Abstract: A parachute device is provided for a divisible shell that includes an active body and a shell base. The parachute device includes two parachutes, a first, main parachute connected to the active body by parachute lines and a second parachute connected to the shell base.

Abstract: A method for modifying a separable projectile between a test embodiment or an effect embodiment includes detaching the front projectile body from the rear projectile body, arranging a payload container in the front projectile body where the payload container comprises measuring equipment or an effect part, and fitting the front projectile body to the rear projectile body by way of a belt. A separable projectile which can be modified between a test embodiment and an effect embodiment is also provided.

Abstract: A dividable parachute grenade is provided including a grenade casing, a nose cone, a detonating fuse, a dividing charge, a payload, a parachute device, a grenade bottom, and a supporting device, wherein the supporting device is annular and includes pretensioned sector elements fixed to a fixing ring in the recess on the inner side of the grenade casing, the sector elements are pretensioned with a tension ring arranged around the annular supporting device via recessed grooves in the sector elements, whereof the supporting device is arranged extensibly in the radial direction in a recess on the inner side of the grenade casing behind the payload and supports the payload in the extended position during the acceleration phase of the grenade, and stays in the grenade after the separation of the payload from the grenade.

Abstract: A fin deployment mechanism for a projectile. The mechanism includes at least one fin and at least one actuator. The fin is arranged in a deployable and retractable manner on the projectile. The fin and at least one balance weight are arranged so that, when the fin is deployed, the weight is displaced towards a center of the projectile and, when the fin is retracted, the weight is displaced from the center of the projectile. A method for deploying and retracting fins on a projectile. At least one fin is arranged in a deployable and retractable manner on the projectile. The fin is fitted to at least one balance weight such that when the fin is displaced from the center of the projectile the weight is displaced towards the center, and when the fin is displaced towards the center of the projectile the weight is displaced from the center.

Abstract: A parachute device is provided for a divisible shell that includes an active body and a shell base. The parachute device includes two parachutes, a first, main parachute connected to the active body by parachute lines and a second parachute connected to the shell base.

Abstract: A dividable parachute grenade is provided including a grenade casing, a nose cone, a detonating fuse, a dividing charge, a payload, a parachute device, a grenade bottom, and a supporting device, wherein the supporting device is annular and includes pretensioned sector elements fixed to a fixing ring in the recess on the inner side of the grenade casing, the sector elements are pretensioned with a tension ring arranged around the annular supporting device via recessed grooves in the sector elements, whereof the supporting device is arranged extensibly in the radial direction in a recess on the inner side of the grenade casing behind the payload and supports the payload in the extended position during the acceleration phase of the grenade, and stays in the grenade after the separation of the payload from the grenade.

Abstract: A method for direction limitation of a firing system. A first calculating unit controls the firing system and knows direction limitation positions. An elevation of the firing system and a traverse of the firing system are measured. A position of the firing system is calculated in the first calculating unit based on the elevation and traverse. The position of the firing system is calculated in a second calculating unit based on the elevation and traverse. The calculated positions of the firing system are compared with direction limitation positions. It is decided whether the firing system is positioned outside the direction limitation positions. Also, a direction limitation system for a firing system.

Abstract: An ammunition management system for firing mixed ammunition in an automatic cannon. The ammunition management system includes a rotatable ammunition magazine including ammunition shot, a breech casing and an ammunition feed device for feeding of ammunition shot between the ammunition magazine and the breech casing. A drive device drives the ammunition magazine via a chain drive mechanism disposed in the ammunition magazine. A decoupling device engages and disengages the ammunition magazine with respect to the ammunition feed device, so that ammunition can be moved between different positions in the ammunition magazine, via an alternating process including: feeding of ammunition from the ammunition magazine to the ammunition feed device, disengagement of the ammunition magazine, rotation of the ammunition magazine, engagement of the ammunition magazine, and feedback of ammunition from the ammunition feed device to the ammunition magazine. A method for sorting ammunition in a ammunition magazine.

Abstract: The invention relates to a fin deployment mechanism (1) comprising a base unit (3), deployable fins (8) movably arranged on the base unit (3) and, in the retracted position, bearing against the base unit (3), as well as a gas-generating device, in which the fins in the retracted position are fixed to the base unit, and in which at least one gas duct (6, 7) is arranged in the base unit (3) so as to conduct pressurized gas generated by the gas-generating device to the bottom side of the fins (8), which in the retracted position bear against the base unit (3), in order to create a force which acts on the fins (8) for deployment of the same (8?). The invention further relates to an artillery projectile comprising a fin deployment mechanism.

Abstract: The invention relates to a brake panel (3, 3?) for a projectile (1), in which those surfaces (A) of the brake panel (3, 3?) which are facing in the direction of travel of the projectile are wholly or partially angled in such a way that the normal from the said surfaces (A) is not parallel with the center line (C) of the projectile (1) in order to reduce or counteract the Magnus torque generated during and after the extension of the brake panel (3, 3?). The invention further relates to a detonator (2) for a projectile (1) and a projectile (1) comprising such a brake panel.

Abstract: A method of fire control against aerial targets traveling towards an object of protection. A position of the object of protection is known. A position of the aerial target is measured. The position of the aerial target is estimated. A velocity of the aerial target is estimated. A model of a guidance law of the aerial target is applied. An acceleration of the aerial target sufficient to hit the object of protection is calculated. A future trajectory of the aerial target is predicted based on the position of the object of protection, the estimated position of the aerial target, the estimated velocity of the aerial target, and the calculated acceleration of the aerial target. Points of aim along the predicted future trajectory are calculated. A fire control system includes at least one sensor for measuring the position of the aerial target as a function of time.

Abstract: The invention relates to a method for the repeatable initiation of propellent charges in a weapon system, for example in the firing of projectiles from a barrel weapon, through electrical discharge between a rear electrode (22) and a front electrode (21) in a combustion chamber channel (3) filled with filler gas and comprising a combustion chamber combustion element (30), in which the filler gas in the combustion chamber channel (3) is ionized via a high-voltage potential from at least one ionizing electrode (100, 101, 102, 103), which ionization increases the electrical conductivity in the combustion chamber channel (3) so that an electrical flashover, through electrical discharge via a high-voltage generator (5) between the rear electrode (22) and the front electrode (21), is generated from the rear electrode (22) via at least one ionizing electrode (100, 101, 102, 103) onward to the front electrode (21), which results in hot ignition gas with plasma-like state being expelled from the combustion chamber cha

Abstract: An ammunition management system for firing mixed ammunition in an automatic cannon. The ammunition management system includes a rotatable ammunition magazine including ammunition shot, a breech casing and an ammunition feed device for feeding of ammunition shot between the ammunition magazine and the breech casing. A drive device drives the ammunition magazine via a chain drive mechanism disposed in the ammunition magazine. A decoupling device engages and disengages the ammunition magazine with respect to the ammunition feed device, so that ammunition can be moved between different positions in the ammunition magazine, via an alternating process including: feeding of ammunition from the ammunition magazine to the ammunition feed device, disengagement of the ammunition magazine, rotation of the ammunition magazine, engagement of the ammunition magazine, and feedback of ammunition from the ammunition feed device to the ammunition magazine. A method for sorting ammunition in a ammunition magazine.

Abstract: The invention relates to a method of, with a projectile (1) comprising a reactive charge (4), combating an explosive-charged weapon unit (7), preferably an enemy shell, so that undesirable harmful effects on the environment are reduced, wherein the projectile (1) is configured to penetrate the surface (8) of the weapon unit (7) upon impact so that a passage (9) is opened into the explosive (10) of the weapon unit (7), through which passage (9) the reactive charge (4), under the influence of the kinetic energy of the projectile (1), is transferred to the explosive (10) of the weapon unit (7). The method can be deemed to be characterized in that the reactive charge (4), upon contact with the explosive (10) of the weapon unit (7), reacts and starts a hypergolic reaction with the explosive (10). The invention also relates to a projectile (1) for the said method.

Abstract: A method for direction limitation of a firing system. A first calculating unit controls the firing system and knows direction limitation positions. An elevation of the firing system and a traverse of the firing system are measured. A position of the firing system is calculated in the first calculating unit based on the elevation and traverse. The position of the firing system is calculated in a second calculating unit based on the elevation and traverse. The calculated positions of the firing system are compared with direction limitation positions. It is decided whether the firing system is positioned outside the direction limitation positions. Also, a direction limitation system for a firing system.

Abstract: The present invention relates to a shell (1) comprising a shell casing (2), a detonator (3), a payload (4), a shell base (5) and a separation charge (6) intended for ejection of the payload (4) and the shell base (5) from the shell (1) over a target area. The invention is characterized in that the shell base (5), following separation from the shell (1), can be divided into smaller parts which are harmless for the environment.

Abstract: The invention concerns a method for repeatable ignition of propellant charges in a weapon system, e.g. for firing shells from a barrel weapon, through electrical discharge in a combustion chamber duct (3) containing a combustion chamber substance (30), wherein the filling gas in the combustion chamber duct (3) is ionized by the high-voltage potential applied to the ionizing electrode (7), which is connected to a first high-voltage generator (2), thus increasing the electrical conduction capacity in the combustion chamber duct (3) such that an electrical sparkover through electrical discharge via a second high-voltage generator (5) between a rear electrode (22) and a front electrode (21) is generated and produces an effect, with subsequent ionization of the surface of the combustion chamber substance (30), which causes hot gas in a plasma-like state to be expelled from the combustion chamber duct (3).

Abstract: The invention relates to a rotationally stabilized projectile (1) for launching from a barrel, which projectile (1) comprises a front projectile part (22), a rear projectile part (20) comprising a rotating band (4), and an intermediate projectile part (21) comprising a freely rotatable middle section (2) arranged with guide wings (3) for improving the gliding capability and guidance capability during the gliding phase and end phase of the projectile. The guide wings (3) are arranged extensibly on the freely rotatable middle section (2), and the intermediate projectile part (21) also comprises a regulator device (14) for regulating the rotation of the middle section (2). The invention also relates to a method for guiding a rotationally stabilized projectile.

Abstract: The invention relates to a method for determining the roll angle of a guidable and substantially or partially roll-stable projectile comprising control system, radio-based positioning receiver and sensor for measuring roll angular velocity, in which the following steps are included: actuation of the actuators of the projectile by the control system, included in the projectile, for maneuvering of the projectile; estimation of a first signal, the projectile control force, on the basis of the control system included in the projectile; measurement of a second signal, the velocity of the projectile relative to the ground-fixed coordinate system, with the radio-based positioning receiver mounted in the projectile; measurement of a third signal, the rotational velocity, with the sensor for roll angular velocity mounted in the projectile; calculation of a roll angle on the basis of the first, second and third signals, estimated projectile control force, measured projectile velocity, and measured rotational velocity,

Abstract: The invention relates to a method for determining angle of incidence for a projectile in the path of the projectile from launcher to target, which projectile is guidable and substantially or partially roll-stable and comprises a control system and at least two actuators with associated control members, in which the following steps are included: determination of applied force for pitch control by evaluation of the moment upon the actuators of the projectile, determination of applied force for yaw control by evaluation of the moment upon the actuators of the projectile, calculation of the pitch component a of the angle of incidence and of the yaw component ? of the angle of incidence, based on comparison between the evaluated moments and reference data for moments. The invention also relates to a GNC system.