In-flight reconfigurable FPGA based electronics for INTEGRAL Imager prototype

Describes the unprecedented implementation of "in-flight" reconfigurable on-board data handling electronics using reprogrammable FPGA (field programmable gate array) technology. The electronics design was realized for a prototype of the Imager for the INTEGRAL mission that is an ESA "...

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Bibliographic Details
Published inIEEE transactions on nuclear science Vol. 42; no. 4; pp. 917 - 920
Main Authors Corba, M., Quadrini, E.M.
Format Journal Article Conference Proceeding
LanguageEnglish
Published New York, NY IEEE 01.08.1995
Institute of Electrical and Electronics Engineers
Subjects
Aerospace electronics
Aerospace engineering
Arrays
Astronomical and space-research instrumentation
Astronomy
Balloons
CMOS integrated circuits
Costs
Data handling
Design engineering
Digital signal processing
Earth, ocean, space
Exact sciences and technology
Field programmable gate arrays
Flexible structures
Fundamental astronomy and astrophysics. Instrumentation, techniques, and astronomical observations
Imaging systems
International collaboration
Logic circuits
Payloads
Photodiodes
Power engineering and energy
Prototypes
Radio transmission
Random access storage
Scintillation counters
X-ray and γ-ray telescopes and instrumentation
Gamma astronomy
Data handling
Electronics
Imager
Instrumentation
Spaceborne instruments
Performance
Balloons
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Summary:Describes the unprecedented implementation of "in-flight" reconfigurable on-board data handling electronics using reprogrammable FPGA (field programmable gate array) technology. The electronics design was realized for a prototype of the Imager for the INTEGRAL mission that is an ESA "Horizon 2000" long term plan, now in the second selection cycle (M2). The Imager prototype was developed by an international collaboration, and was flown successfully on a balloon from Fort-Sumner, New Mexico in October 1993. The purpose of this reconfigurable electronics was to demonstrate a new engineering approach that would reduce the cost of mass and power of the payload. The accomplishment of using a flexible structure in an instrument prototype combined with the demonstration of high performance during hostile environmental flight conditions is presented.< >
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ISSN:0018-9499
1558-1578
DOI:10.1109/23.467882