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Optical, Spectroscopic, and Infrared Remote Imaging System

Optical, Spectroscopic, and Infrared Remote Imaging System

This page has been archived and is no longer updated.OSIRIS is the scientific camera on board of the Rosetta spacecraft. It is a versatile imaging system designed to address key problems of the cosmogeny of comets by investigating the physical and chemical processes that occur in and near the nucleus.

Scientific Objectives

The investigation of the nucleus itself requires high spatial resolution over a wide wavelength range but with modest spectral resolution. The investigation of the innermost dust and gas coma requires a wide field of view with a selection of narrow band interference filters to image the 2-D gas distribution. OSIRIS consists of two cameras:

Narrow angle camera (NAC) with a 2.4×2.4° FOV
Wide angle camera (WAC) with a 12×12° FOV
Two identical full-frame, 2048×2048 pixel CCDs with 14 mm pixels equip both the NAC and the WAC.

OSIRIS was pre-selected as a PI instrument in April 1996, to be provided by a European consortium under the leadership of Dr U. Keller (MPAe, Lindau, Germany). Following funding difficulties for the original consortium, ESA was asked to participate in the development of the Data Processing Unit (DPU). The Solar System Division accepted this challenge because its participation in OSIRIS is an important step for future scientific expertise in planetary imaging.

The request to provide the OSIRIS DPU was implemented in the design and development phase by a joint venture between the former Technical and Operational Support Directorate (Payload Systems Division) and the Science Directorate (Solar System Division). This partnership provided the opportunity to direct the development of an onboard payload data processor within the ESA Technological Research programme (TRP) to a specific, real application, thus providing a cost-effective contribution to the Rosetta instrumentation.

Payload

OSIRIS DPU Flight model, board level test at EADS/ Astrium

Stiffener plate for DSP circuit board, needed for improved mechanical stability

OSIRIS DPU flight model, pre- integration

The DPU consists of two Digital Signal Processors (DSP) modules, a solid state mass memory, and spacecraft and camera interfaces. It facilitates image acquisition from both cameras, image compression and autonomous control of the entire instrument.

The Solar System Division provided a total of 3 fully-equipped "elegant breadboards" for system testing during the development phase. Furthermore, one qualification and 2 flight models were produced and delivered to the PI institute.

The hardware was delivered with an industry-standard real time operating system (VIRTUOSO) and specific low level device drivers.


Performance Specifications

  • Power consumption: 8W (compressing and transferring data at max. rate) 3.5W (low power mode)
  • Total mass: 1.4 kg (electronic boards, excl. housing)

Item Specification
Central Microprocessor Rad-hard Temic processor TSC21020, 20 MHz, 60 MFLOPS, data transfer speed from DSP memory to mass memory > 38 Mbps continuous
Mass Memory 4 Gbit netto DRAM- based
Program Memory
  • 8 kByte (8 bit) PROM (Bootstrap Kernel)
  • 256 kword (48 bit) EEPROM (OS, Task Specific Program Modules)
  • 256 kword (48 bit) Program SRAM (zero wait state)
  • All program memory is latch up and SEU immune
Local Data Memory
  • 4 Mwords (32 bit) fast SRAM image store, latch up and (almost) SEU immune
  • 128 kword (32 bit) fast SRAM variables + stack, latch up and SEU immune
  • 128 kByte Non-Volatile EEPROM
Digital Interfaces
  • Serial command I/F to NAC and WAC
  • Serial data I/F to NAC and WAC
  • Serial command and data I/F to mechanism controller
  • Serial command and data I/F to power converter
  • OBDH spacecraft I/F
Redundancy DSP board, S/C-interface: Dual cold redundancy
Mass memory board: Graceful Degradation
Protection Against Single Event Radiation Effects
  • SEL: Latchup detectors for mass memory, else LU immune components
  • SEU: Memory Error Correction (SSCDSD)
  • DSP Watchdog (two stage)
Power Management Low-Power Mode (program SRAM de-select, partial clock disabling)
Operating System Standard Real Time Operating System (Virtuoso)

Collaborating Institutions

  • The electronic boards of the DPUs were designed and manufactured under the responsibility of Astrium GmbH, Ottobrunn, Germany
  • Rosetta was launched in March 2004. First OSIRIS images were received during the commissioning phase in May 2004. They demonstrate the flawless performance of cameras and DPU.
  • Key SCI-SO personnel: P. Wenzel (lead, 'double- CoI'), U. Telljohann (technical manager), D. Koschny (deputy), B. Johlander (components procurement)

Web Links

Last Update: 1 September 2019
14-Nov-2019 06:26 UT

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Shortcut URL

https://sci.esa.int/s/AM9lYrA

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