USING A PASSIVE SEPARATOR TO SEPARATE AIR AND FUEL OF A FUEL MIXTURE PASSIVELY WHEN DELIVERING FUEL TO A COMBUSTION ENGINE OF AN UNMANNED AERIAL VEHICLE
A fuel delivery system has a tank, a fuel pump, and an air filtering apparatus coupled with the tank and the fuel pump. The air filtering apparatus includes a housing that defines a housing chamber, a fuel flow controller coupled with the housing, and a passive separator disposed within the housing chamber. The passive separator is constructed and arranged to separate air and fuel of a fuel mixture passively while the fuel mixture enters the housing chamber from the tank and while filtered fuel exits the housing chamber toward the fuel pump in response to operation of the fuel flow controller. Such a system is well-suited for supplying fuel to a combustion engine in which consistent fuel pressure may be critical. Furthermore, the passive separator alleviates the need for a power source for active air and fuel separation, a control mechanism, and so on.
F02M 37/54 - Dispositions d'épuration du combustible liquide spécialement conçues pour les moteurs à combustion interne ou aménagées sur ceux-ci, p.ex. aménagées dans le système d'alimentation caractérisées par des moyens pour purger l’air
F02M 37/46 - Filtres associés structurellement à des régulateurs de pression
F02M 37/48 - Filtres associés structurellement à des soupapes de combustible
B64D 37/34 - Conditionnement du carburant, p.ex. réchauffage
F02M 37/00 - Appareils ou systèmes pour transférer le combustible liquide des réservoirs de stockage aux carburateurs ou aux injecteurs; Dispositions d'épuration du combustible liquide spécialement conçues pour les moteurs à combustion interne ou aménagées sur ceux-ci
2.
CASED TELESCOPED AMMUNITION FIREARM WITH TRANSLATING CHAMBER
A weapon (10) for firing cased telescoped (CT) ammunition includes a barrel (12), a chamber assembly (42) with a chamber member (54) and a carrier assembly (38). The chamber member defines a chamber for a CT round for firing, and translates between a firing position aligned with the barrel and an ejection/loading position. The chamber member is spring-biased toward the firing position. The carrier assembly carries the firing pin (104) and performs a recoil in which a carrier and rammer (114) move rearward from a battery position to bring the next CT round into a ramming position and to move the chamber member from the firing position to the ejection/ loading position, and performs a counter-recoil to return to the battery position and cause the rammer to push the next CT round into the chamber. The chamber member is released for biased return to the firing position for a next firing cycle.
F41A 9/45 - Dispositions pour le chargement, c. à d. pour amener les munitions en position de tir la chambre de cartouche ou le tube de l'arme basculant en entier d'une position de chargement vers une position de tir et vice versa
F41A 3/26 - Mécanismes à verrous rigides, c. à d. les éléments de verrouillage formant un assemblage rigide avec, respectivement, le bloc de culasse ou son levier de manœuvre, et le tube de l'arme ou la boîte de culasse les verrous tournant autour de l'axe du tube de l'arme, p.ex. verrous de culasse cylindriques rotatifs à action semi-automatique ou automatique, p.ex. le bloc de culasse comportant un support coulissant et une tête rotative
F41A 3/30 - Eléments de verrouillage, p.ex. tenons de verrouillage, filets de vis
F41A 9/23 - Plateaux ou augets mobiles de chargement des munitions, p.ex. pour l'alimentation à partir de chargeurs coulissants, p.ex. à mouvement de va-et-vient montés dans une arme individuelle
F41A 21/12 - Chambres de cartouche; Chemisage intérieur des chambres de cartouche
F41A 15/00 - Extracteurs de cartouche, c. à d. dispositifs pour retirer les cartouches ou les douilles au moins partiellement de la chambre de cartouche; Ejecteurs de cartouche, c. à d. dispositifs pour éjecter les cartouches ou les douilles retirées de l'arme à feu
F42B 5/045 - Cartouches, c. à d. projectile et douille avec charge propulsive formant un tout du type télescopique
F41A 5/18 - Mécanismes ou systèmes automatiques de déverrouillage de la culasse à l'aide d'une force créée par une charge propulsive par emprunt des gaz
An aircraft employs articulated, variable-position electric rotors having different operating configurations and transitions therebetween, as well as variable-pitch airfoils or blades, for generating vectored thrust in the different configurations. Control circuitry generates rotor position signals and blade pitch signals to independently control rotor thrust, rotor orientation and rotor blade pitch of the variable-position rotors in a manner providing (i) the transitions among the operating configurations for corresponding flight modes of the aircraft, which may include both vertical takeoff and landing (VTOL) mode as well as a forward-flight mode, and (ii) commanded thrust-vectoring maneuvering of the aircraft in the different configurations, including tailoring blade pitch to optimize aspects of aircraft performance.
A weapon for firing cased telescoped (CT) ammunition includes a barrel. a chamber cavity aligned with the barrel, and a translating chamber member defining a chamber for holding a CT round for firing. The chamber member moves between a firing position in the chamber cavity and an ejection/loading position for ejecting a spent CT round and receiving a next CT round. A breech member closes a rear end of the chamber. A carrier performs a counter-recoil operation in which (1) the chamber member is moved from the ejection/loading position to the firing position with the next CT round therein, and (2) the breech is urged into a closed position against the next CT round in the chamber to remove headspace before the next CT round is fired from the weapon.
5.
VTOL AIRCRAFT HAVING FIXED-WING AND ROTORCRAFT CONFIGURATIONS
An aircraft includes an airframe having a fixed-wing section and a plurality of articulated electric rotors, at least some of which are variable-position rotors having different operating configurations based on rotor position. A first operating configuration is a vertical-flight configuration in which the rotors generate primarily vertical thrust for vertical flight, and a second operating configuration is a horizontal-flight configuration in which the rotors generate primarily horizontal thrust for horizontal fixed-wing flight. Control circuitry independently controls rotor thrust and rotor orientation of the variable-position rotors to provide thrust-vectoring maneuvering. The fixed-wing section may employ removable wing panels so the aircraft can be deployed both in fixed-wing and rotorcraft configurations for different missions.
A firearm for firing cased telescoped (CT) ammunition cartridges that includes a split chamber configured to fully support a CT cartridge when it is fired, and that includes i) a dynamic rear chamber portion (106) defining a pocket (108) in a face of a bolt (110), and ii) a static front chamber portion (112) that is integral to the barrel (100) and separate from the bolt. A cartridge extraction mechanism (116) engages the CT cartridge prior to the CT cartridge being fired, and holds the CT cartridge in the pocket in the bolt face as the bolt moves rearward to pull the CT cartridge out of the static front chamber portion and into an ejection position. An ejector (114) is operable to eject the CT cartridge from the pocket in the face of the bolt when the CT cartridge reaches the ejection position.
F41A 9/46 - Dispositions pour le chargement, c. à d. pour amener les munitions en position de tir la chambre de cartouche étant formée de deux éléments complémentaires, mobiles l'un par rapport à l'autre en vue du chargement
F41A 15/04 - Extracteurs de cartouche, c. à d. dispositifs pour retirer les cartouches ou les douilles au moins partiellement de la chambre de cartouche; Ejecteurs de cartouche, c. à d. dispositifs pour éjecter les cartouches ou les douilles retirées de l'arme à feu spécialement adaptés pour retirer des douilles qui ont été déformées pendant le tir, p.ex. des douilles en matière plastique
F41A 15/14 - Extracteurs de cartouche, c. à d. dispositifs pour retirer les cartouches ou les douilles au moins partiellement de la chambre de cartouche; Ejecteurs de cartouche, c. à d. dispositifs pour éjecter les cartouches ou les douilles retirées de l'arme à feu pour des armes à feu à culasse mobile axialement l'éjecteur étant monté sur ou dans le bloc de culasse
F41A 3/26 - Mécanismes à verrous rigides, c. à d. les éléments de verrouillage formant un assemblage rigide avec, respectivement, le bloc de culasse ou son levier de manœuvre, et le tube de l'arme ou la boîte de culasse les verrous tournant autour de l'axe du tube de l'arme, p.ex. verrous de culasse cylindriques rotatifs à action semi-automatique ou automatique, p.ex. le bloc de culasse comportant un support coulissant et une tête rotative
7.
MAGAZINE FOR CASED TELESCOPED AMMUNITION CARTRIDGES WITH SIDE-WALLS HAVING CARTRIDGE ORIENTATION RIBS
A magazine (100) for storing cased telescoped (CT) cartridges. The magazine includes vertically extending side-wall ribs (110, 112) that project inwards into a loading channel. The side-wall ribs are positioned in alignment with a circumferential groove (202) in each CT cartridge. The side-wall ribs prevent a backwards oriented CT cartridge from being pushed from the loading position through the loading channel into a body of the magazine. A moveable lip (1404) at the top of the magazine may move out of the way when the magazine is attached to a firearm, to allow the CT cartridge located in the loading position to be fed vertically out of the top of magazine. Each CT cartridge may include a thermal protective insert that provides thermal insulation from heat emanating from a barrel of a firearm when the CT cartridge is located in a chamber of the firearm.
A technique for adaptively disrupting UAVs detects a target UAV using a camera, monitors the target UAV's communications using a directional antenna aligned with the camera, and attempts to communicate with the target UAV to request that it land, fly away, or return to launch. With the camera trained on the UAV, the directional antenna detects down-link signals from the UAV, which the UAV may employ to communicate with a ground-based controller. Control circuitry analyzes the down-link signals and generates a disrupting signal based thereon. The disrupting signal shares characteristics with the down-link signal, such as its protocol, bit rate, and/or packet length. The directional antenna transmits the disrupting signal back toward the UAV to affect the UAV's flight.
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
F41H 11/02 - Installations ou systèmes de défense anti-aérienne ou antimissiles
F41H 13/00 - Moyens d'attaque ou de défense non prévus ailleurs
G08G 1/09 - Dispositions pour donner des instructions variables pour le trafic
H04K 3/00 - Brouillage de la communication; Contre-mesures
G01S 7/41 - DÉTERMINATION DE LA DIRECTION PAR RADIO; RADIO-NAVIGATION; DÉTERMINATION DE LA DISTANCE OU DE LA VITESSE EN UTILISANT DES ONDES RADIO; LOCALISATION OU DÉTECTION DE LA PRÉSENCE EN UTILISANT LA RÉFLEXION OU LA RERADIATION D'ONDES RADIO; DISPOSITIONS ANALOGUES UTILISANT D'AUTRES ONDES - Détails des systèmes correspondant aux groupes , , de systèmes selon le groupe utilisant l'analyse du signal d'écho pour la caractérisation de la cible; Signature de cible; Surface équivalente de cible
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
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
An articulated support includes a base and pitch-roll-yaw assembly having a pitch/roll subassembly and a yaw subassembly. The pitch/roll subassembly includes a central member configured for spring-loaded rotation about a pitch/roll axis, and the yaw subassembly has a U-shaped member configured (a) at end portions to engage under-wing connection lugs of an unmanned aircraft system (UAS) and (b) at a central portion to mate to the central member of the pitch/roll subassembly in a rotatable manner providing for rotation of the yaw subassembly about a yaw axis. The pitch/roll subassembly and yaw subassembly are further co-configured to define first and second fixed yaw positions in which a fuselage of the UAS is, respectively, parallel to and perpendicular to the pitch/roll axis, permitting roll motion and pitch motion of the UAS when mounted on the articulated support.
A technique for testing an electronic UUT by a test apparatus includes obtaining multiple DFTs of a test signal received from the UUT with the test apparatus configured differently for obtaining each DFT. The resulting DFTs include both valid content representing the test signal and invalid content introduced by the test apparatus. The improved technique suppresses the invalid content by generating a corrected DFT, which provides minimum magnitude values for corresponding frequencies relative to the test signal across the multiple DFTs.
A technique is directed to operating an unmanned aerial vehicle (UAV) having a fuselage defining a flight direction of the UAV and wing-plate assemblies that propel the UAV in the flight direction defined by the fuselage. The technique involves providing, while the flight direction defined by fuselage of the UAV points vertically from a takeoff location on the ground, thrust from propulsion units of the wing plate assemblies to fly the UAV along a vertical takeoff path. The technique further involves maneuvering, after the UAV flies along the vertical takeoff path, the UAV to align the flight direction along a horizontal flight path that is perpendicular to the vertical takeoff path. The technique further involves providing, after the UAV flies along the horizontal flight path, thrust from the propulsion units of the wing-plate assemblies to land the UAV along a vertical landing path.
B64C 29/02 - Aéronefs capables d'atterrir ou de décoller à la verticale, p.ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL] dont l'axe matérialisant la direction du vol est vertical lorsque l'aéronef est au sol
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
12.
UTILIZING AN UNMANNED AERIAL VEHICLE PLATFORM WHICH IS EQUIPPED WITH A TURNTABLE ASSEMBLY
An unmanned aerial vehicle (UAV) platform includes a stationary base constructed and arranged to reside over a fixed location on a surface (e.g., a ground location, a ship's deck, a trailer or other vehicle, etc.). The UAV platform further includes a set of UAV interfaces constructed and arranged to interface directly with a UAV (e.g., a launcher, a net apparatus, etc.). The UAV platform further includes a turntable assembly which couples to the stationary base. The turntable assembly is constructed and arranged to couple to each UAV interface and control angular direction of that UAV interface over the fixed location. A method of operating a UAV platform includes deploying the UAV platform over a fixed location, preparing a UAV interface on a turntable assembly of the UAV platform, and rotating the turntable to control angular direction of the UAV interface over the fixed location.
A modular mounting structure (12) is described which allows for the easy installation and removal of various payloads (30) from an air vehicle structure (12). An embedded electrical bus feature (18) further supports the installation of the various payloads (30) into the air vehicle structure (12).
The apparatus for attenuating noise from engine exhaust includes a first tube having an input end which receives the engine exhaust from the engine, and an output end which outputs the engine exhaust. The apparatus further includes a second tube which encircles the output end of the first tube. The second tube has an exhaust end through which the engine exhaust outputted by the output end of the first tube is allowed to escape, and a resonator end which is opposite the exhaust end. The apparatus further includes a reverse resonator disposed at the resonator end of the second tube. The reverse resonator defines a reverse resonator chamber and a reverse resonator chamber diameter which is larger than a second tube diameter defined by the second tube.
F01N 1/02 - Silencieux caractérisés par leur principe de fonctionnement utilisant la résonance
F01N 1/06 - Silencieux caractérisés par leur principe de fonctionnement utilisant les effets d'interférence
F01N 1/14 - Silencieux caractérisés par leur principe de fonctionnement par addition d'air aux gaz à évacuer
F01N 3/34 - Aménagements pour l'alimentation en air additionnel utilisant des conduits d'air ou des pompes à air à jet, p.ex. à proximité de l'orifice d'échappement du moteur
F01N 3/32 - Aménagements pour l'alimentation en air additionnel utilisant des pompes à air
A cooling air bypass is disclosed which prevents premature failure of an engine in the event the cooling air from an external blower is somehow obstructed or shut off.
B64D 33/08 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des systèmes de refroidissement des ensembles fonctionnels de propulsion
F01P 5/06 - Guidage ou conduite de l'air vers ou depuis les ventilateurs
16.
PROVIDING VISIBILITY TO A VEHICLE'S ENVIRONMENT VIA A SET OF CAMERAS WHICH IS CONFORMAL TO THE VEHICLE
An aircraft camera system provides visibility to a vehicle's environment. The vehicle has a set of vehicle surface portions (e.g., aircraft sections, panels, surfaces, combinations thereof, etc.) which defines a shape of the vehicle. The aircraft camera system includes a set of cameras integrated with the set of vehicle surface portions to avoid adding fluid drag force on the vehicle as the vehicle moves within the vehicle's environment. The aircraft camera system further includes a controller coupled to the set of cameras. The controller is constructed and arranged to obtain a set of camera signals from the set of cameras and output a set of electronic signals based on the set of camera signals. The set of electronic signals provides a set of images of the vehicle's environment from a perspective of the vehicle.
An apparatus and a method for the removable retention of a store/ payload to a vehicle comprising: a housing (15) having an elongated base, said base having a first and second distal end; a retention receptacle (14) disposed adjacent said first distal end, said retention receptacle configured to removably receive and retain the store/ payload; a release receptacle (18) disposed adjacent said second distal end, said release receptacle configured to house a release mechanism assembly; and said release mechanism assembly configured to move between a closed and locked position and an opened and unlocked position, wherein when the release mechanism assembly is in said closed and locked position the store/payload is retained to the vehicle, and wherein when the release mechanism assembly is in said open and unlocked position the store/payload may be disengaged from the vehicle.
B64D 1/00 - Largage, éjection ou réception, en cours de vol, d'objets, de liquides ou similaires
E05C 1/14 - Dispositifs d'immobilisation avec pênes se déplaçant de façon rectiligne avec action d'une clenche avec poignée de manœuvre ou organe équivalent se déplaçant autrement que rigidement avec la clenche dont la poignée ou organe se déplace essentiellement vers le ou à l'encontre du, plan du battant ou du dormant
A UAV includes a body. The body defines a payload opening (14). The payload opening is circular, but any shape may be used. A payload of the UAV is arranged in the payload opening. The payload may be a camera, sensors, a package, etc. A payload shroud may be installed which prohibits or reduced ingress of foreign material via payload opening. A payload shroud may include a diverter. The diverter may act as a barrier wall preventing the water or debris from entering the body of the UAV. The diverter should fit flush with the payload opening in the body of the UAV.
B64C 1/32 - Fuselages; Caractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés Éléments de fuselage séparables ou largables facilitant l'évacuation de secours
A fuzzy logic controller for controlling towed objects includes comprises a winch controller to control extension or retraction of a tow cable based on a control signal. A fuzzy logic controller controls a speed at which the tow cable is extended or retracted. The fuzzy logic controller includes an altitude controller storing a membership function defining ranges for a delta altitude variable and determines an altitude control signal based on the range for the measured delta altitude variable. A gain controller stores respective membership functions defining ranges for speed, heading rate, and cable length variables and determines a gain control signal based on the ranges for the determined speed, heading rate, and cable length variables. A command controller determines the control signal based on the gain control signal and the altitude control signal.
G05B 15/02 - Systèmes commandés par un calculateur électriques
G05B 13/02 - Systèmes de commande adaptatifs, c. à d. systèmes se réglant eux-mêmes automatiquement pour obtenir un rendement optimal suivant un critère prédéterminé électriques
A fuzzy logic controller for controlling towed objects includes comprises a winch controller to control extension or retraction of a tow cable based on a control signal. A fuzzy logic controller controls a speed at which the tow cable is extended or retracted. The fuzzy logic controller includes an altitude controller storing a membership function defining ranges for a delta altitude variable and determines an altitude control signal based on the range for the measured delta altitude variable. A gain controller stores respective membership functions defining ranges for speed, heading rate, and cable length variables and determines a gain control signal based on the ranges for the determined speed, heading rate, and cable length variables. A command controller determines the control signal based on the gain control signal and the altitude control signal.
A parser may be graphically modified without needing to directly alter the parser software and may be graphically modified to adjust for extensibility of the source test program language. The parser may be graphically modify to adjust for extensibility of the destination test program language and to translate a new text based test program language not inherently built into the parser.
A system, method and computer program product provides for estimating the range of a target. An acquisition window of an imaging device is adjusted to fit a target at an unknown range in response to a user input. An angle subtended by the largest dimension of the target viewed from the acquisition window is determined. The range of the target is estimated from a largest dimension of the target and the angle subtended by the largest dimension of the target. The device may be a man-portable aircraft survivability equipment (ASE) system trainer (MAST), or any simulator simulating a man-portable air defense system (MANPADS).
G01C 3/22 - Mesure des distances dans la ligne de visée; Télémètres optiques en utilisant un triangle parallactique ayant des angles variables et une base de longueur fixe, se trouvant sur l'objet, au voisinage de celui-ci, ou constitué par l'objet lui-même
23.
Ballistic sealing, component retention, and projectile launch control for an ammunition cartridge assembly
A telescoped ammunition cartridge assembly including a case having a front end and a base end positioned along a longitudinal axis. A projectile is positioned along the longitudinal axis towards the front end of the case. An endcap is coupled to the front end of the case and is adapted to retain the projectile entirely within the case. A primer is positioned along the longitudinal axis towards the base end of the case. A primer support is coupled to the base end of the case and is adapted to support the primer within the case. The cartridge assembly includes at least one obturating lip seal to seal at least one of the endcap or the primer support to the case.
A telescoped ammunition cartridge assembly including a case having a front end and a base end positioned along a longitudinal axis. A projectile is positioned along the longitudinal axis towards the front end of the case. An endcap is coupled to the front end of the case and is adapted to retain the projectile entirely within the case. A primer is positioned along the longitudinal axis towards the base end of the case. A primer support is coupled to the base end of the case and is adapted to support the primer within the case. The cartrige assembly includes at least one obturating lip seal to seal at least one of the endcap or the primer support to the case.
A high fidelity simulation of Doppler that may exactly replicate the phenomenology of the physical world. Compute the linear (Line of sight) kinematics (Slant Range, Radial Velocity, and Radial Acceleration) for each of a multiplicity of emitter-receiver pairs in accordance with exact 3D vector mathematics. Smoothly interpolate the linear kinematic parameters to produce accurate instantaneous values of these parameters at sample rates sufficient to produce negligible error effects in the presence of realistic aircraft maneuvers. Calculate the Doppler frequency, in accordance with well known physics, from the emitter carrier wavelength and a high sample rate. Calculate the Doppler effect as a differential phase (Doppler frequency×sample time) and apply the effect as incremental phase shifts to the carrier signal.
A system and method for correlating first pulsed signals with second pulsed signals includes a first receiving unit, a second receiving unit and a correlation device. The first receiving unit is disposed to receive from a first device one or more first pulsed signals. The first device may include a plurality of pulsed radio frequency source under test signal sources. The second receiving unit is disposed to receive from a second device one or more second pulsed signals. The second device may include a local oscillator pulsed signal source. The correlation device can correlate the first pulsed signals with the second pulsed signals to align a timing characteristic of the first pulsed signals to the equivalent timing characteristic of the second pulsed signals.
An apparatus for the recovery of an aircraft includes a capture device and first and second pole pairs. The first pole pair includes first top and bottom poles respectively placed near first top and bottom portions of the capture device. The first pole pair is configured to move from a first position, in which the pole pair holds the capture device in an open position to capture the aircraft, to a second position, in which the pole pair holds the capture device in a closed position to contain the captured aircraft after impact of the aircraft on the capture device. The second pole pair includes second top and bottom poles respectively placed near second top and bottom portions of the capture device. The second pole pair is also configured to move from the first position to the second position. Further, energy elements are coupled on one end to a respective top or bottom portion of the capture device and on another end to a respective top or bottom pole. The energy elements are disposed to absorb the force of the impact of the aircraft.
Apparatus for the recovery of an aircraft includes a capture device and first and second pole pairs. Each first and second pole pair includes top and bottom poles. First pole pair is configured to move from a first position, in which the pole pair holds the capture device in an open position to capture the aircraft, to a second position, in which the pole pair holds the capture device in a closed position to contain the captured aircraft after impact of the aircraft on the capture device. The second pole pair is also configured to move from the first position to the second position. Energy elements coupled on one end to a respective top or bottom portion of the capture device and on another end to a respective top or bottom pole, are disposed to absorb the force of the impact of the aircraft.
Apparatus for the recovery of an aircraft includes a capture device and first and second pole pairs. Each first and second pole pair includes top and bottom poles. First pole pair is configured to move from a first position, in which the pole pair holds the capture device in an open position to capture the aircraft, to a second position, in which the pole pair holds the capture device in a closed position to contain the captured aircraft after impact of the aircraft on the capture device. The second pole pair is also configured to move from the first position to the second position. Energy elements coupled on one end to a respective top or bottom portion of the capture device and on another end to a respective top or bottom pole, are disposed to absorb the force of the impact of the aircraft.
A method for using a “B” channel of a dual channel measurement receiver as a transfer standard for power measurement, which may include, in an exemplary embodiment, correlating a measurement made with an “A” channel of the dual channel measurement receiver to a measurement made with an RF Power Meter on one RF signal source, so that readings from the “A” channel are aligned to the RF Power Meter; aligning the “B” Channel to the “A” Channel, once the “A” channel has been aligned to read the same as the RF Power Meter; and using the “B” Channel as a transfer standard to measure all remaining RF signal sources in the system.
An exemplary embodiment, the present invention sets forth a method for correlating at least one weapon firing event to at least one scoring event. The method comprising: receiving information relating to a first scoring event; receiving information relating to a first weapon firing event; calculating an angle between a reference line, extending from location of the first weapon event to the location of the first scoring event, and the reference direction at the first computing device; comparing the time of the first scoring event to the time of the weapon firing event at the first computing device; comparing the angle of incidence for the projectile to the calculated angle at the first computing device; and identifying whether the weapon firing event and the scoring event are an unambiguous, one-to-one pairings at the first computing device.
An exemplary embodiment of the present invention sets forth an apparatus for registering time and location of a weapon firing of a weapon. The apparatus includes a microcontroller, a pressure sensor located in proximately to the weapon and adapted to determine pressure data based on air pressure in proximity to the weapon and provide the pressure data to a microcontroller, an accelerometer located in proximity to the weapon and adapted to determine acceleration data based on movement of the weapon and provide the acceleration data to the microcontroller; a time device adapted to keep time and provide the time to the microcontroller; a location sensor located in proximity to the weapon and adapted to determine a location of the weapon and provide the location of the weapon to the microcontroller; and a memory coupled to the microcontroller.
An exemplary embodiment of the present invention sets forth an apparatus for registering a scoring event. The apparatus includes a target having a surface; a sensor, positioned in proximity to the target, adapted to detect the occurrence of a scoring event caused by the presence of a projectile in the scoring area and to determine a trajectory of the projectile; a time tracking device adapted to keep track of time of the scoring event; a location sensing device adapted to identify a location of the apparatus; a true north detection device adapted to detect the direction of true north with respect to the surface of the target; and a controller, coupled to the sensor and the true north detection device.
An apparatus for registering time and location of a weapon firing of a weapon. The apparatus includes a microcontroller, a pressure sensor located in proximately is provided to the weapon and adapted to determine pressure data based on air pressure in proximity to the weapon and provide the pressure data to a microcontroller, an accelerometer located in proximity to the weapon and adapted to determine acceleration data based on movement of the weapon and provide the acceleration data to the microcontroller; a time device adapted to keep time and provide the time to the microcontroller; a location sensor located in proximity to the weapon and adapted to determine a location of the weapon and provide the location of the weapon to the microcontroller; and a memory coupled to the microcontroller.
An exemplary embodiment, the present invention sets forth a method for correlating at least one weapon firing event to at least one scoring event. The method comprising: receiving information relating to a first scoring event; receiving information relating to a first weapon firing event; calculating an angle between a reference line, extending from location of the first weapon event to the location of the first scoring event, and the reference direction at the first computing device; comparing the time of the first scoring event to the time of the weapon firing event at the first computing device; comparing the angle of incidence for the projectile to the calculated angle at the first computing device; and identifying whether the weapon firing event and the scoring event are an unambiguous, one-to-one pairings at the first computing device.
An exemplary embodiment of the present invention sets forth an apparatus for registering a scoring event. The apparatus includes a target having a surface; a sensor, positioned in proximity to the target, adapted to detect the occurrence of a scoring event caused by the presence of a projectile in the scoring area and to determine a trajectory of the projectile; a time tracking device adapted to keep track of time of the scoring event; a location sensing device adapted to identify a location of the apparatus; a true north detection device adapted to detect the direction of true north with respect to the surface of the target; and a controller, coupled to the sensor and the true north detection device.
G01B 17/00 - Dispositions pour la mesure caractérisées par l'utilisation de vibrations infrasonores, sonores ou ultrasonores
G01H 17/00 - Mesure des vibrations mécaniques ou des ondes ultrasonores, sonores ou infrasonores non prévue dans les autres groupes de la présente sous-classe
G01P 13/00 - Indication ou enregistrement de l'existence ou de l'absence d'un mouvement; Indication ou enregistrement de la direction d'un mouvement
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)
G06F 17/40 - Acquisition et consignation de données
37.
Method apparatus system and computer program product for automated collection and correlation for tactical information
A method, and corresponding system, apparatus, and computer program product for automated collection and correlation for tactical information includes identifying an entity in imagery based on a field of view of the imagery using a processor, creating a relationship between the imagery and the entity, and storing the relationship in a database.
A method, and corresponding system, apparatus, and computer program product for automated collection and correlation for tactical information includes identifying an entity in imagery based on a field of view of the imagery using a processor, creating a relationship between the imagery and the entity, and storing the relationship in a database.
A system and device that provides for the retention of a sensor shield for a sensor such as a microphone, hydrometer, chemical sensor, or other detector. This invention provides for the quick attachment and release of a reduced visibility and reduced bulk shield retention assembly. In a battlefield environment, a smaller profile sensor shield presents less visibility as a prospective target of interest to enemy forces. Also, the sensor shield may be readily replaced without the use of any tools. The snap-lock feature provides a positive means for holding, for example, a windscreen in its respective position, requiring reasonable, but yet not objectionable force to install and remove the windscreen from the sensor's mounting shaft. Furthermore, the snap-lock feature, when engaged, may provide positive location of the sensor shield's sweet spot by maintaining a slight air space between the sensor shield and the sensor, and thereby precluding direct physical contact.
A method for characterizing the effect of each step attenuator state, on phase and amplitude, which may include in an exemplary embodiment: activating each step attenuator state as the sole contributor to attenuation, and measuring at least one of a step attenuator amplitude contribution (SAAC) and/or a step attenuator phase contribution (SAPC).
Systems and methods provide for a flexible fuel bladder assembly disposed to store fuel and supply the fuel to a vehicle. The flexible fuel bladder assembly may include: a fuel bladder including a fuel-resistant film disposed to store the fuel and supply the fuel therefrom at a manifold assembly connected thereto; and a netting disposed within the fuel bladder and disposed to prevent collapsing of any two or more sides of the fuel bladder upon each other and permit a substantial portion of the fuel to be supplied from the fuel bladder to the manifold assembly in an uninterrupted fashion until the substantial portion of fuel is removed from the fuel bladder. The flexible fuel bladder may be used in an unmanned aerial vehicle (UAV), which may be any one of: an organic air vehicle (OAV), a micro air vehicle (MAV), an unmanned ground vehicle (UGV) or an unmanned combat air vehicle (UCAV).
Systems and methods provide for a flexible fuel bladder assembly disposed to store fuel and supply the fuel to a vehicle. The flexible fuel bladder assembly may include: a fuel bladder including a fuel-resistant film disposed to store the fuel and supply the fuel therefrom at a manifold assembly connected thereto; and a spiral tubing disposed within the fuel bladder and disposed to prevent collapsing of any two or more sides of the fuel bladder upon each other and permit a substantial portion of the fuel to be supplied from the fuel bladder to the manifold assembly in an uninterrupted fashion until the substantial portion of fuel is removed from the fuel bladder. The flexible fuel bladder may be used in an unmanned aerial vehicle (UAV), which may be any one of: an organic air vehicle (OAV), a micro air vehicle (MAV), an unmanned ground vehicle (UGV) or an unmanned combat air vehicle (UCAV).
A method for using a “B” channel of a dual channel measurement receiver as a transfer standard for power measurement, which may include in an exemplary embodiment: correlating measurements made with an “A” channel to measurements made with an RF Power Meter on one RF signal source, so that readings from the “A” channel are aligned to the RF Power Meter; aligning the “B” Channel to the “A” Channel (Transfer alignment of Channel B to the RF Power Meter), once the “A” channel has been aligned to read the same as the RF Power Meter; and using the “B” Channel as a transfer standard to measure all remaining RF signal sources in the system, on a time-line much faster than may be accomplished using a power meter.
Systems and methods provide for a flexible fuel bladder assembly disposed to store fuel and supply the fuel to a vehicle. The flexible fuel bladder assembly may include: a fuel bladder including a fuel-resistant film disposed to store the fuel and supply the fuel therefrom at a manifold assembly connected thereto. The fuel bladder may include an embossed pattern disposed to prevent a vacuum being formed by the collapsing of any two or more sides of the fuel bladder upon each other and permit a substantial portion of the fuel to be supplied from the fuel bladder to the manifold assembly in an uninterrupted fashion until the substantial portion of fuel is removed from the fuel bladder. The flexible fuel bladder may be used in an unmanned aerial vehicle (UAV), which may be any one of: an organic air vehicle (OAV), a micro air vehicle (MAV), an unmanned ground vehicle (UGV) or an unmanned combat air vehicle (UCAV).
An aircraft launcher includes a base frame, a first sliding frame that slides with respect to the base frame, a second sliding frame that slides with respect to the first sliding frame, an aircraft support located on the second sliding frame, and a drive apparatus adapted to slide at least one of the first sliding frame and the second sliding frame with respect to the base frame.
An aircraft launcher includes a base frame, a first sliding frame that slides with respect to the base frame, a second sliding frame that slides with respect to the first sliding frame, an aircraft support located on the second sliding frame, and a drive apparatus adapted to slide at least one of the first sliding frame and the second sliding frame with respect to the base frame.
A shock tube apparatus may include a plenum to hold a volume of gas. The plenum may include a hollow chamber having a first end and a second end located opposite one another along a longitudinal axis, the first end of the chamber defining a shock egress opening. A valve assembly may be positioned at the first end of the chamber to seal the shock egress opening. A piston may be positioned within a recess located at the second end of the chamber. The piston may separate a first volume located between the piston and the first end of the chamber from a smaller second volume located between the piston and the second end of the chamber. A tension supporting rod may connect the valve assembly to the piston. A release valve may be in fluid connection with the second volume and a switch may be operable to open the release valve to release gas from the second volume and trigger opening of the valve assembly to generate a shock wave through the shock egress opening.
A shock tube apparatus may include a plenum to hold a volume of gas. The plenum may include a hollow chamber having a first end and a second end located opposite one another along a longitudinal axis, the first end of the chamber defining a shock egress opening. A valve assembly may be positioned at the first end of the chamber to seal the shock egress opening. A piston may be positioned within a recess located at the second end of the chamber. The piston may separate a first volume located between the piston and the first end of the chamber from a smaller second volume located between the piston and the second end of the chamber. A tension supporting rod may connect the valve assembly to the piston. A release valve may be in fluid connection with the second volume and a switch may be operable to open the release valve to release gas from the second volume and trigger opening of the valve assembly to generate a shock wave through the shock egress opening.
A system, method and computer program product provides for integrating a sensor system data and a weapon system data with a graphical user interface (GUI) is provided. An area surrounding the mobile object on the GUI system is displayed. The respective locations of one or more sensed objects sensed by the sensor system in the area may be determined in response to a user selected sensor system input. The one or more sensed objects on the GUI system may be displayed. The weapon system may be targeted upon the one or more sensed objects in response to a user selected weapon system input.
A method of providing an integrated approach to automated system alignment is set forth, which may include in an exemplary embodiment: providing amplifier compression alignment, (which may include characterizing and/or compensating for a parasitic effect); providing continuous internal alignment of phase and amplitude of a synthetic stimulus instrument (SSI) output signal; providing external measurement port alignment; and providing transfer alignment of internal measurement paths. According to another exemplary embodiment, a receiver apparatus may include: a dual-channel coherent measurement receiver which may include at least one internal channel operative to measure time-division-multiplexed (TDM) feedback signals from each signal source of a synthetic stimulus instrument (SSI); and at least one external channel operative to make direct measurement at an external alignment port output.
A fuel pickup includes a fuel pickup tube having a plurality of holes for receiving fuel from inside a fuel container; and a wicking material enveloping at least one of the plurality of holes. Aircraft fuel systems including a fuel pickup comprising a wicking material are also disclosed.
A weapon flyout simulation method, system, and computer program product, includes modeling a target as a plurality of ellipsoidal zones corresponding to a plurality of zones on the target, and performing hit/miss assessment on the target by determining if said trajectory of the weapon interferes with at least one of said plurality of ellipsoids.
A system, method and computer program product provides for avoiding collision between a vehicle and a target object. Pluralities of images from the target object are sensed. Pluralities of polarized images are generated from the sensed images. One or more composite images are calculated from the two or more polarized images by performing a subtraction between the two or more polarized images. The target object is tracked based on composite images. A set of evasive maneuver instructions are established for the respective hazard associated with the target object.
A method of providing an integrated approach to automated system alignment is set forth, which may include in an exemplary embodiment: providing amplifier compression alignment, (which may include characterizing and/or compensating for a parasitic effect); providing continuous internal alignment of phase and amplitude of a synthetic stimulus instrument (SSI) output signal; providing external measurement port alignment; and providing transfer alignment of internal measurement paths. According to another exemplary embodiment, a receiver apparatus may include: a dual-channel coherent measurement receiver which may include at least one internal channel operative to measure time-division-multiplexed (TDM) feedback signals from each signal source of a synthetic stimulus instrument (SSI); and at least one external channel operative to make direct measurement at an external alignment port output.
A system and method for correlating first pulsed signals with second pulsed signals includes a first receiving unit, a second receiving unit and a corrlation device. The first receiving unit is disposed to received from a first device one or more first pulsed signals. The first device may include a plurality of pulsed radio frequency source under test signal sources. The second receiving unit is disposed to receive from a second device one or more second pulsed signals. The second device may include a local oscillator pulsed signal source. The correlation device can correlate the first pulsed signals with the second pulsed signals to align a timing characteristic of the first pulsed signals to the equivalent timing characteristic of the second pulsed signals.
A vent-on-demand fuel sump and vehicle fuel system having such a fuel sump are provided. The fuel sump may include a pressurized vessel and at least two sensors configured to detect a level of fuel within the vessel. A valve coupled to the vessel may be configured to release air and/or fuel vapor to the atmosphere. The fuel sump may also include a programmable electronic controller configured to modulate the valve between a closed position and an open position based on signals received from the sensors corresponding to the fuel level. The valve may be configured to remain in the closed position until the fuel level drops below a predetermined level and the controller sends a signal to open the valve to release air and/or fuel vapor from the vessel into the atmosphere. The vehicle fuel system having such a fuel sump may include a fuel container and an engine having an intake. The pressurized vessel of the fuel sump may include a fuel inlet coupled to the fuel container and a fuel outlet coupled to the engine intake.
F02M 37/20 - Appareils ou systèmes pour transférer le combustible liquide des réservoirs de stockage aux carburateurs ou aux injecteurs; Dispositions d'épuration du combustible liquide spécialement conçues pour les moteurs à combustion interne ou aménagées sur ceux-ci caractérisées par des moyens d'éviter le tampon de vapeur
A fuel pickup may include a fuel pickup tube having a plurality of holes for receiving fuel from inside a fuel container. A wicking material may envelop at least one of the plurality of holes. Aircraft fuel systems including such a fuel pickup are also disclosed. A vent-on-demand fuel sump and vehicle fuel system having such a fuel sump are provided. The fuel sump may include a pressurized vessel and at least two sensors configured to detect a level of fuel within the vessel. A valve coupled to the vessel may be configured to release air and/or fuel vapor to the atmosphere. The fuel sump may also include a programmable electronic controller configured to modulate the valve between a closed position and an open position based on signals received from the sensors corresponding to the fuel level.
A portable unmanned air vehicle and launcher system that includes a foldable unmanned air vehicle having a pressure tube; a launch gas reservoir for holding launch gas; a launch tube operatively connected to the launch gas reservoir and having a free end that is positioned in the pressure tube of the air vehicle; a free piston positioned within the launch tube; and a free piston stop to prevent the free piston from leaving the launch tube. A first portion of the launch gas in the launch gas reservoir is released into the launch tube and forces the free piston from an initial position to an end position at which the free piston is stopped by the free piston stop.
A lithium battery system for providing power to a load and a method for controlling the same. The system includes an alternator and a battery pack coupled in parallel with the alternator and the load via a vehicle voltage bus. The battery pack includes a lithium battery having a plurality of cells connected to the vehicle voltage bus to filter noise thereon and a battery management system coupled to the lithium battery. The battery management system is configured to vary a voltage output of the alternator based on a voltage and/or a current of the lithium battery. The noise along the vehicle voltage bus is reduced by the placement of the lithium battery.
A method for generating a synthesized waveform from a desired arbitrary waveform via a convolution processor includes: providing a data stream input signal to the convolution processor including an extended duration impulse signal; computing one or more filter coefficients of the convolution processor; and generating the synthesized waveform substantially similar to the desired arbitrary waveform using the filter coefficients. The convolution processor may be a finite impulse response (FlR) filter. The convolution processor may perform a convolution upon the extended duration impulse signal, where: the extended duration impulse signal is successively delayed via one or more taps and the output of each tap is multiplied by a filter coefficient corresponding to a delay; and the summation of the products of tap outputs and filter coefficients is the desired arbitrary waveform.
G01S 7/02 - DÉTERMINATION DE LA DIRECTION PAR RADIO; RADIO-NAVIGATION; DÉTERMINATION DE LA DISTANCE OU DE LA VITESSE EN UTILISANT DES ONDES RADIO; LOCALISATION OU DÉTECTION DE LA PRÉSENCE EN UTILISANT LA RÉFLEXION OU LA RERADIATION D'ONDES RADIO; DISPOSITIONS ANALOGUES UTILISANT D'AUTRES ONDES - Détails des systèmes correspondant aux groupes , , de systèmes selon le groupe
H03B 21/02 - Production d'oscillations par combinaison de signaux non modulés de fréquences différentes par battement de signaux non modulés de fréquences différentes par battements multiples, c. à d. pour synthèse de fréquence
61.
APPARATUS, METHOD AND COMPUTER PROGRAM PRODUCT FOR SYNTHESIZING ARBITRARY WAVEFORMS USING CONVOLUTION PROCESSORS
A method for generating a synthesized waveform from a desired arbitrary waveform via a convolution processor includes: providing a data stream input signal to the convolution processor including an extended duration impulse signal; computing one or more filter coefficients of the convolution processor; and generating the synthesized waveform substantially similar to the desired arbitrary waveform using the filter coefficients. The convolution processor may be a finite impulse response (FlR) filter. The convolution processor may perform a convolution upon the extended duration impulse signal, where: the extended duration impulse signal is successively delayed via one or more taps and the output of each tap is multiplied by a filter coefficient corresponding to a delay; and the summation of the products of tap outputs and filter coefficients is the desired arbitrary waveform.
H03B 28/00 - Génération d'oscillations par des procédés non couverts par les groupes , y compris la modification de la forme d'onde afin de produire des oscillations sinusoïdales
62.
Synthesizing arbitrary waveforms using convolution processors
A method for generating a synthesized waveform from a desired arbitrary waveform via a convolution processor includes: providing a data stream input signal to the convolution processor including an extended duration impulse signal; computing one or more filter coefficients of the convolution processor; and generating the synthesized waveform substantially similar to the desired arbitrary waveform using the filter coefficients. The convolution processor may be a finite impulse response (FIR) filter. The convolution processor may perform a convolution upon the extended duration impulse signal, where: the extended duration impulse signal is successively delayed via one or more taps and the output of each tap is multiplied by a filter coefficient corresponding to a delay; and the summation of the products of tap outputs and filter coefficients is the desired arbitrary waveform.
G01S 7/02 - DÉTERMINATION DE LA DIRECTION PAR RADIO; RADIO-NAVIGATION; DÉTERMINATION DE LA DISTANCE OU DE LA VITESSE EN UTILISANT DES ONDES RADIO; LOCALISATION OU DÉTECTION DE LA PRÉSENCE EN UTILISANT LA RÉFLEXION OU LA RERADIATION D'ONDES RADIO; DISPOSITIONS ANALOGUES UTILISANT D'AUTRES ONDES - Détails des systèmes correspondant aux groupes , , de systèmes selon le groupe
H03B 21/02 - Production d'oscillations par combinaison de signaux non modulés de fréquences différentes par battement de signaux non modulés de fréquences différentes par battements multiples, c. à d. pour synthèse de fréquence
A switch mechanism is provided that has a tubular enclosure; a contact pin electrically insulated from the tubular enclosure; a g-weight positioned inside the tubular enclosure and movable from an open position to a closed position; and a transparent closure that encloses one end of the tubular enclosure. The g-weight is in electrical contact with the contact pin and the tubular enclosure when the g-weight is in the closed position, such that a continuous electrical path exists from the contact pin to the tubular enclosure. The g-weight is for moving from the open position to the closed position when the switch mechanism is subjected to an acceleration greater than a threshold acceleration. The g-weight is visible through the transparent closure such that the position of the g-weight can be determined without removing the transparent closure from the tubular enclosure.
F42C 15/24 - 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 est effectuée par des dispositifs à inertie
64.
APPARATUS FOR USE IN OPERATOR TRAINING WITH, AND THE TESTING AND EVALUATION OF, INFRARED SENSORS WHICH ARE FOR MISSILE DETECTION
Apparatus (2) for use in operator training with, and the testing and evaluation of, missile detection systems which use infrared sensors which integrate incident energy over a finite time period, which apparatus (2) comprises at least one infrared illumination source (4) for illuminating the sensors, characterised in that the infrared illumination source (4) is a pseudo continuous wave laser infrared illumination source (4) with signal duty and peak power controlled by means of an amplitude, pulse width and pulse repetition interval modulation circuit (8), whereby the laser infrared illumination source (4) operates at shorter repetition intervals than the finite time period so that the laser infrared illumination source (4) appears to the infrared sensors to be a real missile signature.
A method and system for canceling VSWR effects is provided. The exemplary method includes taking multiple measurements of parameters of a signal with a phase of the microwave signal shifted for each measurement; and processing the measured parameters to eliminate VSWR effects and determine the true magnitude and phase of the signal.
H04B 15/00 - Suppression ou limitation du bruit ou des interférences
G01R 29/26 - Mesure du coefficient de bruit; Mesure de rapport signal-bruit
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)
66.
Angular encapsulation of tandem stacked printed circuit boards
A method is provided for making an encapsulated stack of circuit boards. The method includes assembling the stack of circuit boards from a plurality of circuit boards, the circuit boards being spaced apart from each other; inserting the stack into an internal volume of a shell, the shell having a first end and a second end opposite the first end, an input orifice adjacent the first end, and an output orifice adjacent the second end and on a side opposite the input orifice; positioning the shell such that the input orifice is at a lowest point of any part of the internal volume of the shell, and such that the output orifice is at a highest point of any part of the internal volume of the shell; angling the shell relative to horizontal; and injecting an encapsulating compound into the input orifice to fill the internal volume of the shell with the encapsulating compound.
H01R 43/00 - Appareils ou procédés spécialement adaptés à la fabrication, l'assemblage, l'entretien ou la réparation de connecteurs de lignes ou de collecteurs de courant ou pour relier les conducteurs électriques
H05K 13/00 - Appareils ou procédés spécialement adaptés à la fabrication ou l'ajustage d'ensembles de composants électriques
H05K 3/36 - Assemblage de circuits imprimés avec d'autres circuits imprimés
H05K 3/30 - Assemblage de circuits imprimés avec des composants électriques, p.ex. avec une résistance
B28B 1/00 - Fabrication d'objets façonnés à partir du matériau
B32B 15/00 - Produits stratifiés composés essentiellement de métal
67.
System and method for controlling and communicating with a vehicle
Embodiments of the present invention provide a software core controller for facilitating communication between a UAV control system, a UAV, and other peripheral devices used to control or to determine the status of the UAV. Different UAVs, control systems, and peripheral devices may require that data be transmitted and received according to their own particular specifications, such as a particular data rate and a particular format. The software core controller may be configurable to interface with these devices using the devices' interfaces. The interfaces may be specified by the devices' interface control documents (ICDs). The ICDs may be used to configure the software core controller upon initialization. The software core controller may asynchronously receive and provide data at the data rate specified in the various ICDs. The software core controller may support a plurality of different physical interfaces in order to communicate with different control systems, UAVs, and peripheral devices.
G06F 17/00 - TRAITEMENT ÉLECTRIQUE DE DONNÉES NUMÉRIQUES Équipement ou méthodes de traitement de données ou de calcul numérique, spécialement adaptés à des fonctions spécifiques
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
68.
SYSTEM AND METHOD FOR CONTROLLING AND COMMUNICATING WITH A VEHICLE
The present invention provide a software core controller (201 ) for facilitating communication between a UAV control system (203), a UAV (205), and other peripheral devices (202, 204, 208) used to control or to determine the status of the UAV (205). Different UAVs (205), control systems (203), and peripheral devices (202, 204, 208) may require that data be transmitted and received according to their own particular specifications, such as a particular data rate and a particular format. The software core controller (201 ) may be configurable to interface with these devices using the devices' interfaces (E1, E2, E3, E7). The interfaces (E1, E2, E3, E7) may be specified by the devices' interface control documents (ICDs). The ICDs may be used to configure the software core controller (201) upon initialization. The software core controller (201) may asynchronously receive and provide data at the data rate specified in the various ICDs. The software core controller (201) may support a plurality of different physical interfaces in order to communicate with different control systems (203), UAVs (205), and peripheral devices (202, 204, 208).
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
69.
SYSTEM AND METHOD FOR IMPLEMENTING REAL-TIME ADAPTIVE THRESHOLD TRIGGERING IN ACOUSTIC DETECTION SYSTEMS
A system and method to generate a trigger signal based on a real-time adaptive threshold. The system may includes a microphone to receive an audio signal (4), a device to generate a trigger signal (400) based on a real-time adaptive threshold coupled to the microphone to form an adaptive threshold and generate a trigger signal if a magnitude of the audio signal is greater than a magnitude of the adaptive threshold. The system may also include a waveform capture module coupled to the microphone to receive the audio signal and convert the audio signal into a series of waveform packets and a waveform analysis processor to extract characteritics from the waveform packets.
G10L 15/20 - Techniques de reconnaissance de la parole spécialement adaptées de par leur robustesse contre les perturbations environnantes, p.ex. en milieu bruyant ou reconnaissance de la parole émise dans une situation de stress
G10L 19/02 - Techniques d'analyse ou de synthèse de la parole ou des signaux audio pour la réduction de la redondance, p.ex. dans les vocodeurs; Codage ou décodage de la parole ou des signaux audio utilisant les modèles source-filtre ou l’analyse psychoacoustique utilisant l'analyse spectrale, p.ex. vocodeurs à transformée ou vocodeurs à sous-bandes
70.
System and method for implementing real-time adaptive threshold triggering in acoustic detection systems
A system and method to generate a trigger signal based on a real-time adaptive threshold. The system may include a microphone to receive an audio signal, a device to generate a trigger signal based on a real-time adaptive threshold coupled to the microphone to form an adaptive threshold and generate a trigger signal if a magnitude of the audio signal is greater than a magnitude of the adaptive threshold. The system may also include a waveform capture module coupled to the microphone to receive the audio signal and convert the audio signal into a series of waveform packets and a waveform analysis processor to extract characteristics from the waveform packets.
A phase persistent agile signal source method, apparatus, and/or computer program product provides a direct digital synthesizer (DDS) clock rate, provides a frequency tuning word (FTW) for a desired output frequency, provides a DDS update for a desired DDS update rate, provides an equivalent frequency least significant bit (LSB) for the desired DDS update rate, provides a current phase of an LSB accumulator, and generates a coherent phase of the desired output frequency based on the DDS clock rate, FTW, DDS update rate to the DDS, equivalent LSB for the desired DDS update rate, and current phase of the LSB accumulator. The coherent phase can be the fraction portion of the result obtained from the multiplication of the FTW and the current phase of the LSB accumulator.
G06G 1/02 - Dispositifs de calcul manipulés manuellement dans lesquels le calcul est effectué par addition, soustraction, ou comparaison de longueurs d'échelles graduées parallèles ou concentriques
72.
PHASE PERSISTENT AGILE SIGNAL SOURCE METHOD, APPARATUS, AND COMPUTER PROGRAM PRODUCT
A phase persistent agile signal source method, apparatus, and/or computer program product provides a direct digital synthesizer (DDS) clock rate, provides a frequency tuning word (FTW) for a desired output frequency, provides a DDS update for a desired DDS update rate, provides an equivalent frequency least significant bit (LSB) for the desired DDS update rate, provides a current phase of an LSB accumulator, and generates a coherent phase of the desired output frequency based on the DDS clock rate, FTW, DDS update rate to the DDS, equivalent LSB for the desired DDS update rate, and current phase of the LSB accumulator. The coherent phase can be the fraction portion of the result obtained from the multiplication of the FTW and the current phase of the LSB accumulator.
A launcher includes a plurality of launch tubes for stowing and launching a plurality of air vehicles. A central air manifold is operatively connected to an air storage tank; a first launch tube air manifold is operatively connected to a first group of the launch tubes and operatively connected to the central air manifold. The first launch tube air manifold has a separate port corresponding to each launch tube of the first group of launch tubes. A release valve mechanism is removably mounted in one of the ports of the first launch tube air manifold, the release valve mechanism controlling the passage of launch air between the first launch tube air manifold and the launch tube corresponding to the port in which the release valve mechanism is mounted. A plug is removably mounted in each of the ports not occupied by the release valve mechanism.
A portable unmanned air vehicle and launcher system including a foldable unmanned air vehicle with a pressure tube; a launch gas reservoir for holding launch gas; a launch tube operatively connected to the launch gas reservoir and having a free end that is positioned in the pressure tube of the air vehicle; a free piston positioned within the launch tube; and a free piston stop to prevent the free piston from leaving the launch tube. A first portion of the launch gas in the launch gas reservoir is released into the launch tube and forces the free piston from an initial position to an end position at which the free piston is stopped by the free piston stop.
A portable unmanned air vehicle and launcher system is provided that includes a foldable unmanned air vehicle having a pressure tube; a launch gas reservoir for holding launch gas; a launch tube operatively connected to the launch gas reservoir and having a free end that is positioned in the pressure tube of the air vehicle; a free piston positioned within the launch tube; and a free piston stop to prevent the free piston from leaving the launch tube. A first portion of the launch gas in the launch gas reservoir is released into the launch tube and forces the free piston from an initial position to an end position at which the free piston is stopped by the free piston stop.
brevets
