Abstract: The invention relates to systems for aiding the piloting of aircraft, mainly for take-off and landing under poor conditions of visibility.In order to benefit from the contribution of head-up displays, which exhibit symbols for the artificial horizon line, aircraft longitudinal attitude and ground speed vector, without using an IRS inertial unit to supply the heading and attitude information, it is proposed to use a non-inertial AHRS unit associated with a compass, and periodically to correct the information which it supplies, in order to exhibit the attitude symbols with the aid of the corrected information rather than the raw information from the AHRS unit. The correction is given by two GPS receivers (GPS1, GPS2) associated with antennas (A1, A2) on the top of the aircraft, an interferometric measurement of radiofrequency carrier phase being made to determine a direction vector of the aircraft.

Abstract: Disclosed is an improvement to the guidance, during the approach and landing stages, of aircraft operating in the categories 2 or 3A of the certification system used by recognized civilian organizations such as the DGAC, the FAA or the JAA, this improvement being designed to render the aircraft capable of working in the immediately lower category, namely the 3A or 3B category, at lower cost. The improvement consists of the addition of a head-up display visor HUD to the attitude heading reference system AHRS and to the air data computer ADC and of the displaying, on the head-up display visor HUD, of the flight path vector whose angular coordinates are drawn from information on east-west and north-south horizontal ground speed delivered by a global positioning receiver GPS according to the avionics standard furthermore used for the localization and navigation of the aircraft.

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 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 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.