Abstract: A sound capture device is disclosed, including plural microphone capsules, distributed over portion P of sphere S circumscribed between two or three planes perpendicular to each other, the three planes intersecting at a point corresponding to the center of the sphere S, and the two planes intersecting at a straight line passing through the center of the sphere S, and the sphere portion P being such that P=n S/8, with n=1,2; and a processing unit connected to the capsules to receive the signals captured by the capsules. The processing unit is arranged to matrix the signals in an ambisonic representation which retains only the ambisonic components associated with spherical harmonics that are symmetrical in relation to at least two of the aforementioned planes, and process a matrix thus obtained to identify a sound source surrounding the sphere portion and interpret a sound signal from the source.

Abstract: A sound capture device is disclosed, including plural microphone capsules, distributed over portion P of sphere S circumscribed between two or three planes perpendicular to each other, the three planes intersecting at a point corresponding to the center of the sphere S, and the two planes intersecting at a straight line passing through the center of the sphere S, and the sphere portion P being such that P=n S/8, with n=1,2; and a processing unit connected to the capsules to receive the signals captured by the capsules. The processing unit is arranged to matrix the signals in an ambisonic representation which retains only the ambisonic components associated with spherical harmonics that are symmetrical in relation to at least two of the aforementioned planes, and process a matrix thus obtained to identify a sound source surrounding the sphere portion and interpret a sound signal from the source.

Abstract: A device for constructing a synthetic image of an aircraft environment may include information sources having information relating to the aircraft and to its environment. An information processor constructs a synthetic image of the environment of the aircraft on the basis of information emanating from the information sources. A display presents, on at least one part of a display screen, a synthetic image, which is constructed with the aid of a conical projection onto a plane of projection that is orthogonal to a line of aim that forms angles of lateral separation and angles of vertical separation with the course of the aircraft.

Abstract: The device (1) comprises information sources (2) comprising information relating to the aircraft and to its environment, information processing means (3) able to construct a synthetic image of the environment of the aircraft on the basis of information emanating from the information sources (2) and display means (5) able to present, on at least one part of a display screen (7), a synthetic image. This image is constructed with the aid of a conical projection onto a plane of projection which is orthogonal to a line of aim which forms angles of lateral separation and angles of vertical separation with the course of the aircraft.

Abstract: A process and a device for detecting inconsistencies in the operation of a system with multiple phases of operation, controlled by at least one operator. The current phase of operation of the system is determined. For the determined phase, reference is made to at least one theoretical model representative of at least one feature of the system. The effective values of the variables used in the theoretical model is detected. The detected effective values are compared to theoretical data defined in the theoretical model. Any incompatibility detected during these comparisons is signaled together with the nature of this incompatibility. The detection system can be used with the pilotage of aircraft.

Abstract: The present invention relates to a device for supervising the propulsion system of an aircraft, including a set of sensors (C1, C2, Cn) delivering information regarding the propulsion system. According to the invention, the device moreover includes:a set of peripheral computers (M1, M2, Mp) each implementing a mathematical model representing a sub-system of propulsion system; anda main computer (CAL), which is linked to the set of sensors (C1, C2, Cn) and to the set of peripheral computers (M1, M2, Mp), which checks the intercompatibility of the information delivered by the sensors (C1, C2, Cn) and the compatibility between the information delivered and the results provided by the peripheral computers (M1, M2, Mp).

Abstract: A process and device for detecting the current phase of operation of a system with multiple phases of operation. According to the invention, the operation is partitioned into a set of phases (I to X) from which is chosen a reference phase (I). The set of possible switches to the other phases is determined for each phase. And, a set of parameters is defined for each of the switches, the set of parameters being characteristic of the switch. The sets of parameters are continuously detected. The chain of switches actually involved is determined on the basis of the reference phase (I) with the aid of variations in the parameters, and the current phase of operation is deduced from the chain of switches. Although the invention is applicable to numerous systems, one such system to which it is applicable is the operation of a transport airplane.