The invention is related to a system that provides information about the characteristics of the target to be hit by means of the laser marking code in laser guided missile systems, and the method thereof. With the invention, the characteristics of the target to be hit can be defined before or after firing in laser guided missile systems.
The invention relates to a device that provides a more homogenised flow characteristic in both directions by periodically changing the rotation direction of the swirling flow to be used in rocket injectors, fluid distributing components such as shower heads, and to be used as an aerodynamic flow control actuator.
The invention relates to a durable explosive reactive armour in the form of a modular, light, and flexible fabric bag that can be transported and assembled easily,as a joint add-on protection for all military land vehicles, including light armoured vehicles, to protect vehicles and personnel from munitions containing a shaped charged warhead and to reduce the collateral damage.
The invention relates to a liquid fuel rocket engine test setup that ensures the accuracy of the data received from the load cell during the test by calibrating the load cell used in the static ignition test of the liquid fuel rocket engine with full automation.
G01L 25/00 - Test ou étalonnage des appareils pour la mesure des forces, du couple, du travail, de la puissance ou du rendement mécanique
G01L 5/13 - Appareils ou procédés pour la mesure des forces, du travail, de la puissance mécanique ou du couple, spécialement adaptés à des fins spécifiques pour la mesure de la puissance de traction ou propulsive des véhicules
B64G 1/36 - Appareils de guidage ou de commande, p.ex. de commande d'assiette par des capteurs, p.ex. par des capteurs solaires, des capteurs d'horizon
G01S 3/78 - Radiogoniomètres pour déterminer la direction d'où proviennent des ondes infrasonores, sonores, ultrasonores ou électromagnétiques ou des émissions de particules sans caractéristiques de direction utilisant des ondes électromagnétiques autres que les ondes radio
G01C 21/02 - Navigation; Instruments de navigation non prévus dans les groupes par des moyens astronomiques
6.
DETONATION TRANSFER MODULE AND OPERATING METHOD THEREOF
The invention relates to a multi-input, single-output detonation transfer module that can be used in intelligent explosive reactive armour (ERA-Explosive Reactive Armour) systems and military counter-protection systems, and its operating method thereof.
The invention relates to a towed communication and observation vehicle that enables underwater vehicles to communicate, locate and observe without coming up/approaching the water surface.
H04B 13/02 - Systèmes de transmission dans lesquels le milieu de propagation est constitué par la terre ou une grande masse d'eau la recouvrant, p.ex. télégraphie par le sol
8.
INERTIAL MEASUREMENT UNIT COMPRISING A BODY WITH A LATTICE STRUCTURE AND A SENSOR BLOCK
The invention relates to inertial sensor technologies. In particular, the invention relates to a system comprising mechanical solutions for a low-mass inertial sensor unit that is resistant to environmental influences such as vibration and thermal shock.
G01C 21/16 - Navigation; Instruments de navigation non prévus dans les groupes en utilisant des mesures de la vitesse ou de l'accélération exécutées à bord de l'objet navigant; Navigation à l'estime en intégrant l'accélération ou la vitesse, c. à d. navigation par inertie
F16F 15/02 - Suppression des vibrations dans les systèmes non rotatifs, p.ex. dans des systèmes alternatifs; Suppression des vibrations dans les systèmes rotatifs par l'utilisation d'organes ne se déplaçant pas avec le système rotatif
9.
INTER-COMPONENT TIME SHIFT ESTIMATION AND SIGNAL ALIGNMENT METHOD FOR HARDWARE AND SOFTWARE INTEGRATED SIMULATIONS
The invention relates to the ability to estimate data and signal delays between hardware and software components in real-time and with high precision. In order to estimate the communication delay and to protect the simultaneous transactions in the system from the negative effects of the delay, input and output data, depending on the Master-Slave topology, are created in which the delay between computers that are physically far from each other, but that are on the same communication network (101) are definitely monitored.
ABLATIVE THERMAL INSULATION MATERIALS WITH ABLATION PERFORMANCE IMPROVED BY SILICA FABRIC REINFORCEMENT DEVELOPED FOR MOTOR CASE INSULATION OF SOLID PROPELLANT ROCKETS WORKING IN HIGHLY EROSIVE REGIME
The present invention relates particularly to an ablative thermal insulation material with increased erosion performance comprising EPDM rubber material containing organic reinforcement increasing erosion resistance, inorganic reinforcement increasing char yield, increasing adhesion, process facilitating chemicals and oils, and curing system with and sulphur curing agent, and the silica fabric combined with this rubber layer, developed for use in high erosion areas of solid propellant rocket motor with vortex or high velocity flow, and to the production method thereof.
The present invention relates to an angle measurement device that allows measuring the variation of the yaw, pitch and rolling angles from three axes of a reflective surface placed at a certain distance.
The present invention relates to a gradual range correction mechanism that is designed to reduce the diversion that occurs in the range in firing of the high-spin artillery ammunition, that corrects the range error by increasing the air fraction with the opening of the brake plates on the air, thereby decelerating it gradually. The present invention particularly relates to a gradual range correction mechanism that is based on the ability of correcting the range by gradually increasing the front surface area of the ammunition more than once during flight, depending on the aerodynamic effects and the need for correcting, that basically consists of brake plates, retainer pins, guide, single-grade rotating part, and pin pulling mechanisms.
This invention relates to a system that harvests the energy of the electronic units used in fuse systems by using the separate environmental conditions.
H02H 3/10 - Circuits de protection de sécurité pour déconnexion automatique due directement à un changement indésirable des conditions électriques normales de travail avec ou sans reconnexion sensibles à une surcharge sensibles de plus à quelque autre condition électrique anormale
15.
VIBRATION DAMPENING CONNECTION SYSTEM IN THE FORM OF A RUBBER WASHER FOR INERTIAL MEASUREMENT SYSTEMS
The invention relates to a vibration dampening connection system in the form of a rubber washer to protect the inertial sensor assembly to be placed therein from distorting environmental effects such as vibration or mechanical shock.
F16F 15/04 - Suppression des vibrations dans les systèmes non rotatifs, p.ex. dans des systèmes alternatifs; Suppression des vibrations dans les systèmes rotatifs par l'utilisation d'organes ne se déplaçant pas avec le système rotatif utilisant des moyens élastiques
The invention relates to a seeker working in three wavelengths and comprising a compact structure. In particular, the invention relates to seeker that enables the seeker to work in all infra-red bands simultaneously by separating three different wavelengths (SWIR, MWIR and LWIR) into three different detectors by means of the pentagon having a selectively permeable coating.
This invention relates to a system that enables obtaining multiple field of view points by applying different voltage differences with a single optic structure.
This invention relates to an isolation box ensuring the protection of inertial sensors from destructive environmental effects such as vibration, mechanical shock and thermal shock.
The present invention is a polymethacrylimide foam production method that comprises the process steps of; uniformly mixing a reactant that contains 30-80% methacrylic acid by weight, and 20-70% acrylonitrile by weight, and 1-3% acrylamide by weight, or a mixture of derivatives thereof, and the components that contain a polymerization initiator, a nucleating agent and a foaming agent such that it forms a reaction mixture; obtaining a crosslinked foamable pre-polymerization product by means of exposing the reaction mixture to UV light during a pre-polymerization, and molding the pre-polymerization product, and curing it at 100-260°C until polymethacrylimide foam is obtained by polymerization such that it forms a crosslink, and the polymer foam that is obtained by means of this method.
The present invention relates to a bearing assembly with spin stabilizer capable of bringing the spinning motion of the missile under control on the roll axis on the rest of the missile by spinning the rear fins relative to the missile by means of the bearings located on guided missiles. The present invention particularly relates to a bearing assembly with spin stabilizer that provides spin stabilization on the roll axis of a missile that is launched with high velocity and without being spun from a smoothbore tube system and that operates with a supersonic speed regime throughout a certain period of its flight time.
The present invention relates to a distance measurement system that allows for measuring the altitude of a missile with respect to the surface of the earth by means of applying microwave radio-frequency radiation to the surface of the earth over the missile and by processing the signals reflected from the surface and a method thereof.
The present invention relates to a system that renders a torpedo ineffective that is caught by a net by means of being used by surface and underwater platforms against a torpedo or a similar threat.
The invention relates to a test assembly so as to determine the effect of shoulder-launched ammunition on the shooting personnel. The test device comprises a model body (1) having a fixing apparatus (8) at the shoulder part so as to adapt ammunition (1)
The present invention relates to a distributed missile system having multiple miniature missile units (n) comprising the following; an elongated body (10) with a warhead (11); a drive motor (12) fixed to the body (10); a fin (14) that is provided in the body (10) and that rotates the body (10) towards a predetermined course during the cruise by being driven with the drive motor (12) and a controller (40) connected to the drive motor (12) to control the fin (14) position. The missile system comprises at least one relative awareness sensor (30) that scans the outer periphery of the body (10) by collecting 360° environmental awareness data (v) and transmits a signal to the controller (40).
A nozzle protection system for a rocket-propelled projectile comprising an adapter body (10) that limits an opening (16) centered on a propulsion axis (x) and that has a structure, which allows it to be attached to a rocket nozzle (1) from an inner part thereof by means of a connection interface (11); a cover (60) that is mounted on adapter body (10) from an outer part thereof such that it covers a hole (64) in a protection position; a cartridge (20) that is fixed to a distal end of the adapter body (10) from a circumferential connection end (28) such that it detaches upon firing and such that a pressure chamber (24), which is adjacent to a trigger-activated explosive chamber (22), faces a front wall (66) of the cover (60). The nozzle protection system further comprises at least one rotary curtain (30, 40) that is equipped with a hinge assembly (50) that is positioned such that the cover (60) serves as a block in front of the hole (64) when in a protection position and that is rotatably adjusted such that it gets out of the way of the hole (64) once the cartridge (20) is separated.
F42B 10/18 - Dispositions pour la stabilisation utilisant des ailettes qui sont déployées après le lancement, p.ex. après la sortie du tube de l'arme les ailettes étant montées sur un support, susceptible de coulisser longitudinalement
F42B 10/20 - Dispositions pour la stabilisation utilisant des ailettes qui sont déployées après le lancement, p.ex. après la sortie du tube de l'arme déployées par la pression des gaz de combustion, ou par des forces hydrauliques ou pneumatiques
F42B 10/40 - Dispositions pour augmenter la portée par la combustion d'une charge à vitesse de combustion lente, p.ex. projectiles du type à écoulement par le culot
27.
A SEMI-ACTIVE LASER SEEKER FOR MINIATURE, LASER-GUIDED MISSILE SYSTEMS
The present invention relates to a semi-active laser seeker head for miniature, laser-guided missile systems comprising a housing (20) limiting an inner chamber (23); a lens element (40) that is seated in a gap (26) of the housing (20) reaching the inner chamber (23) so as to receive electromagnetic radiation. The laser seeker head comprises; a body (44) that has a convex surface (42) on which the lens element (40) gets completely seated in a gap (26) on one hand and that extends into the inner chamber (23) on the other hand; and a filter (52) that directly receives the electromagnetic radiation, which is focused by the convex surface (42), from the body (44) that lies before and selectively transfers it to a multi-channel sensor (56) arranged at the rear portion thereof based on a predetermined wavelength threshold.
The present invention relates to a control actuation assembly for a miniature, guided missile comprising a seat (20) having a support plate (22) that is transversally mounted to an inner chamber limited by a hollow, elongated main body (10); and at least one wing pair (40) having first and second aerodynamic control members (41, 43) that are adjacent to one another such that a distal end (47) thereof is seated into the inner chamber when it is in a folded position, and that are opposite to one another, that are supported by the seat (20) by means of respective pins (44) fixing them on an extension axis from a proximal end (46) thereof such that it extends outward from the main body (10) when in a deployment position. Control actuation system comprises a threaded rod member (65) that is arranged in close proximity of the wing pair (40) and that converts the shaft (64) linear motion of motor (60), which comprises a shaft (64) that extends towards the wing pair (40) inside the inner chamber, to rotational motion on the shaft (64) axis; and a pendulum arm (82) that is adapted on the wing pair (40) such that it rotates on the pin (44) axis on one hand and that it is seated therein so as to rotate a protrusion (66) of the threaded rod member (65), which extends outwards radially on the other hand.
The present invention relates to an electronic safety, arming and firing system for missiles comprising a central controller (20); a power conditioner (12) supplied from a power distribution unit (50) and comprising at least one storing capacitor (13) adapted to supply power to the central controller (20) in case of power cut-off; an accelerometer unit (16) adjusted to provide acceleration information to the central controller (20) designed as a microelectro-mechanical system (MEMS). The system further comprises an ignition unit (18) that is connected to trigger a low-energy foil detonator (70) through an activation signal and through which the central controller (20) controls an activation signal and a high-voltage ignition capacitor (19) adjusted to charge a voltage to the ignition unit (18) in a value range of 1600-1300 volts to activate the low-energy foil detonator (70) by means of the activation signal.
F42C 15/18 - Dispositifs d'armement des fusées; Dispositifs de sécurité pour empêcher l'explosion prématurée des fusées ou des charges dans lesquels le support d'un élément de la chaîne pyrotechnique ou explosive est mobile
F42C 15/40 - Dispositifs d'armement des fusées; Dispositifs de sécurité pour empêcher l'explosion prématurée des fusées ou des charges dans lesquels l'action de sécurité ou d'armement s'effectue électriquement
30.
LASER-GUIDED MINIATURE MISSILE SYSTEM FOR HYBRID THREATS
The present invention relates to a laser-guided miniature missile system comprising a launch station (70); and a miniature missile (30) that is provided in said launch station (70), that has an elongated body (32) configured such that it may be launched from a canister (10) or a launch pod (20). The inventive miniature missile system comprises; a remote control station (80) that is connected such that it communicates by means of an RF receiver/transmitter (74) of the launch station (70) accommodated on a mobile vehicle (1) and an opposite RF receiver/transmitter (82); a central controller (72) that triggers a canister (10) or a launch pod (20) such that they launch the miniature missile (30) by means of a pod control member (76) driven by determining a launch command transmitted from the control station (80) to the launch station (70); and a flight controller (38) to the which the central controller (72) is connected such that said central controller (72) ensures signal transmission in a storage mode and that is mounted on the body (32) that activates a flight motor (38) at a predetermined flight motor activation time (t2) by being configured such that it can interrupt the signal communication with the central controller (72) subsequent to a launching moment (t0).
The present invention relates to a miniature missile system having a hollow grenade launcher barrel (10) equipped with a trigger (2) and also a miniature missile (30) with a body (32) positioned on the barrel (10). Said missile system comprises a launching capsule (20) with a powder chamber (22) adjusted, such that it is provided at the rear portion (14) of the barrel (10) and creates a launching pressure area (23) allowing for raising the body (34) up to an effective flight height (h) from the barrel (10) in a ground level at the rear portion of the body (32), when activated by the trigger (2). Said miniature missile (30) comprises a flight controller (38) configured to actuate a flight motor (34) at the rear portion of the body (34), when reached up the flight height (h).
The present invention is a multi-barrel rocket launcher pod comprising a front frame (20); a rear frame (10) that is positioned spaced from the front frame (20); a monobloc body (30) that is made of cured polymeric resin and that extends adjacent to and between the front frame (20) and the rear frame (10) along a partition line (16); a plurality of cylindrical conduits (40) that are positioned spaced from one another and that extend longitudinally inside the monobloc body (30) such that they define the launch tubes. In the inventive rocket launcher pod, each of the inner walls (42) of said cylindrical conduits (40) inside the monobloc body (30) are formed directly from the cured resin of the monobloc body (30).
The present invention relates to a bolt connection apparatus (12) for the purpose of the ammunition-canister connection, which is fastened to an ammunition connection component (3) connected with an ammunition body (10) by way of extending over a flange (2) connected with a canister.
F16B 35/00 - Boulons filetés; Boulons d'ancrage; Goujons filetés; Vis; Vis de pression
F16B 43/02 - Rondelles ou dispositifs équivalents; Autres dispositifs de support pour têtes de boulons ou d'écrous avec dispositions particulières pour engager les surfaces qui ne sont pas perpendiculaires à l'axe du boulon ou qui n'entourent pas celui-ci
F42B 39/22 - Blocage des munitions dans leurs emballages de transport
F42B 15/36 - Moyens de liaison entre le moteur-fusée et le corps d'une roquette; Raccords pour relier les différents étages d'une roquette; Moyens de désassemblage
34.
IN-CANISTER TYPE COLLAPSIBLE MISSILE FASTENER MECHANISM
The present invention is a collapsible support mechanism, which comprises a front arm assembly (2) and a rear arm assembly (3) rotatably hinged to a base assembly (1) from each lower end and to a movable plate assembly (5) from each upper end and designed to fasten missile in the canister, wherein the movable plate assembly (5) is seated on the base assembly (1) by being collapsed on the front arm assembly (2) and rear arm assembly (3) in an unlocked position and is elevated in a supporting position, such that the movable plate assembly (5) provides a distance between the base assembly (1) and movable plate assembly (5).
The present invention relates to an ablative insulation coating formulation that can be applied through a spraying method on at least one exterior surface of metal components of missile systems and features a low thermal conductivity. Said formulation comprises at least one solvent; at least one epoxy-novolac based resin; at least one insulating filler material selected from a group comprising vermiculite, fumed silica, a dried mushroom powder, phenolic micro balloon and/or combinations thereof, at least one flame-retardant material comprising the mixture of ammonium polyphosphate and/or boric acid; a hardening agent; at least one diluting agent and at least one bonding silicone resin.
The invention is an underwater location detection assembly for an underwater system which is provided on an underwater body (10) and comprises a casing (12) having a laser transmissive section (14), characterized in that, it comprises a laser source (16) which is adjusted to a predetermined power output value (P) forming an indicator (45) with the refraction of a laser beam (40) that travels underwater (20) on the surface (22) of the water body (24) in which the underwater body (10) is submerged and is positioned in a casing (12) by being aligned to the laser transmissive section (14) and a controller (11) which activates the laser source (16) in a location detection mode.
G01S 17/88 - Systèmes lidar, spécialement adaptés pour des applications spécifiques
G01C 3/00 - Mesure des distances dans la ligne de visée; Télémètres optiques
G01C 21/00 - Navigation; Instruments de navigation non prévus dans les groupes
G01B 21/00 - Dispositions pour la mesure ou leurs détails, où la technique de mesure n'est pas couverte par les autres groupes de la présente sous-classe, est non spécifiée ou est non significative
G06F 17/40 - Acquisition et consignation de données
G01S 1/76 - Systèmes pour déterminer une direction ou une ligne de position
The present invention relates to a vibration isolator (10), which is arranged identically and adjacently in multiple numbers on the adapter (3), comprises an upper connector (20) adjusted to be connected to a payload (2) placed on an adapter (3) provided on a launch vehicle (1) and lower connector (40) adjusted to be connected to the adapter (3). A vibration isolator (10) comprises respectively, a carrier arm (24) and a support arm (44) having a mounting part (22, 42) provided on one of the proximal ends (26, 46) of which upper connector (20) and the lower connector (40) have them opposingly and it further comprises an elevator element (30) having an elevator arm (34) extending between each of their distal ends (28, 48) so as to fix the carrier arm (24) and the support arm (44) at a certain distance from each other.
F16F 15/04 - Suppression des vibrations dans les systèmes non rotatifs, p.ex. dans des systèmes alternatifs; Suppression des vibrations dans les systèmes rotatifs par l'utilisation d'organes ne se déplaçant pas avec le système rotatif utilisant des moyens élastiques
The present invention relates to a cover for a canister comprising an outer frame (24) and a front plate (20) with at least one wing (30) extending radially inwards from the outer frame (24); a coating layer (50) made of a flexible tearable material coating the front plate (20) along the outer frame (24) in a sealing manner. The cover comprises a hinge (26) in the form of a metal plate integrated with the outer frame (24) by way of adjusting the neck portion (38), through which the wing (30) is engaged with the outer frame (24) when a predetermined threshold force value (fe) is exceeded.
Invention relates to a laser source simulator for a laser seeking ammunition head comprising a LED light source configured to emit light in IR wavelength in a firing mode; an oscillator driving the LED light source in a predefined pulse repetition frequency; an electronic control unit connected to the oscillator in a signal transmitting manner and a casing (10) having an output from which an infra- red light in pulse repetition frequency is radiated. The laser pulse source simulator comprises an output energy magnitude controller is configuring LED light source to define a short reflection pulse and a subsequent longer target pulse in predefined magnitude and repetition by means of an electronic control unit in a firing mode.
Invention relates to a wing folding mechanism for a pair of wings comprising a lower wing (5) and a co-operative upper wing (6) extending opposite to each other in a deployment position and approach each other when rotated from respective remote ends to a resting position. According to the invention, a spherical rolling element slots (10) is adapted to receive a number of uniform spherical rolling elements provided at a corresponding lower wing root (20) and a upper wing root (21) so that allowing lower wing (5) and upper wing (6) extending symmetrical to each other; plurality of spherical rolling elements (3) are disposed at the spherical rolling element slot (10); an alignment element(2) is positioned in coaxially with a wing pin hole (18) and linear energy storage element (4) arranged in a such manner that release the stored energy accrued during the folding of the wings and disposed around the alignment element (2) to exert a pressing force to the upper wing (6).
brevets
