集成化模块式航空电子设备过程/方法

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航空

Processes and Methods for
Integrated Modular Avionics
Presentation at USA - EU Workshop
Paris, July 7th 2005
Presented by
Gert DÖHMEN
AIRBUS Germany
Page 2
© AIRBUS DEUTSCHLAND GmbH. Alle Rechte vorbehalten. Vertrauliches und geschütztes Dokument.
Integrated Modular Avionics (IMA)
A
LRU A
LRU B
B Airborne
Functions
Integrated
Avionics
Conventional
Avionics
LRU C C
LRM 1
LRM 2
Identical Hardware & Kernel Software used for different
Airborne Functions in Flight Control & Utility Functions
Page 3
© AIRBUS DEUTSCHLAND GmbH. Alle Rechte vorbehalten. Vertrauliches und geschütztes Dokument. Targeted IMA Advantages
• Reduction of Weight / Volume / Power consumption of
the Avionics
• Reduction of material stocks within Airline Maintenance
Centers
• Reduction of cost for Versions-Upgrades (core HW &
SW)
• Reduction of cost for functional enhancements
• Reduction of cost through the emerging market of open
standards
Page 4
© AIRBUS DEUTSCHLAND GmbH. Alle Rechte vorbehalten. Vertrauliches und geschütztes Dokument. IMA Concept -
LRU /
LRM based Architecture
AFDX Switch
LRU
AFDX interface
Static cabling configuration
1 new link = AFDX switch configuration
table update
LRM
module
AFDX link
LRU6
ARINC 429 world IMA world
LRU5
LRU2
LRU1
LRU7
ARINC 429 interface
LRU4
1 new link = 1 new cable
ARINC 429 link
CPIOM
CPIOM
IOM
LRU
AFDX Switch
AFDX E/S
Page 5
© AIRBUS DEUTSCHLAND GmbH. Alle Rechte vorbehalten. Vertrauliches und geschütztes Dokument. ADCN Network Architecture -
Functional Domains
WARNING: old obsolete architecture for functional domain description only!
Engines
Cabin
Fuel&LG
Energy
Cockpit
Flight
Control
AESU1
EEC1
EEC2
FCSC1
COM MON
FCGC2 FCSC2
FCGC3
SFCC2
COM MON COM MON
SFCC1
FCGC1
ADIRU1
ADIRU3
ADIRU2
FM3
FM1 FM2
FW2
FCDC2
FW1
FCDC1
AESU2
ACR2 opt
SCI
L1 L2 R2 R1
C2 R3
C1
SW13
IOM
ELM
CBM
SB24
ELM
CBM
SB24
Fuel
COM MON
Fuel
COM MON LG,TP&BS
CIDS
CPIOM-B-1&2
CIDS
CPIOM-A-3&4CPIOM-B-3&4
IRDC
COM MON
LG,TP&BS
COM MON
COM MON COM MON COM MON
IOM
ACR1
SCI
CPIOM-A-1&2
PESC
SPDB
IPCU
SPDB
VSC
PWCU
IRDC
DSMC1&2 DSMC3
ext lights
ctrl
IPCU
ECB
HSM
AIC?
HSM
AIC?
COM MON FCSC3 TBC
COM MON
L3
IOM CDAM IOM
ATC1
ATC2
A
AB
B
EEC3
EEC4 AB
BA
S_2
_1
S_3
_1
S_4
_1
S_1
_1
S_3
_2
S_4
_2
S_1
_2
S_2
_2
S_1
_3
Page 6
© AIRBUS DEUTSCHLAND GmbH. Alle Rechte vorbehalten. Vertrauliches und geschütztes Dokument. Flow Separation Concept
VL1
VL2
VL3
Physical
Logical Link
representation
of a Virtual Link
Ethernet
controller
Switching Fabric
SWITCH
TX Transmit MAC
RX TX RX TX RX TX
Appl. 1
Appl. 2
Appl. 3
Physical Link
Virtual Links
End-System 1
End-System 1
End-System 2
End-System 3
End-System 4
End-
System
3
TX RX
End-
System
3
TX RX
End-
System
3
TX RX
RX Receive MAC
The Virtual Link Concept
VL2
Page 7
© AIRBUS DEUTSCHLAND GmbH. Alle Rechte vorbehalten. Vertrauliches und geschütztes Dokument. LRM /
CPIOM Hardware
Four electronic boards :
- One CPU board
- One Power supply and I/O board
- Two I/O boards
ARINC 600 SIZE 2
Connector
Backplane
SIS module connector
PCI interconection
board
• ARINC 600, 3 MCU
• Approximately 4 kg
• Powered by 28VDC (some on ESS bus)
• ARINC 600 conn., 368 pins + 2 QUADRAX
• Hardware pin programming identifies domain, location,
side, aircraft (MAC and IP addressing on Aircraft Data
Communication Network (ADCN))
Page 8
© AIRBUS DEUTSCHLAND GmbH. Alle Rechte vorbehalten. Vertrauliches und geschütztes Dokument. Building blocks of an Integrated CPIOM
Instrumentation Service
Dataloading
Operating System
Hardware
􀁹 Memory Management
􀁹 Scheduling
􀁹 Data I/O, Communication
Application Programming Interface
Configuration
TableResource BITE
MIB - SNMP
Monitoring
User System
Application n
User System
Application 1
User System
Application 2
...
AFDX Communication
ARINC Communication
CAN Communication
Analogue Signals
Discrete Signals
Page 9
© AIRBUS DEUTSCHLAND GmbH. Alle Rechte vorbehalten. Vertrauliches und geschütztes Dokument. IMA Configuration Process Aspects
• Classification of Configuration Parameter (Module, Global, Local).
• Hardware/OS specific configuration parameter.
• Manual assignment of resources supported by databases.
• Automated tool-chain to produce the load.
Function Supplier 3
Function Supplier 1
Function Supplier 2
System Depart. 3
System Depart. 1
System Depart. 2
Module Integrator
ADCN & IMA
Module Supplier
Airbus
A380: 7 Module types; Up to 4 redundant Modules; 22 Physical Modules
Information & Data Flow
for one Module Type
Page 10
© AIRBUS DEUTSCHLAND GmbH. Alle Rechte vorbehalten. Vertrauliches und geschütztes Dokument.
Visions for IMA
Processes & Methods
Page 11
© AIRBUS DEUTSCHLAND GmbH. Alle Rechte vorbehalten. Vertrauliches und geschütztes Dokument. Configuration based on System Model
• Configuration bound to System Description Language
• Support of different Layer (e.g. Application, OS, Hardware)
• Decoration of Abstract Syntax Tree with configuration data
CPIOM
BOOT KERNEL
I/O
(discrete,
analog)
AFDX
1
CAN
DRV_MGR
ARINC 429
MODULE KERNEL
PARTITION PARTITION
MANAGEMENT
SERVICES
0..*
API
Scheduler
PARTITION A Queuing Com 001 PARTITION B
reset reset
OUT P1 P2 IN
• Declaration of dependencies
between parameter on the
same or adjacent layer.
Page 12
© AIRBUS DEUTSCHLAND GmbH. Alle Rechte vorbehalten. Vertrauliches und geschütztes Dokument. Component-based System Development
• Concept of building up the
system architecture from
exchangeable (heterogeneous)
components.
• Components are enriched with
functional and non-functional
aspects as “Heterogeneous
Rich Components” (HRC).
• Their characteristics can be
assessed on the basis of those
aspects.
Assumed
From/by lower
design layers
from
neighbors
Promised
From/by higher
design layers
to
neighbors
EL
FL
SL
HL
• Design-space exploration is used to find a semi-optimal
mapping of applications to LRMs under multi-dimensional
constraints.
Page 13
© AIRBUS DEUTSCHLAND GmbH. Alle Rechte vorbehalten. Vertrauliches und geschütztes Dokument. Improvement of the Development Process
• Ubiquitous seamless model-based design access
􀀗hiding heterogeneity and semantic diversity of
representations and methods, and
􀀗providing a design-centric access to all design activities.
• During all design phases, process steps must be guided by
an estimation how far overall requirements (e.g. safety,
costs) are fulfilled. This “speculative” design can be based
on HRC analysis methods.
• High flexibility and robustness with respect to late changes
and overlapping design activities.
Page 14
© AIRBUS DEUTSCHLAND GmbH. Alle Rechte vorbehalten. Vertrauliches und geschütztes Dokument. From Structural to Analytical Redundancy
• Identical Hardware & Kernel Software is the prerequisite for
a flexible allocation (reconfiguration) of applications.
• The amount of Structural Redundancy (and thus number of
LRM) can be reduced by the use of Analytical Redundancy.
• Analytical Redundancy requests design-space exploration
with safety constraints.
• The Analytical Redundancy has to respect certification
aspects.
Page 15
© AIRBUS DEUTSCHLAND GmbH. Alle Rechte vorbehalten. Vertrauliches und geschütztes Dokument.
Dieses Dokument und alle darin enthaltenen Informationen
sind das alleinige Eigentum von AIRBUS DEUTSCHLAND
GmbH. Die Zustellung dieses Dokumentes oder die
Offenlegung seines Inhalts begründen keine Rechte am
geistigen Eigentum. Dieses Dokument darf ohne die
ausdrückliche schriftliche Genehmigung von AIRBUS
DEUTSCHLAND GmbH nicht vervielfältigt oder einem Dritten
gegenüber enthüllt werden. Dieses Dokument und sein Inhalt
dürfen nur zu bestimmungsgemäßen Zwecken verwendet
werden.
Die in diesem Dokument gemachten Aussagen stellen kein
Angebot dar. Sie wurden auf der Grundlage der aufgeführten
Annahmen und in gutem Glauben gemacht. Wenn die
zugehörigen Begründungen für diese Aussagen nicht
angegeben sind, ist AIRBUS DEUTSCHLAND GmbH gern
bereit, deren Grundlage zu erläutern.

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