Abstract: A device for assisting the piloting of a vehicle by instruments. Various indications are displayed on an aircraft head-up view finder including a horizontal line graduated in terms of heading, a perpendicular line graduated in terms of atitude, an aircraft symbol representing the direction of the longitudinal axis of the aircraft above the horizontal line and a velocity vector symbol representing the tracking slope followed by the aircraft with respect to the ground. These are determined with respect to the tracking and atitude scales. The guidance window whose position is references with respect to the same axis is also displayed. The pilot must control the aircraft as to bring the velocity vector into the guidance window and keep it there. The window is placed on the screen at a position which is computed by the computer and which corresponds to the direction of a point of the desired path of the aircraft, this point being at a predetermined distance ahead of the aircraft.

Abstract: A device for assisting the extinguishing of fires by water-bombing aircraft. The device includes at least one sensor for sensing the source of the fire, a device for pinpointing the position of the aircraft, a geographical database and a calculator for calculating the route of the aircraft as a function of its position and the position of the source as pinpointed in the database.

Abstract: This device relates to assistance in the piloting of an aircraft or helicopter in conditions of poor visibility, at the landing stage, during the final approach before touchdown. In case of poor visibility, the landing operations are facilitated by ILS radioelectrical installations that enable an automatic approach to the runway threshold. All that remains to be done is to perform a flare-out for touchdown which has to be done in a certain zone at the start of the runway. It happens, in the event of poor visibility, that this touchdown zone is difficult to assess. This causes risks of overshooting. The disclosed device is aimed at putting out an alarm in the event of overshooting of the nominal touchdown zone.

Abstract: A device for the substitution of an artificial image shown to an aircraft pilot by the corresponding real image includes a device for the simulation of human vision; criteria for the exploitation of the simulated image; compare to a device for comparing to compare the simulated image with the criteria of exploitation; a device for attenuating the artificial image, the artificial image being attenuated when the simulated image meets a given number of exploitation criteria.

Abstract: This optoelectronic device is designed to provide assistance in the piloting of an aircraft under conditions of poor visibility, at the final approach stage, during taxiing and at take-off from a runway equipped with an ILS. The device consists of a collimator displaying a reticule symbolizing a runway centerline that is shown to the pilot during flight as well as on the ground, without any break between the in-flight final approach stage and the ground stage of taxiing on the runway. The device takes account of the pilot's off-centered position in the aircraft cockpit.

Abstract: A device to improve the field of vision in aircraft that lack sufficient transparent surface area. The device includes at least one collimator connected to an imaging sensor of the space outside the aircraft. The collimator projects an image in the pilot's field of vision. The image covers both the transparent window surface and the instrument panel of the cockpit. The image coincides with the real image in the field of direct vision produced by the transparent surface. A further image may also be viewed by the pilot through a periscope arrangement.

Abstract: The disclosure relates to systems for piloting aircraft. Equations of the movements of the aircraft are used for computing, in a computer, of the first and second derivatives parameters V.sub.p, .PHI..sub.v, .sigma..sub.a, .beta..sub.v, .alpha., .PHI..sub.v, .sigma..sub.a, .beta..sub.v, of the parameters V.sub.p, .PHI..sub.v, .sigma..sub.a, .beta..sub.v, .alpha. of the movement of the aircraft, and the values thus computed are compared with those computed by means of the values of said parameters V.sub.p, .PHI..sub.v, .sigma..sub.a, .beta..sub.v, .alpha. at the instants t, (t+dt) and (t+2dt). An alarm signal (circuit 23) is generated if equality is not verified to a given precision.

Abstract: A piloting aid system for displaying symbols representative of determined characteristics of the flight of an aircraft and representative of its environment is disclosed. The symbols are displayed on the screen of a display unit which displays a symbol representing the aircraft near a predetermined point on the display screen and a rectangular window for guiding the flight path of the aircraft. The sides of the guidance window are parallel to mutually perpendicular axes provided on the screen. The abscissa and ordinate of the predetermined point are respectively proportional to the drift and to the slope relative to the ground of the aircraft flight path.