AIRCRAFT INCLUDING A SYSTEM FOR MEASURING PRESSURE, AND AN ASSOCIATED METHOD

摘要

The invention relates to an aircraft (10) having a system for measuring a static reference pressure in flight, which system comprises:
a pressure sensor (22) connected to the rear portion of the aircraft by a cable (16) and associated with a pressure intake (24) that is located, in flight, in an undisturbed zone downstream from the aircraft, the pressure signal (22) being suitable firstly for measuring a pressure coming from the pressure intake (24) and secondly for transmitting a signal representative of the measured pressure, e.g. an electric signal, to the aircraft; anda system (34) on board the aircraft, which system is suitable for determining a pressure measurement firstly from the transmitted signal and secondly from a position of the pressure sensor (22) relative to the aircraft (10). Pressure is measured dynamically while the aircraft is climbing or descending.

主权项

1. An aircraft (10) including a system for measuring pressure in flight, the aircraft being characterized in that the measurement system comprises:
at least one pressure sensor (22) connected to the rear portion of the aircraft by an electric cable (16), said at least one pressure sensor being associated with a pressure intake (24) that is arranged downstream from the aircraft when it is in flight and in a zone that is not disturbed by the turbulent flow created around the aircraft, the pressure intake (24) being arranged upstream from said at least one pressure sensor (22) and being connected thereto by at least one air feed tube (26; 50), said at least one pressure sensor (22) being suitable firstly for measuring an air pressure from at least one pressure signal coming from said pressure intake, and secondly for transmitting at least one electric signal representative of the measured pressure to the aircraft via the electric cable (16); and a system (34) on board the aircraft and suitable for determining at least one pressure measurement firstly from said at least one transmitted electric signal and secondly from a position of said at least one pressure sensor (22) relative to the aircraft (10).