Abstract: A device for maintaining and analyzing an aerodynamic probe of stagnation pressure type intended to be installed in an aircraft comprises a channel with a first end that is intended to penetrate into the probe, and an ejector fluidly coupled to the channel to create an air depression in said channel relative to the ambient pressure and a closed vessel recovering any particles sucked into the channel, the ejector and closed vessel being external to the probe when the channel is inserted into the probe. The ejector is coupled to a pressurized gas source and ejects gas in proximity to a second end of the channel opposite the first end to suction the air present in the channel and thereby create the air depression in said channel.

Abstract: A device for maintaining and analyzing an aerodynamic probe of stagnation pressure type intended to be installed in an aircraft comprises a channel with a first end that is intended to penetrate into the probe, and means for creating in the channel an air depression relative to the ambient pressure and means for recovering any particles sucked into the channel.

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 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.