Thales

Thales Avionics S.a.

Lionel Collot

Henri Leblond

Nicolas Hanson

Jo&euml;l Choisnet

Joel Choisnet

Philippe Roberge

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.

Rotary joint for a moving-vane multifunction pressure probe

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.

Multifunction probe with variable flexure

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 (TT) of the airflow, the temperature (TT) 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.

Device and method for determining total temperature for aircraft

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 (&#x3b1;, &#x3b1;), the process consists in determining the angle of attack (&#x3b1;) and/or sideslip (&#x3b2;) 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. This fault detection process consists in:

Method for determining aerodynamic parameters and method for detecting failure of a probe used for determining aerodynamic parameters

A probe for an aircraft, making it possible in particular to measure the total temperature of the air flow surrounding the aircraft. The probe includes a moving vane configured to orientate itself in the axis of an air flow surrounding the moving vane and, fixed to the moving vane, a device for measuring the total temperature of the air flow.

Aircraft probe for measuring total temperature and pressure

A multifunction probe for aircraft to determine in particular the static pressure and the total pressure of an airflow located in the vicinity of the aircraft and the angle of incidence of the aircraft with respect to the airflow. The probe includes a movable blade configured to orient itself along the axis of the airflow. The movable blade includes at least one static pressure tap orifice located on one side of the blade and a pressure tap configured to measure the angle of incidence of the blade with respect to the airflow. The probe further includes a pressure measurement device associated with each pressure tap and a device to calculate the total pressure of the airflow as a function of the measurements carried out by the various measurement devices of the probe.

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Vendome, France

Lionel Collot