BIRD (satellite)

BIRD denotes a small satellite of the German Aerospace Center (DLR ), which was developed and built at DLR Berlin Adlershof in collaboration with other DLR sites. Essential components and contributions come from the Fraunhofer Institute for Computer Architecture and Software Technology ( FIRST) ( on-board computer ), the Jena- Optronic GmbH ( star sensor ), the Astro and precision engineering Adlershof GmbH ( reaction wheels ), the Institute of Aeronautics and Astronautics at the Technical University Berlin and the alpha-board ( PCB layout for electronic components).

BIRD is an acronym for Bispectral InfraRed Detection. The satellite can detect fires on earth through their radiation in the infrared range. The findings on spread and intensity of large-scale and small fires are extremely helpful for the local firefighters. Therefore, the German Aerospace Center (DLR ) passes this information as quickly as possible to the appropriate personnel. The evaluation and classification of the data is carried on board the satellite, so that already processed data are passed on to the end user.

The satellite will be operated by GSOC, wherein the data reception via the DFD Neustrelitz done and an operation can also be performed on experimental ground stations of DLR Berlin -Adlershof and in Ny -Ålesund (Spitzbergen ). Project was to 2003 Prof. K. Briess (now Institute of Aeronautics and Astronautics TU Berlin) and since then it is Dr. E. Lorenz from DLR Berlin -Adlershof.

The mission was a success and the satellite functioned as part of its design lifetime of one year successful. In particular, the scientific IR payload processing algorithms and the satellite bus ' could be verified. Due to this success, the BIRD satellite bus serves as the basis for the new OOV program line of the DLR.

The BIRD satellite was launched on 22 October 2001 with the Indian PSLV and is still in operation. It is located in a 572 km sun-synchronous orbit high (SSO).

As a successor to the two satellite BIRD and TET Biros are provided by one-year test operation.

Specifications

  • Payload: WAOSS -B camera ( 0.6 to 0.67 and from 0.84 to 0.9 microns)
  • 1 MIR sensor ( 3.4 to 4.2 microns)
  • 1 TIR sensor ( 8.5 to 9.3 microns)
  • 65 kg Busmasse, 30 kg payload
  • 2 fold-out solar panels, one permanently installed solar panel
  • 8 NiH2 battery cells
  • 4 high-performance on-board computer ( 2 hot and 2 cold redundant)
  • Autonomous position control in state space 2 star sensors
  • Magnetic field sensor
  • GPS sensor
  • IMU (3 axle gyro )
  • 4 reaction wheels
  • Solenoids
  • 2 heatpipes
  • 2 radiators
  • 2 Stirling engines ( for cooling the MIR / TIR sensors)
  • Heater and temperature sensors
  • CFC - conductor of heat
  • Multilayer insulation
International Designator Satish Dhawan Space Centre Polar Satellite Launch Vehicle Orbital inclination TET-1
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