Tornado CSAS Pitch Computer

Technical Information

Catalogue No: C0412
Category: Flight Control
Object Type: Signal/Data Processor
Object Name: Tornado CSAS Pitch Computer
Part No: 47-022-04
Serial No: 029
Manufacturer: Marconi-Elliott Avionics
Division: Unknown
Platform(s): Tornado 
Year of Manufacture: Unknown
Dimensions:
Width (mm):
260 
Height (mm):
196 
Depth (mm):
385 
Weight (g):
15,900 
Location: Archive Object Store
Inscription(s):

Elliott/Bodenseewerk
Pitch Computer
Type No. 47-022-04
Serial No. 029
Spec No. SP-P-41600
Ident No.
NATO Stock No.
Modification Record -
Mfd by Marconi-Elliott Avionics Systems Ltd
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Elliott/Bodenseewerk
Electronic Equipment Assembly
Type No. 7914-00148
Serial No. 028
Spec No. SP-P-41600
Ident No.
NATO Stock No.
Modification Record -
Mfd by Marconi-Elliott Avionics Systems Ltd
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BAE Systems (Electronic Systems)
Contract No. NETMA/C1/40000/88/NR
Ident No.
Property of NAMMO
────────────────
Part No COP47-022-04
Desc Pitch Computer
Locator Museum
Serial Number 0029
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Major Concession PM00268
CN549A
CN569
CN619
────────────────
XCR's
BF-122-00
BF-141-00
BF-135-00
BF-142-00
MQ208-487
MQ208-493
BF-158-00
BF-162-00
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THREE POWER SUPPLY MODULES:
Elliott/Bodenseewerk
Power Supply Unit
Type No. 7501-00049
Serial No. 085, 086 & 087
Spec No. SP-P-41600
Ident No.
NATO Stock No.
Modification Record -
Mfd by Marconi-Elliott Avionics Systems Ltd

Notes:

The command stability augmentation system: (CSAS) is by its very nature one of the most complex systems on Tornado. Hardly detectable in the cockpit, the CSAS keeps the ride comfortable at all speeds and altitudes, and makes the aircraft controllable throughout the flight envelope.It is a “fly-by-wire” system with auto-stabilisation, the pilot’s control demands being signalled and augmented electrically to maintain good handling qualities over the wide flight envelope. In the pitch axis, the fly-by-wire system has mechanical reversion. The system is triplicated and includes triplex computing, triplex rate gyros, triplex position sensors and a triplex accelerometer, with quadruplex outputs driving quadruplex electro-hydraulic actuators. These “fly-by-wire” actuators were originally designed by Marconi-Elliott Avionic Systems Limited and have now been integrated by Fairey Hydraulic into the aircraft’s main hydraulic power control units.
The CSAS electronics is packaged in two units, the pitch computing circuitry being housed in a single computer and the roll, yaw and spoiler circuitry in a similar computer.
The system uses very high-precision analogue circuitry to provide accurately- matched control lanes, and a unique voter monitor design which reduces transient effects, due to system failures, to a low level and is so designed also that nuisance warnings are rare.
Marconi-Elliott Avionic Systems Limited has design leadership on the CSAS programme, but shared the production with Bodenseewerk Geratetechnik.
The system was designed to Specification SP-P-41600.

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