SCIST Core Business

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SCI-ST Core Business

• Development of an Advanced P/L Technology
  Programme
• P/L cost analysis and cost/resource reduction for
  future missions
• P/L Technology Support to Projects (e.g. SOLO)
• Internal Technology Projects (opticssensors FM
  Instruments)
• P/L Support to ESA Project Reviews

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ST Involvement in Flight-Type Research Projects

• COROT (CNES Seismology/planet finder) RSSD/ST
  DPU
• STEREO (NASA) RSSD/ST ASIC
• SCAM 3 (Superconducting Optical Camera for WHT
  Telescope) RSSD/STcomplete Instrument

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SCI-ST Technology Development Projects

• Compound Semiconductor UV/EUV X-ray Sensors
  bridges fields
• EUV X-ray Optics (bridges fields -gt
  astrophysics planetary)
• Superconductor Sensors (Optical, UV, EUV, X-ray)
• ASICs (developments based on sensors,langmuir,ster
  eo type requirments)
• CCDs for Optical and UV applications
• Cryogenics
• Active Pixel Optical Sensors for future planetary
  and solar missions
• Planetary microscopy (Raman, Laser Plasma
  Spectroscopy)
• Planetary geochemistry ( XPS/Mossbauer/Microcam/LP
  S)
• NIR Interferometry through Genie
• DPUs (building on OSIRIS and COROT) ?
• Biosensors

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Instrument Costs linked to resources

• Consider instrument suites with shared subsystems
• Highly integrated electronics
• Search for low mass low power solutions
• Target early technology developments to reduce
  resource usage

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X-ray opticsResource reductions - change mission
profile
XMM optics 350 kg for 700mm diameter,
910kg/m2
MCP optics 29g for 60mm diameter,
10kg/m2 XMM-size 4 kg
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Room Temperature Compound Semiconductor Sensors
300 ?m
1.2 cm
Design goal ?E180 eV _at_ 5.9 keV
Pitch 350 ?m Thickness 40 ?m, 4 ?m p, lt1 ?m
n Inter-pixel resistivity gt 1010?
X-ray Mapper Rad Hard
1.2 cm
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Superconducting Optical UV Sensors
32x10 pixel array in Molybdenum
With low Tc Superconducting sensors we make a big
step over Ta (Scam1-3 cameras) for Optical-X-ray
astrosolar physics
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Development of Advanced Technology Programme

• Essential for future Solar Planetary programmes
  (More science at lower cost)
• Route for lower cost missions which are
  scientifically useful (e.g. XMM Telescope could
  be flown for a mass of 5 Kg not 400 Kg)
• Resources should be available from within DSCI
  Programme to ensure timely development of core
  technologies for SOLO
• Low resource payloads coupled to SMART spacecraft
  may in future allow mission concepts not
  considered to date (e.g. Interstellar probe)

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Venus Express The old approach
Payload in a shoebox !
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ST support to optimise the Science Programme
Output

• Payload cost database established
• Has led to initial costing of future mission
  payloads
• Provides a spend profile for P/Ls to member
  states
• Will influence the future planning process
• Payload long-term technologies are crucial to
  Science Programme
• Think SMART-CLEVER-LOW RESOURCE Instruments
• SOLO PDD is the basis for the Technology Road-Map
  
• ST supported by SOLO PWG SH will develop the PDD

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Cost Analysis Procedure

• ESA DSCi has established a payload cost database
• Database contains some payload and unit level
  costs from
• XMM
• SOHO
• Mars Express
• Rosetta
• Integral
• Huygens
• Cluster
• Database costs obtained from PIs, CO-Is and
  project teams
• Based in-part on DOD type cost analysis
• All instrument costs are analysed uniformly at
  unit and system level

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The Payload Cost Model Approach

• Establish a coefficient for the total risk
  associated with an instruments development
• The total risk coefficient is comprised of 5
  components
• Design maturity level (from PDD assessment
  reports etc)
• Technical criticality level
• Technology readiness level (from PDD assessment
  reports)
• Model philosophy (e.g. STM-gtEQM-gtFM with EQM
  upgrade-gtFS
• Project management (interfaces/numbers of
  institutes/industry)
• CTC is computed by adding/subtracting a delta
  function of the total risk to the closest
  instrument or unit in the d/b whose cost is
  known.
• Errors are computed based on the uncertainties
  making up the total risk.
• Errors (/-) are generally asymmetric to reflect
  probability to achieve savings is lower than
  probability to incur a cost increase

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Draft Payload Cost Analysis Mission Summary
() SOLO needs further Instrument definition
details
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BC (Light)MPOMMO Spend Profile Total 170
MEuros(Instrument Build Launch Ops support)
Start P/L Delivery
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Potential PICo-I distribution on Bepi
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Solar Orbiter Initial Payload Costs
Solar Orbiter lacks serious instrument definition
for accurate costs
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SOLO SCI-ST Steps

• Instrument specification
• Detailed analysis of instrument requirements
• Production of the Payload Definition Document
• Analysis of the instrument resources
• Specification of the SOLO Technology Road map
• SOLO Technology Development Programme
• Support to SOLO SWT/PWT
• Support to SOLO Industrial studies