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

1. TAS-I - Domain Exploration and Science
Technological road maps
based on STEPS and STEPS 2
developments
May 2013

2. International Scenario (GER 2.0)
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3. International Scenario (GER 2.0)
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4. 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
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5. 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
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6. 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
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7. 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
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8. 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
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9. 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
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10. 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”)
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11. 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€
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12. 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
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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)
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13. 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
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modular
disclosed
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14. 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
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15. 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
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in part nor
disclosed
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16. 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)
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TRL 6
2014
2015
disclosed
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17. 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)
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18. 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)
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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

19. 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

20. 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

21. 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