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Modular Flight Control & Guidance Computer • significant reduction of hardware: : � integration of functions, enabled by computing performance (mixed criticality levels!) � → reduced amount of interfacing (computer ↔ computer, lane ↔ lane) • more efficient use of retained hardware: � more paths through system: move away from rigid lane structure � resource sharing, multi-use I/O hardware � no single-thread operation → reduced output h/w redundancy � graceful degradation (shedding of lower criticality functions (FG) to retain higher (FC)) • lower cost hardware: � no “ARINC-65X” backplane databus, connectors, module lever • strict separation of I/O from computational functions • dissimilarity BGT Bodenseewerk Gerätetechnik GmbH Concept: 108 ©1995-1997 F.M.G. Dörenberg
Modular Flight Control & Guidance Computer System architecture: 2 modular FCGCs •per FCGC: � 2 dual Computing Modules (CPMs) � 2 dual I/O Modules (IOM type “A”): – one mainly for PFC, the other mainly for FG � 2 dual I/O Modules (IOM type “B”): – one mainly for Hi-Lift and Maintenance – the other mainly for PFC/SFC, and – can act as “NGU” minimum-PFC backup � 2 or 3 Power Supply Modules (dep. on dispatch req’s) � A429 inter-FCGC, 10 Mbs serial inter-module � A650 cabinet form factor, shorter LRMs BGT Bodenseewerk Gerätetechnik GmbH - all modules are dual → fail-passive - 109 ©1995-1997 F.M.G. Dörenberg
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Integrated and Modular Systems for
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Integrated and Modular Systems for
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Integrated and Modular Avionics •
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Engine thrust Structure & Gear Comp
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Why change avionics? • Airline/Op
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Operators seek revenue enhancement
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Why change avionics? (cont’d) •
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Why change avionics? (cont’d) •
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Avionics business • high-tech but
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Changing airtransport environment 1
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5000 Pax-km (billions, log-scale) 1
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Billions of 1995 US $ 80 60 40 20 9
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24% 23% 23% 30% 737-300 ($1834/hr)
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Big $ numbers life-time maintenance
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Save now and save later • increas
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Average schedule deviation costs de
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Integrated Modular Avionics Archite
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Fault Avoidance - prevent (by const
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Fault Tolerance Taxonomy Fault Tole
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Redundancy • Attributes: � form
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Basic ways to increase system relia
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1 System Reliability λunit = 5x10-
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Note: log-log scale F (t) 2-out-of-
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System architecture and design deci
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1.0 Rconfig(t) 0.9 0.8 dual Redunda
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Simplex Dual Triplex Quad Dual-Dual
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Integration is necessary because...
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Integration trend: Multi-Mode Recei
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Integration issues • “integrate
Page 59 and 60: Fault Tolerance for Safety, Reliabi
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Page 73 and 74: Integration & Modularization • LR
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Page 79 and 80: assumes integration of related func
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Page 87 and 88: Modular Electronics: Not a New Conc
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Page 91 and 92: IMA - Integrated Modular Avionics L
Page 93 and 94: IMA Level-1 • LRUs re-packaged as
Page 95 and 96: IMA Level-4 & -5 • Level-4: funct
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Page 99 and 100: ATC/ATM FMS Functional Integration
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Page 103 and 104: Integrated Flight & Thrust Control
Page 105 and 106: Modular Flight Control & Guidance C
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Page 113 and 114: FCGC redundancy management - exampl
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1 Integrated and Modular Avionics
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3 FANS: Future Air Navigation Syste
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5 Component and System Performance
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7 Component and System Performance
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9 Future ........ (cont’d) • im
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11 150 k ↑ Total airplane signal
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13 100 MB 80 MB 20 MB 10 MB 747-200
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15 System Complexity and Size Typic
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17 Given: Extrapolation ...... •
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19 Enabling technologies - componen
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Enabling technologies - drivers for
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23 Enabling technologies - design /
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25 236-pin connector Example: PC mo
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27 Example: integrated X-band power
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29 Cold-Cathode Field Emission Disp
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31 Enabling technologies - componen
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33 Resource Partitioning - part of
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35 Enabling technologies - communic
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37 High Medium Low Enabling technol
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39 Enabling technologies � s/w
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1 BOOKS BIBLIOGRAPHY F.J. Redmill (
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3 M.L. Shooman: "A study of occurre
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