded projects in brackets)

ASI : (AMALIA)PAD : (STEPS), STEPS2 => 740 K€TAS-I Int R&D => Included in

1

2

3

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

Exploitation on Exploration Missions

Validation

2, 3

2, 3

2

2, 3

Energy Management Roadmap

Technical and business motivation:Objective: Future planetary exploration will requir e advanced energy storage technologies in order to provide higher power and higher storage de nsities 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 4 00 Wh/kg for target power systems of up to 8 kW (required for a Pressurized Lunar Rover app lication). The Reversible solution under development is based on the Alkaline technology.Interest: Enables the management of energy for surf ace planetary exploration that today cannot be satisfied by Secondary batteries

Team & State-of-the-art: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 P

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ISS Exploitation

Lunar lander & Lunar Polar S. Return


ISS for Techno Demos and European Contribution to Human Explor



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 possibleTest

benchRecirculation

testEnhancement

to 0g

System design and AIT

Environmental test

Reversible fuel cell system (1 stack)

Regenerative fuel cell (2 stack)

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High density energy storage

High efficiency Micro-g fluid management

TRL 4

TRL 6

TRL 6TRL 5

Environmental test

2013 2014 2015 2016 2017 2018 2019 2020 2021 2022


Flight model for On-Orbit demo

Set-up for to Expl. mission

Flight model for On-Orbit demo

Set-up for to Expl. mission


PAD : (STEPS), STEPS2 => 1 M€


Following proposed steps:• Proposed at ESA call for ideas for IOD of a single

stack reversible fuel cell with a budget of 15 M€ and 3 year development schedule

• Dedicated GSTP • H2020 complement for specific development

1

2 1

1, 2

1, 2

1, 2

Inflatable Structures RoadmapTechnical and business motivation:

Objectives (manned): increase the on-orbit habitabl e volumes (up to 5 times increase wrt current metallic modules) in spite of a launch highly packa ged & mass effective configuration exploiting existing or next generation launchers. Application envisaged for Orbiting Infrastructures, Planetary Transfer, Surface Habitats on Moon & Mars (includin g pressurized cabin for manned rovers). The safety standard & functionality of rigid modules ar e maintained through a multi-layering solution for the inflatable shell including: sensorized inte rnal barrier, air containment bladder, pressure containment restraint, MMOD (micro-meteoroids & orb ital debris) & MLI (multi-layer insulation).Objectives (unmanned): increase the capability to d eploy 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 ant enna deployment, inflatable heat shields and airbags in EDLS, capture mechanisms for retrieval o f sample containers, orbiting debris, etc.

Team & State-of-the-art: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; P

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Human Exploration

Enabling Technologies Preparation for Future Roboti cs Exploration Missions

Option for 2022 Mission: Mars Sample Return



Academy and SMEs: PoliTO; Sistemi Compositi; CISAS; ALTA; AerosekurEnd-user and other stakeholders: Bigelow major competitor in US for manned modules


ESA : ( IMOD, IHAB, FLEXWIN, ICM)

ASI : (FLECS)


PAD : (STEPS), STEPS2 =>1475K€

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CAB & Inflatable Greenhouse

Cap

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ty Sustainable Human Orbiting, Cruise & Surface Habita bility/Ops

Entry Deceleration & Descent (Aero-braking, Heat Sh ielding)

Soft Landing (Airbags)

Large Orbital Deployable/Inflatable/Rigidizable Stru ctures (e.g. radiators, solar arrays, booms)

Unmanned Inflatable Applications

Inflatable Habitable ModulesTRL 4-5 TRL 6-7

Full Scale Module Prototype On-orbit Demo

Full Scale Adaptation for Exploration Missions

On-orbit Rigidization by UV

curing

TRL 2-3

Full scale development of Inflatable Structures for Aerobraking, Heat Shielding, Airbags, Large Deployable Structures TRL 4

3,41, 2, 3,4

3

Scaled Module Prototype Development

Inf Capture

Mech1

1

2

3

4

Following proposed steps:• On orbit demostration (IOD proposal issued 50 M)

of inflatable manned module at ISS• Techno studies for Inflatable elements development

(GSTP, TRP, etc)20142013 20192018201720162015 20212020 2022

TRL 6

4

RVD & Capture Roadmap

Technical and business motivation:The creation of space infrastructure (e.g. for plan etary exploration or debris removal) requires the capability of performing complex operations int erfacing with other spacecrafts. The control of such operations is implemented by means of mecha nisms and robots wich require both system capabilities and new sensors and actuators t echnologies. Rendezvous and Docking capability is extremely important for planets explo ration 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)

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Space Tugs



2, 3, 4

optimizations (TRL 2-3)Academy and SMEs: PoliTO, various local SME

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RdV and Docking with collaborative target


MIUR : SAPERE - STRONG=> 200 K€PAD : (STEPS), STEPS2 => 1040 K€TAS-I Int R&D => Included in ESA : DELIAN => 30 K€

1

2

3

Following proposed steps:• GNC dev. & validation: 2 M€ (GSTP, H2020 , Clean

Space,ADR,SSA)• Mechanism: 3 M€ (GSTP, H2020, Clean Space,ADR,

SSA)

1,2Algorithms for GNC

prototype

GNC for RVD-capture on Space Tug/ADR

RvD engineering Technological area

TRL 5

GNC upgrade & SoftwareTailoring for

specific mission

Mechanism Breadboard

Mechanism for RVD/ADR on Space Tug

Qualification

RVD development for Post-EXM Exploration missions

GNC Validation

2013 2014 2015 2016 2017 2018 2019 2020 2021 2022

1,3

2,34

4

Technical and business motivation:A critical element of entry vehicles is the selecti on of high performance and cost effective solutions for Thermal protection of the external la yer of the structure. Ablative materials allows the thermal insulation by phase change and mass los s. 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 flight-dynamics requires the development of sophisticated analysis and simulation tools which can be combined with algorithms for the multi-disciplin ary optimization of the system architecture.

Team & State-of-the-art: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

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Surface Ascent and Return (Robotic / Human)

Entry, Deceleration and Descent (Earth, targets)

Enabling Technologies for Exploration Missions (Mar co Polo - R, post Exomars, MSR preparation,…)

Entry demos and pre-operational (IXV Evo – PRIDE)

Hypersonic Transportation & Crew Commercial Vehicl es

Atmosphere Entry technologies Roadmap



4

1

1, 2,3, 4

3, 4

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

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2013 2014 2015 2016 2017 2018 2019 2020 2021 2022

Tile Manufacturing & Verification

Heat shield Integration& Test

Lightweight Ablative Material for Low Heat fluxes

Ablative Material for Medium-High Heat fluxes

Aerogel Insulation

Material Charact.

Tile Manufacturing & PWT test

Tile array verification

Multi-physics Optimization methodologies for Aerothermodynamics

Integrated Engineering Simulation Environments

Aeroshape optimization

Full N-S CFD code

High altitude DSMC aerotd.

Exploitation

Heat shield Integration for in-orbit demonstration Exploitation

Performance Evaluation and Validation In-orbit demonstrationManufacturing

Processes Qualif. Exploitation

High Performance ComputingTherm.Fluid.Chem. Modeling

Airframe/Propulsion System Simulator

Entry Vehicles Flight Dynamics Simulator


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

1

2

3

4

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 sub-assy PWT validation (about 700-1000 k€)

• Multi-physics Optimization for Aerothermodynamics Design/Simulation Tools validation (e.g. Expert and IXV Post-flight Analysis Level2, about 500k€)

• Atmosphere Entry Technologies in-orbit demonstration in relevant operational environment (Marco Polo and PRIDE mission) (about 2,5 M€ for HW design/MAIT/Post-flight Analysis)

• IOD/GSTP/H2020

2, 3

1

3, 4

2, 4

1, 3, 4

4

TRL 4TRL 4

Advanced structures and Health Management Roadmap

Technical and business motivation:HMS technology is aimed at embedding, into space in frastructures and reusable vehicles, ‘self inspection’ functions for generating real time heal th diagnostics (anomalies, ageing, integrity) and raising early prognosis about actual residual s trength and/or lifetime capability of fulfilling the mission without replacement ad/or maintenance s ervicing.The objective is to develop a structure embedded He alth Monitoring System which is based on ultrasound piezo polymeric sensors/actuators techno logy and which integrates both passive detection of impacts and automatic integrity inspec tion functions

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 HMSP

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Post Exomars Prepar.: Options for 2022 Mission & En abling Technologies preparation for future Robotic Exploration Missions

Launchers and Transportation services (including se rvices to orbiting infrastructures and Human Transportation for Exploration, e.g. MPCV)

PRIDE and IXV operational evolution



3

1, 2,5, 6

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.

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Sustainable Surface Habitability

Breadboard developmentFlight Demonstration

Set-up for Exploitation

Reusable TPS impact detection sensors

HMS Breadboard for reusable TPS

Exploitation

HMS for Reusable Hot structures and TPS (< 1 MW/m2)

Health management system for composite tanks and structures

TRL 5TRL 7

2013 2014 2015 2016 2017 2018 2019 2020 2021 2022

PRIDE and IXV operational evolution

Human Cruise

On-board NDI techniques

Flight Demonstration

TRL 7TRL 4

TRL 5


MoD: (OFFSET)ESA: (FLPP1 HMS study)ASI : ASA2 => 1300K€EC: THOR => 500K€PAD : (STEPS), STEPS2 => 912 K€TAS-I Int R&D => Included in

1

2

3

Following proposed steps:�Two IOD proposals for PRIDE (reusable TPS) and ISS exploitation (impact detection on modules) are identified and submitted to ESA•H2020 complement for specific development

4

4

5

6 5

5, 6

4, 6

5, 6

DEVICE RoadmapTechnical and business motivation:

Objective: Study, Prototype and Validate a so called DEVICE architecture of infrastructure andrelated process, able to support design activities during p roject phases A-B-C/D, so to: ImproveOnline/Offline Collaboration; Enable MBSE: have more mode ls, less documents; Have a commonbaseline, machine-interpretable; Have more time for engin eering, less time for searching; Enablethe SE Vision 2020 of INCOSE.Obtain a stable DEVICE versions increments trough a Spiral l ife cycle allowing: System Modeldefinition (driven by ESA); Functional and Physical Design integration; Simulation integration andMDO; Asynchronous and distributed support process; Correl ated 2D formal notation and 3D hi-fidelity visualization; 4D (3D + t) manual procedures execu tion support in a hi-fidelity SyntheticEnvironment in both VR and AR; Be as much as possible COTS inde pendent; No changes incurrent tools and methods for the single discipline, but “ad apters” of tools to the centralized dataand improvement in the process; Historical data capture/re trieval.

Team & State-of-the-art:TAS-I: DESI/ENG Disciplines, CC-AIT, ISTAS, THALESP

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All projects & studies



TAS, THALESAcademy and SMEs: PoliTO, UniTO, Blue Eng…End-user and other stakeholders: Space Agencies, EC

Validation

Demonstration

DEVICE & SYSTEM DATA MODEL


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

VERITAS

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MBSE & SYSTEM DATA MODEL

2013 2014 2015 2016 2017 2018 2019 2020 2021 2022Following proposed steps:• Enhanced Tools (SW, AR device: Investment) 0,4 M€• Demonstration on real project (GSTP6) 2.0 M€

1

2

3Developments

Developments

1,5,6,7

2,3,5,6,7

Validation

Spiral life-cycle Increments Developments4

5

6

7

4

8

Collaborative working with other entities

Yearly increments/ Interaction trough innovative de vices

Yearly increments/ Updating-optimising

Yearly increments/ Updating-optimising

TRL 3/4

TRL 4/5

Demonstration

TRL 4/5

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



21

• 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

exploration and sciences technologies in thales alenia space towards horizone 2020

Technology

steps steps

technologies of steps

following space exploration

material form

future space projects

steps project synergies

mechanismsthis document

tonsthis document