A roller-and-rail cargo handling system that includes tracked rollers and side rails for receiving cargo pallets. A trolley system is used to move the pallets along the tracked rollers, which includes a trolley movable along a trolley track by one or more cables. The trolley includes (1) a body sized and configured for sliding beneath the pallet located on the tracked rollers, and (2) a pawl in a cavity of the body which is mounted for rotation between closed and open positions. In the open position the pawl extends above an upper surface of the body to engage a cutout of a pallet and exert a moving force thereto, and in the closed position the pawl is sufficiently within the cavity to permit the trolley to slide beneath the pallet without engagement thereof.
B65G 35/06 - Mechanical conveyors not otherwise provided for comprising a load-carrier moving along a path, e.g. a closed path, and adapted to be engaged by any one of a series of traction elements spaced along the path
A heatshield is made of a heatshield material including an insulative-fiber matrix fully impregnated with a polyphenylene sulfide resin. The heatshield material may be a multi-layer fiber matrix having higher-weight forms at an outer ablative surface and lower-weight forms more inwardly, for insulation. In one example, PPS fiber is combined with carbon or carbon precursor fibers and both woven into fabric form and manufactured into nonwoven sheet stock. The final tailored stackup may be needled together, and the needled fabric stackup saturated with molten PPS resin.
B29C 70/22 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
B29C 70/00 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
B29C 70/54 - Component parts, details or accessories; Auxiliary operations
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
3.
AUTOMATED TAPE LAYERING FOR CONICAL COMPOSITE COMPONENTS
Techniques for providing a conical composite involve receiving a starting portion of a tape from a tape supply, the tape having a first tape edge and a second tape edge. The techniques further involve positioning the starting portion of the tape in contact with a conical tool structure. The techniques further involve, after the starting portion of the tape is positioned in contact with the conical tool structure, maneuvering at least one of (i) a tape deployment head relative to the conical tool structure and (ii) the conical tool structure relative to the tape deployment head to deploy the tape around the conical tool structure with the first tape edge adjacent to conical tool structure and the second tape edge extending outwardly from the conical tool structure to form the conical composite.
B29C 70/32 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core on a rotating mould, former or core
B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
4.
REMOTE OPERATION OF UNMANNED VEHICLE USING HOSTED WEB SERVER
A system for remote operation of an unmanned vehicle (UV) includes a control station having a communication link to the UV and executing a web browser for (1) receiving web pages of a UV control web application, (2) rendering the web pages on the control station, (3) receiving control input from an operator via rendered web pages, and (4) generating messages on the communication link based on the control input. A hosted server system is coupled to the control station via the communication link and to internal subsystems of the UV for flight control, mission control, navigation, and system monitoring, and (1) executes a web server serving the web pages of the UV control web application to the control station for the above operations of the web browser, and (2) provides back-end controls to the internal subsystems based on the control input from the operator.
A shielded, multi-layer heatshield material for hypersonic flight applications includes an ablative/insulative structure having a thickness and providing both thermal insulation and a first ablation resistance, and a separate shield layer bound to an outer surface of the ablative/insulative structure, the shield layer being thinner than the ablative/insulative structure while providing a second higher ablation resistance greater than the first ablation resistance. In one arrangement the ablative/insulative structure includes a carbon/carbon composite layer attached to a syntactic carbon foam layer, using carbon fiber stitched loops for reinforcement, and the shield layer is a carbide outer layer. In another arrangement the ablative/insulative structure includes a silica composite layer attached to a silica insulative foam layer, using stitched loops for reinforcement, and the shield layer is a ceramic outer layer.
B32B 27/12 - Layered products essentially comprising synthetic resin next to a fibrous or filamentary layer
B32B 27/20 - Layered products essentially comprising synthetic resin characterised by the use of special additives using fillers, pigments, thixotroping agents
B32B 5/06 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments characterised by a fibrous layer needled to another layer, e.g. of fibres, of paper
B32B 9/00 - Layered products essentially comprising a particular substance not covered by groups
B32B 9/04 - Layered products essentially comprising a particular substance not covered by groups comprising such substance as the main or only constituent of a layer, next to another layer of a specific substance
6.
PAYLOAD INTERFACE MODULE FOR REMOTELY PILOTED VEHICLES
In a remotely piloted vehicle system, a ground station has a payload controller (PC), ground data terminal (GDT), and first payload interface module (PIM) having a first interface of a payload-specific type to the PC and a first network interface to the GDT, and the first PIM converts between signals of the first interface and corresponding messages of the first network interface. Aa remotely piloted vehicle has a payload (PL), a vehicle data terminal (VDT), and a second PIM having a second interface of the payload-specific type to the PL and a second network interface to the VDT. The VDT is communicatively coupled to the GDT for transfer of messages, and the second PIM converts between messages of the second network interface and corresponding signals of the second interface. The PIMs form respective endpoints of a ground-to-vehicle channel between the PC and PL.
Techniques are directed to a modular vehicle belly armor kit, as well as systems and methods which utilize such a kit. The kit includes a bottom plate, a top plate, and a plurality of wall sections connecting with the bottom plate and the top plate to form an armor structure that protects a belly portion of the vehicle. After the modular vehicle belly armor kit is positioned underneath a vehicle, the bottom plate may be placed in contact with the vehicle. After the bottom plate is placed in contact with the vehicle, the bottom plate may be fastened to vehicle.
B62D 65/16 - Joining sub-units or components to, or positioning sub-units or components with respect to, body shell or other sub-units or components the sub-units or components being exterior fittings, e.g. bumpers, lights, wipers
9.
UTILIZING A SEAT ASSEMBLY HAVING A SET OF LIMIT STRAPS TO LIMIT DEFLECTION
A vehicle includes a vehicle ceiling, a vehicle floor, and a vehicle seat assembly that couples with the vehicle ceiling and the vehicle floor. The vehicle seat assembly includes a seat support that supports a vehicle seat from the vehicle ceiling, a base that forms a slip joint with the seat support from the vehicle floor, and a set of limit straps constructed and arranged to limit deflection of the slip joint in response to deformation between the vehicle ceiling and the vehicle floor (e.g., a vehicle collision, deformation between the vehicle ceiling and the vehicle floor possibly due to a blast, etc.). Each limit strap of the set of limit straps has a first end that attaches to a portion of the slip joint and a second end that attaches to the vehicle floor.
A technique of jamming a victim radar includes digitizing an incident waveform received from the victim radar and convolving the digitized waveform with contents of a range trace memory. The range trace memory stores a sequence of impulses, which, when convolved with the digitized waveform, creates a corresponding sequence of delayed versions of the digitized waveform, one for each impulse in the sequence, and adds together the delayed versions to produce a single output signal. The output signal is then converted to analog form and transmitted back toward the victim radar.
An unmanned aerial vehicle (UAV) includes a fuselage assembly, a further portion that attaches with the fuselage assembly, and a propulsion assembly coupled with the further portion. The propulsion assembly is constructed and arranged to provide propulsion for the UAV. The fuselage assembly includes a fuselage body constructed and arranged to operate as a forward portion of the UAV, lateral stringers coupled with the fuselage body and extending laterally along the fuselage body, and a set of interchangeable covers to cover at least a portion of a payload bay opening defined by the fuselage body. Utilizing such a fuselage assembly offers a highly configurable mounting architecture to accommodate a wide variety of payloads.
A weapon is capable of firing cased telescoped (CT) ammunition rounds. The weapon includes a barrel, a chamber member that defines a chamber configured to hold a CT round for firing from the weapon, a non-rotating carrier body, and linkage. The linkage is constructed and arranged to move the chamber member (i) from a firing position in which the chamber member is aligned with the barrel for firing the CT round to an ejection/loading position in which the chamber member is not aligned with the barrel for ejecting a spent CT round and receiving a next CT round in response to the non-rotating carrier body moving away from the barrel, and (ii) from the ejection/loading position to the firing position in response to the non-rotating carrier body moving toward the barrel.
F41A 9/45 - Loading arrangements, i.e. for bringing the ammunition into the firing position the cartridge chamber or the barrel as a whole being tiltable between a loading and a firing position
F41A 3/10 - Block action, i.e. the main breech opening movement being transverse to the barrel axis with sliding breech-block, e.g. vertically
F41A 15/10 - Cartridge extractors, i.e. devices for pulling cartridges or cartridge cases at least partially out of the cartridge chamber; Cartridge ejectors, i.e. devices for throwing the extracted cartridges or cartridge cases free of the gun for block-action guns of sliding-block type
13.
Suppressing spurious signals in direct-digital synthesizers
A technique for generating analog waveforms includes combining a desired, in-band signal with a randomizing, out-of-band signal at an input of a DAC, operating the DAC to generate DAC output based on a combination of the desired signal and the randomizing signal, and filtering the DAC output to pass the desired signal while removing the randomizing signal.
Techniques are directed to utilizing a break-in assembly to break-in a gear box. The break-in assembly includes a gear box support to support the gear box. The break-in assembly further includes a drive apparatus coupled with the gear box support, the drive apparatus being constructed and arranged to drive the gear box while the gear box is supported by the gear box support. The break-in assembly further includes a loading apparatus disposed in a fixed position relative to the gear box support, the loading apparatus being constructed and arranged to apply loading to the gear box while the drive apparatus drives the gear box. Accordingly, the gear box may be installed on the break-in assembly, broken in during a gear box break-in period while the gear box is installed on the break-in assembly, removed from the break-in assembly, and installed on a water vessel.
G01M 13/025 - Test-benches with rotational drive means and loading means; Load or drive simulation
B63H 23/06 - Transmitting power from propulsion power plant to propulsive elements with mechanical gearing for transmitting drive from a single propulsion power unit
A belt-fed weapon includes an upper part defining a feed tray cavity, and a feed tray in the feed tray cavity, wherein the feed tray and feed-tray cavity are co-configured for lateral sliding insertion and removal of the feed tray to and from an installed position in the feed tray cavity. The arrangement enables insertion and removal of the feed tray without interference with an installed scope or similar optic, enabling maintenance or field stripping without requiring removal or re-sighting of the scope.
A flight control arrangement for a hybrid aircraft includes a fixed-wing flight (F/W) control module and vertical takeoff/landing flight (VTOL) control module. The F/W control module is an integrated component having a respective network interface connected to an aircraft data network via which it provides fixed-wing control output to network-connected fixed-wing flight components including one or more horizontal-thrust components. The VTOL control module is also an integrated component having a respective network interface to the aircraft data network via which the VTOL control module (1) observes flight status as reflected in network messages originated by the fixed-wing flight control module, and (2) based on the observed flight status, generates VTOL control output to network-connected VTOL flight components including one or more vertical-thrust components, to control VTOL flight as well as transitions to and from fixed-wing flight.
A firearm for firing case-telescoped (CT) rounds includes a barrel configured for transit of a bullet of a live CT cartridge in a live-fire operating mode. The live CT cartridge is chambered and fired from a live-fire chamber installed in the live-fire operating mode. The firearm further includes a blank-fire chamber configured to chamber and fire a blank CT cartridge in a blank-fire operating mode, wherein the blank-fire chamber has a second diameter less than a first diameter of the live-fire chamber, to prevent chambering of the live CT cartridge in the blank-fire operating mode. The arrangement can enhance safety by preventing accidental firing of a live round during operation when it is assumed that only blanks are being fired.
A light apparatus includes an array of light-emitting diodes (LEDs) in parallel arrangement, in which the LEDs have respective first terminals coupled together for connection to a supply node of a power source that provides the drive current to the LEDs during operation. Driver circuity is disposed between respective second terminals of the LEDs and a return node of the power source. The driver circuitry includes a respective LED driver for each of the LEDs, and each LED driver includes (1) a transistor connected to the second terminal of the respective LED, and (2) a resistor in series between the transistor and a return node of the power source, the transistors of the LED drivers having respective control inputs for receiving respective LED drive signals to control operation of the LEDs.
Techniques involve utilizing a multi-track cargo handling assembly to guide individual cargo items in parallel tracks to an aft end of a deck of an amphibious air cushion vehicle when unloading from the aft end. Such a multi-track cargo handling assembly includes a framework constructed and arranged to couple with the deck of the amphibious air cushion vehicle, and a set of guide rails coupled with the framework. The set of guide rails defines the parallel tracks and is constructed and arranged to constrain movement of the cargo items along the parallel tracks.
B63B 25/28 - Load-accommodating arrangements, e.g. stowing or trimming; Vessels characterised thereby for deck loads
B60P 1/52 - Vehicles predominantly for transporting loads and modified to facilitate loading, consolidating the load, or unloading using rollers in the load supporting or containing element
B63B 25/22 - Load-accommodating arrangements, e.g. stowing or trimming; Vessels characterised thereby for palletised articles
B63B 35/00 - Vessels or similar floating structures specially adapted for specific purposes and not otherwise provided for
Techniques involve an air flow assembly to provide pressurized air, e.g., for use by an air-cushion vehicle (ACV) or other craft. The air flow assembly includes a volute having a central chamber, a lift duct, and a thruster duct. The air flow assembly further includes a set of guide members disposed between the central chamber and the thruster duct, and linkage coupled to the set of guide members. The linkage is constructed and arranged to transition the set of guide members between a closed configuration in which the set of guide members closes an opening between the central chamber and the thruster duct, and an opened configuration in which the set of guide members opens the opening between the central chamber and the thruster duct.
A feed tray assembly for a belt-fed weapon includes a bottom tray portion configured for mounting at a top of the weapon. The feed tray assembly further includes a feed tray cover mounted to the bottom tray portion and configured for lateral sliding opening and closing movement, such as on laterally extending pins riding in corresponding channels of the bottom tray portion. The feed tray cover has (1) a closed position in which it covers the bottom tray portion to retain the belt of ammunition during operation, and (2) an open position laterally displaced from the closed position to enable insertion of the belt of ammunition. Due to this lateral sliding movement of the feed tray cover, a sighting optic may be mounted on the weapon with a forward portion directly above the feed tray assembly without any undesired mechanical interference.
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 defining a pocket in a face of a bolt, and ii) a static front chamber portion that is integral to the barrel and separate from the bolt. A cartridge extraction mechanism 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 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 15/14 - Cartridge extractors, i.e. devices for pulling cartridges or cartridge cases at least partially out of the cartridge chamber; Cartridge ejectors, i.e. devices for throwing the extracted cartridges or cartridge cases free of the gun for bolt-action guns the ejector being mounted on, or within, the bolt
F41A 3/26 - Rigid bolt locks, i.e. having locking elements rigidly mounted on the bolt or bolt handle and on the barrel or breech-housing respectively the locking elements effecting a rotary movement about the barrel axis, e.g. rotating cylinder bolt locks semi-automatically or automatically operated, e.g. having a slidable bolt-carrier and a rotatable bolt
F42B 5/045 - Cartridges, i.e. cases with propellant charge and missile of telescopic type
23.
Providing a load from a motor to inhibit further rotation of a propeller of an aerial vehicle while in flight
A technique for operating an aerial vehicle involves enabling a vertical takeoff and landing (VTOL) propeller of the aerial vehicle to rotate freely. The VTOL propeller is coupled with a VTOL motor (e.g., a 3-phase brushless DC motor). The technique further involves detecting when the VTOL propeller rotates to a predefined position relative to a direction of flight for the aerial vehicle (e.g., when blades of the VTOL propeller extend along an axis that is parallel to the direction of flight). The technique further involves, in response to detecting that the VTOL propeller has rotated to the predefined position, providing a load from the VTOL motor that inhibits further rotation of the VTOL propeller. Accordingly, while the aerial vehicle is in fixed wing horizontal flight, the controller is able to align the VTOL propeller in the direction of horizontal flight to minimize drag from the VTOL propeller.
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
B64D 31/06 - Initiating means actuated automatically
B64D 35/04 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors
B64C 39/02 - Aircraft not otherwise provided for characterised by special use
B64D 35/02 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the type of power plant
B64C 11/00 - Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
24.
UTILIZING A LIFTGATE ASSEMBLY THAT HARDWARE MOUNTS TO A VEHICLE BODY
Techniques are directed to utilizing a liftgate assembly having a platform, a lift subsystem constructed and arranged to selectively raise and lower the platform, and a set of steel beams coupled with the lift subsystem. The set of steel beams is constructed and arranged to hardware mount to a set of aluminum beams of a vehicle. Although the sets of beams are made of different materials, the liftgate assembly and the vehicle body may be securely fastened to each other making the vehicle well suited for a variety of conditions.
B60P 1/44 - Vehicles predominantly for transporting loads and modified to facilitate loading, consolidating the load, or unloading having a loading platform thereon raising the load to the level of the load supporting or containing element
B62D 21/02 - Understructures, i.e. chassis frame on which a vehicle body may be mounted comprising longitudinally or transversely arranged frame members
B62D 29/00 - Superstructures characterised by material thereof
A technique of safeguarding equipment involves deriving a pressure pulse amplitude based on operation of a pump of the equipment, and performing a comparison operation that compares the pressure pulse amplitude value to a predefined threshold. The technique further involves performing, in response to a result of the comparison operation indicating that the pressure pulse amplitude value has fallen below the predefined threshold, a remedial activity to prevent damage to the equipment or to prevent endangerment to persons affected by the failure of the equipment. For example, in the case of an unmanned aerial vehicle (UAV), the remedial action may be to transit the UAV from a densely populated area to a rural area where landing may be possible without injuring persons or damaging the UAV.
Techniques involve releasing and/or capturing a fixed-wing aircraft using an aerial vehicle with VTOL capabilities while the fixed-wing aircraft is in flight. For example, the VTOL aerial vehicle may take off vertically while carrying the fixed-wing aircraft and then fly horizontally before releasing the fixed-wing aircraft. Upon release, the fixed-wing aircraft flies independently to perform a mission (e.g., surveillance, payload delivery, combinations thereof, etc.). After the fixed-wing aircraft has completed its mission, the VTOL aerial vehicle may capture the fixed-wing aircraft while both are in flight, and then land together vertically. Such operation enables the fixed-wing aircraft to vertically take off and/or land while avoiding certain drawbacks associated with a conventional VTOL kit such as being burdened by weight and drag from the VTOL kit's rotors/propellers, mounting hardware, etc. during a mission which otherwise would limit the fixed-wing aircraft's maximum airspeed, ceiling, payload capacity, endurance, and so on.
A separated lift-thrust (SLT) aircraft includes a longitudinal-thrust engine and articulated electric rotors, at least some of which are variable-position rotors having variable orientations based on rotor position signals. Control circuitry independently controls thrust of the longitudinal-thrust engine and the thrust and orientation of each of the variable-position rotors, relative to the aircraft lifting surface and longitudinal thrust engine, to provide for commanded thrust-vectoring maneuvering of the aircraft during VTOL, fixed wing flight, and intermediate transitional states, including maintenance of a desired pose of the lifting surface independent of orientation of the rotor orientations when hovering the aircraft in windy conditions. A flight and navigation control system automates flight maneuvers and maintains desired aircraft pose and position relative to static or dynamic coordinates during station keeping, tracking, avoidance, or convergence maneuvers.
A technique of managing communications among multiple modules of a munition includes receiving, by a first module of the munition, a first set of messages from a second module of the munition. The first set of messages is received in a first protocol used for communicating among the modules of the munition over a computer network. The technique further includes translating, by an interface assembly of the first module, the first set of messages in the first protocol into a second set of messages in a second protocol. The second protocol is a native protocol of the first module and is different from the first protocol. The technique still further includes providing the second set of messages from the interface module to an operational component of the first module, the operational component then responding to the second set of messages for performing a function of the munition.
H04L 67/12 - Protocols specially adapted for proprietary or special-purpose networking environments, e.g. medical networks, sensor networks, networks in vehicles or remote metering networks
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 defining a pocket in a face of a bolt, and ii) a static front chamber portion that is integral to the barrel and separate from the bolt. A cartridge extraction mechanism 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 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 15/14 - Cartridge extractors, i.e. devices for pulling cartridges or cartridge cases at least partially out of the cartridge chamber; Cartridge ejectors, i.e. devices for throwing the extracted cartridges or cartridge cases free of the gun for bolt-action guns the ejector being mounted on, or within, the bolt
F41A 3/26 - Rigid bolt locks, i.e. having locking elements rigidly mounted on the bolt or bolt handle and on the barrel or breech-housing respectively the locking elements effecting a rotary movement about the barrel axis, e.g. rotating cylinder bolt locks semi-automatically or automatically operated, e.g. having a slidable bolt-carrier and a rotatable bolt
F42B 5/045 - Cartridges, i.e. cases with propellant charge and missile of telescopic type
30.
Magazine with a moveable lip for cased telescoped ammunition cartridges
A magazine for storing cased telescoped (CT) cartridges and delivering the CT cartridges to a firearm configured to fire CT cartridges. The magazine includes a fixed lip and a moveable lip. The fixed lip and the moveable lip of the magazine are configured to prevent a CT cartridge located in a top-most position within the magazine from being pushed out a top of the magazine when the magazine is not fully inserted into a magazine well of the firearm configured to fire CT cartridges. The moveable lip may pivot laterally on a pivot point and move out of the way of the CT cartridge located in the top-most position within the magazine when the magazine is fully inserted and locked into the magazine well of the firearm configured to fire CT cartridges.
A weapon for firing cased telescoped (CT) ammunition includes a barrel, a chamber member and a carrier assembly. 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. Dual-feed structure provides for both a magazine mode as well as a belt feed mode of operation.
A cased telescoped cartridge that includes a cylindrical case surrounding a projectile, a front end through which the projectile exits when the cased telescoped cartridge is fired, and a thermal protective insert located at the front end. The thermal protective insert insulates the cased telescoped cartridge from heat emanating from a barrel of a firearm into a chamber of a firearm when the cartridge is loaded into the chamber of the firearm. The thermal protective insert is made up of at least one thermally insulating material, and is integrated into the front end of the cased telescoped cartridge.
F42B 5/045 - Cartridges, i.e. cases with propellant charge and missile of telescopic type
33.
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 37/22 - Arrangements for purifying liquid fuel specially adapted for, or arranged on, internal-combustion engines, e.g. arrangements in the feeding system
F02M 37/44 - Filters structurally associated with pumps
B01D 36/00 - Filter circuits or combinations of filters with other separating devices
34.
In-flight aircraft refueling by jettisoning and onboarding replaceable fuel tanks
A method of operating an aircraft includes, prior to an in-flight refueling operation, operating the aircraft using fuel from a first fuel tank connected to a fuel delivery system. Subsequently, the in-flight refueling operation is performed over a refueling area while operating the aircraft from another fuel tank, including (1) disconnecting the first fuel tank from the fuel delivery system, (2) jettisoning the first fuel tank, and (3) taking on a replacement fuel tank by (a) capturing the replacement fuel tank from the refueling area and (b) bringing the captured replacement fuel tank onboard the aircraft. The replacement fuel tank is then connected to the fuel delivery system and the aircraft is operated using fuel from the replacement fuel tank.
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.
B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
A 1-to-N munitions adapter that includes a physical launcher interface, a physical munitions interface, and electronic control circuitry. The physical launcher interface is operable to connect the 1-to-N munitions adapter to a single munition launcher that is i) configured and arranged to carry and launch a single munition of a first type, and ii) integrated to an airborne platform. The physical munitions interface is operable to connect the 1-to-N munitions adapter to multiple munitions of a second type. The 1-N munitions adapter i) emulates a control interface of a single munition of the first type to the single munition launcher, in part by identifying the 1-to-N munitions adapter to the single munition launcher as a single munition of the first type, and ii) selectively controls the release of munitions of the second type while the airborne platform is in flight in response to signals received from the single munition launcher.
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 defining a pocket in a face of a bolt, and ii) a static front chamber portion that is integral to the barrel and separate from the bolt. A cartridge extraction mechanism 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 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 15/14 - Cartridge extractors, i.e. devices for pulling cartridges or cartridge cases at least partially out of the cartridge chamber; Cartridge ejectors, i.e. devices for throwing the extracted cartridges or cartridge cases free of the gun for bolt-action guns the ejector being mounted on, or within, the bolt
F41A 3/34 - Rigid bolt locks, i.e. having locking elements rigidly mounted on the bolt or bolt handle and on the barrel or breech-housing respectively the bolt additionally effecting a sliding movement transverse to the barrel axis
F41A 9/45 - Loading arrangements, i.e. for bringing the ammunition into the firing position the cartridge chamber or the barrel as a whole being tiltable between a loading and a firing position
F41A 3/26 - Rigid bolt locks, i.e. having locking elements rigidly mounted on the bolt or bolt handle and on the barrel or breech-housing respectively the locking elements effecting a rotary movement about the barrel axis, e.g. rotating cylinder bolt locks semi-automatically or automatically operated, e.g. having a slidable bolt-carrier and a rotatable bolt
F41A 9/23 - Movable ammunition carriers or loading trays, e.g. for feeding from magazines sliding, e.g. reciprocating mounted within a smallarm
F41A 3/30 - Interlocking means, e.g. locking lugs, screw threads
F41A 3/10 - Block action, i.e. the main breech opening movement being transverse to the barrel axis with sliding breech-block, e.g. vertically
A weapon for firing cased telescoped (CT) ammunition includes a barrel, a chamber member and a carrier assembly. 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 and (1) performs a recoil in which a carrier and rammer 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 (2) 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 3/34 - Rigid bolt locks, i.e. having locking elements rigidly mounted on the bolt or bolt handle and on the barrel or breech-housing respectively the bolt additionally effecting a sliding movement transverse to the barrel axis
F41A 9/45 - Loading arrangements, i.e. for bringing the ammunition into the firing position the cartridge chamber or the barrel as a whole being tiltable between a loading and a firing position
F41A 3/26 - Rigid bolt locks, i.e. having locking elements rigidly mounted on the bolt or bolt handle and on the barrel or breech-housing respectively the locking elements effecting a rotary movement about the barrel axis, e.g. rotating cylinder bolt locks semi-automatically or automatically operated, e.g. having a slidable bolt-carrier and a rotatable bolt
F41A 9/23 - Movable ammunition carriers or loading trays, e.g. for feeding from magazines sliding, e.g. reciprocating mounted within a smallarm
F41A 3/30 - Interlocking means, e.g. locking lugs, screw threads
F41A 3/10 - Block action, i.e. the main breech opening movement being transverse to the barrel axis with sliding breech-block, e.g. vertically
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.
F41A 3/34 - Rigid bolt locks, i.e. having locking elements rigidly mounted on the bolt or bolt handle and on the barrel or breech-housing respectively the bolt additionally effecting a sliding movement transverse to the barrel axis
F41A 9/45 - Loading arrangements, i.e. for bringing the ammunition into the firing position the cartridge chamber or the barrel as a whole being tiltable between a loading and a firing position
F41A 3/26 - Rigid bolt locks, i.e. having locking elements rigidly mounted on the bolt or bolt handle and on the barrel or breech-housing respectively the locking elements effecting a rotary movement about the barrel axis, e.g. rotating cylinder bolt locks semi-automatically or automatically operated, e.g. having a slidable bolt-carrier and a rotatable bolt
F41A 9/23 - Movable ammunition carriers or loading trays, e.g. for feeding from magazines sliding, e.g. reciprocating mounted within a smallarm
F41A 3/30 - Interlocking means, e.g. locking lugs, screw threads
F41A 15/14 - Cartridge extractors, i.e. devices for pulling cartridges or cartridge cases at least partially out of the cartridge chamber; Cartridge ejectors, i.e. devices for throwing the extracted cartridges or cartridge cases free of the gun for bolt-action guns the ejector being mounted on, or within, the bolt
F41A 3/10 - Block action, i.e. the main breech opening movement being transverse to the barrel axis with sliding breech-block, e.g. vertically
A magazine for storing cased telescoped (CT) cartridges. The magazine includes vertically extending side-wall ribs that project inwards into a loading channel. The side-wall ribs are positioned in alignment with a circumferential groove 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 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.
F41A 3/34 - Rigid bolt locks, i.e. having locking elements rigidly mounted on the bolt or bolt handle and on the barrel or breech-housing respectively the bolt additionally effecting a sliding movement transverse to the barrel axis
F41A 9/66 - Arrangements thereon for charging, i.e. reloading
F41A 9/75 - Drum magazines having a spiral cartridge channel
F41A 9/67 - Arrangements thereon for charging, i.e. reloading having means for depressing the cartridge follower, or for locking it in a depressed position
F41A 9/69 - Box magazines having a cartridge follower characterised by multiple-row or zigzag arrangement of cartridges
F41A 3/10 - Block action, i.e. the main breech opening movement being transverse to the barrel axis with sliding breech-block, e.g. vertically
F41A 5/18 - Mechanisms or systems operated by propellant charge energy for automatically opening the lock gas-operated
F41A 15/14 - Cartridge extractors, i.e. devices for pulling cartridges or cartridge cases at least partially out of the cartridge chamber; Cartridge ejectors, i.e. devices for throwing the extracted cartridges or cartridge cases free of the gun for bolt-action guns the ejector being mounted on, or within, the bolt
F42B 5/045 - Cartridges, i.e. cases with propellant charge and missile of telescopic type
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.
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 that is perpendicular to the horizontal flight path.
B64C 27/50 - Blades foldable to facilitate stowage of aircraft
B64C 39/02 - Aircraft not otherwise provided for characterised by special use
B64C 25/34 - Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
B64C 29/02 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
B64D 17/80 - Parachutes in association with aircraft, e.g. for braking thereof
G05D 1/00 - Control of position, course, altitude, or attitude of land, water, air, or space vehicles, e.g. automatic pilot
G05D 1/08 - Control of attitude, i.e. control of roll, pitch, or yaw
A technique involves operating a vehicle. The technique includes receiving, by processing circuitry, an accelerometer signal from an accelerometer. The technique further includes processing, by the processing circuitry, the accelerometer signal to determine whether the vehicle is currently experiencing tire skid. The technique further includes controlling, by the processing circuitry, the vehicle based on whether the vehicle is currently experiencing tire skid.
B60T 8/1761 - Brake regulation specially adapted to prevent excessive wheel slip during vehicle deceleration, e.g. ABS responsive to wheel or brake dynamics, e.g. wheel slip, wheel acceleration or rate of change of brake fluid pressure
B60T 8/17 - Using electrical or electronic regulation means to control braking
B60T 8/88 - Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force responsive to a speed condition, e.g. acceleration or deceleration with failure responsive means, i.e. means for detecting and indicating faulty operation of the speed responsive control means
B60T 8/171 - Detecting parameters used in the regulation; Measuring values used in the regulation
47.
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.
An in soil data collection and analysis system and process is disclosed where the data from a plurality of in soil sensors is combined with other data that is acquired by an unmanned aerial vehicle (UAV) to create a fused data set that can be used to determine an appropriate corrective action or response to the fused data.
A technique is directed to launching an unmanned aerial vehicle (UAV). The technique involves positioning a UAV launcher over a ground location. The technique further involves installing, after the UAV launcher is positioned over the ground location and prior to launching the UAV, an anchor into the ground location to anchor the UAV launcher to the ground location. The technique further involves operating, after the UAV launcher is anchored to the ground location, the UAV launcher to impart launching force onto the UAV to launch the UAV, the anchor holding the UAV launcher substantially in place at the ground location to minimize energy loss as the UAV launcher imparts launching force onto the UAV. In some arrangements, the UAV launcher is capable of pivoting while remaining anchored between launches to accommodate changes in wind direction while maintaining substantial connection to the ground location for enhanced consistency and performance.
An aircraft hybrid fuel system includes a main tank and a set of flexible bladders, the main tank and the set of flexible bladders defining a fuel containment space. The system further includes a set of pathways coupling the set of flexible bladders to the main tank. The set of pathways is constructed and arranged to vent gas out of the set of flexible bladders into the main tank while fuel from a fuel source is provided into the fuel containment space defined by the main tank and the set of flexible bladders. Along these lines, each flexible bladder can be provisioned with a fuel port to provide fuel, and a separate vent port to vent gas to the main tank.
A modular mounting structure is described which allows for the easy installation and removal of various payloads from a vehicle structure. An embedded electrical bus feature further supports the installation of the various payloads into the vehicle structure.
B64C 1/22 - Other structures integral with fuselages to facilitate loading
B64D 7/00 - Arrangement of military equipment, e.g. armaments, armament accessories, or military shielding, in aircraft; Adaptations of armament mountings for aircraft
B64D 9/00 - Equipment for handling freight; Equipment for facilitating passenger embarkation or the like
A technique is directed to launching an unmanned aerial vehicle (UAV). The technique involves attaching a UAV launcher to a hand-held weapon, and installing a UAV onto the UAV launcher while the UAV launcher is attached to the hand-held weapon. The technique further involves activating the hand-held weapon to launch the UAV into flight from the UAV launcher. Since a user already may be carrying the hand-held weapon for firing ammunition, the user simply needs to further carry the UAV launcher and the UAV which, in some situations, can be packaged into an easy-to-carry container such as a backpack, a carrying case, and so on.
Techniques involve attenuating noise from engine exhaust from an engine. For example, an apparatus 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.
A cooling air bypass prevents premature failure of an engine in the event that cooling air from an external blower is somehow obstructed or shut off. The cooling air bypass includes a normally-closed valve in a wall of a conduit. During proper operation of the blower, the conduit conducts cooling air from the blower to the engine. If the blower malfunctions, however, such that airflow from the blower is impeded or stops, the valve opens to provide an auxiliary airflow path through the valve in the wall of the conduit and into the engine.
A technique that uses a thermoelectric generator for generating electrical power employs a safe, initially dormant, stable, non-radioactive fuel sample which is activated on-demand by a neutron source to initiate and control activation of the fuel sample. The technique allows thermoelectric generators to be fully assembled and stored for extended periods of time before they are deployed for use, and then activated on demand only when the need arises for them to generate power.
An apparatus and method for attachment of a payload or store to the external surface of an aerial vehicle includes a single point release feature. The apparatus includes an elongated base having a first distal end and a second distal end. A retention receptacle including a hollow tube is disposed adjacent the first distal end and is configured to removably receive and retain the store or payload. In addition, a release receptacle housing a release mechanism assembly is disposed adjacent said second distal end. When the release mechanism assembly is in the closed and locked position, the store or payload is retained to the vehicle via a spring loaded lock pin advanced into the retention receptacle. When the release mechanism assembly is in the open and unlocked position, the store or payload may be disengaged from the vehicle.
B64D 9/00 - Equipment for handling freight; Equipment for facilitating passenger embarkation or the like
B64C 39/02 - Aircraft not otherwise provided for characterised by special use
B64D 1/00 - Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
E05C 1/14 - Fastening devices with bolts moving rectilinearly with latching action with operating handle or equivalent member moving otherwise than rigidly with the latch the handle or member moving essentially towards, or away from, the plane of the wing or frame
An aircraft hybrid fuel system includes a main tank and a set of flexible bladders, the main tank and the set of flexible bladders defining a fuel containment space. The system further includes a set of pathways coupling the set of flexible bladders to the main tank. The set of pathways is constructed and arranged to vent gas out of the set of flexible bladders into the main tank while fuel from a fuel source is provided into the fuel containment space defined by the main tank and the set of flexible bladders. Along these lines, each flexible bladder can be provisioned with a fuel port to provide fuel, and a separate vent port to vent gas to the main tank.
A level sensing device is disclosed that provides a lightweight but robust design and incorporates the use of an LVDT to determine the level of a fluid in a container.
G01F 23/72 - Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm by floats of the free float type using magnetically actuated indicating means
G01F 23/68 - Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm by floats of the free float type using electrically actuated indicating means
59.
Evaluating aileron deflection while an unmanned aerial vehicle is in flight
A technique is directed to operating a UAV. The technique involves launching (or guiding) the UAV into flight. The technique further involves performing a series of aileron (or other control surface) deflection evaluations while the UAV is in flight. The technique further involves performing a UAV remedial operation in response to the series of aileron deflection evaluations indicating abnormal aileron behavior, e.g., the UAV can send a warning message to a ground control station (GCS), land the UAV at a target location, deploy a chute, and so on. Such operation enables detection of an unexpected change in the UAV's center of gravity, e.g., due to a blocked fuel bladder connection, icing on one side of the UAV, mechanical failure of an aileron, etc.
A cylindrical warhead is divided into a conical central segment and peripheral segments. The central segment has a disk-shaped liner bounding a cavity with high explosive and forming a penetrating projectile. The peripheral segments are hingedly attached to the central segment and have outer segment faces bounding respective cavities with high explosive, the segment faces forming sidewalls of the warhead in a closed position. The peripheral segments can be released to an open position in which the segment faces point in the forward direction for detonation. The warhead may be used in the closed position for single hardened targets such as armored vehicles and in the open position for area targets such as lighter vehicles and personnel. Opening of the warhead may be enabled at a time of launch of the warhead, or at a time of target acquisition after launch.
F42B 12/02 - Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
F42B 12/10 - Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of armour-piercing type with shaped or hollow charge
F42B 12/24 - Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of high-explosive type with fragmentation-hull construction with grooves, recesses or other wall weakenings
F42B 12/58 - Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles
61.
Cloud based command and control system integrating services across multiple platforms
A command and control system is provided which links users and platforms in real time and with touch screen ease, delivering a highly intuitive, integrated user experience with minimal infrastructure. Capitalizing on a cloud based architecture, from the cloud, to the touch table, to a hand held device, the command and control system creates seamless connections between sensors, leaders and users for up-to-the-minute information clarity.
G05B 15/02 - Systems controlled by a computer electric
G08B 25/00 - Alarm systems in which the location of the alarm condition is signalled to a central station, e.g. fire or police telegraphic systems
G08B 25/08 - Alarm systems in which the location of the alarm condition is signalled to a central station, e.g. fire or police telegraphic systems characterised by the transmission medium using communication transmission lines
62.
Techniques utilizing high performance armor penetrating round
An armor penetrating round includes an elongated core portion (e.g., a hollow tool steel core) defining a front end, an aft end, and a central cavity which extends from the aft end toward the front end. The central cavity has (i) an aft cross-sectional diameter adjacent the aft end and (ii) a front cross-sectional diameter adjacent the front end, the aft cross-sectional diameter being larger than the front cross-sectional diameter. The armor penetrating round further includes a slug portion (e.g., a pre-compacted pellet of powdered metal) which is disposed within the central cavity adjacent the aft end, and an outer jacket (e.g., a copper jacket) which extends around the elongated core portion to operate as an interface between the armor penetrating round and a gun barrel when the armor penetrating round is fired through the gun barrel.
F42B 12/04 - Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of armour-piercing type
A system configured to generate an optical beam from a fiber laser is presented. The system includes a fiber gain medium having a core and a cladding, the core being configured to convert radiation from a pump beam into an output beam, the cladding having a mode propagating section and a mode stripping section bounded on a near end and a distal end by the mode propagating section, the mode stripping section of the cladding being configured to scatter excess pump radiation received from the mode propagating section in a substantially outwardly radial direction. The system also includes a rigid support member into which the fiber gain medium is placed, the rigid support member completely encompassing the mode stripping section of the cladding and joined to the fiber at the mode propagating section of the cladding.
An electronic assembly includes an electronic device and a solar shield coupled to the electronic device. The solar shield has an attachment portion which attaches to the electronic device, and a shield portion coupled to the attachment portion. The shield portion prevents direct sunlight from substantially reaching a section of the electronic device. The shield portion defines (i) at least a portion of an air intake, (ii) at least a portion of an air exhaust, and (iii) at least a portion of an air passageway which extends from the air intake to the air exhaust. The air passageway overlies the section of the electronic device enabling ambient air adjacent the air intake to form natural convective airflow into the air intake and out the air exhaust through the air passageway to carry away heat from the section of the electronic device during electronic operation of the electronic device.
In a sensor-fuzed munition system and method, the munition is provided with an additional laser designator/repeater mode of operation. In the laser designator/repeater mode, the munition has the option of initiating a target strike additionally based on whether a laser appointer energy is detected as being present on the target. The laser appointer energy signal is generated at a wavelength that is consistent with the wavelength of the laser rangefinder of the munition, and is generated based on the detected presence of a designator signal at a designator spot on the target. The laser appointer signal is directed to the designator spot and detected by the munition laser rangefinder receiver. In one embodiment, the repeater system for detecting the designator signal and for generating the appointer signal is provided on the delivery vehicle for the submunition. This additional mode of operation is preferably achieved using the existing laser receiver of the rangefinder hardware, with minimal additional hardware and software systems for detecting and processing the additional laser appointer signal energy. In this manner, collateral damage and false-target firings are decreased to near-zero probability.
An explosive device detection system includes sensors and base station that detect and report on suspected Improvised Explosive Devices (IED) or landmine emplacement activity within a geographic area. When disposed within a geographic area, each sensor forms part of a wireless communications network which allows communication among neighboring sensors. As a sensor detects activity in its proximity, such as activity that indicates emplacement of an IED, the sensor transmits a reporting signal through the network to the base station. The neighboring sensors receive and transmit the reporting signal in a sequential manner toward the base station. Because the reporting signal takes multiple hops toward the base station, the sensors do not require large amounts of power to transmit the signal. Furthermore, the detection system allows detection of IED emplacement within the geographic area as the activity occurs. As a result, the base station can direct mobile response units to take immediate responsive action to prevent detonation of the IED's.
G08B 1/08 - Systems for signalling characterised solely by the form of transmission of the signal using electric transmission
G08B 13/14 - Mechanical actuation by lifting or attempted removal of hand-portable articles
H04Q 5/22 - Selecting arrangements wherein two or more subscriber stations are connected by the same line to the exchange with indirect connection, i.e. through subordinate switching centre the subordinate centre not permitting interconnection of subscribers connected thereto
H04W 4/00 - Services specially adapted for wireless communication networks; Facilities therefor
H04L 12/28 - Data switching networks characterised by path configuration, e.g. LAN [Local Area Networks] or WAN [Wide Area Networks]
A surveillance system is configured to detect a rotary-wing aircraft approaching a fixed facility and provide a warning upon detection. The system includes acoustic processing nodes that receive acoustic signals from the environment surrounding the fixed facility. As the nodes receive the acoustic signals, the nodes perform a spectral analysis of the signals to detect if the source of the acoustic signals is a rotary-wing aircraft. Additionally, based upon the acoustic signals, the nodes detect an altitude of the rotary-wing aircraft and a distance between the rotary-wing aircraft and the fixed facility. In the case where the system identifies the rotary-wing aircraft as encroaching a predefined geographical area outside of the facility, based upon the altitude and distance between the rotary-wing aircraft and the facility, the system generates a warning to allow security forces to intercept the rotary-wing aircraft prior to its arrival at the facility.
G01S 3/80 - Direction-finders for determining the direction from which infrasonic, sonic, ultrasonic, or electromagnetic waves, or particle emission, not having a directional significance, are being received using ultrasonic, sonic, or infrasonic waves
69.
Techniques for forming temporary protective coatings and bondable surfaces
A method for forming temporary protective coatings and bondable surfaces is disclosed. In the method, a soluble layer is disposed on a material surface, such as the interior surfaces of cell walls of a web material. The soluble material is then removed or leached from the web material to form and expose a roughly textured, bondable surface for bonding with another material, such as AVCOAT insulation. Use of the soluble layer, therefore, enhances the bondability of any surface that requires good adhesion, such as where the surface is difficult to reach for conventional surface preparation techniques.
B32B 3/12 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure
B32B 19/00 - Layered products essentially comprising natural mineral fibres or particles, e.g. asbestos, mica
B32B 7/06 - Interconnection of layers permitting easy separation
70.
Devices and method for detecting emplacement of improvised explosive devices
An explosive device detection system includes sensors and base station that detect and report on suspected Improvised Explosive Devices (IED) or landmine emplacement activity within a geographic area. When disposed within a geographic area, each sensor forms part of a wireless communications network which allows communication among neighboring sensors. As a sensor detects activity in its proximity, such as activity that indicates emplacement of an IED, the sensor transmits a reporting signal through the network to the base station. The neighboring sensors receive and transmit the reporting signal in a sequential manner toward the base station. Because the reporting signal takes multiple hops toward the base station, the sensors do not require large amounts of power to transmit the signal. Furthermore, the detection system allows detection of IED emplacement within the geographic area as the activity occurs. As a result, the base station can direct mobile response units to take immediate responsive action to prevent detonation of the IED's.
A deployable stationary device includes a device support, rate gyros supported by the device support, the rate gyros being oriented along different axes, and a controller supported by the device support. The controller is arranged to receive rate gyro signals from the rate gyros. Each rate gyro signal indicates a rate of rotation about a respective axis associated with a particular rate gyro. The controller is further arranged to perform a vector sum operation based on the rate gyro signals, and generate a direction signal which identifies a direction resulting from performance of the vector summing operation. Such a deployable stationary device is capable of operating as one of a network of such devices in a surveillance system to enable detection and precise location of suspicious activity.
A heterodyne receiver includes first and second laser sources such as laser diodes which generate optical receiver oscillator (RO) signals having respective RO frequencies. Temperature control circuitry controls a temperature difference between the operating temperatures of the sources such that the RO frequencies differ by a difference frequency corresponding to the temperature difference, the difference frequency being offset from a frequency of a modulated millimeter-wave signal by a predetermined intermediate frequency. An electro-optical nonlinear mixer such as a photodiode receives the optical RO signals and the modulated millimeter-wave signal and generates an electrical intermediate-frequency (IF) signal, which is provided to an electrical amplifier/detector to detect the output signal corresponding to the modulation of the modulated millimeter-wave signal. The receiver may be used as part of a heterodyne transceiver which includes a transmitter, and the transmitter may also employ an optical heterodyne structure for generating a millimeter-wave signal for transmission.
H04B 1/38 - Transceivers, i.e. devices in which transmitter and receiver form a structural unit and in which at least one part is used for functions of transmitting and receiving
The electrical tape has a flexible conductor strip defining a conductor strip contact surface configured to interact with a first electrical connector and a second electrical connector, the flexible conductor strip being arranged to provide electrical connectivity between the first electrical connector and the second electrical connector. The electrical tape has a flexible insulator portion substantially surrounding the flexible conductor strip, the flexible insulator portion being arranged to expose the conductor strip contact surface along the length of the tape.
H01R 25/00 - Coupling parts adapted for simultaneous co-operation with two or more identical counterparts, e.g. for distributing energy to two or more circuits
74.
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 zig-zag laser has the ability to generate a high power beam while effectively removing heat without degrading the beam quality. The laser has a series of gaps interposed between the thin slabs, the gain medium, and between the thin slabs and the quartz windows to receive coolant and cool the cell assembly. The coolant flows transversely relative to the path of the laser and the flow of the coolant is in the opposite direction on each side of the thin slab to minimize the temperature gradient. The gaps in conjunction with the inner channel portions in the secondary manifold flow the coolant through the cell assembly in a laminar manner therein not degrading the laser beam quality. A transparent quartz/quartz interface between the secondary manifold and the cell assembly allow the fluorescence to move away from the cell assembly and minimizes heat in the cell assembly.
A detection system operating on a scalable Radiation Sensor Unit (RSU) data stream employs a detection module triggering an alarm based on fee dynamic temporal features of gross count. Two spectroscopic buffers, one holding a long-term background and one holding the integrated detection event data are passed on for identification. The detector data incorporates sets of counts measured at channelized gamma energies. Each multi-channel data set is reduced to highly accurate peak locations. The absolute energy of the peaks is determined using innovative techniques and the background peaks and other secondary peaks are eliminated to provide a concise list of corrected source peak locations and intensities. This, together with spectral region analysis results is used with pattern recognition algorithms to identify fee source isotope or combination of isotopes from a standard library.
Aspects of the present invention are directed to the use of optical gain structures that include alternating layers of gain medium and transparent heat conductors in which the gain medium itself functions as a correction optic. The gain medium changes to an optimum or desired shape because of the thermal changes occurring as the materials of the optical gain structure(s) reach a desired optical output condition. At the desired optical output conditions, the gain medium conforms to a desired shape. The desired shape may be, for example, that of an optical surface of a transparent heat conductor. By designing the initial shape of the gain medium such that the physical contact with the transparent heat conductor is maximized at the desired optical output conditions, conductive heat transfer between the gain medium and heat conductor(s) is maximized at the desired optical output condition.
A dispenser system provides a means to automatically deploy systems using a controlled dispense approach capable of providing desired operational flexibility. Components such as unattended ground sensors (UGS) are deployed according to a method which includes incorporating the components into an elongated ejection system to form a payload assembly, the ejection system including axially-displaced ejector bays each for holding respective components. Each ejector bay retains the respective components until a respective ejection event upon which the ejector bay ejects the components in a radial direction. The payload assembly includes a stabilizer such as a drogue parachute that substantially prevents the payload assembly from rotating about its elongated axis. A timing sequence for the ejection events is programmed into the ejection system to achieve a desired coverage pattern of the components after deployment. The timing sequence can be chosen to result in a coverage pattern along a continuum from maximum component density to maximum total area coverage. The payload assembly is subsequently released from an aerial vehicle above the area with activation of the timing sequence, such that the ejection events occur during flight of the payload assembly at respective times after its release.
An optical parametric oscillator includes a source of coherent energetic pump optical signals and an optical resonator cavity which includes a set of optical parametric amplifying (OPA) crystals and a set of optical elements such as mirrors disposed along an optical path. The optical elements are configured (1) to direct an oscillation optical signal generated by the OPA crystals along the optical path, (2) to provide input coupling of the energetic pump optical signals such that each energetic pump optical signal travels through only one of the OPA crystals to result in a corresponding depleted pump optical signal, and (3) to provide output coupling of the depleted pump optical signals to prevent each depleted pump optical signal from traveling through more than one of the OPA crystals. Resonator cavities have multiple-leg configurations, including “L” and “U” shapes, and either linear (or standing-wave) or ring architectures. The pump source may employ wavefront division or alternatively amplitude division of a single relatively high-power optical pump beam.
A gimbal for a gimbaled mirror optical sensor system includes a mirror support rotatable about a first axis along which an optical sensor suite lies, the first axis being spaced apart from a desired pivot point of a variable line of sight, which may be for example a fixed-size window in the outer wall of an aircraft. The gimbal further includes two generally planar mirrors supported by and rotatable with the mirror support. A first mirror is spaced apart from the optical sensor suite along the first axis and is non-orthogonal to the first axis so as to reflect light from a second axis to the optical sensor suite, wherein the second axis sweeps an arcuate path about the first axis upon rotation of the mirror support. A second mirror lies along the second axis so as to follow the arcuate path upon rotation of the mirror support. The second mirror is pivotable so as to reflect light from the variable line of sight to the first mirror along the second axis. A motion control subsystem controls the rotation of the mirror support and the pivoting of the second mirror such that the variable line of sight pivots about the desired pivot point.
G02B 26/08 - Optical devices or arrangements for the control of light using movable or deformable optical elements for controlling the direction of light
G01S 17/66 - Tracking systems using electromagnetic waves other than radio waves
81.
Methods and apparatus for active deployment of a samara wing
Methods and apparatus are disclosed for the controllable deployment of a samara wing from a spinning housing by use of an active deployment system. The active deployment system operates to deploy the samara wing as a function of time, for example a step function, or a monotonic function. The samara wing may be attached to a base, which may include a releasable portion. The active deployment system may include an electronic control unit and release means. Suitable release means include, but are not limited to pin actuators, explosively actuated cutters, and the like. Suitable electronic control units include programmable electronic sequencers and the like.
In a sensor-fuzed munition system and method, the munition is provided with an additional laser designator mode of operation. In the laser designator mode, the munition has the option of initiating a target strike additionally based on whether laser designator energy is detected as being present on the target. This additional mode of operation is preferably achieved using the existing laser receiver of the rangefinder hardware, with minimal additional hardware and software systems for detecting and processing the additional laser designator signal energy. In this manner, collateral damage and false-target firings are decreased to near-zero probability.
Aspects of the present invention are directed to the use of optical gain structures that include alternating layers of gain medium and transparent heat conductors in which the gain medium itself functions as a correction optic. The gain medium changes to an optimum or desired shape because of the thermal changes occurring as the materials of the optical gain structure(s) reach a desired optical output condition. At the desired optical output conditions, the gain medium conforms to a desired shape. The desired shape may be, for example, that of an optical surface of a transparent heat conductor. By designing the initial shape of the gain medium such that the physical contact with the transparent heat conductor is maximized at the desired optical output conditions, conductive heat transfer between the gain medium and heat conductor(s) is maximized at the desired optical output condition.
Amplified spontaneous emission (ASE) ducts are disclosed for use with various gain media. An ASE duct may be configured and arranged to remove ASE from solid state or liquid gain media and transmit the ASE to an exterior optical medium. The refractive index of an ASE duct is selected as desired based on the refractive index of a gain medium and an exterior optical medium. An ASE duct may include first and second boundary surfaces joined at a vertex having an included angle that allows ASE (light) reflected off on one boundary surface to be incident on the another boundary surface at less than the critical angle and transmitted outside of the ASE duct. Laser systems using ASE ducts and methods of using and manufacturing ASE ducts are disclosed.
Embodiments of the present invention are directed to staggered arrays of laser diode bars positioned on stepped support structures. Optical waveguides may direct the outputs of the individual diode bars to a desired location, for example, a common output plane. The optical waveguides may be glass plates in certain embodiments. Waste heat generated by the diode bars may be removed from the support structures at certain locations and as a result, the diode bars may be closely positioned with respect to each other. By closely positioning the laser diode bars and directing the diode bar outputs to a desired orientation, the effective brightness and fluence may be increased for a given output area and operational power compared to the prior art. Associated methods of manufacturing staggered array couplers and producing high-power pump energy are also described.
In a countermeasure system for an aircraft, a countermeasure module includes a chamber. Countermeasure equipment is housed in the chamber of the countermeasure module. An attachment mechanism allows for releasable attachment of the countermeasure module to an aircraft. A flight mechanism is provided on the countermeasure module for returning the countermeasure module to a location, such that when an aircraft to which the countermeasure module is attached reaches a desired airborne position, the attachment mechanism releases the countermeasure module from the aircraft, and the flight mechanism on the released countermeasure module returns the countermeasure module to the location.
A light source produces a pump wave that is used to pump a parametric device. The parametric device is configured at or near its degeneracy point and produces a broadband output. The broadband output is directed to a remote location where chemical agents may be located. The broadband output may be transmitted through or scattered from the remote location and chemical agents located at the remote location may absorb portions of the broadband output. The broadband output may be collected and dispersed to produce channels or sub-bands that are detected by a detector array. The detector array may multiplex the intensities of the sub-bands and produce an absorption spectrum. The absorption spectrum may be compared to a library of known chemical agents and the presence of a chemical agent at the remote location can be determined in or near real time.
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