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Dual P-S Air Pressure Transducer Module

Technical Information

Catalogue No: C1048
Category: Air Data
Object Type: Sensor/Transducer
Object Name: Dual P-S Air Pressure Transducer Module
Part No: 81-40-11
Serial No: 036/69
Manufacturer: Elliott Bros
Division: Unknown
Platform(s): Jaguar 
Year of Manufacture: 1969
Dimensions:
Width (mm):
79 
Height (mm):
183 
Depth (mm):
201 
Weight (g):
1,698 
Location: Main Object Store
Inscription(s):

Elliott
Type 81-40-11
P-S Transducer
Ref. STP1991654
Ser. 035/69
Mod. -
[comprising these modules]
────────────────
Elliott
Ser 065/69
P-S Capsule Unit
Type 81-04-05
Mod. No. -
────────────────
Elliott
Ser 066/69
P-S Capsule Unit
Type 81-04-05
Mod. No. -
────────────────
[repair mark]
E.B.L.R. Apr. 90

Notes:

This Pitot-Static Transducer was used in the Jaguar Air Data system. The unit contains two independent P-S Capsule Units and each aneroid capsule (or usually two capsules to magnify the movement) is coupled to an arm sliding along a wire wound resistor. A small servo motor was used to further amplify the movement of the capsules to operate the internal gear train. This simple arrangement transmits the difference signal between the Pitot and Static pressure to a remote indicator for Indicated Air Speed. The signal is also fed to a locking solenoid used in Height Lock mode to maintain barometric height.

Air data systems provide accurate information on quantities such as pressure altitude, vertical speed, calibrated airspeed, true airspeed, Mach number, static air temperature and air density ratio. This information is essential for the pilot to fly the aircraft safely and is also required by a number of key avionic subsystems which enable the pilot to carry out the mission. It is thus one of the key avionic systems in its own right and forms part of the essential core of avionic sub systems required in all modern aircraft, civil or military.

The air data quantities; pressure, altitude, vertical speed, calibrated airspeed, true airspeed, Mach number etc. are derived from three basic measurements by sensors connected to probes which measure:

Total (or Pitot) pressure
Static pressure
Total (or indicated) air temperature

The total pressure, PT, is measured by means of an absolute pressure sensor (or transducer) connected to a Pitot tube facing the moving airstream. The Pitot pressure is a measure of ram air pressure (the air pressure created by vehicle motion or the air ramming into the tube). When airspeed increases, the ram air pressure is increased, which can be translated by the airspeed indicator.

The static pressure of the free airstream, PS, is measured by an absolute pressure transducer connected to a suitable orifice located where the surface pressure is nearly the same as the pressure of the surrounding atmosphere. The static pressure is obtained through a static port which most often is a flush-mounted hole on the fuselage of an aircraft located where it can access the air flow in a relatively undisturbed area. Some aircraft may have a single static port, while others may have more than one. When the aircraft climbs, static pressure will decrease.

High performance military aircraft generally have a combined Pitot/static probe which extends out in front of the aircraft so as to be as far away as practicable from aerodynamic interference effects and shock waves generated by the aircraft structure. A Pitot-static tube effectively integrates the static ports into the Pitot probe. It incorporates a second coaxial tube (or tubes) with pressure sampling holes on the sides of the probe, outside the direct airflow, to measure the static pressure. Some civil transport aircraft have Pitot probes with separate static pressure orifices located in the fuselage generally somewhere between the nose and the wing.

From the measurements of static pressure PT and total pressure PS it is possible to derive the Pressure Altitude, Vertical Speed, Calibrated Airspeed and Mach number. Measurement of the air temperature is made by means of a temperature sensor installed in a probe in the airstream and from this a function called Total Air Temperature can be calculated.

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