A long-distance blast banger (10) comprising a cartridge (20) loaded with a blast banger made up from plastic material. The blast banger encompasses a sound of explosives cup (21) and a delay cup (22). The sound explosives cup (21) is loaded with a sound explosives formulation having components including perchloryl potassium, magnesium powder and aluminium powder. A sufficient sound value is acquired through appropriate compacting of the sound explosive cup, and therefrom realizes uniform shattering of the cup into small fragments that are insufficient to cause injury. Furthermore, at least two helical grooves (11 ) extending from a bottom to a top of the cartridge (10) are defined on an inner wall of the cartridge, and ear attachments (23) are configured on a base of an outer wall of the blast banger so as to correspond with the helical grooves, thereby engendering a spinning stability effect during flight time of the blast banger, reducing wind resistance, and thus increasing flight range.

Bei einer Vorrichtung zum Auswurf von drallstabilisierten Flugkörpern (1) aus einem übergeordneten Raumflugkörper, insbesondere aus einer Raumstation, bei der der auszustoßende Flugkörper (1) über ein Drehantriebselement (6) in eine kombinierte Rotations- und Translationsbewegung versetzt wird und bei der Mittel zum Haltern und zum Führen des auszustoßenden Flugkörpers in einem Auswurfbehälter (2) vorgesehen sind, ist der auszustoßende Flugkörper (1) mittels Kugeln (5) im Auswurfbehälter (2) gelagert, die in wenigstens einer spiralförmig in Ausstoßrichtung ansteigenden Rillenbahn (3,4) zwischen der Außenwand des Flugkörpers und der Innenwand des Auswurfbehälters angeordnet sind.

Le dispositif utilisable sur une munition d'attaque de véhicule à moteur thermique comprend un détecteur à faible champ angulaire ayant un capteur (24) sensible dans la plage allant de 3 à 5 µm et un capteur (34) sensible à l'infrarouge proche ; des moyens pour échantillonner la sortie des capteurs à une cadence telle qu'il y ait recouvrement des zones correspondant aux échantillons successifs; des moyens de mémorisation d'un nombre prédéterminé d'échantillons successifs ; des moyens de calcul faisant la différence entre les échan­tillons de la réponse du premier capteur et la moyenne de n échantillons précédents et provoquant, en cas de dépassement d'un seuil, la recherche d'une fin de transition par comparaison entre échantillons successifs mémorisés et la comparaison entre les échantillons du signal fourni par le second capteur pour la zone de transition avec des valeurs minimale et maximale déterminées.

Arrangement for a terminally guided projectile (4) provided with a target seeking arrangement (19) and path correction arrangement (21). The arrangement includes a preferably fin-stabilized, slowly-rotating artillery shell (1) which is provided with an elongated cavity (2) into which the terminally guided projectile, which comprises a fin-stabilized mortar projectile (4), is introduced. The mortar projectile (4) is arranged so that it is ejected rearwards from the artillery shell (1) by means of a separation charge (13) in the vicinity of a selected target, after which the mortar projectile (4) is terminally guided towards the target in a manner known per se.

An inertial measurement system for a spinning projectile comprising: first (roll), second and third gyros with axes arranged such that they define a three dimensional coordinate system; at least a first linear accelerometer; a controller, arranged to: compute a current projectile attitude comprising a roll angle, a pitch angle and a yaw angle; compute a current velocity vector from the accelerometer; combine a magnitude of said velocity vector with an expected direction for said vector to form a pseudo-velocity vector; provide the velocity vector and the pseudo-velocity vector to a Kalman filter that outputs a roll gyro scale factor error calculated as a function of the difference between the velocity vector and the pseudo-velocity vector; and apply the roll gyro scale factor error from the Kalman filter as a correction to the output of the roll gyro. This system does not rely on an Euler rate filter, instead using an error observation process that is more direct and hence more sensitive. By avoiding the Euler rate filter, this approach avoids the tuning requirements associated with that filter and allows the problem to be handled wholly within a Kalman filter architecture. This process exploits the fact that rolling projectiles generally follow a predictable trajectory when not subject to controlled guidance.

A bearing system for a spin-stabilized projectile (P) including bearing configurations (20,36) that permit selective relative rotation between a spindle (18) and a body portion (14) and which facilitate automatic centering of the spindle (18). Each bearing configuration (20,36) includes a conical bearing surface rotatable with respect to a corresponding conical body surface. One bearing configuration (20) is in a forward portion of the body portion and selectively engages a first body surface upon the projectile experiencing set-back forces to direct forces away from bearing elements, and another bearing configuration (36) is in a rearward portion of the body portion and engages a second body surface upon the projectile experiencing set-forward forces to direct forces away from the bearing elements. Biasing elements work in cooperation with the bearing configurations (20,36) to automatically maintain the spindle (18) centered with respect to the body portion (14) during pre-launch and in-flight and to re-center the spindle after set-back, balloting and/or set-forward phases.