Abstract: Methods for graphically managing a pitch scale displayed in an on-board viewing system for an aircraft, the viewing system comprises a graphics computer carrying out the graphical management of the symbols and a viewing screen. The symbolic representation displayed on the viewing screen includes an angular pitch scale, a symbol, referred to as the aircraft icon, that is representative of the attitude of the aircraft and a symbol, referred to as the speed vector that is representative of the direction of the speed of the aircraft. The angular distance separating the “bars” of the scale varies so that the symbols representative of the attitude of the aircraft and of the speed vector remain constantly close to one of the two bars of the scale, even in the event of a strong crosswind. The shape of the bars is either constant or variable.

Abstract: Methods for graphically managing a pitch scale displayed in an on-board viewing system for an aircraft, the viewing system comprises a graphics computer carrying out the graphical management of the symbols and a viewing screen. The symbolic representation displayed on the viewing screen includes an angular pitch scale, a symbol, referred to as the aircraft icon, that is representative of the attitude of the aircraft and a symbol, referred to as the speed vector that is representative of the direction of the speed of the aircraft. The angular distance separating the “bars” of the scale varies so that the symbols representative of the attitude of the aircraft and of the speed vector remain constantly close to one of the two bars of the scale, even in the event of a strong crosswind. The shape of the bars is either constant or variable.

Abstract: The general field of the invention is that of methods of displaying an “attitude director indicator” in a head viewing system for aircraft comprising: a head support bearing a viewing device; a detection of posture; sensors for detecting the various parameters defining the attitude of the said aircraft; means for computing and graphically generating the said attitude, the set of parameters displayed being termed the “attitude director indicator”; In the method according to the invention, when the head support is oriented in a determined direction making, with the horizon line and/or with the “speed vector”, an angle greater than a first value, and/or when at least one of the attitude parameters of the aircraft becomes greater than a second value, the attitude director indicator is displayed locally in a reference frame tied to the head support and in the field of the viewing device.