Abstract: This disclosure relates to a method of limiting the yawing motion on the trajectory of an artillery shell during the firing phase using a sliding driving band and completely folded-in guide fins. The shell is converted as soon as possible outside the mouth of the barrel of the firing piece by fold-out of the guide fins into a fin-stabilized artillery shell. Any form of non-uniform fin fold-out is avoided by virtue of all the guide fins being interconnected to form a system which gives all the fins the same movement pattern and the same fold-out speed in each phase of fin fold-out. This disclosure also includes a shell in which synchronization of fin fold-out includes a rotatable control ring that is arranged around the axis of the shell and is connected to the rotation spindles of all the fins.

Abstract: This disclosure relates to a method and an arrangement for low or non-rotating artillery shells fired from launch weaponry, and which introduces a portion of the barrel pressure built up in the barrel during the launch phase into a chamber arranged in the low or non-rotating artillery shell which is delimited in at least one direction by an element which is movable relative to the rest of the shell when a differential pressure between the chamber and the external environment of the shell is sufficient to move the element. The moveable element may be a protective casing covering fins of the artillery shell.

Abstract: This disclosure relates to a method of limiting the yawing motion on the trajectory of an artillery shell during the firing phase using a sliding driving band and completely folded-in guide fins. The shell is converted as soon as possible outside the mouth of the barrel of the firing piece by fold-out of the guide fins into a fin-stabilized artillery shell. Any form of non-uniform fin fold-out is avoided by virtue of all the guide fins being interconnected to form a system which gives all the fins the same movement pattern and the same fold-out speed in each phase of fin fold-out. This disclosure also includes a shell in which synchronization of fin fold-out includes a rotatable control ring that is arranged around the axis of the shell and is connected to the rotation spindles of all the fins.

Abstract: This disclosure relates to a method and an arrangement for low or non-rotating artillery shells fired from launch weaponry, and which introduces a portion of the barrel pressure built up in the barrel during the launch phase into a chamber arranged in the low or non-rotating artillery shell which is delimited in at least one direction by an element which is movable relative to the rest of the shell when a differential pressure between the chamber and the external environment of the shell is sufficient to move the element. The moveable element may be a protective casing covering fins of the artillery shell.

Abstract: This disclosure relates to a method of limiting the yawing motion on the trajectory of an artillery shell during the firing phase using a sliding driving band and completely folded-in guide fins. The shell is converted as soon as possible outside the mouth of the barrel of the firing piece by fold-out of the guide fins into a fin-stabilized artillery shell. Any form of non-uniform fin fold-out is avoided by virtue of all the guide fins being interconnected to form a system which gives all the fins the same movement pattern and the same fold-out speed in each phase of fin fold-out. This disclosure also includes a shell in which synchronization of fin fold-out includes a rotatable control ring that is arranged around the axis of the shell and is connected to the rotation spindles of all the fins.

Abstract: The present invention relates to a method of as far as possible limiting the yawing motion on the trajectory of an artillery shell(1), provided during the firing phase with a sliding driving band and completely folded-in guide fins (3, 16), which shell, as soon as possible outside the mouth of the barrel of the firing piece, is converted, by fold-out of the guide fins (3, 16), into a fin-stabilized artillery shell, any form of non-uniform fin fold-out being avoided by virtue of all the guide fins (3, 16) being interconnected, by means (18, 19, 20) adapted thereto, to form a system which gives all the fins (3, 16) the same movement pattern and the same fold-out speed in each phase of fin fold-out. The invention also includes a shell (1) designed in accordance therewith, in which the means for synchronization of fin fold-out consists of a rotatable control ring (19) which is arranged around the axis of the shell and is connected to the rotation spindles (13) of all the fins.

Abstract: The present invention relates to a fin-stabilized artillery shell (1) comprising a body part (8, 26, 36) which can be axially displaced rearwards, in the direction of flight of the shell, once the latter has left the barrel from which it has been fired, and which in the original position is fully retracted in the shell (1), and in which a number of deployable fins (18, 24, 29-30, 42-47) are in turn secured, and from which the fins are automatically deployed as soon as the body part has reached its rear position in which it is locked relative to the rest of the shell. One of the advantages of the invention is that in the flight position it gives the shell a greater length than is permitted by the charging position of the artillery piece launching the shell. This gives the shell considerably better stability in its trajectory towards the target.

Abstract: The present invention relates to a fin-stabilized missile (1) of the type which is intended to be fired at high acceleration towards a defined target along its trajectory and which can be guided in the trajectory and which, for stabilizing it in the trajectory, is provided with stabilizing fins (3, 32) arranged at its rear end, and control elements (6, 7) which are arranged at its front end and are intended to guide the latter, and whose rear part, in which the fins are secured, consists of a body part (4, 31) which can rotate freely relative to the main part (1, 29) of the missile about a bearing (14, 36) arranged concentric to the longitudinal axis (L) of the missile (1).

Abstract: The present invention relates to a method and an arrangement for shells (1a, 1b) fired from launch weaponry, using some of the barrel pressure built up in the barrel during the launch phase for an additional active function over and above that of giving the shell (1a, 1b) in question its trajectory velocity. According to the invention, during the launch phase, some of the propellant powder gas accelerating the shell is therefore introduced into a chamber (12, 38, 60) which is arranged in the same and which is delimited in at least one direction by an element (8, 31, 58, 52, 53) which is movable relative to the rest of the shell and on which the barrel pressure acting on the shell simultaneously acts to maintain the original direction as long as the shell is located inside the barrel during the launch phase. This technique can thus be used to remove protective casings covering the fins, in order to push out fin units and to deploy initially retracted fins.

Abstract: The present invention relates to a fin-stabilized artillery shell (1) comprising a body part (8, 26, 36) which can be axially displaced rearwards, in the direction of flight of the shell, once the latter has left the barrel from which it has been fired, and which in the original position is fully retracted in the shell (1), and in which a number of deployable fins (18, 24, 29-30, 42-47) are in turn secured, and from which the fins are automatically deployed as soon as the body part has reached its rear position in which it is locked relative to the rest of the shell. One of the advantages of the invention is that in the flight position it gives the shell a greater length than is permitted by the charging position of the artillery piece launching the shell. This gives the shell considerably better stability in its trajectory towards the target.

Abstract: The present invention relates to a fin-stabilized missile (1) of the type which is intended to be fired at high acceleration towards a defined target along its trajectory and which can be guided in the trajectory and which, for stabilizing it in the trajectory, is provided with stabilizing fins (3, 32) arranged at its rear end, and control elements (6, 7) which are arranged at its front end and are intended to guide the latter, and whose rear part, in which the fins are secured, consists of a body part (4, 31) which can rotate freely relative to the main part (1, 29) of the missile about a bearing (14, 36) arranged concentric to the longitudinal axis (L) of the missile (1).

Abstract: The present invention relates to a method and a device designed for use with such shells (1) that are equipped with a base-bleed unit (8) for extended range and which during the first phase of their trajectory are spin-stabilised but which in the subsequent phase are subjected to spin deceleration by fins (9-13) that deploy from the shell body and take over the stabilising function. More exactly the present invention is a method and a device that enables the said shells (1) to achieve an effective and functional deployment of the fins (9-13) at the desired point in time with simultaneous ejection of the base-bleed unit (8) which at this point in time either no longer performs any useful function since it is burnt-out and solely constitutes a dead-weight or its function is no longer required.

Abstract: The present invention relates to a method and a device relating to shells with deployable fins and which are fired from large caliber guns into ballistic trajectories, for preventing the propellant gas pressure in the barrel during firing from directly or indirectly deforming the said fins (9-13). The type of fins that the present invention primarily relates to are those that are deployed on command in order to fin-stabilize the shell. Usually such fins are protected prior to deployment by an ejectable fin protector (19). To prevent this fin protector from being deformed and consequently impeding fin deployment or degrading fin functionality, the present invention proposes that all unoccupied space inside the said fin protector be filled with an inert, noncombustible, non-glutinous substance (32) of low compressibility and very low inherent strength.

Abstract: The present invention relates to a method and device for combating identified targets (F) using warheads (2) from a launching vehicle (1) flying over a target area, by separating from this launching vehicle (1) warheads (2) which act independently after separation, and including those targets which lie close to the flight trajectory of the launching vehicle (1) and those which lie well to the side of same flight trajectory. The invention is based on the use of that part of the kinetic energy of the launching vehicle (1) which the warhead (2) takes over from the same when it is separated in order to give the warhead (2) a looping trajectory or any other programmed flight trajectory, which carries it up to a starting height adapted to its active use, which lies considerably above the actual flight trajectory of the launching vehicle (1), and which, if so required, can carry the warhead (2) back to the geographical position where it was separated from the launching vehicle (1).

Abstract: A method of separating from one another subcombat units transported by a rotationally-stabilized carrier body to a predetermined target area. The method comprises the steps of:ejecting the subcombat units and a plurality of masses or bodies from the carrier body;utilizing rotational energy from the rotationally-stabilized carrier body to generate axially directed separation forces in the masses or bodies, the separation forces acting concentrically in relation to a common center axis of the carrier body; andseparating the subcombat units from one another so that they spread out and each cover a predetermined portion of a target area by utilizing the separation forces in the masses or bodies to cause the separation of the subcombat units after their ejection from the carrier body.