Abstract: The present invention relates to pressure probes for measuring the aerodynamic flight parameters of an aircraft and more particularly those in which the orifices for measuring the static pressure and total pressure are located on a moving angle-of-attack or angle-of-sideslip measurement vane designed to be oriented in the direction of the wind. It consists of a pneumatic rotary joint employing flexible tubings rather than friction rotary joints between abutted parts of rigid tubings. Such a joint offers a much smaller resistance to the rotational movement of the moving vane, which consequently is oriented with greater accuracy in the direction of the wind.

Abstract: The present invention relates to pressure probes for measuring the aerodynamic flight parameters of an aircraft and more particularly those in which the orifices for measuring the static pressure and total pressure are located on a moving angle-of-attack or angle-of-sideslip measurement vane designed to be oriented in the direction of the wind. It consists of a pneumatic rotary joint employing flexible tubings rather than friction rotary joints between abutted parts of rigid tubings. Such a joint offers a much smaller resistance to the rotational movement of the moving vane, which consequently is oriented with greater accuracy in the direction of the wind.

Abstract: The invention relates to a multifunction probe for aircraft. The probe has a mobile vane intended to align with the axis of an air flow around the probe. The mobile vane comprises first pressure pickup means for measuring the total pressure of the flow and second pressure pickup means for measuring the static pressure of the flow. The mobile vane furthermore has a profile whose flexure is variable.

Abstract: The invention relates to a device for determining total temperature for aircraft. This device is particularly useful in a probe, called a multifunction probe, for measuring several aerodynamic parameters such as, for example, the total pressure (Pt), the static pressure (Ps) and the total temperature (TT) of an airflow surrounding the aircraft. The device includes a deiced temperature probe. To obtain the total temperature (TTcorrected) of the airflow, the temperature (TTmeasured) recorded by the temperature probe is corrected as a function of the upstream infinity parameters (M?, Pt?, Ps?) of the aircraft and of the power (P) dissipated in the probe in order to deice it.

Abstract: The invention concerns a multifunction probe for aircraft. The probe measures the total pressure and measures the total temperature of an air flow surrounding the aircraft. The total pressure is measured by a first tube, the so-called Pitot tube oriented substantially along the axis of the air flow surrounding the aircraft, the total temperature is measured by a second tube open to the air flow and oriented substantially in the axis of the air flow. The first tube is situated inside the second tube. The invention also concerns a process for shaping a heating wire forming means of deicing of the multifunction probe. The process includes: winding the heating wire helically around a first mandrel, inserting the first mandrel into a second hollow mandrel, continuing the winding of the heating wire around the second mandrel, and placing the heating wire, thus formed, inside the two tubes and being fixed therein.

Abstract: The invention pertains to a process for determining aerodynamic parameters of an airflow surrounding an aircraft. On the basis of at least two probes situated on the skin of the aircraft, each probe comprising means for measuring the local angle of attack (?loc i, ?loc j), the process consists in determining the angle of attack (?) and/or sideslip (?) of the aircraft, as a function of the local angle of attack of each probe and of the aerodynamic field of the aircraft. The invention also pertains to a process for detecting a fault with a probe used to determine the aerodynamic parameters of the airflow surrounding an aircraft.

Abstract: The invention relates to a multifunction probe for aircraft. The probe has a mobile vane intended to align with the axis of an air flow around the probe. The mobile vane comprises first pressure pickup means for measuring the total pressure of the flow and second pressure pickup means for measuring the static pressure of the flow. The mobile vane furthermore has a profile whose flexure is variable.

Abstract: The invention concerns a multifunction probe for aircraft. The probe comprises means for measuring the total pressure and means for measuring the total temperature of an air flow surrounding the aircraft. The means for measuring the total pressure comprise a first tube the so-called Pitot tube oriented substantially along the axis of the air flow surrounding the aircraft and the means for measuring the total temperature comprise a second tube open to the air flow and oriented substantially in the axis of the air flow. The first tube is situated inside the second tube. The invention also concerns a process for shaping a heating wire forming means of deicing of the multifunction probe. The process includes: winding the heating wire helically around a first mandrel, inserting the first mandrel into a second hollow mandrel, continuing the winding of the heating wire around the second mandrel, and placing the heating wire, thus formed, inside the two tubes and being fixed therein.

Abstract: The invention pertains to a process for determining aerodynamic parameters of an airflow surrounding an aircraft. On the basis of at least two probes situated on the skin of the aircraft, each probe comprising means for measuring the local angle of attack (&agr;loc i, &agr;loc j), the process consists in determining the angle of attack (&agr;) and/or sideslip (&bgr;) of the aircraft, as a function of the local angle of attack of each probe and of the aerodynamic field of the aircraft. The invention also pertains to a process for detecting a fault with a probe used to determine the aerodynamic parameters of the airflow surrounding an aircraft.