Technical Overview

The technical outline of the DIAMANT system has been studied in 1997 on feasibility / phase A level for all required elements ("DAVID"). This study did not show criticalities for system implementation. The scientific and technical concepts for the DIAMANT System elements - elaborated in Phase A - constitute the baseline for the currently running sensor development.

MSRS Sensor and Space Segment


The MSRS Sensor reflects an innovative approach based on proven technology:

Telescope

well established technology based on extensive past experience.
Detector

innovative new MS CCD TDI detector based on proven technology for space applications.
Filters

innovative new multi narrow band interference filter design based on proven space technology. In addition dichroic filter design for innovative FPA structure.
Sensor

low power/low volume multi channel electronics based on Electronics advanced ASIC components.

Sensor Control (DSP)

floating point DSP optimised for image pre-processing like cloud detection and data compression.
Data Storage

space proven technology based on 60 GBits user accessible solid state storage with 12 x 100 Mbit/s input data rate.
X-Band

space proven technology providing up to 320 MBits/s
Power Supply

space proven technology


 

 MSRS Sensor Characteristics
  • Lightweight (70 kg)
  • Low power consumption (peak. ~120 W)
  • Low volume 60x58x58 cm (flexible)
  • 12 spectral bands VIS / NIR, 5 m resolution
  • 4 TDI detectors with 3 channels each
  • On-board calibration
  • Image scene size: 26 km x 40 km
  • 60GBit data storage for 10 scenes per orbit (up to 200 GBits)
  • X- Band 100MBit/s data downlink (optional 280 MBit/s)
  • Compression optional

DIAMANT S/C Bus Characteristics

  • Mass / Volume: < 250kg / < 1m x 1m x 1m (including the MSRS Sensor)
  • Advanced ACS Subsystem:
    • Slewing capability ± 30°, off-track / in-track ==> stereo imaging;
    • <10% target error of 30 km = 3 km (0.26°);
    • Stability: <2 Pixel per Image (3.2 arcsec) after 6 sec imaging
  • Power: 141 W peak, 55 W average per orbital period
  • Launch preferable secondary / dual: COSMOS, ARIANE 5, Pegasus



Orbit Characteristics

The orbit of the DIAMANT system is optimised for complete earth coverage after 3 days above 27° latitude, considering the 30° slewing capability.

  • 670km, polar, sunsynchronous
  • Cycle of complete coverage:
    • 4 days at ±20° latitude;
    • 3 days at ±27° latitude
  • Revisit cycle: 3 days = 45 orbits
  • Maximum observable latitude with sun incidence angle > 30°:
  • +59,5° in spring or autumn.
  • Orbit decay: < 35 km in five years
  • Descending node: 11:30 TBC


Orbit repetition optimisation

The cycle of complete coverage and the Revisit cycle will be improved by the installation of the DIAMANT satellite constellation. Daily coverage will be achieved by a constellation of 3 satellites and the system performance will increase to more than 420 scenes per day as shown below

 

Ground Segment and Coverage


The Ground Segment consists of a Satellite Control Station and a Data Archive & Distribution Center including data reception connected via existing ground infrastructure to the users. For near real-time data delivery DIAMANT will use an existing data reception station infrastructure (see figure below). The coverage of this network allows real-time data transmission over the whole European continent. Level 1 and 2 (standard path orientated data) data pre-processing is performed at the Data Reception Station.

DIAMANT/MSRS Spectral Characteristics and commercial/scientific features


 

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For comments or further information, please contact: Boris Penné

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