Abstract: The invention relates to an aerodynamic measurement probe of an airstream along a wall. The invention makes it possible notably to determine the attack of an airstream relative to an axial reference tangential to the wall. The invention is particularly useful in the aeronautical field. According to the invention, the probe comprises several emitters that can each emit a sound wave and a receiver sensitive to the different sound waves. Thus, there is forewarning of the receiver error that is common to all the measurements of travel time of a sound wave between one of the emitters and the receiver.

Abstract: The invention relates to a probe for aerodynamic measurement of an airflow. The probe comprises a plate rotating about an axis, a transmitter for transmitting a sound wave and a receiver responsive to the sound wave, the transmitter and the receiver forming two elements which are integrally connected to the plate and are placed at separate positions on the plate, the probe furthermore comprising means for delivering information representing a time of flight of the sound wave between the two elements and a temporal variation of the information. In the case of using the probe on board a helicopter, the rotating plate is advantageously placed at the centre of the rotor of the helicopter while being integrally connected to it. This type of probe makes it possible to carry out aerodynamic measurements even at low airspeeds of the helicopter.

Abstract: The invention relates to a device and to a method for measuring the total pressure of a flow. According to the invention, the device comprises a Pitot tube (25), means for measuring the total pressure at a stagnation point (4, 12) and comparison means (32, 33) for comparing pressures measured by the Pitot tube (25) and the means for measuring total pressure at the stagnation point (4, 12), the Pitot tube (25) and the means for measuring total pressure at the stagnation point (4, 12) being joined together and tapping air streams off the flow along the same axis (7). The method implementing the device includes comparing the measured pressures and if the difference between the two measured pressures is greater than a given discrepancy, then a warning is generated specifying that only the higher pressure has a good likelihood of being correct.

Abstract: The invention relates to an aerodynamic measurement probe of an airstream along a wall. The invention makes it possible notably to determine the attack of an airstream relative to an axial reference tangential to the wall. The invention is particularly useful in the aeronautical field. According to the invention, the probe comprises several emitters that can each emit a sound wave and a receiver sensitive to the different sound waves. Thus, there is forewarning of the receiver error that is common to all the measurements of travel time of a sound wave between one of the emitters and the receiver.

Abstract: The invention relates to a probe for aerodynamic measurement of an airflow. The probe comprises a plate rotating about an axis, a transmitter for transmitting a sound wave and a receiver responsive to the sound wave, the transmitter and the receiver forming two elements which are integrally connected to the plate and are placed at separate positions on the plate, the probe furthermore comprising means for delivering information representing a time of flight of the sound wave between the two elements and a temporal variation of the information. In the case of using the probe on board a helicopter, the rotating plate is advantageously placed at the centre of the rotor of the helicopter while being integrally connected to it. This type of probe makes it possible to carry out aerodynamic measurements even at low airspeeds of the helicopter.

Abstract: The invention relates to a device and to a method for measuring the total pressure of a flow. According to the invention, the device comprises a Pitot tube (25), means for measuring the total pressure at a stagnation point (4, 12) and comparison means (32, 33) for comparing pressures measured by the Pitot tube (25) and the means for measuring total pressure at the stagnation point (4, 12), the Pitot tube (25) and the means for measuring total pressure at the stagnation point (4, 12) being joined together and tapping air streams off the flow along the same axis (7). The method implementing the device includes comparing the measured pressures and if the difference between the two measured pressures is greater than a given discrepancy, then a warning is generated specifying that only the higher pressure has a good likelihood of being correct.

Abstract: The invention pertains to an incidence probe intended to measure the incidence of an air stream flowing outside a skin. The invention finds particular utility in aeronautics for measuring the incidence of an aircraft. According to the invention, the incidence probe comprises a body situated outside the skin and means of measurement of a stress exerted by the air stream on the body.

Abstract: A device for regulating the temperature of a heating wire powered by a DC voltage is described. The invention has a particular, but not exclusive, utility in the de-icing of aerodynamic probes used in aeronautics. The device comprises an electronic switch connected in series with the heating wire and means for controlling the electronic switch. The device also comprises means for controlling a switching time of the electronic switch.

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 the measurement of the total pressure of a fluid flow, especially the total pressure of the airflow surrounding an aircraft. The invention proposes to replace a pitot tube with a device in which at least two fluid streams are taken off from the flow. These streams are brought into contact with each other so as to be mutually slowed down in a region (11) where the pressure is measured. This measured pressure is representative of the total pressure (Pt).

Abstract: Device for measuring the total pressure of a flow The invention relates to the measurement of the total pressure of a fluid flow, especially the total pressure of the airflow surrounding an aircraft. The invention proposes to replace a pitot tube with a device in which at least two fluid streams are taken off from the flow. These streams are brought into contact with each other so as to be mutually slowed down in a region (11) where the pressure is measured. This measured pressure is representative of the total pressure (Pt).

Abstract: 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.

Abstract: A vane designed to get oriented in the axis of an ambient airflow. The vane allows for the intake of differential pressure presenting the aerodynamic incidence &agr; of the vane. According to the invention, the differential pressure intake is balanced when the vane is oriented naturally in the axis of the airflow.

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.

Abstract: 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.

Abstract: A device for monitoring the flow of a current in a load powered by a DC voltage source and a method for the implementation of the device. The device includes, series-connected with the load, a first device to detect the presence of an alternating current and a second device to interrupt the current flowing in the first device while keeping the current substantially direct in the load. Advantageously, the second device includes at least one first electronic switch series-connected with the load and with the first device, the first electronic switch being controlled so as to set up the alternating current in the first device. A method of implementing the device cyclically opens and closes the electronic switch while making the second device operable or inoperable, also cyclically, to keep the current substantially direct in the load and let the current flowing in the load pass through the second device only periodically.

Abstract: The subject of the invention is a probe for an aircraft, making it possible in particular to measure the total temperature of the air flow surrounding the aircraft. The probe comprises a moving vane (1) intended to orientate itself in the axis (8) of an air flow surrounding the moving vane (1) and, fixed to the moving vane, means (10, 13, 16) for measuring the total temperature of the air flow.

Abstract: The invention pertains to a multifunction probe for aircraft intended for determining in particular the static pressure (Ps) and the total pressure (Pt) of an airflow located in the vicinity of the aircraft and the angle of incidence (&agr;) of the aircraft with respect to the flow. The probe comprises a movable blade (1) intended to orient itself along the axis of the airflow, the movable blade (1) comprising at least one static pressure tap orifice (13, 14) located on one side of the blade (1) and a pressure tap intended for measuring the angle of incidence (&agr;) of the blade (1) with respect to the flow. The probe furthermore comprises pressure measurement means associated with each pressure tap and means for calculating the total pressure (Pt) of the flow as a function of the measurements carried out by the various measurement means of the probe.

Abstract: A fixed multifunction probe, e.g., for aircraft and configured to measure air flow parameters near an airplane. The probe includes a body closed by a rounded cap, at least three pressure taps situated at specified positions of the body, a pressure measurement mechanism for measuring at least as many pressures as pressure taps, and a calculation device for calculating the air flow parameters.

Abstract: An optical device on board an aircraft for detecting icing conditions including an optical beam emitter to create at least one illuminated external volume of measurement through which there circulates a flow of air charged with water particles; a collector optical system for the collection of at least a part of the light beam back-scattered by the water particles (the external volume of measurement being located on the optical axis of said collector optical system); a photodetector for detecting back-scattered optical beams; a signal processor for processing the signal delivered by the photodetector to compute the severity of the icing conditions; an information provider for providing information on the calculated severity of the icing conditions. Advantageously, the optical means for the differentiation of device includes a differentiation for differentiating between liquid water particles and solid water particles, based on analysis of the polarization.