Abstract: The invention relates to a continuous detonation wave engine and aircraft provided with such an engine. The continuous detonation wave engine (1) operates with a detonation mixture of fuel and oxidant and includes, in particular, a detonation chamber (3) comprising an injection base (10), the length of which is defined along an open line (17), such as to form a detonation chamber (3) having an elongate form in a transverse plane, as well as an injection system (4) arranged such as to inject the fuel/oxidant mixture into the detonation chamber (3) at at least one segment of the injection base (10).

Abstract: The invention relates to a device (1) comprising: means (3) for receiving an image of a pre-determined area, containing the heights of points therein; means (8) for determining the directions of flow; means (9) for finding source points that can be used to create a binary image; means (11) for filtering the binary image; processing means (13) that can be used to obtain a set of lines formed by source points; means (15) for creating, from said set of lines, a set of sequences of segments illustrating the ridge lines of the area; and means (19) for transmitting said set of sequences of segments to user means (22).

Abstract: The invention relates to a flying device (1), in particular an air missile, which is of the inertial navigation type, which is rotatable and includes a pitch rate gyroscope (2), wherein said device also comprises automatic control means (8) for rotating same about the longitudinal axis (3) thereof, regularly alternating the direction of rotation, so as to cancel the effect of the scale factor of the pitch rate gyroscope (2), in addition to correcting ordinary drifts.

Abstract: According to the invention, the projectile (1) is provided with a strapdown homing device (2), said device having a lock-on phase during which the latter attempts to detect a target (C), and including an viewing direction (3), said viewing direction (3) being fixed with respect to the projectile (1) and extending along the longitudinal axis (4) of the latter, said projectile (1) further comprising control means (8) for automatically controlling said projectile (1) so as to cause the longitudinal axis (4) thereof, in flight and during the lock-on phase of the homing device (2), to trace a circle, the radius of which increases in time, until the target (C) is detected.