Sextant Avionique

Badin-crouzet

Thales

Thomson-csf Sextant

Badin Crouzet Aerodrom De Toussus-le-noble

Henri Leblond

Jacques Mandle

Joel Choisnet

Jean-Philippe Pineau

Philippe Guichard

Lionel Collot

Christian Gohin

Yves Jaulain

Gerard Beigbeder

Michel Bruneau

Jean-Ren&eacute; Chevalier

Edouard Escobar

Philippe Herzog

Gregoire Dodel

Louis Cabot

A probe for measuring the total pressure of a flow and a method for implementing the probe is provided. The probe is intended to be fitted in an aircraft. The probe comprises a Pitot tube and means for reheating the probe assembly. The probe also comprises means for measuring a local temperature of regions of the Pitot tube likely to accumulate particles conveyed by the flow independently of the means for determining the average temperature of the probe. If the temperature delivered by the means for measuring a local temperature of regions of the Pitot tube likely to accumulate particles conveyed by the flow is less than the first reference temperature, then an additional reheating of regions of the Pitot tube likely to accumulate particles conveyed by the flow is triggered.

Probe for measuring the total pressure of a flow and method for implementing the probe

A device is provided for checking a flow pressure measurement probe as well as a probe comprising the device. The probe includes an internal volume and at least one orifice for communication with the outside of the volume. The device includes: an acoustic transmitter and an acoustic receiver that are intended to be connected to the internal volume so that the transmitter transmits an acoustic signal that propagates in the internal volume and so that the receiver picks up an observed acoustic signal; and, means for comparing the observed signal with a reference signal. The device may be a stand-alone device or may be integrated into the probe.

Device for checking a flow pressure measurement probe, and probe comprising the device

The present invention relates to back-up instruments for aiding the piloting of an aircraft, which instruments are intended to provide, with high security of operation, indications relating to the pressure altitude, the conventional speed and the attitude (angles of roll and of pitch) of the aircraft, this being for the purpose of serving both as reference for the control of the proper operation of the main systems of on-board and back-up instruments in the event of a fault with the main system or systems of on-board instruments. It relates more particularly to combined back-up instruments including an electronic portion endowing them with a degree of calculational power. It consists in providing, in these combined back-up instruments which operate exclusively on the basis of measurements of total pressure and of static pressure and inertial measurements originating from their own sensors, a correction of the static pressure measurement error due to the aerodynamic angle of incidence of the aircraft as computed solely on the basis of the information already at the disposal of these back-up instruments, doing so in order to improve the accuracy of the indication of pressure altitude without thereby increasing the cost or reducing the safety of operation of the combined back-up instruments.

Combined standby instruments for aircraft

A method and apparatus for determining the severity of icing conditions for an aircraft in flight. A mobile probe projecting from a surface of the aircraft is heated to a predetermined range of temperatures, and the total power required for the heating is measured. The measured total power is divided into a basic power corresponding to the thermal exchange in dry air having the same flow parameters as those measured and a complimentary power corresponding to the evaporating of drops of water contained in the actual air. A parameter representative of the speed at which the thickness of ice increases at the surface of the aircraft is computed from the complementary power.

Procedure and devices to determine the severity of icing conditions for

The present invention relates to an incidence probe, in particular for an aircraft, comprising at least two pressure inlets. To this end, it comprises a least one flowmeter (1) and a pneumatic restriction (4) arranged in series between two pressure inlets.

Incidence probe with multiple pressure inlets

The probe comprises a wind vane (1) mounted for rotation on the aircraft in order to orient itself in the direction of the flow and provided with a detector (15) for detection of differential pressure representative of the aerodynamic angle of incidence of the wind vane, and a device for determining the orientation of the wind vane with respect to the aircraft. The probe comprises a control loop (14) adapted to cancel out the aerodynamic angle of incidence of the wind vane and controlled by the detector (15). The probe supplies the true angle of incidence of the aircraft directly.

Aircraft probe for measuring aerodynamic parameters of amient flow

The gyrometer comprises a cavity filled with a fluid in the form of a body of revolution having an axis coinciding with the axis of a rotation to be measured. An excitation transducer and a measuring transducer are disposed on the wall of the cavity in a same cross section and offset at an angle of 90.degree.. The excitation transducer excites a first acoustic resonance mode of the cavity and the measuring transducer measures a second mode of resonance induced by Coriolis forces when the cavity is subjected to the rotation to be measured. Such a gyrometer, less sensitive to mechanical embodiment inaccuracies, is assembled on, a moving body, for example, in order to measure its speed(s) of rotation.

Acoustic gyrometer

The invention relates to a gyrometer, without material rotor, of the type using the Coriolis forces on the particles of a fluid contained in a resonant cavity. It comprises, in addition to the conventional excitation and detection unit, a unit for effecting servo-control in phase of the longitudinal acoustic oscillation in the cavity and employs a weak coupling mode between exciter and cavity. The gyrometer according to the invention overcomes the variations in length of the cavity and the fluctuations in the speed of propagation of the oscillations in the fluid as a function of the temperature.

Disclosed is an apparatus for measuring the aerodynamic parameters of an airflow around an aircraft. A streamlined body is rotatably mounted in the airflow such that it aligns itself freely with the flow. Total and static pressure pick-off apertures are provided in the body. The measurement of the true angle of incidence is obtained from two distinct measurements. A first measurement mechanically provides the orientation .alpha.m of the streamlined body relative to the aircraft and the other provides the aerodynamic pressure orientation .alpha.a of the same streamlined body relative to the airflow. The true angle of incidence .alpha. is then determined by summing .alpha.m and .alpha.a.

Multi-function pressure probe for aircraft

A device is provided comprising a circuit using the properties of a resonating cavity sensor whose resonance frequency is modified by the electric capacity variations due to the mechanical deformation of a wall under the effect of the pressure to be measured. It uses a single coaxial cable for connecting the sensor to the user circuit and the sensor, through the coaxial cable, is placed in the leg of an impedance bridge providing the value of the standing wave rate characteristic of the difference between the tuning frequency of the cavity and the frequency of an oscillator controlled by this rate.

Growing community of inventors

Versailles, France

Henri Leblond