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A pitot–static system is a system of pressure-sensitive instruments that is most often used in aviation to determine an aircraft's airspeed, Mach number, altitude, and altitude trend. A pitot–static system generally consists of a pitot tube, a static port, and the pitot–static instruments. [1]
It does this by giving an accurate measurement of the ambient atmospheric pressure (static pressure) well clear of the aircraft's fuselage. The trailing cone system trails at least one fuselage length behind the aircraft (SpaceAge Control) via a high-strength pressure tube. Static pressure is measured forward of the cone by several static ports.
A pitot-static system generally consists of a pitot tube, a static port, and the pitot-static instruments. [5] Errors in pitot-static system readings can be extremely dangerous as the information obtained from the pitot static system, such as airspeed, is potentially safety-critical. Several commercial airline incidents and accidents have been ...
The pitot tube may become blocked, because of insects, dirt or failure to remove the pitot cover. A blockage will prevent ram air from entering the system. If the pitot opening is blocked, but the drain hole is open, the system pressure will drop to ambient pressure, and the ASI pointer will drop to a zero reading. If both the opening and drain ...
As all information from the sensors is transmitted electrically, routing of pitot and static pressure lines through the aircraft and associated maintenance tasks is avoided. [ 5 ] In simpler aircraft and helicopters, the air data computers, generally two in number, and smaller, lighter and simpler than an ADIRU, may be called air data units ...
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An air data computer with inputs of pitot and static pressures is able to provide a Mach number and, if static temperature is known, true airspeed. [citation needed] Some authors in the field of compressible flows use the term dynamic pressure or compressible dynamic pressure instead of impact pressure. [3] [4]
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