Abstract: A rocket engine having guide vanes in the engine nozzle the guide vanes (2) being mounted for turning at or near the rearmost ends of fixed vanes (1) being parallel to the axis of the nozzle and protruding into the combustion chamber of the engine. The foremost ends (4) of the guide vanes (2) may be shielded by the rearmost ends of the fixed vanes (1), and the guide vanes (2) may be individually turnable.

Abstract: A pyrotechnic charge structure, in particular for use as propellant in a rocket motor, is disclosed. The charge structure has a predetermined longitudinal extension and cross sectional area adapted to the intended purpose. The pyrotechnic charge structure (1; 2; 3; 4) is in cross sectional view in cellular form aimed at having similar wall thickness for all the cells of the charge structure. The wall (6) of the cells comprises the pyrotechnic charge, i.e. the propellant, and each cavity of the cells occupies air or oxygen-rich gas.

Abstract: A release mechanism between a projectile and a rocket motor in a missile. The projectile releases from the rocket motor during flight of the missile when the rocket motor burns out and aerodynamic retardation commences. The front end of the rocket motor comprises a forward closure, a lock retainer received and movable within the forward closure, at least one lock, at least one spring that biases the lock against the lock retainer in a direction opposite the to the direction of motion of the missile. The rear end of the projectile has a central boss surrounded by the forward closure of the rocket motor, wherein the boss comprises recesses or a circumferential groove in which the at least one lock lies and keeps the forward closure and the boss axially together.

Abstract: A retarding and locking mechanism for use between two mutually translatable bodies. A first body can be induced into motion and guided into a second body and, after a predetermined movement of the first body, the first body is subject to retardation and interlocked to the second body, such that the first and second bodies together form a unitary, integrated body. The first body has a radially outwardly directed shoulder and the second body has a radially inwardly directed shoulder corresponding to the radially outwardly directed shoulder of the first body. A compressible element is provided between the shoulders of the first and second bodies.

Abstract: A propelling device for a projectile that is lying in a standby position within a rocket motor in a missile. The projectile is translated with respect to the rocket motor by means of a pyrotechnic charge before the rocket motor is ignited. The projectile is lying within a translation tube centrally located in the rocket motor. The projectile comprises a power piston in the rear end thereof. The power piston encloses a pyrotechnic power charge and a pyrotechnic squib. The translation tube is sealable closed behind the power piston and forms a closed expansion chamber for the pyrotechnic charges which, by ignition, generate gas pressure that activates the power piston and thus propels the projectile forward within the translation tube.

Abstract: A translation and locking mechanism for a projectile that is lying in a standby position within a rocket motor in a missile, wherein the projectile is translated with respect to the rocket motor by means of a pyrotechnic charge before the rocket motor is ignited. The rear end of the projectile includes at least one radially spring biased lock and the front part of the rocket motor includes an internal circumferential groove that the at least one lock snaps into when the at least one lock is translated to the groove.

Abstract: A tracer sleeve having a self-destruction charge, for use with a projectile. The tracer sleeve is screwed into a threaded bore in a rearward end of the projectile. The self-destruction charge is situated in a recess in a forward bottom of the tracer sleeve. A closed bushing bottom in the projectile separates the bore from a more forwardly situated charge member. The recess being a blind bore from the front side of the bottom of the tracer sleeve, and the blind bore being closed by a disc which is sealingly attached in front of the blind bore.

Abstract: A training rocket for smoke development. The training rocket includes a rocket tube which contains powder and constitutes a propulsion motor for the rocket. The rocket includes a forward training head which contains a smoke composition adapted to emit visible smoke upon impact. An igniter charge, such as a tracer charge, which can be ignited by the propellant powder is situated in the rearmost of the training head, behind a bursting charge which can be ignited by the igniter charge. The igniter charge and the bursting charge are situated behind the smoke composition in the training head, for igniting the smoke composition, in a capsule which can be forced rearwardly from the training head due to the increased pressure caused by combustion of the smoke composition, whereby an aperture is formed for passage of smoke gases rearwardly in the rocket, through the rocket tube and out of it.