Abstract: The present invention provides a method and device for automatically determining a capture trajectory of a flight trajectory for an aircraft, as well as a procedure and system for automatic guidance of an aircraft. The flight trajectory includes at least one lateral trajectory furnished at least with a plurality of rectilinear stretches. The capture trajectory is a lateral capture trajectory that allows the aircraft to join up laterally with a particular rectilinear stretch of the lateral trajectory of the flight trajectory. The capture trajectory is defined to allow a minimum capture duration. An automatic navigation mode is engaged as soon as requested by the pilot to, if necessary, capture and follow the planned flight trajectory.

Abstract: A method and device for determines a safe altitude for an aircraft. The device includes a unit that determines a clear zone corresponding to a lateral area dependent on the flight of the aircraft. A unit determines the highest altitude of the ground that is located under this clear zone. A unit determines a safe altitude, by calculating the sum of the aformentioned highest altitude and a guard height.

Abstract: The device (1) for guiding an aircraft at least over an intermediate trajectory between a first flight trajectory for a low-altitude flight and a second flight trajectory which starts at an initial point, and from which trajectory a parachute drop is carried out, comprises means (9) for determining a point of transition which lies on the first flight trajectory which represents the start of the intermediate trajectory, and which corresponds to the point where the aircraft must exit the first flight trajectory so as to reach the initial point under predetermined flight conditions, and means (13A, 13B) which use the point of transition to aid the guidance of the aircraft between the first and second flight trajectories.

Abstract: A flight plan revision device may include a first component that determines an auxiliary flight plan corresponding to a lateral revision of the current flight plan, at least over a low altitude flight section. A second component automatically determines at least one decision point indicating the last position of the aircraft along the current flight plan where the auxiliary flight plan can still be activated, so as to allow the aircraft to overfly the terrain in complete safety by following the auxiliary flight plan under the same flight conditions as those envisaged for the current flight plan. A third component automatically presents at least the decision point to a pilot of the aircraft. And a fourth actuatable component allows a pilot to activate the auxiliary flight plan, so as to carry out the lateral revision of the current flight plan.

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 device (1) for guiding an aircraft at least over an intermediate trajectory between a first flight trajectory for a low-altitude flight and a second flight trajectory which starts at an initial point, and from which trajectory a parachute drop is carried out, comprises means (9) for determining a point of transition which lies on the first flight trajectory which represents the start of the intermediate trajectory, and which corresponds to the point where the aircraft must exit the first flight trajectory so as to reach the initial point under predetermined flight conditions, and means (13A, 13B) which use the point of transition to aid the guidance of the aircraft between the first and second flight trajectories.

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: Method and device for ensuring the safety of a low-altitude flight of an aircraft. The device (1) comprises a recording means (8) corresponding to an operation critical instrument for recording, during a low-altitude flight, one part at least of the lateral trajectory of the flight trajectory situated ahead of the current position of the aircraft, a monitoring means (11) for monitoring, during a low-altitude flight, the availability at least of said lateral trajectory, and a guidance system (3) for taking the aircraft up to a safe altitude, taking into account said part of the trajectory recorded by said recording means (8), when said monitoring means (11) has detected a loss of said lateral trajectory.

Abstract: Method and device for automatic guidance of an aircraft, for a flight at least in part at low altitude. The device (1) for automatic guidance comprises means (7) for determining at least one LLF trajectory section corresponding to a low altitude trajectory part, which makes it possible to follow the terrain overflown, which is able to be flown by the aircraft and which takes account of predictions of mass and of speed, as well as of predictions of climb and descent performance of the aircraft, and means (2) for automatically guiding the aircraft in such a way that, successively, it captures, follows and leaves said LLF trajectory section.

Abstract: A method and device for ensuring the safety of a low-altitude flight of an aircraft is disclosed, wherein low-altitude flight is flight along a flight trajectory at low altitude, for example 500 feet, that allows an aircraft to follow as closely as possible the terrain being over-flown. To avoid collision with the terrain, a safety corridor, devoid of any obstacle, is determined which is delimited on either side of the lateral trajectory, and whose width depends on a global uncertainty, and the aircraft is guided along the flight trajectory, avoiding any exit of the aircraft from the safety corridor.

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: Method and device for guiding an aircraft. The device (1) for guiding an aircraft at least over an intermediate trajectory between a first flight trajectory for a low-altitude flight and a second flight trajectory which starts at an initial point, and from which trajectory a tactical landing is carried out, comprises means (9) for determining a point of transition which lies on the first flight trajectory which represents the start of the intermediate trajectory, and which corresponds to the point where the aircraft must exit the first flight trajectory so as to reach the initial point under predetermined flight conditions, and the second means (13A, 13B) which use the point of transition to aid the guidance of the aircraft between the first and second flight trajectories.

Abstract: The device (1) comprises means (6) for determining an auxiliary flight plan corresponding to a lateral revision of the current flight plan, at least over a low altitude flight section, means (3) for automatically determining at least one decision point which indicates the last position of the aircraft along the current flight plan, where the auxiliary flight plan can still be activated, so as to allow the aircraft to overfly the terrain in complete safety by following the auxiliary flight plan, under the same flight conditions as those envisaged for the current flight plan, means (9) for automatically presenting at least the decision point to a pilot of the aircraft, and means actuatable (13), allowing a pilot to activate the auxiliary flight plan, so as to carry out the lateral revision of the current flight plan.

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: Method and device for determining a safe altitude for an aircraft. The device (1) includes means (2) for determining a clear zone corresponding to a lateral area dependent on the flight of the aircraft, means for determining the highest altitude of the ground that is located under this clear zone, and means (8) for determining a safe altitude, by calculating the sum of said highest altitude and a guard height.

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.