4 Bergeron HERO

Slide1: 

Martin Bergeron, Allan Hollinger, Peter Oswald Canadian Space Agency The Hyperspectral Environment and Resource Observer (HERO) Mission Workshop on Resource and Environmental Monitoring Products January 24th, 2005

Slide2: 

"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.” Mission Statement

Slide3: 

Climate Change Sustainable Development of Natural Resources A Clean Environment Strong and Safe Communities Development of the North Innovation Connecting Canadians Natural Resources Canada – Geoscience, Forestry Environment Canada – Environment Department of Fisheries and Ocean – Coastal and Inland Waters Agriculture and Agri-Food Canada – Agriculture Mission & Government Issues Federal Dept – Applications Area Mission and Issues

Slide4: 

The user requirements from the U&ST 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. User & Science Requirements

Mission Objectives: 

Mission Objectives

Slide6: 

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.

Slide7: 

Mission Context

Mission Overview: 

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

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. 11:00 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 Mission Characteristics

Slide10: 

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

Slide11: 

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

Key Payload Characteristics: 

Key Payload Characteristics Targeting mission supporting mapping as background Spatial Swath width: > 30 km for VNIR and SWIR Ground Sampling Distance: 30m Keystone <0.1 x Ground Sampling Distance Geolocation with Ground Control Points: ~ 30m at Nadir Geolocation without Ground Control Point ~ 300m at Nadir Spectral Spectral Range <430 nm to >2450 nm Spectral Sampling Interval 10nm Smile <0.1 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)

Slide13: 

Payload Mechanical Design Two modules Separate fore-optics Each with dual Dyson Spectrometers; VNIR and SWIR detectors to provide ½ of the >30km swath, with overlap Instrument, and SWIR detector, passively cooled Thermally isolated from Bus

Slide14: 

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. Payload Function

Slide15: 

Payload Optical Layout

Slide16: 

Signal to Noise Ratio

Includes residual PRNU 0.1%, DCNU 1%: 

Includes residual PRNU 0.1%, DCNU 1% Effective SNR

Slide18: 

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

Slide19: 

Non Real-time VQ 1 Compression engine Throughput of a the board : ~0.3+ Gbps Estimated Power: ~10 W

Ordering and Spacecraft Control: 

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.

Slide21: 

Ordering & Dissemination

Slide22: 

0=Option, I=To internal Users only Mission Data and Products

Slide23: 

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

Slide24: 

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

Slide25: 

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

Slide26: 

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.

Slide27: 

Payload Diagram

PFCU : 

PFCU

Slide29: 

Order Handling and Planning

Slide30: 

Mission Spacecraft Control

Slide31: 

Slit Detail

Slide32: 

Spectrometer Detail First surface(s) of Dyson lens(es)