Abstract: A solid-propellant motor includes an outer casing and a combustion chamber which is disposed within the outer casing. In order to simplify the attachment of fittings, the combustion chamber is in the form of a separate component, which is separate from the outer casing.

Abstract: A missile head has a shroud which forms its tip and which can be detached in its totality during flight from the fuselage of the missile. The missile head further has a rear part, which is connected to the fuselage, and a front nose, which can be disconnected from the rear part and forms the tip. A separating device separates the rear part from the fuselage and the nose from the rear part during flight. A physically small shroud can be achieved, and damage to the fuselage of the missile by separation of the shroud can be prevented, if the nose is split into at least two parts and the separating device is prepared to split the nose into these two parts during flight.

Abstract: A surrounding area is imaged onto a detector of a detector device. An optical system produces an imaging beam path and a panel, which is arranged in the imaging beam path, shadows a subarea of the image of the surrounding area on the detector. In order to mask out an object which would dazzle the detector device, while nevertheless being able to monitor the surrounding area, the panel is illuminated in a subarea, and the transmission of the panel in the subarea is reduced by the illumination in the entire frequency range in which the detector is sensitive. The illuminated subarea of the panel shadows the selected subarea of the image.

Abstract: An image of a surrounding area is projected onto a detector of a detector device by way of an optical system that produces an imaging beam path. A screen is disposed in the imaging beam path and the screen shadows a subarea of the image of the surrounding area on the detector. In order to allow an object which is dazzling the detector device to be masked out and nevertheless to allow the surrounding area to be monitored, the screen is subdivided into a plurality of segments which can be operated individually, and segments which are associated with the subarea are selected and operated, and are in this way heated. The transmission of the selected segments is reduced by the heating throughout the frequency range in which the detector is sensitive, and the selected segments of the screen thus shadow the subarea of the image.

Abstract: A multimodal explosive, in particular for blast charges, which has, for increasing the power, a powder additive which is formed by a hydrogen-terminated monocrystalline silicon powder of at least one grain size range, which powder has the advantage that no oxidation phenomenon takes place even over many years—even at storage in ambient air. Due to the non-oxidized crystal surfaces, advantageously an immediate joint reaction with the explosive takes place in the detonation front and also extends into the post-reaction period with increasing crystal sizes, so that a different propellant effect is achieved depending on the additive.

Abstract: A method for determining a location of a flying target included identifying and measuring the target by at least two seeker systems disposed at a distance from one another. The position of the target relative to at least one of the two seeker systems is determined from measurement data derived therefrom. The position of the target is measured inconspicuously and without active radiation, in that the seeker systems are data-networked, passive target tracking systems for missiles, which autonomously track the target and align the missile with the target. The measurement data determined by the data-networked seeker systems are combined, and the location of the target is determined from the combined data.

Abstract: A missile includes a pyrotechnic charge. The missile is constructed in such a way that the pyrotechnic charge is made to burn deflagratively when the missile is used correctly. The pyrotechnic charge includes a mixture containing at least one metal or a metal alloy as a fuel and at least one metal oxide as an oxidizing agent. The fuel and the oxidizing agent are selected in such a manner that they can react with one another by burning. The mixture is compressed to a density of at least 85% of a theoretical density of the mixture, and the fuel, the oxidizing agent and a quantitative ratio between the fuel and the oxidizing agent are selected in such a manner that a density of the mixture is at least 6 g/cm3.

Abstract: The present invention relates to a grenade that can be fired from a barrel, for recoilless firing. The barrel is open at both ends and is without any flow cross-section constrictions. The grenade is formed of a grenade base body which surrounds at least one explosive charge, and a flow cross-section reduction device for reducing the flow cross-section of the barrel. The device is arranged in the opposite direction to the firing direction X with respect to the grenade base body. The flow cross-section reduction device is connected to the grenade base body, separated from it, via a connecting device, and is connected to it such that it is stable during firing. A grenade launcher or shell firing apparatus has a grenade such as this, and the grenade firing apparatus has a barrel which is open at both ends and does not have any flow cross-section constrictions.

Abstract: An optical swiveling device is specified for imaging and/or projection of an object scene, having a supporting structure, having a detection/transmission unit arranged in the supporting structure, having a pitch frame and having a roll frame, with the pitch frame being mounted in the roll frame such that it can rotate about a pitch axis and with the roll frame being mounted in the supporting structure such that it can rotate about a roll axis. In this case the pitch axis and the roll axis intersect at an intersection angle of less than 90°. First deflection optics are arranged in the pitch frame such that a beam propagating along the pitch axis is deflected in an object-side direction which intersects the pitch axis at the intersection angle, and vice versa, and second deflection optics are arranged in the roll frame such that a beam propagating along the pitch axis is deflected in the direction along the roll axis, and vice versa.

Abstract: A weapon system uses caseless munitions. In order to permit a further use of the weapon system essentially without delay on jamming, a configuration of the weapon system is disclosed that has a weapon barrel, a projectile magazine with individual chambers and a propellant charge magazine with individual chambers. In order to guarantee a firing position, the projectile magazine and the propellant charge magazine, may be moved relative to the weapon barrel. The projectile magazine has a chamber located in a discharge position in which an ejector device for the projectile in the chamber may be activated. A further chamber of the projectile magazine may be loaded in the movement position for the projectile magazine and the propellant charge magazine has a chamber, located in a discharge position in which an ejector device for the propellant charge in the chamber may be activated. The further chamber of the propellant charge magazine may be loaded in the movement position of the propellant charge magazine.

Abstract: An apparatus for wing unfolding is particularly suited for an airborne vehicle. The apparatus has a base body with a longitudinal axis, a number of moveable flaps, and a number of lateral recesses. Attachment devices are configured for fitting the base body to an end face of a wing, with the one or more moveable flap being formed to influence a drag of the wing. Each lateral recess is designed for self-detachable attachment of the base body to the wing. Furthermore, a folding wing is specified, in particular for an airborne vehicle, having a wing, having a swiveling mechanism for extension of the wing to a limit position, having a wing pocket for holding the wing on the longitudinal side in the retracted state, and having an apparatus, which is arranged at the end, for wing unfolding of the type already known. A flying object, such as a guided missile, has a number of such folding wing assemblies.

Abstract: A propellant charge for use for ammunition, in which the propellant charge is separate from the projectile, has a propellant charge substance which can be initiated by a fuse. In order to solve the problem of providing a propellant charge for use in a two-part munition, which on the one hand can be produced easily and at low cost and on the other hand does not present any risk of damage when mechanically loaded before use, it is proposed that a propellant charge casing be provided which surrounds the propellant charge substance, with the propellant charge casing being in the form of a plastic part which is composed of a non-combustible, temperature-stable plastic material.

Abstract: A guided missile has a sensor unit, a propulsion unit, and a payload unit. A missile casing forms the outer contour, extends along a longitudinal direction, and accommodates the sensor unit, the propulsion unit, and the payload unit. At least two of the units can be fitted alongside one another in the longitudinal direction. In comparison to conventional guided missiles, the guided missile is distinguished by increased modularity and thus by increased flexibility with regard to different operational scenarios.

Abstract: An optical system for a missile has optics for imaging an object through a beam path on an imaging plane. The optics have external optics, rotatably mounted about a roll axis and a pitch axis of the missile, and internal optics, and one of the ends of the beam paths is fixed with respect to the structure in the missile. In order to prevent image disturbances caused by shadows which are caused at a high squint angle by an element which is fixed to the structure, the optical system includes a shutter, which can be introduced into the beam path during flight of the missile, in order to mask out a shadow, which is produced by an element of the missile, in the beam path in a viewing direction of the external optics which is tilted with respect to the roll axis.

Abstract: A microwave generator (10) having a hollow central electrode (12) with a front face including hollow emmission element (18), and having an outer electrode (14), which coaxially surrounds the central electrode (12) along an axially extending resonator section (16). The two electrodes (12, 14) define a spark gap (36) and are connected to a high-voltage source (38). An ultracompact microwave generator (10) is implemented by the high-voltage source (38) being arranged in the hollow central electrode (12) of the microwave generator (10) rather than on the outside thereof.

Abstract: A method for production of an infrared area emitter which can be used for defense against guided missiles with infrared homing heads, for example for ships. According to the invention, an aerosol cloud which is emissive in the infrared range is produced by the reaction of a first primary aerosol composed of an aqueous solution of an electron acceptor with a second primary aerosol composed of an aqueous solution of an electron donor in order to produce the infrared area emitter. The use of primary aerosols such as these leads to emission at 3-5 and 8-14 ?m, and does not produce any visual signature either.

Abstract: An apparatus for deployment and recovery of an underwater vehicle can be introduced into a recovery tube of an underwater recovery vehicle. The apparatus has a moveable tube provided with an insertion/extraction device at one of its ends. The device is in the form of a tube or of a ring in a retracted state and in the form of a funnel in an extended state. There is also disclosed a method for deployment and a method for recovery of an underwater vehicle by way of the above-mentioned apparatus that is introduced into a recovery tube of an underwater recovery vehicle. Additionally, there is disclosed a method for docking an underwater vehicle at a recovery tube of an underwater recovery vehicle provided with the above-mentioned apparatus.

Abstract: A motion-restraint arrangement (48) with elongate lines of elements (10), wherein each line of elements (10) has a number of individual elements (12) which can be erected by spring elements (20) from a small-volume thin storage condition into a large-volume active condition. Each respective individual element (12) has flexible lateral edge elements (16, 18), which in the active condition define a parallelepiped. The spring elements (20) extend in spatially diagonal relationship between the corners (22) of the respective parallelepiped (14). A motion-restraint arrangement (48) which is easy and inexpensive to produce and which has optimum restraint properties is obtained in that the spatially diagonal spring elements (20) are formed by spring wires (24), which extend in a zigzag shape in the longitudinal direction of the respective line of elements (10).

Abstract: The production and emission of high-energy microwave pulses are made possible by means of a device with a particularly compact design if the capacitor column (12-12) of the Marx generator (11) whose series circuit conventionally itself feeds a microwave generator with a matched antenna geometry, is now itself used—dispensing with the microwave generator and its antenna—directly as a resonator and Hertzian antenna dipole (24). Its oscillation response can be optimized by triggered spark gaps (14) for the switching of capacitors (12), and by means of plates (19) connected at the ends, in order to increase the stray capacitances.

Abstract: A method for varying the flight path of a missile, in particular of a spin-stabilized projectile, which has an outer wall and which is provided with at least one impulse device. The impulse device can be activated deliberately at a defined time during the flight of the missile. The impulse device is arranged with respect to the longitudinal axis of the missile such that, when it is activated, it generates an impulse that initiates a tumbling movement which causes the flight-path of the missile to be shortened or varied. A spin-stabilized projectile is provided with such an impulse device and it is configured so that the impulse device may be triggered during flight so as to initiate the flight-altering tumbling movement.