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: 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.

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 present invention relates to a method for packing fin-stabilized penetrators (8) in a carrier shell (1), which penetrators (8) comprise a front penetrator part (10) and a rear fin part (9, 9?) comprising fin sides (14, 14?), so that the empty space between the penetrators (8) and problems with the penetrators upon the release of the penetrators (8) from the carrier shell (1) are minimized, wherein the penetrators (8) are packed in groups (7) and are joined together to form larger packing units (6), in which each group (7) is arranged with a centrally located penetrator (8) flanked by at least three outer penetrators (8), which outer penetrators (8) are arranged so that their front penetrator parts (10) lie side to side against the fin sides (14, 14?) of the centrally located penetrator (8).

Abstract: The invention relates to a method and a presentation device for presenting information about the angle to a target to a wearer (2) by means of a display (1) worn by the wearer tracking movement of the wearer's head, the wearer's head movements being detected and the angle of the wearer's head relative to a target being indicated on the display. According to the invention, movements of the wearer's (2) head are detected independently of the target, the position of the wearer is determined locally, the position of the target is designated and the display is controlled on the basis of local information about the wearer's head movement, the wearer's position and the position designated as the target in order to indicate the angle of the wearer's head relative to the target.

Abstract: The present invention relates to a mine protection accessory for fitting to military or civil wheeled vehicles (2) as protection against landmines (12, 12?, 12?) or homemade bombs. The mine protection ( ) is characterized in that the mine protection accessory is configured for fitting to the underside of the vehicle (2) adjacent to one of the wheels (3) of the vehicle (2), and in that the mine protection accessory comprises at least one guard plate (1, 11) configured to deflect pressure, splinters and gravel from a landmine (12, 12?, 12?) away from the underside of the vehicle (2).

Abstract: The invention relates to a projectile (6) provided with a slipping rotating band (1) which is designed for firing from a weapon system with a rifled barrel. The rotating band (1) comprises an inner ring (2) and an outer ring (3) that seals against the barrel. The outer ring is fitted on the outer surface of the inner ring and the inner ring is slippably fitted on the projectile. The rotating band (1) is configured to remain fitted on the projectile (6) from launcher to target by virtue of the fact that the inner ring (2) is made of fibre-reinforced polymer composite or particle-reinforced polymer composite, or fibre-reinforced metal matrix composite or particle-reinforced metal matrix composite. The invention also relates to a slipping rotating band (1) and to a method for producing a slipping rotating band (1) in which the outer ring (3) is affixed to the inner ring (2).

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 centre 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: The present invention relates to a method for packing fin-stabilized penetrators (8) in a carrier shell (1), which penetrators (8) comprise a front penetrator part (10) and a rear fin part (9, 9?) comprising fin sides (14, 14?), so that the empty space between the penetrators (8) and problems with the penetrators upon the release of the penetrators (8) from the carrier shell (1) are minimized, wherein the penetrators (8) are packed in groups (7) and are joined together to form larger packing units (6), in which each group (7) is arranged with a centrally located penetrator (8) flanked by at least three outer penetrators (8), which outer penetrators (8) are arranged so that their front penetrator parts (10) lie side to side against the fin sides (14, 14?) of the centrally located penetrator (8).

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 ? 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.

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 manoeuvring 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 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: 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 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 shell (1) arranged with extensible wings (3) having improved guidance characteristics during the gliding and final phase of the shell (1). The invention is characterized in that the extensible wings (3), via threaded wing fixtures (8), are movably arranged on rotatable axial guide shafts (6) on the shell body (2) for separate or simultaneous displacement of the wings (3) in the longitudinal direction A of the shell (1), for guidance of the shell (1) in the vertical and lateral directions during the trajectory phase of the shell, and in that the wings (3) are also rotatably arranged on radial guide shafts for controlling the angle of incidence of the wings (3) during the final phase of the shell (1).

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 shell (1) intended for firing from a weapon (6), preferably a mortar weapon (6), the shell (1) being designed for securing the shell (1) in a mortar weapon (6) in order thereby to prevent movement of the shell (1) when adjusting the angle of elevation of the weapon (6). According to the invention this is achieved in that the shell (1) comprises a locking part (19, 28, 37), the locking part (19, 28, 37) forming an integral part of the shell (1) and being designed so that the shell (1) after ramming home is locked to a corresponding securing part (19) in the mortar (6). The invention also relates to a mortar (6) intended for firing said shell (1), the mortar (6) being characterized in that the mortar (6) comprises a corresponding securing part (19) for locking the shell (1).