EUROPEAN SPACE AGENCY INDUSTRIAL POLICY COMMITTEE

Transcription

1 Att. : Annexes Paris, 20 th March 2008 (English only) EUROPEAN SPACE AGENCY INDUSTRIAL POLICY COMMITTEE GENERAL SUPPORT TECHNOLOGY PROGRAMME UPDATE OF THE GSTP-4 SPECIFIC AREA WORK PLAN AND PROCUREMENT PLAN FOR PROBA-V The IPC is invited to approve this update of the GSTP-4 Work Plan / Procurement Plan for PROBA-V by simple majority of the Participating States in GSTP. A, B, CH, D, DK, E, F, FIN, GR, I, IRL, LUX, N, NL, P, S, UK & CDN SUMMARY PROBA-V is a mission based on an advanced PROBA platform carrying a multi-spectral instrument capable of providing enhanced data continuity to the Vegetation mission carried out by SPOT-4 and SPOT-5. Based on the Lightsat approach as presented to IPC (In-Orbit demonstration strategy, see ESA/IPC(2007)113 rev.1) and on the outcome of the preparatory activities for the PROBA-V mission, the main set of activities for the implementation of such PROBA-V mission (phases B, C, D and E1) is herewith presented as a GSTP-4 Specific Area Work Plan / Procurement Plan. REQUIRED ACTIONS The Industrial Policy Committee is invited: To approve the main GSTP-4 Specific Area Work Plan / Procurement Plan for PROBA-V (PV-1 and PV-2 activities in Annex 1 identified with the label IPC), based on the description provided in Annex 2 and the additional information provided in Annexes 3 and 4. NEXT STEPS GSTP Participating States are invited to indicate their support to the individual activities added to the Work Plan. The RFQ will be issued as soon as the contributions from the Participating States cover the Phase B budget (but not earlier than 2 months following the approval by IPC). ecpb

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3 Page 3 BACKGROUND In recent years, several missions (e.g. CHRIS hyper-spectral instrument on PROBA-1, DMC constellation to Disaster Monitoring, Topsat for high resolution) have demonstrated that small platform based satellites can operationally achieve focused mission objectives. Indeed, advanced technology and miniaturisation for platform and payload have made it possible to implement high performance missions fulfilling a single focused objective on spacecraft weighting around 150 kg. In investigating how the Lightsat approach proposed by ESA for its in-orbit demonstration strategy could be applied to such missions, ESA has in particular studied, internally and with industry and CNES, whether the VEGETATION (VGT) mission could be fulfilled with a small spacecraft. These studies have demonstrated that, thanks to the progress made since the inception of the first VGT instrument back in the 1990 s (in particular in the fields of optical design), a PROBA like platform can serve a mission capable of providing products of the same quality as the VGT mission on the SPOT satellites with significantly lower resources. With the present procurement proposal, it is proposed to implement a mission on a small satellite using today s technology and advanced development practices which will also provide enhanced data continuity to SPOT s VGT. The PROBA platform will be enhanced, and such enhancements will be opportunities to demonstrate new technology. This is in line with ESA s concept of the Lightsat approach 1 to assess punctual issues, e.g. reducing the risks of data gaps. Since April 1998, the VGT Mission has operationally delivered to its users daily global monitoring of continental surfaces at kilometric resolution. Onboard SPOT 4 and 5, the two successive sensors VGT 1 (launched in March 1998) and VGT 2 (launched in May 2002) are quasi similar optical imagers operating in the Visible (VIS), blue, red, Near InfraRed (NIR) and Short Wave InfraRed range (SWIR) bands. Jointly developed and founded by France, Belgium, Italy, Sweden and the European Commission, VGT address mainly key applications in the different domains: land use, land cover and its changes, vegetation behaviour in response to strong meteorological events (e.g. severe drought) and to climatic changes (long term behaviour of the vegetation), disaster management (detection of fires and surface water bodies), biophysical parameters for models devoted to water budget and primary productivity (agriculture, ecosystem vulnerability, etc.). These applications interest both institutional and scientific users. An important asset of VGT is the 10 year archive of consistent global data set which makes possible research based on long term time series. The VGT mission will be continued with enhanced performance by the Sentinel 3 of GMES as from The multi-spectral sensor VGT-GF carried by the PROBA V will contribute to reduce the risks of gaps between the SPOT and Sentinel 3 series. For this to succeed a fast implementation is required. 1 ESA/IPC(2007)113, In-orbit demonstration strategy

4 Page 4 Preparatory activities for PROBA-V were finalised in Also some technology and system pre-developments are being carried out. The present document presents then the main set of activities for the next phases of the PROBA-V mission, i.e. phases BCDE as per ECSS-M-30. As shown in annex 1, the work plan is organised in three main activities: - PV-01, covering the industrial activities for space and ground segment from start of phase B to end of commissioning - PV-02, covering the industrial activities for the development of the Image Processing Centre - PV-03, covering the installation of the ground segment, the launch, LEOP and the operations. Supporting PV-01 and/or PV-02 implies pro-rata support to PV-03.

5 ANNEX I List of the proposed Activities

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7 Annex I, Page 1 ANNEX I: Additional activities to GSTP-4 Specific Area Work Plan: PROBA-V PROBA-V Mission Approval GSTP-4 Reference Title Budget (K ) IPC PV-01 PROBA-V space and ground segment BCDE1 46,700 C Proc. Policy IPC PV-02 Image processing centre 8,000 DN/C Remarks (Company DN, etc.) Budget based on preparatory activities cost estimates. DN/C with VITO (B). Budget based on preparatory activities cost estimates. IPC PV-03* Ground segment preparation, launch services, LEOP support and operations TBD C Allocated pro-rata to the industrial costs of PV-01 and PV-2 above. Total PROBA-V Mission TBD For more details on the budget estimates made per activity please refer to Annexes 1 and 2. (*): This activity will be subject of a subsequent procurement proposal

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9 ANNEX II Detailed Descriptions of the Activities

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11 Annex II, Page 1 Specific Area Work Plan / Procurement Plan PROBA-V Ref. Number: PV-01 Budget: 46,700 K Activity Title: PROBA-V space and ground segment BCDE1 Description: The system design relies on a micro-satellite of the PROBA type, fitted with a Three Mirror Anastigmatic (TMA) based multi-band VGT instrument. The proposed system satisfies the original VGT requirements. However, the instrument implementation is different between PROBA-V and SPOT, therefore raw data will not be identical (pixel size, instrument radiometry) and the VGT product generation chain will have to be adapted. Instrument The proposed concept is made up of 3 identical Telescopes (TMA). For each telescope the angular field of view is 34 o so as to cover a total of 102, equivalent to a swath of 2250 km from an altitude of 800 km. Each TMA telescope is made up of 3 mirrors (two aspherical mirrors with a sag of 50 µm and one spherical). The distortion is lower than 1.5% at the edge of the field of view and the MTF consistent with the requirements. Each telescope has 2 focal planes, one for the short wave infrared (SWIR) band and one for the visible and near-infrared (VNIR) bands. The mass is lower than 5 kg for each telescope, including the focal planes and their correspondent front-end electronics. The global instrument mass with the plate supporting the 3 telescopes is lower than 20 kg including 20% margin. The ground sample distance (GSD) in the VNIR bands is 250 m at nadir and 900 m at the edges of the swath. For the SWIR band the GSD is 500 m at nadir and 1700 m at the edges. Both GSD are compatible with SPOT VGT. Platform The PROBA-V spacecraft relies on an adapted PROBA 2 platform. The system budgets for the PROBA-V mission are similar to those of PROBA 2, the main difference is the Earth viewing instead of Sun pointing and a possible higher telemetry rate for one of the options. These modifications will also impose a modification of the solar array design. In terms of functionality, the avionics system, the attitude control system and the on board software of PROBA 2 are applicable to PROBA-V with possibly the addition of a larger mass memory, a small propulsion system and a payload data handling (PDHT) and transmission system in X band. The operations architecture and the associated infrastructure for ground

12 Annex II, Page 2 testing and operations are also re-usable without major modification. Ground Segment The nominal ground station for satellite commanding and acquisition of housekeeping is the ESA Redu station, already used for PROBA satellites. It will be used to control the PROBA-V satellite. Payload data acquisition will be performed from Redu and Kiruna ground stations as in PROBA-1 already, with the option of an X-band downlink in Svalbard. This option would allow reducing the number of passes required to downlink payload data to 4 to 5 passes per day and would also allow getting the data in less than 6 hours for processing. This will have to be decided with the users. Payload data and associated ancillary data will then be transferred in raw format to the Image Processing Centre located at VITO. More details on the PROBA-V characteristics relative to the space and ground segment are given in Annex 2, including the baseline and options and the associated costs (nominal and maximum). Current TRL: Target TRL: Duration: 36 Months Application / Timeframe: Applicability of SW. Clause: Proc. Policy: C ESTER Ref: N/A Harmonisation Roadmap: Not linked to harmonised technology

13 Annex II, Page 3 Ref. Number: PV-02 Budget: 8,000K Activity Title: Image processing centre Description: VITO (B) is assumed to be the data processing facility. VITO s processing centre of VGT 1 and 2 is operational since VITO has a generic software environment Flexsys used for several missions. The centre includes: - The systematic Processing and Archiving Service, - The Production and Distribution Service, - The interface to the sensor programming, - The Calibration Service. The recommended solution is to implement the PROBA-V data processing centre based on the Flexsys multimission system such that the existing archive and catalogue system and the workflow management are re-used for PROBA-V. The archive and dissemination specifications shall be aligned to the interoperability interfaces for data access (HMA). Current TRL: Target TRL: Duration: 36 Months Application / Timeframe: Applicability of SW. Clause: TBD following definition of the SW baseline and detailed re-use Proc. Policy: DN/C VITO (B) The Image Processing Centre for PROBA-V shall be based on the Flexsys system developed by VITO (B). Moreover this company was in charge of the processing centres for VGT-1 and VGT-2 (operational since 1999). Non-competitive tendering is justified according to Article 6.1.c of the Contracts Regulations. ESTER Ref: N/A Harmonisation Roadmap: Not linked to harmonised technology

14 Annex II, Page 4 Ref. Number: PV-03 Budget: TBDK Activity Title: Ground segment preparation, launch services, LEOP support and operations Description: To be analysed and budgeted in Phase B taking into account launch opportunities (auxiliary passenger, main small passenger, ) available for the orbit required by the PROBA-V mission and operations detailed requirements. For the selection of the launch opportunity, the implementation of the ESA launch service policy for technological in-orbit demonstration missions will take into account the specificity of such missions which must stay within a budget which makes worth the investment. Low cost launch service opportunities as co-passengers of fully qualified launch systems or as main payload of new launcher configuration demonstration flights will be identified for PROBA-V. Such opportunity will have however to be compatible with the orbit requirement for PROBA-V. For the ground segment, operations and exploitation, the set-up will be based on the specific PROBA project set-up namely: - industrial includes the provision of the ground segment infrastructure, - limited LEOP cross support is required, - industry is responsible for spacecraft and ground segment commissioning with the support of ESA, - operations are performed in an offline mode and fast (< 1 week) ground response time is not required, - the flight dynamics system is implemented at the Mission Operations Centre, - industry will support operations beyond commissioning. Current TRL: Target TRL: Duration: Months Application / Timeframe: Applicability of SW. Clause: Proc. Policy: C ESTER Ref: N/A Harmonisation Roadmap: Not linked to harmonised technology

15 ANNEX III PROBA-V Implementation

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17 Annex III, Page 1 1. Project Background In recent years, it has been demonstrated that small spacecraft can achieve specific mission objectives. Examples in Europe are PROBA-1 with the CHRIS hyper-spectral instrument, the DMC constellation for Disaster Monitoring and Topsat for high resolution imaging among others. Advanced technology and miniaturisation for platform and payload make possible to implement high performance missions fulfilling a single focused objective on spacecraft weighting around 150 kg. This implies that development and operation practices of small satellites, such as the Lightsat approach proposed by ESA for its in-orbit demonstration strategy can be applied to such missions. ESA has investigated in the past 2 years, internally and with industry and CNES, if the VEGETATION (VGT) mission could be fulfilled with a small spacecraft. Since the design of the first VGT instrument back in the 1990 s, spacecraft technology has progressed impressively in particular in the fields of optical design and of miniaturisation. These preliminary studies have demonstrated that a PROBA like satellite can implement a mission capable of providing products of the same quality as the VGT mission on the SPOT satellites with significantly lower resources. This is shown in Fig.1.1 that compares the mass and power of the SPOT VGT payload with a potential VGT gap filler (VGT-GF) payload to be carried on a PROBA platform VGT VGT-GF Power Mass Fig. 1.1 From the SPOT VGT to a PROBA VGT It can then be envisaged to implement a demonstration mission on a small satellite using today s technology and advanced development practices which will also provide enhanced data continuity to SPOT s VGT. The PROBA platform will be enhanced, and such enhancements will be opportunities to demonstrate new technology. This is in line with ESA s concept of the Lightsat approach 2 to assess punctual issues, e.g. reducing the risks of data gaps. 2 ESA/IPC(2007)113, In-orbit demonstration strategy

18 Annex III, Page 2 2. VEGETATION background Since April 1998, the VGT Mission has operationally delivered to its users daily global monitoring of continental surfaces at kilometric resolution. Onboard SPOT 4 and 5, the two successive sensors VGT 1 (launched in March 1998) and VGT 2 (launched in May 2002) are quasi similar optical imagers operating in the Visible (VIS), blue, red, Near InfraRed (NIR) and Short Wave InfraRed range (SWIR) bands. Jointly developed and founded by France, Belgium, Italy, Sweden and the European Commission, VGT address mainly key applications in the different domains: land use, land cover and its changes, vegetation behaviour in response to strong meteorological events (e.g. severe drought) and to climatic changes (long term behaviour of the vegetation), disaster management (detection of fires and surface water bodies), biophysical parameters for models devoted to water budget and primary productivity (agriculture, ecosystem vulnerability, ). These applications interest both institutional and scientific users. An important asset of VGT is the 10 year archive of consistent global data set which makes possible research based on long term time series. The VGT mission will be continued with enhanced performance by the Sentinel 3 of GMES as from The multi-spectral sensor VGT-GF carried by the PROBA V will contribute to GMES and enhance observation capabilities.

19 Annex III, Page 3 3. Project Objectives The objectives of the PROBA-V mission are to demonstrate that small spacecraft technology and development approaches can be used to address specific issues such as supporting an operational mission. There are three sets of complementary objectives and requirements Objectives and requirements related to the mission / payload The basic driving requirement for the PROBA-V mission and payload is to provide continuity to the current VGT products, therefore spectral bands, resolution, illumination, earth coverage and instrument performance shall be at least the same as for VGT on SPOT. The VGT requirements are summarized in the tables below. Requirement Implementation Coverage Earth daily at least of Europe Equator crossing time 10:30 +/- 20 mn GSD Better than 1 km at Nadir MTF > 0.3 at Nyquist (Nadir) Geo-localisation < 0.3 pixel Bands co-registration < 0.3 pixel Spectral bands Blue: (0.455) Red: (0.655) NIR: (0.835) SWIR: (1.665) Blue Green Red NIR SWIR Max. Radiance (W/m2/st/µm) Min. Radiance (W/m2/st/µm) SNR (@ Lmin) The data must be compatible with the continuity required for the products also in terms of resolution, localization, temporal coverage, and timing. The duration of the mission is three years with a goal of five years.

20 Annex III, Page Objectives and requirements related to the technology The PROBA-V mission will capitalize on the previous VGT and PROBA missions. The platform will reuse as much as possible the PROBA platform. Nevertheless, as new capabilities are required the implementation of advanced technology will be considered, e.g. green propulsion for orbit maintenance, new miniaturized star trackers in gyro-less attitude control, LEON based avionics, strengthened FDIR with MEMS based rate sensor, etc. High automation on ground and autonomy onboard will be implemented building on the PROBA experience so as to operate the mission with minimum human intervention Objectives related to the development approach To meet the tight schedule, the financial limitations and the desired lifetime, the approach to development of small satellites Lightsat will be pursued. Flat Work Breakdown and Project structures will be established. Practices as Concurrent Engineering will be used. The spacecraft operations will reuse as much as possible the ground infrastructure deployed at Redu for the PROBA missions and the modifications to the VGT product processing chain will be minimized. Finally, the mission shall be fulfilled with a space segment compatible with a secondary passenger launch in order to target low cost launch opportunities.

21 Annex III, Page 5 4. Project Description The project includes a space segment (platform and instrument), the operations ground segment, the image processing centre and image quality system and the launch services. Spacecraft operations will be performed from the ESA Redu station using also additional ground stations located at Kiruna and Svalbard (TBD). Raw image data together with required ancillary data will be delivered by the Redu station to the image processing centre at VITO System For optimum illumination, cloud free conditions and continuity with VGT on SPOT, the best orbit is sun synchronous with 10:30 equator crossing time. A classical orbit altitude around 800 km is chosen, since it presents the advantage of being less subject to radiations and offering opportunities for piggyback launches. A total angular swath of 102 (2250 km ground swath) is then required for a quasi daily earth coverage to yield the well known recurrent VGT 10 days synthesis product. The system design relies on a micro-satellite of the PROBA type, fitted with a Three Mirror Anastigmatic (TMA) based multi-band VGT instrument. The proposed system satisfies the original VGT requirements. However, the instrument implementation is different between PROBA-V and SPOT, therefore raw data will not be identical (pixel size, instrument radiometry) and the VGT product generation chain will have to be adapted. The PROBA-V characteristics are summarized in the table below (baseline and options are listed in section 4.4).

22 Annex III, Page 6 General Baseline Options Remarks Orbit altitude SSO, 800 km LTDN 10:30 (+/- 20 mn) Lifetime 3 years Extension to 5 years On consumable only Availability No hard Best effort requirement Spacecraft System Derived from PROBA-2 Development approach Lightsat (evolution of PROBA) Payload Instrument 3 TMA VNIR: m SWIR: m 3 TMA VNIR: m SWIR: m Platform Structure Mixed aluminium CFRP Thermal Passive control Propulsion No propulsion / Cold gas Power ACS Body mounted solar panels and Li-ion battery 3-axis stabilized star sensor only attitude determination All CFRP Data Handling LEON based centralized avionics Communications S-band X-band No propulsion Green propellant Techno-demo green propellant Last generation Li-ion Last generation STR, MEMS rate sensor for FDIR Several new IP cores Launch services Launcher Secondary payload opportunity Main passenger on a multiple launch Ground Segment & Operations Planning Ground station Redu and Kiruna Svalbard PROBA baseline Mission Operations & Satellite Control Redu PROBA baseline Payload data VITO VGT heritage ground segment Start phase B 2008 As soon as possible Launch Target 2011 As potential gap-filler, Lightsat approach 4.2. Instrument The proposed concept is made up of 3 identical Telescopes (TMA). For each telescope the angular field of view is 34 o so as to cover a total of 102, equivalent to a swath of 2250 km from an altitude of 800 km.

23 Annex III, Page 7 Each TMA telescope is made up of 3 mirrors (two aspherical mirrors with a sag of 50 µm and one spherical). The distorsion is lower than 1.5% at the edge of the field of view and the MTF consistent with the requirements. Each telescope has 2 focal planes, one for the short wave infrared (SWIR) band and one for the visible and near-infrared (VNIR) bands. The mass is lower than 5 kg for each telescope, including the focal planes and their correspondent front-end electronics. The global instrument mass with the plate supporting the 3 telescopes is lower than 20 kg including 20% margin. The ground sample distance (GSD) in the VNIR bands is 250 m at nadir and 900 m at the edges of the swath. For the SWIR band the GSD is 500 m at nadir and 1700 m at the edges. Both GSD are compatible with SPOT VGT Platform The PROBA-V spacecraft relies on an adapted PROBA 2 platform. The system budgets for the PROBA-V mission are similar to those of PROBA 2, the main difference is the Earth viewing instead of Sun pointing and a possible higher telemetry rate for one of the options. These modifications will also impose a modification of the solar array design. In terms of functionality, the avionics system, the attitude control system and the on board software of PROBA 2 are applicable to PROBA-V with possibly the addition of a larger mass memory, a small propulsion system and a payload data handling (PDHT) and transmission system in X band. The operations architecture and the associated infrastructure for ground testing and operations are also re-usable without major modification.

24 Annex III, Page Baseline and options The system is currently defined as a baseline (compatible with the mission requirements) and possible options either to improve the results of the mission or to reduce the overall cost of the mission. Main options are the following: - Addition of a band (0.555) in the green - Improved spatial resolution in the VNIR bands, 100 m at nadir and 300 m at the edges of the swath, and the SWIR band, 200 m Nadir and 600 m at edge - Instrument configuration with 3 or 2 TMA, both options are compatible with the VGT requirements but offering different resolutions - Data downlink with S band only for a 1 km resolution and with on board binning and compression or with the addition of an X band system for higher resolution VGT data downlink - Accommodation of a propulsion system to guarantee an adequate orbit for a 5 years lifetime. These options will be investigated in the system pre-development activity and the early Phase B. They will be closed at Phase B SRR Ground stations The nominal ground station for satellite commanding and acquisition of housekeeping is the ESA Redu station, already used for PROBA satellites. It will be used to control the PROBA- V satellite. Payload data acquisition will be performed from Redu and Kiruna ground stations as in PROBA-1 already, with the option of an X-band downlink in Svalbard. This option would allow reducing the number of passes required to downlink payload data to 4 to 5 passes per day and would also allow getting the data in less than 6 hours for processing. This will have to be decided with the users. Payload data and associated ancillary data will then be transferred in raw format to the Image Processing Centre located at VITO Image Processing Centre VITO (B) is assumed to be the data processing facility. VITO s processing centre of VGT 1 and 2 is operational since VITO has also another data processing environment named Flexsys used for several missions. The centre includes: - The systematic Processing and Archiving Service, - The Production and Distribution Service, - The interface to the sensor programming, - The Calibration Service. The recommended solution is to implement the PROBA-V data processing centre using the existing Flexsys multimission system such that the existing archive and catalogue system and the workflow management are re-used for PROBA-V.

25 Annex III, Page System Image quality To be able to offer to the end users the same level of image quality as for SPOT VGT, a set of system requirements, tools and methods shall be defined, implemented and operated in order to perform: System trade-offs about image quality : on-board / ground compromises and arbitration System performance budget estimation Definition of the instrument geometrical and radiometric models Development of prototypes or mock-ups of processing algorithms Definition of calibration methods, tools, and operational monitoring System performance acceptance Operational performance monitoring tools This could be done benefiting from the background and expertise of VITO. Other partners of VGT could upgrade their own processing chains Technical risks The main risks affecting the technical feasibility as well as the planning and cost of the mission have been identified during the early studies: The availability of the SWIR detector The SWIR detector requires either a delta-development and characterization of an available European detector (Xenics) or a procurement outside Europe for which no suitable and available candidate has been yet identified. A new development for the instrument The instrument relies on a 3 TMA telescope design for which no previous space experience is available in the foreseen companies and the manufacturability of aspherical mirrors is critical. End of life de-orbiting rules The enforcement of the IADC de-orbiting rule (25 years after nominal life) would have a major technical and cost impact. Launch cost For secondary passenger, launch date and final orbit are driven by the main passenger. PROBA-V would require to find a suitable launch opportunity in terms of orbit and launch date otherwise it would be required to depart from the strict secondary passenger option and the launch cost would be significantly increased. Technical actions (pre-developments) have been initiated for the 2 first items to reduce the risk Development approach It is also an objective to adopt a design, development and validation approach (Lightsat approach) compatible with a reduced delivery time to orbit required for small operational missions. Associated tools and facilities are therefore integral part of the project and their development and validation are an objective of PROBA-V. Usage of ECSS tailoring, implementation of failure tolerance and redundancy will be simple and commensurate with a small mission following the IOD (In Orbit Demonstration) Lightsat concept.

26 Annex III, Page Programmatic 5.1. Industrial Project Organisation The Project consists in the delivery in orbit of a full system including a commissioned space system and a spacecraft operations and image processing system. An industrial Prime will be responsible for the development of the complete space segment (up to in orbit delivery), the mission control centre, the preparation of the operations and the interface to the image processing centre. The image processing centre upgrade from SPOT VGT will be the responsibility of VITO (B). The nominal operations will be performed by ESA-Redu following successful commissioning with engineering support from the industrial team. The image processing and distribution will be performed by VITO Project Phases and Schedule The project is subdivided in classical space project phases (the definition of the phases follows the ECSS-M-30 definition). They are running in parallel with the technology developments required by the PROBA-V mission. - Phase 0 (internal) was completed 2007, - Preparatory activities (industrial) was also completed in 2007 with a Preliminary Requirements Review, - Phase B is planned to be initiated Phase C/D is planned to be initiated 2009 and finalised in Phase E is foreseen for 2011 onwards Phase B will follow the standard definition and will classically include a System Requirements Review (SRR) and be concluded by the Preliminary Design Review (PDR). Due to the specificity of the project, special emphasis will be put on the following subjects: - In depth review of Technology Readiness Levels (TRL) achieved in the parallel technology developments (mainly SWIR detector and TMA design), - Prototyping of the flight software running into a system simulator to anticipate the system validation, - Tailoring of ECSS standards and establishment of detailed development plan following the Lightsat approach, - Small spacecraft platform early design and design to cost actions, - Technology review and selection of new space technologies selected for PROBA-V. Phase C/D will follow the standard definition and will classically include a Critical Design Review (CDR), Qualification Design Review (QDR) and will be concluded by the Flight Acceptance Review (FAR). The project covering space and ground segment, the following tasks are also included: - The design and development of the ground segment infrastructure (common for spacecraft testing and mission control centre),

27 Annex III, Page 11 - The preparation of the operation plan and procedures, - All technical tasks related to the launcher interfacing and procurement. Phase E1 will include the launch support, early operations and commissioning activities. Early in Phase B the Agency will analyse the possibility to accommodate technology experiments and issue a call as agreed with the participants. The proposals submitted will be reviewed and the final decision as what experiments to embark will be taken at PDR Cost estimates The following presents the cost estimate of the project and scale of contributions by Participating States for the PROBA-V project. This does not include the technology predevelopments already initiated. Independent cost estimates have been performed for the PROBA-V mission by Industry and by ESA in the frame of the internal study. System, cost (spacecraft) estimate: 15 M Space segment cost (instrument) estimate: 11.7 M to 17.6 M (low high resolution), Margin for risk, cost modelling accuracy, design maturity on space segment (platform and instrument): 11.5 M to 14.1 M Ground segment and operations (3 years): 9 (when implemented as reduced requirements mission) to 13.5 M depending on operational requirements and technical options (this is included in PV-03) Data processing centre and image quality: 8 M The preliminary cost estimate (depending on the instrument configuration and the operations approach) including 3 years of operations, margins and excluding launch service costs is between 55.2 M and 68.2 M Processing G/S and operations Margin Instrument System, platform Nominal Maximum Fig Cost estimates The cost of the launch service may range from 1.5 M (secondary passenger as the PROBA 1 and 2) to 14.5 M (main passenger on demonstration flight, PROBA-3), primary

28 Annex III, Page 12 passenger, depending on the launch requirements (launch date, orbit specification, etc) and opportunities. The achieved technology readiness levels, the available launch opportunities and the impact of the requirement on data availability will be carefully reviewed during phase B so as to review the cost margins and establish the committing cost. An Activity/Procurement Proposal is herewith submitted to IPC as a special work area of GSTP so as to allow releasing the RFQ for the Phase B/C/D/E1. The target contributions from Participating States to the Procurement Proposal will guide the preparation by Industry of a proposal in line with the intended contributions. The Procurement Proposal will foresee a Firm Fixed Price (FFP) proposal for the Phase B and a ceiling price to be converted to Firm Fixed Price proposal for the Phase C/D/E1 for which an updated proposal will be submitted before the completion of the Phase B. At the time of the submission of the C/D/E1 proposal, new participants to the project may be included based on tasks identified for these new participants during the Phase B and according to GSTP rules. The subscription to the activity will therefore be re-opened during Phase B to allow additional participants to join in the activity. All participants to the project will also support, pro-rata to their contribution, the common costs, launch services and operations PROBA-V procurement steps and schedule Two procurement actions will be implemented, one for the full development of the space segment and mission control centre and one for the image processing centre upgrade activities. The schedule for the PROBA-VGT project together with the program approval milestones is as follows: Activity Date Remarks Preparatory activities 2007 Concluded Technologies and system pre-developments Mar. 08 Activity/Procurement proposal to IPC Apr. 08 Participants Meetings Apr. 08 RFQ for Phase B/C/D/E1 Jun. 08 Proposal for Phase B/C/D/E1 Aug. 08 Phase B Sep. 08 Feb. 09 Updated proposal for Phase C/D/E1 Jan. 09 PDR Feb. 09 TRL6 Phase C/D Mar. 09 Oct. 11 CDR Mar. 10 FAR Sep. 11 Phase E1 Oct. 11 Dec. 11 Phase E2 The RFQ will be issued as soon as the contributions from the Participating States cover the Phase B budget. Phase C/D will be authorised as soon as the contributions of the participating States cover 100 % of the project cost. Contributions for Phase C/D must be confirmed by Participating States before the end of the Phase B.

29 Annex III, Page Management Project Management The PROBA V project, including space (platform and instrument) segment, ground segment and data processing centre will be managed by a single project team at ESA. The project team will be set up in TEC supported by specialists of the TEC departments in a matrix structure. The needs of the VGT GF mission need complementary arrangements in particular with the Directorate of Earth Observation Programmes. EOP will provide guidance for the VGT GF mission aspects, including definition of the mission, data products, support to translating data requirements into technical requirements, support to the upgrade of the Image Processing Centre. EOP will also be the interface for the project to the overall GMES Project Margins The PROBA-V project will be managed by ESA and management margins will be allocated at various level. The industrial team will set-up a management reserve built at industrial level. This contractual reserve will be of 10 % (TBC). The Procurement Proposal will include a contingency margin, in addition to the figure corresponding to the estimated industrial budget of 10 % to cover Class A changes of the mission Overrun and delays Increase of cost beyond the industrial and ESA management margins will require the approval of the Participating State(s) involved when this increase is allocated to a single (a set of) participant(s) and the approval by the majority of the Participating States involved when it affects all the Participants (e.g. common costs). 6. Delivery and exploitation of PROBA-V The satellite and ground segment will be delivered to ESA following successful completion of the commissioning activities. Detailed criteria to complete commissioning will be defined and agreed by ESA and industry during the development phase in compliance with ESA requirements to the mission. The mission will contribute to GMES and it shall be exploited by ESA following commissioning. 7. Regime of results and follow-on Data resulting form the exploitation of PROBA-V will be provided to the VGT data centre at VITO. An agreement between parties (ESA, VITO) will be submitted for approval during Phase B.