european space agency industrial policy committee revision ...2011)118_add.3.pdf · esa...

ESA Unclassified ESA/IPC(2011)118,add.3 For official use Att.: Annexes Paris, 11 November 2011 (Original: English)

EUROPEAN SPACE AGENCY INDUSTRIAL POLICY COMMITTEE

REVISION OF THE STRATEGIC INITIATIVE

WORK PLAN/PROCUREMENT PLAN 2011

Summary The Strategic Initiative (StrIn) has been started after the approval by Council on 17 June 2010. According to the rules established, work plans/procurement plans covering the activities of the Initiative have to be presented to IPC for approval. This document contains the additional activities identified for approval in 2011. Action required The Industrial Policy Committee is invited to approve the attached revision of the StrIn work plan/procurement plan, by simple majority of Member States. Other procurement plans of concerned activities and programmes shall be automatically updated accordingly where necessary.

The Industrial Policy Committee is invited to approve the addendum 3 to the Strategic Initiative Work Plan/Procurement Plan

by simple majority of Participating States: AT, BE, CZ, DK, FI, FR, DE, GR, IE, IT, PT, LU, NL, NO, ES, SE, CH, UK

eCPB-2011-1653

ESA/IPC(2011)118,add.3

1. Introduction Following the adoption by Council of the “Resolution on the return coefficient, discontinuation of geographical return statistics and the Strategic Initiative” on 17 June 2010 (ref. ESA/C/CCXV/Res.2 (Final), the Agency has been mandated to implement the Strategic Initiative Programme as outlined in the documents ESA/C(2010)43 and ESA/C(2010)73. The programmatic approach is further detailed in ESA/IPC(2011)89, rev.1 Eligible Member States benefiting from the Strategic Initiative are those having a forecast geographical return of 0.96 or below at end-2014L, namely Austria, Denmark, Finland, Ireland, Norway, Switzerland and, since June 2011, Sweden. Following the decisions by IPC in September 2011 (ESA/IPC(2011)113) about the conditions for the inclusion of Sweden in StrIn Member States, the share of StrIn in all co-funded activities new or in the pipeline not yet committed has been decreased from 50% to 33 %’. Adjustments will also follow for the activities in Best Practices.

2. Procurement policies Following the decisions by IPC (ESA/IPC(2010)89, rev. 1), the following procurement policies are being put in place for the activities selected in the StrIn work plans/procurement plans:

Procurement policy Explanation Best Practices For selected projects/programmes, the Prime

will be invited to identify in the IPP the activities which can be awarded in DN or RC to firms from StrIn eligible countries. Awarding will be possible if offers receive a mark of at least 55 and are judged to be competitive (quality/price ratio), and not inducing excessive risks to the programme.

Activities in programme’s work plans and exploratory activities: C PC (STRIN), or PC(StrIn) RC RC(StrIn) DN DN/S DN/C

Open competition Preferential clause for StrIn eligible countries: in this case offers from eligible States featuring a min score of 55 in the evaluation are selected Restricted competition Restricted competition among companies from StrIn eligible countries. A min mark of 55 is sought Direct negotiation, where a min mark of 55 is sought Direct negotiation, due to specialisation purposes Direct negotiation, due to continuation of previous activities

Announcements of Opportunity (AOs)

Issued either in RC for one StrIn eligible country or in RC(StrIn); they may be followed by a request for a full proposal for the selected activities

ESA/IPC(2011)118,add.3

Additional policies, if necessary, will be proposed to IPC for approval. 3. Content of the 2011 work plan/procurement plan

The plan contains activities in the domains of Telecom, Exploration and Technology.

a) Activities in Best Practices (Annex I) No additional efforts are requested for the time being. Adjustments will be possible in early 2012.

b) Activities in programmes’ work plans (Annex II)

Most of the activities are in open competition with the StrIn preferential clause 1. .For certain activities in TRP, it is proposed to adopt the same clause C(PC), applicable to StrIn eligible States, to firms from Portugal and Greece, with the understanding that the funds indicated are valid only for StrIn countries, and, should Portuguese or Greek companies win the competition, their share will be totally covered by TRP, as special measures, in line with ESA/IPC(2011)113. For Artes 20 activities listed below, the procurement policy approved by IPC ( ESA/IPC(2011)292) will apply.

c) Prospect activities (Annex III) For information, were selected two additional activities from the Irish AO.

d) Activities covered by Canada compensations through StrIn (Annex IV)

One additional activity has been added. As usual, these activities are reported for information only.

e) Special measures for Greece and Portugal

A chapter on the special effort made by different ESA projects towards Greece and Portugal has been also added, for information only.

4. Conclusion The Industrial Policy Committee is invited to approve the attached update of the StrIn work plan/procurement plan, by simple majority of Member States. Other procurement plans of concerned activities and programmes shall be automatically updated accordingly where necessary.

1 Is or To be published in the ITT cover Letter. 2 “In the case of open competition activities contemplated in this work plan and in case of bidders from countries eligible for the Strategic Initiative, the Executive will reserve the right to award parallel contracts in line with Strategic Initiative procedures.”

ESA/IPC(2011)118,add.3 Annex I, page 1

Annex I

Activities in Best Practices


No additional efforts are requested for the time being.


Annex II

Activities in Programme Work Plans

ESA/IPC(2011)118,add.3 Annex II, page 2

For all StrIn countries

Approval StrIN Ref# Prg Ref# Activity Title Co-

funding entity

Nominal Budget

(kE)

Str. Ini. Share

Budget (kE)

Year of implementation

Comments

IPC StrIN-TEC-17-

xxx T224-002QI

Material compatibility assessment with a hydrogen peroxide sterilisation

process TRP/CTP 150 50 2012

C3, PC (StrIn) ESA/IPC(2011)81,rev.1

IPC StrIN-SRE-01-

xxx C223-056QE

Qualification of radiation tolerant FLASH memory

CTP 500 165 2012 PC (StrIn) ,

ESA/IPC(2011)81,rev.1

IPC StrIN-SRE-02-

xxx C215-118MS

Characterisation of actuator behaviour for a cryogenic fine

steering tip-tilt mechanism CTP 300 100 2012

C1, PC (StrIn) ESA/IPC(2011)81,rev.1

IPC StrIN-TEC-18-

xxx T218-004MP

Marco Polo R earth re-entry capsule dynamic stability characterization

TRP/CTP 450 150 2012 PC (StrIn) ,


IPC StrIN-SRE-03-

xxx C217-028PA

Sub-Megahertz linewidth laser for Fundamental Physics Missions

CTP 450 150 2012 C1 and PC (StrIn),


IPC StrIN-TEC-19-

xxx T207-035EE

Large radii Half-Wave Plate (HWP) development

TRP/CTP 600 200 2012 PC (StrIn)


IPC StrIN-TEC-20-

xxx T207-036EE

Next generation sub-millimetre wave focal plane array coupling concepts

TRP/CTP 400 135 2012 C1 and PC (StrIn)


IPC StrIN-SRE-04-

xxx E901-002ED

Tailored On-Board Computer EM for planetary landers,

MREP 700 235 2012 PC (StrIn)

ESA/IPC(2011)117

IPC StrIN-SRE-05-

xxx E905-016EC Accelerometer component to TRL5 MREP 700 235 2012

PC (StrIn) ESA/IPC(2011)117

Pending on MREP georeturn StrIn will be applied or not for this activity.

IPC StrIN-SRE-06-

xxx T924-002QT

High specific stiffness metallic materials

TRP/MREP 500 165 2012 PC (StrIn)

ESA/IPC(2011)117

IPC StrIN-TIA-02-

xxx

9C.009

Prediction, Monitoring and Alerting of Landslides and Subsidence

Affecting the Transport Infrastructure (OC)

Artes 20

300 100 2012 PC (StrIn)

ESA/IPC(2011)29

IPC StrIN-TIA-03-

xxx 9B.015

Improvement of Maritime Safety in the Baltic Sea through Enhanced

Situational Awareness (OC)

Artes 20 300 100 2012

PC (StrIn) ESA/IPC(2011)29


IPC StrIN-TIA-04-

xxx 9E.002

Coastal Surveillance and Water Quality monitoring in the Baltic Sea

(OC)

Artes 20 300 100 2012

PC (StrIn) , ESA/IPC(2011)29

IPC StrIN-TEC-21-

xxx G526-002MS Modular Cable Reel SADM Family

GTSP 1900 630 2012

PC (STRIN), ESA/IPC(2011)29 , up to 630 Keur

IPC

StrIN-TIA-06-xxx

9B.010

Special Meteorological Services for Maritime Search and Rescue (OC)

Artes 20 300 100 2012 PC (STRIN), ESA/IPC(2011)29

IPC

StrIN-TIA-07-

xxx

9B.011

Piracy Prevention and Commercial Navigation in Insecure Waters (OC)

Artes 20

300

100

2012

PC (STRIN),

ESA/IPC(2011)29

IPC

StrIN-TIA-08-

xxx

9C.008

Optimising Inter-modal Freight

Transport through European Ports (OC)

Artes 20

300

100

2012

PC (STRIN),

ESA/IPC(2011)29

IPC StrIN-TEC-26-

xxx T116-306MM

Advanced laser ranging technologies for altimetry

TRP 600 200 2012 PC(StrIn ) + PT:

ESA/IPC(2011) 3, Add.5

IPC

StrIN-TEC-40-

xxx

T117-302MM

2.05 Microns Pulsed Holmium-Laser for Atmospheric CO2 and Methane

Monitoring

TRP

600

200

2012 PC(StrIn ) + GR and PT,


IPC

StrIN-TEC-28-

xxx

T117-307MM

Versatile high-fidelity reference gas cell as laser wavelength stabilisation

unit for DIAL measurements of atmospheric trace gases

TRP

400

135

2012

PC(StrIn ) + GR,


IPC

StrIN-TEC-29-

xxx

T126-301GT

Enriching EO ontology services using Product Trees - PTREE

TRP

150

50

2012

PC(StrIn ) + GR,


IPC

StrIN-TEC-30-

xxx

T126-303GT

PDGS e-Collaboration - PDGSE

TRP

200

70

2012

PC(StrIn ) + PT, ESA/IPC(2011) 3, Add.5

IPC

StrIN-TEC-33-

xxx

T314-006MM

Quality of Experience (QoE) tool for

Telemedicine

TRP

200

70

2012

PC(StrIn ) +GR and PT , ESA/IPC(2011) 3, Add.5

IPC

StrIN-TEC-35-xxx

T322-003MM

Biocide management for long term

water storage

TRP

200

70

2012

PC(StrIn ) +GR and PT, ESA/IPC(2011) 3, Add.5

IPC

StrIN-TEC-41-

xxx

T402-301SW

Hardware-Software Dependability

for Launchers

TRP

300

100

2012

PC(StrIn ) + GR and PT,


IPC

StrIN-TEC-42-xxx

T404-301EE

Improvement of solar flare prediction

TRP

100

35

2012

PC(StrIn ) + GR and PT ,



IPC

StrIN-TEC-31-

xxx

T401-301ED

Ultra-wideband as a multi-purpose robust and reliable wireless

communication technology for tests, spacecraft and launchers

TRP

500

165

2012



IPC

StrIN-TEC-37-

xxx

T506-303ET

Ultra low phase noise reference

oscillator

TRP

300

100

2012



IPC

StrIN-TEC-43-

xxx

Y2011 T506-

308ET

Advanced modem techniques for

future satellite access

TRP

250

85

2012



IPC

StrIN-TEC-44-

xxx

Y2011 T507-

301EE

Lens-Like Multiple Beam Antenna

TRP

250

85

2012



IPC

StrIN-TEC-32-xxx

Y2011 T520-

301MS

Thermally conductive RTM CFRP

TRP

200

70

2012



IPC

StrIN-TEC-38-xxx

T707-304EE

Multi-Magnetometer Methods for

Magnetic Dipole Modelling

TRP

250

85

2012



IPC

StrIN-TEC-45-xxx

T708-301SW

Automated testing using ECSS-E-70-

32 Test and Operations procedure language

TRP

500

165

2012



IPC

StrIN-TEC-47-

xxx

T724-303QT

Metal Matrix Composites (MMCs) as

high performance metallic material

TRP

300

100

2012



IPC

StrIN-TEC-48-xxx

T724-304QE

Nano-hybrid transparent materials

TRP

300

100

2012



IPC

StrIN-TEC-49-xxx

T702-303SW

System-Hardware-Software co-

engineering

TRP

200

70

2012



IPC

StrIN-TEC-25-xxx

T701-316ED

Dynamic Latchup protection chip for

COTS components

TRP

600

200

2012



IPC

StrIN-TEC-39-xxx

T723-307QT

Development of a monolithic pulse-

width-modulated (PWM)IC.

TRP

350

115

2012



IPC

StrIN-TEC-23-xxx

T703-305EP

Miniaturised core element for Point

of Load (PoL) conversion

TRP

500

165

2012



IPC

StrIN-TEC-24-

xxx

T723-320QT

Embedded passive component: a way

to miniaturization

TRP

400

135

2012




IPC

StrIN-TEC-46-

xxx

T720-304MS

SAFE (Shock Attenuator For

Equipment)

TRP

300

100

2012



IPC StrIN-EOP-03-

xxx 11.156.13

Critical Elements for Risk Mitigation of the K-band Downlink Antenna for

MetOp-SG EOP 2400 800 2012

400 KEUR x 2 C1 + StrIn clause

ESA/IPC(2011)1, add.47 (StrIn on both parallel activities)

IPC StrIN-EOP-04-

xxx 11.156.14

Highly Stable Antenna Breadboard of the Wind Scatterometer for MetOp-

SG EOP 1200 400 2012

200 KEUR x 2 C1 + StrIn clause

ESA/IPC(2011)1, add.47 (StrIn on both parallel activities)

IPC

StrIN-EOP-07-

xxx

EOP

GRAS-2 design and breadboarding

EOEP

1500

500

2012

PC (StrIn)

IPC

StrIN-EOP-05-

xxx

EOP

Consolidation of Radio Occultation

concept for Jason-CS

EOEP

240

80

2012

PC (StrIn)

IPC

StrIN-EOP-06-

xxx

EOP

Evaluation of AGGA-4 ASIC devices

EOEP

450

150

2012

PC (StrIn)

IPC

StrIN-EOP-08-

xxx

EOP

Study of geophysical retrieval

methods in the microwave spectral region

EOEP

200

70

2012

PC (StrIn)

IPC StrIN-EOP-09-AT+CH

EOP Algorithms for estimating snow grain size

EOEP 150 50 2012 DN with ENVEO (Austria) and Gamma Remote Sensing (Switzerland)

IPC

StrIN-EOP-09-

xxx

EOP

Study of high-resolution wide-swath

SAR applications

EOEP

250

85

2012

PC (StrIn)

Grand Total 22790 7620


Ireland


funding entity

Nominal Budget

(kE)

Str. Ini.

Share Budget

(kE)

Year of implementatio

n Comments

IPC StrIN-TIA-11-IE 8G.015 SATMODO ARTES

34 300 100 2012 DN with Treemetrics Ltd. (IRL)

IPC StrIN-LAU-02-IE 11.343.22

FLPP Period 2 Step 2 (SDT sub-envelope) Core Technologies – Materials & Structures –

Thermoplastic technologies FLPP 931 231 2012 DN with Eire Composites (IE)

1231 331

Sweden

Approval StrIN Ref# Prg Ref# Activity Title Co-funding entity Nominal Budget

(kE)

Str. Ini. Share

Budget (kE)


Comments

IPC StrIN-TIA-01-SE 4F.073 RAD HARD Miniature POINT of LOAD

ARTES 5.2 Phase I 1500 500 2012 AAC Microtec AB (SE)

IPC StrIN-TEC-08-SE Development of array radiometer core

breadboard 800 800 2012 DN with OMNISYS (SE)

2300 1300

ESA/IPC(2011)118,add.3 Annex II, page 7 Norway


(kE)

Str. Ini. Share

Budget (kE)


Comments

IPC StrIN-TIA-06-NO 5D.025 Development of 2nd Generation Telemetry

and Beacon transmitter ARTES 34 1500 500 2012

DN with Norspace AS (NO)

IPC StrIN-TEC-05-NO G513-058MM ANITA2 for International Space Station GSTP 500 33% of

Norwegian Share

2012 DN with SINTEF (NO),

Approved in ESA/IPC(2011)5, add.3

2000

Denmark


(kE)

Str. Ini. Share

Budget (kE)


Comments

IPC StrIN-TEC-08-DK G604-11EP Study, Development & Verification of

a Planar Transformer

GSTP 390 40 2011 Flux A/S (DK)

ESA/IPC(2011)4, add.4

IPC IPI-TEC-01-DK IPI-TEC-01-

DK Solar Array Simulator : phase 2 Industry ( Rovsing) 2000 1000 2012

Contract phase 1 4200022953. Phase 1, was covered out of SIUC : 300 Keur. This part is co-funded

with Industry. 2390 1040

Switzerland


(kE)

Str. Ini. Share Budget

(kE)


Comments

IPC StrIN-PFL-01-CH

Glacier Lake High Mountain Hazard/Risk Estimation Service

(GLOF)

STRIN 300 300 2012 DN with Gamma RS

(CH)

300 300

ESA/IPC(2011)118, Rev.2 Annex III, page 1

Annex III

Prospect Activities

ESA/IPC(2011)118,add.2 Annex III, page 2

Ireland Approval StrIN Ref# Prg Ref# Activity Title Co-funding entity

Nominal Budget

(kE)

Str. Ini. Share

Budget (kE)


Comments

For Info. Novel AIS Antenna and evaluation of new

AIS frequencies (AIS-ANS) NA 200 200 2011

Activity resulting from the Irish AO which is

applicable for Telecom area

For Info HIPERFREQ – High performance frequency

dissemination techniques NA 298.839 298.839 2012

University College Cork (IRL) with Xylophone

Optics (IRL)

498.839 498.839

ESA/IPC(2011)118,add.3 Annex IV, page 1

Annex IV

Compensation by Canada through the Strategic Initiative Programme:

For information only

ESA/IPC(2011)118,add.3 Annex IV, page 2

Approv

al StrIN Ref# Prg Ref# Activity Title

Co-funding entity

Nominal Budget

(kE)

Str. Ini. Share Budget(kE)


Comments

For Info. StrIN-LAU-02-IE

11.343.23

FLPP Period 2 Step 2 (SDT sub-envelope) Core Technologies – Materials & Structures – Upper

part structures FLPP 1330 330 2012

DN with Ruag (CH)

1330 330

ESA/IPC(2011)118,add.3 Annex V, page 1

Annex V

Updates of SIUC/STRIN Activities



funding entity

Nominal Budget

(kE)

Str. Ini. Share Budget(kE)

Year of implementati

on Comments

For information

StrIN-TEC-11-IE G512-008PA Silicon Photomultiplier Module for Scintillator Detection Applications.

GSTP 300 100 2012

Already approved in ESA /IPC(2011)5, add.3, follow on of activity in CV work

plan – SIUC DN with Seusl (IE)

300 100

ESA/IPC(2011)118,add.3 Annex VI, page 1

Annex VI

Activity Descriptions

ESA/IPC(2011)118,add.3 Annex VII, page 2

Programme: EOP Reference: 11.156.13

Title: Optics pre-development for the Multi-directional Multi-polarization Multi-spectral Imager of MetOp-SG – Critical Elements

Total Budget: 2 × 1.000.000 EURO (firm fixed price)

Objectives

The objective of the activity is to demonstrate, through representative breadboarding and environmental/lifetime tests, the feasibility of achieving the required antenna pointing performance and reliability under the predicted MetOp-SG platform and orbital conditions (i.e. 8.5 years, with at least two or three downlinks per orbit). System requirements for this activity will be derived from the results of the two parallel Phase A/B1 studies. Description

The MetOp Second Generation (MetOp-SG) satellites will ensure, starting in the 2019-2020 timeframe, the continuity of the Low Earth Orbit (LEO) meteorological observations currently performed by the MetOp series of satellites. Data downlink rates in the order of 1 Gb/s will be required, which are substantially higher than what the X-band (i.e. between 7.750 and 7.9 GHz) for meteorological satellites can support. For this reason, MetOp-SG considers as baseline to use the K-band (i.e. also called 26-GHz band, between 25.5 and 27 GHz) for the data downlink. Unfortunately, this band suffers from higher propagation losses than in the traditional X-band, and these losses can only be compensated with the use of steerable antennas that provide higher directivity than the traditional isoflux fixed antennas. Mechanical steerable antennas are simpler than electrical steerable antennas, which may suffer from possible phase jumps that could seriously affect the tracking performance. In the two MetOp-SG Phase A/B1 parallel studies led by Astrium SAS (F) and Thales Alenia Space France (F), the downlink baseline consists of two redundant mechanically steerable antennas. The main concern is now to ensure that the antenna pointing mechanism can meet the high reliability expected for this operational mission.

Deliverables

Current TRL: 4 Target TRL: 5 Application Need/Date:

Application Mission: Contract Duration: 24 Months

S/W Clause: NA Reference to ESTER

Consistency with Harmonisation Roadmap and conclusion:

NA


Programme: EOP Reference: 11.156.14

Title: Highly Stable Antenna Breadboard for the Wind Scatterometer of MetOp-SG

Total Budget: 2 × 600.000 EURO (firm fixed price)

Objectives

The objective of the activity is to demonstrate, through breadboarding and tests, the feasibility of achieving the required antenna gain stability of better than 0.03~0.04 dB under the predicted LEO conditions. Requirements for this activity will be derived from the results of the two parallel phase A/B1 studies, led by Astrium SAS (F) and Thales Alenia Space France (F).

Description

The MetOp Second Generation (MetOp-SG) satellites will ensure, starting in the 2019-2020 timeframe, the continuity of Low Earth Orbit (LEO) meteorological observations currently performed by the MetOp series of satellites. The windscatterometer (SCA) instrument will deliver Earth surface radar backscatter measurements for primarily deriving vector wind fields over ocean and soil moisture over land. SCA will provide wide coverage, high sensitivity, good spatial resolution (≤ 25 km) and very high (calibrated) radiometric performance. Addition of second polarisation measurements, i.e. VH, is considered as an option. At the conclusion of Phase 0, an ASCAT-type fixed fan-beam concept has been selected as baseline. The on-going Phase A/B1 of MetOp-SG therefore assumes use of 6 waveguide array antennas configured in 3 antenna-pair assemblies similar to those of ASCAT. The antennas, with a length of 2.9 to 4 m, shall be passive, low loss and highly stable in order to meet the stringent instrument radiometric stability requirement of 0.1 dB

Deliverables


Application Mission:

Contract Duration: 18 Months



NA


Programme: EOEP Reference: Title: Algorithms for estimating snow grain size Total Budget: 150 keuro

Objectives

The activity aims to answer a key issue for the retrieval of snow water equivalent from SAR data, namely the estimation of effective grain size. A reasonable estimate for effective grain size (background value for regularisation) is essential for the performance of the retrieval algorithms. In order not to tie the retrievals to sparse weather/snow pit stations (as applied e.g. in GLOBSNOW), the procedure to be developed should be globally applicable. This means the algorithm should use time-varying auxiliary data that are globally available (e.g. data from land surface parameterisation of GCMs). A possible procedure is known but it needs further development, tests and systematic analysis over several different snow and ice regimes. Description

The activity will comprise tasks covering: - State-of-the-art, problem analysis and requirements. - Elaboration of physical concepts for grain size parameterisation scheme - Development of algorithms for grain size parameterisation, including selection of time-varying auxiliary data to be used

- Software implementation, documentation - Performance analysis, testing with experimental data - Conclusions and recommendations.

Deliverables

Reports; Validated samples;

Current TRL: NA Target TRL: NA Application Need/Date: 2012


CoReH2O Earth Explorer, future SAR missions at small wavelengths Contract Duration: 6 mo.

S/W Clause: Reference to ESTER


N/A

ESA/IPC(2011)118,add.3 Annex VI, page 5 Programme: EO Dev Exploitation Reference: Title: Glacier Lake High Mountain Hazard/Risk Estimation Service Total Budget: 300k Euros Objectives The proposed activity shall address the outcome of the ESA DUE Innovator2 GLOF (GLOF) project evaluation and evolution assessment. Within the GLOF project a service for glacier lake mapping was established in corporation with a strong user community consisting of ICIMOD in Himalaya, FOCUS Humanitarian in Tajikistan, SDC (Swiss Development Agency), FOEN (Swiss Federal Office for Environment) and the integrated high mountain risk management scientific community through GAPHAZ. The service is currently applied for the monitoring of a glacier lake in China within a Swiss-Sino project funded by SDC. Within the service evaluation and evolution activity major requirements were formulated by the user community for a continuation activity: • Capacity development/building needed* • Integration of information* • Linked with other hazards* • Focus on community level* • The activity has to be seen in the context of High Mountain Risks and the development has to address this.* • Service needs to be extent/adapted to Arctic and South American GLOF* Consequently possible future lines of activities are: • Addressing immediate needs of the users* • Glacial lake inventory** • Support of hazard/risk assessment* • Systematic monitoring • Operational detection of changes While the focus of the GLOF project was the mapping of glacier lake outlines, a follow-up activity needs to focus on the context of Glacier Lakes, information integration, completion with additional information/modelling, first order risk/hazard assessment. The requirements indicated by * are addressed within this proposed activity, ** are partly addressed.

Description Following the User Requirements summarized above the following work tasks can be identified: l. Bring together information based on EO data related to GLOF, namely: • the glacier lake extent and temporal behaviour, possibly volume (e.g. inventory for a given area, at defined interval) • the mass movements above, around and below the lake • the glaciers state • topographic analysis of lake dams and downstream area and complement • with simple models on permafrost • potential outburst assessment • ice/snow avalanche assessment 2. Use the information of l. for an initial first-order risk/hazard assessment including. 3. Capacity building on l. and 2. in the target areas (training courses etc.) depends on additional funding by SDC-The activity is planned in three phases, the initial phase, the implementation phase and the evaluation and evolution phase: I. The initial phase is conducted as a pilot study in the Canton of Valais (Switzerland) supported by FOEN using as much as possible existing data (EO products, maps) from other projects such as Terrafirma, DORIS, DUE GLOF and in-kind contributions from FOEN. The aim is to do the work tasks outlined above (data production and assimilation, modelling and hazard/risk assessment) as a demonstrator that can be transferred to the target areas of Phase 2, the implementation of the methodology. II. Adapt the pilot study to the target areas below: l. Tajikistan (Priority country of SDC, collaboration with FOCUS) 2. Peru/Bolivia (Priority country of SDC) 3. Greenland (Asiaq) 4. Island (potentially) III. Evaluation and Evolution of the Service and Methodologies in particular with respect of a regular monitoring. A good project team is crucial for the task as the project is demanding on expertise for various disciplines and good interaction of the different experts is necessary. The foreseen project team consists of experts with a long track record and established links: • GAMMA Remote Sensing AG, Switzerland, Project Lead and EO (SAR data) expert, PI of the GLOF project. • ENVEO IT, Austria, EO expert • Geographical Inst. Uni Oslo (GUIO), Norway, Scientific Advisor, risk/hazard assessment • Geo Uni Zuerich (UZH), Switzerland, risk/hazard assessment • ASIAQ, Greenland, Denmark, local partner, experts in mapping, geographic information, hydrology, climate, environment, and surveying and geotechnical investigation. Foreseen users/partners: • FOEN (Swiss Federal Office for Environment), partner for pilot study • SDC (Swiss Development Agency), partner for Peru/Bolivia and Tajikistan • FOCUS Humanitarian (partner for Tajikistan)

Deliverables l. Pilot Study Report 2. Tajikistan Implementation Report 3. Peru/Bolivia Implementation Report 4. Greenland Implementation Report 5. Island Implementation Report 6. Evaluation and Evolution Report

Current TRL: Target TRL: Application NeedlDate:


Terrasar-X, Cosmo-Skymed, Radarsat2, Sentinel

Contract Duration: 24 -36 Months

SlW Clause: No software will be developed within the project

Reference to ESTER



Programme: StrIn Reference:

Title: Development of array radiometer core breadboard

Total Budget: 800 kEuro

Objectives

The objective of the activity is to build demonstrator modules on subsystem level. The target instrument is a 14 pixel heterodyne radiometer with 340 GHz center frequency and a total analysed bandwidth of 12 GHz for each pixel. The radiometer core consist of front-ends, IF system and back-ends. The activity will benefit from individual components and functions that have been prototyped and verified in earlier activities. The focus in this activity is to package these functions into flight representative hardware in terms of mass and volume and also further verify the system performance. The instrument is split into 4 subsystems, 2 with 4 pixels and 2 with 3 pixel radiometer channels each. These can be verified independently.

Description

The activity is split into three phases that partly overlap. 1) Updated component prototypes for selecting components and details of implementation 2) Subsystem design, implementation and performance verification 3) System implementation of a 4 pixel part of the instrument and performance verification

Subsystem performance is also verified on system level, i.e. there is a smooth transition from (2) to (3). The basic subsystems are Integrated Front-end demonstrator, quad (x4) module with physical integration, interfaces towards horn array and thermal interfaces taken into consideration Back-end demonstrator where the main focus in on meeting size, mass and power consumption targets LNA demonstrator, new design iteration on module level IF system, quad module demonstrator including bias circuits, meeting bandwidth, gain and stability requirements

Deliverables

Technical Notes Technical Reports

Current TRL: TRL 4 Target TRL: TRL 5 Application Need/Date:

Application Mission: EO missions for atmospheric composition monitoring”

Contract Duration: 2011



NA

ESA/IPC(2011)118,add.3 Annex VI, page 7 Tailored On-Board Computer EM for planetary landers

Programme: MREP Reference: E901-002ED

Title: Tailored On-Board Computer EM for planetary landers

Total Budget: 700

Objectives

The main objective of this activity is to develop an engineering model of a tailored, highly integrated, low mass and low power On Board Computer core to be used in planetary landers.

Description

The Robotic exploration programme requires the use of on board computers in planetary landers where mass, power and sizes are critical constraints.In particular the Network Science mission concept asks for a drastic mass miniaturization of the lander (approx. 150kg entry mass with P/L). Existing on board computers cannot satisfy these requirements and there is the need to rationalise the computer architecture with the prospect of a significant mass, power and dimensions reduction. This activity will study and develop the concept of an architecture based on SCOC3 ASIC (SoC) and to be used as part of the On Board Computer of a lander in robotic exploration programs. One of main objectives of the activity shall be to optimise as much as possible the mass/volume/power of the Controller and the needed surrounding electronics (memories, power supplies regulators, etc.) whilst keeping an acceptable level of performances. The Controller shall include the TM/TC, the reconfiguration and the main computer functions and shall provide standardised hardware and software interfaces (SpW, 1553, CAN, but also future evolution like SpaceFibre) with the other Space Segment S/s. The On Board Computer shall implement a modular architecture that allows to include additional modules (like Mass Memory , HK modules, Motion Control module) controlled by the On board Controller. Also power distribution modules can be added to the OBC (e.g. to supply the GNC units). The modular architecture could be physically implemented into a single unit or as a decentralized one (i.e. more modules/units ). In both the cases standardized electrical interfaces (e.g. SpW) shall be used also as internal I/Fs. The use of miniaturized connectors, highly-integrated interfaces and wireless technologies (for debugging purposes at least on ground) shall be exploited. Hardware and software power saving techniques (such as processor-frequency scaling and software driven off-idle-operative states individually selectable for the various implemented functions) shall be investigated in order to optimise the power consumption and leave the Controller in the lowest power state that satisfy the functional requirements during each phase of the mission. Depending on the mission scenarious the Controller shall be able to be configured as a reliable computing system or as high available system. In the first case the Controller must be operational for a long period of time and in case of failure a reconfiguration outage is acceptable. In the second case the availability of the Controller during critical phases like entry, descent and landing shall be guaranteed also in case of failure. Configurability according to the availability requirements shall be a driver for the design of the Controller and different redundancies schemes shall be properly addressed at hardware and software level. The activity shall start with the definition of the requirements for a Tailored OBC for Small Landers.

Deliverables

1) Requirements Specification and Design & Analysis docs 2) AIT procedures and reports, 3) An Engineering Model (EM) of a miniaturised on Board Controller unit.


2012

Application Mission: Network Science Contract Duration: 18

S/W Clause: Operational SW Reference to ESTER T-8382 ,T-7803,


A highly integrated core built up into few large ASICSs is mentioned in the Data Systems and OBCs harmonization dossier.


Accelerometer component to TRL5

Programme: MREP Reference: E905-016EC

Title: Accelerometer component to TRL5

Total Budget: 700

Objectives

1) To develop and demonstrate by test, a European accelerometer component with integrated readout electronics and performances compatible with future ESA exploration missions

Description

This activity shall be based on the TRP accelerometer feasibility demonstrator protoyping (T705-032EC). That activity has already shown the feasibility of the detector element via manufacture and test and performed the feasibility assessment of the enhanced, radiation hard analogue ASIC required to drive and condition the detectors. No radiation testing has been performed. This activity shall develop, manufacture and test to TRL5, an European accelerometer as a component suitable for integration into a gyro and compatible with being used as a stand alone acceleromter. The accelerometer component shall consist of co-packaged 1g and 20g detectors with a fully radiation hardened analogue readout and control ASIC allowing enhanced performances. This activity shall result in a prototype fully representative of the envisaged end product in terms of performance, packaging and radiation hardness. The prototype accelerometer shall be subjected to full performance and radiation testing. The remaining work to reach a to fully qualified EEE component is expected to consist of implementation of any design corrections arising from testing, full batch procurement and detailed evaluation and qualification testing. This would be handled under separate contractual cover.

Deliverables

Final report Prototype accelerometer components *10


TRL5 by 2013

Application Mission: All future exploration missions Contract Duration: 21

S/W Clause: NA Reference to ESTER T-7818


AOCS Sensors and Actuators Harmonisation 2009 - Accelerometers, AIM A2 and A3

ESA/IPC(2011)118,add.3 Annex VI, page 9 High specific stiffness metallic materials

Programme: TRP Reference: T924-002QT

Title: High specific stiffness metallic materials

Total Budget: 500

Objectives

To select and characterise metallic based materials having specific stiffness above currently used metals in view of reducing lander/ rover structural mass.

Description

The specific stiffness of all metals widely used in space application is about 24 GPa cm3/g. Hence, the benefit of using one metal instead of another is limited when dealing with stiffness driven applications. In this study the metallic reinforcement state of the art will be reviewed for aluminium and titanium alloys; only means of increasing steadily specific stiffness for metallic materials. The in-situ formation of TiB reinforcement in titanium alloy, the Oxide Dispertion Strengthening (ODS) in Aluminium alloys and the concept of Metal Matrix Composites (MMCs) for both Aluminium and Titanium will be traded-off and the most promising materials will be selected for further development and characterisation. Characterisation will be performed according to Martian mission conditions. With the hypothesis that the current design can be retained with highest specific stifffness alloy the weight saving could be up to 70% (probably quite optimisic) - With the hypothesis that current design has to be modified to accommodate processing limitations of the high specific stiffness material weight saving could be 50% (less optimistic). With the hypothesis that only some high stiffness ODS alloy is used, weitht saving would be 20% (pessimistic). Upon adequate characterisation of materials and associated processes, design could be refined to allow additional weight saving. As example, data in literature show: MMC based Ti alloys specific stifffness increased from 40 to 70%. For aluminium alloys, specific stiffness doubled. This leads to a 50% weight saving. With ODS aluminium, increase is 20% in specific stiffness. These types of technologies are required to reach the mass target value of landers / rover. Such high performances alloys could be used also in less demanding application reducing further the mass. NB: This TDA is not competing with the activities on magnesium alloys currently led by David Jarvis, where the structural aspects are not the primarily objectives

Deliverables

Technical notes, test-plan, test report, test-samples

Current TRL: 3 Target TRL: 5/6 Application Need/Date:

2014

Application Mission: IM Contract Duration: 18

S/W Clause: NA Reference to ESTER T8393



Material compatibility assessment with a hydrogen peroxide sterilisation process

Programme: TRP Reference: T224-002QI

Title: Material compatibility assessment with a hydrogen peroxide sterilisation process

Total Budget: 150

Objectives

Planetary protection regulations limit the probability of contamination of the Jovian moon Europa to less than 1E-4 per mission. Should this requirement not be met by implementing sufficient reliability of the flight system avoiding accidental impact on Europa, a low temperature sterilisation process could be envisaged. This activity would assess material compatibility with such a low temperature sterilisation process.

Description

Materials representing a large surface area on the proposed Laplace spacecraft are identified based on the two industrial team's study results. A material test program is established based on standard test procedures for the specific material, its specific use and the particular impact expected from exposing the material to a hydrogen peroxide sterilisation cycle. Test program is carried out and material compatibilities are identified for subsequent use in the Laplace development phase. The activity will be carried out with reference to process ECSS-Q-ST-70-56.

Deliverables

Material test program for review; Material compatibility assessment report.

Current TRL: N/A Target TRL: N/A Application Need/Date:

2013

Application Mission: JUICE Contract Duration: 18



ESA/IPC(2011)118,add.3 Annex VI, page 11 Qualification of radiation tolerant FLASH memory

Programme: CTP Reference: C223-056QE

Title: Qualification of radiation tolerant FLASH memory

Total Budget: 500

Objectives

NAND-Flash provides non-volatility and the highest storage density of today's semiconductor memory technologies. They also present a relative good tolerance to the space radiation environment. The objective of this activity will be to radiation qualify the next generation of FLASH memory and to secure the supply of memories for the needs of the Laplace mission.

Description

The radiation requirements for Laplace are quite severe, in particular for TID (total ionizing dose, > 150krad), but also SEE (single event effects). TID typically induces a progressive shift of the device characteristics and terminates in non-functionality at high dose. SEE is a random phenomenon, which can potentially induce transient or persistent Functional Interrupts (SEFIs), or latch-up or destruction. Both TID and SEE can have dramatic effects and should be carefully assessed. The radiation tests of the present generation of NAND Flash memories have shown that NAND Flash are more sensitive to TID than conventional present-day CMOS technologies, mainly because of the internal high voltage circuitry used for cell programming. The high voltage generator, as well as the state machine and all the periphery (register, address and data buffers) are also sensitive to SEFIs. Device destruction have also been observed but in extreme conditions and with a low probability for a space mission. The radiation study for the next generation of NAND-Flash will involve: 1. Selection and procurement of three types of NAND Flash memory candidates from the COTS market (Samsung, Micron, etc) 2. TID testing, investigation of dose rate effects, annealing, memory operation mode during irradiation, part to part variations 3. SEE testing, characterization of SEFIs and destructive events (if any), investigation of angle effects (from normal to grazing) 4. Analysis of radiation results for the Laplace mission, calculation of the in-flight SEE rates (depending on the mission phase). In particular, the TID results will be the bottleneck for the Laplace mission. The TID tests will focus on the device behavior as a function of the operation modes (storage, read, program). The influence of the dose rate and annealing, the part-to-part and lot-to-lot variations will be studied. A FLASH type will be selected in order to meet the mission requirements. One of the lessons learned from the previous and present radiation studies concerns the short lifetime of COTS components, especially in the competitive memory market. Technologies are rapidly evolving, and components are usually obsolete within 3 or 4 years. An important point of the study will be to rapidly select one preferred candidate among three types of NAND-Flash. This will be the objective of the first TID and SEE experiments. The selected candidate will then be purchased in large quantity for the Laplace applications. The following TID and SEE experiments will then concentrate on the selected candidate for an accurate prediction of the memory in-flight behaviour.

Deliverables

T0 + 6 months: Procurement of three types of NAND-Flash T0 + 12 months: Report 1, first TID experiments, T0 + 18 months: Report 2, first SEE experiments, procurement of the selected candidate in large quantity, T0 + 24 months: Report 3, second TID experiments on the selected candidate, T0 + 30 months: Report 4, second SEE experiments on the selected candidate, T0 + 36 months: Final Report, analysis and calculation of the failure rate for Laplace


2015

Application Mission: JUICE Contract Duration: 36



Characterisation of actuator behaviour for a cryogenic fine steering tip-tilt mechanism

Programme: CTP Reference: C215-118MS

Title: Characterisation of actuator behaviour for a cryogenic fine steering tip-tilt mechanism

Total Budget: 300

Objectives

This activity aims at the characterisation of a space qualified actuator (e.g. piezo-electric) that would be used in a 2 degree-of-freedom mirror fine steering mechanism operating under cryogenic temperature conditions (<50K).

Description

This activity aims at the characterisation of a space qualified actuator (e.g. piezo-electric) that would be used in a 2 degree-of-freedom mirror fine steering mechanism operating under cryogenic temperature conditions (<50K). Among other science missions, this would largely benefit EChO, by simplifying its fine pointing control and eventually replacing the constraining micro-propulsion solutions. The main effort will be focused on the evaluation of thermo-mechanical behaviour and performances of the actuator in operational conditions, to reach TRL 5, and its capabilities to sustain stresses due to thermal cycles between room and cryo temperatures.


A test campaign under cryogenic temperature shall be performed covering at least: - functional and performance test - thermal cycling - life test under operational conditions

Deliverables

Technical data package


2014

Application Mission: ECHO Contract Duration: 12



Marco Polo R earth re-entry capsule dynamic stability characterization

Programme: TRP Reference: T218-004MP

Title: Marco Polo R earth re-entry capsule dynamic stability characterization

Total Budget: 450

Objectives

To identify different capsule shapes suitable for the Marco Polo R mission and perform a detailed dynamic stability characterization of the selected configuration(s).

Description

The Marco Polo R mission foresees a capsule re-entering the earth atmosphere at high velocity (typically ranging from 11 to 14 km/s) without the usage of a supersonic parachute. In such a situation, the shape of the earth re-entry capsule (ERC) is the result of a difficult compromise between different and conflicting needs: the aerodynamic drag should be as high as possible so to brake high in the atmosphere, the experienced thermal conditions should be confined within the TPS capabilities, and finally static and dynamic stability have to be guaranteed down to the subsonic regime. During the proposed study a preliminary investigation and a subsequent trade-off of different re-entry capsule shapes shall be carried out identifying pros and cons concerning accommodation capability, stability, CoG positioning, thermal exposition, and landing conditions. The focus of the activity shall be the dynamic stability characterization of the ERC. A detailed aerodynamic characterization of the selected configuration(s) shall be obtained with a proper combination of wind tunnel tests (eventually with free oscillation, free to tumble or forced oscillation techniques), free flight models (ballistic and open range tests, drop tests) and CFD simulations.

Deliverables

Reports, recommendations, results of calculations and tests, databases, validated codes and instrumented wind tunnel models, synthesis, recommendations on methodologies.

Current TRL: N/A Target TRL: N/A Application Need/Date:

2014

Application Mission: Marco Polo R, Exploration missions Contract Duration: 24



Sub-Megahertz linewidth laser for Fundamental Physics Missions

Programme: CTP Reference: C217-028PA

Title: Sub-Megahertz linewidth laser for Fundamental Physics Missions

Total Budget: 450

Objectives

The TDA objective is to design, fabricate and test a sub-megahertz linewidth laser operating at 780 nm with performance meeting the requirements of future Fundamental Physics missions.

Description

The TDA objective is to design, fabricate and test a narrow linewidth laser operating at 780 nm with performance meeting the requirements of future Fundamental Physics missions. Key areas to be addressed are output power, spectral and noise performance as well as device reliability and lifetime. The following major tasks shall be addressed in the activity:

ESA/IPC(2011)118,add.3 Annex VI, page 13 - Laser device design - Wafer growth and laser fabrication - Laser characterisation - Device packaging for athermal operation and thermal feedback control - Manufacture of representative number of devices for statistical analysis - Reliability and lifetime testing The contractor shall consider both discrete mode 780 nm devices and frequency doubled 1560 nm devices including the frequency conversion element required to reach the desired final wavelength starting at 1560 nm. Key performance requirements: Laser power: > 100 mW Frequency noise: ~100 Hz2/Hz in the 1-1000 Hz frequency band when locked; Long term frequency stability: <10-10; Power spectrum: 90% of power in 400 kHz; Linear polarization: >95%; RIN: -80 dB/Hz in the 1-100 Hz frequency band ; Long term power stability: 10-2; Hermetic package leakage: <<10-8 Pa.l/s; Angular stability of the beams: <10-4 rad; Transverse position stability: <10 um; Gaussian beam: at 90%.

Deliverables

Laser devices, test reports and technical data package


2014

Application Mission: STE-QUEST, Fundamental Physics Contract Duration: 24




Large radii Half-Wave Plate (HWP) development

Programme: TRP Reference: T207-035EE

Title: Large radii Half-Wave Plate (HWP) development

Total Budget: 600

Objectives

To ensure availability of half-wave plates of sufficient dimension to fulfill the requirements of future Cosmic Microwave Background (CMB) polarization missions.

Description

The Halve-Wave plate proposed as a polarization modulation element in future CMB missions plays a critical role in the overall system performance. This plate is a polarizer modulator which rotates in front of the instruments focal plain detectors. This component allows to measure the B-mode polarization of the cosmic microwave background radiation. This activity will be targeted to the following main areas: ? Study and design of Half Wave Plate (HWP) architectures. ? Address critical technological areas identifying potential solutions. ? Perform critical breadboard development The activity will start with a careful assessment on the requirements. This activity will identify and select the mechanical, thermal and technological solutions and HWP architectures required to achieve the necessary accuracy and stability for a future CMB mission. These solutions/architectures will have to be demonstrated by critical breadboarding (as a minimum at electro and thermo-mechanical representative sample level). Specific attention will need to be given to: Capability to recover the Stokes parameters, capability for foreground removal, cryo operation (if applicable), cooling, power dissipation, noise, wear/tear, diameter, diameter/thickness ratio, anti-reflection coating. A technology roadmap to bring the technology to flight level shall be provided.

Deliverables

HWP breadboard at sample level, technical data package


2013

Application Mission: CMP Polarisation Contract Duration: 18



Fully consistent with the following Dossier: Technologies for (sub) millimeter wave passive instruments

Programme: GSTP Reference: G513-058MM

Title: ANITA2 for International Space Station

Total Budget: 500,000 eur

Objectives

The objective of this activity is to further understand the ANITA-2 accomodation at the ISS and to develop and mature technologies for the development of the second generation ANITA FTIR gas analysis instrument – ANITA2 for use on the ISS. In particular, it intends to: - Assess the ANITA2 accomodation at the ISS, resources required, possible operational scenarios (used together with other ISS monitoring devices to provide a station contamination awareness), including possibility of re-location within different modules (e.g. Columbus EDR facility/Destiny laboratories) or provision of samples from different modules including the ISS airlock with associated possible external contamination products, and provision of data off-line or real time with on-orbit processing. - Improve the design of the optical modulator of the instrument with respect to homogeneity of displacement (i.e. reduce friction forces and improve the magnetic drive mechanism) and associated electronics and control system. - Study and develop the optical alignment hardware, as well as alignment strategy - Develop and characterise a modular breadboard of the ANITA2 instrument, able to accommodate both commercial and custom made parts - Study and confirm hardware requirements related to line shape stability (i.e. wave number stability) and baseline curvature/slope. - Further develop an identified technique to significantly reduce the sensitivity of calibration models to observed significant hardware instabilities (i.e. spectral line shape instabilities), validate its applicability to all molecules of the ANITA2 gas analysis scenario and produce improved calibration models - Increase the general robustness of the improved calibration models with respect to other, less intense line shape disturbances of the spectra acquired by ANITA2 - Assess the impact of these improved calibrations models on precision and accuracy of measurements produced by ANITA2

Description

ESA/IPC(2011)118,add.3 Annex VI, page 15 Following successful mission of the first generation ANITA instrument on board the ISS, lessons learned have been drawn, critical items have been identified and improvements are currently being studied and tested, both on calibration models and hardware side. A technique to make calibration models less sensitive to hardware instabilities has been identified. This technique will also ease the transfer of calibration models from one instrument to the other (e.g. from ground model to flight model). The optical modulator of the instrument has been identified as the main critical issue. A new, custom modulator design has been proposed and successfully tested, standalone, at preliminary breadboard level. Further development of improved, more robust calibration models, as well as further improvement of new optical modulator design is needed. Also, improvements related to other identified hardware-related critical issues (i.e. optical alignment) have to be developed and tested, standalone and integrated into a breadboard of the complete ANITA2 instrument.

Deliverables

Technical notes and documentation, including design and test plans; models and breadboard.

Current TRL: TRL3 Target TRL: TRL4 Application Need/Date:

ANITA instrument for the International Space Station.


ISS Contract Duration: 24 months


N/A


NA

Next generation sub-millimetre wave focal plane array coupling concepts


Title: Next generation sub-millimetre wave focal plane array coupling concepts

Total Budget: 400

Objectives

To develop methods to ensure efficient coupling to large format focal plane arrays.

Description

Observation of celestial features by space telescopes benefits from simultaneous data acquisition by co-located multi-frequency focal plane detector arrays. The benefit comes from the ability to use this co-located data to characterise with low systematic errors the foreground signals of celestial bodies, which is useful to extrapolate their signature at other frequencies, and therefore facilitate their removal when searching for background bodies. Therefore, focal plane elements that are able to operate in various spectral bands are required. At sub-millimetre wave bands, coupling of incoming radiation onto these focal plane elements is achieved by means of either horns or lenses. However, the relatively large size and number of these elements leads to large focal plane array sizes. A potential future B-mode Cosmic Microwave Background mission could be based for example on a dual-reflector telescope system. However, it is not obvious that dual-reflector systems are able to compensate for all aberrations at large offset positions with respect to the telescope’s focal point, therefore making it very difficult to achieve homogeneity of beam patterns across all focal plane detectors. This homogeneity is required to reduce the effect of systematic effects in the combined image obtained by the focal plane array. Therefore techniques to reduce the size of the focal plane are seen as very important enabling technologies. To solve this issue this activity will address the fabrication of multi-frequency/multi-polarization detecting elements. Consequently, the activity shall focus on: - the design of arrays of detecting elements able to operate at various (sub)mm-wave bands and dual polarizations. Methods to interleave several arrays working at different frequencies shall also be investigated. A technology roadmap to bring the technology to flight level shall be provided.

Deliverables

Optimum array layout to reduce size of the focal plane array. Results of the simulations run during the study.


Breadboard of representative multi-frequency/dual polarization focal plane array.


2013

Application Mission: CMB Polarisation Contract Duration: 18



Fully consistent with the following Dossier: Technologies for (sub) millimeter wave passive instruments

Programme: ARTES 20 Reference: 9C.009

Title: Prediction, Monitoring and Alerting of Landslides and Subsidence Affecting the Transport Infrastructure

Total Budget: 300 kEuro (provision for potential StrIn support included in ITT cover letter; relevance of StrIn funding will only become apparent after TEB evaluation)

Objectives

The proposed feasibility study shall assess the feasibility of using space-based assets to assist in developing models that can accurately predict landslides and subsidence likely to affect the transport infrastructure in a number of specific locations; and of integrating this with space-based monitoring and alerting systems in order to reduce damage to the infrastructure, risk to transport users and the costs of both operation and travel disruption.

Description

The study will be carried out in close cooperation with representative users collaborating with ESA (Transport Scotland, Network Rail) in an advisory role as well as in support to the contractor with respect to the tasks as described below.

During the study, the contractor(s) shall:

> engage with the user and stakeholder community and arrive at a complete and consistent definition of the user requirements for predicting, monitoring and alerting of landslides and subsidence affecting the transport infrastructure, based on the shortcomings and challenges in the present operational processes for monitoring, predicting and alerting,

> specify an integrated solution and associated services providing support to the user community across infrastructure management to optimise their monitoring, predicting and alerting, compliant to the user needs and stakeholder conditions, and which employs at least two kinds of space assets, and which will interface to the systems presently in use by the stakeholders and users for monitoring, predicting and alerting of landslides and subsidence,

> identify and evaluate the economic and non economic viability, critical success factors and risks pertaining to the implementation of the integrated solution and associated services, to increase the reliability of, and confidence in predicting of landslides and subsidence for transport infrastructure.

> identify the most critical elements of the integrated solution and associated services, and specify a proof-of-concept to validate these feasibility of this critical elements. This may be a technical or a non technical element. Validation may be by e.g. demonstration, simulation, or analysis.

> conclude on the overall feasibility of the proposed solution and, in case of positive results, to prepare a roadmap presenting the major


milestones towards the successful implementation of a commercially beneficial and sustainable operational service, based on the time needed to comply with the identified critical success factors and mitigate the identified risks,

> identify those users and other stakeholders willing to engage in a demonstration project, providing relevant contributions, driving the solution, enabling market access and promoting the services.

The study is planned for duration of 12 months and represents the first step of activities towards the development of operational services. In case of successful conclusion of the feasibility study and sufficient interest / involvement of relevant users / stakeholders in the targeted services, the continuation with a demonstration project is foreseen (subject to separate approval by JCB, AC, IPC).

Deliverables

Deliverables will include the standard set of documentation of IAP Feasibility Studies, i.e. User / Stakeholder overview and requirements, state of the art analysis, system and service architecture and specification, proof-of-concept (incl. digital media if relevant), viability analysis, implementation roadmap, project web page, and final report. In case, hardware and/or software is developed during the proof-of-concept task, this will also be deliverables.

Current TRL: 1 Target TRL: 2-3 Application Need/Date: 2014/2015

Application Mission: Prediction, monitoring, alerting of landslides and subsidence affecting the transport infrastructure

Contract Duration: 12 months

S/W Clause: n.a. Reference to ESTER n.a.


n.a.

Programme: ARTES 20 Reference: 9B.011

Title: Piracy Prevention and Commercial Navigation in Insecure Waters

Total Budget: 300 kEuro

Objectives

The objective of this ARTES 20 Feasibility Study is to assess the technical feasibility and commercial viability of space based services in order to improve the dual-way enrolment of transiting merchant ships into global anti-piracy situational awareness.

Identified solutions and services shall be able to augment the ship’s near-real time awareness of the already known “possible threats” before they come in the range by receiving the local information of the situation awareness picture from regional anti-piracy centres and anti-piracy coalitions, as well as to augment reciprocally the detection and tracking capabilities of these centres by transmitting relevant information from these commercial ships.

The user community interested in such services typically include ship owners, ship brokers, maritime insurance companies, regional anti-piracy centres, international organisations, anti-piracy coalitions, coastguards, civil authorities in charge of Maritime Safety, etc.

Description

The study will be carried out in close cooperation with representative users proposed by the contractor in support of the tasks as described below.


> map comprehensively the stakeholder community, engage with the user and stakeholder community, consolidate the user demand and identify the key criteria for the targeted services based on the shortcomings and challenges in the present operational processes,

> assess the currently used approaches, to identify the gaps of the current utilized technologies and to envisage the most appropriate technologies to support the service definition,

> specify an integrated solution and associated services in support of the user community involved in piracy prevention activities in order to improve the exchange of information between ships and piracy prevention entities and to generate improved situational awareness integrating at least two types of space assets

> identify and evaluate the economic and non economic viability, critical success factors and risks pertaining to the implementation of the integrated solution and associated services,


> identify the most critical elements of the integrated solution and associated services, and specify a proof-of-concept to validate the feasibility of the critical elements. This may be a technical or a non technical element. Validation may be by e.g. or analysis, simulation, prototyping, or demonstration,

> conclude on the overall feasibility of the proposed solution and, in case of positive results, to prepare a roadmap presenting the major milestones towards the successful implementation of a commercially beneficial and sustainable operational service, based on the time needed to comply with the identified critical success factors and mitigate the identified risks,



Deliverables

Deliverables will include the standard set of documentation of ARTES20 Feasibility Studies, i.e. User / Stakeholder overview and requirements, state of the art analysis, system and service architecture and specification, proof-of-concept (incl. digital media if relevant), viability analysis, implementation roadmap, project web page, and final report. In case, hardware and/or software are developed during the proof-of-concept task, this will also be deliverables.

Current TRL: 1 Target TRL: 2-3 Application Need/Date:

2014/2015

Application Mission: Piracy Prevention and Commercial Navigation in Insecure Waters Contract Duration: 12 months



n.a.


Title: Improvement of Maritime Safety in the Baltic Sea through Enhanced Situational Awareness

Total Budget: 300 kEuro (provision for potential StrIn support will be included in ITT cover letter; relevance of StrIn funding will only become apparent after TEB evaluation)

Objectives

The proposed feasibility study shall assess the feasibility of using space-based assets to improve the situational awareness in the Baltic Sea in order to support the safety of vessel traffic and operations. The study shall identify and assess the viability of services which meet the needs and conditions of the user community on order to support both the prevention of grounding and collision of vessels as well as reducing safety risks and consequential damage after acollision or grounding has occurred.

Description

The study will be carried out in close cooperation with representative users proposed by the contractor in support of the tasks as described below.


> engage with the user and stakeholder community and arrive at a complete and consistent definition of the user requirements for improving the maritime safety in the Baltic Sea through enhanced situational awareness, based on the shortcomings and challenges in the present operational processes for monitoring, predicting and alerting,


> specify an integrated solution and associated services providing support to the user community involved in maritime safety in the Baltic Sea to improve the situational awareness in prevention of grounding and collision of vessels as well as reducing safety risks and consequential damage after a collision or grounding has occurred, compliant to the user needs and stakeholder conditions, and which employs at least two kinds of space assets, and which will interface to the systems presently in use by the stakeholders and users for monitoring, predicting and alerting of landslides and subsidence,

> identify and evaluate the economic and non economic viability, critical success factors and risks pertaining to the implementation of the integrated solution and associated services, to improve the situational awareness in the Baltic Sea.

ESA/IPC(2011)118,add.3 Annex VI, page 19 > identify the most critical elements of the integrated solution and associated services, and specify a proof-of-concept to validate these feasibility of

this critical elements. This may be a technical or a non technical element. Validation may be by e.g. demonstration, simulation, or analysis.


> identify the way forward preparing a demonstration project including a full prototype system and the related pre-operational service to be deployed in the Baltic widely advertised to the regional stakeholder community; to perform dissemination tasks enlarging the awareness and to continue federating the demand (e.g. in the form of a stakeholder workshop)..


Deliverables

Deliverables will include the standard set of documentation of ARTES20 Feasibility Studies, i.e. User / Stakeholder overview and requirements, state of the art analysis, system and service architecture and specification, proof-of-concept (incl. digital media if relevant), viability analysis, implementation roadmap, project web page, and final report. In case, hardware and/or software are developed during the proof-of-concept task, this will also be deliverables.


Application Mission: Improvement of Maritime Safety in the Baltic Sea through Enhanced Situational Awareness




n.a.

Programme: ARTES 20 Reference: 9E.002

Title: Coastal Surveillance and Water Quality monitoring in the Baltic Sea


Objectives

The objective of this ARTES 20 Feasibility Study is to assess the feasibility of using space-based assets to deliver water quality information that has been validated in near real-time in the Baltic Sea region. The proposed integrated solution shall satisfy the needs and constraints of the relevant stakeholders and users, shall be viable for providing sustainable services, and shall employ at least two different types of satellite assets (e.g. satellite navigation, earth observation, satellite telecommunication).

Description

The study will be carried out in close cooperation with representative users in support to the contractor with respect to the tasks as described below.


> engage with the user and stakeholder community and arrive at a complete and consistent definition of the user requirements for monitoring water quality in the Baltic Sea Region, based on the shortcomings and challenges in the present operational processes for monitoring and alerting,


> specify an integrated solution and associated services providing support to the user community across infrastructure management to optimise their monitoring and alerting, compliant to the user needs and stakeholder conditions, and which employs at least two kinds of space assets, and which will interface to the systems presently in use by the stakeholders and users for monitoring water quality in the Baltic Sea Region,

> identify and evaluate the economic and non economic viability, critical success factors and risks pertaining to the implementation of the integrated solution and associated services, to increase the reliability of, and confidence in monitoring water quality in the Baltic Sea Region.

> identify the most critical elements of the integrated solution and associated services, and specify a proof-of-concept to validate these feasibility of


this critical elements. This may be a technical or a non technical element. Validation may be by e.g. demonstration, simulation, or analysis.




Deliverables

Deliverables will include the standard set of documentation of IAP Feasibility Studies, i.e. User / Stakeholder overview and requirements, state of the art analysis, system and service architecture and specification, proof-of-concept (incl. digital media if relevant), viability analysis, implementation roadmap, project web page, and final report. In case hardware and/or software is developed during the proof-of-concept task this will also be a deliverable.


Application Mission: Coastal surveillance and water quality monitoring in the Baltic Sea




n.a.


Title: Special Meteorological Services for Maritime Search and Rescue


Objectives

The objective of this ARTES 20 Feasibility Study is to assess the technical feasibility and commercial viability of space based services improving Search and Rescue (SAR) operations at sea.

SAR operations at sea are highly weather dependant. To make the right choice of intervention means, to optimise the speed of operations, to secure maximum effectiveness without endangering the life of the rescue teams, a very accurate near-real-time meteorological service must be available at small scale (the few miles around the point of operations) and short notice (preferably no more than one hour).

The user community interested in such services are all actors involved in Maritime Search and Rescue, such as operation centres, operators of intervention vessels and helicopters, ship owners, civil authorities, etc.

Description

The study will be carried out in close cooperation with representative users in support to the contractor with respect to the tasks as described below.


> engage with the user and stakeholder community and arrive at a complete and consistent definition of the user requirements for providing near-real-time meteorological services for Search and Rescue (SAR) operations at sea based on the shortcomings and challenges in the present operational processes of the actors involved in Search and Rescue,


> specify an integrated solution and associated services, compliant to the user needs and stakeholder conditions, providing support to the user community in order to optimise their knowledge about the area of operations and support their activities in this area integrating at least two kinds of


space assets,

> identify and evaluate the economic and non economic viability, critical success factors and risks pertaining to the implementation of the integrated solution and associated services, to increase the accuracy and availability of near-real time meteorological services in the area of SAR operations.

> identify the most critical elements of the integrated solution and associated services, and specify a proof-of-concept to validate the feasibility of the critical elements. This may be a technical or a non technical element. Validation may be by e.g. or analysis, simulation, prototyping, or demonstration.

> conclude on the overall feasibility of the proposed solution and, in case of positive results, prepare a roadmap presenting the major milestones towards the successful implementation of a commercially beneficial and sustainable operational service, based on the time needed to comply with the identified critical success factors and mitigate the identified risks,



Deliverables

Deliverables will include the standard set of documentation of IAP Feasibility Studies, i.e. User / Stakeholder overview and requirements, state of the art analysis, system and service architecture and specification, proof-of-concept (incl. digital media if relevant), viability analysis, implementation roadmap, project web page, and final report. In case hardware and/or software is developed during the proof-of-concept task this will also be a deliverable.


Application Mission: Special Meteorological Services for Maritime Search and Rescue




n.a.

Programme: GSTP-5, el.-2 Reference: G526-002MS

Title: Modular Cable Reel SADM Family

Total Budget: 1900 K€

Objectives

The objective is to develop a family of standard Modular Cable Reel SADM (MCR-SADM) for different power transfer which covers most of the future mission needs.

Description

The Solar Array Drive Assembly (SADA) type MCR-SADM shall include all the mechanical and electrical items required to support and rotate the Solar Array Wing (SAW) towards the sun with a maximal travel angle of +/-180°. The required main functions of the MCR-SADM are the following:

to link mechanically the solar array to the platform, once deployed to transfer the solar array power to the platform to provide the solar array grounding to the platform to transfer the solar array sensor signals to the platform to drive the solar array toward the sun within the travel angle to provide the SAW wing angular position with respect to the platform to deliver the SADA house keeping signal (only temperature) to the

platform. The assembly shall also incorporate redundant angular position sensors (most likely a potentiometer) to determine the SADM shaft position with respect to a prefixed reference.


The Power and Signal Modules shall be modular standalone units, able to carry out typical functionalities or applications of transfer modules. The modules shall be easily adapted to the requirements of the customers (e.g. requested number of power transfer) and to the characteristics of the platform (platform interface). The architecture of this modular equipment shall be based on three main parts: � An actuator to drive the SAW and the cable reel � A modular mechanical structured Cable Reel Assembly to fulfil a wide range of power transfer. The following types of modules shall be designed: o 2.5 kW Power Module o 4.5 kW Power Module o Signal Module � Platform Interfaces and Harness The MCR-SADM shall be able to fulfil the SAW maintaining to the sun for all LEO Orbits, e.g. SSO and for GSO, IGSO and MEO.

Deliverables

QM with the associated QR data package

Current TRL: TRL 3 Target TRL: TRL 6 Application Need/Date:


EO and Telecom missions. 2014. This design should be applicable to a wide range of missions.




Harmonisation Roadmap: Solar Array Drive Mechanisms – Activity C3


Programme: GSTP Reference: G512-008PA

Title: Silicon Photomultiplier Module for Scintillator Detection Applications.


Objectives

This activity is a direct continuation of the ongoing CTP/StrIn activity “Enhancement of a silicon photomultiplier module for scintillator detection applications”, funded with 490k€, being developed by SensL (IRL).

Description

The new generation of high resolution gamma-ray spectrometers for remote planetary sensing are based on large volume, high light output scintillators - the cerium doped lanthanum halides (LaX3). These materials achieve excellent spectral resolution, due to the large number of scintillation photons produced per MeV of absorbed energy. In fact, the light output is such that their performance is currently limited by conventional readout systems based on vacuum photomultiplier tubes (PMTs). In order to replace vacuum tube PMTs, ESA is working towards the development of a new solid state readout system, and a previous activity has shown that Silicon Photomultiplier (SiPMT) detectors are viable options for scintillation readout. These devices are robust, operate at low bias voltage, are radiation hard, are immune to magnetic fields and have the necessary gain and dynamic range to allow the linear operation of lanthanum halide based spectrometers. The technology is further being developed by a currently running CTP activity which involves the design and fabrication of new detector structure optimized for blue detection response. Following confirmation of the detector performance, the detector will be assembled into an appropriate package and full readout electronics designed and incorporated into the detection module. Within this context, the objective of this activity is to continue the work already initiated in the CTP activity, focusing on the testing and qualification of the silicon photomultiplier module developed. Task 1.- Qualification testing. The testing shall include radiation dose testing, vibration/shock, thermal vacuum and reliability in line with component related ECSS and ESA PSS standards. Task 2. - Module performance verification. A module performance test programme demonstrating the module performance compliance with the requirements will be undertaken.

Deliverables

Technical notes and documentation; tested SiPMT modules, test and qualification reports.


2012


Applicable to future Cosmic Vision programme missions in both the solar system and astrophysics domains. The SiPMT technology is also generically




NA


Programme: GSTP Reference: G517-116SW

Title: Mission On-Board Planning System

Total Budget: 150

Objectives

The objective of this activity is to develop an advanced mission planning prototype to TRL 5 so that it is available for flight and operations in future missions.

Description

Previous ESA funded activities (O-BIPPS and MMOPS – Mars Mission On Board Planner and Scheduler) have led to the development of an artificial intelligence based planning and scheduling system for on-board use. Having demonstrated the functionality of the system in a representative environment the goal is now to turn the prototype software component into software which is fully compatible with the current on-board computational environment. There is often debate over the suitability of autonomy for some missions so the activity will also characterise the performance and benefits of this technology using spacecraft simulators and emulation environments.

Deliverables

Technical notes and documentation; software component, test hareness; operations software.

Current TRL: Prototype Target TRL: Beta version Application Need/Date:


Any mission needing autonomy. Contract Duration: 18 Months


On Board Software Roadmap


T-7743


Programme: GSTP Reference: G604-11EP

Title: Study, Development & Verification of a Planar Transformer

Total Budget: 40

Objectives

.

Description

The changes concern the scope and budget of the activity. The objective of the proposed additional work is to qualify the process for producing planar transformers for a power range of 10 W to 500 W, whereas the current maximum power is 100 W. Several European companies expressed interest in this technology during the ESPC (European Space Power Conference) conference held in June 2011, when the results obtained so far were presented. However, these potential customers were demanding a slight increase in power, hence leading to the now targeted 10-500 W range. This increased power range will be able to cover most of the applications of power converters in a satellite: from a small DC/DC converter used as an auxiliary supply to one of the main converters used in a PCDU (Power Control and Distribution Unit). Moreover, the new higher power limit does not imply the use of new technologies, being rather a matter of size increase (designing a bigger transformer). The main advantages of these transformers lie in better electrical performance and lower height of the component. For instance, leakage inductance can be reduced by 50% and height can be reduced by more than 30%. It therefore becomes possible to build more compact modules and reduce the overall volume. These improvements are significant when compared to conventional transformers which are relatively tall and often constitute the bottleneck to reduce the height of a PCDU (Power Control and Distribution Unit) module. Whereas planar transformers have been used in terrestrial applications since the mid 90s, their qualification for space applications was undertaken through this GSTP-4 activity, initiated in 2008. Several EMs were successfully manufactured and tested, with a designed power range going from 10 W to 100 W. The prototypes underwent a full test process although not in vacuum. The thermal cycling was performed with air. The TRL reached is 4. The results were promising, showing that the qualification is possible since no showstoppers were identified. Qualifying the process to produce this type of transformers will eventually turn them into an available product for the European space industry. The qualification of the full power range requires various technologies such as polyamide PCBs, copper foil isolated with kapton, aluminium clips to drain heat, adhesives, coatings, etc. All have to be put together in such a way that the process qualification is successful.

Deliverables

The test sequence definition still has to be completed but is expected to include: Visual inspection,

Physical properties,

Screening,

Functional electrical,

Dielectric strength,

Power burn-in,

Thermal cycling,

Shock and vibration.

For lot acceptance, DPA (Destructive Physical Analysis) will be also performed.

Current TRL: Target TRL: Application Need/Date:

Application Mission: Contract Duration:




Programme: ARTES 3-4 Reference: 5D.025

Title: Development of 2nd Generation Telemetry and Beacon transmitter

Total Budget: 1,500,000 € (price to ESA) / 3,000,000 € (cost)

Objectives

To design, develop and qualify the second generation Norspace Telecommand and Beacon Transmitter (Bx2/Tx2) for GEO satcoms

Description

The proposed development will result in a more competitive Telecommand and Beacon Transmitter for the commercial telecommunication GEO market, covering also the Ka frequency band. It is foreseen to update the unit architecture to accommodate all frequency plans (C, Ku, Ka) but at the same time maintain its modular design. The modular design allows flexible integration of unit variants (transmitter/beacon, single/dual/multiple frequency, output frequency band, transmitter power and bus interface), keeping the unit cost down and the time-to-order low. The LO section will be modified, using a LO output signal with frequency in C-band instead of the presently used L-band. This requires redesigning the LO section as well as the L-band phase modulator hybrid. Furthermore, the design will be modified to also accept digital (RS422) telemetry input signals instead of the analogue inputs, broadening the possibility to satisfy potential customer needs. The transmitter output stages will be modified to accommodate the Ka-band, in a design where the TAS power amplifier hybrid is replaced with an alternative component. The power conversion of the unit will match all potential primary bus voltages and support any new internal voltages that may be required. Two EQMs, one of the 2nd generation beacon and one of the 2nd generation transmitter will be manufactured to cover the most important equipment variants requested by the market. They will be fully tested to a set of environmental requirements enveloping those of all major telecom satellite manufacturers.

Deliverables

EQM 1 Beacon transmitter unit in Ka-band, at 27dBm output power and 50-100V power bus interface. EQM 2 Telemetry transmitter unit at Ku-band, at 28dBm output power, with RS422 digital TLM interface and

35-50V power bus interface. All associated Design and verification Documentation: Specifications, Manuals, Design, Manufacturing and

Verification documents

Current TRL: Target TRL: Application Need/Date:

2013/2014




N/A



Programme: ARTES 34 Reference: 8G.015

Title: SATMODO

Total Budget: 610,000 € (cost)/ 300,000 € (price to ESA)

Objectives

SATMODO will demonstrate the possibility to provide harvester with a “Forest Warehouse” operating model, assigning the most appropriate instruction files to the most appropriate in-forest harvesters in order to meet industry demands.

Description

The SATMODO system will be used to provide a data back-haul and communications platform for harvesting vehicles, whereby the harvesting work flow can be managed in near real-time in order to deliver a fully integrated management system to customers. In the proposed baseline, SATMODO envisages to use the new Inmarsat IsatM2M services supporting two-way burst messaging over world-wide satellite coverage (except the poles), using L-band remote terminals with highly compact antennae. The following hardware and software subsystems will be developed during the project:

Power management unit (with power conditioning) In-vehicle unit Communication server Applications SW, user tools and associated Graphical User Interface

The SATMODO system will be deployed on the field and integrated in 20 forest harvesting machines in Ireland, with three different user organisations (two public organisations: Green Belt and Forestry Commission of Scotland, and one private: Coillte). Several logging sites will be affected by the pilot operations. The pilot utilisation will be aimed at validating the SATODO system, understanding how the system will influence the behaviour of the users, gathering their experience and measuring the potential benefits through a set of Key Performance Indicators.

Deliverables

Project documentation including requirements definition, development and verification. Communications server and remote terminals (HW and SW), web based management system, pilot utilisation report.


Q1/2013


Contract Duration:


N/A



Programme: Reference:

Title: RAD HARD Miniature POINT of LOAD

Total Budget: 1500,000 EUR

Objectives

This μPOL unit can replace existing legacy devices as well as US components that provide power conversion for any low voltage powered electronics. The intent is to use European components, especially in close collaboration with ST Microelectronics. Furthermore, standardized μPOL devices will drastically streamline and reduce the development cost of equipment’s power distribution systems, in the sense that a recurring μPOL part will act very much as a tested and qualified “building block” for the design engineer and the secondary power distribution will not be a fully customized new design for each new equipment design. The proposal is based on heritage from three years of national developments for the Swedish National Space Board and includes important technologies such as patent pending microfabricated microcoils (μCoils) with ultra-low resistance which holds promise to enhance the performance above internationally available related products. As a summary, the μPOL serves as an accurate voltage control on multiple nodes achieving multifactorial improvements for the Space Equipment manufacturing: - Increased performance can be achieved on low voltage regulation accuracy - Transient performance for low voltage/high current nodes is improved - Efficiency optimisation is easier to control for the designer - Reduction of total mass and volume - NRE development costs can be lowered - Extended temperature range

Description

In two national projects, a miniaturised POL using radiation tested commercial components has been developed. Certain elements from this design can be used as a starting point in this development. Several techniques, such as resonant gate driving, different control loop structures and different kinds of protection circuitry have been evaluated in these projects. Techniques used in the miniaturisation of power electronics have also been developed. This provides valuable knowledge for an proposed POL design. In the same project, a patent-pending power coil has also been designed. This coil is based on the principle of depositing copper directly into milled tracks on the coil ferrite, reducing the size and weight of the coil while also reducing the series resistance. Using this technique, it is possible to build a smaller and more efficient POL compared to using commercially available coils. Two previous projects has been carried out on national funding for the Swedish National Space Board (SNSB), “POL2 – Manufacturing and space qualification of μPOW™ Point-of-Load”, and “POL – Development of Point-of-Load”. Four POL devices from POL2 have been prepared for space flight on the ÅAC spacecraft payload QuadSat-PnP on the OHB built Venta-1 spacecraft due for launch in Q4 2011. The current design includes over voltage protection, resonant gate drive, input current limiter, and a mixed assembly technique combining wire bonding and flipchip soldering.

Deliverables

EM fully tested and validated


end 2014 (end of the ARTES 3-4 follow-on activity)


The scope of this proposal is to develop a radiation-tolerant, low cost, miniature Point-of-Load (μPOL) European power converter, primary for geostationary telecommunication satellites, as well as earth observation, science missions and national long duration missions.

Contract Duration: 24 Months


N/A


NA


Programme: TRP Reference: T303-001EP TD03

Title: Regenerative High Temperature PEM Fuel Cell (HTPEM) Development


Objectives

To select regenerative high temperature Polymer Electrolyte Membrane (PEM) fuel cell system, to assess technology against space exploration requirements and to characterise the technology by tests

Description

The achievable energy density of a regenerative fuel cell system stack is significantly higher than that of any practical battery, but it has significantly higher complexity than batteries. The alkaline fuel cell used onboard the American space shuttle has a specific energy of 1kW/kg including reactants for a ten days mission. High temperature Polymer Electrolyte Membrane fuel cell (HTPEM) offers high specific energy like alkaline fuel cell but works at much higher temperature. The HTPEM has a one phase system when alkaline fuel cell (below 100°C) has a two phases system (gas and liquid). The complexity can be significantly reduced by operations above 100°C, when only 1-phase gas loops are present. Higher working temperatures facilitate the waste heat removal as well, therefore HTPEM fuel cell is proposed with working temperatures between 150 and 200°C. Fuel cell efficiency is lower than batteries efficiency, but can be improved by using more expensive materials and pure oxygen instead of air. Reactants shall be pure hydrogen and oxygen. The electrolyser shall be capable of operation up to 100 bar, which requires conventional PEM electrolyte, but avoids any mechanical compression. Fuel cell and electrolyser components are available. The present activity focuses on a complete regenerative fuel cell, high temperature PEM fuel and electrolyser. The following tasks will be included in the activity:

- Review of regenerative HTPEM fuel cell elements (fuel cells and electrolyser) available in Europe and worldwide.

- Assessment of the technology against space requirements in term of specific energy, cyclability, degradation

(lifetime).

- Selection of best available European technology.

- Evaluation of selected regenerative fuel cell system by characterisation testing.

Deliverables

Study Report

Current TRL: TRL2 Target TRL: TRL 3 Application Need/Date:

Moderate cycle life requirement missions initially targeting 2016-2017 need date.

Application Mission: Contract Duration: 24 months

S/W Clause: NA Reference to ESTER T-7761,



Programme: FLPP Period 2 Reference: Item 11.343.22

Title: FLPP Period-2 Step 2 - Activities related to Materials & Structures: Thermoplastic Composite for Primary Structure

Total Budget: 1.4 M€ (out of which 700 k€ from Strategic Initiative)

Objectives

To design, manufacture and test a significant section of a thermoplastic composite (TPC) Interstage Structure (ISS) To bring the various technologies in thermoplastic composites for launcher structures to TRL 4/5

Description

The demonstrator will consist of a structurally-significant representation of the large diameter structure, complete with integrally-assembled stringers and frames. The following technologies will be demonstrated to TRL 4/5: Automated tape-placement of TPC skins Press-forming of TPC stringers and frames More cost-effective production of pre-consolidated TPC sheets for press-forming Machining, drilling and trimming of TPC structures Bonding of stringers and frames to skin structure Non-destructive testing of TPC structures Mechanical testing of sub-elements Design, stress and test engineering support I/F with TP if needed

Deliverables

Demonstrator for the thermoplastic composite (TPC) Interstage Structure (ISS). Engineering, test and cost reports on the completed work.

Current TRL: TRL 2 Target TRL: TRL 4/5 Application Need/Date:

NGL 2025 (targeting TRL 6 by 2015)

Application Mission: NGL (Next Generation Launcher) Contract Duration: 18 Months





Title: Lens-Like Multiple Beam Antenna


Objectives

Investigate lens-like multiple beam antennas for array and imaging array configurations with a large number of beams. Description

Multiple beam antennas are of great interest for satellite telecommunication applications as they enable increased capacity through frequency/polarisation reuse. Several technical solutions of multiple beam forming networks are known, each having its advantages and disadvantages. One of them is based on lens-like solutions. It includes lenses, such as the Rotman lens or the Luneberg lens, but also reflector-like structures such as the pillbox antennas. Recently, attention has been given to these solutions including for space applications because the resulting designs are easier to manufacture than their guided wave networks counterparts, specially for large arrays. This range of application is also preferred because these lens-like structures are known to be limited by their efficiency for smaller arrays. Examples of realisations with more than 40 beams are reported. This study will perform a state of the art review, propose lens concepts and perform analyses on the most promising ones. The performance will be validated by test on breadboard of the most critical components. Deliverables

Study report. Breadboard. Current TRL: 2 Target TRL: 3 Contract Duration: 18

Application Need/Date: Multiple beam antennas (focal arrays and imaging arrays) with a large number of beams (more than 40) for next generation telecommunication satellites. Need date: 2015.


Consistency with Harmonisation Roadmap and conclusion No


Programme: TRP Reference: T520-301MS

Title: Thermally conductive RTM CFRP


Objectives

Develop and qualify a thermally conductive RTM CFRP material Description

Carbon fibre-reinforced polymer or carbon fibre-reinforced plastic (CFRP) housing for electronic boxes could be produced using Resin Transfer Molding (RTM) technology. However, the material needs to be thermally conductive. This activity aims at developing and qualifying a thermally conductive RTM resin, adding e.g. copper powder. Deliverables

Breadboard

Current TRL: 1 Target TRL: 3 Contract Duration: 18

Application Need/Date: Mostly for telecom even if other applications could benefit S/W Clause: NA Reference to ESTER T-7750, T-8840

Consistency with Harmonisation Roadmap and conclusion NA



Title: Multi-Magnetometer Methods for Magnetic Dipole Modelling


Objectives

Use of multiple magnetometers to reduce test time and to improve accuracy for magnetic cleanliness programmes. Description

Background: The magnetic cleanliness of past or present programmes for Science and Earth Observation has been extensively based on multiple dipole modelling at unit level using so-called Mobile Coil Facilities (MCF) and at system level e.g. in the Magnetic Field Simulation Facility (German: Magnetfeldsimulationsanlage, MFSA) of IABG. These facilities use a small number of magnetometers and employ rotational measurements to obtain a magnetic signature around a unit under test. Disturbances of the ambient field during the test can require several repetitions. The rotation could be replaced by an increased number of fixed magnetometers. This could increase reproducibility and reduce measurement uncertainty while considerably reducing test time and operator expertise. Activity:1) Study possible multi-magnetometer setups, which reduce measurement time below 1 s to allow obtaining a "snap-shot" of the magnetic signature for a unit. Focus on optimum number of magnetometers and optimal locations for minimum uncertainty and maximum reproducibility of results. This includes consideration of combining individual magnetometers to gradiometer configurations. 2) Develop new software or adapt existing programs to solve the discrete inverse problem of finding the minimum number of magnetic sources able to cause the measured magnetic signature within an allowed uncertainty margin. 3) Build demonstration facility for proof-of-concept, including a. hardware facility with magnetometers and/or gradiometers and mechanical unit support, b. automatic data acquisition system, c. modelling software based on 2) and report generator. 4) Verify with known magnetic sources like arrangements of dipole magnets, quadrupole sources and current-fed coils. Deliverables

Study Report, Software, Demonstration facility


Application Need/Date: Industrial competitiveness (All Spacecraft) / 2015




Programme: TRP Reference: T708-301SW

Title: Automated testing using ECSS-E-70-32 Test and Operations procedure language


Objectives

The ECSS-E-70-32A test and operations procedure language standard was published in 2006 and there is still no system fully compliant with this standard and fully adequate for being used in both AIT and Operations. The objective of this activity is to perform all pre-requisite work that is required for ensuring a successful development. Description

A few systems have been prototyped/developed based on updating existing facilities but full compliance with the standard is still not achieved. The objective of this activity is to perform all pre-requisite work that is required for ensuring a successful development of a new generation of test and operations automated procedure language and related preparation and execution environment, based and fully compliant with ECSS-E-70-32, guaranteeing: - full adequacy to AIT and operations automation needs including configuration for domain specific issues, - long-term maintainability as required by long-term missions, - adherence to ECSS-E-70-31 (monitoring and control data definition) and ECSS-E-70-32 abstractions as required in order to support extensive procedure validation and verification campaigns, operations support and components stability and evolution, etc. The work to be performed will consist in: -identifying and specifying the components of an overall procedure preparation and execution systems including interactions with the space system monitoring and control database software; -identifying and specifying the domain specific needs and where needed, additions to , i.e. tailoring, the standard; -developing standard parsers/compilers for ECSS-E-70-32 procedures and producing feasibility reports for full compliance to the standard. Deliverables

Prototype

Current TRL: Target TRL: Contract Duration: 24

Application Need/Date: All missions

S/W Clause: Open Source Code Reference to ESTER T-7557

Consistency with Harmonisation Roadmap and conclusion No



Title: System-Hardware-Software co-engineering


Objectives

The activity investigates a model based and automated process going from system (avionics) models to software and microelectronic models. Description

Using the avionics architectural language, the system model should be able to express microelectronic blocs as well as hardware components and software elements. The interface between hardware, software and microelectronic will be defined. The model should contain parameters allowing to verify some particular properties related to the hw-sw co-design, e.g. for the performance. This would allow some tools to decide on the best implementation, and to initialize the software and the microelectronics models from the avionics model. The activity will include: - Analyse of the process leading from a complete avionics model towards software and microelectronics models and hardware components. - selection of the most appropriate languages to express the various models, - investigation of potential model transformation to initialize the software and microelectronic models from the avionics model, - investigation of techniques and tools to use the models and their parameters to drive the microelectronic or software implementation decision. Deliverables

Prototype


Application Need/Date: All missions/2013


Consistency with Harmonisation Roadmap and conclusion TBD


Programme: EOP Reference:

Title: Consolidation of Radio Occultation concept for Jason-CS


Objectives

The objective of the activity is to complement Jason-CS phase B1 by assessing the feasibility of embarking a full Radio Occultation (RO) instrument on the Jason-CS spacecraft, as recommended by users. Eumetsat has confirmed the interest of adding to Jason-CS a full RO instrument similar to the one in MetOp Second Generation (MOS). The activity will therefore enhance the interest of AT and SE in contributing to Jason-CS at CMIN12.

Description

As starting point, the same GNSS receiver as for the MetOp Second Generation (MOS) RO instrument can be considered. Accommodation (mechanical, thermal, interfaces, RF interference) issues need to be studied and may result in a slightly different antenna configuration from the one currently considered for MOS (studied in the Phase AB1). A different antenna may have an impact on link budgets or other assumptions that need to be iterated at system level. Most of the work is to be done by the RUAG AT and SE, mainly regarding the consolidation of the RO instrument architecture and suitability or adaptation of the current Jason-CS instrument concept, which is driven only by precise orbit determination. The activity will be run by RUAG Sweden and RUAG Austria. Both RUAGs developed the GRAS instrument, which is the predecessor of the MOS RO instrument.

Deliverables

Documentation equivalent to Phase B1 for instrument and some simulations of antennas.

Current TRL: N/A (mission concept, not technology)

Target TRL: N/A (mission concept, not technology)


Application Need/Date: Jason-CS - 2018




Programme: EOP Reference: Title: Evaluation of AGGA-4 ASIC devices

Total Budget: 450 keuro

Objectives

The activity aims to evaluate the AGGA-4 (Advanced GPS and Galileo ASIC baseband processor). The AGGA-4 ASIC sample devices are being produced by Atmel (F) under contract to Astrium GmbH under ESA contract 18831/03/NL/FF where RUAG-A is sub-contractor for the definition of requirements and the preliminary validation on an FPGA prototype of the GNSS processing from functional standpoint. This ASIC evaluation activity will establish whether the design, jointly elaborated by Astrium and RUAG, has been implemented correctly in the ASIC device and whether the device is (functionally and performance-wise) suitable for the intended applications, which include navigation of Earth-orbiting satellites, precise orbit determination for altimetry and gravimetry, radio occultation sounding. Note that the FPGA prototypes (previously validated by RUAG) had the same functionality as the final ASIC (e.g. LEON2 microprocessor, FFT module, etc) with the only difference that the number of

GNSS channels is just 4 in the FPGA and will be 36 in the ASIC. Description

The activity will have several tasks covering: 5. Simple block level (e.g. correlators) similar to the evaluation of the FPGA prototype 6. characterisation of internal timing and load performance of the internal resources of AGGA-4 (e.g. AMBA bus

traffic, LEON microprocessor) when using the 36 GNSS channels. 7. possibly some timing and power measurements under environmental conditions 8. (partial) performance characterisation for typical GNSS basic processing using all the 36 GNSS channels Experience in characterising the limits of the AGGA-4 ASIC gives a timing advantage that is of high strategic value for the contractor. The final report will include key aspects of this characterisation.

Deliverables

Reports; Validated samples;


2013


MetOp-SG, Jason-CS, all future Earthorbiting missions requiring precise orbit determination




N/A


Programme: EOEP Reference: Title: GRAS-2 design and breadboarding

Total Budget: 1500 keuro

Objectives

The first objective of this activity is to take advantage of the experience gained by the contractor in the development and usage of the MetOp GRAS instrument launched in 2006 for atmospheric sounding through GNSS Radio Occultation (RO) observation to define a second-generation of the instrument. Relevant system work is also being done in the frame of MetOp-SG Phase AB1, and potentially for Jason-CS too, regarding the detailed definition of the next generation of GRAS, hereon called GRAS-2. The main objective of this activity is to design and prototype the key hardware modules of GRAS-2 (i.e. antenna, RF Front End, digital modules based on AGGA-4 GNSS baseband processor) as well as the key software modules required for the Radio Occultation (RO) application.

Description

The activity will comprise several tasks:

-Detailed design of the GRAS-2 receiver, based on the MetOp-SG and Jason-CS architectural inputs but aiming at a wider applicability in view of e.g. commercial opportunities, -Prototyping at breadboard level the GRAS-2 receiver, including both key hardware and software modules, with high representativity of the space components utilised (e.g. baseband and RF chips) -Characterisation and validation of the GRAS-2 breadboard performance for the RO application

Although the contractors have been involved in a number of preparatory activities for GRAS-2, the detailed design and breadboarding is made complex by the rather challenging requirements of users in meteorology, climatology and space weather.

Deliverables

Reports; Validated breadboard;


2014 Application Mission:

MetOp-SG, Jason-CS Contract Duration: 24



N/A


Programme: EOEP Reference: Title: Study of geophysical retrieval methods in the microwave spectral region Total Budget: 200 keuro

Objectives

The activity aims to provide a multi-disciplinary survey and analyses aimed to obtain a comprehensive overview of the status and trends in retrieval methods applied to transform microwave remote sensing signals to geophysical parameters. Description

Microwave remote sensing instruments have for several decades importantly contributed to both research andoperational applications. Instrumental configurations are quite numerous and include: passive and activetechniques, incoherent and coherent radar measurements, multiple incidence and different polarisationmeasurements. Moreover, different electromagnetic (EM) wavelengths in the microwave region have also been utilised. Accordingly, this may offer means to infer constrained and consistent interpretations of the surfacescattering EM-spectrum. Yet, present retrieval methods are still often empirical and limited to one instrumental configuration, such as, for instance, scatterometer-based vector wind field observations. In this activity the goal is first to establish a comprehensive matrix that identifies the range of retrieval methods,physical based and/or empirical based, used in satellite remote sensing for the ocean, the biosphere and thecryosphere. Based on this, specific Strength-Weaknesses-Opportunities-Threats analyses will be conducted to highlight new potential and needs for improvements. The state-of-the-art and the trends in the different domains will be analysed in depth. The results will be presented at a Progress Meeting and in the Final Presentation andsummarized in a report.

Deliverables

Reports

Current TRL: NA (study) Target TRL: NA (study) Application Need/Date:

2018+


all future EO missions using microwave sensing

Contract Duration: 6 - 8 months



N/A


Programme: EOEP Reference: Title: Study of high-resolution wide-swath SAR applications Total Budget: 250 keuro

Objectives

The study, starting from a parametric definition of these technical enhancements, will include extensive simulations and analyse the impacts of these advances on the key SAR system observables and identify : - extensions and improvements to existing applications planned in the frame of ESA SARmissions, including monitoring of forest, marine, arctic and sea-ice environments, land motion risks, ocean surveillance, water and flood management, etc.

- new applications enabled by the improved flexibility and performance, e.g. urban mapping

Description

Europe is leading the world in the area of remote sensing by means of Synthetic Aperture Radars (SAR). Projects by ESA and by European national agencies have established the state-of-the-art, which today covers the use of different frequencies, of interferometric techniques, of polarimetric techniques, etc., and so enable amultitude of applications. There are still further enhancements being prepared and planned for SAR systems inorder in particular to achieve improved spatial / temporal coverage, thanks to wider sensing swaths obtained bymeans of techniques such as digital beam-forming, and improved spatial resolution in the order of a few metres,and to larger radar bandwidths (e.g. increase from ~150 to ~300 MHz in the C-band). The study, starting from a parametric definition of these technical enhancements, will analyse the impacts of these advances on the key SAR system observables and identify:

- extensions and improvements applicable to existing SAR applications, with emphasis on those planned in theframe of ESA SAR missions, including monitoring of forest, marine, arctic and sea-ice environments, land motion risks, ocean surveillance, water and flood management, etc.

- the new applications enabled by the improved flexibility and performance, e.g. urban mapping, traded-off where applicable with operational constraints.

The study will be harmonised with current and imminent activities on the technological side and will allow theconsortium to develop an early understanding of the issues at stake, e.g. with respect to retrieval and processingdemands of future systems.

Deliverables

Reports

Current TRL: NA (study) Target TRL: NA (study) Application Need/Date:

2018


all future EO missions using SAR sensing Contract Duration: 12 months



N/A


Programme: TRP Reference: T701-316ED

Title: Dynamic Latchup protection chip for COTS components


Objectives

Development of a stand alone chip that is able to shut down the component and holds it powered-down for a preset time. Phase 1 Definition of requirements and scenario of potential usages, Architectural design Phase 2 Detailed Design, Breadboarding, Cost estimation and supplier identification for ASIC/Hybrid solution Phase 3 ASIC/Hybrid development Phase 4 ASIC/HYbrid implementation & Qualification

Description

The use of Commercial Off the Shelf (COTS) components is and will always be an option to achieve space system performances that cannot be achieved with available space qualified components. For such components that are not latchup proof by design the use of protection circuitry is essential. In this activity, a highly reliable analogue or mixed signal protection chip shall be designed which provides the following functions: - protection of the COTS target chip from damaging effects of a latchup - possibility for programming (hardwired) maximum currents in a wide range daisy chaining of such chips for protection/ concurrent switch-off of multiple supply voltages signalling the occurrence of latchup to a monitoring chip/ processor via a simple interface (interrupt line) automated recovery after a programmable time, or controlled recovery via an enable input connected to a monitoring chip / processor (pin programmable) control of external components for supply currents higher than those that the chip can sustain in standalone mode. The chip shall be developed, prototyped and tested under realistic conditions (radiation, load, latchup) for a range of latchup-capable target chips. Deliverables

Demonstration model Current TRL: 2 Target TRL: 4 Contract Duration: 18

Application Need/Date:

Application will be immediate as Latch Up (LU) sensitive components are already used but the new device will considerably simplify the design of the protection electronics.

S/W Clause: Reference to ESTER T-697, T-8658, T-7800, T-8845

Consistency with Harmonisation Roadmap and conclusion: NA



Title: Development of a monolithic pulse-width-modulated (PWM)IC.


Objectives

Develop and evaluate a standard Pulse Width Modulator (PWM) integrated circuit (IC). Such a device shall withstand without degradation a total dose level of at least 100krads and shall not be latch-up sensitive in the usual space radiation environment. In order to avoid the risk of ITAR issues, the development shall be performed using a fully European design house and foundry. Description

DC/DC converters destined for space applications have in the past presented serious problems to the designer.Regarding specifically the control aspects of the DC/DC converter, many of the problems are derived from the fact that the IC controllers used were not initially conceived for space-borne products. In general, they are up-screened MIL-quality parts with limited radiation test data, intended for low total doses that barely justify their use. In addition these devices show dose rate dependency and high variation. Also, these non-European products appear and disappear from the catalogue and are exposed to obsolescence without notice and control. The activity, consistent also with the CTB (Component Technology Board) Silicon Dossier shall consist of conducting a technology and market study in order to firstly understand if the PWM controller answers to a big enough market to become a standard in the vast majority of DC-DC converters for space applications and secondly if the development and the recurrent costs remain competitive. A technology feasibility assessment shall be performed to assess the existing manufacturing capability for the production of a radiation hardened PWM controller, to identify the most promising technologies and lines of products that shall best suit the space application constraints in terms of performance and radiation tolerance. Any radiation data already obtained for the selected device type(s), if any, shall be shared with the Agency. The Pulse Width Modulator (PWM) specification shall be developed during the course of this activity, while the design, manufacture and characterisation of PWM prototypes shall lead to the definition of a draft PWM controller specification. Deliverables


Application Need/Date: All types of space applications are considered, including Earth Observation, Science, Telecoms & Navigation. TRL5>2016


Consistency with Harmonisation Roadmap and conclusion Yes


Programme: TRP Reference: T703-305EP

Title: Miniaturised core element for Point of Load (PoL) conversion


Objectives

Design, development, manufacturing and test of a core for PoL converters to be used in a distributed power conversion scheme (Application Specific Integrated Circuit (ASIC), or advanced, low-cost and reliable hybrid technology). Note that the PoL converter core is the part of the DC/DC converter that do not contain the required magnetic elements and the input/output capacitance. Description

The need of integrated PoL conversion solution is linked with the appearance of advanced digital technologies, to be used in all ESA and non-ESA space programs. Note that PoL converters might become the ONLY feasible/efficient power supply solution for all equipments provided with advanced digital technologies (memories, programmable gate arrays, processors, line drivers and receivers), due to the relevant static and dynamic accuracies and noise requirements over very low supply voltages (down to 1.8V or less, one notable example being the sub-micron 65nm technologies for which voltages as low as 1.2V are foreseen). Additionally, point of load conversion architecture might allow quick and economic implementation of any secondary power distribution needs (within usual voltage and currents required for generic platform or payload users), with clear benefits on overall reliability. The activity shall entail 1. the evaluation of the promising, in-house, available, reliability-proven technologies to realise a radiation hardened Point of Load (PoL) conversion core (note that technology qualification is excluded from the activity); 2. the selection and the robustness of the technology to meet space environment (especially Total Ionizing Dose (TiD) and Single Event Effects (SEE)); 3. the design, development, manufacturing and test of the core for PoL conversion. The deliverables of the activity shall be: - A prototype of the PoL converter core (in integrated form); - Preliminary analyses (application notes, Worst Case Analysis, Parts Stress Analysis, Failure Modes Effects and Criticality Analysis , Thermal and Mechanical analyses, Reliability analysis, Radiation analyses - TiD/SEE - ) for the final qualified product(s) - Technical specification to identify the application corners of the final product(s) - Evaluation and qualification plan for following qualification phase

Deliverables

Prototype


Application Need/Date: All missions/technologies. S/W Clause: Reference to ESTER T-8614

Consistency with Harmonisation Roadmap and conclusion: Yes



Title: Embedded passive component: a way to miniaturization


Objectives

Passive components like chip resistors, capacitors and inductors are used in huge number and have a large footprint on the PCB. This study proposes to evaluate embedded passive technologies. 2 types of technologies shall be used: - Specifically designed passive chip components embedded in a PCB. - Embedded layers in the PCB like a polymer ceramic dielectric layer for replacing capacitors The use of these technologies may allow space savings on the PCB by placing passives devices inside the PCB reducing the size of board and hence equipment by reducing the distance between passive and active components (improvement of signal performance). Description

Embedded passive devices such as resistors are a fast emerging technology and already widely used in commercial applications. This technology is driven by signal performance and miniaturization. The subject has been discussed in the frame of the CTB (Component Technology Board) and the activity has been approved by the CTB Passive components working group.The study shall encompass an initial survey of the existing solutions, an assessment of the various designs of embedded devices, their reliability in assembly and their ability to withstand the space environment. Deliverables


Application Need/Date: All type of application using chips, resistors and capacitors leading to board miniaturisation. S/W Clause: Reference to ESTER T-7890, T-8385



Programme: TRP Reference: T116-306MM

Title: Advanced laser ranging technologies for altimetry


Objectives

The objective of this activity is to design, manufacture and test a breadboard for technology demonstration of novel laser ranging techniques and critical technologies that can be implemented for future Earth Observation altimeter missions. For example: 3D imaging (using novel CMOS detector technologies), waveform analysis or advanced continuous wave modulation techniques. Description

Novel laser ranging techniques (like pseudo-random-noise or frequency-chirped CW modulations) and technologies (like APD arrays) can offer significant improvement in terms of system performance (including reduction of mass and power consumption, while promoting the increase of spatial resolution) for future long-range laser ranging systems for altimetry. Examples of future Earth Observation applications that could take advantage of novel laser ranging technologies include canopy height and structure, 3D surface topography, snow and ice depth and cover, and bathymetry (potential candidates for Earth Explorer 9). A recently started GSP study ('Laser altimeter for Earth Observation and planetary missions') shall identify and define scientific requirements for future Earth Observation applications involving laser altimeter concepts and technologies and will establish conceptual instrument designs. Based on these instrument concepts the proposed TRP activity will demonstrate the feasibility and maturity of critical technologies and techniques identified during a General Studies Programme study in view of the selected EO altimeter applications by breadboarding and testing the critical subsystems of the selected altimeter instrument concept. Deliverables

Breadboard


Application Need/Date: Earth Explorer 9, TRL 5 by 2015

S/W Clause: Reference to ESTER T-8193




Title: 2.05 Microns Pulsed Holmium-Laser for Atmospheric CO2 and Methane Monitoring


Objectives

Demonstration of a lidar transmitter laser breadboard at 2.05 microns based on Holmium-doped solid-state materials. In particular the development shall demonstrate both the extremely challenging spectral performance as well as the pulse energy levels of the transmitter required for the measurements. Description

The measurement of atmospheric greenhouse gases from space represents a technical challenge in terms of laser transmitter and receiver technology. Previous studies have identified the spectral bands around 1.57 microns and 2.05 microns as the best candidates for active sensing of CO2 and methane. For the generation of laser radiation at any of the considered frequencies in the targeted bands there is either the possibility of frequency conversion (FC) of an established laser source, e.g. Nd:YAG, to the target wavelength or the option of direct generation (DG) from a suitable laser material. While the FC approach in general benefits from a certain flexibility with respect to the choice of target wavelength, the DG approach shows potential for a lower overall system complexity and increased wall-plug efficiency. In the 2 microns spectral domain powerful Holmium-lasers have been demonstrated suitable for (terrestrial) atmospheric water vapour Differential Absorption LIDAR (DIAL). Such a laser source offers the potential of DG generation of laser radiation at 2.05 microns for CO2 and methane spaceborne monitoring. This activity shall complement ongoing TRP activities on the development of source (laser + FC or fibre laser) and receiver technology in the 2.05 microns domain by exploring the feasibility and performance of a Holmium solid-state laser source at 2.05 microns for spaceborne DIAL measurements of CO2 and methane. Deliverables

Breadboard


Application Need/Date: Earth Explorer 9, TRL5 by 2015

S/W Clause: NA Reference to ESTER T-7757, T-8883



Programme: TRP Reference: T126-301GT

Title: Enriching EO ontology services using Product Trees - PTREE


Objectives

This project aims at developing new technologies capable of improving EO product and service retrieval by considering Product Tree hierarchies; in combination with an ontology framework. This project should be considered in a context such as GMES with numerous Service Operators and Providers and the consequent proliferation of EO Products and Service which require effective retrieval and dynamic classification. More frequently, new EO services are based on the combination of pre-existing processing components; typically using the orchestration of Web-based services but also using specialized frameworks for EO processing like the TRP project Knowledge-centred Earth Observation (KEO). In turn, products delivered by such new services can be classified and, therefore, retrieved considering the logic of their orchestration workflows; or processing graphs. Ontologies devised to effectively retrieve EO products and services operate in synergy with the relations extracted from the processing graphs. Description

This project will try to identify innovative technologies capable of overcoming current limitations and in particular the fact that Ontology learning techniques have been developed based on reverse engineering of relational databases and, generally, from formal relations between different data objects. On the other hand, trends on EO data exploitation are moving towards the production of EO high level products using multiple of low level products, from different satellites and service providers; leading to complex data processing chains represented by graphs (e.g. BPMN) which users can directly edit and modify. Deliverables 1- Prototype demonstrator of ontology learning techniques applied to a number of EO applications whose processing chains formally expressed in standard form; BPEL, BPMN or equivalent. Input from reference ESA applications like Knowledge-centred Earth Observation (KEO) and Service Support Environment (SSE). 2- Comparison of the Demonstrator with current ontology used by GMES portal (http://gmesdata.esa.int/web/gsc/home)

Deliverables

Prototype


Application Need/Date: All EE and EW missions, 2014

S/W Clause: Open Source Code Reference to ESTER T-553



Programme: TRP Reference: T126-303GT

Title: PDGS e-Collaboration - PDGSE


Objectives

The objective of this project is to develop innovative technologies and advance the techniques for eCollaboration within the PDGS (Payload Data Ground System). Objective if this project is to identify critical areas of improvement within the PDGS, analyse the available e-collaboration techniques and identify the scenarios where they could be used, identify the metrics for evaluation and the architectural changes eventually needed and finally provide a ranking of selected technologies and prototype most promising use cases. Description

The technologies to be addressed include: 1- traditional e-collaboration and group management tools and techniques like shared whiteboarding, multimedia conferencing, calendaring and scheduling, e-mailing; 2- social networking techniques like wiki, forums and blogs and the most recent ones like Twitter ; 3 - tools for information publishing and public use like Google Earth and the tool used by non governmental organisation for disaster response "Ushahidi" which has the goal of aggregating information from the public for use in crisis response. The Ushahidi platform allows to gather distributed data via SMS, email or web and visualize it on a map or timeline and it was used in the Haiti earthquake response. Last but not least the project shall address the collaboration aspect of 4 - peer to peer for data dissemination, as this subject is normally addressed as a telecommunication topic, even if several of the telecommunication peer-to-peer technologies show an improvement (performance, resilience) over traditional telecommunication technologies. Further, only if the data is used in a e-collaboration context where individual user resources (computing, network and storage) are made available to the other users within the community. All the PDGS (Payload Data Ground System) components and functions shall be addressed, however priority shall be given to certain horizontal subjects which appear of interest within the PDGS and at the interface between PDGS and users, like monitoring, notification, alerting, issue tracking, product quality and validation, discovery and publishing. Previous activities on the subject include the THEVOICE GSP Study http://www.esa-thevoice.org/ and the limited experience on the use of social networking techniques for e-collaboration on ground segment interface standardisation, see http://wiki.services.eoportal.org. Deliverables User Requirement and Operational Scenarios TN Strategy for PDGS e-collaboration TN, including impact and improvements on ground segment performance and operability TN Selected Techniques for PDGS e-collaboration TN Prototype Demonstration Requirements Prototype Implementation Plan Test and evaluation TN

Deliverables

Prototype


Application Need/Date: All missions, 2014

S/W Clause: Reference to ESTER T-539




Title: Quality of Experience (QoE) tool for Telemedicine


Objectives

The objective is to develop and validate a system capable of providing useful parameters to assess the video/audio quality of a multimedia application / equipment / system as it would be perceived by the target user, especially for media transmitted through satellite networks. Description

Considering the crucial role of video and audio data in many systems developed within ESA projects (e.g. tele-diagnostic though transmission of ultrasound exams, tele-assisted surgery, distance learning via satellite with medical videos, etc), assessing the quality of video/audio parameters is of utmost importance for qualifying systems, in particular when video/audio data can have an impact on human lives, such as for above-mentioned telemedical systems. Typically the quality assessment of these parameters (see hereafter) is performed by means of subjective tests, carried out by a set of users rating the audiovisual quality according to the well-known Mean Opinion Score (1 to 5 MOS) scales, defined in the ITU-T P.800 Recommendation for audio, and similarly used in the ITU-R BT.500-11 for image . This process is however very much time consuming, not easily reproducible, is context dependent (for specific video content, e.g. surgery acts, opinion from specialists is required) and often not cost effective. Trying to overcome the aforementioned problem, industry has recently started to develop tools capable of providing an automatic MOS and other quality parameters. Nevertheless, such tools do not still provide a sufficient number of parameters/metrics and accuracy, to rigorously assess the Quality of Experience (QoE) of a system. Considering the ESA domains and projects mentioned before, the scope of the activity is therefore to develop a tool capable of performing an automatic initial qualification of a multimedia system, providing time referenced objective indicators and statistics related to the user QoE (e.g. video blurriness, colour deviations, delay, audio-video synchronization). In addition, the tool should monitor in real time the QoE of the system during its utilization, providing warnings and troubleshooting indicators. Finally, the tool should offer the capability to be customized according to a specific application area (e.g. telemedicine). The results of the objective QoE assessment will be validated with a series of subjective tests involving relevant end user community (e.g. medical specialists involved in telemedicine). Deliverables

Software


Application Need/Date: Telemedicine projects (interest for technologies, human space flight and telecommunication applications) / 2013





Title: Biocide management for long term water storage


Objectives

The objective of this activity is to study, characterise and control biocide concentration fluctuations inside potable water tanks, from production to launch and ideally for long term storage. Description

In the context of manned space mission, water represents the first metabolic consumable in terms of mass. Long shelf life for potable water is required and is ensured by the presence of biocidal molecules, aimed at preventing microbial contamination of the resource. Today aboard ISS, two types of potable water, according to Russian or US standards respectively, coexist. These two types of potable water contain either silver (Russian water) or iodine (US water) as biocide. Independent of the water quality standard considered, biocide concentration is known to fluctuate (e.g. ATV1 launch campaign experience), thereby explaining partially the current level of microbial contamination of the ISS water systems. On the long term, potential threat to crew health cannot be excluded. Therefore, it is necessary to study, understand and control physical/chemical phenomena responsible for these fluctuations of biocide concentration in order to ensure long term stored water always meets its quality requirements. Deliverables

Study Report Current TRL: 2 Target TRL: 3 Contract Duration: 18

Application Need/Date: Need asap (2013 - ATV4 launch campaign) S/W Clause: NA Reference to ESTER T-7762




Title: Hardware-Software Dependability for Launchers


Objectives

Develop dependability design approach for critical launcher Software. Refine, adapt and specialise the technologies developed in the frame of the COMPASS project to cope with the specificities of the Launcher Systems domain. Provide facilities for automated Model-Based diagnosability analysis and FDIR verification. Description

Launcher systems are characterised by high Dependability and Safety demands in general and critical Hard Real-Time operation of the Software-based functions in particular. In this respect the interplay between the continuous and discrete control elements is of major importance. Current development practices suffer from discontinuity between the Software and System RAMS (reliability, maintanability, availability, safety) activities, hindering the System-level analysis of the operational correctness, the reached Dependability levels, and the effectiveness of the FDIR (Failure Detection, Isolation and Recovery). Dedicated Software RAMS processes coherent with the System RAMS approaches are required to facilitate the Launcher Development Process and to enable effective System-level analyses from the early Development Phases. The ESA COMPASS TRP project has developed the basic technologies required to achieve the integration of the Software and System perspectives, the means of formal specification of the nominal and probabilistic fault behaviour, and the automation of the corresponding System-level analyses. These facilities shall be refined and extended for use in the context of the Launcher Software Systems specificities, providing the dedicated support to diagnosability and diagnosis trade-off analyses, RAMS analyses and Probabilistic Risk Assessment, and probabilistic FDIR evaluation. It shall allow building the Launcher systems with the required Dependability and Safety levels. Deliverables

Prototype


Application Need/Date: All launchers (NGL in particular) Software Systems Engineering / TRL5 by 2015

S/W Clause: NA Reference to ESTER T-7743, T-908, T-7660, T-7662




Title: Improvement of solar flare prediction


Objectives

The objective of this activity is to improve solar flare prediction applicable for launcher mission of a duration up to 12h

Description

Background: Launcher on-board electronics are not tolerant to solar flare environment. For Sun Synchronous (SSO) missions as well as for Geostationary (GEO) mission (12h including de-orbiting), the launcher is not protected by the geomagnetic field from solar flare induced radiation environment, particularly resulting in single event effects (SEE). Prediction techniques are needed to avoid to launch while there is a significant risk of solar flare for the mission duration. Proposed activity: 1) review of scientific methods for prediction of solar events that produce SEE at Earth based on solar and other observation 2) characterisation of the requirements, and different methods performance & limitations 3) prototype a system for warning of possible events and informing of magnitudes of events in progress

Deliverables

Prototype


Application Need/Date: SW operative>2014




Programme: TRP Reference: T401-301ED

Title: Ultra-wideband as a multi-purpose robust and reliable wireless communication technology for tests, spacecraft and launchers


Objectives

The objectives are twofold: 1) Assess, demonstrate and prototype a (A) low-medium-speed (100kbps-27Mbps) low-power and robust wireless sensor bus for spacecraft and (B) wireless bridge for high-speed (10-500Mbps) spacecraft payload point-to-point data link (e.g. as a UWB2SpW bridge). 2) Execute EMC characterization activities on Ultra-wideband technologies. Description

Compared to traditional wireless systems using 1) a narrow bandwidth (e.g. 2MHz-wide channel), 2) a high transmitting power (creating the typical power spectral density spike) and 3) an already crowded frequency band (e.g. 2.4GHz), Ultra-wideband (UWB) technology modulates the communication on a bandwidth greater than 500MHz at extremely low transmitting power density (typically <-41.3dBm/MHz), barely above the average noise level. It is an extremely promising technology for spacecraft because of the quasi-absence of electromagnetic interferences with onboard payloads and instruments. Commercial UWB technologies have been developed to allow communication data rates up to 675Mbps on short distance (< 1-5m). These systems could dramatically simplify actual high-speed wired payload data systems onboard spacecraft, without decreasing their reliability. This activity is to adapt and demonstrate the technology for space applications and possibly in space environment. The expected overall advantages are mass savings from harness reduction (nominal, redundant, cross-strapping) and a reduction of design and test complexities. Deliverables

Breadboard



Typical application: - Even thought the Exomars design is mostly frozen, it could have benefited from a wireless high-speed link on the mast to connect the navigation cameras and the onboard computer. This would have reduced the complexity and the mass of the data harness in the mast, while simplifying the test phase.- Launchers can use the technology to establish the communication between stages and avoid wires, unbalanced loads and pyrotechnics at separation. The same device would be usable for the communication between the launcher and the payload during launch.

S/W Clause: NA Reference to ESTER T-7753, T-7756, T-8382, T-8602



Programme: TRP Reference: T506-303ET

Title: Ultra low phase noise reference oscillator


Objectives

The objective of the activity is the demonstration of the practical feasibility of a 1 GHz reference oscillator based on the microwave optoelectronic oscillator approach. Description

Background: More stringent requirements related to complex modulations as well as flexibility based on multiple frequency conversion schemes call for a significant improvement (up to 10 dB) of the phase noise of the oscillators used on-board future telecom payloads. Recent developments in the field of microwave optoelectronic oscillators have led to the demonstration of unprecedented phase noise performance. Description: In a first Phase, an exhaustive patent and literature review will be carried out and the two most promising potential topologies will be assessed. In a second Phase, one of the two pre-selected topologies will be breadboarded and the RF performance will be analysed. Deliverables

Study report Current TRL: 1 Target TRL: 3 Contract Duration: 24

Application Need/Date: TRL5 in 2015




Programme: TRP Reference: T506-308ET

Title: Advanced modem techniques for future satellite access networks


Objectives

The main objective of this activity is to design and validate, in a realistic and representative environment, new techniques to enhance the spectral efficiency of air interface by at least 15% compared to what is currently achievable using the existing air interface standard

Description

Digital transmission techniques are essential elements of today satellite communications systems. Air interface Standards such as DVB-S2 and the Next Generation of DVB-RCS reflect the evolution of digital modulation and coding and techniques that allow significant improvement in power and bandwidth efficiency. The cost of satellite capacity remains a major factor in the overall cost of satellite communication services. This can hinder the competitiveness of satellite based solutions in comparison to terrestrial counterparts. There is a need for investigations of novel techniques for transmitter/receiver design to further improve the overall spectral efficiency of satellite communications, especially for digital broadcasting and broadband satellite access networks. The proposed activity is aimed to investigate state-of-the art techniques to enhance the flexibility and performance of digital modems in the future satellite access networks targeting different markets such as consumer and professional sectors. For the broadband and broadcasting applications, digital transmission techniques such as new signalling schemes to increase the transponders capacity shall be investigated. Other techniques to extend modulation and coding threshold range, synchronization improvement at low signal to noise operating points, turbo equalization techniques and new physical frame structures shall also be studied and their applicability to satellite communication environment shall be evaluated. The proposed activity shall also investigate advance digital transmission techniques for the return satellite channel to allow reducing the spacing between adjacent carriers using techniques such as Interleave Division Multiple Access (IDMA) in conjunction with interference cancellation techniques. The use of time-frequency packing techniques to improve the spectral efficiency of Multi-Frequency Time Division Multiple Access (MF-TDMA) access scheme shall also be investigated. The study of the selected techniques shall be complemented by a thorough simulation campaign to establish a quantitative assessment of the overall proposed air interface under a realistic channel models. Deliverables


Application Need/Date: TRL5>2017




Programme: TRP Reference: T720-304MS

Title: SAFE (Shock Attenuator For Equipment)


Objectives

To develop and qualify an isolation system compatible with existing interfaces. Description

Compatibility problem with respect to shock environment is often discovered too late (i.e. when S/C design is frozen, and hardware is already manufactured). Any design modification at this stage of the development would have a dramatic impact on the project. Some viscoelastic isolation systems for equipment are widely available, however non of them can be implemented on a spacecraft if the compatibility problem is evidenced late in the development. Indeed the commercial isolation systems require a specific mounting condition. The objective is to develop and qualify an isolation system compatible with existing interfaces (existing hole in the equipment flange, existing threaded hole on spacecraft wall). The isolation system should be versatile, and should be designed for several loads and attenuation targets. Deliverables

Prototype



Some viscoelastic isolation systems for equipment are widely available, however none of them can be implemented on a spacecraft if the compatibility problem is evidenced late in the development. Indeed the commercial isolation systems require a specific mounting condition. There is a gap between S/C needs and available solutions: The need from a spacecraft is a versatile isolation system which can be implemented as a curative solution, without modifying the existing interfaces.



Programme: TRP Reference: T724-304QE

Title: Nano-hybrid transparent materials


Objectives

Evaluation of materials functionalities reg. their radiation resistance Tailoring of material composition and processing techniques Focus on LEO applications, mainly UV/VUV and thermal cycling

Description

This study shall aim to develop a highly transparent (colourless or low solar absorbing with a high thermal emittance) hybrid material in combination with a high radiation resistance (Proton, electron, UV, VuV, X-ray etc.), good handling flexibility as well as being resistant to thermal cycling seen in space. This material shall be used as the first target application as a Second Surface Mirror (SSM) configuration and its performance shall supersede commonly used FEP SSMs. It is clear that a material development will only be successful after several iterations/improvements and that progress can only be achieved in a step by step approach. Deliverables


Application Need/Date: EO, SCI missions, TRL5>2016





Title: Versatile high-fidelity reference gas cell as laser wavelength stabilisation unit for DIAL measurements of atmospheric trace gases


Objectives

The present activity aims at the development and miniaturisation of an elegant breadboard of a laser wavelength stabilisation unit (LWSU) for lidar applications. The LWSU shall be based on a low power continuous-wave semiconductor laser that is referenced to the selected absorption feature of a target trace gas, e.g. CO2, CH4, H2O vapour, N2O, etc. For this purpose the semiconductor laser is locked to a miniature gas cell filled with the target gas. The LWSU shall demonstrate the aimed functionality not only for locking to the centre of a molecular absorption feature but also be capable of generating a wavelength with substantial offset (e.g. several GHz to several tens of GHz) from centre. The locking technique and electronics shall be versatile such that the same system architecture can be used without major modifications for various molecular species and a variety of their absorption features. The activity shall also comprise a trade-off study of the gas-cell-based LWSU vice-versa the use of an optical frequency comb in terms of performance, versatility, power/mass/volume, space-worthiness and cost. Description

The use of lidar systems for spaceborne monitoring of atmospheric constituents and processes offers a number of advantages as compared to passive optical instruments. In general such transmitter lasers require at least a very precise knowledge of the emitted laser wavelength, e.g. for Doppler wind measurements (ALADIN) or aerosol detection (ATLID). Although for this type of lidar a stabilisation of the output to an absolute wavelength reference is not mandatory and a continuous wavelength monitoring is sufficient it might nevertheless offer significant advantages on system level (transmit/receive/data processing). However, in the context of differential absorption lidar (DIAL) measurements, the measurement principle relies on determining the relative absorption of two close by laser wavelengths to retrieve the concentration profile of an atmospheric constituent, like e.g. CO2, CH4 or various other trace gases. Therefore, it is essential to lock the output laser wavelength(s) very precisely and with a very high degree of stability to a specific molecular absorption feature. The outcome of two parallel ESA system level studies on the spaceborne monitoring of CO2 and CH4 has clearly indicated the highly challenging requirements on the wavelength accuracy (few tens of MHz) and stability (several hundred kHz) in order to achieve the necessary level of precision in trace gas concentration retrieval. The most straightforward way to produce such an absolute wavelength reference in a single step, i.e. without the need of on-board calibration or two-stage referencing, is to use the monitored species itself to generate this wavelength reference. To this end a low power semiconductor laser (subsequently used to seed the laser oscillator of the DIAL transmitter laser) is locked to a reference gas cell, e.g. containing CO2, using the transmission gradient of a molecular absorption feature. As most DIAL measurements from space require to place the transmitter laser wavelength into the wings of the chosen molecular absorption feature, i.e. off-centre, it is crucial that the LWSU provides the possibility to generate a minimum of two output wavelengths. These can be swept with high precision over a large range (several GHz for the ON line to several tens of GHz for the OFF line) from the centre of the absorption feature. The activity shall also investigate the pros and cons regarding a competitive approach to wavelength stabilisation and referencing as presented by an optical frequency comb (OFC). While the OFC forming a tightly spaced ruler across a wide frequency range is capable of covering a large number of wavelengths at the same time it still requires the use of additional technologies (highly accurate RF local oscillator, self-referencing or gas absorption cell) in order to achieve absolute wavelength reference properties. In this sense the gas-cell-based LWSU could form a necessary subunit to an OFC frequency ruler. Deliverables

Breadboard


Application Need/Date: Future missions, e.g. in the context of an Earth Explorer 9 Core Mission, incorporating a lidar instrument for the measurement of atmospheric trace gases

S/W Clause: Reference to ESTER T-7757, T-8883, T-8885


Programme: STRIN Reference: Title: Solar Array Simulator Product Development Total Budget: 2.00 M€

Objectives

To develop a European Solar Array Simulator (full product) compatible with most used Electrical Power Subsystem architectures and Solar Array Regulators

Description


Following a first activity in the frame of the Strategic Initiative for Denmark, which purpose was to demonstrate the feasibility of a Solar Array Simulator (SAS), it is proposed now to develop a full product on the basis of abusiness case backed by a market analysis by the contractor. The back ground is the following: SAS is a complex piece of EGSE (Electrical Ground Support Equipment)mainly consisting into a number of power supplies with extremely demanding dynamic properties both small andlarge signal. Nowadays essentially two suppliers, both US, are able to provide such equipments at an acceptable level of performance and at a relatively high price. The initial study by the contractor (already performed) hasshown that the core functionalities of a SAS can be achieved. However, as an intermediate step in the proposed activity, the development of the complete power stage of one simulator section should be first performed in orderto get the go-ahead for the full unit development.

Deliverables

A complete Solar Array Simulator unit of which one section will be first produced to authorize the full development.

Current TRL: 4/5 Target TRL: 7/8 Application Need/Date:

As soon as available


All missions having a solar generator Contract Duration: 18 months



This is a Ground Support Equipment and has no direct relation with the Harmonisation (PMD dossier)


Programme: FLPP Period 2 Step 2 (SDT sub-envelope) Reference: 11.343.23

Title: Activities related to Materials & Structures: Upper part structures – Payload Fairing (PLF)

Total Budget: 0.931 M€ (out of which 0.231 M€ from Strategic Initiative)

Objectives

The main objective of the activity is to mature technologies related to PLF Upper part structures in answer to competitiveness factors stemming from for a Next Generation Launcher (NGL), in particular targeting: - Mass saving - Saving in terms of recurrent cost and more globally exploitation for producing Hardware (which covers: materials, design, manufacturing and

control processes). This activity is in continuation of the procurement action item n° 09.343.32 (ESA/IPC(2009)37 add3) which currently under implementation and targets a TRL 4. The objective of this activity is to further pursue the TRL increase, targeting TRL 5.

Description

A first phase of activity (covered by procurement action item n° 09.343.32) targets: - A trade of materials and manufacturing techniques and the selection of a sub-scale demonstrator, - The preliminary design of sub-scale demonstrator. The proposed activity will include: - testing at sample level to derive material characteristics - manufacturing and test of bread-board (typically curved bread-board) - detailed design of the 360° demonstrator - material procurement of the manufacturing of the demonstrator - Jigs & tools adaptation / procurement - Tailored CDR (tCDR) of the demonstrator - Manufacturing of the demonstrator - Intermediate evaluation of the technology wrt competitiveness factors - Test prediction The activity will be completed by the TRR of the demonstrator. A continuation will be proposed as part of FLPP period 3 with the test performance (targeting TRL 6) and final evaluation of the technology wrt competitiveness factors.

Deliverables

Material properties Detailed design of demonstrator Adapted jigs & tools tCDR data package (incl. manufacturing drawings) Sub-scale 360° demonstrator Intermediate evaluation of the technology wrt competitiveness factors Demonstrator test prediction

Current TRL: TRL 43 Target TRL: TRL 4 - 5 Application Need/Date:

NGL 2025 (targeting TRL 6 by 2015)

Application Mission: NGL (Next Generation Launcher) Contract Duration: 12 Months



3 TRL 4 anticipated at the end of the activities performed under ESA/IPC(2009)37 add3 item n° 09.343.32


ANNEX VII

Information on Special Measures in favour of

Portugal and Greece


Country Special measures Ref#

Prg Ref#

Activity Title Co-funding entity

Nominal Budget (kE)

Share entities


Comments

Greece SP-01-GR 11.335.14

Development of Closed loop Regenerative High Temperature PEM Fuel Cell system

TRP/CTP/TF

1000 SRE, TEC, Task Force for Greece

2012 ESA/IPC(2011)1, add.46 DN/S with ADVENT

Portugal SP-01-PT G 517-118MP

Al-Ti Welding Demonstration and Pre-Qualification

GSTP 490 TEC 2012 ESA/IPC(2011)5,add.3 DN/S RTG (D) subcos. Omnidea and IST (Portugal)

Portugal SP-02-PT C218-001MP

Characterisation of radiation for high speed entry

CTP 750 SRE 2012 ESA/IPC(2011)81,rev.1 DN/C with IST-IPFN

european space agency industrial policy committee revision ...2011)118_add.3.pdf · esa...

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