Abstract: A method for reducing the low-frequency component of the measurement noise of a photosensitive imager and applications of same. The invention involves intentionally creating a non-straight scanning movement of the observed scene on the photosensitive matrix of the imager.

Abstract: The invention relates to a method and system for the terminal-phase guiding of an interceptor missile towards a mobile aerial target. According to the invention, measurements delivered by the terminal guiding sensor are used to deduce a set of components of the interceptor missile-target dynamic, by means of Bayesian estimation, and the future of this dynamic is digitally integrated on line.

Abstract: A method for reducing the low-frequency component of the measurement noise of a photosensitive imager and applications of same. The invention involves intentionally creating a non-straight scanning movement of the observed scene on the photosensitive matrix of the imager.

Abstract: The invention relates to a method and system for the terminal-phase guiding of an interceptor missile towards a mobile aerial target. According to the invention, measurements delivered by the terminal guiding sensor are used to deduce a set of components of the interceptor missile-target dynamic, by means of Bayesian estimation, and the future of this dynamic is digitally integrated on line.

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.

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: 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.