Abstract: A height indicator for an aircraft, the height indicator being provided with a controller controlling a display means to display a height scale and a pointer. The height scale is able to move in relation to the pointer along an axis on the display means, the height scale being a piecewise linear scale comprising several graduated sections, each graduated section having its own linear scale, each graduated section having a scale factor different from a scale factor of another graduated section, each scale factor representing the quotient between a distance on the graduated section along axis and a corresponding actual height.

Abstract: A method of assisting piloting, which method comprises the steps of designating a landing point and determining a sighting axis. A single three-dimensional main symbol providing a conformal position of the landing point is displayed on the screen so long as it is present in a field of view along the sighting axis, the three-dimensional main symbol extending in elevation upwards from the ground from a bottom zone positioned on the ground up to a top zone positioned at a top height relative to the ground. At least while the aircraft is situated at a distance from the landing point that is less than a first threshold distance, at least one two-dimensional main symbol covering a target zone is displayed.

Abstract: A method of assisting piloting, which method comprises the steps of designating a landing point and determining a sighting axis. A single three-dimensional main symbol providing a conformal position of the landing point is displayed on the screen so long as it is present in a field of view along the sighting axis, the three-dimensional main symbol extending in elevation upwards from the ground from a bottom zone positioned on the ground up to a top zone positioned at a top height relative to the ground. At least while the aircraft is situated at a distance from the landing point that is less than a first threshold distance, at least one two-dimensional main symbol covering a target zone is displayed.

Abstract: A method of controlling subsystems of an aircraft. During a preparation step, at least one global order is stored in a database, each global order including an eligibility condition, and at least one global order including an activation condition, each global order specifying a command sequence comprising at least two actions to be implemented one after another or in parallel by two different members. During an initialization step, an onboard computer determines whether a global order is selected automatically or by a pilot. During an activation step, an onboard computer determines, where appropriate, whether the selected global order is feasible. During an implementation step, and providing the selected global order is feasible, the onboard computer performs the actions specified by the selected global order.

Abstract: An aircraft having a cockpit, said cockpit including a canopy provided with transparent surfaces fastened to bars, a central console, and two seats arranged transversely on either side of the central console. The aircraft includes at least one support (31, 33) connected to the central console and at least one display unit for displaying multiple indications for assisting piloting, each display unit being carried by at least one support (31, 32, 33, 34) interposed between a bar and a theoretical position of the eye of a person sitting on one of said two seats, each support (31, 32, 33, 34) visually masking a bar at least in part, in order to optimize the visibility to the outside of the cockpit as made available to that person, the theoretical position being defined by the manufacturer.

Abstract: A method of controlling subsystems of an aircraft. During a preparation step, at least one global order is stored in a database, each global order including an eligibility condition, and at least one global order including an activation condition, each global order specifying a command sequence comprising at least two actions to be implemented one after another or in parallel by two different members. During an initialization step, an onboard computer determines whether a global order is selected automatically or by a pilot. During an activation step, an onboard computer determines, where appropriate, whether the selected global order is feasible. During an implementation step, and providing the selected global order is feasible, the onboard computer performs the actions specified by the selected global order.

Abstract: A method of simultaneously transforming at least two input voice signals xi of a communications system (30), each input voice signal xi being received at a specific reception frequency Fi and corresponding to the voice of a remote party communicating with a user of the communications system (30). During an initialization stage, a transformation Ti is allocated to at least one reception frequency Fi of the input voice signals xi, and during a utilization stage, transformations Ti are applied simultaneously to the input voice signals xi as a function of the reception frequencies Fi, modifying at least one characteristic of each of the input voice signals xi. Thus, the voice of each remote party in communication with the user of the communications system (30) is modified artificially by a transformation Ti, thereby making it easier for the user to perceive and discriminate between simultaneous voices from the remote parties.

Abstract: A method of simultaneously transforming at least two input voice signals xi of a communications system (30), each input voice signal xi being received at a specific reception frequency Fi and corresponding to the voice of a remote party communicating with a user of the communications system (30). During an initialization stage, a transformation Ti is allocated to at least one reception frequency Fi of the input voice signals xi, and during a utilization stage, transformations Ti are applied simultaneously to the input voice signals xi as a function of the reception frequencies Fi, modifying at least one characteristic of each of the input voice signals xi. Thus, the voice of each remote party in communication with the user of the communications system (30) is modified artificially by a transformation Ti, thereby making it easier for the user to perceive and discriminate between simultaneous voices from the remote parties.

Abstract: A method of simultaneously transforming at least two input voice signals xi of a communications system (30), each input voice signal xi being received at a specific reception frequency Fi and corresponding to the voice of a remote party communicating with a user of the communications system (30). During an initialization stage, a transformation Ti is allocated to at least one reception frequency Fi of the input voice signals xi, and during a utilization stage, transformations Ti are applied simultaneously to the input voice signals xi as a function of the reception frequencies Fi, modifying at least one characteristic of each of the input voice signals xi. Thus, the voice of each remote party in communication with the user of the communications system (30) is modified artificially by a transformation Ti, thereby making it easier for the user to perceive and discriminate between simultaneous voices from the remote parties.

Abstract: A method of adapting a man-machine interface (20) of an aircraft (50) depending on the functional level of a pilot, the method comprising a plurality of successive steps. Firstly, before starting a mission, the characteristics of said mission and the characteristics and the physiological state of said pilot are determined. Thereafter, during said mission, the state of the mission and the current state of said aircraft together with a current behavior of said pilot are determined and a current functional level of said pilot is estimated. Thereafter, said current functional level of said pilot is compared with reference functional levels, and said man-machine interface (20) is then adapted in order to assist said pilot automatically and in optimum manner in making the pilot aware of the situation, in the pilot's decision-making, or in the actions taken by the pilot depending on the pilot's stress state or work load state.

Abstract: An aircraft having a cockpit, said cockpit including a canopy provided with transparent surfaces fastened to bars, a central console, and two seats arranged transversely on either side of the central console. The aircraft includes at least one support (31, 33) connected to the central console and at least one display unit for displaying multiple indications for assisting piloting, each display unit being carried by at least one support (31, 32, 33, 34) interposed between a bar and a theoretical position of the eye of a person sitting on one of said two seats, each support (31, 32, 33, 34) visually masking a bar at least in part, in order to optimize the visibility to the outside of the cockpit as made available to that person, the theoretical position being defined by the manufacturer.

Abstract: A method of simultaneously transforming at least two input voice signals xi of a communications system (30), each input voice signal xi being received at a specific reception frequency Fi and corresponding to the voice of a remote party communicating with a user of the communications system (30). During an initialization stage, a transformation Ti is allocated to at least one reception frequency Fi of the input voice signals xi, and during a utilization stage, transformations Ti are applied simultaneously to the input voice signals xi as a function of the reception frequencies Fi, modifying at least one characteristic of each of the input voice signals xi. Thus, the voice of each remote party in communication with the user of the communications system (30) is modified artificially by a transformation Ti, thereby making it easier for the user to perceive and discriminate between simultaneous voices from the remote parties.

Abstract: A method of adapting a man-machine interface (20) of an aircraft (50) depending on the functional level of a pilot, the method comprising a plurality of successive steps. Firstly, before starting a mission, the characteristics of said mission and the characteristics and the physiological state of said pilot are determined. Thereafter, during said mission, the state of the mission and the current state of said aircraft together with a current behavior of said pilot are determined and a current functional level of said pilot is estimated. Thereafter, said current functional level of said pilot is compared with reference functional levels, and said man-machine interface (20) is then adapted in order to assist said pilot automatically and in optimum manner in making the pilot aware of the situation, in the pilot's decision-making, or in the actions taken by the pilot depending on the pilot's stress state or work load state.

Abstract: Device assisting with interception by an aircraft of a flight path segment located in a horizontal plane and a system of assistance with interception and follow-up of such a segment. The device includes means of determining a ground speed vector and means of displaying to present, on a screen, a means of indication (10) of the ground speed corresponding to a first rectilinear section (10) in the horizontal plane, connected to a symbol (7) whose angular orientation corresponds to the direction of said ground speed vector and whose length is variable, a means of interception approach indication (12) corresponding to a second recipient section (3) in the horizontal plane of variable width and provided for as an extension of first rectilinear section (11) and a means of indication (14) of the interception turn corresponding to at least one circle arc (15) in the horizontal plane, provided to extend second rectilinear section (13).

Abstract: Device assisting with interception by an aircraft of a flight path segment located in a horizontal plane and a system of assistance with interception and follow-up of such a segment. The device includes means of determining a ground speed vector and means of displaying to present, on a screen, a means of indication (10) of the ground speed corresponding to a first rectilinear section (11) in the horizontal plane, connected to a symbol (7) whose angular orientation corresponds to the direction of said ground speed vector and whose length is variable, a means of interception approach indication (12) corresponding to a second rectilinear section (13) in the horizontal plane of variable width and provided for as an extension of first rectilinear section (11) and a means of indication (14) of the interception turn corresponding to at least one circular arc (15) in the horizontal plane, provided to extend second rectilinear section (13).

Abstract: Device assisting with interception by an aircraft of a flight path segment located in a horizontal plane and a system of assistance with interception and follow-up of such a segment. The device includes means of determining a ground speed vector and means of displaying to present, on a screen, a means of indication (10) of the ground speed corresponding to a first rectilinear section (10) in the horizontal plane, connected to a symbol (7) whose angular orientation corresponds to the direction of said ground speed vector and whose length is variable, a means of interception approach indication (12) corresponding to a second recipient section (3) in the horizontal plane of variable width and provided for as an extension of first rectilinear section (11) and a means of indication (14) of the interception turn corresponding to at least one circle arc (15) in the horizontal plane, provided to extend second rectilinear section (13).

Abstract: Device assisting with interception by an aircraft of a flight path segment located in a horizontal plane and a system of assistance with interception and follow-up of such a segment. The device includes means of determining a ground speed vector and means of displaying to present, on a screen, a means of indication (10) of the ground speed corresponding to a first rectilinear section (11) in the horizontal plane, connected to a symbol (7) whose angular orientation corresponds to the direction of said ground speed vector and whose length is variable, a means of interception approach indication (12) corresponding to a second rectilinear section (13) in the horizontal plane of variable width and provided for as an extension of first rectilinear section (11) and a means of indication (14) of the interception turn corresponding to at least one circular arc (15) in the horizontal plane, provided to extend second rectilinear section (13).

Abstract: The indicator (1A) according to the invention comprises means (13) for determining first and second target values respectively of a variable and of its derivative with respect to time, and display means (5, 6, 7) which depict on a display screen (7) a means of indication (14) of the first target value, which is arranged in such a way as to indicate this first target value on a graduated scale (8), and a means of indication (16B) of the second target value which is associated at least with an indicator element (11) indicating said derivative so that, when the latter points toward said means of indication (16B), said variable of the aircraft becomes equal to and remains equal to said first target value and said derivative is equal to said second target value.

Abstract: Indicator of a variable for an aircraft. The indicator (1A) according to the invention comprises means (13) for determining first and second target values respectively of a variable and of its derivative with respect to time, and display means (5, 6, 7) which depict on a display screen (7) a means of indication (14) of the first target value, which is arranged in such a way as to indicate this first target value on a graduated scale (8), and a means of indication (16B) of the second target value which is associated at least with an indicator element (11) indicating said derivative so that, when the latter points toward said means of indication (16B), said variable of the aircraft becomes equal to and remains equal to said first target value and said derivative is equal to said second target value.