A missile launching system for launching missiles from a mobile platform includes a rectangular primary carrier frame having a platform coupling structure for releasably fastening the first carrier frame to the mobile platform, and a launch tube. A locking device on the primary carrier frame includes a lock hook which projects from the primary carrier frame and has a receiving piece. A stop piece extends transverse to the receiving piece. A locking plate is inserted between the receiving piece and the stop piece. The launch tube has a fastening bracket with a fastening recess fitted onto the receiving piece and locked with the lock hook by inserting the locking plate between the stop piece and the receiving piece. Alternatively, two launch tube receiving devices are laterally attached to the primary carrier frame, each of which is designed as a closed frame defining a receiving opening.
A modular missile launch system for launching missiles from a mobile platform includes a rectangular first support frame having a first longitudinal beam having a platform coupling structure formed for releasably fastening the first support frame to the mobile platform. A second longitudinal beam arranged at a distance from the first longitudinal beam includes a first connecting structure on an underside and a launch tube securing structure for mounting a missile launch tube to the first support frame. The first connecting structure defines a first plug connection portion extending in a longitudinal direction, onto which a second support frame with a second plug connection portion can be plugged in the vertical direction, having at least two first through bores that are spaced apart in the longitudinal direction, through each of which one connecting device can be passed in order to secure the first and the second support frame.
A flight-path determination device for determining a flight path of a flying object has a position determination apparatus to detect a position of the flying object, an alignment apparatus that to verify whether the position of the flying object is within one specified approach path of a number of specified approach paths, and a path determination apparatus to output the relevant approach path as the flight path of the flying object if the position of the flying object is within one of the specified approach paths.
G01S 13/58 - Systèmes de détermination de la vitesse ou de la trajectoire; Systèmes de détermination du sens d'un mouvement
G01C 23/00 - Instruments combinés indiquant plus d’une valeur de navigation, p.ex. pour l’aviation; Dispositifs de mesure combinés pour mesurer plusieurs variables du mouvement, p.ex. la distance, la vitesse ou l’accélération
F41H 11/02 - Installations ou systèmes de défense anti-aérienne ou antimissiles
G01S 13/72 - Systèmes radar de poursuite; Systèmes analogues pour la poursuite en deux dimensions, p.ex. combinaison de la poursuite en angle et de celle en distance, radar de poursuite pendant l'exploration
G01S 13/88 - Radar ou systèmes analogues, spécialement adaptés pour des applications spécifiques
G08G 5/02 - Aides pour l'atterrissage automatique, c. à d. systèmes dans lesquels les données des vols d'avions arrivant sont traitées de façon à fournir les données d'atterrissage
G01S 13/86 - Combinaisons de systèmes radar avec des systèmes autres que radar, p.ex. sonar, chercheur de direction
A folding wing for a missile comprises a wing root, an upper wing part foldably supported at the wing root around a swiveling axis, at least one first elastically pre-stressed force element and a latching device. The at least one first elastically pre-stressed force element is coupled with the wing root and the upper wing part and is designed for permanently urging the upper wing part into a working position relative to the wing root through introducing a torque. The latching device is designed for arresting the upper wing part on reaching the working position automatically.
A folding wing comprises a wing root, an upper wing part foldable relative to the wing root, at least one guiding device, and an elastically pre-stressed force element. The upper wing part comprises an end edge and a profile foot, wherein the wing root comprises a base and an opposing receiving groove, which is designed to receive the profile foot in a flush manner and is delimited by two delimiting edges having a separation distance that at least equals the maximum profile thickness of the profile foot. The guiding device is arranged at one of the upper wing part and the wing root and is designed for guiding the profile foot in a variable distance to the ground of the receiving groove. The force element is coupled with the wing root and the upper wing part and urges the upper wing part into the receiving groove through the pre-stress.
A safety function module for a vehicle is provided. The safety function module comprises a status determination unit which is configured to determine at least a position of the vehicle. Thereby, the safety function module is configured to be reversibly coupled with a signal interface of the vehicle and is further configured to execute a comparison of the determined position of the vehicle with a predeterminable position range and to transmit an activation signal for a safe state of the vehicle to the signal interface if the position of the vehicle departs from the predeterminable position range. As the safety function module is functionally separated from the remaining components of the vehicle, the extent of possible interdependencies of the safety functions with other components of the vehicle may be reduced or eliminated.
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p.ex. pilote automatique
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
The present embodiment relates to a guided missile launch system comprising a launch tube with a guided missile space for receiving a guided missile and with a cartridge space for receiving a blank cartridge, further comprising a handle piece mountable on the launch tube and separable from the launch tube, the handle piece having a striking pin system for firing the blank cartridge.
An image of a target object may be captured by a method in which the target object is illuminated by a pulsed laser beam emitted by an illumination laser, which beam is aimed at the target object in the form of an illumination beam by an illumination optics unit. The illumination beam laser light reflected from the target object may be received by a receiving optics unit and directed to an image capturing device to generate an image of the target object on the image capturing device. The method may also include detecting the angular offset of the image of the target object with respect to a reference axis of the receiving optics unit, and stabilizing the visual axis of the image capturing device detected by imaging of the target object device by a first optical correcting element of the receiving optics unit that compensates for the angular offset.
G02B 27/64 - Systèmes pour donner des images utilisant des éléments optiques pour la stabilisation latérale et angulaire de l'image
G01S 17/10 - Systèmes déterminant les données relatives à la position d'une cible pour mesurer la distance uniquement utilisant la transmission d'ondes à modulation d'impulsion interrompues
G01S 17/66 - Systèmes de poursuite utilisant d'autres ondes électromagnétiques que les ondes radio
G01S 17/89 - Systèmes lidar, spécialement adaptés pour des applications spécifiques pour la cartographie ou l'imagerie
G02F 1/03 - Dispositifs ou dispositions pour la commande de l'intensité, de la couleur, de la phase, de la polarisation ou de la direction de la lumière arrivant d'une source lumineuse indépendante, p.ex. commutation, ouverture de porte ou modulation; Optique non linéaire pour la commande de l'intensité, de la phase, de la polarisation ou de la couleur basés sur des céramiques ou des cristaux électro-optiques, p.ex. produisant un effet Pockels ou un effet Kerr
An adjustable mounting arrangement to position an object of an optical reflecting telescope relative to a base includes at least two support structures connected to the base and to the object. Each of the at least two support structures has two four-link beams arranged nonparallel to each other and a cradle having two connecting links. Each of the two four-link beams has a first strut and a second strut running nonparallel to each other, where each of the first and second struts have a first end and a second end, respectively, and where each of the first and second struts is mounted with articulation via their respective first end in a corresponding inner joint on the object. The first strut and the second struts are equipped on each of their second ends with a corresponding outer joint, where the outer joints of the two four-link beams are connected to each other via the connecting links such that a distance between the outer joints is less than a distance between the inner joints, and a first and a second joint axis of each four-link beam lie in or at an angle to a plane defined by a corresponding one of the two four-link beams. A third and a fourth joint axis of each four-link beam lie in the plane is defined by a corresponding one of the two four-link beams. Each of the at least two support structures forms a three-dimensional multi-articulated structure comprising the two four-link beams coupled to each other, and each of the two four-link beams is offset to an inner side in relation to a straight line connecting the outer joints, where each of the connecting links is configured with a bearing surface of a support bearing. Finally, each of the at least two support structures is mounted with articulation relative to the base by the support bearing.
G02B 7/182 - Montures, moyens de réglage ou raccords étanches à la lumière pour éléments optiques pour miroirs pour miroirs
G02B 7/183 - Montures, moyens de réglage ou raccords étanches à la lumière pour éléments optiques pour miroirs pour miroirs spécialement adaptés à de très grands miroirs, p.ex. pour l'astronomie
G02B 23/02 - Télescopes ou lunettes d'approche, p.ex. jumelles; Périscopes; Instruments pour voir à l'intérieur de corps creux; Viseurs; Pointage optique ou appareils de visée comprenant des prismes ou des miroirs
11.
Adjustable mounting arrangement for an object to be positioned precisely relative to a base
An adjustable support assembly for an object to be accurately positioned relative to a base, in particular for a secondary mirror of an optical mirror telescope, has at least one support structure connected to the base and to the object. The support structure has at least two struts extending in a non-parallel manner relative to each other, where each strut has associated therewith a drivable actuator element in such a way that the actuator element applies a force onto the strut that deflects the strut transversely to the longitudinal extension thereof. The support structure may be supported in an articulated manner relative to the base.
G02B 7/182 - Montures, moyens de réglage ou raccords étanches à la lumière pour éléments optiques pour miroirs pour miroirs
G02B 7/183 - Montures, moyens de réglage ou raccords étanches à la lumière pour éléments optiques pour miroirs pour miroirs spécialement adaptés à de très grands miroirs, p.ex. pour l'astronomie
G02B 23/02 - Télescopes ou lunettes d'approche, p.ex. jumelles; Périscopes; Instruments pour voir à l'intérieur de corps creux; Viseurs; Pointage optique ou appareils de visée comprenant des prismes ou des miroirs
A stationary test device for a missile includes a retaining device for an avionics testpiece of the missile, where the retaining device enables a movement of the avionics testpiece in three rotational degrees of freedom, and a display device configured to display information on the missile surroundings, where the display device is configured to be moved inside a virtual plane by a translational carriage system. The display device can be detected by the avionics testpiece if the avionics testpiece is disposed on the retaining device. A mobile test device for the missile includes a flight platform, a carrier device mounted on the flight platform, for an avionics testpiece of the missile, wherein the carrier device enables a movement of the avionics testpiece in three rotational degrees of freedom, and a control module, where the control module is configured to control the flight platform for taking off on a specified reference trajectory, control the carrier device for orientation of the avionics testpiece, and store navigation data generated by the avionics testpiece. Finally, a test system for the missile includes the stationary test device and the mobile test device.
An active system includes a transmitting/capturing device having a detection device configured to capture a target object, where the transmitting/capturing device includes a laser source and a camera. The active system also includes a first control system configured to drive a first positioning system to align a beam path between the transmitting/capturing device and the target object, and a second control system configured to drive a second positioning system to align the beam path. The active system further includes a third control system configured to drive a third positioning system to align the transmitting/capturing device, where the third control system has an additional capturing device, and the third positioning system can be driven on the basis of data from the additional capturing device.
G01S 11/14 - Systèmes pour déterminer la distance ou la vitesse sans utiliser la réflexion ou la reradiation utilisant des ondes ultrasonores, sonores ou infrasonores
G01S 17/66 - Systèmes de poursuite utilisant d'autres ondes électromagnétiques que les ondes radio
H04B 10/112 - Transmission dans la ligne de visée sur une distance étendue
G01S 17/02 - Systèmes utilisant la réflexion d'ondes électromagnétiques autres que les ondes radio
14.
Method and device for local stabilization of a radiation spot on a remote target object
A method for local stabilization of a radiation spot on a remote target object, where the radiation spot is formed by a high energy laser beam that is aimed at the target object by a high energy radiation emitter, the includes illuminating the target object is illuminated by an illumination beam that is aimed at the target object by an illumination device. The method also includes receiving, by an image acquisition device, radiation reflected by the target object that is illuminated by the illumination beam, where the radiation reflected by the target object to the image acquisition device passes through the same optical path as the high energy laser beam. An image processing is performed by analyzing and comparing an image of the illuminated target object or part of the illuminated target object acquired by the image acquisition device to at least one image of the illuminated target object or part of the illuminated target object produced at a prior point in time or to an image stored in an object database. And a correction signal is determined, based on the comparison, with which an optical correction device arranged in the optical path passed through by both the high energy laser beam and the reflected radiation is actuated.
A method for local stabilization of a radiation spot formed by a high energy laser beam includes receiving radiation reflected by the target object, where the radiation reflected by the target object passes through the same optical path as the high energy laser beam. An image processing is performed by analyzing and comparing the image of the illuminated target object or part of the illuminated target object to at least one image of the illuminated target object or part of the illuminated target object produced at a prior point in time. A correction signal is computed, with which an optical correction device is actuated. A filter correction signal is produced by a filter device, while a controller correction signal is produced by a fine tracking controller. Finally, the correction signal is formed from the filter correction signal and the controller correction signal.
F41H 13/00 - Moyens d'attaque ou de défense non prévus ailleurs
G02B 26/06 - Dispositifs ou dispositions optiques pour la commande de la lumière utilisant des éléments optiques mobiles ou déformables pour commander la phase de la lumière
H01S 3/00 - Lasers, c. à d. dispositifs utilisant l'émission stimulée de rayonnement électromagnétique dans la gamme de l’infrarouge, du visible ou de l’ultraviolet
A folding fin system includes a fin root and an upper fin part that is rotatably borne on the fin root. The upper fin part may be moved relative to the fin root between an unfolded and a folded position, and wherein the upper fin part and the fin root may be locked relative to one another using a slot-and-key system when the upper fin part is in the unfolded position.
An airborne laser weapon system is divided into a ground-based unit and an airborne unit. The relatively heavy components of the laser weapon system, such as the generator, cooling elements with cooling fluid, accumulators, pump diodes, beam couplers and the control station for an operator, are concentrated and/or arranged in the ground-based part. The relatively lightweight components and/or those that ultimately determine the quality of the laser beam, such as active laser element(s), in particular the output stage(s) thereof, the focusing drive, the telescope and the necessary sensors, may be provided on the airborne platform and may be connected by means of a relatively long, e.g. multiple kilometers, optical waveguide to the ground-based part.
H01S 3/00 - Lasers, c. à d. dispositifs utilisant l'émission stimulée de rayonnement électromagnétique dans la gamme de l’infrarouge, du visible ou de l’ultraviolet
F41H 13/00 - Moyens d'attaque ou de défense non prévus ailleurs
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
H04B 10/25 - Dispositions spécifiques à la transmission par fibres
The present invention relates to a monitoring apparatus for a laser beam, including a body having a passage opening and a sensor that is disposed on the body, wherein impact of the laser beam onto the body can be detected using the sensor.
H01S 3/00 - Lasers, c. à d. dispositifs utilisant l'émission stimulée de rayonnement électromagnétique dans la gamme de l’infrarouge, du visible ou de l’ultraviolet
G01J 1/42 - Photométrie, p.ex. posemètres photographiques en utilisant des détecteurs électriques de radiations
A support structure for an optical reflecting telescope including a beam inlet a primary support for a primary mirror, a secondary support for a secondary mirror, struts which extend between the primary support and the secondary support, and a beam outlet. The support structure has a contour of a single shell hyperboloid. The primary support, the secondary support and the struts are configured so that they support the primary mirror and the secondary mirror so that a z-shaped beam path is provided between the beam inlet, the primary mirror, the secondary mirror and the beam outlet. The struts have identical length.
G02B 23/00 - Télescopes ou lunettes d'approche, p.ex. jumelles; Périscopes; Instruments pour voir à l'intérieur de corps creux; Viseurs; Pointage optique ou appareils de visée
G02B 23/16 - Logements; Couvercles; Montures; Supports, p.ex. avec contrepoids
G02B 7/18 - Montures, moyens de réglage ou raccords étanches à la lumière pour éléments optiques pour miroirs
G02B 7/183 - Montures, moyens de réglage ou raccords étanches à la lumière pour éléments optiques pour miroirs pour miroirs spécialement adaptés à de très grands miroirs, p.ex. pour l'astronomie
G02B 7/182 - Montures, moyens de réglage ou raccords étanches à la lumière pour éléments optiques pour miroirs pour miroirs
G02B 23/06 - Télescopes ou lunettes d'approche, p.ex. jumelles; Périscopes; Instruments pour voir à l'intérieur de corps creux; Viseurs; Pointage optique ou appareils de visée comprenant des prismes ou des miroirs ayant une action de mise au point, p.ex. miroir parabolique
G02B 17/06 - Systèmes catoptriques, p.ex. systèmes redressant et renversant une image utilisant uniquement des miroirs
20.
Laser beam directing system and method for orienting optical components of the laser beam directing system
A laser beam directing system including a first deflection mirror which is connected with an elevation axis of the laser beam directing system; a primary laser which is coupleable into telescope optics by the first deflection mirror; a first auxiliary laser that is oriented in parallel to an azimuth rotation axis of the laser beam directing system; a second auxiliary laser that is oriented parallel to an elevation rotation axis of the laser beam directing system; and a first detector, wherein the first auxiliary laser, the second auxiliary laser and the first detector are arranged and oriented in the laser beam directing system so that the first deflection mirror is alignable by comparing beams of the first auxiliary laser and the second auxiliary laser impacting the first detector so that a beam from the primary laser is coupleable into the telescope optics parallel to the elevation rotation axis.
G02B 26/08 - Dispositifs ou dispositions optiques pour la commande de la lumière utilisant des éléments optiques mobiles ou déformables pour commander la direction de la lumière
G02B 7/182 - Montures, moyens de réglage ou raccords étanches à la lumière pour éléments optiques pour miroirs pour miroirs
A measuring apparatus for measuring the trajectory of a target object includes a receiving device having a primary mirror and a secondary mirror; a first detector for detecting first electromagnetic radiation having a first wavelength and a second detector for detecting second electromagnetic radiation having a second wavelength. The primary mirror is designed to reflect the first electromagnetic radiation and the second electromagnetic radiation and to direct the radiation onto a focal region. The secondary mirror is arranged between the primary mirror and the focal region and is designed to reflect only the second electromagnetic radiation in the direction of the second detector. The first detector is arranged behind the secondary mirror in the focal region of the primary mirror.
G01S 13/06 - Systèmes déterminant les données relatives à la position d'une cible
G01S 13/86 - Combinaisons de systèmes radar avec des systèmes autres que radar, p.ex. sonar, chercheur de direction
H01Q 19/19 - Combinaisons d'éléments actifs primaires d'antennes avec des dispositifs secondaires, p.ex. avec des dispositifs quasi optiques, pour donner à une antenne une caractéristique directionnelle désirée utilisant des surfaces réfléchissantes comportant plusieurs surfaces réfléchissantes comprenant une surface réfléchissante principale concave associée à une surface réfléchissante auxiliaire
G01S 13/58 - Systèmes de détermination de la vitesse ou de la trajectoire; Systèmes de détermination du sens d'un mouvement
A laser illumination unit for illuminating a target object with high-power laser radiation includes multiple rigidly-interconnected laser beam modules that are designed to emit laser radiation and an aiming unit to aim the laser beam modules at the target object. Each of the laser beam modules includes an optical element that is designed to aim laser radiation at a target point of the target object.
A fire control sight for a hand-held firearm includes a sight housing, a front sight, and a sight guide having two sight guide side pieces with a plurality of sight crosspieces forming rear sights. The fire control sight also includes a range finder, at least one inertial sensor and/or a magnetic field sensor, a control computer, and a display device for displaying an optimal orientation of the barrel axis of the hand-held firearm determined by the control computer.
G06G 7/80 - Calculateurs analogiques pour des procédés, des systèmes ou des dispositifs spécifiques, p.ex. simulateurs pour le guidage de missiles
F41G 1/01 - Appareils de visée caractérisés par l'effet visuel créé par la superposition des formes géométriques du guidon et du cran de mire
F41G 1/34 - Appareils de visée de nuit, p.ex. luminescents combinés à une source lumineuse, p.ex. projecteur
F41G 1/473 - Appareils de visée pour utilisations particulières pour l'indication de correction de vitesse ou de distance, p.ex. sur les fusils ou les fusils de chasse
F41G 1/48 - Appareils de visée pour utilisations particulières pour lancer des grenades au moyen de fusils
F41G 3/06 - Dispositifs de pointage avec télémètre
24.
Supply module for supplying an effector system and effector system with a supply module
A supply module for supplying a weapon system includes an electric storage device and a thermal storage device that stores coolant. The supply module also includes at least one electrical connection via which power can be transferred from the electric storage device to the effector system, and at least one thermal connection via which the coolant can be transferred from the thermal storage device to the effector system.
H05K 7/20 - Modifications en vue de faciliter la réfrigération, l'aération ou le chauffage
F41H 13/00 - Moyens d'attaque ou de défense non prévus ailleurs
F28D 20/00 - Appareils ou ensembles fonctionnels d'accumulation de chaleur en général; Appareils échangeurs de chaleur de régénération non couverts par les groupes ou
H01M 10/613 - Refroidissement ou maintien du froid
F28D 20/02 - Appareils ou ensembles fonctionnels d'accumulation de chaleur en général; Appareils échangeurs de chaleur de régénération non couverts par les groupes ou utilisant la chaleur latente
H01M 10/0525 - Batteries du type "rocking chair" ou "fauteuil à bascule", p.ex. batteries à insertion ou intercalation de lithium dans les deux électrodes; Batteries à l'ion lithium
F28D 15/00 - Appareils échangeurs de chaleur dans lesquels l'agent intermédiaire de transfert de chaleur en tubes fermés passe dans ou à travers les parois des canalisations
H01S 3/0941 - Procédés ou appareils pour l'excitation, p.ex. pompage utilisant le pompage optique par de la lumière cohérente produite par un laser à semi-conducteur, p.ex. par une diode laser
H01S 3/04 - Dispositions pour la gestion thermique
F28D 21/00 - Appareils échangeurs de chaleur non couverts par l'un des groupes
25.
Illumination device and method for controlling the illumination device
An illumination device for illuminating a target to be combated includes a laser light source for emitting light along a beam path, a first modulator in the beam path and configured to manipulate a direction of the beam path in a first plane, a phase plate in the beam path having a variety of different optical thicknesses, and a control device connected to the light source and the first modulator and is configured to activate the first modulator using different frequencies, so that the beam path is deflected over a control period of time up to a first angle.
G02F 1/33 - Dispositifs de déflexion acousto-optique
G02B 27/48 - Systèmes optiques utilisant la granulation produite par laser
G01S 7/481 - Caractéristiques de structure, p.ex. agencements d'éléments optiques
G01S 17/89 - Systèmes lidar, spécialement adaptés pour des applications spécifiques pour la cartographie ou l'imagerie
G01S 17/10 - Systèmes déterminant les données relatives à la position d'une cible pour mesurer la distance uniquement utilisant la transmission d'ondes à modulation d'impulsion interrompues
A radiation emitter includes a device for coupling radiation from at least one radiation generator and a radiation combining device that combines the radiation to bundled radiation. The radiation combining device includes a telescopic optic with a collimation reflector and a secondary reflector. The radiation combining device is configured to accept directional radiation from a plurality of light conducting devices from at least one radiation generator.
B23K 26/06 - Mise en forme du faisceau laser, p.ex. à l’aide de masques ou de foyers multiples
F41H 13/00 - Moyens d'attaque ou de défense non prévus ailleurs
H01S 3/00 - Lasers, c. à d. dispositifs utilisant l'émission stimulée de rayonnement électromagnétique dans la gamme de l’infrarouge, du visible ou de l’ultraviolet
A load test stand includes a frame, a flange, and a spring mechanism. The spring mechanism is mounted on the frame and includes a symmetrical arrangement of at least four spring elements. The spring mechanism also includes frame points connecting the spring mechanism and the frame and articulation points connecting the spring mechanism and the flange. The flange can be coupled, by an adapter, to the output shaft of a servo system that is to be tested.
A beam focusing unit for a laser weapon system includes a laser generating unit, an output element unit, and a beam optics element. The beam focusing unit includes a stationary/partly movable part and a fully movable part. The stationary/partly movable part is adapted for positioning or for transporting the beam focusing unit between operations. The fully movable part is adapted for targeting and target-following of the laser weapon system. The beam optics element and the at least one output element unit is arranged on the fully movable part.
A digital filter for reducing a sampling rate for an input signal includes a parallelizing block for splitting the input signal into at least two parallel raw signals, an integration block for converting the parallel raw signals into an intermediate signal, and a differentiation block for generating an output signal by differentiating the intermediate signal. The integration block includes a logic block that is designed for generating two parallel sum signals from the parallel raw signals using summation operations, and a recursion block that is designed for generating the intermediate signal recursively from the parallel sum signals.
A device for testing and/or operating an effector unit for acting on a target includes a positioner unit for moving the effector unit and a control unit for driving the positioner unit. The control unit is configured to simulate and/or to damp the accelerations of a carrier platform, on which the device can be mounted under real conditions, by means of the positioner unit.
G06F 19/00 - Équipement ou méthodes de traitement de données ou de calcul numérique, spécialement adaptés à des applications spécifiques (spécialement adaptés à des fonctions spécifiques G06F 17/00;systèmes ou méthodes de traitement de données spécialement adaptés à des fins administratives, commerciales, financières, de gestion, de surveillance ou de prévision G06Q;informatique médicale G16H)
G05D 1/10 - Commande de la position ou du cap dans les trois dimensions simultanément
F41H 13/00 - Moyens d'attaque ou de défense non prévus ailleurs
Unmanned missile and method for releasing the unmanned missile from a carrier aircraft, in which the missile has an autonomous flight control device that acts on control devices of the missile. The method includes adjusting vertical rudders and elevators of the missile into a neutral position in which a respective rudder angle is 0°, separating electrical and mechanical connections between the missile and the carrier aircraft, and detecting, via sensors of the missile, that the separating has occurred. The method also includes activating the autonomous flight control device and automatically controlling the missile with the flight control device and the control devices based upon correction flight condition variables caused by a prevailing downwash between the missile and the carrier aircraft, and automatically controlling the missile with the flight control device and the control devices based on data stored in at least one storage device on the missile.
A method for automatically generating a three-dimensional reference model as terrain information for a seeker head of an unmanned missile. A three-dimensional terrain model formed from model elements obtained with the aid of satellite and/or aerial reconnaissance is provided. Position data of the imaging device at least at one planned position and a direction vector from the planned position of the imaging device to a predetermined target point in the three-dimensional terrain model are provided. A three-dimensional reference model of the three dimensional terrain model is generated that incorporates only those model elements and sections of model elements from the terrain model, which in the viewing direction of the direction vector from the planned position of the imaging device, are not covered by other model elements and/or are not located outside the field of view of the imaging device.
G01S 3/786 - Systèmes pour déterminer une direction ou une déviation par rapport à une direction prédéterminée utilisant le réglage d'une orientation des caractéristiques de directivité d'un détecteur ou d'un système de détecteurs afin d'obtenir une valeur désirée du signal provenant de ce détecteur ou de ce système de détecteurs la valeur désirée étant maintenue automatiquement
A device for launching unmanned missiles from an aircraft with a pallet, on which at least one container is provided to receive a missile. The container has an upper container section that has a pylon for the suspended, detachable support of the missile. The container has a lower container section that is embodied as a support area for the missile.
brevets
