Abstract: Missile balancing assemblies include two balancing rings configured for mounting on a missile, each balancing ring having a ballast. Each balancing ring is configured to be rotated and rotationally fixed, and may include materials having different densities at different locations. Each balancing ring may further include an angular graduation.

Abstract: A device is configured for deflecting a stream of particles for a projectile guided by a link wire, the projectile having a fuselage and an engine capable of producing a propulsive jet containing the stream of particles. The device includes a device support including an inner surface configured to attach the device support to the fuselage of the projectile, and a deflector strip assuming at least an unfolded position in which the deflector strip forms an angle with the device support in order to deflect the stream of particles.

Abstract: A device is configured for deflecting a stream of particles for a projectile guided by a link wire, the projectile having a fuselage and an engine capable of producing a propulsive jet containing the stream of particles. The device includes a device support including an inner surface configured to attach the device support to the fuselage of the projectile, and a deflector strip assuming at least an unfolded position in which the deflector strip forms an angle with the device support in order to deflect the stream of particles.

Abstract: Missile balancing assemblies include two balancing rings configured for mounting on a missile, each balancing ring having a ballast. Each balancing ring is configured to be rotated and rotationally fixed, and may include materials having different densities at different locations. Each balancing ring may further include an angular graduation.

Abstract: A method for the inertial navigation of a projectile equipped with a mediocre-quality inertial init that is fired from a carrier equipped with a precision inertial unit includes, before firing the projectile, the biases of the accelerometers and of the gyrometers of the inertial unit of the projectile are determined using the inertial unit of the carrier. During the inertial navigation of the projectile, the measurements of the accelermeters and of the gyrometers output by the inertial unit of the projectile are corrected by the biases determined before launching.

Abstract: According to the invention, before firing said projectile (M) from the carrier (L), the mean biases of the accelerometers and of the gyrometers of the inertial unit (IM) of said craft are determined using the inertial unit (IL) of said carrier (L) and, during the inertial navigation of said craft (M), the measurements of the accelerometers and of the gyrometers output by said inertial unit (IM) of said craft (M) are corrected by said mean biases determined before launching.

Abstract: The invention relates to a guidance system comprising estimation means able to estimate, in the course of flight, the attitude and the aerodynamic speed of a projectile, as well as the variations in the speed of the wind, on the basis of guidance orders formulated by guidance means of the guidance system, of a reference trajectory and of measurements obtained by measurement means of the system, using a model of the dynamic behavior of the projectile and a model of the dynamics of the wind.

Abstract: The invention relates to a guidance system comprising estimation means able to estimate, in the course of flight, the attitude and the aerodynamic speed of a projectile, as well as the variations in the speed of the wind, on the basis of guidance orders formulated by guidance means of the guidance system, of a reference trajectory and of measurements obtained by measurement means of the system, using a model of the dynamic behaviour of the projectile and a model of the dynamics of the wind.