Abstract: A method and device for aiding the navigation of an aircraft flying at low altitude as described. The device (1) includes positioning means (2) generating the current position of the aircraft, and calculation means (4) for detecting when the budgets allocated to a position error of the aircraft are exceeded by protection ranges.

Abstract: The device (1) comprises a first system (3) which comprises means (14) for calculating the vector difference between a position generated by this first system (3) and a realignment position received from a second system (4), for one and the same date-stamping, and means (16) for adding this difference to any new position of the aircraft, generated by said first system (3), so as to obtain each time a realigned position.

Abstract: Disclosed is a method and device, which provide an enhanced ability to monitor the navigation of an aircraft during a phase of flight in which the aircraft is close to the ground in which the aircraft uses positional information supplied by a satellite positioning system for the navigation. A display screen is used to display a first characteristic sign representing a selected setpoint value for a height parameter of the aircraft. The display screen also displays a second characteristic sign representing a current auxiliary value expressed in the form of an achievable height parameter. An alert is emitted when the second characteristic sign is determined to be within a predetermined height value of the first characteristic sign, and the alert is shown in visual format on the display screen. An alarm is also emitted following a predetermined time after the alert is emitted, if the setpoint value is not replaced by a new setpoint value.

Abstract: The invention relates to a method and device for determining a reliable position of an aircraft. The device (1) includes means (3, 10) for determining different aircraft position values and means (8, 16, 18) for deducing a reliable position therefrom, using coherence tests and a consolidation method.

Abstract: A method for monitoring the integrity of an aircraft position computed on board including on-board means for monitoring the aircraft position that are able to detect common-mode failures. Dissimilar computing channels of the aircraft position are utilized, the dissimilar channels being on-board in the aircraft. Each aircraft position primary computing channel is supplemented by a dissimilar computing channel, which allows the coherence of the primary aircraft position, the position computed by the primary computing channels, to be verified. Mechanisms for verifying the reliability of the results from dissimilar computing channels are implemented to limit a loss of performance from the utilization of dissimilar computing channels, which are less performing than primary computing channels.

Abstract: A method and device for aiding the navigation of an aircraft flying at low altitude as described. The device (1) includes positioning means (2) generating the current position of the aircraft, and calculation means (4) for detecting when the budgets allocated to a position error of the aircraft are exceeded by protection ranges.

Abstract: A device and method calculate a global error relating to a position indication of an aircraft and compare the global error with a threshold value, which depends on flight constraints.

Abstract: An aircraft standby display device includes a set of data sources, a data processing unit, and a display. The display presents altitude control indicators representing speed, altitude, attitude, and a heading scale that includes a characteristic symbol indicating a next route point of an aircraft flight plan. The heading scale is independent of the altitude control indicators. The display also presents a quantitative value that: (1) indicates the remaining distance of flight of the aircraft to reach the next route point and (2) is associated with the characteristic symbol.

Abstract: The invention relates to a method and device for determining a reliable position of an aircraft. The device (1) includes means (3, 10) for determining different aircraft position values and means (8, 16, 18) for deducing a reliable position therefrom, using coherence tests and a consolidation method.

Abstract: The device (1) comprises a screen (13) which simultaneously displays a sign representing a selected setpoint value relating to a height parameter which is used during the phase of flight, and a sign illustrating a corresponding value which is representative of an estimated positional error.

Abstract: The invention concerns a device comprising a set of data sources, a data processing unit, and a display which presents on a display unit (8) altitude control indicators (9, 10, 11) representing at least speed, altitude and altitude data of the aircraft and a heading scale (12) including a characteristic symbol (13) indicating at least one next route point of the aircraft flight plan, said heading scale (12) being independent of said altitude control indicators (9, 10, 11), as well as a quantitative value (14) which indicates the remaining distance of flight of the aircraft to reach said next route point and which is associated with said characteristic symbol (13).

Abstract: The subject of the invention is a method of aiding the piloting of an aircraft (3), which is intended to aid the piloting of the aircraft during an autonomous approach to a landing runway (P) for the purpose of landing, said aircraft comprising at least one locating means (10, 12), wherein: a) an estimated instant of arrival of the aircraft on the runway is determined; b) a prediction of the performance of said locating means of the aircraft at least at this instant of arrival is determined; and c) on the basis of said performance of the locating means and of characteristics of said approach, at least one minimum decision height (Hmin) corresponding to this instant of arrival is determined, above which the aircraft is protected from the risks of collision with the environment when it is guided automatically onto an approach axis (A) corresponding to said approach. The invention also relates to a device for implementing this method.

Abstract: The device (1) comprises a first system (3) which comprises means (14) for calculating the vector difference between a position generated by this first system (3) and a realignment position received from a second system (4), for one and the same date-stamping, and means (16) for adding this difference to any new position of the aircraft, generated by said first system (3), so as to obtain each time a realigned position.

Abstract: The device (1) comprises means (8, 9, 10) for calculating a global error relating to a position indication of the aircraft, means (13) for comparing this global error with a threshold value which depends on the flight constraints, and alarm means (15).

Abstract: The subject of the invention is a method of aiding the piloting of an aircraft (3), which is intended to aid the piloting of the aircraft during an autonomous approach to a landing runway (P) for the purpose of landing, said aircraft comprising at least one locating means (10, 12), wherein: a) an estimated instant of arrival of the aircraft on the runway is determined; b) a prediction of the performance of said locating means of the aircraft at least at this instant of arrival is determined; and c) on the basis of said performance of the locating means and of characteristics of said approach, at least one minimum decision height (Hmin) corresponding to this instant of arrival is determined, above which the aircraft is protected from the risks of collision with the environment when it is guided automatically onto an approach axis (A) corresponding to said approach. The invention also relates to a device for implementing this method.

Abstract: A method for monitoring the integrity of an aircraft position computed on board including on-board means for monitoring the aircraft position that are able to detect common-mode failures. Dissimilar computing channels of the aircraft position are utilized, the dissimilar channels being on-board in the aircraft. Each aircraft position primary computing channel is supplemented by a dissimilar computing channel, which allows the coherence of the primary aircraft position, the position computed by the primary computing channels, to be verified. Mechanisms for verifying the reliability of the results from dissimilar computing channels are implemented to limit a loss of performance from the utilization of dissimilar computing channels, which are less performing than primary computing channels.