Abstract: An accelerometric sensor according to the invention comprises a plane pendulum structure presenting a test body suspended to a fixed part by at least two parallel blades, flexible in the plane of the said test body, in order to be able to move in translation in the said plane according to a sensitive axis perpendicular to the said blades. This test body comprises a moving support element linked to the said flexible blades and a test mass suspended to the said support element by at least a third and fourth blade parallel to the preceding ones and flexible in the plane of the said test body. The invention enables to reduce substantially the sensitivity to the transverse acceleration of the detection structure when it is submitted to an acceleration directed according its sensitive axis S.

Abstract: A gyroscopic artificial horizon comprises a gyroscope suspended in a gimbal ount which has an inner frame and an outer frame pivoted, one within the other, about two orthogonal axes. It also comprises a device for sensing the spatial position of the axis of the gyroscope and for displaying this position in the form of an artificial horizon. To simplify the mechanical structure and to increase the reliability of the gyroscopic artificial horizon, the device for sensing and displaying the spatial position of the gyroscope axis comprises a luminous display screen rotationally coupled to the outer frame of the gimbal mount. It further comprise a sensor for sensing the angular position of the inner frame relative to the outer frame and a processor device adapted to display this angular position on the screen in the form of an artificial horizon.

Abstract: The device according to the invention comprises a member (8) for selecting nd changing a data item displayed on a video screen, a switch associated with the member for selecting and modifying a data item, and means providing a connection between the remote control device and the computer. The device is characterized in that the member for selecting and modifying a data item is a touch-sensitive pad (8) movably mounted on a support (6), and in that the switch is disposed to be actuated by displacing the touch-sensitive pad (8).

Abstract: The invention provides a display device with dissociable structure, making t possible for a user to observe a synthetic light image superimposed in his natural field of vision, said device being formed as two dissociable modules, namely: an image generating module having, inside a case, at least one part of the image generating members and a removable optical module including a support element to which is fixed a curved mixer type optical mount including, in a dihedral configuration, a flat semitransparent mirror and a curved semitransparent mirror.

Abstract: A method and device are provided for guiding an aerodyne on the runway, picularly during the taxiing phase preceding take off, the device including an inertial unit adapted for delivering signals representative of the North speed, of the East speed, of the azimuth and of the ground speed of the aerodyne. From these signals, a computer elaborates a parameter defining the axis of the runway, during an apprenticeship step during which the aerodyne, guided on site by the pilot, taxies along the axis of the runway, and stores this parameter at the end of the step. The computer then delivers to the means piloting the aerodyne a synthetic runway aberration signal between the axis of the runway thus stored and the position of the aerodyne delivered by the inertial unit.

Abstract: A lighting sensor is provided including a sleeve made from a translucent erial having a bottom intended to be exposed to the light whose illumination it is desired to measure, an optoelectronic component positioned inside the sleeve with its sensitive face disposed in line with said bottom and means for securing said component and said sleeve together.The invention overcomes in a simple way the problems due to the non linearity of the signal delivered by the optoelectronic component to the saturation of this component and to the narrowness of its aperture angle.

Abstract: A gamma correction method and device are provided for multichrome cathode y tubes, including, for each of the n-1 electron guns of the tube, a correction circuit adapted for raising the cathode modulation of this gun to a power .gamma.ref/.gamma..sub.i in which the term .gamma..sub.ref is the gamma exponent of the nth gun which is taken as reference and the term .gamma..sub.i is the gamma exponent of the gun considered. With this device the chromaticity of the colors displayed on the screen are conserved throughout the whole contrast dynamics of the tube.

Abstract: A method and device for displaying symbols by means of a liquid crystal matrix. The device comprises an automation driven by a clock which feeds cyclically to the control circuit of a liquid crystal matrix the bits representative of the elementary images contained in a random access memory. The memory has a capacity greater than k (n+m) bits, k being the multiplexing coefficient and n and m being respectively the number of lines and columns of the liquid crystal matrix. The memory is refreshed by a central computer during the interval of emission of the bits.

Abstract: An accelerometer sensor comprising a flat pendular structure having a fixed part and a flat test body suspended from the fixed part by two parallel blades flexible in the plane of said test body, so as to be able to move in translation along a sensitive axis. Said test body extends at least partially into the space between said two flexible blades.

Abstract: Precision incremental-output integrator of the type comprising: an operational amplifier mounted as analog summing integrator, which sums currents I.sub.1 and I.sub.2 at the integrator input, characterized by the fact that current I.sub.2 is obtained by the discharge of a capacitor C.sub.2 and that the symmetrical reference voltage generator (Vr-), (Vr+) is replaced by a simple voltage generator (Vr) and incremental-output servosensors resulting from utilization of the said precision incremental-output integrator in which the measured magnitude, originally electrical, becomes a physical magnitude, evidenced by an electromechanical force generator by the fact that the analog amplifier of the precision incremental-output integrator (terminals A-S, FIG. 2) is replaced by the force generator of the servosensor (FIG. 3), the return current of which is current I.sub.2 discharged from capacitor C.sub.2.

Abstract: Procedure for attenuating linearity errors in a ring type laser rate gyro 21 that uses N mirrors 28, 29, 30 arranged in such a way that the laser beams travel along two identical polygons in opposite directions, wherein at least one of the said mirrors that define the trajectory of the two laser beams is made to oscillate angularly with respect to the body of the rate gyro about an axis perpendicular to the plane defined by these two laser beams; the rotational axis of each of the oscillating mirrors preferably being as close as possible to the perpendicular to the mirror being considered that passes through the point of contact of the laser beams with the mirror in question.

Abstract: Self monitored process control device comprising two complementary circuits (4,5) allowing control signals to be replaced when erroneous, by safety limit values computed by separate circuits (10,11,17,18), a circuit (21) sending a warning signal when signals at the output of the two complementary circuits (4,5) are not identical, a safety circuit (23) permitting selection of the healthy signal from the two complementary circuits (4,5) upon failure of one of the complementary circuits (4,5) and a monitoring circuit (26,28,29) allowing a failure of the safety circuit (23) to be indicated. The invention applies especially to aircraft flight control.

Abstract: The present invention deals with a flight control process and device for an aircraft approach and landing. More in particular, the invention in use simulates ILS by using an infrared radiation source at the desired landing site. The invention comprises the steps of determining an axis defined by the infrared radiation source, forming a predetermined guide slope line with respect to the horizontal and oriented according to a determined approach magnetic heading, recording the aircraft position with respect to the source, determining the angular deviations in azimuth and in elevation of the sighting axis with respect to the said glide slope line, and operating the aircraft flight controls to return said deviations to zero.

Abstract: A method for controlling the decelerated approach of an aerodyne on radioignment generally referred to as "glide," in particular for the purpose of reducing its fuel consumption and reducing the noise, mainly in the final stage of the approach, by approaching the glide at high speed, initiating the descent according to the glide angle, also at high speed then beginning a decelerated phase in order to reach a predetermined speed V sel+k, k being generally equal to 10 knots, on reaching a predetermined altitude, h.sub.F, and then passing progessively from the speed V sel+k to the speed V sel. From the time when the aerodyne reaches the axis of the glide path, a course is determined in two sections, as regards the variables of speed and altitude, for reaching the point situated at the altitude h.sub.

Abstract: A system for the display and indication of information on the windshield of an airplane to the aircraft's pilot. The information to be displayed is converted into optical images which are transferred by a plurality of bundles of optical fibers to a projection system positioned beneath the windshield. The projection system projects the images onto the windshield such that they are reflected therefrom in the axis of the pilot's field of vision.

Abstract: A device for the display and indication of information of various types and coming from various sources, in particular for an aircraft or the like. The system comprises a converter for transforming the information into at least one video signal representative of an image related to the information, transfer means for remotely transmitting the video signal, means for forming an image from the video signal emanating from the transfer means, and a projection apparatus such as a lens for projecting the image onto a screen.

Abstract: A power jack, particularly adapted to equip the control system of an aeroe, including stress-responsive components, for example, a helical coil spring, in which indicator instruments record any locking between the relatively movable elements of the jack, such as a rotatable shaft and an encompassing sleeve to thereby disengage a disengaging element and allow the control functions to bypass the jack.

Abstract: In a gyro horizon type of equipment, roll corrections are fed to the aircraft symbol which is a normally fixed display element and pitch correction is introduced on a movable display element or drum with modification of the position of the display elements of the instrument gyro as a function of an interconnection of the instrument gyro with a gyromaster reference through comparators connected to each of the roll and pitch systems.

Abstract: A flying method using total power, in particular for the take-off and overshoot of an aircraft, is disclosed in which the aerodynamic gradient .gamma.a is governed by reference to a desired gradient .gamma.d which is the total gradient .gamma.t modulated by the difference between the aircraft speed V and a reference speed V.sub.2. An error signal .delta. representative of the difference between the aerodynamic gradient .gamma.a and the desired gradient .gamma.d is displayed. The display of the desired gradient .gamma.d may be by means of the pitching tendency bar of an artificial horizon for example.

Abstract: A flying method using total .[.power.]. .Iadd.energy.Iaddend., in particular for the take-off and overshoot of an aircraft, is disclosed in which the aerodynamic .[.gradient.]. .Iadd.flight path angle .Iaddend..gamma.a is governed by reference to a desired .[.gradient.]. .Iadd.flight path angle .Iaddend..gamma.d which is the .[.total gradient.]. .Iadd.potential flight path .Iaddend..gamma.t modulated by the difference between the aircraft speed V and a reference speed V.sub.2. An error signal .delta. representative of the difference between the aerodynamic .[.gradient.]. .Iadd.flight path angle .Iaddend..gamma.a and the desired .[.gradient.]. .Iadd.flight path angle .Iaddend..gamma.d is displayed. The display of the desired .[.gradient.]. .Iadd.flight path angle .Iaddend..gamma.d may be by means of the .[.pitching tendency bar of the artificial horizon.]. .Iadd.pitch command bar of an attitude director indicator .Iaddend.for example.