Tornado Lateral Accelerometer Unit

Technical Information

Catalogue No: C0989
Category: Flight Control
Object Type: Sensor/Transducer
Object Name: Tornado Lateral Accelerometer Unit
Part No: 12-010-01
Serial No: 005
Manufacturer: Marconi-Elliott Avionics
Division: Unknown
Platform(s): Tornado 
Year of Manufacture: Unknown
Dimensions:
Width (mm):
130 
Height (mm):
50 
Depth (mm):
95 
Weight (g):
560 
Location: Archive Object Store
Inscription(s):

Elliott/Bodenseewerk
Lateral Accelerometer Unit
Type No. 12-010-01
Serial No. 005
Spec. SP-P-41600
Ident. No.
NATO Stock No.
Modification Record
A B C ... X Y Z
Mfd by Marconi-Elliott Avionic Systems Ltd

Notes:

This is a sensor for lateral acceleration driving into the CSAS. A yaw rotation is a movement around the yaw axis of the aircraft that changes the direction it is pointing, to the left or right of its direction of motion. The yaw rate or yaw velocity of the aircraft is the angular velocity of this rotation, or rate of change of the heading angle when the aircraft is horizontal. It is commonly measured in degrees per second or radians per second. The Accelerometer is located as near to the centre of gravity of the aircraft.

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 autostabilisation, 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 electrohydraulic 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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