Abstract: The present invention is directed to a method for production preformed fabrication casing or associated parts intended to generate fragments initiated by the explosive of contained warhead charges. Molded parts having fragmentation bodies (4, 21, 34) embedded therein are produced by a two-stage powder compaction method followed by sintering together the compacted powder metal. The method described in the present invention defines how in an initial stage the fragmentation bodies (4, 21, 34) are fixed in position using a fixture (2) after which the bodies are covered with powder metal that is then compacted until the powder forms a single molded part (2) after which the fixture is replaced with a secondary quantity of powder that is also compacted to form a self-supporting unit (12) together with the first quantity of powder.

Abstract: This invention, as a unit, is a training adjustable combination sight, primarily intended to be mounted on a vehicle of smaller vessel for close-in defense of these against air and ground attacks. In its entirety, aside from the required sight sensors (16-18) situated in an intentionally elevatable sensor housing (4), the combination sight entails a weapon (8) that is controlled by the sensors. The sight sensors (16-18) included in the combination sight can also be utilized for fire control of exterior weapons located elsewhere as well as for gathering purely surveillance data.

Abstract: The invention also relates to a method of manufacturing and use of the ammunition round in other more conventional weapon systems than the said electrothermal and/or electrothermochemical weapon systems.

Abstract: The invention relates to a cartridge case (2) and ammunition round (1) primarily for electrothermal and/or electrothermochemical weapon systems, which round comprises the said cartridge case. According to the invention, the casing (10) of the cartridge case comprises or consists of one or more insulated or insulating shells, layers or surfaces (11, 12, 13) for, at least electrically, insulating the casing of the cartridge case from the barrel (14) of the weapon system and also preferably from at least the bottom (16) and/or firing device (5) of the ammunition round as well, but preferably also from the rest of the ammunition round, when the round is used, and also preferably from at least the bottom and/or firing device of the ammunition round as well, but preferably also from the rest of the ammunition round, when the round is stored and handled.

Abstract: An explosive charge (3) can be equipped with two liners (4, 5) that can be attached to one another. The primary liner (4) is so devised that when choosing a first choice (11) of being able to work independently and by employing a symmetrical form achieving a forward-aimed Shaped Charge Warhead (SCW) effect upon explosive charge initiation by means of the material (7, 8) indicated for the primary liner. A secondary liner (5) is devised with a second choice (12) to be able to work together with the primary liner and together cause an asymmetric form that distributes the material (18, 19) from the liners at different velocities to thereby cause a forward-directed fragmentation effect. The ammunition unit (1) can, thus, be designed or prepared for two different combat cases in a technologically simple and unambiguous manner.

Abstract: A proximity-fuzed ammunition unit (1) that can approach a target and where during approach the proximity fuze function effects or gives rise to a voltage pulse pattern that is dependent on objects located along the flight path of the ammunition unit on its approach to the target. The voltage pulse pattern forms the basis for the actution of at least one triggering device (18) incorporated in the ammunition unit. The electrical circuit or circuits incorporated in or interacting with each triggering device is/are arranged to sense a voltage or amplitude value in the trailing edge of a pulse incorporated in or forming the pattern. If the pattern comprises a number of pulses an indication is given when a predetermined number of pulses has appeared to appears. Each electrical circuit causes or effects the opeation of the triggering device for its actuation depending on the said sensing and/or indication.

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: An ammunition unit, such as a missile, the casing of which contains at least one explosive charge as well as warhead modules arranged in or on the fuselage or casing that comprise a constituent part of the unit's warhead function when the explosive charge is actuated. The warhead effect modules are of modular design, and the various modules are secured to the fuselage or casing by securing devices and/or retention parts. The device includes a range of modules pertaining to different types of warhead effects. When engaging an actual type of target the ammunition unit is assembled with an array of modules-selected from the range of modules-matched to different types of targets or engagement situations, with the array of modules secured to the fuselage or casing by securing devices.

Abstract: An ammunition device (4) comprising one or more warhead effect jackets (17), each jacket containing warhead effect elements (18). The ammunition device also incorporates one or more explosive compositions arranged inside each warhead effect jacket that in or close to the target is/are triggerable by means of a triggering device. One or more separation charges is/are arranged adjacent to each warhead effect jacket that when actuated cause removel of one or more said warhead effect jacket(s). The actuation devices incorporate or interact with a programming device that operates with a first mode that can be an initial mode in which the actuation devices remain non-actuated, and a second mode in which the programming device actuates the actuation devices for initiating the separation charges, thereby causing ejection of each warhead effect jacket concerned.

Abstract: The present invention relates to a method and a device for combating a pre-determined target with submunitions directed at the target from an airborne carrier in the form of a rocket, missile or equivalent (1) whereby the submunitions (17) are of the type whose main effect in target derives from impact with the target. As claimed in the present invention the submunitions (17) are given both a lateral motion vector (34) relative to the direction of flight of the carrier and a motion vector (35) in the direction of flight of the carrier. Jointly these motion vectors give the submunitions a resultant motion vector in a direction (36) towards the target.

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: Method and arrangement for extending the range of fire of a fin-stabilized artillery missile. The fin-stabilized artillery missile (1), which is fired in a ballistic trajectory, has fins (3-6), which have been given a sawtooth-shaped leading wing edge (7) that has been found to give the missile (1) an extended range of fire and improved manoeuvrability.

Abstract: A device arranged to enable the engagement of targets (5) by means of a shaped charge function. An ammunition unit is arranged to operate with at least two configuration modes where in the first mode the ammunition unit comprises solely a first modular charge (3). In the second mode the first modular charge is conjoined with a second modular charge (4). The modular charges each effect their own type of shaped charge function. Another feature is that the ammunition unit is arranged to enable changeover from the first configuration to the second before firing, launch or release of the ammunition unit.

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 method and a device for improving—at least in part—the external ballistieds of primarily the type of artillery shells (1) that are fin-stabilised in their trajectory towards the target and thus have a slipping plastic driving band (6) which, during firing of the said shell from a designated barrel, constitutes the shell's direct contact with the inside of the barrel. The problem that it is the function of the present invention to resolve is that the slipping plastic driving band (6) normally detaches immediately outside the muzzle of the barrel used for firing, thereby leaving an open groove (4) that causes distrubing turbulence which is detrimental to the flight of the said shell.

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 long-range artillery shell (1) that is fin-stabilised in its trajectory and which is designed to be fired in a rifled gun barrel and thus has a slipping driving band (8) as main contact surface with the inside of the barrel, and has a so-called base-bleed unit (3) with a number of stabilization fins (9-14) that are deployable after the shell has left the barrel.

Abstract: The present invention relates to an artillery missile (1) intended for firing on a ballistic trajectory, with gliding characteristics which can be put into effect, after it has reached the summit of this trajectory, to increase the maximum range of the missile.

Abstract: The present invention concerns a method and an arrangement for determining the angle of roll of a launchable body (4) which rotates in its path. The launchable body (4) can consist of a rotating projectile, shell, guided missile or the like, launchable from a launching device (1). According to the invention the transmitter antenna (3) and receiver antenna (5) are each designed with their sweeping beams (6, 9) directed essentially towards each other. By detecting the time the two beams (6, 9) coincide and the signal strength received in the receiver antenna, the angle of roll of the launchable body can be determined.

Abstract: The present invention relates to a method of increasing the range of air defense and artillery shells of the type which for reasons of firing technology have a rear surface which is at right angles to the shell axis, i.e. most conventional air defense and artillery shells. The invention also includes a design of air defense and artillery shells that corresponds with the said method. The invention is characterized by the rear surface of the shell which at the time of firing is at right angles to the shell axis being reformed to an aerodynamically more advantageous form (5, 9) when it has left the gun barrel and is on the way to the target.