초록 ▼

The invention relates to a process for the visual display of the attitude of an aircraft to assist piloting or flying in space. On the basis of the values of cardan or gimbal angles (yqf1) on board the aircraft, in particular the following informations: a cruciform reticule (7,8,9), a piloting or fl

The invention relates to a process for the visual display of the attitude of an aircraft to assist piloting or flying in space. On the basis of the values of cardan or gimbal angles (yqf1) on board the aircraft, in particular the following informations: a cruciform reticule (7,8,9), a piloting or flying circle B, the value of the roll angle (f10), a net formed by portions of meridians (M) and parallels (P) of the celestial cavity, a symbol (V1) representing the direction pointed by the velocity vector of the aircraft, a short term prediction vector (12) for the aircraft attitude, as well as numerical values (19,21,23) for the roll, pitch and yaw velocities. Application is to the piloting of an aircraft in space.

대표청구항 ▼

Process for the display of the attitude of an aircraft or spacecraft for aiding piloting or flying in space, which comprises the steps of: defining a spherical celestial canopy (C) centered on the center of gravity (G) of the aircraft (A), having a polar axis oriented towards the celestial north (N)

Process for the display of the attitude of an aircraft or spacecraft for aiding piloting or flying in space, which comprises the steps of: defining a spherical celestial canopy (C) centered on the center of gravity (G) of the aircraft (A), having a polar axis oriented towards the celestial north (N) and an equatorial plane (E) perpendicular to said polar axis and passing through a vernal reference marking point (ggA, YA, ZA) of the aircraft with three orthogonal axes, having for its origin the center of gravity (G) of the aircraft, a first axis (XA) directed along a longitudinal axis of the aircraft, a second axis (ZA) located in a plane of symmetry passing through the longitudinal axis of the aircraft and a third axis (YA) perpendicular to the first and second axes of the specific reference mark; defining the attitude of the aircraft by calculating the cardan angles, (roll (fqyfqyA) of a net formed from portions of meridians and parallels (M,P) of the celestial canopy projected onto said plane within a piloting or flying circle (B), displayed on a screen (1) and centered on the first axis (XA) of the specific reference mark; displaying a cruciform reticule (7,8,9) with two perpendicular segments (7,8) intersecting the flying circle, intersecting in the center (O) of the circle (B) and corresponding respectively to the second and third axes (ZA, YA) of the specific reference mark, the position of the center (O) of the circle respectively representing the yaw and pitch angles referenced in longitude and latitude, respectively with respect to a meridian portion (M) and a parallel portion (P) of the net; and displaying the value of the roll angle (fA) of the specific reference mark.