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: The cylinder may be an aircraft landing gear axle. The items may be pick-ups the sense axle deformation. A ring (30) for supporting the pick-ups is made of highly resilient material. It is initially of such a size that its cylinder-engaging surface overlaps the cylindrical surface it is to engage. The ring is then deformed by urging at least two points (34 to 37) around its circumference to increase the degree of overlap. While maintaining the deforming force on the ring, its cylinder-engaging surface (31) is machined so that there is no longer any overlap, and still maintaining the force, the ring is engaged with the cylinder. The force is then removed. The said points move resiliently away from the cylinder, but intermediate points are consequently resiliently urged into contact with the cylinder. The contact is smooth and progressive, thus avoiding the kind of stress concentrations that could reduce cylinder life by fatigue, etc.

Abstract: The device comprises central anchor means firmly anchored to a lug (3), e.g. the smooth middle portion of a rod (10) capable of being thermally fitted in a smooth round hole (7) through the lug (3) together with first and second independent fixing means (26, 26') disposed on either side of said central anchor means, e.g. two threaded end portions (27, 27') fitted with nuts (28, 28', 29, 29').

Abstract: An accelerometer is provided using at least one sensor with flat pendular structure formed by micro-machining a fine monocrystal wafer and comprising a flat mobile mass suspended from the rest of the structure by means of two thin parallel strips situated on each side of the mass. The mass comprises at least one mobile capacitor plate disposed between two fixed capacitor plates provided on the fixed part of the structure. The mobile plate is brought to a voltage V.sub.O, whereas the fixed plates are respectively brought to voltages V.sub.1 and V.sub.2 which are capable of generating an electrostatic return force on the mobile mass.

Abstract: The device comprises at least three non-colinear studs (A,B,C) interposed between each lug face (5) against which a sensor or sensor mounting part is pressed. Stud (A) may be closer to a beam (1) than the other studs (b) and (C), thereby maximizing the relative displacement of the sensor parts for a given shear force on the beam (1).

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: A device for detecting the angular position of the rotor of an electric rry machine with electronic switching, comprising more particularly a disk mounted coaxially on the shaft of said rotor and comprising a radial face on which permanent magnets are fixed of alternately reversed polarity producing a magnetic field, Hall effect proximity cells disposed in the vicinity of said radial face of the disk and carried by a structure mounted for rotation on the body of said rotary machine coaxially with said axis, and adapted for detecting the axial component of the magnetic field, means allowing said structure to be locked against rotation on said body.

Abstract: The invention concerns a process for the rapid detection of a wind gradie t.This process utilizes the relationship existing between the aerodynamic slope .gamma.a, the total slope .gamma..sub.T and the anemometric speed V, relation being able to be in the form ##EQU1## in which s is the Laplace operator, A is a value which is substantially constant or zero, in the case of a normal flight without disturbances, and which increases in the case of a wind gradient, wind forward becoming wind behind, the Vsel is an assigned value. This value A is mixed with a value representative of the capacity of the aircraft to overcome a wind gradient, so as to obtain a composite signal compared to a value of reference.The invention can be utilized at the moment of the phase of approach of an aircraft.

Abstract: This invention concerns an improved variometer which is used in aircraft which operates on a circuit that calculates the instantaneous speed hx.degree. of the aircraft and the potential vertical speed of the aircraft h.sub.T .degree.. A luminous display is also provided to display the values so calculated to alert the pilot of the aircraft.The instantaneous vertical speed hx.degree. is obtained by means of a circuit solving the equation: ##EQU1## in which j.sub.z.sbsb. is the component of the acceleration on the vertical axis of the aircraft, g is the acceleration of gravity, .phi. is the angle of roll of the airplane, s is the Laplace operator, .tau..sub.1 and .tau..sub.2 are constants of time and h.degree..sub.A is a signal of vertical speed.

Abstract: A variometer for an aerodyne. The variometer has at least one dial conventionally graduated to represent speed, a needle indicating on said graduation the instantaneous vertical speed. The variometer also has an indicator which is representative of the potential vertical speed, and can move around the dial so that the position of the indicator with respect to the needle indicates instantaneously the acceleration on the trajectory of the aircraft.

Abstract: A process and system for the rapid detection of a wind gradient or change r an aircraft. Such a system provides for, on the one hand, the rapid detection of important or significant wind gradients or changes which can occur during the final phase of approach preceding the landing of the aircraft and, on the other hand, to inform the pilot or the automatic flight control system of the existence of this wind gradient sufficiently early to permit necessary corrective action to be taken.

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 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: The present invention relates to a method of and apparatus for indicating e geographical position of a piloted vehicle equipped with a computer, the method comprising the steps of using a geographical map or a portion of map, approximately orientated, without regard to its method of folding and its dimensions; identifying and transmitting to the computer at any desired moment, basic information such as reference of alignment on a meridian of the map-references of magnetic declination and scale of said map, co-ordinates of at least one radio-navigation transmitter chosen on the map, co-ordinates of at least one objective to be reached on the map, co-ordinates of at least one possible intermediate point on the route; indicating on said map at any instant under the control of the computer which also receives the variable radio-navigation information from the transmitter selected, the geographical position of the vehicle, the above identification and indication steps being effected by the use of a single organiza