Abstract: A flight control indicator for an aircraft has a set of information sources, a computation unit which determines, on the basis of information emanating from the set of information sources, an item of information regarding actual thrust of an engine of the aircraft, and a display device which is a head-up display device and which presents, on a display screen, an indication of the item of information regarding actual thrust. The item of information regarding actual thrust is associated with a thrust scale and both are presented superimposed on the environment prevailing in front of the aircraft.

Abstract: The device (1) comprises means (9, 11) for transposing a time constraint to entry to a constrained section of a flight trajectory having to be followed by the aircraft.

Abstract: The device (1) comprises a first means (2) knowing the profile of the terrain at least that which is located at the front of the aircraft, a second means (3) for determining an avoidance trajectory, a third means (4) which is connected to the first and second means (2, 3) and used to verify if there is a terrain collision risk for the aircraft, a fourth means (7) for emitting an alarm signal in the event of detection of a collision risk by the third means (4), at least one aircraft performance data base (Bi) relating to an avoidance maneuvering gradient which can be flown by the aircraft according to particular flight parameters, and a fifth means (9) for determining the effective values of the particular parameters during the flight of the aircraft, wherein the third means (3) is formed in such a way that it is possible to determine the avoidance trajectory according to the information received from the data base (Bi) and the fifth means (9).

Abstract: A flight control indicator for an aircraft includes a central unit that determines a change of vertical or lateral trajectory. A display, which may present a first indicator of a next vertical change and a second indicator of a next lateral change, presents the one of the first and second indicators indicating the change of trajectory which is closest from the current position of the aircraft.

Abstract: The system (1) comprises means (6) for determining a limit angle of climb corresponding to a climb angle of the aircraft for flying over the ground along an avoidance path and means (8) for displaying a characteristic sign representing said limit angle of climb on a display screen (9).

Abstract: Device for constructing and securing a low altitude flight path intended to be followed by an aircraft. The device comprises a first processing unit which has a DAL C requirement level and which determines a low altitude flight path, making use of data coming from a first database qualified according to a DPAL2 standard, and a second processing unit which has a DAL A requirement level and which checks the flight path determined by said first processing unit, using data coming from a second database qualified according to a DPAL1 standard.

Abstract: A method and device for calculating a target speed of an aircraft may include a flight point time determining section that determines when the aircraft actually gets to a particular flight point, taking account of the aircraft's current target speed. A time interval calculating section calculates a time interval between the predetermined time at which the aircraft must get to the particular flight point and the determined actual time. A speed updating section updates the target speed and applies the updated target speed to the aircraft if the calculated time interval is greater than a duration of comparison, which is variable and depends on the actual distance so as to decrease when the actual distance decreases.

Abstract: The flight control indicator may include a set of information sources, a computation unit connected to said set of information sources, and a head-up display device. The computation unit determines, on the basis of information emanating from the set of information sources, at least one maximum total slope of the aircraft. The maximum total slope corresponds to the maximum thrust and is obtained on the basis of the measurement of the current performance of the aircraft, extrapolated to the condition of maximum slope and in anticipation of an engine fault. The head-up display device presents, on a display screen, at least one indicator which indicates the maximum total slope and which is presented superimposed on the environment existing in front of the aircraft.

Abstract: The flight control indicator (1) comprises a set (2) of information sources, a computation unit (3) connected to said set (2) of information sources and determining, on the basis of information emanating from said set (2) of information sources, at least one maximum total slope of the aircraft, which corresponds to the maximum thrust and is obtained on the basis of the measurement of the current performance of the aircraft, extrapolated to the condition of maximum slope and anticipating an engine fault, and a head-up display device (5) which presents, on a display screen (7), at least one means of indication (8) which indicates said maximum total slope and which is presented superimposed on the environment existing in front of the aircraft.

Abstract: The flight control indicator (1) comprises a central unit (3) able to determine any change of trajectory corresponding to a vertical change which represents a change of vertical segment or a lateral change which represents a change of lateral branch, and means of display (5) which are able to present, on a viewing screen (7), a first means of indication indicating a next vertical change and a second means of indication indicating a next lateral change, and which are formed in such a way as to present at least one of said first and second means of indication, namely the one indicating the change of trajectory which is closest, from the current position of the aircraft.

Abstract: Flight control indicator for an aircraft. The flight control indicator (1) comprises a set (2) of information sources, a computation unit (3) which determines, on the basis of information emanating from said set (2) of information sources, at least one item of information regarding actual thrust of at least one engine of the aircraft, and a display device (5) which is a head-up display device and which presents, on a display screen (7), at least one means of indication which indicates said item of information regarding actual thrust, which is associated with a thrust scale, and which is presented, with this thrust scale, superimposed on the environment prevailing in front of the aircraft.

Abstract: Method and device for ensuring the safety of a low-altitude flight of an aircraft. A device (1) for ensuring the safety of a low-altitude flight comprises information sources (5) able to determine current flight conditions, a monitoring unit (6) for realizing, with the aid of said current flight conditions, a function for global and autonomous monitoring of said low-altitude flight of the aircraft, making it possible to preserve the integrity of said aircraft during said flight, and means (13) for presenting the results of the monitoring function realized by said monitoring unit (6) to an operator.

Abstract: The device (1) comprises means (2) for determining the actual time at which the aircraft gets to a particular flight point, taking account of a current target speed, means (3) for calculating a time interval defined between the predetermined time at which the aircraft must get to the particular flight point and said actual time, means (5) for comparing this time interval with a duration of comparison, means (7) for updating the target speed, which is applied to the aircraft, if this time interval is greater than the duration of comparison, means (10) for determining the actual distance between the current position of the aircraft and the particular flight point, and means (11) for determining said duration of comparison which is variable and which depends on the actual distance in such a way as to decrease when the actual distance decreases.