HERO Mission Victoria Workshop

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The Hyperspectral Environment and Resource
Observer (HERO) Mission Workshop on Resource and
Environmental Monitoring Products January 24th,
2005
Martin Bergeron, Allan Hollinger, Peter
Oswald Canadian Space Agency
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Mission Statement
"The Hyperspectral Environment and Resource
Observer (HERO) will be a Canadian optical Earth
Observation mission that will address the
stewardship of natural resources for sustainable
development within Canada and globally. Through
targeted imaging mapping and regular monitoring
of the Earth's surface, HERO will acquire and
deliver high-quality hyperspectral data that will
support decision-making in the management of
sensitive ecosystems and valuable natural
resources.
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Mission and Issues
Mission Government Issues

• Climate Change
• Sustainable Development of Natural Resources
• A Clean Environment
• Strong and Safe Communities
• Development of the North
• Innovation
• Connecting Canadians

Federal Dept Applications Area

• Natural Resources Canada Geoscience, Forestry
• Environment Canada Environment
• Department of Fisheries and Ocean Coastal and
  Inland Waters
• Agriculture and Agri-Food Canada Agriculture

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User Science Requirements

• The user requirements from the UST have been
  incorporated in a HERO Mission Requirement
  document (v2.0)
• Majority of User's needs satisfied within the
  limitations of the technology and budget
• Phase A2 advances these requirements and proposes
  a design implementation.

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Mission Objectives
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Mission Requirements

• Provide Hyperspectral Data to the Canadian and
  Worldwide User Communities
• Mission shall provide data to support
• Canadian and Global Seasonal Biomass Estimates
• Canadian Natural Resources Inventory
• Inventory of Hazardous Areas
• Ecosystem Surface Coverage Maps
• Periodic Measures of Vegetation Health.
• Changes in the above.

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Mission Context
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Mission Overview
Spacecraft is agile
3 Reception stations
Landsat, Radarsat data
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Mission Characteristics

• One Satellite 5 year life
• Compatible with CSA Generic Smallsat Bus (fully
  agile)
• Nominal Launch date in 2009
• Capable of systematic data co-ordination with
  Landsat
• 705 km Sun Synchronous Orbit acquisition on
  descending node
• Approx. 1100 AM (TBC) equator crossing time
  (descending)
• Access
• 16-day revisit (repeat same view)
• Selectable roll pointing, normally within 7
• Can image anywhere within the Landsat swath
• Selectable roll pointing up to 20
• 7-day relook (any view)
• Coverage (with overlap)
• 22000 km x 30km per day

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Spacecraft

• Mass 500kg
• Power 230W (Bus 120W, Payload 110W)

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Spacecraft characteristics

• Canadian Generic Small Satellite Bus
• Hexagonal structure
• Payload Mounts on end plate
• Body mounted solar panels
• Fully agile spacecraft
• Volume 1.8m (vertices) 1.6m (sides) 2.3m
  (bus and payload, including radiator)
• Mass 500kg
• Orbit Average Power 230W (Bus 120W - Payload
  110W)
• Dnepr, Rockot and Taurus launch compatible

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Key Payload Characteristics

• Targeting mission supporting mapping as
  background
• Spatial
• Swath width gt 30 km for VNIR and SWIR
• Ground Sampling Distance 30m
• Keystone lt0.1 x Ground Sampling Distance
• Geolocation with Ground Control Points 30m at
  Nadir
• Geolocation without Ground Control Point 300m
  at Nadir
• Spectral
• Spectral Range lt430 nm to gt2450 nm
• Spectral Sampling Interval 10nm
• Smile lt0.1 x Spectral Sampling Interval
• Full Width Half Maximum of the spectral line
  shape 10 nm
• 240 Channels (60 VNIR, 180 SWIR)
• VQ Near Lossless Compression Tech demo (TBC)

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Payload Mechanical Design

• Two modules
• Separate fore-optics
• Each with dual Dyson Spectrometers VNIR and SWIR
  detectors to provide ½ of the gt30km swath, with
  overlap
• Instrument, and SWIR detector, passively cooled
• Thermally isolated from Bus

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Payload Function

• Two modules each contain optics, readout
  electronics
• Data is digitized and multiplexed. Data is
  stored in a large memory unit
• The PFCU does all the on-board processing,
  formatting and payload control
• The formatted data is sent to the ground via 2
  150Mbps X-band links
• Mechanical, thermal and electrical subsystems
  support the payload and its interfaces to the
  Bus.

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Payload Optical Layout
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Signal to Noise Ratio
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Includes residual PRNU 0.1, DCNU 1
Effective SNR
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Real-time VQ Compression

• 4 compression engines (CE) operate in parallel
• Throughput of a the board (with 4 CEs) 1.2 Gbps
• Estimated Power 20 W

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Non Real-time VQ

• 1 Compression engine
• Throughput of a the board 0.3 Gbps
• Estimated Power 10 W

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Ordering and Spacecraft Control

• Ground infrastructure includes
• Order desk and Order Management subsystems
• A Scheduler which interfaces to the Spacecraft
  Control and the Image Data Handling subsystems
• The spacecraft control subsystem
• Generates the S/C plan 7 days in advance with
  daily updates
• Communicates to S/C from St-Hubert (and
  Saskatoon)
• Receives and monitors all telemetry from the S/C.

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Ordering Dissemination
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Mission Data and Products
0Option, ITo internal Users only
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Radiometric Calibration

• Absolute Radiometry
• Pre-flight calibration of the instrument in the
  laboratory using traceable standards
• On orbit Periodic (TBD) calibration from
  commissioning to end of-life
• Lunar Irradiance is measured to establish trends
  in calibration
• Periodic dark data acquired
• Spatial uniformity via yaw maneuver
• Issues associated with ACS quality/cost
• TBD on-board Radiometric calibration equipment

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Spectral calibration

• Absolute / Relative Spectral Knowledge
• Ground characterization
• Scanning Etalon for all spectral pixels across
  full swath
• 0.1nm requirement on knowledge of band centre
• Within each spectrometer, registration (including
  tilt, smile and distortions) departs from the
  mean location by less than /- 1nm
• The overlap region (VNIR and SWIR, 1000 nm) is
  characterized
• Spectral Line Shape and FWHM
• On orbit characterization
• Uses atmospheric lines to fit low order
  polynomial to verify absolute and relative
  registration, spectral line shape and FWHM (TBC)
• May use limb sounding with the moon to increase
  the path length for weaker atmospheric absorption
  features
• TBD on-board Spectral calibration equipment

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HERO Schedule
Q1
Q1
Q2
Q3
Q3
Q2
Q1
Q1
Q1
Q1
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Conclusion

• Project Phase A in progress
• Phase B planned to begin next year pending
  funding decisions
• To include Application Development
• Launch planned for 2009
• Ideally suited for remote sensing of Canada's
  resources
• Will maintain Canada's role in Earth observation
• Partnerships actively being pursued.

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Payload Diagram
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PFCU
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Order Handling and Planning
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Mission Spacecraft Control
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Slit Detail
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Spectrometer Detail
First surface(s) of Dyson lens(es)